Author Topic: SCE-200 semi-cryo engine info  (Read 63094 times)

Offline K210

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SCE-200 semi-cryo engine info
« on: 07/29/2013 10:16 AM »
New details have emerged of the 2000kn LOX/kerosene engine that ISRO is developing

Specfic impulse: 330 sec

Thrust (vac) : 2000 KN

Throttle: 60% to 105% of full power

Combustion cycle: staged combustion

estimated completion date: 2016-2017

usage: to replace L-110 stage of GSLV mk-3 and to power core of future ULV rocket family

if anyone has anymore info feel free to add to the list:)


Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #1 on: 07/29/2013 02:12 PM »
Thrust (vacuum) - 2000 kN
Isp (vacuum) - 3285 N-s/kg
Chamber Pressure - 18 MPa
Mixture Ratio - 2.65
Thrust Throttling - 65-105 (% of nominal thrust)
Engine gimbal - 8 degrees (in two planes)

ISRO has started building thrust chamber test facility for semi-cryo engine
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #2 on: 07/30/2013 07:10 AM »
Thrust (vacuum) - 2000 kN
Isp (vacuum) - 3285 N-s/kg
Chamber Pressure - 18 MPa
Mixture Ratio - 2.65
Thrust Throttling - 65-105 (% of nominal thrust)
Engine gimbal - 8 degrees (in two planes)

ISRO has started building thrust chamber test facility for semi-cryo engine

dosen't ISRO already have a test facility for testing liquid engines?

Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #3 on: 07/31/2013 12:28 PM »
Thrust (vacuum) - 2000 kN
Isp (vacuum) - 3285 N-s/kg
Chamber Pressure - 18 MPa
Mixture Ratio - 2.65
Thrust Throttling - 65-105 (% of nominal thrust)
Engine gimbal - 8 degrees (in two planes)

ISRO has started building thrust chamber test facility for semi-cryo engine

dosen't ISRO already have a test facility for testing liquid engines?

Not for a 2000 kN class semo-cryo engine
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline kanaka

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Re: SCE-200 semi-cryo engine info
« Reply #4 on: 07/31/2013 02:21 PM »
Thrust (vacuum) - 2000 kN
Isp (vacuum) - 3285 N-s/kg
Chamber Pressure - 18 MPa
Mixture Ratio - 2.65
Thrust Throttling - 65-105 (% of nominal thrust)
Engine gimbal - 8 degrees (in two planes)

ISRO has started building thrust chamber test facility for semi-cryo engine

dosen't ISRO already have a test facility for testing liquid engines?

Not for a 2000 kN class semo-cryo engine


Need to send to RUSSIA for getting it tested?

Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #5 on: 07/31/2013 03:55 PM »
Thrust (vacuum) - 2000 kN
Isp (vacuum) - 3285 N-s/kg
Chamber Pressure - 18 MPa
Mixture Ratio - 2.65
Thrust Throttling - 65-105 (% of nominal thrust)
Engine gimbal - 8 degrees (in two planes)

ISRO has started building thrust chamber test facility for semi-cryo engine

dosen't ISRO already have a test facility for testing liquid engines?

Not for a 2000 kN class semo-cryo engine


Need to send to RUSSIA for getting it tested?


They are building test facilities in India.
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #6 on: 01/10/2014 12:20 PM »
Rotary Vacuum Brazing Furnace
« Last Edit: 01/10/2014 12:40 PM by antriksh »
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline cave_dweller

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Re: SCE-200 semi-cryo engine info
« Reply #7 on: 01/12/2014 08:16 AM »

Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #8 on: 03/11/2014 02:35 AM »
Single element Thrust chamber (experimental design) hot test
« Last Edit: 03/11/2014 02:36 AM by antriksh »
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #9 on: 03/11/2014 02:40 AM »
Injector design experimental study for Oxidizer Rich Staged Combustion cycle

Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #10 on: 08/05/2014 01:57 PM »
Update:

1) Realisation of semi-cryogenic engine involves the development of performance-critical metallic and non-metallic materials and related processing technologies. 23 metallic materials and 6 non-metallic materials have been developed.

2) Characterisation of injector elements and hypergolic slug igniters with different proportion of Tri-ethyl Aluminium and Tri-ethyl Boron has been completed.

3) Sub-scale models of thrust chamber have been realised and ignition trials have been carried out successfully.

4) Single element thrust chamber hot test in stage combustion cycle mode was also conducted successfully.

Establishment of test facilities like Cold Flow Test Facility and Integrated Engine Test Facility are under various stages of realisation. Fabrication drawings are realised for all sub-systems and fabrication of booster turbo-pump and pre-burner subsystem commenced.
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline vineethgk

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Re: SCE-200 semi-cryo engine info
« Reply #11 on: 08/26/2014 06:47 AM »
A pretty noob question that I have been having for some time in my mind...

Considering that LOX/Kerosene engines have been present from the dawn of the Space Age (R-7 comes to my mind), what exactly would be the primary engineering difficulty in designing a modern high thrust LOX/Kerosene engine like SCE-200? Would it be things like the design of turbopumps with sufficient mass-flow, dealing with combustion instability in thrust chamber etc...  all on account of the huge amount of thrust we are dealing with? And maybe meeting the weight and Isp targets as well?

Are these the challenges that necessitated the Chinese Space Agency and ISRO to approach Russians and Ukrainians respectively to get their LOX/Kerosene engine designs, despite having developed LOX/LH2 engines earlier?
« Last Edit: 08/26/2014 09:15 AM by vineethgk »

Offline baldusi

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Re: SCE-200 semi-cryo engine info
« Reply #12 on: 08/26/2014 03:38 PM »

A pretty noob question that I have been having for some time in my mind...

Considering that LOX/Kerosene engines have been present from the dawn of the Space Age (R-7 comes to my mind), what exactly would be the primary engineering difficulty in designing a modern high thrust LOX/Kerosene engine like SCE-200? Would it be things like the design of turbopumps with sufficient mass-flow, dealing with combustion instability in thrust chamber etc...  all on account of the huge amount of thrust we are dealing with? And maybe meeting the weight and Isp targets as well?

Are these the challenges that necessitated the Chinese Space Agency and ISRO to approach Russians and Ukrainians respectively to get their LOX/Kerosene engine designs, despite having developed LOX/LH2 engines earlier?
Most initial engines were gas generators run fuel rich. But high performance requires staged combustion cycle. Which can only be done with oxygen rich preburners. That's close to an oxy torch environment. Developing the necessary metallurgy so it doesn't corrodes is the main obstacle. Then, the preburner needs to have something like 20 times the mass flow of a gas generator, so you get combustions instability problems on the preburner. And the main combustion chamber and all piping run at least at twice the pressure. And you really can't separate the preburner stability from the main combustion chamber, so you don't know if each part works until you fire the whole thing. For the rest, easy picy :-p

Offline vineethgk

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Re: SCE-200 semi-cryo engine info
« Reply #13 on: 08/27/2014 06:36 AM »

Most initial engines were gas generators run fuel rich. But high performance requires staged combustion cycle. Which can only be done with oxygen rich preburners. That's close to an oxy torch environment. Developing the necessary metallurgy so it doesn't corrodes is the main obstacle. Then, the preburner needs to have something like 20 times the mass flow of a gas generator, so you get combustions instability problems on the preburner. And the main combustion chamber and all piping run at least at twice the pressure. And you really can't separate the preburner stability from the main combustion chamber, so you don't know if each part works until you fire the whole thing. For the rest, easy picy :-p

Thanks for the explanation! Till now I was under the impression that combustion instability is something that affects the main combustion chamber alone.  ???

Any guesses as to what extent ISRO's prior experience of having built a Staged Combustion LOX/LH2 stage, albeit of much lower thrust, help in tackling these challenges?
« Last Edit: 08/27/2014 08:18 AM by vineethgk »

Offline AJA

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Re: SCE-200 semi-cryo engine info
« Reply #14 on: 08/31/2014 07:43 AM »
Any guesses as to what extent ISRO's prior experience of having built a Staged Combustion LOX/LH2 stage, albeit of much lower thrust, help in tackling these challenges?

Guessing here. If you're talking about the CUS-7.5, they "built it" by reverse engineering a Russian engine for the full-cryo, staged combustion engine. They didn't start from basic principles, and therefore there isn't that experience with the fundamental research around cryogens. Not nearly as much as what the Russians and the Americans have.

Watch to get an idea of how long it took the Soviets. Also, starting at 40:21, you get an idea of the ridiculous environment in ox-rich pre-burners.

However, reverse engineering isn't trivial. They'd have learnt to handle cryogens on the ground, and design fuel flow systems without the cryogens boiling off in the middle of the line and causing "geysering". They'd have learnt to design the turbopumps to function without cavitation. They'd have learnt what materials they'd need to use to seal chambers, and valves and piping, and the metallurgy of the tanks and pipes, and combustion chambers to hold cryogens. They'd have built the closed loop electronic systems to monitor engine health, as well as instrumentation that can handle cryogenic temperatures (fuel level sensors etc.). They'd have built some electronic control unit for engine throttling - by altering mixture ratios and/or fuel flow to the pre-burner and/or main combustion chamber. A lot of that should be transferable.

However, the SCE-200 is a bigger engine. So they'd definitely have do revisit thermal and fluid flow solutions. Combustion instabilities, and engine characteristics would be different... so they'd have to start from scratch there. It's not staged combustion though, so that'd probably make things somewhat easier. Nozzle cooling would also have to be carried out with a different fluid (I'm assuming they used LH2 in the CUS-7.5), so that'd need attention. They might need a whole different injector/valve/piping design - in terms of materials used, as well as geometry, since kerosene has different physical and chemical properties. Finally, the entire thermodynamic cycle has changed.

As for why they didn't stick with the staged combustion design - that's been discussed here.

And you really can't separate the preburner stability from the main combustion chamber, so you don't know if each part works until you fire the whole thing.

Can't you test the turbopumps, the valves, the fuel flow, and the pre-burner - each individually? The only thing you'd need a complete engine for would be to test the combustion chamber. You'd need O/F rich hot gas and the remnant of F/O coming in to the combustion chamber. To get those, you'd have had to build a pre-burner .... so you've ended up building an engine. However, you could have really long piping and additional bleed/feed lines on a test rig (exploiting the fact that you're on the ground) - and thereby decouple the instabilities in the pre-burner, from those in the combustion chamber couldn't you?

Offline vineethgk

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Re: SCE-200 semi-cryo engine info
« Reply #15 on: 08/31/2014 11:04 AM »
Thanks AJA for the info and especially the YouTube link..

However, the SCE-200 is a bigger engine. So they'd definitely have do revisit thermal and fluid flow solutions. Combustion instabilities, and engine characteristics would be different... so they'd have to start from scratch there. It's not staged combustion though, so that'd probably make things somewhat easier.

Did you mean CE-20 and not SCE-200 here? I believe SCE-200 is a staged combustion engine as mentioned in the OP?

Btw, I read sometime back that ISRO got the SCE-200 design from Yuzhnoye OKB. Is this the Yuzhnoye counterpart we are talking about - The RD-810?
http://www.yuzhnoye.com/en/technique/rocket-engines/marching/rd-810/


If it is a design that is still under development by Yuzhnoye as mentioned in the link, is SCE-200/RD-810 some kind of ongoing joint ISRO-Yuzhnoye development, or did it stop with the sharing of design?

Offline baldusi

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SCE-200 semi-cryo engine info
« Reply #16 on: 08/31/2014 03:44 PM »
CUS-7.5 is run fuel rich. H2 engines run better when fuel rich, since the thermal properties of H2 give a lot more power on the turbine. And don't have the metallurgy issues of O2. Regrettably, RP-1 would polymerize if run at preburner temperatures.
It's interesting to point out that the CUS-7.5 is air startable, but not restartable. But when they needed a higher thrust restartable engine they went with the easier gas generator cycle. That might say something about their development experience with staged combustion H2/LOX engine.
« Last Edit: 08/31/2014 03:48 PM by baldusi »

Offline vyoma

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Re: SCE-200 semi-cryo engine info
« Reply #17 on: 11/08/2014 02:24 AM »
http://www.newindianexpress.com/states/kerala/ISRO%E2%80%99s-Baby-Steps-at-Cheaper-Missions/2014/11/08/article2513064.ece

Quote
Officials at the LPSC HQ, Valiyamala, said they hoped to run the first major test in connection with the ‘semi-cryogenic’ engine project by November-end. What is special about the engine is that it uses kerosene as fuel instead of Liquid Hydrogen (LH2), the propellant used in cryogenic engines.

“This will be the first sub-system level test and we will be testing the booster pump for the oxidiser used in the engine,’’ LPSC director K Sivan said on Friday.  In both cryogenic and the semi-cryogenic engines, Liquid Oxygen is used as oxidiser, which helps the fuel to burn. In addition to being a low-cost technology, the use of highly refined kerosene (RP-1) will enable easier storage and handling.

The cold flow test facility at the LPSC unit in Mahendragiri, Tamil Nadu, where the test is to be conducted, is expected to be completed shortly, Sivan said. In fact, LPSC has had to postpone the test to November owing to the delay in its completion. An integrated test facility also is planned at Mahendragiri where the ‘hot test’ of the semi-cryo engine - in a hot test, the engine is fired - will be performed.

Offline abhishek

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Re: SCE-200 semi-cryo engine info
« Reply #18 on: 12/18/2014 06:01 PM »
Godrej Aerospace to make semi-cryogenic engines

Quote
The SME project was approved by the Government of India in January 2009 at a sanctioned cost of ₹1,798 crore. Department of Space’s Outcome Budget for 2014-15 says that the project is “in the initial stages”.

It expects the engine to be fully developed “after six years”.

Till the end of March 2013, ISRO had spent ₹155 crore on the project. Godrej will make six engines for ISRO. Vaidya said the company had begun work on three.

The SME is meant to power the future GSLV Mk III rockets as well as the heavy-life Unified Launch Vehicles, or ULV, which is today only a concept. The ULV will be a modular vehicle where the number of engines used will be based on the weight of the satellite or spacecraft.

The rocket will feature a combination of SME and an Indian cryogenic engine.
http://www.thehindubusinessline.com/news/has-been-supplying-the-vikas-engines-for-isros-rockets/article6705014.ece
10, 9, ignition sequence start 6, 5, 4, 3, 2, 1, 0, all engines running Lift off, we have a lift off, lift off

Offline abhishek

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Re: SCE-200 semi-cryo engine info
« Reply #19 on: 02/19/2015 03:09 AM »
Quote
Meanwhile, ISRO has started forming concepts to develop a rocket that can put a 10-tonne satellite into orbit. This vehicle would require powerful engines. One candidate is the semi-cryogenic engine, using kerosene and liquid oxygen, whose design is now over. The hardware is being built and facilities being created. When ready, it will be an efficient lower stage with a thrust of 200 tonnes and controllable in flight, good enough to go into the lower stages of a large rocket. ISRO's plans are to use it in the heavy lifter and the reusable launch vehicle.

http://economictimes.indiatimes.com/articleshow/46294413.cms?utm_source=contentofinterest&utm_medium=text&utm_campaign=cppst

10, 9, ignition sequence start 6, 5, 4, 3, 2, 1, 0, all engines running Lift off, we have a lift off, lift off

Offline TrevorMonty

Re: SCE-200 semi-cryo engine info
« Reply #20 on: 02/19/2015 10:21 AM »
Quote
Meanwhile, ISRO has started forming concepts to develop a rocket that can put a 10-tonne satellite into orbit. This vehicle would require powerful engines. One candidate is the semi-cryogenic engine, using kerosene and liquid oxygen, whose design is now over. The hardware is being built and facilities being created. When ready, it will be an efficient lower stage with a thrust of 200 tonnes and controllable in flight, good enough to go into the lower stages of a large rocket. ISRO's plans are to use it in the heavy lifter and the reusable launch vehicle.

http://economictimes.indiatimes.com/articleshow/46294413.cms?utm_source=contentofinterest&utm_medium=text&utm_campaign=cppst
This LV should be similar to Atlas V ie 2 x 450klb 1st stage RP1 engines plus cryogenic upper stage.

Offline abhishek

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Re: SCE-200 semi-cryo engine info
« Reply #21 on: 03/02/2015 12:44 PM »
Semi-cryogenic Engine: ISRO Charting a Revised Plan

Hit by delays, the Indian Space Research Organisation’s (ISRO) efforts to create a rocket engine which uses kerosene as propellant is getting a revised plan.

Quote
The new ISRO chairman A S Kiran Kumar has asked the Liquid Propulsion Systems Centre (LPSC) to prepare a brand new-schedule for the semi-cryogenic engine project as it is running behind schedule. As per the original plan, the semi-cryogenic engine should have been ready by 2014, but delays in setting up test facilities at the LPSC unit in Mahendragiri, Tamil Nadu, had dragged the project.

Kiran Kumar, who took over as chairman in January, reviewed the progress during a recent visit to the LPSC HQ in Valiyamala, Thiruvananthapuram, and recommended a revised plan.

The new schedule for the semi-cryo engine will be readied on the basis of the report prepared by the LPSC, LPSC director Dr K Sivan said. ‘’We are making all efforts to speed up the project. The ISRO chairman has recommended a revised plan and we are working on it,’’ Sivan said.

http://www.newindianexpress.com/cities/thiruvananthapuram/Semi-cryogenic-Engine-ISRO-Charting-a-Revised-Plan/2015/03/02/article2693939.ece
10, 9, ignition sequence start 6, 5, 4, 3, 2, 1, 0, all engines running Lift off, we have a lift off, lift off

Offline jithinnam

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Re: SCE-200 semi-cryo engine info
« Reply #22 on: 04/02/2015 01:44 AM »
LVM3-SC rocket powered by the SCE-200 Semi-Cryo Engine

The SCE-200 is a liquid-fuel rocket engine being developed by the Liquid Propulsion Systems Centre, a subsidiary of ISRO. It is being developed to power the future heavy-lift Unified Launch Vehicle (ULV) and Reusable Launch Vehicle (RLV) being planned by ISRO but before that it will be tested with GSLV Mk III by replacing L110(powered by old Vikas engine) stage to SC160.

Here is how this version of GSLV-3 would look like. All specifications are based on available valid data.

Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #23 on: 04/25/2015 04:52 AM »
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline baldusi

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Re: SCE-200 semi-cryo engine info
« Reply #24 on: 04/26/2015 08:56 PM »
The appear to increase the upper stage propellant by 20%, too. At 6.2tonnes it can launch, almost, anything commercial.

Offline johnxx9

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Re: SCE-200 semi-cryo engine info
« Reply #25 on: 04/27/2015 06:45 PM »


Nice find! Would be interesting to have the dimensions of the CLC.

Offline Ohsin

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Re: SCE-200 semi-cryo engine info
« Reply #26 on: 08/13/2015 09:10 PM »
Quote
"We are looking at using Russian testing facilities for the semi-cryogenic engine. We will be ready with the engine [SCE-200] in six to eight months. Although we will have our own test facility at Mahendragiri, ours will take some time to come up."

http://www.thehindu.com/sci-tech/science/russian-tieup-to-boost-isros-semicryogenic-launcher-plan/article7536263.ece
"Well, three cheers to Sharma, but our real baby is INSAT."

Offline abhishek

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Re: SCE-200 semi-cryo engine info
« Reply #27 on: 08/14/2015 03:18 AM »
more importantly, what the hell is this thing ?

The ISRO is working on its new-generation, Rs. 1,800-crore third rocket programme, called the semi-cryogenic launch vehicle, to beef up its current portfolio of the PSLV and the GSLV.
10, 9, ignition sequence start 6, 5, 4, 3, 2, 1, 0, all engines running Lift off, we have a lift off, lift off

Offline Ohsin

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Re: SCE-200 semi-cryo engine info
« Reply #28 on: 08/14/2015 03:36 AM »
more importantly, what the hell is this thing ?

The ISRO is working on its new-generation, Rs. 1,800-crore third rocket programme, called the semi-cryogenic launch vehicle, to beef up its current portfolio of the PSLV and the GSLV.

They are referring to HLV

http://www.vssc.gov.in/VSSC_V4/index.php/technology/heavy-lift-launch-vehicles

It needs a thread now :)
"Well, three cheers to Sharma, but our real baby is INSAT."

Offline TrevorMonty

Re: SCE-200 semi-cryo engine info
« Reply #29 on: 08/14/2015 03:41 AM »
The SCE200 is 2MN (460kbl) RP1 engine for the 1st stage. According to Wiki it will fly in GSLV MK3 initial then be used in a new LV.

NB 2 of these engines plus the new upper stage (CE20 200kN LH2 engine) they are developing and ISRO has a Atlas V class LV. 

Offline worldtimedate

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Re: SCE-200 semi-cryo engine info
« Reply #30 on: 08/14/2015 09:10 AM »
Quote from Ohsin

Quote

Quote

    "We are looking at using Russian testing facilities for the semi-cryogenic engine. We will be ready with the engine [SCE-200] in six to eight months. Although we will have our own test facility at Mahendragiri, ours will take some time to come up."


http://www.thehindu.com/sci-tech/science/russian-tieup-to-boost-isros-semicryogenic-launcher-plan/article7536263.ece


This is a rather needless and irresponsible media announcement by ISRO about Russian tie-up vis-à-vis Indian Semi Cryogenic Engine Development as if Russia will transfer technology to India. The cooperation would be just about the testing of the semi cryogenic engine at Russian Test Facilities until ISRO's own Semi Cryogenic Engine Testing Facilities come up later at Mahendra Giri, IPRC ( ISRO Propulsion Complex ).

ISRO shouldn't have made this announcement to avoid being arms-twisted by the USA, as it would not like ISRO to develop Semi Cryogenic Engine Technology that will pave the way for ATLAS V type HLV development in the long run by ISRO. I hope, ISRO does not get into any sort of Cryogenic Engine type trouble of 1990s because of the profuse publicizing of this type of news by the Indian Media that can't keep quite regarding any Hi-tech research that India Scientific Establishment embarks upon. Indian media is India's Scientific Establishment’s biggest enemy. If we search in any search engine with the keywords such as cryogenic engine, semi cryogenic engine, 90% of the websites that will appear in the top 20 to 30 positions will belong to India's cryogenic and semi cryogenic engine related news. While we can't get as much news of China's Semi Cryogenic Engine Development as possible.

By the way the author’s reporting that India will be the third country to achieve this Semi Cryogenic Engine Technology after the USA and the Russia is completely wrong. China has already developed 2 Semi-Cryogenic Engines.

1  )  YF-115 that has Thrust (vac.) of 176.5 KN / Thrust (SL) of 147.1 KN will be used in the Long March 6 second stage and Long March 7 second stage.

2 )  YF-100 Semi Cryogenic Engine that has Thrust (vac.) of 1,340 KN [ Thrust (SL) 1,200 KN ] will be used in the Long March 5 as K3-1 ( 2X YF-100) and K2-1 ( 1X YF-100 boosters ), Long March 6 first stage and Long March 7 first stage and boosters.

« Last Edit: 09/28/2015 12:51 PM by Chris Bergin »

Offline abhishek

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Re: SCE-200 semi-cryo engine info
« Reply #31 on: 08/14/2015 10:23 AM »
Quote


This is a rather needless and irresponsible media announcement by ISRO about Russian tie-up vis-à-vis Indian Semi Cryogenic Engine Development as if Russia will transfer technology to India. The cooperation would be just about the testing of the semi cryogenic engine at Russian Test Facilities until ISRO's own Semi Cryogenic Engine Testing Facilities come up later at Mahendra Giri, IPRC ( ISRO Propulsion Complex ).

ISRO shouldn't have made this announcement to avoid being arms-twisted by the USA, as it would not like ISRO to develop Semi Cryogenic Engine Technology that will pave the way for ATLAS V type HLV development in the long run by ISRO. I hope, ISRO does not get into any sort of Cryogenic Engine type trouble of 1990s because of the profuse publicizing of this type of news by the Indian Media that can't keep quite regarding any Hi-tech research that India Scientific Establishment embarks upon. Indian media is India's Scientific Establishment’s biggest enemy. If we search in any search engine with the keywords such as cryogenic engine, semi cryogenic engine, 90% of the websites that will appear in the top 20 to 30 positions will belong to India's cryogenic and semi cryogenic engine related news. While we can't get as much news of China's Semi Cryogenic Engine Development as possible.


Though this is going quite off topic,but i agree with you.Their jingoistic nature is creating a lot of embarrassment to the government and the society at large.Even more than media i hold ISRO responsible for selectively leaking internal stuffs.I don't know what do they get out of this ?

As far as international reaction is concerned,we should be worrying more about Ukrainian reaction than US's reaction.

Testing an engine of Ukrainian design on Russian facilities,won't that create some political issues ?
10, 9, ignition sequence start 6, 5, 4, 3, 2, 1, 0, all engines running Lift off, we have a lift off, lift off

Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #32 on: 08/14/2015 01:05 PM »
Quote
"We are looking at using Russian testing facilities for the semi-cryogenic engine. We will be ready with the engine [SCE-200] in six to eight months. Although we will have our own test facility at Mahendragiri, ours will take some time to come up."

http://www.thehindu.com/sci-tech/science/russian-tieup-to-boost-isros-semicryogenic-launcher-plan/article7536263.ece

6-8 Months!!!!
« Last Edit: 08/14/2015 01:05 PM by antriksh »
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline mightyprince

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Re: SCE-200 semi-cryo engine info
« Reply #33 on: 08/14/2015 06:00 PM »
If the history in below link is true , then India is at loss as "it could not be copied, modified, upgraded, re-exporter nor transferred to a third party without the permission of Yuzhnoye "

https://en.wikipedia.org/wiki/SCE-200


For any higher thrust engine, India again needs to start from scratch.

Offline baldusi

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Re: SCE-200 semi-cryo engine info
« Reply #34 on: 08/14/2015 06:54 PM »
If the history in below link is true , then India is at loss as "it could not be copied, modified, upgraded, re-exporter nor transferred to a third party without the permission of Yuzhnoye "

https://en.wikipedia.org/wiki/SCE-200


For any higher thrust engine, India again needs to start from scratch.
I wrote that based on WikiLeaks cables of the Kiev US Embassy. That story happened during 2007/8. As you can see, it took the Indians 7/8 years to get to a test stand. That's because they had to figure out why each part worked the way it worked. All they got was a blue print, with no engineering explanations behind it. In fact, now there's a CFD software that ISRO is willing to sell. And there are a long list of pictures of ISRO testing from a single injector element to parts of the powerhead. They can build as many SCE-200 as they want, and they have learned a lot. Please remember that they have already developed a staged combustion engine (the CE-7.5). Without the Ukrainian connection, going straight to a ORSC 200tnf engine would have been almost crazy. But getting something that should work (Yuzhmash didn't built one, only designed it), helps you a lot in reverse engineering it.

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #35 on: 08/15/2015 05:18 AM »
If the history in below link is true , then India is at loss as "it could not be copied, modified, upgraded, re-exporter nor transferred to a third party without the permission of Yuzhnoye "

https://en.wikipedia.org/wiki/SCE-200


For any higher thrust engine, India again needs to start from scratch.

The information is that wikipedia article is outdated and misleading. As far as i am aware Ukraine supplied blueprints for certain components of the engine and provided input into the development of a certain alloy but ISRO still has the ability to upgrade and use the engine however they want. In fact there was some speculation sometime ago about the thurst being increased by 25% for application in a super HLV rocket however there are no official sources to back this up.

Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #36 on: 08/21/2015 03:16 PM »
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #37 on: 09/21/2015 11:29 AM »
Low Pressure Oxidiser Turbo pump, first major component manufactured for semicryo engine
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline kanaka

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Re: SCE-200 semi-cryo engine info
« Reply #38 on: 09/21/2015 11:58 AM »
Low Pressure Oxidiser Turbo pump, first major component manufactured for semicryo engine

Unit Testing Done!!?

Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #39 on: 09/21/2015 03:06 PM »
Low Pressure Oxidiser Turbo pump, first major component manufactured for semicryo engine

Unit Testing Done!!?

my guess is cold flow test is done as they are already talking about hot testing the engine in 6-8 months.
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline vyoma

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Re: SCE-200 semi-cryo engine info
« Reply #40 on: 01/25/2016 09:11 AM »
http://www.thehindu.com/todays-paper/tp-national/tp-tamilnadu/cryogenic-engine-may-be-used-for-gslv-mkiii-by-yearend/article8149770.ece

Quote
The country could become self-reliant once the semi-cryogenic engine is developed, he said. IPRC has started the assembly, integration and testing facilities and is set to achieve a milestone in the next three years, he said.

The semi-cryogenic engine, using kerosene as fuel and liquid oxygen as oxidiser, is currently being designed and developed. The refined and purified kerosene to be used as fuel has been named as ‘isrosene’, the scientist said.

Offline Ohsin

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Re: SCE-200 semi-cryo engine info
« Reply #41 on: 01/25/2016 01:07 PM »
So..this "Special Correspondent" gets to talk about semi cryo progress and doesn't check on status of upcoming tests abroad, gets to talk about air breathing tech doesn't check upon ATV-D02... AND is talking about this absolutely INANE stuff like Isrosene..and "One dollar per one kg by ESA" ??? Doesn't check on HAT tests OR C25 stage integration timeline either... I commented on article I doubt it'll get published.
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Offline Ohsin

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Re: SCE-200 semi-cryo engine info
« Reply #42 on: 03/07/2016 11:24 AM »
Some insight into manufacturing ;D

Quote
A new Brazing process for Semi-Cryo Engine established by ISRO

Manufacture of thrust chamber and pre-burner of Semi-Cryo engine requires joining of two shells by vacuum brazing. The inner shell is made of a copper alloy, whereas the outer shell is made of stainless steel. The inner shell has ribs on its outer surface which need to be joined to the inner shell. This joining is achieved by brazing which results in formation of active cooling channels in the finished hardware.

The usual process of brazing uses a metal foil placed between the two shells. When the assembly is heated, the foil melts and a braze joint is formed. This is a time consuming and labour intensive process. Moreover, the hardware has to be rotated during brazing to avoid accumulation of braze metal in the channels. In order to overcome these limitations, a new brazing process has been developed which involves the use of coated base metals. At appropriate brazing temperature, the sandwich layer melts and forms in-situ braze alloy between the joints. In the present development, an attempt is made to achieve braze joint through ‘static’ technique rather than hitherto followed method at ISRO of ‘rotary’ brazing.

For the thrust chamber, vacuum brazing is to be carried out between martensitic stainless steel and copper alloy. To form the braze joint, a layer of copper and silver coating is provided on the base materials to be joined. A schematic of the coating arrangement is given in Figure 1. Nickel coating is applied to act as a barrier between braze metal and steel. Figure 2 shows a cross section of electroplated steel and copper.

Initial experiments for process optimization were carried in coupon level in a vacuum furnace. Several such experiments were conducted to optimize the silver layer thickness, brazing temperature, brazing time and load. Using the optimized process, flat plates with milled channels were brazed to simulate thrust chamber configuration and pressure tested. Figure 3 shows the joint made with two flat plates. Pressure testing was done up to 600 bar and no de-bonding was observed after the pressure test.Subsequently, pre-burner prototype hardware were fabricated and coated for the performance evaluation. A differential pressure is essential to ensure proper hugging of the cylindrical hardware assembly. For this purpose a Vacuum compression setup was designed and fabricated in-house in VSSC (Figure 4 and 5).Using this setup, subscale hardware was realized and was evaluated through X-Ray radiography and was pressure tested by Semi Cryo Project team. It was confirmed that the hardware were free of blocks in the channels through X-Ray radiography. Pressure testing was done up to 500 bar and no de-bonding was observed. Figure 6 show the hardware and the cut cross section with typical rib fracture observed beyond 500 bar which implies the soundness of the brazed joint.

As it is a simpler process, brazing can be done at industries without any special equipment, and the advantages of this process are:

 • This is a simple method of applying coatings by electroplating in the channels thus avoiding use of costly braze foils
 • Time consuming and laborious brazing foil assembly on the contoured ribs is simplified.


http://www.isro.gov.in/new-brazing-process-semi-cryo-engine-established-isro
« Last Edit: 03/07/2016 11:25 AM by Ohsin »
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Offline vineethgk

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Re: SCE-200 semi-cryo engine info
« Reply #43 on: 03/16/2016 08:07 AM »
Powder metallurgy seals for semi-cryo engine

Offline Ohsin

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Re: SCE-200 semi-cryo engine info
« Reply #44 on: 04/28/2016 01:44 AM »
"Well, three cheers to Sharma, but our real baby is INSAT."

Offline Stan-1967

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Re: SCE-200 semi-cryo engine info
« Reply #45 on: 04/28/2016 02:27 AM »
Some insight into manufacturing ;D

Quote

...Pressure testing was done up to 500 bar and no de-bonding was observed. Figure 6 show the hardware and the cut cross section with typical rib fracture observed beyond 500 bar which implies the soundness of the brazed joint.

As it is a simpler process, brazing can be done at industries without any special equipment, and the advantages of this process are:

 • This is a simple method of applying coatings by electroplating in the channels thus avoiding use of costly braze foils
 • Time consuming and laborious brazing foil assembly on the contoured ribs is simplified.


Yes, the electroplating steps they picked are very basic.  Thickness distribution limits were very generous.  I would like to know when they plan on hot testing this engine?   The pick of the braze filler is going to make this a relatively low temperature joint gated by the liquidus of the silver.  Higher temperature electroplated braze materials are available.  I can't be specific here, please understand. 

Furthermore, pressure testing to 500 bar will only likely test the joint in tension ( normal to the joint ) electroplated deposits often fail in shear, which will be experienced during hot fire.  Thermal gradients between inner & outer jackets, coupled with CTE mismatch between stainless and copper will also induce shear. 

Probably going to be just fine for semi-cryo engine. 


Offline antriksh

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Re: SCE-200 semi-cryo engine info
« Reply #46 on: 04/30/2016 03:25 AM »
Some insight into manufacturing ;D

Quote

...Pressure testing was done up to 500 bar and no de-bonding was observed. Figure 6 show the hardware and the cut cross section with typical rib fracture observed beyond 500 bar which implies the soundness of the brazed joint.

As it is a simpler process, brazing can be done at industries without any special equipment, and the advantages of this process are:

 • This is a simple method of applying coatings by electroplating in the channels thus avoiding use of costly braze foils
 • Time consuming and laborious brazing foil assembly on the contoured ribs is simplified.


Yes, the electroplating steps they picked are very basic.  Thickness distribution limits were very generous.  I would like to know when they plan on hot testing this engine?   The pick of the braze filler is going to make this a relatively low temperature joint gated by the liquidus of the silver.  Higher temperature electroplated braze materials are available.  I can't be specific here, please understand. 

Furthermore, pressure testing to 500 bar will only likely test the joint in tension ( normal to the joint ) electroplated deposits often fail in shear, which will be experienced during hot fire.  Thermal gradients between inner & outer jackets, coupled with CTE mismatch between stainless and copper will also induce shear. 

Probably going to be just fine for semi-cryo engine.

Hopefully, by end of this year testing would start.
Nasadiya Sukta:
Srishti se pehle sat nahin thaa, asat bhi nahin | Antariksh bhi nahin, aakaash bhi nahin thaa | chhipaa thaa kyaa, kahaan, kisne dhakaa thaa | us pal to agam, atal jal bhi kahaan thaa ||

From: 1st verse of 129th Hymn of the 10th Book of Rig Veda

Offline vyoma

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Re: SCE-200 semi-cryo engine info
« Reply #47 on: 05/28/2016 12:04 AM »
From ISRO 2015-16 annual report:

Quote
Integrated Technical Reviews of semi cryogenic Engine by the National Expert Panel has ratified the engine specifications, system configuration and approach adopted for design of major engine sub-systems and the engine development/qualification plan.

Fabrication of engine subsystems i.e., Thrust Chamber, Mixing head, Main Turbo pump, Booster Turbo pumps, Pre-burner and Heat Exchanger are in progress. Cold flow tests (five tests in noncavitation mode) of Low Pressure Oxidiser Turbo Pump (LPOT) were conducted at newly established Cold Flow Test facility (CFT) at IPRC, Mahendragiri. Semi cryo pre burner single element injector hot tests (11 nos.) were also conducted demonstrating the ignition with hypergolic igniter and flame holding at very high mixture ratios.

Design of subscale Pre-Burner and Thrust Chamber is completed and realisation is in progress. Out of 21 types of engine control components, assembly and testing of 16 types have been completed. Assembly and testing of two types and fabrication of three types are in progress. Also, realisation of four types of control components for Hydraulic Actuation System (HAS) is in progress. Preliminary details of overall Stage configuration and stage engineering of Semi-cryo stage with 200 T propellant loading (SC 200) has been worked out.

Offline vyoma

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Re: SCE-200 semi-cryo engine info
« Reply #48 on: 08/14/2016 04:20 AM »
Isrosene commercial-scale production technology seems to be realized (HOCL 2014-15 annual report).

Quote
After initial trial runs on pilot scale the ‘In-house’ developed vapour phase continuous process for ISRO’s specific grade of Kerosene (Isrosene) was fine tuned. A model developed on laboratory scale was also verified on pilot plant scale. Regular runs with optimized parameters in ‘scaled down version’ of HOC’s commercial plant were successfully completed. The product quality from these runs has been re-affirmed and the capacity of the plant has also been established, based on these runs. The technology is now ready for implementation in HOC’s available commercial plant. In this regard meeting with ISRO was held. The detailed proposal was sent to ISRO. Company’s further contribution in IPR field is maintained and grant of three nos. of Indian patents has been obtained during this year.

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #49 on: 09/13/2016 06:27 AM »
ISRO propulsion complex presentation:

Main points

- 5 SCE-200 will be clustered to create SC-500 booster stage
- CE-20 cluster for high thrust + high impulse upper stage
- SCE-500 in turn could be clustered around a larger core to create a super heavy launcher
- S250 might replace S-200 in GSLV MK-3 (maybe)
- Plans to land rockets like spacex
- Air breathing tech being worked on
- First test fire of SCE-200 in one year
- 10 ton thrust methalox thruster in development
« Last Edit: 09/13/2016 06:36 AM by K210 »

Offline Steven Pietrobon

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Re: SCE-200 semi-cryo engine info
« Reply #50 on: 09/13/2016 07:50 AM »
Attached is zip file of some screen captures. Resolution is not so good as the video is only 360p with the slides only partially filling the screen.
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Offline vineethgk

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Re: SCE-200 semi-cryo engine info
« Reply #51 on: 09/13/2016 01:42 PM »
I wonder where they plan to do the first test firing of SCE-200. Is the new test facility at IPRC nearing completion?

Offline cave_dweller

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Re: SCE-200 semi-cryo engine info
« Reply #52 on: 09/14/2016 12:21 AM »
I wonder where they plan to do the first test firing of SCE-200. Is the new test facility at IPRC nearing completion?

Russia

http://www.thehindu.com/sci-tech/science/russian-tieup-to-boost-isros-semicryogenic-launcher-plan/article7536263.ece

I am not sure why ROSCOSMOS doesn't partner more aggressively with India. India is a large market that can help sustain Russian space program by the way of shared costs.

And jointly both India and Russia can endeavor towards cutting edge space research instead of one attempting to re-invent the wheel and the other cutting down on space budgets.

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #53 on: 09/23/2016 07:57 AM »
First test firing of SCE-200 at IPRC is targeted for 3rd quarter 2017. Cold flow tests have already been completed and subsystem testing is underway.

This is going to be a massive leap for ISRO in terms of liquid fuel tech. To go from 76 tons thrust/270-290 sec impulse to 182 tons thrust/299 sec impulse is a jump to say the least. Given the fact they are developing this engine with reusability in mind i wonder why they choose a oxidiser rich cycle instead of a full flow staged combustion cycle which is more efficient and exerts less stress on the engine and improves reusability as a result.

Still with this engine india will have a single chamber RD-180 class engine. 

Offline Steven Pietrobon

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Re: SCE-200 semi-cryo engine info
« Reply #54 on: 09/23/2016 08:36 AM »
Given the fact they are developing this engine with reusability in mind i wonder why they choose a oxidiser rich cycle instead of a full flow staged combustion cycle which is more efficient and exerts less stress on the engine and improves reusability as a result.

I thought an oxidiser rich cycle was full flow stage combustion?!! There are no gases/liquids that do not end up in the combustion chamber.
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Offline rocx

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Re: SCE-200 semi-cryo engine info
« Reply #55 on: 09/23/2016 08:49 AM »
Given the fact they are developing this engine with reusability in mind i wonder why they choose a oxidiser rich cycle instead of a full flow staged combustion cycle which is more efficient and exerts less stress on the engine and improves reusability as a result.

I thought an oxidiser rich cycle was full flow stage combustion?!! There are no gases/liquids that do not end up in the combustion chamber.

I thought the definition of full flow staged combustion is that all propellants go through the turbines, all fluids ending up in the combustion chamber happens in all types of staged combustion, as well as expander cycle. The difference between oxidiser rich and full flow staged combustion, according to my understanding of Wikipedia's https://en.wikipedia.org/wiki/Staged_combustion_cycle, is that in the first not all of the fuel goes through the turbines.
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Offline vineethgk

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Re: SCE-200 semi-cryo engine info
« Reply #56 on: 09/23/2016 08:49 AM »
Given the fact they are developing this engine with reusability in mind i wonder why they choose a oxidiser rich cycle instead of a full flow staged combustion cycle which is more efficient and exerts less stress on the engine and improves reusability as a result.

I thought an oxidiser rich cycle was full flow stage combustion?!! There are no gases/liquids that do not end up in the combustion chamber.
Please correct me on this if I'm wrong. From what I have heard, the advantage of an oxidizer-rich cycle (as against a fuel-rich cycle) is its higher efficiency and better performance characteristics, while the downside is that it is more corrossive to the engine parts and hence impacts reusability?
« Last Edit: 09/23/2016 08:51 AM by vineethgk »

Offline vineethgk

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Re: SCE-200 semi-cryo engine info
« Reply #57 on: 09/23/2016 08:55 AM »
First test firing of SCE-200 at IPRC is targeted for 3rd quarter 2017. Cold flow tests have already been completed and subsystem testing is underway.

This is going to be a massive leap for ISRO in terms of liquid fuel tech. To go from 76 tons thrust/270-290 sec impulse to 182 tons thrust/299 sec impulse is a jump to say the least. Given the fact they are developing this engine with reusability in mind i wonder why they choose a oxidiser rich cycle instead of a full flow staged combustion cycle which is more efficient and exerts less stress on the engine and improves reusability as a result.

Still with this engine india will have a single chamber RD-180 class engine.
This would mean the upcoming test facilities for this engine in IPRC would be ready by then?

Btw, I guess the working equivalent for this engine would be the RD-191 (single chamber version of RD-180) which powers the Angara.

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #58 on: 09/23/2016 08:56 AM »
Given the fact they are developing this engine with reusability in mind i wonder why they choose a oxidiser rich cycle instead of a full flow staged combustion cycle which is more efficient and exerts less stress on the engine and improves reusability as a result.

I thought an oxidiser rich cycle was full flow stage combustion?!! There are no gases/liquids that do not end up in the combustion chamber.

ISRO themselves class it as a "Oxidiser rich staged combustion cycle"

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #59 on: 09/23/2016 09:01 AM »
First test firing of SCE-200 at IPRC is targeted for 3rd quarter 2017. Cold flow tests have already been completed and subsystem testing is underway.

This is going to be a massive leap for ISRO in terms of liquid fuel tech. To go from 76 tons thrust/270-290 sec impulse to 182 tons thrust/299 sec impulse is a jump to say the least. Given the fact they are developing this engine with reusability in mind i wonder why they choose a oxidiser rich cycle instead of a full flow staged combustion cycle which is more efficient and exerts less stress on the engine and improves reusability as a result.

Still with this engine india will have a single chamber RD-180 class engine.
This would mean the upcoming test facilities for this engine in IPRC would be ready by then?

Btw, I guess the working equivalent for this engine would be the RD-191 (single chamber version of RD-180) which powers the Angara.

Yes from my research it seems like they have decided to skip testing in russia and test at their own facility. For the past year or so no mentions of testing in russia have surfaced so i am assuming this is the case.

Offline baldusi

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Re: SCE-200 semi-cryo engine info
« Reply #60 on: 09/23/2016 02:00 PM »
Oxidizer Rich Staged Combustion means passing through the preburner all the oxidizer mass and just enough fuel to convert it to hot gas of the maximum temperature that your turbine will support. Fuel Rich would the the opposite. Full flow means having two preburners, one oxidizer rich and one fuel rich.
With Kerosene you can't do fuel rich because RP-1 would polymerize at SC temperatures. But you can do FFSC with methalox, hydrolox and UDMH/N2H2. In fact, the only three FFSC powerpacks that reached a test stand that I know, each had a different propellant (RD-270->UDMH/N2H2, IPD->hydrolox , Raptor->methalox).
So once they decided to use kerosene/LOX, they had to do ORSC. But you could want to do ORSC even with methalox, like the BE-4 does. The reason is that you go with staged combustion to have more power at your pumps. And the turbines are thermal machines with power proportional to delta-t * mass flow.
Since your maximum temperature is always the same for Oxi rich and Fuel rich, your power could be very well approximated by specific heat * mass flow. Methane has better specific heat than oxygen, but you use 3.5 more mass of O2. When you do your numbers going ORSC gives you something like 20%~30% more power than Fuel rich for the methalox case.
Hydrogen has such a ridiculous high specific heat that you always want to go fuel rich.

Offline baldusi

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Re: SCE-200 semi-cryo engine info
« Reply #61 on: 09/23/2016 03:39 PM »
Let me add that staged combustion is a gas-liquid the injector (one element of the propellant is liquid and the other in gaseous state when injected into the main combustion chamber). Full flow is gas-gas.
Closed expander can be gas-gas or gas-liquid, and bleed expander is liquid-liquid.
Tap-off is liquid-liquid. So is electrically pumped (i.e. Rutherford).
Then you have the strange ones, like the RD-0162, that uses ORSC and fuel expander to be gas-gas.
So trying to be too strict is quite difficult given the engineers creativity.

Offline vineethgk

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Re: SCE-200 semi-cryo engine info
« Reply #62 on: 09/28/2016 01:51 AM »
Mega launchers for ISRO soon

Quote
Pre-project work on what is called the SCE-200 began about four years back. "We plan to have an [semi-cryogenic] engine and stage capable of flight by the end of 2018 and try it on the GSLV-MkIII.
Quote
“The semi-cryogenic engine is getting fabricated. Testing of its pump and components has been going on. An engine testing facility is also getting set up at Mahendragiri,” Dr. Sivan said.
Quote
“The GSLV-MkIII that we plan to test in December has a core liquid fuel stage. When the semi-cryogenic engine gets ready, our plan is to replace the liquid stage with the SCE. We straightaway get six-tonne payload capability, two tonnes over what Mark III can give.”
Subsequently the plan is to have a modular vehicle (earlier called the unified launch vehicle) which allows variations suited to different payloads.
“We can have a bigger semicryogenic stage with clustered engines, similar to what SpaceX did using nine Merlin engines. We can then get a payload of 15 tonnes in the GTO.”

Offline kanaka

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Re: SCE-200 semi-cryo engine info
« Reply #63 on: 09/28/2016 03:23 AM »
Mega launchers for ISRO soon

Quote
Pre-project work on what is called the SCE-200 began about four years back. "We plan to have an [semi-cryogenic] engine and stage capable of flight by the end of 2018 and try it on the GSLV-MkIII.
Quote
“The semi-cryogenic engine is getting fabricated. Testing of its pump and components has been going on. An engine testing facility is also getting set up at Mahendragiri,” Dr. Sivan said.
Quote
“The GSLV-MkIII that we plan to test in December has a core liquid fuel stage. When the semi-cryogenic engine gets ready, our plan is to replace the liquid stage with the SCE. We straightaway get six-tonne payload capability, two tonnes over what Mark III can give.”
Subsequently the plan is to have a modular vehicle (earlier called the unified launch vehicle) which allows variations suited to different payloads.
“We can have a bigger semicryogenic stage with clustered engines, similar to what SpaceX did using nine Merlin engines. We can then get a payload of 15 tonnes in the GTO.”

is December Confirmed?

Offline vyoma

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Re: SCE-200 semi-cryo engine info
« Reply #64 on: 09/28/2016 03:41 AM »
https://twitter.com/jeff_foust/status/780483391045021697?lang=en

Quote
Somanath: planning for GSLV Mark III launch in early 2017, as well as increasing GSLV and PSLV launch rates. #IAC2016

Online sanman

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Re: SCE-200 semi-cryo engine info
« Reply #65 on: 09/28/2016 10:15 PM »
I had a brief word with Mr Somnath (director LPSC) recently, asking him about the potential benefits of propellant densification (isrosene/LOX, hydrolox, methalox) for ISRO - he said the technology was certainly of interest to them.

Offline cave_dweller

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Re: SCE-200 semi-cryo engine info
« Reply #66 on: 10/13/2016 05:52 PM »
Is the SCE-200 essentially a derivative of RD-810 from Yuzhnoye?

http://www.yuzhnoye.com/en/technique/rocket-engines/marching/rd-810/
https://en.wikipedia.org/wiki/SCE-200

The specifications are rather identical.


Offline baldusi

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Re: SCE-200 semi-cryo engine info
« Reply #67 on: 10/13/2016 09:33 PM »
Is the SCE-200 essentially a derivative of RD-810 from Yuzhnoye?

http://www.yuzhnoye.com/en/technique/rocket-engines/marching/rd-810/
https://en.wikipedia.org/wiki/SCE-200

The specifications are rather identical.


From what I have been able to research, the SCE-200 is developed from blueprints sold by Yuzhnoye. That same blueprint could be sold by the Ukrainian as the RD-810, if they had the money to actually build and test the prototypes.
The YF-100 appears to have the same relationship with the RD-801.

Offline worldtimedate

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Re: SCE-200 semi-cryo engine info
« Reply #68 on: 10/14/2016 09:15 PM »
Quote
The semi cryogenic engine, which would help the space vehicles to carry more payload is under development with the support of an international agency and would be ready in two years. There is a roadmap enhancing the capabilities of the Isro to carry upto 10 tonnes of payload in future, he said.

Source : Isro looking at putting a telescope on moon, says A S Kiran Kumar

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Offline worldtimedate

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Re: SCE-200 semi-cryo engine info
« Reply #69 on: 11/08/2016 08:41 PM »
ISRO Annual Report of 2015-2016 has some good information on Semi-Cryogenic Engine Development :

Quote

Page 6 :

Quote
This apart, research and development activities in semi-cryogenic propulsion engine, air breathing propulsion and re-usable launch vehicle technology are also being pursued in earnest in an effort towards reducing the cost of access to space. Development of critical technologies for undertaking human spaceflight has also made additional progress.

Page 13 :

Quote
The activities carried out at IPRC, Mahendragiri are: assembly, integration and testing of earth storable propellant engines, cryogenic engines and stages for launch vehicles; high altitude testing of upper stage engines and spacecraft thrusters as well as testing of its sub systems; production and supply of cryogenic propellants for Indian cryogenic rocket programme, etc. A Semi-cryogenic Cold Flow Test facility (SCFT) has been established at IPRC, Mahendragiri for the development, qualification and acceptance testing of semi-cryogenic engine subsystems.

Page 76 :

Quote
Space Transportation System

The Indian Space Programme has made successful transition in terms of technology acquisition and launch vehicle development in the last year. PSLV went on to become a favoured carrier for satellites of various countries due to its reliability and cost efficiency, promoting unprecedented international collaboration. The Geosynchronous Satellite Launch Vehicle (GSLV) with indigenous Cryogenic stage, graduated to become an operational vehicle for communication satellites. Future readiness is the key to maintaining an edge in technology and ISRO endeavours to optimise, accelerate and enhance its technologies through establishment of facilities and forging partnership with industries. ISRO is moving forward with the development of heavy lift launchers, human spaceflight, reusable launch vehicles, semi-cryogenic engines, etc., to cater to different payloads and an array of missions.

Page 79 & 80 :

Quote
Semi-cryogenic Project :

The semi-cryogenic Project envisages the design and development of a 2000 kN semi-cryogenic engine for a future heavy-lift Unified Launch Vehicle (ULV). The semi-cryogenic engine uses a combination of Liquid Oxygen (LOX) and ISROSENE (propellant-grade kerosene), which are eco-friendly and cost-effective propellants.

Integrated Technical Reviews of semi cryogenic Engine by the National Expert Panel has ratified the engine specifications, system configuration and approach adopted for design of major engine sub-systems and the engine development/qualification plan. Fabrication of engine subsystems i.e., Thrust Chamber, Mixing head, Main Turbo pump, Booster Turbo pumps, Pre-burner and Heat Exchanger are in progress. Cold flow tests (five tests in non-cavitation mode) of Low Pressure Oxidiser Turbo Pump (LPOT) were conducted at newly established Cold Flow Test facility (CFT) at IPRC, Mahendragiri. Semi cryo pre burner single element injector hot tests (11 nos.) were also conducted demonstrating the ignition with hypergolic igniter and flame holding 
at very high mixture ratios. 

Design of subscale Pre-Burner and Thrust Chamber is completed and realisation is in progress. Out of 21 types of engine control components, assembly and testing of 16 types have been completed. Assembly and testing of two types and fabrication of three types are in progress. Also, realisation of four types of control components for Hydraulic Actuation System (HAS) is in progress. Preliminary details of overall Stage configuration and stage engineering of Semi-cryo stage with 200 T propellant loading (SC 200) has been worked out.


Source :
ISRO Annual Report of 2015-2016

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Offline cosmiste

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Re: SCE-200 semi-cryo engine info
« Reply #70 on: 12/11/2016 04:50 PM »
From a november publication of a meeting held on 27–28 February 2016 at VSSC !

Quote
V. Narayanan (Liquid Propulsion System Centre, Thiruvananthapuram) described the issues and problems in the development of liquid rocket engines and the role played by P. J. Paul at several stages. Amongst others, he spoke of issues with ignition in the gas generator section at low mixture ratio, and combustion instability problems of the new design of semi-cryo engine under development now. He emphasized that more theoretical studies were needed in respect of vacuum ignition of steering engine, ignition of gas generator at low mixture ratio, saw tooth pattern observed in the main thrust chamber after hot test and combustion instability modelling of semi-cryogenic engines for providing strength in making critical decisions in short duration high risk development of these engines.

Not so surprising, the development of the ox-rich preburner (refered as "gas generator at low mixture ratio" ?) seems to be a difficult way to go.

http://www.currentscience.ac.in/Volumes/111/09/1440.pdf

Offline srikanthr124

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Re: SCE-200 semi-cryo engine info
« Reply #71 on: 01/15/2017 07:27 PM »
ANY NEWS REGARDING TESTING STATUS.
FROM OFFICIAL SOURCES [SCE-200]

Offline sanjaykumar

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Re: SCE-200 semi-cryo engine info
« Reply #72 on: 01/17/2017 10:37 PM »

http://www.claws.in/1533/india-set-to-boost-the-lift-off-power-radhakrishna-rao.html#sthash.KNDtJoAZ.dpuf


Quote
As things stand now, the Indian semi-cryogenic engine stage is expected to be ready before the end of this decade. It was originally planned to be ready by the middle of this decade. 

Offline vyoma

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Re: SCE-200 semi-cryo engine info
« Reply #73 on: 02/03/2017 02:36 AM »
http://pib.nic.in/newsite/PrintRelease.aspx?relid=157921

Quote
Currently, the project for the development of Semicryogenic engine has been approved and the Semicryogenic engine is under development. The various activities carried out towards the development of the Semicryogenic engine include- (i) Indigenous realisation of 35 materials and 22 coating processes (ii) Qualification of indigenous bearings for turbo pumps (iii) Fabrication of the first hardware for three engine subsystems including low pressure turbo pumps and one high pressure turbo pump through industry (iv) Design validation of the low pressure turbo pumps through cold flow trials.
 
An advanced space launcher that can deliver ten-tonne and heavier communication satellites to space requires a booster stage with clustered Semicryogenic engines. After the successful qualification of the Semicryogenic engine, the development of the Semicryogenic booster stage with clustered engines is expected to be initiated.

Offline srikanthr124

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Re: SCE-200 semi-cryo engine info
« Reply #74 on: 02/03/2017 12:24 PM »
http://pib.nic.in/newsite/PrintRelease.aspx?relid=157921

Quote
Currently, the project for the development of Semicryogenic engine has been approved and the Semicryogenic engine is under development. The various activities carried out towards the development of the Semicryogenic engine include- (i) Indigenous realisation of 35 materials and 22 coating processes (ii) Qualification of indigenous bearings for turbo pumps (iii) Fabrication of the first hardware for three engine subsystems including low pressure turbo pumps and one high pressure turbo pump through industry (iv) Design validation of the low pressure turbo pumps through cold flow trials.
 
An advanced space launcher that can deliver ten-tonne and heavier communication satellites to space requires a booster stage with clustered Semicryogenic engines. After the successful qualification of the Semicryogenic engine, the development of the Semicryogenic booster stage with clustered engines is expected to be initiated.


thank you very much for latest information.....
any possible upcoming test dates.......

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #75 on: 02/03/2017 12:31 PM »
Hopefully we have a test fire in russia before year end. SCE-200 is vital to ISRO from 2019 onwards.

Offline cosmiste

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Re: SCE-200 semi-cryo engine info
« Reply #76 on: 02/22/2017 08:30 PM »
In case you'd like to build your own replica of all pumps of that engine (LPOT, LPFT and main Turbopump), all drawings are here  ::)
http://www.isro.gov.in/sites/default/files/tenders/01te_28092_fabn_semicryo_mockup_turbopump.pdf

Offline Danderman

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Re: SCE-200 semi-cryo engine info
« Reply #77 on: 03/07/2017 12:12 AM »
If the history in below link is true , then India is at loss as "it could not be copied, modified, upgraded, re-exporter nor transferred to a third party without the permission of Yuzhnoye "

https://en.wikipedia.org/wiki/SCE-200


For any higher thrust engine, India again needs to start from scratch.

The information is that wikipedia article is outdated and misleading. As far as i am aware Ukraine supplied blueprints for certain components of the engine and provided input into the development of a certain alloy but ISRO still has the ability to upgrade and use the engine however they want. In fact there was some speculation sometime ago about the thurst being increased by 25% for application in a super HLV rocket however there are no official sources to back this up.

The bottom line here is that it seems that the Ukrainian licensed production of the Energomash RD-120 engine has resulted in the design of that engine spreading by osmosis to India and China and use in their programs. Funny how that happened.

Offline maint1234

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Re: SCE-200 semi-cryo engine info
« Reply #78 on: 03/07/2017 01:07 AM »
Still not funny as the wholescale import of German scientists by USA and UK after WW2 to form the foundation of NASA.

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #79 on: 03/27/2017 04:29 AM »
In a recent interview LPSC director casually mentioned they have began manufacturing the first test engine

Offline worldtimedate

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Re: SCE-200 semi-cryo engine info
« Reply #80 on: 05/05/2017 03:18 PM »
In a recent interview LPSC director casually mentioned they have began manufacturing the first test engine

According to S. Somnath, LPSC Director, ISRO wants to test a semi-crygenic engine prototype in a year.

Quote
Considering that the global space market’s future will be defined by heavy lift boosters, it is imperative for Isro to develop the GSLV’s advanced avatars as soon as possible. The international launch scene is changing rapidly with newer launchers constantly pushing the bar higher on payload capability.

Isro scientists seem ready for the challenge and have set their sights on leapfrogging to GSLVs powered by semi-cryogenic engines. Fuelled by kerosene and liquid oxygen, these engines would be capable of lofting ten-ton satellites into space, cutting launch costs dramatically. "We expect to test the prototype of a semi-cryogenic engine in a year’s time," says Somnath. "And we may fly it by 2021. Engine development takes a very long time, at least 10 years for realisation."

Source :GSAT-9 launch:?With South Asia Satellite Isro moves into heavyweight category

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Online sanman

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Re: SCE-200 semi-cryo engine info
« Reply #81 on: 06/13/2017 02:49 AM »

Offline vineethgk

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Re: SCE-200 semi-cryo engine info
« Reply #82 on: 06/13/2017 02:53 AM »
http://www.newindianexpress.com/nation/2017/jun/13/isro-to-flight-test-kerosene-based-semi-cryogenic-engine-by-2021-1615979.html

Quote
"Various tests are in progress on the engine. Of the four turbo pumps in it, three have undergone tests at the ISRO Propulsion Complex, Mahendragiri. We plan to have the engine ready by 2019 end, the stage by 2020-end and the first flight by 2021,’’ S Somanath, director, LPSC, said.

LPSC had developed the cryogenic engine for the GSLV Mk-II and the much powerful one for the GSLV Mk-III. The idea is to replace the second stage of the GSLV Mk-III, which now uses a liquid stage, with the semi-cryo. The rocket will retain the cryogenic upper, third stage.

The advantage of inducting the semi-cryogenic stage is the payload capacity of the GSLV Mk-III will increase from four tonnes to six tonnes. Using refined kerosene as fuel has quite a few advantages: It is eco-friendly and cost-effective.

Taking into account the '-end' suffix added to the dates (hinting it is more likely *optimistic* targets than what is *likely*) the revised targeted dates would be:

- SCE-200 engine ready by 2020+
- SC-200 stage by 2021+
- first flight by 2022+

There is also a project to cluster 4-5 of these engines to create a more powerful core for future heavy-lift launchers, but that would probably have to wait for much longer due to its inherent complexities, and the need to fabricate stages with a diameter of 5m or more.
« Last Edit: 06/13/2017 02:56 AM by vineethgk »

Offline srikanthr124

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Re: SCE-200 semi-cryo engine info
« Reply #83 on: 06/14/2017 11:26 AM »
is sce-200 being built by isro based on re-usability in mind or not and recently “somanth lpsc director said sce-200 stage will be ready by 2021”

But why that much time why cont we replace GSLV Mark-III L110 liquid stage with sce-200 stage within 1 year after materializing sce-200 engine is it testing will take like 4 years from now…

but chines did it in after 2 years from initial prototype…
« Last Edit: 06/14/2017 12:38 PM by srikanthr124 »

Offline russianhalo117

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Re: SCE-200 semi-cryo engine info
« Reply #84 on: 06/14/2017 02:34 PM »
is sce-200 being built by isro based on re-usability in mind or not and recently “somanth lpsc director said sce-200 stage will be ready by 2021”

But why that much time why cont we replace GSLV Mark-III L110 liquid stage with sce-200 stage within 1 year after materializing sce-200 engine is it testing will take like 4 years from now…

but chines did it in after 2 years from initial prototype…
Current version in development is designed to be expendable with follow-on version designed to support reuse.

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #85 on: 06/15/2017 12:32 PM »
is sce-200 being built by isro based on re-usability in mind or not and recently “somanth lpsc director said sce-200 stage will be ready by 2021”

But why that much time why cont we replace GSLV Mark-III L110 liquid stage with sce-200 stage within 1 year after materializing sce-200 engine is it testing will take like 4 years from now…

but chines did it in after 2 years from initial prototype…
Current version in development is designed to be expendable with follow-on version designed to support reuse.

Actually SCE-200 is being developed with reusability in mind. Each engine can be reused up to 15 times. 

Online sanman

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Re: SCE-200 semi-cryo engine info
« Reply #86 on: 06/15/2017 02:49 PM »
Current version in development is designed to be expendable with follow-on version designed to support reuse.

Actually SCE-200 is being developed with reusability in mind. Each engine can be reused up to 15 times.

I know the semi-cryo engine intended for use in the planned TSTO (Two-Stage-To-Orbit) vehicle is supposed to be reusable as  you've said, however it's not clear to me whether that engine is the same as the SCE-200, which is meant for replacing the GSLV-Mk3's L110 stage (UDMH/N2O4).

Logically, it might be practical for ISRO to first get SCE-200 non-reusably flying on GSLV-Mk3, which is an expendable launch vehicle, even while it works to achieve reusability on its semi-cryo engine meant for TSTO.

Offline srikanthr124

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Re: SCE-200 semi-cryo engine info
« Reply #87 on: 06/15/2017 06:59 PM »
SEE THIS VIDEO IT HAS VERY INTERESTING INFORMATION ABOUT SCE-200 & CE-60 600KN CRYO ENGINE  AND MORE LATEST LPSC FEB 2017 LAST 5 MINUTES REGARDING RE-USABILITY AND MAN RATED ABILITY OF SCE-200

WHAT IS EVIDENT FROM THIS VIDEO IS THAT SCE-200 DESIGNED BASED ON RE-USABILITY IN MIND FROM SCRATCH ONWARDS AND ALSO MAN RATED,SO PROVISIONS FOR MULTIPLE ENGINE BURNS RESTARTS IN SPACE ARE ALSO TAKEN INTO CONSIDERATION HE ALSO SAID UP TO 15 TIMES RE-USABILITY OF ENGINE IS POSSIBLE.... :)



« Last Edit: 06/16/2017 08:27 AM by srikanthr124 »

Offline baldusi

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SCE-200 semi-cryo engine info
« Reply #88 on: 06/15/2017 08:43 PM »
Please understand that all modera rocket engines are somewhat reusable. The reusability is needed so it can be bench tested before installation, and do a graceful launch abort after ignition but before lift off.
It also helps enormously with testing and certification, since you need something close to 100 tests. Without reusability you'd need 100 engines, with 15 you could do away with less than 10.
But, the real question is the ease of refurbishment and the air starts and restart capability. And engine life, of course.
« Last Edit: 06/15/2017 08:44 PM by baldusi »

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #89 on: 06/16/2017 02:02 AM »
Current version in development is designed to be expendable with follow-on version designed to support reuse.

Actually SCE-200 is being developed with reusability in mind. Each engine can be reused up to 15 times.

I know the semi-cryo engine intended for use in the planned TSTO (Two-Stage-To-Orbit) vehicle is supposed to be reusable as  you've said, however it's not clear to me whether that engine is the same as the SCE-200, which is meant for replacing the GSLV-Mk3's L110 stage (UDMH/N2O4).

Logically, it might be practical for ISRO to first get SCE-200 non-reusably flying on GSLV-Mk3, which is an expendable launch vehicle, even while it works to achieve reusability on its semi-cryo engine meant for TSTO.

All liquid fuel rocket engines are reusable to a certain extent. The CE-20 that was recently flown on MK-3 was fired 2-3 times before it was flight tested.

Offline vineethgk

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Re: SCE-200 semi-cryo engine info
« Reply #90 on: 06/18/2017 03:10 AM »
Confirmation on the targeted SCE-200 timelines, current state of tests and other associated activities

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The testing facilities at the ISRO Propulsion Complex, Mahendragiri, are being augmented for the engine being developed by the Liquid Propulsion Systems Centre here under a project codenamed SCE 200. Three of the four turbo pumps of the new engine have been tested and the pre-burner and thrust chamber are being readied for testing, LPSC Director S. Somanath told The Hindu.

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ISRO scientists have simultaneously begun work on the stage configuration. ‘‘We hope to complete the development of the engine by 2019. The stage test is expected to take place by 2020, followed by the first flight test in 2021,’’ he said.

They appear to be considering a configuration with a clustered kerolox core and a more powerful hydrolox upper stage (either clustered CE-20 or a new, more powerful engine) rather than one powered by a single CE-20.
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A clustered semi cryogenic booster with a more powerful cryogenic upper stage is another possibility. ‘‘Once we have mastered the technology, we could possibly go on to modular development of rockets with different configurations,’’ Mr. Somanath said.

On the necessary supporting tech and infrastructure
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But before that, ISRO needs to ensure that critical technologies such as special materials and coatings, brazing process, kerosene refinement, combustion instability and control components are mastered and the necessary infrastructure is in place.
« Last Edit: 06/18/2017 03:12 AM by vineethgk »

Offline Steven Pietrobon

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Re: SCE-200 semi-cryo engine info
« Reply #91 on: 06/18/2017 08:43 AM »
Does any know what the name of GSLV Mk.III with the SCE200? Is it GSLV Mk.IV?
Akin's Laws of Spacecraft Design #1:  Engineering is done with numbers.  Analysis without numbers is only an opinion.

Offline TrevorMonty

Re: SCE-200 semi-cryo engine info
« Reply #92 on: 06/18/2017 09:42 AM »
A 2-3 x SCE200 booster would handle GTO missions HSF to LEO without SRBs. Add there large SRBs with large US and 25-30t might be possible. For HSF the other possibility is flying Dreamchaser for SNC, its in need of low cost LV.


Offline vineethgk

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Re: SCE-200 semi-cryo engine info
« Reply #93 on: 06/18/2017 10:59 AM »
Does any know what the name of GSLV Mk.III with the SCE200? Is it GSLV Mk.IV?
They haven't mentioned any names so far, but it could very well be GSLV MkIV going by their 'functional' naming convention. Unless of course, they plan to use that core with smaller solids to create a family of launchers (Unified Launch Vehicle - ULV) to replace PSLV and GSLV-II as well, in which case the rocket could be named ULV-xx.

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #94 on: 10/23/2017 01:31 PM »
According to ISRO fully integrated SCE-200 will be delivered ready for testing by the end of year. A hot fire should take place between Jan-June 2018 depending on readiness of new testing facility.

Offline srikanthr124

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Re: SCE-200 semi-cryo engine info
« Reply #95 on: 10/26/2017 11:40 PM »
According to ISRO fully integrated SCE-200 will be delivered ready for testing by the end of year. A hot fire should take place between Jan-June 2018 depending on readiness of new testing facility.

from where do you got this information...it is really a very good news but i am unable to find anything regarding this news on Internet...

Offline K210

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Re: SCE-200 semi-cryo engine info
« Reply #96 on: 10/28/2017 01:37 AM »
According to ISRO fully integrated SCE-200 will be delivered ready for testing by the end of year. A hot fire should take place between Jan-June 2018 depending on readiness of new testing facility.

from where do you got this information...it is really a very good news but i am unable to find anything regarding this news on Internet...

I have internal sources from ISRO.....

Offline srikanthr124

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Re: SCE-200 semi-cryo engine info
« Reply #97 on: 10/28/2017 10:48 AM »
According to ISRO fully integrated SCE-200 will be delivered ready for testing by the end of year. A hot fire should take place between Jan-June 2018 depending on readiness of new testing facility.

from where do you got this information...it is really a very good news but i am unable to find anything regarding this news on Internet...

I have internal sources from ISRO.....

Thank you for prompt reply hoping everything would go as per schedule.......
Best Wishes to ISRO & LPSC team...Good Luck!...