Thrust (vacuum) - 2000 kNIsp (vacuum) - 3285 N-s/kgChamber Pressure - 18 MPaMixture Ratio - 2.65Thrust 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
Quote from: antriksh on 07/29/2013 02:12 pmThrust (vacuum) - 2000 kNIsp (vacuum) - 3285 N-s/kgChamber Pressure - 18 MPaMixture Ratio - 2.65Thrust Throttling - 65-105 (% of nominal thrust) Engine gimbal - 8 degrees (in two planes)ISRO has started building thrust chamber test facility for semi-cryo enginedosen't ISRO already have a test facility for testing liquid engines?
Quote from: K210 on 07/30/2013 07:10 amQuote from: antriksh on 07/29/2013 02:12 pmThrust (vacuum) - 2000 kNIsp (vacuum) - 3285 N-s/kgChamber Pressure - 18 MPaMixture Ratio - 2.65Thrust Throttling - 65-105 (% of nominal thrust) Engine gimbal - 8 degrees (in two planes)ISRO has started building thrust chamber test facility for semi-cryo enginedosen't ISRO already have a test facility for testing liquid engines? Not for a 2000 kN class semo-cryo engine
Quote from: antriksh on 07/31/2013 12:28 pmQuote from: K210 on 07/30/2013 07:10 amQuote from: antriksh on 07/29/2013 02:12 pmThrust (vacuum) - 2000 kNIsp (vacuum) - 3285 N-s/kgChamber Pressure - 18 MPaMixture Ratio - 2.65Thrust Throttling - 65-105 (% of nominal thrust) Engine gimbal - 8 degrees (in two planes)ISRO has started building thrust chamber test facility for semi-cryo enginedosen't ISRO already have a test facility for testing liquid engines? Not for a 2000 kN class semo-cryo engineNeed to send to RUSSIA for getting it tested?
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
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?
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.
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.
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.
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.
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.
QuoteMeanwhile, 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
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.
"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."
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.
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.
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
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-200For any higher thrust engine, India again needs to start from scratch.
Low Pressure Oxidiser Turbo pump, first major component manufactured for semicryo engine
Quote from: antriksh on 09/21/2015 11:29 amLow Pressure Oxidiser Turbo pump, first major component manufactured for semicryo engineUnit Testing Done!!?
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.
A new Brazing process for Semi-Cryo Engine established by ISROManufacture 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.
Some insight into manufacturing 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.
...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.
Quote from: Ohsin on 03/07/2016 11:24 amSome insight into manufacturing 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.
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.
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.
I wonder where they plan to do the first test firing of SCE-200. Is the new test facility at IPRC nearing completion?
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.
Quote from: K210 on 09/23/2016 07:57 amGiven 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.
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.
Quote from: K210 on 09/23/2016 07:57 amFirst 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.
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.
“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.
“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.”
Mega launchers for ISRO soonQuotePre-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.”
Somanath: planning for GSLV Mark III launch in early 2017, as well as increasing GSLV and PSLV launch rates. #IAC2016
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-200The specifications are rather identical.
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.
Page 6 :QuoteThis 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 :QuoteThe 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 :QuoteSpace 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 :QuoteSemi-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--- [ --- ]
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.
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.
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.
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.
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.
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.
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.
http://pib.nic.in/newsite/PrintRelease.aspx?relid=157921QuoteCurrently, 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.
Quote from: mightyprince on 08/14/2015 06:00 pmIf 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-200For 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.
In a recent interview LPSC director casually mentioned they have began manufacturing the first test engine
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."
"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.
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…
Quote from: srikanthr124 on 06/14/2017 11:26 amis 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.
Quote from: russianhalo117 on 06/14/2017 02:34 pmCurrent 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.
Current version in development is designed to be expendable with follow-on version designed to support reuse.
Quote from: K210 on 06/15/2017 12:32 pmQuote from: russianhalo117 on 06/14/2017 02:34 pmCurrent 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.
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.
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.
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.
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.
Does any know what the name of GSLV Mk.III with the SCE200? Is it GSLV Mk.IV?
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.
Quote from: K210 on 10/23/2017 01:31 pmAccording 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...
Quote from: srikanthr124 on 10/26/2017 11:40 pmQuote from: K210 on 10/23/2017 01:31 pmAccording 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.....
Ukraine to test components of a powerful Indian rocket engineThe Yuzhmash production plant in Ukraine prepares to begin a series of firings testing critical parts of a large rocket engine intended for India's next-generation heavy launcher. Although it was built entirely in India, the prospective engine was originally designed in Ukraine under designation RD-810.....Foreign roles for RD-810Over the years, various roles were proposed for RD-810, including replacing the Russian RD-171 on the Ukrainian-built Zenit rocket and propelling Ukraine's new-generation Mayak launcher. A four-engine cluster, dubbed RD-810M, was designed to fit into the aft section of a potential space booster with a diameter 3.9 meters, matching the caliber of the Zenit rocket. Each RD-810 was expected to gimbal up to six degrees around one axis, allowing the four-engine cluster to fully steer the rocket.Because none of the indigenous programs could be adequately funded, Ukraine sought to bring the RD-810 design to the international market. Along with several other Ukrainian designs, the RD-810 was proposed for the American super-heavy rocket developed under the Space Launch System, SLS, program. However, despite qualifying RD-810 as in high degree of readiness, American space officials did not seriously consider Ukrainian engines for the SLS project.Indian versionIn 2005, Ukraine agreed to provide India with designs for the RD-810 engine and, on Nov. 20, 2006, the Indian Space Research Organization, ISRO, awarded a contract to KB Yuzhnoe for a project code-named Jasmine, which officially started the development of the RD-810. In India, the RD-810-based engine was dubbed SC-200, which stood for "semi-cryogenic," indicating the use of kerosene fuel, which can be stored at regular temperatures, and liquid oxygen, which requires cryogenic conditions to stay in liquid form. The "200" in the designation denoted its thrust of 200 tons.ISRO planned to install the SC-200 engine on the modified core stage of the GSLV Mark 3 rocket replacing the older propulsion system. It would boost the payload capacity of the rocket to the geostationary transfer orbit from four to six tons. Later, four similar engines could propel a new-generation rocket, which could deliver up to 10 tons to the same orbit without the help of strap-on boosters.In addition to assisting with the design of the engine, KB Yuzhnoe also advised ISRO on the development of the prospective launch vehicle itself.As of 2014, KB Yuzhnoe had produced the full set of design documentation required for the production and testing of the engine. (809) According to industry sources, India then re-issued the blueprints for the engine according to its own standards and, possibly, introduced some modifications.In the meantime, KB Yuzhnoe decided to stop further development of the RD-810 engine inside Ukraine, focusing instead its limited resources on the more powerful RD-815 design, which could potentially be promising on the US market.Testing RD-810In 2017, Indian specialists returned to Ukraine to test fire the actual hardware, which had been built in India within the Jasmine project. According to industry sources, the Ukrainian Yuzhmash factory was contracted to test, not the entire engine, but its critical components, including its gas generator and a turbopump, which had all been manufactured in India. If the firings, apparently planned to be completed by 2019, validated the quality of the Indian manufacturing methods, the fully assembled engine, including the combustion chamber and the nozzle, would be tested at the yet-to-be completed bench facility at Mahendragiri, India....
Seems like India will have a fine engine for an RLV. Just cluster seven SC-200s like Blue Origin is doing with their BE-4 for the first stage.
Quote from: Steven Pietrobon on 01/11/2018 03:19 amSeems like India will have a fine engine for an RLV. Just cluster seven SC-200s like Blue Origin is doing with their BE-4 for the first stage.They have been toying with a design having a cluster of 5 engines for the first stage. Not sure if they can use the central engine for propulsive recovery in that configuration though. I'm guessing the engine would need to be capable of burning at a much lower than nominal thrust for that to work out.
Quote from: vineethgk on 01/11/2018 04:17 amQuote from: Steven Pietrobon on 01/11/2018 03:19 amSeems like India will have a fine engine for an RLV. Just cluster seven SC-200s like Blue Origin is doing with their BE-4 for the first stage.They have been toying with a design having a cluster of 5 engines for the first stage. Not sure if they can use the central engine for propulsive recovery in that configuration though. I'm guessing the engine would need to be capable of burning at a much lower than nominal thrust for that to work out.Maybe hoverslam can compensate for throttleability?
Quote from: sanman on 06/15/2017 02:49 pmQuote from: K210 on 06/15/2017 12:32 pmQuote from: russianhalo117 on 06/14/2017 02:34 pmCurrent 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.
Some very rough math shows a 5 x SCE-200 + 2 x CE-20 can do ~30-33t to LEO while 7 x SCE-200 + 2-3 x CE-20 can do 40-45t. With a 33-50% penalty for first stage recovery, you're looking at a ~15-22t or ~20-30t semi-reusable launcher. If CE-20s aren't too expensive, then 3 on the 7-engine booster would push its second stage comfortably above Centaur-class T/W levels, and at 66% remaining thrust, give the stage a fighting chance at completing the mission in the event of a single-engine failure.
They may go VTOHL. Already proved they can do HL. HL doesn't scale like VL but it is easier to get right first time and that is important R&D cost saving. If VTOHL booster can deliver 4t GTO or 10t LEO, that is most of commercial market. For bigger LV use two fly back boosters with expendable core.
Are you sure of your maths, SCE200 is about same as Merlin and F9 is about 20t to LEO.
“After a presentation before the Space Commission, Isro has got the approval for developing the semi-cryogenic rocket stage. The deadline to develop this stage is 29 months. Once the stage is ready, the carrying capability of GSLV Mk III will increase from the existing four tonnes to five tonnes.”
Isro gets nod for semi-cryogenic engine, will boost GSLV’s lift capability by 1 tonne.Quote“After a presentation before the Space Commission, Isro has got the approval for developing the semi-cryogenic rocket stage. The deadline to develop this stage is 29 months. Once the stage is ready, the carrying capability of GSLV Mk III will increase from the existing four tonnes to five tonnes.”I thought after replacing L110 stage with SCE-200 stage MK3 launch vehicle performance would increase like in the range of around 2000kg.But according above news article they are saying about only 1000kg improvement is this is directly from ISRO are reporter made it out of his own thinking..Isro chairman K Sivan said nothing about exact amount of payload improvement....
Is it SCE-200 engine manufacturing came near to completion by Godrej Industries or still individual component testing is going on at Ukraine facilities....and what about Mahendragiri test facilities status...anybody have any insider information...
The Indian Space Research Organisation (ISRO) has progressed to the testing of subsystems in the development of a semi-cryogenic engine for rockets with heavier payload capacity.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.
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.
2 X SCE-200 (Clustered) --> SC400 Stage
Is that a capsule on top?.
Mr. Somanath said that, eventually, ISRO will phase out Vikas by replacing it first in Mk-III with a cleaner and safer semi-cryogenic engine. The semi-cryo engine is ready for trial; its stage has just been approved. "I cannot predict when it [the replacement] can happen," he said.
Mr. S. Somnath, the director of VSSC has said that the Semi Cryo Engine is ready for trial.Source : Upgraded Vikas engine will soon boost ISRO's rocketsQuoteMr. Somanath said that, eventually, ISRO will phase out Vikas by replacing it first in Mk-III with a cleaner and safer semi-cryogenic engine. The semi-cryo engine is ready for trial; its stage has just been approved. "I cannot predict when it [the replacement] can happen," he said.Link is going to Australian order. Looks like the correct link is:https://www.thehindu.com/sci-tech/upgraded-vikas-engine-will-soon-boost-isros-rockets/article24436241.ece--- [ --- ]
Link is going to Australian order. Looks like the correct link is:https://www.thehindu.com/sci-tech/upgraded-vikas-engine-will-soon-boost-isros-rockets/article24436241.ece
Hmm, I wonder if that means the SCE-200 will also replace the Vikas engine on PSLV.
^^^Design looks very different compared to renders from recent years, are you sure that is SCE-200 and not some other engine?
Quote from: K210 on 11/29/2020 10:11 pm^^^Design looks very different compared to renders from recent years, are you sure that is SCE-200 and not some other engine?It is very clearly RD-120 Family. The engine version that was used for Ukrainian fork of RD-120 Family development might be what is shown there. Also was a version developed in response to AJ-26 failure and larger version for LRB competition of SLS but since foreign made was not taken seriously by the US. Russian Space Web archives some versions well. The Russian successor fork of the former joint Soviet RD-120 family is here however MoD RD-120K version is omitted: https://www.trade.glavkosmos.com/catalog/launch-vehicles/engines/liquid-fuel-rocket-engine/
Quote from: russianhalo117 on 11/29/2020 11:48 pmQuote from: K210 on 11/29/2020 10:11 pm^^^Design looks very different compared to renders from recent years, are you sure that is SCE-200 and not some other engine?It is very clearly RD-120 Family. The engine version that was used for Ukrainian fork of RD-120 Family development might be what is shown there. Also was a version developed in response to AJ-26 failure and larger version for LRB competition of SLS but since foreign made was not taken seriously by the US. Russian Space Web archives some versions well. The Russian successor fork of the former joint Soviet RD-120 family is here however MoD RD-120K version is omitted: https://www.trade.glavkosmos.com/catalog/launch-vehicles/engines/liquid-fuel-rocket-engine/SCE-200 is based on RD-810 not RD-120. Either way if it is SCE-200 in that video then we can expect ground tests to start next year.
Quote from: K210 on 11/30/2020 06:26 amQuote from: russianhalo117 on 11/29/2020 11:48 pmQuote from: K210 on 11/29/2020 10:11 pm^^^Design looks very different compared to renders from recent years, are you sure that is SCE-200 and not some other engine?It is very clearly RD-120 Family. The engine version that was used for Ukrainian fork of RD-120 Family development might be what is shown there. Also was a version developed in response to AJ-26 failure and larger version for LRB competition of SLS but since foreign made was not taken seriously by the US. Russian Space Web archives some versions well. The Russian successor fork of the former joint Soviet RD-120 family is here however MoD RD-120K version is omitted: https://www.trade.glavkosmos.com/catalog/launch-vehicles/engines/liquid-fuel-rocket-engine/SCE-200 is based on RD-810 not RD-120. Either way if it is SCE-200 in that video then we can expect ground tests to start next year.RD-870 is the RD-120 copy.https://yuzhnoye.com/en/technique/rocket-engines/steering/rd-810/
Quote from: russianhalo117 on 11/30/2020 03:38 pmQuote from: K210 on 11/30/2020 06:26 amQuote from: russianhalo117 on 11/29/2020 11:48 pmQuote from: K210 on 11/29/2020 10:11 pm^^^Design looks very different compared to renders from recent years, are you sure that is SCE-200 and not some other engine?It is very clearly RD-120 Family. The engine version that was used for Ukrainian fork of RD-120 Family development might be what is shown there. Also was a version developed in response to AJ-26 failure and larger version for LRB competition of SLS but since foreign made was not taken seriously by the US. Russian Space Web archives some versions well. The Russian successor fork of the former joint Soviet RD-120 family is here however MoD RD-120K version is omitted: https://www.trade.glavkosmos.com/catalog/launch-vehicles/engines/liquid-fuel-rocket-engine/SCE-200 is based on RD-810 not RD-120. Either way if it is SCE-200 in that video then we can expect ground tests to start next year.RD-870 is the RD-120 copy.https://yuzhnoye.com/en/technique/rocket-engines/steering/rd-810/RD-120 was developed by Energomash working hip to hip with Yuzhnoye. After the RD-120K, Yuzhnoye designed their copy, he RD-870. Then an uprated single nozzle derivative, the RD-801. When trying to replace the RD-170 in the Zenith, they developed an uprated version of that, called the RD-810. And they sold those blueprints (but no method nor material formulas) to ISRO for the SCE-200. It is not clear if said development was paid by ISRO. What is known, is that RD-801/810 are mostly "theoretical" engines that were never built, much less tested and actually certified for operations.A little tidbit: apparently the Chinese got hold of a few copies of the RD-120 (throu a Russian company), and that's what they based their YF-100/115 engine on.
There have been reports that Yuzhnoye Design Office in Ukraine has been destroyed. Yuzhnoye is the manufacturer of the 1st stage Antares tank, so if these reports are true, then Antares will never be able to launch again after NG-19.
QuoteThere have been reports that Yuzhnoye Design Office in Ukraine has been destroyed. Yuzhnoye is the manufacturer of the 1st stage Antares tank, so if these reports are true, then Antares will never be able to launch again after NG-19.https://twitter.com/SpaceAtWallops/status/1497231580217098243https://twitter.com/JURISTnews/status/1496847074465357825SCE-200 might be indefinitely delayed now...
To meet ISRO’s objective of achieving higher payloads of 5 tonnes and above in GTO, a powerful, efficient and eco friendly stage was envisaged and this led to the development of Semi cryogenic engine and stage. LPSC has configured and designed a semi-cryogenic core stage, dimensionally optimized to replace the L110 stage of GSLV Mk III. The stage with 120 tonnes of propellant loading and powered by a single SE2000 engine producing a thrust of 200 tonnes will enable GSLV Mk III to carry more than 5.1 tonnes of payload to GTO. Semi-cryogenic engines operate on purified Kerosene (Isrosene) and Liquid Oxygen as propellants and is a combination of high performance, cost-effectiveness, high density impulse and eco friendliness.The engine and stage development is presently at an advanced stage. Engine and stage systems/subsystems have been realised and further testing, qualification and flight stage delivery are progressing as planned.
HAL delivers heaviest semi-cryogenic propellant tank to IsroThe heaviest semi-cryogenic propellant tank (SC120-LOX) ever fabricated by Hindustan Aeronautics Limited (HAL) has been delivered to the Indian Space Research Organisation (Isro). The semi cryo-liquid oxygen (LOX) tank — the first developmental welded hardware — is a part of the SC120 stage intended for payload enhancement by replacing the L110 stage in the existing Mk-III launch vehicle. Last year, HAL had delivered the biggest-ever cryogenic liquid hydrogen tank (C32-LH2), which is four metres in diameter and eight metres in length, much ahead of contractual schedule.
ISRO Chairman Dr. Somnath S said in Varanasi - 'India's first semi-cryogenic engine will be launched after three months'Dr. Somnath told that ISRO is now working on completely indigenous technology. Three months later, the country's first semi-cryogenic engine will be tested. It will have a fuel capacity of 200 tonnes. After its success, the payload capacity of GSLV Mark-III will be increased from four tonnes to 5.5 tonnes. It will be based on kerosene and hydrogen and oxygen oxidizer in the semi cryogenic engine.
LPFT Straightener helps in channelising the flow coming into the pump of the propulsion system.
Closed Impeller is part of the fuel delivery system
Numerical simulations are performed for 60%, 100% and 105% thrust conditions at the inlet duct to the main LOX pump in SCE-200, a staged combustion cycle based semi-cryogenic rocket engine, indigenously being developed in India.
To power future heavy lift launch vehicles and manned space missions, ISRO is developing a 2000 kN oxidizer-rich staged combustion cycle based semi-cryogenic rocket engine SCE-200. As in typical staged combustion cycle based rocket engines, the gas driving the booster turbine is recirculated and mixed with the pump outlet to increase the cycle efficiency [1]. This leads to condensation of hot turbine drive gas (predominantly oxygen and small amounts of CO2 & H2O) when it comes in direct contact with subcooled liquid oxygen at the inlet duct to the main LOX pump[2,3] as shown in Figure 1.Very few researchers [2,4,5,6] have studied this typical direct contact condensation problem occuring at crygenic temperatures, whereas, lot of studies have been reported for the case of steam-water direct contact condensation.
A two fluid Eulerian multiphase model has been implemented in the commercial CFD package ANSYS CFX® to simulate the direct contact condensation process of oxygen vapor jets in flowing subcooled liquid. The plots of plume shapes and heat transfer coefficients for different thrust conditions are plotted and the results were analyzed. It has been observed that the rate of condensation increases with increase in thrust. Since, the vapor and liquid have higher mass fluxes at higher thrust conditions, the plume shapes does not decrease much though the heat transfer coefficients are high. In addition, it has been observed that the vapor plumes escape the pipe domain, which hints the need for modification of the inlet duct size in future.
Thermo-hydraulic simulation of lOX Booster Turbo-pump for Semi-Cryogenic Rocket Engine:SC-2000, India’s indigenous semi-cryogenic rocket engine, is being developed at ISRO’s LPSC. This project helped to develop the Low-Pressure Oxidiser Turbopump (LPOT), which is part of the SC-2000’s staged combustion cycle. In this project, the axial pump in LPOT is powered by a partial admission impulse turbine, which is run by the oxidizer-rich combustion products (hot gas) from the pre-burner. The hot gas at the turbine exit mixes with LOX from the pump exit, forming a multi-component multiphase flow with phase change, leading to solidification of CO2 and H2O.
ISRO is in talks with Roscosmos to supply the engines RD-191M: https://www.militarynews.ru/story.asp?rid=1&nid=586029&lang=RU
About the semi-cryogenic engine, Somanath said ISRO is developing one to replace the LVM-3 or Launch Vehicle Mark-III, previously known as the Geosynchronous Satellite Launch Vehicle Mark III or GSLV Mk III.
According to him, it is a 200-tonne engine, which ISRO has been developing for the past 15 years. "This engine has now reached the first powerhead. The assembly has already been done. We have built a huge test facility. It was commissioned just last month and we have installed it and done the first ever propellant feed into it (sic). So it's successful now," the ISRO chief said.
He added that in another few days the first firing of the engine will take place, followed by six to seven tests, which will take place every two weeks under different conditions. If the tests are successful, the next phase will be to work on the hardware, Somanath said.
He also explained that ISRO had initially planned to conduct the tests in Russia and Ukraine because they had the facilities to conduct the tests, but now due to war those locations are not accessible. "Now the geopolitical situation does not allow us to go there," Somanath said, explaining that it made the space agency accelerate the construction of such a facility in India. "I am happy that the industry is supporting us so much to build a huge facility, which has just been commissioned," he added.
In a major technological breakthrough that will eventually add more lifting-power to Indian rockets, the Indian Space Research Organization (ISRO) successfully test fired its most powerful-yet rocket engine. Chairman ISRO Dr. S. Somanath confirmed the development to WION. The test firing was conducted at the ISRO Propulsion Complex(IPRC) in Mahendragiri, Tamil Nadu.
After a series of further tests are conducted and this engine is fully qualified, this 2000kN thrust engine and its stage(associated components, fuel tanks etc.) will be replacing the current L110(liquid-fuel core stage) of India's largest rocket - Launch Vehicle Mark 3 (LVM3).
ISRO has successfully performed the first proper test firing of the SCE-200 engine! #ISRO
Looks like the test wasn't as much of a success as previously anticipated.At 2 seconds into the firing there was a spike in turbine pressure followed by loss of turbine speed causing the test to be aborted.Regardless, this is a massive milestone in the SCE-200 program! #ISRO
First hot test of the Semi-cryogenic engine conducted at IPRC, MahendragiriJuly 3, 2023On July 1, 2023, ISRO conducted the first hot test on an intermediate configuration of the Semi-cryogenic Engine, known as Power Head Test Article (PHTA) at ISRO Propulsion Complex (IPRC), Mahendragiri, Tamil Nadu. The test was conducted towards developing a 2000 kN thrust semi-cryogenic engine to power the booster stages of future launch vehicles.The objective of the test was to validate the integrated performance of the critical subsystems such as the gas generator, turbo pumps, pre-burner and control components by carrying out a hot-firing for a short-duration of 4.5 s. The ignition and generation of hot-gas within the pre-burner chamber that drives the main turbine to drive the fuel and oxidiser pumps, was focussed.The test proceeded as predicted till 1.9 s validating the ignition and subsequent performance of PHTA. At 2.0 s, an unanticipated spike in the turbine pressure and subsequent loss of turbine-speed was observed. As a precautionary step, the test was terminated. Analysis under progress would offer further understanding before proceeding with further hot-tests for longer duration.The semi-cryogenic engine utilizes a propellant combination of Liquid Oxygen (LOX) and Kerosene, and the power head test article forms the first hardware test of the engine development program. The test was carried out the dedicated test facility recently established at IPRC for testing semi-cryogenic engines and stages. ISRO had commenced the testing of the PHTA in May 2023 at this facility.
Looks like test failed
However, the story of LVM-3 thread"Semi-Cryo engine will be applied from LVM-3 M4"does not match the reality of engine development at all.https://forum.nasaspaceflight.com/index.php?topic=36389.160Any updates on when Semi-Cryo will go live?