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...
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.
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
