Cryogenic engines using Liquid Oxygen (LOX) and Liquid Hydrogen (LH2) propellant combination give maximum performance as compared to other operational rocket propulsion systems. With this background, Indian Space Research Organisation (ISRO) started developing a medium thrust cryogenic engine to achieve higher payload capability for its Geosynchronous Satellite Launch Vehicle (GSLV). This cryogenic engine is turbopump fed and works on gas generator cycle. The thrust chamber which forms the major system of the engine, generates the required thrust for propelling the stage. The complex technologies required for the realisation of the thrust chamber have been indigenously developed and demonstrated. The ignition system, fluid components, cryo fluids and transducers etc. utilised for the tests have been developed within Indian Space Research Organisation (ISRO). Extensive software studies, acceptance tests, calibration and chill down trials were carried out prior to hot test. The thrust chamber has been successfully hot tested at the test facilities established at Liquid Propulsion Systems Centre (LPSC), ISRO. This paper briefly presents the development and testing of the thrust chamber.
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