Development of Turbopump Systems for Cryogenic and Semicryogenic Propulsion Systems of ISRO

In Indian Space Research Organization (ISRO), the studies for the development of cryogenic propulsion were initiated in early 1980’s. The first cryogenic turbopump design (C12) in ISRO was made for 12 tonne (T) thrust engine identified for Geosynchronous Satellite Launch Vehicle (GSLV). The C12 turbopumps have undergone only initial developmental and design validation tests. The specific objective of attaining indigenous capability to launch Indian National Satellite-II (INSAT-II 2.5 T) spacecraft to geo transfer orbit (GTO) led to the need for developing a high-performance stage combustion (SC) cycle cryogenic engine. This cryogenic upper stage (CUS) engine forms the third stage of GSLV-MarkII (GSLV-MkII) launch vehicle (LV). The design check, development, extensive qualification and acceptance tests for these turbopumps were carried out and turbopumps are being used in GSLV-MkII LV. The need for launching 4 T class satellite to GTO led to the development of a high thrust 20 T cryogenic engine (CE-20). The design and development of these turbopumps were indigenously carried out. These turbopumps are rotor dynamically configured and its bearings and seals were indigenously developed. Turbopumps for CE-20 engine has successfully undergone development, qualification and acceptance tests and is being used in GSLV-MkIII vehicle. CE-20 engine turbopumps are the first indigenously designed, realised and qualified high speed turbopump in ISRO. To increase the payload capability of GSLV-MkIII LV and to meet ISRO’s future LV programme, Liquid Propulsion Systems Centre (LPSC), has taken up the development of a 200 T semicryogenic engine (SE-2000). Preliminary design review (PDR) of turbopumps are completed, hardware realisation and developmental tests are in progress.