The CE-7.5 is a cryogenic rocket engine developed by Indian Space Research Organisation .The engine was developed as a part of the Cryogenic Upper Stage Project (CUSP) . It replaced the Russian KVD-1 cryogenic engine which powered the upper stage stage of gslv mk.1 .
The ce-7.5 cryogenic engine uses
staged combustion cycle to achieve high thrust . It has a nominal thrust of of 75 kn but it can be varied between 73.55 to 82 kn depending on requirement .
staged combustion cycle to achieve high thrust . It has a nominal thrust of of 75 kn but it can be varied between 73.55 to 82 kn depending on requirement .
- Operating Cycle – Staged combustion
- Propellant Combination – LOX / LH2
- Maximum thrust (Vacuum) – 75 kN
- Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN
- Chamber Pressure (Nom) – 58 bar
- Engine Mixture ratio (Oxidizer/Fuel by mass) – 5.05
- Engine Specific Impulse - 454 ± 3 seconds (4.452 ± 0.029 km/s)
- Engine Burn Duration (Nom) – 720 seconds
- Propellant Mass – 12500 kg
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