CE-20

 

CE-20 is a cryogenic rocket engine being developed by the Liquid Propulsion Systems Center a subsidy of ISRO. It is developed to power the upper stage of GSLV-Mk.3  .It is a first  Indian cryogenic engine to feature a gas generator cycle .  It burns a mixture of liquid hydrogen and liquid oxygen and generates a thrust of  200kn. Its thrust can set between 180 kn to 220 kn  .

• Operating Cycle - Gas Generator
• Propellant Combination - Liquid oxygen / Liquid hydrogen
• Thrust Nominal (Vacuum) - 200 kN
• Operating Thrust Range - 180 kN to 220 kN (To be set at any fix values)
• Chamber Pressure (Nom) - 6 MPa
• Engine Mixture ratio (Oxidizer/Fuel by weight) - 5.05
• Engine Specific Impulse - 443 ± 3 seconds (4.344 ± 0.029 km/s)
• Engine Burn Duration (Nom) - 595 seconds
• Total Flow rate - 462 kg/s
• Nozzle Area ratio - 100
• Mass - 588 kg