Model of CE-20
|Country of origin||India|
|Application||Upper stage booster|
|Propellant||LOX / LH2|
|Thrust (vac.)||200 kN|
|Chamber pressure||60.00 bar|
|Isp (vac.)||443 seconds (4.34 km/s)|
|Dry weight||588 kg|
Th CE-20 is a cryogenic rocket engine being developed by the Liquid Propulsion Systems Centre, a subsidiary of ISRO. It is being developed to power the upper stage of the Geosynchronous Satellite Launch Vehicle III. It is the first Indian cryogenic engine to feature a gas-generator cycle.
The CE-20 is the first Indian cryogenic engine to feature a gas-generator cycle. The engine produces a nominal thrust of 200 kN, but has an operating thrust range between 180 kN to 220 kN and can be set to any fixed values between them. The combustion chamber burns liquid hydrogen and liquid oxygen at 6 MPa with 5.05 engine mixture ratio. The engine has a thrust-to-weight ratio of 34.7 and a specific impulse of 444 seconds (4.35 km/s) in vacuum.
- Operating Cycle - Gas Generator
- Propellant Combination - LOX / LH2
- 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
- Indigenous Cryogenic Engine Tested Successfully ISRO 12 May 2012
- "Space Transportation". GSLV - Mk III - Status of CE-20. Indian Space Research Organization. 2009-07-15. Retrieved 2009-08-29.
- GSLV MkIII, the next milestone Frontline 7 February 2014
- "LPSC Handouts at Aer India-2009". Specifications of CE-20. Liquid Propulsion Systems Centre. 2009-03-13. Retrieved 2009-08-29.
- LPSC handouts during Aero India-2009 with Ce-20 specifications
- LPSC handouts during Aero India-2009 with specifications of all Liquid-fueled engines of India
- Status of CE-20 in Space Transportation/GSLV - Mk III of ISRO's 2008-09 Annual Report
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