CE-20

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CE-20
IndianCryoEngine25.JPG
Model of CE-20
Country of origin India
Date 2010
Designer ISRO
Manufacturer LPSC
Application Upper stage booster
Status Active
Liquid-fuel engine
Propellant LOX / LH2
Cycle Gas Generator
Configuration
Chamber 1
Nozzle ratio 100
Performance
Thrust (vac.) 200 kN
Chamber pressure 60.00 bar
Isp (vac.) 443 seconds (4.34 km/s)
Dimensions
Dry weight 588 kg

Th CE-20 is a cryogenic rocket engine being developed by India.[1] The CE-20 engine is 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.[2]

Overview[edit]

The CE-20 is the first Indian cryogenic engine to feature a gas-generator cycle.[3] 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.

Specifications[edit]

The specifications of the engine as listed on the LPSC handouts:[4]

  • 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

See also[edit]

References[edit]

Reference Page text.[5] Page text.[1] Additional use of same reference [5] Page text.[1]

Display references

  1. ^ CE-20 Specifications
  2. ^ "Space Transportation". GSLV - Mk III - Status of CE-20. Indian Space Research Organization. 2009-07-15. Retrieved 2009-08-29. 
  3. ^ http://www.frontline.in/cover-story/gslv-mkiii-the-next-milestone/article5596588.ece
  4. ^ "LPSC Handouts at Aer India-2009". Specifications of CE-20. Liquid Propulsion Systems Centre. 2009-03-13. Retrieved 2009-08-29. 
  5. ^ a b http://isro.org/pressrelease/scripts/pressreleasein.aspx?May12_2012, additional text.

External links[edit]


India: SC2000 Liquid Oxygen and Kerosine engine with 2000KN Thrust at SL