CE-20
Model of CE-20
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| Country of origin | India |
|---|---|
| Date | 2015 |
| Designer | LPSC, Indian Space Research Organisation |
| Manufacturer | Hindustan Aeronautics Limited, |
| Application | Upper stage booster |
| Status | Under Development |
| Liquid-fuel engine | |
| Propellant | LOX / LH2 |
| Cycle | Gas Generator |
| Configuration | |
| Chamber | 1 |
| Nozzle ratio | 100 |
| Performance | |
| Thrust (vac.) | 200 kN (45,000 lbf) |
| Isp (vac.) | 443 seconds (4.34 km/s) |
| Dimensions | |
| Dry weight | 588 kg |
The CE-20 is a cryogenic rocket engine being developed by the Liquid Propulsion Systems Centre, a subsidiary of Indian Space Research Organisation. It is being developed to power the upper stage of the Geosynchronous Satellite Launch Vehicle Mk 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. ISRO tested the CE-20 on April 28, 2015 at Mahendragiri test facility and achieved a successful long duration hot test (635 seconds). On July 16, 2015, CE-20 was successfully endurance hot tested for a duration of 800 seconds at ISRO Propulsion Complex, Mahendragiri. This duration is approximately 25% more than the engine burn duration in flight. The CE-20 cryogenic engine was again hot-tested for a duration of 640 seconds at ISRO Propulsion Complex, Mahendragiri on 19 February 2016.
For the upcoming GSLV flight in Jan 2017, it was tested again on December 03 for 25 seconds
The specifications of the engine as listed on the LPSC handouts:
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