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|Country of origin||India|
|Propellant||LOX / LH2|
|Thrust (vac.)||73.5 kN|
|Chamber pressure||5.8 MPa / 7.5 MPa|
|Isp (vac.)||454 seconds (4.45 km/s)|
|Length||2.14 m (7.02 ft)|
|Diameter||1.56 m (5.11 ft)|
|Dry weight||435 kg|
The CE-7.5 is a cryogenic rocket engine developed by ISRO to power the upper stage of its GSLV Mk-2 launch vehicle. The engine was developed as a part of the Cryogenic Upper Stage Project (CUSP). It replaced the KVD-1 (RD-56) Russian cryogenic engine that powered the upper stage of GSLV Mk-1.
The specifications and key characteristics of the engine are:
- 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 – 12800 kg
- Two independent regulators: thrust control and mixture ratio control
- Steering during thrust: provided by two gimbaled steering engines
ISRO formally started the Cryogenic Upper Stage Project in 1994. The engine successfully completed the Flight Acceptance Hot Test in 2008, and was integrated with propellant tanks, third-stage structures and associated feed lines for the first launch. First flight attempt took place in April 2010 using GSLV Mk-2 D3 launch vehicle. However the engine failed to ignite. On 27 March 2013 the engine was successfully tested under vacuum conditions. The engine performed as expected and was qualified to power the third stage of the GSLV Mk-2 rocket. On 5 January 2014 the cryogenic engine performed successfully and launched the GSAT-14 satellite using GSLV D5.
CE-7.5 is being used in the third stage of ISRO's GSLV Mk-2 rocket.
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