The CE-7.5 is a

cryogenic rocket engine A cryogenic rocket engine is a rocket engine that uses a cryogenic fuel and oxidizer; that is, both its fuel and oxidizer are gases which have been liquefied and are stored at very low temperatures. These highly efficient engines were first f ...

developed by the Indian Space Research Organisation to power the upper stage of its

GSLV Geosynchronous Satellite Launch Vehicle (GSLV) is an expendable launch system operated by the Indian Space Research Organisation (ISRO). GSLV was used in fourteen launches from 2001 to 2021. Even though GSLV Mark III shares the name, it is an ...

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

Mk-1.

Overview

CE-7.5 is a regeneratively-cooled, variable-thrust, staged combustion cycle

rocket engine A rocket engine uses stored rocket propellants as the reaction mass for forming a high-speed propulsive jet of fluid, usually high-temperature gas. Rocket engines are reaction engines, producing thrust by ejecting mass rearward, in accorda ...

Specifications

The specifications and key characteristics of the engine are: * Operating Cycle – Staged combustion * Propellant Combination –

LOX Liquid oxygen—abbreviated LOx, LOX or Lox in the aerospace, submarine and gas industries—is the liquid form of molecular oxygen. It was used as the oxidizer in the first liquid-fueled rocket invented in 1926 by Robert H. Goddard, an appli ...

/ LH2 * Maximum thrust (Vacuum) – 73.55 kN * Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN * Engine Specific Impulse - * Engine Burn Duration (Nom) – 720 seconds * Propellant Mass – 12,800 kg * Two independent regulators: thrust control and mixture ratio control * Steering during thrust: provided by two gimballed steering engines

Development

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. The first flight attempt took place in April 2010 during the GSLV Mk.II D3/GSAT-3 mission. The engine ignited, but the ignition did not sustain as the Fuel Booster Turbo Pump (FBTP) shut down after reaching a speed of about 34,500 rpm 480 milliseconds after ignition, due to the FBTP being starved of Liquid Hydrogen (LH2). 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 GSAT-14 is an Indian communications satellite launched in January 2014. It replaced the GSAT-3 satellite, which was launched in 2004. GSAT-14 was launched by a Geosynchronous Satellite Launch Vehicle Mk.II, which incorporated an Indian-built cr ...

satellite in the GSLV-D5/GSAT-14 mission.

Applications

CE-7.5 is being used in the third stage of ISRO's GSLV Mk.II rocket.

References

{{Use Indian English, date=January 2014 Rocket engines of India Rocket engines using hydrogen propellant Rocket engines using the staged combustion cycle

Overview

Specifications

Development

Applications

See also

References