CE-20
Encyclopedia
Th CE-20 is a cryogenic rocket engine
being developed by India
. 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
.
. 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 in vacuum.
handouts:
Cryogenic Rocket Engine
A cryogenic rocket engine is a rocket engine that uses a cryogenic fuel or oxidizer, that is, its fuel or oxidizer are gases liquefied and stored at very low temperatures...
being developed by India
India
India , officially the Republic of India , is a country in South Asia. It is the seventh-largest country by geographical area, the second-most populous country with over 1.2 billion people, and the most populous democracy in the world...
. The CE-20 engine is being developed by the Liquid Propulsion Systems Centre
Liquid Propulsion Systems Centre
The Liquid Propulsion Systems Centre , located at three places, Valiyamala, near Nedumangad in Thiruvananthapuram District, Kerala, Mahendragiri in Thirunelveli District of Tamil Nadu and Bangaluru, Karnataka...
, a subsidiary of ISRO. It is being developed to power the upper stage of the Geosynchronous Satellite Launch Vehicle III
GSLV III
The GSLV-III or Geosynchronous Satellite Launch Vehicle mark III is a launch vehicle currently under development by the Indian Space Research Organization...
. It is the first Indian cryogenic engine to feature a gas-generator cycle
Gas-generator cycle (rocket)
The gas generator cycle is a power cycle of a bipropellant rocket engine. Some of the propellant is burned in a gas-generator and the resulting hot gas is used to power the engine's pumps. The gas is then exhausted...
.
Overview
The CE-20 is the first Indian cryogenic engine to feature a gas-generator cycleGas-generator cycle (rocket)
The gas generator cycle is a power cycle of a bipropellant rocket engine. Some of the propellant is burned in a gas-generator and the resulting hot gas is used to power the engine's pumps. The gas is then exhausted...
. 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
Thrust-to-weight ratio
Thrust-to-weight ratio is a ratio of thrust to weight of a rocket, jet engine, propeller engine, or a vehicle propelled by such an engine. It is a dimensionless quantity and is an indicator of the performance of the engine or vehicle....
of 34.7 and a specific impulse
Specific impulse
Specific impulse is a way to describe the efficiency of rocket and jet engines. It represents the derivative of the impulse with respect to amount of propellant used, i.e., the thrust divided by the amount of propellant used per unit time. If the "amount" of propellant is given in terms of mass ,...
of 444 seconds in vacuum.
Current status
As of 2008, the subsystem level tests were nearing completion and engine tests were planned during 2010. Majority of the facility realization across different launch vehicle centers and industries had been completed.Specifications
The specifications of the engine as listed on the LPSCLiquid Propulsion Systems Centre
The Liquid Propulsion Systems Centre , located at three places, Valiyamala, near Nedumangad in Thiruvananthapuram District, Kerala, Mahendragiri in Thirunelveli District of Tamil Nadu and Bangaluru, Karnataka...
handouts:
- Operating Cycle - Gas GeneratorGas-generator cycle (rocket)The gas generator cycle is a power cycle of a bipropellant rocket engine. Some of the propellant is burned in a gas-generator and the resulting hot gas is used to power the engine's pumps. The gas is then exhausted...
- Propellant Combination - LOXLoxLox is salmon fillet that has been cured. In its most popular form, it is thinly sliced—less than in thickness—and, typically, served on a bagel, often with cream cheese, onion, tomato, cucumber and capers...
/ 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
- Engine Burn Duration (Nom) - 595 seconds
- Total Flow rate - 462 kg/sec
- Nozzle Area ratio - 100
- Mass - 588 kg
