ABOUT CE-20
The CE-20 is India’s first cryogenic engine designed and manufactured indigenously by ISRO, powering the upper stage of the GSLV Mk III (LVM3). It uses a gas-generator cycle burning liquid hydrogen and liquid oxygen, producing 200 kN of vacuum thrust. The development of the CE-20 was a major milestone for India’s space program, achieving self-reliance in cryogenic propulsion.
Image: ISRO
PERFORMANCE
| Thrust (Sea Level) | N/A (upper stage) kN |
| Thrust (Vacuum) | 200 kN (44,960 lbf) kN |
| ISP (Sea Level) | N/A s |
| ISP (Vacuum) | 443 s s |
| Chamber Pressure | 6.0 MPa (870 psi) bar |
| Mass | 588 kg |
| Thrust-to-Weight | 35 |
| Throttle Range | Not throttleable |
| Restart Capable | No |
THRUST CONVERSIONS (VACUUM)
| Kilonewtons | 200.0 kN |
| Pounds-force | 44,962 lbf |
ENGINE CYCLE
Gas Generator
A gas generator cycle taps off a small portion of propellants to drive turbopumps via a separate combustion chamber. The turbine exhaust is dumped overboard, making it less efficient but simpler and more reliable. Used by the Merlin, F-1, and RS-27.
PROPULSION
| Propellant | Liquid Hydrogen (LH₂) |
| Oxidizer | LOX |
| Engine Cycle | Gas Generator |
| Mixture Ratio | 5.05:1 |
| Flow Rate | ~46 kg/s kg/s |
PHYSICAL
| Dimensions | 1.0 m diameter × 2.1 m length |
| Combustion Chambers | 1 |
| Nozzle Expansion Ratio | 100:1:1 |
GENERAL
| Manufacturer | ISRO (Liquid Propulsion Systems Centre) |
| Country | India |
| Status | Active |
| First Flight | April 16, 2026 |
VARIANTS (1)
- CE-20
VEHICLES USING CE-20 (1)
- GSLV Mk III / LVM3
ENGINE LINEAGE
CE-7.5→CE-20→SCE-200 (planned semi-cryo)
⚖ PROPELLANTS
