Engine study

SE2000

ISRO 2000 kN-class semi-cryogenic development engine. Cycle: semi-cryogenic engine. Propellants: kerosene + liquid oxygen.

Run performance calculator

Engine visual

Rocket engine test image

This page includes the generated engine-test image for propulsion, combustion, and simulation context.

Engine Details

Class	2000 kN semi-cryogenic engine
Stage	SC120 concept for LVM3 payload enhancement
Fuel	Kerosene
Oxidizer	LOX
Study theme	non-toxic booster-stage upgrade path

Combustion Study

Public analysis focuses on propellant pair, thermochemistry, chamber pressure class, cooling, turbomachinery architecture, and integration risk. Exact manufacturing recipes and proprietary controls are intentionally excluded.

Powerhead

Pumps, preburners or gas generator, valves, ignition, health monitoring, and start sequence govern reliability.

Chamber and Nozzle

Combustion stability, regenerative cooling, throat erosion, expansion ratio, and plume environment govern performance.

Reuse

Reusable engines need inspection access, thermal margin, data review, and acceptance criteria after each firing.