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TR-107
TRW LOx/kerosene rocket engine. Booster stages. TRW design for NASA's Space Launch Initiative. The engine used duct-cooling of the main combustion chamber and materials that would not interact with kerosene to minimize coking.

Date: 2002. Thrust: 4,900.00 kN (1,101,500 lbf).

The duct separated the fuel from the chamber wall and allowed controlled cooling of the chamber to keep the temperature of the kerosene down. This approach simplified the engine in comparison with competing designs. By eliminating the regenerative cooling circuit, many large manifolds and associated plumbing were eliminated as well, reducing potential failure modes and improving engine reliability. The TR107 engine used oxygen-rich combustion products to alleviate soot build-up when running the turbopumps.

Chamber Pressure: 177.00 bar.



Country: USA. Propellants: Lox/Kerosene. Agency: TRW. Bibliography: 460, 7568.

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