United Technologies Corporation

Gregg W Jones

Donald R Trenschel

Terrence J McMullen

Micki A Marshall

Jim A Clark

Lee E Hansen

J Britt Ingram

A combustion chamber for use in an engine, such as a rocket engine, has an inner wall with a corrugated configuration. The inner wall is formed with a plurality of tubes for carrying a coolant. As a result of the tubular construction, the inner wall has a plurality of spaced apart crowns and a plurality of valleys intermediate with the spaced apart crowns. To enhance the rate of heat flux or transfer in the valleys, a device is installed in each valley to cause local intensification of the turbulence in the hot gas flow in an effective way. The device may take the shape of a chevron or a bump.

Heat transfer enhancement features for a tubular wall combustion chamber

An improved engine construction, such as a rocket engine construction is provided. The engine construction comprises a combustion chamber, a smooth wall nozzle, and a transition zone between the chamber and the smooth wall nozzle. The transition zone has a coolant system which includes a manifold formed from a non-copper material through which a coolant flows. In a high heat transfer embodiment, the transition zone includes an additional manifold formed from a copper based material.

Rocket engine combustion chamber

Method of assembling a rocket engine with a transition zone between the combustion chamber and the coolant system

A combustor element face plate made of a thermally highly conductive material, such as copper, has a plurality of cooling holes extending therethrough. Some of the cooling holes are located about the injector openings, while other cooling holes are located adjacent the peripheral edge of the face plate.

Combustor injector face plate cooling scheme

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Decatur, AL, United States of America

Gregg W Jones