Aero engine or rocket wall cooling method

摘要

The engine wall has a structure of hot inner wall and cooler outer wall, and the fuel flows through the structure for cooling. During operation, the "cold" outer wall (3) is permeated from the outside with a hot fluid flow. This is extracted from the engine and is small in relation to the engine throughput. The flow causes thermal expansion of the wall, or reduces its thermal contraction.The hot fluid flow is formed by combustion gas, extracted from the combustion chamber near the injection head, or by a part flow of the exhaust gases of the turbine, which drives the fuel pumps, or by an uncombusted fuel flow, which has been used as a coolant, and is heated by heat exchange.