| 摘要 |
An aircraft propulsion arrangement including a gas turbine aircraft engine 1 having a compressor 9, an oil system configured to route engine oil through a heat exchanger 19 mounted so as to define part of an aerodynamic surface to the flow of ambient air, and a duct arrangement 13 fluidly connecting the compressor to the heat exchanger. The compressor is provided with a bleed takeoff 12 configured to bleed gas from the compressor wherein said bleed gas is directed by said duct arrangement to flow across the heat exchanger in a heat exchange relationship with said oil. A flow controller 13a is provided actuable to selectively regulate the flow of compressor gas across the heat exchanger. The aerodynamic surface is provided by a pylon 2 and incorporates said heat exchanger. The flow of compressor gas across the heat exchanger may be controlled selectively in dependence on one of; the temperature of engine oil measured within the engine, the airspeed of the aircraft and the aircraft flight cycle conditions. |
