Aircraft electrically powered boundary layer bleed system

摘要

An aircraft gas turbine engine is provided with an electrically powered boundary layer air blood apparatus for bleeding boundary layer air off the nacelle 220 and the wing 180 or another part of the aircraft outer skin in order to reduce boundary layer or surface drag and using the boundary layer air as a source of compressed air and cooling air for the aircraft's environmental control system (ECS) 100. A more particular embodiment of the invention provides means for ducting a portion of the boundary layer air to be further used to produce thrust and reduce base pressure drag in low pressure regions of the aircraft and engine. An electrical generator 32 is driven from the engine HP shaft 38 via a constant speed drive 48 to provide power for a motor 65 of a nacelle boundary layer compressor 60, and for motors 126, 146 150 of the ECS. Boundary layer bleed air is used partly to supply the ECS inlet compressor 210 and partly to cool heat exchangers 110. 125 of the ECS system, which includes a freon cycle cooling system 135.