Patent ID: 7837155
Filing Date: 2010-11-23
Classification: B64C,B64D,F01D,F02K,Y02T

Abstract:
1. A suction arrangement for drawing off a boundary layer on an aircraft with a structure, comprising: an outer skin including suction surfaces in critical flow areas; an air breathing bypass engine, the bypass engine comprising a nacelle, a front fan, a bypass structure, a bleed air branch line, and an engine outlet downstream from the front fan, a bypass structure dividing a main flow entering the nacelle and exiting the engine outlet into a core flow and a bypass flow, wherein the core flow of the bypass engine flows to the engine outlet via a high-pressure compressor region and a high-pressure turbine region, wherein an inlet of the bleed air branch line withdraws bleed air from a the high-pressure compressor region of the bypass engine and the bleed air from the bleed air branch line drives a turbine of a turbo-supercharger assembly, the turbo-supercharger assembly having a compressor serving as a suction source fluidically coupled to the suction surfaces of the outer skin for drawing off the boundary layer, wherein a pressure line from the compressor of the turbo-supercharger assembly fluidically couples the compressor of the turbo-supercharger assembly to the main flow exiting the engine outlet of the bypass engine at a location of lower static pressure than the high-pressure region of the bypass engine, and wherein an exhaust line fluidically couples an exhaust flow of the turbine of the turbo-supercharger assembly to the main flow exiting the engine outlet of the bypass engine.