High performance supersonic bleed inlet

Details High performance supersonic bleed inlet High performance supersonic bleed inlet

1994-03-03

1995-03-14

Kashnikow, Andres

Aeronautics and astronautics

Aircraft power plants

137 151, B64D 3302

Patent

active

053970772

ABSTRACT:
An inlet bleed system for a supersonic aircraft engine having a longitudinally downstream extending inlet bounded by a boundary wall that in part defines a supersonic flowpath through the inlet, a transversely extending boundary layer scoop extends into a boundary layer region of the flowpath and has an upstream facing bleed aperture, and a shock generating means for generating a shockwave in a supersonic flow in the flowpath such that the shockwave passes through the bleed aperture. One embodiment provides a scoop which extends a height above the wall such that it is operable to scoop off no more than a sufficient amount of a boundary layer flow that would exist in the boundary region and be momentum deficient relative to predetermined conditions that would exist downstream of the scoop under supersonic operating conditions. Another embodiment provides for the scoop to be disposed a throat section of the inlet wherein the aperture located is just upstream of the normal shock location.

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