Aircraft engine electrically powered boundary layer bleed system

Details Aircraft engine electrically powered boundary layer bleed system Aircraft engine electrically powered boundary layer bleed system

1990-08-27

1992-05-19

Peters, Jr., Joseph F.

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

2441185, 244134R, 62DIG5, B64C 2106, B64D 1306

Patent

active

051141035

ABSTRACT:
An aircraft gas turbine engine is provided with an electrically powered boundary layer air bleed apparatus for bleeding boundary layer air off the nacelle and the wing 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).

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Fluid-Dynamic Drag by: Signard F. Hoerner Published-1965 pp. 3-18, 3-19, 3-20 and 20-16.

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