Aircraft engine electrically powered boundary layer bleed...

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

B - Operations, Transporting

64

C

B64C 21/06 (2006.01) B64D 13/08 (2006.01) B64D 33/02 (2006.01) F02C 7/14 (2006.01)

Patent

CA 2046765

DV10407A 13DV-10407 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). 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.

Affiliated with

Also associated with

Rating

Aircraft engine electrically powered boundary layer bleed... does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Aircraft engine electrically powered boundary layer bleed..., we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Aircraft engine electrically powered boundary layer bleed... will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-1530368