B - Operations – Transporting – 64 – D
Patent
B - Operations, Transporting
64
D
244/33, 60/81
B64D 29/02 (2006.01) B64C 23/00 (2006.01) B64D 33/02 (2006.01) F02K 1/52 (2006.01) F02K 3/04 (2006.01)
Patent
CA 1185101
DRAG-REDUCING NACELLE ABSTRACT OF THE DISCLOSURE A Wing-mounted gas turbofan engine is provided with an exhaust system that reduces airflow drag during subsonic aircraft flight peration. The system reduces drag by turning the engine bypass exhaust stream away from the underside of the airplane wing to lessen its tenddency to reduce air pressure under the wing. Low pressure below the airplane wing has a detrimental effect on wing lift which, in turn, causes greater airflow drag. The exhaust system construction lessens its pressure lowering influence by first inwardly curving the exhaust system exit to turn the bypass flow away from the airplane wing; second, by determining the location of a nozzle throat within the bypass stream to control exit exhaust pressure so as to match outside air pressure and third, by decreasing the diameter of a portion of the engine nacelle just downstream of the bypass exhaust steam exit to provide a flow region for the exhaust that is further from the airplane wing.
367228
Company General Electric
Eckersley Raymond A.
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