F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
60/89
F02C 7/042 (2006.01) B64D 33/02 (2006.01)
Patent
CA 2034439
ABSTRACT OF THE DISCLOSURE An annular nacelle for a turbine engine of an aircraft has a variable contour annular air inlet. The variable contour annular inlet includes annular outer and inner surface-defining radially-spaced structures on the forward portion of the nacelle, an annular member disposed between the annular outer and inner structures and coupled to the annular outer structure for sliding movement along the interiors of the annular outer and inner structures, and a plurality of actuating mechanisms coupled between the nacelle body and the annular member. The actuating mechanisms are operable for moving the annular member between forward and rearward positions. At the forward position, the annular member is located between the forward ends of the annular outer and inner structures with the annular outer structure expanded to an enlarged diameter such that the annular member forms therewith an inlet lip having an aerodynamically blunt exterior contour adapted to reduce drag during takeoff and landing operation of the aircraft. At the rearward position, the annular member is spaced rearwardly from the forward ends of the annular outer and inner structures with the annular outer structure contracted to a reduced diameter permitting the annular outer and inner structures at the forward ends thereof to form an inlet lip having an aerodynamically sharp exterior contour adapted to reduce drag during cruise operation of the aircraft.
Readnour Jack L.
Wright Jack D.
Company General Electric
Craig Wilson And Company
Readnour Jack L.
Wright Jack D.
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