F - Mech Eng,Light,Heat,Weapons – 02 – K
Patent
F - Mech Eng,Light,Heat,Weapons
02
K
F02K 1/08 (2006.01) F01D 17/10 (2006.01) F02C 9/16 (2006.01)
Patent
CA 2609294
A nozzle assembly (11) for a gas turbine aircraft engine is provided. The nozzle assembly (11) includes a nacelle (24), a core cowl (22) positioned at least partially within the nacelle such that the core cowl and the nacelle are aligned substantially concentrically to each other such that an annular fan bypass duct (26) is defined between the nacelle and the core cowl, a first member (50) coupling the nacelle to the core cowl, the first member including opposing sidewalls (56,58) and a first flap (80) hingedly coupled to each of the first member sidewalls, a second member (54) opposite the first member and coupling the nacelle to the core cowl, the second member including opposing sidewalls (60,62) and a second flap (82) hingedly coupled to each of the second member sidewalls, wherein the first flaps and the second flaps are selectively positionable between a first operational position (130) and a second operational position (132) to vary a throat area of the fan bypass duct.
Kemper Paul D.
Moniz Thomas Ory
Seda Jorge Francisco
Company General Electric
Craig Wilson And Company
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