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 2609228
A nozzle assembly (11) for a gas turbine aircraft engine (10) is provided. The nozzle assembly includes a nacelle (24), a core cowl (22) positioned at least partially within the nacelle such that an annular bypass fan duct (26) is defined between, the core cowl and the nacelle are aligned substantially concentrically with respect to each other. The core cowl includes a first cowl portion (21) positioned within the nacelle, and a split cowl assembly (23) extending downstream from the first cowl portion, the split cowl assembly including a pair of arcuate portions (68, 70), each of the arcuate portions is repositionable within the bypass fan duct to vary an area of the bypass fan duct.
Kemper Paul D.
Moniz Thomas Ory
Seda Jorge Francisco
Company General Electric
Craig Wilson And Company
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