发明名称 |
ENSEMBLE DE TUYERE DE TURBOREACTEUR DOUBLE FLUX |
摘要 |
A nozzle assembly for a gas turbine aircraft engine is provided. The nozzle assembly includes a nacelle and a core cowl positioned at least partially within the nacelle such that the core cowl and the nacelle are aligned substantially concentrically to each other defining an annular fan bypass duct. A first member couples the nacelle to the core cowl and includes a first flap hingedly coupled to each sidewall of the first member. An opposing second member couples the nacelle to the core cowl and includes a second flap hingedly coupled to each sidewall of the second member. The first flaps and the second flaps are selectively positionable between a first operational position and a second operational position to vary a throat area of said fan bypass duct. A turbofan engine assembly and a method for operating the same are also provided. |
申请公布号 |
FR2908470(B1) |
申请公布日期 |
2014.02.14 |
申请号 |
FR20070058674 |
申请日期 |
2007.10.30 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
KEMPER PAUL D;MONIZ ORY THOMAS;SEDA JORGE FRANCISCO |
分类号 |
F02K3/06;F02K1/08;F02K1/15 |
主分类号 |
F02K3/06 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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