发明名称 |
HIGH PERFORMANCE CONVERGENT DIVERGENT NOZZLE |
摘要 |
A turbofan engine includes a fan section. A core engine section drives the fan section. An outer nacelle surrounds the fan section and defines a radially outer surface of a fan duct. An inner nacelle surrounds the core engine section and defines a radially inner surface of the fan duct. A nozzle is disposed at a terminal end of the outer nacelle that defines an exit area for bypass air flow through the fan duct. The nozzle includes a convergent portion forward of a divergent portion and a turning angle for the divergent portion greater than about 12 degrees. A nacelle assembly and method are also disclosed. |
申请公布号 |
WO2015027131(A1) |
申请公布日期 |
2015.02.26 |
申请号 |
WO2014US52225 |
申请日期 |
2014.08.22 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
MURPHY, MICHAEL JOSEPH;PETRENKO, OLEG |
分类号 |
F02K3/06;F02C7/04;F02K1/06 |
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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