发明名称 Cambered aero-engine inlet
摘要 A propulsion system includes an engine with a fan and a nacelle that circumscribes the engine. The engine defines an axis. A distance between a forwardmost point at the top of the nacelle and at the front of the nacelle to a forwardmost point of the fan is greater than a distance between a forwardmost point at the bottom of the nacelle and at the front of the nacelle.
申请公布号 US8528318(B2) 申请公布日期 2013.09.10
申请号 US201213572780 申请日期 2012.08.13
申请人 HENDRICKS GAVIN;UNITED TECHNOLOGIES CORPORATION 发明人 HENDRICKS GAVIN
分类号 F02K3/02 主分类号 F02K3/02
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