发明名称 |
NACELLE FOR AN AIRCRAFT BYPASS TURBOJET ENGINE |
摘要 |
The disclosure relates to a nacelle for a turbojet engine, including an upstream section forming an air intake lip and defining a space for the circulation of a main air flow. The nacelle includes a device for modulating the cross-section of the space and has means for injecting an auxiliary flow of a gas by means of an induced ejector effect; suction means for drawing in the injected auxiliary flow; and an internal auxiliary flow return area in one or more walls, the area being configured to allow the circulation of the injected auxiliary flow and the drawn-in auxiliary flow and to bring part of the injected auxiliary flow into contact with the main air flow. The internal return area includes an outer front part forming an area in which the thickness of the internal return area is reduced. |
申请公布号 |
EP2665909(A2) |
申请公布日期 |
2013.11.27 |
申请号 |
EP20120702596 |
申请日期 |
2012.01.09 |
申请人 |
AIRCELLE |
发明人 |
GONIDEC, PATRICK;BLIN, LAURENT ALBERT |
分类号 |
F02K1/30;B64C21/02;B64D33/00;B64D33/02;B64D33/04;F02C7/00;F02C7/04;F02K3/06 |
主分类号 |
F02K1/30 |
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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