发明名称 |
Engine inlet deep acoustic liner section |
摘要 |
An inlet of an aircraft nacelle having an acoustic barrel configured to reduce engine fan flutter by attenuating various frequencies. The acoustic barrel may comprise an acoustic panel of a honeycomb configuration sandwiched between a first back sheet and a face sheet and extending from a forward bulkhead to an aft bulkhead of the inlet. The acoustic barrel may further comprise a deep liner section bonded to and sandwiched between the first back sheet and a second back sheet. The deep liner section may have a narrower width than the acoustic panel and may be located proximate the aft bulkhead. The sections of the first back sheet, the face sheet, and a septum of the acoustic panel may be perforated and may contain additional holes formed in portions aligned radially inward of the deep liner section.
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申请公布号 |
US7857093(B2) |
申请公布日期 |
2010.12.28 |
申请号 |
US20090405387 |
申请日期 |
2009.03.17 |
申请人 |
SPIRIT AEROSYSTEMS, INC. |
发明人 |
STERNBERGER JOE E.;STRUNK JOHN T. |
分类号 |
B64D33/02;E04B1/74;E04B1/82;F02K1/78 |
主分类号 |
B64D33/02 |
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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