发明名称 Device for soundproofing a gas turbine helicopter engine and engine obtained using same
摘要 The device has a compressor e.g. centrifugal compressor, and an annular passage (12) for supplying air to the compressor. A radial air inlet (34) including lips (30, 32) is connected to the passage in which the lips are partially formed by acoustic attenuators (40, 42) e.g. Helmholtz attenuators. The attenuators attenuate sound frequencies produced by rotation of the compressor, where the lips are made of fibrous reinforcement composite material densified by resin. Another set of acoustic attenuators is integrated to a metallic case (14) defining the passage of the compressor.
申请公布号 EP1902953(A1) 申请公布日期 2008.03.26
申请号 EP20070115944 申请日期 2007.09.07
申请人 TURBOMECA, SOCIETE DITE: 发明人 BAUDE, PIERRE
分类号 B64D33/02;F02C7/045;F02C7/055 主分类号 B64D33/02
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