发明名称 Rotor blade for the compressor of a turbo engine, compressor and turbo machine
摘要 The blade has a blade portion (2) comprising a forward edge (4), a rear edge (6) and a blade tip (12), where a pressure side (8) and a suction side (10) extend among the forward edge, the rear edge and the blade tip. A pressure-side variation profile i.e. shaft profile (14), extends into the rear edge and the blade tip. A recess is formed in a region with a maximum pressure gradient. The variation profile is oriented transverse to a flow direction (X) of the blade portion. The variation profile comprises a set of projections or crests and a set of depressions or troughs. An independent claim is also included for a compressor.
申请公布号 EP2530330(B1) 申请公布日期 2016.05.25
申请号 EP20110168407 申请日期 2011.06.01
申请人 MTU AERO ENGINES AG 发明人 DR. SCHÖNENBORN, HARALD
分类号 F04D29/32;F04D29/52;F04D29/68 主分类号 F04D29/32
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