Compressor for an aircraft engine

申请公布号：US7207772(B2)

申请号：US20040817739

申请日期：2004.04.05

申请公布日期：2007.04.24

申请人：

ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

发明人：JOHANN ERIK

分类号：F04D21/00;B64D33/00;F01D5/14;F01D5/16;F01D5/20;F04D29/66;F04D29/68

主分类号：F04D21/00

摘要：On a compressor with compressor blades, a flow transition fixation mechanism ( 4 ) is provided on the suction side ( 2 ), approximately parallel to the leading edge ( 3 ) and upstream of the compression shocks acting upon the blade, which prevents the transition point from the laminar to the turbulent boundary layer flow from oscillating, thus suppressing oscillation of the compression shocks and their coupling effect with the natural frequencies of the compressor blades.

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