SHOCKWAVE-INDUCED BOUNDARY LAYER BLEED FOR TRANSONIC GAS TURBINE
申请公布号:WO2005108759(A1)
申请号:WO2005CA00706
申请日期:2005.05.06
申请公布日期:2005.11.17
发明人:OUELLET, GILBERT;LEBLANC, ANDRE
分类号:F01D1/00;F01D5/14;F01D5/18;F02C3/06;F02C9/18;F04D21/00;F04D29/68;(IPC1-7):F02C9/18
主分类号:F01D1/00
摘要:<p>An apparatus and method is provided for improving efficiency of a transonic gas turbine engine compressor (20) by bleeding off a shockwave-induced boundary layer from the gas flow passage (42) of the compressor using an array of bleed holes (36) having a downstream edge (39) aligned with a foot (45) of an oblique shock wave (44) which originates on the leading edge (46) of an adjacent transonic rotor blade tip (30).</p>