发明名称 Thermal blade tip clearance control for gas turbine engines
摘要 An axial-flow compressor in which rotor blade clearance, in an area where the stator case surrounding a rotor blade stage is unsupported, is controlled by the cross-sectional area of a ring surrounding the stator case and by a gap between the inner surface of the ring and the outer surface of the stator case established at the time of compressor build.
申请公布号 US5154575(A) 申请公布日期 1992.10.13
申请号 US19910724289 申请日期 1991.07.01
申请人 UNITED TECHNOLOGIES CORPORATION 发明人 BONNER, KURT J.
分类号 F01D11/18;F04D29/16 主分类号 F01D11/18
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