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分散式叶型梳状五孔针—全台压气机级间参数测量新方案

A DISTRIBUTED FIVE-HOLE PROBE RAKE ON STATOR BLADES FOR ROTOR EXIT MEASUREMENT OFA COMPRESSOR
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摘要 Each tube of five-holes probe will be placed at the same radius on five different blades of stator.The diameter of the probe and the wall proximity effect are decreased.The distributed five-hole probe rake has been verified experimentally.Its dynamical frequency response is enhanced seven times.Its characteristics are improved.The parameter measurement of each rotor exit in a multistage compressor becomes practicable. Each tube of five-holes probe will be placed at the same radius on five different blades of stator.The diameter of the probe and the wall proximity effect are decreased.The distributed five-hole probe rake has been verified experimentally.Its dynamical frequency response is enhanced seven times.Its characteristics are improved.The parameter measurement of each rotor exit in a multistage compressor becomes practicable.
机构地区 西北工业大学
出处 《航空动力学报》 EI CAS CSCD 北大核心 1991年第2期137-138,共2页 Journal of Aerospace Power
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  • 1团体著者,航空发动机气动参数测量,1980年

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