Stalled and Stall-free Performance of Axial-flow Compressor Stage with Three Inlet-guide-vane and Stator-blade Settings |
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60 percent approximately 2.5 kilograms AXIAL-FLOW COMPRESSOR blade settings blades at design blades closed 18 blades were closed closed 45 correspondingly lower pressure Cunnan data were obtained design settings design speed occurred downstream stages drop in pressure equivalent weight flow five-stage compressor five-stage environment flow was essentially flow was further flows and correspondingly formance further reduced gradual reduction inlet guide vanes inlet-guide-vane and stator inlet-guide-vane and stator-blade kilograms per second Lewis Research Center line was steep lower flows lower pressure ratios NASA off-design settings overall performance percent of design percentage points plenum tank pressure ratio occurred pressure-ratio gradient radial rake range of inlet-guide-vane ratio against equivalent reduction in pressure relatively sharp drop rotor stage peak efficiency Stall at design stall free stall region stall was encountered STALLED AND STALL-FREE stator blades closed stator-blade settings TEST STAGE thermocouples three inlet-guide-vane total temperature total-pressure ratio total-temperature ratio Urasek vanes and stator