9 pages matching blades at design in this book
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60 percent aspect ratio AXIAL-FLOW COMPRESSOR blades at design blades closed 45 blades were closed closed 18 combinations of inlet-guide-vane correspondingly lower pressure Cunnan data were obtained design settings design speed occurred downstream stages drop in pressure equivalent weight flow essentially unchanged 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-blade kilograms per second Lewis Research Center line was steep lnlet lower flows lower pressure ratios mass-averaged NASA off-design settings overall performance percent of design 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 occurred stall region stall was encountered stall-free performance data stalled and stall-free static pressure stator blades closed stator-blade settings TEST STAGE thermocouples three inlet-guide-vane total-pressure ratio Urasek vanes and stator