Effect of several porous casing treatments on stall limit and on overall performance of an axial-flow compressor rotor
Walter Martin Osborn, George W. Lewis (Jr.), Laurence J. Heidelberg, Lewis Research Center, United States. National Aeronautics and Space Administration
National Aeronautics and Space Administration, 1971 - Technology & Engineering - 44 pages
Several geometrically different porous casings were tested with an axial-flow compressor rotor to determine their effects upon the rotor stall-limit line and overall performance. The tests were conducted using both uniform and nonuniform inlet-flow conditions. The rotor performance with the various casing treatments is compared with that obtained with a solid casing. The ability of the various casing treatments to displace the rotor stall-limit line to lower weight flows was observed. Significant stall-margin increases were obtained with several of the porous casings. Peak efficiencies with two of the porous casings were as high as or slightly higher than that obtained with solid casing.
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40 Equivalent weight 60 70 Equivalent air between slots air is possible approximately av)a axially slotted blade angle slotted blade passing frequency blade tip blade-tip leading edge ciency circumferentially distorted inlet circumferentially grooved design speed displacement distorted inlet flow distortion screen effi Equivalent weight flow flow of 63 flow stream ahead holes honeycomb Ibm/sec Figure increase in stall inlet flow distortions limit line line to lower long slots lower weight flows main flow stream margin increase maximum efficiency open slots overall rotor performance percent were obtained percentage points lower pounds per second presented in figure pressure ratio radially distorted inlet rake recirculation of air reference line reference solid Reference stall reference stall-limit line rotor blades rotor stall-limit line rubber seal second fig shown in figure skewed slotted small cell stall point stall-limit point occurred stall-margin increase test rotor tip region total pressure trailing edges tuned to blade uniform inlet flow