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首页> 美国政府科技报告 >Evaluation of Range and Distortion Tolerance for High Mach Number Transonic Fan Stages. Task 2 Performance of a 1500-Foot-Per-Second Tip Speed Transonic Fan Stage with Variable Geometry Inlet Guide Vanes and Stator
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Evaluation of Range and Distortion Tolerance for High Mach Number Transonic Fan Stages. Task 2 Performance of a 1500-Foot-Per-Second Tip Speed Transonic Fan Stage with Variable Geometry Inlet Guide Vanes and Stator

机译：高马赫数跨音速风扇级的范围和畸变容差评估。任务2具有可变几何入口导叶和定子的1500英尺/秒尖端速度跨音速风扇平台的性能

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A 0.5 hub/tip radius ratio compressor stage consisting of a 1500 ft/sec tip speed rotor, a variable camber inlet guide vane and a variable stagger stator was designed and tested with undistorted inlet flow, flow with tip radial distortion, and flow with 90 degrees, one-per-rev, circumferential distortion. At the design speed and design IGV and stator setting the design stage pressure ratio was achieved at a weight within 1% of the design flow. Analytical results on rotor tip shock structure, deviation angle and part-span shroud losses at different operating conditions are presented. The variable geometry blading enabled efficient operation with adequate stall margin at the design condition and at 70% speed. Closing the inlet guide vanes to 40 degrees changed the speed-versus-weight flow relationship along the stall line and thus provided the flexibility of operation at off-design conditions. Inlet flow distortion caused considerable losses in peak efficiency, efficiency on a constant throttle line through design pressure ratio at design speed, stall pressure ratio, and stall margin at the 0 degrees IGV setting and high rotative speeds. The use of the 40 degrees inlet guide vane setting enabled partial recovery of the stall margin over the standard constant throttle line. (Author)

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