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首页> 美国政府科技报告 >Investigation of a Mach 1.4 Compressor Cascade with Variable Back Pressure Using Flow Visualization
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Investigation of a Mach 1.4 Compressor Cascade with Variable Back Pressure Using Flow Visualization

机译：用流动可视化研究具有可变背压的mach 1.4压缩机叶栅

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Flow through a transonic compressor cascade model was investigated at M = 1.4 using flow visualization and pressure measurements. Shock patterns for two different blade incidences were documented at increasing back pressures. Data were taken up to a maximum pressure ratio of 1.53 at estimated minimum loss incidence conditions. An oblique shock system persisted, producing large flow turning (6.8 deg) and a slightly supersonic exit mach number (1.02). Losses and blade pressure loading were calculated using a combination of test data and computational approximations. Failure of blade retaining tabs occurred with both aluminum and steel cascade blades. Failures were attributed to fatigue from high oscillatory stress levels and redesigned blade mounts were proposed. (Author)

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