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Three-Dimensional Flow Field Measurements in a Transonic Turbine Cascade

机译:跨音速涡轮叶栅的三维流场测量

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摘要

Three-dimensional flow field measurements are presented for a large scale transonic turbine blade cascade. Flow field total pressures and pitch and yaw flow angles were measured at an inlet Reynolds number of 1.0 x 10(exp 6) and at an isentropic exit Mach number of 1.3 in a low turbulence environment. Flow field data was obtained on five pitchwise/spanwise measurement planes, two upstream and three downstream of the cascade, each covering three blade pitches. Three-hole boundary layer probes and five-hole pitch/yaw probes were used to obtain data at over 1200 locations in each of the measurement planes. Blade and endwall static pressures were also measured at an inlet Reynolds number of 0.5 x 10(exp 6) and at an isentropic exit Mach number of 1.0. Tests were conducted in a linear cascade at the NASA Lewis Transonic Turbine Blade Cascade Facility. The test article was a turbine rotor with 136 deg of turning and an axial chord of 12.7 cm. The flow field in the cascade is highly three-dimensional as a result of thick boundary layers at the test section inlet and because of the high degree of flow turning. The large scale allowed for very detailed measurements of both flow field and surface phenomena. The intent of the work is to provide benchmark quality data for CFD code and model verification.
机译:提出了用于大型跨音速涡轮叶片叶栅的三维流场测量。在低湍流环境下,在入口雷诺数为1.0 x 10(exp 6)且等熵出口马赫数为1.3的情况下,测量了流场的总压力,俯仰角和偏航角。流场数据是在级联的两个上游和三个下游的五个螺距/跨度测量平面上获得的,每个覆盖三个叶片螺距。三孔边界层探针和五孔螺距/偏航探针用于在每个测量平面中的1200多个位置获取数据。在入口雷诺数为0.5 x 10(exp 6)和等熵出口马赫数为1.0的情况下,还测量了叶片和端壁的静压。测试是在NASA Lewis Transonic涡轮叶片级联装置上以线性级联进行的。测试物品是具有136度转弯和12.7 cm的轴向弦的涡轮转子。级联中的流场是高度三维的,这归因于测试段入口处的边界层较厚以及流向的高度转向。大规模可对流场和表面现象进行非常详细的测量。该工作的目的是为CFD代码和模型验证提供基准质量数据。

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