Turbine blade endwall heat transfer measurements are given for a range of Reynolds and Mach numbers. Data were obtained for Reynolds numbers based on inlet conditions of 0.5 and 1.0 x 106, for isentropic exit Mach numbers of 1.0 and 1.3, and for freestream turbulence intensities of 0.25% and 7.0%. 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' of turning and an axial chord of 12.7 cm. 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 computational fluid dynamics (CFD) code and model verification. The flow field in the cascade is highly three-dimensional as a result of thick boundary layers at the test section inlet. Endwall heat transfer data were obtained using a steady-state liquid crystal technique.
展开▼
机译：给出了一系列雷诺数和马赫数的涡轮叶片端壁传热测量结果。基于入口条件为0.5和1.0 x 106的雷诺数，等熵出口马赫数为1.0和1.3的自由流湍流强度为0.25％和7.0％的数据获得。测试是在NASA Lewis Transonic涡轮叶片级联装置上以线性级联进行的。测试的物品是具有136'旋转和12.7 cm的轴向弦的涡轮转子。大规模可对流场和表面现象进行非常详细的测量。该工作的目的是为计算流体动力学（CFD）代码和模型验证提供基准质量数据。级联中的流场是高度三维的，这是由于测试部分入口处的边界层较厚。端壁传热数据是使用稳态液晶技术获得的。
展开▼
