This paper reports the results of a combined experimental and numerical investigation carried out to support the design of a film cooling system for a rotor blade platform. A 7 blade cascade of a high-pressure-rotor stage of a heavy-duty gas turbine has been tested in a low speed wind tunnel. Tests have been carried out at a low Mach number (Mct_(2is)=0.27) with a relatively high inlet turbulence intensity level of about 7.6% at the leading edge plane. The same cascade model was also numerically tested by means of a 3D RANS approach. Cascade flow and heat transfer behavior was first experimentally assessed without coolant injection and used to validate the numerical approach. These data were also used to design the platform cooling scheme based on shaped holes that was then tested for variable injection rates. The thermal behavior was measured by using the Binary PSP technique, so to obtain film cooling effectiveness distributions over the passage. RANS 3D CFD simulations were also run on the same cooled model and testing conditions, allowing to critically assess the prediction capability of the selected numerical approach and of the design process.
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机译：本文报道了对支持转子叶片平台的薄膜冷却系统设计的组合实验和数值研究的结果。在低速风隧道中测试了重型燃气轮机的高压转子级的7叶片级联。在低马赫数（MCT_（2IS）= 0.27）处已经进行了测试，在前沿平面处具有相对高的入口湍流强度水平为约7.6％。通过3D RAN方法，也在数值上测试相同的级联模型。首先在实验评估级联流动和传热行为而无需冷却剂注入，并用于验证数值方法。这些数据还用于设计基于成形孔的平台冷却方案，然后测试可变注射率。通过使用二进制PSP技术测量热行为，从而获得通过该通道的薄膜冷却效果分布。 Rans 3D CFD模拟也在相同的冷却模型和测试条件下运行，允许批判性地评估所选数值方法和设计过程的预测能力。
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