Film Cooling Performance on Turbine Blade Suction Side With Various Film Cooling Hole Arrangements

Zhiyu Zhou, Haiwang Li, G. Xie, Ruquan You
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Abstract

Numerical simulations were carried out to study the film cooling effectiveness distributions of different hole arrangements on the suction side of a high pressure turbine blade under rotating condition. The chord length and the height of the blade are 60mm and 80mm, respectively. Totally 12 models with different hole arrangements and different injection angles were studied. Each blade model has three rows of round holes with diameter of 0.9mm on the suction surface. The first row and the third row are fixed at streamwise location of 12.4% and 34% respectively. Three injection angles, 30°, 45°, and 60°, were investigated. Simulations were conducted under three rotational speeds, 600rpm, 800rpm, 1000rpm, with blowing ratio varying from 0.5 to 2.0. The Mainstream Reynolds numbers corresponding to the rotational speeds are 40560, 54080, and 67600 respectively. The temperature of the mainstream and the coolant is set at 463K and 303K so as to control the density ratio at 1.47. Simulations were performed by using SST turbulence model and were solved by using the three-dimensional Reynolds-averaged Navier–Stokes equations. Results showed that on the rotating turbine blade suction surface, film trajectories are drawn toward the midspan. The film trajectory arrangement may be different from the hole arrangement. Inline film trajectory arrangement can achieve higher film cooling effectiveness with slightly larger injection angle. Staggered film trajectory arrangement is better for uniform film cooling effectiveness distribution in spanwise and can achieve higher film cooling effectiveness with smaller injection angle. A smaller distance between the first row and the second row can achieve better film cooling performance at the downstream. With the increase of rotational speed, the mainstream Reynolds number increases, which improves the film cooling performance with smaller blowing ratio.
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不同气膜冷却孔布置对涡轮叶片吸力侧气膜冷却性能的影响
通过数值模拟研究了高压涡轮叶片在旋转工况下吸力侧不同孔布置的气膜冷却效率分布。弦长为60mm,叶片高度为80mm。共研究了12种不同孔位和不同注入角度的模型。每个叶片型号在吸力面上有三排直径为0.9mm的圆孔。第一行和第三行固定在流向位置,分别为12.4%和34%。研究了30°、45°和60°三种注入角度。在600rpm、800rpm、1000rpm三种转速下,吹气比在0.5 ~ 2.0范围内进行了模拟。转速对应的主流雷诺数分别为40560、54080、67600。将主流和冷却液的温度分别设定为463K和303K,从而控制密度比为1.47。采用海温湍流模型进行模拟,采用三维reynolds -average Navier-Stokes方程进行求解。结果表明:在旋转涡轮叶片吸力面上,膜的运动轨迹向跨中方向运动;膜的轨迹排列可能与孔的排列不同。内嵌式气膜轨迹布置可以在较大的喷射角下获得较高的气膜冷却效果。交错排列的气膜轨迹有利于气膜冷却效率在展向上的均匀分布,可以在较小的喷射角下获得较高的气膜冷却效率。第一排与第二排之间的距离越小,下游的气膜冷却性能越好。随着转速的增加,主流雷诺数增大,吹气比越小,气膜冷却性能越好。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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