气膜冷却孔形状对涡轮叶片传热的影响-第二部分:质量流量和非定常的影响

Spencer J. Sperling, Louis E. Christensen, Randall M. Mathison, H. Aksoy, Jong-Shang Liu, Jeremy B. Nickol
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摘要

为了提供涡轮环境中气膜冷却的详细分析,本研究结合了在旋转高压涡轮级上进行的实验和计算研究。涡轮叶片包括在提供给转子的几种不同的冷却质量流量下研究的三种不同的膜冷却孔形状。膜冷却孔的形状包括圆形、扇形和先进的抗涡形状,安装在旋转叶片上的这些冷却系统的性能在时间平均和非定常基础上进行了评估。气膜冷却孔的形状和冷却剂的质量流量在叶片的不同区域提供不同的冷却效果。在压力面、前缘和吸力面,先进的气膜冷却孔对冷却剂质量流量变化的响应最大,通常在最高的气膜冷却流量下具有最高的气膜效率。无论孔的形状如何,膜冷却射流都经历类似的运动。压力面上膜状冷却孔出口的非定常压力梯度引起冷却射流运动。风扇和先进的形孔使冷却气体在稳定的基础上侧向扩散,由于侧向扩散的增加,压力面上更大的区域得到一致的膜覆盖。在时间平均的基础上,这导致更大的横向扩散和增加膜覆盖的形状膜冷却孔。该研究结果有助于确定涡轮环境下形膜冷却孔的性能。不同孔形对非定常的响应对时间平均气膜冷却覆盖率有显著影响。此外,孔的形状对冷却剂质量流量的增加有不同的反应,并在叶片的不同部位提供不同程度的膜冷却覆盖。增加对各种膜冷却几何形状的非定常性能的理解和欣赏是持续技术发展的基础。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Film Cooling Hole Shape Effects on Turbine Blade Heat Transfer – Part II: Effects of Mass Flow Rate and Unsteadiness
To provide a detailed analysis of film cooling in a turbine environment, this study incorporates experimental and computational research performed on a rotating high pressure turbine stage. The turbine blades include rows of three different film cooling hole shapes investigated at several different cooling mass flow rates supplied to the rotor. Film cooling hole shapes include round, fan, and advanced anti-vortex shapes, and the performance of these cooling systems installed on the rotating blades are evaluated on time-averaged and unsteady bases. Film cooling hole shape and coolant mass flow provide different cooling benefits in different areas of the blade. Across the pressure surface, leading edge, and suction surface, advanced film cooling holes show the most response to changing coolant mass flow, and typically have the highest film effectiveness at the highest film cooling flow rate. Film cooling jets experience similar motions regardless of hole shape. Unsteady pressure gradients across the film cooling hole outlets on the pressure surface cause cooling jet motion. Fan and Advanced shaped holes cause lateral spread of cooling gas on a steady basis, and due to the increased lateral spread, a larger region on the pressure surface receives consistent film coverage. On a time-average basis, this results in much more lateral spread and increased film coverage for shaped film cooling holes. The results of this study help identify the performance of shaped film cooling holes in turbine environments. The response of different hole shapes to unsteadiness has a significant impact on the time average film cooling coverage. Additionally, the hole shapes respond differently to increased levels of coolant mass flow rate and provide different degrees of film cooling coverage on different parts of the blade. An increased understanding and appreciation of the unsteady performance of various film cooling geometries is a foundational piece of continued technology development.
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