SiC_f/SiC复合材料涡轮导叶气膜冷却效果

Film cooling effect on turbine guide vane of SiC_f/SiC composite material

摘要

通过对 SiC_f/SiC 陶瓷基复合材料涡轮导向叶片开展数值模拟研究，探究温比和流量比对叶片整体温度及冷却效果的影响。选取变温比和变流量比 16 个工况进行仿真计算，结果表明，当流量比和温比均增加时，叶片的最高温度、最低温度和平均温度均降低，且下缘板前缘位置出现高温；叶背的冷却效果从前缘到尾缘均逐渐增大，叶盆的冷却效果从前缘到尾缘均先减小后增大。针对单点冷效，当流量比分别为5.28%、7.54% 和8.44% 时，平均冷效随温比增大先减小后增大；当流量比为 3.69% 时，平均冷效随温比增大而逐渐减小。同时，中截面平均冷效随流量比增大而增大。

Abstract

A numerical simulation study is conducted on SiC_f/SiC ceramic matrix composite turbine guide vanes to investigate the effects of variations in temperature ratio and flow ratio on the overall temperature and cooling performance of the vanes. A total of 16 operating conditions with variable temperature ratios and flow ratios are selected for simulation calculations. The results show that with the increase of both flow ratio and temperature ratio， the maximum temperature， minimum temperature and average temperature of the vanes all decrease，and high temperature occurs at the leading edge of the lower platform. The cooling efficiency of the vane suction surface increases gradually from the leading edge to the trailing edge，while that of the vane pressure surface first decreases and then increases from the leading edge to the trailing edge. For the local cooling efficiency，when the flow ratios are 5.28%， 7.54%， and 8.44%， respectively， the average cooling efficiency first decreases and then increases with the rise of temperature ratio. When the flow ratio is 3.69%， the average cooling efficiency decreases gradually as the temperature ratio increases. Meanwhile，the average cooling efficiency of the mid-section increases with the rise of flow ratio.

关键词

SiC_f/SiC / 复合材料 / 涡轮导向叶片 / 冷却效果 / 温比 / 流量比

Key words

SiC_f/SiC / composite material / turbine guide vane / cooling effect / temperature ratio / flow ratio

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基金资助

航空发动机及燃气轮机基础科学中心项目(P2022-B-Ⅱ-025-001)