燃气温度和转速对发动机叶片冷却效果的影响

Influence of gas temperature and speed on engine blade cooling effect

叶片冷却效果试验是航空发动机热端部件研制的重要试验,为分析发动机实际运行与实验室工况下叶片冷却效果的差异,利用数值模拟方法,研究了某发动机燃气温度和转速变化对叶片冷却效果的影响。实验结果表明,相同燃气进口平均温度条件下,燃气温度沿径向按一定规律变化比径向均匀分布时叶片平均冷却效果低8%,局部测点最大低16%;燃气进口径向均温时,模化状态下随着燃气进口温度的降低叶片冷却效果逐渐升高,但影响可忽略;转速对叶片平均冷却效果的影响最大偏差为3.7%,在局部测点静止状态比实际工作转速下叶片冷却效果高11%。

The blade cooling effect experiment is an important test for the development of turbine components in the aircraft engine.In order to analyze the difference of the blade cooling effect between laboratory conditions and actual engine operating conditions,the effects of turbine gas temperature and rotate speed variation on blade cooling are studied by numerical simulation.The results show that at the same average gas inlet temperature,the average cooling efficiency is 8% lower in the radial variational temperature by a certain law than that of the radial uniform temperature,and the local point is 16% lower.In the radial uniform gas inlet temperature,the blade cooling efficiency is increased with the decrease of gas inlet temperature on the basis of similar principle,but the influence can be ignored.The rotate speed variation has 3.7% influence on the blade cooling efficiency of the blade,while the local cooling efficiency is 11% higher in the actual engine operating condition than that of the static state.