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采用耦合传热数值计算方法,研究了典型航空发动机阶状蜂窝密封内的传热特性,并利用实验数据对数值方法的正确性进行了考核。计算得到的转子面和静子面上换热系数分布与实验值吻合良好。通过对比5种不同的两方程涡黏湍流模型,结果表明:k-ω湍流模型和SST湍流模型在高温度梯度区域对换热系数分布的求解具有较高的精度,明显优于标准k-ε和k-εRNG湍流模型。与光滑面迷宫密封相比,蜂窝芯格结构对转子面上平均换热系数影响较小,但大幅减小了密封静子面上的换热能力;蜂窝芯格结构使得齿尖温度梯度略微增大,但明显使得静子固体区域的温度梯度减小。
The numerical simulation of coupled heat transfer was used to study the heat transfer characteristics of a typical aero-engine stepped honeycomb seal. The experimental data was used to evaluate the correctness of the numerical method. The calculated heat transfer coefficient distribution on rotor surface and stator surface is in good agreement with the experimental data. The results show that the k-ω turbulence model and the SST turbulence model have higher accuracy in solving the heat transfer coefficient distribution in the high temperature gradient region, which is obviously better than the standard k-ε And k-εRNG turbulence model. Compared with the smooth surface labyrinth seal, the honeycomb core structure has less influence on the average heat transfer coefficient on the rotor surface, but greatly reduces the heat exchange capacity on the sealed stator surface. The honeycomb core structure makes the temperature gradient of the tip slightly increase , But significantly reduces the temperature gradient of the static solid region.