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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。

By adopting the conjugate heat transfer computational method, a typical stepped labyrinth seal with honeycomb land used in the gas turbine engine was selected to investigate the heat transfer performance near the rotor and stator. The reliability and accuracy of the present numerical method was carefully validated with the obtained experimental data. It shows that the computed heat transfer coefficient distributions near the rotor and stator surfaces were in well agreement with the measurements. Based on the numerical computations with five different two-equation eddy viscosity turbulence models, it shows that the k - ~ turbulence model and SST turbulence model have the superior accuracy than that of k - c and k - ~ RNG turbulence models in resolving the heat transfer coefficient distributions in the high temperature gradient region. In contrast to the stepped labyrinth seal with smooth land, the honeycomb configuration has little influence on the averaged heat transfer coefficient of the rotor surface. However, the honeycomb land significantly reduces the heat transfer on the seal stator. Moreover, the honeycomb cell slightly increases the temperature gradient in the stepped labyrinth fins while it significantly decreases the temperature gradient in the solid of the seal stator.