气膜孔流量系数随动量比的增大而增加，在小动量比下，影响尤为明显；
The film hole flow coefficient is increased with momentum ratio, especially when momentum ratio is small.
着重介绍了气膜冷却、涡轮叶片内流冷却技术和气膜孔流量系数的研究进展。
Particular emphasis is given to the development of film cooling, internal cooling technologies and film hole discharge coefficients.
应用微扰方法和有限元法，对端面气膜密封三自由度微扰下，密封气膜的刚度和阻尼系数进行了数值求解。
The small perturbation method and the finite element method were used to calculate the stiffness and damping coefficients of a gas film with three degrees of freedom for a gas film face seal.
采用非结构三角形网格的有限元法求解压强摄动方程，并计算气膜刚度系数和阻尼系数。
The solution of perturbation pressure is used to calculate air bearing's stiffness and damping coefficients.
基于雷诺方程，得到两平行板内部气膜阻尼的解析公式，分析了气膜阻尼系数随接触距离的变化情况。
Based on Reynolds equation, the analytical formula of gas-film damping inside two parallel plates has been obtained, which analyses gas-film damping coefficient changes with contact distance.
实验中发现气膜孔雷诺数和肋角对流量系数有较大的影响。
It is found in the experiments that film hole Reynolds number and Rib Angle have great influence on film hole discharge coefficients.
通过对几种不同的气膜冷却对流换热系数的计算方法的归纳总结，提出用相对气膜冷却换热系数的方法来计算气膜冷却时的对流换热。
By analyzing the methods of calculating different heat transfer coefficients, the film cooling relative heat transfer coefficients was used to calculate the heat transfer.
本文用数值方法计算了无气膜冷却涡轮叶片上包括前驻点的整个型面上的换热系数。
Several problems involved in the prediction of heat transfer coefficient on the turbine blade profiles without film cooling are studied in this paper for the purpose of improving the accuracy.
在压力面密度比对气膜孔流量系数影响较小。
The effect of density ratio on suction surface and leading edge is more evident.
在压力面密度比对气膜孔流量系数影响较小。
The effect of density ratio on suction surface and leading edge is more evident.
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