前缘气膜孔对涡轮静叶冷却效果影响的数值模拟

Numerical Simulation of the Impact of Leading-edge Gas-film Pores on Cooling Effectiveness in Turbine Stator Blades

采用全三维数值模拟技术,利用k-ε双方程湍流模型和SIMPLE算法,通过求解三维粘性可压缩Favre平均Navier-Stokes方程,对某新型燃气轮机第一级气膜冷却静叶叶栅的三维湍流流场进行了数值模拟。分别通过改变燃气轮机前缘气膜孔的参数,计算出叶片外表面的温度分布和冷却空气流量大小。结果表明,前缘气膜孔的直径、数目以及射流方向对叶片表面冷却效果的影响是非常显著的。从而提出了一种叶片前缘气膜冷却设计的新方案,为工程设计提供了有价值的参考。

Through the adoption of a full three-dimensional numerical simulation technology and by use of a k-ε dual equation turbulent model and algorithm SIMPLE,a numerical simulation was conducted of the three-dimensional turbulent flow field of the film cooled stator-blade cascade at the first stage of a new type of gas turbine.The simulation was accomplished by solving a three-dimensional viscous compressible Favre-averaged Navier-Stokes equation.Through a change in parameters of the leading-edge film pores of the gas turbine,the temperature distribution on the outer surface of stator blades and its cooling-air flow rate have been calculated respectively.The results show that the diameter,quantity and jet flow direction of leading-edge film pores can very conspicuously impact on the blade surface cooling effectiveness.In view of the above,a new version is proposed for the blade leading-edge film cooling design,providing a valuable guide for relevant engineering designs.