Study on Cooling Mixing Loss of Gas Turbine Blade with High Load
The development and trend of the mixing loss model for film cooling of turbine blades in recent years are reviewed in this paper.The influence of the blowing ratio and the position of the holes on the mixing loss of high-load gas turbine blades is studied by numerical simulation.At the same time,the variation law of aerodynamic loss is analyzed.The results show that the mixing loss caused by film cooling increases rapidly with the blowing ratio,especially in the leading edge region,and can not be neglected at high blowing ratio.The mixing loss of suction surface is higher than that of pressure surface,and the loss caused by film cooling near the leading edge is larger.These provide data support for the integration of the following factors and the further study of the loss model.
turbine bladesmixing lossnumerical simulationblowing ratiohole row position
NETL
NSTL
万方数据
