Investigation On Film Cooling Performances In Turbine Blade Leading Edge

With the rapid development of aviation gas turbine engines and the continuous improvement ofthermal efficiency and thrust-to-weight ratio, the desired turbine inlet gas temperature is also rising.The leading edge of the turbine blade is the most severe thermal load region which is directly exposedto high-temperature gas to flow impact and affected by a variety of factors. Its heat transfer and floware extremely complex, and this has been the focus of researchers and difficulty of study. This articlecarries the film cooling research by numerical analysis respectively on the turbine stator blades androtor blade leading edge with impact&film cooling structure.It is studied that the different parameters influence of impact hole and film hole on the filmcooling on the leading edge of the stationary blade. The results show that the number of rows of filmcooling holes has greater impact on the leading edge of the film cooling efficiency, five-row filmholes better than three-row film hole. Film cooling effect increases with variation of the film coolingholes spacing.The changement of impact hole location has greater impact on some of the local areatemperature of the leading edge, but the impact hole spacing has little influence on the film coolingeffect. Film cooling effectiveness increases with the blowing ratio increases but the tendency toincrease with blowing ratio further increases slows. Under the specific boundary conditions,preliminary optimization has been carried out on Leading edge of the structure of film cooling holesdiameter of0.4mm，draw a better cooling of the leading edge surface of the leading edge structure.The film cooling characteristic of leading edge of the rotor blade is very different to that of thestationary blade. In rotation state, the Coriolis force, buoyancy in the cascade channel cause a greatimpact on the film cooling efficency. The results show that: the best leading edge structure in astationary state is not necessarily best in the rotational state. The film cooling efficency of the leadingedge surface and the pressure surface and the suction surface will be worse when rotate speed isfaster.Speed increase lead to outflow Film offset, it is very obvious in the pressure surface and thesuction surface but the leading edge surface. With blowing ratio increased, the film cooling efficencyof the leading edge surface, the pressure surface and the suction surface will be better, also the gasfilm offset of the pressure surface will be weakened.