Research On Improving Combined Cooling Structure Design Of Gas Turbine Blade

Many countries have paid wide attention to the gas turbine industry all the time, our country is relatively backward in gas turbine technologies, being blockaded by the Eurafrican countries in key technologies, and dependences on importing of foreign products for a long period. With the increasing of domestic demand for gas turbines, we must develop our own gas turbine industry. Hot components thermal protection is one of the core technologies of gas turbine, gas temperature before turbine has been improved constantly, and already exceeded the capacity of material, to ensure that the turbine normal work must use reasonable protection measures. The traditional turbine blade cooling technologies including the film cooling, impingement cooling and turbulent ribs and so on, combined cooling types which adopt two or more cooling structures are used in most modern gas turbine blade. The main job of this paper is study the conjugate heat transfer problems of an F class heavy-duty gas turbine stator in numerical simulation manner, and research the factors affecting the cooling effect of the combined cooling according to the calculated results, finally, alter blade cooling structure design to improve the cooling efficiency and reduce the loss.The prototype blade has complex cooling structure which includes film cooling, impingement cooling, turbulent ribs, trailingedge slot et al. Firstly, according to the calculated results of the prototype blade making some alterations to the trapezidal film holes, and then end wall cooling structures have been added to, after that the impacts of film holes section area change, the end wall cooling air channels and non-uniform inlet conditions to cooling effectiveness and current position are analyzed. The final cooling structure could meet the require of blade temperature distribution, which also have lower loss in energy.The research work have laid a good foundation for the projects of F class heavy-duty gas turbine stator, further research work should be done on the end wall cooling, film hole optimization and decrease the loss aspects.