Parametric Design And Numerical Research Of Gas Turbine Cooling Structure

With the advent of gas turbine, it has been widely used in aviation, navigation and power industry. In order to get the higher thrust-weight ratio and efficiency, the turbine inlet temperature is rising. Currently, the temperature has been far more than that the blade material can bear. in order to ensure the turbine blades can work safely and improve their life span, complicated cooling technology must be used. The complex cooling method makes the blade structure complicated, the establishment and modification of the model take a long time, so how to design the cooling structure that meet the requirements quickly is important. Based on the typical air-cooled blade, a parametric design method has been raised. This paper also designed the cooling structure of the turbine blade, analyzed the flow and heat transfer of this blade.In parametric design, the blade structure has been divided into four features, include coolant tunnel, ribs, film cooling holes and impingement holes. The parametric design program of different cooling structures has been written with Matlab and UG OPEN API. With this parametric design system, it is easy to generate a new model through control the parameters, this will improve the design efficiency greatly.The cooling structure of a gas turbine stator is designed in this paper. Firstly, the film cooling structure is designed. The position of all film holes is achieved by the temperature distribution without cooling structure. this paper compare the cooling effect of the suction surface with different types of holes, the laid back diffuse holes have the best cooling effect. In this paper, the author designs circular holes in leading edge and pressure surface, laid back diffuse holes in suction surface, a gap in the tail. The numerical simulation is applied for this stator, and analyze the cooling effect of different holes. The research shows that the temperature of the bade meet the design requirement basically with film cooling structure. Secondly, the author add impingement cooling and convection cooling structure in the blade. The impingement structure can enhance the heat transfer coefficient, and temperature of the blade. But, film cooling play a decisive role in the combined cooling.