Numerical Simulation Of Air Cooling Turbine With Conjugate Heat Tansfer

With the rapid development of modern aero engine, it is more and more obvious that the old design method cannot adapt new desire. It is also request higher performance of gas turbine. The inlet temperature of gas turbine has reached a high lever and exceeded the material melting point.Therefor,it has been a key point to all the countries that cool down the hot part of the gas turbine. This paper's primary work is use commercial software CFX to research MARKII and C3X blades which original from NASA Lewis research center, it is also develop the aero-thermal conjugated ability of CFX software at the same time.The MARKII and C3X blades which this paper studied are very prevail conjugated heat transfer model of many counties. The experiment results is base on Hylton's work. The MARKII and C3X blades have ten radially oriented cooling holes and adopt convection cooling method. Because Hylton only supply mid span data of the blade, the numerical simulation made a detailed comparation and analysis of pressure distribution, temperature distribution on blade; it is also describe the temperature and pressure field structure of passage at the same time.This paper gives a detailed discussion of pressure distribution and temperature distribution on turbine blade at different numerical conditions. In the numerical simulation, the author adopt three gird project, 480 thousand,650 thousand and 800 thousand, compare the influence to the pressure and temperature distribution under different turbulent models, inlet turbulence, material heat transfer coefficient, it is also consider the influence of temperature distribution of air properties.Cooling conjugated and uncooled conjugated projects show the variety of temperature field with cooling air or not. It is illustrated that there is tiny difference between the two projects of pressure distribution. Although the flux of cooling air is little, the cooling effect is obvious.