Numerical Study Of The Augmented Cooling On The Trailing Edge Of Turbine Blade

With the rapid development of the aviation, the higher request of the turbine capability has been brought forward, however the available approach to improve the turbine capability is to heighten the gas-fired temperature of turbine inlet. Because of the increasing of the turbine inlet's gas-fired temperature and it already exceed the tolerance of the turbine blade material, it is the emphasis of every country to research to adopt advanced cooling technology which will reduce the temperature of the turbine blade. It is the aim which the aviation turbine blade designer and fabricant to continuously pursue at present that how to design high temperature turbine blade cooling structure to improve the cooling effect.The trailing edge of turbine blade cooling research is a very important part , so the mostly task of this paper is to progress numerical simulation of the trailing edge of turbine blade cooling technology.This paper progresses numerical simulation to the projects that the trailing edge of turbine blade with augmented cooling, and it designs the trailing edge cooling passage, adding circular, square and rhombic pin fins and circular half pin fins, and it also designs the different projects of cooling air inlet manners and cooling air flux change, and then it applies the CFX program to process aero-thermal conjugating numerical simulation toward every project. The paper deals with the account result of the projects, and it carries out the particular description and analyse of the temperature field, flow field , pressure and heat transfer coefficient.Through contrastively analysising, the paper gains the influence of the trailing edge of turbine blade cooling effect of the different cooling projects. With contrastively computing pin fins or no, different cooling air inlet manners, cooling air flux change and so on, the paper elaborately analyses temperature distribution characteristic and the flow field structure of the flow passage and turbine blade. The paper studies emphatically the influence of cooling effect from pin fins of different shapes and half pin fins cooling projects, it contrastively analyzes the flow field structure, cooling efficiency, pressure losing coefficient and heat transfer coefficient of circular, square and rhombic pin fins; it contrastively analyzes cooling efficiency, pressure losing coefficient and heat transfer coefficient of the two circular half pin fins and circular pin-fins.