Film-Cooling Effectiveness Downstream of a Single Row of Holes With Numberical Modeling in ANSYS-Fluent

Abstract

Abstract With the increasing thrust of aero-engine, the temperature of turbine leading edge gradually exceeded the limit that materials can bear. Therefore, it is a common way to cool the turbine blades with a reasonable structure of film cooling. In this paper, the single exhaust film hole is taken as the main research object, and the effects of jet mass flow ratio, different temperature of mainstream and jet flow on the cooling effect are studied. The main research method is numerical modeling, and the modeling results are compared with the existing experimental results. The results show that the results have some error in jet’s flow situation and fluctuation in cooling efficiency, but there are still some errors in the calculation of heat transfer efficiency, which may be related to boundary layer separation phenomenon and the accuracy of the corresponding turbulence model.