Investigation On The Characteristics Of The Flow And Heat Transfer Of Turbine Guide Blade Film Cooling

With the continuous development of aero-engines,the temperature of the turbine leading edge continues to increase,and studies have shown that the temperature of the turbine front of advanced aero-engines has reached 2200 K.The film cooling technology,as the most widely used cooling method,can provide excellent protection for the turbine guide blades.Nowadays,the research on the film cooling effect of ordinary circular film holes has been relatively mature,but it is still difficult to meet the increasing demand for the temperature of the aero engine turbine.In order to solve this problem,many researchers have proposed a new film cooling hole structure-the trench hole.In response to this problem,this article uses the mature commercial software of ANSYS to build 3D models of 4 different blade leading edge structure.In this paper,the effects of Reynolds number of the secondary flow,the position of the film holes,and the shape of film hole on the discharge coefficient are explored.This paper also explores the effects of the blowing ratio,the position of the film holes,the gas inlet pressure,and the degree of turbulence on the heat transfer of the turbine guide vanes.The research in this article shows:The film cooling efficiency of the trench hole is higher than that of the traditional cylindrical hole,especially when the blowing ratio is relatively low;The closer the position of the film hole is to the stagnation point of the leading edge of the turbine guide blade,the worse the effect of attaching the gas film,but the greater the thickness of the formed gas film;When the hole is located on the suction surface,as the blowing ratio continues to increase,the effect of film cooling is first weakened and then enhanced.The coverage area decreases first and then increases;when the hole is located on the pressure surface,as the blowing ratio continues to increase,the effect of film cooling continues to increase.The coverage area increases first,then decreases,and then increases.With the increase of the gas inlet pressure,the effect of gas film cooling is enhanced,but it will inevitably bring about the problem of supersonic speed near the turbine guide blade wall surface;The effect of turbulence on the film cooling of trench hole is not significant.