A Comparative Analysis of Shaped Holes on the Suction Surface of High Pressure Turbine Guide Vanes
In this paper,the flow and heat transfer characteristics of four types of film holes on suction surface of high pressure turbine guide vanes were studied at four blowing ratios.Numerical simulation method was employed to obtain the adiabatic film cooling effectiveness η,heat transfer coefficient ratio hr/h0 and net heat flux reduction NHFR of four types of film holes for comparative analysis.Results showed that the laidback fan-shaped hole showed maximum film cooling effectiveness η and net heat flux reduction NHFR.This was because the laidback fan-shaped hole equipped with a lateral divergence angle(β)and a forward divergence angle(δ),which increased the exit cross section area of coolant and let the injected coolant closer to the surface,respectively.Whereas,the enhanced heat transfer eventually caused that advantages of laidback fan-shaped hole has maximum NHFR were less compared with its advantages in maximum film cooling effectiveness η.Moreover,compared with the cylindrical hole,the laidback hole had not obvious advantages.Therefore,the influence of the lateral divergence angle on the flow and heat transfer characteristics of film holes were greater than that of the forward divergence angle.
Film Cooling EffectivenessHeat Transfer CoefficientNet Heat Flux Reduction(NHFR)Shaped HolesSuction Sur-faceTurbine Guide Vanes
NETL
NSTL
万方数据
