Study on Enhanced Swirl-Film Composite High Efficiency Cooling of Turbine Blade Leading Edge
This paper establishes a composite cooling model for the leading edge of the first stage blade of GE-E3 high-pressure turbine,and numerically studies the flow and heat transfer character-istics of impingement-film composite cooling and swirl-film composite cooling using conjugate heat transfer method.The influence of actual mainstream and solid heat conduction on the blade leading edge composite cooling effect is considered.A new structure of enhanced swirl-film composite cooling with internal ridged wall is proposed.The flow field,heat transfer distribution,and pressure loss of three leading edge cooling models under different blowing ratios are analyzed in detail.The results indicate that within the range of parameters studied,compared to impingement,swirl cooling has a more uniform heat transfer distribution and lower pressure loss.The average Nusselt number of swirl cooling in a smooth inner wall can be increased by more than 17.6％,the overall average cooling efficiency of the leading edge can be increased by 4.7％～7.2％,and the pressure loss can be reduced by 4.7％～5.1％;The average Nusselt number of the swirl cooling in the internal ridged channel can be significantly increased by more than 37.7％,the overall average cooling efficiency can be improved by 6.1％～11.8％,and the pressure loss can be reduced by 3.9％～4.1％.
turbine blade leading edgeimpingement coolingswirl-film composite coolingcooling enhancementconjugate heat transfer
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