Investigations on Film Cooling and Slot Purge Flow Cooling of the Gas Turbine Vane Endwall
The cooling performance of a gas turbine vane endwall near the leading edge was numerically investigated in this paper.The availability of the utilized three-dimensional Reynolds-Averaged Navier-Stokes(RANS)with standard k-ω turbulence model for analyzing the cooling performance of endwall surface was demonstrated by comparison of numerical results with four kinds of turbulent model and experimental data.The numerical result with k-ω turbulence model is well agreement with the experimental result.The effect of blowing ratio,film jet angle,slot mass flow rate and the upstream slot jet angle on the cooling effectiveness of the vane endwall surface were numerically studied.The numerical results show that the gas turbine vane endwall near the leading edge obtains the best film cooling performance with blowing ratio M=1.5 when slot jet angle θ1=45° and film cooling jet angle θ2=30°.The film jet angle θ2 also has great influence on the cooling characteristics of gas turbine vane endwall near the leading edge.The smaller θ2 shows the better cooling performance.When the slot cooling mass flow rate equals 1.0%of mainstream with θ1=45°,it obtains the optimal cooling effectiveness on the vane endwall near the leading edge.The upstream slot angle significantly influences cooling characteristics of gas turbine vane endwall near the leading edge.The numerical simulations illustrate that the smaller upstream slot jet flow angle θ1 obtains the better cooling performance with film cooling jet angle θ2=30°.
Gas Turbine Vane Endwall Slot Purge Flow Cooling Film Cooling Numerical Simulation
Kun DU Jun LI
Institute of Turbomachinery,Xian Jiaotong University,Xian Shaanxi Province,710049,China Institute of Turbomachinery,Xian Jiaotong University,Xian Shaanxi Province,710049,China;Collaborat
国际会议
The 5th International Symposium on Jet Propulsion and Power Engineering(第五届喷气推进与动力工程国际会议)
北京
英文
1-7
2014-09-15（万方平台首次上网日期，不代表论文的发表时间）