A film hole arrangement guideline along the temperature difference is proposed.The performance of different film holes arrangement and the impact of parameters are investigated though cascade wind tunnel test and nume...A film hole arrangement guideline along the temperature difference is proposed.The performance of different film holes arrangement and the impact of parameters are investigated though cascade wind tunnel test and numerical simulations.Finally,the optimized flow field structure and the mechanism of its effects are explored.Under the same operating conditions,Hole pattern#2(arrangement along the 50 K temperature difference line)can reduce coolant consumption by half while achieves the same cooling effect as original film hole arrangement.Additionally,Hole pattern#2 reduces the temperature difference between the suction and pressure sides of the vane,effectively protecting the structural strength.At mass flow ratio is 6.23%,Hole pattern#2 achieves both good cooling effectiveness and relatively saves coolant consumption,offering the highest costeffectiveness.The modulation in the position of film holes results in different local pressures affecting the flow inside the cooling chamber.The coupling of internal and external flows leads to different vortex structures near the outlet of the film holes,thereby influencing the film effectiveness.Hole pattern#2 does not exhibit significant high-cooling regions,but it shows a more uniform distribution of overall cooling effectiveness.Therefore,optimizing the arrangement of film holes and spacing them along the temperature difference is considered a crucial technical means to enhance the efficiency of gas turbines.展开更多
基金co-supported by the Basic Research for National Science and Technology Major Project of China(No. J2019-I-0012)the National Natural Science Foundation of China (No. 12102478)the Natural Science Basic Research Program Youth Project of Shaanxi Province,China (No.2021JQ-356)
文摘A film hole arrangement guideline along the temperature difference is proposed.The performance of different film holes arrangement and the impact of parameters are investigated though cascade wind tunnel test and numerical simulations.Finally,the optimized flow field structure and the mechanism of its effects are explored.Under the same operating conditions,Hole pattern#2(arrangement along the 50 K temperature difference line)can reduce coolant consumption by half while achieves the same cooling effect as original film hole arrangement.Additionally,Hole pattern#2 reduces the temperature difference between the suction and pressure sides of the vane,effectively protecting the structural strength.At mass flow ratio is 6.23%,Hole pattern#2 achieves both good cooling effectiveness and relatively saves coolant consumption,offering the highest costeffectiveness.The modulation in the position of film holes results in different local pressures affecting the flow inside the cooling chamber.The coupling of internal and external flows leads to different vortex structures near the outlet of the film holes,thereby influencing the film effectiveness.Hole pattern#2 does not exhibit significant high-cooling regions,but it shows a more uniform distribution of overall cooling effectiveness.Therefore,optimizing the arrangement of film holes and spacing them along the temperature difference is considered a crucial technical means to enhance the efficiency of gas turbines.
