当前位置: X-MOL 学术Heat Mass Transfer › 论文详情
Our official English website, www.x-mol.net, welcomes your feedback! (Note: you will need to create a separate account there.)
Numerical investigation of nozzle geometry influence on the vortex cooling in an actual gas turbine blade leading edge cooling system
Heat and Mass Transfer ( IF 1.7 ) Pub Date : 2021-09-16 , DOI: 10.1007/s00231-021-03131-9
Xiaojun Fan 1 , Yuan Xue 2
Affiliation  

To investigate the nozzle geometry influence on vortex cooling performance in the actual leading edge region, an improved vortex cooling configuration with a coolant chamber is established based on the middle cross section of stage 1 vane blade of GE-E3 high pressure gas turbine. Numerical simulations are conducted to research the effects of nozzle position, nozzle number and nozzle aspect ratio on the flow and heat transfer behavior. Results show that with the introduction of the coolant chamber, the mass flow of nozzles increases gradually from the upstream to the downstream instead of a uniform mass flow distribution. Configurations with nozzles placed at the sides (the vortex cooling) have better cooling performance than with nozzles placed in the middle (the impingement cooling). What’s more, the configuration with nozzles placed along the pressure side has the best comprehensive cooling performance. Due to the irregular blade line, a flow entrainment that is not found in simplified circular configurations is observed on the pressure side weakening the local heat transfer performance. The cooling performance is most sensitive to the nozzle number. As the nozzle number increases, the friction coefficient and heat transfer intensity both decrease. Moreover, as the nozzle aspect ratio increases, the friction coefficient and heat transfer intensity both increases first and then decrease. Results indicate a certain vortex cooling configuration may have the optimal nozzle number and nozzle aspect ratio. For this paper’s configuration, the best nozzle number is 5 and the best nozzle aspect ratio is 4.



中文翻译:

实际燃气轮机叶片前缘冷却系统中喷嘴几何形状对涡流冷却影响的数值研究

为了研究喷嘴几何形状对实际前缘区域涡流冷却性能的影响,基于 GE-E 3级 1 级叶片的中间截面,建立了带有冷却剂室的改进涡流冷却配置高压燃气轮机。通过数值模拟研究喷嘴位置、喷嘴数量和喷嘴纵横比对流动和传热行为的影响。结果表明,随着冷却剂室的引入,喷嘴的质量流量从上游到下游逐渐增加,而不是均匀的质量流量分布。喷嘴位于侧面的配置(涡流冷却)比喷嘴位于中间的配置(冲击冷却)具有更好的冷却性能。更重要的是,喷嘴沿压力侧放置的配置具有最佳的综合冷却性能。由于不规则的叶片线,在压力侧观察到在简化的圆形配置中没有发现的流动夹带削弱了局部传热性能。冷却性能对喷嘴数量最敏感。随着喷嘴数量的增加,摩擦系数和传热强度均降低。此外,随着喷嘴纵横比的增大,摩擦系数和传热强度均先增大后减小。结果表明,某种涡流冷却配置可能具有最佳的喷嘴数量和喷嘴纵横比。对于本文的配置,最佳喷嘴数量为 5,最佳喷嘴纵横比为 4。结果表明,某种涡流冷却配置可能具有最佳的喷嘴数量和喷嘴纵横比。对于本文的配置,最佳喷嘴数量为 5,最佳喷嘴纵横比为 4。结果表明,某种涡流冷却配置可能具有最佳的喷嘴数量和喷嘴纵横比。对于本文的配置,最佳喷嘴数量为 5,最佳喷嘴纵横比为 4。

更新日期:2021-09-16
down
wechat
bug