某型涡轮过渡流道稳定工作范围优化设计

推进技术 ›› 2013, Vol. 34 ›› Issue (9): 1197-1203.

某型涡轮过渡流道稳定工作范围优化设计

侯朝山,吴虎

西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072

发布日期:2021-08-15
作者简介:侯朝山(1989—),男,博士生,研究领域为叶轮机械气体动力学。E-mail:380695570@qq.com

Optimization Design on Steady Operating Range for Intermediate Turbine Duct

School of Power and Energy, Northwestern Polytechnic University, Xi’an 710072, China;School of Power and Energy, Northwestern Polytechnic University, Xi’an 710072, China

Published:2021-08-15

摘要/Abstract

摘要： 为保证高、低压涡轮间流场参数匹配,要求在高压涡轮出口旋流角增大时,涡轮过渡流道仍处于近最佳工作状态。利用全三维数值模拟方法对涡扇发动机涡轮过渡流道进行了初次优化设计。优化后的过渡流道压力系数提高了20.6%,总压损失系数降低了 5.0%,并且其无流动分离工作范围得到扩大。为进一步扩大非设计稳定工作范围,对初次优化设计结果进行了二次优化。虽然二次优化后涡轮过渡流道设计点性能略有下降,但其无流动分离工作范围进一步扩大,且非设计工况点流道出口流场分布更加均匀,改善了下游低压涡轮的进气条件。 

关键词: 涡轮过渡流道;优化;设计;模拟;性能 

Abstract: To match the flow field between high pressure turbine(HPT)and low pressure turbine(LPT) efficiently, optimum operating state of an intermediate turbine duct(ITD)should be guaranteed with increasing the swirl angle at HPT outlet. At the present study, primary optimization on ITD of a turbofan engine was firstly conducted based on three dimensional numerical simulation method. The results show that the pressure recovery coefficient increases by 20.6% and the total-pressure loss coefficient decreases by 5%.In addition,the unseparated flow operating range is expanded as well. Based on the primary optimization, a secondary optimization was aimed at further increasing the off-design steady operating range. Final results indicate that the unseparated flow operating range is expanded further at the expense of slight decrease of the design point performance.The outlet flow field uniformity of off-design point is improved as well, which provides the LPT with more preferable inlet condition. 

Key words: Intermediate turbine duct(ITD);Optimization;Design;Simulation;Performance

侯朝山,吴虎. 某型涡轮过渡流道稳定工作范围优化设计[J]. 推进技术, 2013, 34(9): 1197-1203.

HOU Chao-shan,WU Hu. Optimization Design on Steady Operating Range for Intermediate Turbine Duct[J]. Journal of Propulsion Technology, 2013, 34(9): 1197-1203.

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