航空学报2025，Vol.46Issue(7)：55-69,15.DOI:10.7527/S1000-6893.2024.30832
高性能涡轮低位预旋供气系统正向设计
Forward design of high-performance turbine low-radius pre-swirl system
摘要
Abstract
Given that it is difficult for reverse design of imitation reconstruction method to meet the performance re-quirements of the advanced aero-engine pre-swirl system,this paper proposes an original forward design framework.Starting from design point parameters,the framework establishes a forward design process for the pre-swirl system,adopting the vane shaped hole nozzle and oblique receiver hole.Through one-dimensional design calculation,the aerodynamic parameters along the characteristic cross-section at the design point of the pre-swirl system,the specific geometrical structural parameters of the characteristic components,are obtained,along with a preliminary prediction of the system temperature drop performance.The results of one-dimensional design are then calibrated through three-dimensional calculation.The performance improvement evaluation of the flow and temperature drop characteristic of the pre-swirl system based on forward design is carried out,with emphasis on revealing the influence of the angle of attack of the airflow at the inlet of the receiver hole on the performance of the system.The study shows that the aver-age deviation of the flow rate between the one-dimensional design and the three-dimensional calculation of the pre-swirl system is only 0.8%,and the average deviation of the system temperature drop efficiency is only 5.12%.Com-bining the entropy increase,temperature drop,power consumption,and other performance parameters of the sys-tem,the range of angle of attack at the inlet of the receiver hole when the system performance parameters are stable is-7° to 3°,indicating that it is feasible to improve the performance of the system based on the forward design method.The discharge coefficient of the vane shaped hole pre-swirl nozzle is 10.63%higher than that of the hole-type nozzle,and 4.58%higher than that of the cascade vane nozzle.The results also show that flow loss in the rotating zone is re-duced by using oblique receiver holes,and the area resistance is lowered.The temperature drop efficiency of the low-radius pre-swirl system designed by the forward design method is 66%,which is more than 45.2%higher compared to the overall level of the low-radius pre-swirl system.关键词
航空发动机/预旋供气系统/正向设计/性能改进/功耗/温降Key words
aero-engine/pre-swirl system/forward design/performance improvement/power consumption/tem-perature drop分类
航空航天引用本文复制引用
姚斡维,刘高文,陈燕,孔晓治,林阿强..高性能涡轮低位预旋供气系统正向设计[J].航空学报,2025,46(7):55-69,15.基金项目
国家自然科学基金(52476091,52476025) （52476091,52476025）
航空发动机及燃气轮机基础科学中心项目(P2022-A-II-007-001) National Natural Science Foundation of China(52476091,52476025) （P2022-A-II-007-001）
Science Center for Gas Turbine Project(P2022-A-II-007-001) （P2022-A-II-007-001）
