摘要
采用数值模拟方法研究了高压轮缘斜向密封几何对燃气入侵的影响,结果表明:小封严冷气流量下,高压轮缘末端径向扩张引起轮缘间隙内压力梯度减小,延缓了低压轮缘边界层分离,而高压轮缘径向扩张引起下端区主流流速增大,流体抵抗逆压梯度能力增强,上述因素综合作用导致轮缘间隙内封严涡涡核径向位置上移,受封严涡卷吸而发生的燃气入侵程度减弱,封严效率因而提升46.95%。随着封严冷气流量的增大,盘腔内封严冷气压力逐渐提升,冷气出流能力增强导致封严效率逐渐提升,高压轮缘径向扩张诱发的封严涡涡核径向上移作用效果弱于冷气流量增大对封严效率的影响,因而随着冷气流量的增加,封严效率的提升幅度逐渐减小。
The numerical simulation method was used to study the influence of the chute seal configuration of the high-pressure wheel flange on hot gas ingestion,and the results showed that under low sealing flow,the radial expansion of the end of the high-pressure wheel flange caused the decrease of pressure gradient in the wheel flange gap,which delayed the separation of the boundary layer of the low-pressure wheel flange,while the radial expansion of the high-pressure wheel flange caused the increase of mainstream flow velocity in the endwall region,and the ability of the fluid to resist the inverse gradient was enhanced.As a result,the sealing efficiency increased by 46.95%;with the increase of the sealing flow,the pressure of the sealing flow in the disk cavity gradually increased,the sealing efficiency was gradually improved due to the enhancement of the sealing flow outflow capacity,and the radial upward movement effect of the sealing vortex core induced by the radial expansion of the high-pressure wheel flange was weaker than the influence of the increase of the sealing flow on the sealing efficiency,so with the increase of the sealing flow,the increase of sealing efficiency gradually decreased.
作者
宋彦庆
隋秀明
佟鑫
宋权斌
赵巍
赵庆军
SONG Yanqing;SUI Xiuming;TONG Xin;SONG Quanbin;ZHAO Wei;ZHAO Qingjun(College of Energy and Power Engineering,Changsha University of Science and Technology,Changsha 410114,China;Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100049,China;Innovation Academy for Light-duty Gas Turbine,Chinese Academy of Sciences,Beijing 100190,China;Beijing Key Laboratory of Distributed Combined Cooling Heating and Power System,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2024年第11期206-215,共10页
Journal of Aerospace Power
基金
国家科技重大专项(J2019-Ⅱ-0011-0031,2017-Ⅲ-0010-0036)。
关键词
燃气入侵
对转涡轮
对转盘腔
轮缘斜向密封
封严效率
hot gas ingestion
counter-rotating turbine
counter-rotating cavity
chute seal configuration
sealing efficiency
