摘要
为减少径向预旋系统的流动损失,运用数值模拟方法对不同盘腔进气位置的径向预旋系统进行分析,结果表明:随着盘腔进气径向位置的增加,预旋喷嘴出口气流旋流比随之逐渐减小,径向预旋系统的温降系数及总压损失系数均随之逐渐增大。当旋转雷诺数等于7.9×10~6,盘腔进气位置由低位向高位变化时温降系数最大可增加525%,同时总压损失系数增加3.93%。径向预旋系统内比熵增主要发生在预旋喷嘴和共转腔,约占系统总体比熵增的80%。随着盘腔进气径向位置的增加,径向预旋系统总体比熵增降低,预旋喷嘴比熵增占比逐渐增大,共转腔比熵增占比逐渐减小。
To reduce the flow loss in radial pre-swirl system,numerical simulation method was used to analyze the radial pre-swirl system with different air entraining positions of the cavity.The results showed that the swirl ratio of air flow at the pre-swirl nozzle outlet decreased,the temperature drop coefficient and total pressure loss coefficient increased with the increase of the radial air entraining position.When rotational Reynolds number was 7.9×10~6,the temperature drop coefficient increased by 525%and the total pressure loss coefficient increased by 3.93%when the air entrainment position changed from low to high.The specific entropy increment in the radial pre-swirl system mainly occurred in the pre-swirl nozzle and the co-rotating cavity,accounting for about 80%of the total specific entropy increment.With the increase of the radial air entraining position,the overall specific entropy increment decreased,and the specific entropy increment proportion of the pre-swirl nozzle increased.However,the spectific entropy increment proportion of co-rotating cavity decreased.
作者
张凯
王锁芳
侯晓亭
韦光礼
ZHANG Kai;WANG Suofang;HOU Xiaoting;WEI Guangli(Aero-engine Thermal Environment and Structure Key Laboratory of Ministry of Industry and Information Technology,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2020年第3期502-509,共8页
Journal of Aerospace Power
基金
国家科技重大专项(2017-Ⅲ-0011-0037).
关键词
进气位置
径向预旋
温降系数
压力损失
比熵增
air entraining position
radial pre-swirl
temperature drop coefficient
pressure loss
specific entropy increment
