轴向超音速来流下超音通流风扇叶型气动特性研究
Study on Performance of Supersonic Through-flow Fan Cascade Under Axial Supersonic Inflow
孙士珺 1李晓龙 1王松涛2
作者信息
- 1. 北京理工大学宇航学院,北京 100081
- 2. 哈尔滨工业大学能源科学与工程学院,哈尔滨 150001
- 折叠
摘要
为研究轴向超音通流风扇(STFF)叶栅的变工况性能,开展了轴向超音速来流对稠度为3.32的STFF典型叶型气动性能影响的数值研究.结果表明:整体上,相较于攻角,来流马赫数对总压损失系数、静压比、负荷系数以及出口气流角的影响较小.当来流马赫数从1.58增大至2.36时,叶型总载荷略有减小,总损失则逐渐增加,且总损失变化主要源于通道损失的变化.另外,相比于激波损失与钝损失,黏性损失受马赫数的影响较小,其变化约占总损失变化的20％.叶片吸力面附面层分离尺度随着来流马赫数的增加而减弱,这是因为前缘激波压力侧分支与相邻叶片吸力面的交点随着马赫数的增加逐渐向下游移动,导致激波角减小、波前马赫数增加,但在两者的综合作用下激波强度降低.
Abstract
To reveal the off-design performance of the axial supersonic flow fan(STFF)cascade,a numerical study on the influence of axial supersonic inflow on the aerodynamic performance of a typical STFF blade with a solidity of 3.32 was carried out.The results show that,on the whole,compared with the incidence angle,the inlet Mach number has less impact on the total pressure loss coefficient,static pressure ratio,load coefficient and exit flow angle.When the incoming Mach number increases from 1.58 to 2.36,the blade loading decreases slightly,while the total loss in-creases gradually.The variation of the total loss is mainly due to the change of the passage losses.Besides,compared to the shock loss and the bluntness loss,the viscosity loss is less affected by Mach number,and its variation accounts for about 20％of the total loss variation.The separa-tion scale of the boundary layer on the blade suction surface is weakened with the increase of the incoming Mach number.This is because the intersection point between the pressure side branch of the leading edge shock and the adjacent blade suction surface moves downstream with the in-crease of inlet Mach number,resulting in a decrease in the shock angle and an increase in the Mach number ahead of the shock.However,under the combined effect of the two,the shock intensity is weakened.
关键词
轴向超音通流风扇/超音速来流/进口马赫数/气动特性Key words
axial supersonic through-flow fan/supersonic inflow/inlet Mach number/aerodynamic characteristic引用本文复制引用
基金项目
国家自然科学基金资助项目(52006011)
北京理工大学青年教师学术启动计划(XSQD-202201002)
出版年
2024
NETL
NSTL
万方数据