摘要
为揭示高亚声速来流条件下压气机叶栅内部流动特性,对高速压气机叶栅通道内旋涡结构和流动损失的产生与演变规律进行研究。首先建立了数值仿真模型并用实验验证,然后详细研究了叶栅通道内主要旋涡结构、拓扑规律和旋涡模型,最后分析了叶栅通道内流动损失与旋涡结构的内在联系。高速压气机叶栅通道内主要存在马蹄涡、端壁展向涡、通道涡、壁角涡、壁面涡、集中脱落涡和尾缘脱落涡7个集中涡系,通道涡由端壁来流附面层中发展而来,是角区复杂旋涡结构的主要诱因;攻角由0°增大为4°,通道涡的涡核更早地脱落端壁附面层向角区发展,但对角区流动的影响减弱,叶片尾缘未形成明显的集中脱落涡。伴随着集中脱落涡的消失,叶栅固壁面拓扑结构中,叶片尾缘吸力面上没有出现与集中脱落涡对应的分离螺旋点,并且与叶中脱落涡层相对应的分离线和再附线消失,尾缘脱落涡仅包含近端区的一个分支。由总压损失沿流向和展向的变化规律,叶栅通道流动损失主要来源于角区复杂旋涡结构引起的强剪切作用,近端壁区的总压损失与角区主要涡系结构的生成和发展密切相关;攻角由0°增大至4°,角区旋涡的影响能力变弱,近端区流动损失减小,与叶中部位总压损失的差异缩小。
In order to find out the internal flow characteristics of compressor cascade in high subsonic flow,research on the occurrence and development of high-speed compressor cascade vortex structures and flow loss are established.Firstly,the simulation model is erected and verified with experimental results;secondly,the main vortex structures,topological patterns and vortex models in the cascade passage are researched in detail;in the end,the relationship between flow loss and vortex structures is analyzed.Seven main vortex structures including horseshoe vortex,endwall span vortex,passage vortex,corner vortex,wall vortex,concentrated shedding vortex and trailing edge shedding vortex are observed in high-speed compressor cascade passage,and passage vortex which originates from the inlet endwall boundary layer is the main reason for the complicated vortex structures.As the angle of attack increases from 0°to 4°,although passage vortex vortex core separates earlier from the corner boundary layer,influences of passage vortex on the passage flow are weakened and concentrated shedding vortex at the trailing edge disappears.According to the cascade topological structure,with the disappearance of concentrated shedding vortex,spiral point corresponding to concentrated shedding vortex on suction surface disappears and the attachment line and separation line at trailing edge corresponding to midspan trailing edge shedding vortex are vanished,indicating that trailing edge shedding vortex only exists near endwall.According to the variance law of totalpressure loss coefficient in streamwise and spanwise direction,cascade passage flow loss is mainly attributed to strong sheering action caused by the complicated corner vortex structures,and the totalpressure loss near endwall is closely related to the occurrence and development of the main corner vortex structures;with the increase of angle of attack from 0°to 4°,however,influences of corner vortex structures are weakened,and the gap between totalpressure loss near endwall and mids
出处
《航空学报》
EI
CAS
CSCD
北大核心
2014年第9期2438-2450,共13页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(50906100
51336011)
高等学校全国优秀博士学位论文作者专项资金(201172)
陕西省科学技术研究发展计划(2013KJXX-83)~~
关键词
高速压气机叶栅
轴向涡量
拓扑规律
旋涡结构
流动损失
high-speed compressor cascade
axial vorticity
topological rule
vortex structure
flow loss
