摘要
为探究附面层抽吸对跨声速压气机的气动性能及其流场结构的影响,以跨声速压气机的静子叶片为研究对象,通过数值模拟计算方法对压气机静叶吸力面开设抽吸槽进行相关研究.对比原型叶栅以及各抽吸方案可以发现:吸力面抽吸对抑制上角区分离效果明显,在降低损失的同时略微提高了扩压能力;当抽吸槽开设在靠近分离涡核心附近时,对角区的抑制最佳,而叶栅整体的总压损失降低了16.68%.利用进口导叶替代动叶营造近失速工况,在后续实验研究中,可以摆脱整级试验台高成本以及恶劣工况下的危险性等不利因素.
To explore the influence of the boundary layer suction on the aerodynamic performance and flow field structure of the transonic compressor, the stator blade of transonic compressor was taken as the study object, the suction slot of the compressor suction surface was studied by using the numerical simulation method. By comparing the prototype cascade with the suction schemes, it can be found that the suction on the surface suction has obvious effect to restrain the upper corner separation, and at the same time of reducing the loss, the diffusion capacity is slightly improved. When the suction slot is near the core of the separation vortex, the suppression of the corner separation is the best, and the total pressure loss of the cascade is reduced by 16.68%. Using imported guide vanes instead of moving vanes to create near stall conditions can get rid of the disadvantageous factors such as high cost of whole stage test bench and danger under bad conditions in subsequent experimental research.
作者
梁锐星
陆华伟
杨刚
郭爽
LIANG Rui-xing;LU Hua-wei;YANG Gang;GUO Shuang(Naval Architecture and Marine Engineering College,Dalian Maritime University,Dalian 116026,China;School of Aeronautics and Astronautics,Dalian University of Technology,Dalian 116024,China)
出处
《大连海事大学学报》
CAS
CSCD
北大核心
2019年第4期102-109,共8页
Journal of Dalian Maritime University
基金
国家自然科学基金资助项目(51676023)
关键词
跨声速静子叶栅
吸力面
附面层抽吸
数值研究
transonic stator cascade
suction surface
boundary layer suction
numerical research
