驻涡式处理机匣对跨声速压气机扩稳的数值模拟  

Numerical simulation on stall margin improvement of transonic compressor by a trapped vortex casing treatment

作　　者：王卓奇[1] 陆利蓬[2] 袁巍[2] 宋西镇[2] 

机构地区：[1]北京航空航天大学无人驾驶飞行器设计研究所,北京100191 [2]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191

出　　处：《航空动力学报》2014年第12期2948-2956,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(50906001)

摘　　要：提出了一种驻涡式处理机匣结构,通过叶片通道前后以及叶片压力面和吸力面共同作用的压差,驱动流体产生回流.将通道后部的附面层流体吸除,然后在叶片前缘注入,增大叶尖泄漏流内的动量,从而达到扩稳的效果.该设计将抽气槽与喷气槽的方向和主流流动方向设计成一致方向,以减少掺混损失.此外,该处理机匣在轴向上完全在转子叶片内部,不需要前伸量,因而可以方便地应用于多级压气机中的任何一级,而不会和静子叶片发生干涉.通过数值模拟对这一设计进行了验证,结果表明该处理机匣可以扩大跨声速压气机转子裕度17.39%,而对效率不会产生明显的影响.A type of trapped vortex casing treatment （CT） was designed, using pressure difference between suction side at front and pressure side at rear of passage to drive fluid flowing back. Boundary flow was sucked into slot at rear of passage, then injected into main flow at front of passage. During this process, momentum of the fluid in the leakage was increased, and then the stall margin of the blade was enhanced. The loss of mixing is decreased by adjusting the direction of suction and injection to the direction of main flow. Also the size of CT in axial direction is inside the blade dimention, which means this CT could be used in each stage of multistage compressors, without overlapping with stators. Numerical simula- tion was used to evaluate the effectiveness of this CT. Result shows that this CT could in- crease the stall margin 17.39% of a transonic compressor rotor without compromise on efficiency.

关 键 词：扩稳 压气机 跨声速 叶尖泄漏流 旋转失速 处理机匣 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]