多级高负荷风扇处理机匣扩稳与静子匹配研究  

Study on casing treatment stability extension and stator matching on multistage high-loading fan

作　　者：袁巍[1,2] 吴闯良 邓哲 YUAN Wei;WU Chuangliang;DENG Zhe(National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China)

机构地区：[1]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 [2]先进航空发动机协同创新中心,北京100191

出　　处：《航空动力学报》2018年第10期2515-2524,共10页Journal of Aerospace Power

基　　金：国家自然基金(51636001)

摘　　要：以双级高负荷风扇为研究对象,以三维数值模拟为手段,探索一种适合多级高负荷风扇而又不影响其大流量点性能的扩稳方案。最终,对风扇采用周向槽对风扇小流量点进行扩稳,同时调节处理机匣上游静子局部基元使之与处理机匣相匹配,解决了风扇大流量点的堵塞问题。风扇的稳定裕度提高到16.3%,同时风扇大流量点的流量也没有减小,从而兼顾了设计状态的推力水平。A two-stage high-loading fan with three-dimensional numerical simulations was studied.The simulation results were used to propose a scheme that enlarged the stall margin of multistage high-loading fans without sacrifice of the flow capacity when operating with a large mass flow rate.Furthermore,a circumferential groove casing treatment was used and adjustments were made to the upstream stator angle to match the casing treatment.The stall margin was thus increased to 16.3%,without reduction in the maximum mass flow rate or the design thrust performance.

关 键 词：双级高负荷风扇 周向槽处理机匣 静子调节 扩稳 匹配 堵塞 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]