采用冷气射流调节对转涡轮高压部件流量的数值研究  

Numerical Study on Flow Control of High Pressure Component in Counter-Rotating Turbine by Using Coolant Jet

作　　者：杨荣菲[1] 李云朋 仲冬冬 葛宁[1] YANG Rongfei;LI Yunpeng;ZHONG Dongdong;GE Ning(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2021年第1期29-32,共4页Machine Building & Automation

基　　金：航空动力基金项目(6141B09050339)。

摘　　要：针对先进发动机对涡轮变工况流量调节的需求,以某对转涡轮高压部件为研究对象,采用源项法模拟冷气射流,对导叶压力面、吸力面射流孔位置、射流角及射流流量对涡轮流量调节效果的影响进行了数值研究。结果表明:射流轨迹通过堵塞流道能实现减小涡轮进口流量的需求;从流量调节效果而言,不存在最佳压力面射流位置,而最佳吸力面射流位置位于喉道上游附近;最佳射流角度为直角及钝角;射流流量越大涡轮流量变化范围越大,并且吸力面射流引起的流量变化范围大于压力面射流。To meet the demand of advanced engines for its ability to adjust the turbine’s variable operating conditions,and taking a pair of parts of high-pressure counter-rotating turbine as the research object,the influence of jet hole position,angle and flow rate on turbine flow control were numerically studied,by the method of the source term simulating coolant jet.The results indicate that the jet can satisfy the demand of reducing the turbine inlet flow by blocking the flow channel.In terms of flow adjustment effect,there is no optimal jet position on the pressure surface.The best position of the suction surface jet is close to the upstream of the throat.The best jet angle is right and obtuse ones.Therefore,the larger the jet flow is,the larger the turbine flow adjustment range is.And the range of the flow control caused by the suction surface jet is greater than the pressure surface jet.

关 键 词：发动机 对转涡轮 流量调节 冷气射流 源项法 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]