旋转爆震环境下涡轮流场及气动激励的演变规律研究  

Evolution of turbine flow field and aerodynamic excitation force under rotating detonation environment

作　　者：张伟昊[1,2] 廖湘力 穆雨墨 李瑞泉 ZHANG Weihao;LIAO Xiangli;MU Yumo;LI Ruiquan(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,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,北京100191 [2]航空发动机气动热力国家级重点实验室,北京100191

出　　处：《燃气涡轮试验与研究》2024年第2期1-10,共10页Gas Turbine Experiment and Research

基　　金：国家自然科学基金(52176033)。

摘　　要：涡轮式旋转爆震发动机有望给航空发动机性能带来变革性提升,但旋转爆震燃烧室的出口流场会对下游涡轮的运行产生显著影响。针对旋转爆震环境下涡轮的工作特性问题,构建了运动激波模型,并基于模型重构了涡轮的非定常入口条件,对该极端工况下的涡轮开展数值模拟研究,分析了其内部流场及气动激励的演变规律与特征。结果表明,涡轮处在强非线性的来流扰动之下,运动激波与涡轮相互作用产生复杂的波系结构,涡轮上下游的波系结构相似,但是涡轮内激波的演化随运动激波模态的不同而有所区别;爆震环境下动叶气动激励的主要激励源是通道内的波系结构,叶表气动激励和压力脉动程度均增大,但是叶片载荷显著下降。The turbine-based rotating detonation engine holds the potential to bring transformative improvements to the performance of aero-engines.However,the exit flow field of the rotating detonation combustor significantly affects the operation of the downstream turbine.To address the operational characteristics of turbines under rotating detonation conditions,a moving shock wave model was established to reconstruct the unsteady inlet conditions of the turbine.Numerical simulations were conducted to study the turbine’s performance under these extreme conditions to analyze the evolution and characteristics of its internal flow field and aerodynamic excitation force.The results indicate that the turbine operates under strong nonlinear inflow disturbances.The interaction between the moving shock wave and the turbine generates a complex wave system structure.While the wave system structures upstream and downstream of the turbine are similar,the evolution of shock waves within the turbine varies with different moving shock wave modes.Under detonation conditions,the main source of aerodynamic excitation force for the rotor blades is the wave system structure within the passage,resulting in increased aerodynamic excitation and pressure oscillation on the blade surfaces,while the blade load significantly decreases.

关 键 词：旋转爆震 涡轮 边界模化 波系演化 流场特性 气动激励 航空发动机 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]