侧向膨胀效应下激波与涡轮平面叶栅相互作用机理研究  

Interaction mechanism between shock wave and turbine cascade under lateral expansion effect

作　　者：李想 武郁文 李群 聂嘉仪 翁春生[1] LI Xiang;WU Yuwen;LI Qun;NIE Jiayi;WENG Chunsheng(National Key Laboratory of Transient Physics,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学瞬态物理国家重点实验室,江苏南京210094

出　　处：《推进技术》2024年第8期66-79,共14页Journal of Propulsion Technology

基　　金：国家自然科学基金面上项目(12172177)。

摘　　要：爆轰燃烧具有更低的熵增率和更高的热循环效率,利用旋转爆轰燃烧室替代涡轮喷气式发动机的主燃烧室可以进一步提高其工作性能。为研究旋转爆轰波组合发动机内部的工作过程,建立激波管与涡轮平面叶栅耦合计算模型,考虑激波传播方向的影响,分析激波在侧向膨胀效应下与涡轮叶片相互作用机理,并在此基础上进一步开展可视化实验研究。结果表明:在侧向膨胀效应影响下,激波波阵面从竖直形状转变为弯曲形状,波后气流在直角台阶处形成一个三角形的局部超声速区域,随后弯曲激波与涡轮叶片的前缘处、压力面、吸力面和尾缘处相互作用,在叶栅通道内形成复杂的波系结构。静子叶栅和转子叶栅对压力和温度有着不同程度的抑制作用,当弯曲激波相对于叶片垂直时,叶栅的抑制更为明显。对比分析了实验与数值模拟获得的激波系在涡轮平面叶栅通道内的传播及演化过程,发现激波演化的时空特性高度一致,实验与数值模拟结果吻合良好。观测到弯曲激波在叶片尾缘处发生衍射,波阵面面积明显增大且激波传播方向改变,随着激波继续传播,叶片尾缘处伴随着脱落涡产生。Detonation combustion exhibits a lower of entropy increase rate and higher thermodynamic effi⁃ciency.The performance of a turbojet engine can be significantly enhanced by replacing its main combustion chamber with a rotating detonation combustion chamber.In order to study the internal working process of a rotat⁃ing detonation wave combined engine,a coupled computational model of shock tube and turbine cascades is es⁃tablished to analyze the interaction mechanism between shock waves and turbine blades under the lateral expan⁃sion effect,considering the influence of the direction of shock wave propagation.Furthermore,a visualization ex⁃perimental platform is constructed to investigate the interaction between shock waves and turbine cascades.The obtained results demonstrate that the shock wave front undergoes a transition from a vertical shape to a curved shape due to lateral expansion.At the right-angle step,the airflow behind the shock wave forms a triangular local supersonic region.Subsequently,the curved shock wave interacts with various components of the turbine blade,including the leading edge,pressure surface,suction surface,and trailing edge,resulting in the formation of com⁃plex wave structures within the cascade channel.Both stator cascades and rotor cascades exhibit varying degrees of suppression on pressure and temperature.The suppression effect of the cascades is more prominent when the curved shock wave is perpendicular to the blades.The propagation and evolution of the shock wave in the cascade channel are thoroughly analyzed by comparing the experimental and numerical simulation data.It is found that the spatio-temporal characteristics of the shock wave evolution exhibit high consistency,demonstrating good agree⁃ment between the experimental and numerical results.Curved shock waves are observed to diffract at the trailing edge of the blade,leading to a substantial increase in the wavefront area and a change in the direction of shock wave propagation.As the shock wave continues to propag

关 键 词：旋转爆轰燃烧室 侧向膨胀效应 涡轮平面叶栅 弯曲激波 纹影观测 

分 类 号：V231.22[航空宇航科学与技术—航空宇航推进理论与工程]