跨声速压气机高负荷通流构型与流动机理研究

Demands on higher thrust weight ratio in aircraft engine lead to reduced numbers of stages resulting in a significant increase of the aerodynamic loading in single stage, which puts forward a new challenge to the design theory and methods of compressor. The key flow field features relative to highly loaded transonic compressor include highly 3-D unsteady flow fields, complex shock systems, rotor/stator interaction, and strong interactions among the shock, boundary layer, and secondary flows. Additionally, the use of blade twist, sweep and lean contributes to the 3-D flow effects. Consequently, application of effective flow organization is considered as the most promising technology to improve the performance of transonic compressor. In this work, a systematic experimental and numerical investigation on the impact of 3-D highly loaded throughflow approach methods on the complex flow features and overall performance of transonic compressor will be undertaken. Based on the experimental data of the highly loaded transonic compressor, the flow mechanism of rotor/stator 3-D configuration on the blade passage flowfield, in particular, the shock wave pattern, the shock interaction with the main flow as well as with wall boundary layers, tip clearance flow and corner separation development will be revealed. The complex flow structure and loss model of the highly loaded transonic compressor will be provided. The design theory, method and criteria of highly loaded transonic axial flow compressor will be summarized.

航空发动机高推重比的需求使得压气机的负荷水平不断提高，对压气机设计理论和方法提出了新的挑战。由于气体的黏性、叶片弯扭掠、叶顶间隙流动、复杂激波结构及转/静子叶片相互干涉，使得高负荷跨声速压气机中的流动呈强三维性、有旋性和非定常性，探索更加合理的流动组织方法，对提高其性能有着重要意义。本项目针对跨声速压气机，开展高负荷通流构型的理论、实验（动叶直列叶栅实验、静叶扇形叶栅实验、跨声速单级压气机试验）和数值研究工作，在获取跨声速高负荷压气机基础实验数据的基础上，深入探索和揭示转/静子高负荷通流构型对压气机内部流场中激波结构、叶顶泄漏、三维角区分离、环壁附面层发展、各种涡系及二次流间相互作用的影响规律，构建跨声速高负荷压气机流场结构和损失模型，探索发展跨声速压气机高负荷通流构型的理论、方法与设计准则。

航空发动机高推重比的需求使得压气机的负荷水平不断提高，对压气机设计理论和方法提出了新的挑战。由于气体的黏性、叶片弯扭掠、叶顶间隙流动、复杂激波结构及转/静子叶片相互干涉，使得跨声速高负荷压气机中的流动呈强三维性、有旋性和非定常性，探索更加合理的流动组织方法，对提高其性能有着重要意义。本项目针对跨声速压气机，开展了：⑴跨声速单级压气机流动特性与损失机理研究；⑵跨声速压气机级中动/静叶高负荷通流构型的理论、实验和数值研究；⑶高负荷条件下压气机叶栅内旋涡结构及其形成机理研究；⑷跨声速压气机高负荷通流构型与流动匹配研究。具体的研究成果包括：⑴揭示了跨声速压气机内部复杂流动特征、损失来源及诱发失稳的关键因素；⑵明晰了动叶三维造型及叶尖小翼对跨声速压气机内部载荷匹配、激波结构、叶顶泄漏流动、环壁附面层增长及通道二次流动的影响及作用机理；⑶获得了静叶三维通流构型对其内部二次流动的作用机理和调控机制；⑷得出了全三维高负荷通流构型的跨声速压气机级间匹配机制以及高负荷通流构型的设计方法和准则；⑸获取了跨声速高负荷压气机的基础实验数据，为高负荷压气机通流构型提供了支撑。