基于仿生学叶片的压气机角区复杂流动控制和模化实验研究

High efficient, highly-loaded compressor design is one of the key technologies of aero-engine development. And it is one of the core contents of Aero-engine Major Project listed in China's plan for scientific and technological development. This study concerns the mechanisms of cascade-corner separation flow, stall and the turbulence phenomenon in highly-loaded axial compressor. Based on bionics principles, simulating the leading edge tubercles of humpback whale flippers, the complex 3-D separation flow and corner stall in axial compressor cascade will be studied by both numerical and experimental methods. Both uniform and non-uniform tubercles are studied to reveal their flow control ability about the corner stall. By the introduction of bionics study, combined with internal flow characteristics, the corner stall in highly-loaded axial compressor is detailed investigated by DES method as well as TR-PIV measurement. The vortex structure and its development process will be subtly captured to reveal the mechanism of reducing corner separation and enhancing aerodynamic performance via bionics blade.

高效、高负荷压气机设计是航空发动机发展的关键技术之一，也是我国重大科技专项“航空发动机重大专项”的核心内容之一。该申请项目瞄准高负荷轴流压气机设计中日益突出的叶片-角区分离流动和失速现象，应用仿生学原理，模仿鲸类鳍状前肢的不规则结状突起，开展基于轴流压气机叶栅角区复杂三维分离流动模式识别的仿生学流动控制研究。通过数值和实验手段重点解决均匀及非均匀结状突起仿生学叶片对高负荷轴流压气机叶栅角区分离流动的影响和分离流动的控制机理等内容。该申请项目以仿生学研究为基础，结合叶轮机械内流流动特点，综合运用基于DES高精度数值计算方法和TR-PIV高频响实验测量研究手段，精细地捕捉压气机叶栅角区流场旋涡结构的发展，从而揭示前缘具有结状突起的仿生学叶片影响高负荷压气机叶栅角区流动、控制流动分离、减小损失并进而提高压气机效率和气动性能的物理机制。

本项目着眼于高效、高负荷压气机设计，在两机专项全面开展的大趋势、大环境下，瞄准高负荷轴流压气机设计中日益突出的叶片-角区分离流动和失速现象，应用仿生学原理，将鲸类鳍状前肢的不规则结状突起结构应用于轴流压气机扩压叶栅设计中，开展基于轴流压气机叶栅角区复杂三维分离流动模式识别的仿生学流动控制研究。通过数值和实验手段基本解决了均匀结状突起仿生学叶片对高负荷轴流压气机叶栅角区分离流动的影响和分离流动的控制机理，为后续非均匀结状突起的研究奠定了基础。本项目以仿生学研究为基础，结合叶轮机械内流流动特点，综合运用高精度数值计算方法和实验测量研究手段，较为精细地捕捉了压气机叶栅角区流场旋涡结构的发展，基本揭示了前缘具有均匀结状突起的仿生学叶片影响高负荷压气机叶栅角区流动、控制流动分离、减小损失并进而提高压气机效率和气动性能的物理机制。