高负荷压气机的轮毂型线三维气动优化及其CFD验证

3D Aerodynamic Optimization of Hub Profile and CFD Validation for High-Load Compressor

针对高负荷压气机难以控制角区的二次流、叶片表面存在大规模边界层分离等技术瓶颈,本文提出了一种三维端壁型线的气动优化方法,对高负荷压气机轮毂型线优化进行了研究,并对所采用的方法进行了验证,开发了相应的优化系统。结果表明,所采用的端壁型线优化方法能有效抑制附面层分离,降低吸力面转角区域二次流的强度和规模。因此,叶片通道控制流动方向和优化流动条件的能力得到了扩展。压气机级的整体气动性能,如失速裕度和等熵效率也得到了提高。优化后,在通流能力较好的情况下,压气机级的气动效率达到了88.59%,提高了1.05%。本文提出的方法和相应的系统很好地促进了压气机气动设计系统的发展,具有良好的工程应用前景,为压缩系统获得更突出的通载能力和更好的流动结构提供了新的思路和解决方案。

To solve the technological bottlenecks of high-loaded compressors such as controlling secondary flow in the corner near the endwall and weakening large-scale boundary layer separation on the blade surface,a 3D aerodynamic optimization method was proposed for optimizing the endwall profile of high-loaded compressors and developing the corresponding optimization system.Then,the adopted method and system were also validated.Based on the calculation results,it was concluded that the applied endwall profile optimization method could ef⁃fectively suppress the boundary layer separation and reduce the intensity of the secondary flow in the corner on the suction surface.Hence,the blade channels’ability of controlling the flow direction and optimizing the flow condition was expanded.Overall aerodynamic performance of the compressor stage,such as the stall margin and the isentropic efficiency,was also improved.After this optimization,the aerodynamic efficiency of the compres⁃sor stage has reached 88.59%,raised by 1.05%.Therefore,the method and corresponding system proposed in this paper can promote the development of the compressor aerodynamic design system well,having a good pros⁃pect of engineering application and providing a new idea and solution for compression systems to acquire more outstanding load-carrying ability and better flow structures.