摘要
基于鲨鱼鳃射流减阻的思想,采用数值方法,将仿鲨鱼鳃结构应用在压气机平面叶栅中。在叶片根部从压力面向吸力面开槽,采用单个进口、两个出口的开槽结构,以期在获得较大的出口射流的情况下实现对压气机叶片的减阻,达到提高叶栅气动性能的效果。在保证开槽结构的进出口宽度、出口起始位置、开槽内的隔板宽度、深度等几何参数不变的基础上,研究开槽进口起始位置、开槽高度对叶栅性能的影响。结果表明:合理的仿鲨鱼鳃开槽结构可以有效改变叶片吸力面根部角区的流动结构,抑制气流沿叶高方向的流动,从而降低流动损失;最佳方案为开槽结构位置位于48%~53%压力面弧长处,开槽高度为15%叶高,可以使压气机叶栅总压损失减小7.16%。
Based on the idea of jetting drag reduction through shark gills, the shark gill-like structure is applied to the plane cascade of compressor by numerical method. In order to reduce the drag of compressor stator vanes and improve the aerodynamic performance of cascade, the slotted structure of single inlet and two outlets is adopted in this paper, which is slotted at the root of the cascade from the pressure to the suction surface. On the basis of ensuring that the geometric parameters such as inlet and outlet width, outlet starting position, diaphragm width and depth in the slotted structure remain unchanged, the effects of slotted inlet starting position and slotted height on cascade performance are studied. The results show that the reasonable shark gill-like slotted structure can effectively change the flow structure in the root corner of the cascade suction surface, inhibit the flow along the cascade height direction and reduce the flow loss. The best scheme is that the slotted structure is located at the arc length of 48% to 53% pressure surface, and the slotted height is 15% cascade height, which can reduce the total pressure loss of compressor cascade by 7.16%.
作者
杨凌
韩露
钟兢军
YANG Ling;HAN Lu;ZHONG Jing-jun(Merchant Marine College,Shanghai Maritime University,Shanghai 201306,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2023年第2期94-104,共11页
Journal of Propulsion Technology
基金
国家自然科学基金重点项目(52236005)
航空发动机及燃气轮机基础科学中心项目(P2022-B-II-007-001)
关键词
压气机静叶
平面叶栅
仿鲨鱼鳃开槽
附面层分离
总压损失
Compressor stator vanes
Plane cascade
Shark gill-like slotted structure
Boundary layer separation
Total pressure loss
