关键词: 喘振裕度, 端弯, 可控扩散叶型, 零级, 匹配, 相似理论

Abstract: The aerodynamic design of a new front stage for a three-stage axial-flow low-speed compressor based on the similarity theory is described, in order to increase the flow by 12.5% and the total pressure ratio. The design and optimization are carried out by using a 3D-viscocity controlled diffusion airfoil (CFD) technology on stator. The new computational fluid dynamics (CDA) profile is adopted to control the profile losses and adverse pressure gradient at trailing areas, so the three dimensional separation is reduced greatly. End-bending technology is also used to further mitigate the accumulation of low-energy fluid at stator end wall. It improves not only the flow at end zone but also the matching between the front stage and the base one, and enhances the zero-stage performance to arrive the design target. It is found that the surge margin is ensured by analyzing the characteristic curves and the base one keeps the similitude operating conditions by comparing the flow angles.

Key words: Controlled diffusion airfoil(CDA), End-bending, Match, Similarity theory, Surge margin, Zero-stage