离心压气机的设计优化方法,对以小微型燃气轮机作为动力源的分布式能源站的推广发展有着重要意义。本文以带有楔形扩压器的离心压气机为研究对象,利用CFD数值模拟方法,通过改变叶轮的典型几何参数,研究离心压气机性能的影响规律并做参数敏感性分析,综合考虑典型几何参数取值,对压气机做气动性能优化设计。研究表明：适当降低进出口半径比、相对出口宽度和分流叶片相对长度,合理选择叶片进口角和出口后弯角对提高气动性能有利。几何参数对压比的影响程度排序为分流叶片相对长度、出口后弯角、进出口半径比、叶片进口角和相对出口宽度；几何参数对效率的影响程度排序为相对出口宽度、分流叶片相对长度、叶片进口角、出口后弯角和进出口半径比。除相对出口宽度外其余几何参数的改变对压比的影响均大于对效率的影响。优化后的离心压气机压比、效率和工作范围都有明显提升,设计流量下的压比由5.074提高到5.198,效率由0.8226提高到0.8427。

The design optimization method of centrifugal compressors is of great significance for the promotion and development of distributed energy stations using micro and small gas turbines as power sources. Taking a centrifugal compressor with a wedge-shaped diffuser as the research object, the CFD numerical simulation method is used to study the influence of typical geometric parameters of the impeller on the performance of the centrifugal compressor and conduct parameter sensitivity analysis. Considering the values of typical geometric parameters, the aerodynamic performance of the compressor is optimized. Research has shown that appropriately reducing the inlet-outlet radius ratio, relative outlet width, and relative length of splitter blades, as well as selecting the appropriate blade inlet angle and outlet back bend angle, are beneficial for improving aerodynamic performance. The degree of influence of geometric parameters on pressure ratio is ranked as follows: relative length of splitter blades, outlet back bend angle, inlet-outlet radius ratio, blade inlet angle, and relative outlet width; the degree of influence on efficiency is ranked as relative outlet width, relative length of splitter blades, blade inlet angle, outlet back bend angle, and inlet-outlet radius ratio. The changes in geometric parameters, except for the relative outlet width, have a greater impact on pressure ratio than on efficiency. The optimized centrifugal compressor has significantly improved pressure ratio, efficiency, and operating range. The pressure ratio at the design flow rate has been increased from 5.074 to 5.198, and the efficiency from 0.8226 to 0.8427.

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国防科技创新特区研究基金项目