摘要
单级离心压气机在中小型航空燃气涡轮发动机中得到了广泛的应用,为了探索高压比离心压气机设计技术,本文利用离心压气机设计系统完成了一台单级压比5.2的离心压气机设计,突破了跨音速离心叶轮、紧凑式扩压器设计关键技术,总结了高压比离心压气机设计方法,并在高速压气机试验台上完成了试验验证,结果表明,该离心压气机内流流动参数分布合理,各项性能完全满足设计指标要求。
Single-stage high pressure ratio centrifugal compressors are widely used in small and medium-sized aviation gas turbine engines.In order to explore the design technology of high pressure ratio compact centrifugal compressor, a high performance centrifugal compressor with pressure ratio of 5.2 was designed using advanced centrifugal compressor design system.The key technologies on designing transonic impeller and compact diffuser were broken through, and the design methods and principle of compact transonic cen-trifugal compressor are briefly presented.Finally, experimental validation of this centrifugal compressor design was fulfilled on a high-speed compressor test rig.The testing results verified this effective aerodynamics design rules of this kind of compressor, and all per-formance characteristics were well achieved against design targets.
出处
《燃气轮机技术》
2014年第4期31-36,共6页
Gas Turbine Technology
关键词
离心压气机
高压比
气动设计
试验验证
centrifugal compressor
high pressure ratio
aerodynamic design
experimental validation
