CAJ | 학술논문

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。
단급리심압기궤재중소형항공연기와륜발동궤중득도료엄범적응용，위료탐색고압비리심압기궤설계기술，본문이용리심압기궤설계계통완성료일태단급압비5．2적리심압기궤설계，돌파료과음속리심협륜、긴주식확압기설계관건기술，총결료고압비리심압기궤설계방법，병재고속압기궤시험태상완성료시험험증，결과표명，해리심압기궤내류류동삼수분포합리，각항성능완전만족설계지표요구。
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.