间冷回热涡扇发动机大涵道比风扇技术  

High bypass ratio fan technology for intercooled recuperated turbofan engine

作　　者：关朝斌[1] 曹志鹏[1] 安利平[1] 王靖宇 

机构地区：[1]中国燃气涡轮研究院,成都610500 [2]中航空天发动机研究院有限公司,北京101304

出　　处：《燃气涡轮试验与研究》2016年第1期25-31,共7页Gas Turbine Experiment and Research

摘　　要：为支持间冷回热循环涡扇发动机技术研究,开展了一台涵道比为16.6的大涵道比风扇的气动设计,获得了较高的效率和稳定工作裕度,并对风扇根部流道弯曲形式、转静连接流道形式、转子造型技术和内涵静子周向弯曲形式进行了研究。结果表明,采用的转子根部反曲率流道、转静连接流道、宽弦-正攻角设计转子叶片、根部反弯设计内涵静子,能有效支持气动方案设计,改善大涵道比风扇气动设计中效率低、内涵裕度不足等问题。In order to support the research on IRA（Intercooled Recuperated Aero-engine）, the aerodynam-ic design of an advanced fan with bypass ratio at 16.6 was performed, and favorable efficiency and surgemargin were obtained. Several important issues in high bypass ratio fan design were studied, including cur-vature of hub path, path between rotor and stator, rotor blading technique and circumferential curvature ofinner duct stator. The results show that the aerodynamic requirements are satisfied by using negative curva-ture path in rotor hub, proper path between rotor and stator, wide-chord rotor blade with positive incidence,and negative bowed stacking at hub of inner duct stator. The deficiencies in high bypass ratio fan design aresignificantly improved including low efficiency and low surge margin of inner duct.

关 键 词：航空发动机 间冷回热循环 大涵道比 气动设计 弯曲静子 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]