新型微型涡扇方案及其复合压缩转子初步设计  

Novel Micro Turbofan Configuration and Preliminary Design of Its Compression System

作　　者：陆惟煜 黄国平[1] 傅鑫[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《南京航空航天大学学报》2017年第3期340-351,共12页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金(51176072)资助项目

摘　　要：在分析国内外已有微型涡扇发动机方案可行性及利弊的基础上,提出一种紧凑型复合压缩系统微型涡扇发动机方案,可在保证结构简化与紧凑的前提下有效降低发动机耗油率。该方案风扇转子与斜流压气机转子构成串列叶片结构,通过对串列叶片独立作用机制和耦合作用机制的研究,认为合理设计串列叶片转子(全串列或半串列形式)能显著提高内涵压缩性能。通过对该方案的总体性能建模及参数分析,给出了一个设计实例的设计参数及性能参数,该实例中,耗油率比相同性能水平微型涡喷发动机约降低24.4%。对复合压缩系统转子进行了初步设计并进行流场数值模拟,得出转子系统内涵在设计流量下压比5.2,效率91%,外涵在设计流量下压比1.6,效率84%。结合对内外涵流场的分析,表明内外涵均可在较高效率下完成增压作用。Based on analysis of feasibility, pros and cons of domestic and foreign existing micro turbofan configurations, a novel configuration with compact and compound compression system is put forward, in order to reduce fuel consumption effectively while keeping the structure simplified and compact. In this scheme, the fan rotor and the mixed flow compressor rotor compose tandem blades. Through the re search of independent mechanism and coupling mechanism of tandem blades, it is thought that fine de sign of tandem blades （tandem totally or partially） can significantly improve the compression perform- ance. By establishing overall performance model and analyzing parameters, it is revealed that specific fuel consumption could be 24.4% lower than corresponding micro turbojet engine approximately. The ro tor of composite compression system is then preliminarily designed and numerically simulated, and it is obtained that the pressure ratio is 5.2 and the efficiency is 91% down the bypass, while 1.6 and 84% in the bypass, of the compound compression system. With flow field analysis, it is indicated that compound compression system both down the bypass and in the bypass can complete the compression in high efficiency.

关 键 词：微型涡扇发动机 总体性能分析 串列叶片 数值模拟 流场分析 

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]