高切线速度低压比单级风扇设计技术及试验验证  

Design technology and experimental verification of a single stage fan with high tip speed and low pressure ratio

作　　者：黄磊[1] 周拜豪[1] 李清华[2] 罗璇[1] 朱朝艺 

机构地区：[1]中国燃气涡轮研究院,成都610500 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《燃气涡轮试验与研究》2016年第6期16-20,共5页Gas Turbine Experiment and Research

摘　　要：针对单级跨声速风扇高切线速度、低压比的特点,采用先进的气动布局及特性分析方法,高切线速度低压比转子设计、低损失可调导叶设计、大攻角范围低损失静子设计技术,以及叶顶激波系控制技术等,完成了该单级风扇的设计,并在此基础上完成机械运转、总性能试验及导叶优化试验。试验结果表明,该单级风扇在满足发动机尺寸设计要求的前提下,各转速流量、效率、压比及稳定裕度均满足设计指标要求,其中效率和稳定裕度远远超过设计指标。Aiming at the characteristics of high tip speed and low pressure ratio, several kinds of design technology have been adopted in the design, such as the advanced methods of aerodynamic distribution and performance analysis, variable guide vanes with low loss, high tip speed low pressure ratio rotors, low loss stators in a wide range of incidence angles and tip shock wave control technology, etc. The overall performance test, guide vanes optimizing test and commissioning test have been undertaken. The results show that the mass flow, efficiency, pressure ratio and surge margin of the single stage fan at all the rotational speeds match the design requirements on the premise that the size of the fan satisfies the requirement of the engine. Moreover, the efficiency and surge margin are much higher than the design requirements.

关 键 词：航空发动机 核心机驱动风扇 高稳定裕度 高切线速度 低压比 变循环 定制叶型 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]