【作者】 牛玉川；

【导师】 朱俊强；

【作者基本信息】 中国科学院研究生院（工程热物理研究所） ， 工程热物理， 2007， 硕士

【摘要】 高推重比是航空涡轮发动机设计过程中最为注重的技术指标之一，吸附式压气机是高推重比发动机研制中关于新型压气机的探索成果之一，有可能用单级吸附式风扇替代目前的两级或三级风扇。吸附式压气机的工作机理是借助叶片吸力面上的开槽吸除叶片表面的低能流体，防止或推迟附面层分离，使槽道气流实现较大的折转，风扇或压气机级负荷大大提高。本文以平面叶栅风洞为实验平台，设计、加工了在叶栅吸力面上不同位置布置吸气槽，以及进行吸气和调节吸气量的设备，同时构建了实验台测量和数据采集系统。在不同来流马赫数、攻角、吸气量和吸气位置等状态下，测试吸附式压气机叶栅吸力面、压力面表面压力分布和叶栅尾缘等参数。借助数值分析和平面叶栅实验结果，讨论了吸气量、吸气位置对叶片表面压力分布、叶型损失的影响，初步总结了一些吸附式压气机叶型的设计准则。结果表明，附面层吸除能有效减弱吸力面角区低能流体积聚，导致附面层减薄，减少分离损失，有助于降低叶栅总压损失，提高气流折转能力，改善叶栅气动性能。选择合适的吸气槽位置和吸气量，有助于进一步提高压气机的性能。更多还原

【Abstract】 High Trust-Weight-Ratio has always been one of main goals for modern aeroengine design. Aspirated compressor in one of outstanding achievements in the IHPTET Project, which has been investigated by many researchers in MIT GTL and GE Company for several decades. With the help of highly loaded aspirated compressor, it should be possible to design a single stage fan instead of 2 or 3 stages fan used widely during the aeroengine design at present. In order to meet the requirements for highly loaded fan design, the primary investigations on the aspirated compressor cascade have been finished by the Institute of Engineering Thermophysics, Chinese Academy of Sciences. Some design criteria for the aspirated compressor and fundamental theory on boundary layer development under the condition of aspiration have been established based on the calculational and experimental results. Meanwhile influences of aspiration location and aspirated flow rate on pressure distribution on blade surfaces and profile loss have been discussed in details according to the numerical and experimental results based on aspirated compressor cascade test. And then some design criteria on aspirated compressor profile have been summed up to provide the technical supports for the advanced aeroengine design.With the subsonic cascade wind tunnel, the author designed the suction slot on the suction surface of compressor blade and the device which could control the suction flow. The effects of suction on the performance of aspirate compressor cascade under different Mach numbers, incidence angle, suction flow rate and suction slot situation were studied. The parameters to be measured included the pressure distributions on the surfaces of the cascade, total pressure, deviation angle. It’s obviously proven that boundary layer suction alleviated the accumulation of low energy fluid at suction surface corners, reduced the total pressure loss and decreased the deviation angle. With the appropriate suction slot location and suction flow rate, the compressor performance should be further improved.更多还原