负荷系数0.5 的高负荷单级轴流压气机设计及试验研究

为探索高负荷多级压气机的设计方法，开展了负荷系数0.5的进口级设计及试验研究。该进口级设计流量35.3 kg/s，压 比2.07，叶尖切线速度388 m/s。设计中采用了反预旋、高反力度的设计思路，转子进口相对速度全叶高超音。转静子均采用小展 弦比设计，其中转子展弦比0.68，静子展弦比1.1。该压气机在中国航发沈阳发动机研究所A219试验器上完成试验，录取了1.0和 0.95相对换算转速特性。试验结果表明：在1.0设计转速，工作点换算流量36.37 kg/s，压比2.121，效率0.894，喘振裕度8%，验证了 高反力度、高负荷多级压气机进口级设计方法。给出了流路、转静子叶型几何坐标等气动设计数据，同时也给出了试验数据，这些 数据可用于仿真软件的校核，对提高仿真软件预测精度具有重要意义。

Design and Experimental Investigation of a Highly Loaded Single-stage Axial Compressor with Loading Coefficient of 0.5

To explore the design method of highly loaded multi-stage axial compressor, the design and experimental investigation of the inlet stage with loading coefficient of 0.5 was carried out. The inlet stage was designed for a pressure ratio of 2.07 at an airflow of 35.3kg/s with a rotor tip speed of 388 m/s. The methodology of high reaction and contra-swirl was adopted, and the inlet relative velocity of the rotor is supersonic across the full span. Low-aspect-ratio blading was also selected for both the rotor and stator. The rotor aspect ratio is 0.68 and the stator aspect ratio is 1.1. The single-stage compressor was tested in the A219 test facility of AECC Shenyang Engine Research Institute. The performance characteristics at 1.0 and 0.95 relative speed were recorded. The test data show that the airflow is 36.37kg/s, the pressure ratio is 2.121, the efficiency is 0.894 at the work point and the surge margin is 8% at 1.0 relative speed. The design methodology of high reaction and highly loaded inlet stage of the multi-stage compressor was validated. The coordinates of the flow path and the airfoils as well as the experimental data are presented in this paper. These data can be used for the verification of the simulation software, which has a significance to improve the precision of the simulation software.