| 刘太秋，赵月振，王咏梅，张志博，刘德龙，江建玲.负荷系数0.5 的高负荷单级轴流压气机设计及试验研究[J].航空发动机,2022,48(5):1-39 |
| Design and Experimental Investigation of a Highly Loaded Single-stage Axial Compressor with Loading Coefficient of 0.5 |
| DOI： |
| Key Words:highly loaded supersonic inlet single-stage multistage compressor experiment aeroengine |
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| Abstract: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. |
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