Anti-icing test technology of low-flow engine intake components in icing wind tunnel

被引：0
|
作者：
Ran L. [1 ]
Xiong J. [1 ,2 ]
Zhao Z. [1 ]
Yi X. [1 ,2 ]
机构：
[1] Key Laboratory of Icing and Anti/De-icing, China Aerodynamics Research and Development Center, Sichuan, Mianyang
[2] State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Sichuan, Mianyang
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 04期
关键词：
anti-icing test; engine intake simulation system; icing wind tunnel; intake flow; low-flow engine intake components;
D O I：
10.13224/j.cnki.jasp.20210576
中图分类号：
学科分类号：
摘要：
In order to meet the requirements of low-flow intake anti-icing test of domestic aeroengines, based on the icing wind tunnel engine intake simulation system, the air intake characteristics of typical low-flow engine intake components were analyzed, and a small-flow engine intake simulation method was developed. A water ring vacuum pump was proposed to solve the problem that the pressure of the suction pipe was greatly reduced due to the large flow resistance of the intake. On this basis, the engine intake simulation system was optimized, and the process of conducting the anti-icing test of the low-flow engine intake components in the icing wind tunnel was established, which was applied to the anti-icing test of a certain type of low-flow engine intake components. The results showed that the engine intake simulation system met the requirements of the anti-icing test of the low-flow engine intake components, and the control accuracy of the intake flow reached ±0.05 kg/s(±0.33%FS). The flow change during the test can be used to identify the anti-icing effect. The relevant research can provide a reference for the design and optimization of the engine intake simulation system and the assessment of the anti-icing characteristics of the low-flow engine intake components. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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