Analysis of method of air mass flow measurement based on array of critical flow Venturi nozzle in high-altitude simulation facility

被引：0
|
作者：
Su J. [1 ,2 ]
Tian J. [2 ]
Tang Z. [1 ]
Yuan S. [2 ]
Li T. [2 ]
Li C. [3 ]
机构：
[1] Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] Science and Technology on Altitude Simulation Laboratory, Sichuan Gas Turbine Establishment, Aero Engine Corporation of China, Mianyang, 621000, Sichuan
[3] National Institute of Metrology, Beijing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2019年 / 34卷 / 10期
关键词：
Air mass flow; Array of critical flow Venturi nozzle(ACFVN); Civil aircraft power; Device design; High-altitude simulation facility;
D O I：
10.13224/j.cnki.jasp.2019.10.008
中图分类号：
学科分类号：
摘要：
In order to meet the accurate measurement of air flow under the low flow intake conditions of the engine high-altitude test, reduce the influence of the air flow surface layer in the intake duct, and weaken the correlation between the air flow measurement and the tested engine, the working characteristics of the single piece/combined critical flow Venturi nozzle (CFVN) were analyzed, and the calculation method of the air flow of the array of critical flow Venturi nozzle (ACFVN) was expounded. The calculation method of combined CFVN was also given. The combination structure was designed according to the given test engine and the size of the high-altitude cabin. The control method and test layout of the combined CFVN in high-altitude cabin were obtained. The design and application methods of the combined nozzles were verified by small-sized nozzles. The results show that the method of opening and closing the nozzles and adjusting the intake pressure could be applied in the high-altitude cabin, the test layout meets the measurement requirements, and the Turbulence of engine intake flow is better than 0.3%, meeting the requirements of engine high altitude simulation test. © 2019, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：2149 / 2157
页数：8
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