Experiment on flow characteristics of a reverse-flow combustor

被引：0
|
作者：
Zhai W. [1 ]
Hu G. [2 ]
Peng J. [1 ]
Jin W. [2 ]
Tang C. [2 ]
Li J. [2 ]
机构：
[1] Hunan Aviation Powerplant Research Institute, Aero Engine Corporation of China, Zhuzhou, 412002, Hunan
[2] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2019年 / 34卷 / 10期
关键词：
Non-reacting flow field; Particle image velocimetry(PIV); Reacting flow field; Reverse-flow combustor; Total pressure loss coefficient;
D O I：
10.13224/j.cnki.jasp.2019.10.001
中图分类号：
学科分类号：
摘要：
To reveal the flow field differences and flow characteristics between the non-reacting flow and the reacting flow, the flow fields at different sections of a reverse-flow combustor with different total pressure loss conditions were measured and investigated through particle image velocimetry (PIV) measurement technology. The result showed that: with the increase of the total pressure loss, the non-reacting flow field in the specific section was consistent, the penetrating depth,jet angle,reverse-zone position and size,and the flow line were all similar. Otherwise, the velocity rose. And the reacting flow field in the specific section was also consistent with the increase of the total pressure loss. Also there were some differences from the reacting flow field to the non-reacting flow field in the same total pressure loss condition. The relative motion of fuel injection and airflow will affect the flow field structure of the head zone of the combustor, and the velocity of reaction is faster than the non-reaction. © 2019, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：2081 / 2090
页数：9
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