进气预旋对环形混合器混合排气系统气动热力性能的影响

吴飞; 谢翌; 邵万仁; 刘坤; 阮登芳; 郑彪

doi:10.13224/j.cnki.jasp.2015.04.017

进气预旋对环形混合器混合排气系统气动热力性能的影响

doi: 10.13224/j.cnki.jasp.2015.04.017

吴飞¹,
谢翌^2,3,,
邵万仁¹,
刘坤³,
阮登芳³,
郑彪³

1. 中国航空工业集团公司沈阳发动机设计研究所, 沈阳 110015;
2. 重庆大学机械传动国家重点实验室, 重庆 400044;
3. 重庆大学汽车工程学院, 重庆 400044

基金项目:

中央高校基本科研业务费(106112013CDJZR13110005)

重庆市基础与前沿研究计划(cstc2013jcyjA00020)

国家自然科学基金青年基金(51405045)

详细信息

作者简介:
吴飞(1982-),男,河南商丘人,工程师,硕士,研究方向为航空发动机排气系统设计.

通讯作者:
谢翌(1983-),男,重庆人,副教授,博士,研究领域为航空发动机排气系统.

中图分类号: V231.3
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出版历程
- 收稿日期: 2013-11-07
- 刊出日期: 2015-04-28

Effect of inlet preswirl on the aerothermodynamic performance of splitter mixing exhaust system

1. Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;
2. The State Key Laboratory of Mechanical Transmissions, Chongqing University, Chongqing 400044, China;
3. College of Automotive Engineering, Chongqing University, Chongqing 400044, China

摘要

摘要: 为了明确混合排气系统内涵进气预旋角对环形混合器混合排气系统气动热力性能的影响,采用基于Navier-Stokes方程组的三维流场数值仿真方法对某环形混合器混合排气系统在不同进气预旋角工况下的流场进行了分析,并将结果同轴向进气的情况进行了对比.结果表明:内、外涵之间剪切层的厚度以及剪切层的扭曲程度随进气预旋角的增加而增大.在环形混合器混合排气系统出口处,随着进气预旋角的增加,热混合效率小幅升高,其中30°进气预旋角模型热混合效率为轴向进气模型的1.36倍;总压恢复系数和环形混合器混合排气系统推力逐渐降低,较轴向进气模型,30°进气预旋角模型总压恢复系数降低了0.0034,而相对推力下降了0.081.
- 环形混合器混合排气系统 /
- 进气预旋 /
- 热混合效率 /
- 总压恢复系数 /
- 推力
Abstract: In order to clarify the effect of core flow inlet preswirl angle of mixing exhaust system on the aerothermodynamic performance of splitter mixing exhaust system, investigation on the flow field of splitter mixing exhaust system at different inlet preswirl angles was carried through the three-dimensional numerical simulation based on Navier-Stokes equations, and the results were compared with flow along the axis. According to the results, the thickness of shear layer increases with the inlet preswirl angle, and it is the same with the twist of shear layer. Besides, at the splitter mixing exhaust system exit, as the inlet preswirl angle increases, the thermal mixing efficiency increase slightly and thermal mixing efficiency of 30 degree inlet preswirl angle model is 1.36 times the model with flow along the axis. Moreover, total pressure recovery coefficient and thrust of splitter mixing exhaust system also decline. Compared with the model with flow along the axis, the total pressure recovery coefficient of 30 degree inlet preswirl angle model falls by 0.0034 and its relative thrust declines by 0.081.
- splitter mixing exhaust system /
- inlet preswirl /
- thermal mixing efficiency /
- total pressure recovery coefficient /
- thrust

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参考文献(15)

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