带支板轴对称弯曲管道的流动特性

卜焕先; 谭慧俊; 何小明; 安利平; 黄萍

doi:10.13224/j.cnki.jasp.2016.05.029

带支板轴对称弯曲管道的流动特性

doi: 10.13224/j.cnki.jasp.2016.05.029

1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016;
2. 先进航空发动机协同创新中心, 北京 100191;
3. 中国航空工业集团公司中国燃气涡轮研究院, 成都 610100

基金项目:

中央高校基本科研业务费专项资金(1002-56XQA1385)

详细信息

作者简介:
卜焕先(1990-),男,江苏扬州人,硕士生,主要从事内流空气动力学研究.

中图分类号: V233.1
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- 文章访问数: 802
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- 被引次数: 0
出版历程
- 收稿日期: 2014-08-27
- 刊出日期: 2016-05-28

Flow field characteristics in an axisymmetric bend duct with struts

1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China;
3. China Gas Turbine Establishment, Aviation Industry Corporation of China, Chengdu 610100, China

摘要

摘要: 以一种带支板的轴对称弯曲管道为研究对象,通过试验与仿真手段,获得了有无支板时的内部流场特性,并探讨了尾迹流特性以及出口马赫数的影响规律.研究结果表明:试验数据与仿真结果在趋势和数值上均吻合良好.气流在弯曲管道中先减速后加速,并在"一弯"中心体侧和"二弯"外罩侧附近形成局部低压区;支板对弯曲管道的内部流动结构影响显著,诱导了尾迹流和旋涡的形成,尾迹区附近不同径向位置处的总压分布规律呈现明显差异;此外,随出口马赫数的增大,弯曲管道壁面沿程静压和出口总压恢复系数均降低,而"一弯"和"二弯"处的逆压力梯度增大,故发生边界层分离的风险性增大.
- 轴对称 /
- 弯曲管道 /
- 支板 /
- 尾迹 /
- 旋涡
Abstract: An axisymmetric bend duct was investigated numerically and experimentally to obtain the flow field characteristics in its internal passage with/without struts. The wake characteristics and influences of exit Mach numbers were also analyzed in detail. Results indicate that experiments agree well with simulations. The airflow accelerated at first and then decelerated in the bend duct. And two local low-pressure areas were generated respectively at both leeward sides of the two bends. Moreover, struts had a great effect on the flow structure in the bend duct, inducing wake and vortexes. At different radial positions near the wake, the total pressure distributions were quite different. In addition, with the increase of exit Mach number, the static pressure on the wall surface and the total pressure recovery of the outlet cross section decreased, but the adverse pressure gradients near the two bends increased. So this indicates a greater risk of boundary layer separation.
- axisymmetric /
- bend duct /
- struts /
- wake /
- vortex

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参考文献(18)

[1]	王亚岗,袁化成,郭荣伟.TBCC用轴对称进气道流量控制技术研究[J].推进技术,2013,34(12):1606-1615. WANG Yagang,YUAN Huacheng,GUO Rongwei.Research on mass-flow controlling technology of TBCC axisymmetric inlet[J].Journal of Propulsion Technology,2013,34(12):1606-1615.(in Chinese)
[2]	谢旅荣,郭荣伟.定几何混压式轴对称超声速进气道气动特性数值仿真和试验验证[J].航空学报,2007,28(1):78-83. XIE Lürong,GUO Rongwei.Numerical simulation and experimental validation of flow in mixed compression axisymmetric inlet with fixed geometry[J].Acta Aeronautica et Astronautica Sinica,2007,28(1):78-83.(in Chinese)
[3]	高彬彬.直升机惯性粒子分离器流道结构型线分析与优化[D].上海:上海交通大学,2012. GAO Binbin.Profile analysis and optimization on helicopter inertial particle separator[D].Shanghai:Shanghai Jiao Tong University,2012.(in Chinese)
[4]	FLORIA Paoli,付耀,王彤,等.发动机入口粒子分离器流场数值模拟及流道改进[J].流体机械,2011,39(4):10-16 FLORIA Paoli,FU Yao,WANG Tong,et al.Improvement method of an inlet particle separator based on streamlines analysis[J].Fluid Machinery,2011,39(4):10-16.(in Chinese)
[5]	吴恒刚.无叶片整体式粒子分离器性能研究[D].南京:南京航空航天大学,2008. WU Henggang.Characteristic study on vaneless integral particle separator[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)
[6]	董晓婷.有叶片粒子分离器性能研究[D].南京:南京航空航天大学,2008. DONG Xiaoting.Characteristic study on integral particle separator with vanes[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2008.(in Chinese)
[7]	高丽敏,冯旭栋,陈璇,等.关于压气机过渡段设计方法的探讨[J].航空学报,2013,34(5):1057-1063. GAO Limin,FENG Xudong,CHEN Xuan,et al.The exploration about compressor annular S-shaped duct design[J].Acta Aeronautica et Astronautica Sinica,2013,34(5):1057-1063.(in Chinese)
[8]	向宏辉,张良,陆庆飞,等.进气条件对压气机中介机匣流场影响的试验研究[J].燃气涡轮试验与研究,2011,24(4):15-19. XIANG Honghui,ZhANG Liang,LU Qingfei,et al.Experimental investigation of condition's effect on compressor intermediate casing flow field[J].Gas Turbine Experiment and Research,2011,24(4):15-19.(in Chinese)
[9]	Wlaker A D,Barker A G,Carrotte J F.Numerical design and experimental evaluation of an aggressive S-shaped compressor transition duct with bleed[R].ASME Paper GT2011-45628,2011.
[10]	Duenas C O,Miller R J,Hodson H P,et al.Effect of length on compressor inter-stage duct performance[R].ASME Paper GT2007-27752,2007.
[11]	阙晓斌,候安平,周盛.轴流压缩系统带支板过渡段的轴对称等效方法[J].航空学报,2010,31(9):1715-1722. QUE Xiaobin,HOU Anping,ZHOU Sheng.Axisymmetric equivalent of S-shaped transition duct with struts in axial compression systems[J].Acta Aeronautica et Astronautica Sinica,2010,31(9):1715-1722.(in Chinese)
[12]	李斌,吴亚东,滕金芳,等.压气机中介机匣几何结构的试验验证[J].航空动力学报,2013,28(10):2326-2331. LI Bin,WU Yadong,TENG Jinfang,et al.Experiment validation of geometry of compressor intermediate casing[J].Journal of Aerospace Power,2013,28(10):2326-2331.(in Chinese)
[13]	胡书珍.高低压涡轮过渡段内部复杂流动机理及调控研究[D].北京:中国科学院研究生院,2011. HU Shuzhen.Flow mechanism and flow control investigation within inter turbine duct[D].Beijing:Graduate School of Chinese Academy of Science,2011.(in Chinese)
[14]	Wlaker A D,Barker A G,Carrotte J F.Integrater OGV design for an aggreessive S-shaped compressor transItion duct[R].ASME Paper GT2011-45627,2011.
[15]	陈兵,徐旭,王元光,等.定几何混压式轴对称超声速进气道设计及性能计算[J].航空动力学报,2005,20(3):373-379. CHEN Bing,XU Xu,WANG Yuanguang,et al.Design and performance calculation of the mixed compression fixed-geometry axisymmetric supersonic inlet[J].Journal of Aerospace Power,2005,20(3):373-379.(in Chinese)
[16]	况开鑫.整体式进气整体式粒子分离器特性研究[D].南京:南京航空航天大学,2011. KUANG Kaixin.Investigation on the characteristics of integral inlet particle separator[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2011.(in Chinese)
[17]	Sonoda T,Arima T,Oana M.The influence of downstream passage on the flow within an S-shaped duct[R].ASME Paper 97-GT-83,1997.
[18]	Sonoda T,Arima T,Oana M.The effect of inlet boundary layer thickness on the flow within an annular S-shaped duct[R].ASME Paper 98-GT-260,1998.