多斜孔壁与机加环气膜冷却燃烧室面换热特性数值研究

张勃; 吉洪湖; 杨芳芳; 郑妹; 程明

多斜孔壁与机加环气膜冷却燃烧室面换热特性数值研究

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
中国航空工业集团公司沈阳发动机设计研究所预研总体部, 沈阳 110085

计量
- 文章访问数: 1870
- HTML浏览量: 312
- PDF量: 663
- 被引次数: 0
出版历程
- 收稿日期: 2011-05-11
- 修回日期: 2012-02-24
- 刊出日期: 2012-04-28

Numerical investigation of heat transfer characteristics of effusion cooling and machinery film cooling combustors

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
System Engineering Department, Shenyang Aeroengine Research Institute, Aviation Industry Corporation of China, Shenyang 110085, China

摘要

摘要: 数值研究了在燃烧室实际工作条件下,多斜孔壁冷却燃烧室和机加环气膜冷却燃烧室的流动、换热特性,比较分析了内、外壁温度场以及冷却流量的变化.研究发现,采用多斜孔壁后,壁面冷却效果得到强化,相比机加环气膜冷却燃烧室,燃烧室前段壁温略有升高,而后段受到气膜冷却效果增强的影响,壁面温度有所降低,壁面温度梯度明显减小.流量系数明显减小,冷却空气量降低23%,用于组织燃烧用气量增加.多斜孔壁冷却技术可以为高温升燃烧室的发展提供有效的冷却技术.
- 多斜孔壁冷却 /
- 燃烧室 /
- 高温升 /
- 强化换热 /
- 流量系数
Abstract: The flowing and heat transfer characteristics of machinery film cooling and effusion cooling combustors were numerically investigated.The results show that in the effusion combustor,heat transfer is enhanced,and temperature of the front wall of combustor increases,while temperature of the back wall decreases,which cause the temperature gradient decrease.The flow efficiency decreases;the amount of cooling gas is reduced by 23% compared with the machinery one.
- effusion cooling /
- combustor /
- high temperature arising /
- heat transfer enhancement /
- flow coefficient

HTML

参考文献(13)

[1]	Lefebvre A H.Gas turbin combustion[M] New York:McGraw-Hill,1983.
[2]	Mellor A M.Design of modern turbine combustor [M].New York:Academic Press,1990.
[3]	胡娅萍,吉洪湖.孔阵排列疏密度对致密多孔壁冷却效果的影响[J].推进技术,2005,26(1):28-33. HU Yaping,JI Honghu.Effect of porosity of holes array on cooling effectiveness of effusion cooling[J].Journal of Propulsion Technology,2005,26(1):282-283.(in Chinese)
[4]	陈焱,吉洪湖,胡娅萍.致密微孔壁复合冷却对流换热系数研究[J].工程热物理学报,2005,26(3):489-491. CHEN Yan JI Honghu HU Yaping.Study of convective heat transfer coefficient of effusion cooling[J].Journal of Engineering Thermophysics,2005,26(3):489-491.(in Chinese)
[5]	徐剑,许全宏,林宇震,等.火焰筒多斜孔冷却方式壁温梯度和冷却效率试验[J].航空动力学报,2008,23(3):425-429. XU Jian,XU Quanhong,LIN Yuzhen,et al.Experimental investigation of the temperature gradient and cooling efficiency for effusion wall cooling methods on combustion liner[J].Journal of Aerospace Power,2008,23(3):425-429.(in Chinese)
[6]	董志锐,周四平,王舟山.复杂边界条件下的多层多孔壁温度场的计算模型[J].航空学报,1995,20(5):404-408. DONG Zhirui,ZHOU Siping,WANG Zhoushan,Calculating model for temperature field of multiple-layer and multiple-hole wall under complex boundary conditions[J].Acta Aeronautica et Astronautica Sinica,1995,20(5):404-408.(in Chinese)
[7]	朱长青,董志锐.钻孔式气膜冷却火焰筒壁温计算[J].航空学报,1991,12(3):206-209. ZHU Changqing,DONG Zhirui.Calculation of wall temperature of flame tube with hole-drilled flame cooled construction[J].Acta Aeronautica et Astrynautica,Sinica,1991,12(3):206-209.(in Chinese)
[8]	韩振兴,朱谷君,冀守礼,等.气膜冷却燃烧室火焰筒二维壁温分布计算[J].航空动力学报,1995,10(1):83-86. HAN Zenxing,ZHU Gujun,JI Shouli,et al.Calculation of 2D wall temperature distribution for film cooled flame tube of combustor chamber[J].Journal of Aerospace Power,1995,10(1):83-86.(in Chinese)
[9]	党新宪,赵坚行,颜应文,等.双旋流器燃烧室壁温试验[J]. 航空动力学报,2010,25(6):1227-1232. DANG Xinxian,ZHAO Jianxing,YAN Yingwen,et al.Experiment of wall temperature in a two-stage swirler combustor[J].Journal of Aerospace Power,2010,25(6):1227-1232.(in Chinese)
[10]	张荣春,樊未军,邢菲.环形级间驻涡燃烧室壁温分布试验[J],航空动力学报,2010,25(6):1238-1244. ZHANG Rongchun,FAN Weijun,XING Fei.Experimental study of wall temperature distribution on annular interstage trapped vortex combustor[J].Journal of Aerospace Power,2010,25(6):1238-1244.(in Chinese)
[11]	左渝钰,张宝诚.航空发动机主燃烧室火焰筒壁冷却的研究[J].航空发动机,2002(4):38-43. ZUO Yuyu,ZHANG Baocheng.Investigation of combustion liner wall cooling in gas turbine combustor[J].Aeroengine,2002(4):38-43.(in Chinese)
[12]	苏克.某型发动机燃烧室火焰筒壁温分析[J].航空发动机,1993(3):22-32.
[13]	Sellers J P Jr.Gaseous film cooling with multiple injection stations[J].AIAA Journal,1963,1(9):2145-2156.