流体力学与飞行力学

多排反向射流角气膜冷却特性研究

  • 丁阳 ,
  • 常海萍 ,
  • 杜治能
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  • 1. 南京航空航天大学 能源与动力学院, 江苏 南京 210016;
    2. 中航工业沈阳发动机设计研究所, 辽宁 沈阳 110015
丁阳 男,博士研究生。主要研究方向:航空发动机传热。 Tel:025-84892201-2608 E-mail:dy02jx006@163.com;常海萍 女,教授,博士生导师。主要研究方向:航空发动机传热。 Tel:025-84892201-2312 E-mail:chppe@nuaa.edu.cn;杜治能 男,高级工程师。主要研究方向:航空发动机传热。 Tel:024-24287495

收稿日期: 2013-01-08

  修回日期: 2013-04-02

  网络出版日期: 2013-04-26

基金资助

省部级项目

Investigation on Characteristics of Multiple Rows of Opposite Lateral Ejection Angle Film Cooling

  • DING Yang ,
  • CHANG Haiping ,
  • DU Zhineng
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  • 1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. AVIC Shenyang Aeroengine Design and Research Institute, Shenyang 110015, China

Received date: 2013-01-08

  Revised date: 2013-04-02

  Online published: 2013-04-26

Supported by

Province Level Project

摘要

借助正交试验对具有多排反向射流角气膜冷却结构的冷却特性进行了研究分析,采用Realizable k-ε湍流模型和速度分布两层模型进行模拟计算,研究了横向射流角β、开孔率F、长宽比S/P以及吹风比M对冷却特性的影响,并分析了其影响机理。研究结果表明:与单排双射流结构相比,多排反向射流角结构虽然涡量分布不对称,但是依靠持续的冷气注入来维持反向涡对,也可以得到理想的冷却效果。在试验参数范围内,对平均冷却效率影响程度由高到低依次为:开孔率,吹风比,长宽比,横向射流角。对平均对流换热系数影响程度由高到低依次为:吹风比,开孔率,横向射流角,长宽比。综合考虑冷却效率和换热特性,较优的结构与流动参数为β=55°、M=1.2、F=2%、S/P=1.4。

本文引用格式

丁阳 , 常海萍 , 杜治能 . 多排反向射流角气膜冷却特性研究[J]. 航空学报, 2013 , 34(11) : 2472 -2481 . DOI: 10.7527/S1000-6893.2013.0210

Abstract

An investigation on the cooling characteristics of multiple rows of opposite lateral ejection angle film cooling is conducted by means of an orthogonal numerical simulation test. The numerical simulation is conducted by a Realizable k-ε turbulent model and a two-layer velocity zonal model using commercial numerical calculation software. The purpose of the investigation is to reveal the influence of such parameters as lateral ejection angle β, orifice coefficient F, length to width ratio S/P and blowing ratio M, on film cooling. Besides, this paper also tries to find how the above parameters act on cooling respectively. The results show that, compared with the classical counter-rotating vortex pair which appears in the flow field of double-jet film cooling, the vortex pair structure in the downstream of the film-outlet of multiple-rows of opposite lateral ejection angle film cooling is asymmetrical, and cooling is maintained by ejecting cooling jets through rows of holes continuously. It is worth noting that this structure of film cooling achieves excellent cooling effect. The orifice coefficient is found to have the greatest impact on average film cooling effectiveness. Descending order of other parameters, based on their impacts on the average film cooling effectiveness, is: blowing ratio, length to width ratio, and lateral ejection angle, while descending order of the parameters, based on their influence on the heat transfer, is: β=55, M=1.2, F=2%, S/P=1.4.

参考文献

[1] Mayle R E,Camarata F J.Multihole cooling film effectiveness and heat transfer.Journal of Heat Transfer,1975,97(2): 534-538.

[2] Sasaki M,Takahara K,Kumagai T,et al.Film cooling effectiveness for injection from multirow holes.ASME Paper,1978-GT-32,1978.

[3] Andrews G E,Khalifa I M,Asere A A,et al.Full coverage effusion film cooling with inclined holes.ASME Paper,1995-GT-274,1995.

[4] Fric T,Campbell R,Rettig M.Quantitative visualization of full coverage discrete hole film cooling.ASME Paper,1997-GT-328,1997.

[5] Lin Y Z,Song B,Li B,et al.Investigation of film cooling effectiveness of full-coverage inclined multihole walls with different hole arrangements.ASME Paper,2003-GT-38881,2003.

[6] Lin Y Z,Song B,Li B.Investigation of adiabatic wall effectiveness of the inclined multihole wall film cooling with different angles to the wall surface.Acta Aeronautica et Astronautica Sinica,1999,20(3): 201-204.(in Chinese) 林宇震,宋波,李彬.不同倾斜角多斜孔壁冷却方式绝热温比研究.航空学报,1999,20(3): 201-204.

[7] Hu Y P,Ji H H.Effect of porosity of holes array on cooling effectiveness of effusion cooling.Journal of Propulsion Technology,2005,26(1): 28-33.(in Chinese) 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.推进技术,2005,26(1): 28-33.

[8] Tanaka R,Kazari M,Sugimoto T,et al.Double-jet film cooling structure: Japanese.332530.2005-11-17.

[9] Kusterer K,Bohn D,Sugimoto T,et al.Double-jet of cooling air for improved film-cooling.ASME Paper,2006-GT-90854,2006.

[10] Kusterer K,Bohn D,Sugimoto T,et al.Influence of blowing ratio on the double-jet ejection of cooling air.ASME Paper,2007-GT-27301,2007.

[11] Tanaka R,Sugimoto T,Ryu M,et al.Continuing improvements of 20MW-Class GT Kawasaki L20A.ASME Paper,2006-GT-90394,2006.

[12] Kusterer K,Elyas A,Bohn D,et al.Double-jet film-cooling for highly efficient film-cooling with low blowing ratios.ASME Paper,2008-GT-50073,2008.

[13] Kusterer K,Bohn D,Sugimoto T,et al.A parametric study on the influence of the lateral ejection angle of double-jet holes on the film cooling effectiveness for high blowing rations.ASME Paper,2009-GT-59321,2009.

[14] Wang W S,Tang F,Zhao Q J,et al.An investigation of the effect of new-type double-jet film cooling(DJFC) hole on film cooling effectiveness.Journal of Engineering Thermophysics,2011,32(8): 1291-1294.(in Chinese) 王文三,唐菲,赵庆军,等.新型双射流冷却孔对气膜冷却效率影响的研究.工程热物理学报,2011,32(8):1291-1294.

[15] Yu X H,Dong Z R,Liu S L,et al.Study for flow resistance characteristics of the modelled laminated porous wall.Journal of Propulsion Technology,2000,21(4): 47-50.(in Chinese) 郁新华,董志锐,刘松岭,等.层板模型流阻特性的研究.推进技术,2000,21(4): 47-50.

[16] Yang C F,Zhang J Z,Yang W H.Effect of the holes array arrangement on the full coverage film cooling characteristics.Journal of Aerospace Power,2010,25(7): 1524-1529.(in Chinese) 杨成风,张靖周,杨卫华.全覆盖气膜孔阵列方式对冷却特性的影响.航空动力学报,2010,25(7): 1524-1529.

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