旋转封严篦齿风阻温升的试验研究与数值分析

王鹏飞; 郭文; 张靖周

旋转封严篦齿风阻温升的试验研究与数值分析

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中国燃气涡轮研究院, 成都 610500

计量
- 文章访问数: 1894
- HTML浏览量: 122
- PDF量: 928
- 被引次数: 0
出版历程
- 收稿日期: 2012-06-01
- 刊出日期: 2013-06-28

Experimental investigation and numerical analysis of windage heating in rotating labyrinth seals

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
China Gas Turbine Establishment, Aviation Industry Corporation of China, Chengdu 610500, China

摘要

摘要: 选取具有典型封严结构的真实尺寸台阶型封严篦齿,通过高速旋转条件下的风阻温升特性试验,进行了进出口压比(1.05~2.8)、封严间隙与齿尖厚度比(相对封严间隙)(2.4~4.0)、雷诺数(1900~28000)及转速(0~12000r/min)等参数对篦齿泄漏流风阻温升的影响研究.并基于试验条件,采用renormalization group(RNG)k-ε湍流模型,对同一篦齿的风阻温升特性进行了数值计算.结果表明:篦齿泄漏流温升随进出口压比、雷诺数、封严间隙与齿尖厚度比的增加而减小,但随转速的增加而增大.数值计算结果与试验数据吻合良好,台阶型封严篦齿第1道和第2道封严齿内的风阻温升最为显著,前两道封严齿内的温升占总温升的60%. 根据试验结果,提出了计算台阶型篦齿泄漏流温升的经验公式,其计算结果与试验数据具有较好的符合性.
- 空气系统 /
- 篦齿 /
- 风阻温升 /
- 泄漏流 /
- 湍流模型
Abstract: Experiments were conducted to investigate the windage heating characteristics in real size models of stepped labyrinth seals.The change in total temperature across the labyrinth seal was measured in a high speed test facility at different pressure ratios (1.05-2.8),relative sealing clearances(2.4-4.0),Reynolds numbers(1900-28000) and rotational speeds (0-12000r/min).Based on the experiments,the renormalization group (RNG) k-ε turbulence model was used to compute the windage heating characteristics of the same stepped labyrinth seals.The results indicate that the temperature rise decreases with the increases of pressure ratio,Reynolds number and relative sealing clearance,and it increases with the increase of rotational speed.In addition,the numerical simulation satisfies the experiment.The most of the windage heating takes place in the first half of the seals,and the value of temperature rise is about 60% in the first two tooth chambers.An empirical expression for the windage heating coefficient was obtained and it fits the experimental results well.
- air system /
- labyrinth seals /
- windage heating /
- leakage airflow /
- turbulence model

HTML

参考文献(16)

[1]	Stocker C.Aerodynamic performance of conventional and advanced design labyrinth seals with solid-smooth,abradable and honeycomb lands[R].NASA CR-135307,1977.
[2]	Haaser F, Jack J, McGreehan W F. Windage rise and flowpath gas ingestions in turbine rim cavities[R].ASME Paper 87-GT-164, 1987.
[3]	McGreehan W, Ko S.Power dissipation in smooth and honeycomb labyrinth seals.ASME Paper 89-GT-220,1989.
[4]	Millward J,Edwards M.Windage heating of air passing through labyrinth seals[J].Journal of Turbomachinery,1996,118(3):414-419.
[5]	Lewis L.In-engine measurements of temperature rises in axial,compressor shrouded stator cavities[R].ASME Paper GT2002-30245,2002.
[6]	Denecke J,Dullenkopf K,Wittig S.Experimental investigation of the total temperature increase and swirl development in rotating labyrinth seals[R].ASME Paper GT2005-68677,2005.
[7]	Irebert R,Margaret P.Continued investigation of leakage and power loss test results for competing turbine engine seals.AIAA 2006-4754,2006.
[8]	纪国剑,吉洪湖,黄云霞,等.直通篦齿蜂窝封严结构的风阻特性试验[J].航空动力学报,2011,26(12):2648-2654. JI Guojian,JI Honghu,HUANG Yunxia,et al.Experiment investigation of windage heating on straight-through labyrinth seals with honeycomb bush[J].Journal of Aerospace Power,2011,26(12):2648-2654.(in Chinese)
[9]	Scherer T,Waschka W,Wittig S.Numerical predictions of high-speed rotating labyrinth seal performance:influence of rotation on power dissipation and temperature rise[R].Athens,Greece:ICHMT 1992 International Symposium on Heat Transfer,in Turbomachinery,1992:1514-1522.
[10]	Nayak K C,Musthafa T.The effects of tooth tip wear and its axial displacement in rub-grooves on leakage and windage heating of labyrinth seals with honeycomb lands.AIAA 2007-5736,2007.
[11]	Nayak K C,Musthafa T,Sudipta D.The effects of rub-grooves on leakage and windage heating in labyrinth seals with honeycomb lands[R].AIAA 2007-5737,2007.
[12]	宴鑫,李军,丰镇平.高速旋转光滑面迷宫密封内流动和传热特性的研究[J].动力工程,2008,28(2):190-194. YAN Xin,LI Jun,FENG Zhenping.Investigations on the flow and heat transfer characteristics in high rotating smooth labyrinth seals[J].Journal of Power Engineering,2008,28(2):190-194.(in Chinese)
[13]	宴鑫,李军,丰镇平.预旋对蜂窝密封和迷宫密封内流动传热特性影响[J].航空动力学报,2009,24(4):772-776. YAN Xin,LI Jun,FENG Zhenping.Influence of inlet pre-swirl on discharge and heat transfer characteristics of honeycomb and smooth labyrinth seals[J].Journal of Aerospace Power,2009,24(4):772-776.(in Chinese)
[14]	宴鑫,李军,丰镇平.预旋对迷宫密封内流动传热特性影响的研究[J].热能动力工程,2008,23(1):7-10. YAN Xin,LI Jun,FENG Zhenping.A study of influence of inlet pre-swirl on flow and heat transfer characteristics of a labyrinth seal[J].Journal of Engineering for Thermal Energy and Power,2008,23(1):7-10.(in Chinese)
[15]	YAN Xin,LI Jun,SONG Liming,et al.Investigations on the discharge and total temperature increase characteristics of the labyrinth seals with honeycomb and smooth lands.ASME Paper GT2008-50399,2008.
[16]	王鹏飞,刘玉芳,郭文,等.直通式篦齿封严特性的数值分析和试验研究[J].燃气涡轮试验与研究,2009,22(1):32-36. WANG Pengfei,LIU Yufang,GUO Wen,et al.Numerical analysis and experimental investigation of straight-through labyrinth sealing characteristic[J].Journal of Gas Turbine Experiment and Research,2009,22(1):32-36.(in Chinese)