高转速旋转篦齿流动与温升特性实验研究

王志伟; 查天衡; 刘博文; 陈燕; 林阿强; 刘高文

doi:10.7527/S1000-6893.2025.31534

航空学报 >

0 1 - 0

DOI: https://doi.org/10.7527/S1000-6893.2025.31534

高转速旋转篦齿流动与温升特性实验研究

王志伟 ,
查天衡 ,
刘博文 ,
陈燕 ,
林阿强 ,
刘高文

展开

1. 西北工业大学
2. 中国航发商用发动机有限责任公司
3. 中国航发湖南动力机械研究所

收稿日期: 2024-11-14

修回日期: 2025-04-09

网络出版日期: 2025-04-10

基金资助

国家自然科学基金

收起

Experimental study on flow and windage heating characteristics of high-speed rotating laby-rinth

WANG Zhi-Wei ,
CHA Tian-Heng ,
LIU Bo-Wen ,
CHEN Yan ,
LIN A-Qiang ,
LIU Gao-Wen

Expand

Received date: 2024-11-14

Revised date: 2025-04-09

Online published: 2025-04-10

Supported by

National Natural Science Foundation of China

Fold

摘要

封严篦齿系统的性能对航空发动机的效率提升和功耗控制具有重要意义。设计并搭建了高转速旋转篦齿实验台，系统地研究了几何参数与气动参数对台阶型斜齿泄漏、温升和旋流特性的影响，定量分析评估各参数对篦齿封严性能的影响机理。实验结果表明：在所研究的工况下，篦齿间隙从0.17 mm增加到0.61 mm，流量系数随着篦齿间隙的增大先降低后升高；当旋转马赫数为0.348、压比为1.1，进气温度从16.5 ℃升高到100 ℃，温升系数增加幅度为49.4%；当设计间隙为0.6 mm、压比为2.0时，温升系数从0.371增加到0.764，增加幅度为105.9%，出口旋转比增加幅度为14.8%；流量系数随着压比的升高呈线性增加的趋势，而温升系数与出口旋转比随压比的升高而减小；对于设计间隙为0.6 mm，压比从1.1提高至2.0，当旋转马赫数为0.418时，流量系数增加幅度为26.5%，温升系数与出口旋转比减小幅度分别为27.9%、11.1%。

关键词： 航空发动机; 篦齿封严; 泄漏特性; 温升特性; 旋流特性; 实验测量

本文引用格式

王志伟 , 查天衡 , 刘博文 , 陈燕 , 林阿强 , 刘高文 . 高转速旋转篦齿流动与温升特性实验研究[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.31534

Abstract

The performance of sealing labyrinth systems significantly impacts aero-engine efficiency and power consump-tion. This study investigates the effects of geometric and aerodynamic parameters on the leakage, windage heat-ing, and swirl characteristics of stepped-type inclined labyrinth teeth using a high-speed rotating test rig. The influence mechanism of each parameter on sealing performance is quantitatively analyzed and evaluated. Exper-imental results show: within the studied range, the seal clearance increases from 0.17 mm to 0.61 mm ,and flow coefficient initially as the seal clearance increase, before subsequently. At a rotating Mach number of 0.348 and a pressure ratio of 1.1, increasing the inlet temperature from 16.5 °C to 100 °C results in a 49.4% increase in the windage heating coefficient. At a design clearance of 0.6 mm and a pressure ratio of 2.0, windage heating coeffi-cient increases by 105.9%, from 0.371 to 0.764, as rotating Mach number increases. Concurrently, outlet swirl ratio exhibits a 14.8% increase. The flow coefficient exhibits a linear increase with increasing pressure ratio, whereas windage heating coefficient and outlet swirl ratio both decrease as the pressure ratio increases. For a design clearance of 0.6 mm and a rotating Mach number of 0.418, increasing the pressure ratio from 1.1 to 2.0 results in a 26.5% increase in the flow coefficient, while the windage heating coefficient and outlet swirl ratio decrease by 27.9% and 11.1%, respectively.

Key words： Aero-engine; Labyrinth seal; Leakage characteristic; Windage heating characteristic; Swirl charac-teristic; Experimental measurement

参考文献

[1] Hu S, Feng W, Gong W, Zou T, Gui P. Research on internal flow field analysis and power loss modeling of the expansion seal ring[J]. Physics of Fluids, 2023, 35 (11) :113116. [2] 韩灵生,程奕舜,段鑫博,等.考虑空化作用的超低温流体迷宫密封特性[J/OL].航空学报,1-18[2024-11-10].http://kns.cnki.net/kcms/detail/11.1929.V.20240910.1605.003.html. HAN L S, CHEN Y S, DUAN X B, et al. Cryogentic fluid labyrinth sealing characteristics considering cavitation effect[J/OL]. Acta Aeronautica et Astronautica Sinica 1-18[2024-11-10]. http://kns.cnki.net/kcms/detail/11.1929.V.20240910.1605.003.html.(in Chinese). [3] 张延超,陈国定,申晓龙.指尖密封动态性能分析与泄漏量计算[J].航空学报,2009,30(11):2193-2199. ZHANG Y C, CHEN G D, SHEN X L. Analysis of dynamic performance and leakage for finger seal[J]. Acta Aeronautica et Astronautica Sinica, 2009,30(11):2193-2199. (in Chinese). [4] 肖传民,田立敏,李明文,等.级间篦齿泄漏对压气机性能的影响[J]. 机械工程与自动化, 2024, (05): 38-40. XIAO C M, TIAN L M, LI M W, et al. Effect of interstage labyrinth leakage on compressor performance[J]. Mechanical Engineering & Automation, 2024, (05): 38-40 (in Chinese). [5] Sturgess G, Datta P. Application of CFD to gas turbine engine secondary flow systems - the labyrinth seal[C]. AIAA 1988-3203. 24th Joint Propulsion Conference. July 1988. [6] Martin H M. Labyrinth Packings[J]. Engineering, 1908: 35-36. [7] Stodola A. Steam and Gas Turbines 6th[M]. 1927. [8] Vermes G. A Fluid Mechanics Approach to the Laby-rinth Seal Leakage Problem[J]. Journal of Engineering for Power, 1961, 83(2): 161-169. [9] Wittig. Scaling Effects on Leakage Losses in Labyrinth Seals[J]. Journal of Engineering for Power, 1983, 105(2): 305-309. [10] Willenborg K, Kim S, Wittig S. Effects of Reynolds number and pressure ratio on leakage loss and heat transfer in a stepped labyrinth seal[J]. Journal of Tur-bomachinery, 2001,123(4): 815-822. [11] Willenborg K, Schramm V, Kim S, et al. Influence of a honeycomb facing on the heat transfer in a stepped labyrinth seal[C]. Proc. ASME Turbo Expo2000: Pow-er for Land, Sea, and Air. 3 (2000), Paper No: 2000-GT-0290. [12] Denecke J, Schramm V, Kim S. Influence of Rub-Grooves on labyrinth seal leakage[J]. Journal of Tur-bomachinery, 2003, 125(2): 387-393. [13] Denecke J, F?rber J, Dullenkopf K. Dimensional anal-ysis and scaling of rotating seals[C]. Proc. ASME Tur-bo Expo 2005: Power for Land, Sea, and Air, 3 (2005), Paper No: GT2005-68676. [14] Denecke J, Dullenkopf K, Wittig S. Experimental in-vestigation of the total temperature increases and swirl development in rotation labyrinth seals[C]. Proc. ASME Turbo Expo2005: Power for Land, Sea, and Air, 3 (2005), Paper No: GT2005-68677. [15] Denecke J, F?rber J, Dullenkopf K. Interdependence of discharge behavior, swirl development and total tem-perature increase in rotation labyrinth seals[C]. Proc. ASME Turbo Expo2008: Power for Land, Sea, and Air. 4 (2008), Paper No: GT2008-51429. [16] McGreehan W F, Ko S H. Power dissipation in smooth and honeycomb labyrinth seals[C]. Proc. ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. 1 (1989), Paper No: 89-GT-220. [17] Millward J A, Edwards M F. Windage heating of air passing through labyrinth seals[J]. Journal of Tur-bomachinery,1996, 118(2) : 414-419. [18] 吴丁毅, 刘振侠. 交错式篦齿封严特性的实验研究[J]. 推进技术, 1997(02): 87-90. WU D Y, LIU Z X. An experimental investigation on sealing characteristics of interlacing labyrinth[J]. Jour-nal of Propulsion Technology, 1997(02): 87-90 (in Chinese). [19] 吴丁毅. 台阶式篦齿密封特性的实验研究[J]. 流体机械, 1995(11): 7-10. WU D Y. Experimental study of sealing characteristics of stepped labyrinth[J]. Fluid Machinery, 1995(11): 7-10 (in Chinese). [20] 吴丁毅. 直通式篦齿封严特性的实验研究[J]. 推进技术, 1997(03): 79-81, 97. WU D Y. An experimental investigation on seal char-acter of straight-through labyrinth[J]. Journal of Pro-pulsion Technology, 1997(03): 79-81, 97 (in Chinese). [21] 徐再清, 朱惠人, 白江涛. 航空发动机篦齿封严特性数值分析[J]. 机械设计与制造, 2008(06): 31-33. XU Z Q, ZHU H R, BAI J T. Numerical analysis of labyrinth seal aircraft engines[J]. Machinery Design and Manufacture, 2008(06): 31-33 (in Chinese). [22] 张效伟, 朱惠人, 张霞等. 直通型篦齿泄漏的特性试验[J]. 航空动力学报, 2011, 26(09): 1970-1974. ZHANG X W, ZHU H R, ZHANG X, et al. Experiment on discharge characteristics of straight-through laby-rinth[J]. Journal of Aerospace Power, 2011, 26(09): 1970-1974 (in Chinese). [23] 刘高文, 蒋兆午, 务卫涛等. 基于数值模拟的矩形凹槽对直通型篦齿封严特性影响研究[J]. 推进技术, 2013, 34(02): 181-186. LIU G W, JIANG Z W, WU W T. Investigation on ef-fects of rectangular groove on leakage of straight-through labyrinth seal based on numerical simula-tion[J]. Journal of Propulsion Technology, 2013, 34(02): 181-186 (in Chinese). [24] 刘高文, 孔晓治, 陈凯等. 转动和旋流对压气机级间封严影响的数值研究[J]. 推进技术, 2014, 35(12): 1687-1693. LIU G W, KONG X Z, CHEN K, et al. Numerical study for effects of rotation and swirl on labyrinth seal-ing in a compressor stator well[J]. Journal of Propul-sion Technology, 2014, 35(12): 1687-1693 (in Chinese). [25] 刘高文, 陈凯, 刚铁等. 压比和雷诺数对压气机级间篦齿封严流动特性的影响[J]. 航空动力学报, 2015, 30(07): 1554-1560. LIU G W, CHEN K, GANG T, et al. Influence of pres-sure ratio and Reynolds number on flow characteristics of labyrinth seal in compressor stator well[J]. Journal of Aerospace Power, 2015, 30(07): 1554-1560 (in Chi-nese). [26] 孔晓治, 刘高文, 陈凯. 齿位置对压气机级间封严影响的数值研究[J]. 航空动力学报, 2015, 30(12): 2925-2933. KONG X Z, LIU G W, CHEN K. Numerical study on the influence of tooth position in compressor stator well sealing[J]. Journal of Aerospace Power, 2015, 30(12): 2925-2933 (in Chinese). [27] 孔晓治, 刘高文, 雷昭等. 齿型对压气机级间封严特性影响的实验研究[J]. 推进技术, 2018, 39(09): 2085-2093. KONG X Z, LIU G W, LEI Z, et al. Experimental in-vestigation for effects of tooth shapes on compressor Inter-Stage steal[J]. Journal of Propulsion Technology, 2018, 39(09): 2085-2093 (in Chinese). [28] 孔晓治, 刘高文, 雷昭等. 转速对压气机级间篦齿封严影响的实验[J]. 航空动力学报, 2016, 31(07): 1575-1582. KONG X Z, LIU G W , LEI Z, et al. Experiment on in-fluence of rotational speeds on labyrinth seal in com-pressor stator well[J]. Journal of Aerospace Power, 2016, 31(07): 1575-1582 (in Chinese). [29] 郭海龙, 冯青, 刘高文等. 考虑间隙变化的旋转篦齿流动特性实验[J]. 航空动力学报, 2018, 33(07): 1779-1786. GUO H L, FENG Q, LIU G W, et al. Experiment on flow characteristics in rotating labyrinth with consid-eration of clearance change[J]. Journal of Aerospace Power, 2018, 33(07): 1779-1786 (in Chinese). [30] 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[J]. 航空动力学报, 2013, 28(06): 1402-1408. WANG P F, GUO W, ZHANG J Z, et al. Experimental investigation and numerical analysis of windage heat-ing in rotating labyrinth seals[J]. Journal of Aerospace Power, 2013, 28(06): 1402-1408 (in Chinese). [31] 务卫涛. 压气机级间篦齿封严结构的流动特性研究[D]. 西安: 西北工业大学硕士学位论文, 2014. WU W T. Investigations on the flow characteristics of the stator well sealing[D]. Xi’an: Northwestern Poly-technical University, 2014 (in Chinese). [32] 李驰, 张勃, 马壮等．台阶式斜篦齿封严压降与风阻温升数值分析[J]. 润滑与密封, 2024, 49(06):29-35. LI C, ZHANG B, MA Z, et al. Numerical analysis on pressure drop and wind resistance temperature rise of stepped inclined grate teeth sealing[J]. Lubrication Engineering, 2024, 49(06):29-35 (in Chinese). [33] 徐文峰,邹世龙,任国哲,等.篦齿封严结构对压气机叶栅性能影响研究[J/OL].航空动力学报,1-9[2024-11-05].https://doi.org/10.13224/j.cnki.jasp.20240075. XU W F, ZOU S L, REN G Z, et al. Study on the influ-ence of the labyrinth seal structure on the compressor cascade performance[J/OL]. Journal of Aerospace Power, 1-9[2024-11-05]. https://doi.org/10.13224/j.cnki.jasp.20240075 (in Chi-nese). [34] 任国哲,卢德正,孙丹,等.结构参数对篦齿封严流动特性与最佳封严齿数影响研究[J/OL]. 推进技术, 1-13[2024-11-05]. https://doi.org/10.13675/j.cnki.tjjs.2312084. REN G Z， LU D Z, SUN D, et al. Effects of structur-al parameters on flow characteristics and optional number of sealing teeth of labyrinth seals[J]. Journal of Propulsion Technology, 1-13[2024-11-05]. https://doi.org/10.13675/j.cnki.tjjs.2312084 (in Chi-nese).

Options

文章导航

模态框（Modal）标题

摘要

本文引用格式

Abstract

参考文献