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CLC number: TG115.5; V250

On-line Access: 2016-12-06

Received: 2016-05-10

Revision Accepted: 2016-08-09

Crosschecked: 2016-11-10

Cited: 1

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Citations:  Bibtex RefMan EndNote GB/T7714


Na Zhang


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Journal of Zhejiang University SCIENCE A 2016 Vol.17 No.12 P.947-960


Investigation of high-speed rubbing behavior of labyrinth-honeycomb seal for turbine engine application

Author(s):  Na Zhang, Hai-jun Xuan, Xiao-jun Guo, Chao-peng Guan, Wei-rong Hong

Affiliation(s):  High-speed Rotating Machinery Laboratory, College of Energy Engineering, Zhejiang University, Hangzhou 310027, China; more

Corresponding email(s):   marine@zju.edu.cn

Key Words:  Labyrinth-honeycomb seal, Aeroengine shrouded turbine blade, Abradability, Rubbing mechanism, Rubbing interaction

Na Zhang, Hai-jun Xuan, Xiao-jun Guo, Chao-peng Guan, Wei-rong Hong. Investigation of high-speed rubbing behavior of labyrinth-honeycomb seal for turbine engine application[J]. Journal of Zhejiang University Science A, 2016, 17(12): 947-960.

@article{title="Investigation of high-speed rubbing behavior of labyrinth-honeycomb seal for turbine engine application",
author="Na Zhang, Hai-jun Xuan, Xiao-jun Guo, Chao-peng Guan, Wei-rong Hong",
journal="Journal of Zhejiang University Science A",
publisher="Zhejiang University Press & Springer",

%0 Journal Article
%T Investigation of high-speed rubbing behavior of labyrinth-honeycomb seal for turbine engine application
%A Na Zhang
%A Hai-jun Xuan
%A Xiao-jun Guo
%A Chao-peng Guan
%A Wei-rong Hong
%J Journal of Zhejiang University SCIENCE A
%V 17
%N 12
%P 947-960
%@ 1673-565X
%D 2016
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A1600367

T1 - Investigation of high-speed rubbing behavior of labyrinth-honeycomb seal for turbine engine application
A1 - Na Zhang
A1 - Hai-jun Xuan
A1 - Xiao-jun Guo
A1 - Chao-peng Guan
A1 - Wei-rong Hong
J0 - Journal of Zhejiang University Science A
VL - 17
IS - 12
SP - 947
EP - 960
%@ 1673-565X
Y1 - 2016
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A1600367

The labyrinth-honeycomb seal has been widely used in gas turbine engines as an abradable gas path seal to protect the rotor from wear and damage in rubbing interaction. It usually works with a stepped labyrinth because the knife-edged tips could produce a special dynamic sealing system, and then the minimum clearance is possible between the rotor and stationary component. To investigate the high-speed rubbing behavior between a Hastelloy-X honeycomb material and a GH4169 double stepped labyrinth, nine rubbing tests were conducted using a high-speed abrasion test rig while the blade tip speed varied from 150 to 450 m/s, and the incursion rate from 120 to 360 μm/s. The abradability of honeycomb made from Hastelloy-X was fully verified by analyzing the visual rubbing observations, rubbing forces, and impact acceleration. It is shown that compression deformation happens to the honeycomb material during the rubbing process with the labyrinth blade except for a simple cutting mechanism, which is mainly affected by the parameter of incursion rate. Thermal ablation and oxidation were the main damage occurring on the labyrinth tip and appeared more obviously at a higher blade tip speed. Rubbing forces and impact acceleration were obtained from a piezoelectric dynamometer and acceleration sensor during the rubbing process. At a blade tip speed of 300 m/s and incursion rate of 360 μm/s, radial and tangential forces show their maximum values of 716 N and 871 N, respectively. The peak value of acceleration presents 341g with the highest blade tip speed of 450 m/s and the highest incursion rate of 360 μm/s. All testing results provide a great deal of effective information on high-speed rubbing behavior for the abradablility evaluation of a honeycomb.


创新点:1. 成功研制了模拟封严材料高速碰磨行为的可磨耗试验机,最高叶尖线速度可达520 m/s;2. 进行了不同试验条件下的高速碰磨试验,验证了蜂窝材料的可磨耗性能;3. 通过高速碰磨试验,掌握篦齿叶片和金属蜂窝的磨耗机理;4. 获得了高速碰摩力和冲击加速度数据,对应用具有指导作用。
方法:1. 研制高速可磨耗试验机;径向进给系统驱动封严试样主动与高速旋转的模拟叶片接触并发生高速碰磨作用;试验机可模拟的最高叶尖线速度为520 m/s,进给速率为5~1000 μm/s。2. 在可磨耗试验机上进行不同叶尖线速度和进给速率条件下的高速碰磨试验,通过对试验现象以及试验后金属蜂窝和篦齿叶片的磨损形貌进行分析,了解高速碰磨过程中的磨损机理。3. 通过三向测力传感器对试验中的高速碰磨力进行测量,分析碰摩力的变化规律。4. 通过加速度传感器测量瞬时冲击响应,了解冲击作用的大小。
结论:1. 高速碰磨时,金属蜂窝会发生切削和挤压变形,进给速率对挤压变形具有重要影响。2. 高速碰磨 时篦齿与蜂窝的接触区域会产生摩擦火花,导致篦齿叶尖发生烧蚀和氧化,摩擦热的聚集会导致蜂窝材料在被切削时发生涂抹,同时伴随有蜂窝材料向篦齿叶尖的转移。3. 随着碰磨时间的延长,摩擦热逐渐增多,且在高叶尖线速度条件下更加明显。4. 测试到的碰摩力曲线可以分为四个典型阶段:碰磨前、碰磨中、停留和退出;试验测试到的最大径向和切向碰摩力分别为716 N和871 N,不会对转子部件造成损坏。5. 在最大叶尖线速度和最大进给速率参数下测得的冲击加速度最大,约为341g


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[1]Bardi, U., Giolli, C., Scrivani, A., et al., 2008. Development and investigation on new composite and ceramic coatings as possible abradable seals. Journal of Thermal Spray Technology, 17(5-6):805-811.

[2]Bill, R.C., Shiembob, L.T., 1977. Friction and wear of sintered fiber-metal abradable seal materials. Journal of Lubrication Technology, 99(4):421-427.

[3]Bill, R.C., Shiembob, L.T., 1981. Some considerations of the performance of two honeycomb gas path seal material systems. Lubrication Engineering, 37(4):209-217.

[4]Bounazef, M., Guessasma, S., Saadi, B.A., 2004. The wear, deterioration and transformation phenomena of abradable coating BN-SiAl-bounding organic element, caused by the friction between the blades and the turbine casing. Materials Letters, 58(27-28):3375-3380.

[5]Chen, L.S., Wang, Y.L., Lu, J.H., et al., 2008. Development of study and application of aeroengine sealing technology. Aeronautical Manufacturing Technology, (8):82-95 (in Chinese).

[6]Chupp, R., Ghasripoor, F., Moore, G., 2002. Applying abradable seals to industrial gas turbines. 38th AIAA/ ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Indianapolis, USA. AIAA, Virginia, USA, p.3795.

[7]Chupp, R.E., Lau, Y.C., Ghaspripoor, F., et al., 2004. Development of higher temperature abradable seals for gas turbine applications. ASME Turbo Expo 2004: Power for Land, Sea, and Air, Vienna, Austria. ASME, New York, USA, p.221-229.

[8]Collins, D., Teixeira, J., Crudgington, P., 2008. The degradation of abradable honeycomb labyrinth seal performance due to wear. Sealing Technology, 2008(8):82-84.

[9]Dadouche, A., Conlon, M.J., Dmochowski, W., 2008. Experimental evaluation of abradable seal performance at high temperature. ASME Turbo Expo 2008: Power for Land, Sea, and Air, Berlin, Germany. ASME, New York, USA, p.143-150.

[10]Dalzell, W.J., Sanders, S.A., Crawford, G.L., et al., 2002. Abradable seal with improved properties. Sealing Technology, 2002(8):14-15.

[11]DeMasi-Marcin, J.T., Gupta, D.K., 1994. Protective coatings in the gas turbine engine. Surface and Coatings Technology, 68-69:1-9.

[12]Delebarre, C., Wagner, V., Paris, J.Y., et al., 2014. An experimental study of the high speed interaction between a labyrinth seal and an abradable coating in a turbo-engine application. Wear, 316(1-2):109-118.

[13]Dorfman, M., Erning, U., Mallon, J., 2002. Gas turbines use ‘abradable’ coatings for clearance-control seal. Sealing Technology, 2002(1):7-8.

[14]Dowson, P., Walker, M.S., Watson, A.P., 2004. Development of abradable and rub-tolerant seal materials for application in centrifugal compressors and steam turbines. Sealing Technology, 2004(12):5-10.

[15]Draskovich, B.S., Frani, N.E., Joseph, S.S., et al., 1998. Abrasive Tip/Abradable Shroud System and Method for Gas Turbine Compressor Clearance Control. US Patent 5704759.

[16]Fois, N., Stringer, J., Marshall, M.B., 2013. Adhesive transfer in aero-engine abradable linings contact. Wear, 304(1-2):202-210.

[17]Fu, L., Feng, Z.P., Li, G.J., et al., 2015. Experimental validation of an integrated optimization design of a radial turbine for micro gas turbines. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 16(3):241-249.

[18]Ghasripoor, F., Dorfman, M., Schmid, R., 1997. Abradables improve gas turbine efficiency. Materials World, 5(6):328-330.

[19]He, K., Li, J., Yan, X., et al., 2012. Investigation of the conjugate heat transfer and windage effect in stepped labyrinth seals. International Journal of Heat and Mass Transfer, 55(17-18):4536-4547.

[20]Ma, X., Matthews, A., 2007. Investigation of abradable seal coating performance using scratch testing. Surface and Coatings Technology, 202(4-7):1214-1220.

[21]Ma, X.F., Duan, Z., Shi, H.J., et al., 2010. Fatigue and fracture behavior of nickel-based superalloy Inconel 718 up to the very high cycle regime. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 11(10):727-737.

[22]Miao, R.H., 2008. Application of metal cellular gas-tight seal in steam turbine. Taiyuan Science and Technology, (2):68-72 (in Chinese).

[23]Padova, C., Barton, J., Dunn, M.G., et al., 2006. Experimental results from controlled blade tip/shroud rubs at engine speed. Journal of Turbomachinery, 129(4):713-723.

[24]Potter, D.J., Chai, Y.W., Tatlock, G.J., 2009. Improvements in honeycomb abradable seals. Materials at High Temperatures, 26(2):127-135.

[25]Pychynski, T., Höefler, C., Bauer, H.J., 2015. Experimental study on the friction contact between a labyrinth seal fin and a honeycomb stator. Journal of Engineering for Gas Turbines and Power, 138(6):062501.

[26]Rathmann, U., Olmes, S., Simeon, A., 2007. Sealing technology: rub test rig for abrasive/abradable systems. ASME Turbo Expo 2007: Power for Land, Sea, and Air, Montreal, Canada. ASME, New York, USA, p.223-228.

[27]Schmid, R.K., Ghasripoor, F., Dorfman, M., et al., 2000. An overview of compressor abradable thermal spray. Proceedings of Surface Engineering Interaction Thermal Spray Conference ITSC, Montreal, Canada, p.1087-1093.

[28]Shen, H., Zheng, T.H., Chen, Y.J., 2011. Improvement of aero-engine sealing technology. Gas Turbine Experimental and Research, 24(4):51-55 (in Chinese).

[29]Shen, M.X., Zheng, J.P., Meng, X.K., et al., 2015. Influence of Al2O3 particles on the friction and wear behaviors of nitrile rubber against 316L stainless steel. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 16(2):151-160.

[30]Sporer, D.R., Shiembob, L.T., Sporer, D.R., et al., 2004. Alloy selection for honeycomb gas path seal systems. ASME Turbo Expo 2004: Power for Land, Sea, and Air, Vienna, Austria. ASME, New York, USA, p.763-774.

[31]Stringer, J., Marshall, M.B., 2012. High speed wear testing of an abradable coating. Wear, 294-295(31):257-263.

[32]Vakili, A.D., Meganathan, A.J., Michaud, M., et al., 2005. An experimental and numerical study of labyrinth seal flow. ASME Turbo Expo 2005: Power for Land, Sea, and Air, Reno, Nevada, USA. ASME, New York, USA, p.1121-1128.

[33]Wei, L.J., Li, C.Q., Gao, L., et al., 2005. Application and development of steam turbine sealing technology. Journal of Engineering for Thermal Energy and Power, 20(5):455-458 (in Chinese).

[34]Wiebe, D.J., 1994. Abradeable Labyrinth Stator Seal. US Patent 5314304.

[35]Wu, J.H., 2011. Compound cellular steam seal and its application on turbine shaft seal. Journal of Shenyang Institute of Engineering (Natural Science), 7(1):24-28 (in Chinese).

[36]Zhang, N., Shen, J., Xuan, H.J., et al., 2016. Evaluation of an AlSi-polyester abradable seal coating performance using high-temperature and high-velocity abrasion tests. Proceedings of the Institution of Mechanical Engineers, Part J: Journal of Engineering Tribology, 230(7):842-851.

[37]Zhang, X.L., Yao, B., Feng, W., et al., 2015. Modeling of a virtual grinding wheel based on random distribution of multi-grains and simulation of machine-process interaction. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 16(11):874-884.

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