Experiment on flow and windage heating characteristics of high-speed rotating labyrinth

Zhiwei WANG; Tianheng ZHA; Bowen LIU; Yan CHEN; Aqiang LIN; Gaowen LIU

doi:10.7527/S1000-6893.2025.31534

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2025 , Vol. 46 >Issue 15: 131534 - 131534

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

Fluid Mechanics and Flight Mechanics

Experiment on flow and windage heating characteristics of high-speed rotating labyrinth

Zhiwei WANG ,
Tianheng ZHA ,
Bowen LIU ,
Yan CHEN ,
Aqiang LIN ,
Gaowen LIU

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^1.School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China
^2.AECC Commercial Aircraft Engine Co. ，Ltd. ，Shanghai 200241，China
^3.AECC Hunan Aviation Powerplant Research Institute，Zhuzhou 412002，China
^4.Shandong Zuoyao Intelligent Equipment Co. ，Ltd. ，Weihai 264300，China

E-mail： xjtu.chenyan@nwpu.edu.cn

Received date: 2024-11-14

Revised date: 2024-12-24

Accepted date: 2025-03-31

Online published: 2025-04-10

Supported by

National Natural Science Foundation of China(52476091);Aeronautical Science Foundation of China(2024M070053001);China Postdoctoral Science Foundation(2025T181167);Taishan Industrial Experts Program

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Abstract

The performance of sealing labyrinth systems significantly impacts aero-engine efficiency and power consumption. a high-speed rotating test rig was designed and constructed. Based on the calibration of measurement parameters from instruments， this study investigates the effects of geometric and aerodynamic parameters， especially the incoming flow temperature， on the leakage， windage heating， and swirl flow characteristics of a typical stepped-slanted labyrinth seal. The influence mechanism of each parameter on sealing performance is quantitatively analyzed. Experimental results show that at rotating Mach numbers of 0 to 0.557 and pressure ratios of 1.1 to 2.0， the seal clearance increases from 0.17 mm to 0.61 mm， and discharge coefficient initially decreased and then increased. 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 coefficient 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 discharge 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 discharge 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 flow characteristic

Cite this article

Zhiwei WANG , Tianheng ZHA , Bowen LIU , Yan CHEN , Aqiang LIN , Gaowen LIU . Experiment on flow and windage heating characteristics of high-speed rotating labyrinth[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(15) : 131534 -131534 . DOI: 10.7527/S1000-6893.2025.31534

References

[1]	HU S， FENG W， GONG W Q， et al. Research on internal flow field analysis and power loss modeling of the expansion seal ring［J］. Physics of Fluids， 2023， 35（11）：113116.
[2]	姚斡维，刘高文，陈燕，等. 高性能涡轮低位预旋供气系统正向设计［J］. 航空学报， 2025， 46（7）： 130832.
	YAO G W， LIU G W， CHEN Y， et al. Forward design of high-performance turbine low-radius pre-swirl system?［J］. Acta Aeronautica et Astronautica Sinica， 2025， 46（7）： 130832 （in Chinese）.
[3]	杨显赵，刘高文，郭令颖，等. 高温降涡轮高位预旋供气系统的设计研究［J］. 航空学报， 2025， 46（2）： 130672.
	YANG X Z， LIU G W， GUO L Y， et al. Design of turbine high radius pre-swirl system with high temperature drop［J］. Acta Aeronautica et Astronautica Sinica， 2025， 46（2）： 130672 （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（5）： 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（5）： 38-40 （in Chinese）.
[5]	STURGESS G， DATTA P. Application of CFD to gas turbine engine secondary flow systems-The labyrinth seal［C］∥24th Joint Propulsion Conference. Reston： AIAA， 1988.
[6]	MARTIN H M. Labyrinth Packings?［J］. Engineering， 1908， 85： 35.
[7]	STODOLA A. Steam and Gas Turbines 6th?［M］. New York： McGraw-Hill， 1927.
[8]	VERMES G. A fluid mechanics approach to the labyrinth seal leakage problem?［J］. Journal of Engineering for Power， 1961， 83（2）： 161-169.
[9]	WITTIG S L K， D?RR L， KIM S. 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 Turbomachinery， 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］∥ASME Turbo Expo 1995： Land， Sea， and Air. New York： ASME， 1995.
[12]	DENECKE J， SCHARAMM V， KIM S， et al. Influence of Rub-Grooves on labyrinth seal leakage［J］. Journal of Turbomachinery， 2003， 125（2）： 387-39.
[13]	DENECKE J， F?RBER J， DULLENKOPF K， et al. Dimensional analysis and scaling of rotating seals［C］∥ ASME Turbo Expo 2005： Power for Land， Sea， and Air. New York： ASME， 2008.
[14]	DENECKE J， DULLENKOPF K， WITTIG S， et al. Experimental investigation of the total temperature increases and swirl development in rotation labyrinth seals［C］∥ASME Turbo Expo2005： Power for Land， Sea， and Air. New York： ASME， 2008.
[15]	DENECKE J， F?RBER J， DULLENKOPF K， et al. Interdependence of discharge behavior， swirl development and total temperature increase in rotating labyrinth seals［C］∥ASME Turbo Expo 2008： Power for Land， Sea， and Air. New York： ASME， 2009.
[16]	MCGREEHAN W F， KO S H. Power dissipation in smooth and honeycomb labyrinth seals［C］∥Proceeding of the ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. New York： ASME， 1989.
[17]	MILLWARD J A， EDWARDS M F. Windage heating of air passing through labyrinth seals［J］. Journal of Turbomachinery， 1996， 118（2）： 414-419.
[18]	吴丁毅，刘振侠. 交错式生篦齿封严特性的实验研究［J］. 推进技术， 1997， 18（2）： 87-90.
	WU D Y， LIU Z X. An experimental investigation on sealing characteristics of interlacing labyrinth［J］. Journal of Propulsion Technology， 1997， 18（2）： 87-90 （in Chinese）.
[19]	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（2）： 181-186.
	LIU G W， JIANG Z W， WU W T. Investigation on effects of rectangular groove on leakage of straight-through labyrinth seal based on numerical simulation［J］. Journal of Propulsion Technology， 2013， 34（2）： 181-186 （in Chinese）.
[20]	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 sealing in a compressor stator well?［J］. Journal of Propulsion Technology， 2014， 35（12）： 1687-1693 （in Chinese）.
[21]	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（7）： 1554-1560.
	LIU G W， CHEN K， GANG T， et al. Influences of pressure ratio and Reynolds number on flow characteristics of labyrinth seal in compressor stator well?［J］. Journal of Aerospace Power， 2015， 30（7）： 1554-1560 （in Chinese）.
[22]	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 influences of tooth position in compressor stator well sealing［J］. Journal of Aerospace Power， 2015， 30（12）： 2925-2933 （in Chinese）.
[23]	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（9）： 2085-2093.
	KONG X Z， LIU G W， LEI Z， et al. Experimental investigation for effects of tooth shapes on compressor inter-stage seal［J］. Journal of Propulsion Technology， 2018， 39（9）： 2085-2093 （in Chinese）.
[24]	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（7）： 1575-1582.
	KONG X Z， LIU G W， LEI Z， et al. Experiment on influence of rotational speeds on labyrinth seal in compressor stator well［J］. Journal of Aerospace Power， 2016， 31（7）： 1575-1582 （in Chinese）.
[25]	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（7）： 1779-1786.
	GUO H L， FENG Q， LIU G W， et al. Experiment on flow characteristic in rotating labyrinth with consideration of clearance change?［J］. Journal of Aerospace Power， 2018， 33（7）： 1779-1786 （in Chinese）.
[26]	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（6）： 1402-1408.
	WANG P F， GUO W， ZHANG J Z. Experimental investigation and numerical analysis of windage heating in rotating labyrinth seals?［J］. Journal of Aerospace Power， 2013， 28（6）： 1402-1408 （in Chinese）.
[27]	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，（2024-10-11）［2024-11-05］. .
	XU W F， ZOU S L， REN G Z， et al. Study on the influence of the labyrinth seal structure on the compressor cascade performance［J/OL］. Journal of Aerospace Power，（2024-10-11）［2024-11-05］. （in Chinese）.
[28]	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］. 推进技术， 2025， 46（2）： 2312084.
	REN G Z， LU D Z， SUN D，et al. Effects of structural parameters on flow characteristics and optional number of sealing teeth of labyrinth seals［J］. Journal of Propulsion Technology， 2025， 46（2）： 2312084 （in Chinese）.

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