Leakage Flow in Honeycomb-Labyrinth Seal Cavity in Stator of Low-Speed Research Compressor

doi:10.16183/j.cnki.jsjtu.2024.280

Abstract

Abstract:

The honeycomb at the inner band of a compressor stator and the labyrinth on the disk form a sealed cavity, in which the clearance leakage flow has a key impact on the aerodynamic performance of the axial flow compressor. In this paper, focusing on the first 1.5-stage of a low-speed research compressor, numerical simulations are conducted to compare the impact of honeycomb seal structure and slide wall on the aerodynamic performance of the compressor, as well as the performance changes of honeycomb seal structure under two different labyrinth seal clearance conditions. The performance calculation results show that the isentropic efficiency of the compressor equipped with the 0.2-mm-clearance honeycomb cavity model is slightly lower than that of the slide-wall cavity model, which is attributed to the elevated total temperature rise induced by the leakage flow inside the cavity. Comparative analysis of cavity leakage flow characteristics and detailed flow field investigation indicate that honeycomb structure induces a simultaneous increase in both the cavity leakage flow rate and swirl angle. A strong interaction is observed between the airflow within the cavity and the honeycomb structure, creating a complex vortex flow that significantly elevates the total temperature in both the seal cavity and the honeycomb itself. This temperature elevation ultimately leads to a reduction in compressor efficiency. In contrast, when the zero-clearance honeycomb model is compared with the 0.2-mm-clearance honeycomb model, the decreased total temperature ratio contributes to an improvement in isentropic efficiency. In the zero-clearance model, although the average total temperature of the leakage flow rises owing to the reduced clearance, the compressor efficiency is enhanced by the substantial reduction in leakage flow rate. The findings in this paper clarify the quantitative relationship and influence mechanism of leakage flow under different clearance conditions on the performance of the honeycomb and labyrinth seal structure applied to the compressor stator, which therefore provide certain references for the engineering design of honeycomb seal cavities.

Key words: low-speed research compressor (LSRC), honeycomb, labyrinth, seal clearance, leakage

CLC Number:

V231.3

SHAO Runzhu, TENG Jinfang, FAN Lin, ZHONG Yongjian, JU Zhenzhou, ZHU Mingmin. Leakage Flow in Honeycomb-Labyrinth Seal Cavity in Stator of Low-Speed Research Compressor[J]. Journal of Shanghai Jiao Tong University, 2026, 60(3): 486-498.

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References 13

[1]	HEIDEGGER N, HALL E, DELANEY R. Parameterized study of high-speed compressor seal cavity flow[C]// 32nd Joint Propulsion Conference & Exhibit. Lake Buena Vista, USA: AIAA, 1996: AIAA 1996-2807.
[2]	WELLBORN S R, OKIISHI T H. The influence of shrouded stator cavity flows on multistage compressor performance[J]. Journal of Turbomachinery, 1999, 121(3): 486-497. doi: 10.1115/1.2841341 URL
[3]	KIM J W, SONG S J, KIM T. Streamwise evolution of loss in a shrouded axial compressor cascade passage[J]. Journal of Propulsion & Power, 2011, 27(4): 884-889.
[4]	FARKAS B, DE WYER N V, BROUCKAERT J F. Numerical study on the effect of seal leakage flow on low pressure axial compressor performance[C]// ASME Turbo Expo 2013:Turbine Technical Conference & Exposition. San Antonio, USA: ASME, 2013: V06AT35A039.
[5]	YOON S, SELMEIER R, CARGILL P, et al. Effect of the stator hub configuration and stage design parameters on aerodynamic loss in axial compressors[J]. Journal of Turbomachinery, 2015, 137(9): 091001. doi: 10.1115/1.4029598 URL
[6]	DE DOMINICIS I, ROBENS S, WOLFRUM N, et al. Interacting effects in a multistage axial compressor using shrouded and cantilevered stators[J]. Journal of Propulsion & Power, 2021, 37(4): 615-624.
[7]	KAMDAR N, LOU F Y, KEY N L. Details of shrouded stator hub cavity flow in a multi-stage axial compressor part 1: Interactions with the primary flow[C]// ASME Turbo Expo 2021: Turbomachinery Technical Conference & Exposition. Virtual, Online:ASME, 2021: V02AT31A041.
[8]	KAMDAR N, LOU F Y, KEY N L. Details of shrouded stator hub cavity flow in a multistage axial compressor part 2: Leakage flow characteristics in stator wells[J]. Journal of Engineering for Gas Turbines & Power, 2022, 144: 011027.
[9]	KONG X Z, LIU Y X, LIU G W, et al. Attempts on the reduction of leakage flow through the stator well in an axial compressor[J]. Journal of Engineering for Gas Turbines & Power, 2019, 141(8): 082501.
[10]	KONG X Z, LIU Y X, LU H W, et al. Performance analysis of inter-stage leakage flows at rotating conditions in an axial compressor[J]. Journal of Thermal Science, 2020, 29(6): 1558-1568. doi: 10.1007/s11630-020-1378-z
[11]	孔晓治, 黄天硕, 刘育心, 等. 不同来流附面层厚度下容腔泄漏流对围带式静叶性能影响[J]. 航空动力学报, 2023, 38(1): 184-196.
[14]	WRÓBLEWSKI W, FRĄCZEK D, MARUGI K. Leakage reduction by optimisation of the straight-through labyrinth seal with a honeycomb and alternative land configurations[J]. International Journal of Heat & Mass Transfer, 2018, 126: 725-739.
[15]	XU W F, WANG Z M, SUN D, et al. Numerical and experimental study on the influence of honeycomb bushing wear on the leakage flow characteristics of labyrinth seal[J]. Journal of Engineering for Gas Turbines & Power, 2024, 146(8): 081021.
[16]	陈远翔. 不同转速下蜂窝篦齿封严的泄漏与风阻温升特性研究[D]. 南京: 南京航空航天大学, 2021.
	CHEN Yuanxiang. Research on the leakage and windage heating characteristics of labyrinth seal with honeycomb land at varying rotational speeds[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2021.
[17]	王泽铭, 徐文峰, 任国哲, 等. 蜂窝衬套对篦齿封严静力与动力特性影响机理研究[J]. 推进技术, 2024, 45(2): 166-177.
	WANG Zeming, XU Wenfeng, REN Guozhe, et al. Influence mechanism of honeycomb bushing on static and dynamic characteristics of labyrinth seal[J]. Journal of Propulsion Technology, 2024, 45(2): 166-177.
[18]	WALLIN S, JOHANSSON A V. An explicit algebraic Reynolds stress model for incompressible and compressible turbulent flows[J]. Journal of Fluid Mechanics, 2000, 403: 89-132. doi: 10.1017/S0022112099007004 URL
[19]	ZHENG B J, SHAO R Z, ZHANG S A, et al. Optimization and experimental study of stationary endwall of stator labyrinth cavity in a low-speed research compressor[J]. Aerospace Science & Technology, 2024, 147: 109036.
[20]	SHAO R Z, HE X, ZHU M M, et al. Characterizing shrouded stator cavity flow on the performance of a single-stage axial transonic compressor[J]. Journal of Turbomachinery, 2023, 145(11): 111004. doi: 10.1115/1.4063296 URL
[11]	KONG Xiaozhi, HUANG Tianshuo, LIU Yuxin, et al. Influences of the cavity leakage flow on shrouded stator performance at different inlet boundary layer thicknesses[J]. Journal of Aerospace Power, 2023, 38(1): 184-196.
[12]	STOCKER H L, COX D M, HOLLE G F. Aerodynamic performance of conventional and advanced design labyrinth seals with solid-smooth abradable, and honeycomb lands[R]. Indianapolis, USA: NASA Lewis Research Center, 1977.
[13]	ALIZADEH M, NIKKHAHI B, FARAHANI A S, et al. Numerical study on the effect of geometrical parameters on the labyrinth-honeycomb seal performance[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2018, 232(2): 362-373. doi: 10.1177/0954410017742227 URL

结构	流量系数	叶片数	设计转速/(r·min^-1)	弦长(中径)/mm	轮毂比	稠度(中径)	展弦比(中径)
IGV	0.467	42		81.3	0.88	0.77	1.11
R1	0.467	52	900	113.3	0.88	1.33	0.79
S1	0.467	78		73.7	0.88	1.30	1.22