Research on Flow Characteristics of Upstream Cavity with Labyrinth Seals in Axial Compressor
International Journal of Fluid Mechanics & Thermal Sciences
Volume 5, Issue 3, September 2019, Pages: 82-90
Received: Jul. 13, 2019; Accepted: Sep. 10, 2019; Published: Sep. 23, 2019
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Authors
Xin Fu, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, China
Yingying Xu, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, China
Yan Zhang, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, China
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Abstract
The sealing between rotating components and stator components has become one of the main issues to be studied in the compressor. The mixing of stator root leakage flow and the mainstream can seriously affect the performance of the compressor. This article does a series of work on numerical calculation of plane diffuser cascade with the stator cavity and three-stage labyrinth seal. It also analyzes the details of the flow structure on upstream cavity. In this paper, the 3D streamlines distribution of the cascade corner region is studied, respectively for the no leakage case and the mixing mechanism of the secondary flow and mainstream with leakage. On this basis, the upstream cavity configuration is optimized and some results are obtained as fellows. The mainstream in the blade leading edge into the upstream cavity comes into being the secondary flow, which similar to leakage flow. It can affect the highest 80% leaves of the high range. Leakage flow is mainly influence on the performance of the blade root flow field and weakly of next to casing area. Compared to no leakage case, angular separation position ahead of time and range increased when there is leakage. Thus, added rib on both sides of the vessel wall can reduce the total pressure loss of the S3 section, and the relative position of ribbed effect significantly. The research shows that first layer of rib is better when set on the hub wall surface, the total pressure loss coefficient decreased by 3.49%.
Keywords
Aerospace Propulsion Theory and Engineering, Blade Root Leakage, Sealing Labyrinth Seals, Upstream Cavity, Secondary Flow
To cite this article
Xin Fu, Yingying Xu, Yan Zhang, Research on Flow Characteristics of Upstream Cavity with Labyrinth Seals in Axial Compressor, International Journal of Fluid Mechanics & Thermal Sciences. Special Issue: Fluid Mechanics & Thermal Sciences in Turbomachines. Vol. 5, No. 3, 2019, pp. 82-90. doi: 10.11648/j.ijfmts.20190503.14
Copyright
Copyright © 2019 Authors retain the copyright of this article.
This article is an open access article distributed under the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0/) which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
References
[1]
Campobasso M. S, Mattheiss A, Wenger U, et al. Complementary use of CFD and experimental measurements to assess the impact of shrouded and cantilevered stators in axial compressors. ASME International Gas Turbine and Aeroengine Congress and Exhibition, Indianapolis, Indiana, USA, 1999.
[2]
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 Turbomach, 2015, 137 (9): 091001.
[3]
Zi-nan Wang. Experimental and numerical investigation on endwall flow of cantilevered stator in axial compressor. The University of Chinese Academy of Sciences. Beijing, China, 2016.
[4]
Geoffrey J. Sturgess. Application of CFD to gas turbine engine secondary flow system-the labyrinth seal. In: AIAA/ASME/SAE/ASEE 24th joint propulsion conference, Boston, Massachusetts, 1988.
[5]
Wellborn S. R. and Okiishi T. H. Effects of shrouded stator cavity flows on multistage axial compressor aerodynamic performance. Iowa State University: NASA, CR-198536, 1996; 90-101.
[6]
Wellborn S. R., Okiishi T. H. The influence of shrouded stator cavity flows on multistage compressor performance. J Turbomach 1999; 121 (3), pp.486-497.
[7]
Wellborn S. R., Tolchinsky I. Modeling shrouded stator cavity flows in axial flow compressors. J Turbomach 2000; 122 (1), 55-61.
[8]
Heidegger N, Hall E, Delaney R. Parameterized study of high-speed compressor seal cavity flow [C]//Joint Propulsion Conference & Exhibit. 1996.
[9]
Popovic I. and Hodson H. P. The effects of a parametric variation of the rim seal geometry on the interaction between hub leakage and mainstream flows in high pressure turbines. J Eng Gas Turb Power 2012; 135 (11), 1823-1833.
[10]
Demargne A. and Longley J. P. The aerodynamic interaction of stator shroud leakage and mainstream flows in compressors. ASME Turbo Expo Power for Land Sea and Air, Munich, Germany, 2000; paper no.2000-GT-0570.
[11]
Kim J. W., Song S. J. and Kim T. Streamwise evolution of loss in a shrouded axial compressor cascade passage. AIAA J Propul Power, 2011; 27 (4), 884-889.
[12]
Sohn D. W., Kim T. and Song S. J. Influence of the leakage flow tangential velocity on the loss generation and leakage flow kinematics in shrouded axial compressor cascades. 51st ASME Turbo Expo, Barcelona, Spain, 2006; 389-397.
[13]
Xin. Fu., Wan-yue. Wang, and Yan. Zhang. Simulation of the flow structure of the mainstream in the upstream cavity in an axial compressor. Ordnance Industry Automation, 2018; 37 (07), 83-88.
[14]
Yong-hua. Cao. A study based on using jet to suppress leakage flow in the labyrinth seal. Nanjing University of Aeronautics and Astronautics, 2017.
[15]
Jian-feng. Zhu, Guo-ping. Huang, and Xin. Fu. Preliminary experiment of suppressing flow separation in cascade by micro pulsed jet without external device. Journal of Aerospace Power, 2014; 29 (02), 391-397.
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