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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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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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%.
Aerospace Propulsion Theory and Engineering, Blade Root Leakage, Sealing Labyrinth Seals, Upstream Cavity, Secondary Flow
To cite this article
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.
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.
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