Mathematical Problems in Engineering | Volume 2018 ,2018-12-05 |
Loss Mechanism of Static Interstage Components of Multistage Centrifugal Compressors for Integrated Blade Design | |
Research Article | |
Chunjun Ji ^{1} , ^{2} Chunyang Li ^{1} Junyi Fang ^{1} Qi Sun ^{3} | |
Show affiliations | |
DOI：10.1155/2018/9025650 | |
Received 2018-08-09, accepted for publication 2018-11-25, Published 2018-11-25 | |
摘要
Although centrifugal compressors are widely used in construction, they consume a large amount of energy; in existing multistage centrifugal compressors, there is a serious pressure loss of ~15.13% when gas flows through the diffuser, bend, and return channel. In this study, we analyze the loss mechanisms of these stages in detail, using computational fluid dynamics. Based on this analysis, we present a new type of integrated blade, connecting the diffuser, bend, and return channels, which can eliminate the airflow stall phenomenon. Through effective control of the airflow spreading process, we minimized losses in the component, which improved its efficiency by 4.39% and increased the pressure ratio by 2.86% relative to a compressor without the newly-designed integrated blade. The concepts used in the creation of this component can provide a reference for the future design of blades for flow through parts of multistage compressors.
授权许可
Copyright © 2018 Chunjun Ji et al. 2018
This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
图表
Meridional section of a centrifugal compressor.
3D model of the original compressor used in analysis.
Total pressure distribution in the meridional section of the original compressor model.
Total pressure distribution in the diffuser of the original compressor model.
Static pressure distribution in the diffuser of the original compressor model.
Distribution of the airflow angle in the meridional plane of the original compressor model.
Variation of the airflow angle in each bend section of the original compressor model.
Velocity distribution in the return channel of the original compressor.
Vortex at the suction surface of the return channel in the original compressor.
Meridional profile of the integrated blade. The solid line is the meridional line of the original model, and the dashed line is the meridional line of the new integrated blade.
3D model of the integrated blade.
3D model of the modified compressor.
Relationship between the number of mesh elements, and predicted compressor level efficiency and pressure ratio when Din=750 mm.
Computational grid for a single channel model.
Distribution of y+ values on the solid walls of the model.
Comparison of the (a) pressure ratio and (b) compressor efficiency performance curves predicted using different turbulence models, with experimental data.
Comparison of the (a) pressure ratio and (b) compressor efficiency performance curves predicted using different turbulence models, with experimental data.
Convergence history for a compressor model with Din=750 mm.
Compressor efficiency and pressure ratio of the modified model as a function of the integrated blade’s inlet design angle.
Total pressure distribution at the meridional surface of the modified compressor model with integrated blade inlet design angles at (a) 73°, (b) 62°, and (c) 50°.
Total pressure distribution at the meridional surface of the modified compressor model with integrated blade inlet design angles at (a) 73°, (b) 62°, and (c) 50°.
Total pressure distribution at the meridional surface of the modified compressor model with integrated blade inlet design angles at (a) 73°, (b) 62°, and (c) 50°.
Velocity vectors (enlarged by an additional 50%) for selected integrated blade inlet design angles and surfaces. (a) Integrated blade’s inlet pressure surface at 73°. (b) Integrated blade’s suction surface at 73°. Integrated blade’s inlet pressure surface at (c) 50° and (d) 62°.
Velocity vectors (enlarged by an additional 50%) for selected integrated blade inlet design angles and surfaces. (a) Integrated blade’s inlet pressure surface at 73°. (b) Integrated blade’s suction surface at 73°. Integrated blade’s inlet pressure surface at (c) 50° and (d) 62°.
Velocity vectors (enlarged by an additional 50%) for selected integrated blade inlet design angles and surfaces. (a) Integrated blade’s inlet pressure surface at 73°. (b) Integrated blade’s suction surface at 73°. Integrated blade’s inlet pressure surface at (c) 50° and (d) 62°.
Velocity vectors (enlarged by an additional 50%) for selected integrated blade inlet design angles and surfaces. (a) Integrated blade’s inlet pressure surface at 73°. (b) Integrated blade’s suction surface at 73°. Integrated blade’s inlet pressure surface at (c) 50° and (d) 62°.
Effect of modifying the distance between moving and static components on blade structure.
Variation of compressor level efficiency and pressure ratio with the radial spacing between moving and static components.
Total pressure distribution at the meridional plane of the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Total pressure distribution at the meridional plane of the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Total pressure distribution at the meridional plane of the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Static pressure distribution at the meridional plane of the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Static pressure distribution at the meridional plane of the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Static pressure distribution at the meridional plane of the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Airflow angle distribution at the outlet section of impeller blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Airflow angle distribution at the outlet section of impeller blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Airflow angle distribution at the outlet section of impeller blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Airflow angle distribution at the inlet section of the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Airflow angle distribution at the inlet section of the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Airflow angle distribution at the inlet section of the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Enlarged (50%) map of the velocity distribution at the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Enlarged (50%) map of the velocity distribution at the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Enlarged (50%) map of the velocity distribution at the integrated blade. (a) R=15 mm, (b) R=45 mm, and (c) R=60 mm.
Total pressure distribution at the meridional plane of the (a) original model and (b) improved model.
Total pressure distribution at the meridional plane of the (a) original model and (b) improved model.
Static pressure distribution at the meridional surface of the (a) original mode, and (b) improved model.
Static pressure distribution at the meridional surface of the (a) original mode, and (b) improved model.
Distribution of airflow angles in each section of the bend in the (a) original model and (b) improved model.
Distribution of airflow angles in each section of the bend in the (a) original model and (b) improved model.
Velocity distribution of the internal flow field in the different compressors. (a) Return channel in the original model. (b) Vortex at the suction surface in the return channel of the original model. (c) Integrated blade in the improved model.
Velocity distribution of the internal flow field in the different compressors. (a) Return channel in the original model. (b) Vortex at the suction surface in the return channel of the original model. (c) Integrated blade in the improved model.
Velocity distribution of the internal flow field in the different compressors. (a) Return channel in the original model. (b) Vortex at the suction surface in the return channel of the original model. (c) Integrated blade in the improved model.
通讯作者
Chunyang Li.School of Energy and Power Engineering, Dalian University of Technology, Dalian 116024, China, dlut.edu.cn.906549286@qq.com
推荐引用方式
Chunjun Ji,Chunyang Li,Junyi Fang,Qi Sun. Loss Mechanism of Static Interstage Components of Multistage Centrifugal Compressors for Integrated Blade Design. Mathematical Problems in Engineering ,Vol.2018(2018)
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