Research Papers

Performance Improvement of a Return Channel in a Multistage Centrifugal Compressor Using Multiobjective Optimization

[+] Author and Article Information
Yoshifumi Nishida

e-mail: yoshifumi.nishida.cx@hitachi-pt.com

Hiromi Kobayashi

e-mail: hiromi.kobayashi.zm@hitachi-pt.com

Hideo Nishida

e-mail: hideo.nishida.cr@hitachi-pt.com
Tsuchiura Research Laboratory,
Research & Development Group,
Hitachi Plant Technologies, Ltd.
603 Kandatsu-machi,
Ibaraki-ken, 300-0013, Japan

Kazuyuki Sugimura

e-mail: Kazuyuki.sugimura.hk@hitachi.com
Department of Advanced Simulation Research,
Mechanical Engineering Center,
Hitachi Research Laboratory, Hitachi, Ltd.
832-2 Horiguchi, Hitachinaka-shi, Ibaraki-ken,
312-0034, Japan

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 3, 2012; final manuscript received August 21, 2012; published online March 25, 2013. Editor: David Wisler.

J. Turbomach 135(3), 031026 (Mar 25, 2013) (8 pages) Paper No: TURBO-12-1117; doi: 10.1115/1.4007518 History: Received July 03, 2012; Revised August 21, 2012

The effect of the design parameters of a return channel on the performance of a multistage centrifugal compressor was numerically investigated, and the shape of the return channel was optimized using a multiobjective optimization method based on a genetic algorithm to improve the performance of the centrifugal compressor. The results of sensitivity analysis using Latin hypercube sampling suggested that the inlet-to-outlet area ratio of the return vane affected the total pressure loss in the return channel, and that the inlet-to-outlet radius ratio of the return vane affected the outlet flow angle from the return vane. Moreover, this analysis suggested that the number of return vanes affected both the loss and the flow angle at the outlet. As a result of optimization, the number of return vane was increased from 14 to 22 and the area ratio was decreased from 0.71 to 0.66. The radius ratio was also decreased from 2.1 to 2.0. Performance tests on a centrifugal compressor with two return channels (the original design and optimized design) were carried out using two-stage test apparatus. The measured flow distribution exhibited a swirl flow in the center region and a reversed swirl flow near the hub and shroud sides. The exit flow of the optimized design was more uniform than that of the original design. For the optimized design, the overall two-stage efficiency and pressure coefficient were increased by 0.7% and 1.5%, respectively. Moreover, the second-stage efficiency and pressure coefficient were respectively increased by 1.0% and 3.2%. It is considered that the increase in the second-stage efficiency was caused by the increased uniformity of the flow, and the rise in the pressure coefficient was caused by a decrease in the residual swirl flow. It was thus concluded from the numerical and experimental results that the optimized return channel improved the performance of the multistage centrifugal compressor.

Copyright © 2013 by ASME
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
Fig. 1

Parameters of return channel

Grahic Jump Location
Fig. 2

Flow chart of the return channel optimization system

Grahic Jump Location
Fig. 3

Calculation models

Grahic Jump Location
Fig. 4

Results of sensitivity analysis

Grahic Jump Location
Fig. 5

Relationships between the design variables and objective functions

Grahic Jump Location
Fig. 6

Meridional and vane shapes of return channel

Grahic Jump Location
Fig. 7

Performance characteristics of impeller (CFD)

Grahic Jump Location
Fig. 8

Compressor test apparatus

Grahic Jump Location
Fig. 9

Model compressor cross section

Grahic Jump Location
Fig. 10

Pitot tube measurement positions

Grahic Jump Location
Fig. 11

Measured flow angle distribution in first-stage outlet

Grahic Jump Location
Fig. 12

Calculated flow angle distribution in first-stage outlet

Grahic Jump Location
Fig. 13

Measured overall performance characteristics

Grahic Jump Location
Fig. 14

Measured first-stage performance characteristics

Grahic Jump Location
Fig. 15

Measured second-stage performance characteristics




Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In