0
Research Papers: Gas Turbines: Turbomachinery

Parametric Studies of Pipe Diffuser on Performance of a Highly Loaded Centrifugal Compressor

[+] Author and Article Information
Ge Han

Key Laboratory of Light-Duty Gas-Turbine,
Institute of Engineering Thermophysics,
Chinese Academy of Science,
Beijing 100190, China
University of Chinese Academy of Science,
Beijing 100190, China
e-mail: hange898525@sina.com

Xingen Lu

Key Laboratory of Light-Duty Gas-Turbine,
Institute of Engineering Thermophysics,
Chinese Academy of Science,
Beijing 100190, China
e-mail: xingenlu@hotmail.com

Shengfeng Zhao

Key Laboratory of Light-Duty Gas-Turbine,
Institute of Engineering Thermophysics,
Chinese Academy of Science,
Beijing 100190, China
e-mail: zhaoshengfeng@iet.cn

Chengwu Yang

Key Laboratory of Light-Duty Gas-Turbine,
Institute of Engineering Thermophysics,
Chinese Academy of Science,
Beijing 100190, China
University of Chinese Academy of Science,
Beijing 100190, China
e-mail: yangchengwu@iet.cn

Junqiang Zhu

Key Laboratory of Light-Duty Gas-Turbine,
Institute of Engineering Thermophysics,
Chinese Academy of Science,
Beijing 100190, China
e-mail: zhujq@mail.etp.ac.cn

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received April 22, 2014; final manuscript received May 12, 2014; published online July 2, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(12), 122604 (Jul 02, 2014) (10 pages) Paper No: GTP-14-1206; doi: 10.1115/1.4027867 History: Received April 22, 2014; Revised May 12, 2014

Pipe diffusers with several different geometries were designed for a highly loaded centrifugal compressor originally using a wedge diffuser. Parametric studies on the effect of pipe diffuser performance of a highly loaded centrifugal compressor by varying pipe diffuser inlet-to-impeller exit radius ratio, throat length, divergence angle, and throat area on centrifugal compressor performance were performed using a state-of-the-art multiblock flow solver. An optimum design of pipe diffuser was obtained from the parametric study, and the numerical results indicate that this pipe diffuser has remarkable advantageous effects on the compressor performance. Furthermore, a detailed comparison of flow visualization between the pipe diffuser and the wedge diffuser was conducted to identify the physical mechanism that account for the beneficial effects of the pipe diffuser on the performance and stability of the compressor. It was found that the performance enhancement afforded by the pipe diffuser is a result of the unique diffuse inlet flow pattern. Alleviating flow distortion in the diffuser inlet and reducing the possibility of a flow separation in discrete passages are the physical mechanisms responsible for improving the highly loaded centrifugal compressor performance.

Copyright © 2014 by ASME
Your Session has timed out. Please sign back in to continue.

References

Kenny, D. P., 1969, “A Novel Low-Cost Diffuser for High-Performance Centrifugal Compressors,” ASME J. Eng. Gas Turbines Power, 91(1), pp. 37–46. [CrossRef]
Bourgeois, J. A., Robert, J. M., Roberts, D., Savory, E., and Zhang, C., 2009, “Experimental and Numerical Investigation of an Aero-Engine Centrifugal Compressor,” ASME Turbo Expo, Orlando, FL, June 8–12, ASME Paper No. GT2009-59808. [CrossRef]
Zachau, U., and Buescher, C., 2008, “Experimental Investigation of a Centrifugal Compressor Stage With Focus on the Flow in the Pipe Diffuser Supported by Particle Image Velocimetry (PIV) Measurements,” ASME Turbo Expo, Berlin, Germany, June 9–13, ASME Paper No. GT2008-51538. [CrossRef]
Zachau, U., and Niehuis, R., 2009, “Experiential Investigation of the Flow in the Pipe Diffuser of a Centrifugal Compressor Stage Under Selected Parameter Variations,” ASME Turbo Expo, Orlando, FL, June 8–12, ASME Paper No. GT2009-59320. [CrossRef]
Kunte, R., Jeschke, P., and Smythe, C., 2012, “Experimental Investigation of a Truncated Pipe Diffuser With a Tandem Deswirler in a Centrifugal Compressor Stage,” ASME Turbo Expo, Copenhagen, Denmark, June 11–15, ASME Paper No. GT2012-68449. [CrossRef]
Kunte, R., Schwarz, P., Wilkosz, B., Jeschke, P., and Smythe, C., 2011, “Experimental and Numerical Investigation of Tip Clearance and Bleed Effects in a Centrifugal Compressor Stage With Pipe Diffuser,” ASME Turbo Expo, Vancouver, Canada, June 6–10, ASME Paper No. GT2011-45128. [CrossRef]
Grates, D. R., Jeschke, P., and Niehuis, R., 2013, “Numerical Investigation of the Unsteady Flow Inside a Centrifugal Compressor Stage With Pipe Diffuser,” ASME Turbo Expo, San Antonio, TX, June 3–7, ASME Paper No. GT2013-95465. [CrossRef]
Gould, K. A., Tan, C. S., and Macrorie, M., 2007, “Characterization of Unsteady Impeller-Blade Loading in a Centrifugal Compressor With a Discrete-Passage Diffuser,” ASME Turbo Expo, Montreal, Canada, May 14–17, ASME Paper No. GT2007-28002. [CrossRef]
Peeters, M., and Sleiman, M., 2000, “A Numerical Investigation of the Unsteady Flow in Centrifugal Stages,” ASME Turbo Expo, Munich, Germany, May 8–11, ASME Paper No. GT2000-426.
Wrong, C. B., 1981, “Turbine Engine Design,” AIAA 1981 Annual Meeting and Technical Display, Long Beach, CA, May 12–14, AIAA Paper No. 81-0915. [CrossRef]
Moustapha, H., 2003, “Small Gas Turbine Technology: Evolution and Challenges,” AIAA/ICAS International Air and Space Symposium and Exposition: The Next 100 Years, Dayton, OH, July 14–17, AIAA Paper No. 2003-2559. [CrossRef]
Skoch, G. J., Prahst, P. S., Wernet, M. P., Wood, J. R., and Strazisar, A. J., 1997, “Laser Anemometer Measurements of the Flow Field in a 4:1 Pressure Ratio Centrifugal Impeller,” Army Research Laboratory, Lewis Research Center, Technical Report No. ARLTR-1448.
McKain, T. F., and Holbrook, G. J., 1997, “Coordinates for a High Performance 4:1 Pressure Ratio Centrifugal Compressor,” Detroit Diesel Allison, Indianapolis, IN, NASA Contractor Report No. 204134.
Izumi, M., and Hirose, E., 2003, “Diffuser Arrangement for Centrifugal Compressors,” U.S. Patent No. 2003/6537028 B1.
Bennett, I., Tourlidakis, A., and Elder, R. L., 2000, “The Design and Analysis of Pipe Diffuser for Centrifugal Compressors,” Proc. Inst. Mech. Eng. A, J. Power Energy, 214(1), pp. 87–96. [CrossRef]
Yang, H., Nuernberger, D., Nicke, V., and Weber, A., 2003, “Numerical Investigation of Casing Treatment Mechanisms With a Conservative Mixed-Cell Approach,” ASME Turbo Expo, Atlanta, GA, June 16–19, ASME Paper No. GT2003-38483. [CrossRef]
Marsan, A., Coste, S., Trebinjas, I., and Leroy, G., 2012, “Numerical Investigation of the Flow in a Radial Vaned Diffuser Without and With Aspiration,” ASME Turbo Expo, Copenhagen, Denmark, June 11–15, ASME Paper No. GT2012-68610. [CrossRef]

Figures

Grahic Jump Location
Fig. 1

Sketch of a pipe diffuser

Grahic Jump Location
Fig. 2

Meridional flow path with stations of measurement

Grahic Jump Location
Fig. 3

Pipe diffusers geometry. (a) Pipe diffuser with a cylinder. (b) Pipe diffuser without a cylinder.

Grahic Jump Location
Fig. 4

Computational grid

Grahic Jump Location
Fig. 5

Computed and measured centrifugal compressor performance at design speed. (a) Total pressure ratio and (b) adiabatic efficiency.

Grahic Jump Location
Fig. 6

Stage performance with different R3/R2 at design point

Grahic Jump Location
Fig. 7

Mach number contours on cutting planes aligned orthogonally to the center line of the pipe of different R3/R2

Grahic Jump Location
Fig. 8

Streamlines on 5% passage height plane of different R3/R2

Grahic Jump Location
Fig. 9

Compressor performance for different throat length. (a) Total pressure ratio and (b) adiabatic efficiency.

Grahic Jump Location
Fig. 10

Streamwise Mach number distribution for L/D4 = 0 and L/D4 = 3

Grahic Jump Location
Fig. 11

Mach number contours and streamlines at midspan near surge: L/D4 = 0 and L/D4 = 3

Grahic Jump Location
Fig. 12

Stage performance with different divergence angle at design point

Grahic Jump Location
Fig. 13

Total pressure loss contours on cutting planes aligned orthogonally to the center line of the pipe of different divergence angle

Grahic Jump Location
Fig. 14

Streamlines on 5% passage height plane of different divergence angles

Grahic Jump Location
Fig. 15

Compressor performance for different throat area: (a) total pressure ratio and (b) adiabatic efficiency

Grahic Jump Location
Fig. 16

Stage peak performance of baseline and optimized pipe diffuser

Grahic Jump Location
Fig. 17

Comparison of centrifugal compressor stage performance with pipe diffuser and wedge diffuser. (a) Total pressure ratio; (b) adiabatic efficiency; and (c) diffuser static pressure recovery coefficient.

Grahic Jump Location
Fig. 18

Comparison of Mach number contours at seven sections: (a) sections along flow passage; (b) Mach number contours at different sections

Grahic Jump Location
Fig. 19

Distribution of Mach number contours and streamlines on 5% passage height plane: (a) wedge diffuser and (b) pipe diffuser

Tables

Errata

Discussions

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