Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output

Munzer Shehadeh Yousef Ebaid; Qusai Zuhair Mohmmad Al-Hamdan

doi:doi:10.11648/j.ajae.20170402.11

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Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output

Munzer Shehadeh Yousef Ebaid, Qusai Zuhair Mohmmad Al-Hamdan

Published in American Journal of Aerospace Engineering (Volume 4, Issue 2)

Received: 6 March 2017 Accepted: 5 April 2017 Published: 20 July 2017

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Abstract

In this current work, the design of a single stage centrifugal compressor as part of a complete small gas turbine coupled directly to high speed permanent magnet running at 60000rpm and developing a maximum electrical power of 60kW is presented. The choice of a radial impeller was considered and the design was based on using a non-linear optimisation code to determine the geometric dimensions of the impeller. Also, the optimum axial length and the flow passage of the impeller were found based on prescribed mean stream velocity. The proposed code was verified and showed quite good agreement with the published data in the open literature. The design of a vaneless diffuser and a volute were considered based on satisfying the governing equations of conservation of mass, momentum, and energy conservation simultaneously. Results showed good agreement with the CFD analysis found in the open literature. This work was motivated by the growing interest in micro-gas turbines for electrical power generation, transport and other applications.

Published in	American Journal of Aerospace Engineering (Volume 4, Issue 2)
DOI	10.11648/j.ajae.20170402.11
Page(s)	6-21
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2017. Published by Science Publishing Group

Keywords

Centrifugal Compressor, Vaneless Diffuser, Impeller, Mean Stream Velocity, Optimization

References

[1]	Japikse, D. “Decisive factors in advanced centrifugal compressor design and development,” in Proceedings of the International Mechanical Engineering Congress & Exposition, Nov. 2000.
[2]	Xu C., Amano R. S., “Development of a low flow coefficient single stage centrifugal compressor,” International Journal of International Journal of Computational Methods in Engineering Science and Mechanics, Vol. 10, 2009, pp. 282–289.
[3]	Aungier R. H., “Centrifugal Compressors—A Strategy for Aerodynamic Design and Analysis”. ASME Press, New York, NY, USA, 2002.
[4]	Xu C., “Design experience and considerations for centrifugal compressor development,” Proceedings of the Institution of Mechanical Engineers, Part G, Vol. 221, 2007, pp. 273–287.
[5]	Cosentino R., Alsalihi Z., Braembussche V. R. A., “Expert system for radial impeller optimization”. Proceedings of Euroturbo, 2001.
[6]	Perdichizzi A., Savini M., “Aerodynamic and geometric optimization for the design of centrifugal compressors”. International Journal of Heat and Fluid Flow, Vol. 6, issue 1, March 1985, pp. 49–56.
[7]	Al-Zibaidy S. N., “A proposed design package for centrifugal impellers”. Computers and structures, Vol. 55, issue 2, April 1995, pp. 347–356.
[8]	Xu C., Amano R. S., “Empirical Design Considerations for Industrial Centrifugal Compressors”. International Journal of Rotating Machinery, Vol. 2012, 15 pages.
[9]	Cho S. Y., Ahn K. Y., Lee Y. D., Kim Y. C., “Optimal Design of a Centrifugal Compressor Impeller Using Evolutionary Algorithms”. Mathematical Problems in Engineering, Vol. 2012, 22 pages.
[10]	Ibaraki S., Sugimoto K., Tomito I., “Aerodynamic design optimization of a centrifugal compressor impeller based on an artificial neural network and genetic algorithm” Mitsubishi Heavy Industries Technical Review, Vol. 52, 1, March, 2015.
[11]	Bonaiuti D., Arnone A., Ermini M., Baldassarre L., “Analysis and optimization of transonic centrifugal compressor impellers using the design of experimental technique,” GT-2002-30619, 2002.
[12]	Verstraete T., Alkaloid Z., Van den R. A., “Multidisciplinary optimization of a radial compressor for microgas turbine applications,” Journal of Turbomachinery, Vol. 132, 3, 2010, 7 pages.
[13]	Ingham, D. R. and Bhinder, F. S., “The effect of inducer shape on the performance of high pressure ratio centrifugal compressors”. ASME paper, No. 74-GT-122, 1974.
[14]	Stahler, A. F., “Transonic flow problems in centrifugal compressors”. SAE, preprint No. 268C, Jan. 1961.
[15]	Polikovsky, V. and Nevelson, M., “The performance of a vaneless diffuser fan”. NACA. TM 1038, 1942.
[16]	Brown, W. B. “Friction coefficient in a vaneless diffuser”. NACA. TN 1311, 1947.
[17]	Brown, W. B. and Bradshaw, G. R. “Methods of designing vaneless diffusers and experimental investigation of certain undetermined parameters”. NACA. TN 1426, 1947.
[18]	Stantiz, J. D. “Some theoretical aerodynamic investigations of impellers in radial and mixed flow centrifugal compressors”. Transaction of ASME 74:374, 1952.
[19]	Dean, R. C., Senoo, Y. “Rotating wakes in a radial vaneless diffuser”. ASME., Series D, Sept. 1960.
[20]	Johnston, J. R., Dean, R. C. “Losses in vaneless diffuser on centrifugal compressors and pumps” Transaction ASME, Journal of engineering for power, Vol. 88, No. 1, Jan. 1966.
[21]	Bettini C., Cravero C., Rosatelli F., Zito D., "The Design of the centrifugal Compressor for a 100kW micro gas turbine power plant".
[22]	Zahed A. H., Bayomi N. N., “ISESCO Journal of Science and Technology”, Vol. 10, 17, 2014, pp. 77-91.
[23]	Marefat A., Shahhosseini M. R., Ashjari M. A. "Adapted design of multistage centrifugal compressor and comparison with available data", International Journal of Materials, Mechanics and Manufacturing. Vol. 1, 2, May 2013.
[24]	Kurauchi S. K. Barbosa J. R. "Design of centrifugal compressor for natural gas". Vol. 12, 2, 2013, pp.40 -45.
[25]	Li P. y., Gu C. W., Song Y. "A new optimization method for centrifugal compressors based on 1D calculations and analysis". Energies. Vol. 8, 2015, pp. 4317-4334.
[26]	Gui F., Reinarts T. R., Scaringe R. P., Gottschlich J. M., "Design and experimental study on high speed low flow rate centrifugal compressors". IECECP, paper No. CT-39.
[27]	Moroz L., Govoruschenko Y., Pagur P., Romaneko L. "Integrated conceptual design environment for centrifugal compressors flow path design". Proceedings of IMECE, 2008.
[28]	Bowade A., Parashhkar C. "A review of different design methods for radial flow centrifugal pumps". International Journal of Scientific Engineering and Research (IJSER). Vol. 3, 7, 2015.
[29]	Biggs, M. C., “Recursive quadratic programming methods for non-linear constraints”. In Powel, M. J. C., ed., “Nonlinear optimization”. 1981.
[30]	Biggs, M. C., “Further methods for nonlinear optimization”. Mathematics division, University of Hertfordshire, 1999.
[31]	Numerical optimization centre. “Optima manual”. School of Information sciences, Hatfield Polytechnic. Issue No.8, July 1989.
[32]	Dallenbach, Coppage et al. “Study of supersonic radial compressors for refrigeration and pressurization”. WADC Techincal Report 55-257, A. S. T. I. A document No. AD110467, Dec 1956.
[33]	Rodgers C., A diffusion factor correlation for centrifugal impeller stalling, Trans. ASME. Jr. of Eng. for Power, Vol. 100. Oct, 1978.
[34]	Eckardt D. “Detailed flow investigations within a high-speed centrifugal compressor impeller”, Trans. ASME, September, 1976.
[35]	Tough R. A., Tousi A. M., Ghaffari J., “Improving of the micro-turbine's centrifugal impeller performance by changing the blade angles”. ICCES, Vol. 14(1), pp. 1-22, 2010.
[36]	Fisher, F. B., “Development of vaned diffuser components for heavy duty diesel engine turbocharger”. I. MechE, Conference on turbocharging and Turbochargers, London, Paper No. C108/86, 1986, pp. 21-30.

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Munzer Shehadeh Yousef Ebaid, Qusai Zuhair Mohmmad Al-Hamdan. (2017). Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output. American Journal of Aerospace Engineering, 4(2), 6-21. https://doi.org/10.11648/j.ajae.20170402.11

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ACS Style

Munzer Shehadeh Yousef Ebaid; Qusai Zuhair Mohmmad Al-Hamdan. Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output. Am. J. Aerosp. Eng. 2017, 4(2), 6-21. doi: 10.11648/j.ajae.20170402.11

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AMA Style

Munzer Shehadeh Yousef Ebaid, Qusai Zuhair Mohmmad Al-Hamdan. Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output. Am J Aerosp Eng. 2017;4(2):6-21. doi: 10.11648/j.ajae.20170402.11

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@article{10.11648/j.ajae.20170402.11,
  author = {Munzer Shehadeh Yousef Ebaid and Qusai Zuhair Mohmmad Al-Hamdan},
  title = {Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output},
  journal = {American Journal of Aerospace Engineering},
  volume = {4},
  number = {2},
  pages = {6-21},
  doi = {10.11648/j.ajae.20170402.11},
  url = {https://doi.org/10.11648/j.ajae.20170402.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.20170402.11},
  abstract = {In this current work, the design of a single stage centrifugal compressor as part of a complete small gas turbine coupled directly to high speed permanent magnet running at 60000rpm and developing a maximum electrical power of 60kW is presented. The choice of a radial impeller was considered and the design was based on using a non-linear optimisation code to determine the geometric dimensions of the impeller. Also, the optimum axial length and the flow passage of the impeller were found based on prescribed mean stream velocity. The proposed code was verified and showed quite good agreement with the published data in the open literature. The design of a vaneless diffuser and a volute were considered based on satisfying the governing equations of conservation of mass, momentum, and energy conservation simultaneously. Results showed good agreement with the CFD analysis found in the open literature. This work was motivated by the growing interest in micro-gas turbines for electrical power generation, transport and other applications.},
 year = {2017}
}

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TY  - JOUR
T1  - Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output
AU  - Munzer Shehadeh Yousef Ebaid
AU  - Qusai Zuhair Mohmmad Al-Hamdan
Y1  - 2017/07/20
PY  - 2017
N1  - https://doi.org/10.11648/j.ajae.20170402.11
DO  - 10.11648/j.ajae.20170402.11
T2  - American Journal of Aerospace Engineering
JF  - American Journal of Aerospace Engineering
JO  - American Journal of Aerospace Engineering
SP  - 6
EP  - 21
PB  - Science Publishing Group
SN  - 2376-4821
UR  - https://doi.org/10.11648/j.ajae.20170402.11
AB  - In this current work, the design of a single stage centrifugal compressor as part of a complete small gas turbine coupled directly to high speed permanent magnet running at 60000rpm and developing a maximum electrical power of 60kW is presented. The choice of a radial impeller was considered and the design was based on using a non-linear optimisation code to determine the geometric dimensions of the impeller. Also, the optimum axial length and the flow passage of the impeller were found based on prescribed mean stream velocity. The proposed code was verified and showed quite good agreement with the published data in the open literature. The design of a vaneless diffuser and a volute were considered based on satisfying the governing equations of conservation of mass, momentum, and energy conservation simultaneously. Results showed good agreement with the CFD analysis found in the open literature. This work was motivated by the growing interest in micro-gas turbines for electrical power generation, transport and other applications.
VL  - 4
IS  - 2
ER  -

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Author Information

Munzer Shehadeh Yousef Ebaid

Mechanical Engineering Department, Faculty of Engineering, Philadelphia University, Amman, Jordan
Qusai Zuhair Mohmmad Al-Hamdan

Aircraft Engineering Department, Perth College, University of the Highlands and Islands, Perth PH2 8PD, Scotland, UK

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APA Style

Munzer Shehadeh Yousef Ebaid, Qusai Zuhair Mohmmad Al-Hamdan. (2017). Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output. American Journal of Aerospace Engineering, 4(2), 6-21. https://doi.org/10.11648/j.ajae.20170402.11

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ACS Style

Munzer Shehadeh Yousef Ebaid; Qusai Zuhair Mohmmad Al-Hamdan. Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output. Am. J. Aerosp. Eng. 2017, 4(2), 6-21. doi: 10.11648/j.ajae.20170402.11

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AMA Style

Munzer Shehadeh Yousef Ebaid, Qusai Zuhair Mohmmad Al-Hamdan. Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output. Am J Aerosp Eng. 2017;4(2):6-21. doi: 10.11648/j.ajae.20170402.11

Copy | Download

@article{10.11648/j.ajae.20170402.11,
  author = {Munzer Shehadeh Yousef Ebaid and Qusai Zuhair Mohmmad Al-Hamdan},
  title = {Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output},
  journal = {American Journal of Aerospace Engineering},
  volume = {4},
  number = {2},
  pages = {6-21},
  doi = {10.11648/j.ajae.20170402.11},
  url = {https://doi.org/10.11648/j.ajae.20170402.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.20170402.11},
  abstract = {In this current work, the design of a single stage centrifugal compressor as part of a complete small gas turbine coupled directly to high speed permanent magnet running at 60000rpm and developing a maximum electrical power of 60kW is presented. The choice of a radial impeller was considered and the design was based on using a non-linear optimisation code to determine the geometric dimensions of the impeller. Also, the optimum axial length and the flow passage of the impeller were found based on prescribed mean stream velocity. The proposed code was verified and showed quite good agreement with the published data in the open literature. The design of a vaneless diffuser and a volute were considered based on satisfying the governing equations of conservation of mass, momentum, and energy conservation simultaneously. Results showed good agreement with the CFD analysis found in the open literature. This work was motivated by the growing interest in micro-gas turbines for electrical power generation, transport and other applications.},
 year = {2017}
}

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TY  - JOUR
T1  - Design of a Single Stage Centrifugal Compressor as Part of a Microturbine Running at 60000 rpm, Developing a Maximum of 60 kW Electrical Power Output
AU  - Munzer Shehadeh Yousef Ebaid
AU  - Qusai Zuhair Mohmmad Al-Hamdan
Y1  - 2017/07/20
PY  - 2017
N1  - https://doi.org/10.11648/j.ajae.20170402.11
DO  - 10.11648/j.ajae.20170402.11
T2  - American Journal of Aerospace Engineering
JF  - American Journal of Aerospace Engineering
JO  - American Journal of Aerospace Engineering
SP  - 6
EP  - 21
PB  - Science Publishing Group
SN  - 2376-4821
UR  - https://doi.org/10.11648/j.ajae.20170402.11
AB  - In this current work, the design of a single stage centrifugal compressor as part of a complete small gas turbine coupled directly to high speed permanent magnet running at 60000rpm and developing a maximum electrical power of 60kW is presented. The choice of a radial impeller was considered and the design was based on using a non-linear optimisation code to determine the geometric dimensions of the impeller. Also, the optimum axial length and the flow passage of the impeller were found based on prescribed mean stream velocity. The proposed code was verified and showed quite good agreement with the published data in the open literature. The design of a vaneless diffuser and a volute were considered based on satisfying the governing equations of conservation of mass, momentum, and energy conservation simultaneously. Results showed good agreement with the CFD analysis found in the open literature. This work was motivated by the growing interest in micro-gas turbines for electrical power generation, transport and other applications.
VL  - 4
IS  - 2
ER  -

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