American Journal of Aerospace Engineering

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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

Received: 06 March 2017    Accepted: 05 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.

DOI 10.11648/j.ajae.20170402.11
Published in American Journal of Aerospace Engineering (Volume 4, Issue 2, April 2017)
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), 2024. Published by Science Publishing Group

Keywords

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

References
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Author Information
  • Mechanical Engineering Department, Faculty of Engineering, Philadelphia University, Amman, Jordan

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

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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://download.sciencepg.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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    AU  - Munzer Shehadeh Yousef Ebaid
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    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.
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