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Effects of Some Key Parameters on the Overall Performance of Gas Turbine

Received: 6 April 2021    Accepted: 23 April 2021    Published: 8 May 2021
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Abstract

A method for power plant Gas Turbine overall performance evaluation was developed based on the thermodynamic cycle. Some key parameters affecting the simple cycle efficiency and power of the GT, such as compressor pressure ratio, turbine inlet temperature, compressor efficiency, compressor exit diffuser Cp, combustor pressure loss, turbine efficiency, OTDF, RTDF, blade metal allowable temperature and turbine exit diffuser Cp has been studied across a wide range of possible operating conditions. The effects on simple cycle of GT efficiency, GT specific power and turbine exit temperature of these parameters were discussed: The compressor pressure ratio should be chosen to give an optimumGT specific power, and should match turbine inlet temperature; When compressor efficiency increases 1%, the GT efficiency increases about 0.3%, while turbine efficiency increases 1%, the GT efficiency increases about 0.6%; When compressor exit diffuser Cp increases 0.1, the GT efficiency increases about 0.1%, while turbine exit diffuser Cp increases 0.1, the GT efficiency increases about 0.25%; RTDF is more important than OTDF for GT efficiency, When RTDF increases 0.05, the GT efficiency decreases about 0.15%, but When OTDF increases 0.05, the GT efficiency only decreases about 0.02%; When combustor pressure loss increases 1%, the GT efficiency decreases about 0.2%, but combustor pressure loss also effect turbine Nozzle1 cooling design; these parameters should be carefully considered in a new GT design.

Published in International Journal of Energy and Power Engineering (Volume 10, Issue 2)
DOI 10.11648/j.ijepe.20211002.12
Page(s) 37-49
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

Gas Turbine, Overall Performance Prediction, Thermodynamic Cycle, Turbine

References
[1] UshiyamaI. Theoretically estimating the performance of gas turbines under varying atmospheric conditions [J], Journal of Engineering for Power, 1976, 98: 68-79.
[2] Hadik A AEl. The Impact of atmospheric conditions on gas turbine performance [J], Journal of Engineering for Gas Turbines and Power, 1990, 112 (4): 590.
[3] Baugh J W, Mckillop A A, Trelevan K. An analysis of the performance of a gas turbine cogeneration plant [J], Journal of Engineering for Gas Turbines and Power, 1983, 105 (4): 816-820.
[4] KhaliqA, ChoudharyK. Thermodynamic performance assessment of an indirect intercooled reheat regenerative gas turbine cycle with inlet air cooling and evaporative aftercooling of the compressor discharge [J], International Journal of Energy Research, 2010, 30 (15): 1295-1312.
[5] Cai R X. The basic performance of combined cycles and their optimum gas turbine pressure ratios [C], ASME Paper, 1995, 95-GT-416.
[6] Yoshida T, Morikawa T, GotouJ, Hayashi Y. Gas turbine performance analysis method and gas turbine performance analysis system [P], US7797113B2, 2010-09-14.
[7] Sanjay, Singh O, Prasad B N. Comparative performance analysis of cogeneration gas turbine cycle for different blade cooling means [J], International Journal of Thermal Sciences, 2009, 48: 1432-1440.
[8] Sanjay, Investigation of effect of variation of cycle parameters on thermodynamic performance of gas-steam combined cycle [J], Energy, 2011, 36: 157-167.
[9] Kumar S, Singh O. Performance evaluation of simple aero gas turbine cycle with transpiration cooling of gas turbine blades [J], International Journal of Emerging Technology and Advanced Engineering, 2013, 3 (3): 416-420.
[10] Shukla A K, Singh O. Performance evaluation of steam injected gas turbine based power plant with inlet evaporative cooling, Applied Thermal Engineering, 2016, 102: 454-464.
[11] Elwekeel F N M, Abdala A M M. Effect of mist cooling technique on exergy and energy analysis of steam injected gas turbine cycle [J], Applied Thermal Engineering, 2016, 98: 298-309.
[12] Singh H, Tayal P K, Goyal N, Rastogi P M. Effect of ambient temperature, gas turbine inlet temperature and compressor pressure ratio on performance of combined cycle power plant [J], International Journal of Advanced Technology in Engineering and Science, 2016, 4 (1): 1-13.
[13] Gas Turbine Performance. P. P. Walsh& P Fletcher, Blackwell Science 1998 ISBN 0-632-04874-3
[14] Takao Sugimoto, Katsushi Nagai et al. Developoment of a 20MW-Class high-efficiency Gas Turbine L20A [C], ASME Paper, 2002, 2002-GT-30255.
[15] E. Akita et al. ‘M501F/M701F Gas Turbine Uprating’, ASME TURBO EXPO 2001.
[16] EnnioMacchi, GiovanniLozza et al. ‘Gas/Steam Combined Cycles Fueled by Various Energy Sources for Large-Scale Power Production’, 2015
[17] MHI J-Series Gas Turbine Development, 2012.
[18] 9HA POWER PLANTS.
[19] Hitachi, Ltd, Smart AHAT System Smart Energy Solutions by Advanced Humid Air Turbine, 2013.
[20] Barry, B, VKI Lecture Series 83, 1976.
[21] Kacker, S. C, Okapuu, U. ‘A mean line prediction method for axial flow turbine efficiency’ ASME 81-GT-58 1981.
Cite This Article
  • APA Style

    Pengfei Su, Jianmin Gao, Shiquan Zhao, Xiangling Kong, Yu Fang. (2021). Effects of Some Key Parameters on the Overall Performance of Gas Turbine. International Journal of Energy and Power Engineering, 10(2), 37-49. https://doi.org/10.11648/j.ijepe.20211002.12

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    ACS Style

    Pengfei Su; Jianmin Gao; Shiquan Zhao; Xiangling Kong; Yu Fang. Effects of Some Key Parameters on the Overall Performance of Gas Turbine. Int. J. Energy Power Eng. 2021, 10(2), 37-49. doi: 10.11648/j.ijepe.20211002.12

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    AMA Style

    Pengfei Su, Jianmin Gao, Shiquan Zhao, Xiangling Kong, Yu Fang. Effects of Some Key Parameters on the Overall Performance of Gas Turbine. Int J Energy Power Eng. 2021;10(2):37-49. doi: 10.11648/j.ijepe.20211002.12

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  • @article{10.11648/j.ijepe.20211002.12,
      author = {Pengfei Su and Jianmin Gao and Shiquan Zhao and Xiangling Kong and Yu Fang},
      title = {Effects of Some Key Parameters on the Overall Performance of Gas Turbine},
      journal = {International Journal of Energy and Power Engineering},
      volume = {10},
      number = {2},
      pages = {37-49},
      doi = {10.11648/j.ijepe.20211002.12},
      url = {https://doi.org/10.11648/j.ijepe.20211002.12},
      eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijepe.20211002.12},
      abstract = {A method for power plant Gas Turbine overall performance evaluation was developed based on the thermodynamic cycle. Some key parameters affecting the simple cycle efficiency and power of the GT, such as compressor pressure ratio, turbine inlet temperature, compressor efficiency, compressor exit diffuser Cp, combustor pressure loss, turbine efficiency, OTDF, RTDF, blade metal allowable temperature and turbine exit diffuser Cp has been studied across a wide range of possible operating conditions. The effects on simple cycle of GT efficiency, GT specific power and turbine exit temperature of these parameters were discussed: The compressor pressure ratio should be chosen to give an optimumGT specific power, and should match turbine inlet temperature; When compressor efficiency increases 1%, the GT efficiency increases about 0.3%, while turbine efficiency increases 1%, the GT efficiency increases about 0.6%; When compressor exit diffuser Cp increases 0.1, the GT efficiency increases about 0.1%, while turbine exit diffuser Cp increases 0.1, the GT efficiency increases about 0.25%; RTDF is more important than OTDF for GT efficiency, When RTDF increases 0.05, the GT efficiency decreases about 0.15%, but When OTDF increases 0.05, the GT efficiency only decreases about 0.02%; When combustor pressure loss increases 1%, the GT efficiency decreases about 0.2%, but combustor pressure loss also effect turbine Nozzle1 cooling design; these parameters should be carefully considered in a new GT design.},
     year = {2021}
    }
    

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  • TY  - JOUR
    T1  - Effects of Some Key Parameters on the Overall Performance of Gas Turbine
    AU  - Pengfei Su
    AU  - Jianmin Gao
    AU  - Shiquan Zhao
    AU  - Xiangling Kong
    AU  - Yu Fang
    Y1  - 2021/05/08
    PY  - 2021
    N1  - https://doi.org/10.11648/j.ijepe.20211002.12
    DO  - 10.11648/j.ijepe.20211002.12
    T2  - International Journal of Energy and Power Engineering
    JF  - International Journal of Energy and Power Engineering
    JO  - International Journal of Energy and Power Engineering
    SP  - 37
    EP  - 49
    PB  - Science Publishing Group
    SN  - 2326-960X
    UR  - https://doi.org/10.11648/j.ijepe.20211002.12
    AB  - A method for power plant Gas Turbine overall performance evaluation was developed based on the thermodynamic cycle. Some key parameters affecting the simple cycle efficiency and power of the GT, such as compressor pressure ratio, turbine inlet temperature, compressor efficiency, compressor exit diffuser Cp, combustor pressure loss, turbine efficiency, OTDF, RTDF, blade metal allowable temperature and turbine exit diffuser Cp has been studied across a wide range of possible operating conditions. The effects on simple cycle of GT efficiency, GT specific power and turbine exit temperature of these parameters were discussed: The compressor pressure ratio should be chosen to give an optimumGT specific power, and should match turbine inlet temperature; When compressor efficiency increases 1%, the GT efficiency increases about 0.3%, while turbine efficiency increases 1%, the GT efficiency increases about 0.6%; When compressor exit diffuser Cp increases 0.1, the GT efficiency increases about 0.1%, while turbine exit diffuser Cp increases 0.1, the GT efficiency increases about 0.25%; RTDF is more important than OTDF for GT efficiency, When RTDF increases 0.05, the GT efficiency decreases about 0.15%, but When OTDF increases 0.05, the GT efficiency only decreases about 0.02%; When combustor pressure loss increases 1%, the GT efficiency decreases about 0.2%, but combustor pressure loss also effect turbine Nozzle1 cooling design; these parameters should be carefully considered in a new GT design.
    VL  - 10
    IS  - 2
    ER  - 

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Author Information
  • State Key Laboratory of Mechanical Manufacturing Systems Engineering, Xi’an Jiaotong University, Xi’an, China; Dongfang Turbine Co., Ltd., Deyang, China

  • State Key Laboratory of Mechanical Manufacturing Systems Engineering, Xi’an Jiaotong University, Xi’an, China

  • Dongfang Turbine Co., Ltd., Deyang, China

  • Dongfang Turbine Co., Ltd., Deyang, China

  • Dongfang Turbine Co., Ltd., Deyang, China

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