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Bleed air CFD modelling in aerodynamic simulation of A heavy duty gas turbine compressor

Author

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  • Qiang, Xiaoqing
  • Lu, Yao
  • Li, Jian

Abstract

This study investigates the effects of different bleed air CFD modelling methods on the aerodynamic simulation of a heavy-duty gas turbine multistage compressor with bleed airflow. Two methods, the local source term method and the simplified bleed off-take geometry method, are compared. The results reveal that while overall compressor performance shows minimal variation between the methods, significant differences are observed near the blade tip region. The bleed source term method predicts a more uniform flow field in the bleed cavity, leading to a larger surge margin for the compressor. Therefore, in the analysis of multistage compressors, it is advisable to adopt simplified geometric modeling method for simulating bleed air extraction. Moreover, when utilizing this approach, careful consideration should be given to the choice of the slot inclination angle. This design parameter presents a crucial trade-off between losses within the exhaust structure and those arising from the entry of mainstream flow into the exhaust slot cavity.

Suggested Citation

  • Qiang, Xiaoqing & Lu, Yao & Li, Jian, 2024. "Bleed air CFD modelling in aerodynamic simulation of A heavy duty gas turbine compressor," Energy, Elsevier, vol. 299(C).
    • Handle: RePEc:eee:energy:v:299:y:2024:i:c:s0360544224011964
    DOI: 10.1016/j.energy.2024.131423
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    References listed on IDEAS

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    1. Mohammadian, Poorya Keshavarz & Saidi, Mohammad Hassan, 2019. "Simulation of startup operation of an industrial twin-shaft gas turbine based on geometry and control logic," Energy, Elsevier, vol. 183(C), pages 1295-1313.
    2. Sun, Haoran & Duan, Zhongdi & Wang, Xuyang & Wang, Dawei & Wu, Chengyun, 2023. "A pressure-node based dynamic model for simulation and control of aircraft air-conditioning systems," Energy, Elsevier, vol. 263(PD).
    3. Kim, Sangjo & Son, Changmin & Kim, Kuisoon, 2017. "Combining effect of optimized axial compressor variable guide vanes and bleed air on the thermodynamic performance of aircraft engine system," Energy, Elsevier, vol. 119(C), pages 199-210.
    4. Kim, Sangjo, 2021. "A new performance adaptation method for aero gas turbine engines based on large amounts of measured data," Energy, Elsevier, vol. 221(C).
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    Cited by:

    1. Yuan, Wei & Lu, Xiangwu & Feng, Xueheng & Zhang, Qian & Zhang, Lei, 2026. "Influence of inlet distortion on stall inception in supercritical CO2 compressor," Energy, Elsevier, vol. 347(C).
    2. Luo, Qiao & Luo, Lei & Du, Wei & Yan, Han & Wang, Songtao, 2024. "Numerical investigations of aerodynamic characteristics in highly loaded tandem cascades with end-bend," Energy, Elsevier, vol. 311(C).

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