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A new transient performance adaptation method for an aero gas turbine engine

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  • Kim, Sangjo
  • Kim, Kuisoon
  • Son, Changmin

Abstract

The performance adaptation method based on the transient measurement data is proposed to generate a dynamic simulation model for gas turbine engines. The performance maps of the compressors and turbines are adjusted by using scaling factors. The time delay in transient temperature measurement is considered in the performance adaptation process by independently modeling a thermocouple section. A new heat transfer correction factor is introduced for the thermocouple modeling. Optimization techniques are employed to find the scaling factors and the heat transfer correction factor. Low-bypass ratio mixed-flow turbofan engines (F100 and F404-GE-400 engines) are employed for testing the proposed method and evaluating its effectiveness. The results reveal that the adapted engine model has good agreement with transient measurement data for the turbofan engines. In particular, the turbine exit temperature from a thermocouple shows a large time delay during transient operation. It has been confirmed that the proposed method can predict the temperatures for the thermocouple and the main flow path, respectively. As a result, the accuracy of the performance adaptation could be improved by considering the time delay for the turbine outlet temperature.

Suggested Citation

  • Kim, Sangjo & Kim, Kuisoon & Son, Changmin, 2020. "A new transient performance adaptation method for an aero gas turbine engine," Energy, Elsevier, vol. 193(C).
    • Handle: RePEc:eee:energy:v:193:y:2020:i:c:s0360544219324478
    DOI: 10.1016/j.energy.2019.116752
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    References listed on IDEAS

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    1. 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.
    2. Tsoutsanis, Elias & Meskin, Nader & Benammar, Mohieddine & Khorasani, Khashayar, 2014. "A component map tuning method for performance prediction and diagnostics of gas turbine compressors," Applied Energy, Elsevier, vol. 135(C), pages 572-585.
    3. 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.
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    Citations

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    Cited by:

    1. Cheng, Xianda & Zheng, Haoran & Yang, Qian & Zheng, Peiying & Dong, Wei, 2023. "Surrogate model-based real-time gas path fault diagnosis for gas turbines under transient conditions," Energy, Elsevier, vol. 278(PA).
    2. Cui, Zhiquan & Yan, Zhiqi & Zhao, Minghang & Zhong, Shisheng, 2022. "Gas path parameter prediction of aero-engine based on an autoregressive discrete convolution sum process neural network," Chaos, Solitons & Fractals, Elsevier, vol. 154(C).
    3. 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).
    4. Cheng, Xianda & Zheng, Haoran & Dong, Wei & Yang, Xuesen, 2023. "Performance prediction of marine intercooled cycle gas turbine based on expanded similarity parameters," Energy, Elsevier, vol. 265(C).
    5. Zhao, Hang & Liao, Zengbu & Liu, Jinxin & Li, Ming & Liu, Wei & Wang, Lei & Song, Zhiping, 2022. "A highly robust thrust estimation method with dissimilar redundancy framework for gas turbine engine," Energy, Elsevier, vol. 245(C).
    6. Xu, Maojun & Liu, Jinxin & Li, Ming & Geng, Jia & Wu, Yun & Song, Zhiping, 2022. "Improved hybrid modeling method with input and output self-tuning for gas turbine engine," Energy, Elsevier, vol. 238(PA).
    7. Chen, Yu-Zhi & Zhao, Xu-Dong & Xiang, Heng-Chao & Tsoutsanis, Elias, 2021. "A sequential model-based approach for gas turbine performance diagnostics," Energy, Elsevier, vol. 220(C).
    8. Wei, Zhiyuan & Zhang, Shuguang & Jafari, Soheil & Nikolaidis, Theoklis, 2022. "Self-enhancing model-based control for active transient protection and thrust response improvement of gas turbine aero-engines," Energy, Elsevier, vol. 242(C).

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