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An Enhanced Flow-Thermo-Structural Modeling and Validation for the Integrated Analysis of a Film Cooling Nozzle Guide Vane

Author

Listed:
  • Peng Guan

    (School of Power and Energy, Northwestern Ploytechnical University, Xi’an 710072, China)

  • Yan-Ting Ai

    (Faculty of Aviation Engine, Shenyang Aerospace University, Shenyang 110136, China)

  • Cheng-Wei Fei

    (Department of Aeronautics and Astronautics, Fudan University, Shanghai 200433, China)

Abstract

The target of this paper is to develop an enhanced flow-thermo-structural (FTS) model with high computational accuracy, to perform the integrated analysis of film cooling nozzle guide vane (NGV). An efficient turbulence model and weak spring approach are utilized in the enhanced FTS model. In respect of the power balance principle of aeroengine rotor shaft and temperature test of a typical combustor, the mean temperature inlet and five normalization temperature curves were confirmed, respectively. The temperature-sensitive paint (TSP) technology was used to verify the numerical simulation. From this study, we find that the predicted temperature caters for the TSP test well, between which the maximum error is less than 6%, and the maximum thermal stress is 758 MPa around the hole edges and the location of stress concentration keeps the consistency with that of the cracks. The maximum thermal stress increases by 10% with the increasing inlet temperature and reduces by about 16% with the shifting of flame peak from the outer to inner hub. The prediction provides general information on the initiation of cracks on a vane segment. The developed enhanced FTS model is validated to be workable and precise in the integrated analysis of film cooling NGV. The efforts of this study provide an integrated analysis approach of film cooling NGV and are promising to provide guidance for the integrated design of film cooling components besides NGV.

Suggested Citation

  • Peng Guan & Yan-Ting Ai & Cheng-Wei Fei, 2019. "An Enhanced Flow-Thermo-Structural Modeling and Validation for the Integrated Analysis of a Film Cooling Nozzle Guide Vane," Energies, MDPI, vol. 12(14), pages 1-20, July.
    • Handle: RePEc:gam:jeners:v:12:y:2019:i:14:p:2775-:d:249829
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    References listed on IDEAS

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    1. Huixiang Chen & Daqing Zhou & Yuan Zheng & Shengwen Jiang & An Yu & You Guo, 2018. "Load Rejection Transient Process Simulation of a Kaplan Turbine Model by Co-Adjusting Guide Vanes and Runner Blades," Energies, MDPI, vol. 11(12), pages 1-18, November.
    2. Kim, Kyung Min & Jeon, Yun Heung & Yun, Namgeon & Lee, Dong Hyun & Cho, Hyung Hee, 2011. "Thermo-mechanical life prediction for material lifetime improvement of an internal cooling system in a combustion liner," Energy, Elsevier, vol. 36(2), pages 942-949.
    3. Chung, Heeyoon & Sohn, Ho-Seong & Park, Jun Su & Kim, Kyung Min & Cho, Hyung Hee, 2017. "Thermo-structural analysis of cracks on gas turbine vane segment having multiple airfoils," Energy, Elsevier, vol. 118(C), pages 1275-1285.
    4. Kim, Kyung Min & Moon, Hokyu & Park, Jun Su & Cho, Hyung Hee, 2014. "Optimal design of impinging jets in an impingement/effusion cooling system," Energy, Elsevier, vol. 66(C), pages 839-848.
    5. Prasert Prapamonthon & Huazhao Xu & Wenshuo Yang & Jianhua Wang, 2017. "Numerical Study of the Effects of Thermal Barrier Coating and Turbulence Intensity on Cooling Performances of a Nozzle Guide Vane," Energies, MDPI, vol. 10(3), pages 1-16, March.
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    Cited by:

    1. Ke Tian & Zicheng Tang & Jin Wang & Milan Vujanović & Min Zeng & Qiuwang Wang, 2021. "Numerical Investigations of Film Cooling and Particle Impact on the Blade Leading Edge," Energies, MDPI, vol. 14(4), pages 1-14, February.
    2. Hongjie Tang & Shicheng Zhang & Jinhui Li & Lingwei Kong & Baoqiang Zhang & Fei Xing & Huageng Luo, 2023. "Imprecise P-Box Sensitivity Analysis of an Aero-Engine Combustor Performance Simulation Model Considering Correlated Variables," Energies, MDPI, vol. 16(5), pages 1-22, March.

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