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Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine

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  • Myung Gon Choi

    (School of Mechanical Engineering, Chung-Ang University, 84, Heukseok-ro, Dongjak-gu, Seoul 06974, Korea)

  • Jaiyoung Ryu

    (School of Mechanical Engineering, Chung-Ang University, 84, Heukseok-ro, Dongjak-gu, Seoul 06974, Korea)

Abstract

Combined cycle power plants (CCPPs) are becoming more important as the global demand for electrical power increases. The power and efficiency of CCPPs are directly affected by the performance and thermal efficiency of the gas turbines. This study is the first unsteady numerical study that comprehensively considers axial gap (AG) in the first-stage stator and first-stage rotor (R1) and hot streaks in the combustor outlet throughout an entire two-stage turbine, as these factors affect the aerodynamic performance of the turbine. To resolve the three-dimensional unsteady-state compressible flow, an unsteady Reynolds-averaged Navier–Stokes (RANS) equation was used to calculate a k − ω SST γ turbulence model. The AG distance d was set as 80% (case 1) and 120% (case 3) for the design value case 2 (13 mm or d/Cs 1 = 0.307) in a GE-E 3 gas turbine model. Changes in the AG affect the overall flow field characteristics and efficiency. If AG decreases, the time-averaged maximum temperature and pressure of R1 exhibit differences of approximately 3 K and 400 Pa, respectively. In addition, the low-temperature zone around the hub and tip regions of R1 and second-stage rotor (R2) on the suction side becomes smaller owing to a secondary flow and the area-averaged surface temperature increases. The area-averaged heat flux of the blade surface increases by a maximum of 10.6% at the second-stage stator and 2.8% at R2 as the AG decreases. The total-to-total efficiencies of the overall turbine increase by 0.306% and 0.295% when the AG decreases.

Suggested Citation

  • Myung Gon Choi & Jaiyoung Ryu, 2018. "Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine," Energies, MDPI, vol. 11(10), pages 1-15, October.
  • Handle: RePEc:gam:jeners:v:11:y:2018:i:10:p:2654-:d:173766
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    References listed on IDEAS

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    1. Xiuli Mao & Andrea Dal Monte & Ernesto Benini & Yuan Zheng, 2017. "Numerical Study on the Internal Flow Field of a Reversible Turbine during Continuous Guide Vane Closing," Energies, MDPI, vol. 10(7), pages 1-22, July.
    2. Roberto Meloni & Vincenzo Naso, 2013. "An Insight into the Effect of Advanced Injection Strategies on Pollutant Emissions of a Heavy-Duty Diesel Engine," Energies, MDPI, vol. 6(9), pages 1-21, August.
    3. Zeng-Rong Hao & Chun-Wei Gu & Xiao-Dong Ren, 2014. "The Application of Discontinuous Galerkin Methods in Conjugate Heat Transfer Simulations of Gas Turbines," Energies, MDPI, vol. 7(12), pages 1-21, November.
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    1. Jae-Sung Oh & Taehak Kang & Seokgyun Ham & Kwan-Sup Lee & Yong-Jun Jang & Hong-Sun Ryou & Jaiyoung Ryu, 2019. "Numerical Analysis of Aerodynamic Characteristics of Hyperloop System," Energies, MDPI, vol. 12(3), pages 1-17, February.
    2. Thi Thanh Giang Le & Kyeong Sik Jang & Kwan-Sup Lee & Jaiyoung Ryu, 2020. "Numerical Investigation of Aerodynamic Drag and Pressure Waves in Hyperloop Systems," Mathematics, MDPI, vol. 8(11), pages 1-23, November.
    3. Thanh Dam Mai & Jaiyoung Ryu, 2021. "Effects of Damaged Rotor Blades on the Aerodynamic Behavior and Heat-Transfer Characteristics of High-Pressure Gas Turbines," Mathematics, MDPI, vol. 9(6), pages 1-21, March.
    4. Seung Il Baek & Jaiyoung Ryu & Joon Ahn, 2021. "Large Eddy Simulation of Film Cooling with Forward Expansion Hole: Comparative Study with LES and RANS Simulations," Energies, MDPI, vol. 14(8), pages 1-19, April.
    5. Thanh Dam Mai & Jaiyoung Ryu, 2020. "Effects of Leading-Edge Modification in Damaged Rotor Blades on Aerodynamic Characteristics of High-Pressure Gas Turbine," Mathematics, MDPI, vol. 8(12), pages 1-21, December.

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