한국유체기계학회 논문집 (The KSFM Journal of Fluid Machinery)

한국유체기계학회 (Korean Society for Fluid machinery)
권호 표지
DOI QR코드

DOI QR Code

항공기용 가스터빈의 고압 냉각터빈 노즐에 대한 복합열전달 해석

Conjugate Heat Transfer Analysis for High Pressure Cooled Turbine Vane in Aircraft Gas Turbine

  • 김진욱 (한양대학교 기계공학과) ;
  • 박정규 (한양대학교 기계공학과) ;
  • 강영석 (한국항공우주연구원 엔진부품연구팀) ;
  • 조진수 (한양대학교 기계공학과)
  • Kim, Jinuk (Dept. of Mechanical Engineering, Hanyang Univ.) ;
  • Bak, Jeonggyu (Dept. of Mechanical Engineering, Hanyang Univ.) ;
  • Kang, Young-Seok (Engine Component Research Team, Korea Aerospace Research Institute) ;
  • Cho, Jinsoo (Dept. of Mechanical Engineering, Hanyang Univ.)
  • 투고 : 2014.10.20
  • 심사 : 2015.02.13
  • 발행 : 2015.04.01
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

Conjugate heat transfer analysis was performed to investigate the flow and cooling performance of the high pressure turbine nozzle of gas turbine engine. The CHT code was verified by comparison between CFD results and experimental results of C3X vane. The combination of k-${\omega}$ based SST turbulence model and transition model was used to solve the flow and thermal field of the fluid zone and the material property of CMSX-4 was applied to the solid zone. The turbine nozzle has two internal cooling channels and each channel has a complex cooling configurations, such as the film cooling, jet impingement, pedestal and rib turbulator. The parabolic temperature profile was given to the inlet condition of the nozzle to simulate the combustor exit condition. The flow characteristics were analyzed by comparing with uncooled nozzle vane. The Mach number around the vane increased due to the increase of coolant mass flow flowed in the main flow passage. The maximum cooling effectiveness (91 %) at the vane surface is located in the middle of pressure side which is effected by the film cooling and the rib turbulrator. The region of the minimum cooling effectiveness (44.8 %) was positioned at the leading edge. And the results show that the TBC layer increases the average cooling effectiveness up to 18 %.

키워드

참고문헌

  1. Tsukamoto, K., Horiuchi, Y., Sugimura, K. and Higuchi, S., 2014, "Conjugate Heat Transfer Analysis in an Actural Gas Turbine Rotor Blade in Comparison with Pyrometer Data," ASME Turbo Expo, GT2014-26962.
  2. Ho, K. S., Urwiller, C., Konan, S. M., Liu, J. S. and Aguilar, B., 2014, "Conjugate Heat Transfer Analysis for Gas Turbine Cooled Blade," ASME Turbo Expo, GT2014-25952.
  3. Insinna, M., Griffini, D., Salvadori, S. and Martelli, F., 2014, "Conjugate Heat Transfer Analysis of a Film Cooled High-Pressure Turbine Vane under Realistic Combustor Exit Flow Conditions," ASME Turbo Expo, GT2014-25280.
  4. Hylton. L. D., Mihelc. M. S., Turner. E. R., Nealy. D. A. and York. R. E., 1983, "Analytical and Experimental Evaluation of The Heat Transfer Distribution over the Surfaces of Turbine Vanes," AAS/Division of Dynamical Astronomy Meeting.
  5. Qiang, W., Zhaoyuan, G., Chi, Z., Guotai, F. and Zhongqi, W., 2009, "Coupled Heat Transfer Simulation of a High-pressure Turbine Nozzle Guide Vane," Chinese Journal of Aeronautics, 22(2009), pp. 230-236. https://doi.org/10.1016/S1000-9361(08)60092-8
  6. Kim, J., Bak, J., Kang, Y., Cho, L. and Cho, J., 2014, "A Study on the Numerical Analysis Methodology for Thermal and Flow Characteristics of High Pressure Turbine in Aircraft Gas Turbine Engine," The KSFM Journal of Fluid Machinery, Vol. 17, No. 3, pp. 46-51. https://doi.org/10.5293/kfma.2014.17.3.046
  7. Kang, Y. S., Rhee, D. H. and Cha, B. J., 2012, "Aerodynamic design of high pressure turbine for aircraft turbofan engine," Proceeding of the 7th National Congress on Fluids Engineering, pp. 246-247
  8. Seo., J. C., Kim., K. W., Hwang., S. W., Son., C. M., Kim., K. S., Rhee., D. H. and Cha., B. J., 2013, "Design of Gas Turbine Engine 1st stage High Pressure Turbine Nozzle Cooling System," Proceedings of the KFMA Annual Meeting, pp. 137-138.
  9. Song, X., Xie, M., Zhou, F., Jia, G., Hao, X. and An, S., 2011, "High-Temperature Thermal Properties of Yttria Fully Stabilized Zirconia Ceramics," Journal of Rare Earth, Vol. 29, No. 2, pp. 155-159. https://doi.org/10.1016/S1002-0721(10)60422-X
  10. Zhu, D. and Miller, R, A., 1999, "Thermal Conductivity and Elastic Modulus Evolution of Thermal Barrier Coatings Under High Heat Flux Conditions," NASA, TM-1999-209069.
  11. Reed., R. C., Matan., N., Cox., D. C., Rist, M. A. and Rae., C. M. F., 1999, "Creep of CMSX-4 Superalloy Single Crystals: Effects of Rafting At High Temperature," Acta Materialia, Vol. 47, Issue 12, pp. 3367-3381. https://doi.org/10.1016/S1359-6454(99)00217-7

피인용 문헌

  1. 2015년 가스·스팀터빈 분야 연구동향 vol.19, pp.2, 2016, https://doi.org/10.5293/kfma.2016.19.2.063