The KSFM Journal of Fluid Machinery (한국유체기계학회 논문집)

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

DOI QR Code

Design Optimization of Fan-shaped Film Cooling Hole Array on Pressure Side Surface of High Pressure Turbine Nozzle

고압터빈 노즐 압력면에서의 확장 형상 막냉각 홀 배열 최적설계

  • Lee, Sanga (Seoul National University, Department of Mechanical and Aerospace Engineering) ;
  • Rhee, Dong-Ho (Korea Aerospace Research Institute, Engine component technology team) ;
  • Kang, Young-Seok (Korea Aerospace Research Institute, Engine component technology team) ;
  • Kim, Jinuk (Hanyang University, Department of Mechanical Engineering) ;
  • Seo, Do-Young (Pusan National University, Department of Aerospace Engineering) ;
  • Yee, Kwanjung (Seoul National University, Department of Mechanical and Aerospace Engineering)
  • 이상아 (서울대학교 기계항공공학부) ;
  • 이동호 (한국항공우주연구원 엔진요소기술팀) ;
  • 강영석 (한국항공우주연구원 엔진요소기술팀) ;
  • 김진욱 (한양대학교 기계공학과) ;
  • 서도영 (부산대학교 항공우주공학과) ;
  • 이관중 (서울대학교 기계항공공학부)
  • Received : 2014.11.14
  • Accepted : 2014.10.09
  • Published : 2014.12.01
Download PDF
⟨ Previous Next ⟩

Abstract

In the present work, design optimization of film-cooling hole array on the pressure side of high pressure turbine nozzle was conducted. There are four rows of fan-shaped film cooling holes on the nozzle pressure side surface and each row has a straight array of holes in the spanwise direction for baseline model. For design optimization, hole distributions in streamwise and spanwise directions for three rows of holes except first row are parameterized as a 2nd-order shape function. Three-dimensional compressible RANS equations are used for flow and thermal analysis around the nozzle surface and optimization technique using Design of Experiment, Kriging surrogate model and Genetic Algorithm is used. The results shows that averaged adiabatic wall temperature at the whole nozzle surface decreases about 2.7% and averaged film cooling effectiveness at the pressure side of nozzle increased about 8.2%.

Keywords

References

  1. Bunker, R. S., 2005, "A Review of Shaped Hole Turbine Film-Cooling Technology," J. Heat Transfer, Vol. 127, No. 4, pp. 441-4532. https://doi.org/10.1115/1.1860562
  2. Lu, Y., 2007, "Effect of Hole Configurations on Film Cooling from Cylindrical Inclined Holes for the Application to Gas Turbine Blades," Ph. D Thesis, Luoisiana State University.
  3. Kim, Y. B., Rhee, D. H., Lee, Y. S., and Cho, H. H., 2004, "The Effects of Staggered Rows of Rectangular Shaped Holes on Film Cooling," Trans. of the KSME (B), Vol. 28, No. 3, pp. 304-314. https://doi.org/10.3795/KSME-B.2004.28.3.304
  4. Ahn, J., Jung, I. S., Lee, J. S., 2001, "Film Cooling from Two Rows of Holes with Opposite Orientation Angles (I)," Trans. of the KSME (B) Vol. 25, No. 8, pp. 1122-1130.
  5. Johnson, J. J., King, P. I., Clark, J. P., and Ooten, M. K. 2013, "Genetic Algorithm Optimization of a High-Pressure Turbine Vane Pressure Side Film Cooling Array," Journal of Turbomachinery, Vol. 136, No. 1, p 011011. https://doi.org/10.1115/1.4023470
  6. Kang, Y. S., Rhee, D. H., 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.
  7. 서종철, 김경우, 황선우, 손창민, 김귀순, 이동호, 차봉준, 2013, "가스터빈 엔진 고압 터빈 1단 노즐의 내각계통 설계," 한국유체기계학회 학술대회, 137-138.
  8. R. H. Myers, D. C. Montgomery, C. M. anderson-cook, 2009, Response Surface Methodology, Wiley.
  9. T. W. Simpson, T. M. Mauery, J. J. Korte, F. Mistree, 2001, "Kriging Models for Global Approximation in Simulation-Based Multidisciplinary Design Optimization," AIAA Journal, Vol. 39, No. 12.
  10. K. Deb, A. Pratap, S. Agarwal, Metarivan, 2002, "A Fast and Elitist Multiobjective Genetic Algorithm : NSGA-II," IEEE Transactions On Evolutionary Computation, Vol. 6, No. 2, pp. 182-198. https://doi.org/10.1109/4235.996017
  11. 채상현, 양충모, 정신규, Takashi Aoyama, Shigeru Obayashi, 이관중, 2009, "헬리콥터의 고속충격소음 감소를 위한 블레이드 평면형상 최적화," 한국전산유체공학회지, 제 14권, 제 1호, pp. 53-61.

Cited by

  1. 2014년 가스·스팀터빈 분야 연구동향 vol.18, pp.2, 2014, https://doi.org/10.5293/kfma.2015.18.2.082