한국유체기계학회 논문집 (The KSFM Journal of Fluid Machinery)

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

DOI QR Code

케이싱 그루브가 존재하는 축류압축기의 성능특성 연구

A Study on Performance Characteristics of an Axial Compressor with the Casing Groove

  • 최광진 (인하대학교 대학원 기계공학과) ;
  • 김진혁 (인하대학교 대학원 기계공학과) ;
  • 김광용 (인하대학교 기계공학부)
  • 투고 : 2009.12.16
  • 심사 : 2010.02.23
  • 발행 : 2010.04.01
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

This paper presents a study on the performance of NASA Rotor 37 with the casing grooves based on three-dimensional numerical analysis. Reynolds-averaged Navier-Stokes equations are solved on a hexahedral grid with the shear stress transport model as a turbulence closure model. The governing equations are discretized by a finite volume method. The validation of the numerical results is performed through experimental data for the total pressure ratio and the adiabatic efficiency. The investigation for an axial compressor with a smooth casing and the casing grooves is carried out to compare the performance parameters, for example, surge margin and efficiency, etc. The surge margin is improved in the case of the casing grooves while remarkable improvement of the efficiency is not produced. The result shows that the casing groove is beneficial to expand the operating range of NASA Rotor 37.

키워드

참고문헌

  1. Gourdain, N., Burguburu, S., Leboeuf, F., and Miton, H., 2006, “Numerical Simulation of Rotating Stall in a Subsonic Compressor,” Aerospace Science and Technology, Vol. 10, pp. 9-18. https://doi.org/10.1016/j.ast.2005.07.006
  2. Choi, M. S., Oh, S. H., Ko, H. Y., and Baek, J. H., 2008, “Effects of the Inlet Boundary Layer Thickness on Rotating Stall in Axial Compressor,” ASME Turbo Expo, GT2008-50886.
  3. Saxer-Felici H. M., Saxer, A. P., Inderbitzin, A., and Gyarmathy, G., 2000, “Numerical and Experimental Study of Rotating Stall in an Axial Compressor Stage,” AIAA Journal, vol. 38, No. 7, pp. 1132-1141. https://doi.org/10.2514/2.1106
  4. Hah, C., Rabe, D. C., and Wadia, A. R., 2004, “Role of Tip-Leakage Vortices and Passage Shock in Stall Inception in a Swept Transonic Compressor Rotor,” ASME Turbo Expo, GT2004- 53867.
  5. Huang, X., Chen, H., and Fu, S., 2008, “CFD Investigation on the Circumferential Grooves Casing Treatment of Transonic Compressor,” ASME Turbo Expo, GT2008-51107.
  6. Muller, M. W., Schiffer, H. P., and Hah, C., 2007, “Effect of Circumferential Grooves on the Aerodynamic Performance of an Axial Single-stage Transonic Compressor,” ASME Turbo Expo, GT2007-27365.
  7. Houghton, T., and Day, I., 2009, “Enhancing the Stability of Subsonic Compressors Using Casing Grooves,” ASME Turbo Expo, GT2009-59210.
  8. Shabbir, A., and Adamczyk, J. J., 2005, “Flow Mechanism for Stall Margin Improvement due to Circumferential Casing Grooves on Axial Compressors,” Journal of Turbomachinery, Vol. 127. No. 4, pp. 708-717. https://doi.org/10.1115/1.2008970
  9. Reid, L., and Moore, R. D., 1978, “Design and Overall Performance of Four Highly-Loaded, High-Speed Inlet Stages for an Advanced, High-Pressure-Ratio Core Compressor,” NASA TP-1337.
  10. Dunham, J., 1998, “CFD Validation for Through-Flow Calculations,” AGARD Advisory Report 355, ISBN 92-836-1075-X.
  11. ANSYS CFX-11.0, 2006, Ansys inc.
  12. Bardina, J. E., Huang, P. G., and Coakley, T., 1997, “Turbulence Modeling Validation,” 28th AIAA Fluid Dynamics Conference, AIAA-1997- 2121.
  13. Chen, H., Huang, X., Fu, S., 2006, “CFD Investigation on Stall Mechanisms and Casing Treatment of a Transonic Compressor,” AIAA-2006-4799.