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Compressibility correction of the Panel Method in Flow Analysis of a High Subsonic Turbine Cascade  

Kim, Hark-Bong (한국항공대학교 항공우주 및 기계공학부)
Kim, Jin-Kon (한국항공대학교 항공우주 및 기계공학부)
Kwak, Jae-Su (한국항공대학교 항공우주 및 기계공학부)
Kang, Jeong-Seek (한국항공우주연구원 엔진팀(KHP))
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.12, no.1, 2008 , pp. 23-28 More about this Journal
Abstract
Flow analysis in a turbine cascade by Euler or Navier-Stokes equation gives relatively accurate solution, however, those method require large computer memory or computing time. On contrast, the panel method, which is applied to incompressible and inviscid flow, provides fast and reasonal solution but the compressibility correction is required for a high air velocity case. In this paper, the compressibility corrected panel method was applied in order to find velocity distribution on turbine blades. Results showed that the calculated velocity in a turbine cascade by the compressibility corrected panel method gave good agreement with the solution by finite volume method for compressible flow.
Keywords
Panel Method; Compressibility Correction; Turbine Cascade;
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  • Reference
1 Lakshminarayana, B., "Fluid Dynamics and Heat Transfer of Turbomachinery", Wiley-Iterscience Publication, 1996, pp.233-239
2 Lewis, R. I., "Vortex Element Methods for Fluid Dynamics Analysis of Engineering Systems", Cambridge , 1991, pp.75-91
3 Lieblein, S. & Stockman, N. O., "Compressibility Correction for Internal Flow Solutions", J. of Aircraft, Vol.9, No.4, April, 1972, pp.312-313   DOI
4 Verdon, J. M. & Hall, K. C., "Development of a Linearized Unsteady Aerodynamic Analysis for Cascade Gust Response Predictions", NASA CR-4308, July, 1990
5 Katsanis, T., "Fortran Program for Calculating Transoinc Velocities on a Blade-to-Blade Stream Surface of a Turbomachine", NASA TN D-5427, Sept. 1969
6 Anderson, J. D., "Mordern Compressible Flow", McGraw-Hill, 1982, pp.226-229