Hostname: page-component-78c5997874-dh8gc Total loading time: 0 Render date: 2024-11-08T04:51:26.052Z Has data issue: false hasContentIssue false
  • English
  • Français

Computations of bladerow stall inception in transonic flows

Published online by Cambridge University Press:  04 July 2016

L. He  and
J. O. Ismael
L. He
Affiliation:
School of Engineering University of Durham, Durham, UK
J. O. Ismael
Affiliation:
Department of Engineering Systems, Brunel University, Uxbridge, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

A three-dimensional unsteady Navier-Stokes solver has been used to simulate stall inception in a single row ten passage segment of a transonic fan, the NASA rotor-67. At subsonic flow conditions, the 3D results illustrate a rotating stall inception with short scale part-span cells rotating at around 80% rotor speed, similar to that observed in some low speed experiments. However, at a supersonic relative inflow condition, the results show that an isolated blade row tends to stall in a one-dimensional breakdown pattern without first experiencing rotating stall. At near-stall conditions, significant self-excited unsteadiness is generated by the interaction between the tip-leakage vortex and the passage shock wave. Further computations for two-dimensional configurations indicate that it is possible to have a rotating pattern of instability in transonic blade rows associated with circumferential synchronised shock oscillation.

Type
Research Article
Information
The Aeronautical Journal , Volume 103 , Issue 1025 , July 1999 , pp. 317 - 324
Copyright
Copyright © Royal Aeronautical Society 1999 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Day, I.J. Active suppression of rotating stall and surge in axial compressors, ASME J Turbom, 1993, 115, (1).Google Scholar
2. Epstein, A.H., Ffowcs-williams, J.E. and Greitzer, E.M. Active suppression of aerodynamic instabilities in turbomachines, AIAA J Prop and Pow, 1989,5, (2).Google Scholar
3. Moore, F.K. and Greitzer, E.M. A theory of post-stall transients in axial compressors: Part I — development of the equations, ASME J Eng Gas Turb and Pow, 1986, 108, pp 231–239.Google Scholar
4. Greitzer, E.M. Surge and rotating stall in axial flow compressors, ASME J Eng Gas Turb and Pow, 1976,98, pp 190–217.Google Scholar
5. Sisto, F., Wu, W., Thangam, S. and Jonnavithula, S. Computational aerodynamics of oscillating cascade with evolution of rotating stall, AIAA J, 1989,27, (4), pp 462–471.Google Scholar
6. Outa, E., Kato, D. and Chiba, K. A N-S simulation of stall cell behaviour in a 2D compressor rotor-stator system at various loads, ASME Paper, 94-GT-257, 1994.Google Scholar
7. He, L. Integration of 2D fluid/structure coupled system for calculations of turbomachinery aerodynamic/aeroelastic instabilities, Int J CFD, 1994,3, pp 217–231.Google Scholar
8. Straziar, A.J. and Powell, J.A. Laser anemometer measurements in a transonic axial flow compressor rotor, ASME J Eng Pow, 1981, 103, (2).Google Scholar
9. Hughes, W.F. and Brighton, J.A. Fluid Dynamics, 1967, Schaum's Outline Series, McGraw-Hill, New York.Google Scholar
10. Baldwin, B.S. and Lomax, H. Thin layer approximation and algebraic model for separated turbulent flows, AIAA Paper 78-0257, January 1978.Google Scholar
11. He, L. and Denton, J.D. Three-dimensional time-marching inviscid and viscous solutions for unsteady flows around vibrating blades, ASME J Turbom, 1994, 116.Google Scholar
12. Giles, M.B. Nonreflecting boundary conditions for Euler equation calculations, AIAA J, 1990,28, (12).Google Scholar
13. Jameson, A., Schmidt, W. and Turkel, E. 1981, Numerical solution of Euler equations by finite volume methods using Runge-Kutta time-stepping schemes, AIAA Paper 81-1259,1981.Google Scholar
14. He, L. New two-grid acceleration method for unsteady Navier-Stokes calculations, AIAA J Prop and Pow, 1993, 9, (2).Google Scholar
15. Arnone, A. Viscous analysis of three-dimensional rotor flow using a multi-grid method, ASME J Turbom, 1994, 116, (1).Google Scholar
16. Puterbaugh, S.L. and Brendel, M., Tip-clearance flow-shock interaction in a transonic compressor rotor, AIAA J Prop and Pow, 1997, 13, (1).Google Scholar
17. Ismael, J.O. and He, L. Three-dimensional computation of rotating stall inception, 2nd European Conference on Turbomachinery, Antwerp, Belgium, March, 1997.Google Scholar
18. Emmons, H.W., Pearson, C.E. and Grant, H.P. Compressor surge and stall propagation, Trans ASME, 1955, 77, (4).Google Scholar
19. Adamczyk, J., Celestina, M.L. and Greitzer, E.M. The role of tip clearance in high speed fan stall, ASME J Turbom, 1993, 115.Google Scholar
20. He, L. Computational study of rotating stall inception in axial compressors, AIAAJ Prop and Pow, 1997, 13, (1).Google Scholar
21. Day, I.J. Stall inception in axial flow compressors, ASME J Turbom, 1993, 115, January 1993, pp 1–9.Google Scholar