Hostname: page-component-68945f75b7-lndnj Total loading time: 0 Render date: 2024-09-04T22:16:07.919Z Has data issue: false hasContentIssue false
  • English
  • Français

Linearized analysis of the three-dimensional compressible flow through a rotating annular blade row

Published online by Cambridge University Press:  20 April 2006

John A. Lordi  and
Gregory F. Homicz
John A. Lordi
Affiliation:
Aerodynamic Research Department, Calspan Advanced Technology Center, Buffalo, New York
Gregory F. Homicz
Affiliation:
Aerodynamic Research Department, Calspan Advanced Technology Center, Buffalo, New York
Get access Rights & Permissions [Opens in a new window]

Abstract

Linearized solutions for the flow field of a rotating blade row in an infinitely long annular duct are reviewed. An isolated rotor is assumed to operate in a uniform axial flow so that the disturbance field is steady in a blade fixed co-ordinate system. Both three-dimensional and compressibility effects are included, but attention is confined to subsonic flows. Previously published source-flow solutions omitted a term which affected the thickness part of the rotor flow field constructed from them. Corrected source and rotor-thickness solutions are given, and then the source or monopole solution is used to form a pressure dipole solution. The rotor-loading contribution to the flow field is found by superposition of the revised dipole solutions. The present version of the dipole representation of the steady-loading field is shown to be equivalent to an existing vortex representation, but different from an existing dipole representation. The behaviour of the blade-surface pressure and velocity distributions is described for both the thickness and loading cases. Sample numerical evaluations of the surface quantities are presented.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 103 , February 1981 , pp. 413 - 442
Copyright
© 1981 Cambridge University Press

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

Ashley, H. & Landahl, M. 1965 Aerodynamics of Wings and Bodies. Addison-Wesley.
Erickson, J. C., Lordi, J. A. & Rae, W. J. 1971 On the transonic aerodynamics of a compressor blade row. Calspan Corp. Rep. no. AI-3003-A-1.Google Scholar
Homicz, G. F. & Lordi, J. A. 1979 Three-dimensional lifting-surface theory for an annular blade row. A.S.M.E. Paper 79-GT-182.Google Scholar
Lordi, J. A. 1971 Noise generation by a rotating blade row in an infinite annulus. A.I.A.A. 4th Fluid and Plasma Dynamic Conf., paper 71–617. (Also Report on a study of noise generation by a rotating blade row in an infinite annulus. Calspan Corp. Rep. no. AI-2836-A-1.)
McCune, J. E. 1958a A three-dimensional theory of axial compressor blade rows - application in subsonic and supersonic flows. J. Aerospace Sci. 25, 544.Google Scholar
McCune, J. E. 1958b The transonic flowfield of an axial compressor blade row. J. Aerospace Sci. 25, 616.Google Scholar
McCune, J. E. & Dharwadkar, S. P. 1972 Lifting-line theory for subsonic axial compressor rotors. MIT Gas Turbine, Lab. Rep. no. 110.
Namba, M. 1972 Lifting surface theory for a rotating subsonic or transonic blade row. Aero. Res. Counc. R. & M. 3740.Google Scholar
Namba, M. 1976 Lifting surface theory for unsteady flows in a rotating annular cascade. Proceedings of IUTAM Symposium on Aeroelasticity in Turbomachines, Paris, Oct. 1976. Revue Française de Mécanique, special issue, p. 39.
Namba, M. 1977 Three-dimensional analysis of blade force and sound generation for an annular cascade in distorted flows. J. Sound Vib. 50 (4), 479.Google Scholar
Okurounmu, O. & McCune, J. E. 1970 Three-dimensional vortex theory of axial compressor blade rows at subsonic and transonic speeds. A.I.A.A. J. 8, 1275.Google Scholar
Okurounmu, O. & McCune, J. E. 1974 Lifting surface theory of axial compressor blade rows. I: Subsonic compressor. A.I.A.A. J. 12, 1363. II: Transonic compressor. A.I.A.A. J. 12, 1372.Google Scholar
Reissner, H. 1937 On the vortex theory of the screw propeller. J. Aero. Sci. 5, 1.Google Scholar
Salaun, P. 1974 Unsteady aerodynamic pressure on an annular cascade in subsonic flow. Office National d'Etudes et de Recherches Aérospatiale Publ. no. 158. (Translated as European Space Agency Tech. Transl. ESA-TT-173, July 1975.)
Salaun, P. 1976 Flutter instability in an annular cascade. Proceedings of IUTAM Symposium on Aeroelasticity in Turbomachines, Paris, Oct. 1976. Revue Française de Mécanique, special issue, p. 35.
Shames, I. 1962 Mechanics of Fluids. McGraw-Hill.
Wu, Chung-Hua 1952 A general theory of three-dimensional flow in subsonic and supersonic turbomachines of axial-, radial-, and mixed-flow types. N.A.C.A. TN 2604.Google Scholar