Three-dimensional flows through cascades of blades are studied, the blading being fully choked internally. Initially the two-dimensional flow through a ‘zero stagger, zero camber’ blade row, with subsonic entry and exit flow, is described. The radial flows are produced by radial variations in throat area, or by a variety of entry shear flows. Subsequently, the analysis is developed to describe similar fully choked flows through staggered blade rows, particularly the first rotating row of a transonic compressor.
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References
1.
LewisR. I.HorlockJ. H.‘Flow disturbances due to blade thickness in turbomachines’, J. mech. Engng Sci.196911, 88–108.
2.
StanitzJ. D.‘Effect of blade thickness taper on axial-velocity distribution at the leading edge of an entrance rotor blade row with axial inlet’, 1953, N.A.C.A., Tech. Note 2986.
3.
HorlockJ. H.GraingerC. ‘Supersonic flow through turbomachinery blade rows’, A.S.M.E. Paper No. 80-FE-7, 1980.
HawthorneW. R.RingroseJ. ‘Actuator disc theory of the compressible flow in free-vortex turbo-machinery’, Proc. Instn mech. Engrs1963–4178, 3, I(ii), 1–13.
6.
ShapiroA. H.The dynamics and thermodynamics of compressible fluid flow, 1953 (Ronald Press, New York).
7.
MarshH. ‘The uniqueness of turbomachinery flow calculations using the streamlines curvature and matrix through-flow methods’, J. mech. Engng Sci.197113, 376–379.
8.
GraingerC. F.‘Three-dimensional supersonic flow through a cascade of twisted flat plates’, A.S.M.E. Paper No. 80-FE-3, 1980.
9.
DentonJ. D.‘A time marching technique for two- and three-dimensional blade flows’Aero. Res. Council Rep. and Mem.3775, 1975.
