The equations for the flow through cascades of blades are averaged across the pitch and then compared with those for the flow through hypothetical models of blade rows; a closely spaced blade row, an axisymmetric flow with body forces and the flow on a mean stream surface. It is shown that these models can provide an accurate representation for the overall flow changes across a blade row, but they cannot give an exact local matching with the averaged properties of the flow in the real cascade. The nature of the blade forces in the real flow and the body forces in the hypothetical flow is discussed.
MarshH.‘A digital computer program for the through-flow mechanics in an arbitrary turbomachine using a matrix method’, N.G.T.E. Rept No. R282, 1966; also A.R.C. rep. memor. 3509, 1968.
HorlockJ. H.Boundary layer problems in axial turbo-machines; Brown Boveri symposium, Flow research on blading1969 (Elsevier, Amsterdam).
5.
Gregory-SmithD. G.‘An investigation of annulus wall boundary layers in axial flow turbomachines’, A.S.M.E. Paper No. 70-GT-92, 1970.
6.
WuC. H.‘A general theory of three-dimensional flow in subsonic and supersonic turbomachines of axial, radial and mixed-flow types’, N.A.C.A. tech. note 2604, 1952.
7.
MarshH.‘The through flow analysis of axial flow compressors’, AGARD LS No. 39, 1970.
