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0-plane adjacent adjusted analysis appendix arbitrary assumed becomes blade shape boundaries extending Cleveland component compressible compressor computed cone angle conic flow surface conic radii considerations considered constant coordinates correspond defined density ratio determined developed distribution downstream boundaries effect equal equation 18 equivalent estimated values example figure flow field flow rate fluid given grid points grid spacing height impeller incompressible indicates inflow interior grid points Joukowski condition less lines Lines of constant machine mixed-flow negative blade surface normal obtained occur operating conditions outflow passage plane positive blade surface problem quasi boundaries extending radial radius ratio reference relative relaxation methods relaxation solution residuals rotating rotor satisfy shown simplified slip factor spacing specified value speed stator stream function streamlines subscript tangential thin tion transformed turbomachines uniform flow United upstream and downstream values variation velocity ratio whirl ratio zero
Page 11 - considered to be unaffected by the inlet configuration of the impeller and by the diffuser vanes
Page 14 - is compressible, incompressible solutions give poor quantitative results (exception, the slip factor) and, in some respects, poor qualitative results.
Page 1 - A general method of analysis is developed for two-dimensional, steady, compressible flow in stators or rotors of radial-
Page 14 - conic flow surfaces (surfaces of right circular cones generated by center line of flow passage in
Page 14 - to be unaffected by the inlet configuration of the impeller or by the diffuser vanes
Page 14 - It is concluded that, if the fluid in highspeed, rotating, radial- and mixed-flow