Accession Number : AD0766537
Title : Throughflow Theory for Turbomachines.
Descriptive Note : Final rept. Oct 71-May 72,
Corporate Author : WASHINGTON UNIV SEATTLE AEROSPACE RESEARCH LAB
Personal Author(s) : Oates,Gordon C. ; Knight,Charles J.
Report Date : JUN 1973
Pagination or Media Count : 114
Abstract : Throughflow theory for flow in axial turbomachines is formulated in a way to allow consideration of the effects of variable hub and tip radii, the effects of free boundaries and the effects of compressibility. A procedure is developed for the very rapid calculation of incompressible flow through many blade rows in an annulus of constant hub and tip radii. An analysis formulation including the effects of variation in wall radii is also presented. A variational procedure for the numerical description of highly nonlinear flow field is developed for the description of incompressible flows through many blade rows in ducts of varying hub and tip radii. The associated computer program leads to rapid calculation of desired examples. Finally, a computer program is given to calculate the effects of compressibility on radial equilibrium flows. (Author)
Descriptors : (*INCOMPRESSIBLE FLOW, NUMERICAL ANALYSIS), (*AXIAL FLOW TURBINES, INCOMPRESSIBLE FLOW), BOUNDARY VALUE PROBLEMS, AXIAL FLOW COMPRESSOR BLADES, CASCADE STRUCTURES, NUMERICAL INTEGRATION, FLOW FIELDS, COMPUTER PROGRAMS, INTEGRAL EQUATIONS, PARTIAL DIFFERENTIAL EQUATIONS
Subject Categories : Fluid Mechanics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE