A Study of Inlet Conditions for Three-Dimensional Transonic Compressor Flows PDF Download
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Author: William J. Rae Publisher: ISBN: Category : Languages : en Pages : 66
Book Description
This report contains a study of the conditions at the inlet of a transonic compressor, with special reference to the formulation of these conditions in a manner suitable for flowfield computation. Several candidate methods for specifying the inlet conditions are reviewed, and details are given for a procedure that uses a matching between finite-difference results and linear-theory formulas at a plane upstream of the rotor. (Author).
Author: William J. Rae Publisher: ISBN: Category : Languages : en Pages : 66
Book Description
This report contains a study of the conditions at the inlet of a transonic compressor, with special reference to the formulation of these conditions in a manner suitable for flowfield computation. Several candidate methods for specifying the inlet conditions are reviewed, and details are given for a procedure that uses a matching between finite-difference results and linear-theory formulas at a plane upstream of the rotor. (Author).
Author: John I. Erdos Publisher: ISBN: Category : Languages : en Pages : 61
Book Description
A method of analysis of transonic multistage compressors is described. The three dimensional, compressible non-steady flow equations are solved numerically by a finite difference method subject to steady boundary conditions. The approach utilizes circumferential averaging of flow properties; however the essential aspects of three dimensional flow are retained through consideration of a three component blade force and blockage of the annular area due to the combined effects of blade thickness and actual circumferential variations in the flow. (Author).
Author: William J. Rae Publisher: ISBN: Category : Languages : en Pages : 43
Book Description
A derivation is given of the nonlinear, small-disturbance equations governing three-dimensional transonic flow through a fan or compressor rotor. These equations represent the counterpart, for turbomachinery flows, of the small-disturbance equations appropriate to an isolated airfoil. Thus, they facilitate the application to turbomachinery flows of the many numerical solution methods developed in recent years for isolated-airfoil problems. Boundary conditions for design and off-design conditions are formulated, at a level of approximation consistent with the small-disturbance field equations. An order-of-magnitude analysis is presented, which reveals the transonic similarity parameters for flow in blade rows of low and high solidity. The validity of a rectilinear transonic shear flow as a representation of the flow through a fan or rotor is also discussed. (Author).
Author: William J. Rae
Author: William J. Rae
Author: Antoine Bourgeade
Author: Panagiotis Sparis
Author: 
Author: John I. Erdos
Author: William J. Rae
Author: Wai Kong Cheng
Author: J. E. McCune
Author: Massachusetts Institute of Technology. Gas Turbine Laboratory
Author: Guido Haymann-Haber