Two-dimensional Compressible Flow in Centrifugal Compressors with Straight Blades PDF Download
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Author: John D. Stanitz Publisher: ISBN: Category : Aeronautics Languages : en Pages : 712
Book Description
Six numerical examples are presented for steady, two-dimensional, compressible, nonviscous flow in centrifugal compressors with straight blades. A seventh example is presented for incompressible flow. The solutions also applye to radial-flow turbines with rotation and flow direction reversed. The effects of variations in following parameters were investigated: (1) flow rate, (2) impeller-tip speed, (3) variation of passage height with radius, and (4) number of blades. The numerical results are presented in plots of the streamlines, constant Mach number lines, and constant pressure-ratio lines. Correlation equations are developed whereby the flow conditions in any impeller with straight blades can be determined for all operating conditions.
Author: John D. Stanitz Publisher: ISBN: Category : Aeronautics Languages : en Pages : 712
Book Description
Six numerical examples are presented for steady, two-dimensional, compressible, nonviscous flow in centrifugal compressors with straight blades. A seventh example is presented for incompressible flow. The solutions also applye to radial-flow turbines with rotation and flow direction reversed. The effects of variations in following parameters were investigated: (1) flow rate, (2) impeller-tip speed, (3) variation of passage height with radius, and (4) number of blades. The numerical results are presented in plots of the streamlines, constant Mach number lines, and constant pressure-ratio lines. Correlation equations are developed whereby the flow conditions in any impeller with straight blades can be determined for all operating conditions.
Author: Gaylord O. Ellis Publisher: ISBN: Category : Air flow Languages : en Pages : 54
Book Description
Two numerical examples are presented for two-dimensional, compressible, nonviscous flow in centrifugal compressors with backward-curved, logarithmic-spiral blades. The two examples are for different blade angles and are compared with a third example for straight, radial blades. The numerical results are presented in tables of the stream-function distribution and in plots of the streamlines, constant Mach number lines, and constant-pressure-ratio lines. In addition, a simplified analysis for logarithmic-spiral blades is presented that can be used to determine flow conditions within the impeller except near the imperller tip and impeller inlet.
Author: John Stanitz Publisher: Рипол Классик ISBN: 5881585658 Category : History Languages : en Pages : 79
Book Description
An approximate blade-element design method is developed for compressible or incompressible nonviscous flow in high-solidity stators or rotors of axial-, radial-, or mixed-flow compressors, turbines, or two-dimensinal cascades. The method is based upon channel-type flow between blade elements on a specified surface of revolution that lies between the hub and shroud (casing) and is concentric with the axis of the compressor turbine. The blade elements is designed for prescribed velocities along the blade-element profile as a function of distance along meridonal lines on the surface of revolution. Two numerical examples are presented: (1) the design of a blade-element profile for a plane two-dimensional cascade in compressible flow with the prescribed velocities along the profiles; and (2) the design of a blade element for the impeller of a mixed-flow centrifugal compressor.
Author: John D. Stanitz
Author: John D. Stanitz
Author: Gaylord O. Ellis
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: John Stanitz
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: