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Two-dimensional Compressible Flow in Centrifugal Compressors with Straight Blades

Author: John D. Stanitz

Publisher:

Published: 1949

Total Pages: 712

ISBN-13:

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.

Two-dimensional Compressible Flow in Centrifugal Compressors with Logarithmic-spiral Blades

Author: Gaylord O. Ellis

Publisher:

Published: 1951

Total Pages: 54

ISBN-13:

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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.

Technical Note

Author:

Publisher:

Published: 1948

Total Pages: 550

ISBN-13:

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Annual Report of the National Advisory Committee for Aeronautics

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published: 1950

Total Pages: 988

ISBN-13:

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Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.

Technical Note - National Advisory Committee for Aeronautics

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published: 1955

Total Pages: 886

ISBN-13:

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Approximate design method for high-solidity blade elements in compressors and turbines

Author: John Stanitz

Publisher: Рипол Классик

Published: 1951

Total Pages: 79

ISBN-13: 5881585658

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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.