Two-dimensional Flow on General Surfaces of Revolution in Turbomachines

Two-dimensional Flow on General Surfaces of Revolution in Turbomachines PDF

Author: John D. Stanitz

Publisher:

Published: 1952

Total Pages: 734

ISBN-13:

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A method of analysis is developed for two dimensional flow on general surfaces of revolution in turbomachines with arbitrary blade shapes. The method of analysis is developed for steady, compressible, nonviscous, irrotational flow that is assumed uniform normal to the surfaces of revolution. Incompressible solutions on a mean surface of revolution between the hub and shroud are presented for four rates through each of two centrifugal impellers with the same hub-shroud contours but with different blade spacings. In addition, correlation equations are developed whereby the velocity components and the stream function distribution can be predicted for compressible or incompressible flow in straight-blade impellers only, with any tip speed, flow rate, area variation, blade spacing, and for any flow surface of revolution.

Aerothermodynamics of Aircraft Engine Components

Aerothermodynamics of Aircraft Engine Components PDF

Author: Gordon C. Oates

Publisher: AIAA

Published: 1985

Total Pages: 568

ISBN-13: 9781600860058

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Annotation Design and R & D engineers and students will value the comprehensive, meticulous coverage in this volume. Beginning with the basic principles and concepts of aeropropulsion combustion, chapters explore specific processes, limitations, and analytical methods as they bear on component design.

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

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

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.

Monthly Catalog of United States Government Publications

Monthly Catalog of United States Government Publications PDF

Author: United States. Superintendent of Documents

Publisher:

Published: 1952

Total Pages: 1360

ISBN-13:

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February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index.

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