Methods of Designing Cascade Blades with Prescribed Velocity Distributions in Compressible Potential Flows PDF Download
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Author: George R. Costello
Publisher:
ISBN:
Category : Cascades (Fluid dynamics)
Languages : en
Pages : 30
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Book Description
If the prescribed velocity distribution is not theoretically attainable, the method gives a way of modifying the distribution so as to obtain a blade shape.
Author: George R. Costello
Publisher:
ISBN:
Category : Cascades (Fluid dynamics)
Languages : en
Pages : 30
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Book Description
If the prescribed velocity distribution is not theoretically attainable, the method gives a way of modifying the distribution so as to obtain a blade shape.
Author: George R. Costello
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 56
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Book Description
The computational procedure includes several ways of adjusting the prescribed velocity to satisfy the restriction imposed by the method. Tables of coefficients are given for evaluating the necessary integrals, including the determination of the harmonic conjugate. Numerical examples are included.
Author: George R. Costello
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 11
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Book Description
If the prescribed velocity distribution is not theoretically attainable, the method gives a way of modifying the distribution so as to obtain a blade shape.
Author: Arthur G. Hansen
Publisher:
ISBN:
Category : Cascades (Fluid dynamics)
Languages : en
Pages : 51
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Book Description
A numerical procedure based on conformal-mappng theory is presented for design of an airfoil cascade with prescribed velocity distribution in incompressible flow. A set of tables is included as a guide for computations, and a numerical example is presented to illustrate specific solutions to problems arising in design of a cascade by this method.
Author: John D. Stanitz
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 72
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Book Description
A technique is developed for the application of a channel design method to the design of high-solidity cascades with prescribed velocity distributions as a function of arc length along the blade-element profile. The technique applies to both incompressible and subsonic linearized compressible (ratio of specific heats equal to -1.0), nonviscous, irrotational, fluid motion. An impulse cascade with 90 degree turning was designed for incompressible flow and was tested at the design angle of attack over a range of downstream Mach number from 0.2 to choke flow. To achieve good efficiency, the cascade was designed for prescribed velocities with maximum allowable blade loading according to limitations imposed by considerations of boundary-layer separation.
Author: George R. Costello
Publisher:
ISBN:
Category :
Languages : en
Pages : 49
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Book Description
Author: John Stanitz
Publisher: Рипол Классик
ISBN: 5881585658
Category : History
Languages : en
Pages : 79
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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: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1026
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Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 486
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Book Description
Author: Alois T. Sutor
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 706
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Book Description
Analytical expressions are derived to show the geometric, thermodynamic, and aerodynamic relations among compressor, turbine, and exhaust nozzle for a gas-turbine engine. For a known compressor performance map, a matching method is described to show some of the design compromises that must be made when the components are to be combined into a turbine-propeller engine. A method of predicting engine performance for a range of operating conditions from known component maps is presented. An illustrative example of the matching method and the performance analysis is presented, showing some of the practical limitations of engine operation.
