Analysis of Three-dimensional Transonic Compressors PDF Download

Author: Antoine Bourgeade
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 114

View

Book Description

Author: Antoine Bourgeade
Publisher:
ISBN: 9781333034214
Category : Mathematics
Languages : en
Pages : 118

View

Book Description
Excerpt from An Analysis of Three-Dimensional Transonic Compressors The potential equation has already been solved numerically in the three-dimensional case for oblique and swept-wings However, because of the periodicity of the compressor problem, the square-root transformation used in those works is not practical here. We therefore propose a new transformation, which maps the surface of the blade into a plane and includes periodicity implicitly. About the Publisher Forgotten Books publishes hundreds of thousands of rare and classic books. Find more at www.forgottenbooks.com This book is a reproduction of an important historical work. Forgotten Books uses state-of-the-art technology to digitally reconstruct the work, preserving the original format whilst repairing imperfections present in the aged copy. In rare cases, an imperfection in the original, such as a blemish or missing page, may be replicated in our edition. We do, however, repair the vast majority of imperfections successfully; any imperfections that remain are intentionally left to preserve the state of such historical works.

Author: Antoine Bourgeade
Publisher: Palala Press
ISBN: 9781342372727
Category :
Languages : en
Pages : 114

View

Book Description
This work has been selected by scholars as being culturally important, and is part of the knowledge base of civilization as we know it. This work was reproduced from the original artifact, and remains as true to the original work as possible. Therefore, you will see the original copyright references, library stamps (as most of these works have been housed in our most important libraries around the world), and other notations in the work. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work.As a reproduction of a historical artifact, this work may contain missing or blurred pages, poor pictures, errant marks, etc. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.

Author: John I. Erdos
Publisher:
ISBN:
Category :
Languages : en
Pages : 61

View

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: Stephane Baralon
Publisher:
ISBN: 9789171979179
Category :
Languages : en
Pages : 137

View

Book Description

Author: William J. Rae
Publisher:
ISBN:
Category :
Languages : en
Pages : 12

View

Book Description
Three-dimensional flow effects play an important role in the performance of axial-flow fans and compressors that operate at transonic speeds. The coupling between transonic and three-dimensional effects limits the applicability of the two-dimensional analysis methods that have been in use for some years. The present research program was undertaken with the aim of extending these numerical techniques, so as to handle more fully the nonlinearity of the problem. Thus, heavily loaded blades with large turning angles are to be considered, and the simplifications of small-disturbance theory (such as satisfaction of boundary conditions on mean-chord surfaces, neglect of trailing vortex-sheet deformation) will not be used.

Author: O. Nozaki
Publisher:
ISBN:
Category :
Languages : en
Pages :

View

Book Description

Author: Panagiotis Sparis
Publisher:
ISBN:
Category :
Languages : en
Pages : 188

View

Book Description

Author: T. C Adamson (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 23

View

Book Description
This project was begun in 1979 as a study of three dimensional transonic flows through channels and between compressor blades. In the latter problem, the blades were to be lightly loaded. In 1981, a three year study with the broadened goal of studying flow problems in turbomachines was initiated. Specifically, the work was to include a continuation of that in progress on three-dimensional transonic flows through a lightly loaded compressor blade row, supersonic flow over a compression ramp with a turbulent boundary layer, and consideration of transonic flows over heavily loaded blades in a compressor, starting with a two-dimensional cascade and then going to a three-dimensional rotor if the calculations for the cascade was successful. The work in heavily loaded cascades was to build on the experience gained in the lightly loaded case. The work on the compression ramp has application at blade-shroud interfaces in transonic and supersonic flows. Asymptotic methods of analysis have been employed in all the problems to be described, with numerical methods of solution used as needed in some of the inner regions of the flow fields and to illustrate results for example problems.

Author: William J. Rae
Publisher:
ISBN:
Category :
Languages : en
Pages : 66

View

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).