An Analytical Analysis of the Effects of Instantaneous Vorticity on Compressor Performance PDF Download
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Author: James Edward Shoemaker
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 0
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Book Description
Vorticity forms the basis for a new approach to the analysis of inlet distortion in axial flow fans and compressors. Farmer first formulated this approach and this paper represents a test of the usefulness of his theory. A summary of recent developments in the field along with a discussion of the effects of distortion on stall margin forms a background for this complex problem. A computer program calculates the vorticity pattern at the compressor face using data that are read from a magnetic tape. The data, which were provided by NASA Lewis Research Center in Cleveland, consist of eleven stall events. The output of the program contains tables of stagnation pressure and the partial derivatives of pressure and the partial derivatives of pressure in the R and theta directions as well as three maps. The three maps are of pressure and radial and circumferential vorticity. The results of the program show a correlation between a ring of large positive circumferential vorticity and stall, leading to the conclusion that the stall was caused by the increase in blade loading induced by the vorticity. This conclusion suggests a formulation for a universal inlet distortion index and provides a basis for the evaluation of the vorticity approach to the problem. (Author).
Author: James Edward Shoemaker
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 0
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Book Description
Vorticity forms the basis for a new approach to the analysis of inlet distortion in axial flow fans and compressors. Farmer first formulated this approach and this paper represents a test of the usefulness of his theory. A summary of recent developments in the field along with a discussion of the effects of distortion on stall margin forms a background for this complex problem. A computer program calculates the vorticity pattern at the compressor face using data that are read from a magnetic tape. The data, which were provided by NASA Lewis Research Center in Cleveland, consist of eleven stall events. The output of the program contains tables of stagnation pressure and the partial derivatives of pressure and the partial derivatives of pressure in the R and theta directions as well as three maps. The three maps are of pressure and radial and circumferential vorticity. The results of the program show a correlation between a ring of large positive circumferential vorticity and stall, leading to the conclusion that the stall was caused by the increase in blade loading induced by the vorticity. This conclusion suggests a formulation for a universal inlet distortion index and provides a basis for the evaluation of the vorticity approach to the problem. (Author).
Author: James Edward Shoemaker
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 89
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Book Description
Vorticity forms the basis for a new approach to the analysis of inlet distortion in axial flow fans and compressors. Farmer first formulated this approach and this paper represents a test of the usefulness of his theory. A summary of recent developments in the field along with a discussion of the effects of distortion on stall margin forms a background for this complex problem. A computer program calculates the vorticity pattern at the compressor face using data that are read from a magnetic tape. The data, which were provided by NASA Lewis Research Center in Cleveland, consist of eleven stall events. The output of the program contains tables of stagnation pressure and the partial derivatives of pressure and the partial derivatives of pressure in the R and theta directions as well as three maps. The three maps are of pressure and radial and circumferential vorticity. The results of the program show a correlation between a ring of large positive circumferential vorticity and stall, leading to the conclusion that the stall was caused by the increase in blade loading induced by the vorticity. This conclusion suggests a formulation for a universal inlet distortion index and provides a basis for the evaluation of the vorticity approach to the problem. (Author).
Author: Wade H. Shafer
Publisher: Springer Science & Business Media
ISBN: 147575776X
Category : Science
Languages : en
Pages : 299
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Book Description
Masters Theses in the Pure and Applied Sciences was first conceived, published, and dis seminated by the Center for Information and Numerical Data Analysis and Synthesis, (CINDAS) *at Purdue University in 1957, starting its coverage of theses with the academic year 1955. Beginning with Volume 13, the printing and dissemination phases of the ac tivity was transferred to University Microfilms/Xerox of Ann Arbor, Michigan, with the thought that such an arrangement would be more beneficial to the academic and general scientific and technical community. After five years of this joint undertaking we had concluded that it was in the interest of all concerned if the printing and distribution of the volume were handled by an international publishing house to assure improved service and broader dissemination. Hence, starting with Volume 18, Masters Theses in the Pure and Applied Sciences has been disseminated on a worldwide basis by Plenum Publishing Corporation of New York, and in the same year the coverage was broadened to include Canadian universities. All back issues can also be ordered from Plenum. We have reported in Volume 19 (thesis year 1974) a total of 10,045 theses titles from 20 Canadian and 209 United States universities. We are sure that this broader base for theses titles reported will greatly enhance the value of this important annual reference work. The organization of Volume 19 is identical to that of past years. It consists of theses titles arranged by discipline and by university within each discipline.
Author: Naval Postgraduate School (U.S.)
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 434
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Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 596
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 500
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Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 194
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Author: John T. Sinnette (Jr.)
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 66
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Author: Melvyn Savage
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 40
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Multistage compressors composed of high-pressure-ratio stages have higher over-all off-design efficiencies and a wider operating range than those made up of low-pressure-ratio stages if the blade-row efficiency curves for the two cases are assumed to be somewhat similar.
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1262
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