Preliminary Design Study of Advanced Multistage Axial Flow Core Compressors
Author : D. C. Wisler
Publisher :
Page : 86 pages
File Size : 30,92 MB
Release : 1977
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Author : D. C. Wisler
Publisher :
Page : 86 pages
File Size : 30,92 MB
Release : 1977
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ISBN :
Author : H. V. Marman
Publisher :
Page : 54 pages
File Size : 32,10 MB
Release : 1976
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Author : Louis M. Larosiliere
Publisher :
Page : 36 pages
File Size : 35,75 MB
Release : 2002
Category : Compressors
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Author : M. L. Miller
Publisher :
Page : 76 pages
File Size : 14,6 MB
Release : 1967
Category : Compressors
ISBN :
Author :
Publisher :
Page : 310 pages
File Size : 26,26 MB
Release : 1982
Category : Aeronautics
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Author : Lewis Research Center
Publisher :
Page : 542 pages
File Size : 42,52 MB
Release : 1965
Category : Axial flow compressors
ISBN :
Author :
Publisher :
Page : 375 pages
File Size : 25,81 MB
Release : 1976
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Complete experimental results are presented from tests of an axial compressor stage designed for a flow per frontal area of 39.7 lb/sec/ft square, a total pressure ratio of 1.912 and a tip speed of 1500 ft/sec. The performance objectives of this stage were derived from a preliminary design study of a multi-stage compressor for an advanced turbojet engine. Since the most serious aerodynamic design problems of the over-all compressor were observed to be associated with the first stage, this stage was chosen as the subject of a research program. Results of the tests indicated that, at design speed, design flow was achieved with a rotor isentropic efficiency of 90.4 percent, a stage isentropic efficiency of 88.2 percent and a stage total pressure ratio of 2.065.
Author :
Publisher :
Page : 298 pages
File Size : 40,88 MB
Release : 1976
Category :
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This report describes the aerodynamic design of a transonic axial- flow compressor inlet stage designed for high flow rate per unit frontal area and relatively high aerodynamic loading. The performance objectives of this stage were derived from a preliminary design study of a multi-stage compressor for an advanced turbojet engine. The design goals chosen included a tip speed of 1500 ft/sec, a flow rate of 39.7 lb/sec per square foot of frontal area, a stage total pressure ratio of 1.91 and a stage isentropic efficiency of 0.83. The techniques used in the preliminary and detail designs are described. The complete aerodynamic flow field pertaining to the design point is defined on twenty-one stream surfaces, and radial and meridional distributions of significant parameters are presented. Finally, the detailed flowpath geometry is defined and airfoil coordinates are included for both stream surfaces and cartesian manufacturing sections.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 544 pages
File Size : 45,63 MB
Release : 1946
Category : Axial flow compressors
ISBN :
In order to establish a standard procedure for rating and testing multistage axial-flow compressors, the NACA Subcommittee on Compressors appointed a panel to write such a procedure. This panel made recommendations for standardization of test setups, instrumentation, test procedure, data to be taken, and the presentation of the data. These recommendations are presented.
Author : Robert O. Bullock
Publisher :
Page : 552 pages
File Size : 42,55 MB
Release : 1965
Category : Axial flow compressors
ISBN :