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Author : M. L. Miller,A. C. Bryans
Publisher : Unknown
Page : 76 pages
File Size : 52,5 Mb
Release : 1967
Category : Compressors
ISBN : UIUC:30112106581496
Author : Lewis Research Center
Publisher : Unknown
Page : 542 pages
File Size : 51,9 Mb
Release : 1965
Category : Axial flow compressors
ISBN : STANFORD:36105113764901
Author : Anonim
Publisher : Unknown
Page : 704 pages
File Size : 46,7 Mb
Release : 1995
Category : Aeronautics
ISBN : UIUC:30112050127304
Author : Anonim
Publisher : Unknown
Page : 128 pages
File Size : 45,9 Mb
Release : 1967
Category : Government publications
ISBN : UCR:31210023919135
Author : United States. Superintendent of Documents
Publisher : Unknown
Page : 1504 pages
File Size : 55,8 Mb
Release : 1979
Category : United States
ISBN : STANFORD:36105019598296
Author : United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher : Unknown
Page : 428 pages
File Size : 53,5 Mb
Release : 1968
Category : Aeronautics
ISBN : STANFORD:36105024415957
Author : Melvyn Savage,Willard R. Westphal
Publisher : Unknown
Page : 40 pages
File Size : 52,7 Mb
Release : 1950
Category : Axial flow compressors
ISBN : UOM:39015086494799
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 : United States. Superintendent of Documents
Publisher : Unknown
Page : 1320 pages
File Size : 54,7 Mb
Release : 1966
Category : Government publications
ISBN : WISC:89035089036
Author : Ronald H. Aungier
Publisher : American Society of Mechanical Engineers
Page : 386 pages
File Size : 46,7 Mb
Release : 2003
Category : Science
ISBN : UOM:39015052660845
This book provides a thorough description of an aerodynamic design and analysis systems for Axial-Flow Compressors. It describes the basic fluid dynamic and thermodynamic principles, empirical models and numerical methods used for the full range of procedures and analytical tools that an engineer needs for virtually any tupe of Axial-Flow Compressor, aerodynamic design or analysis activity. It reviews and evaluates several design strategies that have been recommended in the literature or which have been found to be effective. It gives a complete description of an actual working system, such that readers can implement all or part of the system. Engineers responsible for developing, maintaining of improving design and analysis systems can benefit greatly from this type of reference. The technology has become so complex and the role of computers so pervasive that about the only way this can be done today is to concentrate on a specific design and analysis system. The author provides practical methodology as well as the details needed to implement the suggested procedures.
Author : B. Lakshminarayana,Werner R. Britsch,Walter S. Gearhart
Publisher : Unknown
Page : 468 pages
File Size : 50,7 Mb
Release : 1974
Category : Fluid mechanics
ISBN : STANFORD:36105113767763
Author : Robert O. Bullock
Publisher : Unknown
Page : 552 pages
File Size : 45,8 Mb
Release : 1965
Category : Axial flow compressors
ISBN : NASA:31769000652464
Author : United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher : Unknown
Page : 436 pages
File Size : 52,6 Mb
Release : 1968
Category : Aeronautics
ISBN : CORNELL:31924057848842
Author : John T. Sinnette,Oscar W. Schey,J. Austin King
Publisher : Unknown
Page : 74 pages
File Size : 46,7 Mb
Release : 1944
Category : Aerofoils
ISBN : UOM:39015095014299
The NACA has conducted an investigation to determine the performance that can be obtained from a multistage axial-flow compressor based on airfoil research. A theory was developed; an eight-stage axial-flow compressor was designed, constructed, and tested.
Author : Anonim
Publisher : Unknown
Page : 996 pages
File Size : 42,6 Mb
Release : 1967
Category : Aeronautics
ISBN : MINN:319510008439082
Author : Shawn A. Miller
Publisher : Unknown
Page : 94 pages
File Size : 49,8 Mb
Release : 1998-03-01
Category : Axial flow compressors
ISBN : 1423563298
The development of jet engines has become an integral part of maintaining air superiority. In order to achieve the most advanced engine, research has turned to traditional optimization methods to aid in creating new engine designs. To develop simplified mathematical models representative of the engine, the engine can be separated into its components. A jet engine has three major elements, the compressor, combustion chamber and turbine. This research attempts to make an initial analysis of a two stage compressor to determine values of blade angles and spacing to chord ratios for both stages that produce the highest possible efficiency for the overall two stage compressor. A pitch line model is developed for a two stage compressor and is used in conjunction with a optimization method to solve for the on design air angles and spacing to chord ratios. The results of the model were compared to examples available in current literature to ensure the model properly represents a compressor stage. The off design performance of the results was calculated to determine how the designs for on design operated under off design conditions. Since practical compressors are made up of many stages, consideration is given to which optimization method would be most useful in solving for a multistage compressor.
