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Author : Younes Elkacimi
Publisher : Unknown
Page : 280 pages
File Size : 55,8 Mb
Release : 2007
Category : Compressors
ISBN : MSU:31293029563206
Author : Anonim
Publisher : Unknown
Page : 988 pages
File Size : 54,7 Mb
Release : 1979
Category : Power resources
ISBN : MSU:31293010867442
Author : Anonim
Publisher : Unknown
Page : 1282 pages
File Size : 46,8 Mb
Release : 1982
Category : Aeronautics
ISBN : UIUC:30112102359566
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author : Anonim
Publisher : Unknown
Page : 572 pages
File Size : 49,9 Mb
Release : 1987
Category : Engineering
ISBN : STANFORD:36105010856404
Author : Anonim
Publisher : Unknown
Page : 538 pages
File Size : 53,5 Mb
Release : 1991
Category : Aeronautics
ISBN : UOM:39015023295143
Author : Willard R. Westphal,John W. Maynard
Publisher : Unknown
Page : 66 pages
File Size : 54,9 Mb
Release : 1958
Category : Axial flow compressors
ISBN : UOM:39015086414565
A six-stage axial-flow compressor with a tip speed of 550 feet per second and a flat operating characteristics at constant speed has been designed and tested. It was designed for a constant power input per pound of flow in expectation that this would result in a wider mass-flow operating range at a given stagnation-presssure ratio. The design specific weight flow was 21.3 pounds per second per square foot of frontal area at atmospheric discharge with a stagnation-pressure ratio of 3.25 and an inlet hub-tip radius ratio of 0.7. Several configurations consisting of various blade setting angles and solidities were tested. Tests showed that the design flow, pressure ratio, and flat operating characteristic were obtained over a range of 10 percent of design flow at a peak efficiency of 82 percent for design conditions. The compressor had a possible immediate application for air removal from a large slotted-throat transonic wind tunnel, but the design theory could apply to any low-speed industrial compressor or second spool of a turbojet engine.
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 26 pages
File Size : 42,9 Mb
Release : 2018-05-22
Category : Electronic
ISBN : 1719398968
The main focus of this study is to apply a computational tool for the flow analysis of the engine that has been tested with ice crystal ingestion in the Propulsion Systems Laboratory (PSL) of NASA Glenn Research Center. A data point was selected for analysis during which the engine experienced a full roll back event due to the ice accretion on the blades and flow path of the low pressure compressor. The computational tool consists of the Numerical Propulsion System Simulation (NPSS) engine system thermodynamic cycle code, and an Euler-based compressor flow analysis code, that has an ice particle melt estimation code with the capability of determining the rate of sublimation, melting, and evaporation through the compressor blade rows. Decreasing the performance characteristics of the low pressure compressor (LPC) within the NPSS cycle analysis resulted in matching the overall engine performance parameters measured during testing at data points in short time intervals through the progression of the roll back event. Detailed analysis of the fan-core and LPC with the compressor flow analysis code simulated the effects of ice accretion by increasing the aerodynamic blockage and pressure losses through the low pressure compressor until achieving a match with the NPSS cycle analysis results, at each scan. With the additional blockages and losses in the LPC, the compressor flow analysis code results were able to numerically reproduce the performance that was determined by the NPSS cycle analysis, which was in agreement with the PSL engine test data. The compressor flow analysis indicated that the blockage due to ice accretion in the LPC exit guide vane stators caused the exit guide vane (EGV) to be nearly choked, significantly reducing the air flow rate into the core. This caused the LPC to eventually be in stall due to increasing levels of diffusion in the rotors and high incidence angles in the inlet guide vane (IGV) and EGV stators. The flow analysis indicating compressor stall is substantiated by the video images of the IGV taken during the PSL test, which showed water on the surface of the IGV flowing upstream out of the engine, indicating flow reversal, which is characteristic of a stalled compressor. Veres, Joseph P. and Jorgenson, Philip, C. E. and Jones, Scott M. Glenn Research Center COMPRESSORS; PROPULSION SYSTEM PERFORMANCE; ENGINE TESTS; ICE FORMATION; AIR FLOW; FLOW VELOCITY; PROPULSION SYSTEM CONFIGURATIONS; THERMODYNAMIC CYCLES; DIFFUSION; GUIDE VANES; ROTATING STALLS; COMPRESSOR BLADES
Author : John T. Sinnette,Oscar W. Schey,J. Austin King
Publisher : Unknown
Page : 74 pages
File Size : 43,6 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 : National Academies of Sciences, Engineering, and Medicine,Division on Engineering and Physical Sciences,Aeronautics and Space Engineering Board,Committee on Propulsion and Energy Systems to Reduce Commercial Aviation Carbon Emissions
Publisher : National Academies Press
Page : 123 pages
File Size : 55,5 Mb
Release : 2016-08-09
Category : Technology & Engineering
ISBN : 9780309440998
The primary human activities that release carbon dioxide (CO2) into the atmosphere are the combustion of fossil fuels (coal, natural gas, and oil) to generate electricity, the provision of energy for transportation, and as a consequence of some industrial processes. Although aviation CO2 emissions only make up approximately 2.0 to 2.5 percent of total global annual CO2 emissions, research to reduce CO2 emissions is urgent because (1) such reductions may be legislated even as commercial air travel grows, (2) because it takes new technology a long time to propagate into and through the aviation fleet, and (3) because of the ongoing impact of global CO2 emissions. Commercial Aircraft Propulsion and Energy Systems Research develops a national research agenda for reducing CO2 emissions from commercial aviation. This report focuses on propulsion and energy technologies for reducing carbon emissions from large, commercial aircraftâ€" single-aisle and twin-aisle aircraft that carry 100 or more passengersâ€"because such aircraft account for more than 90 percent of global emissions from commercial aircraft. Moreover, while smaller aircraft also emit CO2, they make only a minor contribution to global emissions, and many technologies that reduce CO2 emissions for large aircraft also apply to smaller aircraft. As commercial aviation continues to grow in terms of revenue-passenger miles and cargo ton miles, CO2 emissions are expected to increase. To reduce the contribution of aviation to climate change, it is essential to improve the effectiveness of ongoing efforts to reduce emissions and initiate research into new approaches.
Author : Lewis Research Center
Publisher : Unknown
Page : 542 pages
File Size : 55,8 Mb
Release : 1965
Category : Axial flow compressors
ISBN : STANFORD:36105113764901
Author : Linwood C. Wright,John F. Klapproth
Publisher : Unknown
Page : 34 pages
File Size : 42,5 Mb
Release : 1949
Category : Aeronautics
ISBN : UOM:39015086432344
Author : Anonim
Publisher : Unknown
Page : 892 pages
File Size : 53,8 Mb
Release : 1976-07
Category : Mechanical engineering
ISBN : UOM:39076000172366
Author : Anonim
Publisher : Unknown
Page : 24 pages
File Size : 45,9 Mb
Release : 1981
Category : Electronic
ISBN : NASA:31769000551823
The aerodynamic performance of the inlet manifold and stator assembly of the compressor-drive turbine was experimentally determined with cold air as the working fluid. The investigation included measurements of mass flow and stator-exit fluid torque as well as radial surveys of total pressure and flow angle at the stator inlet and annulus surveys of total pressure and flow angle at the stator exit. The stator-exit aftermixed flow conditions and overall stator efficiency were obtained and compared with their design values and the experimental results from three other stators. In addition, an analysis was made to determine the constituent aerodynamic losses that made up the stator kinetic energy loss. (Author).
Author : Anonim
Publisher : Unknown
Page : 954 pages
File Size : 49,6 Mb
Release : 1968
Category : Nuclear energy
ISBN : UOM:39015026176951
Author : David Emerson Muir
Publisher : National Library of Canada
Page : 0 pages
File Size : 52,5 Mb
Release : 1988
Category : Axial flow compressors
ISBN : 0315406372
