Relevant bibliographies by topics / Compressors Leading edges (Aerodynamics) Aerofoils

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  1. Dissertations / Theses
  2. Books
  3. Conference papers

Academic literature on the topic 'Compressors Leading edges (Aerodynamics) Aerofoils'

Author: Grafiati
Published: 4 June 2021
Last updated: 16 February 2022

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Dissertations / Theses on the topic "Compressors Leading edges (Aerodynamics) Aerofoils"

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Elmstrom, Michael E. "Numerical prediction of the impact of non-uniform leading edge coatings on the aerodynamic performance of compressor airfoils." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2004. http://library.nps.navy.mil/uhtbin/hyperion/04Jun%5FElmstrom.pdf.

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Grohsmeyer, Steven P. "Numerical investigation of the effect of leading edge geometry on dynamic stall of airfoils." Thesis, Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA239949.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, September 1990.<br>Thesis Advisor(s): Ekaterinaris, John A. ; Platzer, Max. "September 1990." Description based on title screen as viewed on December 21, 2009. DTIC Identifier(s): Dynamics, leading edges, airfoils, dynamic stall, oscillating airfoil, pitching airfoil, leading edge geometry, pressure gradient, theses. Author(s) subject terms: Dynamic stall, oscillating airfoil, pitching airfoil, leading edge geometry, pressure gradient. Includes bibliographical references (p. 111-112). Also available in print.
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Powell, Jonathan D. "Impact of leading-edge orientation and shape on performance of a compressor blade." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2005. http://library.nps.navy.mil/uhtbin/hyperion/05Jun%5FPowell.pdf.

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Young, John Aerospace Civil &amp Mechanical Engineering Australian Defence Force Academy UNSW. "Numerical simulation of the unsteady aerodynamics of flapping airfoils." Awarded by:University of New South Wales - Australian Defence Force Academy. School of Aerospace, Civil and Mechanical Engineering, 2005. http://handle.unsw.edu.au/1959.4/38656.

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There is currently a great deal of interest within the aviation community in the design of small, slow-flying but manoeuvrable uninhabited vehicles for reconnaissance, surveillance, and search and rescue operations in urban environments. Inspired by observation of birds, insects, fish and cetaceans, flapping wings are being actively studied in the hope that they may provide greater propulsive efficiencies than propellers and rotors at low Reynolds numbers for such Micro-Air Vehicles (MAVs). Researchers have posited the Strouhal number (combining flapping frequency, amplitude and forward speed)
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Books on the topic "Compressors Leading edges (Aerodynamics) Aerofoils"

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Center, Lewis Research, ed. Navier-Stokes analysis of airfoils with leading edge ice accretions. Lewis Research Center, 1993.

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Center, Lewis Research, ed. Navier-Stokes analysis of airfoils with leading edge ice accretions. Lewis Research Center, 1993.

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Navier-Stokes analysis of airfoils with leading edge ice accretions. Lewis Research Center, 1993.

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Conference papers on the topic "Compressors Leading edges (Aerodynamics) Aerofoils"

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Xing, X. Q., S. Zhou, and X. L. Zhao. "Probing Into the Connotation of Sweep Aerodynamics of Transonic Fans and Compressors." In ASME Turbo Expo 2001: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/2001-gt-0352.

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Theory researches, numerical analyses and experiment studies of sweep aerodynamics in turbo-machinery had rapidly developed during the 1990s. Taking a low-aspect-ratio, high-loaded axial flow transonic rotor as the baseline, this paper attempts to probe the connotation of sweep aerodynamics of transonic fans and compressors. The definition of sweep angle was discussed. Flow field, key factors that affect structures of flow fields, linkage between leading edges as well as flow field structures in swept rotors were presented. In order to find out the optimum sweep leading edge curve under prescr
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Abdelwahab, Ahmed. "The Aerodynamics of Three-Dimensional Vaned Diffusers in Industrial Centrifugal Compressors." In ASME 2005 Fluids Engineering Division Summer Meeting. ASMEDC, 2005. http://dx.doi.org/10.1115/fedsm2005-77333.

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Vaned diffusers have been used successfully as efficient and compact dynamic pressure recovery devices in industrial centrifugal compressor stages. Typically such diffusers consist of a cascade of two-dimensional blades distributed circumferentially at close proximity to the impeller exit. In this paper three low-solidity diffuser blade geometries are numerically investigated. The first geometry employs variable stagger stacking of similar blade sections along the blade span. The second employs linearly inclined stacking to generate blade lean along the diffuser span. The third geometry employ
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Hanschke, Benjamin, Thomas Klauke, and Arnold Kühhorn. "The Effect of Foreign Object Damage on Compressor Blade High Cycle Fatigue Strength." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63599.

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For a considerable amount of time blade integrated disks (blisks) are established as a standard component of high pressure compressors (HPCs) in aero engines. Due to the steady requirement to increase the efficiency of modern HPCs, blade profiles get thinned out and aerodynamic stage loading increases. Ever since, aerofoil design has to balance structural and aerodynamic requirements. One particularity of aero engines is the possibility to ingest different kinds of debris during operation and some of those particles are hard enough to seriously damage the aerofoil. Lately, a growing number of
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Dutta, Amit Kumar, Peter Michael Flassig, and Dieter Bestle. "A Non-Dimensional Quasi-3D Blade Design Approach With Respect to Aerodynamic Criteria." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50687.

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The competition between aero-engine manufacturers has increased dramatically in the last decades. Saving computational time within the design process, which is equivalent to saving money, is of major importance for the industry. Talking about the aerodynamic compressor blading process, it becomes indispensable to go for new or alternative ways in designing blades in order to fulfill raised performance demands. The focus of this paper, therefore, is to propose a quasi-3D aerodynamic design concept with extended and improved parameterization of the aerofoil in order to support the industrial bla
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Keller, Christian, Andreas Kellersmann, Jens Friedrichs, and Joerg R. Seume. "Influence of Geometric Imperfections on Aerodynamic and Aeroelastic Behavior of a Compressor Blisk." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63556.

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Impacts of foreign objects can cause cracks and dents in airfoils, especially in the leading edge. The regeneration of high-pressure compressors blisks with current repair methods is often restricted to a local blending of these edges. This can cause significant changes in the airfoils’ geometrical properties, which in turn influence their aerodynamic and aeroelastic characteristics. Changes at the leading edge have a particularly strong influence on the airfoils’ aerodynamic properties. In order to be able to make an informed decision about if and how a repair should be performed, consequence
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Mustafa, Zainol, Pericles Pilidis, and Joao A. Amaral Teixeira. "CFD Aerodynamic Investigation of Air-Water Trajectories on Rotor-Stator Blade of an Axial Compressor." In ASME 2005 Power Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/pwr2005-50069.

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In multistage axial-flow compressors, the droplet size distribution of the injected fluid depends upon the entry conditions. In general, droplet trajectory prediction is important for particulate laden flow turbomachinery as it helps to understand the pitting and the cutting of the blade leading and trailing edges as well as to improve the design of blade passages. An investigation was carried out using CFXTASCflow on the aerodynamics of an axial-flow compressor designed for operation with air while operating with an air-fluid droplet mixture during field operation. In this study, a 3D rotor-s
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