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Relevant bibliographies by topics / Design of axial compressors

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Dissertations / Theses

Academic literature on the topic 'Design of axial compressors'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

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Dissertations / Theses on the topic "Design of axial compressors"

1

Piscopo, Giovanni. "Preliminary aerothermal design of axial compressors." Thesis, Cranfield University, 2013. http://dspace.lib.cranfield.ac.uk/handle/1826/7909.

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The research work disclosed in this publication is partially funded by the Strategic Educational Pathways Scholarship Scheme (Malta). The scholarship is part-financed by the European Union – European Social Fund under Programme II – Cohesion Policy 2007-2013.<br>This dissertation documents a compressor preliminary design study conducted by the author in fulfilment of his MSc thesis requirements. The compressor is intended for a new development engine within the 20Klbf thrust category, planned to be used on a short-haul aircraft, namely the ERJ-190. A market research suggests that there exists

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2

Lopes, Fernando de Oliveira. "Modelo computacional para projeto de compressores axiais." [s.n.], 2007. http://repositorio.unicamp.br/jspui/handle/REPOSIP/265338.

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Orientador: Jorge Isaias Llagostera Beltran<br>Dissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecanica<br>Made available in DSpace on 2018-08-08T17:53:07Z (GMT). No. of bitstreams: 1 Lopes_FernandodeOliveira_M.pdf: 4254683 bytes, checksum: 3714a253c99b8967319409a00b69058a (MD5) Previous issue date: 2007<br>Resumo: Este trabalho apresenta o desenvolvimento de um programa computacional para modelagem inicial de compressores axiais de vários estágios pertencentes ao conjunto de turbinas a gás. O desenvolvimento do programa se baseia na metodologia adotada p

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3

Nucara, Pascal. "Design of gas turbine axial compressors for fuel flexibility." Thesis, University of Sussex, 2014. http://sro.sussex.ac.uk/id/eprint/48905/.

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Current gas turbine technology for power generation is generally optimised for natural gas. On the basis of current instabilities in natural gas price and supply, the use of alternative fuels, such as syngas, has recently gained high interest. Due to the different thermodynamic properties of syngas compared to natural gas the behaviour of existing gas turbine components may significantly change. From practical and economic points of view, it is generally considered that in order to meet the new fuel properties, the main effort should be put on the adaptation of conventional gas turbines in int

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4

Camp, Timothy Richard. "Aspects of the off-design performance of axial flow compressors." Thesis, University of Cambridge, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.387517.

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5

Robinson, Christopher J. "End-wall flows and blading design for axial flow compressors." Thesis, Cranfield University, 1991. http://dspace.lib.cranfield.ac.uk/handle/1826/6929.

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The flow in multistage axial flow compressors is particularly complex in nature because of the proximity of moving bladerows, the growth of end-wall boundary layers and the presence of tip and seal leakages and secondary flow. The problems associated with these phenomena are at their most acute in the latter, subsonic stages of the core compressor, where Reynolds numbers are modest and the blading has low aspect ratio. Indeed, much of the inefficiency of axial stages is believed to be associated with the interaction between blading and end-wall flows. The fact that the end-wall flow phenomena

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6

Ando, Victor Fujii. "Genetic algorithm for preliminary design optimisation of high-performance axial-flow compressors." Instituto Tecnológico de Aeronáutica, 2011. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1969.

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This work presents an approach to optimise the preliminary design of high-performance axial-flow compressors. The preliminary design within the Gas Turbine Group at ITA, is carried on with an in-house computational program based upon the streamline curvature method, using correlations from the literature to assess the losses. The choice of many parameters of the thermodynamic cycle and of geometries relies upon the expertise from the members of the Group. Nevertheless, it is still a laborious and time-consuming task, requiring successive trial and errors. Therefore, to support the compressor d

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7

Birkenheier, David Andrew. "Non-uniform radial meanline method for off-design performance estimation of multistage axial compressors." Thesis, Massachusetts Institute of Technology, 2018. http://hdl.handle.net/1721.1/119062.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2018.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 111-112).<br>The increasing use of renewable energy sources necessitates power-generating gas turbines capable of frequently and rapidly starting up to supplement the energy supply when renewable sources alone cannot meet demand [1], [21. This makes the off-design performance of such gas turbines more important as they spend more of their operational life off the design point. Currently off-design performan

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8

Iyengar, Vishwas. "A First Principles Based Methodology for Design of Axial Compressor Configurations." Diss., Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/16163.

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Axial compressors are widely used in many aerodynamic applications. The design of an axial compressor configuration presents many challenges. Until recently, compressor design was done using 2-D viscous flow analyses that solve the flow field around cascades or in meridional planes or 3-D inviscid analyses. With the advent of modern computational methods it is now possible to analyze the 3-D viscous flow and accurately predict the performance of 3-D multistage compressors. It is necessary to retool the design methodologies to take advantage of the improved accuracy and physical fidelity of the

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9

Ramakdawala, Rizwan R. "Preliminary design code for an axial stage compressor." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2001. http://handle.dtic.mil/100.2/ADA397395.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, Sept. 2001.<br>Thesis advisor, Shreeve, Raymond P. "September 2001." Includes bibliographical references (p. 117-119). Also available in print.

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10

Merchant, Ali A. (Ali Abbas). "Design and analysis of axial aspirated compressor stages." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/9362.

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Thesis (Ph.D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.<br>Includes bibliographical references (p. 145-150).<br>The pressure ratio of axial compressor stages can be significantly increased by controlling the development of blade and endwall boundary layers in regions of adverse pressure gradient by means of boundary layer suction. This concept is validated and demonstrated through the design and analysis of two unique aspirated compressor stages: a low-speed stage with a design pressure ratio of 1.6 at a tip speed of 750 ft/s, and a high-speed stage

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