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

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Published: 4 June 2021

Last updated: 1 February 2022

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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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11

Wisnia, Arnaud Irving. "A computational model for multistage axial compressor design." Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/50318.

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12

Bendali-Amor, M. "Secondary and endwall losses in an axial flow compressor." Thesis, University of Newcastle Upon Tyne, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.316159.

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13

Reid, William D. "Transonic axial compressor design case study and preparations for testing." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1995. http://handle.dtic.mil/100.2/ADA306259.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, September 1995.<br>Thesis advisor(s): Raymond P. Shreeve. "September 1995." Includes bibliographical references. Also available online.

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14

Fréchette, Luc G. (Luc Guy). "Implications of stability modeling for high-speed axial compressor design." Thesis, Massachusetts Institute of Technology, 1997. http://hdl.handle.net/1721.1/10721.

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15

Dorca, Luque Josep M. (Josep Maria) 1981. "Application of an energy-like stability metric for axial compressor design." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/82800.

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16

Brand, Maximilian Lewis. "An improved blade passage model for estimating off-design axial compressor performance." Thesis, Massachusetts Institute of Technology, 2013. http://hdl.handle.net/1721.1/85765.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2013.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 127-129).<br>Accurate estimates of multistage axial compressor performance at off-design operating conditions are essential to the determination of key performance metrics of aircraft gas turbine engines, such as fuel burn, thrust output, and stable operating range. However, conventional RANS based CFD calculations of multistage axial compressors diverge at off-design operating conditions where large separa

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17

Blanvillain, Emmanuel 1979. "Dynamic stability analysis of a multi-stage axial compressor with design implications." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/82255.

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18

Mahmood, Syed Moez Hussain. "Optimization Capabilities for Axial Compressor Blades and Seal Teeth Cavity." University of Cincinnati / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1458300148.

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19

Jones, James A. "A multidisciplinary algorithm for the 3-D design optimization of transonic axial compressor blades." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Jun%5FJones%5FJames.pdf.

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Thesis (Ph. D. in Aeronautics and Astronautics)--Naval Postgraduate School, June 2002.<br>Dissertation supervisor: Raymond P. Shreeve. Includes bibliographical references (p. 157-161). Also available online.

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20

Drayton, Scott. "Design, test, and evaluation of a transonic axial compressor rotor with splitter blades." Thesis, Monterey, California: Naval Postgraduate School, 2013. http://hdl.handle.net/10945/37616.

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Approved for public release; distribution is unlimited<br>A new design procedure was developed and documented that uses commercial-off-the-shelf software (MATLAB, SolidWorks, and ANSYS-CFX) for the geometric rendering and analysis of a transonic axial compressor rotor with splitter blades. Predictive numerical simulations were conducted and experimental data were collected at the NPS TPL utilizing the Transonic Compressor Rig. This study advanced the understanding of splitter blade geometry, placement, and performance benefits. In particular, it was determined that moving the splitter blade fo

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21

Lyes, Peter A. "Low speed axial compressor design and evaluation : High speed representation and endwall flow control studies." Thesis, Cranfield University, 1999. http://hdl.handle.net/1826/4251.

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This Thesis reports the design, build and test of two sets of blading for the Cranfield University low speed research compressor. The first of these was a datum low speed design based on the fourth stage of the DERA high speed research compressor C 147. The emphasis of this datum design was on the high-to-low speed transformation process and the evaluation of such a process through comparing detailed flow measurements from both compressors. Area traverse measurements in both the stationary and rotating frame of reference were taken at Cranfield along with overall performance, blade surface sta

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22

Van, Rooij Michael P. C. "Development of a three-dimensional multistage inverse design method for aerodynamic matching of axial compressor blading." Related electronic resource: Current Research at SU : database of SU dissertations, recent titles available full text, 2008. http://wwwlib.umi.com/cr/syr/main.

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23

Jia, H.-X., G. Xi, L. Müller, R. Mailach, and K. Vogeler. "Effect of clocking on unsteady rotor blade loading in a low-speed axial compressor at design and off-design operating conditions." Sage, 2008. https://publish.fid-move.qucosa.de/id/qucosa%3A38439.

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This paper presents the results of stator clocking investigations at a design point and an operating point near the stability limit in a low-speed research compressor (LSRC). The unsteady flow field of the LSRC at several clocking configurations was investigated using a three-dimensional unsteady, viscous solver. The unsteady pressure on the rotor blades at midspan (MS) was measured using time-resolving piezoresistive miniature pressure transducers. The effect of clocking on the unsteady pressure fluctuation at MS on the rotor blades is discussed for different operating points. Based on the un

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24

Li, Yan Sheng. "Mixing in axial compressors." Thesis, University of Cambridge, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.334235.

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25

Grimshaw, Samuel David. "Bleed in axial compressors." Thesis, University of Cambridge, 2014. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.707970.

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26

McDougall, Neil Malcolm. "Stall inception in axial compressors." Thesis, University of Cambridge, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.237803.

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27

Khalsa, Amrit Singh. "Endwall blockage in axial compressors." Thesis, Massachusetts Institute of Technology, 1996. http://hdl.handle.net/1721.1/10826.

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28

Power, Bronwyn. "Aspirated compressors." Thesis, University of Cambridge, 2013. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.648363.

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29

Young, Anna Mollie. "Tip-clearance effects in axial compressors." Thesis, University of Cambridge, 2012. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.610603.

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30

Seitz, Peter Alexander. "Casing treatment for axial flow compressors." Thesis, University of Cambridge, 1999. https://www.repository.cam.ac.uk/handle/1810/251677.

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31

Storer, John Andrew. "Tip clearance flow in axial compressors." Thesis, University of Cambridge, 1991. https://www.repository.cam.ac.uk/handle/1810/251503.

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32

Leggett, John. "Detailed investigation of loss prediction of an axial compressor cascade at off-design conditions in the presence of incident free-stream disturbances using large eddy simulations." Thesis, University of Southampton, 2018. https://eprints.soton.ac.uk/422285/.

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The prediction of an axial compressor’s loss early on in the design phase is a valuable and important part of the design process. The work presented here focuses on assessing the accuracy of current prediction methods, Reynolds Averaged Navier Stokes (RANS), compared with highly accurate Large Eddy Simulations (LES). The simulations were performed at the challenging running conditions of engine relevant Mach (0.67) and Reynolds (300,000) numbers. The work looks at the effects of off-design incidence and the influence of different free-stream disturbances on loss prediction. From the highly acc

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33

Zaki, Mina Adel. "Physics based modeling of axial compressor stall." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/31683.

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Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2010.<br>Committee Chair: Dr. Lakshmi N. Sankar; Committee Member: Dr. Alex Stein; Committee Member: Dr. J.V. R. Prasad; Committee Member: Dr. Richard Gaeta; Committee Member: Dr. Suresh Menon. Part of the SMARTech Electronic Thesis and Dissertation Collection.

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34

Wilson, Alexander George. "Stall and surge in axial flow compressors." Thesis, Cranfield University, 1996. http://dspace.lib.cranfield.ac.uk/handle/1826/10432.

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The objective of the work described in this thesis is twofold; to elucidate the nature of stall and surge in an axial flow aeroengine compressor, and to improve on current computational stall modelling techniques. Particular attention is paid to the initial stages of the stall/surge transient, and to the possibility of using active control techniques to prevent or delay the onset of stall/surge. A detailed analysis is presented of measurements of the stalling behaviour of a Rolls- Royce VIPER jet engine, showing a wide variety of stall inception and post-stall behaviour. Stall transients are

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35

Gallimore, Simon John. "Spanwise mixing in multi-stage axial compressors." Thesis, University of Cambridge, 1986. https://www.repository.cam.ac.uk/handle/1810/250879.

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36

Thomas, Keegan Darrall. "Blade row and blockage modelling in an axial compressor throughflow code /." Link to the online version, 2005. http://hdl.handle.net/10019/1239.

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37

Gill, M. E. "Surge prediction in multistage axial and centrifugal compressors." Thesis, Cranfield University, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.370630.

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38

Paduano, James D. (James Donald). "Active control of rotating stall in axial compressors." Thesis, Massachusetts Institute of Technology, 1992. http://hdl.handle.net/1721.1/11630.

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39

Meehan, Anthony. "Steady state response of an axial compression system to a constant heat input." Thesis, Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/15975.

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40

Li, Yan-Ling. "Numerical simulations of rotating stall in axial flow compressors." Thesis, University of Sussex, 2014. http://sro.sussex.ac.uk/id/eprint/47428/.

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Gas turbine compressor performance may encounter deterioration during service for various reasons such as damage by debris from the casing or foreign objects impacting on the blades, typically near the rotor's tip. Moreover, mal-schedule of Variable Stator Vanes (VSVs) during start-up may also result in performance deterioration and reduction in the surge margin. Ability to assess the effect of compressor deterioration using Computational Fluid Dynamics (CFD) is important at both design stage and in service. Compressor blade damage breaks the cyclic symmetry and the VSVs mal-schecule creates m

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41

DiOrio, Austin Graf. "Small core axial compressors for high efficiency jet aircraft." Thesis, Massachusetts Institute of Technology, 2012. http://hdl.handle.net/1721.1/77107.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2012.<br>Cataloged from department-submitted PDF version of thesis. This electronic version was submitted and approved by the author's academic department as part of an electronic thesis pilot project. The certified thesis is available in the Institute Archives and Special Collections.<br>Includes bibliographical references (p. 115-117).<br>This thesis quantifies mechanisms that limit efficiency in small core axial compressors, defined here as compressor exit corrected flow between 1.5 and 3.0 lbm/s. T

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42

Etchevers, Olivier. "Evaluation of rotating stall warning schemes for axial compressors." Thesis, Massachusetts Institute of Technology, 1992. http://hdl.handle.net/1721.1/12939.

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43

Bae, Jinwoo W. "Active control of tip clearance flow in axial compressors." Thesis, Massachusetts Institute of Technology, 2001. http://hdl.handle.net/1721.1/8705.

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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2001.<br>Includes bibliographical references.<br>Control of compressor tip clearance flows is explored in a linear cascade using three types of fluidic actuators; Normal Synthetic Jet (NSJ; unsteady jet normal to the mean flow with zero net mass flux), Directed Synthetic Jet (DSJ; injection roughly aligned with the mean flow), and Steady Directed Jet (SDJ), mounted on the casing wall. The objective is to affect the following measures: (1) reduction of tip leakage flow rate, (2) mixing enhancement bet

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44

White, N. M. "Optimising stator vane settings in multistage axial flow compressors." Thesis, Cranfield University, 2002. http://dspace.lib.cranfield.ac.uk/handle/1826/10756.

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There is a common requirement in the process, oil and gas turbine industries for high performance axial flow compressors operating over a wide range of mass flow rate and rotational speed at high efficiency. The trends have been for higher blade loadings (greater pressure rise per stage) and higher efficiency which are increasingly achieved through sophisticated Computational Fluid Dynamics designs. These trends, however, tend to mitigate against stable operating flow range (reduced surge margin), which can often lead to performance compromises. The objective of this work is to investigate the

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45

White, Nicholas M. "Optimising stator vane settings in multistage axial flow compressors." Thesis, Cranfield University, 2002. http://dspace.lib.cranfield.ac.uk/handle/1826/10756.

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There is a common requirement in the process, oil and gas turbine industries for high performance axial flow compressors operating over a wide range of mass flow rate and rotational speed at high efficiency. The trends have been for higher blade loadings (greater pressure rise per stage) and higher efficiency which are increasingly achieved through sophisticated Computational Fluid Dynamics designs. These trends, however, tend to mitigate against stable operating flow range (reduced surge margin), which can often lead to performance compromises. The objective of this work is to investigate the

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46

Bloch, Gregory S. "A wide-range axial-flow compressor stage performance model." Thesis, This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-08182009-040326/.

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47

Baker, Jonathan D. "Analysis of the sensitivity of multi-stage axial compressors to fouling at various stages." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Sep%5FBaker.pdf.

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48

Gill, Andrew. "A comparison between stall prediction models for axial flow compressors." Thesis, Stellenbosch : Stellenbosch University, 2006. http://hdl.handle.net/10019.1/18702.

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Thesis (MScEng)--Stellenbosch University, 2006.<br>ENGLISH ABSTRACT: The Stellenbosch University Compressor Code (SUCC) has been developed for the purpose of predicting the performance of axial flow compressors by means of axisymmetric inviscid throughflow methods with boundary layer blockage and empirical blade row loss models. This thesis describes the process of the implementation and verification of a number of stall prediction criteria in the SUCC. In addition, it was considered desirable to determine how certain factors influence the accuracy of the stall prediction criteria, namely

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49

Pantelidis, Konstantinos. "Reynolds number effects on the aerodynamics of compact axial compressors." Thesis, University of Cambridge, 2018. https://www.repository.cam.ac.uk/handle/1810/284940.

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An axial compressor for a domestic appliance can be designed to be smaller than an equivalent centrifugal compressor. However, the performance of such a compact axial compression system is limited by increased viscous losses and reduced flow turning at low Reynolds numbers ($Re$). In domestic appliance compressors, $Re$ is typically in the range $10^4$ - $10^5$. Although the aerodynamics of isolated aerofoils operating at these $Re$ have been studied extensively, the flow fields within low $Re$ axial compressors have not been investigated in detail. This dissertation aims to develop an improve

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50

Lavrich, Philip Lewis. "Time resolved measurements of rotating stall in axial flow compressors." Thesis, Massachusetts Institute of Technology, 1988. http://hdl.handle.net/1721.1/14567.

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