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Dissertations / Theses on the topic 'Gas turbione'

Author: Grafiati

Published: 3 June 2025

Last updated: 31 July 2025

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1

Rice, Matthew Jason. "Simulation of Isothermal Combustion in Gas Turbines." Thesis, Virginia Tech, 2004. http://hdl.handle.net/10919/9723.

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Current improvements in gas turbine engine performance have arisen primarily due to increases in turbine inlet temperature and compressor pressure ratios. However, a maximum possible turbine inlet temperature exits in the form of the adiabatic combustion temperature of the fuel. In addition, thermal limits of turbine blade materials also places an upper bound on turbine inlet temperatures. Thus, the current strategy for improving gas turbine efficiency is inherently limited. Introduction of a new gas turbine, based on an alternative work cycle utilizing isothermal combustion (i.e. combustion w

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2

Crosby, Jared M. "Particle Size, Gas Temperature, and Impingement Cooling Effects on High Pressure Turbine Deposition in Land Based Gas Turbines from Various Synfuels." Diss., CLICK HERE for online access, 2007. http://contentdm.lib.byu.edu/ETD/image/etd1774.pdf.

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3

Aslanidou, Ioanna. "Combustor and turbine aerothermal interactions in gas turbines with can combustors." Thesis, University of Oxford, 2015. https://ora.ox.ac.uk/objects/uuid:b1527fd0-8e54-4831-8625-32722141511e.

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As the research into the improvement of gas turbine performance progresses, the combustor-turbine interface becomes of increasing importance. In new engine designs components come closer together and the study of the combustor and turbine interactions can prove to be valuable for the improvement of the aerothermal performance of the vane. This thesis presents an experimental and numerical investigation of the aerodynamic and heat transfer aspect of the interactions between the combustor and the nozzle guide vane. In the gas turbine studied the trailing edge of the combustor transition duct wal

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4

Psarra, Aikaterini. "Gas turbine shaft failure modelling friction and wear modelling of turbines in contact." Thesis, Cranfield University, 2010. http://dspace.lib.cranfield.ac.uk/handle/1826/8348.

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A possible shaft failure event can trigger a number of mechanisms affecting the mechanical integrity particular of turbine discs and blades. A predominant aim in engine design and development is to satisfy that passenger lives are not to be endangered by the release of high energy debris. In a typical Intermediate Pressure shaft failure scenario of a 3-spool high bypass ratio turbofan engine, a potential mechanism to limit the terminal speed of the free running turbine, within acceptable values, is proven to be the impact of the free running turbine with the following stationary arrangement.

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5

Yen, Hsin-Yi. "NEW ANALYSIS AND DESIGN PROCEDURES FOR ENSURING GAS TURBINE BLADES AND ADHESIVE BONDED JOINTS STRUCTURAL INTEGRITY AND DURABILITY." [Columbus, Ohio] : Ohio State University, 2000. http://www.ohiolink.edu/etd/send-pdf.cgi?osu967666610.

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Thesis (Ph. D.)--Ohio State University, 2000.<br>Includes vita. Title from title page display. Abstract. Advisor: M.-H. Herman Shen, Dept. of Aerospace Engineering, Applied Mechanics, and Aviation. Includes bibliographical references (p. 152-154).

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6

Ozmen, Teoman. "Gas Turbine Monitoring System." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/12607957/index.pdf.

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In this study, a new gas turbine monitoring system being able to carry out appropriate run process is set up for a gas turbine with 250 kW power rating and its accessories. The system with the mechanical and electrical connections of the required sub-parts is transformed to a kind of the test stand. Performance test result calculation method is described. In addition that, performance evaluation software being able to apply with the completion of the preliminary performance tests is developed for this gas turbine. This system has infrastructure for the gas turbine sub-components performance an

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7

Flesland, Synnøve Mangerud. "Gas Turbine Optimum Operation." Thesis, Norges teknisk-naturvitenskapelige universitet, Institutt for energi- og prosessteknikk, 2010. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-12409.

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Many offshore installations are dependent on power generated by gas turbines and a critical issue is that these experience performance deterioration over time. Performance deterioration causes reduced plant efficiency and power output as well as increased environmental emissions. It is therefore of highest importance to detect and control recoverable losses in order to reduce their effect. This thesis project was therefore initiated to evaluate parameters for detecting performance deterioration in addition to document different aspects of gas turbine degradation and performance recovery. Compr

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8

Spencer, Matthew Richard. "Gas turbine lubricant evaluation." Thesis, University of Birmingham, 2014. http://etheses.bham.ac.uk//id/eprint/5423/.

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This thesis is a study of the chemical and physical changes which can occur to gas turbine lubricants as a result of exposure to operational conditions. The continual evolution toward more efficient gas turbines is accompanied by increasing thermal and mechanical loading which the lubricant must be able to withstand. In this thesis two major degradation issues are studied; thermal oxidative degradation and lubricant deposition. In the area of thermal oxidative degradation, efforts are made to better understand the key parameters which determine the lubricant breakdown mechanism. Through contro

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9

Patel, Hardik Dipan. "Experimental Investigation of Initial Onset of Sand Deposition in the Turbine Section of Gas Turbines." Thesis, Virginia Tech, 2015. http://hdl.handle.net/10919/56595.

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Particle ingestion and deposition is an issue of concern for gas turbine engines operating in harsh environments. The ingested particles accelerate the deterioration of engine components and thus reduce its service life. This effect is observed to a greater extent in aircrafts/helicopters operating in particle laden environment. Understanding the effects of particle ingestion at engine representative condition leads to improved designs for turbomachinery. Experiments have been in an Aerothermal Rig facility at Virginia Tech to study particle deposition at engine representative temperatures. Th

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10

Laycock, Robert. "Particle Deposition Behavior from Coal-Derived Syngas in Gas Turbines at Modern Turbine Inlet Temperatures." BYU ScholarsArchive, 2017. https://scholarsarchive.byu.edu/etd/6519.

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Certain types of fuel used for combustion in land-based gas turbines can contain traces of ash when introduced into a gas turbine. Examples include synfuel, from the gasification of coal, and heavy fuel oil. When these ash particles travel through the hot gas path of the gas turbine they can deposit on turbine vanes and blades. As deposits grow, they can reduce turbine efficiency and damage turbine hardware. As turbine inlet temperatures increase, ash deposition rates increase as well.Experiments were conducted in the Turbine Accelerated Deposition Facility (TADF) at Brigham Young University t

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11

Ebaid, Munzer Shehadeh Yousef. "Design and construction of a small gas turbine to drive a permanent magnet high speed generator." Thesis, University of Hertfordshire, 2002. http://hdl.handle.net/2299/14046.

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Radial gas turbines engines have established prominence in the field of small turbomachinery because of their simplicity, relatively high performance and installation features. Thus they have been used in a variety of applications such as generator sets, small auxiliary power units (APu), air conditioning of aircraft cabins and hybrid electric vehicles turbines. The current research describes the design, manufacturing, construction and testing a radial type small gas turbine. The aim was to design and build the engine to drive directly a high-speed permanent magnet alternator running at 60000

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12

Barringer, Michael David. "Developing and Testing a Combustor Simulator For Investigating High Pressure Turbine Aerodynamics and Heat Transfer." Diss., Virginia Tech, 2006. http://hdl.handle.net/10919/79726.

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Within a gas turbine engine, the turbine nozzle guide vanes are subjected to very harsh conditions from the highly turbulent and hot gases exiting the combustor. The temperature and pressure fields exiting combustors are highly nonuniform and dictate the heat transfer and aero losses that occur in the turbine passages. To better understand these effects, the goal of this work was to develop an adjustable combustor exit profile simulator for the Turbine Research Facility (TRF) at the Air Force Research Laboratory. The TRF is a high temperature, high pressure, short duration blow-down test facil

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13

Spelling, James. "Hybrid Solar Gas-Turbine Power Plants : A Thermoeconomic Analysis." Doctoral thesis, KTH, Kraft- och värmeteknologi, 2013. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-121315.

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The provision of a sustainable energy supply is one of the most importantissues facing humanity at the current time, and solar thermal power hasestablished itself as one of the more viable sources of renewable energy. Thedispatchable nature of this technology makes it ideally suited to forming thebackbone of a future low-carbon electricity system.However, the cost of electricity from contemporary solar thermal power plantsremains high, despite several decades of development, and a step-change intechnology is needed to drive down costs. Solar gas-turbine power plants are apromising new alternat

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14

Bartlett, Michael. "Developing Humidified Gas Turbine Cycles." Doctoral thesis, KTH, Chemical Engineering and Technology, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3437.

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<p>As a result of their unique heat recovery properties,Humidified Gas Turbine (HGT) cycles have the potential todeliver resource-effective energy to society. The EvaporativeGas Turbine (EvGT) Consortium in Sweden has been studying thesetypes of cycles for nearly a decade, but now stands at acrossroads, with commercial demonstration remaining. Thisthesis binds together several key elements for the developmentof humidified gas turbines: water recovery and air and waterquality in the cycle, cycle selection for near-term, mid-sizedpower generation, and identifying a feasible niche market fordemon

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15

Pachidis, Vassilios A. "Gas turbine advanced performance simulation." Thesis, Cranfield University, 2006. http://dspace.lib.cranfield.ac.uk/handle/1826/4529.

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Current commercial 'state of the art' engine simulation software is of a low fidelity. Individual component performance characteristics are typically represented via nondimensional maps with empirical adjustments for off-design effects. Component nondimensional characteristics are usually obtained through the averaging of experimental readings from rig test analyses carried out under nominal operating conditions. In those cases where actual component characteristics are not available and default maps are used instead, conventional simulation tools can offer a good prediction of the performance

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16

Pachidis, Vassilios. "Gas Turbine Advanced Performance Simulation." Thesis, Cranfield University, 2006. http://hdl.handle.net/1826/4529.

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Current commercial `state of the art' engine simulation software is of a low fidelity. Individual component performance characteristics are typically represented via nondimensional maps with empirical adjustments for off-design effects. Component nondimensional characteristics are usually obtained through the averaging of experimental readings from rig test analyses carried out under nominal operating conditions. In those cases where actual component characteristics are not available and default maps are used instead, conventional simulation tools can offer a good prediction of the performance

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17

Spencer, A. "Gas turbine combustor port flows." Thesis, Loughborough University, 1998. https://dspace.lboro.ac.uk/2134/6883.

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Competitive pressure and stringent emissions legislation have placed an urgent demand on research to improve our understanding of the gas turbine combustor flow field. Flow through the air admission ports of a combustor plays an essential role in determining the internal flow patterns on which many features of combustor performance depend. This thesis explains how a combination of experimental and computational research has helped improve our understanding, and ability to predict, the flow characteristics of jets entering a combustor. The experiments focused on a simplified generic geometry of

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18

Ahmad, N. T. "Swirl stabilised gas turbine combustion." Thesis, University of Leeds, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.356423.

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19

Pishva, S. M. R. (S Mohammed Reza) Carleton University Dissertation Engineering Mechanical. "Rejuvenation of gas turbine discs." Ottawa, 1988.

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20

Asere, Abraham Awolola. "Gas turbine combustor wall cooling." Thesis, University of Leeds, 1986. http://etheses.whiterose.ac.uk/2590/.

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The need for better methods of cooling gas turbine combustors and a review of current cooling techniques have been presented. Three cooling methods are investigated: (a) Full Coverage Discrete Hole Film Cooling (Effusion), (b) Impingement/Effusion Hybrid Cooling Systems, and (c) Transpiration Cooling. The aim of these cooling techniques is to effectively and efficiently cool gas turbine combustors with a significant reduction in current cooling air requirements. The range of test conditions were coolant temperature, Tc, of 289 < Tc 710 K and combustion gases temperature, Tg, of 500 Tg N< 1900

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21

Skidmore, F. W., and n/a. "The influence of gas turbine combustor fluid mechanics on smoke emissions." Swinburne University of Technology, 1988. http://adt.lib.swin.edu.au./public/adt-VSWT20070420.131227.

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This thesis describes an experimental program covering the development of certain simple combustion chamber modifications to alleviate smoke emissions from the Allison T56 turboprop engines operated by the Royal Australian Air Force. The work includes a literature survey, smoke emission tests on two variants of the T56 engine, flow visualisation studies of the combustion system in a water tunnel and combustion rig tests of a standard combustor and four possible modifications. The rig tests showed that reductions in smoke emissions of 80% were possible by simple modifications that reduced the

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22

Schutte, Jeffrey Scott. "Simultaneous multi-design point approach to gas turbine on-design cycle analysis for aircraft engines." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/28169.

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Thesis (M. S.)--Aerospace Engineering, Georgia Institute of Technology, 2009.<br>Committee Chair: Mavris, Dimitri; Committee Member: Gaeta, Richard; Committee Member: German, Brian; Committee Member: Jones, Scott; Committee Member: Schrage, Daniel; Committee Member: Tai, Jimmy.

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23

Motsamai, Oboetswe Seraga. "Optimisation techniques for combustor design." Pretoria : [s.n.], 2009. http://upetd.up.ac.za/thesis/available/etd-04072009-222336/.

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24

Smith, Warren Robert. "High velocity gas journal bearings." Thesis, University of Oxford, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.317910.

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25

Šíblová, Kamila. "Návrh spalovací turbíny pro osobní automobil." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2013. http://www.nusl.cz/ntk/nusl-230622.

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This diploma thesis deals about the combustion turbine, design, processing and utilization. This work can be divided into three parts. The first part focuses on the theoretical knowledge gained in the field of gas turbines and their applications. The second part addresses the design of combustion turbine and its integral part. The third section describes the expected characteristics of combustion turbines. The work also includes the annex, which includes the technical documentation.

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26

Løver, Kristian Aase. "Biomass gasification integration in recuperative gas turbine cycles and recuperative fuel cell integrated gas turbine cycles : -." Thesis, Norwegian University of Science and Technology, Department of Energy and Process Engineering, 2007. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-9658.

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<p>A multi-reactor, multi-temperature, waste-heat driven biomass thermochemical converter is proposed and simulated in the process simulation tool Aspen Plus. The thermochemical converter is in Aspen Plus integrated with a gas turbine power cycle and a combined fuel cell/gas turbine power cycle. Both power cycles are recuperative, and supply the thermochemical converter with waste heat. For result comparison, the power cycles are also integrated with a reference conventional single-reactor thermochemical converter, utilizing partial oxidation to drive the conversion process. Exergy analysis

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Guarinelo, Júnior Flávio Fernando. "Análise termodinâmica de ciclo combinado operando fora das condições de projeto." [s.n.], 2012. http://repositorio.unicamp.br/jspui/handle/REPOSIP/265044.

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Orientador: Jorge Isaías Llagostera Beltrán<br>Tese (doutorado) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecânica<br>Made available in DSpace on 2018-08-20T08:08:23Z (GMT). No. of bitstreams: 1 GuarineloJunior_FlavioFernando_D.pdf: 112586941 bytes, checksum: 8ca74b9cc6e907dc47ec88f2c901a8b1 (MD5) Previous issue date: 2012<br>Resumo: O atendimento da demanda crescente de eletricidade, associado à necessidade do cumprimento de metas de emissões de gases causadores do aquecimento global, será um grande desafio ao setor elétrico nas próximas décadas. A geração de eletricidade

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28

Knost, Daniel G. "Predictions and Measurements of Film-Cooling on the Endwall of a First Stage Vane." Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/35186.

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In gas turbine development, the direction has been toward higher turbine inlet temperatures to increase the work output and thermal efficiency. This extreme environment can significantly impact component life. One means of preventing component burnout in the turbine is to effectively use film-cooling whereby coolant is extracted from the compressor and injected through component surfaces. One such surface is the endwall of the first stage nozzle guide vane. <p> This thesis details the design, prediction, and testing of two endwall film-cooling hole patterns provided by leading gas turbine

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29

Smith, Christopher Stephen. "Experimental Validation of a Hot Gas Turbine Particle Deposition Facility." The Ohio State University, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=osu1269547595.

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30

Eskner, Mats. "Mechanical Behaviour of Gas Turbine Coatings." Doctoral thesis, KTH, Materials Science and Engineering, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3776.

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<p>Coatings are frequently applied on gas turbine components inorder to restrict surface degradation such as corrosion andoxidation of the structural material or to thermally insulatethe structural material against the hot environment, therebyincreasing the efficiency of the turbine. However, in order toobtain accurate lifetime expectancies and performance of thecoatings system it is necessary to have a reliableunderstanding of the mechanical properties and failuremechanisms of the coatings.</p><p>In this thesis, mechanical and fracture behaviour have beenstudied for a NiAl coating applied by

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31

Cavaliere, Davide Egidio. "Blow-off in gas turbine combustors." Thesis, University of Cambridge, 2014. https://www.repository.cam.ac.uk/handle/1810/265575.

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This thesis describes an experimental investigation of the flame structure close to the extinction and the blow-off events of non-premixed and spray flames stabilized on an axisymmetric bluff body in a confined swirl configuration. The comparison of flames of different canonical types in the same basic aerodynamic field allows insights on the relative blow-off behaviour. The first part of the thesis describes several velocity measurements in non-reacting and reacting flows. The main usefulness of this data is to provide the aerodynamic flow pattern and some discussion on the velocity field and

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32

Bengtsson, Karl. "ThermoacousticInstabilities in a Gas Turbine Combustor." Thesis, KTH, MWL Marcus Wallenberg Laboratoriet, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-226530.

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Stationary gas turbines are widely used today for power generation and mechanical drive applications. The introduction of new regulations on emissions in the last decades have led to extensive development and new technologies used within modern gas turbines. The majority of the gas turbines sold today have a so called DLE (Dry Low Emission) combustion system that mainly operates in the leanpremixed combustion regime. The lean-premixed regime is characterized by low emission capabilities but are more likely to exhibit stability issues compared to traditional non-premixed combustion systems. The

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33

Murthy, J. N. "Gas turbine combustor modelling for design." Thesis, Cranfield University, 1988. http://hdl.handle.net/1826/2626.

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The design and development of gas turbine combustors is a crucial but uncertain part of an engine development process. Combustion within a gas turbine is a complex interaction of, among other things, fluid dynamics, heat and mass transfer and chemical kinetics. At present, the design process relies upon a wealth of experimental data and correlations. The proper use of this information requires experienced combustion engineers and even for them the design process is very time consuming. Some major engine manufacturers have attempted to address the above problem by developing one dimensional com

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Ismail, Ibrahim H. "Simulation of aircraft gas turbine engine." Thesis, University of Hertfordshire, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.303465.

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35

Farahani, Arash. "Gas turbine engine static strip seals." Thesis, University of Sussex, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.444118.

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Andrews, G. E. "Gas turbine combustion with low emissions." Thesis, University of Leeds, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.329381.

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Abdul, Husein Reyad Abdul Ameer. "Impingement cooling of gas turbine components." Thesis, University of Leeds, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.255236.

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ASSUMPCAO, VICTOR DOS SANTOS. "CONTROL STRATEGY OF A GAS TURBINE." PONTIFÍCIA UNIVERSIDADE CATÓLICA DO RIO DE JANEIRO, 2012. http://www.maxwell.vrac.puc-rio.br/Busca_etds.php?strSecao=resultado&nrSeq=21016@1.

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PONTIFÍCIA UNIVERSIDADE CATÓLICA DO RIO DE JANEIRO<br>Após um período de baixa nas bacias hidrográficas, o Brasil investiu em novas fontes de geração de energia elétrica. O gás natural é um dos exemplos destas novas fontes de energia. Dentre as usinas usuárias deste combustível, existem aquelas que operam com turbinas a gás. Muitos estudos sobre modelagem de turbinas a gás, simulação de desempenho, diagnóstico e controle começaram devido a importância dessas usinas. Assim, torna-se necessário que estas usinas trabalhem com segurança e confiabilidade. Para garantir esta estabilidade, é necessár

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Wyse, Saffron Gale. "Automated optimisation of gas turbine combustors." Thesis, University of Cambridge, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.612335.

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Olivi, Alessandro. "Survival analysis of gas turbine components." Thesis, Linköpings universitet, Statistik, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-129707.

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Survival analysis is applied on mechanical components installed in gas turbines. We use field experience data collected from repair inspection reports. These data are highly censored since the exact time-to-event is unknown. We only know that it lies before or after the repair inspection time. As event we consider irreparability level of the mechanical components. The aim is to estimate survival functions that depend on the different environmental attributes of the sites where the gas turbines operate. Then, the goal is to use this information to obtain optimal time points for preventive maint

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Allcock, D. C. J. "Abradable stator gas turbine labyrinth seals." Thesis, Cranfield University, 1999. http://dspace.lib.cranfield.ac.uk/handle/1826/10702.

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This is a detailed study into the internal aerodynamics of labyrinth seals, with pmic| reference to the effects of abradable honeycomb stators on labyrinth seal leakage.- A extensive experimental programme established tables of friction factor for three different grades of honeycomb used by industry, and examined the effect of both Reynolds number and clearance on these friction factors. The friction factor associated with a aerodynamically smooth surface was also experimentally determined in order to establish the experimental method. The experimental data was used to model the different grad

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Jasuja, A. K. "Structure of gas turbine fuel sprays." Thesis, Cranfield University, 2001. http://dspace.lib.cranfield.ac.uk/handle/1826/10729.

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Son, Changmin. "Gas turbine impingement cooling system studies." Thesis, University of Oxford, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.670200.

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Eriksson, Sara. "Development of catalysts for natural gas-fired gas turbine combustors." Doctoral thesis, Stockholm : Department of Chemical and Engineering and Technology, School of Chemical Science and Engineering, KTH - Royal Institute of Technology, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4239.

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Batt, J. J. M. "Three-dimensional unsteady gas turbine flow measurement." Thesis, University of Oxford, 1997. http://ora.ox.ac.uk/objects/uuid:3302ca8f-0618-4440-9e23-3bf99bc3705d.

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The high pressure turbine stage can be considered the most important component for the efficiency and longevity of a modern gas turbine. The flow field within this stage is highly complex and is both unsteady and three-dimensional. Understanding this flow field is essential if improvements are to be made to future engine designs. Increasingly designers are placing more emphasis on the use of Computational Fluid Dynamics (CFD) rather than experimental results. CFD methods can be more flexible and cost effective. However before these predictions can be used they must be validated against experim

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Couch, Eric L. "Measurements of Cooling Effectiveness Along the Tip of a Turbine Blade." Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/76815.

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In a gas turbine engine, turbine blades are exposed to temperatures above their melting point. Film-cooling and internal cooling techniques can prolong blade life and allow for higher engine temperatures. This study examines a novel cooling technique called a microcircuit, which combines internal convection and pressure side injection on a turbine blade tip. Holes on the tip called dirt purge holes expel dirt from the blade, so other holes are not clogged. Wind tunnel tests are used to observe how effectively dirt purge and microcircuit designs cool the tip. Tip gap size and blowing ratio are

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Scheepers, Gerard. "An experimental and numerical study of heat transfer augmentation near the entrance to a film cooling hole." Pretoria : [s.n.], 2007. http://upetd.up.ac.za/thesis/available/etd-08272008-163851/.

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48

Lin, Ye Hone. "Evaluation of vibration responses of ceramic candle filters using an accelerometer and a laser vibrometer." Morgantown, W. Va. : [West Virginia University Libraries], 2000. http://etd.wvu.edu/templates/showETD.cfm?recnum=1369.

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Main, A. D. J. "Annular turbine cascade aerodynamics." Thesis, University of Oxford, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.239350.

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Apostolidis, Asteris. "Turbine cooling and heat transfer modelling for gas turbine performance simulation." Thesis, Cranfield University, 2015. http://dspace.lib.cranfield.ac.uk/handle/1826/9234.

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The successful design of cooling systems for gas turbine engines is a key factor to feasibility of new projects, as the trend for increasing turbine entry temperatures implies requirements for more sophisticated cooling methods. This work focuses on the prediction of cooling performance of turbines, starting from local heat transfer effects at the surface of blades and vanes and expanding to performance simulation of cooled high pressure turbines and engines. In this context, this thesis establishes a new method that investigates the following topics: • The connection between the gas flow fiel

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