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Дисертації з теми "Turbine a Gas Aeronautiche"

Автор: Grafiati
Опубліковано: 10 березня 2023

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1

Martinez-Tamayo, Federico. "The impact of evaporatively cooled turbine blades on gas turbine performance." Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/47385.

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2

Bradshaw, Sean D. (Sean Darien) 1978. "Probabilistic aerothermal design of gas turbine combustors." Thesis, Massachusetts Institute of Technology, 2006. http://hdl.handle.net/1721.1/36286.

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Анотація:
Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2006.<br>Includes bibliographical references (p. 87-89).<br>This thesis presents a probability-based framework for assessing the impact of manufacturing variability on combustor liner durability. Simplified models are used to link combustor liner life, liner temperature variability, and the effects of manufacturing variability. A probabilistic analysis is then applied to the simplified models to estimate the combustor life distribution. The material property and liner temperature variations accounted
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3

Underwood, David Scott. "Primary zone modeling for gas turbine combustors." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/32700.

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Анотація:
Thesis (Sc.D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.<br>"June 1999."<br>Includes bibliographical references (p. 107-110).<br>Gas turbine combustor primary zone flows are typified by swirling flow with heat release in a variable area duct, where a central toroidal recirculation zone is formed. The goal of the research was to develop reduced-order models for these flows in an attempt to gain insight into, and understanding of the behavior of swirling flows with combustion. The specific research objectives were (i) to develop a quantitative understan
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4

Evans, Simon William 1977. "Thermal design of a cooled micro gas turbine." Thesis, Massachusetts Institute of Technology, 2001. http://hdl.handle.net/1721.1/8093.

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Анотація:
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2001.<br>Includes bibliographical references (p. 169-170).<br>One of the major challenges associated with designing a micro gas turbine engine is the problem of heat transfer. The demonstration version of the engine deals with this problem by transferring excess heat from the turbine, to the compressor wall, through the rotor shaft. This is necessary to keep the turbine wall within its temperature constraints. The resulting heat transfer into the compressor flow however reduces the compressor performan
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5

Koupper, Charlie. "Unsteady multi-component simulations dedicated to the impact of the combustion chamber on the turbine of aeronautical gas turbines." Phd thesis, Toulouse, INPT, 2015. http://oatao.univ-toulouse.fr/14187/1/koupper_partie_1_sur_2.pdf.

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Анотація:
De nos jours, seules les turbines à gaz sont à même de propulser les larges aéronefs (avions ou hélicoptères). Depuis les premiers prototypes construits dans les années 40, l’efficacité et la puissance de ces moteurs n’ont cessé de s’améliorer. Chaque composant atteint de tels niveaux de performance que seules une rupture technologique ou un investissement conséquent peuvent permettre de repousser les limites d’efficacité d’une turbine à gaz. Une solution alternative peut être trouvée en constatant qu’un moteur est un système intégré complexe dans lequel tous les composants interagissent entre
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6

Zhang, K. "Turbulent combustion simulation in realistic gas-turbine combustors." Thesis, City, University of London, 2017. http://openaccess.city.ac.uk/17689/.

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The work presented in this thesis addresses issues involving the accurate and efficient numerical modelling of turbulence combustion with an emphasis on an industrially representative Tay model combustor. This combustor retained all essential features of a modern aero-engine rich burn combustor and thus the turbulence combustion within this combustor is much more complicated than those observed in the combustor-like burners typically considered in laboratory experiments. A comparative study of two combustion models based on a non-premixed assumption or a partially premixed assumption using the
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7

Groshenry, Christophe. "Preliminary design study of a micro-gas turbine engine." Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/10386.

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8

Liu, Chunmeni 1970. "Dynamical system modeling of a micro gas turbine engine." Thesis, Massachusetts Institute of Technology, 2000. http://hdl.handle.net/1721.1/9249.

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Анотація:
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2000.<br>Also available online at the MIT Theses Online homepage <http://thesis.mit.edu>.<br>Includes bibliographical references (p. 123).<br>Since 1995, MIT has been developing the technology for a micro gas turbine engine capable of producing tens of watts of power in a package less than one cubic centimeter in volume. The demo engine developed for this research has low and diabtic component performance and severe heat transfer from the turbine side to the compressor side. The goals of this thesis ar
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9

Kleiven, Thomas J. (Thomas John). "Effect of gas path heat transfer on turbine loss." Thesis, Massachusetts Institute of Technology, 2017. http://hdl.handle.net/1721.1/112466.

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Анотація:
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 117-118).<br>This thesis presents an assessment of the impact of gas path, i.e., streamtube-to-streamtube, heat transfer on aero engine turbine loss and efficiency. The assessment, based on the concept of mechanical work potential [19], was carried out for two model problems to introduce the ideas. Three-dimensional RANS calculations were also conducted to show the application to realistic configurations. T
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10

Savoulides, Nicholas 1978. "Development of a MEMS turbocharger and gas turbine engine." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/17815.

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Анотація:
Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004.<br>Includes bibliographical references.<br>As portable electronic devices proliferate (laptops, GPS, radios etc.), the demand for compact energy sources to power them increases. Primary (non-rechargeable) batteries now provide energy densities upwards of 180 W-hr/kg, secondary (rechargeable) batteries offer about 1/2 that level. Hydrocarbon fuels have a chemical energy density of 13,000-14,000 W-hr/kg. A power source using hydrocarbon fuels with an electric power conversion efficiency of order
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11

Prashanth, Prakash. "Post-combustion emissions control for aero-gas turbine engines." Thesis, Massachusetts Institute of Technology, 2018. https://hdl.handle.net/1721.1/122402.

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Анотація:
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 47-50).<br>Aviation NO[subscript x] emissions have an impact on air quality and climate change, where the latter is magnified due to the higher sensitivity of the upper troposphere and lower stratosphere. In the aviation industry, efforts to increase the efficiency of propulsion systems are giving rise to higher overall pressure ratios which results in higher NO[subscript x] emissions due to increased combus
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12

Allaire, Douglas L. "A physics-based emissions model for aircraft gas turbine combustors." Thesis, Massachusetts Institute of Technology, 2006. http://hdl.handle.net/1721.1/35584.

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Анотація:
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2006.<br>Includes bibliographical references (p. 103-105).<br>In this thesis, a physics-based model of an aircraft gas turbine combustor is developed for predicting NO. and CO emissions. The objective of the model is to predict the emissions of current and potential future gas turbine engines within quantified uncertainty bounds for the purpose of assessing design tradeoffs and interdependencies in a policy-making setting. The approach taken is to capture the physical relationships among operating cond
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13

Jackson, Keith S. (Keith Stuart). "CAD-casting of gas turbine airfoils using three dimensional printing." Thesis, Massachusetts Institute of Technology, 1997. http://hdl.handle.net/1721.1/10518.

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14

Kluka, James Anthony. "The design of low-leakage modular regenerators for gas-turbine engines." Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/46564.

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Анотація:
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1995.<br>Includes bibliographical references (p. [229]-231).<br>The design of a modular regenerator concept (patented by Wilson and MIT) for gas-turbine engines is investigated. Mechanical design analysis and theoretical performance calculations were made to show the concept's functionality and performance benefits over current regenerator designs. The modular regenerator concept consists of a ceramic-honeycomb matrix discretized into rectangular blocks, called modules. The modules are exposed to hot (
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15

Berg, Rachel A. (Rachel Antonette). "Experimental and analytical assessment of cavity modes in a gas turbine wheelspace." Thesis, Massachusetts Institute of Technology, 2016. http://hdl.handle.net/1721.1/103445.

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Анотація:
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2016.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 103-106).<br>High response pressure data from a high-speed 1.5-stage turbine Hot Gas Ingestion Rig shows the existence of cavity modes in the rim-seal-wheelspace cavity for representative turbine engine operating conditions with purge flow. The experimental results and observations are complemented by computational assessments of cavity modes associated with flow in canonical cavity configurations. The cavi
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16

Bae, Jinwoo W. "An experimental study of surge control in a helicopter gas turbine engine." Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/50319.

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17

Dupuy, Fabien. "Reduced Order Models and Large Eddy Simulation for Combustion Instabilities in aeronautical Gas Turbines." Thesis, Toulouse, INPT, 2020. http://www.theses.fr/2020INPT0046.

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Des réglementations de plus en plus strictes et un intérêt environnemental grandissant ont poussé les constructeurs de moteurs aéronautiques à développer la génération actuelle de chambres de combustion, affichant des consommations et émissions de polluants plus basses que jamais. Cependant, les phases de conception de chambres modernes ont clairement mis en évidence que celles-ci sont plus susceptibles de développer des instabilités de combustion, où le couplage entre l'acoustique de la chambre et la flamme suscite de larges oscillations de pression ainsi que des vibrations de la structure. C
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18

McNulty, Gregory Scott. "A study of dynamic compressor surge control strategies for a gas turbine engine." Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/47350.

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19

McCabe, Niall 1971. "A system study on the use of aspirated technology in gas turbine engines." Thesis, Massachusetts Institute of Technology, 2001. http://hdl.handle.net/1721.1/8720.

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Анотація:
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2001.<br>Includes bibliographical references (p. 99).<br>Increasing aircraft engine efficiency and reducing the engines weight have driven innovation in the aircraft engine business since its inception. By simply looking at the Brayton cycle increasing the compressor pressure ratio can bring about an increase in efficiency. To achieve this high pressure ratio, multi-stage axial compressors are used, which tend to be both heavy and expansive. Increasing the number of stages in an axial compressor can in
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20

Goh, Shaun Shiao Sing 1980. "Sustainment of commercial aircraft gas turbine engines : an organizational and cognitive engineering approach." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/82760.

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21

Napert, Gary Arthur 1956. "Fatigue performance of electroless nickel coatings on stainless steel gas turbine compressor rotors." Thesis, Massachusetts Institute of Technology, 1989. http://hdl.handle.net/1721.1/41318.

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22

Monroe, Mark A. (Mark Alan). "A market and engineering study of a 3-kilowatt class gas turbine generator." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/42200.

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Анотація:
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2003.<br>Includes bibliographical references (p. 147-149).<br>Market and engineering studies were performed for the world's only commercially available 3 kW class gas turbine generator, the IHI Aerospace Dynajet. The objectives of the market study were to determine the competitive requirements for small generators in various U.S. applications, assess the unit's current suitability for these applications, and recommend ways to modify performance or marketing practices to make it more competitive. Engine
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23

Martini, Bastien. "Development and assessment of a soot emissions model for aircraft gas turbine engines." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/45256.

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Анотація:
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2008.<br>Includes bibliographical references.<br>Assessing candidate policies designed to address the impact of aviation on the environment requires a simplified method to estimate pollutant emissions for current and future aircraft gas turbine engines under different design and operating assumptions. A method for NOx and CO emissions was developed in a previous research effort. This thesis focuses on the addition of a soot mechanism to the existing model. The goal is to estimate soot emissions of exis
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24

Peck, Jhongwoo 1976. "Development of a catalytic combustion system for the MIT Micro Gas Turbine Engine." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/28292.

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Анотація:
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2003.<br>Includes bibliographical references (p. 71-72).<br>As part of the MIT micro-gas turbine engine project, the development of a hydrocarbon-fueled catalytic micro-combustion system is presented. A conventionally-machined catalytic flow reactor was built to simulate the micro-combustor and to better understand the catalytic combustion at micro-scale. In the conventionally-machined catalytic flow reactor, catalytic propane/air combustion was achieved over platinum. A 3-D finite element heat transfe
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25

Lackner, Matthew 1980. "Vibration and crack detection in gas turbine engine compressor blades using Eddy current sensors." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/28895.

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Анотація:
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, September 2004.<br>Includes bibliographical references (p. 97).<br>(cont.) in the ECS signal, no definitive method for sensing blade vibration using an ECS has yet been developed.<br>High cycle fatigue (HCF) cracks generated by compressor blade vibrations are a common source of failure in gas turbine engines. Current methods for crack detection are costly, time consuming, and prone to errors. In-situ blade vibration detection would help operators avoid critical engine speeds, and help infer the presenc
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26

Borror, Sean Leander. "Natural and forced response measurement of hydrodynamic stability in an aircraft gas turbine engine." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/47364.

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27

Mehra, Amitav. "Development of a high power density combustion system for a silicon micro gas turbine engine." Thesis, Massachusetts Institute of Technology, 2000. http://hdl.handle.net/1721.1/9269.

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Анотація:
Thesis (Ph.D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2000.<br>"February 2000."<br>Includes bibliographical references (p. 203-211).<br>As part of an effort to develop a microfabricated gas turbine engine capable of providing 10-50 Watts of electrical power in a package less than one cubic centimeter in volume, this thesis presents the design, fabrication, packaging and testing of the first combustion system for a silicon micro heat engine. The design and operation of a microcombustor is fundamentally limited by the chemical reaction times of the fuel, b
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28

Rock, Peter Joseph Jr. "Computational assessment of turbine rim seal system parametric variation on hot gas ingestion and flow pattern." Thesis, Massachusetts Institute of Technology, 2018. http://hdl.handle.net/1721.1/119310.

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Анотація:
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 125-127).<br>A design of experiments (DOE) is carried out to assess the turbine rim cavity system parametric variation on hot gas ingestion, flow pattern, and turbine stage efficiency. The parameters focused on are purge to main mass flow rate ratio, axial gap to rim radius ratio, radial gap to rim radius ratio, normalized axial position of the blade leading edge, and internal purge cavity radius ratios. Th
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29

Kocer, Gulru. "Aerothermodynamic Modeling And Simulation Of Gas Turbines For Transient Operating Conditions." Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/12609642/index.pdf.

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Анотація:
In this thesis, development of a generic transient aero-thermal gas turbine model is presented. A simulation code, gtSIM is developed based on an algorithm which is composed of a set of differential equations and a set of non-linear algebraic equations representing each gas turbine engine component. These equations are the governing equations which represents the aero-thermodynamic process of the each engine component and they are solved according to a specific solving sequence which is defined in the simulation code algorithm. At each time step, ordinary differential equations are integrated
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30

Everitt, Stewart. "Developments in advanced high temperature disc and blade materials for aero-engine gas turbine applications." Thesis, University of Southampton, 2012. https://eprints.soton.ac.uk/348897/.

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Анотація:
The research carried out as part of this EngD is aimed at understanding the high temperature materials used in modern gas turbine applications and providing QinetiQ with the information required to assess component performance in new propulsion systems. Performance gains are achieved through increased turbine gas temperatures which lead to hotter turbine disc rims and blades. The work has focussed on two key areas: (1) Disc Alloy Assessment of High Temperature Properties; and (2) Thermal Barrier Coating Life Assessment; which are drawn together by the overarching theme of the EngD: Lifing of C
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31

Stanley, Felix. "Dimensional reduction and design optimization of gas turbine engine casings for tip clearance studies." Thesis, University of Southampton, 2010. https://eprints.soton.ac.uk/342789/.

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The objective of this research is to develop a design process that can optimize an engine casing assembly to reduce tip clearance losses. Performing design optimization on the casings that form a gas turbine engine's external structure is a very tedious and cumbersome process. The design process involves the conceptual, the preliminary and the detailed design stages. The redesign costs involved are high when changes are made to the design of a part in the detailed design stage. Normally a 2D configuration is envisaged by the design team in the conceptual design stage. Engine thrust, mass flow,
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32

Novikov, Yaroslav. "Development Of A High-fidelity Transient Aerothermal Model For A Helicopter Turboshaft Engine For Inlet Distortion And Engine Deterioration Simulations." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12614389/index.pdf.

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Presented in this thesis is the development of a high-fidelity aerothermal model for GE T700 turboshaft engine. The model was constructed using thermodynamic relations governing change of flow properties across engine components, and by applying real component maps for the compressor and turbines as well as empirical relations for specific heats. Included in the model were bleed flows, turbine cooling and heat sink effects. Transient dynamics were modeled using inter-component volumes method in which mass imbalance between two engine components was used to calculate the inter-component pressur
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33

Giles, M. (Michael). "Newton solution of steady two-dimensional transonic flow." Thesis, Massachusetts Institute of Technology, 1985. http://hdl.handle.net/1721.1/15250.

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Анотація:
Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1985.<br>MICROFICHE COPY AVAILABLE IN ARCHIVES AND AERONAUTICS.<br>Bibliography: leaves 167-169.<br>by Michael Bryce Giles.<br>Ph.D.
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34

Tanaka, Shinji S. M. Massachusetts Institute of Technology. "Acoustic and thermal packaging of small gas turbines for portable power." Thesis, Massachusetts Institute of Technology, 2009. http://hdl.handle.net/1721.1/51648.

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Анотація:
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2009.<br>Includes bibliographical references (p. 201-203).<br>To meet the increasing demand for advanced portable power units, for example for use in personal electronics and robotics, a number of studies have focused on portable small gas turbines. This research is concerned with gas turbine generator units in the 1 kW range. The compact and small-scale architecture of the portable gas turbine engine poses major challenges in the acoustic treatment that is required to attenuate the broadband and tonal
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35

Leung, Kai Yuen Eric. "3D turbine tip clearance flow redistribution due to gap variation." Thesis, Massachusetts Institute of Technology, 1991. http://hdl.handle.net/1721.1/42513.

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36

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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Анотація:
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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37

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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Анотація:
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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38

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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39

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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Анотація:
<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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40

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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41

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

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Анотація:
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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42

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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43

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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44

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

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45

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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46

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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47

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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48

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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49

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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50

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

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Анотація:
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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