Дисертації з теми "Combustore"
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Romanelli, Mirko. "Modellazione del comportamento di un combustore e turbina aeronautica con fogging." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2016. http://amslaurea.unibo.it/12374/.
Повний текст джерелаGobbato, Paolo. "Studio delle instabilità termoacustiche in un combustore di turbina a gas." Doctoral thesis, Università degli studi di Padova, 2010. http://hdl.handle.net/11577/3427348.
Повний текст джерелаL'instabilità di combustione peggiora le prestazioni di un combustore a flusso continuo e pertanto deve essere considerata un fenomeno indesiderato. Fluttuazioni della pressione e del rilascio termico possono infatti causare vibrazioni meccaniche, rumore, formazione di punti caldi sulle pareti della camera di combustione e incremento delle emissioni inquinanti. La combustione instabile è particolarmente dannosa nei combustori per turbina a gas nei quali ampie oscillazioni di portata e di rilascio termico possono danneggiare irreparabilmente le parti fisse e rotanti della turbina. Nel lavoro che si presenta viene studiato il comportamento termoacustico di un combustore di turbina a gas. Il combustore esaminato è del tipo tubolare, con singolo bruciatore a fiamma diffusiva ed è stato modificato dal costruttore per essere alimentato non solo a gas naturale ma anche a idrogeno. Il processo di sviluppo è stato supportato da prove di combustione su scala reale eseguite su un banco prova in grado di riprodurre le condizioni di pieno carico. L’analisi termoacustica viene condotta seguendo una procedura di indagine basata sulla simulazione numerica del fenomeno mediante un codice numerico commerciale con modelli di turbolenza di tipo RANS. Nelle analisi numeriche i modelli numerici e le griglie di calcolo sono scelti in modo da minimizzare tempi e risorse di calcolo. In questo modo è possibile simulare un intervallo temporale sufficientemente ampio da consentire al sistema di evolvere liberamente fino alle condizioni di regime per poter così valutare l’eventuale presenza di instabilità termoacustiche. Le misure raccolte durante le prove sperimentali sono impiegate nei calcoli sia per l’imposizione delle condizioni al contorno sia per la valutazione dei risultati. I segnali di pressione registrati durante le simulazioni mostrano la permanenza di oscillazioni di pressione nel combustore caratterizzate da un’ampiezza piuttosto ridotta. Queste oscillazioni sono dunque ampiamente tollerabili dal sistema (la combustione è ovunque completa e non vi sono fenomeni di estinzione di fiamma e di surriscaldamento delle pareti del combustore), in accordo con quanto osservato durante le prove sperimentali. Gli spettri calcolati al termine delle simulazioni sono comparati con gli spettri acquisiti durante le prove di combustione. Dal confronto emerge una sostanziale corrispondenza tra i modi di vibrare calcolati e quelli misurati al banco prova.
Khandelwal, Bhupendra. "Development of gas turbine combustor preliminary design methodologies and preliminary assessments of advanced low emission combustor concepts." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/9157.
Повний текст джерелаAslanidou, 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.
Повний текст джерелаAbraham, Santosh. "Heat Transfer and Flow Measurements on a One-Scale Gas Turbine Can Combustor Model." Thesis, Virginia Tech, 2008. http://hdl.handle.net/10919/35177.
Повний текст джерелаMaster of Science
Carmack, Andrew Cardin. "Heat Transfer and Flow Measurements in Gas Turbine Engine Can and Annular Combustors." Thesis, Virginia Tech, 2012. http://hdl.handle.net/10919/32466.
Повний текст джерелаMaster of Science
Jelercic, David. "Experiments in annular combustors." Thesis, Imperial College London, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.251891.
Повний текст джерелаAnand, Vijay G. "Rotating Detonation Combustor Mechanics." University of Cincinnati / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1530798871271548.
Повний текст джерелаAyache, Simon Victor. "Simulations of turbulent swirl combustors." Thesis, University of Cambridge, 2012. https://www.repository.cam.ac.uk/handle/1810/243609.
Повний текст джерелаGray, D. T. "The control of fluidised combustors." Thesis, University of Cambridge, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.373677.
Повний текст джерелаForster, Robin Norman George. "CFD modelling of vortex combustors." Thesis, University of Surrey, 1999. http://epubs.surrey.ac.uk/770204/.
Повний текст джерелаUbhi, G. S. "Emissivity measurement of gas turbine combustor ceramic coatings and its influence on combustor design." Thesis, Cranfield University, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.378890.
Повний текст джерелаSpencer, A. "Gas turbine combustor port flows." Thesis, Loughborough University, 1998. https://dspace.lboro.ac.uk/2134/6883.
Повний текст джерелаMotsamai, Oboetswe Seraga. "Optimisation techniques for combustor design." Pretoria : [s.n.], 2009. http://upetd.up.ac.za/thesis/available/etd-04072009-222336/.
Повний текст джерелаAsere, Abraham Awolola. "Gas turbine combustor wall cooling." Thesis, University of Leeds, 1986. http://etheses.whiterose.ac.uk/2590/.
Повний текст джерелаGogebakan, Yusuf. "Simulation Of Circulating Fluidized Bed Combustors." Phd thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/2/12607775/index.pdf.
Повний текст джерелаwhereas outputs include transient values of combustor temperatures, gas concentrations, char and inert hold-ups and their size distributions. The solution procedure employs method of lines approach for the governing non-linear partial differential equations and combined bisection and secant rule for non-linear algebraic equations. The initial conditions required for the model are provided from the simultaneous solution of governing equations of dynamic model with all temporal derivatives set to zero. By setting all temporal derivatives to zero, model can also be utilized for steady state performance prediction. In order to assess the validity and predictive accuracy of the model, it was applied to the prediction of the steady state behavior of Technical University of Nova Scotia 0.3 MWt CFBC Test Rig and predictions were compared with measurements taken on the same rig. Comparison of model predictions at steady state conditions revealed that the predictions of the model are physically correct and agree well with the measurements and the model is successful in qualitatively and quantitatively simulating the processes taking place in a circulating fluidized bed combustor.
Cavaliere, Davide Egidio. "Blow-off in gas turbine combustors." Thesis, University of Cambridge, 2014. https://www.repository.cam.ac.uk/handle/1810/265575.
Повний текст джерелаWyse, Saffron Gale. "Automated optimisation of gas turbine combustors." Thesis, University of Cambridge, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.612335.
Повний текст джерелаMatteucci, Simona. "Numerical Modelling of a Flameless Combustor." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.
Знайти повний текст джерелаBengtsson, 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.
Повний текст джерелаMurthy, J. N. "Gas turbine combustor modelling for design." Thesis, Cranfield University, 1988. http://hdl.handle.net/1826/2626.
Повний текст джерелаSoon, Lee Aik. "Two Combustor Engine for Military Applications." Thesis, Cranfield University, 2009. http://hdl.handle.net/1826/4491.
Повний текст джерелаHao, Beilene 1973. "Effect of variability on combustor performance." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/82779.
Повний текст джерелаGoodro, Robert Matthew. "Improved understanding of combustor liner cooling." Thesis, University of Oxford, 2009. http://ora.ox.ac.uk/objects/uuid:51596540-f4cf-480c-aa40-7fc5b9a97abb.
Повний текст джерелаHall, Benjamin F. "Combustor simulators for scaled turbine experiments." Thesis, University of Oxford, 2015. https://ora.ox.ac.uk/objects/uuid:9c8e46e6-218f-4715-b2bd-8c8abbee446a.
Повний текст джерелаOrain, Mikaël. "Experiments with gas and liquid-fuelled flames." Thesis, Imperial College London, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.252000.
Повний текст джерелаFabbri, Federico. "Controllo multiparametro della combustione." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2013. http://amslaurea.unibo.it/5121/.
Повний текст джерелаReuter, Dierk Martin. "Investigation of combustion instability in ramjet combustors." Diss., Georgia Institute of Technology, 1988. http://hdl.handle.net/1853/12271.
Повний текст джерелаAu-Yeung, Hok Wang. "NOx formation in gas-fired pulse combustors." Thesis, Loughborough University, 1998. https://dspace.lboro.ac.uk/2134/10384.
Повний текст джерелаBradshaw, 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.
Повний текст джерелаIncludes bibliographical references (p. 87-89).
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 for approximately 80 percent and 20 percent, respectively, of the combustor life variability. Furthermore, the typical combustor life was found to be approximately 20 percent less than the life estimated using deterministic methods for these combustors, and the probability that a randomly selected combustor will fail earlier than predicted using deterministic methods is approximately 80 percent. Finally, the application of a sensitivity analysis to a surrogate model for the life identified the leading drivers of the minimum combustor life and the typical combustor life as the material property variability and the variability of the near-wall combustor gas temperature, respectively.
by Sean Darien Bradshaw.
Ph.D.
Underwood, David Scott. "Primary zone modeling for gas turbine combustors." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/32700.
Повний текст джерела"June 1999."
Includes bibliographical references (p. 107-110).
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 understanding and ability to compute the behavior of swirling flows with heat addition at conditions typical of gas turbine combustors, (ii) to assess the relative merits of various reduced-order models, and (iii) to define the applicability of these models in the design process. To this end, several reduced-order models of combustor primary zones were developed and assessed. The models represent different levels of modeling approximations and complexity. The models include a quasi-one-dimensional control volume analysis, a streamline curvature model, a quasi-one- dimensional model with recirculation zone capturing (CFLOW), and an axisymmetric Reynolds averaged Navier-Stokes code (UTNS). The models were evaluated through inter-comparison, and comparison with experiment. Following this evaluation, CFLOW was applied to a lean-premixed combustor for which three-dimensional Navier-Stokes solutions existed. These simplified analyses/models were able to capture the features of swirling flows with heat release across flow regimes of interest in gas turbine combustors, provide insight into the underlying physics, and yield guidelines for design purposes. Cross-comparison of the reduced-order models highlighted the aspects of these flows that need to be described accurately. Specifically, modeling of the mixing on the downstream boundary of a recirculation zone is crucial for accurate computation of these flows, with both Reynolds stresses and bulk transport across the interface being accounted for in order to capture recirculation zone closure. The simplified mixing and heat release models used had limitations arising from the need to input empirically-derived parameters. Calibration of these parameters with higher-fidelity computations and experiments allowed comparison of the models across the flow regimes of interest. Following calibration of the mixing and heat release models, CFLOW was able to compute recirculation zone volumes to within 25% of those given by both the axisymmetric and three-dimensional Navier-Stokes codes for swirl ratios between 0.5 and 1.0 and equivalence ratios between 0.0 and 0.8.
by David Scott Underwood.
Sc.D.
Redemann, Kai. "Ash management in circulating fluidized bed combustors." Aachen Shaker, 2008. http://d-nb.info/991096231/04.
Повний текст джерелаRowan, Scott A. "Viscous drag reduction in a scramjet combustor /." St. Lucia, Qld, 2003. http://www.library.uq.edu.au/pdfserve.php?image=thesisabs/absthe17438.pdf.
Повний текст джерелаDavid, Jiri. "Emissions from a gas-burning pulse combustor." Thesis, Middlesex University, 1993. http://eprints.mdx.ac.uk/10176/.
Повний текст джерелаStowe, Robert Alan. "Performance prediction of a ducted rocket combustor." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2001. http://www.collectionscanada.ca/obj/s4/f2/dsk3/ftp04/NQ65434.pdf.
Повний текст джерелаTajiri, Kazuya. "Simulations of combustion dynamics in pulse combustor." Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12175.
Повний текст джерелаPoppe, Christian. "Scalar measurements in a gas turbine combustor." Thesis, Imperial College London, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.264987.
Повний текст джерелаMenzies, Kevin Robert. "Grid adaptation for gas trubine combustor calculations." Thesis, Imperial College London, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.504933.
Повний текст джерелаBradshaw, Sean D. (Sean Darien) 1978. "Physics-based, reduced-order combustor flow modeling." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/82215.
Повний текст джерелаPeck, Jhongwoo 1976. "Development of a liquid-fueled micro-combustor." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/45271.
Повний текст джерелаIncludes bibliographical references (p. 177-184).
Advances in Micro-Electro-Mechanical Systems (MEMS) have made possible the development of shirtbutton-sized gas turbine engines for use as portable power sources. As part of an effort to develop a microscale gas turbine engine, this thesis presents the modeling, design, fabrication, and experimental characterization of a microcombustor that catalytically burns JP8 fuel. Due to high energy densities stored in hydrocarbon fuels, microscale heat engines based on them are estimated to have specific energies about one order of magnitude higher than those of current battery systems. In addition, utilizing a commonly available logistics fuel would provide advantages for military applications. Thus, a microengine burning JP8 fuel is attractive as a portable power source and potential replacement for batteries. The thesis first presents a number of models developed to design the fuel vaporizer, the fuel-air mixing chamber, and the combustion chamber. Among these is a reduced-order mass transfer model that simulates catalytic combustion of a slow diffusing hydrocarbon fuel. A two-phase heat transfer model was also developed to design an on-board fuel vaporizer with an array of micro-channels. Using the model results, a liquid-fueled micro-combustor test rig with a combustion chamber volume of 1.hcc and an overall die size of 36.4 mm x 36.4 mm x 6.5 mm was built. This device is a hybrid structure composed of silicon, sapphire, and glass. Deep reactive ion etching was mainly used to fabricate the silicon parts. The sapphire and glass parts were built by ultrasonic machining. The liquid-fueled micro-combustor was then experimentally characterized. Two configurations were tested and compared; one with the whole combustion chamber filled with a catalyst, and the other with a catalyst filling the chamber only partially.
(cont.) In the fully-loaded configuration, JP8 combustion was stably sustained at mass flow rates up to 0.1 g/sec, and an exit gas temperature of 780 K, an overall combustor efficiency of 19%, and a power density of 43 MW/m" were achieved. The primary limitation on increasing the mass flow rates and temperatures further was structural failure of the device due to thermal stresses. With the partially-loaded configuration, a mass flow rate of 0.2 g/sec, and a corresponding power density of 54 MW/mrn were obtained. The exit gas temperature for the partially-loaded configuration was as high as 720 K, and the maximum overall efficiency was over 22%. Although the reduced amount of catalyst led to incomplete combustion, smaller thermal losses resulted in an increase in the overall combustor efficiencies and power densities. The overall efficiency and the exit gas temperature were lower than the operational requirement of the microengine in both of the device configurations. A non-dimensional operating map was constructed based on the experiment, and suggestions for future liquid fueled micro-combustors were made; to achieve maximum efficiency for a volume as small as possible, improving the thermal efficiency would be necessary. Thesis keywords: Power-MEMS, microengine, micro-combustor, catalytic combustion, JP8 combustor, micro fuel vaporizer, micro-fabrication, deep reactive ion etching
by Jhongwoo Jay Peck.
Ph.D.
Moscahlaidis, George. "Investigation of air control on chunkwood combustor." Thesis, Virginia Tech, 1989. http://hdl.handle.net/10919/43101.
Повний текст джерелаMaster of Science
Mescher, Ann M. "Flame structures in a pulverized coal combustor /." The Ohio State University, 1995. http://rave.ohiolink.edu/etdc/view?acc_num=osu1487862399449444.
Повний текст джерелаSt, George Andrew. "Development and Testing of Pulsed and Rotating Detonation Combustors." University of Cincinnati / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1458893231.
Повний текст джерелаZanotti, Giacomo. "L'impiego del sensore di pressione in camera di combustione per il controllo della combustione." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2017.
Знайти повний текст джерелаMorgan, D. J. "Characteristics of non slagging cyclone combustors for solid fuels." Thesis, Cardiff University, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.292580.
Повний текст джерелаAhmed, Mahbub. "Investigation on the flame dynamics of meso-combustors." To access this resource online via ProQuest Dissertations and Theses @ UTEP, 2008. http://0-proquest.umi.com.lib.utep.edu/login?COPT=REJTPTU0YmImSU5UPTAmVkVSPTI=&clientId=2515.
Повний текст джерелаArunajatesan, Srinivasan. "Numerical modeling of waste incineration in dump combustors." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12332.
Повний текст джерелаKandamby, Naminda Harisinghe. "Mathematical modelling of gasifier fuelled gas turbine combustors." Thesis, Imperial College London, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.267305.
Повний текст джерелаDolan, Brian. "Flame Interactions and Thermoacoustics in Multiple-Nozzle Combustors." University of Cincinnati / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1479822588098224.
Повний текст джерелаWischnewski, Reiner. "Simulation of large-scale circulating fluidized bed combustors." Aachen Shaker, 2008. http://d-nb.info/993341691/04.
Повний текст джерела