Дисертації з теми "Gas Turbine Engine Combustion"
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Ahmad, N. T. "Swirl stabilised gas turbine combustion." Thesis, University of Leeds, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.356423.
Повний текст джерелаPerry, Matthew Vincent. "An Investigation of Lean Premixed Hydrogen Combustion in a Gas Turbine Engine." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/43532.
Повний текст джерела
The strong lean combustion stability of hydrogen-air flames is due primarily to high reaction rates and the associated high turbulent burning velocities. While this is advantageous at low equivalence ratios, it presents a significant danger of flashbackâ the upstream propagation of the flame into the premixing deviceâ at higher equivalence ratios. An investigation has been conducted into the operation of a specific hydrogen-air premixer design in a gas turbine engine. Laboratory tests were first conducted to determine the upper stability limits of a single premixer. Tests were then carried out in which eighteen premixers and a custom-fabricated combustor liner were installed in a modified Pratt and Whitney Canada PT6A-20 turboprop engine. The tests examined the premixer and engine operability as a result of the modifications. A computer cycle analysis model was created to help analyze and predict the behavior of the modified engine and premixers. The model, which uses scaled component maps to predict off-design engine performance, was integral in the analysis of premixer flashback which limited the operation of the modified engine.
Master of Science
MacCallum, N. R. L. "Studies in gas turbine performance and in combustion." Thesis, University of Glasgow, 2000. http://theses.gla.ac.uk/5335/.
Повний текст джерелаGhulam, Mohamad. "Characterization of Swirling Flow in a Gas Turbine Fuel Injector." University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1563877023803877.
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 джерелаPeck, 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.
Повний текст джерелаIncludes bibliographical references (p. 71-72).
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 transfer model was also developed to assess the heat transfer characteristics of the catalytic micro-combustor. It has been concluded that catalytic combustion in the micro-combustor is limited by diffusion of fuel into the catalyst surface. To address this issue, a catalytic structure with larger surface area was suggested and tested. It was shown that the larger surface area catalyst increased the chemical efficiency. Design guidelines for the next generation catalytic micro-combustor are presented as well.
by Jhongwoo Peck.
S.M.
Hinse, Mathieu. "Investigation of Transpiration Cooling Film Protection for Gas Turbine Engine Combustion Liner Application." Thesis, Université d'Ottawa / University of Ottawa, 2021. http://hdl.handle.net/10393/42425.
Повний текст джерелаManners, A. P. "The calculation of the flows in gas turbine combustion systems." Thesis, Imperial College London, 1998. http://hdl.handle.net/10044/1/8397.
Повний текст джерелаVillarreal, Daniel Christopher. "Digital Fuel Control for a Lean Premixed Hydrogen-Fueled Gas Turbine Engine." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/34974.
Повний текст джерелаParallel to this study, an investigation of the existing hydrogen combustor design was performed to analyze the upper stability limits that were restricting the operability of the engine. The upstream propagation of the flame into the premixer, more commonly known as a flashback, routinely occurred at 150 shaft horsepower during engine testing. The procedures for protecting the engine from a flashback were automated within the fuel controller, significantly reducing the response time from the previous (manual) method. Additionally, protection measures were added to ensure the inter-turbine temperature of the engine did not exceed published limits. Automatic engine starting and shutdown procedures were also added to the control logic, minimizing the effort needed by the operator. The tested performance of the engine with each of the control functions demonstrated the capability of the controller.
Methods to generate an engine-specific fuel control map were also studied. The control map would not only takes into account the operability limits of the engine, but also the stability limits of the premixing devices. Such a map is integral in the complete design of the engine fuel
controller.
Master of Science
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.
Повний текст джерелаPrashanth, Prakash. "Post-combustion emissions control for aero-gas turbine engines." Thesis, Massachusetts Institute of Technology, 2018. https://hdl.handle.net/1721.1/122402.
Повний текст джерелаCataloged from PDF version of thesis.
Includes bibliographical references (pages 47-50).
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 combustion temperatures. This thesis identifies that the trend towards smaller engine cores (gas generators) that are power dense and contribute little to the thrust output presents new opportunities for emissions control that were previously unthinkable when the core exhaust stream contributed significant thrust. This thesis proposes and assesses selective catalytic reduction (SCR), which is a post-combustion emissions control method used in ground-based sources such as power generation and heavy-duty diesel engines, for use in aero-gas turbines.
The SCR system increases aircraft weight and introduces a pressure drop in the core stream. The effects of these are evaluated using representative engine cycle models provided by a major aero-gas turbine manufacturer. This thesis finds that employing an ammonia-based SCR can achieve close to 95% reduction in NO[subscript x] emissions for ~0.4% increase in block fuel burn. The large size of the catalyst needs to be housed in the body of the aircraft and hence would be suitable for future designs where the engine core is also within the fuselage, such as would be possible with turbo-electric or hybrid-electric designs. The performance of the post-combustion emissions control is shown to improve for smaller core engines in new aircraft in the NASA N+3 time-line (2030-2035), suggesting the potential to further decrease the cost of the ~95% NO[subscript x] reduction to below ~0.4% fuel burn.
Using a global chemistry and transport model (GEOS-Chem) this thesis estimates that using ultra-low sulfur (<15 ppm fuel sulfur content) in tandem with post-combustion emissions control results in a ~92% reduction in annual average population exposure to PM₂.₅ and a ~95% reduction in population exposure to ozone. This averts approximately 93% of the air pollution impact of aviation.
by Prakash Prashanth.
S.M.
S.M. Massachusetts Institute of Technology, Department of Aeronautics and Astronautics
Stitzel, Sarah M. "Flow Field Computations of Combustor-Turbine Interactions in a Gas Turbine Engine." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/30992.
Повний текст джерелаMaster of Science
Melia, Thomas. "Heat transfer characteristics of pulse combustors for gas turbine engines." Thesis, Loughborough University, 2012. https://dspace.lboro.ac.uk/2134/10278.
Повний текст джерелаMehra, 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.
Повний текст джерела"February 2000."
Includes bibliographical references (p. 203-211).
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, by silicon material and fabrication constraints, and by the inherently non-adiabatic nature of the operating space. This differs from the design of a modern macro combustion system that is typically driven by emissions, stability, durability and pattern factor requirements. The combustor developed herein is shown to operate at a power density level that is at least an order of magnitude higher than that of any other power-MEMS device (2000 MW/m 3), and establishes the viability of using high power density, silicon-based combustion systems for heat engine applications at the micro-scale. This thesis presents the development of two specific devices - the first device is a 3-wafer level microcombustor that established the viability of non-premixed hydrogen-air combustion in a volume as small as 0.066 cm 3, and within the structural constraints of silicon; the second device is known as the engine "static-structure", and integrated the 3-stack microcombustor with the other non-rotating components of the engine. Fabricated by aligned fusion bonding of 6 silicon wafers, the static structure measures 2.1 cm x 2.1 cm x 0.38 cm, and was largely fabricated by deep reactive ion etching through a total thickness of 3,800 pm. Packaged with a set of fuel plenums, pressure ports, fuel injectors, igniters, fluidic interconnects, and compressor and turbine static airfoils, this structure is the first demonstration of the complete hot flow path of a multi-level microengine. The 0.195 cm 3 combustion chamber has been tested for several tens of hours and is shown to sustain stable hydrogen combustion with exit gas temperatures above 1600K and combustor efficiencies as high as 95%. The structure also serves as the first experimental demonstration of hydrocarbon microcombustion with power density levels of 500 MW/m 3 and 140 MW/m 3 for ethylene-air and propane-air combustion, respectively. In addition to the development of the two combustion devices, this thesis also presents simple analytical models to identify and explain the primary drivers of combustion phenomena at the micro-scale. The chemical efficiency of the combustor is shown to have a strong correlation with the Damkohler number in the chamber, and asymptotes to unity for sufficiently large values of Da. The maximum power density of the combustor is also shown to be primarily limited by the structural and fabrication constraints of the material. Overall, this thesis synthesizes experimental and computational results to propose a simple design methodology for microcombustion devices, and to present design recommendations for future microcombustor development. Combined with parallel efforts to develop thin-film igniters and temperature sensors for the engine, it serves as the first experimental demonstration of the design, fabrication, packaging and operation of a silicon-based combustion system for power generation applications at the micro-scale.
by Amitav Mehra.
Ph.D.
Dsouza, Jason Brian. "Numerical Analysis of a Flameless Swirl Stabilized Cavity Combustor for Gas Turbine Engine Applications." University of Cincinnati / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1627663015527799.
Повний текст джерелаChiu, Ya-Tien. "A Performance Study of a Super-cruise Engine with Isothermal Combustion inside the Turbine." Diss., Virginia Tech, 2004. http://hdl.handle.net/10919/30202.
Повний текст джерелаPh. D.
Chiu, Ya-tien. "A Performance Study of a Super-cruise Engine with Isothermal Combustion inside the Turbine." Diss., Virginia Tech, 2004. http://hdl.handle.net/10919/30202.
Повний текст джерелаPh. D.
Farrell, Brian Henry. "An experimental and theoretical investigation into simple, low cost combustion chambers for small gas turbines." Thesis, Queen's University Belfast, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.335334.
Повний текст джерелаOVERMAN, NICHOLAS. "FLAMELESS COMBUSTION APPLICATION FOR GAS TURBINE ENGINES IN THE AEROSPACE INDUSTRY." University of Cincinnati / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1163776616.
Повний текст джерелаPlewacki, Nicholas. "Modeling High Temperature Deposition in Gas Turbines." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1587714424017527.
Повний текст джерелаBarringer, Michael David. "Design and Benchmarking of a Combustor Simulator Relevant to Gas Turbine Engines." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/35519.
Повний текст джерелаMaster of Science
Materano, Blanco Gilberto Ignacio. "Numerical modelling of pressure rise combustion for reducing emissions of future civil aircraft." Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/9259.
Повний текст джерелаBurger, Victor. "The influence of fuel properties on threshold combustion in aviation gas turbine engines." Doctoral thesis, University of Cape Town, 2017. http://hdl.handle.net/11427/25248.
Повний текст джерелаHollis, David. "Particle image velocimetry in gas turbine combustor flow fields." Thesis, Loughborough University, 2004. https://dspace.lboro.ac.uk/2134/7640.
Повний текст джерелаWang, Jianguo. "Numerical simulation of noise attenuating perforated combustor liners and the combustion instability issue in gas turbine engines." Thesis, University of Hull, 2017. http://hydra.hull.ac.uk/resources/hull:16076.
Повний текст джерелаPetrov, Miroslav. "Biomass and Natural Gas Hybrid Combined Cycles." Licentiate thesis, KTH, Energy Technology, 2003. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-1660.
Повний текст джерелаBiomass is one of the main natural resources in Sweden.Increased utilisation of biomass for energy purposes incombined heat and power (CHP) plants can help the country meetits nuclear phase-out commitment. The present low-CO2 emissioncharacteristics of the Swedish electricity production system(governed by hydropower and nuclear power) can be retained onlyby expansion of biofuels in the CHP sector. Domestic Swedishbiomass resources are vast and renewable, but not infinite.They should be utilised as efficiently as possible in order tomeet the conditions for sustainability in the future.Application of efficient power generation cycles at low cost isessential for meeting this challenge. This applies also tomunicipal solid waste (MSW) incineration with energyextraction, which is to be preferred to landfilling.
Modern gas turbines and internal combustion engines firedwith natural gas have comparatively low installation costs,good efficiency characteristics and show reliable performancein power applications. Environmental and source-of-supplyfactors place natural gas at a disadvantage as compared tobiofuels. However, from a rational perspective, the use ofnatural gas (being the least polluting fossil fuel) togetherwith biofuels contributes to a diverse and more secure resourcemix. The question then arises if both these fuels can beutilised more efficiently if they are employed at the samelocation, in one combined cycle unit.
The work presented herein concentrates on the hybriddual-fuel combined cycle concept in cold-condensing and CHPmode, with a biofuel-fired bottoming steam cycle and naturalgas fired topping gas turbine or engine. Higher electricalefficiency attributable to both fuels is sought, while keepingthe impact on environment at a low level and incorporating onlyproven technology with standard components. The study attemptsto perform a generalized and systematic evaluation of thethermodynamic advantages of various hybrid configurations withthe help of computer simulations, comparing the efficiencyresults to clearly defined reference values.
Results show that the electrical efficiency of hybridconfigurations rises with up to 3-5 %-points in cold-condensingmode (up to 3 %-points in CHP mode), compared to the sum of twosingle-fuel reference units at the relevant scales, dependingon type of arrangement and type of bottoming fuel. Electricalefficiency of utilisation of the bottoming fuel (biomass orMSW) within the overall hybrid configuration can increase withup to 8-10 %-points, if all benefits from the thermalintegration are assigned to the bottoming cycle and effects ofscale on the reference electrical efficiency are accounted for.All fully-fired (windbox) configurations show advantages of upto 4 %-points in total efficiency in CHP mode with districtheating output, when flue gas condensation is applied. Theadvantages of parallel-powered configurations in terms of totalefficiency in CHP mode are only marginal. Emissions offossil-based CO2 can be reduced with 20 to 40 kg CO2/MWhel incold-condensing mode and with 5-8 kg CO2 per MWh total outputin CHP mode at the optimum performance points.
Keywords: Biomass, Municipal Solid Waste (MSW), Natural Gas,Simulation, Hybrid, Combined Cycle, Gas Turbine, InternalCombustion Engine, Utilization, Electrical Efficiency, TotalEfficiency, CHP.
Cornwell, Michael. "Causes of Combustion Instabilities with Passive and Active Methods of Control for practical application to Gas Turbine Engines." University of Cincinnati / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1307323433.
Повний текст джерелаGodswill, Uchechukwu Megwai. "Process Simulations of Small Scale Biomass Power Plant." Thesis, Högskolan i Borås, Institutionen Ingenjörshögskolan, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:hb:diva-17969.
Повний текст джерелаProgram: Masterutbildning i energi- och materialåtervinning
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
Comer, Adam Landon. "Optimisation of liquid fuel injection in gas turbine engines." Thesis, University of Cambridge, 2013. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.607844.
Повний текст джерелаVakil, Sachin Suresh. "Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aero-Engine." Thesis, Virginia Tech, 2002. http://hdl.handle.net/10919/36324.
Повний текст джерелаThe highly competitive gas turbine industry has been motivated by consumer demands for higher power-to-weight ratios, increased thermal efficiencies, and reliability while maintaining affordability. In its continual quest, the industry must continually try to raise the turbine inlet temperature, which according to the well-known Brayton cycle is key to higher engine efficiencies. The desire for increased turbine inlet temperatures creates an extremely harsh environment for the combustor liner in addition to the components downstream of the combustor. Shear layers between the dilution jets and the mainstream, as well as combustor liner film-cooling interactions create a complex mean flow field within the combustor, which is not easy to model. A completely uniform temperature and velocity profile at the combustor exit is desirable from the standpoint of reducing the secondary flows in the turbine. However, this seldom occurs due to a lack of thorough mixing within the combustor. Poor mixing results in non-uniformities, such as hot streaks, and allow non-combusted fuel to exit the combustor.
This investigation developed a database documenting the thermal and flow characteristics within a combustor simulator representative of the flowfield within a gas turbine aero-engine. Three- and two-component laser Doppler velocimeter measurements were completed to quantify the flow and turbulence fields, while a thermocouple rake was used to quantify the thermal fields.
The measured results show very high turbulence levels due to the dilution flow injection. Directly downstream of the dilution jets, an increased thickness in the film-cooling was noted with a fairly non-homogeneous temperature field across the combustor width. A highly turbulent shear layer was found at the leading edge of the dilution jets. Measurements also showed that a relatively extensive recirculation region existed downstream of the dilution jets. Despite the lack of film-cooling injection at the trailing edge of the dilution hole, there existed coolant flow indicative of a horse-shoe vortex wrapping around the jet. As a result of the dilution jet interaction with the mainstream flow, kidney-shaped thermal fields and counter-rotating vortices developed. These vortices serve to enhance combustor mixing.
Master of Science
Rupp, Jochen. "Acoustic absorption and the unsteady flow associated with circular apertures in a gas turbine environment." Thesis, Loughborough University, 2013. https://dspace.lboro.ac.uk/2134/12984.
Повний текст джерелаWammack, James Edward. "Evolution of Turbine Blade Deposits in an Accelerated Deposition Facility: Roughness and Thermal Analysis." Diss., CLICK HERE for online access, 2005. http://contentdm.lib.byu.edu/ETD/image/etd1067.pdf.
Повний текст джерелаHermeth, Sébastian. "Mechanisms affecting the dynamic response of swirled flames in gas turbines." Thesis, Toulouse, INPT, 2012. http://www.theses.fr/2012INPT0064/document.
Повний текст джерелаModern pollutant regulation have led to a trend towards lean combustion systems which are prone to thermo-acoustic instabilities. The ability of Large Eddy Simulation (LES) to handle complex industrial heavy-duty gas turbines is evidenced during this thesis work. First, LES is applied to an academic single burner in order to validate the modeling against measurements performed at TU Berlin and against OpenFoam LES simulations done at Siemens. The coupling between acoustic and combustion is modeled with the Flame Transfer Function (FTF) approach and swirl number fluctuations are identified changing the FTF amplitude response of the flame. Then, an industrial gas turbine is analyzed for two different burner geometries and operating conditions. The FTF is only slightly influenced for the two operating points but slight modifications of the swirler geometry do modify the characteristics of the FTF showing that a simple model taking only into account the flight time is not appropriate and additional mechanisms are at play. Those mechanisms are identified being the inlet velocity, the swirl and the inlet mixture fraction fluctuations. The latter is caused by two mechanisms: 1) the pulsating injected fuel flow rate and 2) the fluctuating trajectory of the fuel jets. Although the diagonal swirler is designed to provide good mixing, effects of mixing heterogeneities at the combustion chamber inlet occur. Mixture perturbations phase with velocity (and hence with swirl) fluctuations and combine with them to lead to different FTF results. Another FTF approach linking heat release to inlet velocity and mixture fraction fluctuation (MISO model) shows further to be a good solution for complex systems. A nonlinear analysis shows that the forcing amplitude not only leads to a saturation of the flame but also to changes of the delay response. Flame saturation is only true for the global FTF and the gain increases locally with increasing forcing amplitude. Both, the linear and the nonlinear flames, are not compact: flame regions located right next to each other exhibited significant differences in delay meaning that at the same instant certain parts of the flame damp the excitation while others feed it
Jonsson, Maria. "Advanced power cycles with mixture as the working fluid." Doctoral thesis, KTH, Chemical Engineering and Technology, 2003. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3492.
Повний текст джерелаThe world demand for electrical power increasescontinuously, requiring efficient and low-cost methods forpower generation. This thesis investigates two advanced powercycles with mixtures as the working fluid: the Kalina cycle,alternatively called the ammonia-water cycle, and theevaporative gas turbine cycle. These cycles have the potentialof improved performance regarding electrical efficiency,specific power output, specific investment cost and cost ofelectricity compared with the conventional technology, sincethe mixture working fluids enable efficient energyrecovery.
This thesis shows that the ammonia-water cycle has a betterthermodynamic performance than the steam Rankine cycle as abottoming process for natural gas-fired gas and gas-dieselengines, since the majority of the ammonia-water cycleconfigurations investigated generated more power than steamcycles. The best ammonia-water cycle produced approximately40-50 % more power than a single-pressure steam cycle and 20-24% more power than a dual-pressure steam cycle. The investmentcost for an ammonia-water bottoming cycle is probably higherthan for a steam cycle; however, the specific investment costmay be lower due to the higher power output.
A comparison between combined cycles with ammonia-waterbottoming processes and evaporative gas turbine cycles showedthat the ammonia-water cycle could recover the exhaust gasenergy of a high pressure ratio gas turbine more efficientlythan a part-flow evaporative gas turbine cycle. For a mediumpressure ratio gas turbine, the situation was the opposite,except when a complex ammonia-water cycle configuration withreheat was used. An exergy analysis showed that evaporativecycles with part-flow humidification could recover energy asefficiently as, or more efficiently than, full-flow cycles. Aneconomic analysis confirmed that the specific investment costfor part-flow cycles was lower than for full-flow cycles, sincepart-flow humidification reduces the heat exchanger area andhumidification tower volume. In addition, the part-flow cycleshad lower or similar costs of electricity compared with thefull-flow cycles. Compared with combined cycles, the part-flowevaporative cycles had significantly lower total and specificinvestment costs and lower or almost equal costs ofelectricity; thus, part-flow evaporative cycles could competewith the combined cycle for mid-size power generation.
Keywords:power cycle, mixture working fluid, Kalinacycle, ammonia-water mixture, reciprocating internal combustionengine, bottoming cycle, gas turbine, evaporative gas turbine,air-water mixture, exergy
Blunt, Rory Alexander Fabian. "A Study of the Effects of Turning Angle on Particle Deposition in Gas Turbine Combustor Liner Effusion Cooling Holes." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1460735904.
Повний текст джерелаLaurent, Charlelie. "Low-order modeling and high-fidelity simulations for the prediction of combustion instabilities in liquid rocket engines and gas turbines." Thesis, Toulouse, INPT, 2020. http://www.theses.fr/2020INPT0038.
Повний текст джерелаOver the last decades, combustion instabilities have been a major concern for a number of industrial projects, especially in the design of Liquid Rocket Engines (LREs) and gas turbines. Mitigating their effects requires a solid scientific understanding of the intricate interplay between flame dynamics and acoustic waves that they involve. During this PhD work, several directions were explored to provide a better comprehension of flame dynamics in cryogenic rocket engines, as well as more efficient and robust numerical methods for the prediction of thermoacoustic instabilities in complex combustors. The first facet of this work consisted in the resolution of unstable thermoacoustic modes in complex multi-injectors combustors, a task that often requires a number of simplifications to be computationally affordable. These necessary physics-based assumptions led to the growing popularity of acoustic Low-Order Models (LOMs), among which Galerkin expansion LOMs have displayed a promising efficiency while retaining a satisfactory accuracy. Those are however limited to simple geometries that do not incorporate the complex features of industrial systems. A major part of this work therefore consisted first in clearly identifying the mathematical limitations of the classical Galerkin expansion, and then in designing a novel type of modal expansion, named a frame expansion, that does not suffer from the same restrictions. In particular, the frame expansion is able to accurately represent the acoustic velocity field, near non-rigid-wall boundaries of the combustor, a crucial ability that the Galerkin method lacks. In this work, the concept of surface modal expansion is also introduced to model topologically complex boundaries, such as multi-perforated liners encountered in gas turbines. These novel numerical methods were combined with the state-space formalism to build acoustic networks of complex systems. The resulting LOM framework was implemented in the code STORM (State-space Thermoacoustic low-ORder Model), which enables the low-order modeling of thermoacoustic instabilities in arbitrarily complex geometries. The second ingredient in the prediction of thermoacoustic instabilities is the flame dynamics modeling. This work dealt with this problem, in the specific case of a cryogenic coaxial jet-flame characteristic of a LRE. Flame dynamics driving phenomena were identified thanks to three-dimensional Large Eddy Simulations (LES) of the Mascotte experimental test rig where both reactants (CH4 and O2) are injected in transcritical conditions. A first simulation provides a detailed insight into the flame intrinsic dynamics. Several LES with harmonic modulation of the fuel inflow at various frequencies and amplitudes were performed in order to evaluate the flame response to acoustic oscillations and compute a Flame Transfer Function (FTF). The flame nonlinear response, including interactions between intrinsic and forced oscillations, were also investigated. Finally, the stabilization of this flame in the near-injector region, which is of primary importance on the overall flame dynamics, was investigated thanks to muulti-physics two-dimensional Direct Numerical Simulations (DNS), where a conjugate heat transfer problem is resolved at the injector lip
Spencer, A. "Gas turbine combustor port flows." Thesis, Loughborough University, 1998. https://dspace.lboro.ac.uk/2134/6883.
Повний текст джерелаKoutmos, P. "An isothermal study of gas turbine combustor flows." Thesis, Imperial College London, 1985. http://hdl.handle.net/10044/1/37748.
Повний текст джерелаDa, Palma Jose Manuel Laginha Mestre. "Mixing in non-reacting gas turbine combustor flows." Thesis, Imperial College London, 1989. http://hdl.handle.net/10044/1/47606.
Повний текст джерелаStuttaford, Peter J. "Preliminary gas turbine combustor design using a network approach." Thesis, Cranfield University, 1997. http://hdl.handle.net/1826/1038.
Повний текст джерелаKashinath, Karthik. "Nonlinear thermoacoustic oscillations of a ducted laminar premixed flame." Thesis, University of Cambridge, 2013. https://www.repository.cam.ac.uk/handle/1810/264291.
Повний текст джерелаBehrens, Christopher Karl. "An Experimental Investigation into NOx Control of a Gas Turbine Combustor and Augmentor Tube Incorporating a Catalytic Reduction System." Thesis, Monterey, Califonia : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA231427.
Повний текст джерелаThesis Advisor(s): Netzer, D. W. Second Reader: Shreeve, R. P. "March 1990." Description based on signature page as viewed on August 25, 2009. DTIC Descriptor(s): Air, augmentation, catalysis, catalysts, combustors, configurations, engines, fuels, gas generating systems, gas turbines, measurement, pressure, profiles, ratios, reduction, tubes, velocity. DTIC Identifier(s): Nitrogen oxides, NOx control, Gas turbines, Gas analyzers, Pollution abatement, computer programs, Emissions control, Exhaust augmentor tubes, Thesis. Author(s) subject terms: Nox control, gas turbine combustors; emissions control exhaust augmentor tubes; gas analyzers; pollution control. Includes bibliographical references (p. 73-74). Also available online.
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.
Повний текст джерелаIsmail, Ibrahim H. "Simulation of aircraft gas turbine engine." Thesis, University of Hertfordshire, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.303465.
Повний текст джерелаFarahani, Arash. "Gas turbine engine static strip seals." Thesis, University of Sussex, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.444118.
Повний текст джерелаХамза, Омар Адел Хамза. "Вибір параметрів силової установки із системою утилізації попутного нафтового газу". Thesis, НТУ "ХПІ", 2017. http://repository.kpi.kharkov.ua/handle/KhPI-Press/29868.
Повний текст джерелаThesis for the degree of candidate of technical sciences by specialty 05.05.03 - engines and power units. - National Technical University "Kharkiv Polytechnic Institute". - Kharkiv, 2017. The thesis is devoted to the choice of the scheme and parameters of the power plant for utilization of associated petroleum gas. The paper analyzes the possibility of using various power plants for utilization of associated petroleum gas. The schemes of power units using gas turbine and gas piston internal combustion engines to generate power electricity have been developed by using associated petroleum gas in oil refinery. The anergy-exergy method was used to analys the effectiveness of the proposed schemes. An economic analysis of the feasibility of constructing power generating capacities that will consume the associated oil gas with an analysis of sensitivity for such parameters as a change in the price of electricity and the impact of high ambient temperatures has been carried out. If the ambient temperature is changed from +15 to + 45 ° C, the amount of energy generated for Project A will be reduced by 26%, for Project B - by 10.9%. It is determined that despite the high cost of Project B ($ 2,843,009.55) against Project A ($ 1964,434.69), the payback period is: for Project A - 6 years, 1 month; For Project B - 3 years, 8 months. The expediency of using the piston-internal ICE as part of the power generating unit is substantiated.
Chleboun, Peter Victor. "Mathematical modelling relevant to gas turbine combustion." Thesis, University of Leeds, 1987. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.343286.
Повний текст джерелаUyanwaththa, Asela R. "CFD modelling of gas turbine combustion processes." Thesis, Loughborough University, 2018. https://dspace.lboro.ac.uk/2134/34686.
Повний текст джерелаZedda, M. "Gas turbine engine and sensor fault diagnosis." Thesis, Cranfield University, 1999. http://dspace.lib.cranfield.ac.uk/handle/1826/9117.
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