Дисертації з теми "Gas turbine combustion chambers"
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Kister, Guillaume. "Ceramic-matrix composites for gas turbine applications." Thesis, University of Bath, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.299850.
Повний текст джерелаCavaliere, Davide Egidio. "Blow-off in gas turbine combustors." Thesis, University of Cambridge, 2014. https://www.repository.cam.ac.uk/handle/1810/265575.
Повний текст джерелаBainbridge, William David Quillen. "The numerical similation of oscillations in gas turbine combustion chambers." Thesis, University of Cambridge, 2014. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.648428.
Повний текст джерелаFortunato, Valentina. "Development and testing of combustion chambers for residential micro gas turbine applications." Doctoral thesis, Universite Libre de Bruxelles, 2017. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/256708.
Повний текст джерелаDoctorat en Sciences de l'ingénieur et technologie
info:eu-repo/semantics/nonPublished
Ku, Shiuh-Huei. "An investigation of the gas fired pulsating combustor." Diss., Georgia Institute of Technology, 1988. http://hdl.handle.net/1853/13062.
Повний текст джерелаFarrell, 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 джерелаNeumeier, Yedidia. "Frequency domain analysis of a gas fired mechanically valved pulse combustor." Diss., Georgia Institute of Technology, 1993. http://hdl.handle.net/1853/13354.
Повний текст джерелаRobinson, Alexander. "Development and testing of hydrogen fuelled combustion chambers for the possible use in an ultra micro gas turbine." Doctoral thesis, Universite Libre de Bruxelles, 2012. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/209706.
Повний текст джерелаThis PhD thesis presents the scientific evaluation and development history of different combustion chamber designs based upon the “PowerMEMS” design parameters. With hydrogen as chosen fuel, the non-premixed diffusive “micromix” concept was selected as combustion principle. Originally designed for full scale gas turbine applications in two different variants, consequently the microcombustor development had to start with the downscaling of these two principles towards ì-scale. Both principles have the advantage to be inherently safe against flashback, due to the non-premixed concept, which is an important issue even in this small scale application when burning hydrogen. By means of water analogy and CFD simulations the hydrogen injection system and the chamber geometry could be validated and optimized. Besides the specific design topics that emerged during the downscaling process of the chosen combustion concepts, the general difficulties of microcombustor design like e.g. high power density, low Reynolds numbers, short residence time, and manufacturing restrictions had to be tackled as well.
As full scale experimental test campaigns are still mandatory in the field of combustion research, extensive experimental testing of the different prototypes was performed. All test campaigns were conducted with a newly designed test rig in a combustion lab modified for microcombustion investigations, allowing testing of miniaturized combustors according to full engine requirements with regard to mass flow, inlet temperature, and chamber pressure. The main results regarding efficiency, equivalence ratio, and combustion temperature were obtained by evaluating the measured exhaust gas composition. Together with the performed ignition and extinction trials, the evaluation and analysis of the obtained test results leads to a full characterization of each tested prototype and delivered vital information about the possible operating regime in a later UMGT application. In addition to the stability and efficiency characteristics, another critical parameter in combustor research, the NOx emissions, was investigated and analyzed for the different combustor prototypes.
As an advancement of the initial downscaled micromix prototypes, the following microcombustor prototype was not only a combustion demonstrator any more, but already aimed for easy module integration into the real UMGT. With a further optimized combustion efficiency, it also featured an innovative recuperative cooling of the chamber walls and thus allowing an cost effective all stainless steel design.
Finally, a statement about the pros and cons of the different micromix combustion concepts and their correspondent combustor designs towards a possible ì-scale application could be given.
Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished
Mohanraj, Rajendran. "Modeling of combustion instabilities and their active control in a gas fueled combustor." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12089.
Повний текст джерелаLieuwen, Tim C. "Investigation of combustion instability mechanisms in premixed gas turbines." Diss., Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/20300.
Повний текст джерелаHummel, Tobias [Verfasser]. "Modeling and Analysis of High-Frequency Thermoacoustic Oscillations in Gas Turbine Combustion Chambers / Tobias Hummel." München : Verlag Dr. Hut, 2019. http://d-nb.info/118151424X/34.
Повний текст джерелаKoupper, 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.
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
Lee, John C. Y. "Reduction of NOx emission for lean prevaporized-premixed combustors /." Thesis, Connect to this title online; UW restricted, 2000. http://hdl.handle.net/1773/7035.
Повний текст джерелаYaqub, Sarmad. "Experimental investigation of flame dynamics in an industrial gas turbine combustion chamber." Thesis, University of Manchester, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.488996.
Повний текст джерелаBirmaher, Shai. "A method for aircraft afterburner combustion without flameholders." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/28081.
Повний текст джерелаCommittee Chair: Zinn, Ben; Committee Member: Fuller, Thomas; Committee Member: Gaeta, Rick; Committee Member: Jagoda, Jeff; Committee Member: Neumeier, Yedidia
Wolf, Pierre. "Large Eddy Simulation of thermoacoustic instabilities in annular combustion chambers." Thesis, Toulouse, INPT, 2011. http://www.theses.fr/2011INPT0111.
Повний текст джерелаIncreasingly stringent regulations and the need to tackle rising fuel prices have placed great emphasis on the design of aeronautical gas turbines. This drive towards innovation has resulted sometimes in new concepts being prone to combustion instabilities. Combustion instabilities arise from the coupling of acoustics and combustion. In the particular field of annular combustion chambers, these instabilities often take the form of azimuthal modes. To predict these modes, one must consider the full combustion chamber, which, in the numerical simulation domain, remained out of reach until very recently and the development of massively parallel computers. In this work, azimuthal modes that may develop in annular combustors are studied with different numerical approaches: a low order model, a 3D Helmholtz solver and Large Eddy Simulations. Combining these methods allows a better understanding of the structure of the instabilities and may provide guidelines to build intrinsically stable combustion chambers
Bobba, Mohan Krishna. "Flame stabilization and mixing characteristics in a stagnation point reverse flow combustor." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/26502.
Повний текст джерелаCommittee Chair: Seitzman, Jerry; Committee Member: Filatyev, Sergei; Committee Member: Jagoda, Jechiel; Committee Member: Lieuwen, Timothy; Committee Member: Shelton, Samuel; Committee Member: Zinn, Ben. Part of the SMARTech Electronic Thesis and Dissertation Collection.
Reichling, Gilles [Verfasser], and Manfred [Akademischer Betreuer] Aigner. "Development of numerical methods for the calculation of thermo-acoustic interactions in gas turbine combustion chambers / Gilles Reichling. Betreuer: Manfred Aigner." Stuttgart : Universitätsbibliothek der Universität Stuttgart, 2015. http://d-nb.info/1072073056/34.
Повний текст джерелаCosic, Bernhard [Verfasser], Christian Oliver [Akademischer Betreuer] Paschereit, and Nicolas [Akademischer Betreuer] Noiray. "Nonlinear thermoacoustic stability analysis of gas turbine combustion chambers / Bernhard Cosic. Gutachter: Christian Oliver Paschereit ; Nicolas Noiray. Betreuer: Christian Oliver Paschereit." Berlin : Technische Universität Berlin, 2015. http://d-nb.info/1067388281/34.
Повний текст джерелаCrawford, Jackie H. III. "Factors that limit control effectiveness in self-excited noise driven combustors." Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/43647.
Повний текст джерелаAcharya, Vishal Srinivas. "Dynamics of premixed flames in non-axisymmetric disturbance fields." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50213.
Повний текст джерелаWang, Hongjuan. "Simulation of fuel injectors excited by synthetic microjets." Thesis, Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/11862.
Повний текст джерелаFortier-Topping, Hugo. "Conception d'une chambre de combustion pour la microturbine à gaz SRGT-2." Mémoire, Université de Sherbrooke, 2014. http://hdl.handle.net/11143/5417.
Повний текст джерелаGibson, R. E. N. "The design of a catalytic combustion chamber for a gas turbine using woodgas as a fuel." Thesis, Queen's University Belfast, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.426730.
Повний текст джерелаPinto, Daniel Vieira. "Análise comparativa do desempenho de turbocompressores veiculares com câmara de combustão tubular na microgeração de energia." reponame:Repositório Institucional da UCS, 2017. https://repositorio.ucs.br/handle/11338/3253.
Повний текст джерелаSubmitted by Ana Guimarães Pereira (agpereir@ucs.br) on 2017-10-25T17:02:08Z No. of bitstreams: 1 Dissertacao Daniel Vieira Pinto.pdf: 7889874 bytes, checksum: a3dd417da94a3175c511cb73b3577fd2 (MD5)
Made available in DSpace on 2017-10-25T17:02:08Z (GMT). No. of bitstreams: 1 Dissertacao Daniel Vieira Pinto.pdf: 7889874 bytes, checksum: a3dd417da94a3175c511cb73b3577fd2 (MD5) Previous issue date: 2017-10-25
This master's work presents the development of a work that has the objective of evaluating the composition of vehicular turbochargers for microgeneration of energy and to develop a tubular combustion chamber model to equip gas microturbines derived from turbochargers. In the development of the work, using the software Cycle-Tempo, it is made the evaluation of possible configurations of gas micro turbines derived from turbochargers, with respect to the number of axes and devices of increasing thermal efficiency (intercoolers, heat recover e reheater). In total, ten different configurations were simulated, and the analyzes were done directly in the thermal efficiency parameters of the sets, evaluating the relation between the energy contributed by the fuel and the energy delivered in a hypothetical electric generator. Turbochargers are then defined to form a particular gas micro turbine configuration and, being used the turbocharger performance maps from a manufacturer. From the operating parameters of the equipment, a three-dimensional combustion chamber model was developed in CAD software. The model went through five stages of simulations in Computational Fluid Dynamics (CFD). The first three steps served to develop and improve the three-dimensional model of combustion chamber and, due to software limitations, did not involve combustion. Using operational contour conditions, the velocity profile along the combustion chamber, the pressure loss, the turbulence intensity, the homogenization between the air and fuel reactants and the division of the mass flow in each section of the combustion chamber were evaluated. From the three-dimensional model was developed a prototype of the combustion chamber, built from commercial PVC pipes. The prototype was evaluated experimentally with air flow at room temperature using the coupling in series between a centrifugal fan and a blower. In the experiment the air mass flow division in each section of the combustion chamber and the loss of pressure were evaluated. The CFD simulations were redone in the fourth stage, where the boundary conditions were the parameters of mass flow, pressure and temperature, obtained experimentally. Thus, a direct comparison between the results obtained experimentally and the results of CFD simulations can be made. At the end of the work the fifth step was performed, where a heat source was inserted simulating the energy input of the combustion, allowing the temperature evaluation in the combustion chamber. The CFD simulations indicated results similar to those predicted in the literature, regarding the division of mass flow, pressure loss and velocity distribution. However, the experimental evaluations presented high measurement uncertainty for the mass flow division. Regarding pressure loss, the experimental method proved to be adequate.
Šíblová, Kamila. "Návrh spalovací turbíny pro osobní automobil." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2013. http://www.nusl.cz/ntk/nusl-230622.
Повний текст джерелаZhang, Qingguo. "Lean blowoff characteristics of swirling H2/CO/CH4 Flames." Diss., Georgia Institute of Technology, 2008. http://hdl.handle.net/1853/22641.
Повний текст джерелаRubensdörffer, Frank G. "Numerical and Experimental Investigations of Design Parameters Defining Gas Turbine Nozzle Guide Vane Endwall Heat Transfer." Doctoral thesis, KTH, Energiteknik, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3884.
Повний текст джерелаQC 20100917
Natarajan, Jayaprakash. "Experimental and numerical investigation of laminar flame speeds of H₂/CO/CO₂/N₂ mixtures." Diss., Georgia Institute of Technology, 2008. http://hdl.handle.net/1853/22685.
Повний текст джерелаAhmad, 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 джерелаAndrews, 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 джерелаSöderberg, Jakob. "CAE of Gas Turbine Combustor Chamber : Improving workflow in product lifecycle management systems." Thesis, Linköpings universitet, Maskinkonstruktion, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-168687.
Повний текст джерелаChleboun, 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 джерелаEngelbrecht, Geoffrey E. "Modelling of premixed combustion in a gas turbine." Thesis, Cranfield University, 1998. http://hdl.handle.net/1826/3987.
Повний текст джерелаMacCallum, N. R. L. "Studies in gas turbine performance and in combustion." Thesis, University of Glasgow, 2000. http://theses.gla.ac.uk/5335/.
Повний текст джерелаEccles, Neil C. "Structured grid generation for gas turbine combustion systems." Thesis, Loughborough University, 2000. https://dspace.lboro.ac.uk/2134/7348.
Повний текст джерелаAbdul, Aziz M. M. "Liquid fuelled jet shear layer gas turbine combustion." Thesis, University of Leeds, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.233835.
Повний текст джерелаZhang, K. "Turbulent combustion simulation in realistic gas-turbine combustors." Thesis, City, University of London, 2017. http://openaccess.city.ac.uk/17689/.
Повний текст джерелаAl-Kabie, Hisham Salman. "Radial swirlers for low emissions gas turbine combustion." Thesis, University of Leeds, 1989. http://etheses.whiterose.ac.uk/21157/.
Повний текст джерелаBednář, František. "Analýza možností akumulační tepelné elektrárny v podmínkách ČR." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2014. http://www.nusl.cz/ntk/nusl-231650.
Повний текст джерелаPapadogiannis, Dimitrios. "Coupled Large Eddy Simulations of combustion chamber-turbine interactions." Phd thesis, Toulouse, INPT, 2015. http://oatao.univ-toulouse.fr/14169/1/Papadogiannis_partie_1_sur_3.pdf.
Повний текст джерелаJohansson, Magnus. "Catalytic combustion of gasified biomass for gas turbine applications." Doctoral thesis, KTH, Chemical Engineering and Technology, 1998. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-2701.
Повний текст джерелаCatalytic combustion is an ultra-low emission technology forgas turbines. In parallel to the ongoing development andcommercialization of catalytic combustors fired by naturalgas,an increasing interest is aimed towards renewables, such asgasified biomass. Gasified biomass is a low-heating value (LHV)fuel, rich in hydrogen and carbon monoxide, with apotentiallyhigh level of ammonia. Consequently, specialconsiderations must be taken in the development of catalyticgas turbine combustors with gasified biomass as fuel.The first part of the present thesis reports onfundamental phenomena related to catalyticcombustion ofgasified biomass for gas turbine applications. Successfuldevelopment of the catalyst involves knowledge of both gasturbine technology and gasification of biomass.Therefore, basicconsiderations applied to integration of gasification and gasturbinetechnology are discussed. Moreover, formation ofnitrogen oxide emissions in combustion isdiscussed and asummary of the appended papers is given. Finally, recentdevelopments incatalytic combustion in gas turbines arereviewed in Paper I in the present thesis.
The second part of the present thesis, Papers II-VIII,concerns preparation and testing ofpotential combustioncatalysts. The objectives of this work have been focused onpreparationmethods and development of thermally stable andactive hexaaluminate-based catalysts (Papers II, IV-VII),ignition of the LHV-gas (Papers III-VII), conversion offuel-bound nitrogen(Papers III, V-VI) and deactivation bythermal treatment and sulphur poisoning (PapersVI-VII).Moreover, enhancing catalytic activity for totaloxidation of methane through doping ofceria has been studied(Paper VIII). The experimental investigation included activitytesting inbench-scale monolithic, single-channel annular andfixed bed reactors, and characterisationsuch as BET, XRD, SEM,EDX, XPS and SIMS.
In conclusion, lanthanum hexaaluminate impregnated with lowloading of palladiumignites the LHV-fuel at temperaturesbetween 200-250°C. At even lower palladium loading highconversion rates of carbon monoxide and hydrogen were stillobtained, while methaneconversion decreased substantially.Thermal stability and sulphur resistance of thepalladiumcatalyst exceeds those of similar platinum andtransition metal catalysts, with respect toignition of carbonmonoxide and hydrogen. Modification of the hexaaluminate phase,i.e. byion-substitution with manganese or iron, increasescatalytic activity and stability of the crystalphase, althoughsurface areas were equal to or smaller than those forunsubstituted samples.The conversion of ammonia to nitrogenoxides or molecular nitrogen (N2) was influenced by the inlettemperature and the catalyst composition. A high selectivity toN2 was observed in certain temperature regimes; higher overcatalysts based on manganese than on palladium
KEYWORDS:Catalytic combustion, gasified biomass, gasturbines, low-heating value, methanefuel-nitrogen,hexaaluminate, Pd, Pt, base metals, CeO2, deactivation, sulphurpoisoning,
Prashanth, 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
Ndiaye, Aïssatou. "Uncertainty Quantification of Thermo-acousticinstabilities in gas turbine combustors." Thesis, Montpellier, 2017. http://www.theses.fr/2017MONTS062/document.
Повний текст джерелаThermoacoustic instabilities result from the interaction between acoustic pressure oscillations and flame heat release rate fluctuations. These combustion instabilities are of particular concern due to their frequent occurrence in modern, low emission gas turbine engines. Their major undesirable consequence is a reduced time of operation due to large amplitude oscillations of the flame position and structural vibrations within the combustor. Computational Fluid Dynamics (CFD) has now become one a key approach to understand and predict these instabilities at industrial readiness level. Still, predicting this phenomenon remains difficult due to modelling and computational challenges; this is even more true when physical parameters of the modelling process are uncertain, which is always the case in practical situations. Introducing Uncertainty Quantification for thermoacoustics is the only way to study and control the stability of gas turbine combustors operated under realistic conditions; this is the objective of this work.First, a laboratory-scale combustor (with only one injector and flame) as well as two industrial helicopter engines (with N injectors and flames) are investigated. Calculations based on a Helmholtz solver and quasi analytical low order tool provide suitable estimates of the frequency and modal structures for each geometry. The analysis suggests that the flame response to acoustic perturbations plays the predominant role in the dynamics of the combustor. Accounting for the uncertainties of the flame representation is thus identified as a key step towards a robust stability analysis.Second, the notion of Risk Factor, that is to say the probability for a particular thermoacoustic mode to be unstable, is introduced in order to provide a more general description of the system than the classical binary (stable/unstable) classification. Monte Carlo and surrogate modelling approaches are then combined to perform an uncertainty quantification analysis of the laboratory-scale combustor with two uncertain parameters (amplitude and time delay of the flame response). It is shown that the use of algebraic surrogate models reduces drastically the number of state computations, thus the computational load, while providing accurate estimates of the modal risk factor. To deal with the curse of dimensionality, a strategy to reduce the number of uncertain parameters is further introduced in order to properly handle the two industrial helicopter engines. The active subspace algorithm used together with a change of variables allows identifying three dominant directions (instead of N initial uncertain parameters) which are sufficient to describe the dynamics of the industrial systems. Combined with appropriate surrogate models construction, this allows to conduct computationally efficient uncertainty quantification analysis of complex thermoacoustic systems.Third, the perspective of using adjoint method for the sensitivity analysis of thermoacoustic systems represented by 3D Helmholtz solvers is examined. The results obtained for 2D and 3D test cases are promising and suggest to further explore the potential of this method on even more complex thermoacoustic problems
Rice, Matthew Jason. "Simulation of Isothermal Combustion in Gas Turbines." Thesis, Virginia Tech, 2004. http://hdl.handle.net/10919/9723.
Повний текст джерелаMaster of Science
Manners, 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 джерелаManners, A. P. "The calculation of the flows in gas turbine combustion systems." Online version, 1988. http://ethos.bl.uk/OrderDetails.do?did=1&uin=uk.bl.ethos.366981.
Повний текст джерелаHonegger, Ueli. "Gas turbine combustion modeling for a Parametric Emissions Monitoring System." Thesis, Manhattan, Kan. : Kansas State University, 2007. http://hdl.handle.net/2097/371.
Повний текст джерела