Relevant bibliographies by topics / Combustore

Academic literature on the topic 'Combustore'

Author: Grafiati
Published: 10 March 2023

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Journal articles on the topic "Combustore"

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Davidović, Nikola S., Nenad M. Kolarević, Miloš B. Stanković, and Marko V. Miloš. "Research of expendable turbojet tubular combustion chamber." Advances in Mechanical Engineering 14, no. 5 (May 2022): 168781322210959. http://dx.doi.org/10.1177/16878132221095999.

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This paper presents research related to the tubular combustion chamber of an expendable turbojet. Although annular combustors are dominant at present, tubular combustors are still attractive because they are simpler to produce and require lower amounts of air flow for testing. The objective of this research was to assess the combustor’s primary zone configuration, and four configurations were tested to obtain experimental answers for use in future work. The configuration of the combustion chamber is a simple and classic design in line with its expendable purpose. The test methodology was to perform initial testing of the primary and secondary zones under atmospheric conditions using the four configurations, and then to subsequently complete the combustor using the best configuration. The complete combustor was then tested under both atmospheric conditions and working conditions. The results showed that the stability margin was wide enough to cover the combustor’s entire working area. The measured efficiency and pressure drop were in very good agreement with the corresponding designed values. The design and testing methodology proposed here could be used for similar scientific and engineering research applications.
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Hosseini, Seyed, Evan Owens, John Krohn, and James Leylek. "Experimental Investigation into the Effects of Thermal Recuperation on the Combustion Characteristics of a Non-Premixed Meso-Scale Vortex Combustor." Energies 11, no. 12 (December 4, 2018): 3390. http://dx.doi.org/10.3390/en11123390.

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In small-scale combustors, the ratio of area to the combustor volume increases and hence heat loss from the combustor’s wall is significantly enhanced and flame quenching occurs. To solve this problem, non-premixed vortex flow is employed to stabilize flames in a meso-scale combustion chamber to generate small-scale power or thrust for propulsion systems. In this experimental investigation, the effects of thermal recuperation on the characteristics of asymmetric non-premixed vortex combustion are studied. The exhaust gases temperature, emissions and the combustor wall temperature are measured to evaluate thermal and emitter efficiencies. The results illustrate that in both combustors (with/without thermal recuperator), by increasing the combustion air mass flowrate, the wall temperature increases while the wall temperature of combustor with thermal recuperator is higher. The emitter efficiency calculated based on the combustor wall temperature is significantly increased by using thermal recuperator. Thermal efficiency of the combustion system increases up to 10% when thermal recuperator is employed especially in moderate Reynolds numbers (combustion air flow rate is 120 mg/s).
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Wang, T., J. S. Kapat, W. R. Ryan, I. S. Diakunchak, and R. L. Bannister. "Effect of Air Extraction for Cooling and/or Gasification on Combustor Flow Uniformity." Journal of Engineering for Gas Turbines and Power 121, no. 1 (January 1, 1999): 46–54. http://dx.doi.org/10.1115/1.2816311.

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Reducing emissions is an important issue facing gas turbine manufacturers. Almost all of the previous and current research and development for reducing emissions has focused, however, on flow, heat transfer, and combustion behavior in the combustors or on the uniformity of fuel injection without placing strong emphasis on the flow uniformity of fuel injection without placing strong emphasis entering the combustors. In response to the incomplete understanding of the combustor’s inlet air flow field, experiments were conducted in a 48 percent scale, 360 deg model of the diffuser-combustor section of an industrial gas turbine. In addition, the effect of air extraction for cooling or gasification on the flow distributions at the combustors’ inlets was also investigated. The following three different air extraction rates were studied: 0 percent (baseline), 5 percent (airfoil cooling), and 20 percent (for coal gasification). The flow uniformity was investigated for the following two aspects: (a) global uniformity, which compared the mass flow rates of combustors at different locations relative to the extraction port, and (b) local uniformity, which examined the circumferential flow distribution into each combustor. The results indicate that even for the baseline case with no air extraction there was an inherent local flow non uniformity of 10 ∼ 20 percent at the inlet of each combustor due to the complex flow field in the dump diffuser and the blockage effect of the cross-flame tube. More flow was seen in the portion further away from the gas turbine center axis. The effect of 5 percent air extraction was small. Twenty percent air extraction introduced approximately 35 percent global flow asymmetry diametrically across the dump diffuser. The effect of air extraction on the combustor’s local flow uniformity varied with the distances between the extraction port and each individual combustor. Longer top hats were installed with the initial intention of increasing flow mixing prior to entering the combustor. However, the results indicated that longer top hats do not improve the flow uniformity; sometimes, adverse effects can be seen. Although a specific geometry was selected for this study, the results provide sufficient generality to benefit other industrial gas turbines.
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Khandelwal, B., A. Karakurt, V. Sethi, R. Singh, and Z. Quan. "Preliminary design and performance analysis of a low emission aero-derived gas turbine combustor." Aeronautical Journal 117, no. 1198 (December 2013): 1249–71. http://dx.doi.org/10.1017/s0001924000008848.

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Abstract Modern gas turbine combustor design is a complex task which includes both experimental and empirical knowledge. Numerous parameters have to be considered for combustor designs which include combustor size, combustion efficiency, emissions and so on. Several empirical correlations and experienced approaches have been developed and summarised in literature for designing conventional combustors. A large number of advanced technologies have been successfully employed to reduce emissions significantly in the last few decades. There is no literature in the public domain for providing detailed design methodologies of triple annular combustors. The objective of this study is to provide a detailed method designing a triple annular dry low emission industrial combustor and evaluate its performance, based on the operating conditions of an industrial engine. The design methodology employs semi-empirical and empirical models for designing different components of gas turbine combustors. Meanwhile, advanced DLE methods such as lean fuel combustion, premixed methods, staged combustion, triple annular, multi-passage diffusers, machined cooling rings, DACRS and heat shields are employed to cut down emissions. The design process is shown step by step for design and performance evaluation of the combustor. The performance of this combustor is predicted, it shows that NO x emissions could be reduced by 60%-90% as compared with conventional single annular combustors.
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Burunsuz, К. S., V. V. Kuklinovsky, and S. I. Serbin. "Investigations of the emission characteristics of a gas turbine combustor with water steam injection." Refrigeration Engineering and Technology 55, no. 2 (April 30, 2019): 77–83. http://dx.doi.org/10.15673/ret.v55i2.1356.

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The article is devoted to investigation of the possibilities of creating highly efficient and competitive Ukrainian gas turbine engines (GTEs), which correspond to modern environmental requirements for new generation energy modules. One of the most important directions of solving this problem is considered, namely, the possibility of realizing a complex thermal circuit of a gas turbine unit (GTU) - the scheme "Aquarius" with the utilization of exhaust gases heat and the injection of ecological and energy water steam into the flowing part of a combustor. The possibilities of reducing emission of harmful components, in particular, of nitrogen oxides, are analyzed, while organizing the process of a 25 MW gas turbine combustor with the supply of water steam to the primary and secondary chamber’s zones. Three-dimensional calculations of the aerodynamic structure of chemically reacting flows in a gas turbine combustor were performed with the help of methods of computational fluid dynamics (CFD). The results of theoretical investigations of gas turbine combustor’s emission characteristics at different ratios of the ecological and energy steam consumptions are presented, their rational values are revealed. The main results of the work can be used at power engineering enterprises for upgrading and modernizing existing and designing models of low-emission combustors of GTE.
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Kanta Mukherjee, Nalini. "Analytic description of flame intrinsic instability in one-dimensional model of open–open combustors with ideal and non-ideal end boundaries." International Journal of Spray and Combustion Dynamics 10, no. 4 (August 27, 2018): 287–314. http://dx.doi.org/10.1177/1756827718795518.

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This paper is concerned with the theoretical study of thermo-acoustic instabilities in combustors and focuses upon recently discovered flame intrinsic modes. Here, a complete analytical description of the salient properties of intrinsic modes is provided for a linearized one-dimensional model of open–open combustors with temperature and cross-section jump across the flame taken into account. The standard [Formula: see text] model of heat release is adopted, where n is the interaction index and τ is the time lag. We build upon the recent key finding that for a closed–lopen combustor, on the neutral curve, the intrinsic mode frequencies become completely decoupled from the combustor parameters like cross-section jump, temperature jump and flame location. Here, we show that this remarkable decoupling phenomenon holds not only for closed–open combustors but also for all combustors with the ideal boundary conditions (i.e. closed–open, open–open and closed–closed). Making use of this decoupling phenomenon for the open–open combustors, we derive explicit analytic expressions for the neutral curve of intrinsic mode instability on the [Formula: see text] plane as well as for the linear growth/decay rate near the neutral curve taking into account temperature and cross-section jumps. The instability domain on the [Formula: see text] plane is shown to be qualitatively different from that of the closed–open combustor; in open–open combustors it is not confined for large τ. To find the instability domain and growth rate characteristics for non-ideal open–open boundaries the combustor end boundaries are perturbed and explicit analytical formulae derived and verified by numerics.
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Fąfara, Jean-Marc. "Overview of low emission combustors of aircraft turbine drive units." Combustion Engines 183, no. 4 (December 15, 2020): 45–49. http://dx.doi.org/10.19206/ce-2020-407.

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It is important to notice that aircraft turbine drive units are commonly used in the modern aviation. The piston engines are often reserved for small and/or sportive aircraft. The turbine drive units are also combustion engine. This paper presents the most popular combustors used in the aeronautical turbine engines. Firstly there are listed the requirements that a combustor has to achieve. Then are presented the combustor designs that permit to achieve the firstly presented requirements. In this work are presented the LPP, TAPS, RQL, graduated combustion zone, VGC, exhaust recirculation system combustors. For each combustor design is enlighten its principle of work, described the etymology of the given name to this design and shown a scheme. The work is closed by a briefly conclusion about the described combustor.
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Saputro, Herman, Aris Purwanto, Laila Fitriana, Danar S. Wijayanto, Valiant L. P. Sutrisno, Eka D. Ariyanto, Marshal Bima, et al. "Analysis of flame stabilization limit in a cylindrical of step micro-combustor with different material through the numerical simulation." MATEC Web of Conferences 197 (2018): 08003. http://dx.doi.org/10.1051/matecconf/201819708003.

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The flame stabilization limit on micro-combustor had studied to support the micro power generator system. Micro-combustion became the crucial components in a micro power generation system as heat resource that will be converted into electricity. However, the unstable flame in micro-combustor became the main problem that faced by researchers, especially the excess of heat losses. The objective of this study is to observe the flame stabilization limit in a rearward facing step micro-combustor. This study was focused on the effect of micro-combustor material and flame stabilization through the numerical simulation. The micro-combustor material that was used in this study is quartz glass and stainless steel. Micro-combustor was divided into unburned region and burned region. The dimensions of micro-combustor are 3.5 mm inner diameter of unburned region, 4.5 mm inner diameter of burned region and 1 mm thickness. The results have shown that the material of micro-combustor and model of the flame holder have direct relationship with the characteristics of flame stabilization in the micro-combustors. The effects of the flame holder designs and micro-combustors dimensions on the flame stabilization were discussed in detail in this paper.
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Feitelberg, A. S., V. E. Tangirala, R. A. Elliott, R. E. Pavri, and R. B. Schiefer. "Reduced NOx Diffusion Flame Combustors for Industrial Gas Turbines." Journal of Engineering for Gas Turbines and Power 123, no. 4 (October 1, 2000): 757–65. http://dx.doi.org/10.1115/1.1376722.

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This paper describes reduced NOx diffusion flame combustors that have been developed for both simple cycle and regenerative cycle MS3002 and MS5002 gas turbines. Laboratory tests have shown that when firing with natural gas, without water or steam injection, NOx emissions from the new combustors are about 40 percent lower than NOx emissions from the standard combustors. CO emissions are virtually unchanged at base load, but increase at part load conditions. Commercial demonstration tests have confirmed the laboratory results. The standard combustors on both the MS3002 and MS5002 gas turbine are cylindrical cans, approximately 10.5 inches (27 cm) in diameter. A single fuel nozzle is centered at the inlet to each can and produces a swirl stabilized diffusion flame. The walls of the cans are louvered for cooling, and contain an array of mixing and dilution holes that provide the air needed to complete combustion and dilute the burned gas to the desired turbine inlet temperature. The MS3002 turbine is equipped with six combustor cans, while the MS5002 turbine is equipped with twelve combustors. The new, reduced NOx emissions combustors (referred to as a “lean head end,” or LHE, combustors) retain all of the key features of the conventional combustors; the only major difference is the arrangement of the mixing and dilution holes in the cylindrical combustor cans. By optimizing the number, diameter, and location of these holes, NOx emissions can be reduced considerably. Minor changes are also sometimes made to the combustor cap. The materials of construction, pressure drop, and fuel nozzle are all unchanged. The differences in NOx emissions between the standard and LHE combustors, as well as the variations in NOx emissions with firing temperature, are well correlated using turbulent flame length arguments. Details of this correlation are presented.
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Chand, Dharmahinder Singh, Daamanjyot Barara, Gautam Ganesh, and Suraj Anand. "Comparison of Efficiency of Conventional Shaped Circular and Elliptical Shaped Combustor." MATEC Web of Conferences 151 (2018): 02002. http://dx.doi.org/10.1051/matecconf/201815102002.

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There have been concerted efforts towards improving the fuel efficiency of the jet engines in the past, with an aim of reducing the incomplete combustion. The process of combustion in a jet engine takes place in the combustor. A study was conducted for enhancement of air-fuel mixing process by computational analysis of an elliptically shaped combustor for a gas turbine engine. The results of computational analysis of an elliptical shape combustor were compared with a circular shape combustor used in gas turbine engines with a identical cross sectional area. The comparison of the computationally derived parameters of the two combustors i.e. temperature, pressure, and velocity are studied and analyzed. The study intends towards the comparison of the combustion efficiencies of the circular and elliptically shaped combustors. The combustion efficency of elliptical chamber is found to be 98.72% at the same time it was observed 56.26% in case of circular type combustor.
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Dissertations / Theses on the topic "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/.

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Tra i vari metodi di produzione di energia meccanica le turbomacchine rappresentano sicuramente uno dei metodi più sviluppati e di maggiore interesse per via del loro utilizzo in ambito aeronautico, per la produzione di energia elettrica e la movimentazione di grosse macchine motrici. A causa della loro diffusione è diventato di fondamentale importanza trovare delle metodologie per aumentarne la potenza, l'ecosostenibilità e i rendimenti. A tale scopo la tecnica del fogging rappresenta una valida opzione per cercare di raggiungere tali obiettivi. In questo elaborato è stato prima effettuato uno studio in ambiente MatLab del comportamento di un turboalbero Allison 250 C18 variando la portata di acqua iniettata all'interno della motorizzazione cercando di determinare analiticamente, mediante le conoscenze teoriche acquisite, l'andamento di alcune grandezze fondamentali quali temperatura e pressione per poi confrontare i risultati ottenuti con i dati sperimentali raccolti precedentemente presso il "Laboratorio di macchine e propulsione" della Scuola di Ingegneria e Architettura, sede di Forlì. Successivamente si è passati alla creazione tramite Simulink, un tool di MatLab, di un modello dinamico che ci permettesse di estendere i risultati ottenuti dallo studio di alcuni punti di funzionamento a un range più elevato in modo da avere un quadro completo del comportamento del turboalbero.
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Gobbato, 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.

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Combustion instabilities are a major technical problem in most of industrial applications since they cause a performance deterioration of the combustion process. Under unstable operation the large amplitude oscillations of the flow induce many dangerous effects such as large mechanical vibrations, noise, augmented heat transfer rates at the combustor walls and increased pollutant emissions. In the gas turbines, an unstable heat release inside the combustion chamber can damage the hottest components of the combustor and reduce the life of the turbine blades. This study presents an investigation of the thermoacoustic behaviour of a single can gas turbine combustor. The combustor, originally conceived for operation with liquid and gaseous fossil fuels, was modified by the manufacturer to burn pure hydrogen or hydrogen/natural gas mixtures. Combustor design development was supported by experimental activities performed on a full-scale full-pressure test rig. A detailed procedure is proposed in this work to study the thermoacoustic instabilities in the combustor. Both hydrogen and natural gas operation are simulated by means of CFD RANS simulations carried out on a finite volume commercial code. The three-dimensional CFD analyses are performed on a coarse grid and take advantage of simplified numerical models to reduce the computation time. Due to this approach, the CFD analyses can simulate the time dependent thermoacoustic reactive flow field for a period of time large enough to capture unstable oscillation regimes, if present. Experimental measurements are used to impose the model boundary conditions and to validate the numerical results. The pressure signals recorded during the simulated period show a constant low-amplitude oscillation (a limit cycle) which does not affect the combustor performance. This behaviour agrees with the experimental data acquired during the combustion tests. The final part of this study compares the computed frequency spectra with the measured ones. The good agreement between the numerical results and the experimental values validate the potential of the low computational cost CFD approach to describe the thermoacoustic behaviour of the considered combustor.
L'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.
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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.

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It is widely accepted that climate change is a very serious environmental concern. Levels of carbon dioxide (CO2) and other emissions in the global atmosphere have increased substantially since the industrial revolution and now increasing faster than ever before. There is a thought that this has already led to dangerous warming in the Earth’s atmosphere and relevant changes around. Emissions legislations are going to be stringent as the years will pass. Hydro carbon fuel cost is also increasing substantially; more over this is non- renewable source of energy. There is an urgent need for novel combustor technologies for reducing emission as well as exploring alternative renewable fuels without effecting combustor performance. Development of novel combustors needs comprehensive understanding of conventional combustors. The design and development of gas turbine combustors is a crucial but uncertain part of an engine development process. At present, the design process relies upon a wealth of experimental data and correlations. Some major engine manufacturers have addressed the above problem by developing computer programs based on tests and empirical data to assist combustor designers, but such programs are proprietary. There is a need of developing design methodologies for combustors which would lead to substantial contribution to knowledge in field of combustors. Developed design methodologies would be useful for researchers for preliminary design assessments of a gas turbine combustor. In this study, step by step design methodologies of dual annular radial and axial combustor, triple annular combustor and reverse flow combustor have been developed. Design methodologies developed could be used to carry out preliminary design along with performance analysis for conventional combustion chambers. In this study the author has also proposed and undertaken preliminary studies of some novel combustor concepts. A novel concept of a dilution zone less combustor has been proposed in this study. According to this concept dilution air would be introduced through nozzle guide vanes to provide an optimum temperature traverse for turbine blades. Preliminary study on novel dilution zone less combustor predicts that the length of this combustor would be shorter compared to conventional case, resulting in reduced weight, fuel burn and vibrations. Reduced fuel burn eventually leads to lower emissions. Another novel concept of combustor with hydrogen synthesis from kerosene reformation has been proposed and a preliminary studies has been undertaken in this work. Addition of hydrogen as an additive in gas turbine combustor shows large benefits to the performance of gas turbine engines in addition to reduction in NOx levels. The novel combustor would have two stages, combustion of ~5% of the hydrocarbon fuel would occur in the first stage at higher equivalence ratios in the presence of a catalyst, which would eventually lead to the formation of hydrogen rich flue gases. In the subsequent stage the hydrogen rich flue gases from the first stage would act as an additive to combustion of the hydrocarbon fuel. It has been preliminary estimated that the mixture of the hydrocarbon fuel and air could subsequently be burned at much lower equivalence ratios than conventional cases, giving better temperature profiles, flame stability limits and lower NOx emissions. The effect of different geometrical parameters on the performance of vortex controlled hybrid diffuser has also been studied. It has been predicted that vortex chamber in vortex controlled hybrid diffuser does not play any role in altering the performance of diffuser. The overall contribution to knowledge of this study is development of combustor preliminary design methodologies with different variants. The other contribution to knowledge is related to novel combustors with a capability to produce low emissions. Study on novel combustor and diffuser has yielded application of two patent applications with several other publications which has resulted in a contribution to knowledge. A list of research articles, two patents, awards and achievements are presented in Appendix C.
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Aslanidou, Ioanna. "Combustor and turbine aerothermal interactions in gas turbines with can combustors." Thesis, University of Oxford, 2015. https://ora.ox.ac.uk/objects/uuid:b1527fd0-8e54-4831-8625-32722141511e.

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As the research into the improvement of gas turbine performance progresses, the combustor-turbine interface becomes of increasing importance. In new engine designs components come closer together and the study of the combustor and turbine interactions can prove to be valuable for the improvement of the aerothermal performance of the vane. This thesis presents an experimental and numerical investigation of the aerodynamic and heat transfer aspect of the interactions between the combustor and the nozzle guide vane. In the gas turbine studied the trailing edge of the combustor transition duct wall is found upstream of every second vane. In the experimental measurements carried out in a purpose-built high speed experimental facility, the wake of this wall is shown to increase the aerodynamic loss of the vane. On the other hand, the wall alters secondary flow structures and has a protective effect on the heat transfer in the leading edge-endwall junction, a region that has proven to be detrimental to component life. The effect of different clocking positions of the vane relative to the combustor wall are tested experimentally and shown to alter the aerodynamic field and the heat transfer to the vane. The experimental methods and processing techniques adopted in this work are utilized to highlight the differences between the different cases studied. A new concept of using the combustor wall to shield the nozzle guide vane leading edge is introduced, followed by a proposed design that is numerically analysed, including a new cooling system. This uses continuous cooling slots on the upstream combustor wall to cool the vane leading edge. Coolant to the endwalls is provided from continuous slots on the combustor-turbine interface. The reduction of secondary flow through the removal of the horseshoe vortex in the new design results in improved cooling of the endwalls, with a higher average adiabatic effectiveness than in the original case, using the same coolant mass flow rate. The vane surface and suction side are also successfully cooled using less air than that required for a showerhead. The new vane is tested in the experimental facility. The improved aerodynamic and thermal performance of the shielded vane is demonstrated under engine-representative inlet conditions. The new design is shown to have a lower average total pressure loss than the original vane for all inlet conditions. The heat transfer on the vane surface is overall reduced for all inlet conditions and the peak heat transfer on the vane leading edge-endwall junction is moved further upstream, to a region that can be effectively cooled from the upstream cooling slots on the combustor wall trailing edge and the endwalls.
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Abraham, 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.

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Combustion designers have considered back-side impingement cooling as the solution for modern DLE combustors. The idea is to provide more cooling to the deserved local hot spots and reserve unnecessary coolant air from local cold spots. Therefore, if accurate heat load distribution on the liners can be obtained, then an intelligent cooling system can be designed to focus more on the localized hot spots. The goal of this study is to determine the heat transfer and pressure distribution inside a typical can-annular gas turbine combustor. This is one of the first efforts in the public domain to investigate the convective heat load to combustor liner due to swirling flow generated by swirler nozzles. An experimental combustor test model was designed and fitted with a swirler nozzle provided by Solar Turbines Inc. Heat transfer and pressure distribution measurements were carried out along the combustor wall to determine the thermo-fluid dynamic effects inside a combustor. The temperature and heat transfer profile along the length of the combustor liner were determined and a heat transfer peak region was established. Constant-heat-flux boundary condition was established using two identical surface heaters, and the Infrared Thermal Imaging system was used to capture the real-time steady-state temperature distribution at the combustor liner wall. Analysis on the flow characteristics was also performed to compare the pressure distributions with the heat transfer results. The experiment was conducted at two different Reynolds numbers (Re 50,000 and Re 80,000), to investigate the effect of Reynolds Number on the heat transfer peak locations and pressure distributions. The results reveal that the heat transfer peak regions at both the Reynolds numbers occur at approximately the same location. The results from this study on a broader scale will help in understanding and predicting swirling flow effects on the local convective heat load to the combustor liner, thereby enabling the combustion engineer to design more effective cooling systems to improve combustor durability and performance.
Master of Science
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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.

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A comparison study between axial and radial swirler performance in a gas turbine can combustor was conducted by investigating the correlation between combustor flow field geometry and convective heat transfer at cold flow conditions for Reynolds numbers of 50,000 and 80,000. Flow velocities were measured using Particle Image Velocimetry (PIV) along the center axial plane and radial cross sections of the flow. It was observed that both swirlers produced a strong rotating flow with a reverse flow core. The axial swirler induced larger recirculation zones at both the backside wall and the central area as the flow exits the swirler, and created a much more uniform rotational velocity distribution. The radial swirler however, produced greater rotational velocity as well as a thicker and higher velocity reverse flow core. Wall heat transfer and temperature measurements were also taken. Peak heat transfer regions directly correspond to the location of the flow as it exits each swirler and impinges on the combustor liner wall. Convective heat transfer was also measured along the liner wall of a gas turbine annular combustor fitted with radial swirlers for Reynolds numbers 210000, 420000, and 840000. The impingement location of the flow exiting from the radial swirler resulted in peak heat transfer regions along the concave wall of the annular combustor. The convex side showed peak heat transfer regions above and below the impingement area. This behavior is due to the recirculation zones caused by the interaction between the swirlers inside the annulus.
Master of Science
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Jelercic, David. "Experiments in annular combustors." Thesis, Imperial College London, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.251891.

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Anand, Vijay G. "Rotating Detonation Combustor Mechanics." University of Cincinnati / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1530798871271548.

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9

Ayache, Simon Victor. "Simulations of turbulent swirl combustors." Thesis, University of Cambridge, 2012. https://www.repository.cam.ac.uk/handle/1810/243609.

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This thesis aims at improving our knowledge on swirl combustors. The work presented here is based on Large Eddy Simulations (LES) coupled to an advanced combustion model: the Conditional Moment Closure (CMC). Numerical predictions have been systematically compared and validated with detailed experimental datasets. In order to analyze further the physics underlying the large numerical datasets, Proper Orthogonal Decomposition (POD) has also been used throughout the thesis. Various aspects of the aerodynamics of swirling flames are investigated, such as precession or vortex formation caused by flow oscillations, as well as various combustion aspects such as localized extinctions and flame lift-off. All the above affect flame stabilization in different ways and are explored through focused simulations. The first study investigates isothermal air flows behind an enclosed bluff body, with the incoming flow being pulsated. These flows have strong similarities to flows found in combustors experiencing self-excited oscillations and can therefore be considered as canonical problems. At high enough forcing frequencies, double ring vortices are shed from the air pipe exit. Various harmonics of the pulsating frequency are observed in the spectra and their relation with the vortex shedding is investigated through POD. The second study explores the structure of the Delft III piloted turbulent non-premixed flame. The simple configuration allows to analyze further key combustion aspects of combustors, with further insights provided on the dynamics of localized extinctions and re-ignition, as well as the pollutants emissions. The third study presents a comprehensive analysis of the aerodynamics of swirl flows based on the TECFLAM confined non-premixed S09c configuration. A periodic component inside the air inlet pipe and around the central bluff body is observed, for both the inert and reactive flows. POD shows that these flow oscillations are due to single and double helical vortices, similar to Precessing Vortex Cores (PVC), that develop inside the air inlet pipe and whose axes rotate around the burner. The combustion process is found to affect the swirl flow aerodynamics. Finally, the fourth study investigates the TECFLAM configuration again, but here attention is given to the flame lift-off evident in experiments and reproduced by the LES-CMC formulation. The stabilization process and the pollutants emission of the flame are investigated in detail.
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Gray, D. T. "The control of fluidised combustors." Thesis, University of Cambridge, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.373677.

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Books on the topic "Combustore"

1

Young, Mark F. Measurements of gas turbine combustor and engine augmentor tube sooting characteristics. Monterey, Calif: Naval Postgraduate School, 1988.

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Lee, Richard S. L., James H. Whitelaw, and T. S. Wung, eds. Aerothermodynamics in Combustors. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4.

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Center, Langley Research, ed. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

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Center, Langley Research, ed. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

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Lieuwen, Timothy C. Unsteady combustor physics. Cambridge: Cambridge University Press, 2013.

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Kumar, Sanjiv. A computer model for the simulation of turbulent reacting flow in a jet assisted ram combustor. Chofu, Tokyo: National Aerospace Laboratory, 1995.

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M, Mellor A., ed. Design of modern turbine combustors. London: Academic Press, 1990.

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United States. Environmental Protection Agency. Office of Water, ed. Development document for final effluent limitations guidelines and standards for the commercial hazardous waste combustor subcategory of the waste combustors point source category. Washington, DC: U.S. Environmental Protection Agency, Office of Water, 2000.

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J, Breisacher Kevin, and United States. National Aeronautics and Space Administration., eds. 3D rocket combustor acoustics model. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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P, Menees Gene, and Ames Research Center, eds. Wave combustors for trans-atmospheric vehicles. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1989.

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Book chapters on the topic "Combustore"

1

Seitz, Timo, Ansgar Lechtenberg, and Peter Gerlinger. "Rocket Combustion Chamber Simulations Using High-Order Methods." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 381–94. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_24.

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Abstract High-order spatial discretizations significantly improve the accuracy of flow simulations. In this work, a multi-dimensional limiting process with low diffusion (MLP$$^\text {ld}$$) and up to fifth order accuracy is employed. The advantage of MLP is that all surrounding volumes of a specific volume may be used to obtain cell interface values. This prevents oscillations at oblique discontinuities and improves convergence. This numerical scheme is utilized to investigate three different rocket combustors, namely a seven injector methane/oxygen combustion chamber, the widely simulated PennState preburner combustor and a single injector chamber called BKC, where pressure oscillations are important.
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Bilger, R. W. "Advanced Laser Diagnostics: Implications of Recent Results for Advanced Combustor Models." In Aerothermodynamics in Combustors, 3–16. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_1.

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Lindstedt, R. P. "A Simple Reaction Mechanism for Soot Formation in Non-Premixed Flames." In Aerothermodynamics in Combustors, 145–56. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_10.

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Chiu, H. H. "Droplet Vaporization Law in Non-Dilute Sprays." In Aerothermodynamics in Combustors, 159–73. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_11.

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Roth, N., K. Anders, and A. Frohn. "Experimental Investigation of the Reduction of Burning Rate Due to Finite Spacing Between Droplets." In Aerothermodynamics in Combustors, 175–83. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_12.

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Hiroyasu, Hiroyuki, Masataka Arai, Kaoru Nakamori, and Shinji Nakaso. "Blue Flame Combustion in a Jet-Mixing-Type Spray Combustor." In Aerothermodynamics in Combustors, 185–96. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_13.

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Liu, Chi-Chang, and Ta-Hui Lin. "The Influence of Upstream Prevaporization on Flame Extinction of One-Dimensional Dilute Sprays." In Aerothermodynamics in Combustors, 197–211. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_14.

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Hendricks, E. W., S. Sivasegaram, and J. H. Whitelaw. "Control of Oscillations in Ducted Premixed Flames." In Aerothermodynamics in Combustors, 215–30. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_15.

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Tien, Ta-Ching, and James S. T’ien. "Catalytic Ignition Model in Monolithic Reactor with In-Depth Reaction." In Aerothermodynamics in Combustors, 231–44. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_16.

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Bai, T., S. Shani, B. R. Daniel, and B. T. Zinn. "Combustion of Heavy Fuel Oils in a Rijke Type Pulse Combustor with a Tangential Injection Stream." In Aerothermodynamics in Combustors, 245–64. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_17.

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Conference papers on the topic "Combustore"

1

Wang, T., J. S. Kapat, W. R. Ryan, I. S. Diakunchak, and R. L. Bannister. "Effect of Air Extraction for Cooling and/or Gasification on Combustor Flow Uniformity." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-102.

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Reducing emissions is an important issue facing gas turbine manufacturers. Almost all of the previous and current research and development for reducing emissions has focused, however, on flow, heat transfer, and combustion behavior in the combustors or on the uniformity of fuel injection without placing strong emphasis on the flow uniformity entering the combustors. In response to the incomplete understanding of the combustor’s inlet air flow field, experiments were conducted in a 48% scale, 360° model of the diffuser-combustor section of an industrial gas turbine. In addition, the effect of air extraction for cooling or gasification on the flow distributions at the combustors’ inlets was also investigated. Three different air extraction rates were studied: 0% (baseline), 5% (airfoil cooling), and 20% (for coal gasification). The flow uniformity was investigated for two aspects: (a) global uniformity, which compared the mass flow rates of combustors at different locations relative to the extraction port, and (b) local uniformity, which examined the circumferential flow distribution into each combustor. The results indicate that even for the baseline case with no air extraction there was an inherent local flow aonuniformity of 10 ∼ 20% at the inlet of each combustor due to the complex flow field in the dump diffuser and the blockage effect of the cross-flame tube. More flow was seen in the portion further away from the gas turbine center axis. The effect of 5% air extraction was small. Twenty-percent air extraction introduced approximately 35% global flow asymmetry diametrically across the dump diffuser. The effect of air extraction on the combustor’s local flow uniformity varied with the distances between the extraction port and each individual combustor. Longer top hats were installed with the initial intention of increasing flow mixing prior to entering the combustor. However, the results indicated that longer top hats do not improve the flow uniformity; sometimes, adverse effects can be seen. Although a specific geometry was selected for this study, the results provide sufficient generality to benefit other industrial gas turbines.
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Walker, A. Duncan, Jon F. Carrotte, and James J. McGuirk. "Compressor/Diffuser/Combustor Aerodynamic Interactions in Lean Module Combustors." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27872.

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The paper reports an experimental investigation into the possibility of increased interactions between combustor external aerodynamics and upstream components e.g. pre-diffuser, compressor OGV and even the compressor rotor, caused by the trend in lean module fuel injectors to larger mass flows entering the combustor cowl. To explore these component interaction effects, measurements were made on a fully annular rig comprising a single stage compressor, an advanced integrated OGV/pre-diffuser, followed by a dump diffuser and a generic combustor flametube with metered cowl and inner/outer annulus flows. The flow split entering the cowl was increased from 30% to 70%. The results demonstrate that, with fixed geometry, as the injector flow increases, the performance of the pre-diffuser and feed annuli suffer. Pre-diffuser losses increase and at high injector flow rates the diffuser moves close to separation. The substantial circumferential variation in cowl flow can feed upstream and cause rotor forcing. Notable differences in performance were observed inline and between injectors at OGV exit, suggesting that geometry changes such as an increased dump gap or non axisymmetric pre-diffuser designs may be beneficial.
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Samarasinghe, Janith, Stephen J. Peluso, Bryan D. Quay, and Domenic A. Santavicca. "The 3-D Structure of Swirl-Stabilized Flames in a Lean Premixed Multi-Nozzle Can Combustor." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42167.

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Flame structure is an important aspect of the combustion process which must be considered in the design of gas turbine combustors as it can have a significant effect on the combustor’s static stability (blowoff) and dynamic stability (combustion instability). The relationship between flame structure and flame stability has been studied extensively in single-nozzle combustors. However, relatively few studies have been conducted in multi-nozzle combustor configurations typical of actual gas turbine combustion systems. In this paper, a chemiluminescence-based tomographic reconstruction technique is used to obtain three-dimensional images of the flame structure in a laboratory-scale five-nozzle can combustor. The images reveal the complex three-dimensional structure of this multi-nozzle flame, as well as, the effects of interacting swirling flows, flame-flame interactions and flame-wall interactions on flame structure.
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Zahn, Max, Michael Betz, Moritz Schulze, Christoph Hirsch, and Thomas Sattelmayer. "Predicting the Influence of Damping Devices on the Stability Margin of an Annular Combustor." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64238.

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A numerical modeling approach based on linearized Euler equations is applied to predict the linear stability of an annular combustor with and without dampers. The acoustic properties of all relevant combustor components such as damping devices, swirl burner characteristics, swirl flame dynamics, and combustor exit are individually evaluated via experimental and numerical approaches. All of the components are incorporated subsequently into the combustor model using impedances and acoustic transfer matrices to obtain an efficient procedure. This study focuses on using this approach to predict an annular combustor’s stability margin and to assess how dampers influence the modal dynamics of the first azimuthal mode. Stability predictions are successfully validated with experimental data. Different combustor components’ contributions to the acoustic damping of the entire system is also determined based on that numerical approach. Damper application in combustors can engender uncertainties in resonance frequency in the case of hot-gas ingestion. The impact of “detuned” resonators on the predicted damping rates with respect to a deviation in the resonance frequency and the eigenfrequency of the attenuated acoustic mode is therefore evaluated. The influence of dampers on the annular combustor’s stability margin is also determined.
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Lieuwen, Tim, Vince McDonell, Eric Petersen, and Domenic Santavicca. "Fuel Flexibility Influences on Premixed Combustor Blowout, Flashback, Autoignition and Instability." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90770.

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This paper addresses the impact of fuel composition on the operability of lean premixed gas turbine combustors. This is an issue of current importance due to variability in the composition of natural gas fuel supplies and interest in the use of syngas fuels. Of particular concern is the effect of fuel composition on combustor blowout, flashback, dynamic stability, and autoignition. This paper reviews available results and current understanding of the effects of fuel composition on the operability of lean premixed combustors. It summarizes the underlying processes that must be considered when evaluating how a given combustor’s operability will be affected as fuel composition is varied.
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Garland, R. V., P. W. Pillsbury, and T. E. Dowdy. "Design and Test of a Candidate Topping Combustor for Second Generation PFB Applications." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-113.

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Second Generation Pressurized Fluidized Bed Combustion Combined Cycles utilize topping combustion to raise the combustion turbine inlet temperature to the state of the art. Principally for this reason, cycle efficiency is improved over first generation PFB systems. Topping combustor design requirements differ from conventional gas turbine combustors since hot, vitiated air from the PFB is used for both cooling and combustion. In addition, the topping combustor fuel, a hot, low-heating value gas produced from coal pyrolysis, contains ammonia. This NOx-forming constituent adds to the combustor’s unique design challenges. The candidate combustor is the multi-annular swirl burner (MASB) based on the design described by J.M. Beér. This concept embodies rich-burn, quick quench, and lean-burn zones formed aerodynamically. The initial test sponsored by the Department of Energy, Morgantown, West Virginia, has been completed and the results of that test are presented.
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Lieuwen, Tim, and Andrzej Banaszuk. "Background Noise Effects on Combustor Stability." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30062.

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This paper considers the effects of background turbulent fluctuations upon a combustor’s stability boundaries. Inherent turbulent fluctuations act as both additive and parametric (also called multiplicative) excitation sources to acoustic waves in combustors. While additive noise sources exert primarily quantitative effects upon combustor oscillations, parametric noise sources can exert qualitative impacts upon its dynamics; particularly of interest here is their ability to destabilize a “nominally” stable system. The significance of these parametric noise sources increases with increased background noise levels and, thus, may play more of a role in realistic, high Reynolds number systems than experiments on simplified, lab scale combustors might suggest. The objective of this paper is to determine whether and/or when these effects might be significant. The analysis considers the effects of fluctuations in damping rate, frequency and combustion response. It is found that the effects of noisy damping and frequency upon the combustor’s stability limits is quite small, at least for the fluctuation intensities estimated here. The effects of a noisy combustion response, particularly of a fluctuating time delay between flow and heat release perturbations, can be quite significant, however, in some cases for turbulence intensities as low as <(u′/u¯)2>1/2∼5–10%. These results suggest that deterministic stability models calibrated on low turbulence intensity, lab scale combustors may not adequately describe the stability limits of realistic, highly turbulent combustors.
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Hegde, Gajanana B., Bhupendra Khandelwal, Vishal Sethi, and Riti Singh. "Design, Evaluation and Performance Analysis of Staged Low Emission Combustors." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-69215.

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The most uncertain and challenging part in the design of a gas turbine has long been the combustion chamber. There has been large number of experimentations in industries and universities alike to better understand the dynamic and complex processes that occur inside a combustion chamber. This study concentrates on gas turbine combustors as a whole, and formulates a theoretical design procedure for staged combustors in particular. Not much of literatures available currently in public domain provide intensive study on designing staged combustors. The work covers an extensive study of design methods applied in conventional combustor designs, which includes the reverse flow combustor and the axial flow annular combustors. The knowledge acquired from this study is then applied to develop a theoretical design methodology for double staged (radial and axial) low emission annular combustors. Additionally a model combustor is designed for each type; radial and axial staging using the developed methodology. A prediction of the performance for the model combustors is executed. The main conclusion is that the dimensions of model combustors obtained from the developed design methodology are within the feasibility limits. The comparison between the radially staged and the axially staged combustor has yielded the predicted results such as lower NOx prediction for the latter and shorter combustor length for the former. The NOx emission result of the new combustor models are found to be in the range of 50–60ppm. However the predicted NOx results are only very crude and need further detailed study.
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Rida, Samir, Saugata Chakravorty, Jaydeep Basani, Stefano Orsino, and Naseem Ansari. "An Assessment of Flamelet Generated Manifold Combustion Model for Predicting Combustor Performance." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42340.

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In Rich-Quench-Lean design of aircraft gas turbine combustors, primary zone mixing is critical for emissions, flame shape, and heat transfer. From a modeling perspective, the primary zone flow prediction is largely impacted by the fidelity of the mixing model and the type of combustion model used. The assumption that fuel spray burns in a diffusion flame or in a partially premixed flame has an impact on the combustor’s performance parameters. In this paper, we compare the non-premixed steady diffusion flamelet model with the partially premixed flamelet generated manifold model for several Honeywell combustors using the commercial CFD code ANSYS FLUENT. The validations are made in the context of Large Eddy Simulation and the time averaged CFD results are compared with rig data highlighting the impact of the combustion models on combustor performance. Results show that the flamelet generated manifold combustion model provides a more realistic lifted flame shape that is not in contact with the fuel nozzle.
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Hirano, Kohshi, Yoshiharu Nonaka, Yasuhiro Kinoshita, Masaya Muto, and Ryoichi Kurose. "Large-Eddy Simulation of Turbulent Combustion in Multi Combustors for L30A Gas Turbine Engine." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42545.

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When designing a combustor, numerical analysis should be used to effectively predict different performances, such as flame temperature, emission, and combustion stability. However, even with the use of numerical analysis, several problems cannot be solved by investigating single combustors because, in an actual engine, interactions occur between multiple combustors. Therefore, to evaluate the detailed phenomenon in an actual combustor, the interactions between all combustors should be considered in any numerical analysis. On the other hand, a huge amount of computational cost is required for this type of analysis. Here a large-eddy simulation employing a flamelet/progress variable approach is applied to the numerical analysis of industrial combustors. The combustor used for this study is the L30A from Kawasaki Heavy Industries, Ltd. Computations are conducted with a supercomputer (referred to as the “K-computer”) in the RIKEN Advanced Institute for Computational Science. All combustors in the L30A engine (from the compressor outlet to the turbine inlet) are simulated, including the fuel manifold. This engine has eight can combustors that are connected through the fuel manifold and compressed air housing unit. The total number of elements is approximately 140 million. The flow patterns for each combustor are similar in all cans. A swirling flow from the main burner is formed and accelerated by the supplemental burner. There is a high-temperature region before the supplemental burner. The flow field and temperature distribution in an actual combustor interacting with other combustor cans are simulated adequately. The mass flow rate of the air and those of the fuels are distributed equally for each can. Therefore, the outlet temperature difference for each can is also very small.
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Reports on the topic "Combustore"

1

Bray, C. Transport in Dump Combustors. Fort Belvoir, VA: Defense Technical Information Center, August 1986. http://dx.doi.org/10.21236/ada224790.

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Vreeland, Heidi, Christina Norris, Lauren Shum, Jaya Pokuri, Emily Shannon, Anmol Raina, Ayushman Tripathi, et al. Collaborative Efforts to Investigate Emissions From Residential and Municipal Trash Burning in India. RTI Press, September 2018. http://dx.doi.org/10.3768/rtipress.2018.rb.0019.1809.

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Emissions from trash burning represent an important component of regional air quality, especially in countries such as India where the practice of roadside, residential, and municipal trash burning is highly prevalent. However, research on trash emissions is limited due to difficulties associated with measuring a source that varies widely in composition and burning characteristics. To investigate trash burning in India, a collaborative program was formed among RTI, Duke University, and the India Institute of Technology (IIT) in Gandhinagar, involving both senior researchers and students. In addition to researching emission measurement techniques, this program aimed to foster international partnerships and provide students with a hands-on educational experience, culminating in a pilot study in India. Before traveling, students from Duke and IIT met virtually to design experiments. IIT students were able to visit proposed sites and offer specified knowledge on burning practices prior to the pilot study, allowing potential experiments to be iteratively improved. The results demonstrated a proof of concept of using a low-cost sensor attached to a commercial drone to measure emissions from a municipal dump site. In addition, for small-scale residential and roadside trash burning, a combustor was designed to burn trash in a consistent way. Results suggested that thermocouples and low-cost sensors may offer an affordable way for combustor designers to assess particulate emissions during prototype iterations. More experiences like this should be made available so that future research can benefit from the unique insights that come from having veteran researchers work with students and from forming international partnerships.
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Santavicca, Domenic A. Combustion Instabilities in Lean Premixed Combustors. Fort Belvoir, VA: Defense Technical Information Center, July 2001. http://dx.doi.org/10.21236/ada400629.

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W. R. Laster, E. Anoshkina, and P. Szedlacsek. Catalytic Combustor for Fuel-Flexible Turbine. Office of Scientific and Technical Information (OSTI), March 2006. http://dx.doi.org/10.2172/907883.

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Crayon, D., A. E. Fish, E. Hyland, R. W. Messler, and jr. Coatings Evaluation Using a Vented Combustor. Fort Belvoir, VA: Defense Technical Information Center, December 2001. http://dx.doi.org/10.21236/ada397759.

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Laster, W. R., and E. Anoshkina. Catalytic Combustor for Fuel-Flexible Turbine. Office of Scientific and Technical Information (OSTI), January 2008. http://dx.doi.org/10.2172/1083745.

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W. R. Laster and E. Anoshkina. Catalytic Combustor for Fuel-Flexible Turbine. Office of Scientific and Technical Information (OSTI), January 2008. http://dx.doi.org/10.2172/973070.

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National Energy Technology Laboratory. Pulse Combustor Design, A DOE Assessment. Office of Scientific and Technical Information (OSTI), July 2003. http://dx.doi.org/10.2172/812682.

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Gidaspow, D. Predictive models of circulating fluidized bed combustors. Office of Scientific and Technical Information (OSTI), July 1992. http://dx.doi.org/10.2172/7195746.

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Louge, M. Y. Scale-up circulating fluidized bed coal combustors. Office of Scientific and Technical Information (OSTI), November 1991. http://dx.doi.org/10.2172/5520104.

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