Relevant bibliographies by topics / Lean burn combustor

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Lean burn combustor'

Author: Grafiati
Published: 10 March 2023

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Journal articles on the topic "Lean burn combustor"

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Straub, Douglas L., Kent H. Casleton, Robie E. Lewis, Todd G. Sidwell, Daniel J. Maloney, and George A. Richards. "Assessment of Rich-Burn, Quick-Mix, Lean-Burn Trapped Vortex Combustor for Stationary Gas Turbines." Journal of Engineering for Gas Turbines and Power 127, no. 1 (January 1, 2005): 36–41. http://dx.doi.org/10.1115/1.1789152.

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This paper describes the evaluation of an alternative combustion approach to achieve low emissions for a wide range of fuel types. This approach combines the potential advantages of a staged rich-burn, quick-mix, lean-burn (RQL) combustor with the revolutionary trapped vortex combustor (TVC) concept. Although RQL combustors have been proposed for low-Btu fuels, this paper considers the application of an RQL combustor for high-Btu natural gas applications. This paper will describe the RQL/TVC concept and experimental results conducted at 10 atm (1013 kPa or 147 psia) and an inlet-air temperature of 644 K (700°F). The results from a simple network reactor model using detailed kinetics are compared to the experimental observations. Neglecting mixing limitations, the simplified model suggests that NOx and CO performance below 10 parts per million could be achieved in an RQL approach. The CO levels predicted by the model are reasonably close to the experimental results over a wide range of operating conditions. The predicted NOx levels are reasonably close for some operating conditions; however, as the rich-stage equivalence ratio increases, the discrepancy between the experiment and the model increases. Mixing limitations are critical in any RQL combustor, and the mixing limitations for this RQL/TVC design are discussed.
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Micklow, G. J., S. Roychoudhury, H. L. Nguyen, and M. C. Cline. "Emissions Reduction by Varying the Swirler Airflow Split in Advanced Gas Turbine Combustors." Journal of Engineering for Gas Turbines and Power 115, no. 3 (July 1, 1993): 563–69. http://dx.doi.org/10.1115/1.2906744.

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A staged combustor concept for reducing pollutant emissions is currently under investigation. A numerical study was performed to investigate the chemically reactive flow with liquid spray injection for staged combustion. The staged combustor consists of an airblast atomizer fuel injector, a rich burn section, a converging connecting pipe, a quick mix zone, a diverging connecting pipe and a lean combustion zone. For computational efficiency, the combustor was split into two subsystems, i.e., the fuel nozzle/rich burn section and the quick mix/lean burn section. The current study investigates the effect of varying the mass flow rate split between the swirler passages for an equivalence ratio of 2.0 on fuel distribution, temperature distribution, and emissions for the fuel nozzle/rich burn section of a staged combustor. It is seen that optimizing these parameters can substantially improve combustor performance and reduce combustor emissions. The optimal mass flow rate split for reducing NOx emissions based on the numerical study was the same as found by experiment.
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Di Sarli, Valeria. "Stability and Emissions of a Lean Pre-Mixed Combustor with Rich Catalytic/Lean-burn Pilot." International Journal of Chemical Reactor Engineering 12, no. 1 (January 1, 2014): 77–89. http://dx.doi.org/10.1515/ijcre-2013-0112.

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Abstract In this work, a reactor network model was developed to study homogeneous gas-phase methane combustion taking place under typical operating conditions of lean pre-mixed combustors piloted by rich catalytic/lean-burn (RCL) systems. In particular, the thermo-kinetic interaction between the pilot stream (i.e. the stream exiting the RCL stage) and the main feeding stream to the homogeneous reactor was investigated in terms of combustion stability and emissions. The homogeneous combustor was modeled as a perfectly stirred reactor (PSR). The pilot stream was mixed with the main feeding stream prior to entering the PSR. Numerical results have shown that the opportunity to stabilize combustion is strongly linked to the presence of hydrogen in the pilot stream. Combustion stability is highly sensitive to variations in fuel split between catalytic pilot and homogeneous reactor. The increase in pilot fuel split (and, thus, in the inlet hydrogen concentration to the PSR) enlarges the operating window of stable combustion (in terms of higher heat losses, lower preheat temperatures and lower residence times), while still achieving NOx and CO emissions lower than 9 ppm (at 15% O2). These results highlight the potential of the RCL technology as a valuable alternative to conventional diffusion flame-based pilots.
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Hendricks, R. C., D. T. Shouse, W. M. Roquemore, D. L. Burrus, B. S. Duncan, R. C. Ryder, A. Brankovic, N. S. Liu, J. R. Gallagher, and J. A. Hendricks. "Experimental and Computational Study of Trapped Vortex Combustor Sector Rig with High-Speed Diffuser Flow." International Journal of Rotating Machinery 7, no. 6 (2001): 375–85. http://dx.doi.org/10.1155/s1023621x0100032x.

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The Trapped Vortex Combustor (TVC) potentially offers numerous operational advantages over current production gas turbine engine combustors. These include lower weight, lower pollutant emissions, effective flame stabilization, high combustion efficiency, excellent high altitude relight capability, and operation in the lean burn or RQL modes of combustion. The present work describes the operational principles of the TVC, and extends diffuser velocities toward choked flow and provides system performance data. Performance data include EINOx results for various fuel-air ratios and combustor residence times, combustion efficiency as a function of combustor residence time, and combustor lean blow-out (LBO) performance. Computational fluid dynamics (CFD) simulations using liquid spray droplet evaporation and combustion modeling are performed and related to flow structures observed in photographs of the combustor. The CFD results are used to understand the aerodynamics and combustion features under different fueling conditions. Performance data acquired to date are favorable compared to conventional gas turbine combustors. Further testing over a wider range of fuel-air ratios, fuel flow splits, and pressure ratios is in progress to explore the TVC performance. In addition, alternate configurations for the upstream pressure feed, including bi-pass diffusion schemes, as well as variations on the fuel injection patterns, are currently in test and evaluation phases.
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Serbin, Serhiy, and Nataliia Goncharova. "Investigations of a Gas Turbine Low-Emission Combustor Operating on the Synthesis Gas." International Journal of Chemical Engineering 2017 (2017): 1–14. http://dx.doi.org/10.1155/2017/6146984.

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Investigations of the working processes in a gas turbine low-emission combustor operating on the synthesis gas, in which the principle of RQL (Rich-Burn, Quick-Mix, and Lean-Burn) combustion technology is realized, have been performed. Selected concept of a gas turbine combustor can provide higher performance and lower emission of nitrogen oxides and demonstrates satisfactory major key parameters. Obtained results and recommendations can be used for the gas turbine combustor operation modes modeling, geometry optimization, and prospective power generation units design and engineering.
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Li, J., X. Sun, Y. Liu, and V. Sethi. "Preliminary aerodynamic design methodology for aero engine lean direct injection combustors." Aeronautical Journal 121, no. 1242 (June 21, 2017): 1087–108. http://dx.doi.org/10.1017/aer.2017.47.

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ABSTRACTThe Lean Direct Injection (LDI) combustor is one of the low-emissions combustors with great potential in aero-engine applications, especially those with high overall pressure ratio. A preliminary design tool providing basic combustor sizing information and qualitative assessment of performance and emission characteristics of the LDI combustor within a short period of time will be of great value to designers. In this research, the methodology of preliminary aerodynamic design for a second-generation LDI (LDI-2) combustor was explored. A computer code was developed based on this method covering the design of air distribution, combustor sizing, diffuser, dilution holes and swirlers. The NASA correlations for NOxemissions are also embedded in the program in order to estimate the NOx production of the designed LDI combustor. A case study was carried out through the design of an LDI-2 combustor named as CULDI2015 and the comparison with an existing rich-burn, quick-quench, lean-burn combustor operating at identical conditions. It is discovered that the LDI combustor could potentially achieve a reduction in liner length and NOxemissions by 18% and 67%, respectively. A sensitivity study on parameters such as equivalence ratio, dome and passage velocity and fuel staging is performed to investigate the effect of design uncertainties on both preliminary design results and NOxproduction. A summary on the variation of design parameters and their impact is presented. The developed tool is proved to be valuable to preliminarily evaluate the LDI combustor performance and NOxemission at the early design stage.
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Talpallikar, M. V., C. E. Smith, M. C. Lai, and J. D. Holdeman. "CFD Analysis of Jet Mixing in Low NOx Flametube Combustors." Journal of Engineering for Gas Turbines and Power 114, no. 2 (April 1, 1992): 416–24. http://dx.doi.org/10.1115/1.2906607.

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The Rich-burn/Quick-mix/Lean-burn (RQL) combustor has been identified as a potential gas turbine combustor concept to reduce NOx emissions in High Speed Civil Transport (HSCT) aircraft. To demonstrate reduced NOx levels, cylindrical flametube versions of RQL combustors are being tested at NASA Lewis Research Center. A critical technology needed for the RQL combustor is a method of quickly mixing bypass combustion air with rich-burn gases. In this study, jet mixing in a cylindrical quick-mix section was numerically analyzed. The quick-mix configuration was five inches in diameter and employed 12 radial-inflow slots. The numerical analyses were performed with an advanced, validated 3-D Computational Fluid Dynamics (CFD) code named REFLEQS. Parametric varation of jet-to-mainstream momentum flux ratio (J) and slot aspect ratio was investigated. Both nonreacting and reacting analyses were performed. Results showed mixing and NOx emissions to be highly sensitive to J and slot aspect ratio. Lowest NOx emissions occurred when the dilution jet penetrated to approximately midradius. The viability of using 3-D CFD analyses for optimizing jet mixing was demonstrated.
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Garland, R. V., and P. W. Pillsbury. "Status of Topping Combustor Development for Second-Generation Fluidized Bed Combined Cycles." Journal of Engineering for Gas Turbines and Power 114, no. 1 (January 1, 1992): 126–31. http://dx.doi.org/10.1115/1.2906294.

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Addition of a fluidized bed combustor to a high-efficiency combined cycle plant enables direct firing of inexpensive run-of-the-mine coal in an environmentally acceptable manner. To attain high thermal efficiencies, coal pyrolysis is included. The low heating value fuel gas from the pyrolyzer is burned in a topping combustion system that boosts gas turbine inlet temperature to state of the art while the pyrolyzer-produced char is burned in the bed. The candidate topping combustor, the multi-annular swirl burner, based on a design by J. M. Bee´r, is presented and discussed. Design requirements differ from conventional gas turbine combustors. The use of hot, vitiated air for cooling and combustion, and the use of low heating value fuel containing ammonia, are two factors that make the design requirements unique. The multi-annular swirl burner contains rich-burn, quick-quench, and lean-burn zones formed aerodynamically rather than the physically separate volumes found in other rich-lean combustors. Although fuel is injected through a centrally located nozzle, the combustion air enters axially through a series of swirlers. Wall temperatures are controlled by relatively thick layers of air entering through the various swirler sections, which allows the combustor to be of all-metal construction rather than the ceramic often used in rich-lean concepts. This 12-in.-dia design utilizes some of the features of the previous 5-in. and 10-in. versions of the multi-annular swirl burner; test results from the previous projects were utilized in the formulation of the test for the present program. In the upcoming tests, vitiated air will be provided to simulate a pressurized fluidized bed effluent. Hot syngas seeded with ammonia will be used to simulate the low-Btu gas produced in the pyrolyzer.
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Blomeyer, M., B. Krautkremer, D. K. Hennecke, and T. Doerr. "Mixing Zone Optimization of a Rich-Burn/Quick-Mix/Lean-Burn Combustor." Journal of Propulsion and Power 15, no. 2 (March 1999): 288–95. http://dx.doi.org/10.2514/2.5425.

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McGuirk, J. J. "The aerodynamic challenges of aeroengine gas-turbine combustion systems." Aeronautical Journal 118, no. 1204 (June 2014): 557–99. http://dx.doi.org/10.1017/s0001924000009386.

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Abstract The components of an aeroengine gas-turbine combustor have to perform multiple tasks – control of external and internal air distribution, fuel injector feed, fuel/air atomisation, evaporation, and mixing, flame stabilisation, wall cooling, etc. The ‘rich-burn’ concept has achieved great success in optimising combustion efficiency, combustor life, and operational stability over the whole engine cycle. This paper first illustrates the crucial role of aerodynamic processes in achieving these performance goals. Next, the extra aerodynamic challenges of the ‘lean-burn’ injectors required to meet the ever more stringent NO x emissions regulations are introduced, demonstrating that a new multi-disciplinary and ‘whole system’ approach is required. For example, high swirl causes complex unsteady injector aerodynamics; the threat of thermo-acoustic instabilities means both aerodynamic and aeroacoustic characteristics of injectors and other air admission features must be considered; and high injector mass flow means potentially strong compressor/combustor and combustor/turbine coupling. The paper illustrates how research at Loughborough University, based on complementary use of advanced experimental and computational methods, and applied to both isolated sub-components and fully annular combustion systems, has improved understanding and identified novel ideas for combustion system design.
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Dissertations / Theses on the topic "Lean burn combustor"

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Wankhede, Moresh J. "Multi-fidelity strategies for lean burn combustor design." Thesis, University of Southampton, 2012. https://eprints.soton.ac.uk/210785/.

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In combustor design and development, the use of unsteady computational fluid dynamics (CFD) simulations of transient combustor aero-thermo-dynamics to provide an insight into the complex reacting flow-field is expensive in terms of computational time. A large number of such high-fidelity reactive CFD analyses of the objective and constraint functions are normally required in combustor design and optimisation process. Hence, traditional design strategies utilizing only high-fidelity CFD analyses are often ruled out, given the complexity in obtaining accurate flow predictions and limits on available computational resources and time. This necessitates a careful design of fast, reliable and efficient design strategies. Surrogate modeling design strategies, including Kriging models, are currently being used to balance the challenges of accuracy and computational resource to accelerate the combustor design process. However, its feasibility still largely relies on the total number of design variables, objective and constraint functions, as only high-fidelity CFD analyses are used to construct the surrogate model. This thesis explores these issues in combustor design by aiming to minimize the total number of high fidelity CFD runs and to accelerate the process of finding a good design earlier in the design process. Initially, various multi-fidelity design strategies employing a co-Kriging surrogate modeling approach were developed and assessed for performance and confidence against a traditional Kriging based design strategy, within a fixed computational budget. Later, a time-parallel combustor CFD simulation methodology is proposed, based on temporal domain decomposition, and further developed into a novel time-parallel co-Kriging based multi-fidelity design strategy requiring only a single CFD simulation to be setup for various fidelities. The performance and confidence assessment of the newly developed multi-fidelity strategies shows that they are, in general, competitive against the traditional Kriging based design strategy, and evidence exists of finding a good design early in the design optimisation process
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Peacock, Graham. "Enhanced cold-side cooling techniques for lean burn combustor liners." Thesis, Loughborough University, 2013. https://dspace.lboro.ac.uk/2134/12329.

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In order to meet the increasingly strict emissions targets required in modern civil aviation, lean burn combustors are being pursued as a means to reduce the environmental impact of gas-turbine engines. By adopting a lean air/fuel mixture NOx production may be reduced. The increase in proportional amount of high pressure air entering directly into the combustor reduces the amount available for cooling of the combustor liner tiles. A reduced mass of air places restrictions on the porosity of cooling arrays, requiring a departure from applications of pedestal and slotted film cooling typically used to cool double skin combustor liners. An alternative approach applied to lean burn combustors places impingement and effusion arrays on the cold and hot skins respectively for cooling of both sides of the hot liner skin. Although impingement cooling is well established as a means of promoting forced convection cooling, there are many areas on a liner tile where cooling behaviour is not well characterised. Additionally, film cooling reduces combustive efficiency and increases the production of NOx and CO, prompting interest in reducing its use in combustor cooling. The research for this thesis has focussed on investigations into current and proposed geometries to identify methods to enhance cold side cooling in lean burn applications. A fully modelled combustor liner tile has been used for investigation into the impact of structural and pressure blockages on cold side cooling performance of an impingementeffusion array using a transient liquid crystal technique to measure heat transfer performance. Research has found structural blockages can reduce heat transfer performance to ~60% of typical values, with crossflow development due to pressure blockage producing similar reductions in Nusselt values to ~70% of typical. A second investigation explored enhanced cooling geometries combining a distributed impingement feed over roughened channels of pedestals at variable height (H/D) and pitch (P/D). A newly proposed 'Shielded Impingement' concept combines full height pedestals, to protect impingement jets from developing crossflow, with quarter height pedestals for turbulence enhancement of crossflow cooling. The research has found that Shielded Impingement geometries displayed the strongest cooling performance of all tested designs due primarily to increased downstream Nusselt numbers. Pressure losses were comparable to short pedestal geometries, with little apparent effect of full height pedestals. Low pressure losses mean that application to extended channels in line with the full tile geometry is possible.
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Hull, David Richard. "Combustion technology in the lean-burn spark-ignition engines." Thesis, Imperial College London, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.244514.

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Pashley, Nicholas C. "Ignition systems for lean burn gas engines." Thesis, University of Oxford, 1997. http://ora.ox.ac.uk/objects/uuid:b5fcf2d4-b27b-4b3b-a593-ee307ec80f3a.

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This thesis describes an experimental investigation into ignition systems, their effects on the combustion process, and how the discharge is affected by the prevailing pressure, temperature and flow. The work is divided into four main areas, a comprehensive literature review, engine testing for ignition system suitability, non-flow rig testing (including erosion) and flow rig testing. The literature review concluded that the most practical ignition system for lean burn gas engines will continue to be based on the spark plug, but in the medium to long term, laser ignition may become viable. The measurement of the HT voltage and current is not straightforward, and appropriate methods have been identified. Capacitive and inductive ignition system types were compared in lean and diluted conditions on a single cylinder research engine of modern design at different engine loads and speeds. It was found that the most beneficial ignition system was an inductive ignition system, although that for some conditions, capacitive systems induced better engine performance with a fraction of the stored energy of the inductive alternative. Non flow tests showed that the early part of the spark discharge is sensitive to pressure and temperature effects, and as a consequence, the latter stages of the discharge are also affected. A correlation has been developed, for use with conventional nickel electrode spark plugs, to predict breakdown voltage as a function of pressure, temperature and gap. Experiments were carried out at elevated pressures in a stream of flowing air with capacitive and inductive ignition systems. Different electrode designs and orientations were also compared. It was shown that when exposed to a flow field, the discharge can be stretched which results in a shortened spark duration; in some cases the electrode can shield the discharge from flow field effects. This work showed that flow through the spark gap is a hindrance to the spark process, especially for longer duration systems. However for flame kernel growth, the literature review identified that flow is beneficial, serving to convect the kernel away from the electrodes, reducing the heat transfer from the flame. Analysis of the glow voltage history in the pressurised flow rig has been used to develop a correlation relating the voltage, current, flow velocity, pressure and time. This correlation was used to analyse the velocity records from the spark plug in a firing engine. The predicted velocities and turbulence intensity were in agreement with independent measurements.
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Goldwitz, Joshua A. (Joshua Arlen) 1980. "Combustion optimization in a hydrogen-enhanced lean burn SI engine." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/27061.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2004.
Includes bibliographical references (p. 95-97).
Lean operation of spark ignition (SI) automotive engines offers attractive performance incentives. Lowered combustion temperatures inhibit NO[sub]x pollutant formation while reduced manifold throttling minimizes pumping losses, leading to higher efficiency. These benefits are offset by the reduced combustion speed of lean mixtures, which can lead to high cycle-to-cycle variation and unacceptable engine behavior characteristics. Hydrogen-enhancement can suppress the undesirable consequences of lean operation by accelerating the combustion process, thereby extending the "lean limit." Hydrogen can be produced onboard the vehicle with a plasmatron fuel reformer device. Combustion optimization experiments focused on three key areas: the ignition system, charge motion in the inlet ports, and mixture preparation. The ignition system tests compared a standard inductive coil scheme against high-energy discharge systems. Charge motion experiments focused on the impact of turbulence patterns generated by conventional restrictor plates as well as novel inlet flow modification cones. The turbulent motion of each configuration was characterized using swirl and tumble flow benches. Mixture preparation tests compared a standard single-hole pintle injector against a fine atomizing 12-hole injector. Lastly, a further series of trials was also run to investigate the impact of high exhaust gas recirculation (EGR) dilution rates on combustion stability. Results indicate that optimizations of the combustion system in conjunction with hydrogen-enhancement can extend the lean limit of operation by roughly 25% compared against the baseline configuration. Nearly half of this improvement may be attributed to improvements in the combustion system.
(cont.) An inductive ignition system in conjunction with a high tumble-motion inlet configuration leads to the highest levels of combustion performance. Furthermore, hydrogen enhancement affects a nearly constant absolute improvement in the lean misfire limit regardless of baseline combustion behavior. Conversely, the amount of improvement in the point of peak engine NIMEP output is inversely related to the level of baseline performance.
by Joshua A. Goldwitz.
S.M.
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Yates, D. A. "Hydrocarbon sampling from the combustion chamber of a lean burn engine." Thesis, Coventry University, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.374271.

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Hickman, David Gary. "A study of lean burn combustion in a spark ignition engine." Thesis, University of Newcastle Upon Tyne, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.388654.

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Gidney, Jeremy. "The performance stability of a homogeneous charge lean-burn spark-ignition engine." Thesis, University of Liverpool, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.303644.

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Lake, Timothy Hugh. "Gasoline combustion systems for improved fuel economy and emissions." Thesis, University of Brighton, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.302289.

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This document is the statement of independent and original contribution to knowledge represented by the published works in partial fulfilment of the requirements of the University of Brighton for the degree of Doctor of Philosophy (by publication). The thesis reviews the impact of research work conducted between 1992 and 1998 on various concepts to improve the economy and emissions of gasoline engines in order to address environmental and legislative pressures. The research has a common theme, examining the dilution of the intake charge (with either recycled exhaust gas [EGR], excess air, or the two in combination) in both conventional port injected [MPI] and direct injection [G-DI] combustion systems. After establishing the current status of gasoline engine technology before the programme of research was started, the thesis concentrates on seven major pieces of research between 1992 and 1996. These explored a subsequently patented method of applying recycled exhaust gas to conventional port injected gasoline engines to improve their economy and emissions whilst staying compatible with three-way catalyst systems. Nine other studies are reviewed which took place between 1992 and 1999 covering other methods of improving gasoline engines, specifically direct injection and two-stroke operation. Together, all the studies provide a treatise on methods to improve the gasoline engine and the thesis allows a view from a broader perspective than was possible at the time each study was conducted. In particular, the review identifies a range of strategies that use elements of the research that can be used to improve economy and emissions. Four major categories of systems researched include: conventional stoichiometric MPI engines developed to tolerate high EGR rates [CCVS]; two-stroke G-DI engines; G-DI engines operating stoichiometrically with high EGR rates; and G-DI engines operating with high dilution from both excess air and EGR. The findings of the studies illustrate that although good fuel economy improvements and emissions can be obtained with EGR dilution of stoichiometric engines, the highest fuel economy improvements require lean deNOx aftertreatment [LNA] and these, in turn, require new aftertreatment technologies and preferably new fuel specifications. The development of suitable LNA and the cost of implementation of these approaches represents one of the main barriers to improving gasoline engine fuel economy and emissions.
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Norum, Viggo Lauritz. "Analysis of Ignition and Combustion in Otto Lean-Burn Engines with Prechambers." Doctoral thesis, Norwegian University of Science and Technology, Department of Marine Technology, 2008. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-2185.

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Otto-engines in which the combustion chamber has richer fuel/air mix close to the ignition source and leaner charge further away from the ignition source are often called "stratified charge engines". Stratified charge can be used to increase the combustion speed in an internal combustion engine and thereby enable the engine to run on a fuel/air mix that would normally burn too slowly or not burn at all. The use of prechambers is one way to obtain stratified charge.

This thesis presents and uses methods for studying a prechamber more or less indepently from the rest of the engine.

When the prechamber is studied like an engine of itself, then the output of the "engine" is not mechanical power, but rather one or more hot jets into the main chamber. "Prechamber efficiencies" can be defined based on how much of the initial chemical energy is delivered as kinetic or thermal energy into the main chamber. Models of other important characteristics including the jet length and duration are also presented and used.

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Books on the topic "Lean burn combustor"

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Institution of Mechanical Engineers (Great Britain). Combustion Engines Group., ed. Lean burn combustion engines: 3-4 December 1996. Bury St. Edmunds: Published by Mechanical Engineering Publications Limited for the Institution of Mechanical Engineers, 1996.

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Lean Burn Combustion Engines (IMechE Seminar Publications). Society of Automotive Engineers Inc, 1997.

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Evans, R. L. Combustion chamber design for a Lean-Burn SI engine. Society of Automotive Engineers., 1992.

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Beyerlein, Steven W. Catalytic charge activation in a lean-burn internal combustion engine. 1987.

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Ahmadi-Befrui, B. Calculation of inhomogeneous-charge combustion in a swirl-assisted Lean-Burn engine. Society of Automotive Engineers, 1991.

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Book chapters on the topic "Lean burn combustor"

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Luszcz, Pawel, K. Takeuchi, P. Pfeilmaier, M. Gerhardt, P. Adomeit, A. Brunn, C. Kupiek, and B. Franzke. "Homogeneous lean burn engine combustion system development – Concept study." In Proceedings, 205–23. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-21194-3_19.

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Kalwar, Ankur, and Avinash Kumar Agarwal. "Lean-Burn Combustion in Direct-Injection Spark-Ignition Engines." In Energy, Environment, and Sustainability, 281–317. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-1513-9_12.

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Suzuki, Takanori, Bastian Lehrheuer, Tamara Ottenwälder, Max Mally, and Stefan Pischinger. "Combustion stability improvement with turbulence control by air injection for a lean-burn SI engine." In Proceedings, 214–28. Wiesbaden: Springer Fachmedien Wiesbaden, 2019. http://dx.doi.org/10.1007/978-3-658-25939-6_19.

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Rapp, V., N. Killingsworth, P. Therkelsen, and R. Evans. "Lean-Burn Internal Combustion Engines." In Lean Combustion, 111–46. Elsevier, 2016. http://dx.doi.org/10.1016/b978-0-12-804557-2.00004-3.

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Evans, Robert L. "Lean-Burn Spark-Ignited Internal Combustion Engines." In Lean Combustion, 95–120. Elsevier, 2008. http://dx.doi.org/10.1016/b978-012370619-5.50005-4.

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Couto, Luíza Camargos, Maria Clara Martins Avelar, Vitória Bernardes, and Lamara Laguardia Valente Rocha. "Inhalation of Toxic Gases in the Kiss Nightclub Disaster: an Example of Inhalation Injury from Indoor Fires." In COLLECTION OF INTERNATIONAL TOPICS IN HEALTH SCIENCE- V1. Seven Editora, 2023. http://dx.doi.org/10.56238/colleinternhealthscienv1-003.

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The Kiss Nightclub disaster, which occurred on January 27, 2013, in Santa Maria, Brazil, had an impact both on a national and global scale, as it was an accident with 230 immediate fatalities and can be compared to other indoors fires. In addition to bodily burns, inhalation injuries stood out, that is, thermal injuries of the airway, chemical injuries and intoxication by toxic gases. Carbon monoxide and cyanide are the main toxic gases produced in indoor fire situations and are formed from the incomplete combustion of hydrocarbons and carbonaceous and nitrogenous materials, respectively. While carbon monoxide, at high concentrations in the blood, promotes a shift of the oxyhemoglobin curve to the left and a consequent hypoxia condition, cyanide blocks the respiratory cycle, activating anaerobic respiration and evolving to an excessive production of lactic acid, which can lead the victim to death. Considering that in the accident of Santa Maria 169 individuals were hospitalized in a critical condition, it is necessary to understand the consequences and pathophysiology of inhalation injuries, being that the focus of this narrative review is the knowledge about poisoning by toxic gases. Moreover, it is essential to discuss proper diagnosis and treatment, in order to improve the prognosis of future victims of new fires in closed environments. Therefore, having knowledge about the potential causes of indoor fires helps in the prevention of similar disasters to the one that happened in the Kiss Nightclub.
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McElroy, Michael B. "Natural Gas : The Least Polluting Of The Fossil Fuels." In Energy and Climate. Oxford University Press, 2016. http://dx.doi.org/10.1093/oso/9780190490331.003.0012.

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In terms of emissions from combustion, natural gas, composed mainly of methane (CH4), is the least polluting of the fossil fuels. Per unit of energy produced, CO2 emissions from natural gas are 45.7% lower than those from coal (lignite), 27.5% lower than from diesel, and 25.6% lower than from gasoline. As discussed by Olah et al. (2006), humans have long been aware of the properties of natural gas. Gas leaking out of the ground would frequently catch fire, ignited, for example, by lightning. A leak and a subsequent fire on Mount Parnassus in Greece more than 3,000 years ago prompted the Ancient Greeks to attach mystical properties to the phenomenon— a flame than could burn for a long time without need for an external supply of fuel. They identified the location of this gas leak with the center of the Earth and Universe and built a temple to Apollo to celebrate its unique properties. The temple subsequently became the home for the Oracle of Delphi, celebrated for the prophecies inspired by the temple’s perpetual flame. The first recorded productive use of natural gas was in China, dated at approximately 500 BC. A primitive pipeline constructed using stems of bamboo was deployed to trans¬port gas from its source to a site where it could be used to boil brine to produce both economically valuable salt and potable water. Almost 2,000 years would elapse before natural gas would be tapped for productive use in the West. Gas from a well drilled near Fredonia, New York, was used to provide an energy source for street lighting in 1821. The Fredonia Gas Light Company, formed in 1858, was the first commercial entity established specifically to market natural gas. Joseph Newton Pew, founder of the Sun Oil Company (now Sunoco), established a company in 1883 to deliver natural gas to Pittsburgh, where it was used as a substitute for manufactured coal gas (known also as town gas). Pew later sold his interests in natural gas to J. D. Rockefeller’s Standard Oil. The early application of natural gas was primarily for lighting, not only for streets but also for factories and homes.
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Conference papers on the topic "Lean burn combustor"

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Bertini, D., L. Mazzei, A. Andreini, and B. Facchini. "Multiphysics Numerical Investigation of an Aeronautical Lean Burn Combustor." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91437.

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Abstract The importance of the combustion chamber has been underestimated for years by aeroengine manufacturers that focused their research efforts mainly on other components, such as compressor and turbine, to improve the engine performance. Nevertheless, stricter requirements on pollutant emissions have contributed to increase the interest on combustor development and, nowadays, new design concepts are widely investigated. To meet the goals of ACARE FlightPath 2050 and future ICAO-CAEP standards one of the most promising results is provided by the Lean Burn technology. As this combustion mode is based on a lean Primary Zone, the air devoted to liner cooling is restricted and advanced cooling systems must be exploited to obtain higher overall effectiveness. The pushing trends of Turbine Inlet Temperature and Overall Pressure Ratio in modern aeroengine are not supported enough by the development of materials, thus making the research branch of liner cooling increasingly relevant. In this context, Computational Fluid Dynamics is able to predict the flow field and the complex interactions between the involved phenomena, supporting the design of modern Lean Burn combustors in all stages of the process. RANS approaches provide a solution of the problem with low computational cost, but can lack in accuracy when the flow unsteadiness dominates the fluid dynamics and the strong interactions, as in aeroengine combustors. Even if steady simulations can be easily employed in the preliminary design, their inaccuracy can be detrimental for an optimized combustor design and Scale-Resolving methods should be preferred, at least, in the final stages. Unfortunately, having to deal with a multiphysics problem as Conjugate Heat Transfer (CHT) in presence of radiation, these simulations can become computationally expensive and some numerical treatments are required to handle the wide range of time and space scales in an unsteady framework. In the present work the metal temperature distribution is investigated from a numerical perspective on a full annular aeronautical lean burn combustor operated at real conditions. For this purpose, the U-THERM3D multiphysics tool was developed in ANSYS Fluent and applied on the test case. The results are compared against RANS and experimental data to assess the tool capability to handle the CHT problem in the context of scale-resolving simulations.
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Wey, Changju T. "Lean Blowout (LBO) Simulations in a Rich-Burn Quick-Quench Lean-Burn (RQL) Gas Turbine Combustor." In AIAA Propulsion and Energy 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3694.

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Andreini, Antonio, Riccardo Becchi, Bruno Facchini, Lorenzo Mazzei, Alessio Picchi, and Antonio Peschiulli. "Effusion Cooling System Optimization for Modern Lean Burn Combustor." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57721.

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Stricter legislation limits concerning NOx emissions are leading main aero-engine manufacturers to update the architecture of the combustors towards the implementation of lean burn combustion concept. Cooling air availability for the thermal management of combustor liners is significantly reduced, demanding even more effective liner cooling schemes. The state-of-the-art of liner cooling technology is represented by effusion cooling, consisting in a very efficient cooling strategy based on multi-perforated liners, where metal temperature is lowered by the combined protective effect of coolant film and heat removal inside the holes. The present research study aims at deepening the knowledge of effusion systems, exploiting the results of a thorough experimental campaign carried out in two different planar test rigs, equipped with a complete liner cooling scheme composed by slot injection and effusion array. The film cooling protection was analysed using PSP (Pressure Sensitive Paint) technique, while the effect of cooling injection and extraction from the annulus on heat transfer distribution were studied by means of TLC (Thermochromic Liquid Crystals) thermography. Thermal measurements were supported by flow field investigation with standard 2D PIV (Particle Image Velocimetry) in order to highlight the typical velocity distributions generated by a realistic lean injector. These detailed experimental data were exploited in a 1D thermal flow-network solver that allows to better assess the main cooling mechanisms characterising the proposed cooling system. Moreover, an optimized cooling configuration with enhanced back-side convective cooling was proposed and compared with the standard configuration in terms of metal temperature and cooling consumption.
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Andreini, Antonio, Bruno Facchini, Andrea Giusti, Ignazio Vitale, and Fabio Turrini. "Thermoacoustic Analysis of a Full Annular Lean Burn Aero-Engine Combustor." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94877.

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In order to reduce NOx emissions, modern gas turbines are often equipped with lean burn combustion systems, where the engine operates near the lean blow-out limits. One of the most critical issues of lean combustion technology is the onset of combustion instabilities related to a coupling between pressure oscillations and thermal fluctuations excited by the unsteady heat release. In this work a thermoacoustic analysis of a full annular combustor developed by AVIO is discussed. The system is equipped with an advanced PERM (Partially Evaporating and Rapid Mixing) injection system based on a piloted lean burn spray flame generated by a pre-filming atomizer. Combustor walls are based on multi-perforated liners to control metal temperature: these devices are also recognized as very effective sound absorbers, thus in innovative lean combustors they could represent a good means both for wall cooling and damping combustion instabilities. The performed analysis is based on the resolution of the eigenvalue problem related to an inhomogeneous wave equation which includes a source term representing heat release fluctuations (the so called Flame Transfer Function, FTF) in the flame region using a three-dimensional FEM code. A model representing the entire combustor was assembled including all the acoustically relevant geometrical features. In particular, the acoustic effect of multi-perforated liners was introduced by modeling the corresponding surfaces with an equivalent internal impedance. Different simulations with and without the presence of the flame were performed analyzing the influence of the multi-perforated liners. Furthermore, different modeling approaches for the FTF were examined and compared with each other. Comparisons with available experimental data showed a good agreement in terms of resonant frequencies in the case of passive simulations. On the other hand, when the presence of the flame is considered, comparisons with experiments showed the inadequacy of FTFs commonly used for premixed combustion and thus the necessity of an improved FTF, more suitable for liquid fueled gas turbines where the evaporation process could play an important role in the flame heat release fluctuations.
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Andreini, A., B. Facchini, L. Mazzei, L. Bellocci, and F. Turrini. "Assessment of Aero-Thermal Design Methodology for Effusion Cooled Lean Burn Annular Combustors." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26764.

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Increasingly stringent limitations imposed on aircraft engine emissions have led many manufacturers toward lean combustion technology, which involves a relevant increase in mass flow rate dedicated to primary combustion, leading as a consequence to a reduction of air dedicated to cooling of liners. One of the most promising cooling techniques in such conditions is represented by effusion cooling, which consists of an array of closely spaced discrete film cooling holes. This cooling method is based on a protective layer of cooling flow on the hot side of the liner, enhancing at the same time the heat removal within the holes. In the latest years many aero engine manufacturers have increased the research and technology investment on this combustion technology. Working in partnership with the University of Florence, specific component design tools and experimental techniques have been improved by Avio Aero for combustor gas turbine investigation. From a design perspective, CFD analysis has become a key tool up to the early stages of novel combustor design process, producing affordable direct 3D optimization of combustor aerodynamics. Nevertheless, a RANS simulation of even only a single sector of an annular combustor still presents a challenge when the cooling system is taken into account. This issue becomes more critical in case of modern effusion cooled combustors, which may contain up to two thousand holes for the single sector. For this reason, many efforts have been devoted to develop methodologies based on film cooling modeling. Among the approaches published in the literature, models based on local sources represent a good compromise between simplicity and accuracy, with the capability to automatically perform a Conjugate Heat Transfer analysis. This type of methodology has been already defined and validated by the authors, with comparison on effusion cooled plates in terms of experimental overall effectiveness measurements as well as the application on a tubular combustor test case. In the context of this work, the proposed approach has been applied to the analysis of a lean annular combustor with the purpose of investigating pressure losses, flow split and metal temperature field. The results obtained have been compared to experimental data and different numerical tools exploited during the preliminary design of these devices.
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Soworka, T., M. Gerendas, R. L. G. M. Eggels, and Epaminondas Mastorakos. "Numerical Investigation of Ignition Performance of a Lean Burn Combustor at Sub-Atmospheric Conditions." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-25644.

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Stringent environmental requirements are pushing the current development of aero gas turbine combustors towards lean combustion concepts with relatively small combustor volume. This approach has a detrimental effect on the high altitude relight capability of an aeronautical engine. But the ability to light up at a specific altitude is one of the certification requirements that an engine has to fulfil. To ensure the relight capability, extensive testing for new combustor developments is needed. These test set-ups are expensive as they have to be conducted at sub-atmospheric conditions. Thus, the use of a simple tool to evaluate the ignition tendency of a combustor at an early development stage is advantageous. The code SPINTHIR, developed by Cambridge University, is capable of calculating the ignition performance in turbulent spray flames in a simplified approach. It has been previously validated for different types of flames and applications. In order to adjust the code for lean burn combustors, a new function for a better resemblance of the turbulent spray dispersion has been introduced and the high sensitivity towards cell sizes has been balanced by modifying the ignition criteria. Finally, the results of the code have been compared in this work with recently obtained ignition test performed by Rolls-Royce. Thereby, the influence of varying combustor geometries on the lean ignition limit has been tested. In comparison with these tests, the code’s results show very good matches which verify the conducted changes and give further credence to the model.
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Lazik, W., Th Doerr, S. Bake, R. v. d. Bank, and L. Rackwitz. "Development of Lean-Burn Low-NOx Combustion Technology at Rolls-Royce Deutschland." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-51115.

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Lean-burn combustion technology is identified to be the key technology for aero-engine combustion systems to achieve future legislative requirements for NOx. The lean-burn low NOx combustor development at Rolls-Royce Deutschland RRD for the upcoming generation of aero-engines is presented, which has been supported by the German aeronautical research programme. The down selection process of different injector concepts is described in detail to develop lean-burn fuel injection technology up to a technology level for engine application. Initial concept validation with testing on single sector combustion rigs applying advanced laser measurement techniques is followed by high power single sector emission tests to prove low emission characteristics. Climbing the level of technology readiness, which is in each phase substantiated by intense CFD simulations, the most promising low emissions design concepts have been investigated for unrestricted combustor operability compared to conventional rich burn systems. Altitude relight, weak extinction margins, fuel staging optimisation and combustion efficiency in the vicinity of staging points have been optimised on different sub-atmospheric, atmospheric, medium and high-pressure test vehicles. The validation process concludes with sub-atmospheric and high-pressure testing within a fully annular test environment before the final lean-burn fuel injector configuration has been selected for core engine testing to prove emission performance and operability of the fuel-staged combustion system. Two fuel injector configurations were successfully tested in a high-pressure fully annular rig. The combustor module and both injector standards have been cleared for core engine operation.
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Micklow, Gerald J., Subir Roychoudhury, H. Lee Nguyen, and Michael C. Cline. "Emissions Reduction by Varying the Swirler Airflow Split in Advanced Gas Turbine Combustors." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-110.

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A rich burn/quick mix/lean burn (RQL) combustor concept for reducing pollutant emissions is currently under investigation at the NASA Lewis Research Center (LeRC). A numerical study was performed to investigate the chemically reactive flow with liquid spray injection for the RQL combustor. The RQL combustor consists of an airblast atomizer fuel injector, a rich burn section, a converging connecting pipe, a quick mix zone, a diverging connecting pipe and a lean combustion zone. For computational efficiency, the combustor was split into two sub systems, i.e. the fuel nozzle/rich burn section and the quick mix/lean burn section. The current study investigates the effect of varying the mass flow rate split between the swirler passages for an equivalence ratio of 2.0 on fuel distribution, temperature distribution, and emissions for the fuel nozzle/rich burn section of an RQL combustor. The input conditions used in the study were chosen based on tests completed at LeRC. It is seen that optimizing these parameters can substantially improve combustor performance and reduce combustor emissions. The optimal mass flow rate split for reducing NOx emissions based on the numerical study was the same as found by experiment at LeRC.
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Stiehl, Bernhard, Tyler Worbington, Alexander Miegel, Scott Martin, Carlos Velez, and Kareem Ahmed. "Combustion and Emission Characteristics of a Lean Axial-Stage Combustor." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91796.

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Abstract Gas turbine engines with high operational flexibility represent an important area of research. In support of this, the stage change of NOx emissions at high-temperature, full-load conditions are the main target of this research study. To overcome the challenge of decreasing the residence time of hot exhaust gas in the burner, the approach of axial-staged combustion has been used, which aims to burn at lean conditions. A main combustion stage with a conventional burner is followed by a jet-in-crossflow (JIC) stage downstream. This second combustion stage, the test section, burns well over a third of the total fuel amount, which is added by a jet inlet. The entire combustor is designed to run at a pressure of 5 bar, featuring a challenging point of experimental operation. Hence, a steady Computational Fluid Dynamics (CFD) model was created in Star-CCM+ to analyze the JIC stage. A structured mesh grid with local refinement domains was used along with RANS equations, Realizable k-ε turbulence, Complex Chemistry model with Laminar Flame Concept (LFC) applied. The findings of the computational model include a detailed description of the flow field, focusing on vortex formation and penetration depth. Three vortex types and local pressure losses in the shear domain were identified. Results were compared with similar data from literature and a very good match was proven. Optical laser diagnostics should work well to capture the predicted flow penetration. The highest local reaction rates were observed inside a thin flame front between 4 and 6 diameters downstream of the jet. The jet showed a limited expansion into the available channel domain, resulting in a low total heat release and a methane conversion of 52%. Along with production of just under 1% CO, the potential of axial-staged combustion has been outlined by two boundary cases, using either equilibrium main burner stage NOx, which showed a reduction of high incoming NOx, or setting incoming NOx fractions to zero, which yielded a total production of only 17 ppm NOx in the JIC stage.
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Liu, Haoyang, Wenkai Qian, Min Zhu, and Suhui Li. "Kinetics Modeling on NOx Emissions of a Syngas Turbine Combustor Using RQL Combustion Method." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-90826.

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Abstract To avoid flashback issues of the high-H2 syngas fuel, current syngas turbines usually use non-premixed combustors, which have high NOx emissions. A promising solution to this dilemma is RQL (rich-burn, quick-mix, lean-burn) combustion, which not only reduces NOx emissions, but also mitigates flashback. This paper presents a kinetics modeling study on NOx emissions of a syngas-fueled gas turbine combustor using RQL architecture. The combustor was simulated with a chemical reactor network model in CHEMKIN-PRO software. The combustion and NOx formation reactions were modeled using a detailed kinetics mechanism that was developed for syngas. Impacts of combustor design/operating parameters on NOx emissions were systematically investigated, including combustor outlet temperature, rich/lean air flow split and residence time split. The mixing effects in both the rich-burn zone and the quick-mix zone were also investigated. Results show that for an RQL combustor, the NOx emissions initially decrease and then increase with combustor outlet temperature. The leading parameters for NOx control are temperature-dependent. At typical modern gas turbine combustor operating temperatures (e.g., < 1890 K), the air flow split is the most effective parameter for NOx control, followed by the mixing at the rich-burn zone. However, as the combustor outlet temperature increases, the impacts of air flow split and mixing in the rich-burn zone on NOx reduction become less pronounced, whereas both the residence time split and the mixing in the quick-mix zone become important.
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Reports on the topic "Lean burn combustor"

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Shahrokh Etemad, Lance Smith, and Kevin Burns. System Study of Rich Catalytic/Lean burn (RCL) Catalytic Combustion for Natural Gas and Coal-Derived Syngas Combustion Turbines. Office of Scientific and Technical Information (OSTI), December 2004. http://dx.doi.org/10.2172/886021.

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Effect of Spark Discharge Duration and Timing on the Combustion Initiation in a Lean Burn SI Engine. SAE International, April 2021. http://dx.doi.org/10.4271/2021-01-0478.

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Meeting the increasingly stringent emission and fuel efficiency standards is the primary objective of the automotive research. Lean/diluted combustion is a promising avenue to realize high-efficiency combustion and reduce emissions in SI engines. Under the diluted conditions, the flame propagation speed is reduced because of the reduced charge reactivity. Enhancing the in-cylinder charge motion and turbulence, and thereby increasing the flame speed, is a possible way to harness the combustion process in SI engines. However, the charge motion can have a significant effect on the spark ignition process because of the reduced discharge duration and frequent restrikes. A longer discharge duration can aid in the formation of the self-sustained flame kernel and subsequent stable ignition. Therefore, an empirical study is undertaken to investigate the effect of the discharge duration and ignition timing on the ignition and early combustion in a port fueled SI engine, operated under lean conditions. The discharge duration is modulated from 1 ms to 8 ms through a continuous discharge strategy. The discharge current and voltage measurements are recorded during the engine operation to characterize the discharge process. The in-cylinder charge is diluted using fresh air to achieve lean combustion. The in-cylinder pressure measurement and heat release analysis are used to investigate the ignition and combustion characteristics of the engine. Preliminary results indicate that while the discharge duration has a marginal effect on the ignition delay, cyclic variations are notably impacted.
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