Log in

Relevant bibliographies by topics / Swirl combustor

Contents

Journal articles
Dissertations / Theses
Books
Book chapters
Conference papers
Reports

Academic literature on the topic 'Swirl combustor'

Author: Grafiati

Published: 4 June 2021

Last updated: 11 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Swirl combustor.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Swirl combustor"

1

Pan, J. F., Z. Y. Hou, Y. X. Liu, A. K. Tang, J. Zhou, X. Shao, Z. H. Pan, and Q. Wang. "Design and working performance study of a novel micro parallel plate combustor with two nozzles for micro thermophotovotaic system." Thermal Science 19, no. 6 (2015): 2185–94. http://dx.doi.org/10.2298/tsci141109069p.

Full text

Abstract:

Micro-combustors are a key component in combustion-driven micro power generators, and their performance is significantly affected by their structure. For the application of micro-thermophotovoltaic (MTPV) system, a high and uniform temperature distribution along the walls of the micro combustor is desired. In this paper, a three-dimensional numerical simulation has been conducted on a new-designed parallel plate micro combustor with two nozzles. The flow field and the combustion process in the micro combustor, and the temperature distribution on the wall as well as the combustion efficiency were obtained. The effects of various parameters such as the inlet angle and the fuel volumetric flow rate on the performance of the micro combustor were studied. It was observed that a swirl formed in the center of the combustor and the radius of the swirl increased with the increase of the inlet rate, and the best working condition was achieved at the inlet angle ?=20?. The results indicated that the two-nozzle combustion chamber had a higher and more uniform mean temperature than the conventional combustor under the same condition.

APA, Harvard, Vancouver, ISO, and other styles

2

Durbin, M. D., M. D. Vangsness, D. R. Ballal, and V. R. Katta. "Study of Flame Stability in a Step Swirl Combustor." Journal of Engineering for Gas Turbines and Power 118, no. 2 (April 1, 1996): 308–15. http://dx.doi.org/10.1115/1.2816592.

Full text

Abstract:

A prime requirement in the design of a modern gas turbine combustor is good combustion stability, especially near lean blowout (LBO), to ensure an adequate stability margin. For an aeroengine, combustor blow-off limits are encountered during low engine speeds at high altitudes over a range of flight Mach numbers. For an industrial combustor, requirements of ultralow NOx emissions coupled with high combustion efficiency demand operation at or close to LBO. In this investigation, a step swirl combustor (SSC) was designed to reproduce the swirling flow pattern present in the vicinity of the fuel injector located in the primary zone of a gas turbine combustor. Different flame shapes, structure, and location were observed and detailed experimental measurements and numerical computations were performed. It was found that certain combinations of outer and inner swirling air flows produce multiple attached flames, aflame with a single attached structure just above the fuel injection tube, and finally for higher inner swirl velocity, the flame lifts from the fuel tube and is stabilized by the inner recirculation zone. The observed difference in LBO between co- and counterswirl configurations is primarily a function of how the flame stabilizes, i.e., attached versus lifted. A turbulent combustion model correctly predicts the attached flame location(s), development of inner recirculation zone, a dimple-shaped flame structure, the flame lift-off height, and radial profiles of mean temperature, axial velocity, and tangential velocity at different axial locations. Finally, the significance and applications of anchored and lifted flames to combustor stability and LBO in practical gas turbine combustors are discussed.

APA, Harvard, Vancouver, ISO, and other styles

3

Barmina, I., R. Valdmanis, and M. Zaķe. "Control of the Development of Swirling Airflow Dynamics and Its Impact on Biomass Combustion Characteristics." Latvian Journal of Physics and Technical Sciences 54, no. 3 (June 27, 2017): 30–39. http://dx.doi.org/10.1515/lpts-2017-0018.

Full text

Abstract:

AbstractThe development of the swirling flame flow field and gasification/ combustion dynamics at thermo-chemical conversion of biomass pellets has experimentally been studied using a pilot device, which combines a biomass gasifier and combustor by varying the inlet conditions of the fuel-air mixture into the combustor. Experimental modelling of the formation of the cold nonreacting swirling airflow field above the inlet nozzle of the combustor and the upstream flow formation below the inlet nozzle has been carried out to assess the influence of the inlet nozzle diameter, as well primary and secondary air supply rates on the upstream flow formation and air swirl intensity, which is highly responsible for the formation of fuel-air mixture entering the combustor and the development of combustion dynamics downstream of the combustor. The research results demonstrate that at equal primary axial and secondary swirling air supply into the device a decrease in the inlet nozzle diameter enhances the upstream air swirl formation by increasing swirl intensity below the inlet nozzle of the combustor. This leads to the enhanced mixing of the combustible volatiles with the air swirl below the inlet nozzle of the combustor providing a more complete combustion of volatiles and an increase in the heat output of the device.

APA, Harvard, Vancouver, ISO, and other styles

4

Hwang, Donghyun, and Kyubok Ahn. "Experimental Study on Dynamic Combustion Characteristics in Swirl-Stabilized Combustors." Energies 14, no. 6 (March 14, 2021): 1609. http://dx.doi.org/10.3390/en14061609.

Full text

Abstract:

An experimental study was performed to investigate the combustion instability characteristics of swirl-stabilized combustors. A premixed gas composed of ethylene and air was burned under various flow and geometric conditions. Experiments were conducted by changing the inlet mean velocity, equivalence ratio, swirler vane angle, and combustor length. Two dynamic pressure sensors, a hot-wire anemometer, and a photomultiplier tube were installed to detect the pressure oscillations, velocity perturbations, and heat release fluctuations in the inlet and combustion chambers, respectively. An ICCD camera was used to capture the time-averaged flame structure. The objective was to understand the relationship between combustion instability and the Rayleigh criterion/the flame structure. When combustion instability occurred, the pressure oscillations were in-phase with the heat release oscillations. Even if the Rayleigh criterion between the pressure and heat release oscillations was satisfied, stable combustion with low pressure fluctuations was possible. This was explained by analyzing the dynamic flow and combustion data. The root-mean-square value of the heat release fluctuations was observed to predict the combustion instability region better than that of the inlet velocity fluctuations. The bifurcation of the flame structure was a necessary condition for combustion instability in this combustor. The results shed new insight into combustion instability in swirl-stabilized combustors.

APA, Harvard, Vancouver, ISO, and other styles

5

Sivasegaram, S., and J. H. Whitelaw. "Combustion Oscillations in Dump Combustors with a Constricted Exit." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 202, no. 3 (May 1988): 205–10. http://dx.doi.org/10.1243/pime_proc_1988_202_108_02.

Full text

Abstract:

Combustion oscillations in axisymmetric dump combustors have been examined in terms of amplitude and frequency characteristics for two dump-plane area ratios and as a function of combustor length, exit constriction, diameter, flowrate, equivalence ratio and swirl. The flammability limits are similar to those previously determined in disc- and dump-stabilized flames without a constricted exit, but the stability limits are not. Rough combustion, characterized by radiated sound levels more than 12 dB above that in smooth combustion, was observed at equivalence ratios close to the flammability limits for values of swirl number less than 0.2 and was associated with the bulk-mode frequency. With swirl numbers in the range from 0.2 to 0.4, rough combustion was not encountered and, for higher values, existed in a range of equivalence ratios from around 0.8 to 1.4, provided the combustor length and flowrate led to half-wave frequencies less than around 800 Hz. In those ranges of equivalance ratio where the combustion was smooth, discrete frequencies corresponding to the bk-mode and half-wave were observed. The amplitude of the discrete frequency increased when it coincided with the shedding frequency of the shear layer.

APA, Harvard, Vancouver, ISO, and other styles

6

Anand, M. S., and F. C. Gouldin. "Combustion Efficiency of a Premixed Continuous Flow Combustor." Journal of Engineering for Gas Turbines and Power 107, no. 3 (July 1, 1985): 695–705. http://dx.doi.org/10.1115/1.3239791.

Full text

Abstract:

Experimental data in the form of radial profiles of mean temperature, gas composition and velocity at the combustor exit and combustion efficiency are reported and discussed for a swirling flow, continuous combustor. The combustor is composed of two confined, concentric independently swirling jets: an outer, annular air jet and a central premixed fuel-air jet, the fuel being propane or methane. Combustion is stabilized by a swirl-generated central recirculation zone. The primary objective of this research is to determine the effect of fuel substitution and of changes in outer flow swirl conditions on combustor performance. Results are very similar for both methane and propane. Changes in outer flow swirl cause significant changes in exit profiles, but, surprisingly, combustion efficiency is relatively unchanged. A combustion mechanism is proposed which qualitatively explains the results and identifies important flow characteristics and physical processes determining combustion efficiency. It is hypothesized that combustion occurs in a thin sheet, similar in structure to a premixed turbulent flame, anchored on the combustor centerline just upstream of the recirculation zone and swept downstream with the flow. Combustion efficiency depends on the extent of the radial propagation, across mean flow streamtubes, of this reaction sheet. It is concluded that, in general, this propagation and hence efficiency are extremely sensitive to flow conditions.

APA, Harvard, Vancouver, ISO, and other styles

7

Yilmaz, Ilker, Harun Yilmaz, and Omer Cam. "An experimental study on premixed CNG/H2/CO2 mixture flames." Open Engineering 8, no. 1 (March 13, 2018): 32–40. http://dx.doi.org/10.1515/eng-2018-0003.

Full text

Abstract:

Abstract In this study, the effect of swirl number, gas composition and CO2 dilution on combustion and emission behaviour of CNG/H2/CO2 gas mixtures was experimentally investigated in a laboratory scale combustor. Irrespective of the gas composition, thermal power of the combustor was kept constant (5 kW). All experiments were conducted at or near stoichiometric and the local atmospheric conditions of the city of Kayseri, Turkey. During experiments, swirl number was varied and the combustion performance of this combustor was analysed by means of centreline temperature distributions. On the other hand, emission behaviour was examined with respect to emitted CO, CO2 and NOx levels. Dynamic flame behaviour was also evaluated by analysing instantaneous flame images. Results of this study revealed the great impact of swirl number and gas composition on combustion and emission behaviour of studied flames.

APA, Harvard, Vancouver, ISO, and other styles

8

Sharma, N. Y., and S. K. Som. "Influence of fuel volatility on combustion and emission characteristics in a gas turbine combustor at different inlet pressures and swirl conditions." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 216, no. 3 (May 1, 2002): 257–68. http://dx.doi.org/10.1243/095765002320183577.

Full text

Abstract:

The practical challenges in research in the field of gas turbine combustion mainly centre around a clean emission, a low liner wall temperature and a desirable exit temperature distribution for turboma-chinery applications, along with fuel economy of the combustion process. An attempt has been made in the present paper to develop a computational model based on stochastic separated flow analysis of typical diffusion-controlled spray combustion of liquid fuel in a gas turbine combustor to study the influence of fuel volatility at different combustor pressures and inlet swirls on combustion and emission characteristics. A κ-ɛ model with wall function treatment for the near-wall region has been adopted for the solution of conservation equations in gas phase. The initial spray parameters are specified by a suitable probability distribution function (PDF) size distribution and a given spray cone angle. A radiation model for the gas phase, based on the first-order moment method, has been adopted in consideration of the gas phase as a grey absorbing-emitting medium. The formation of thermal NO x as a post-combustion reaction process is determined from the Zeldovich mechanism. It has been recognized from the present work that an increase in fuel volatility increases combustion efficiency only at higher pressures. For a given fuel, an increase in combustor pressure, at a constant inlet temperature, always reduces the combustion efficiency, while the influence of inlet swirl is found to decrease the combustion efficiency only at higher pressure. The influence of inlet pressure on pattern factor is contrasting in nature for fuels with lower and higher volatilities. For a higher-volatility fuel, a reduction in inlet pressure decreases the value of the pattern factor, while the trend is exactly the opposite in the case of fuels with lower volatilities. The NOx emission level increases with decrease in fuel volatility at all combustor pressures and inlet swirls. For a given fuel, the NOx emission level decreases with a reduction in combustor pressure and an increase in inlet swirl number.

APA, Harvard, Vancouver, ISO, and other styles

9

Mahjoub, Mustafa, Aleksandar Milivojevic, Vuk Adzic, Marija Zivkovic, Vasko Fotev, and Miroljub Adzic. "Numerical analysis of lean premixed combustor fueled by propane-hydrogen mixture." Thermal Science 21, no. 6 Part A (2017): 2599–608. http://dx.doi.org/10.2298/tsci160717131m.

Full text

Abstract:

A numerical investigation of combustion of propane-hydrogen mixture in a swirl premixed micro gas turbine combustor is presented. The effects of hydrogen addition into propane on temperature distribution in the combustor, reaction rates of propane and hydrogen and NOx emissions for different equivalence ratios and swirl numbers are given. The propane-hydrogen mixture of 90/10% by volume was assumed. The numerical results and measurements of NOx emissions for pure propane are compared. Excellent agreements are found for all equivalence ratios and swirl numbers, except for the highest swirl number (1.13). It is found that the addition of hydrogen into propane increases NOx emission. On the other hand, the increase of swirl number and the decrease of equivalence ratio decrease the NOx emissions.

APA, Harvard, Vancouver, ISO, and other styles

10

Kang, D. M., F. E. C. Culick, and A. Ratner. "Combustion dynamics of a low-swirl combustor." Combustion and Flame 151, no. 3 (November 2007): 412–25. http://dx.doi.org/10.1016/j.combustflame.2007.07.017.

Full text

APA, Harvard, Vancouver, ISO, and other styles

More sources

Dissertations / Theses on the topic "Swirl combustor"

1

LI, GUOQIANG. "EMISSIONS, COMBUSTION DYNAMICS, AND CONTROL OF A MULTIPLE SWIRL COMBUSTOR." University of Cincinnati / OhioLINK, 2004. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1092767684.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Yellugari, Kranthi. "Effects of Swirl Number and Central Rod on Flow in Lean Premixed Swirl Combustor." University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1563872979440851.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Okon, Aniekan. "Combustion dynamics in a lean premixed combustor with swirl forcing and fuel conditions." Thesis, Cardiff University, 2017. http://orca.cf.ac.uk/108265/.

Full text

Abstract:

Fossil fuels still account for a large percentage of global energy demand according to available statistics. Natural gas is increasingly gaining the share of these fuels due to the retired coal and nuclear plants. The more stringent emission standards have also put natural gas ahead of other fuels as a result of its efficiency, cost, environmental attributes as well as the operational efficiency of the gas turbine, an engine that uses this fuel. A standard low emission combustion technique in gas turbines is the dry low NOx combustion, with lean fuel and fuel-air premixed upstream of the flame holder. However, this condition is highly susceptible to combustion instabilities characterised by large amplitude oscillations of the combustor’s acoustic modes excited by unsteady combustion processes. These pressure oscillations are detrimental both to the efficiency of performance as well as the hardware of the system. Although the processes and mechanisms that result in instabilities are well known, however, the current challenges facing gas turbine operators are the precise understanding of the operational conditions that cause combustion instabilities, accurate prediction of the instability modes and the control of the disturbances. In a bid to expand this knowledge frontier, this study uses a 100kW swirl premixed combustor to examine the evolution of the flow structures, its influence on the flame dynamics, in terms of heat release fluctuation and the overall effects on the pressure field, under different, swirl, fuel and external excitation conditions. The aim is to determine the operational conditions whose pressure oscillation is reduced to the barest minimum to keep the system in an excellent running condition. The results of this study are expected to contribute towards the design of a new control system to damp instabilities in gas turbines.

APA, Harvard, Vancouver, ISO, and other styles

4

Abdulsada, Mohammed. "Flashback and blowoff characteristics of gas turbine swirl combustor." Thesis, Cardiff University, 2011. http://orca.cf.ac.uk/24193/.

Full text

Abstract:

Gas turbines are extensively used in combined cycle power systems. These form about 20% of global power generating capacity, normally being fired on natural gas, but this is expected in the future to move towards hydrogen enriched gaseous fuels to reduce CO2 emissions. Gas turbine combined cycles can give electrical power generation efficiencies of up to 60%, with the aim of increasing this to 70% in the next 10 to 15 years, whilst at the same time substantially reducing emissions of contaminants such as NOx. The gas turbine combustor is an essential and critical component here. These are universally stabilized with swirl flows, which give very wide blowoff limits, and with appropriate modification can be adjusted to give very low NOx and other emission. Lean premixed combustion is commonly used at pressures between 15 to 30 bar, these even out hot spots and minimise formation of thermal NOx. Problems arise because improving materials technology/improved cooling techniques allow higher turbine inlet temperatures, hence higher efficiencies, but with the drawback of potentially higher emissions and stability problems. This PhD study has widely investigated and analysed two different kinds of gas turbine swirl burners. The research has included experimental investigation and computational simulation. Mainly, the flashback and blowoff limits have been comprehensively analysed to investigate their effect upon swirl burner operation. The study was extended by using different gas mixtures, including either pure gas or a combination of more than one gas like natural gas, methane, hydrogen and carbon dioxide. The first combustor is a 100 kW tangential swirl combustor made of stainless steel that has been experimentally and theoretically analysed to study and mitigate the effect of flashback phenomena. The use of a central fuel injector, cylindrical confinement and exhaust sleeve are shown to give large benefits in terms of flashback resistance and acts to reduce and sometimes eliminate any coherent structures which may be located along the axis of symmetry. The Critical Boundary Velocity Gradient is used for characterisation of flashback, both via the original Lewis and von Elbe formula and via new analysis using CFD and investigation of boundary layer conditions just in front of the flame front. Conclusions are drawn as to mitigation technologies. It is recognized how isothermal conditions produce strong Precessing Vortex Cores that are fundamental in producing the ii final flow field, whilst the Central Recirculation Zones are dependent on pressure decay ratio inside the combustion chamber. Combustion conditions showed the high similarity between experiments and simulation. Flashback was demonstrated to be a factor highly related to the strength of the Central Recirculation Zone for those cases where a Combustion Induced Vortex Breakdown was allowed to enter the swirl chamber, whilst cases where a bluff body impeded its passage showed a considerable improvement to the resistance of the phenomenon. The use of nozzle constrictions also reduced flashback at high Reynolds number (Re). All these results were intended to contribute to better designs of future combustors. The second piece of work of this PhD research included comprehensive experimental work using a generic swirl burner (with three different blade inserts to give different swirl numbers) and has been used to examine the phenomena of flashback and blowoff in the swirl burner in the context of lean premixed combustion. Cylindrical and conical confinements have been set up and assembled with the original design of the generic swirl combustor. In addition to that, multi-fuel blends used during the experimental work include pure methane, pure hydrogen, hydrogen / methane mixture, carbon dioxide/ methane mixture and coke oven gas. The above investigational analysis has proved the flashback limits decrease when swirl numbers decrease for the fuel blends that contain 30% or less hydrogen. Confinements would improve the flashback limit as well. Blowoff limits improve with a lower swirl number and it is easier to recognise the gradual extinction of the flame under blowoff conditions. The use of exhaust confinement has created a considerable improvement in blowoff. Hydrogen enriched fuels can improve the blowoff limit in terms of increasing heat release, which is higher than heat release with natural gas. However, the confinements complicate the flashback, especially when the fuel contains a high percentage of hydrogen. The flashback propensity of the hydrogen/methane blends becomes quite strong. The most important features in gas turbines is the possibility of using different kinds of fuel. This matter has been discussed extensively in this project. By matching flashback/blowoff limits, it has been found that for fuels containing up to 30% of hydrogen, the designer would be able to switch the same gas turbine combustor to multifuels whilst producing the same power output.

APA, Harvard, Vancouver, ISO, and other styles

5

Colby, Jonathan A. "Flow Field Measurements in a Counter-Swirl Stabilized Liquid Combustor." Thesis, Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/10470.

Full text

Abstract:

To adhere to the current requirements for NOx and CO emissions in combustion systems, modern land and air based gas turbine engines often operate in the fuel lean regime. While operating near the lean blow out (LBO) limit does reduce some harmful emissions, combustor stability is sacrificed and extinction becomes a major concern. To fully understand the characteristics of lean operation, an experimental study was conducted to map the time averaged flow field in a typical industrial, counter-swirling, liquid fuel combustor. This study examined two steady-state operating conditions, both near the lean extinction limit for this swirl burner. Using an LDV/PDPA system, 2-D mean and fluctuating velocities, as well as Reynolds stresses, were measured throughout the combustor. These measurements were taken for both the non-reacting and reacting flow fields, enabling a direct analysis of the result of heat addition and increased load on a turbulent swirling flow field. To further understand the overall flow field, liquid droplet diameter measurements were taken to determine the fuel spray characteristics as a function of operating pressure and rated spray angle. Chemical composition at the combustor exit was also measured, with an emphasis on the concentrations of both CO and NOx emissions. This large database of aerodynamic and droplet measurements improves understanding of the swirling, reacting flow field and aids in the accurate prediction of lean blow-out events. With this understanding of the lean blow-out limit, increased fuel efficiency and decreased pollutant emissions can be achieved in industrial combustors, especially those used for thrust in the airline industry.

APA, Harvard, Vancouver, ISO, and other styles

6

Sheen, Dong-Hyon. "Swirl-stabilised turbulent spray flames in an axisymmetric model combustor." Thesis, Imperial College London, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.445249.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Thiruchengode, Muruganandam. "Sensing and Dynamics of Lean Blowout in a Swirl Dump Combustor." Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/10538.

Full text

Abstract:

This thesis describes an investigation on the blowout phenomenon in gas turbine combustors. The combustor primarily used for this study was a swirl- and dump-stabilized, atmospheric pressure device, which did not exhibit dynamic combustion instabilities. The first part of the thesis work concentrated on finding a sensing methodology to be able to predict the onset of approach of combustor blowout using optical methods. Temporary extinction-reignition events that occurred prior to blowout were found to be precursor events to blowout. A threshold based method was developed to identify these events in the time-resolved sensor output. The number and the average length of each event were found to increase as the LBO limit (fuel-air ratio) is approached. This behavior is used to predict the proximity to lean blowout. In the second part of this study, the blowout sensor was incorporated into a control system that monitored the approach of blowout and then actuated an alternate mechanism to stabilize the combustor near blowout. Enhanced stabilization was achieved by redirecting a part of the main fuel to a central preinjection pilot injection. The sensing methodology, without modification, was effective for the combustor with pilot stabilization. An event based control algorithm for controlling the combustor from blowing out was also developed in this study. The control system was proven to stabilize the combustor even when the combustor loading was rapidly changed. The final part of this study focused on understanding the physical mechanisms behind the precursor events. High speed movies of flame chemiluminescence and laser sheet scattering from oil droplets seeded into the reactants were analyzed to explain the physical processes that cause the extinction and the reignition of the combustor during a precursor event. A physical model for coupling of the fluid dynamics of vortex breakdown and combustion during precursor and blowout events is proposed. This model of blowout phenomenon, along with the sensing and control strategies developed in this study could enable the gas turbine combustor designers to design combustors with wider operability regimes. This could have significant payoffs in terms of reduction in NOx emissions from the combustor.

APA, Harvard, Vancouver, ISO, and other styles

8

Linck, Martin Brendan. "Spray flame and exhaust jet characteristics of a pressurized swirl combustor." College Park, Md. : University of Maryland, 2006. http://hdl.handle.net/1903/3627.

Full text

Abstract:

Thesis (Ph. D.) -- University of Maryland, College Park, 2006.
Thesis research directed by: Mechanical Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.

APA, Harvard, Vancouver, ISO, and other styles

9

WANG, DEXIN. "STRONGLY SWIRLING FLOW STUDY ON PRESSURE-SWIRL ATOMIZER AND CYCLONE COMBUSTOR." University of Cincinnati / OhioLINK, 2002. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1032210020.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

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

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

More sources

Books on the topic "Swirl combustor"

1

Radial-bias-combustion and central-fuel-rich swirl pulverized coal burners for wall-fired boilers. Hauppauge, N.Y: Nova Science Publishers, 2009.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

2

Experimental Results for a High Swirl, Ultra Compact Combustor for Gas Turbine Engines. Storming Media, 2003.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

3

United States. National Aeronautics and Space Administration., ed. Velocity and drop size measurements in a swirl-stabilized, combusting spray. [Washington, DC: National Aeronautics and Space Administration, 1993.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

4

United States. National Aeronautics and Space Administration., ed. Structure of a swirl-stabilized combusting spray. Washington, DC: American Institute of Aeronautics and Astronautics, Inc., 1995.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

5

United States. National Aeronautics and Space Administration., ed. Structure of a swirl-stabilized combusting spray. Washington, DC: American Institute of Aeronautics and Astronautics, Inc., 1995.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

6

Structure of a swirl-stabilized combusting spray. [Washington, DC]: National Aeronautics and Space Administration, 1994.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

7

United States. National Aeronautics and Space Administration., ed. Structure of a swirl-stabilized combusting spray. [Washington, DC]: National Aeronautics and Space Administration, 1994.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

8

Structure of a swirl-stabilized combusting spray. [Washington, DC]: National Aeronautics and Space Administration, 1994.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

9

United States. National Aeronautics and Space Administration., ed. Structure of a swirl-stabilized combusting spray. Washington, DC: American Institute of Aeronautics and Astronautics, Inc., 1995.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

10

United States. National Aeronautics and Space Administration., ed. Structure of a swirl-stabilized combusting spray. Washington, DC: American Institute of Aeronautics and Astronautics, Inc., 1995.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

Book chapters on the topic "Swirl combustor"

1

Aoki, K., M. Shibata, and Y. Nakayama. "The Flow Characteristics in a Swirl Type Combustor." In Laser Diagnostics and Modeling of Combustion, 45–54. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-45635-0_6.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Feser, Joseph S., Serhat Karyeyen, and Ashwani K. Gupta. "Impact of Flowfield on Pollutants’ Emission from a Swirl-Assisted Distributed Combustor." In Lecture Notes in Mechanical Engineering, 3–11. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5996-9_1.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Rajpara, Parag, Rupesh Shah, and Jyotirmay Banerjee. "Performance Evaluation of Upward Swirl Combustor with Reverse Fuel Injector and Hydrogen Blending." In Green Energy and Technology, 383–410. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-2648-7_17.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Cardoso de Souza, T., R. J. M. Bastiaans, B. J. Geurts, and L. P. H. De Goey. "Numerical Analysis of a Swirl Stabilized Premixed Combustor with the Flamelet Generated Manifold approach." In ERCOFTAC Series, 321–26. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-2482-2_51.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Ghose, Prakash, and A. Datta. "Effect of Inlet Swirl and Turbulence Levels on Combustion Performance in a Model Kerosene Spray Gas Turbine Combustor." In Lecture Notes in Mechanical Engineering, 493–504. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-7831-1_46.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Bhawarker, Yogesh, Prakash Katdare, Manish Kale, Hitesh Kumar, Shri Krishna Mishra, and Rahul Kumar. "CFD Analysis of Temperature Profile and Pattern Factor at the Exit of Swirl Dump Combustor." In Springer Proceedings in Energy, 589–604. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-0235-1_45.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Jones, W. P., and A. Pascau. "Calculations of Velocity, Composition and Temperature Fields in a Model Swirl Combustor with a Reynolds-Stress Transport Turbulence Model." In Heat Transfer in Radiating and Combusting Systems, 128–45. Berlin, Heidelberg: Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-84637-3_7.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Bender, C., F. Zhang, P. Habisreuther, H. Büchner, and H. Bockhorn. "Measurement and Simulation of Combustion Noise emitted from Swirl Burners." In Combustion Noise, 33–62. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-02038-4_2.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Grigoryev, K. A., Yu A. Roundyguine, V. E. Skuditskii, R. G. Anoshin, A. P. Paramonov, and A. A. Trinchenko. "Low-Temperature Swirl Fuel Combustion: Development and Experience." In Cleaner Combustion and Sustainable World, 999–1003. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-30445-3_133.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Weyermann, Fabian, Christoph Hirsch, and Thomas Sattelmayer. "Influence of boundary conditions on the noise emission of turbulent premixed swirl flames." In Combustion Noise, 147–74. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-02038-4_6.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Swirl combustor"

1

GUPTA, A. "Swirl combustor design effects on emission and combustion characteristics." In 28th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-548.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Katta, Viswanath R., and William M. Roquemore. "Modeling of Emissions in a Laboratory Swirl Combustor." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43977.

Full text

Abstract:

A swirl-stabilized combustor utilizes recirculation zones for stabilizing the flame. The performance of such combustors could depend on the fuel used as the cracked fuel products may enter the recirculation-zones and alter their characteristics. A numerical study is conducted for understanding the effects of fuel variation on the combustion and unburned-hydrocarbon-emission characteristics of a laboratory swirl combustor. A time-dependent, detailed-chemistry CFD model UNICORN is used. Six binary fuel mixtures formulated with n-dodecane and n-heptane, m-xylene, iso-octane or hexadecane are considered. A semi-detailed chemical-kinetics model (CRECK-0810) involving 206 species and 5652 reactions for the combustion of these fuels is incorporated into UNICORN code. Calculations are performed for a fuel-lean condition, which represents cruise operation of an aircraft. Combustor flows simulated with different fuel mixtures yielded nearly the same flowfields and flame structures. Production of the intermediate cracked fuel species that are key for the final flame structure and emissions seems to be independent of the fuel used. This finding could greatly simplify the detailed chemical kinetics used for obtaining cracked products. As the cracked fuel species are completely consumed with in the flame zone, no emissions are observed at the combustor exit for the considered fuel-lean condition.

APA, Harvard, Vancouver, ISO, and other styles

3

Katta, Viswanath, and William Roquemore. "Modeling Soot in a Swirl Combustor." In 42nd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-645.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Durbin, Mark D., Marlin D. Vangsness, Dilip R. Ballal, and Viswanath R. Katta. "Study of Flame Stability in a Step Swirl Combustor." In ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/95-gt-111.

Full text

Abstract:

A prime requirement in the design of a modem gas turbine combustor is good combustion stability, especially near lean blowout (LBO), to ensure an adequate stability margin. For an aeroengine, combustor blow-off limits are encountered during low engine speeds at high altitudes over a range of flight Mach numbers. For an industrial combustor, requirements of ultra-low NOx emissions coupled with high combustion efficiency demand operation at or close to LBO. In this investigation, a step swirl combustor (SSC) was designed to reproduce the swirling flow pattern present in the vicinity of the fuel injector located in the primary zone of a gas turbine combustor. Different flame shapes, structure and location were observed and detailed experimental measurements and numerical computations were performed. It was found that certain combinations of outer and inner swirling air flows produce multiple attached flames, a flame with a single attached structure just above the fuel injection tube, and finally for higher inner swirl velocity, the flame lifts from the fuel tube and is stabilized by the inner recirculation zone. The observed difference in LBO between co- and counter-swirl configurations is primarily a function of how the flame stabilizes i.e., attached vs. lifted. A turbulent combustion model correctly predicts the attached flame location(s), development of inner recirculation zone, a dimple-shaped flame structure, the flame lift-off height, and radial profiles of mean temperature, axial velocity, and tangential velocity at different axial locations. Finally, the significance and applications of anchored and lifted flames to combustor stability and LBO in practical gas turbine combustors are discussed.

APA, Harvard, Vancouver, ISO, and other styles

5

Lal, Mihir, Miodrag Oljaca, Eugene Lubarsky, Dimitriy Shcherbik, Suresh Menon, and Balu Sekar. "Controlling Combustion Dynamics in a Swirl Combustor via Spray Optimization." In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-4517.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Breaux, Baine B., Srinibas Karmakar, Shengrong Zhu, and Sumanta Acharya. "Evaluation of Hydrous Ethanol Combustion in a Swirl-Stabilized Combustor." In ASME 2011 International Mechanical Engineering Congress and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/imece2011-63688.

Full text

Abstract:

The use of commercial hydrous ethanol reduces the energy cost of producing that fuel, and results in a larger net energy gain per dollar invested. Current production of commercial grade ethanol contains 5% water, and is used routinely in gasoline engines, primarily as an additive, and is currently being considered for use in gas turbines. In this study ethanol is burned in a swirl-stabilized combustor, air is introduced at a constant flow rate through a dump diffuser, and fuels ranging from 0%–20% water in ethanol are injected via pressure-orifice atomizing nozzles. The goal of the study is to examine the combustion characteristics of hydrous ethanol and to make an assessment of its suitability for a gas turbine engine. The flame structure is observed using high speed OH and CH radical chemiluminescence imaging. These observations, combined with overall metrics such as lean blowout, flame holding, heat release and emissions, are a necessity in obtaining the complete picture of hydrous ethanol combustion and are required to fully evaluate hydrous fuel as an option in continuous flame applications.

APA, Harvard, Vancouver, ISO, and other styles

7

Saurabh, Aditya, and C. O. Paschereit. "Combustion Instability in a Swirl Flow Combustor With Transverse Extensions." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-95732.

Full text

Abstract:

The present investigation is an analysis of self-excited combustion instability in a swirl flame-based combustor with transverse extensions. Transverse extensions create the possibility of studying flame interaction with transverse acoustic oscillations. Such investigation important for understanding the phenomenon of thermoacoustic instability in annular combustors, where during thermoacoustic instability, azimuthal acoustic modes of the combustor couple with the multiple flames of the combustor. Flame and flow field dynamics during self-excited thermoacoustic instability in the single burner test-rig is presented here. These results are then compared to the dynamics of the isothermal and reacting flows in response to axial and transverse acoustic forcing. Both axial and transverse forcing led to the formation of axisymmetric shear layer vortices. Adding to the insight gained from previous investigations, these results suggest that that swirl flow dynamics in response to transverse acoustics consists of a non-trivial, direct effect of transverse acoustics on the flow field, in addition to its response to longitudinal fluctuations induced by transverse forcing.

APA, Harvard, Vancouver, ISO, and other styles

8

Yi, Tongxun, and Ephraim Gutmark. "Combustion Instabilities and Control of a Multi-Swirl Atmospheric Combustor." In 42nd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-635.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Monz, T. O., M. Stöhr, W. O’Loughlin, J. Zanger, M. Hohloch, and M. Aigner. "Experimental Characterization of a Swirl Stabilized MGT Combustor." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42387.

Full text

Abstract:

A swirl stabilized MGT combustor (Turbec T100) was operated with natural gas and was experimentally characterized in two test rigs, a pressurized and optically accessible MGT test rig and an atmospheric combustor test rig. For the detailed characterization of the combustion processes, planar OH-PLIF and simultaneous 3D-stereo PIV measurements were performed in the atmospheric combustor test rig. Flow fields, reaction zones and exhaust gas emissions are reported for a range of pressure scaled MGT load points. Parameter studies on combustor inlet conditions (e.g. air preheating temperature, air and fuel mass flow rates and fuel split) were conducted in the atmospheric combustor test rig. From the parameters studies the fuel split between the pilot and the main stage and the air preheating temperature were found to have the biggest impact on the flame shape, flame stabilization and exhaust gas emissions. The measurements of the ATM test rig are compared with measurements of the pressurized MGT test rig with and without an optically accessible combustion chamber. Opened and closed conical flame and flow pattern were found in both test rigs. Reasons for the two flame and flow pattern are supposed to be the interaction of pilot stage combustion and flow field and the interaction of the dilution air with the combustion and the flow field. The results are discussed and compared with repect to a transferability of combustion characteristics from the ATM test rig to the MGT test rigs.

APA, Harvard, Vancouver, ISO, and other styles

10

NEJAD, R., R. BORAY, S. AHMED, and P. BUCKLEY. "Inlet swirl effects on dump combustor flows." In 28th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-35.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Reports on the topic "Swirl combustor"

1

Parr, T., K. Wilson, K. Schadow, J. Cole, and N. Widmer. Sludge Combustor Using Swirl and Active Combustion Control. Fort Belvoir, VA: Defense Technical Information Center, January 2000. http://dx.doi.org/10.21236/ada382663.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Gutmark, Ephralm J., and Guoqiang Li. Combustion Control in Industrial Multi-Swirl Stabilized Spray Combustor. Fort Belvoir, VA: Defense Technical Information Center, August 2005. http://dx.doi.org/10.21236/ada441269.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Gutmark, Ephraim. Emissions Control in Swirl Stabilized Spray Combusters, an Experimental and Computational Study. Fort Belvoir, VA: Defense Technical Information Center, February 2007. http://dx.doi.org/10.21236/ada463219.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Chang, Hui-Ting, Chih-Wei Huang, Kuan-Hsu Lin, and Wen-Cheng Hu. Effects of Intake System with Swirl and Tumble Valve on the Combustion in a Small Four Stroke Engine. Warrendale, PA: SAE International, October 2013. http://dx.doi.org/10.4271/2013-32-9002.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Misawa, Masahiro, Yuzo Aoyagi, Masayuki Kobayashi, Yuichi Goto, and Hisakazu Suzuki. High EGR Diesel Combustion and Emission Reduction Study by Multi-Cylinder Engine (Fourth Report)~Effect of Variable Swirl of Multi-Cylinder Engine. Warrendale, PA: SAE International, September 2005. http://dx.doi.org/10.4271/2005-08-0652.

Full text

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!