Journal articles: 'Swirl combustor'

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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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.

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Klose, G., R. Schmehl, R. Meier, G. Maier, R. Koch, S. Wittig, M. Hettel, W. Leuckel, and N. Zarzalis. "Evaluation of Advanced Two-Phase Flow and Combustion Models for Predicting Low Emission Combustors." Journal of Engineering for Gas Turbines and Power 123, no. 4 (October 1, 2000): 817–23. http://dx.doi.org/10.1115/1.1377010.

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The development of low-emission aero-engine combustors strongly depends on the availability of accurate and efficient numerical models. The prediction of the interaction between two-phase flow and chemical combustion is one of the major objectives of the simulation of combustor flows. In this paper, predictions of a swirl stabilized model combustor are compared to experimental data. The computational method is based on an Eulerian two-phase model in conjunction with an eddy dissipation (ED) and a presumed-shape-PDF (JPDF) combustion model. The combination of an Eulerian two-phase model with a JPDF combustion model is a novelty. It was found to give good agreement to the experimental data.

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Ran, Jing Yu, Li Juan Liu, Chai Zuo Li, and Li Zhang. "Numerical Study on Optimum Designing of the Air Distribution Structure of a New Cyclone Combustor." Advanced Materials Research 347-353 (October 2011): 3005–14. http://dx.doi.org/10.4028/www.scientific.net/amr.347-353.3005.

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A new type of cyclone combustor is designed based on the traditional pulverized coal liquid slag combustor in this paper. According to the characteristics of swirl combustion and flow, numerical simulation of pulverized coal combustion in a new cyclone combustor has carried out using Realizable k-ε equation model with swirl modified to gas phase and stochastic trajectory model under Lagrange coordinate system to particle phase. Flows and combustion characteristics under different working conditions are mainly studied by changing the angles of primary and secondary air inlets, and then structural characteristics of the combustor are analyzed. Results show that structural characteristics of the primary and secondary air have great influence on internal flow and combustion characteristics of the combustor. When the pitch angle, the rotation angle of the secondary air and the expansion angle of the primary air respectively are 20°, 51° and 60°, the combustion efficiency of the combustor can reach up to 98.1% and it is conducive to high-temperature liquid slagging. It is also helpful to prevented pulverized coal depositing and accumulating near the wall and then plugging the combusting channel during the starting stage in low temperature region.

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Kasani, Adam, Mazlan Abdul Wahid, Ahmad Dairobi Ghazali, and Mohammed Bashir Abdulrahman. "The Effects of Multiple Swirl Generator Inlets Circumferential Distribution to a Liquid Fuelled Ultra-High Swirl Flameless Combustion Characteristics." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 76, no. 2 (October 23, 2020): 65–74. http://dx.doi.org/10.37934/arfmts.76.2.6574.

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This paper presents the experimental results of a simple cylindrical shaped, liquid fuelled flameless combustor which utilizes ultra-high swirl flow in the combustion process. 4 different swirl generator inlet configurations were tested in this work. Ethanol fuel were used during flameless mode. The experiments were conducted at equivalence ratio (F=1), with the flow rate of fuel set at 4.48*104 kg/s, and flow rate of air at 3.854*103 kg/s. The results revealed that by using all 12 tangential air inlets (swirl generator injectors), the swirl strength was reduced through evenly distributing the position of the injectors circumferentially. As a result, the combustor successfully suppressed the emission of NOx and CO to zero ppm for both gasses. It was also reported that flameless mode was established in all configurations, regardless of the swirl strength.

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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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Hasini, Hasril, Norshah Hafeez Shuaib, and Wan Ahmad Fahmi Wan Abdullah. "CFD Analysis of Temperature Distribution in Can-Type Combustor Firing Synthetic Gas." Applied Mechanics and Materials 393 (September 2013): 741–46. http://dx.doi.org/10.4028/www.scientific.net/amm.393.741.

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This paper presents CFD analysis of the effect of syngas combustion in a full scale gas turbine combustor with specific emphasis given to the flame and flue gas temperature distribution. A base case solution was first established using conventional natural gas combustion. Actual operating boundary conditions such as swirl, diffusion and fuel mass flow were imposed on the model. The simulation result is validated with the flame temperature of typical natural gas combustion. Result from flow and combustion calculation shows reasonable trend of the swirl mixing effect. The maximum flame temperature was found to be the highest for syngas with the highest H2/CO ratio. However, the flue gas temperature was found to be approximately identical for all cases. The prediction of temperature distribution in the combustor would enable further estimation of pollutant species such as CO2and NOxin complex regions within the combustor.

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Jeong, Hwanghui, and Keeman Lee. "Effect of Swirl Angles and Combustion Characteristics of Low Swirl Model Combustor." Journal of the Korean Society of Propulsion Engineers 20, no. 4 (August 1, 2016): 40–49. http://dx.doi.org/10.6108/kspe.2016.20.4.040.

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Popescu, F., R. A. Mahu, N. A. Antonescu, and I. V. Ion. "CFD prediction of combustion in a swirl combustor." IOP Conference Series: Materials Science and Engineering 444 (November 29, 2018): 082009. http://dx.doi.org/10.1088/1757-899x/444/8/082009.

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Huang, Ying, and Vigor Yang. "Effect of swirl on combustion dynamics in a lean-premixed swirl-stabilized combustor." Proceedings of the Combustion Institute 30, no. 2 (January 2005): 1775–82. http://dx.doi.org/10.1016/j.proci.2004.08.237.

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Yi, Tongxun, and Ephraim J. Gutmark. "Combustion Instabilities and Control of a Multiswirl Atmospheric Combustor." Journal of Engineering for Gas Turbines and Power 129, no. 1 (January 22, 2006): 31–37. http://dx.doi.org/10.1115/1.2181595.

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Thermoacoustic instability and lean blowout (LBO) are investigated experimentally in an atmospheric swirl-stabilized combustor fueled with gaseous propane. Factors affecting combustion instability are identified. Sinusoidal or steady air forcing of either the swirling air shear layer or the fuel line, with less than 1.0% of combustion air, can reduce pressure oscillations amplitude by more than 20dB. Phase-shifted close-loop air forcing of the flame can reduce the pressure oscillations amplitude by 13dB. For a constant air flow rate and air inlet temperature, initially smooth turbulent combustion exhibits relatively intense heat release oscillations with decreasing equivalence ratio, followed by a quiet state before blowout. High outer swirl intensity and a rich burning flame stabilization region can effectively extend the LBO limit.

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Onuma, Yoshiaki, Masaharu Morikawa, Junichi Kimura, Shigeto Nakagawa, and Tatsuya Ichihashi. "Fuel-Lean Premixed Combustion by a Swirl-Flow Combustor." Transactions of the Japan Society of Mechanical Engineers Series B 61, no. 584 (1995): 1534–39. http://dx.doi.org/10.1299/kikaib.61.1534.

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Liu, Yin Li, and Hao Tang. "Numerical Study on the Interaction Mechanism between Swirl and Reverse Flow Rate in a Twin Swirl Combustor." Advanced Materials Research 960-961 (June 2014): 341–48. http://dx.doi.org/10.4028/www.scientific.net/amr.960-961.341.

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An isothermal flow in a Twin Swirl Combustor (TSC) was simulated with the Renormalized Group (RNG) k-ε turbulence model. The swirling and recirculation intensity was studied under different structures and inlet conditions. The results confirmed that there was a significant negative correlation between the trend lines of the swirl number (S) and reversed flow rate (Xr). The gradient of reversed flow rate was larger in the front and middle parts of the combustor than that of swirl number. The end-surface-inlet structure had a better swirl and recirculation enhancement effect. With the end-surface-inlet structure, the internal swirl and reverse intensity could be flexibly adjusted by switching the swirl intensity of the primary air. Under the structure of staggered-inlet, there was a critical distance between primary and secondary air inlets. When exceeded, it would be more difficult to enhance the swirl and reverse flow effect by increasing the swirl intensity of the secondary air.

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Yu, Han, Jianqin Suo, Pengfei Zhu, and Longxi Zheng. "The Characteristic of Flow Field and Emissions of a Concentric Staged Lean Direct Injection (LDI) Combustor." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 36, no. 5 (October 2018): 816–23. http://dx.doi.org/10.1051/jnwpu/20183650816.

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The characteristic of flow field and emissions was investigated by numerical simulation for a concentric staged lean direct injection combustor, the non-reaction and reaction flow fields were studied under idle and takeoff conditions, and the effect of combustion heat release on flow field was analyzed, then the influence of injection angle on emissions were obtained. The investigation results indicated that the steady central recirculation zone could be formed under non-reaction and reaction conditions by medium swirl strength which the swirl angle is 32°, however, the size and reverse mass flow at reaction conditions is significantly increased than non-reaction conditions; the combustion reaction zone moves toward the outlet as the decrease of fuel injection angle, which reduce the resistant time of hot gas in combustor, and then the production of nitrogen oxides would be decreased.

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Aoki, Katsumi, and Yasuki Nakayama. "Flow characteristics of swirl type combustor." JOURNAL OF THE FLOW VISUALIZATION SOCIETY OF JAPAN 7, no. 26 (1987): 363–66. http://dx.doi.org/10.3154/jvs1981.7.363.

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Aoki, Katsumi, and Yasuki Nakayama. "Flow characteristics of swirl type combustor." JOURNAL OF THE FLOW VISUALIZATION SOCIETY OF JAPAN 7, Supplement (1987): 127–30. http://dx.doi.org/10.3154/jvs1981.7.supplement_127.

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Grinstein, Fernando F., Ted R. Young, Ephraim J. Gutmark, Guoqiang Li, George Hsiao, and Hukam C. Mongia. "Flow dynamics in a swirl combustor." Journal of Turbulence 3 (January 2002): N30. http://dx.doi.org/10.1088/1468-5248/3/1/030.

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Durbin, M. D., and D. R. Ballal. "Studies of Lean Blowout in a Step Swirl Combustor." Journal of Engineering for Gas Turbines and Power 118, no. 1 (January 1, 1996): 72–77. http://dx.doi.org/10.1115/1.2816552.

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The design requirements of a modern gas turbine combustor are increasingly dictated by wide stability limits, short flame length, and uniform mixing. To achieve the best trade-off between these three factors, flame characteristics (length, shape, mixedness), lean blowout (LBO), and optimum combustor configuration should be investigated over a wide range of inner and outer air velocities, inner and outer vane angles, and co- versus counterswirl arrangements. Such an investigation was performed in a step swirl combustor (SSC) designed to simulate the fuel–air mixing pattern in a gas turbine combustor dome fitted with an airblast atomizer. It was found that an increase in the outer vane angle and a decrease in inner air velocity decreased the flame length. LBO was improved when outer flow swirl intensity was increased. An optimum hardware and velocity configuration for the SSC was found for inner swirl = 45 deg, outer swirl = 60 deg, coswirl direction, and inner air velocity = outer air velocity = 16 m/s. This optimum SSC configuration yielded: (i) low values of LBO, (ii) short flame length, (iii) uniformly mixed stable flame, and (iv) little or no variation in these characteristics over the range of operation of SSC. Finally, the co- versus counterswirl arrangements and the operation of the optimized combustor configuration are discussed.

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Giani, Claudio, and Derek Dunn-Rankin. "Miniature Fuel Film Combustor: Swirl Vane Design and Combustor Characterization." Combustion Science and Technology 185, no. 10 (October 3, 2013): 1464–81. http://dx.doi.org/10.1080/00102202.2013.804181.

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Feitelberg, Alan S., Michael D. Starkey, Richard B. Schiefer, Roointon E. Pavri, Matt Bender, John L. Booth, and Gordon R. Schmidt. "Performance of a Reduced NOx Diffusion Flame Combustor for the MS5002 Gas Turbine." Journal of Engineering for Gas Turbines and Power 122, no. 2 (January 3, 2000): 301–6. http://dx.doi.org/10.1115/1.483217.

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This paper describes a reduced NOx diffusion flame combustor that has been developed for the MS5002 gas turbine. Laboratory tests have shown that when firing with natural gas, without water or steam injection, NOx emissions from the new combustor are about 40 percent lower than NOx emissions from the standard MS5002 combustor. CO emissions are virtually unchanged at base load, but increase at part load conditions. The laboratory results were confirmed in 1997 by a commercial demonstration test at a British Petroleum site in Prudhoe Bay, Alaska. The standard MS5002 gas turbine is equipped with a conventional, swirl stabilized diffusion flame combustion system. The twelve standard combustors in an MS5002 turbine are cylindrical cans, approximately 27 cm (10.5 in.) in diameter and 112 cm (44 in.) long. A small, annular, vortex generator surrounds the single fuel nozzle that is centered at the inlet to each can. The walls of the cans are louvered for cooling, and contain an array of mixing and dilution holes that provide the air needed to complete combustion and dilute the burned gas to the desired turbine inlet temperature. The new, reduced NOx emissions combustor (referred to as a “lean head end,” or LHE, combustor) retains all of the key features of the conventional combustor; the only significant difference is the arrangement of the mixing and dilution holes in the cylindrical combustor can. By optimizing the number, diameter, and location of these holes, NOx emissions were substantially reduced. The materials of construction, fuel nozzle, and total combustor air flow were unchanged. The differences in NOx emissions between the standard and LHE combustors, as well as the variations in NOx emissions with firing temperature, were well correlated using turbulent flame length arguments. Details of this correlation are also presented. [S0742-4795(00)01602-1]

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Kim, Jonghyun, and Jungsoo Park. "Conceptual Approach to Combustor Nozzle and Reformer Characteristics for Micro-Gas Turbine with an On-Board Reforming System: A Novel Thermal and Low Emission Cycle." Sustainability 12, no. 24 (December 17, 2020): 10558. http://dx.doi.org/10.3390/su122410558.

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In order to implement moderate or intensive low oxygen dilution (MILD) combustion, it is necessary to extend the flame stability and operating range. In the present study, the conceptual designs of a combustor single nozzle and reformer were numerically suggested for a micro-gas turbine with an on-board reformer. The target micro-gas turbine achieved a thermal power of 150 kW and a turbine inlet temperature (TIT) of 1200 K. Studies on a nozzle and reformer applying an open-loop concept have been separately conducted. For the nozzle concept, a single down-scaled nozzle was applied based on a reference nozzle for a heavy-duty gas turbine. The nozzle can achieve a good mixture with a high swirl with a splined swirl curve lower NOx emissions and smaller pressure drop in the combustor. The concept of the non-catalytic partial-oxidation reforming reformate was designed using the combustor outlet temperature (COT) of the exhaust gas. Feasible hydrogen yields were mapped through the reformer. Based on the hydrogen yields from the reformer, hydrogen was added to the nozzle to investigate its combustion behavior. By increasing the hydrogen addition and decreasing the O2 fraction, the OH concentrations were decreased and widely distributed similar to the fundamental characteristics of MILD combustion.

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Stone, C., and S. Menon. "Swirl control of combustion instabilities in a gas turbine combustor." Proceedings of the Combustion Institute 29, no. 1 (January 2002): 155–60. http://dx.doi.org/10.1016/s1540-7489(02)80024-4.

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Ikeda, Yuji, Naoki Yamada, Tsuyoshi Nakajima, Masataka Ohta, Mitsuru Inada, and Shigemi Nandai. "Spray combustion characteristics in a highly pressurized swirl-stabilized combustor." Proceedings of the Combustion Institute 29, no. 1 (January 2002): 853–59. http://dx.doi.org/10.1016/s1540-7489(02)80109-2.

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Choi, Jeongan, Rajavasanth Rajasegar, Qili Liu, Tonghun Lee, and Jihyung Yoo. "Jet A Combustion in a Mesoscale Swirl-Stabilized Combustor Array." Energy & Fuels 35, no. 13 (June 14, 2021): 10796–804. http://dx.doi.org/10.1021/acs.energyfuels.1c00707.

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Kinoshita, Y., T. Oda, and J. Kitajima. "Research on a Methane-Fueled Low NOx Combustor for a Mach 3 Supersonic Transporter Turbojet Engine." Journal of Engineering for Gas Turbines and Power 123, no. 4 (October 1, 2000): 787–95. http://dx.doi.org/10.1115/1.1377009.

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Methane-fueled low NOx combustor research had been conducted under the Japanese supersonic/hypersonic propulsion research program. A unique form of premixture jet swirl combustor (PJSC) was proposed for the ultra low NOx combustor of a Mach 3 turbojet engine. Fuel-air mixing tests and fundamental combustion tests were conducted to obtain the design data and combustion characteristics in the first phase of the research. A single can-type combustor was fabricated and high-temperature and high-pressure combustion tests were carried out for the evaluation on NOx emission reduction capability of the PJSC concept in the second phase. In the final phase of research, a multisector combustor was fabricated and the performance demonstration test was conducted for the final evaluation of the pollutant exhaust emission goals and the combustor performance goals set in the HYPR project. The sequential three-phased program was completed successfully, and the project goals of NOx emission, combustion efficiency, pressure loss and exit gas temperature pattern factor at the Mach 3 cruise condition, together with the ICAO regulatory levels for supersonic aircraft at LTO conditions, were all achieved in the performance demonstration test.

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Umeh, Chukwueloka O. U., Zvi Rusak, and Ephraim Gutmark. "Vortex Breakdown in a Swirl-Stabilized Combustor." Journal of Propulsion and Power 28, no. 5 (September 2012): 1037–51. http://dx.doi.org/10.2514/1.b34377.

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Sarkar, Soumalya, Satyanarayanan R. Chakravarthy, Vikram Ramanan, and Asok Ray. "Dynamic data-driven prediction of instability in a swirl-stabilized combustor." International Journal of Spray and Combustion Dynamics 8, no. 4 (July 8, 2016): 235–53. http://dx.doi.org/10.1177/1756827716642091.

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Combustion instability poses a negative impact on the performance and structural durability of both land-based and aircraft gas turbine engines, and early detection of combustion instabilities is of paramount importance not only for performance monitoring and fault diagnosis, but also for initiating efficient decision and control of such engines. Combustion instability is, in general, characterized by self-sustained growth of large-amplitude pressure tones that are caused by a positive feedback arising from complex coupling of localized hydrodynamic perturbations, heat energy release, and acoustics of the combustor. This paper proposes a fast dynamic data-driven method for detecting early onsets of thermo-acoustic instabilities, where the underlying algorithms are built upon the concepts of symbolic time series analysis (STSA) via generalization of D-Markov machine construction. The proposed method captures the spatiotemporal co-dependence among time series from heterogeneous sensors (e.g. pressure and chemiluminescence) to generate an information-theoretic precursor, which is uniformly applicable across multiple operating regimes of the combustion process. The proposed method is experimentally validated on the time-series data, generated from a laboratory-scale swirl-stabilized combustor, while inducing thermo-acoustic instabilities for various protocols (e.g. increasing Reynolds number ( Re) at a constant fuel flow rate and reducing equivalence ratio at a constant air flow rate) at varying air-fuel premixing levels. The underlying algorithms are developed based on D-Markov entropy rates, and the resulting instability precursor measure is rigorously compared with the state-of-the-art techniques in terms of its performance of instability prediction, computational complexity, and robustness to sensor noise.

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GHAFFARPOUR, Mohammad, and Alireza NOORPOOR. "Effects of Swirl Flow on Spray Characteristics in a Swirl-Stabilized Combustor." Journal of Fluid Science and Technology 3, no. 7 (2008): 906–20. http://dx.doi.org/10.1299/jfst.3.906.

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V., Kirubakaran, and David Bhatt. "Experimental and numerical prediction of lean blowout limits for micro gas turbine combustor." Aircraft Engineering and Aerospace Technology 93, no. 4 (April 8, 2021): 607–14. http://dx.doi.org/10.1108/aeat-04-2020-0066.

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Purpose The lean blowout (LBO) limit of the combustor is one of the important performance parameters for any gas turbine combustor design. This study aims to predict the LBO limits of an in-house designed swirl stabilized 3kW can-type micro gas turbine combustor. Design/methodology/approach The experimental prediction of LBO limits was performed on 3kW swirl stabilized combustor fueled with methane for the combustor inlet velocity ranging from 1.70 m/s to 6.80 m/s. The numerical prediction of LBO limits of combustor was performed on two-dimensional axisymmetric model. The blowout limits of combustor were predicted through calculated average exit gas temperature (AEGT) method and compared with experimental predictions. Findings The results show that the predicted LBO equivalence ratio decreases gradually with an increase in combustor inlet velocity. Practical implications This LBO limits predictions will use to fix the operating boundary conditions of 3kW can-type micro gas turbine combustor. This methodology will be used in design stage as well as in the testing stage of the combustor. Originality/value This is a first effort to predict the LBO limits on micro gas turbine combustor through AEGT method. The maximum uncertainty in LBO limit prediction with AEGT is 6 % in comparison with experimental results.

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Som, S. K., S. S. Mondal, and S. K. Dash. "Energy and Exergy Balance in the Process of Pulverized Coal Combustion in a Tubular Combustor." Journal of Heat Transfer 127, no. 12 (July 25, 2005): 1322–33. http://dx.doi.org/10.1115/1.2101860.

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A theoretical model of exergy balance, based on availability transfer and flow availability, in the process of pulverized coal combustion in a tubular air-coal combustor has been developed to evaluate the total thermodynamic irreversibility and second law efficiency of the process at various operating conditions. The velocity, temperature, and concentration fields required for the evaluation of flow availability have been computed numerically from a two-phase separated flow model on a Eulerian-Lagrangian frame in the process of combustion of pulverized coal particles in air. The total thermodynamic irreversibility in the process has been determined from the difference in the flow availability at the inlet and outlet of the combustor. A comparative picture of the variations of combustion efficiency and second law efficiency at different operating conditions, such as inlet pressure and temperature of air, total air flow rate and inlet air swirl, initial mean particle diameter, and length of the combustor, has been provided to shed light on the trade-off between the effectiveness of combustion and the lost work in the process of pulverized coal combustion in a tubular combustor.

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Kim, Jong-Chan, Won-Chul Jung, Ji-Seok Hong, and Hong-Gye Sung. "The Effects of Turbulent Burning Velocity Models in a Swirl-Stabilized Lean Premixed Combustor." International Journal of Turbo & Jet-Engines 35, no. 4 (December 19, 2018): 365–72. http://dx.doi.org/10.1515/tjj-2016-0053.

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Abstract The effects of turbulent burning velocities in a turbulent premixed combustion simulation with a G-equation are investigated using the 3D LES technique. Two turbulent burning velocity models – Kobayashi model, which takes into account the burning velocity pressure effect, and the Pitsch model, which considers the flame regions on the premixed flame structure – are implemented. An LM6000 combustor is employed to validate the turbulent premixed combustion model. The results show that the flame structures in front of the injector have different shapes in each model because of the different turbulent burning velocities. These different flame structures induce changes in the entire combustor flow field, including in the recirculation zone. The dynamic mode decomposition (DMD) method and linear acoustic analysis provide the dominant acoustic mode.

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V., Kirubakaran, and Naren Shankar R. "Prediction of lean blowout performance on variation of combustor inlet area ratio for micro gas turbine combustor." Aircraft Engineering and Aerospace Technology 93, no. 5 (July 9, 2021): 915–24. http://dx.doi.org/10.1108/aeat-02-2021-0042.

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Purpose This paper aims to predict the effect of combustor inlet area ratio (CIAR) on the lean blowout limit (LBO) of a swirl stabilized can-type micro gas turbine combustor having a thermal capacity of 3 kW. Design/methodology/approach The blowout limits of the combustor were predicted predominantly from numerical simulations by using the average exit gas temperature (AEGT) method. In this method, the blowout limit is determined from characteristics of the average exit gas temperature of the combustion products for varying equivalence. The CIAR value considered in this study ranges from 0.2 to 0.4 and combustor inlet velocities range from 1.70 to 6.80 m/s. Findings The LBO equivalence ratio decreases gradually with an increase in inlet velocity. On the other hand, the LBO equivalence ratio decreases significantly especially at low inlet velocities with a decrease in CIAR. These results were backed by experimental results for a case of CIAR equal to 0.2. Practical implications Gas turbine combustors are vulnerable to operate on lean equivalence ratios at cruise flight to avoid high thermal stresses. A flame blowout is the main issue faced in lean operations. Based on literature and studies, the combustor lean blowout performance significantly depends on the primary zone mass flow rate. By incorporating variable area snout in the combustor will alter the primary zone mass flow rates by which the combustor will experience extended lean blowout limit characteristics. Originality/value This is a first effort to predict the lean blowout performance on the variation of combustor inlet area ratio on gas turbine combustor. This would help to extend the flame stability region for the gas turbine combustor.

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Ammar, Nader R., and Ahmed I. Farag. "CFD Modeling of Syngas Combustion and Emissions for Marine Gas Turbine Applications." Polish Maritime Research 23, no. 3 (September 1, 2016): 39–49. http://dx.doi.org/10.1515/pomr-2016-0030.

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Abstract Strong restrictions on emissions from marine power plants will probably be adopted in the near future. One of the measures which can be considered to reduce exhaust gases emissions is the use of alternative fuels. Synthesis gases are considered competitive renewable gaseous fuels which can be used in marine gas turbines for both propulsion and electric power generation on ships. The paper analyses combustion and emission characteristics of syngas fuel in marine gas turbines. Syngas fuel is burned in a gas turbine can combustor. The gas turbine can combustor with swirl is designed to burn the fuel efficiently and reduce the emissions. The analysis is performed numerically using the computational fluid dynamics code ANSYS FLUENT. Different operating conditions are considered within the numerical runs. The obtained numerical results are compared with experimental data and satisfactory agreement is obtained. The effect of syngas fuel composition and the swirl number values on temperature contours, and exhaust gas species concentrations are presented in this paper. The results show an increase of peak flame temperature for the syngas compared to natural gas fuel combustion at the same operating conditions while the NO emission becomes lower. In addition, lower CO2 emissions and increased CO emissions at the combustor exit are obtained for the syngas, compared to the natural gas fuel.

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Jang Munseok, 강기중, and 이용호. "A Study of Combustion Instability Mode in a Dual Swirl Combustor." Journal of the Korean Society of Mechanical Technology 19, no. 5 (October 2017): 592–99. http://dx.doi.org/10.17958/ksmt.19.5.201710.592.

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Lee, J. K., C. G. Hu, Y. S. Shin, and H. S. Chun. "Combustion characteristics of a two-stage swirl-flow fluidized bed combustor." Canadian Journal of Chemical Engineering 68, no. 5 (October 1990): 824–30. http://dx.doi.org/10.1002/cjce.5450680513.

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Peng, Lei, and Jian Zhang. "Simulation of turbulent combustion and NO formation in a swirl combustor." Chemical Engineering Science 64, no. 12 (June 2009): 2903–14. http://dx.doi.org/10.1016/j.ces.2009.03.001.

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Kim, Kyu Tae. "Combustion instability feedback mechanisms in a lean-premixed swirl-stabilized combustor." Combustion and Flame 171 (September 2016): 137–51. http://dx.doi.org/10.1016/j.combustflame.2016.06.003.

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Agwu, Ogbonnaya, and Agustin Valera-Medina. "Diesel/syngas co-combustion in a swirl-stabilised gas turbine combustor." International Journal of Thermofluids 3-4 (May 2020): 100026. http://dx.doi.org/10.1016/j.ijft.2020.100026.

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Kurosaka, Takuya, Shinga Masuda, and Hiroshi Gotoda. "Attenuation of thermoacoustic combustion oscillations in a swirl-stabilized turbulent combustor." Chaos: An Interdisciplinary Journal of Nonlinear Science 31, no. 7 (July 1, 2021): 073121. http://dx.doi.org/10.1063/5.0045127.

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Fooladgar, Ehsan, and C. K. Chan. "Large Eddy Simulation of a Swirl-Stabilized Pilot Combustor from Conventional to Flameless Mode." Journal of Combustion 2016 (2016): 1–16. http://dx.doi.org/10.1155/2016/8261560.

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This paper investigates flame and flow structure of a swirl-stabilized pilot combustor in conventional, high temperature, and flameless modes by means of a partially stirred reactor combustion model to provide a better insight into designing lean premixed combustion devices with preheating system. Finite rate chemistry combustion model with one step tuned mechanism and large eddy simulation is used to numerically simulate six cases in these modes. Results show that moving towards high temperature mode by increasing the preheating level, the combustor is prone to formation of thermalNOxwith higher risks of flashback. In addition, the flame becomes shorter and thinner with higher turbulent kinetic energies. On the other hand, towards the flameless mode, leaning the preheated mixture leads to almost thermalNOx-free combustion with lower risk of flashback and thicker and longer flames. Simulations also show qualitative agreements with available experiments, indicating that the current combustion model with one step tuned mechanisms is capable of capturing main features of the turbulent flame in a wide range of mixture temperature and equivalence ratios.

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Vanoverberghe, K. P., E. V. Van den Bulck, M. J. Tummers, and W. A. Hu¨bner. "Multiflame Patterns in Swirl-Driven Partially Premixed Natural Gas Combustion." Journal of Engineering for Gas Turbines and Power 125, no. 1 (December 27, 2002): 40–45. http://dx.doi.org/10.1115/1.1520159.

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Five different flame states are identified in a compact combustion chamber that is fired by a 30 kW swirl-stabilized partially premixed natural gas burner working at atmospheric pressure. These flame states include a nozzle-attached tulip shaped flame, a nonattached torroidal-ring shaped flame (SSF) suitable for very low NOx emission in a gas turbine combustor and a Coanda flame (CSF) that clings to the bottom wall of the combustion chamber. Flame state transition is generated by changing the swirl number and by premixing the combustion air with 70% of the natural gas flow. The flame state transition pathways reveal strong hysteresis and bifurcation phenomena. The paper also presents major species concentrations, temperature and velocity profiles of the lifted flame state and the Coanda flame and discusses the mechanisms of flame transition and stabilization.

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Vengadesan, S., and C. Sony. "Enhanced vortex stability in trapped vortex combustor." Aeronautical Journal 114, no. 1155 (May 2010): 333–37. http://dx.doi.org/10.1017/s000192400000378x.

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Abstract The Trapped Vortex Combustor (TVC) is a new design concept in which cavities are designed to trap a vortex flow structure established through the use of driver air jets located along the cavity walls. TVC offers many advantages when compared to conventional swirl-stabilised combustors. In the present work, numerical investigation of cold flow (non-reacting) through the two-cavity trapped vortex combustor is performed. The numerical simulation involves passive flow through the two-cavity TVC to obtain an optimum cavity size to trap stable vortices inside the second cavity and to observe the characteristics of the two cavity TVC. From the flow attributes, it is inferred that vortex stability is achieved by circulation and the vortex is trapped inside when a second afterbody is added.

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Journal articles on the topic 'Swirl combustor'

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