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Journal articles on the topic 'Gas turbine swirl injector'

Author: Grafiati

Published: 6 September 2023

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1

Pham, Vu Thanh Nam. "AN IMAGE PROCESSING APPROACH FOR DETERMINING THE SPRAY CONE ANGLE OF A PRESSURE SWIRL INJECTOR EQUIPPED IN A GAS-TURBINE ENGINE." Journal of Science and Technique 16, no. 2 (2022): 33–47. http://dx.doi.org/10.56651/lqdtu.jst.v16.n02.265.

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This paper adopts the directionality tool provided by the ImageJ package to determine the spray cone angle of a gas-turbine engine’s injector. An imaging experiment system has been developed in this study to image a spray of a practical gas-turbine injector under injection pressure conditions varying from 2 to 6 bars. The results show that the reliability of the measurement is achieved when analyzing at least 500 images. Preferably, using 1500 images shows the uncertainty of less than 0.5% (approximately corresponding with 0.2° of the angle). The average spray cone angle varies between 100° an

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2

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

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Abstract The components of an aeroengine gas-turbine combustor have to perform multiple tasks – control of external and internal air distribution, fuel injector feed, fuel/air atomisation, evaporation, and mixing, flame stabilisation, wall cooling, etc. The ‘rich-burn’ concept has achieved great success in optimising combustion efficiency, combustor life, and operational stability over the whole engine cycle. This paper first illustrates the crucial role of aerodynamic processes in achieving these performance goals. Next, the extra aerodynamic challenges of the ‘lean-burn’ injectors required t

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3

So, Younseok, Yeoungmin Han, and Sejin Kwon. "Combustion Characteristics of Multi-Element Swirl Coaxial Jet Injectors under Varying Momentum Ratios." Energies 14, no. 13 (2021): 4064. http://dx.doi.org/10.3390/en14134064.

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The combustion characteristics of a staged combustion cycle engine with an oxidizer-rich preburner were experimentally studied at different momentum ratios of multi-element injectors. Propellants were simultaneously supplied as a liquid–liquid–liquid system, and an injector was designed in which a swirl coaxial jet is sprayed. The injector burned the propellants in the inner chamber which had a temperature greater than 2000 K. To cool the combustion gas, a liquid oxidizer was supplied to the cooling channel outside the injector. To prevent the turbine blades from melting, the temperature of th

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4

WANG, SHANWU, VIGOR YANG, GEORGE HSIAO, SHIH-YANG HSIEH, and HUKAM C. MONGIA. "Large-eddy simulations of gas-turbine swirl injector flow dynamics." Journal of Fluid Mechanics 583 (July 4, 2007): 99–122. http://dx.doi.org/10.1017/s0022112007006155.

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A comprehensive study on confined swirling flows in an operational gas-turbine injector was performed by means of large-eddy simulations. The formulation was based on the Favre-filtered conservation equations and a modified Smagorinsky treatment of subgrid-scale motions. The model was then numerically solved by means of a preconditioned density-based finite-volume approach. Calculated mean velocities and turbulence properties show good agreement with experimental data obtained from the laser-Doppler velocimetry measurements. Various aspects of the swirling flow development (such as the central

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5

Woo, Seongphil, Jungho Lee, Yeoungmin Han, and Youngbin Yoon. "Experimental Study of the Combustion Efficiency in Multi-Element Gas-Centered Swirl Coaxial Injectors." Energies 13, no. 22 (2020): 6055. http://dx.doi.org/10.3390/en13226055.

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The effects of the momentum-flux ratio of propellant upon the combustion efficiency of a gas-centered-swirl-coaxial (GCSC) injector used in the combustion chamber of a full-scale 9-tonf staged-combustion-cycle engine were studied experimentally. In the combustion experiment, liquid oxygen was used as an oxidizer, and kerosene was used as fuel. The liquid oxygen and kerosene burned in the preburner drive the turbine of the turbopump under the oxidizer-rich hot-gas condition before flowing into the GCSC injector of the combustion chamber. The oxidizer-rich hot gas is mixed with liquid kerosene p

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6

Lezsovits, Ferenc, Sándor Könczöl, and Krisztián Sztankó. "CO emission reduction of a HRSG duct burner." Thermal Science 14, no. 3 (2010): 845–54. http://dx.doi.org/10.2298/tsci1003845l.

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A heat-recovery steam generator was erected after a gas-turbine with a duct burner into the district heat centre. After commissioning, the CO emissions were found to be above the acceptable level specified in the initial contract. The Department of Energy Engineering of the BME was asked for their expert contribution in solving the problem of reducing these CO emissions. This team investigated the factors that cause incomplete combustion: the flue-gas outlet of the gas-turbine has significant swirl and rotation, the diffuser in between the gas-turbine and heat-recovery steam generator is too s

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7

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 (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

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8

Sung, Hong-Gye. "Combustion dynamics in a model lean-premixed gas turbine with a swirl stabilized injector." Journal of Mechanical Science and Technology 21, no. 3 (2007): 495–504. http://dx.doi.org/10.1007/bf02916311.

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9

Mardani, Amir, Rezapour Rastaaghi, and Fazlollahi Ghomshi. "Liquid petroleum gas flame in a double-swirl gas turbine model combustor: Lean blow-out, pollutant, preheating." Thermal Science, no. 00 (2020): 139. http://dx.doi.org/10.2298/tsci190623139m.

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In this paper, lean blow-out (LBO) limits in a double swirl gas turbine model combustor were investigated experimentally for Liquid Petroleum Gas (LPG) fuel. The LBO curve was extracted for different combustor configurations. While burner could operate reasonably under ultra-lean conditions, two different sets of operating conditions, one with a low flow rate (LFR) and another one with high flow rate (HFR), are identified and studied in terms of LBO and pollutant. Results showed that while the flame structure was similar in both cases, the chamber responses to geometrical changes and also preh

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10

Cheng, R. K., D. Littlejohn, P. A. Strakey, and T. Sidwell. "Laboratory investigations of a low-swirl injector with H2 and CH4 at gas turbine conditions." Proceedings of the Combustion Institute 32, no. 2 (2009): 3001–9. http://dx.doi.org/10.1016/j.proci.2008.06.141.

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11

Choi, Myeung Hwan, Jeongwoo An, and Jaye Koo. "Breakup Mechanism of a Jet in the L-Shape Crossflow of a Gas Turbine Combustor." Energies 15, no. 9 (2022): 3360. http://dx.doi.org/10.3390/en15093360.

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Experimental investigations are conducted to determine the mechanism and characteristics of a jet in an L-shape crossflow simulating the radial swirl injector of a lean premixed-prevaporized (LPP) combustor. To simplify the radial flow of the actual injector while ignoring the centrifugal effect, the L-shaped 2D-channel is used for the crossflow, and water is used as a fuel simulant. The jet breakup is captured using a high-speed camera, and the density gradient magnitude is post-processed to clarify the spray. The Sauter mean diameter (SMD) of the spray is measured via a laser diffraction met

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12

Cao, Cheng, Yaping Gao, Shaolin Wang, et al. "Numerical Investigation on Mechanism of Swirling Flow of the Prefilming Air-Blast Fuel Injector." Energies 16, no. 2 (2023): 650. http://dx.doi.org/10.3390/en16020650.

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Prefilming air-blast atomizers are widely used in modern gas turbine combustors. Due to insufficient awareness of the coupling mechanism of multi-stage swirling flow in gas turbines, there is a lack of effective methods for flow field optimization in combustor. In this study, the effect of some critical parameters on the flow field of a prefilming air-blast atomizer was analyzed with CFD. The parameters include the angle and number of the first swirler blades, the angle of the second swirler blades and the angle of sleeve. Furthermore, the coupling mechanism of two-stage swirling airflows of p

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13

Ford, C. L., J. F. Carrotte, and A. D. Walker. "The application of porous media to simulate the upstream effects of gas turbine injector swirl vanes." Computers & Fluids 77 (April 2013): 143–51. http://dx.doi.org/10.1016/j.compfluid.2013.03.001.

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14

Littlejohn, D., and R. K. Cheng. "Fuel effects on a low-swirl injector for lean premixed gas turbines." Proceedings of the Combustion Institute 31, no. 2 (2007): 3155–62. http://dx.doi.org/10.1016/j.proci.2006.07.146.

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15

Baba-Ahmadi, M. H., and G. R. Tabor. "Inlet Conditions for Large Eddy Simulation of Gas-Turbine Swirl Injectors." AIAA Journal 46, no. 7 (2008): 1782–90. http://dx.doi.org/10.2514/1.35259.

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16

Daniels, W. A., B. V. Johnson, D. J. Graber, and R. J. Martin. "Rim Seal Experiments and Analysis for Turbine Applications." Journal of Turbomachinery 114, no. 2 (1992): 426–32. http://dx.doi.org/10.1115/1.2929161.

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An experimental investigation was conducted to determine the sealing effectiveness and the aerodynamic characteristics of four rim seal models for a number of flow conditions. The experiments were conducted to obtain an extended data base for advanced turbine rim seal design. The class of rim seals investigated are those found on the downstream side of the rotor where the boundary layer on the disk is pumped directly into the seal gap. The experiments were conducted at disk tangential Reynolds numbers up to 5.1 × 106 with a simulated gas path flow across the top of the seal. The simulated gas

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17

Tolpadi, A. K., D. L. Burrus, and R. J. Lawson. "Numerical Computation and Validation of Two-Phase Flow Downstream of a Gas Turbine Combustor Dome Swirl Cup." Journal of Engineering for Gas Turbines and Power 117, no. 4 (1995): 704–12. http://dx.doi.org/10.1115/1.2815456.

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The two-phase axisymmetric flow field downstream of the swirl cup of an advanced gas turbine combustor is studied numerically and validated against experimental Phase-Doppler Particle Analyzer (PDPA) data. The swirl cup analyzed is that of a single annular GE/SNECMA CFM56 turbofan engine that is comprised of a pair of coaxial counterswirling air streams together with a fuel atomizer. The atomized fuel mixes with the swirling air stream, resulting in the establishment of a complex two-phase flow field within the swirl chamber. The analysis procedure involves the solution of the gas phase equati

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18

Vandervort, C. L. "9 ppm NOx/CO Combustion System for “F” Class Industrial Gas Turbines." Journal of Engineering for Gas Turbines and Power 123, no. 2 (2001): 317–21. http://dx.doi.org/10.1115/1.1362661.

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The Dry Low NOx (DLN) -2.6 combustion system has achieved emission rates of lower than 9 ppm NOx (dry, corrected to 15 percent O2) and CO from 50 to 100 percent load for the GE MS7001FA industrial gas turbine on natural gas. The system uses lean premixed combustion with fuel staging for low load stability. The first unit achieved commercial operation in March of 1996 with a firing temperature of 2350°F. As of September 9, 1999, it has accumulated over 11,800 hours of operation in peaking and base load service. Sixteen more units have since entered commercial service. Emissions data are shown f

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19

Kim, Lina, Ji-Seok Hong, Won Cheol Jeong, Kwang-Hee Yoo, Jong-Chan Kim, and Hong-Gye Sung. "Turbulent Combustion Characteristics of a Swirl Injector in a Gas Turbine Annular Combustor Using LES and Level-set Flamelet." Journal of the Korean Society of Propulsion Engineers 18, no. 2 (2014): 1–9. http://dx.doi.org/10.6108/kspe.2014.18.2.001.

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20

N. R. Kartjanov, M. G. Zhumagulov, and S. B. Sadykova. "AERODYNAMIC FLOWS INSIDE GAS TURBINE COMBUSTION CHAMBER MODULE." Bulletin of Toraighyrov University. Energetics series, no. 4.2021 (November 28, 2021): 33–43. http://dx.doi.org/10.48081/qrfa5104.

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The article contains the results of experiments on the research of aerodynamic parameters in the cylindrical module of the combustion chamber in a gas turbine. The intensity of turbulence and flow velocity are considered in the article as the main factors affecting the efficiency of the formation of the fuel-air mixture and, as a consequence, the efficiency of its subsequent combustion. The air flow is studied under isothermal conditions inside two cylindrical channels of different diameters with swirl blades at the inlet. Turbulence intensity and flow velocity are obtained for various points

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21

Touchton, G. L. "Influence of Gas Turbine Combustor Design and Operating Parameters on Effectiveness of NOx Suppression by Injected Steam or Water." Journal of Engineering for Gas Turbines and Power 107, no. 3 (1985): 706–13. http://dx.doi.org/10.1115/1.3239792.

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Steam or water injection has become the state-of-the-art abatement technique for NOx, with steam strongly preferred for combined-cycle application. In combined-cycle plants, the degradation of the plant efficiency due to steam injection into the gas turbine combustor provides a powerful incentive for minimizing this flow over the entire plant operating map. This paper presents the results of extensive tests carried out on a variety of gas turbine combustor designs. Both test stand and field test data are presented. The usual fuel in the tests is methane; however, some data are presented for co

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22

Heath, Christopher M. "Characterization of Swirl-Venturi Lean Direct Injection Designs for Aviation Gas Turbine Combustion." Journal of Propulsion and Power 30, no. 5 (2014): 1334–56. http://dx.doi.org/10.2514/1.b35077.

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23

Davis, D. W., P. L. Therkelsen, D. Littlejohn, and R. K. Cheng. "Effects of hydrogen on the thermo-acoustics coupling mechanisms of low-swirl injector flames in a model gas turbine combustor." Proceedings of the Combustion Institute 34, no. 2 (2013): 3135–43. http://dx.doi.org/10.1016/j.proci.2012.05.050.

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24

Feitelberg, A. S., V. E. Tangirala, R. A. Elliott, R. E. Pavri, and R. B. Schiefer. "Reduced NOx Diffusion Flame Combustors for Industrial Gas Turbines." Journal of Engineering for Gas Turbines and Power 123, no. 4 (2000): 757–65. http://dx.doi.org/10.1115/1.1376722.

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This paper describes reduced NOx diffusion flame combustors that have been developed for both simple cycle and regenerative cycle MS3002 and MS5002 gas turbines. Laboratory tests have shown that when firing with natural gas, without water or steam injection, NOx emissions from the new combustors are about 40 percent lower than NOx emissions from the standard combustors. CO emissions are virtually unchanged at base load, but increase at part load conditions. Commercial demonstration tests have confirmed the laboratory results. The standard combustors on both the MS3002 and MS5002 gas turbine ar

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25

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 (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

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Paschereit, Christian Oliver, Peter Flohr, and Ephraim J. Gutmark. "Combustion Control by Vortex Breakdown Stabilization." Journal of Turbomachinery 128, no. 4 (2002): 679–88. http://dx.doi.org/10.1115/1.2218521.

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Flame anchoring in a swirl-stabilized combustor occurs in an aerodynamically generated recirculation region which is a result of vortex breakdown (VBD). The characteristics of the recirculating flow are dependent on the swirl number and on axial pressure gradients. Coupling with downstream pressure pulsations in the combustor affects the VBD process. The present paper describes combustion instability that is associated with vortex breakdown. The mechanism of the onset of this instability is discussed. Passive control of the instability was achieved by stabilizing the location of vortex breakdo

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27

Akinyemi, Oladapo S., and Lulin Jiang. "Development and combustion characterization of a novel twin-fluid fuel injector in a swirl-stabilized gas turbine burner operating on straight vegetable oil." Experimental Thermal and Fluid Science 102 (April 2019): 279–90. http://dx.doi.org/10.1016/j.expthermflusci.2018.11.014.

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28

Vermes, G., L. E. Barta, and J. M. Bee´r. "Low NOx Emission From an Ambient Pressure Diffusion Flame Fired Gas Turbine Cycle (APGC)." Journal of Engineering for Gas Turbines and Power 125, no. 1 (2002): 46–50. http://dx.doi.org/10.1115/1.1520160.

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The prospects of reduced NOx emission, improved efficiency, stable, and oscillation-free combustion, and reduced construction costs achieved by an “Inverted Brayton Cycle” applied to midsize (0.5 to 5.0 MWe) power plants are discussed. In this cycle, the combustion products of an atmospheric pressure combustor are expanded in the gas turbine to subatmospheric pressure and following heat extraction are compressed back to slightly above the atmospheric, sufficient to enable a controlled fraction of the exhaust gas to be recirculated to the combustor. Due to the larger volume flow rate of the gas

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29

Crocker, D. S., and C. E. Smith. "Numerical Investigation of Enhanced Dilution Zone Mixing in a Reverse Flow Gas Turbine Combustor." Journal of Engineering for Gas Turbines and Power 117, no. 2 (1995): 272–81. http://dx.doi.org/10.1115/1.2814091.

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An advanced method for dilution zone mixing in a reverse flow gas turbine combustor was numerically investigated. For long mixing lengths associated with reverse flow combustors (X/H > 2.0), pattern factor was found to be mainly driven by nozzle-to-nozzle fuel flow and/or circumferential airflow variations; conventional radially injected dilution jets could not effectively mix out circumferential nonuniformities. To enhance circumferential mixing, dilution jets were angled to produce a high circumferential (swirl) velocity component. The jets on the outer liner were angled in one direction

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30

Feitelberg, Alan S., Michael D. Starkey, Richard B. Schiefer, et al. "Performance of a Reduced NOx Diffusion Flame Combustor for the MS5002 Gas Turbine." Journal of Engineering for Gas Turbines and Power 122, no. 2 (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

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31

Kuharonak, G. M., M. Klesso, A. Predko, and D. Telyuk. "Organization of Six-Cylinder Tractor Diesel Working Process." Science & Technique 20, no. 5 (2021): 427–33. http://dx.doi.org/10.21122/2227-1031-2021-20-5-427-433.

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The purpose of the work is to consider the organization of the working process of six-cylinder diesel engines with a power of 116 and 156 kW and exhaust gas recirculation. The following systems and components were used in the experimental configurations of the engine: Common Rail BOSСH accumulator fuel injection system with an injection pressure of 140 MPa, equipped with electro-hydraulic injectors with seven-hole nozzle and a 500 mm3 hydraulic flow; direct fuel injection system with MOTORPAL fuel pump with a maximum injection pressure of 100 MPa, equipped with MOTORPAL and AZPI five-hole nozz

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32

Correa, S. M., A. J. Dean, and I. Z. Hu. "Combustion Technology for Low-Emissions Gas-Turbines:Selected Phenomena Beyond NOx." Journal of Energy Resources Technology 118, no. 3 (1996): 193–200. http://dx.doi.org/10.1115/1.2793862.

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Since recent reviews cover the issues in NOx formation under gas-turbine canditions, and since regulations essentially dictate use of the premixed mode of combustion for minimum NOx, this review concentrates on phenomena that can arise in premixed combustion. Specifically, 1) the initial unmixedness in a fuel-air premixer has been shown to make overall lean mixtures autoignite sooner than might be expected based on the overall fuel-air ratio, because the richer portions of the mixture lead the process;2) combustion pressure oscillations caused by the interplay between acoustic waves and unstea

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33

Zhang, Tao, Bo Dong, Xun Zhou, Linan Guan, Weizhong Li, and Shengqi Zhou. "Experimental Study of Spray Characteristics of Kerosene-Ethanol Blends from a Pressure-Swirl Nozzle." International Journal of Aerospace Engineering 2018 (November 7, 2018): 1–14. http://dx.doi.org/10.1155/2018/2894908.

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Partial replacement of kerosene by ethanol in a gas turbine is regarded as a good way to improve the spray quality and reduce the fossil energy consumption. The present work is aimed at studying the spray characteristics of kerosene-ethanol blends discharging from a pressure-swirl nozzle. The spray cone angle, discharge coefficient, breakup length, and velocity distribution are obtained by particle image velocimetry, while droplet size is acquired by particle/droplet imaging analysis. Kerosene, E10 (10% ethanol, 90% kerosene), E20 (20% ethanol, 80% kerosene), and E30 (30% ethanol, 70% kerosene

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Kim, Sangwook, Hyungyu Lee, Jungsoo Lee, Donghwa Kim, and Jinsoo Cho. "Comparative Study on a Tangential and Radial On-Board Injection Pre-swirl System of Gas Turbine Secondary Air System." KSFM Journal of Fluid Machinery 21, no. 1 (2018): 19–26. http://dx.doi.org/10.5293/kfma.2018.21.1.019.

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35

Payri, R., R. Novella, M. Carreres, and M. Belmar-Gil. "Modeling gaseous non-reactive flow in a lean direct injection gas turbine combustor through an advanced mesh control strategy." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 11 (2020): 1788–810. http://dx.doi.org/10.1177/0954410020919619.

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Fuel efficiency improvement and harmful emissions reduction are the main motivations for the development of gas turbine combustors. Numerical computational fluid dynamics (CFD) simulations of these devices are usually computationally expensive since they imply a multi-scale problem. In this work, gaseous non-reactive unsteady Reynolds-Averaged Navier–Stokes and large eddy simulations of a gaseous-fueled radial-swirled lean direct injection combustor have been carried out through CONVERGE™ CFD code by solving the complete inlet flow path through the swirl vanes and the combustor. The geometry c

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36

Wang, H. Y., V. G. McDonell, and S. Samuelsen. "Influence of Hardware Design on the Flow Field Structures and the Patterns of Droplet Dispersion: Part I—Mean Quantities." Journal of Engineering for Gas Turbines and Power 117, no. 2 (1995): 282–89. http://dx.doi.org/10.1115/1.2814092.

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In a gas turbine engine combustor, performance is likely tied to the spatial distribution of the fuel injected into the dome. The GE/SNECMA CFM56 combustor swirl cup is one example of a design established to provide a uniform presentation of droplets to the dome. The present study is part of a series to detail the dispersion of droplets in practical hardware, and to assess the effect of isolated parameters on the continuous- and dispersed-phase distributions. In this study, the influence of the swirling air outlet geometry is evaluated relative to the effect on the flow field structures and th

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37

BARATA, Jorge. "On the modeling of droplet transport, dispersion and evaporation in turbulent flows." Combustion Engines 122, no. 3 (2005): 42–55. http://dx.doi.org/10.19206/ce-117399.

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The present paper presents a numerical study on evaporating droplets injected through a turbulent cross-stream. Several models have been used with more or less success to describe similar phenomena, but much of the reported work deals only with sprays in stagnant surroundings. The ultimate goal of this study is to develop an Eulerian/Lagragian approach to account for turbulent transport, dispersion, evaporation and coupling between both processes in practical spray injection systems, which usually include air flows in the combustion chamber like swirl, tumble and squish in I.C. engines or cros

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38

Dulin, Vladimir, Leonid Chikishev, Dmitriy Sharaborin, et al. "On the Flow Structure and Dynamics of Methane and Syngas Lean Flames in a Model Gas-Turbine Combustor." Energies 14, no. 24 (2021): 8267. http://dx.doi.org/10.3390/en14248267.

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The present paper compares the flow structure and flame dynamics during combustion of methane and syngas in a model gas-turbine swirl burner. The burner is based on a design by Turbomeca. The fuel is supplied through injection holes between the swirler blades to provide well-premixed combustion, or fed as a central jet from the swirler’s centerbody to increase flame stability via a pilot flame. The measurements of flow structure and flame front are performed by using the stereo particle image velocimetry and OH planar laser-induced fluorescence methods. The measurements are performed for the a

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Fossi, Alain, Alain DeChamplain, and Benjamin Akih-Kumgeh. "Unsteady RANS and scale adaptive simulations of a turbulent spray flame in a swirled-stabilized gas turbine model combustor using tabulated chemistry." International Journal of Numerical Methods for Heat & Fluid Flow 25, no. 5 (2015): 1064–88. http://dx.doi.org/10.1108/hff-09-2014-0272.

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Purpose – The purpose of this paper is to numerically investigate the three-dimensional (3D) reacting turbulent two-phase flow field of a scaled swirl-stabilized gas turbine combustor using the commercial computational fluid dynamic (CFD) software ANSYS FLUENT. The first scope of the study aims to explicitly compare the predictive capabilities of two turbulence models namely Unsteady Reynolds Averaged Navier-Stokes and Scale Adaptive Simulation for a reasonable trade-off between accuracy of results and global computational cost when applied to simulate swirl-stabilized spray combustion. The se

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Somarathne, Kapuruge Don Kunkuma Amila, Sotaro Hatakeyama, Akihiro Hayakawa, and Hideaki Kobayashi. "Numerical study of a low emission gas turbine like combustor for turbulent ammonia/air premixed swirl flames with a secondary air injection at high pressure." International Journal of Hydrogen Energy 42, no. 44 (2017): 27388–99. http://dx.doi.org/10.1016/j.ijhydene.2017.09.089.

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Arai, Masataka, Kenji Amagai, and Toshio Mogi. "Catalytic Combustion of Pre-Vaporized Liquid Fuel." Journal of Energy Resources Technology 123, no. 1 (2000): 44–49. http://dx.doi.org/10.1115/1.1345893.

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Fundamental characteristics of the catalytic combustion of vaporized kerosene spray were experimentally investigated. This study is a part of the development of a ceramic gas turbine engine for automobiles. Kerosene was used as a test fuel and its spray was injected from a swirl atomizer into a hot air stream. The inlet air temperature was elevated up to 900 K to vaporize the kerosene spray. Premixed gas of air and kerosene vapor was introduced into the catalyst. The total equivalence ratio was controlled from ϕ=0.18–0.32. The palladium catalyst was supported on a cordierite honeycomb monolith

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Anand, Rahul, PR Ajayalal, Vikash Kumar, A. Salih, and K. Nandakumar. "Spray and atomization characteristics of gas-centered swirl coaxial injectors." International Journal of Spray and Combustion Dynamics 9, no. 2 (2016): 127–40. http://dx.doi.org/10.1177/1756827716660225.

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To achieve uniform and efficient combustion in a rocket engine, a fine uniform spray is needed. The same is achieved by designing an injector with good atomization characteristics. Gas-centered swirl coaxial (GCSC) injector elements have been preferred recently in liquid rocket engines because of an inherent capability to dampen the pressure oscillations in the thrust chamber. The gas-centered swirl coaxial injector chosen for this study is proposed to be used in a semi-cryogenic rocket engine operating with oxidizer rich hot exhaust gases from the pre-burner and liquid kerosene as fuel. In th

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Siddharth, K. S., Mahesh V. Panchagnula, and T. John Tharakan. "EFFECT OF GAS SWIRL ON THE PERFORMANCE OF A GAS-CENTERED SWIRL CO-AXIAL INJECTOR." Atomization and Sprays 27, no. 8 (2017): 741–57. http://dx.doi.org/10.1615/atomizspr.2017019923.

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Yang, Li-jun, Ming-he Ge, Meng-zheng Zhang, Qing-fei Fu, and Guo-biao Cai. "Spray Characteristics of Recessed Gas-Liquid Coaxial Swirl Injector." Journal of Propulsion and Power 24, no. 6 (2008): 1332–39. http://dx.doi.org/10.2514/1.23977.

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Khalil, Ahmed E. E., and Ashwani K. Gupta. "Distributed swirl combustion for gas turbine application." Applied Energy 88, no. 12 (2011): 4898–907. http://dx.doi.org/10.1016/j.apenergy.2011.06.051.

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Jia, Lei, Shi Liu, Yao Song Huang, Neng Wang, Fu Zhen Wang, and Zhi Hong Li. "Numerical Simulation of Burner for Micro Gas Turbine." Advanced Materials Research 569 (September 2012): 51–55. http://dx.doi.org/10.4028/www.scientific.net/amr.569.51.

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In order to study affects of oxy fuel combustion on micro gas turbine ,three axial swirl burners with different installation angles for micro gas turbine were designed, flue gas recycle/oxy fuel was used to burn natural gas. Numerical simulation was used to study flow field and combustion conditions. The result shows that application of axial swirl burner promotes mixing process of natural gas and oxygen and recirculation brought about to promote the stability of fire, uniformity of outlet temperature was reduced. With the increase of swirl installation angle, backflow becomes more intense, an

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Chong, Cheng Tung, and Simone Hochgreb. "Flow Field of a Model Gas Turbine Swirl Burner." Advanced Materials Research 622-623 (December 2012): 1119–24. http://dx.doi.org/10.4028/www.scientific.net/amr.622-623.1119.

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The flow field of a lab-scale model gas turbine swirl burner was characterised using particle imaging velocimetry (PIV) at atmospheric condition. The swirl burner consists of an axial swirler, a twin-fluid atomizer and a quartz tube as combustor wall. The main non-reacting swirling air flow without spray was compared to swirl flow with spray under unconfined and enclosed conditions. The introduction of liquid fuel spray changes the flow field of the main swirling air flow at the burner outlet where the radial velocity components are enhanced. Under reacting conditions, the enclosure generates

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Johnson, M. R., D. Littlejohn, W. A. Nazeer, K. O. Smith, and R. K. Cheng. "A comparison of the flowfields and emissions of high-swirl injectors and low-swirl injectors for lean premixed gas turbines." Proceedings of the Combustion Institute 30, no. 2 (2005): 2867–74. http://dx.doi.org/10.1016/j.proci.2004.07.040.

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Ghaffar, Zulkifli Abdul, Ahmad Hussein Abdul Hamid, and Mohd Syazwan Firdaus Mat Rashid. "Spray Characteristics of Swirl Effervescent Injector in Rocket Application: A Review." Applied Mechanics and Materials 225 (November 2012): 423–28. http://dx.doi.org/10.4028/www.scientific.net/amm.225.423.

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Injector is one of the vital devices in liquid rocket engine (LRE) as small changes in its configurations and design can result in significantly different LRE performance. Characteristics of spray such as spray cone angle, breakup length and Sauter mean diameter (SMD) are examples of crucial parameters that play the important role in the performance of liquid propellant rocket engine. Wider spray cone angle is beneficial for widespread of fuel in the combustion chamber for fast quiet ignition and a shorter breakup length provides shorter combustion chamber to be utilized and small SMD will res

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Woo, Seongphil, Jungho Lee, Ingyu Lee, Seunghan Kim, Yeoungmin Han, and Youngbin Yoon. "Analyzing Combustion Efficiency According to Spray Characteristics of Gas-Centered Swirl-Coaxial Injector." Aerospace 10, no. 3 (2023): 274. http://dx.doi.org/10.3390/aerospace10030274.

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The momentum flux ratio (MFR) significantly affects the mixing characteristics and combustion efficiency of propellants in rocket engine injectors. The spray characteristics of three gas-centered swirl-coaxial injectors used in a full-scale combustion test were investigated according to the change in the momentum flux ratio. The difference in combustion efficiency was analyzed through the comparison with combustion test results using spray visualization and quantification. The spray cross-sectional shape and droplet distribution were measured using a structured laser illumination planar imagin

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