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Journal articles on the topic 'Gas Turbine Swirl Injectors'

Author: Grafiati

Published: 6 September 2023

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1

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

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

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2

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 (November 19, 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 passed through combustion chamber’s cooling channel at the injector outlet. This mixture has a dimensionless momentum-flux ratio that depends upon the dispensing speed of the two fluids. Combustion tests were performed under varying mixture ratios and combustion pressures for different injector shapes and numbers of injectors, and the characteristic velocities and performance efficiencies of the combustion were compared. It was found that, for 61 gas-centered swirl-coaxial injectors, as the moment flux ratio increased from 9 to 23, the combustion-characteristic velocity increased linearly and the performance efficiency increased from 0.904 to 0.938. In addition, excellent combustion efficiency was observed when the combustion chamber had a large number of injectors at the same momentum-flux ratio.

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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 (July 5, 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 the combustion gas was maintained below 700 K. To confirm the combustion characteristics at different momentum ratios of the high-temperature combustion gas inside the injector and the low-temperature liquid oxidizer outside the injector, three types of injectors were designed and manufactured with different momentum ratios: MR 3.0, MR 3.3, and MR 3.7. In this study, the results of the combustion test for each type were compared for 30 s. For ORPB-A, a combustion pressure of 18.5 MPaA, fuel mass flow rate of 0.26 kg/s, oxidizer mass flow rate of 15.3 kg/s, and turbine inlet temperature of 686 K were obtained in the combustion stability period of 29.0–29.5 s. The combustion efficiency was 98% for MR 3.0 (ORPB-A), which was superior to that for other momentum ratios. In addition, during the combustion test for MR 3.0, the fluctuations in the characteristic velocity, combustion pressure, and propellant mass flow rate were low, indicating that combustion was stable. The three types of combustion instability were all less than 0.8%, thus confirming that the combustion stability was excellent.

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4

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

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5

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 (August 29, 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° and 128.15° when the injection pressure increases from 2 to 6 bars. An accurate determination of the spray cone angle helps to improve the quality of research on micro and macro spray characteristics including the droplet concentration and distribution. The results could also be utilized to develop a diagnostic technique for gas-turbine injectors.

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6

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 (January 2005): 2867–74. http://dx.doi.org/10.1016/j.proci.2004.07.040.

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7

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 recirculating flow, precessing vortex core and Kelvin–Helmholtz instability) were explored in detail. Both co- and counter-rotating configurations were considered, and the effects of swirl direction on flow characteristics were examined. The flow evolution inside the injector is dictated mainly by the air delivered through the primary swirler. The impact of the secondary swirler appears to be limited.

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8

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 (January 1, 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 for operation on natural gas. The DLN-2.6 system can operate on liquid fuel with water injection for NOx abatement. Power augmentation with steam injection is allowable while operating on natural gas. The premixed gas nozzles utilize swirl for flame stabilization. Aerodynamically shaped natural gas injectors are applied for flashback or flame-holding resistance.

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9

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 short and has a large cone angle, the velocity of flue-gas entering the duct burner is greater than expected, and the outlet direction of the flammable mixture from the injector of the duct burner was not optimal. After reducing the flow swirl of flue-gas and modifying the nozzle of the duct burner as suggested by the Department of Energy Engineering of the BME, CO emissions have been reduced to an acceptable level. The method involves the application of CFD modeling and studying images of the flames which proved to be very informative.

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10

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 (September 1, 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 unsteady heat release in a one-dimensional system can be calculated in good accordance with measured data, and set the stage for multi-dimensional CFD;3) carbon deposition arising from the flow of liquid fuel over metal surfaces such as found in fuel injectors and swirl cups has been described as a function of temperature and of surface composition; and 4) quenching and subsequent emissions of carbon monoxide can be minimized by preservation of a boundary-layer rather than an impingement type of flow over combustor liners.

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11

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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12

Kuharonak, G. M., M. Klesso, A. Predko, and D. Telyuk. "Organization of Six-Cylinder Tractor Diesel Working Process." Science & Technique 20, no. 5 (October 7, 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 nozzle injectors; two combustion chambers with volumes of 55 and 56 cm3 and bowl diameters of 55.0 and 67.5 mm, respectively; cylinder heads providing a 3.0–4.0 swirl ratio for Common Rail system, 3.5–4.5 for mechanical injection system. The recirculation rate was set by gas throttling before the turbine using a rotary valve of an original design. The tests have been conducted at characteristic points of the NRSC cycle: minimum idle speed 800 rpm, maximum torque speed 1600 rpm, rated power speed 2100 rpm. It has been established that it is possible to achieve the standards of emissions of harmful substances: on the 116 kW diesel engine using of direct-action fuel equipment and a semi-open combustion chamber; on the 156 kW diesel using Common Rail fuel supply system of the Low Cost type and an open combustion chamber.

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13

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 (March 2007): 495–504. http://dx.doi.org/10.1007/bf02916311.

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14

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 preheating are minimal at the LFR. That means confinement and injector type have desirable effects on stability borders but not for the LFR. The channeled injector shifted down the LBO limit around 28 percent at HFR. Measurements on the combustor exhaust gas composition and temperature indicate a region with relatively complete combustion and reasonable temperature and a very low level of exhaust NOx pollutants (i.e., below ten ppm) at about 25-50% above the LBO. In this operating envelope, a burner power increment led to a higher exhaust average temperature and combustion efficiency, while NOx formation decreased. Preheating the inlet air up to 100?C results in an improvement in burner stability in about 10 percent, but NOx production intensifies more than three times. Results indicate that the LBO limit is configured more by the burner design and aerodynamic aspects rather than the fuel type.

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15

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 (October 1, 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 equations in an Eulerian frame of reference using the code CONCERT. CONCERT has been developed and used extensively in the past and represents a fully elliptic body-fitted computational fluid dynamics code to predict flow fields in practical full-scale combustors. The flow in this study is assumed to be nonreacting and isothermal. The liquid phase is simulated by using a droplet spray model and by treating the motion of the fuel droplets in a Lagrangian frame of reference. Extensive PDPA data for the CFM56 engine swirl cup have been obtained at atmospheric pressure by using water as the fuel (Wang et al., 1992a). The PDPA system makes pointwise measurements that are fundamentally Eulerian. Measurements have been made of the continuous gas phase velocity together with discrete phase attributes such as droplet size, droplet number count, and droplet velocity distribution at various axial stations downstream of the injector. Numerical calculations were performed under the exact inlet and boundary conditions as the experimental measurements. The computed gas phase velocity field showed good agreement with the test data. The agreement was found to be best at the stations close to the primary venturi of the swirler and to be reasonable at later stations. The unique contribution of this work is the formulation of a numerical PDPA scheme for comparing droplet data. The numerical PDPA scheme essentially converts the Lagrangian droplet phase data to the format of the experimental PDPA. Several sampling volumes (bins) were selected within the computational domain. The trajectories of various droplets passing through these volumes were monitored and appropriately integrated to obtain the distribution of the droplet characteristics in space. The calculated droplet count and mean droplet velocity distributions were compared with the measurements and showed very good agreement in the case of larger size droplets and fair agreement for smaller size droplets.

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16

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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17

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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18

Cao, Cheng, Yaping Gao, Shaolin Wang, Fuqiang Liu, Cunxi Liu, Yong Mu, Deqing Mei, and Gang Xu. "Numerical Investigation on Mechanism of Swirling Flow of the Prefilming Air-Blast Fuel Injector." Energies 16, no. 2 (January 5, 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 prefilming air-blast atomizer was discussed. Moreover, the influence of the interaction between two-stage counter swirling airflows on the characteristics of flow field was explained. The results show that with the increase in SNi, the axial length of the primary recirculation zone decreased, while the radial width increased. The starting position of primary recirculation zone (PRZ) moves forward with the increase in SNo. Reducing the sleeve angle β helps to form the primary recirculation zone. The results indicate that it is the transition of tangential velocity of airflow to radial velocity that promotes the formation of the PRZ. These results provide theoretical support for optimization of the flow field in swirl combustor.

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19

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 (May 5, 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 method with a helium–neon laser optical system (HELOS). The characteristics of the jet in the L-shape crossflow are compared with the characteristics of the jet in a typical crossflow through the flat channel. The results for different outlet heights of the L-shape channel (H/d0) and different injector positions (L/d0) are presented. A dimensionless number (τ) consisting of a time ratio is introduced to describe the jet characteristics. In a previous work, the spraying tendency was demonstrated for different injector positions. In addition, the effect of the recirculation area on H/d0 was empirically shown. H/d0 determines the size of the recirculation area, and the range of τ determines the jet breakup mechanism inside the L-shape channel. The results of this study present the breakup mechanism of the jet in the L-shape channel flow, which simulates a jet in a radial swirler injector for gas turbine engines. It is expected that these results can be used to assist in designing gas turbine engines with more combustion efficiency.

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20

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 (April 1, 2014): 1–9. http://dx.doi.org/10.6108/kspe.2014.18.2.001.

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21

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 (January 2013): 3135–43. http://dx.doi.org/10.1016/j.proci.2012.05.050.

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22

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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23

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 (August 5, 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 this paper, nine different configurations of gas-centered swirl coaxial injector, sorted out by studying the spray angle and coefficient of discharge with swirl number varying from 9 to 20 and recess ratio of 0.5, 1, and 1.5 are investigated for their atomization characteristics. Spray uniformity, spray cone angle, and droplet size in terms of Sauter mean diameter and mass median diameter are studied at various momentum flux ratios for all configurations. Sauter mean diameter is almost independent of recess ratio, whereas cone angle was inversely proportional to the recess ratio. A finer atomization was observed for injectors of high swirl number but the pressure drop also increased to achieve the same flow rate. An injector of medium swirl number and recess ratio of 1.5 is deemed most fit for above-mentioned application.

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24

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 (January 2007): 3155–62. http://dx.doi.org/10.1016/j.proci.2006.07.146.

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25

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

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26

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, and uniformity of outlet temperature becomes smaller, however, total pressure loss coefficient increased. These results will have a great significance in the design of better burners.

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27

Fu, Qing-fei. "Numerical simulation of the internal flow of swirl atomizer under ambient pressure." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 230, no. 15 (August 8, 2016): 2650–59. http://dx.doi.org/10.1177/0954406215598803.

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This paper presents the simulation study of internal flow of open-end swirl injectors under steady and oscillating ambient pressures. A two-dimensional swirl axisymmetric model based on the volume of fluid method was developed to study the effect of ambient pressure on the internal flow of open-end swirl injectors. The response of injector flow to the ambient pressure oscillation was investigated by superimposing periodical oscillation of ambient pressure at the spout outlet. The results show that the variation of ambient pressure affects the liquid phase volumetric fraction within the gas–liquid shear layer. The spray angle near the wall remains constant independent of the ambient pressure. The velocity distribution on different axial sections rarely varies with ambient pressure. When the ambient pressure oscillated, the ambient pressure oscillation would cause the flow rate oscillation at the spout. The phase delay between the flow rate oscillation at spout and the ambient pressure oscillation is proportional to the oscillation frequency.

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28

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 a corner recirculation zone that intensifies the strength of the radial velocity. Comparison of the flow fields with a spray flame using diesel and palm biodiesel shows very similar flow fields. The flow field data can be used as validation target for swirl flame modelling.

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29

Son, Jinwoo, Chae Hoon Sohn, Gujeong Park, and Youngbin Yoon. "Spray Patterns and Injection Characteristics of Gas-Centered Swirl Coaxial Injectors." Journal of Aerospace Engineering 30, no. 5 (September 2017): 04017035. http://dx.doi.org/10.1061/(asce)as.1943-5525.0000745.

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30

Park, Gujeong, Jungho Lee, Ingyu Lee, and Youngbin Yoon. "Spray Characteristics of Gas-Centered Swirl Coaxial Injectors according to Injection Conditions." Journal of ILASS-Korea 19, no. 4 (December 31, 2014): 167–73. http://dx.doi.org/10.15435/jilasskr.2014.19.4.167.

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31

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 (March 10, 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 imaging technique. As the swirl effect was more apparent at a low MFR, the flow rate of the liquid that was sprayed outside was high. The flow rate of the liquid sprayed around the gas injection increased with the MFR. The Sauter mean diameter (SMD) of each injector liquid spray was obtained using the laser shadow imaging method. The SMD decreased as the MFR of all injector types increased, and the injector with a high liquid flow rate and small SMD injected towards the gas center exhibited higher combustion efficiency than the injector with a dominant liquid spray and the large SMD at a large injection angle. The outcomes of the study could help contribute to the increase in the combustion efficiency of the full-scale staged combustion cycle engine combustor.

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32

Kang, Zhongtao, Qinglian Li, Jiaqi Zhang, and Peng Cheng. "Effects of gas liquid ratio on the atomization characteristics of gas-liquid swirl coaxial injectors." Acta Astronautica 146 (May 2018): 24–32. http://dx.doi.org/10.1016/j.actaastro.2018.02.026.

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33

Perevoschikov, S. I. "PROCEDURE OF PARAMETRIC DIAGNOSTICS OF GAS PUMPING UNITSWITH TURBINE DRIVE." Oil and Gas Studies, no. 5 (November 1, 2016): 101–8. http://dx.doi.org/10.31660/0445-0108-2016-5-101-108.

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The article describes the procedure of parametric diagnostics of gas pumping units with a turbine drive which enables to detect the unit state on the minimum information base with determination of the diagnostic conclusions probability. A two-level diagnostics is considered, namely by the units basic components (their injectors and gas turbine units, GTU) and by the GTU components (axial compressors, turbines and combustion chambers).

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34

Jeong, Gijeong, Yeseung Lee, Juntae Yoon, Hyeontaek Jo, and Youngbin Yoon. "ATOMIZATION AND DISTRIBUTION OF DROPLETS IN GAS-LIQUID SPRAYS BY COAXIAL SWIRL INJECTORS." Atomization and Sprays 30, no. 8 (2020): 607–26. http://dx.doi.org/10.1615/atomizspr.2020033825.

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35

Wang, Xingjian, Liwei Zhang, Yixing Li, Shiang-Ting Yeh, and Vigor Yang. "Supercritical combustion of gas-centered liquid-swirl coaxial injectors for staged-combustion engines." Combustion and Flame 197 (November 2018): 204–14. http://dx.doi.org/10.1016/j.combustflame.2018.07.018.

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36

Zhang, Liwei, Xingjian Wang, Yixing Li, Shiang-Ting Yeh, and Vigor Yang. "Supercritical fluid flow dynamics and mixing in gas-centered liquid-swirl coaxial injectors." Physics of Fluids 30, no. 7 (July 2018): 075106. http://dx.doi.org/10.1063/1.5026786.

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37

Greenberg, Steven J., Neil K. McDougald, Christopher K. Weakley, Robert M. Kendall, and Leonel O. Arellano. "Surface-Stabilized Fuel Injectors With Sub-Three PPM NOx Emissions for a 5.5 MW Gas Turbine Engine." Journal of Engineering for Gas Turbines and Power 127, no. 2 (April 1, 2005): 276–85. http://dx.doi.org/10.1115/1.1839920.

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ALZETA Corporation has developed surface-stabilized fuel injectors for use with lean premixed combustors which provide extended turndown and ultralow NOx emission performance. These injectors use a patented technique to form interacting radiant and blue-flame zones immediately above a selectively perforated porous metal surface. This allows stable operation at low reaction temperatures. A previous ASME paper (IJPGC2002-26088) described the development of this technology from the proof-of-concept stage to prototype testing. In 2002 development of these fuel injectors for the 5.5 MW turbine accelerated. Additional single-injector rig tests were performed which also demonstrated ultralow emissions of NOx and CO at pressures up to 1.68 MPa (16.6 atm) and inlet temperatures up to 670°K (750°F). A pressurized multi-injector “sector rig” test was conducted in which two injectors were operated simultaneously in the same geometric configuration as that expected in the engine combustor liner. The multi-injector package was operated with various combinations of fired and unfired injectors, which resulted in low emissions performance and no adverse affects due to injector proximity. To date sub-3 ppm NOx emissions with sub-10 ppm CO emissions have been obtained over an operating range of 0.18–1.68 MPa (1.8–16.6 atm), inlet temperatures from 340 to 670K (186–750°F), and adiabatic flame temperatures from 1740 to 1840K (2670–2850°F). A full scale multi-injector engine simulation is scheduled for the beginning of 2003, with engine tests beginning later that year.

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38

Hu, Bo, Yulong Yao, Minfeng Wang, Chuan Wang, and Yanming Liu. "Flow and Performance of the Disk Cavity of a Marine Gas Turbine at Varying Nozzle Pressure and Low Rotation Speeds: A Numerical Investigation." Machines 11, no. 1 (January 5, 2023): 68. http://dx.doi.org/10.3390/machines11010068.

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In marine gas turbines, variations in rotational speed occur all the time. To ensure adequate cooling effects on the turbine blades, the valves need to be adjusted to change the pressure upstream of the pre-swirl nozzle. Changing such pressure will have significant effects on the local or overall parameters, such as core swirl ratio, temperature, flow rate coefficient, moment coefficient, axial thrust coefficient, etc. In this paper, we studied the flow characteristics within the pre-swirl system of a marine gas turbine at low rotational speed by varying the pressure at the pre-swirl nozzle. The corresponding global Reynolds number ranged from Re = 2.3793 × 105 to 9.5172 × 105. The flow in the rotor-stator cavities was analyzed to find the effects of nozzle pressure on the radial velocity, core swirl ratio, and pressure. According to the simulation results, we introduced a new leakage flow term into the formulary in the references to calculate the values of K between the inner seal and the pre-swirl nozzle. The matching characteristics between the pre-swirl nozzle and the inclined receiving hole was predicted. Performance of the pre-swirl system was also analyzed, such as the pressure drop, through-flow capacity, and cooling effects. After that, the moment coefficient and the axial thrust coefficient were predicted. This study provides some reference for designers to better design the pre-swirl system.

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39

Adzic, Miroljub, Marija Zivkovic, Vasko Fotev, Aleksandar Milivojevic, and Vuk Adzic. "Influential parameters of nitrogen oxides emissions for microturbine swirl burner with pilot burner." Chemical Industry 64, no. 4 (2010): 357–63. http://dx.doi.org/10.2298/hemind100319019a.

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Swirl burners are the most common type of device in wide range of applications, including gas turbine combustors. Due to their characteristics, swirl flows are extensively used in combustion systems because they enable high energy conversion in small volume with good stabilization behavior over the wide operating range. The flow and mixing process generated by the swirl afford excellent flame stability and reduced NOx emissions. Experimental investigation of NOx emission of a purposely designed micro turbine gas burner with pilot burner is presented. Both burners are equipped with swirlers. Mixtures of air and fuel are introduced separately: through the inner swirler - primary mixture for pilot burner, and through the outer swirler - secondary mixture for main burner. The effects of swirl number variations for the both burners were investigated, including parametric variations of the thermal power and air coefficient. It was found that the outer swirler affects the emission of NOx only for the air coefficient less than 1.4. The increase of swirl number resulted in decrease of NOx emission. The inner swirler and thermal power were found to have negligible effect on emission.

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40

Semenov, A. N., and A. A. Sazanov. "Improving the efficiency of assembly technology for fuel injectors of gas-turbine engines by management of functional parameters of spray package parts." Izvestiya MGTU MAMI 8, no. 1-2 (March 10, 2014): 79–84. http://dx.doi.org/10.17816/2074-0530-67748.

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The article considers the problem of ensuring the quality of fuel injectors for gas-turbine engines at assembly time. The way of increasing the effectiveness of the implementation of the assembly process is discussed.

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41

Liu, Jiao, Jinfu Liu, Daren Yu, Myeongsu Kang, Weizhong Yan, Zhongqi Wang, and Michael Pecht. "Fault Detection for Gas Turbine Hot Components Based on a Convolutional Neural Network." Energies 11, no. 8 (August 17, 2018): 2149. http://dx.doi.org/10.3390/en11082149.

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Gas turbine hot component failures often cause catastrophic consequences. Fault detection can improve the availability and economy of hot components. The exhaust gas temperature (EGT) profile is usually used to monitor the performance of the hot components. The EGT profile is uniform when the hot component is healthy, whereas hot component faults lead to large temperature differences between different EGT values. The EGT profile swirl under different operating and ambient conditions also cause temperature differences. Therefore, the influence of EGT profile swirl on EGT values must be eliminated. To improve the detection sensitivity, this paper develops a fault detection method for hot components based on a convolutional neural network (CNN). This paper demonstrates that a CNN can extract the information between adjacent EGT values and consider the impact of the EGT profile swirl. This paper reveals, in principle, that a CNN is a viable solution for dealing with fault detection for hot components. Based on the distribution characteristics of EGT thermocouples, the circular padding method is developed in the CNN. The sensitivity of the developed method is verified by real-world data. Moreover, the developed method is visualized in detail. The visualization results reveal that the CNN effectively considers the influence of the EGT profile swirl.

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42

Relation, H. L., J. L. Battaglioli, and W. F. Ng. "Numerical Simulations of Nonreacting Flows for Industrial Gas Turbine Combustor Geometries." Journal of Engineering for Gas Turbines and Power 120, no. 3 (July 1, 1998): 460–67. http://dx.doi.org/10.1115/1.2818167.

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This study evaluates the application of the computational fluid dynamics (CFD) to calculate the flowfields in industrial combustors. Two-burner test cases, which contain the elemental flow characteristics of an industrial gas turbine combustor, are studied. Comparisons were made between the standard k-epsilon turbulence model and a modified version of the k-epsilon turbulence model. The modification was based on the work of Chen and Kim in which a second time scale was added to the turbulent dissipation equation. Results from the CFD calculations were compared to experimental data. For the two-burner test cases under study, the standard k-epsilon model diffuses the swirl and axial momentum, which results in the inconsistent prediction of the location of the recirculation zone for both burner test cases. However, the modified k-epsilon model shows an improved prediction of the location, shape, and size of the primary centerline recirculation zone for both cases. The large swirl and axial velocity gradients, which are diffused by the standard k-epsilon; model, are preserved by the modified model, and good agreements were obtained between the calculated and measured axial and swirl velocities. The overprediction of turbulent eddy viscosity in regions of high shear, which is characteristic of the standard k-epsilon model, is controlled by the modified turbulence model.

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43

Im, Ji-Hyuk, Seongho Cho, Youngbin Yoon, and Insang Moon. "Comparative Study of Spray Characteristics of Gas-Centered and Liquid-Centered Swirl Coaxial Injectors." Journal of Propulsion and Power 26, no. 6 (November 2010): 1196–204. http://dx.doi.org/10.2514/1.48436.

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44

Skachkov, S. V., and D. D. Shpakovskiy. "Numerical simulation of gas flow in jet nozzle." Journal of «Almaz – Antey» Air and Space Defence Corporation, no. 3 (September 30, 2016): 41–46. http://dx.doi.org/10.38013/2542-0542-2016-3-41-46.

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We determined traction and hydraulic characteristics of the jet nozzle of a gas turbine engine, taking into account the geometry of the internal structural elements and flow swirl in the inlet section according to the results of numerical simulation.

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45

Du, Haifen, Daimei Xie, Wei Jiang, Tong Chen, and Jianshu Gao. "Numerical Study on Heat Transfer Enhancement of Swirl Chamber on Gas Turbine Blade." International Journal of Turbo & Jet-Engines 35, no. 4 (December 19, 2018): 403–12. http://dx.doi.org/10.1515/tjj-2016-0049.

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Abstract The optimization of turbine cooling design has become a new research field of gas turbine. The swirl chamber is a prospect cooling concept. In this paper, the numerical simulation of the swirl chamber is carried out by FLUENT. The influence of inlet size parameters, temperature ratio and inlet Reynolds number on the enhanced heat transfer of swirl chamber is studied. The results show that, in the range of the studied condition, Nusselt number decreases with the height, the width, the ratio of width to height and Reynolds number. It also shows that comprehensive heat transfer effect is best at d=20 mm and enhances observably with the enlargement of width, width height ratio, and Reynolds number. Friction factor increases with height, width, temperature ratio and Reynolds number decreases. It is increased by increasing width height ratio. Nusselt number and comprehensive heat transfer effect decrease a little with aggrandizement of temperature ratio.

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46

Chong, Cheng Tung, and Simone Hochgreb. "Spray Flame Study Using a Model Gas Turbine Swirl Burner." Applied Mechanics and Materials 316-317 (April 2013): 17–22. http://dx.doi.org/10.4028/www.scientific.net/amm.316-317.17.

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A model gas turbine burner was employed to investigate spray flames established under globally lean, continuous, swirling conditions. Two types of fuel were used to generate liquid spray flames: palm biodiesel and Jet-A1. The main swirling air flow was preheated to 350 °C prior to mixing with airblast-atomized fuel droplets at atmospheric pressure. The global flame structure of flame and flow field were investigated at the fixed power output of 6 kW. Flame chemiluminescence imaging technique was employed to investigate the flame reaction zones, while particle imaging velocimetry (PIV) was utilized to measure the flow field within the combustor. The flow fields of both flames are almost identical despite some differences in the flame reaction zones.

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47

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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48

Meier, W., X. R. Duan, and P. Weigand. "Investigations of swirl flames in a gas turbine model combustor." Combustion and Flame 144, no. 1-2 (January 2006): 225–36. http://dx.doi.org/10.1016/j.combustflame.2005.07.009.

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49

Weigand, P., W. Meier, X. R. Duan, W. Stricker, and M. Aigner. "Investigations of swirl flames in a gas turbine model combustor." Combustion and Flame 144, no. 1-2 (January 2006): 205–24. http://dx.doi.org/10.1016/j.combustflame.2005.07.010.

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50

Lee, Jungsoo, Hyungyu Lee, Donghwa Kim, and Jinsoo Cho. "Pre-swirl Vane Geometry Optimization to Improve Discharge Coefficient of Gas Turbine Pre-swirl System." Transactions of the Korean Society of Mechanical Engineers - B 42, no. 2 (February 28, 2018): 101–10. http://dx.doi.org/10.3795/ksme-b.2018.42.2.101.

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