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Relevant bibliographies by topics / Gas turbine swirl injector

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Journal articles

Academic literature on the topic 'Gas turbine swirl injector'

Author: Grafiati

Published: 6 September 2023

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Journal articles on the topic "Gas turbine swirl injector"

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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