Experimental investigation of the effects of fuel diffusive injectors on premixed swirling flames

Hatem, Fares, Valera-Medina, Agustin ORCID: https://orcid.org/0000-0003-1580-7133, Syred, Nick, Marsh, Richard ORCID: https://orcid.org/0000-0003-2110-5744 and Bowen, Phil ORCID: https://orcid.org/0000-0002-3644-6878 2015. Experimental investigation of the effects of fuel diffusive injectors on premixed swirling flames. Presented at: 53rd AIAA Aerospace Sciences Meeting, Kissimmee, Florida, USA, 5-9 January 2015. 53rd AIAA Aerospace Sciences Meeting, AIAA SciTech Forum, (AIAA 2015-2076). American Institute of Aeronautics and Astronautics, 10.2514/6.2015-2076

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Abstract

The demand for alternative fuels has increased significantly during the previous decades in order to reduce pollutants and increase the amount of energy that can be generated from non-fossil fuels. However, the use of new fuels faces many issues especially the problem of stability of operation which sometimes can cause severe damages to the system hardware. Thus the development of flexible combustion systems for gas turbines becomes urgent in order to achieve high reliability with these new sources of energy. Swirl stabilized combustion is the most widely spread deployed technology used to stabilize and control combustion in gas turbines and numerous other systems. However, the interaction of the swirling flows with the burner geometries is very complex and it has been proved that any change in the burner geometry can affect the flow field inside the combustion chamber, close to the burner mouth and downstream the combustion zone. Most burners are generally provided with a diffusive injector that centrally delivers well-known fuels allowing the stabilization of the system previous to entirely premixed conditions. Moreover, the injector anchors the central recirculation zone formed downstream of the nozzle. However, the use of injectors can also affect the stability limits of the system, especially the propagation of flashback through changes of shape of the shear layer since other structures such as the Combustion Induced Vortex Breakdown are suppressed due to the presence of this central body. However, the characterization of the flow and its impacts on the propagation of these and other flashback structures using different injectors has been briefly documented. Thus, this paper presents a series of experiments using a well-characterized tangential swirl burner to determine the impact of different central injector geometries on the flow field characteristics which directly affect the flow stagnation point downstream of the burner mouth and consequently the propagation of the Combustion Induced Vortex Breakdown. Results show how the use of various injectors and swirl numbers can impact on the flashback limits with a minimum outside diameter before which the Combustion Induced Vortex Breakdown is altered.

Item Type:	Conference or Workshop Item (Paper)
Date Type:	Publication
Status:	Published
Schools:	Engineering
Subjects:	T Technology > TJ Mechanical engineering and machinery
Publisher:	American Institute of Aeronautics and Astronautics
Last Modified:	27 Jan 2023 02:18
URI:	https://orca.cardiff.ac.uk/id/eprint/99777

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