Please use this identifier to cite or link to this item: https://hdl.handle.net/20.500.11851/5815
Title: Large-eddy simulation of a full annular RQL combustion chamber: Fuel distribution effects on the combustor exit temperature profile
Authors: Kocaman, Ozan Can
Aksu, T.
Uslu S.
Issue Date: 2016
Publisher: American Institute of Aeronautics and Astronautics Inc, AIAA
Source: 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016, 25 July 2016 through 27 July 2016, , 179039
Abstract: The design of an aero engine combustion chamber is a difficult process in order to meet engine performance requirements. One of the most important problems in the design and development of an aero engine combustion chamber is to achieve uniform temperature pattern in circumferential direction and a radial temperature profile in traverse direction with a peak in the middle. The exit temperature profile affects the turbine nozzle guide vane and the overall engine life time. Moreover, Large Eddy Simulation(LES), is a substantial technique for prediction of reacting flow simulations that contain turbulent mixing and combustion process. Hence, in this study LES of non-premixed reacting flow in a full annular RQL, Rich-burn, quick-Quench, Lean-burn, combustor is performed to investigate the effects of fuel distribution on combustion chamber exit temperature for both uniform and non-uniform fuel distribution for fuel injectors. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
URI: https://doi.org/10.2514/6.2016-4786
https://hdl.handle.net/20.500.11851/5815
ISBN: 9781624104060
Appears in Collections:Makine Mühendisliği Bölümü / Department of Mechanical Engineering
Scopus İndeksli Yayınlar Koleksiyonu / Scopus Indexed Publications Collection

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