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Numerical investigation of a trapped vortex miniature ramjet combustor

Chen, Song, Chue, Randy S M, Schluter, Jorg, Nguyen, Tue T Q and Yu, Simon C M 2015, Numerical investigation of a trapped vortex miniature ramjet combustor, Journal of propulsion and power: devoted to aerospace propulsion and power, vol. 31, no. 3, pp. 872-882, doi: 10.2514/1.B35602.


Title Numerical investigation of a trapped vortex miniature ramjet combustor
Author(s) Chen, Song
Chue, Randy S M
Schluter, JorgORCID iD for Schluter, Jorg orcid.org/0000-0001-7783-1361
Nguyen, Tue T Q
Yu, Simon C M
Journal name Journal of propulsion and power: devoted to aerospace propulsion and power
Volume number 31
Issue number 3
Start page 872
End page 882
Total pages 11
Publisher American Institute of Aeronautics and Astronautics Inc.
Place of publication Reston, VA
Publication date 2015-05
ISSN 1533-3876
Summary The design of a miniature ramjet combustor using gaseous methane fuel for Mach 2.5 has been conducted. The main challenges stem mainly from the insufficient space for mixing and burning, short residence time, and the flame stabilization. Impossible utilization of relatively large air-blast fuel injectors provides more difficulties for the design. The trapped vortex combustor, as a novel way of flameholding by trapping the pilot flame inside a cavity instead of exposing it to the mainstream, is selected. Three main parts are studied numerically, which include the cold flowfield characteristics, the fuel-injection schemes, and the overall combustion performance. The results show that the drag coefficient can helptodetermine the optimum cavity size for trappingastable vortex. Injecting all the fuel inthe cavity always leads to an overly fuel-rich condition, whereas injecting in front of the cavity with a momentum flux ratio q between 0.61 and 1.0 can successfully achieve stoichiometric mixing in the cavity. However, compared to nonreacting fuel mixing, the combustion performance is found to be more sensitive to the value of q. Among the cases studied, the one with a small q of about 0.61 has more intense pilot flames andshorter main combustor flames. The effectsofangled injection, upstream injection location, and the combustor length based on the found q are also investigated.
Language eng
DOI 10.2514/1.B35602
Field of Research 090199 Aerospace Engineering not elsewhere classified
Socio Economic Objective 970109 Expanding Knowledge in Engineering
HERDC Research category C1.1 Refereed article in a scholarly journal
ERA Research output type C Journal article
Copyright notice ©2016, American Institute of Aeronautics and Astronautics Inc.
Persistent URL http://hdl.handle.net/10536/DRO/DU:30087778

Document type: Journal Article
Collection: School of Engineering
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