Spinning effects on a trapped vortex combustor

Chen, Song, Chue, Randy S.M., Yu, Simon C.M. and Schlüter, Jörg U. 2016, Spinning effects on a trapped vortex combustor, Journal of propulsion and power, vol. 32, no. 5, pp. 1133-1145, doi: 10.2514/1.B36005.


Title Spinning effects on a trapped vortex combustor
Author(s) Chen, Song
Chue, Randy S.M.
Yu, Simon C.M.
Schlüter, Jörg U.ORCID iD for Schlüter, Jörg U. orcid.org/0000-0001-7783-1361
Journal name Journal of propulsion and power
Volume number 32
Issue number 5
Start page 1133
End page 1145
Total pages 13
Publisher American Institute of Aeronautics and Astronautics
Place of publication Reston, Va.
Publication date 2016
ISSN 0748-4658
1533-3876
Keyword(s) Science & Technology
Technology
Engineering, Aerospace
Engineering
AXIAL THROUGHFLOW
ROTATING CAVITY
COOLING AIR
FLOW
DYNAMICS
Summary The trapped vortex combustor concept provides a simple design for flame stabilization by trapping a pilot flame inside a cavity instead of exposing it to the mainstream. Under some circumstances, the combustor may operate in a high-spinning motion (for example, when it is installed in a spin-stabilized ramjet projectile), in which the spinning rate can be as high as 30,000 rpm. The objective of this study is to numerically investigate the effects of high-spinning motion on the trapped vortex combustor, including the cavity vortex dynamics, fuel-air mixing, and combustion performance. Numerical computations have been performed with the Reynolds stress model for turbulence and the eddy dissipation model for combustion in a rotating reference frame. The results of the spinning trapped vortex combustor show that the Coriolis effects dominate the flow in the cavity whenit is subjectedto ahigh-spinning motion (30,000 rpm). The vortex breakdowninthe cavity brings strong three-dimensional flow and promotes fuel-air mixing so that a stronger cavity pilot flame is generated. But, the effect of the centrifugal force also generates a short recirculation zone in the main combustor and concentrates the fuel stream on the combustor axis, which in turn impairs fuel-air mixing and leads to a longer main combustor flame.
Language eng
DOI 10.2514/1.B36005
Field of Research 090199 Aerospace Engineering not elsewhere classified
091399 Mechanical Engineering not elsewhere classified
Socio Economic Objective 970109 Expanding Knowledge in Engineering
HERDC Research category C1 Refereed article in a scholarly journal
ERA Research output type C Journal article
Copyright notice ©2015, American Institute of Aeronautics and Astronautics
Persistent URL http://hdl.handle.net/10536/DRO/DU:30087781

Document type: Journal Article
Collection: School of Engineering
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