Extinction and interruption of diffusion flame interacting with a large scale vortex

2009 ◽  
Vol 32 (1) ◽  
pp. 1099-1106
Author(s):  
Masaharu Komiyama ◽  
Ryoji Kawabe ◽  
Toshimi Takagi
2005 ◽  
Vol 30 (1) ◽  
pp. 465-473 ◽  
Author(s):  
Masaharu Komiyama ◽  
Tomoya Fujimura ◽  
Toshimi Takagi ◽  
Shinichi Kinoshita

2003 ◽  
Vol 69 (681) ◽  
pp. 1296-1302
Author(s):  
Masaharu KOMIYAMA ◽  
Ryoji KAWABE ◽  
Akinori HAYASHI ◽  
Toshimi TAKAGI

2018 ◽  
Vol 11 (2) ◽  
pp. 31-39
Author(s):  
L. М. Chikishev ◽  
◽  
V. М. Dulin ◽  
A. S. Lobasov ◽  
D. М. Markovich ◽  
...  

2006 ◽  
Author(s):  
Peng Sun ◽  
Guotal Feng

A time-accurate three-dimensional Navier-Stokes solver of the unsteady flow field in a transonic fan was carried out using "Fluent-parallel" in a parallel supercomputer. The numerical simulation focused on a transonic fan with inlet square wave total pressure distortion and the analysis of result consisted of three aspects. The first was about inlet parameters redistribution and outlet total temperature distortion induced by inlet total pressure distortion. The pattern and causation of flow loss caused by pressure distortion in rotor were analyzed secondly. It was found that the influence of distortion was different at different radial positions. In hub area, transportation-loss and mixing-loss were the main loss patterns. Distortion not only complicated them but enhanced them. Especially in stator, inlet total pressure distortion induced large-scale vortex, which produced backflow and increased the loss. While in casing area, distortion changed the format of shock wave and increased the shock loss. Finally, the format of shock wave and the hysteresis of rotor to distortion were analyzed in detail.


2021 ◽  
Vol 2119 (1) ◽  
pp. 012015
Author(s):  
A S Lobasov

Abstract The present paper reports on the investigation of unsteady combustion of a methane-air mixture, including combustion at increased pressure in the combustion chamber and increased temperature of mixture heating for a model gas-turbine swirl burner based on a design by Turbomeca. To measure the velocity and OH fluorescence fields in the flows a combination of stereoscopic PIV and acetone PLIF systems is used. In all cases, the flow dynamics is associated with the movement of large-scale vortex structures in the inner and outer mixing layers and the flow structure corresponds to a swirling jet with a central recirculation zone containing combustion products. An increase in the heating temperature of the mixture and pressure in the combustion chamber leads to a periodic partial separation of the flame from the model swirl nozzle. However, the flow of fuel through the central channel will stabilize the flame.


2007 ◽  
Vol 42 (4) ◽  
pp. 571-580 ◽  
Author(s):  
V. M. Ponomarev ◽  
O. G. Chkhetiani ◽  
L. V. Shestakova

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