NUMERICAL ANALYSIS OF COHERENT STRUCTURES IN BIDIRECTIONAL SWIRL COMBUSTION CHAMBER

2016 ◽  
Vol 8 (3) ◽  
pp. 265-289 ◽  
Author(s):  
V. Aghakashi ◽  
P. M. Keshavarz ◽  
Mohammad Hassan Saidi
Keyword(s):  
Numerical Analysis ◽  
Combustion Chamber ◽  
Coherent Structures ◽  
Swirl Combustion

Effects of combustion chamber diameter on comprehensive performance of the lateral swirl combustion system under various conditions

Fuel ◽  
2022 ◽  
Vol 312 ◽  
pp. 122925
Author(s):  
Xiangrong Li ◽  
Jiang Chang ◽  
Yanlin Chen ◽  
Dong Liu ◽  
Yuning Kang
Keyword(s):  
Combustion Chamber ◽  
Combustion System ◽  
Swirl Combustion ◽  
Comprehensive Performance ◽  
Chamber Diameter

Numerical analysis of laser-pulse transient ignition of oxygen/methane mixtures in rocket-like combustion chamber

2019 ◽  
Vol 159 ◽  
pp. 136-155 ◽  
Author(s):  
G. Gargiulo ◽  
P.P. Ciottoli ◽  
E. Martelli ◽  
R. Malpica Galassi ◽  
M. Valorani
Keyword(s):  
Numerical Analysis ◽  
Laser Pulse ◽  
Combustion Chamber

Research on Parametric Design Method of Combustion Chamber on Diesel Engine

2011 ◽  
Vol 383-390 ◽  
pp. 1431-1440
Author(s):  
Yong Shang ◽  
Fu Shui Liu ◽  
Xiang Rong Li ◽  
Jing Wu
Keyword(s):  
Diesel Engine ◽  
Combustion Chamber ◽  
Calculation Result ◽  
Parametric Design ◽  
Design Method ◽  
Geometrical Parameters ◽  
Combustion Chambers ◽  
Heat Efficiency ◽  
Swirl Combustion ◽  
Combustion Duration

One method of parametric design on combustion chamber is used in this paper. Several independent geometrical parameters of ω type and double swirl combustion chamber are brought forward. Different series of ω type and double swirl combustion chambers have been designed by using this method. The effect of the independent geometrical parameters on the performance of diesel engine has been studied by using CFD code AVL FIRE. According to this method of parametric design and calculation result, two pistons with ω type and double swirl combustion chamber has been designed with the target of the highest indicated heat efficiency. The test result shows that, contrasting with ω type chamber, BSFC and main combustion duration of double swirl combustion chamber is lower by 7.5 and 6.9 percent respectively, while indicated heat efficiency is 7.1 percent higher. And the calculation result has coherence with the experiment. It is proved that the method of parametric design on combustion chamber can satisfy the requirement of designing. At the same time, this method can be extended to design other combustion chambers.

scholarly journals Optimization of Convergent –Divergent Taper Angle with Combustion Chamber of Rocket Engine through Numerical Analysis

2020 ◽  
Vol 9 (6) ◽  
pp. 76-81
Keyword(s):  
Carbon Dioxide ◽  
Steady State ◽  
Numerical Analysis ◽  
Combustion Chamber ◽  
Main Part ◽  
Rocket Engine ◽  
Taper Angle ◽  
Optimal Values ◽  
Mach Numbers ◽  
Divergent Angle

Present days speed of vehicle is concerned in both sub -sonic vehicle( like car, bus and truck etc) super -sonic vehicles (like rockets). Convergent divergent component is the main part which decide the speed of any vehicle. A attempt is made to find the optimal convergent angle (inlet taper angle ) and divergent angle(outlet taper angle [ .) with the help of Numerical analysis through ANSYS 19.0(R3). Deciding parameter for greater thrust is angles i.e.; and [ . So, Convergent divergent nozzles with combustion chamber is designed, modelled and analysed numerical for getting optimal values of convergent and divergent angles . The various angles used are [35,15] [35,20] [35,25] [40,15] [40,20] [40,25] [45,15] [45,20] [45,25]. At these different angle the parameters such as velocity, temperature, pressure and Mach numbers are estimated with the help of steady state fluent with carbon dioxide as inlet to the combustion chamber.

Advanced Rayleigh Pressure Loss Model for High-Swirl Combustion in a Rotating Combustion Chamber

2015 ◽  
Author(s):  
Andreas Penkner ◽  
Peter Jeschke
Keyword(s):  
Heat Transfer ◽  
Combustion Chamber ◽  
Dynamic Model ◽  
Gas Turbines ◽  
Total Pressure ◽  
Fluid Flows ◽  
Pressure Losses ◽  
Gas Dynamic ◽  
Swirl Combustion ◽  
Transfer Problems

This paper considers the effect of excessive total pressure losses for heat transfer problems in fluid flows with a high circumferential swirl component. At RWTH Aachen University, a novel gas generator concept is under research. This design avoids some disadvantages of small gas turbines and uses a rotating combustion chamber. During the pre-design of the rotating combustion chamber using CFD tools, unexpected high total pressure losses were detected. To analyze this unknown phenomenon, a gas-dynamic model of the rotating combustion chamber has been developed to explain the unexpected high Rayleigh pressure losses. The derivation of the gas-dynamic model, the physical phenomenon related to the high total pressure losses in high-swirl combustion, the influencing factors, as well as thermodynamic interpretation of the Rayleigh pressure losses, are presented in this paper. In addition, the CFD results are validated by the gas-dynamic model derived. The results presented here are of possible interest for a wide range of applications, since these fundamental findings can be transferred to all heat transfer problems in fluid flows with a high circumferential swirl component.

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