Document Type : Original Article
Authors
1 Dr., Department of Aerospace Engineering, Shahid satari University, Tehran, Iran.
2 Department of Aerospace Engineering, Malek-Ashtar University of Technology, Tehran, Iran
Abstract
A new method for cooling the combustion chamber walls, it is cooled by the bidirectional vortex Flow. Combustion stability, reducing the temperature of the combustion chamber walls and reduces losses and increase efficiency and uniformity are the properties of the vortex combustion engine. In similar circumstances the volume of flame the vortex engine is greater than the volume of flame at common axial engine. However; temperature of the Wall of the combustion chamber of the vortex engines less than temperature of the Wall of the combustion chamber of the engine Axial. Because cooled by the external vortex. In this study, was carried out Simulation and Numerical Solution the combustion chamber a special vortex engine in conditions single phase gaseous to fuel hydrogen and oxidant oxygen and assuming incompressible flow and irrespective of effect nozzle In order to simplify for review conditions governing on flow the combustion chamber. Examination of the streamlines shows a forced vortex in the center of the core and a free vortex around the core. The simulation results show that the pitch of the Stream lines near the roof is very small and the intensity of the flow rotation is high, which causes the maximum mixing of fuel and oxidizer. The flame is surrounded by an external vortex. In the simulated chamber, by increasing the distance from the edge of the stairs to the ceiling, the mixing and combustion will increase, and as a result, we will have an increase in the temperature of the wall.
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