Mohd. Jaafar, Mohammad Nazri and Nor, M. K. F. M. and Ishak, M. S. A. (2011) Aerodynamic study of combustor using axial swirler. International Review of Mechanical Engineering, 5 (1). pp. 92-99. ISSN 1970-8734
Full text not available from this repository.
Official URL: http://www.praiseworthyprize.com/IREME-latest/IREM...
A study has been conducted to investigate the flow pattern in a gas turbine combustion chamber by simulation and experimental approaches. Flow pattern inside a combustor is important to self sustain the flame, increase mixing of air and fuel and combustion intensity. Aerodynamically curved vanes allow the incoming axial flow to turn gradually. This inhibits flow separation on the suction side of the vane. Thus, more complete turning and higher swirl and radial-velocity components can be generated at the swirler exit, with the added advantage of lower pressure loss. The swirl number was varied from 0.48, 0.83 and 1.43. The highest swirl number of 1.43 for axial swirler is capable to create a clear reversal mass flow rate zone.
|Uncontrolled Keywords:||axial swirlers, cfd simulation, combustor flow pattern, recirculation zone, swirl number|
|Subjects:||T Technology > TJ Mechanical engineering and machinery|
|Deposited By:||Liza Porijo|
|Deposited On:||12 Nov 2012 07:39|
|Last Modified:||13 Feb 2017 02:42|
Repository Staff Only: item control page