LES of a Multi-burner Annular Gas Turbine Combustor

2009 ◽  
Vol 84 (3) ◽  
pp. 543-564 ◽  
Author(s):  
Christer Fureby
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Combustor ◽  
Annular Gas Turbine Combustor

Lean Blow-out Studies in a Swirl Stabilized Annular Gas Turbine Combustor

2015 ◽  
Vol 32 (2) ◽  
Author(s):  
R. K. Mishra ◽  
S. Kishore Kumar ◽  
Sunil Chandel
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Gas Turbine ◽  
Cfd Analysis ◽  
Gas Turbine Combustor ◽  
Tetrahedral Meshes ◽  
Annular Combustor ◽  
Unstructured Tetrahedral Meshes ◽  
Annular Gas Turbine Combustor

AbstractLean blow out characteristics in a swirl stabilized aero gas turbine combustor have been studied using computational fluid dynamics. For CFD analysis, a 22.5° sector of an annular combustor is modeled using unstructured tetrahedral meshes comprising 1.2 × 10

Experimental Investigations on Isothermal Swirling Flows in a Reverse Flow Annular Gas Turbine Combustor

2005 ◽  
Author(s):  
K. Sudhakar Reddy ◽  
D. N. Reddy ◽  
C. M. Vara Prasad
Keyword(s):  
Reynolds Number ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Reverse Flow ◽  
Swirling Flows ◽  
Recirculation Region ◽  
Gas Turbine Combustor ◽  
Swirl Number ◽  
Inlet Swirl ◽  
Annular Gas Turbine Combustor

An experimental work was carried out on confined swirling flows under non-combusting conditions in a reverse flow annular gas turbine combustor. Flow measurements with a five hole pitot probe are carried out in a flow apparatus of a geometrical configuration similar to the model of a swirl combustor. Mean flow results are obtained for different flow conditions to determine the effect of swirl on the recirculation zone and the variation of the swirl strength along the axis of the gas turbine combustion chamber. The boundaries of the recirculation region are plotted to compare the size and length of the zone with various swirlers. Minimum flow Reynolds number is required for flow recirculation; the effect of Reynolds number on determining which flow class is present for flow of interest in combustion chamber was investigated. The inlet swirl number is optimized for higher swirl strength and the inlet swirl number for which recirculation completely vanishes is also estimated.

Calculations of the dilution system in an annular gas turbine combustor

AIAA Journal ◽  
1992 ◽  
Vol 30 (4) ◽  
pp. 963-972 ◽  
Author(s):  
J. McGuirk ◽  
J. M. L. M. Palma
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Combustor ◽  
Annular Gas Turbine Combustor
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