COLD FLOW ANALYSIS IN AN ANNULAR GAS TURBINE COMBUSTOR USING CFD TOOL
Keywords:
Annular gas turbine combustor, Mach number, Computational fluid Dynamics, Finite element analysiAbstract
In continuous devices such as a gas turbine combustor, there exists a range of complex interacting physics,
included are vortex flows with turbulent effect. Rigorous descriptions of these phenomena are, however, either not available
or require mathematical models which are complex for computation, when taken together in the context of multi-dimensional
flows. For these reasons, models of varying degrees of sophistication in the model are continuously increasing with
improvements in numerical methods, computer capabilities and physical understanding. This paper focused on the velocity
profiles, flow distribution and pressure drop in an annular gas turbine combustor. Flow-split through different liner holes
and swirler has been estimated. It is seen that percentage flow-split through the outer liner surface holes and inner liner
surface holes can be varied by changing the diameter of the liner holes even though the inlet velocity has been maintained
constant. Various parameters like pressure loss, velocity, mass flow distribution, Mach number, and speed at various
locations, have been estimated. In addition, the effect of varying the primary inner holes on the cold flow performance of the
combustor has been studied. A 180
sector of the combustor has been modeled in Pro-E Wildfire 4.0 and cold flow analysis
has been carried out using the software CFD tool 10.
