Abstract:
The present application provides a clocked combustor can array for coherence reduction in a gas turbine engine. The clocked combustor can array may include a number of combustor cans positioned in a circumferential array. A first set of the combustor cans may have a first orientation and a second set of the combustor cans may have a second orientation.
Abstract:
A combustion arrangement includes a combustion section. Also included is an air discharge section downstream of the combustion section. Further included is a transition region disposed between the combustion section and the air discharge section. Yet further included is a transition piece defining the combustion section and the transition region, wherein the transition piece is configured to carry a combusted gas flow from the combustion section to the air discharge section. Also included is a damping device operatively coupled to the transition piece proximate the air discharge section.
Abstract:
The present application provides a clocked combustor can array for coherence reduction in a gas turbine engine. The clocked combustor can array may include a number of combustor cans positioned in a circumferential array. A first set of the combustor cans may have a first orientation and a second set of the combustor cans may have a second orientation.