Flow conditioner in a combustor of a gas turbine engine

A combustor in a gas turbine comprises a liner (48) having an interior volume defining a main combustion zone; a fuel injection system for delivering fuel into the main combustion zone; a flow sleeve (42) located radially outwardly from the liner (48) and defining, with the liner (48), a passageway (60) for air to flow on its way to be mixed with fuel from the fuel injection system, wherein the mixture is burned in the main combustion zone to create hot combustion gases; a transition assembly (50) comprising a transition duct (22) located downstream from the liner (48) with respect to a flow direction of the hot combustion gases out of the combustor toward a turbine section of the engine, the flow direction of the hot combustion gases defining an axial direction. The combustor further comprises a flow conditioner (40) affixed to at least one of the liner (48) and the transition assembly (50) and extending to within close proximity of the flow sleeve (42) but not coupled to the flow sleeve (42), the flow conditioner (40) comprising at least one panel (72) having a configuration such that air is able to pass through the at least one panel (72) on its way to the passageway (60), wherein at least a substantial portion of the air that enters the passageway (60) for being burned in the main combustion zone passes through the at least one panel (72). Several panels (72) are removably secured to a frame (70) such that the panels (72) can be replaced without detaching the frame (70) from a transition ring (54). The panels (72) have a desired air permeability realised with holes such that the air flow through each panel (72) can be controlled. The combustor further comprises perforated resonator boxes (80) extending radially outwardly from the liner (48) into the passageway (60).