Patent ID: 9163837
Filing Date: 2015-10-20
Classification: F01D,F23R

Abstract:
1. A combustor in a gas turbine comprising: a liner having an interior volume defining a main combustion zone; a fuel injection system for delivering fuel into the main combustion zone; a flow sleeve located radially outwardly from the liner and defining, with the liner, a passageway 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 comprising a transition duct located downstream from the liner 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; and a flow conditioner affixed to at least one of the liner and the transition assembly and extending to within close proximity of the flow sleeve but not coupled to the flow sleeve, the flow conditioner comprising at least one panel having a configuration such that air is able to pass through the at least one panel on its way to the passageway, wherein at least a substantial portion of the air that enters the passageway for being burned in the main combustion zone passes through the at least one panel wherein: the flow conditioner further comprises a frame; and the at least one panel comprises a plurality of panels secured to the frame wherein the panels are removably secured to the frame such that the panels are capable of being removed and replaced without detaching the frame from a transition ring, wherein each panel can be selected with a desired air permeability such that an amount of air permitted to flow through each respective panel can be controlled.