FLOW CONDITIONER IN COMBUSTOR OF GAS TURBINE ENGINE Russian patent published in 2018 - IPC F23R3/10 

FIELD: motors and pumps.

SUBSTANCE: combustor in a gas turbine comprises a liner, a fuel injection system for delivering fuel into the main combustion zone, a flow sleeve, transition assembly. Flow sleeve is located radially outwardly from the liner and defines, with the liner, a passageway for air to flow on its way to be mixed with fuel from the fuel injection system. Transition assembly comprises 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. Combustor further comprises 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. Flow conditioner includes 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. 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. Plurality of panels are removably secured to the frame such that the panels can be replaced without detaching the frame from the transition ring. Combustor further comprises perforated resonator boxes extending radially outwardly from the liner into the passageway.

EFFECT: invention is aimed at attenuating vibration in the liner.

9 cl, 8 dwg