Abstract: A transition piece can include: an inner transition piece providing a gas channel; a plurality of cooling rings disposed on the inner transition piece; a plurality of film holes formed on the inner transition piece; and a plurality of impingement holes formed on the plurality of cooling rings, wherein the plurality of film holes are arranged to correspond to the plurality of cooling rings. Each of the plurality of cooling rings includes a cavity such that the plurality of film holes connect the cavity to the gas channel and the plurality of impingement holes connect the cavity to an outside of the inner transition piece.

Abstract: A gas turbine combustor includes a combustion chamber, a liner adjacent to the combustion chamber, a liner cap capping the combustion chamber, and a swirler cup passing through the liner cap. The liner cap includes a first cavity having a first inlet receiving an air, a second cavity having a first outlet facing the combustion chamber, and an impingement plate between the first cavity and the second cavity. The air flows from the first inlet to the combustion chamber through the first cavity, the impingement plate, and the second cavity.

Abstract: A flow conditioner in a combustor of a gas turbine comprises a body and a flow conditioning portion configured to be placed in an air path providing air flow to a combustion chamber, the flow conditioning portion including a plurality of holes tuned to a damping frequency to dampen a pressure fluctuation caused by combustion dynamics from the combustion chamber.

Abstract: A combustion system can include: a liner defining a combustion chamber; a casing covering the combustion chamber; a first tube disposed in the liner; a machined union disposed inside the casing and connected to the first tube; a second tube passing through the casing and connected to the machined union; a sensor housing disposed outside the casing and connected to the second tube; and an infinite tube connected to the sensor housing.

Abstract: A combustion system can include: a liner defining a combustion chamber; a casing covering the combustion chamber; a first tube disposed in the liner; a machined union disposed inside the casing and connected to the first tube; a second tube passing through the casing and connected to the machined union; a sensor housing disposed outside the casing and connected to the second tube; and an infinite tube connected to the sensor housing.

Abstract: A transition piece can include: an inner transition piece providing a gas channel; a plurality of cooling rings disposed on the inner transition piece; a plurality of film holes formed on the inner transition piece; and a plurality of impingement holes formed on the plurality of cooling rings, wherein the plurality of film holes are arranged to correspond to the plurality of cooling rings. Each of the plurality of cooling rings includes a cavity such that the plurality of film holes connect the cavity to the gas channel and the plurality of impingement holes connect the cavity to an outside of the inner transition piece.

Abstract: A system for designing a resonator to dampen acoustic energy in a combustion system includes a design module configured to generate a resonator design to dampen a target frequency and acceptable damping, a system analysis module configured to evaluate the resonator design within a modeled combustion system environment to determine a damping effect of the resonator design on the combustion system as a whole, and a system optimization module configured to adjust the resonator design to optimize an overall effect on the combustion system as a whole.

Abstract: A flow controller in a combustor of a gas turbine includes a body and a flow regulating portion configured to be placed in an air path providing air flow to a combustion chamber, the flow regulating portion including a plurality of holes configured to regulate the amount of air provided to one or more fuel nozzles in the combustor.

Abstract: A resonator in a combustor of a gas turbine comprises a flow sleeve defining an air path to provide air flow to a combustion chamber of the combustor, and one or more impingement holes disposed on the flow sleeve tuned to a damping frequency.

Abstract: A flow conditioner in a combustor of a gas turbine comprises a body and a flow conditioning portion configured to be placed in an air path providing air flow to a combustion chamber, the flow conditioning portion including a plurality of holes tuned to a damping frequency to dampen a pressure fluctuation caused by combustion dynamics from the combustion chamber.

Abstract: A gas turbine combustor includes a combustion chamber, a liner adjacent to the combustion chamber, a liner cap capping the combustion chamber, and a swirler cup passing through the liner cap. The liner cap includes a first cavity having a first inlet receiving an air, a second cavity having a first outlet facing the combustion chamber, and an impingement plate between the first cavity and the second cavity. The air flows from the first inlet to the combustion chamber through the first cavity, the impingement plate, and the second cavity.

Abstract: A gas turbine engine (202) including a secondary fuel stage (218) which also functions as a dual frequency resonator. The engine includes a combustor (210) and a casing (205) enclosing the combustor to define a volume (214). The secondary fuel stage includes a nozzle (217) sized to be effective as a transverse resonator at a high frequency. The nozzle and the volume (214) of the casing are sized to be effective as a longitudinal resonator at an intermediate frequency.