General Electric Company

Siemens Aktiengesellschaft

Sven Georg Bethke

Lucas John Stoia

Kwanwoo Kim

Jayaprakash Natarajan

Richard Martin DiCintio

Bruno Schuermans

Fei Han

Jeffrey Scott LeBegue

Donald Mark Bailey

Timothy James Purcell

Mohan Krishna Bobba

Seth Reynolds Hoffman

Praveen Babulal Jain

Venkateswarlu Narra

Dheeraj Sharma

Venkat Narra

Yongqiang Fu

Praveen Kumar Babulal Jain

Jeffrey Scott Lebegue

Richard Martin Dicintio

Praveen Jain

A combustor having bundled tube fuel nozzles is provided. At least one of the fuel nozzles has a dynamics-mitigating adapter removably coupled thereto. The adapter includes a mounting body defining at least one flow passage aligned with an inlet of at least one tube of the at least one fuel nozzle. The at least one flow passage extends an axial length of the at least one tube. The adapter may include extenders aligned with each tube of the fuel nozzle, and the extenders may have identical or different lengths. Adapters may be used for each fuel nozzle of the combustor. The mounting body may be a monolithic unit through which the flow passages are defined or may include a plurality of extenders affixed to and extending upstream of the mounting body.

Dynamics-mitigating adapter for bundled tube fuel nozzle

A fuel nozzle assembly includes a fuel plenum for delivering fuel to a combustion zone of a combustor. At least one narrow-band acoustic damper is provided in the fuel nozzle assembly. The narrow-band acoustic damper is tuned to dampen pressure oscillations within the combustor. The narrow-band acoustic damper may be a quarter-wave tube mounted to a cap plate within or adjacent to the fuel nozzle assembly.

Fuel nozzle with narrow-band acoustic damper

A combustion liner assembly includes a combustion liner having an upstream end portion and a downstream end portion and a resonator disposed proximate to the upstream end portion of the combustion liner. The resonator includes a plurality of circumferentially spaced inlet apertures disposed along a radially outer surface of the resonator, an air chamber defined within the resonator and a plurality of outlet apertures disposed along a radially inner surface of the resonator. The plurality of inlet apertures provide for fluid flow into the air chamber and the plurality of outlet apertures provide for fluid flow out of the air chamber and into a radial flow passage defined within the combustor.

Combustion dynamics mitigation system

A bundled tube fuel nozzle assembly including a fuel plenum and an air plenum. A plurality of mixing tubes extend through the fuel plenum and the air plenum. At least one resonator is positioned in the air plenum surrounding at least one of the plurality of mixing tubes.

Fuel nozzle assembly with resonator

A combustor includes a plurality of bundled tube fuel nozzles which are annularly arranged around a common axial centerline. The plurality of bundled tube fuel nozzles comprise a first bundled tube fuel nozzle and a second bundled tube fuel nozzle. The first bundled tube fuel nozzle includes a first fuel plenum and a plurality of premix tubes which extend axially therethrough. The second bundled tube fuel nozzle includes a second fuel plenum and a plurality of premix tubes which extend axially therethrough. The first fuel plenum is axially offset at a predefined axial distance from the second fuel plenum so as to mitigate combustion tones within the combustor. In one embodiment, premix tube fuel ports disposed within the first and/or second fuel plenums may be axially offset with respect to each other within the corresponding fuel plenums at a predefined axial distance to mitigate combustion tones within the combustor.

Combustor dynamics mitigation

A system includes a compressor that compresses incoming airflow, and a combustor assembly mixing the compressed incoming airflow with fuel and combusting the air and fuel mixture in a combustion zone. The combustor assembly includes a hot side downstream of the combustion zone and a cold side upstream of the combustion zone. The system also includes a turbine receiving products of combustion from the combustor. The combustor assembly includes a resonator positioned in the cold side of the combustor assembly in an annular passage between a flow sleeve and a casing of the combustor assembly.

Acoustic resonator located at flow sleeve of gas turbine combustor

A dampener or resonator is provided within a combustor casing to mitigate combustion dynamics. The combustor casing head end volume is reduced by the resonator to mitigate combustion dynamics. The resonator is formed by a ring shaped plate that carries a continuous inwardly protruding wall or segmented inwardly protruding wall portions. The resonator can be a stand alone part that is inserted into the combustor casing or it can be integrally formed with the combustor casing.

Combustor casing for combustion dynamics mitigation

Certain embodiments include a resonator for the head end of a turbine combustor. The resonator is partially defined by first and second plates disposed about a fuel nozzle in the head end of the turbine combustor. The resonator is further configured to receive an air flow which extends through the resonator and into the fuel nozzle.

System for damping oscillations in a turbine combustor

A burner system is provided that includes at least two adjacent burners that are separate from each other. Each of the two burners has at least one combustion chamber and a head end. The head end includes at least a fuel injection and a fuel-air premix. Each burner has a cap with a cap side and cap upper side, wherein at least the cap upper side is arranged ahead of the head end, seen in the direction of flow. In this manner, a burner plenum is formed between the cap upper side and the head end. The at least two burner plenums thus formed have an acoustic connection. A method for damping such a burner system is also provided.

Growing community of inventors

Greenville, SC, United States of America

Sven Georg Bethke