General Electric Company

Qingguo Zhang

Fei Han

Kwanwoo Kim

Kapil Kumar Singh

Shiva Kumar Srinivasan

Preetham Balasubramanyam

Wei A Chen

Joel Meier Haynes

David Leach

Ping Yu

John Joseph Lipinski

Wenjie Wu

Nan Zong

Suhui Li

Manuel Moises Cardenas

Deepali Nitin Bhate

Shiva Kumar Srnivasan

Balasubramanyam Preetham

A fuel nozzle system for enabling a gas turbine to start and operate on low-Btu fuel includes a primary tip having primary fuel orifices and a primary fuel passage in fluid communication with the primary fuel orifices, and a fuel circuit capable of controlling flow rates of a first and second low-Btu fuel gases flowing into the fuel nozzle. The system is capable of operating at an ignition status, in which at least the first low-Btu fuel gas is fed to the primary fuel orifices and ignited to start the gas turbine, and a baseload status, in which at least the second low-Btu fuel gas is fired at baseload. The low-Btu fuel gas ignited at the ignition status has a content of the first low-Btu fuel gas higher than that of the low-Btu fuel gas fired at the baseload status. Methods for using the system are also provided.

Nozzle system and method for starting and operating gas turbines on low-Btu fuels

A turbomachine combustor is provided. The turbomachine includes a combustion chamber and multiple micro-mixer nozzles arranged concentrically within a radial combustion liner and configured to receive fuel from one or more fuel supply pipes affixed to each of the plurality of micro-mixer nozzles at an upstream face. The multiple micro-mixer nozzle are also configured to receive air from a flow sleeve surrounding the radial combustion liner. Each of the micro-mixer nozzles include an annular strip having a multiple tubes or passages extending axially from the upstream face to a downstream face of each of the micro-mixer nozzles.

Annular strip micro-mixers for turbomachine combustor

A combustion dynamics control system for an aviation based or land based gas turbine engine employs an acoustic driver that is configured to drive pressure perturbations across a premixed fuel injection orifice to substantially zero in response to a control signal such that fuel flow perturbations across the fuel injection orifice are substantially zero.

System and method for combustion dynamics control by acoustic control/cancellation of fuel flow fluctuation at fuel injection location

A gas turbine engine control system comprises a data acquisition and analysis system for receiving a signal from a combustion dynamics sensor and providing an output signal and a combustion dynamics control system for controlling combustion dynamics based on the output signal. The control system is associated with a purge-air flow and comprises an acoustic driver, or a flow-manipulating device, or both to perturb the purge-air flow entering the combustor can for controlling combustion dynamics.

Gas turbine combustion dynamics control system and method

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Niskayuna, NY, United States of America

Qingguo Zhang