A method for operating a combustor (14) includes firing a bundled tube fuel nozzle assembly (100) within a combustion liner (36) of the combustor (14) to generate combustion gases (26) at a first temperature within a first combustion zone length (92). The ...

An igniter 100 for a combustor 16 of a turbomachine includes a fuel inlet 102 in fluid communication with a mixing plenum 110. The mixing plenum 110 is positioned upstream of a mixing channel 126. An air inlet 104 is in fluid communication with the mixing ...

Exhaust frequency mitigation apparatus (100), exhaust diffusers (34), and gas turbines (10) are provided. An exhaust frequency mitigation apparatus (100) includes a main body (102) extending along an axial centerline from a base (104) to a tip (106). The b...

A system and related method for providing a highly reactive fuel to a combustor of a gas turbine are disclosed herein. The system includes a fuel supply system that is in fluid communication with a fuel supply. The fuel supply system includes multiple fuel...