A system and method for operating a combustion system comprising a fuel nozzle defining
at least one main fuel circuit and at least one pilot fuel circuit is generally provided. The …

A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial
direction and a radial direction, a primary air passageway centrally defined axially in the …

A method, control unit and rotating machine for determining a fuel split setting value for
adjusting a fuel split setting for a combustion device, the fuel split setting defining a relation …

BACKGROUND Combustors on both new and upgraded industrial gas tur bines have
recently and increasingly utilized Dry Low NOx combustion systems (“DLN combustors' or …

A combustor assembly of a gas turbine engine having a trapped vortex feature to reduce
emissions where the trapped vortex is formed using ammonia injected into an annular cavity …

Disclosed herein is a combustion oscillation estimating apparatus which estimates
combustion oscillation in a combustion chamber connected with a burner so that a flame is …

The present disclosure provides a method for controlling combustor cans of a gas turbine.
Detectors disposed on combustor cans are operable to detect combustion vibration values …

A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine
includes directing fuel from a fuel source through a flow splitter to provide at least two …

US20240301835A1 - Method of controlling a combustor - Google Patents
US20240301835A1 - Method of controlling a combustor - Google Patents Method of …

A controller for a gas turbine, wherein the gas turbine includes the compressor arranged to
operate at a rotational speed n, the combustor and the fuel supply including the first fuel …