Gas turbine engine and fuel nozzle assembly therefor

Abstract

A method of operating a gas turbine engine having a compressor section, a combustion section including a combustion chamber, and a turbine section in a serial flow arrangement, the method comprises providing gaseous hydrogen fuel to a gaseous fuel nozzle assembly fluidly coupled with the combustion chamber; providing steam to the gaseous fuel nozzle assembly. The method also comprises controlling a flame speed of a flame in the combustion chamber by providing the steam from the gaseous fuel nozzle assembly to the combustion chamber.

Dependencies are inferred from the claim text.