The invention relates to a gas turbine assembly which substantially includes at least one
compressor, at least one first burner, at least one second burner that is connected …

The present disclosure is directed to a fuel nozzle for a gas turbine engine. The fuel nozzle
includes a sleeve defining a plurality of radially oriented air inlet ports. The sleeve defines a …

The present disclosure is directed to a fuel injector including a centerbody defining an air
inlet opening defined substan tially radially through the centerbody; an outer sleeve sur …

The present disclosure is directed to a fuel injector for a gas turbine engine including an end
wall defining a fluid chamber, a centerbody, and an outer sleeve surrounding the centerbody …

(57) ABSTRACT A burner for a combustion chamber of a turbine, with an injection device for
the introduction of at least one gaseous and/or liquid fuel into the burner is proposed. The …

The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector
includes an end wall defining a fluid chamber, a centerbody, an outer sleeve surrounding …

A gas turbine system includes a turbine combustor. The turbine combustor includes one or
more first fuel injectors coupled to a head end of the turbine combustor and configured to …

The disclosure relates to a burner Such as for a secondary combustion chamber of a gas
turbine with sequential com bustion having a first and a second combustion chamber, with …

A burner, such as for a secondary combustion chamber of a gas turbine with sequential
combustion having first and second combustion chambers, includes an injection device for …

A reheat burner arrangement including a center body, an annular duct with a cross-section
area, an intermediate fuel injection plane located along the center body and being actively …