A combustion chamber with two-stage combustion has primary burners (110) of the premix
type of construction, in which the fuel injected via nozzles (117) is intensively mixed with the …

In a combustion chamber (100) which is designed as an annular combustion chamber and a
mixing essentially comprises a primary zone (1), a mixing section (2) arranged downstream …

(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 …

(57) ABSTRACT A lance is presented for introducing fuel into a second burner of a
combustion chamber of a gas turbine installation with sequential combustion, having a first …

A gas turbine engine, Such as an aircraft jet engine or an industrial gas turbine engine used
for electric power produc tion, include a turbine in which a plurality of stages of Stator Vanes …

The disclosure relates to a diffuser apparatus and system. The diffuser apparatus includes a
gas supply line with an injection port facing a first direction for emitting a gas stream into a …

An engine component includes a hot surface in thermal communication with a hot
combustion gas flow, and a cooling surface, opposite the hot surface, along which a cooling …

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 …

The invention relates to a vortex generator in a flow duct to which a fluid medium is applied,
as well as method for controlling the wake flow of such a vortex generator. The task of safely …