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 …

A turbofan gas turbine engine augmenter includes a fuel/air swirler disposed between an
axially extending bypass flowpath and an axially extending exhaust flowpath. A swirler inlet …

An asymmetric tetrahedral vortex generator that provides for control of three-dimensional
flow separation over an underlying surface by bringing high momentum outer region flow to …

In a burner for operating a heat generator, which burner essentially comprises a Swirl
generator (100), a transition piece (200) arranged downstream of the Swirl generator, and a …

(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 …

In a combustion chamber, a gaseous or liquid fuel is injected as a secondary flow into a
gaseous, channelized main flow. The main flow is directed to pass over a plurality of vortex …

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 …

(57) ABSTRACT A detonation chamber for a pulse detonation combustor including: a
plurality of duplex tab obstacles disposed on at least a portion of an inner Surface of the …