A swirler including an annular housing with limiting walls. At least two vanes are arranged in
the annular housing including the sidewalls of the swirler. The leading edge area of each …

(57) ABSTRACT A fuel lance is disclosed for injecting a gaseous and/or liquid fuel mixed
with air into an axial hot gas flow flowing through a sequential combustor of a gas turbine …

The present invention generally relates to a sequential combustor for a gas turbine having
second and/or subse quent stages of a re-heat, sequential or axially-staged com bustion …

Embodiments of the present disclosure provide an apparatus including: a first injector
located on a surface of a turbine nozzle of a turbine stage positioned downstream of a …

The invention relates to a burner arrangement for using in a single combustion chamber or
in a can-combustor comprising a center body burner located upstream of a combustion …

An acoustic damper for a rotary machine includes at least one wall, at least one cooling air
inlet, at least one outlet, and at least one cap. The at least one wall extends from a back side …

Disclosed is a fuel injector device having a body with a leading edge and a trailing edge and
defining a streamwise direction from the leading edge to the trailing edge, the fuel injector …

Embodiments of the present disclosure provide an apparatus comprising: a reaction
chamber positioned between a first turbine stage of a power generation system and a …

Apparatus and method for a combustion turbine engine are provided. The apparatus may
include a fuel-injecting lance (12) to convey a liquid fuel to a downstream end (16) of the …

In some embodiments, systems, apparatuses and methods are provided herein useful for
spraying fuel in an augmented gas turbine engine. The embodiments may include a spray …