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 …

An anti-icing system for annular gas turbine engine inlet housings includes a substantially
closed annular housing at a leading edge of the gas turbine engine inlet housing, the …

The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for
separating a space region through which hot working medium flows from a space region …

The present disclosure relates to a fuel-air premixer for a turbine system. The fuel-air
premixer includes a swirler and a centerbody. The swirler is configured to direct a flow of air …

The invention provides a new path of combustion technol ogy for gas turbine operation with
multifuel capability, low emissions of NO, and CO and high thermal efficiency. Further to the …

The invention refers to a sequential combustor arrangement including a first combustor with
a first burner for admitting a first fuel into a combustor inlet gas during operation and a first …

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 …

A lobe lance is disclosed for a gas turbine combustor which includes a plurality of N (N≥ 4)
lobe fingers, each configured as a streamlined body with two lateral surfaces. A plurality of …

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 …