Ansaldo Energia IP UK Limited

6k Inc.

Siemens Aktiengesellschaft

Siemens Energy, Inc.

H2 IP UK Limited

Pawel Matys

Peter Stuttaford

Douglas Pennell

Stephen Wilder Jorgensen

Donald Gauthier

Michael C Kozlowski

Thomas R Ruck

Joshua R McNally

Bernard Tam-Yen Sam

Marc Paskin

Makhlouf Redjdal

John A Orosa

Zongren Shang

Joseph Robert Caruso

Michael Resnick

Stephen W Jorgensen

Douglas Pennel

Peter John Stuttaford

Disclosed herein are systems, methods, and devices processing feed material utilizing an upstream swirl module and composite gas flows. Some embodiments are directed to a microwave plasma apparatus for processing a material, comprising: a first flow module, a second flow module, and a liner.

Plasma apparatus and methods for processing feed material utilizing an upstream swirl module and composite gas flows

An apparatus for providing material feedstock into a plasma of a plasma torch includes a material feeding device having an input end and an output end. The output end of the material feeding device extends at least partially around the periphery of a plasma generated near the output end of the plasma torch. The material feeding device is oriented at an angle with respect to a central axis of the plasma torch.

Method and apparatus for feeding material into a plasma

Systems and methods for dual-fuel operation of a gas turbine combustor are provided. An exemplary gas turbine combustor may comprise one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly, one or more of which may be configured to supply either a gaseous or a liquid fuel to the combustion liner, depending on whether gaseous fuel operation or liquid fuel operation of the combustor is desired.

Fuel injection locations based on combustor flow path

Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly. An exemplary fuel cartridge assembly may comprise first and second fuel manifolds which are connected to respective fuel circuits which supply fuel, such as liquid fuel, through a plurality of fuel passages within the fuel cartridge assembly or to other locations within an associated combustor. The fuel cartridge assembly may further include a plurality of fuel injector tips located at a tip plate of the fuel cartridge assembly through which fuel may be supplied to an associated combustor.

Gas turbine fuel components

An exhaust diffuser comprising an inner boundary and an outer boundary forming an annular gas path, and a plurality of strut structures extending radially within the gas path. Each of the strut structures include pressure and suction side walls, and a plurality of radially spaced flow injectors are formed in at least one of the pressure and suction side walls for injecting a fluid flow into the gas path adjacent to the strut structure. At least two fluid supply conduits provide a fluid flow to respective radially spaced flow injectors, and a flow control device is associated with each of the conduits to independently control a fluid flow from a fluid source to each of the radially spaced flow injectors.

Gas turbine diffuser strut including coanda flow injection

A flow passage defined between an inner and an outer boundary for guiding a fluid flow in an axial direction. A flow control vane is supported at a radial location between the inner and outer boundaries. A fluid discharge opening is provided for discharging a flow of the compressed fluid from a trailing edge of the vane, and a fluid control surface is provided adjacent to the fluid discharge opening and extends in the axial direction at the trailing edge of the vane. The fluid control surface has a curved trailing edge forming a Coanda surface. The fluid discharge opening is selectively provided with a compressed fluid to produce a Coanda effect along the control surface. The Coanda effect has a component in the radial direction effecting a turning of the fluid flow in the flow path radially inward or outward toward one of the inner and outer boundaries.

Gas turbine engine exhaust diffuser including circumferential vane

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Jupiter, FL, United States of America

Pawel Matys