Power Systems Mfg., LLC

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

H2 IP UK Limited

Joshua R McNally

Stephen Wilder Jorgensen

Peter Stuttaford

Gregory Edwin Vogel

Bernard Tam-Yen Sam

Hany Rizkalla

Douglas Pennell

Donald Gauthier

Thomas R Ruck

Pawel Matys

Matthew Yaquinto

Fred Hernandez

Marc Paskin

Bryan Kalb

Adnan Eroglu

Khalid Oumejjoud

Nicolas Demougeot

Thomas Zierer

Alfredo Cires

Frank Graf

Daniel Seng

Gene Chong

Marcos Escudero Olano

Davide Aratori

Heinz Gerber

Ramesh Keshava-Bhattu

Stephan Strueken

Vladimir Kitaigorod

Afzal Pasha Mohammed

Ramesh Keshava Bhattu

Douglas Anthony Pennel

Thomas Rosenbarger

James Brackett

Bernard Tam Yen Sam

David E Paredes

Peter John Stuttaford

Stephen W Jorgensen

Douglas Pennel

An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. Each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes includes a substantially quadrilateral cross-sectional profile, and each of the air/fuel mixing tubes of the radially inner subset of air/fuel mixing tubes includes a substantially circular cross-sectional profile.

Multitube pilot injector having a split airflow for a gas turbine engine

Modular assemblies for gas turbine engines such as modular vane assemblies and methods of manufacturing the same. The modular assembly includes a first modular component such as a vane platform having a first mating pocket, and a second modular such as an airfoil. The second modular component includes circumferentially extending first and second surfaces at first and second distal ends thereof, respectively, with the first surface being received within the first pocket when the modular assembly is in the assembled state. The second modular component also includes a coating pocket extending from the first surface to the second surface. The coating pocket is recessed towards an interior of the second modular component with respect to first surface and the second surface, and a thermal barrier coating is included within the coating pocket and not included on the first surface or the surface.

Modular components for gas turbine engines and methods of manufacturing the same

An airfoil and turbine vanes and vane assemblies incorporating the same. The airfoil has an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1, carried to four decimal places. The Z values refer to a percentage of the radial span of the airfoil measured radially from a radially outwardly facing surface of the inner platform. The turbine vane includes an inner platform, an outer platform, and an airfoil such as the one discussed above extending radially outward from the inner platform toward the outer platform. And the vane assembly includes an inner platform, an outer platform, and two or more first stage vanes extending from the inner platform to the outer platform. Each of the two or more first stage vanes include an airfoil as discussed above.

Additive manufacturing optimized first stage vane

A sealing arrangement at an interface between a combustor and a turbine of a gas turbine. The turbine can include deflecting vanes at its inlet, which deflecting vanes are each mounted within the turbine so as to define an inner or outer diameter platform and are in sealing engagement via an inner or outer diameter vane tooth with a seal arranged at the corresponding inner or outer diameter part of the outlet of the combustor. The seal is movable and is pressed on the inner or outer diameter vane tooth by a differential pressure such that the pressure of the mainstream hot gas flow is a lower pressure.

Sealing device arrangement at the interface between a combustor and a turbine of a gas turbine and gas turbine with such a sealing arrangement

A diffusion cartridge assembly for a gas turbine engine, and methods of using the same. The diffusion cartridge assembly includes a tip plate with an array of fuel supply openings and a mounting hole radially inward of the array of fuel supply openings, an end cover, and an outer sleeve extending from the tip plate to the end cover and defining an open inner chamber. A fuel supply line is coupled to the end cover and extends within the open inner chamber toward the tip plate. A manifold is coupled to an end of the fuel supply line proximate to the tip plate, and includes an array of fuel injector tips. Each of the fuel injector tips extends through a respective one of the array of fuel supply openings in the tip plate. The manifold also includes a thermally free mounting pin extending into the mounting hole.

Flamesheet diffusion cartridge

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

A mounting and dismounting device for a liner of a gas turbine includes two inner rails attached at the turbine housing and each one having a first straight portion, two straight outer rails releasably attached at the turbine housing, wherein the adjacent free ends of the inner and outer rails can be positioned in full alignment one to the other. The rails are adapted to support the liner to be moveable in its axial direction. The inner rails include a second straight portion connected to the first straight portion through a curved portion wherein the axis of the second straight portion is parallel to the axis of the combustion gas passageway.

Mounting and dismounting device for a liner of a gas turbine and a related method

Growing community of inventors

Jupiter, FL, United States of America

Joshua R McNally