Florida Turbine Technologies, Inc.

Siemens Energy, Inc.

Walter Marussich

Kenneth K Landis

George P Liang

Ching-Pang Lee

Jay Alan Morrison

David James Wiebe

Alexander Ralph Beeck

Richard Colin Charron

Alex Pinera

Todd A Ebert

William W Pankey

Nicholas F Martin, Jr

Brian J Wessell

Daniel J Pierce

Marco Claudio Pio Brunelli

Sameer A Khan

Beatriz Suarez-Crosse

A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.

Turbine transition component formed from an air-cooled multi-layer outer panel for use in a gas turbine engine

A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes a cooling fluid supply trench having an open top portion and extending radially inwardly from a central recessed portion of the panel. The cooling system further includes a plurality of cooling fluid passages extending from the cooling fluid supply trench to a leading edge and/or a trailing edge of the panel. The cooling fluid passages receive cooling fluid from the cooling fluid supply trench, wherein the cooling fluid provides convective cooling to the panel as it passes through the cooling fluid passages.

Ring segment with cooling fluid supply trench

A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.

Gas turbine sealing apparatus

An air bearing with a rotor and a static land forming a clearance gap, the rotor including a compressible fluid supply channel to supply fluid to the bearing, and the rotor including a bearing inner race rotatably secured to the rotor, the inner race having an outer surface with a plurality of pockets opening outward and connected to a high pressure reservoir on the inner surface of the inner race through a plurality of radial extending supply channels that function as centrifugal pumps when the inner race is rotating to increase the bearing fluid pressure within the air bearing and increase the bearing stiffness. The inner race pockets extend around the full annular surface.

Air bearing

A rotary shaft to hub connection, such as that used between a centrifugal compressor or pump and a shaft. The hub includes inner and outer axial extending members that fit within inner and outer annular grooves formed within the rotary shaft so that a tight fit between the shaft and the hub is maintained during high speed rotation. An inwardly extending projection is formed on the outer axial extending member of the hub that forms a tight fit against the shaft.

Hub to shaft connection

A turbomachine having a rotor blade with a tip seal formed between the blade tip and the shroud, where the tip seal is formed by a thin metal plate extending from the blade tip and bending away from the direction of rotation of the blade such that a flat surface of the thin metal plate floats against the shroud surface by a cushion of air formed due to the rotation. The tip seal is forced against the shroud surface due to centrifugal force from rotation so that the tip seals maintain a seal even in cases of high eccentricity. Because of the cushion of air formed from rotation, the tip seal does not wear from rubbing. The flexible plate tip seal is formed from a material such as titanium for use in a compressor, or from a high temperature resistant metal alloy such as Inco 625 for use in a turbine of a gas turbine engine.

Pressure balanced centrifugal tip seal

A rotor disk assembly having a plurality of rotor disks secured together by annular projections with screw threads thereon for easy assembly and disassembly. The annular projections include a plurality of spring biased pins that push against an opposing annular projection due to centrifugal forces during rotation of the rotor disks at such a force as to hold the rotor disks against loosening from vibrations. The spring biased pins have a low enough spring constant that the pins are disengaged when enough torque is applied to unscrew the rotor disk from one another.

Threaded rotor assembly with a centrifugal lock

A hydrostatic air bearing in which a journal rotates within a cavity formed within a bearing race, and a sleeve that rotates with the journal within the cavity of the bearing race, where the sleeve is formed of a porous metallic material that allows for a bearing fluid such as air to flow from a high pressure side of the journal to a low pressure side of the journal through the porous sleeve that acts to dampen the bearing fluid flow, and therefore dampen the bearing. Another embodiment is for a hydrodynamic air bearing with an annular sleeve arranged between the rotating journal and the bearing race, where the annular sleeve is formed of a porous metallic material to dampen air flow across the journal.

Growing community of inventors

Palm Beach Gardens, FL, United States of America

Walter Marussich