General Electric Company

Gary Charles Liotta

Robert Francis Manning

Paul J Acquaviva

Zachary John Snider

Brian Denver Potter

Andres Jose Garcia-Crespo

John Wesley Harris, Jr

Thomas Raymond Farrell

Randall Richard Good

James William Vehr

Anthony Aaron Chiurato

Benjamin Arnette LaGrange

Bin Wei

Ian David Wilson

Stephen Paul Wassynger

Larry W Plemmons

Melvin Bobo

Stanley Frank Simpson

John Howard Starkweather

David Richard Johns

John David Ward, Jr

Robert Walter Coign

Carlos Miguel Miranda

John Herbert Dimmick

Eric Richard Bonini

Elias Harry Lampes

Jeffrey Carl Mayer

David A Niday

Matthew Durham Collier

Scott Patrick Ryczek

Robert John Parks

James N Fleck

Peter Andrew Simeone

Andres Jose Garcia Crespo

Jon Robert DeLong

James Patrick McGovern

John Robert Sech

Antonio C Gominho

Patrick Shawn Reilly

Jeffrey Todd Knapp

Christopher Sean Bowes

Jonathan David Crim

Gianni Busso

Robert Edwin Shockley

Garth Kneeland Grover

Kiran Sreeram

Alan P Wilds

Leston M Freeman, Jr

Richard Henry Langdon, Ii

John Herbert Iii Dimmick

David Andrew Niday

A method for constructing a variable nozzle assembly within a turbine engine that includes: constructing a variable nozzle sub-assembly; attaching the variable nozzle sub-assembly to a casing; and linking segments of a segmented shaft via an opening. Constructing the variable nozzle sub-assembly may include: attaching a downstream inner platform to a upstream inner platform; inserting an outer stem of a first segment through an outer stem opening formed through the downstream outer platform; connecting the first segment to the downstream outer platform by loading a first bearing about a protruding spherical shaped section of the outer stem; inserting the inner stem through an opening formed through the downstream inner platform while aligning sidewalls of the downstream and upstream outer platforms; mechanically securing the aligned sidewalls; and connecting the first segment to the downstream inner platform by loading a second bearing about a protruding spherical shaped section of the inner stem.

Variable nozzles in turbine engines and methods related thereto

A turbine engine having a variable nozzle assembly that includes: a variable nozzle having an airfoil that extends radially across an annulus formed between inner and outer platforms; and a segmented shaft that translates a torque between segments included therewithin. The segmented shaft may include a first and second segment. The first segment of the segmented shaft may include: the airfoil of the variable nozzle; an outer stem extending from the outer end of the airfoil; and an inner stem extending from the inner end of the airfoil. A first and second connector may connect the first segment to the inner platform and outer platform, respectively. A third connector may connect the first segment to the second segment. The first and second connector may include a first and second spherical bearing, respectively. The third connector may include a first universal joint.

A rotor wheel for an engine includes a plurality of impeller vanes and a plurality of fluid passages defined by adjacent impeller vanes. The fluid passages are radially disposed across at least a portion of the rotor wheel. One or more impeller inserts may be disposed within one or more of the plurality of fluid passages, respectively. The impeller inserts define an impeller passage with a passage shape that controls a flow of fluid through the one or more of the plurality of fluid passages.

Rotor wheel and impeller inserts

A system includes a multi-stage turbine. The multi-stage turbine has an interstage seal extending axially between a first turbine stage and a second turbine stage. The interstage seal has an upper body that extends from an upstream seating arm to a downstream seating arm. The upstream and downstream seating arms are designed to constrain movement of the interstage seal along a radial direction of the multi-stage turbine. The interstage seal also has a lower body that extends from a seating end to a hook end. The seating end is designed to constrain movement of the interstage seal along the radial direction. The hook end has a protrusion that extends crosswise relative to a base of the lower body. The hook end is designed to constrain movement of the interstage seal along the radial direction and an axial direction of the multi-stage turbine.

Turbine interstage seal system

A sealing component for reducing secondary airflow in a turbine system includes a first end segment configured to be disposed between, and retained in a radial direction by, a first land on a first rotor disk and a first turbine bucket platform operatively coupled to the first rotor disk. Also included is a second end segment configured to be disposed between, and retained in a radial direction by, a second land on a second rotor disk and a second turbine bucket platform operatively coupled to the second rotor disk. Further included is a main body portion extending axially from the first end segment to the second end segment.

Sealing component for reducing secondary airflow in a turbine system

The present application provides a cover plate assembly for use with a rotor disk. The cover plate assembly may include a radial flange extending from the rotor disk, a flange aperture extending through the radial flange, a cover plate segment with a fastening aperture and a hook for receiving the radial flange, and a fastener extending through the flange aperture and the fastening aperture.

Turbine cover plate assembly

In one aspect, the present subject matter discloses a seal including a substrate material. The substrate material has a first portion having a first abradability and a second portion having a second abradability, the first abradability being different from the second abradability.

Modification of turbine engine seal abradability

A thermally actuated assembly for a gas turbine assembly for a gas turbine system includes a heat transfer component having a first portion and a second portion, wherein the first portion is disposed within a first cavity having a first temperature and the second portion is disposed in a second cavity having a second temperature, wherein the heat transfer component extends through a cavity wall, wherein the first temperature is greater than the second temperature. Also included is a temperature sensitive element disposed within the second cavity and in operable communication with the heat transfer component. Further included is a flow manipulating device disposed within the second cavity and configured to displace in response to a temperature change in the first cavity.

Thermally actuated assembly for a gas turbine system and method of controlling a cooling airflow path

An apparatus for restricting fluid flow in a turbo-machine is disclosed. The apparatus includes: a first inter-stage sealing member configured to be located between a first rotating airfoil stage and a second rotating airfoil stage attached to a rotor shaft, the first inter-stage sealing member including a segmented structure that includes a plurality of segments forming a circumferential surface, the first inter-stage sealing member including: a first base portion including a securing mechanism configured to at least substantially radially and tangentially secure the inter-stage sealing member to an inter-stage support structure; a first axial retention mechanism; and a first axially extending sealing portion configured to be outwardly radially loaded against at least one of the first rotating airfoil stage and the second rotating airfoil stage.

Apparatus and system for sealing a turbine rotor

A turbine bucket includes an airfoil portion and a tip shroud at a radially outer end of the airfoil portion. The tip shroud includes a first radially inner tip shroud component formed integrally with the airfoil portion and composed of a first metal material, and a second radially outer structural tip shroud component composed of a second metal material bonded to the first radially inner tip shroud component.

Bonded turbine bucket tip shroud and related method

A composite turbine blade assembly includes a ceramic blade including an airfoil portion, a shank portion and an attachment portion; and a transition assembly adapted to attach the ceramic blade to a turbine disk or rotor, the transition assembly including first and second transition components clamped together, trapping said ceramic airfoil therebetween. Interior surfaces of the first and second transition portions are formed to mate with the shank portion and the attachment portion of the ceramic blade, and exterior surfaces of said first and second transition components are formed to include an attachment feature enabling the transition assembly to be attached to the turbine rotor or disk.

Composite turbine bucket assembly

A nozzle is disclosed for use in a turbine or compressor. In an embodiment, each of a plurality of vanes is supported by an outer shroud including a plurality of outer shroud segments disposed adjacent to adjoining segments in end-to-end relationship. Each segment includes a hole therethrough, dimensioned to receive a vane extension sleeve. This system may be used in conjunction with a modulated cooling system and may allow for improved removal for overhaul.

Variable turbine nozzle system

A system for modulating the amount of air supplied through a pressure boundary in a gas turbine is disclosed that includes a passageway located on the pressure boundary. Additionally, a temperature activated valve is mounted within the passageway and is configured to activate at a predetermined temperature threshold. Specifically, the temperature activated valve activates from a closed position to an open position when the local temperature at the temperature activated valve reaches or exceeds the predetermined temperature threshold to allow air to flow through the passageway.

Temperature activated valves for gas turbines

An electrode for an electrochemical machining process is provided. The electrode comprises a curved, electrically conductive member, and an insulating coating covering at least a portion of a side surface of the curved, electrically conductive member. An electrochemical machining assembly is also provided for machining curved holes in a workpiece. The assembly includes at least one curved electrode and a power supply operatively connected to provide a pulsed voltage to the at least one curved electrode and to the workpiece. The assembly further includes a rotational driver operatively connected to move the at least one curved electrode along a curved path within the workpiece. The assembly is configured to remove material from the workpiece upon application of the pulsed voltage to the at least one curved electrode and to the workpiece. An electrochemical machining method is also provided for forming one or more curved holes in an electrically conductive workpiece.

Electrochemical machining assembly with curved electrode

A seal for a dovetail joint in a turbomachine is provided. The seal includes an arcuate member having a first end, a middle portion and a second end. The seal also includes sealing means, which include at least one sealing member. The sealing member can comprise a first sealing member connected to the first end and/or a second sealing member connected to the second end. The dovetail joint is the interface between a bucket dovetail and a rotor dovetail groove, and the seal reduces the amount of cooling flow leakage from the dovetail joint.

Clamped plate seal

Growing community of inventors

Simpsonville, SC, United States of America

Gary Charles Liotta