General Electric Company

Ge Infrastructure Technology, LLC

General Electric Technology Gmbh

Jacob Andrew Salm

James Ryan Connor

Gareth William David Lewis

Keith Alan Lord

Srikanth Chandrudu Kottilingam

Gregory Lee Hovis

William Farris Ranson

Stanley Frank Simpson

Jonathan Matthew Lomas

Mark Carmine Bellino

Kassy Moy Hart

John David Ward, Jr

Jason Lee Burnside

Cem Murat Eminoglu

Shan Liu

Jason Adam Neville

Blake Allen Fulton

Jeffrey David Erno

Alexander James Pistner

Parvangada Ganapathy Bojappa

Kelsey Elizabeth Beach

Birol Turan

James Warren Pemrick

Carrie Lynn Grimard

Mark Lawrence Hunt

Onat Bas

Serhat Yumusak

Richard Bowles

Marina Karr

Jillian Jamison Woolridge

Craig Sarratt

Kristen O'brien

Nathan Nicholas Ostrout

Carrie L Grimard

Blakde Allen Fulton

A metal coupon for repairing a component includes an additively manufactured (AM) metal member having a sealed cavity in an interior of the AM metal member, and a porous region around the sealed cavity. A metal coupon system may include at least two AM metal parts with each AM metal part including at least a section of a sealed cavity therein and a porous region around the at least section of the sealed cavity. The AM metal parts combine to form the metal coupon, i.e., AM metal member, with the sealed cavity in an interior thereof and the porous region around the sealed cavity. In any event, the sealed cavity is hollow. The metal coupon with the sealed cavity provides reduced mass and allows braze material to be directed based on characteristics of the porous region of the metal coupon.

Porous metal coupon with sealed cavity for repairing component, component with same and related method

The present application provides a variable spray system for spraying a workpiece with a spray-able material at different angles. The variable spray system may include a linear actuator, a cam follower assembly, and a spray arm assembly. The linear actuator drives the cam follower assembly such that the cam follower assembly positions the spray arm assembly at a first angle with respect to the workpiece in a first stroke of the linear actuator and positions the spray arm assembly at a second angle with respect to the workpiece in a second stroke of the linear actuator.

Machine motion cam track follower

Method of forming or repairing a part with an overhung section. The method may include removing a portion, and adding a section to the part. The section includes the overhung section. The adding includes sequentially layering at least one plurality of material layers on the part, the at least one plurality of material layers approximating dimensions of the section including the overhung section. The sequential layering may include, for example, laser welding, and may be carried out in a number of ways that create varied layers within the overhung section. The method may include machining the at least one plurality of material layers to form the section including the overhung section.

Methods of forming or repairing part with overhung section, and related turbomachine part

Systems and methods for identifying and mitigating gas turbine component misalignment using virtual simulation are disclosed herein. An example method may include capturing data associated with a first nozzle segment and a second nozzle segment of a gas turbine. The method may also include creating, based on the captured data, a virtual representation of the first nozzle segment and the second nozzle segment. The method may also include determining that a misalignment exists in a connection between the virtual representation first nozzle segment and the virtual representation of the second nozzle segment. The method may also include identifying, based on the determination that the misalignment exists, a third nozzle segment. The method may also include determining that a connection between a third nozzle segment and the first nozzle segment includes a smaller misalignment.

Systems and methods for identifying and mitigating gas turbine component misalignment using virtual simulation

Methods for monitoring a components include locating a plurality of machined surface features on the component, locating at least one reference point, and measuring a plurality of first distances between the plurality of machined surface features and the at least one reference point.

Methods for monitoring turbine components

A system and method for virtually inspecting a blade stage is disclosed. The system may include a digitizing device for obtaining a three-dimensional model of a shroud of each blade of the blade stage. A computer system may include at least one module configured to perform the following processes: extract a geometric location data of a plurality of reference points of each shroud from a three-dimensional model of a shroud of each blade of the blade stage created by digitizing using a digitizing device; generate a 3D virtual rendering of the shrouds of the blade stage based on the geometric location data and the known dimensions of the blade stage, the three-dimensional virtual rendering including a rendering of the plurality of reference points of each shroud; and inspect the blade stage using the three-dimensional virtual rendering.

Virtual blade inspection

A system for adaptively machining a shroud of a blade used in a turbomachine is provided. The system may include a computer system including a module(s) configured to: extract geometric location data from a 3D model of the shroud after use in the turbomachine, the 3D model created by digitizing using a digitizing device. The geometric location data includes geometric location data of a hard face plane of the shroud exposed to wear during turbomachine operation and of a non-worn surface adjacent to the hard face plane substantially unexposed to wear during turbomachine operation. Comparing the geometric location data of the non-worn surface from the three-dimensional model to a manufacturing model of the blade determines a change in position of the non-worn surface from use of the blade in the turbomachine. The change in position is used to modify a machining instruction used by a machining device to repair the hard face plane.

Adaptive machining turbomachine blade shroud hard face

An apparatus for inspecting a turbine blade tip shroud includes a frame comprising a top surface and a bottom surface that is alignable with the turbine blade tip shroud, and, at least one z-notch inspection slot that passes through the frame from the top surface to the bottom surface and is positioned to align with at least one z-notch of the turbine blade tip shroud when the frame is aligned on the turbine blade tip shroud. The apparatus further includes a removable z-notch inspection insert comprising a cross-sectional profile substantially matching the at least one z-notch inspection slot and comprising a z-notch guide face that faces the z-notch of the turbine blade tip shroud when the removable z-notch inspection insert is passed through the z-notch inspection slot

Apparatus and method for inspecting a turbine blade tip shroud

According to one aspect, a fixture for an airfoil shroud having a first end edge, a second end edge, a leading edge, a trailing edge, a radially outer side and a radially inner side with respect to a rotor axis of a bucket having the airfoil shroud is provided. The fixture includes a base plate, a first member extending from the base plate configured to locate and abut the first end edge, a second member extending from the base plate configured to locate and abut a side of a seal rail, a third member extending from the base plate configured to locate and abut the radially outer side of the airfoil shroud and a template recess formed in the base plate proximate the first end edge to define a geometry of a relief cut in the trailing edge of the airfoil shroud.

Fixture for an airfoil shroud and method for modifying an airfoil shroud

A system and method for virtually inspecting contact gaps of a blade stage of a turbomachine is disclosed. The system may include a digitizing device for obtaining a three-dimensional model of a shroud of each blade of the blade stage. A computer system may include at least one module configured to perform the following steps: extracting a geometric location data of a hard place plane of each shroud from the three-dimensional model; generating a three-dimensional virtual rendering of the shrouds of the blade stage based on the geometric location data and the known dimensions of the blade stage, the three-dimensional virtual rendering including a rendering of contact gaps between adjacent shrouds; and inspecting the blade stage using the three-dimensional virtual rendering.

Virtual turbomachine blade contact gap inspection

Braze methods include providing a substrate comprising a pre-sintered preform disposed thereon, wherein the pre-sintered preform comprises a mixture comprising a base alloy comprising about 30 weight percent to about 90 weight percent of the mixture and a second alloy comprising a sufficient amount of melting point depressant to have a lower melting temperature than the base alloy. Braze methods further include at least partially covering the pre-sintered preform with a heat resistant material, wherein a melt temperature of the heat resistant material is higher than a melt temperature of the pre-sintered preform, and heating the pre-sintered preform on the substrate.

Braze methods and components with heat resistant materials

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Mauldin, SC, United States of America

Jacob Andrew Salm