General Electric Company

Ronald Lance Galley

David Edwin Budinger

Stephen Joseph Ferrigno

Roger Dale Wustman

Jonathan Philip Clarke

Wayne Alan Demo

Alistair Smith

Ching-Pang Lee

Nripendra Nath Das

Clifford Earl Shamblen

Joshua L Miller

Thomas Froats Broderick

David Allen Kastrup

Mark Dean Pezzutti

Vincent Marion Drerup

Roger Owen Barbe

Daniel Padraic O'Reilly

L Timothy Rasch

Reed Roy Oliver

Douglas M Carlson

Mariusz Pawel Staszak

Jae Yong Um

Richard W Albrecht

Craig Douglas Carmichael

Ashwin Sreekant Raghavan

Anthony Philip Italiano

Brian Robert Graham

A direct metal laser sintered material including a substrate formed from a laser sintering process, the substrate having at least one surface, and a cladding material brazed onto at least a portion of the surface.

Blaze cladding for direct metal laser sintered materials

A method for restoring a crack formed within a turbo charger engine transition section, the method including preparing a crack in the transition section to receive a material within the crack, applying the material within the crack, and retaining structural integrity of the transition section proximate the crack while at least one of preparing the crack and applying the material.

Method, system, and computer software code for repairing a transition section of an engine

A process for brazing components formed of superalloys that contain elements prone to oxidation during brazing. At least one braze tape is applied to at least one faying surface of at least a first of the components being joined by brazing. The braze tape comprises a braze tape alloy containing the base metal of the superalloys and a melting point suppressant, and is applied so as to substantially cover the faying surface. The braze tape is then bonded to the faying surface by heating the first component to a temperature not exceeding the brazing temperature required to join the components. Thereafter, the components are assembled so that the bonded braze tape are between the respective faying surfaces of the components. The components are then brazed together by applying and heating a braze alloy to the braze temperature.

Process of brazing superalloy components

A method for restoring a length of at least one of a master rod and an articulating rod, the method including determining a length of the rod, if the rod is within an acceptable length, cleaning the rod, applying a masking material to a part of the rod to be protected, grit blasting the part of the rod not protected by the masking material, and applying a thermal spray to the part of the rod not protected by the masking material to increase the length of the rod.

Method, computer software code, and system for restoration of master and articulating rods

The pulsed partial pressure hydrogen cleaning of cobalt-based alloys in turbine components is achieved by disposing the component within a vacuum furnace and heating the component. Upon heating to about 1400&#xb0; F., a partial pressure hydrogen gas and a vacuum are repetitively cycled within the furnace by supplying in each cycle a fresh supply of hydrogen gas, followed by removal of reaction products between the hydrogen gas and surface contaminants and substantially all residual hydrogen gas from within the furnace. The repetitious cycling renders the surfaces clean, enabling refurbishment thereof by activated diffusion healing repair.

Methods of hydrogen cleaning of metallic surfaces

A method for assembling a vane sector for a gas turbine engine, the vane sector including an airfoil vane and a platform includes depositing a wear coating material onto a selected area of the platform, positioning the platform adjacent to the airfoil vane, and executing a brazing operation such that the airfoil vane is permanently coupled to the platform portion and such that the wear coating material is bonded across a predefined area of the platform.

Method for coating gas turbine engine components

A gas turbine engine compressor including a stator assembly and a method of assembling the same are provided. The method includes providing a compressor casing including at least two stator vane casing rails extending from the casing, coupling a rail liner within each respective casing rail, and coupling a stator vane assembly including two dovetails, and at least two stator vanes coupled together within the casing rails within the liner such that a first dovetail is received within a first casing rail and a first rail liner, and a second dovetail is received within a second casing rail and a second rail liner.

Methods and apparatus for assembling gas turbine engines

A method enables a nozzle assembly for a gas turbine engine rotor assembly to be fabricated. The rotor assembly includes at least two adjacent rows of rotor blades coupled together by a disk spacer arm. The method includes providing a nozzle assembly that includes at least one nozzle including a vane that extends outwardly from a radially outer side of an inner band, coupling the nozzle assembly into the rotor assembly between the two adjacent rows of rotor blades, and coupling a seal assembly that includes a backing piece to the nozzle assembly such that the backing piece is substantially parallel to the rotor assembly disk spacer arm.

Methods and apparatus to reduce seal rubbing within gas turbine engines

A built-up gas turbine component is prepared by providing a gas turbine component having a component surface and being made of a component base metal having a component base metal composition. A buildup tape is supplied having a net metallic buildup composition different from the component base metal composition. The buildup tape includes a first metallic constituent having a first melting point, and a second metallic constituent having a second melting point. The first metallic constituent and second metallic constituent together have the net metallic buildup composition. A nonmetallic binder binds together the first metallic constituent and the second metallic constituent. The buildup tape is applied to the component surface and heated to a brazing temperature greater than the first melting point and less than the second melting point. The first metallic constituent melts and fuses the first metallic constituent and the second metallic constituent to the component surface as a buildup deposit on the built-up gas turbine component.

Built-up gas turbine component and its fabrication

A tip cap hole is loaded with a first composition comprising particles of a first alloy having a solidus temperature above the brazing temperature. The first composition is covered with a second composition comprising particles of a second alloy having a liquidus temperature below the brazing temperature. The second composition is heated to the brazing temperature to cause particles of the second alloy to melt to form a liquid of the second alloy which is carried into spaces between the particles of the first alloy by capillarity. The liquid of the second alloy is cooled to form a solid securely bonding the particles of the first alloy. By weight, the second alloy has no more than 1% B and from 3% to 11% Si. The first alloy has Cr and at least about 5% Al, at least about 0.5% Hf, no more than 0.5% Ti.

Tip cap hole brazing and oxidation resistant alloy therefor

An airfoil and a band or platform member of a vane segment, such as of a turbine engine, are bonded at a non-linear clearance slot formed between a shelf in the band and an end and edge of the airfoil. A reservoir bead of a bonding alloy slurry is deposited at one slot opening, a metallic powder is packed into the slot, and another reservoir bead is applied at a slot second opening substantially to close the slot and entrap the powder therein. Then the reservoir beads and powder are heated to flow material of the beads into the clearance slot. This bonds the airfoil and band securely at a deep pocket or blind slot.

Growing community of inventors

Mason, OH, United States of America

Ronald Lance Galley