General Electric Company

Ansaldo Energia IP UK Limited

Alstom Technology Limited

Ansaldo Energia Switzerland Ag

Alstom Technologies Ltd

Warren Martin Miglietti

Paul Stephen DiMascio

Steve Paul Byam

Matthew James O'Connell

Srikanth Chandrudu Kottilingam

Yan Cui

Canan Uslu Hardwicke

David Vincent Bucci

Mark Lawrence Hunt

Brian L Henderson

David R Kaser

Andrew C Pappadouplos

Charles Gitahi Mukira

Ganjiang Feng

Liang Jiang

Laurent Cretegny

Arthur Samuel Peck

Christopher Michael Penny

Michael Seemann

Steven Charles Rauch

Raphael Schweizer

Ahmad Zaki Bin Ahmad Zainuddin

Emmerson Denver Rene

Richard Douglas Konney

John Roderick

Kivilcim Onal Hance

Matthias Stampfli

Reto Maitz

Matthias Stämpfli

A method for repairing a blade tip of a turbine blade based on welding below and above a designated depth recommended for repair of turbine blades. A damaged portion of the turbine blade is inspected to identify a standard cut portion and an angled cut portion. The standard cut portion is damaged above a standard cut line and the angled cut portion is damaged below the standard cut line. The damaged portion of the turbine blade is removed. The standard cut portion is removed using a first removal process and the angled cut portion is removed using a second removal process. The angled cut portion is built up with a first weld repair process. The angled cut portion is built up to the standard cut portion. The standard cut portion and the angled cut portion are built up with a second weld repair process.

Deep trailing edge repair

A method is provided for reconditioning a turbine blade. The turbine blade includes a blade airfoil which extends longitudinally and into the hollow inner space of which inserts can be inserted in the longitudinal direction of the blade for distribution and guiding cooling air which flows in the inner space. The inserts with a rib engage with sealing effect in a U-shaped sealing groove which is machined out on the inner wall of the blade airfoil and extend in the longitudinal direction of the blade. A damaged sealing groove is reconditioned by the sealing groove being removed from the inner wall of the blade airfoil, forming a slot, by an insertion strip, which is provided for sealing, being inserted into the slot, and by the insertion strip, which is seated in the slot, being connected in a materially bonding manner to the inner wall of the blade airfoil.

Method for reconditioning a turbine blade

A method for repairing a blade tip of a turbine blade based on a dual fusion weld process for portions of a tip plate and a mechanical locking bead over the tip plate. A damaged portion of blade is removed. The damaged portion is removed at an initial cut level. An undamaged portion of the turbine blade exists as a base below the initial cut level. A replacement section is rebuilt via laser cladding. The replacement section is machined to form a tip pocket. A tip plate is placed in the tip pocket. The tip plate comprises at least a first portion and a second portion. The tip plate is welded using a dual fusion weld process comprising a first weld process and a second weld process. A squealer tip is built using a welding process that forms a mechanical locking bead over the tip plate.

Turbine blade tip repair using dual fusion welding

The present invention discloses various methods for repairing a side seal region of a transition duct aft frame region. Embodiments of the present invention include application of a braze filler material to worn locations of seal teeth, brazing of a braze preform to the seal teeth or removal of a worn seal tooth and brazing of material compatible with the transition duct to form a replacement tooth of the side seal. The transition duct is brazed in a furnace in an incremental heated process which elevates the transition duct to a temperature where the braze filler material adheres to the side seal region while also providing a stress relief to the transition duct.

Method of repairing a transition duct side seal

A method of extending the useable life of a gas turbine component fabricated from a cobalt-based alloy is disclosed. The method includes applying a rejuvenation process to the alloy where the alloy is placed in a protected atmosphere and heated to three different elevated temperatures and held at the elevated temperatures for approximately four hours each. Application of the rejuvenation process allows gas turbine components to be returned to service for at least one more service interval of approximately 24,000 operating hours.

Extending useful life of a cobalt-based gas turbine component

A composite turbine blade and a method of manufacture thereof is disclosed. The composite turbine blade comprises a turbine blade portion comprising a first material and a first tip plate comprising a second material. The turbine blade portion has an exterior wall and an interior wall surrounding a hollow interior cavity, and a top surface extending from the exterior wall to the interior wall bounding an orifice that is fluidly connected to the hollow interior cavity. The first tip plate may be attached to the turbine blade along the top surface and extending from proximate the exterior wall of the turbine blade across the orifice to cover the orifice.

Composite turbine blade and method of manufacture

Composite turbine blade and method of manufacture thereof

A process for filling openings, including blind holes, through-holes, and cavities, in high temperature components. The process entails forming a powder mixture by mixing particles of at least a base alloy and a second alloy that contains a sufficient amount of a melting point depressant to have a lower melting temperature than the base alloy. The powder mixture is combined with a binder and compacted to form a compacted preform, which is then heated to remove the binder and form a rigid sintered preform. The sintered preform is produced, or optionally is further shaped, to have a cross-sectional shape and dimensions to achieve a clearance of up to 200 micrometers with the opening, after which the preform is placed in the opening and diffusion bonded within the opening to form a brazement comprising the particles of the base alloy dispersed in a matrix formed by the second alloy.

Process of filling openings in a component

Improved compositions are described for the protection of gas turbine parts at elevated temperatures. The compositions are of the MCrAlY type, wherein M is selected from nickel, or a combination of nickel with cobalt, iron, or combinations thereof. The compositions further comprise ruthenium, rhenium, or a combination thereof, a Group 4 metal (e.g., hafnium, zirconium, titanium), and can further include silicon and/or germanium, where the composition results in improved aluminum diffusion properties. Also disclosed herein are articles comprising the composition.

Metal alloy compositions and articles comprising the same

A nickel-based high-temperature braze alloy composition includes Cr, Hf, and B. Furthermore, a cobalt-based high-temperature braze alloy composition includes Cr, Hf, and B. The braze alloys can be used, for example, as a single homogenous braze. The braze alloys can also be used, for example, as a component in a wide gap braze mixture where higher or lower melting point superalloy and/or brazing powder is used. The braze alloys may permit joining/repairing of superalloy articles with complex shape and may be used in high temperature applications.

Braze alloy compositions

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Jupiter, FL, United States of America

Warren Martin Miglietti