United Technologies Corporation

Raytheon Technologies Corporation

Monika D Kinstler

David A Rutz

Lei Chen

William J Brindley

Igor V Belousov

Igor S Malashenko

Gregory A Serhiyenko

Evgeniy A Shelkovoy, Legal Representative

Zhiwei Yang

William M Rose

Chris Vargas

James J Moor

Andrew DeBiccari

David R Malley

Billie W Bunting

Derek W Anderson

John F Mullooly

David A Gaudreau

Steven Ivory

Nicole Sullivan

Bruce R Saxton

Anatoli N Shelkovoy

A nickel-chromium (Ni&#x2014;Cr) alloy and a method for electrodepositing the Ni&#x2014;Cr alloy on a turbine engine component for dimensionally restoring the engine component are described. The engine component is restored by re-building wall thickness with the Ni&#x2014;Cr alloy including from 2 to 50 wt % chromium balanced with nickel. The turbine component coated with the Ni&#x2014;Cr alloy is heat-treated at a high temperature to homogenize composition of the alloy to mimic the base alloy and to restore materials lost during repair of the turbine component.

Electrodeposited nickel-chromium alloy

An electrodeposited nickel-chromium-aluminum (Ni&#x2014;Cr&#x2014;Al) composite including nickel-chromium alloy and aluminum, and alloys or compounds formed by Al, Cr and Ni applied on turbine components comprises from 2 to 50 wt % chromium, from 0.1 to 6 wt % aluminum, and a remaining balance of nickel, wherein the Ni&#x2014;Cr&#x2014;Al composite is heat-treated to form an aluminum compound and to restore materials lost during repair processes of the turbine components.

Nickel-chromium-aluminum composite by electrodeposition

Aspects of the disclosure are directed to repairing or restoring a liner associated with a combustor of an aircraft engine. The liner is at least partially stripped of at least one detail. An automated welding operation is applied to the liner. A coating of the liner on a cold side of the liner is retained on the liner during the welding operation.

Automated weld repair of combustor liners

A method of hole defect repair includes removing one or more defects at or near a desired hole in a part by removing a portion of the part proximate the desired hole in a series of chain link patterns, and welding a filler material to the part after removing the chain link pattern portion of the part.

Bolt hole repair technique

A method for working or repairing a combustor wall panel that may be damaged is disclosed. The method comprises providing a supplemental body to a combustor float wall panel, and attaching at least one cooling pin to the supplemental body.

Method for working of combustor float wall panels

Methods for repairing gas turbine components damaged by corrosion that not only restores the components back to their original dimensions to ensure proper engine operations, but also have the added benefit of mitigating future corrosion attacks thereby extending the useful life of the components.

Corrosion protective coating through cold spray

A method for depositing a first material on a substrate includes providing the substrate in a deposition chamber. A molten body is formed between the substrate and a source of the first material by melting one or more second materials. A flow of the first material is passed through the molten body and from the molten body to the substrate as a vapor flow. An essentially non-expending portion of the molten body comprises an alloy having a melting temperature below a melting temperature of the first material.

Vapor deposition of dissimilar materials

A gas turbine engine blade has a platform. A root depends from the platform and an airfoil extends from the platform. The airfoil has leading and trailing edges and pressure and suction sides. The blade has a substrate having a surface. A compressive stress exists below a first region of the surface. The first region extends over a majority of a streamwise perimeter of the airfoil at a location at a spanwise distance from the tip or more than 50% of a tip-to-platform span. A coating is on the surface including at the location.

Pre-coating burnishing of erosion coated parts

A method for repairing a turbine engine component is provided. The method broadly comprises the steps of providing a turbine engine component having an airfoil portion, applying a coating to the airfoil portion, and restoring a tip portion, a chord, and surfaces of the airfoil portion to original dimensions in a single operation. A system for repairing the turbine engine component is also described.

Compressor blade flow form technique for repair

A method for restoring blade dovetails to their original shape comprising the steps of removing damaged material from a blade dovetail at a damage site, physically depositing a metal at the damage site in an amount sufficient to replace the removed damaged material, and machining the blade dovetail to the original shape.

Fan and compressor blade dovetail restoration process

In accordance with the present invention, a process for repairing metal workpieces, such as turbine engine components, is provided. The process comprises the steps of forming a braze paste containing a first nickel base alloy material containing boron and chromium and a second nickel base alloy material containing chromium and cobalt, applying the brazing paste to an area of the metal workpiece containing at least one crack, and subjecting the workpiece and the brazing paste to a brazing cycle by heating the brazing paste and the workpiece, preferably to a temperature in the range of from 2000 to 2200 degrees Fahrenheit. During the brazing cycle, the brazing paste flows into and fills the at least one crack and thus repairs the metal workpiece.

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Glastonbury, CT, United States of America

Monika D Kinstler