United Technologies Corporation

Raytheon Technologies Corporation

Rolls-royce Corporation

Iowa State University Research Foundation Inc

Rtx Corporation

University of Connecticut

William J Brindley

Gary D Roberge

Sergei F Burlatsky

Zhong Ouyang

Lei Chen

William Bogue

David Ulrich Furrer

Monika D Kinstler

Raymond Ruiwen Xu

Nicholas M LoRicco

Zhongfen Ding

John D Riehl

Dmitri Novikov

Xuan Liu

Andrew DeBiccari

Christopher J Bischof

Eric H Jordan

Zhiwei Yang

Wangen Lin

Kathryn Macauley

Timothy Fuesting

Kevin D Smith

Joseph D Drescher

David A Raulerson

Daniel J Sordelet

Xiaomei Fang

Albert Rabinovich

Brian M Gleeson

David Norwood Potter

Dorel M Moisei

Waled T Hassan

Lisa J Brasche

Steven Ivory

Michael W Renfro

Bingtao Li

Bruce R Saxton

William M Rose

David N Potter

David Ullrich Furrer

Willliam M Rose

Andrew Debiccari

Monika D Kintsler

A method for forming a reinforced metallic structure includes providing a tool having a formation surface corresponding to a desired structure shape of the reinforced metallic structure. The method also includes positioning a plurality of fibers on the formation surface of the tool. The method also includes depositing a layer of material on the plurality of fibers using a cold-spray technique. The method also includes removing the layer of material with the plurality of fibers from the tool to create the reinforced metallic structure.

Reinforcement of a deposited structure forming a metal matrix composite

A method for forming a metallic structure having a secondary component includes positioning the secondary component on a main formation surface of a main tool, the main formation surface corresponding to a desired shape of a first layer of material. The method also includes depositing a layer of material on the secondary component and the main formation surface using a cold-spray technique such that the layer of material bonds to the secondary component. The method also includes removing the layer of material and the secondary component to form the metallic structure.

Deposited material structure with integrated component

A method for forming a metallic structure having multiple layers includes providing a main tool having a main formation surface corresponding to a desired shape of a first layer of material. The method also includes depositing the first layer of material on the main formation surface using a cold-spray deposition technique. The method also includes positioning a secondary tool having a secondary formation surface in a portion of a first volume defined by a first surface of the first layer of material. The method also includes depositing a second layer of material on the secondary formation surface using the cold-spray deposition technique. The method also includes removing the secondary tool such that the first volume is positioned between the first layer of material and the second layer of material.

Multi-wall deposited thin sheet structure

A blade repair apparatus is provided and includes a deposition head which is movable relative to base materials and configured to execute a repair operation that includes a deposition of additional materials onto the base materials during deposition head movements, a temperature control system including a temperature regulating assembly coupled with the deposition head in a trailing position and a controller. The controller is operably coupled to the deposition head and the temperature control system. The controller is configured to control the deposition head movements and depositional operations of the deposition head. The controller is configured to control the temperature control system such that the temperature regulating assembly controls temperatures of at least the base materials and the additional materials during at least the deposition head movements and the depositional operations.

Gas impingement in-process cooling system

A method is provided that involves rotational equipment that includes a case and a first rotor blade within the case. During the method, a probe is arranged within the case adjacent the first rotor blade. A magnetic characteristic of the first rotor blade is measured using the probe. Presence of internal corrosion within the first rotor blade is determined based on the measured magnetic characteristic.

Determining presence of internal corrosion within a rotor blade by measuring magnetic characteristic(s)

Disclosed is a method of detecting mixed mode corrosion of a turbine airfoil. The method includes heat treating the turbine airfoil at a temperature of 1600 to 2100&#xb0; F. in a Ni/Co oxide reducing atmosphere; and scanning the heat treated turbine airfoil with a magnetometer to determine the presence of mixed mode corrosion, wherein the turbine airfoil comprises a nickel superalloy and has internal passages.

Method of nondestructive turbine airfoil inspection and repair

A material removal method comprises receiving a component that includes a component body and a coating on the component body, the component body comprising metallic first material, and the coating comprising a second material that is different from the first material, wherein the component is a component of an item of rotational equipment. The method also includes receiving a solution comprising nitric acid and hydrogen peroxide and subjecting at least a portion of the coating to the solution in supercritical condition in order to remove at least some of the second material from the component, wherein a chemistry of the solution is selected such that the solution is substantially non-reactive with the first material.

Turbine blade internal hot corrosion oxide cleaning

A magnetoscop inspection system includes a magnetoscop, a computed tomography unit, and a corrosion model unit. The magnetoscop measures a permeability at a plurality of inspection points of a turbine component. The computed tomography unit generates a measured profile of a hollowed portion of the turbine component based at least in part on the permeability at the measured inspection points. The corrosion model unit stores in memory at least one reference computed tomography profile of a known turbine component. The magnetoscop inspection system determines a structural integrity of the turbine component based on a comparison between the measured profile and the reference profile corresponding to the turbine component currently under inspection.

Multi-zone automatic magnetoscop inspection system

Disclosed is an apparatus and method for inspecting a component of a gas turbine engine, which includes a sleeve configured to surround a component of a gas turbine engine, the sleeve including: a pair of opposing wall members being secured to each other at at least one of a pair of opposite ends; an internal cavity located between the pair of opposing wall members, wherein the internal cavity extends from one end of the sleeve to an opposite end of the sleeve; and a plurality of orifices extending through the pair of opposing wall members, and wherein a probe is inserted in each orifice in one of the pair of opposing wall members to determine the state of the internal cavities of a gas turbine component and determine the structural integrity of the component.

Apparatus and method and system for inspecting a component of a gas turbine engine

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

A method for forming a sheet structure includes providing a tool having a formation surface corresponding to a shape of the sheet structure. The method also includes depositing at least one layer of material on the formation surface using a cold-spray deposition technique. The method also includes removing the at least one layer of material from the formation surface to create the sheet structure.

Material deposition to form a sheet structure

Growing community of inventors

Hebron, CT, United States of America

William J Brindley