United Technologies Corporation

Raytheon Technologies Corporation

Wangen Lin

Herbert A Chin

James J Moor

Andrew L Haynes

Giovanni Whitman

Robert P Schaefer

Gary J Larson

Eberhardt Privitzer

Vincent Nevins

Greg Czeladko

Thomas DeMichael

Brian J Schwartz

Billie W Bunting

Joseph M Wilson

Scott Poeppel

Kenneth T Raczewski

Svitlana Vasylivna Maksymova

F Michael Hosking

Viktor Fedorovich Khorunov

Wendell V Twelves

John Joseph Marcin

Jesse R Boyer

Mario P Bochiechio

Joseph Parkos, Jr

William J Brindley

John T Ols

Thomas J Watson

Henry H Thayer

Donn Blankenship

Edward R Szela

David G Alexander

James Romanelli

Robert P Delisle

Christopher A Sanchez

Michael J Labbe

Scott Boynton

Steven Ivory

Gene A Danko

Pawel Kaniowski

Piotr Kaczor

Robert Wozniak

Alex Neese Brown

Sonia A Martinez

Bruce R Saxton

Melissa R Hill

Samuel T Davidson

Adam Quagliaroli

John E Matz

Robert W Jackson

David N Potter

Scott Lewis Boynton

Joseph Wilson

Aswin Raghavan

Richard A Stone

John Matz

Jr Nevins Nevins

A process of welding fittings to ends of a double wall pipe comprising forming a first welded joint between an inner pipe and an inner receiver of a first fitting; forming a second welded joint between an outer pipe and an outer receiver of the first fitting; forming a third welded joint between the outer pipe and an outer receiver of a second fitting; and forming a fourth welded joint between the inner pipe and an inner receiver of the second fitting.

Radially outward orbital welding technique as a joining method used for inner tube to fitting connections in double wall tube configurations

A method of reworking or repairing a component includes removing a casting defect from a component manufactured of a non-fusion weldable base alloy to form a cavity that results in a through hole; sealing the through hole with a backing; and at least partially filling the cavity with a multiple of layers of a multiple of laser powder deposition spots, each of the multiple of laser powder deposition spots formed of a filler alloy, a first layer of the multiple of layers includes a perimeter of the multiple of laser powder deposition spots that overlap a wall of the cavity and the backing.

Laser powder deposition weld rework for gas turbine engine non-fusion weldable nickel castings

A method of reworking an aerospace component includes removing a casting defect from a component manufactured of a non-fusion weldable base alloy to form a cavity. The cavity is then at least partially filled with a multiple of layers of discrete laser powder deposition spots of a filler alloy. A cast component for a gas turbine engine includes a cast component non-fusion weldable base alloy with a cavity filled with a multiple of layers of laser powder deposition spots of a filler alloy. The filler alloy may be different than the non-fusion weldable base alloy. A layer of non-fusion weldable base alloy is at least partially within the cavity and over the filler alloy.

A laser cladding head comprises a protective housing, a focal array, a turning mirror, and a powder nozzle. The housing extends along a primary axis from a proximal end to a distal end. The focal array is situated at the proximal end and oriented to receive and focus collimated light in a beam directed substantially along the primary axis. The turning mirror is situated at the distal end and disposed to redirect the beam in an emission direction, towards a target point separated from the turning mirror by a working distance of at most a tenth the focal length. The turning mirror is a nonfocal reflective surface indexable to alter an impingement location of the beam on the turning mirror. The powder nozzle is situated at the distal end and receives and directs weld material towards the target point for melting.

Laser cladding system and method

The present disclosure relates generally to a system and method for applying a metallic coating. A first metallic coating may be applied to a portion of a total surface of a part and a second metallic coating may be applied to substantially the total surface. The metallic coating may be applied to a vane cluster for use in a turbomachine.

System and method for applying a metallic coating

A method is provided for reworking a component. The method includes at least partially filling a cavity in a non-fusion weldable base alloy with a multiple of layers of a multiple of laser powder deposition spots formed of a filler alloy. Each of the multiple of laser powder deposition spots at least partially overlaps at least one of another of the multiple of laser powder deposition spots. The filler alloy may be different than the non-fusion weldable base alloy.

A process for solid state deposition of a material onto a workpiece includes the steps of providing a rod of metallic deposition material, exerting pressure at one end of the rod to move the metallic deposition material into a deposition zone, rotating the rod while the pressure is being exerted to generate frictional heat when the rod contacts a surface of the workpiece, and raising the temperature of the metallic deposition material to reduce the amount of frictional heat which needs to be generated during the rotating step and to produce a microstructure which is substantially free of porosity and which has a fine grain size.

Solid state additive manufacturing system

An example method of attaching an airfoil for an integrally bladed rotor includes placing a support collar in an installed position around at least a leading edge and trailing edge of an airfoil stub to be repaired in an integrally bladed rotor. The support collar and the airfoil stub together have a midline that is positioned between opposing, laterally outer surfaces of the airfoil stub when the support collar is in the installed position. The method performs linear friction welding to add a replacement airfoil to the airfoil stub.

Support collar geometry for linear friction welding

A method of repairing a rotor blade, for example on an integrally bladed rotor, includes preparing a surface on a damaged area of the blade. The blade has first and second airfoil surfaces adjoining the prepared surface that are spaced apart a distance. An edge of a patch abuts the prepared surface to provide a weld interface defining a welding plane. First and second cover sheets respectively overlap the first and second airfoil surfaces. The first and second cover sheets adjoin the edge and the first and second airfoil surfaces. The blade, patch and first and second cover sheets are welded along the welding plane providing a welded joint at the weld interface. The first and second cover sheets are substantially unsecured to the first and second airfoil surfaces subsequent to the welding operation.

Welding repair method of an integrally bladed rotor

A method is provided for repairing a damaged rotor blade on an integrally bladed rotor by removing a damaged portion of a damaged blade leaving a blade stub extending outwardly from the disk and performing a linear friction welding operation to attach a replacement blade segment to the blade stub. The rotor may be disposed operation using a linear friction welding apparatus. The method includes disposing a support collar about the blade stub and securing the support collar to the linear friction welding apparatus prior to a commencement of the bonding operation. A lower surface of the support collar is contoured to mate with a portion of an outer circumference surface of the rotor disk.

Repair of integrally bladed rotors

A device and method for locally heat treating at least one airfoil in an integrally bladed rotor device. A pair of IR heat sources are positioned to direct IR heat rays in the direction where local heat treatment is required. A pair of parabolic mirrors are positioned to direct the IR heat rays on to the metal component. The heat treating is useful after welding the airfoil on to the rotor device.

Local heat treatment of IBR blade using infrared heating

A method of repairing an integrally bladed rotor includes the steps of placing a support collar around at least a leading and trailing edge portions of the blade stub, and performing linear friction welding to add a replacement airfoil to the blade stub. The linear friction welding is generally along a direction between the leading and trailing edges. In addition, the support collar leading and trailing edge portions are connected together.

Consumable collar for linear friction welding of blade replacement for damaged integrally bladed rotors

A process for heat treating selected portions of an integrally bladed rotor (IBR) having a plurality of blades, the process using an IBR on a fixture having a rotor engaging portion that moves the IBR into an environmental chamber. An IR heater is placed on one of the IBR blades and heat treated after air has been removed from the chamber and an inert gas is added. The IR heater is lifted from the blade and indexed to position another blade on the IBR. The process is repeated until all the IBR blades are heat treated.

Method and apparatus of heat treating an integrally bladed rotor

Growing community of inventors

South Glastonbury, CT, United States of America

Wangen Lin