United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Hamilton Sundstrand Corporation

Dmitri Novikov

Sergei F Burlatsky

David Ulrich Furrer

William J Brindley

Henry H Thayer

Daniel A Bales

Eric W Malmborg

Robert C Dolan

Steven T Gordon

Christopher W Strock

David A Litton

John D Riehl

Shahram Amini

Michael A Weisse

Charles R Watson

Mladen F Trubelja

Vadim V Atrazhev

Joseph A DePalma

Bartolomeo Palmieri

Francis B Parisi

Robert J Meehan

Hillary Anne Huttenhower

Vadim I Sultanov

Dmitry Dmitriev

Sergey Mironets

Mark R Jaworowski

Lei Chen

Sameh Dardona

Russell Albert Beers

Diana Giulietti

Christopher J Hertel

William R Graves

Xiaomei Fang

Xuedong Zhou

Alexander Madinger

Kenneth A Frisk

Randy P Salva

Russell A Beers

Tri Nguyen

Donald H Spencer

Christopher Treese

Amra Peles

David Ullrich Furrer

Eric W Malmberg

A method for forming a hollow component includes injecting a fluid into an internal cavity of the hollow component to achieve a pressure of the fluid within the internal cavity that is greater than an ambient pressure. The method further includes drilling at least one hole through the hollow component from an external surface of the hollow component to the internal cavity by applying a laser beam to the hollow component with a laser generator. The method further includes directing the fluid from the internal cavity and through the at least one hole so as to exit the hollow component via the at least one hole.

Method and system for preventing back strikes when laser drilling hollow parts

An apparatus for use in a coating process includes a chamber, a crucible configured to hold a coating material in the chamber, an energy source operable to heat the interior of the chamber, a coating envelope situated with respect to the crucible, and at least one gas manifold located near the coating envelope. The at least one gas manifold is configured to provide a gas screen between the coating envelope and the crucible.

Apparatus for use in coating process

An airfoil for a gas turbine engine includes a first portion joined to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section. The airfoil section includes an airfoil body that extends between leading and trailing edges in a chordwise direction, between pressure and suction sides separated in a thickness direction, and from the root section to a tip portion in a spanwise direction. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib that bounds a respective pocket within a perimeter of the recessed region. The recessed region and the at least one rib are dimensioned to extend across the interface. A cover skin is coupled to the airfoil body along the at least one rib to enclose the recessed region.

Hybridized airfoil for a gas turbine engine

A method for stripping ceramic from a component includes applying a liquid to a ceramic coating of an outer surface of the component. The method also includes directing a plurality of laser pulses at the ceramic coating with the applied liquid in order to spall the ceramic coating from the component.

Liquid enhanced laser stripping

A method for treating a surface of a contoured titanium substrate used for adhesively bonded engine components. The method including applying energy from a fiber laser system to a contoured surface of a titanium substrate, the laser energy is distributed to the contoured titanium surface by at least one of direct light of sight, reflection, or scattering of one or more laser beam.

Method for adhesive bonding of titanium components using a fiber laser system

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, a first portion welded to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section mountable to a rotatable hub. The airfoil section includes an airfoil body extending between leading and trailing edges in a chordwise direction, extending between pressure and suction sides separated in a thickness direction, and extending from the root section in a spanwise direction to a tip portion. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib bounding a respective pocket within a perimeter of the recessed region. A cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. A method of forming a gas turbine engine component is also disclosed.

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil body defining a recessed region and including at least one rib dimensioned to loop about a respective pocket within a perimeter of the recessed region. At least one cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. The at least one cover skin is welded to the at least one rib along a respective weld path. The weld path defines a weld width, the at least one rib defines a rib width, and a ratio of the weld width to the rib width is equal to or greater than 3:1 for each position along the weld path. A method of forming a gas turbine engine component is also disclosed.

Airfoil with cover for gas turbine engine

A splatter shield system for an additive manufacturing machine includes one or more splatter shields configured to cover at least a portion of a build area during energy application such that the at least one splatter shield is positioned between an energy source of an additive manufacturing machine and the build area during energy application. The one or more splatter shields are transparent to an energy source (e.g., a laser) of the additive manufacturing system such that energy application occurs through the splatter shield.

Splatter shield systems and methods for additive manufacturing

An article includes a MAX phase solid and a high temperature melting point metallic material interdispersed with the MAX phase material.

Vibration damping material for high temperature use

A stiffness controlled abradable seal system for a gas turbine engine includes a cantilevered arm that supports one of a rotating seal surface and a static seal surface, a stiffness of the cantilevered arm controlled to achieve a desired operational temperature at a seal interface, and an optimally matched abradeable seal material with required thermo-physical and friction properties to enable desired wear mechanisms and maximized sealing and durability.

Stiffness controlled abradeable seal system and methods of making same

A method of removing scale from a casting may include positioning the casting relative to a laser emitter. The casting may comprise a superalloy and the scale may have formed on the surfaces thereof, with the scale being a byproduct of a method of manufacturing the casting. The method may also include passing a laser beam emitted from the laser emitter across the casting such that the laser beam causes the scale to at least one of crack, break, shatter, and spall. The superalloy may be a nickel-based superalloy and the scale may include a metal carbide layer.

Laser removal of casting scale

A polymeric material process includes increasing a mobility within a polymer to enables specific alignment of polymer chains.

High performance polymide and process therefor

A vibration resistant fan guide vane for a gas turbine engine is provided. The fan guide vane comprises a vibration damping component made of a MAXMET composite. The damping component may be a cover that covers some or all of the fan guide vane body. Alternatively, portions of the fan guide vane body or the entire vane body may be made from MAXMET composites. The disclosure makes use of the ultrahigh, fully reversible, non-linear elastic hysteresis behavior that MAXMET composites exhibit during cyclic elastic deformation in order to damp vibration.

Turbine engine component with vibration damping

An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.

Power beam welded cavity-back titanium hollow fan blade

Growing community of inventors

Avon, CT, United States of America

Dmitri Novikov