United Technologies Corporation

Raytheon Technologies Corporation

United States of America As Represented by the Administrator of Nasa

Rtx Corporation

Utc Fuel Cells, LLC

Christopher J Hertel

James Olaf Hansen

Joseph Parkos, Jr

Charles R Watson

William Bogue

Brian Kenneth Holland

Michael A Weisse

John D Riehl

Xiaomei Fang

Jesse C Meyer

Louis Blackburn

John J Klein

Carl Anthony Reiser

JinQuan Xu

John W Connell

Grant O Cook, Iii

Wendell V Twelves

Daniel A Bales

Glenn Levasseur

James T Roach

Kathryn S Read

Barry Barnett

Colin J Kling

Foster Philip Lamm

Dmitri Novikov

Gary M Lomasney

Thomas J Watson

William R Graves

Lee Drozdenko

Henry H Thayer

Steven Clarkson

David R Lyders

Michael Parkin

Matthew A Turner

Shari L Bugaj

Michael G Abbott

Frank L Palmieri

John W Hopkins

Andrew J Murphy

Jeffrey S LeShane

Sol S Blecherman

Anthony Rivera

Thomas L Cumella

Kelly L Hoover

John A S Bett

Jay Thomas Abraham

Gregory C Hildebrand

Michael Caulfield

Ashley P Phillips

Donald H Spencer

Ted H Lancaster

Steven T Holland

William F Bogue

Methods and systems for the laser surface treatment on stainless steel alloys and nickel alloys may include a computer may be programmed to set a laser path corresponding to a predetermined geometric pattern. A laser may be coupled to the computer and apply a pulsed laser beam to a contact surface of the substrate along the predefined geometric pattern. The pulsed laser beam may have a laser power between 0.1 W and 100 W, single pulse fluence 1 mJ/mmand 1025 mJ/mmand a laser speed between 25.4 cm/s and 127 cm/s. The laser may generate an open pore oxide layer on the contact surface of the substrate with a thickness of 0.1-1 μm, an open pore distance of 0.05-1 μm. The open pore oxide layer may have a topography corresponding to the predefined geometric pattern. The topography may contain open pore structures and promote adhesive bond performance.

Laser surface treatment on stainless steel and nickel alloys for adhesive bonding

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

Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Plated polymer fan

A fan of a gas turbine engine includes a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end, wherein the airfoil comprises pockets filled with an elastomeric composite.

Fan blade with filled pocket

An electroformed sheath for protecting an airfoil includes a sheath body and a mandrel insert is provided. The sheath body includes a leading edge. The sheath body includes a pressure side wall and an opposed suction side wall, which side walls meet at the leading edge and extend away from the leading edge to define a cavity between the side walls. The sheath body includes a head section between the leading edge and the cavity. The mandrel insert is positioned between the pressure side and suction side walls, and includes a generally wedge-shaped geometry. A method for protecting an airfoil includes: 1) securing a mandrel insert to a mandrel; 2) electroplating a sheath body onto the mandrel and the mandrel insert; 3) removing the mandrel from the sheath body so that a sheath cavity is defined within the sheath body; and 4) securing the airfoil within the sheath cavity.

Electroformed sheath

An airfoil for a gas turbine engine includes a substrate and a sheath providing an edge. A cured adhesive secures the sheath to the substrate. The cured adhesive has a fillet that extends beyond the edge that includes a mechanically worked finished surface. A method of manufacturing the airfoil includes the steps of securing a sheath to a substrate with adhesive, curing the adhesive, and mechanically removing a portion of the adhesive extending beyond the sheath.

Fan blade and method of manufacturing same

A fan blade and method of covering a fan blade root portion for a gas turbine engine are disclosed. The fan blade includes an airfoil having a leading edge end and a trailing edge end, a root portion having a first side surface extending from the leading edge end to the trailing edge end and a second side surface at an opposite side of the first side surface and extending from the leading edge end to the trailing edge end, and a covering disposed against the first side surface and the second side surface, wherein the covering is positioned against the root portion as a single member.

Fan blade and method of covering a fan blade root portion

A process for manufacturing a ceramic matrix composite component, said process comprising inserting at least one fibrous sheet into a resin transfer molding system. The process includes wetting the at least one fibrous sheet with a pre-ceramic polymer resin. The process includes applying a pressure to the at least one fibrous sheet and pre-ceramic polymer resin with an intensifier responsive to thermal expansion and curing the pre-ceramic polymer resin.

Method for improving laminate quality during resin transfer molding

A rotary blade is provided that includes a root, an airfoil, and a tip insert. The airfoil is attached to the root, and has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip. The slot extends in a chordwise direction between the leading edge and trailing edge. The tip insert has a base end and a rub end. The base end of the tip insert is disposed within the slot. The rub end of the tip insert extends radially outward from the airfoil tip.

Gas turbine rotary blade with tip insert

A component to be repaired includes a relatively rigid plate. On a surface that may have been subject to fracture, a resin material is first laid down, then a relatively flexible material is positioned outwardly of the resin material to repair the barrier. A part may also be formed initially with the flexible material. In another feature of this application, a method of forming a barrier includes providing a composite material, and applying a relatively flexible material on a surface of the composite material, and concurrently molding the relatively flexible material with the composite material using a composite mold.

Fluid barriers with flexible backing material and methods of repairing and manufacturing the same

An apparatus and method for repairing defects in composite materials using a tapered disk sized to fit the part being repaired. Also included is a bolt sized to fit through a central hole in the disk. A spring is positioned on the bolt with a washer. A nut is attached to the end of the bolt and tightened to place pressure on the washer to compress the biasing device. An adhesive is applied to the tapered disk prior to engaging the composite material. A threaded bushing is used to fixedly attach a second bolt completely in the hole.

Method for adhesive bonding plug details for composite structures

A method of finishing a fan blade includes bonding a sheath and a cover to an aluminum fan blade with an airfoil, a root, a leading edge and a tip; imparting residual stresses onto the blade; coating the blade to protect exposed areas of the blade; and curing the blade in low-temperature cure cycles to preserve residual stresses imparted.

Fan blade finishing

A method for protecting a fan blade with an airfoil, a tip, a root and a sheath, the root to be inserted into a hub includes peening the airfoil of the blade; inserting a scrim cloth between the fan blade and the sheath to galvanically isolate the fan blade from the sheath; bonding the sheath to the blade with an epoxy adhesive; peening the blade root; bonding wear pads to the root with epoxy adhesive to galvanically isolate the root from the hub; applying a protective cover to the tip of the blade; and applying a coating to all exposed areas of the blade to inhibit corrosion.

Fan blade protection system

A method for bonding a sheath made of a first metallic material to an airfoil made of a second metallic material includes treating the bonding surface of the airfoil; treating the bonding surface of the sheath; placing an adhesive between the bonding surfaces of the airfoil and the sheath; and pressing the airfoil and sheath together so that the adhesive bonds the sheath to the airfoil.

Method for securing a sheath to a blade

A doubler assembly repairs at least one damaged aperture of a composite flange. The doubler assembly includes an insert, an adhesive, and a support. The insert is positioned in the damaged aperture to provide compressive load transfer through the composite flange. The adhesive is positioned directly on at least a portion of the composite flange proximate the damaged aperture. The support is positioned over the adhesive.

Metallic double repair of composite arcuate flanges

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Wethersfield, CT, United States of America

Christopher J Hertel