United Technologies Corporation

Raytheon Technologies Corporation

James Olaf Hansen

Christopher J Hertel

Jesse C Meyer

Lee Drozdenko

Christopher W Strock

Mark R Jaworowski

Michael A Weisse

Joseph Parkos, Jr

Thomas J Watson

William R Graves

Scot Adams Webb

Brandon A Gates

David Ulrich Furrer

John D Riehl

John J Schirra

Scott C Billings

John Joseph Marcin

Daniel A Bales

Changsheng Guo

Melvin Freling

Thomas J Robertson, Jr

Russell Albert Beers

Michael A Morden

James L Deal

Maria C Kirejczyk

Raymond P Martina

Joseph Jalowka

Jay Thomas Abraham

Richard B Bergethon

Gary M Lomasney

Venkatarama K Seetharaman

David R Lyders

Thomas J Garosshen

Michael Parkin

Iuliana Cernatescu

Andrew J Murphy

Thomas M Morin

David W Anderson

Randy P Salva

Henry M Hodgens

Kenneth C Long

John Palitsch

Ethan C Drew

Daniel Gynther

Mark Quinn

Kelly L Hoover

Scot A Webb

Stephen E Graushinsky

John H Nortrup

Robert M Shemenski

Ashley P Phillips

Steven T Holland

Gregory C Hildebrand

Michael A Jackson

David Novotnak

Lee M Drozdenko

Nicolas Figueiredo

Christopher A Hertel

John Richard Palitsch

Jr Joseph Parkos

Jay T Abraham

Kevin W Schichting

Curtis H Riewe

David William Anderson

The present disclosure provides methods and systems for the bonding of dissimilar substrates. For example, a first substrate may be coupled to a second substrate by a composite joint between the first substrate and the second substrate. The composite joint may be comprised of a first adhesive material and a second adhesive material. The first adhesive material may be disposed on the first substrate, and the second adhesive material may be disposed to the first adhesive material. The composite joint between the first substrate and the second substrate may provide an isolation layer therebetween, preventing galvanic corrosion.

Systems and methods for bonding of dissimilar substrates

A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.

Fan blade with adhesive fabric stackup

An airfoil for a gas turbine engine is disclosed. The airfoil may include a first side, and a second side opposite the first side. The first side and the second side may extend axially from a leading edge to a trailing edge and radially from a base to a tip. The tip may include an oblique surface between the first side and the second side.

Fan blade tip as a cutting tool

A rotating component includes an airfoil section with a free end, the airfoil section being formed of a composite core with a metallic skin and an abrasive coating applied to the free end.

Abrasive tip for composite fan blades

A method of forming an airfoil includes placing a material onto a die that is heated to a predetermined temperature to pre-heat the material to a first temperature, while the die is in an open position. The method further includes closing the die at a predetermined rate and holding the die in a closed position for a predetermined period of time at a first force. The method still further includes removing the part from the die, cooling the die, placing the part onto the die, and closing the die at a second force.

Method of forming aluminum alloy airfoils

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 abrasive tip comprises an additive layer having an additive; the additive is configured to prevent adhesion of an organic component from an abradable seal onto an abrasive blade tip.

Abrasive blade tips with additive layer resistant to clogging

An abrasive tip comprises an additive, the additive is configured to prevent adhesion of an organic component from an abradable seal onto an abrasive blade tip.

Abrasive blade tips with additive resistant to clogging by organic matrix abradable

An airfoil member () comprising has a substrate () along at least a portion of an airfoil () of the airfoil member. A sheath () has a channel () receiving a portion () of the substrate. A scrim () is between the substrate and the sheath. A spacer () is between the sheath and the substrate and has a plurality of spaced-apart portions () with gaps between the spaced-apart portions.

Fan blades and manufacture methods

A method is provided for manufacturing a blade. The blade comprises an airfoil () having: a root end and a tip (); a metallic substrate () along at least a portion of the airfoil; and an anodized layer (). The method comprises roughening the tip to form protrusions () and anodizing to form the anodized layer so that the protrusions form an abrasive ().

Abrasive tip blade manufacture methods

An airfoil member () comprising has a substrate () along at least a portion of an airfoil () of the airfoil member. A sheath () has a channel () receiving a portion () of the substrate. A plurality of separate spacers () are between the sheath and the substrate and have a plurality of gaps between the spacers.

An airfoil includes an airfoil body that extends at least between leading and trailing edges, first and second sides, and radially inner and outer ends. The airfoil body includes an aluminum alloy that has a controlled crystallographic texture with respect to a predefined three-dimensional coordinate system. The airfoil can be used in the fan of a gas turbine engine.

Aluminum alloy airfoil with designed crystallographic texture

A turbine engine rotor component has a Ti-based first member () circumscribing an axis () and has either a circumferential array of integrally formed airfoils () or a circumferential array of blade retention features. A TiB particulate reinforced second member () also circumscribes the axis.

Turbine engine hybrid rotor

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

A fan blade of a gas turbine engine includes an airfoil, a root received in a slot of a hub, and a wear pad covering at least a portion of the root and made of an integrally bonded woven composite laminate.

Wear pad to prevent cracking of fan blade

Growing community of inventors

Glastonbury, CT, United States of America

James Olaf Hansen