United Technologies Corporation

Raytheon Technologies Corporation

Jesse C Meyer

James Olaf Hansen

Lee Drozdenko

Scot Adams Webb

Brandon A Gates

John D Riehl

Christopher J Hertel

Michael A Morden

Maria C Kirejczyk

Raymond P Martina

Joseph Jalowka

Richard B Bergethon

John Joseph Marcin

Michael A Weisse

Joseph Parkos, Jr

Charles R Watson

John Henry Vontell, Sr

John H Vontell, Sr

Scot A Webb

Lee M Drozdenko

Robert M Shemenski

Gregory C Hildebrand

Christopher A Hertel

Jr Joseph Parkos

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 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

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.

A method of adhering a first structure to a second structure using a primer, containing a primer fugitive inhibitor, and a film adhesive by removing the primer fugitive inhibitor under vacuum at room temperature conditions.

Method for adhering structures using silicone adhesive system

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 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

Growing community of inventors

Colchester, CT, United States of America

Jesse C Meyer