United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Daniel A Bales

Thomas DeMichael

Eric W Malmborg

Robert C Dolan

Michael A Weisse

Dmitri Novikov

Thomas J Watson

Andrew L Haynes

Francis B Parisi

Steven T Gordon

Mark L Hartman

Sudhangshu Bose

Edward R Szela

Luke H Rettberg

Carl R Verner

Russell Albert Beers

William R Graves

David A Rutz

Steven M Burns

Mark T Ucasz

Bradford A Cowles

Tyrus E Royal

Merritt W Wight

Michael A Joy

Leroy F Turner, Sr

Michael DuPont

James Thompson Beals

Steven J Bullied

Brian T Hazel

Dilip M Shah

Alan David Cetel

William Bogue

Joseph Parkos, Jr

James Olaf Hansen

Christopher J Hertel

Gary M Lomasney

Dinesh K Gupta

Keith A Santeler

Chris Vargas

Stephen Douglas Murray

Daniel F Paulonis

John J Marcin

Joshua E Persky

Agnes Klucha

Xuedong Zhou

Gregory M Dolansky

Glenn A Cotnoir

Jacob A Snyder

John D Wiedemer

Kenneth A Frisk

Randy P Salva

Steven D Jenkel

Stuart C Kozan

Mimi Nguyen-Vu

Philip H Ratliff

Steven M Miller

Venkat Seetharaman

Christopher Treese

Tri Nguyen

Lawrence J Whims

James R Joyce

Russell J Melnick

Russell A Beers

Eric W Malmberg

Ted A Asare

Thomas J Bales

Stephen D Murray

Keith Santeler

A powder metallurgy method includes a canister that has canister walls that define a hermetic chamber that circumscribes an open central region. A metallic alloy powder is inserted into the hermetic chamber, followed by evacuating the hermetic chamber. The canister with the metallic alloy powder is then subjected to a hot isostatic pressing process that includes heating the canister and the metallic alloy powder and applying isostatic pressure to the canister. The heating and the isostatic pressure causes fusion and consolidation of the metallic alloy powder to form a solid workpiece. The canister is then removed from the solid workpiece.

Powder metallurgy method using a four-wall cylindrical canister

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil body extending between leading and trailing edges and extending from a root section, and the airfoil body defining pressure and suction sides. The airfoil body defines a recessed region extending inwardly from at least one of the pressure and suction sides, and the airfoil body includes one or more ribs that define a plurality of pockets within a perimeter of the recessed region. A plurality of cover skins is welded to the airfoil body along the one or more ribs to enclose respective ones of the plurality of pockets. The plurality of cover skins are formed from a common cover having a perimeter that is dimensioned to mate with the perimeter of the recess.

Multi-cover gas turbine engine component

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 furnace for removing a molybdenum-alloy refractory metal core through sublimation comprising a retort furnace having an interior; a sublimation fixture insertable within the interior of the retort furnace, the sublimation fixture configured to receive at least one turbine blade having the molybdenum-alloy refractory metal core; a flow passage thermally coupled to the retort furnace configured to heat a fluid flowing through the flow passage and deliver the fluid to the molybdenum-alloy refractory metal core causing sublimation of the molybdenum-alloy refractory metal core.

Method for removing refractory metal cores

During a bonding process, a tip cap and an airfoil base are provided. The tip cap is arranged on the airfoil base. The tip cap is diffusion bonded to the airfoil base.

Methods and assemblies for bonding airfoil components together

A fixture assembly includes a first fixture portion, a second fixture portion that interfaces with the first fixture portion, and a sub-fixture movably mounted to the first fixture portion. A multiple of actuators selectively move the sub-fixture toward the second fixture portion. A method of manufacturing a fan blade includes deploying the sub-fixture from the first fixture portion to effectuate a peripheral diffusion bond to join the blade body and the cover of the fan blade.

Processes and tooling associated with diffusion bonding the periphery of a cavity-back airfoil

A clamp for securing a component to an isogrid case of a gas turbine engine includes a top having an attachment feature for coupling the clamp to the component. The clamp further includes a bottom. The clamp further includes two sides extending from the top towards the bottom, each of the two sides being thicker at the bottom than at the top, and the two sides defining a shaped slot closer to the bottom than the top for receiving a rib of the isogrid case.

Mechanical attachment scheme for isogrid ducts

A tool for simultaneous local stress relief of each of a multiple of linear friction welds includes a columnar track defined along an axis, the columnar track having a helical slot; and a support structure engaged with the helical slot to translate and rotate a heat treat fixture portion along the axis.

Tool for simultaneous local stress relief of each of a multiple of linear friction welds of a rotor forging

A mounting plate for forming a gas turbine engine component according to an example of the present disclosure includes, among other things, a plate body defining an abutment dimensioned to mate with a forming die. The plate body defines at least one internal cooling circuit. The at least one internal cooling circuit includes a passageway having an intermediate portion interconnecting inlet and outlet portions. The intermediate portion is dimensioned to follow a perimeter of the abutment. The intermediate portion includes a plurality of fins extending partially from a first sidewall towards a second sidewall opposed to the first sidewall. A method of forming a gas turbine engine component is also disclosed.

Assembly and method of forming gas turbine engine components

A fixture assembly including a first fixture portion; a second fixture portion that interfaces with the first fixture portion; and a bladder assembly mounted to the second fixture portion to face the first fixture portion. A method of manufacturing a fan blade includes inserting a blade body and a cover into a fixture; and deploying a bladder assembly within the fixture to press the cover into the blade body.

Processes and tooling associated with diffusion bonding

A laser welding by-product removal device comprises a housing that includes distal and proximate ends separated along a central axis by a peripheral sidewall. A first plenum circumscribes the peripheral sidewall at the proximate housing end and includes a gas inlet and a first plenum base surface that includes a plurality of gas outlet holes. A second plenum circumscribes the peripheral sidewall between the first plenum and the distal housing end, where the second plenum includes a second plenum base surface, radially inner and outer sidewalls that extend axially distal from the second plenum base surface. The second plenum includes a top surface extending between the radially inner and outer sidewalls, and a by-product outlet in the top surface, where at least one of the second plenum base surface and the radially outer sidewall includes a plurality of by-product inlet holes.

By-product removal device for laser welding

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 extending between leading and trailing edges in a chordwise direction and extending from a root section in a spanwise direction, and the airfoil body defining pressure and suction sides separated in a thickness direction. The airfoil body defines a recessed region extending inwardly from at least one of the pressure and suction sides, and the airfoil body includes one or more ribs that define a plurality of pockets within a perimeter of the recessed region. A plurality of cover skins is welded to the airfoil body along the one or more ribs to enclose respective ones of the plurality of pockets. The plurality of cover skins formed from a common cover having a perimeter that is dimensioned to mate with the perimeter of the recess. A method of forming a gas turbine engine component is also disclosed.

An airfoil includes a first airfoil piece and a second airfoil piece that is bonded to the first airfoil piece at a joint. The first airfoil piece and the second airfoil piece are formed of aluminum alloys. At least one of the aluminum alloys is an aluminum alloy composition that has greater than 0.8% by weight of zinc. The joint includes a braze element of magnesium, zinc, or combinations thereof in a higher concentration than in other portions of the first airfoil piece and the second airfoil piece.

Aluminum airfoil

Growing community of inventors

Avon, CT, United States of America

Daniel A Bales