United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporaton

Dilip M Shah

Alan David Cetel

Steven J Bullied

John Joseph Marcin

Venkatarama K Seetharaman

Carl R Verner

Ryan C Breneman

Shiela R Woodard

John J Marcin

Paul D Genereux

James Thompson Beals

Raymond C Surace

Kevin W Schlichting

Mario P Bochiechio

David N Duhl

William Patrick Allen

Marc R Sauerhoefer

Raymond Paul Langevin

Richard Alan Stone

Justin Andreas Neutra

James Peter Aduskevich

David Henry Abbott

Dorothea Nadette Carraway

Gabriel L Suciu

Michael G McCaffrey

David Ulrich Furrer

Eric A Hudson

Herbert A Chin

Norman S Bornstein

Alan W Stoner

Stephen Chin

Jacob A Snyder

John D Wiedemer

Paul L Reynolds

Bradford A Cowles

Donald R Parille

Emily K Kreek

Carl E Kelly

Frederick M Schwarz

Thomas N Slavens

Michael J Maloney

Timothy M Davis

Daniel A Bales

Mark John Rogers

Pantcho P Stoyanov

John A Sharon

John R Farris

Dinesh K Gupta

Walter E Olson

Keith A Santeler

Daniel E Kane

Norman Pietruska

Sudhangshu Bose

Chris Vargas

Daniel F Paulonis

Stephen Douglas Murray

Edward R Szela

Joshua E Persky

Glenn A Cotnoir

Albert Rabinovich

Reade R Clemens

Gopal Das

Jeffrey M Wittman

Weiduo Yu

Joseph G Hillebrand

Venkat Seetharaman

David Lee Roe

Donald Anton

Katelyn Kwoka

Luliana Cernatescu

John J Marcin Jr

Carl R Vernel

Jr John J Marcin

Stephen D Murray

Keith Santeler

A casting method includes: forming a seed, the seed having a first end and a second end, the forming including bending a seed precursor; placing the seed second end in contact or spaced facing relation with a chill plate; contacting the first end with molten material; and cooling and solidifying the molten material so that a crystalline structure of the seed propagates into the solidifying material. The forming further included reducing a thickness of the seed proximate the first end relative to a thickness of the seed proximate the second end.

Arcuate seed casting method

In a method for manufacturing a turbine engine element such as a blade or vane, the element has an airfoil. The method includes: applying a load across an assembly of a first cast portion of the airfoil and a second cast portion of the airfoil; and applying current across a junction of the first cast portion and the second cast portion to fuse the second cast portion to the first cast portion.

Multi-zone blade fabrication

A casting method includes forming a seed. The seed has a first end and a second end. The forming includes bending a seed precursor. The seed second end is placed in contact or spaced facing relation a chill plate. The first end is contacted with molten material. The molten material is cooled and solidifies so that a crystalline structure of the seed propagates into the solidifying material. The forming further includes inserting the bent seed precursor into a sleeve leaving the bent seed precursor protruding from a first end of the sleeve.

A casting method includes forming a seed. The seed has a first end and a second end and an inner diameter (ID) surface and an outer diameter (OD) surface. The seed second end is placed in contact or spaced facing relation with a chill plate. The first end is contacted with molten material. The molten material is cooled and solidified so that a crystalline structure of the seed propagates into the solidifying material. At least a portion of the seed contacted with the molten material has a solidus higher than a solidus of at least an initial pour portion of the molten material.

A method for manufacturing a blade, the method includes casting a nickel alloy blade precursor having an airfoil and a root. The airfoil and the root are solution heat treating differently from each other. After the solution heat treating, the root is wrought processed. After the wrought processing, an exterior of the root is machined.

Wrought root blade manufacture methods

A blade has an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The blade has a compositional variation along the airfoil.

Hybrid turbine blade for improved engine performance or architecture

A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.

Turbine component with a thin interior partition

A casting mold () comprises a shell () extending from a lower end () to an upper end () and having: an interior space () for casting metal; and an opening () for receiving metal to be cast. A plurality of thermocouples () are vertically-spaced from each other on the shell.

Casting molds, manufacture and use methods

A blade (-) comprises an airfoil () and an attachment root (). The blade has a tipward zone (--) and a rootward zone (-). The rootward zone has a single crystal structure. The tipward zone has a single crystal structure. The crystalline orientations of the rootward zone and tipward zone are at least 15&#xb0; out of registry with each other.

Turbine blades and manufacture methods

A method comprises: providing a spiral metallic workpiece having a cast structure associated with such spiral; and at least partially flattening the workpiece.

Cast components and manufacture and use methods

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Glastonbury, CT, United States of America

Dilip M Shah