United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Pratt-whitney Canada Corp

United Technologies Corporaton

Alan David Cetel

Dilip M Shah

Steven J Bullied

John Joseph Marcin

Venkatarama K Seetharaman

Mario P Bochiechio

David N Duhl

Raymond C Surace

Carl R Verner

Kevin W Schlichting

Eric A Hudson

William Patrick Allen

Bradford A Cowles

Michael G McCaffrey

David A Litton

James Thompson Beals

Michael J Maloney

John J Marcin

David Ulrich Furrer

Brian S Tryon

Sudhangshu Bose

Alan W Stoner

Paul D Genereux

Reade R Clemens

Emily K Kreek

Joel Larose

Timothy M Davis

Daniel A Bales

Mark John Rogers

John A Sharon

John R Farris

Raymond C Benn

Peter J Draghi

Dinesh K Gupta

Walter E Olson

Norman Pietruska

Charles M Biondo

Daniel P DeLuca

Edward R Szela

Luke H Rettberg

Maurice L Gell

Raymond P Ristau

Curtis Heath Riewe

Kirk C Newton

Jeffrey M Wittman

Dwayne A Braithwaite

Dilip N Shah

Katelyn Kwoka

D Slade Stolz

Samir V Patel

John J Marcin Jr

Carl R Vernel

Jr John J Marcin

Shiela R Woodward

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

An alloy comprises, by weight: nickel (Ni) as a largest constituent; 6.0% to 7.5% chromium; up to 5.0% cobalt; 5.3% to 6.5% aluminum; up to 5.0% rhenium; 3.7% to 7.0% tungsten; and 3.7% to 7.0% tantalum.

High temperature combustor and vane alloy

A coating-substrate combination includes: a Ni-based superalloy substrate comprising, by weight percent: 2.0-5.1 Cr; 0.9-3.3 Mo; 3.9-9.8 W; 2.2-6.8 Ta; 5.4-6.5 Al; 1.8-12.8 Co; 2.8-5.8 Re; 2.8-7.2 Ru; and a coating comprising, exclusive of Pt group elements, by weight percent: Ni as a largest content; 5.8-9.3 Al; 4.4-25 Cr; 3.0-13.5 Co; up to 6.0 Ta, if any; up to 6.2 W, if any; up to 2.4 Mo, if any; 0.3-0.6 Hf; 0.1-0.4 Si; up to 0.6 Y, if any; up to 0.4 Zr, if any; up to 1.0 Re, if any.

Oxidation-resistant coated superalloy

An apparatus for countergravity casting a metallic material, has: a crucible for holding melted metallic material; a casting chamber for containing a mold; a fill tube capable of extending into the crucible to communicate melted metallic material to the casting chamber; and a gas source coupled to a headspace of the melting vessel to allow the gas source to pressurize the headspace to establish a pressure differential to force the melted metallic material upwardly through the fill tube into the mold. Extraneous sulfur is prevented from entering the molten metal from the surrounding environment.

Countergravity casting apparatus and desulfurization methods

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

An apparatus for countergravity casting a metallic has: a crucible for holding melted metallic material; a casting chamber for containing a mold; a fill tube capable of extending into the crucible to communicate melted metallic material to the casting chamber; and a gas source coupled to a headspace of the melting vessel to allow the gas source to pressurize said headspace to establish a pressure differential to force the melted metallic material upwardly through said fill tube into the mold. Added sulfur-gettering particles subsequently filtered or sulfur-gettering material removes sulfur from the melted metallic material.

Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

Thin seal for an engine

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

The present disclosure relates to advanced materials, particularly single crystal grain structures including the formation of single crystal grain structures. Single crystal grain structures offer improved mechanical properties when used with individual components. Improving mechanical properties is favorable for components that are used in applications with high temperature, pressure, and stress. In these applications, mechanical failure is extremely undesirable. Individual components, such as seals, can be designed with a single crystal grain structure in a preferred direction. By selecting a preferred direction, and orienting the single crystal grain structure accordingly, the single crystal grain structure can improve the component's mechanical properties. Single crystal grain structure seals and the method of forming the seals, therefore, offer various improvements to individual components, specifically when the components are designed for high temperature, pressure, and stress applications.

Single crystal grain structure seals and method of forming

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West Hartford, CT, United States of America

Alan David Cetel