United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporaton

Venkatarama K Seetharaman

Alan David Cetel

Dilip M Shah

David Ulrich Furrer

Kevin W Schlichting

Steven J Bullied

John Joseph Marcin

David A Litton

Grant O Cook, Iii

Michael J Maloney

Mario P Bochiechio

Carl R Verner

Iuliana Cernatescu

Paul D Genereux

Bradford A Cowles

Michael G McCaffrey

Raymond C Surace

Michael A Weisse

Brian S Tryon

James Olaf Hansen

Benjamin Joseph Zimmerman

Sudhangshu Bose

John J Marcin

Scott C Billings

Ethan C Drew

Jay Thomas Abraham

Katelyn Kwoka

Grant O Iii Cook

Shiela R Woodward

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 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

Aspects of the disclosure are directed to an analysis of a material of a component. A radiation source is activated to transmit radiation to the component. A beam pattern is obtained based on the component interfering with the radiation. The beam pattern is compared to a reference beam pattern. An anomaly is detected to exist in the material when the comparison indicates a deviation between the beam pattern and the reference beam pattern.

Detection of crystallographic properties in aerospace components

A process includes solution heat treating a nickel based superalloy with greater than about 40% by volume of gamma prime precipitate to dissolve the gamma prime precipitate in the nickel based superalloy; cooling the nickel based superalloy to about 85% of a solution temperature measured on an absolute scale to coarsen the gamma prime precipitate such that a precipitate structure is greater than about 0.7 micron size; and wrought processing the nickel based superalloy at a temperature below a recrystallization temperature of the nickel based superalloy. A material includes a nickel based superalloy with greater than about 40% by volume of gamma prime precipitate in which the precipitate structure is greater than about 0.7 micron size.

Nickel based superalloy with high volume fraction of precipitate phase

An intermetallic matrix composite has an intermetallic matrix and a ceramic reinforcement. The intermetallic matrix comprises, in atomic percent: 28.0&#xb1;2.0 Nb; 27.0&#xb1;2.0 Mo; 27.0&#xb1;2.0 Cr; 9.0 &#xb1;2.0 Si; 9.0 &#xb1;2.0 Al; and no more than 10.0 other alloying elements and impurities, if any.

Intermetallic matrix composite

A method for joining engine components includes positioning a first plurality of thermal protection structures across a thermal protection space between a first thermal protection surface and a second thermal protection surface. The first and second engine components are locally joined by forming a first plurality of transient liquid phase (TLP) or partial transient liquid phase (PTLP) bonds along corresponding ones of the first plurality of thermal protection structures between the first thermal protection surface and the second thermal protection surface. The second thermal protection surface is formed from a second surface material different from a first surface material of the first thermal protection surface.

Method for joining dissimilar engine components

A method for casting comprising: providing a seed, the seed characterized by: an arcuate form and a crystalline orientation progressively varying along an arc of the form; providing molten material; and cooling and solidifying the molten material so that a crystalline structure of the seed propagates into the solidifying material.

Arcuate directionally solidified components and manufacture methods

An embodiment of a turbine assembly includes, among other possible things, a first component including a first component surface, a second component including a second component surface spaced apart from the first component surface, and a brush seal disposed between the first component and the second component. The brush seal includes, among other things, a first bristled region extending in a first direction from a backing plate, and sealingly engaging one of the first component surface and the second component surface. At least one of the backing plate and the first bristled region includes a nickel-based superalloy material having at least 40% of a Ni(Al,X) precipitate phase, X being a metallic or refractory element other than Al.

High temperature seal and method

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

An investment casting apparatus includes a furnace having an opening, a mold support, and a multi-axis actuator connected with the mold support and configured to retract the mold support from the opening with multiple-axis motion. An investment casting method includes withdrawing, with multiple-axis motion, a mold through the opening of the furnace to solidify a molten metal- or metalloid-based material in the mold. The apparatus and method can be used to form a cast article that has a body formed of the metal- or metalloid-based material. The body has a multi-textured, single crystal microstructure.

Casting apparatus and method for forming multi-textured, single crystal microstructure

Growing community of inventors

Rocky Hill, CT, United States of America

Venkatarama K Seetharaman