Mikro Systems, Inc.

Raytheon Technologies Corporation

Siemens Energy, Inc.

Rtx Corporation

Siemens Aktiengesellschaft

United Technologies Corporation

John R Paulus

Michael P Appleby

Iain Fraser

Gary Brian Merrill

Andrew Jeremiah Burns

Benjamin E Heneveld

Jon T Moore

Joel H Wagner

Paul M Lutjen

Ahmed Kamel

Dustin Wayne Davis

Jill Klinger

Dmitriy A Romanov

Cora Schillig

Dhafer Jouini

Jimmy Johnson

Billie Rosalie Maldonado

Morely S Sherman

James R Plante

Richard A Hawkins

Nolan Frederic Quinn

Mary E M Hiller

Thurman C Dabbs

Roy Eakins

Iain Alasdair Fraser

Gabriel Victor Orsinger

Benjamin Edward Heneveld

Daniel Ellgass

Iain A Fraser

A component for a gas turbine engine, including: at least one internal cavity extending through the component, the internal cavity having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal cavity; a plurality of cooling features extending from a surface of the at least one internal cavity, the plurality of cooling features are formed in accordance with at least one of the following groups: i) a plurality of airfoil shaped features that extend upwardly from the surface of the at least one internal cavity and a plurality of wedge shaped features each having a triangular base that has an upstream portion and a downstream portion, the upstream portion extending further from the surface than the downstream portion; ii) a plurality features having a curved or 'J' shaped base that extends upwardly from the surface, a plurality features having a double curved or symmetrically “J” shaped base that extends upwardly from the surface, and a plurality features having a base that extends upwardly from the surface with a curved portion that defines an opening therethrough; iii) a first plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the first plurality of pins and a second plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the second plurality of pins the plurality of grooves formed in the peripheral surface of each of the second plurality of pins are configured such that “V” shapes or inverted “V” shapes are formed in the peripheral surface of each of the second plurality of pins; and iv) a plurality of chevron shaped trip strips that are located in a channel, the plurality of chevron shaped trip strips are spaced from each other such that a “U” shaped passage is formed therebetween and each chevron shaped trip strip has a top portion that curls inwardly towards the channel and a plurality of pairs of features that each extend from a surface of another channel towards each other where a gap is located between distal ends of the plurality of pairs of features.

Cooling features for a component of a gas turbine engine

An investment casting process for a hollow component such as a gas turbine blade utilizing a ceramic core () that is cast in a flexible mold () using a low pressure, vibration assisted casting process. The flexible mold is cast from a master tool () machined from soft metal using a relatively low precision machining process, with relatively higher precision surfaces being defined by a precision formed insert () incorporated into the master tool. A plurality of identical flexible molds may be formed from a single master tool in order to permit the production of ceramic cores at a desired rate with a desired degree of part-to-part precision.

Investment casting process for hollow components

A method of bonding a mini-core to a surface of a core is provided. The method includes providing the mini-core with an attachment device that includes a protrusion of a surface of the mini-core, dipping the protrusion into a supply of paste to transfer a fixed quantity of paste to the protrusion and affixing the protrusion to the surface of the core with the fixed amount of paste interposed between the surface and the protrusion.

Mini-core surface bonding

A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body includes a ceramic material. A shape of the extension includes a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis includes an ellipse. The extension is connected to the investment core body by the connection portion.

Cast-in film cooling hole structures

A method of manufacturing a substrate () with a ceramic thermal barrier coating (). The interface between layers of the coating contains an engineered surface roughness () to enhance the mechanical integrity of the bond there between. The surface roughness is formed in a surface of a mold () and is infused by a subsequently cast layer of material (). The substrate may be partially sintered () prior to application of the coating layer(s) and the coated substrate and coating layer(s) may be co-sintered to form a fully coherent strain-free interlayer.

Method of forming a thermal barrier coating system with engineered surface roughness

A core forming method is provided for forming a core. The core forming method includes forming one or more mold parts of water-soluble polymer (WSP), each mold part including a bond area and a part forming area, moistening the bond areas, bonding the mold parts together with the bond areas moistened and the part forming areas aligned to form a cavity shaped as a negative of the core, injecting a slurry, which is non-reactive with the WSP, into the cavity and removing the WSP with water once the slurry is cured.

Water soluble polymer for core forming

A method of forming an article including: contacting a fugitive tool with a powdered parent material; densifying the powdered material; and destructively removing the fugitive tool. A coating of a different material may be formed against the parent material using a similar approach.

Systems, devices and methods for spark plasma sintering

A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body comprises a ceramic material. A shape of the extension comprises a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis comprises an ellipse. The extension is connected to the investment core body by the connection portion.

Certain exemplary embodiments can provide a system, machine, device, manufacture, and/or composition of matter configured for and/or resulting from, and/or a method for, activities that can comprise and/or relate to, investment casting a product in a mold, the product comprising at least one wall, the mold comprising a core, an inner primary shell, and an outer secondary shell.

Systems, devices, and methods involving precision component castings

Certain exemplary embodiments can provide a composition, system, machine, device, manufacture, circuit, and/or user interface adapted for, and/or a method and/or machine-readable medium comprising machine-implementable instructions for, activities that can comprise, after removing a cast device from a stack-lamination-derived mold, said cast device formed from a molding composition, applying a desired shape to said cast device to form a shaped cast device, said molding composition comprising: a ceramic composition comprising silica; an cycloaliphatic epoxy binder composition, said cycloaliphatic epoxy binder composition present in said molding composition in an amount up to 30% by weight of said molding composition; a silicone composition comprising a siloxane resin, said silicone composition present in said molding composition in an amount up to 30% by weight of said molding composition; and a solvent composition adapted to dissolve said cycloaliphatic epoxy binder composition and said silicone composition.

Systems, devices, and/or methods for manufacturing castings

Growing community of inventors

Afton, VA, United States of America

John R Paulus