Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Hamilton Sundstrand Corporation

Evan J Butcher

Lawrence A Binek

Wendell V Twelves

Joe Ott

Lexia Kironn

Vijay Narayan Jagdale

Sean R Jackson

Gary A Schirtzinger

Dmytro Mykolayovych Voytovych

Matthew B Kennedy

Om Parkash Sharma

Lyutsia Dautova

Jesus A Garcia

Bryan Galbraith Dods

Matthew E Lynch

John P Rizzo, Jr

Faramarz Zarandi

Michael Winter

Gary D Roberge

Zissis A Dardas

Jesse R Boyer

Kathleen E Sinnamon

Leslie F Guzman

Joseph Ott

Donald William Peters

Edwin Otero

Benjamin T Fisk

Daniel A Snyder

Tommy Skiba

Roger O Coffey

Kiley James Versluys

John T Schmitz

Andre Herman Troughton

John D Frish

Caitlin Oswald

Bryan P Conway

Jesse R Boy

Rainer J Herbert

Jr Wendell V Twelves

Wendell V Twelves Jr

Twelves Wendell V

Jr John P Rizzo

Twelves Jr Wendell V

Thomas J Ocken

Wendel V Twelves

Lyustia Dautova

A gas turbine engine with a lubrication system includes a ball bearing assembly and a rotor circumscribing a rotational axis and journaled within the ball bearing assembly. The gas turbine engine also includes a lubrication system located radially outward from a rotational axis and radially outward and adjacent to the ball bearing assembly, which includes a lubrication channel having an inlet and an outlet and a dispersion cone adjacent to the outlet of the lubrication channel.

Lubrication network for an attritable engine

A method for abrasive flow machining includes moving an abrasive media through a high-aspect passage of a workpiece. Local pressure of the abrasive media is increased at target abrasion surfaces of the high-aspect passage using a passage geometry that is configured to direct flow of the abrasive media into the target abrasion surfaces such that the target abrasion surfaces are preferentially polished by the abrasive media over other, non-targeted surfaces of the high-aspect passage at which the flow of the abrasive media is not directed into.

Abrasive flow machining method and article

Disclosed is a method of making a part, comprising: forming the part via an additive manufacturing process, wherein the additive manufacturing process comprises layering, melting, and solidifying a metal alloy based on a three dimensional numerical model, wherein the formed part comprises a microstructure, wherein the microstructure comprises an average columnar grain length; and heat treating the formed part, wherein heat treating comprises heating to between 750° C. and 1200° C. for a time between 0.5 hours and 10 hours and then cooling the formed part below 750° C., wherein after heat treating, the formed part has an average columnar grain length of about 400 micrometers to about 1000 micrometers, as measured using electron backscattered diffraction.

Method of making a radial turbine wheel using additive manufacturing

A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.

Additively controlled surface roughness for designed performance

Lubrication system for an attritable engine

A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.

Kinetic disassembly of support structure system for additively manufactured rotating components

A heat exchanger core includes a first hollow cylinder extending circumferentially around a center axis and extending axially along the center axis. The first hollow cylinder includes a first passage disposed radially within the first hollow cylinder and extending axially through the first hollow cylinder. A second hollow cylinder extends circumferentially around the center axis and extends axially along the center axis. The first hollow cylinder is disposed radially within the second hollow cylinder. The second hollow cylinder includes a second passage disposed radially between the first hollow cylinder and the second hollow cylinder and extending axially between the first hollow cylinder and the second hollow cylinder. The first hollow cylinder fluidically separates the first passage from the second passage. The first and second hollow cylinders and the first and second passages are spaced from one another in a sinusoidal relationship.

Multi-scale unitary radial heat exchanger core

A turbine engine has: a compressor; a combustor; a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and inlet member along the gas flowpath upstream of the compressor. The inlet member includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion; and a nose cap body surrounding the lattice portion.

Attritable engine additively manufactured inlet cap

A monolithic combustor apparatus comprises an outer casing comprising a forward flange, a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing, a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber, a first annular plenum disposed between the outer casing and the combustor liner, an inner liner disposed radially from the combustor liner, a first inner flange extending forward from the combustor liner, and a second inner flange extending radially inward from the first inner flange.

Monolithic combustor for attritiable engine applications

A heat exchanger core includes a first side, a second side, a third side, and a fourth side. A first layer includes a first width extending in a first direction, a first length extending in a second direction, a first height extending in a third direction, and a first plurality of passages, which extend from an inlet to an outlet. A second layer includes a second width extending in the first direction, a second length extending in the second direction, a second height extending in the third direction, and a second plurality of passages extending from the first side to the second side. The first and second plurality of passages are adjacent to one another. The first and second plurality of passages include a sinusoidal profile in the third direction and a sinusoidal profile in the first direction.

Multi-scale heat exchanger core

A lubrication system for an attritable engine includes a bearing chamber, a fluid filtering inlet configured to receive a fluid, and a fluid filtering outlet located downstream of the fluid filtering inlet and configured to deliver the fluid to the bearing chamber. The lubrication system also includes a lattice, integral and conformal with the attritable engine, configured to filter the fluid, and located between the fluid filtering inlet and the fluid filtering outlet. The lubrication system also includes a metering port, configured to meter the fluid and located downstream of the lattice and upstream of the fluid filtering outlet.

Integrated lubricating fluid filtering and metering device

A combustor may comprise an outer wall defining, at least, a portion of a combustion chamber. A dilution chute may extend from an interior surface of the outer wall. A support structure may extend between the dilution chute and the interior surface of the outer wall. A spall plate may extend from the interior surface of the outer wall. The spall plate may be located between the support structure and an outlet of the combustion chamber.

Spall plate for consumable combustor support structures

A double walled stator housing includes a first stator housing wall, a second stator housing wall located radially outward from the first stator housing wall, and an air gap located between the first and the second stator housing walls. The housing also includes at least one support structure attached to the first stator housing wall and the second stator housing wall, spanning the air gap and configured to minimize heat transfer between the first wall and the second wall.

Double walled stator housing

Growing community of inventors

Suffield, CT, United States of America

Evan J Butcher