Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Other

Jesse R Boyer

Lawrence A Binek

Evan J Butcher

Vijay Narayan Jagdale

Dmytro Mykolayovych Voytovych

Randall Joyner

Matthew B Kennedy

Christopher F O'Neill

Om Parkash Sharma

James Romanelli

Jeffry K Pearson

Bryan Galbraith Dods

John P Rizzo, Jr

Joseph D Drescher

Jesus A Garcia

Robert E Erickson

Robert P Delisle

Sergey Mironets

Michael Winter

David W Morganson

Sean R Jackson

Lyutsia Dautova

Agnes Klucha

Adam Z Doherty

Louis Porretti

Anthony Pizzola

Joseph Ott

Caitlin Oswald

Benjamin W Meissner

Timothy S Snyder

Wendell V Twelves

Sergei F Burlatsky

David Ulrich Furrer

Jeffrey S Beattie

James M Koonankeil

Zhong Ouyang

Daniel A Snyder

Herbert A Chin

Wangen Lin

Tommy Skiba

Kevin D Smith

James J Moor

Krzysztof Barnat

David A Raulerson

David A Krause

Richard William Varsell

Erik M Pedersen

Hector M Pinero

Monica C Smith

Jaimie Taraskevich

Stephen D Doll

Dorel M Moisei

Om P Sharma

Faramarz Zarandi

Kun Tong

Rebecca L Runkle

Gene P Allocca

Jeffrey K Pearson

Lukas A Rubino

Zachary Ryan Gibbons

Bryan G Dods

An assembly is provided for a turbine engine. This engine assembly includes a combustor, an engine case, a support structure and a monolithic body. The combustor includes a combustor wall and a combustion chamber within the combustor. The combustor wall forms a peripheral boundary of the combustion chamber. The engine case forms a peripheral boundary of a plenum along the combustor. The support structure extends radially from the combustor wall to the engine case. The monolithic body includes the combustor wall, the engine case, the support structure and a plurality of ports arranged circumferentially about an axis. Each of the ports is fluidly coupled with the plenum and projects axially through the support structure. The ports include a first port. The first port includes a cross-sectional geometry that laterally tapers as the first port extends radially outward within the monolithic body.

Turbine engine support structure with airflow ports

An exhaust duct for an engine includes an outer exhaust duct and a nested exhaust duct capable of having at least two configurations. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a first length of the nested exhaust duct in a first configuration. The nested exhaust duct is circumferentially surrounded by the outer exhaust duct for a second length of the nested exhaust duct in a second configuration, which is less than the first length.

Axial expandable exhaust duct

A stator vane for a gas turbine engine combustor has a vane segment that includes a vane having a leading edge, a trailing edge, a suction side, a pressure side, a vane inner base, and a vane outer base, an inner shroud segment attached to the vane at the vane inner base, and an outer shroud segment attached to the vane at the vane outer base. The stator vane further includes a support structure attached to the vane at a vane trailing edge, and a first weld shield attached to the support structure by a first connector. The first weld shield is positioned over and spaced away from the suction side. The vane, inner shroud segment, outer shroud segment, support structure, and first weld shield are integrally formed during a single, continuous additive manufacturing process.

Integral stator vane weld shield

A method of manufacturing a nested combustor liner includes manufacturing a nested combustor liner into a green state including a plurality of annular interior walls radially adjacent to one another and circumferentially surrounding an exhaust duct aperture and a plurality of annular exterior walls radially adjacent to one another and radially spaced apart from and circumferentially surrounding the plurality of annular interior walls and an ignitor wall attached to a first annular interior wall at a first interior end, extending radially toward and attached to a first annular exterior wall at a first exterior end. The method includes assembling the plurality of annular interior walls and the plurality of annular exterior walls, forming an assembled combustor liner. The method includes densifying the assembled combustor liner.

Article and method for manufacturing an expanded combustor liner

A unitized build assembly for a gas turbine engine includes an exhaust duct, a hot section with a locking structure and including a combustor and turbine section. The hot section at least partially circumferentially surrounds the exhaust duct. The build assembly includes a compressor section with an interface structure and is proximal to the hot section. The hot section at least partially circumferentially surrounds at least part of the compressor section and the locking structure is configured to engage the interface structure to limit movement of the hot section relative to the compressor section.

Unitized manufacturing of a gas turbine engine

A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.

Engine article with integral liner and nozzle

An additively manufactured attritable engine includes an engine case, a fuel ring integral and conformal with the engine case, and a fuel manifold attached to the fuel ring and configured to deliver fuel to the fuel ring. The engine also includes a fuel injector attached to the fuel ring and configured to receive fuel from the fuel ring.

Casing integrated fluid distribution system

An attritable engine includes an engine case, which includes an outer wall and a fuel rail integral with the outer wall. The fuel rail includes a fuel line integral with the outer wall, a fuel ring configured to receive fuel from the fuel line, and an injector throat configured to receive aerated fuel from the fuel ring. The engine case includes counter distortion webbing defining the injector throat and is integral with the fuel rail and the outer wall. The engine case includes a combustion chamber configured to receive fuel from the injector throat.

Integrated additive fuel injectors for attritable engines

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

A combustor for a gas turbine engine includes a combustor liner, a fuel swirler integral and conformal with the combustor liner to provide an outlet for fuel into the combustor, and a dilution chute surrounding the fuel swirler outlet and extending into the combustor to provide a wetting surface for fuel exiting the fuel swirler.

Integrated fuel swirlers

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 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

Growing community of inventors

Middletown, CT, United States of America

Jesse R Boyer