Raytheon Technologies Corporation

Rtx Corporation

Hamilton Sundstrand Corporation

United Technologies Corporation

Carrier Corporation

Next Dynamics Corp.

Other

Raytheon Company

Rohr, Inc.

Utc Fire and Security Corporation

Lawrence A Binek

Jesse R Boyer

Evan J Butcher

Sean R Jackson

David W Morganson

Jose R Paulino

Vijay Narayan Jagdale

Dmytro Mykolayovych Voytovych

Timothy S Snyder

Matthew B Kennedy

Aaron T Nardi

Om Parkash Sharma

Bryan Galbraith Dods

Matthew E Lynch

Jesus A Garcia

Ying She

Joseph Zacchio

Leslie F Guzman

Paul M Lutjen

Craig M Beers

Brent J Merritt

Michael Winter

Andrzej Ernest Kuczek

Christopher D Ramsey

Faramarz Zarandi

Yoel Bugin

Anthony A Binek

Gabriel Idan Romagnolo

Zachary Ryan Gibbons

Adam Kuenzi

Zissis A Dardas

Darryl A Colson

Wayne F Larson

Ulf J Jonsson

James E Benedict

Eric Chrabascz

Gurkan Gok

Vijaya Ramaraju Lakamraju

Matthew S Hill

Nicholas Charles Soldner

Diana Giulietti

Tommy Skiba

Kenji Homma

Jeffrey Michael Mendoza

Julian Winkler

Matthew William Miller

Craig Aaron Reimann

Erika Klek

David A Dorman

Victoria S Richardson

Anthony Van

Brendan T Gustafson

Raffi O Mangoyan

Danielle L Grolman

Ritesh Khire

Randolph T Lyda

Valentina Lugo

John A Ferro

Benjamin G Gardell

Jesse R Boy

Frederick Rosenberger

Garrett Moler

Timothy E Mandel, Jr

Ronald P LaRose

Paul R Braunwart

Matthew S Dushek

Antony Van

Brandon P Williams

Demytro Mykolayovych Voytovych

Andrzej Earnest Kuczek

A combustor system for an aerial vehicle can include an outer case with a first and second end, an inner combustor case with a lumen, a central combustor chamber, an air flow path between the outer case and inner combustor case, an integrated air scoop attached to the inner combustor case at the lumen that directs air from the air flow path into the central combustor chamber, a wedge within the integrated air scoop, a second integrated air scoop attached to the outer case, a bifurcated orifice integrated into the second integrated air scoop, a fuel manifold and fuel orifice within the first integrated air scoop, and a splash plate with a first and second face, the splash plate extending through the lumen into the central combustor chamber. The first and second integrated scoops can interlock and seal by pushing the wedge into the bifurcated orifice.

Unitary case integrated flow scoops

A radio frequency (RF) waveguide comprising a channel, a filter, and a support bridge. The channel can comprise an outer wall defining an inner cavity configured to propagate electromagnetic waves. The filter can be disposed in the inner cavity of the channel and can comprise a perimeter edge and an aperture. The support bridge can comprise a first interface connected to an inner surface of the outer wall at a first location, and a second interface connected to the filter at a position between the perimeter edge and the aperture of the filter to support the filter within the channel. The support bridge can remain in place as connected to the filter, and the filter and waveguide can operate without interference from the support bridge, meaning that the waveguide meets all performance specifications and functions as intended for a particular application even with the support bridge left in place.

Monolithic waveguide and supporting waveguide bridge

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a monolithic body. The monolithic body includes a splash plate and a fuel nozzle. The splash plate includes a splash plate surface. The fuel nozzle includes a nozzle orifice. The fuel nozzle is configured to direct fuel out of the nozzle orifice to impinge against the splash plate surface.

Fuel injector assembly for a turbine engine

According to an aspect, a bearing compartment includes a housing integrally formed with a spring configured to deform in response to a force. The housing includes an overhang region that is supported by the spring during an additive manufacturing build process. The spring includes a plurality of struts that extend axially within the housing.

Spring damping for bearing compartment

A manufacturing method is provided during which a body is additively manufactured. The body includes an engine case for a gas turbine engine, a support structure and an aperture. The support structure projects out from the engine case. The support structure includes a lattice, a wall and an internal volume. The wall surrounds the lattice. The internal volume is within the support structure along the lattice. The internal volume is filled with powder. The aperture is at an intersection between the engine case and the support structure. The powder is extracted from the internal volume through the aperture.

Gas turbine engine support structure with internal lattice

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 additively manufactured vane cluster has a platform, a shroud, and airfoils joining the platform to the shroud. The platform has openings, each opening between a respective two of the airfoils and forming accommodating differential thermal expansion of a leading end of the platform relative to a trailing end of the platform.

Additively manufactured turbine vane cluster

A system for additive manufacturing includes a build chamber including a sidewall and a build plate cooperating to define a build volume, wherein the build chamber is configured to house a part and unfused feedstock powder during a build. An energy source is mounted for movement relative to the build chamber, wherein the energy source is configured to selectively sinter the feedstock powder. A recoater is mounted for movement relative to the build chamber, wherein the recoater is configured to deposit successive layers of the feedstock powder for sintering to the part. A rotational actuator is in operable communication with the build chamber and the recoater configured to rotate the build chamber relative to the recoater.

Rotating relative recoater and part orientation

A centralized multi engine startup system including a pallet structure; an energized gas source supported by the pallet structure; an umbilical gas line fluidly coupled to the energized gas source; and a vehicle in operative communication with the umbilical gas line, wherein each of the energized gas source and umbilical gas line are coupled to the pallet structure and remain with the pallet structure responsive to a vehicle launch from the pallet structure.

Centralized multi engine startup system for palletized applications

In accordance with at least one aspect of this disclosure, a method can include selectively sintering at least a portion of a part and one or more indexing features onto a build plate disposed in a build area of a feedstock powder bed, determining an actual orientation of the part and the build plate relative to a recoater prior to recoating, storing the actual orientation of the part and the build plate relative to the recoater, comparing the actual orientation of the part and the build plate relative to the recoater with a predicted orientation, and recoating the build area with feedstock powder if the actual orientation of the part and the build plate relative to the recoater matches the predicted orientation to achieve a predetermined build quality for a respective layer of the part.

An assembly is provided that includes a regulator manifold and a regulator element. The regulator manifold includes an inlet passage, a first outlet passage and a second outlet passage. The inlet passage is configured to receive bleed gas from a core flowpath. The regulator element is within the regulator manifold and configured to pivot to a first position, a second position and an intermediate position between the first position and the second position. The regulator element is configured to fluidly couple the inlet passage with the first outlet passage in the first position. The regulator element is configured to fluidly couple the inlet passage with the second outlet passage in the second position. The regulator element is configured to fluidly decouple the inlet passage from the first outlet passage and the second outlet passage in the intermediate position.

Aerial vehicle fluid control system with multi-way flow regulator

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

According to an aspect, a support structure is integrally formed with a bearing compartment. The support structure includes a plurality of vertical supports and horizontal supports. The vertical supports and horizontal supports include one or more features to support machining of the bearing compartment and removal of the support structure from the bearing compartment.

Support structure for bearing compartment

A turbine vane for use in a gas turbine engine includes an airfoil section having a concave sidewall and a convex sidewall. Both the concave sidewall and convex sidewall extend spanwise between a platform and a radially outward airfoil tip and chordwise between a leading edge and a trailing edge. The concave sidewall includes a convex ablative region.

Erosion compensated vane geometry

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

Growing community of inventors

Glastonbury, CT, United States of America

Lawrence A Binek