Rtx Corporation

Raytheon Technologies 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

Christopher D Ramsey

Paul M Lutjen

Ying She

Joseph Zacchio

Yoel Bugin

Leslie F Guzman

Craig M Beers

Brent J Merritt

Michael Winter

Andrzej Ernest Kuczek

Faramarz Zarandi

Gabriel Idan Romagnolo

Zachary Ryan Gibbons

Anthony A Binek

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

David A Dorman

Victoria S Richardson

Erika Klek

Raffi O Mangoyan

Anthony Van

Danielle L Grolman

Brendan T Gustafson

Benjamin G Gardell

Ritesh Khire

Randolph T Lyda

Valentina Lugo

John A Ferro

Ronald P LaRose

Jesse R Boy

Paul R Braunwart

Matthew S Dushek

Timothy E Mandel, Jr

Frederick Rosenberger

Garrett Moler

Edward L Hieb

Antony Van

Brandon P Williams

Demytro Mykolayovych Voytovych

Andrzej Earnest Kuczek

An assembly is provided for a turbine engine. This assembly includes an engine structure, and the engine structure includes a plenum, a reverse flow combustor, a nozzle structure and a cooling circuit. The reverse flow combustor is disposed in the plenum and includes a combustion chamber. The nozzle structure is arranged at an outlet from the combustion chamber. The nozzle structure includes a first platform, a second platform and a plurality of vanes arranged circumferentially about an axis. The vanes extend across the flowpath from the first platform to the second platform. The cooling circuit extends in the first platform and between a circuit inlet into the cooling circuit and a circuit outlet from the cooling circuit. The circuit inlet is fluidly coupled with and disposed along the plenum. The circuit outlet is fluidly coupled with and disposed along the flowpath.

Cooling nozzle vanes of a turbine engine

An apparatus is provided for a powerplant. The apparatus includes a heat pipe extending axially along an axis from a first end of the heat pipe to a second end of the heat pipe. The heat pipe extends circumferentially around the axis. The heat pipe includes an evaporator region, a condenser region and a plurality of fluid passages. The evaporator region is disposed at the second end of the heat pipe. The condenser region is disposed at the first end of the heat pipe. The condenser region is disposed radially inboard of the evaporator region. The fluid passages are axially between and fluidly couple the evaporator region and the condenser region.

Powerplant with integrated heat pipe

An additively manufactured attritable engine includes a compressor section, a combustion section, a turbine section, and an engine case wall, which surrounds the compressor section, the combustion section, and the turbine section. The engine case wall includes a first cavity embedded in the engine case wall that defines an injector that is in fluid communication with the combustion section. The engine case wall includes at least one second cavity embedded within the engine case wall and defines at least one cooling channel that is in thermal communication through the engine case wall with the injector.

Cooling fuel injector system for an attritable engine

An oil distributor is provided for a bearing chamber. The oil distributor includes an outer annular manifold, which is integrally formed with an interior surface of the bearing chamber and which defines a first interior cavity receptive of pressurized oil which defines a first interior cavity receptive of pressurized oil, an inner annular manifold, which defines a second interior cavity and comprises an interior facing surface defining holes respectively communicative with the second interior cavity and one or more support struts by which the inner annular manifold is supported within the outer annular manifold. Each of the one or more support struts defines interior lines by which the pressurized oil flows from the first interior cavity to the second interior cavity and to the holes.

Annular oil distributor for bearing chamber

A bearing compartment includes a housing having an upper housing portion and a lower housing portion, and a support structure fabricated within the bearing compartment. The support structure includes an upper portion within the upper housing portion and a spring section within the lower housing portion. The spring section includes a plurality of struts and is separable from the support structure for use as a spring within the housing.

Support structure and spring for bearing compartment

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.

Growing community of inventors

Glastonbury, CT, United States of America

Lawrence A Binek