United Technologies Corporation

Raytheon Technologies Corporation

Pratt & Whitney Rocketdyne, Inc.

United States of America As Represented by the Secretary of the Air Force

Gary A Schirtzinger

Joe Ott

Lexia Kironn

Wendell V Twelves

Evan J Butcher

Roger O Coffey

Dennis M Moura

Stanley J Funk

John J Rup, Jr

Lyutsia Dautova

Shawn Stempinski

Sergey Mironets

George J Kramer

John D Frish

Joseph Ott

Raymond J Bruchez

Rainer J Herbert

Lance Wurzbacher

Joseph L Orr

Gunter Eichhorn

Wendell V Twelves Jr

Wendel V Twelves

A process is provided for additively manufacturing at least one part. The processing includes depositing a substantially uniform layer of material over at least a portion of a support surface using a belt that contacts the material. The process also includes solidifying at least a portion of the layer of material using a solidification device to form at least a portion of the part.

Systems and processes for distributing material during additive manufacturing

A shrouded conduit is provided for arranging, for example, in a gas path of a turbine engine. The shrouded conduit includes a tubular shroud extending longitudinally along a centerline. The shrouded conduit also includes a fluid conduit extending longitudinally in the shroud. A first portion of the fluid conduit is connected laterally to and may be formed integral with a first portion of the shroud.

Shrouded conduit for arranging a fluid flowpath

A fuel injector is provided for a gas turbine engine. The fuel injector includes a fuel conduit and a cooling fluid circuit through a strut. A gas turbine engine is provided that includes a multiple of fuel injectors in communication with a combustor and a cooling system in communication with each of the multiple of fuel injectors.

Cooled fuel injector system for a gas turbine engine

A method is provided involving an additive manufacturing system. This method includes a step of forming a first fluid conduit using the additive manufacturing system. The method also includes a step of providing a fluid coupling. The fluid coupling includes the first fluid conduit and a second fluid conduit. The first fluid conduit is connected to and fluidly coupled with the second fluid conduit. The first fluid conduit has a first configuration. The second fluid conduit has a second configuration that is different than the first configuration.

Fluid couplings and methods for additive manufacturing thereof

A method of monitoring the residual stress in surface and near surface regions of a component includes identifying predetermined locations on the surface of a component that are expected to experience high stress during normal operating conditions of the component. Marker particles are introduced into the component during additive manufacture of the component at the predetermined locations. Then, the residual stress of the component is measured at a location corresponding with the marker material using x-ray techniques.

Method for in-situ markers for thermal mechanical structural health monitoring

A method includes building a tubular object by a layer-by-layer additive manufacturing process. A structure integrally connected to the tubular object for supporting a portion of the tubular object is formed during building of the tubular object. The structure provides vibration dampening, heat shielding, heat transfer, stiffening, energy absorption, or mounting after the tubular object is built.

Method of generating support structure of tube components to become functional features

One embodiment includes a fuel injector. The fuel injector assembly comprises a conduit for conveying fuel from a fuel inlet to a nozzle. The conduit is located in a support, with the conduit, the nozzle, and the support being a single unitary piece. A thermally compliant feature is located at the nozzle which allows the fuel injector to adjust for differential thermal expansion.

Thermally compliant additively manufactured fuel injector

A septum-tied tube pack is provided that includes a first outer wall formed by a multiple of first connected radiuses. A second outer wall is formed by a multiple of second connected radiuses. A first end radius connects the first outer wall and the second outer wall. A second end radius connects the first outer wall and the second outer wall. A multiple of septum elements extend between the first outer wall and the second outer wall. A gas turbine engine is also provided that includes an engine case structure and a fluid conduit mounted to the engine case structure. The fluid conduit includes a septum-tied tube pack section.

Additive manufactured non-round, septum tied, conformal high pressure tubing

A machine for fabricating a fiber-reinforced component by additive manufacturing is disclosed. The machine may have a surface, a matrix feed configured to deposit a plurality of matrix layers on the surface, and a fiber feed configured to deposit a fiber layer on at least one of the plurality of matrix layers. The deposition of the plurality of matrix layers and the fiber layer may be controlled by a computer.

Continuous fiber-reinforced component fabrication

Components may be manufactured by co-extruding a polymer filament and a fiber filament from a nozzle. The polymer filament and the fiber filament may be heated within the nozzle, which may couple the polymer filament to the fiber filament. The co-extruded filament may result in long reinforcing fibers which provide strength to the components.

Methods for manufacturing fiber-reinforced polymeric components

The present disclosure relates to systems for controlling movement of a divergent flap () in an exhaust nozzle (). A nozzle flap assembly may include a first link () pivotably coupled to a divergent flap (). A second link () may be pivotably coupled to the first link and a static portion () of the exhaust nozzle. The second link may comprise a bumper (). The first link may be configured to contact the bumper in response to the divergent flap being in a high thrust mode. The second link may be configured to contact the divergent flap in response to the divergent flap being in a low thrust mode.

Linkage to control and restrain flap movement

A method includes designing a part. The part includes at least one internal structure. The internal structure is designed to provide strain mitigation, energy dissipation, or impact resistance for the part during an emergency condition. The part is built by a layer-by-layer additive manufacturing process. While building the part, the internal structure is connected to the part.

Additively grown enhanced impact resistance features for improved structure and joint protection

The present disclosure relates to an aircraft brush seal comprising a first brush seal member and a second brush seal member comprising a channel that receives a plurality of interwoven brush fibers. The interwoven brush fibers may be coupled to the first brush seal member and/or may extend into the second brush seal member. The interwoven brush fibers may not couple to the second brush seal member and/or may form an air seal. The air seal may be formed between a first air compartment and a second air compartment.

Stationary non-rotating brush seals

A valve system intermediate a secondary flow path and a primary flow path to selectively communicate secondary airflow into the primary gas flow path and control airflow injected from a higher pressure plenum into a lower pressure flowpath.

Growing community of inventors

Glastonbury, CT, United States of America

Gary A Schirtzinger