Hamilton Sundstrand Corporation

Rtx Corporation

United Technologies Corporation

Raytheon Technologies Corporation

Sikorsky Aircraft Corporation

Pratt & Whitney Rocketdyne, Inc.

Paul Attridge

Zaffir A Chaudhry

David L Lincoln

Gregory S Hagen

Janet Shaw

Scott Goyette

Jeffrey P King

Robert H Dold

Kathryn L Kirsch

Alexandru Cadar

Joseph E Turney

Ram Ranjan

John E Holowczak

Thomas J Martin

Paul F Croteau

Curtis C Cowan

Gabriel L Suciu

Joseph V Mantese

Alan Matthew Finn

Jesse M Chandler

Tahany Ibrahim El-Wardany

Hongcheng Wang

David C Jarmon

Ziyou Xiong

Jean Yamanis

Foster Philip Lamm

Kurt J Sobanski

Meggan Harris

Matthew B Kennedy

James P Allore

Abhijit Chakraborty

Stephen A Paul

Mark A Sillence

Curtis Cowan

An assembly for an aircraft propulsion system includes a propulsor and an imaging assembly. The propulsor includes a propulsor disk, a plurality of propulsor blades, and a nose cone. The plurality of propulsor blades are circumferentially distributed about the propulsor disk. Each propulsor blade of the plurality of propulsor blades extends radially between and to a root end and a tip end. The root end is disposed at the propulsor disk. The propulsor disk and the plurality of propulsor blades are configured to rotate about the rotational axis. The nose cone is disposed axially adjacent the propulsor disk. The imaging assembly includes an imaging device disposed on the nose cone. The imaging device includes a camera. The camera is configured to capture image data of each propulsor blade of the plurality of propulsor blades as the plurality of propulsor blades rotate about the rotational axis.

Propulsor blade imaging assembly method for an aircraft propulsion system

An assembly for an aircraft propulsion system includes a propulsor section and an imaging device. The propulsor section includes a propulsor and a structural body. The propulsor includes a plurality of propulsor blades. The structural body forms an outer air flow surface forming a portion of an air flow path through the propulsor section. The imaging device includes a housing and a camera. The housing includes a housing body and a cover. The housing body is mounted in the structural body. The housing body forms a cavity and an opening of the cavity. The cover is pivotable between a stowed position and a deployed position. The camera is disposed in the cavity with the cover positioned in the stowed position. The camera is configured to capture image data of each propulsor blade of the plurality of propulsor blades with the cover positioned in the deployed position.

Propulsor blade imaging assembly for an aircraft propulsion system

An inspection system for rotating fan rotor blades is provided that includes a plurality of cameras and light sources and a system controller. The cameras are controllable to capture an image of a leading edge of a fan rotor blade and produce signals representative of the captured image. Each respective camera is mounted with an inlet guide vane disposed forward of the fan rotor blade stage. The light sources are each associated with a respective camera. The system controller is in communication with the cameras, the light sources, and a non-transitory memory storing instructions. The instructions when executed cause the system controller to: control the light sources to selectively illuminate the fan rotor blades, and control the cameras to image respective fan rotor blades and produce signals representative thereof, and provide inspection information representative of the leading edge of respective fan rotor blades.

Rotor blade inspection system

In accordance with at least one aspect of this disclosure, a transition structure for a heat exchanger can include a body defining a dome cavity. The dome cavity can be configured to transition flow between at least one first channel and a plurality of second channels having a different number than the at least one first channel.

Heat exchanger header structures

A header for a high-pressure heat exchanger includes a first high-pressure transition section with inlets for multiple first high-pressure flow channels that are spaced from one another in a radial direction and collectively arranged in a substantially circular shape. The inlets for the multiple first high-pressure flow channels on a radially outer edge of the first high-pressure transition section are spaced further apart in a circumferential direction from adjacent inlets of the multiple first high-pressure flow channels than radially inward inlets are spaced from adjacent radially inward inlets of the multiple first high-pressure flow channels. The header also includes multiple first high-pressure flow channels extending from the first high-pressure transition section to a second-high pressure transition section that is configured to divide each of the multiple first high-pressure flow channels into at least two first high-pressure sub-flow channels.

Header for high-pressure heat exchanger

A header for a high-pressure heat exchanger includes a first high-pressure transition section with inlets for multiple first high-pressure flow channels that are spaced from one another in a radial direction and collectively arranged in a substantially circular shape. The inlets for the multiple first high-pressure flow channels on a radially outer edge of the first high-pressure transition section are spaced further apart in a circumferential direction from adjacent inlets of the multiple first high-pressure flow channels than radially inward inlets are spaced from adjacent radially inward inlets of the multiple first high-pressure flow channels. The header also includes multiple first high-pressure flow channels extending from the first high-pressure transition section to a second-high pressure transition section that is configured to divide each of the multiple first high-pressure flow channels into at least two first high-pressure sub-flow channels. Each flow channel of the multiple first high-pressure flow channels and each sub-flow channel of the first high-pressure sub-flow channels have a round cross-sectional shape.

An airfoil includes an airfoil section that has an airfoil wall that surrounds a cavity. The airfoil wall includes an exterior monolithic ceramic shell and an interior CMC liner that has CMC plies. An outermost ply of the CMC plies forms tabs that are raised from an underlying ply so as to define a slot. The exterior monolithic ceramic shell includes an underlapping shell piece and an overlapping shell piece. The underlapping shell piece has a portion disposed in the slot and bonded with the tabs. The overlapping shell piece extends over the tabs and is bonded to the tabs. There are channels bounded by adjacent ones of the tabs, the underlapping shell piece, and the overlapping shell piece. Channel orifices through the CMC liner connect the cavity and the channels.

Airfoil with CMC liner and multi-piece monolithic ceramic shell

An airfoil includes an airfoil section that has an airfoil wall that surrounds a cavity. The airfoil wall includes a first wall section comprised of a monolithic ceramic shell, a second wall section comprised of a CMC liner that is bonded along an interface to an interior side of the monolithic ceramic shell, and a ceramic barrier coating that is bonded to an exterior side of the monolithic ceramic shell. The airfoil wall includes at least one of: inter-section cooling channels that extend along the interface and are bounded by the monolithic ceramic shell and the CMC liner, or intra-section cooling channels that extend within the CMC liner.

Airfoil having internally cooled wall with liner and shell

An additive manufacturing system includes an additive manufacturing (AM) device, a first sensor device, and a compute device. The AM device is configured to form a bulk component in a layer-by-layer manner, by at least iteratively depositing a first layer of raw material onto a working surface in a deposition chamber, consolidating the initial layer into an initial additive portion of the bulk component, then forming subsequent additive portions of the bulk component by depositing and consolidating a subsequent plurality of layers of the raw material onto the first additive portion. The first sensor device is configured to measure an actual composition of at least one first byproduct portion formed upon consolidation of one of the first or subsequent layers of raw material in the deposition chamber. The compute device includes a processor and a memory, and is communicatively coupled to the additive manufacturing device and first sensor device. The additive manufacturing device and compute device provide an in situ sensor analysis of the component while in a formation state during a build process by comparing an actual composition of the at least one first byproduct portion to an expected composition range stored in the memory.

Apparatus and method for controlling tolerance of compositions during additive manufacturing

An electromechanical system for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine, and an electrical motor located at a second side of the firewall and configured to drive the mechanical component. The electrical motor mechanically connected to the mechanical component through a firewall opening in the firewall, the first side having a higher operating temperature than the second side. An electrical connection extends between the mechanical component and the electrical motor via the same firewall opening.

Electrical and mechanical connections through firewall

A method of structural masking for progressive health monitoring of a structural component includes receiving a current image of the structural component. A processor aligns the current image and a reference image of the structural component. The processor performs a structure estimation on the current image and the reference image to produce a current structure estimate image and a reference structure estimate image. The processor generates a structural mask from the reference structure estimate image. The processor masks the current structure estimate image with the structural mask to identify one or more health monitoring analysis regions including a potential defect or damaged area appearing in the masked current structure estimate image that does not appear in the reference structure estimate image.

Structural masking for progressive health monitoring

A method of fabricating a circuit includes bonding an electrically conductive layer to a carrier film using an adhesive selected from acrylic polymer and silicone polymer, removing selected portions of the electrically conductive layer from the carrier film to provide a circuit arrangement, and transferring the circuit arrangement from the carrier film to a substrate.

Transfer film and method for fabricating a circuit

A nozzle system includes a multitude of circumferentially distributed divergent seals that circumscribe an engine centerline. Each divergent seal includes a multiple of divergent seal intakes adjacent to a joint structure to receive cooling airflow. Each divergent seal body is manufactured of a metallic hot sheet inner skin and a metallic cold sheet outer skin. The skins form a multiple of longitudinal channels which communicate with a multiple of edge channels formed within the first longitudinal side and the second longitudinal side of each divergent seal. The multiple of edge channels are located transverse to the longitudinal axis and are raked aft to facilitate cooling of the gas path surface of each divergent seal and adjacent divergent flaps.

Convergent divergent nozzle with edge cooled divergent seals

An electrical power generation system incorporates thermoelectric devices (TE Devices) for electrical power generation adjacent a flow path heat exchanger (HEX) adjacent to a vehicle flowpath structure such as a scramjet flow path to take advantage of the waste heat, high thermal gradients, and available, unused volume. A thermally conductive material communicates thermal energy from a vehicle external skin structure to the TE Device while a thermally conductive compliant material allows the TE Device to 'float' with minimal mechanical stress.

Growing community of inventors

Colchester, CT, United States of America

Paul Attridge