Carrier Corporation

Rtx Corporation

Kidde Technologies Incorporated

Raytheon Technologies Corporation

Kidde Fire Protection Limited

Hamilton Sundstrand Corporation

Otis Elevator Company

Rosemount Aerospace Limited

David L Lincoln

Michael J Birnkrant

Peter R Harris

Jennifer M Alexander

Zaffir A Chaudhry

Marcin Piech

Scott Goyette

Gregory S Hagen

Michael T Gorski

Janet Shaw

Jeffrey P King

Jose-Rodrigo Castillo-Garza

Wayde R Schmidt

Paul Attridge

Slade R Culp

Urcan Guler

Xuemei Wang

Alan Matthew Finn

Coy Bruce Wood

Jie Xi

Arthur Blanc

Danbing Seto

Vivek Venugopalan

Joseph Anthony Vidulich

Jeremiah C Lee

Devis Dishnica

Kyle Aaron

Rick Wolf

Joseph V Mantese

Zissis A Dardas

Stephen Karl Kramer

Jonathan Gilson

Hui Fang

Jun Hou

Catherine Thibaud

Michael J Giering

Dustin D Caldwell

Kishore K Reddy

Ramesh Rajagopalan

Andre M Ajami

Kenneth Bell

Alek Gavrilovski

Jagadeswara Reddy Karra

Orin G Avidane

An in-situ system for a gas turbine engine blade inspection including a sensor system configured to capture images of a forward surface of at least one gas turbine engine blade; a processor coupled to the sensor system, the processor configured to determine damage to the at least one gas turbine engine blade based on video analytics; and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored therein that, in response to execution by the processor, cause the processor to perform operations comprising receiving, by the processor, data for the forward surface of at least one gas turbine engine blade from the sensor system; determining, by the processor, a rotational speed of a fan; and determining, by the processor, a fan synchronization.

Optical in-situ inspection system

A method for manufacturing a detector for sensing, detecting and monitoring environmental hazards and conditions, said method including the printing of an electronic circuit on at least a first side of a flexible, printable substrate; coupling at least two electronic components to the electronic circuit on at least the first side of the flexible, printable substrate; thermoforming the flexible, printable substrate to form at least one detection zone from: (i) at least one side of the flexible, printable substrate having an angle for emitting one of a light or a signal from at least one electronic component; and (ii); at least one side of the flexible, printable substrate having an angle for receiving one of a light or a signal by at least one electronic component; and encapsulating the flexible, printable substrate, forming a detector.

Method for manufacturing a detector

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, an imaging device, a plurality of light sources, and a controller. The propulsor section includes a propulsor. The propulsor includes a plurality of propulsor blades. The imaging device is disposed in the propulsor section. The imaging device includes a camera. The plurality of light sources are disposed in the propulsor section. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to: control the plurality of light sources to direct light to the plurality of propulsor blades, control the camera to capture image data of each propulsor blade of the plurality of propulsor blades, and identify a presence or an absence of damage for each propulsor blade of the plurality of propulsor blades using the image data.

Propulsor blade imaging assembly 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.

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

A combustion assembly for a gas turbine engine includes a combustor, a monochromator, and a photodetector assembly. The combustor forms a combustion chamber. The monochromator is disposed outside the combustion chamber. The monochromator is configured to receive an optical input from the combustion chamber and direct an optical output. The optical input has a range of light wavelengths. The optical output has a subset of the range of light wavelengths. The photodetector assembly is disposed outside the combustion chamber. The photodetector assembly is configured to receive the optical output from the monochromator and generate an output signal representative of one or more optical characteristics of the optical output.

Optical detection system for a gas turbine engine combustion assembly

A method of foreign object debris discrimination includes illuminating a particle located within a sensing volume with a modulated electromagnetic radiation pulse emitted from a source; receiving one or more electromagnetic radiation return signals that have been scattered by the particle illuminated by the modulated electromagnetic radiation pulse at a detector; mixing, using a controller, the electromagnetic radiation return signal of amplitude Iand frequency fwith a reference signal of amplitude Iand frequency f; analyzing, using the controller, an amplitude of the mixed signal √{square root over (II)}, and frequency of the mixed signal, f−f; and classifying, using the controller, a particle position, a velocity, and electromagnetic characteristic of the particle based on the amplitude, √{square root over (II)}, and frequency, f−f, of the mixed signal.

Foreign object debris discrimination with modulated laser light

A detector assembly for a duct of a heating ventilation and air conditioning system includes an outer housing having at least one through hole formed therein, an inner sampling support receivable within a hollow interior of the outer housing, and at least one detector mounted to the inner sampling support. The at least one detector is axially aligned with the at least one through hole when the inner sampling support is installed within the hollow interior of the outer housing. The at least one detector is operable to sample air within the duct to detect a hazardous condition.

Chamberless wide area duct smoke detector

A photoacoustic detection system includes a detector that has a chamber, a pulsed light source, piezoelectric tuning forks, and a photosensor. The chamber has an inlet and an outlet for flow of an analyte. The pulsed light source is adjacent the chamber and is operable to emit a light beam along a path through the chamber. The tuning forks are arranged along the path, and each of the tuning forks is operable to emit first sensor signals. The photosensor is arranged along the path and is operable to emit second sensor signals. A controller is connected to receive the first and second sensor signals. The controller is configured to determine whether a target species is present in the analyte based on the first sensor signals and determine whether the target species is present in the analyte based on the second sensor signals.

Photoacoustic detection system with differential amplifier for determing target species presence and triggering fault

An optical particulate detection system for an aircraft is provided. The optical particulate detection system includes an optical particulate detector and a controller. The optical particulate detector includes at least two optical sources and at least one optical sensor distributed in series with respect to a flow path of a component surface of the aircraft. The controller is configured to interface with the optical particulate detector, monitor the at least one optical sensor, and characterize one or more particles of foreign object debris based on a pulse width and two or more scattering ratios determined with respect to light emitted from the at least two optical sources.

Optical particulate detection for an aircraft

An inspection system for fan rotor blades in a gas turbine engine is provided. The gas turbine engine has a sensor that provides a fan rotor stage speed signal. The system includes a plurality of cameras and light sources and a system controller. The cameras are controllable to image a leading edge of a fan rotor blade. Each respective camera and light source is mounted with a static structure disposed forward of the fan rotor blade stage. The system controller is in communication with stored instructions that when executed cause the system controller to monitor the speed of the fan rotor stage during an engine shutdown; upon the fan rotor stage speed reaching a first value, control the light sources to selectively illuminate the fan rotor blades, and control the cameras to image the fan rotor blades, and provide inspection information using signals representative of the captured images.

An inspection system for rotating fan rotor blades in a gas turbine engine is provided. The system includes a plurality of cameras and lids, and a cleaning system. The cameras are each controllable to capture an image of a leading edge of a fan rotor blade and produce signals representative thereof. Each camera is mounted to a static structure disposed forward of the fan rotor blade stage. The lids are attached to the static structure and is selectively movable between closed and open positions. In the closed position at least one camera is enclosed. In the open position the camera is at least partially exposed and has a field of view of the rotating fan rotor blades. The cleaning system is controllable to selectively produce a body of fluid relative to the at least one camera when the respective lid is in the open position.

A method of foreign object debris discrimination includes illuminating a particle located within a sensing volume with a modulated electromagnetic radiation pulse emitted from a source; receiving one or more electromagnetic radiation return signals that have been scattered by the particle illuminated by the modulated electromagnetic radiation pulse at a detector; mixing, using a controller, the electromagnetic radiation return signal of amplitude Iand frequency fwith a reference signal of amplitude Iand frequency f; analyzing, using the controller, an amplitude of the mixed signal √{square root over (II)}, and frequency of the mixed signal, f−f; and classifying, using the controller, a particle position, a velocity, and electromagnetic characteristic of the particle based on the amplitude, √{square root over (II)}, and frequency, f−fof the mixed signal.

Growing community of inventors

Johnston, RI, United States of America

David L Lincoln