Patents by Inventor David L. Lincoln
David L. Lincoln has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20250110095Abstract: An aircraft sensing system includes a power and communications module, a sensor module in optical communication with the power and communications module, the sensor module being disposed in an at least partially enclosed space within the aircraft, and at least one gas sensor in communication with the sensor module, the at least one gas sensor being disposed in the at least partially enclosed space. The at least one gas sensor is configured to sense at least one flammable gas species or non-flammable gas species, and the sensor module and the at least one gas sensor are galvanically isolated from the power and communications module.Type: ApplicationFiled: October 3, 2023Publication date: April 3, 2025Inventors: David L. Lincoln, Joseph V. Mantese, Tianli Zhu, Changmin Cao, Michael T. Gorski, Christopher C. Shovlin
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Publication number: 20250075631Abstract: 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.Type: ApplicationFiled: November 18, 2024Publication date: March 6, 2025Inventors: Scott Goyette, Gregory S. Hagen, Zaffir A. Chaudhry, Paul Attridge, Janet Shaw, David L. Lincoln, Jeffrey P. King
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Publication number: 20250067194Abstract: 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.Type: ApplicationFiled: August 25, 2023Publication date: February 27, 2025Inventors: Jeremiah C. Lee, David L. Lincoln, Scott Goyette, Zaffir A. Chaudhry, Danbing Seto
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Publication number: 20250067899Abstract: A system includes an optical ice detection (OID) sub-system optically coupled to light collection optics. A water vapor differential absorption LIDAR (WV-DIAL) sub-system is optically coupled to the OID laser source or light collection optics. The OID sub-system and the WV-DIAL sub-system share at least a portion of an optical path of the light source or through the light collection optics. The OID sub-system, the WV-DIAL sub-system, and the illumination and light collection optics can all be aboard an aircraft. A method includes using a set of illumination and light collection optics aboard an aircraft to obtain data indicative of optical ice detection (OID) and water vapor differential absorption LIDAR (WV-DIAL), e.g. to detect contrail forming conditions for the aircraft and/or predict persistence of contrails from the aircraft.Type: ApplicationFiled: August 21, 2023Publication date: February 27, 2025Applicant: Rosemount Aerospace Inc.Inventors: David L. Lincoln, Mark D. Ray, Darren G. Jackson, Kaare Josef Anderson, Jose-Rodrigo Castillo-Garza, Michael T. Gorski
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Patent number: 12196658Abstract: 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.Type: GrantFiled: November 18, 2021Date of Patent: January 14, 2025Assignee: RTX CORPORATIONInventors: David L. Lincoln, Xuemei Wang, Alek Gavrilovski, Michael T. Gorski
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Patent number: 12146416Abstract: 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.Type: GrantFiled: April 18, 2023Date of Patent: November 19, 2024Assignee: RTX CorporationInventors: Scott Goyette, Gregory S. Hagen, Zaffir A. Chaudhry, Paul Attridge, Janet Shaw, David L. Lincoln, Jeffrey P. King
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Publication number: 20240352938Abstract: 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.Type: ApplicationFiled: April 18, 2023Publication date: October 24, 2024Inventors: Scott Goyette, Janet Shaw, Gregory S. Hagen, Paul Attridge, Zaffir A. Chaudhry, David L. Lincoln, Jeffrey P. King
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Publication number: 20240352868Abstract: 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.Type: ApplicationFiled: April 21, 2023Publication date: October 24, 2024Inventors: Scott Goyette, Janet Shaw, Gregory S. Hagen, David L. Lincoln, Zaffir A. Chaudhry, Jeremiah C. Lee, Danbing Seto
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Publication number: 20240352867Abstract: 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.Type: ApplicationFiled: April 18, 2023Publication date: October 24, 2024Inventors: Scott Goyette, Gregory S. Hagen, Zaffir A. Chaudhry, Paul Attridge, Janet Shaw, David L. Lincoln, Jeffrey P. King
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Publication number: 20240352869Abstract: An assembly for an aircraft propulsion system includes a propulsor section for the aircraft propulsion system, a plurality of imaging devices, and a controller. The propulsor section includes a propulsor. The propulsor includes a plurality of propulsor blades. The plurality of imaging devices are mounted in the propulsor section. Each imaging device includes a camera. 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 camera of each imaging device of the plurality of imaging devices 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 from the camera of two or more imaging devices of the plurality of imaging devices.Type: ApplicationFiled: April 21, 2023Publication date: October 24, 2024Inventors: Scott Goyette, Janet Shaw, Gregory S. Hagen, David L. Lincoln, Zaffir A. Chaudhry, Danbing Seto
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Publication number: 20240353737Abstract: 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.Type: ApplicationFiled: April 18, 2023Publication date: October 24, 2024Inventors: Gregory S. Hagen, Paul Attridge, David L. Lincoln, Zaffir A. Chaudhry, Scott Goyette, Janet Shaw, Jeffrey P. King
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Publication number: 20240319106Abstract: 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 IRS and frequency fRS with a reference signal of amplitude ILS and frequency fRS; analyzing, using the controller, an amplitude of the mixed signal ?{square root over (ILSIRS)}, and frequency of the mixed signal, fRS?fLS; and classifying, using the controller, a particle position, a velocity, and electromagnetic characteristic of the particle based on the amplitude, ?{square root over (ILSIRS)}, and frequency, fRS?fLS, of the mixed signal.Type: ApplicationFiled: May 20, 2024Publication date: September 26, 2024Applicant: RTX CorporationInventors: Jose-Rodrigo Castillo-Garza, David L. Lincoln
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Publication number: 20240271784Abstract: 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.Type: ApplicationFiled: February 15, 2023Publication date: August 15, 2024Inventors: Orin G. Avidane, Andre M. Ajami, Coy Bruce Wood, Joseph V. Mantese, David L. Lincoln, Stephen K. Kramer, Ramesh Rajagopalan
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Publication number: 20240264092Abstract: Methods of inspecting fan blades of a gas turbine engine for abnormalities are disclosed. One method utilizes a neural network to determine whether a photographic image of at least one fan blade depicts an abnormality of the at least one fan blade. Another method uses a dimensional reduction technique on one or more first photographic images that depict at least one first fan blade to obtain basis vectors, utilizes the basis vectors to obtain a reconstructed version of a second photographic image that depicts at least one second fan blade, and determines whether the at least one second fan blade includes an abnormality based on a difference between the second photographic image and the reconstructed version of the second photographic image. Another method determines whether a fan blade includes an abnormality based on contrast differences between adjacent areas of an image.Type: ApplicationFiled: February 3, 2023Publication date: August 8, 2024Inventors: Jeremiah C. Lee, Paul Attridge, Zaffir A. Chaudhry, Scott Goyette, Gregory S. Hagen, David L. Lincoln, Kin Gwn Lore
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Patent number: 12055055Abstract: 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.Type: GrantFiled: April 18, 2023Date of Patent: August 6, 2024Assignee: RTX CorporationInventors: Scott Goyette, Janet Shaw, Gregory S. Hagen, David L. Lincoln, Zaffir A. Chaudhry, Jeffrey P. King
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Patent number: 12055053Abstract: 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.Type: GrantFiled: April 18, 2023Date of Patent: August 6, 2024Assignee: RTX CorporationInventors: Scott Goyette, Janet Shaw, Gregory S. Hagen, Zaffir A. Chaudhry, David L. Lincoln, Jeffrey P. King
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Patent number: 12019028Abstract: 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 IRS and frequency fRS with a reference signal of amplitude ILS and frequency fRS; analyzing, using the controller, an amplitude of the mixed signal ?{square root over (ILSIRS)}, and frequency of the mixed signal, fRS?fLS; and classifying, using the controller, a particle position, a velocity, and electromagnetic characteristic of the particle based on the amplitude, ?{square root over (ILSIRS)}, and frequency, fRS?fLS of the mixed signal.Type: GrantFiled: July 23, 2021Date of Patent: June 25, 2024Assignee: RTX CorporationInventors: Jose-Rodrigo Castillo-Garza, David L. Lincoln
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Publication number: 20240167426Abstract: A system includes a first sensor positioned to sense presence of a contrail in a first volume, wherein the first volume at least partially overlaps an expected volume of a contrail proximate an aircraft. A second sensor is positioned to sense a background reference in a second volume, where the second volume does not overlap the expected volume of a contrail proximate an aircraft. A controller is operatively connected to the first and second sensors. The controller includes machine readable instructions configured to cause the controller to utilize data input from both the first and second volumes to determine if a contrail is present from the aircraft. A system includes machine readable instructions configured to cause the controller to predict persistence of contrails on an intended route through the volume of airspace and to determine an improved route and/or propulsion operation to reduce contrail formation and persistence relative to the intended route.Type: ApplicationFiled: November 21, 2022Publication date: May 23, 2024Applicant: Rosemount Aerospace Inc.Inventors: David L. Lincoln, Longke Wang, Jordan A. Snyder, Rodrigo Castillo-Garza, Sean C. Emerson, Darren G. Jackson, Mark D. Ray, Kaare Josef Anderson
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Patent number: 11988602Abstract: An example SPR detection system includes a first prism having a first surface adjacent to a first metal layer exposed to a sample gas, and a second prism having a second surface adjacent to a second metal layer exposed to a reference gas. At least one light source is configured to provide respective beams to the first and second surfaces, where each of the beams causes SPR of a respective one of the metal layers. At least one photodetector is configured to measure a reflection property of reflections of the respective beams from the metal layers during the SPR. A controller is configured to determine whether a target gas is present in the sample gas based on a known composition of the reference gas and at least one of an electrical property of the first and second metal layers during the SPR and the reflection property of the metal layers.Type: GrantFiled: May 10, 2019Date of Patent: May 21, 2024Assignee: Carrier CorporationInventors: David L. Lincoln, Michael J. Birnkrant, Jose-Rodrigo Castillo-Garza, Marcin Piech, Catherine Thibaud, Michael J. Giering, Kishore K. Reddy, Vivek Venugopalan
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Patent number: 11879840Abstract: A method of calibrating an optical detector includes installing a calibration system within at least one sensing volume of the optical detector, filling a chamber of the calibration system with a material to achieve a known obscuration, and measuring an obscuration of the material within the chamber.Type: GrantFiled: November 27, 2019Date of Patent: January 23, 2024Assignee: CARRIER CORPORATIONInventors: Urcan Guler, David L. Lincoln