Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A method of inspecting blades of a gas turbine engine for abnormalities includes projecting light from a light source into an illumination area; utilizing a sensor to record data of at least one reflection of the projected light from a blade that is part of a gas turbine engine and is disposed in the illumination area; determining, based on the recorded data, whether the blade is abnormal; and based on the determining indicating that the blade is abnormal, providing a blade abnormality notification. A gas turbine engine is also disclosed.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A method of inspecting blades of a gas turbine engine for abnormalities includes projecting light from a light source into an illumination area; utilizing a sensor to record data of at least one reflection of the projected light from a blade that is part of a gas turbine engine and is disposed in the illumination area; determining, based on the recorded data, whether the blade is abnormal; and based on the determining indicating that the blade is abnormal, providing a blade abnormality notification. A gas turbine engine is also disclosed.