Propulsor blade imaging assembly for an aircraft propulsion system

1. An assembly for an aircraft propulsion system, the assembly comprising:

a propulsor including a propulsor disk, a plurality of propulsor blades, and a nose cone, the propulsor disk extending circumferentially about a rotational axis, the plurality of propulsor blades circumferentially distributed about the propulsor disk, each propulsor blade of the plurality of propulsor blades extending radially between and to a root end and a tip end, the root end disposed at the propulsor disk, the propulsor disk and the plurality of propulsor blades configured to rotate about the rotational axis, the nose cone disposed axially adjacent the propulsor disk; and

an imaging assembly including an imaging device disposed on the nose cone, wherein the nose cone is rotationally fixed relative to the rotational axis, the imaging device including a camera, the camera 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.

2. The assembly of claim 1 , wherein the nose cone extends axially between and to a leading end and a trailing end, the trailing end positioned at the propulsor disk, the nose cone forming an exterior surface extending between and to the leading end and the trailing end, the camera positioned at the exterior surface.

3. The assembly of claim 2 , wherein the nose cone is positioned axially between and spaced from the leading end and the trailing end.

4. The assembly of claim 3 , wherein the exterior surface diverges in a radial direction from the leading end to the trailing end, and divergence of the exterior surface axially between the imaging device and the trailing end is linear.

5. The assembly of claim 1 , wherein the camera is configured to capture the image data for a portion of a radial span of each propulsor blade of the plurality of propulsor blades.

6. The assembly of claim 5 , wherein the portion is at the root end.

7. The assembly of claim 5 , wherein the imaging device includes a plurality of cameras, the plurality of cameras including the camera, and each camera of the plurality of cameras is configured to capture the image data for a different portion of the radial span relative to each other camera of the plurality of cameras.

8. The assembly of claim 1 , wherein the imaging assembly further includes a controller connected in signal communication with the imaging device, the controller including a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to:

initiate the capture of the image data by controlling the camera to capture the image data based on a measured rotation speed of the propulsor about the rotational axis.

9. The assembly of claim 8 , wherein the instructions, when executed by the processor, further cause the processor to initiate the capture of the image data by controlling the camera to capture the image data based on the measured rotation speed when the measured rotation speed is less than or equal to a predetermined rotation speed threshold value.

10. The assembly of claim 9 , wherein the predetermined rotation speed threshold value is greater than zero (0) RPM.

11. The assembly of claim 8 , wherein the instructions, when executed by the processor, further cause the processor to identify a presence or an absence of damage for each propulsor blade of the plurality of propulsor blades using the image data.

12. The assembly of claim 11 , wherein the instructions, when executed by the processor, further cause the processor to transmit to an offboard system an indication of identification of the presence of damage to at least one propulsor blade of the plurality of propulsor blades.

13. A propulsion system for an aircraft, the propulsion system comprising:

a gas turbine engine comprising a rotational assembly and a propulsor, the rotational assembly including a shaft rotatable about a rotational axis, the propulsor including a plurality of propulsor blades and a nose cone, the plurality of propulsor blades configured to be driven by the shaft for rotation about the rotational axis, the nose cone rotationally fixed relative to the rotational axis; and

an imaging assembly including an imaging device disposed on the nose cone, the imaging device including a camera, the camera configured to capture image data of each propulsor blade of the plurality of propulsor blades as the propulsor blades rotate about the rotational axis.

14. The propulsion system of claim 13 , wherein the imaging assembly further includes a controller connected in signal communication with the imaging device, the controller including a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to:

initiate the capture of the image data by controlling the camera to capture the image data based on a rotation speed of the shaft about the rotational axis.

15. The propulsion system of claim 14 , wherein the imaging assembly further includes a shaft speed sensor configured to measure the rotation speed of the shaft, generate an output signal proportional to the measured rotation speed, and transmit the output signal to the controller.

16. The propulsion system of claim 14 , wherein the gas turbine engine further includes a generator, the generator configured to generate and direct electrical power to the imaging assembly.