Inspection device for aircraft engine

• US 5,191,412 A
• Filed: 10/24/1991
• Issued: 03/02/1993
• Est. Priority Date: 10/24/1990
• Status: Expired due to Fees

• Current Assignee: Gec-Ferranti Defence Systems Limited
• Original Assignee: Gec-Ferranti Defence Systems Limited
• Inventors: Thomson, Richard C.
• Primary Examiner(s): Britton, Howard W.
• Application Number:
  US07/782,307
• Time in Patent Office: 495 Days
• Field of Search: 358/93, 358/108, 358/106, 250/213 VT
• US Class Current: 348/148
• CPC Class Codes: B64D 47/08 Arrangements of cameras
• CPC Class Codes: G01P 3/40 using stroboscopic means

Abstract

To permit in-flight inspection of an aircraft engine, an imager views the front of the engine, and includes an image intensifier which is gated on and off at the engine speed. Small variations about the engine speed may be used to sweep all the blades into the field of view of an imager which does not view the whole of the front of the engine.

Claims

1. An imager which is adapted to be mounted on an aircraft for viewing the front of an aircraft engine in flight, which comprises:

means for forming an image of at least a portion of the front of the aircraft engine;

means for intensifying the formed image; and

means for gating the image intensifying means to enable rotating engine parts to be viewed through the front of the aircraft engine as if stationary or rotating slowly.

2. An imager as claimed in claim 1, wherein the aircraft engine has a plurality of blades and which further comprises means for varying the gating speed of the image intensifying means to enable all of the blades of the aircraft engine to sweep through the field of view of the imager.

3. An aircraft including in combination therewith, an imager as claimed in claim 1.

4. An imager as claimed in claim 1, in which the gating means is arranged to switch an accelerating potential for a microchannel plate of the image intensifying means on and off.

5. An imager as claimed in claim 4, wherein the image intensifying means further comprises:

a faceplate upon which an image of at least a portion of the front of the aircraft engine is initially formed; and

photocathode means for receiving the image from the faceplate and producing the image on the microchannel plate.

6. An imager as claimed in claim 5, wherein the faceplate comprises a plurality of optical fibers arranged axially so that the image on the faceplate is imaged directly onto the photocathode means.

7. An imager as claimed in claim 5, wherein the microchannel plate amplifies the image received from the photocathode means.

8. An imager as claimed in claim 7, which further comprises substrate means having an imaging layer for receiving the image from the microchannel plate.

9. An imager as claimed in claim 8, wherein the photocathode means and the microchannel plate are disposed in an evacuated region between the faceplate and the substrate means.

10. An imager as claimed in claim 9, wherein the faceplate comprises a plurality of optical fibers arranged axially so that the image on the faceplate is imaged directly onto the photocathode means.

11. An aircraft including in combination therewith, an imager as recited in claim 10.