Method and system for detecting the ingestion of an object by an aircraft turbine engine during a mission

• US 8,528,317 B2
• Filed: 08/20/2010
• Issued: 09/10/2013
• Est. Priority Date: 08/21/2009
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Gerez, Valerio, Mazur, Claude Alain
• Primary Examiner(s): Gartenberg, Ehud
• Assistant Examiner(s): Subramanian, Karthik
• Application Number:
  US12/859,806
• Publication Number:
  US 20110041474A1
• Time in Patent Office: 1,117 Days
• Field of Search: 60/390.91, 60/390.92, 602/23, 602/261, 244/53.B, 553/06, 415/121.1, 415/121.2, 250330-334, 250/338.1, 250/338.4, 250/208.2, 250/214.1, 250/214.R, 250/206, 250/201.1
• US Class Current: 60/223
• CPC Class Codes: B64D 2033/022 comprising bird or foreign object protections
• CPC Class Codes: B64D 2045/0095 Devices specially adapted to avoid bird strike
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 21/04 responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
• CPC Class Codes: F02C 7/05 having provisions for obviating the penetration of damaging objects or particles
• CPC Class Codes: F02C 7/057 Control or regulation conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16
• CPC Class Codes: G07C 5/0891 Video recorder in combination with video camera

Abstract

A method and a system for detecting the ingestion of an object by an aircraft turbine engine during a mission is disclosed. The method includes: acquiring during the mission digital images of the operating fan of the turbine engine, these images being acquired at an acquisition frequency proportional to the speed of rotation of the fan and to the number of blades of the fan; identifying the different phases of the mission of the aircraft for each phase of the mission; comparing the images of the fan with at least one reference image corresponding to sound operation of the fan; and, if necessary, identifying each abnormal image of the fan which differs from the corresponding reference image, the identification of an abnormal image of the fan corresponding to the crossing of an alert level for detecting the ingestion of an object by the turbine engine.

Claims

1. A method for detecting the ingestion of an object by an aircraft turbine engine during flight, the method comprising:

installing a camera inside a nacelle of said turbine engine, said camera being aimed at a fan of said engine;

connecting said camera to a computer on board of said aircraft, said computer being programmed to identify phases of flight of said aircraft and having on its resident memory a database of fan reference images characteristic to normal operation of said fan in each of said flight phases of said aircraft;

acquiring, with said camera during flight, digital images of said fan, said images being acquired at an acquisition frequency proportional to the speed of rotation and number of blades of said fan;

transmitting said images to said computer;

comparing, using said computer, said acquired digital images with fan reference images corresponding to the same flight phases as said acquired images;

selecting abnormal acquired images which differ from corresponding compared reference images; and

identifying, based on said selecting of abnormal acquired images, an abnormal operation fan condition corresponding to an alert level caused by ingestion of an object by said turbine engine.

2. The method according to claim 1, further comprising:

analyzing the abnormal acquired images to check on the fan for a plurality of criteria for viewing the ingestion of the object by the turbine engine.

3. The method according to claim 2, wherein the plurality of criteria comprises:

a set of criteria related to the viewing of the object in the turbine engine upstream from the fan;

a set of criteria related to the viewing of a phenomenon of deformation of one or more blades of the fan; and

a set of criteria related to the viewing of the extent and of the attenuation over time of the deformation phenomenon of the blades of the fan.

4. The method according to claim 2, further comprising:

establishing a diagnosis depending on the checked criteria.

5. The method according to claim 4, wherein the established diagnosis belongs to the following list:

diagnosis of the presence in the turbine engine upstream from the fan of one or more objects for which the size and velocity are estimated;

diagnosis of the presence of one or more blades of the fan in free and damped oscillations;

diagnosis of the presence of one or more blades of the fan in forced oscillations.

6. The method according to claim 4, further comprising:

emitting an alert of ingestion by the turbine engine of one or more objects.

7. The method according to claim 6, wherein the emitted alert belongs to the following list:

alert of ingestion by the turbine engine of an object, the size, the mass and the density of which are identified;

alert of ingestion by the turbine engine of an object of small size and high density;

alert of ingestion by the turbine engine of an object of small mass and low density.

8. The method according to claim 6, wherein the analyzing the abnormal acquired images, establishing a diagnosis, and emitting an alert of ingestion steps are carried out on a deferred basis.

9. The method according to claim 1, wherein the acquiring, transmitting, comparing, selecting, and identifying steps are carried out continuously during the mission.

10. The method according to claim 1, wherein the frequency for acquiring digital images of the operating fan of the turbine engine is:

11. The method according to claim 1, wherein said phases of flight of said aircraft are identified based on the speed of rotation of the fan and an altitude of the aircraft.

12. The method according to claim 1, wherein said comparing includes superposition of said acquired digital images on said fan reference images corresponding to the same flight phases as said acquired images.

13. A system for detecting the ingestion of an object by an aircraft turbine engine during flight, the system comprising:

a camera installed inside a nacelle of said turbine engine and aimed at a fan of said engine; and

a computer on board of said aircraft and connected to said camera, said computer being programmed to identify phases of flight of said aircraft and having on its resident memory a database of fan reference images characteristic to normal operation of said fan in each of said flight phases of said aircraft,

wherein said computer is programmed to;

acquire, with said camera during flight, digital images of said fan, said images being acquired at an acquisition frequency proportional to the speed of rotation and number of blades of said fan;

compare said acquired digital images with fan reference images corresponding to the same flight phases as said acquired images;

select abnormal acquired images which differ from corresponding compared reference images; and

identify, based on said selecting of abnormal acquired images, an abnormal operation fan condition corresponding to an alert level caused by ingestion of an object by said turbine engine.

14. The system according to claim 13, wherein the camera is a digital camera.

15. A turbine engine comprising a detection system according to claim 13.