ACOUSTIC DIAGNOSTIC OF FIELDED TURBINE ENGINES

• US 20120330499A1
• Filed: 06/23/2011
• Published: 12/27/2012
• Est. Priority Date: 06/23/2011
• Status: Abandoned Application

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Scheid, Paul Raymond, Geib, Andrew F.
• Application Number:
  US13/167,490
• Publication Number:
  US 20120330499A1
• Time in Patent Office: Days
• US Class Current: 701/33.4
• CPC Class Codes: G01N 2291/2693 Rotor or turbine parts
• CPC Class Codes: G01N 2291/2694 Wings or other aircraft parts
• CPC Class Codes: G01N 29/14 using acoustic emission techniques echo of particles G01N29/046; measuring mechanical vibrations or acoustic waves in solids in general G01H1/00
• CPC Class Codes: G01N 29/4427 with stored values, e.g. threshold values

Abstract

A method for diagnosing faults in an aircraft gas turbine engine comprises gathering an acoustic profile from an on-wing turbine, transmitting the acoustic profile to an analysis system, comparing the acoustic profile with known fault profiles, and scheduling maintenance steps based on whether the acoustic profile matches one or more of the known fault profiles. The known fault profiles are retrieved from a library of the analysis system.

Claims

1. A method for diagnosing faults in an aircraft gas turbine engine, the method comprising:

gathering an acoustic profile from an on-wing turbine;

transmitting the acoustic profile to an analysis system;

comparing the acoustic profile with known fault profiles in a library of the analysis system; and

scheduling maintenance steps based on whether the acoustic profile matches one or more of the known fault profiles.

2. The method of claim 1, further comprising:

scheduling additional diagnostics to be performed if the acoustic profile does not match any of the known fault profiles.

3. The method of claim 2, further comprising:

updating the library with the results of the additional diagnostics.

4. The method of claim 1, wherein scheduling maintenance steps comprises advancing line or heavy maintenance times.

5. The method of claim 1, wherein the acoustic profile is gathered by a plurality of external acoustic sensors arranged about the on-wing turbine.

6. The method of claim 5, wherein the external acoustic sensors are mounted at known intervals on a sensor rig.

7. The method of claim 1, wherein the acoustic profile is gathered by a plurality of on-board acoustic sensors integrated into the gas turbine engine or the aircraft body.

8. A system for diagnosing faults in an aircraft gas turbine engine, the system comprising:

an array of acoustic sensors positioned about an on-wing gas turbine engine;

a data acquisition and transmission unit which collects and transmits sensor signals from the acoustic sensors;

a signal analysis station which receives and processes the sensor signals, the signal analysis station comprising;

a database mapping a plurality of known acoustic signatures to known failure states; and

a processor which compares sensor signals to the known acoustic signatures to produce a diagnosis signal.

9. The system of claim 8, further comprising:

a maintenance scheduler which schedules maintenance times according to diagnosis signal.

10. The system of claim 8, further comprising:

non-acoustic diagnostics used when the diagnosis signal indicates an unknown failure state.

11. The system of claim 10, wherein a failure state diagnosis made by the non-acoustic diagnostics is used to update the database.

12. The system of claim 11, wherein the non-acoustic diagnostics unit is configured to perform boroscopic examination of the gas turbine engine.

13. The system of claim 9, wherein processor also uses pressure, temperature, or debris sensor readings from the gas turbine engine to produce a failure state diagnosis.

14. The system of claim 13, wherein the database maps a plurality of sensor signatures including pressure, temperature, or debris signatures, to known failure rates.

15. The system of claim 8, wherein the sensor signals are broadcast to the signal analysis station via wireless communication.

16. A method for diagnosing faults in an aircraft gas turbine engine, the method comprising:

gathering acoustic data from a plurality of acoustic sensors situated about an on-wing turbine;

extracting a plurality of features from the acoustic data to form an acoustic profile;

comparing the acoustic profile to a plurality of library profiles from a signature library, the library profiles corresponding to known failure or non-failure modes of the gas turbine engine; and

scheduling appropriate maintenance for failure modes corresponding to library profiles matching the acoustic profile.

17. The method of claim 16, further comprising:

reporting an unknown failure mode if the acoustic profile does not match any library profile from the signature library.

18. The method of claim 17, further comprising:

performing non-acoustic diagnostics when an unknown failure mode is reported.

19. The method of claim 18, further comprising:

updating the signature library based upon results of non-acoustic diagnostics.

20. The method of claim 16, wherein the plurality of features is exacted from the acoustic data using a MFCC or CELP algorithm, or a combination of MFCC and CELP algorithms.