Engine status detection with external microphone

• US 20060283190A1
• Filed: 06/16/2005
• Published: 12/21/2006
• Est. Priority Date: 06/16/2005
• Status: Abandoned Application

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Thomassin, Jean, Ficklscherer, Peter, Dooley, Kevin
• Application Number:
  US11/153,451
• Publication Number:
  US 20060283190A1
• Time in Patent Office: Days
• US Class Current: 60/772
• CPC Class Codes: G01M 15/12 by monitoring vibrations
• CPC Class Codes: G01M 15/14 Testing gas-turbine engines or jet-propulsion engines

Abstract

A method of detecting at least one engine condition of a gas turbine engine using a microphone disposed outside a region of the gas turbine engine to be monitored. The method includes receiving a signal produced by the microphone in response to audible frequencies, analyzing the signal to determine at least one signal characteristic representative of the engine condition, and detecting the engine condition based on the signal produced by the microphone.

Claims

1. A method of monitoring at least one engine condition of a gas turbine engine comprising:

mounting a microphone within audible range of a region of the gas turbine engine to be monitored, the microphone being spaced apart from said region;

receiving a signal produced by the microphone in response to sound frequencies generated by fluid flow through the gas turbine engine during operation thereof,

analyzing the signal to identify at least one characteristic representative of the engine condition; and

determining the engine condition based principally on the signal produced by the microphone.

2. The method as defined in claim 1, wherein the step of analyzing includes processing the signal into a form configured for frequency analysis.

3. The method as defined in claim 2, further comprising conducting a time-based frequency analysis of the signal.

4. The method as defined in claim 1, wherein the sound frequencies correspond to internal pressure pulsations of the fluid flow, and the step of analyzing includes identifying a pressure pulsation signature produced by a selected rotating component of the gas turbine engine.

5. The method as defined in claim 4, wherein the rotating component is a compressor which produces a distinct pressure pulsation signature and the engine condition is stall of the compressor, the step of determining the compressor stall comprises identifying a change in the distinct pressure pulsation signature.

6. The method as defined in claim 5, wherein identifying a change in the distinct pressure pulsation signature further comprises identifying a marked increase and subsequent decrease of the pressure oscillating at a frequency corresponding to the compressor.

7. The method as defined in claim 4, further comprising identifying at least two distinct pressure pulsation signatures, each having a different defined frequency range corresponding to one of at least two independent rotating components of the gas turbine engine, such that a component status parameter of said at least two independent rotating components is determinable from the signal.

8. The method as defined in claim 1, further comprising measuring a level of the engine condition detected.

9. The method as defined in claim 8, wherein the engine condition is aerodynamic loading of a compressor of the gas turbine engine, the method further comprising predicting a compressor surge based on the measured level of aerodynamic loading on said compressor.

10. The method as defined in claim 1, wherein the step of mounting further comprising mounting the microphone outside an outer casing of the gas turbine engine.

11. The method as defined in claim 1, wherein the step of determining the engine condition is based solely on the signal produced by the microphone.

12. A method of detecting surge of a compressor in a gas turbine engine comprising:

mounting a microphone in spaced apart relation with a main gas flow path of the compressor, within audible range thereof;

receiving a signal produced by the microphone in response to audible frequencies generated by fluid flow through the compressor during operation of the gas turbine engine;

analyzing the signal to determine at least one characteristic representative of compressor surge; and

detecting compressor surge based on said signal produced by said microphone.

13. The method as defined in claim 12, wherein the step of detecting compressor surge further comprises using solely said signal produced by said microphone.

14. A non-intrusive method of monitoring aerodynamic characteristics of at least one aerodynamic component in a gas turbine engine, the method comprising:

using a microphone spaced apart from a region of the gas turbine engine to be monitored and within audible range of the aerodynamic component therewithin, to produce an electrical output in response to audible frequencies corresponding to pressure pulsations in gas flowing past the aerodynamic component during operation of the gas turbine engine, the audible frequencies defining a noise signature of the aerodynamic component;

conducting a time-based frequency analysis of the electrical output to monitor changes in the noise signature; and

detecting an abnormal aerodynamic characteristic based on the electrical output produced by the microphone.

15. The method as defined in claim 14, wherein the step of detecting the abnormal aerodynamic characteristic is based solely on the electrical output produced by the microphone.

16. A system for detecting at least one engine status characteristic of a gas turbine engine comprising:

a microphone spaced apart from a region of the gas turbine engine to be monitored; and

a signal processor operable to receive an electrical signal produced by the microphone in response to audible frequencies defining a noise signature which corresponds to pressure pulsations in fluid flowing through the gas turbine engine during operation thereof, the signal processor being operable to analyze the electrical signal to detect said engine status characteristic based principally on the noise signature representative of said engine status characteristic.

17. The system as defined in claim 16, further comprising an alerting device in communication with said signal processor operable to indicate that said engine status characteristic is present.

18. The system as defined in claim 16, wherein said signal processor detects said engine status characteristic based solely on the noise signature read by the microphone.

19. The system as defined in claim 16, wherein the gas turbine engine compressor, the engine status characteristic detected is aerodynamic stall of the compressor.

20. The system as defined in claim 19, wherein the compressor produces said pressure pulsations, said signal processor permitting a distinct change in said pressure pulsations to be identified which occurs when said compressor approaches said aerodynamic stall condition.