Assembly and method of component monitoring

• US 9,897,479 B2
• Filed: 08/25/2015
• Issued: 02/20/2018
• Est. Priority Date: 09/15/2014
• Status: Active Grant

• Current Assignee: GE Aviation Systems Limited (GE Aerospace)
• Original Assignee: GE Aviation Systems Limited (GE Aerospace)
• Inventors: Bonnett, Steven, North, Timothy Robert, Gilbert, Tod Alexander
• Primary Examiner(s): Kwok, Helen
• Application Number:
  US14/835,029
• Publication Number:
  US 20160076931A1
• Time in Patent Office: 910 Days
• CPC Class Codes: G01H 1/003 of rotating machines G01H1/10 takes precedence
• CPC Class Codes: G01H 3/04 Frequency
• CPC Class Codes: G01P 3/44 for measuring angular speed G01P3/56 takes precedence

Abstract

A method of component monitoring for machinery having multiple rotating elements, which are rotated at different rotational speeds, the method including sampling data from the vibration sensor at a sampling frequency at least as great as the fastest rotational speed of the multiple rotating elements to form a data set and determining an actual rotational frequency for at least some of the rotating elements during the sampling of the data.

Claims

1. A method of component monitoring for machinery having multiple rotating elements, which are rotated at different rotational speeds, and at least one vibration sensor, the method comprising:

sampling data from the vibration sensor at a first sampling rate sufficient to monitor a fastest rotational speed of the multiple rotating elements to form a data set;

determining an actual rotational frequency for at least one of the multiple rotating elements during the sampling of the data; and

generating a virtual vibration waveform from the data set for at least one of the multiple rotating elements by filtering the data set to a resampling rate to monitor each of the at least one of the multiple rotating elements,

wherein generating the virtual vibration waveform comprises determining the resampling rate based at least partially on the actual rotational frequency of the at least one of the multiple rotating elements,

and wherein the first sampling rate is higher than the resampling rate.

2. The method of claim 1, wherein determining the actual rotational frequency for the at least one of the multiple rotating elements comprises determining the actual rotational frequency of more than one of the multiple rotating elements.

3. The method of claim 2, wherein virtual vibration waveforms are generated for all of the multiple rotating elements, and

wherein the resampling rate is at least 2770 Hz.

4. The method of claim 1, further comprising processing the virtual waveform for each of the at least one of the multiple rotating elements to determine a health of the machinery, and

wherein the multiple rotating elements comprise three gears.

5. The method of claim 4, wherein the processing comprises detecting, by a processor, a mechanical fault based on a determined vibration of at least one rotating component.

6. The method of claim 5, further comprising providing an alert to a user when the mechanical fault is detected, and

wherein the resampling rate is at least 4777 Hz.

7. The method of claim 4, wherein the machinery is an aircraft, and

wherein the resampling rate is at least 2770 Hz.

8. The method of claim 7 further comprising flying the aircraft in a fixed flight regime during the sampling,

wherein determining the resampling rate further comprises using a decimation filter in combination with an interpolation filter.

9. The method of claim 8, further comprising repeating the flying, sampling, determining, generating, and processing after a predetermined number of flight hours.

10. The method of claim 7, further comprising communicating the generated virtual vibration waveforms from the aircraft to at least one ground system.

17. The method of claim 5, wherein detecting a mechanical fault further comprises comparison of the determined vibration to a reference value.

18. The method of claim 6, wherein detecting a mechanical fault further comprises comparison of the determined vibration to a previous determined value from a previous flight.

19. The method of claim 18, wherein determining the resampling rate further comprises using a fixed ratio filter in combination with an interpolation filter, and

wherein the rotating machinery is installed on a rotorcraft.

11. An assembly, comprising:

rotating machinery having multiple rotating elements, which are rotated at different rotational speeds;

a vibration sensor configured to measure vibrations of the multiple rotating elements;

a tachometer configured to measure a rotational speed of one of the multiple rotating elements; and

a processor operably coupled to the vibration sensor and the tachometer to receive information therefrom and configured to sample data from the vibration sensor at a first sampling rate sufficient to monitor a fastest rotational speed of the multiple rotating elements to form a data set, determine an actual rotational frequency for at least one of the multiple rotating elements during the sampling of the data and generate a virtual vibration waveform from the data set for at least one of the multiple rotating elements by filtering the data set to a resampling rate to monitor each of the at least one of the multiple rotating elements,

wherein the resampling rate is determined based at least partially on the actual rotational frequency of the at least one of the multiple rotating elements.

12. The assembly of claim 11, further comprising a communication module for transmitting the generated waveforms.

13. The assembly of claim 11, wherein the rotating machinery is a gear box.

14. The assembly of claim 11, wherein the processor is further configured to process the virtual waveforms to determine a health of the rotating machinery.

15. The assembly of claim 11, wherein the processor comprises a filter for generating the virtual vibration waveforms.

16. A system for vibration monitoring for rotorcraft machinery, the system comprising:

rotating machinery having multiple rotating elements, which are rotated at different rotational speeds;

a single vibration sensor configured to measure vibrations of the multiple rotating elements;

a tachometer configured to measure a rotational speed of one of the multiple rotating elements; and

a processor operably coupled to the vibration sensor and the tachometer to receive information therefrom and sampling data from the vibration sensor at a first sampling rate sufficient to monitor a fastest rotational speed of the multiple rotating elements to form a data set, determine an actual rotational frequency for at least one of the multiple rotating elements during the sampling of the data and generate a virtual vibration waveform from the data set for at least one of the multiple rotating elements by filtering the data set to a resampling rate to monitor each of the at least one of the multiple rotating elements,

wherein the resampling rate is determined based at least partially on the actual rotational frequency of the at least one of the multiple rotating elements,

wherein the first sampling rate is higher than the resampling rate,

wherein the multiple rotating elements comprise three or more rotating elements and

wherein the single vibration sensor monitors vibrations of all of the multiple rotating elements simultaneously.