Vibration monitoring system for multiple aircraft engines

• US 5,934,610 A
• Filed: 10/14/1997
• Issued: 08/10/1999
• Est. Priority Date: 10/14/1997
• Status: Expired due to Term

• Current Assignee: Vibro-Meter, SA (Meggitt PLC)
• Original Assignee: Endevco Corporation (Illinois Tool Works Inc.)
• Inventors: GenKuong, Fernando Francisco, Karolys, Alexis Gabriel
• Primary Examiner(s): Jordan, Charles T.
• Assistant Examiner(s): Ducker, Jr., Charles R.
• Application Number:
  US08/949,461
• Time in Patent Office: 665 Days
• Field of Search: 244/1 R, 244/53 R, 244/54, 244/17.13, 439/105, 439/188, 439/365, 439/507, 439/682, 439/692, 73/116, 73/117.2
• US Class Current: 244/53.00R
• CPC Class Codes: G01H 1/003 of rotating machines G01H1/10 takes precedence
• CPC Class Codes: G01M 15/12 by monitoring vibrations
• CPC Class Codes: H01R 13/6453 comprising pin-shaped elements, capable of being orientated in different angular positions around their own longitudinal axes, e.g. pins with hexagonal base
• CPC Class Codes: H01R 13/6616 with resistor
• CPC Class Codes: H01R 13/6683 with built-in sensor
• CPC Class Codes: H01R 31/065 with built-in electric apparatus

Abstract

An aircraft engine vibration analysis system is provided with at least one vibration sensor disposed proximate an aircraft engine. The analysis system is further provided with a vibration analysis module for receiving an input from the vibration sensor and generating an output representative of vibration characteristics of the aircraft engine. The analysis module is provided with a multiple pin input port which is connectable to the vibration sensor. The analysis module is further provided with test sequence select circuity which is in electrical communication with the input port for implementing an appropriate vibration analysis sequence in response to measured conductivity between pins of the multiple pin input port. The analysis system is further provided with a sensor connecting cable which is connectable to the vibration sensor and the analysis module input port. The connecting cable is provided with a multiple pin cable connector, the pins of which having conductivity characteristics corresponding to a vibration analysis sequence associated with a dedicated aircraft engine type.

Claims

1. An aircraft engine vibration analysis system comprising:

at least one vibration sensor disposed proximate an aircraft engine;

a vibration analysis module for receiving an input from the vibration sensor and generating an output representative of vibration characteristics of the aircraft engine, the analysis module comprising a multiple pin input port connectable to the vibration sensor and test sequence select circuity in electrical communication with the input port for implementing an appropriate vibration analysis sequence in response to measured conductivity between pins of the multiple pin input port; and

a sensor connecting cable connectable to the vibration sensor and the analysis module input port, the connecting cable having a multiple pin cable connector, the pins of which having conductivity characteristics corresponding to a vibration analysis sequence associated with a dedicated aircraft engine type.

2. The aircraft engine vibration analysis system of claim 1 wherein the connecting cable comprises an adaptor portion and a cable portion, the adaptor portion being disposed between the cable portion and the cable connector, the adaptor portion being engageable/disengageable from the cable portion.

3. The aircraft engine vibration analysis system of claim 2 wherein the adaptor portion being pin engageable with the cable portion.

4. The aircraft engine vibration analysis system of claim 1 wherein the analysis module further comprising:

a memory, wherein a list of predefined vibration analysis sequences is stored and selection of a particular analysis sequence from the stored list being dependent upon a selection signal from the test sequence selection circuity; and

a micro processor is adapted to receive sensor data and operates on the sensor data in accordance with a selected analysis sequence from the memory.

5. The aircraft engine vibration analysis system of claim 1 wherein the multiple pin input port at least two of the pins being electrically shorted.

6. The aircraft engine vibration analysis system of claim 1 wherein the multiple pin input port at least two of the pins being electrically open.

7. The aircraft engine vibration analysis system of claim 1 wherein the multiple pin cable connector at least two of the pins being electrically shorted.

8. The aircraft engine vibration analysis system of claim 1 wherein the multiple pin cable connector at least two of the pins being electrically open.

9. The aircraft engine vibration analysis system of claim 1 wherein said appropriate vibration analysis sequence corresponding to a vibration analysis sequence associated with a dedicated aircraft engine type.

10. An aircraft engine vibration analysis system comprising:

at least one vibration sensor disposed proximate an aircraft engine;

a vibration analysis module for receiving an input from the vibration sensor and generating an output representative of vibration characteristics of the aircraft engine, the analysis module comprising a multiple pin input port connectable to the vibration sensor and test sequence select circuity in electrical communication with the input port for implementing an appropriate vibration analysis sequence in response to measured conductivity between pins of the multiple pin input port, at least two of the pins being electrically shorted; and

a sensor connecting cable connectable to the vibration sensor and the analysis module input port, the connecting cable having a multiple pin cable connector, the pins of which having conductivity characteristics corresponding to a vibration analysis sequence associated with a dedicated aircraft engine type.

11. The aircraft engine vibration analysis system of claim 10 wherein the connecting cable comprises an adaptor portion and a cable portion, the adaptor portion being disposed between the cable portion and the cable connector, the adaptor portion being engageable/disengageable from the cable portion.

12. The aircraft engine vibration analysis system of claim 11 wherein the adaptor portion being pin engageable with the cable portion.

13. The aircraft engine vibration analysis system of claim 10 wherein the analysis module further comprising:

a memory, wherein a list of predefined vibration analysis sequences is stored and selection of a particular analysis sequence from the stored list being dependent upon a selection signal from the test sequence selection circuity; and

a micro processor is adapted to receive sensor data and operates on the sensor data in accordance with a selected analysis sequence from the memory.

14. The aircraft engine vibration analysis system of claim 11 wherein the multiple pin cable connector at least two of the pins being electrically shorted.

15. The aircraft engine vibration analysis system of claim 11 wherein the multiple pin cable connector at least two of the pins being electrically open.

16. The aircraft engine vibration analysis system of claim 11 wherein said appropriate vibration analysis sequence corresponding to a vibration analysis sequence associated with a dedicated aircraft engine type.

17. An aircraft engine vibration analysis system comprising:

at least one vibration sensor disposed proximate an aircraft engine;

a vibration analysis module for receiving an input from the vibration sensor and generating an output representative of vibration characteristics of the aircraft engine, the analysis module comprising a multiple pin input port connectable to the vibration sensor and test sequence select circuity in electrical communication with the input port for implementing an appropriate vibration analysis sequence in response to measured conductivity between pins of the multiple pin input port, at least two of the pins being electrically open; and

a sensor connecting cable connectable to the vibration sensor and the analysis module input port, the connecting cable having a multiple pin cable connector, the pins of which having conductivity characteristics corresponding to a vibration analysis sequence associated with a dedicated aircraft engine type.

18. The aircraft engine vibration analysis system of claim 17 wherein the connecting cable comprises an adaptor portion and a cable portion, the adaptor portion being disposed between the cable portion and the cable connector, the adaptor portion being engageable/disengageable from the cable portion.

19. The aircraft engine vibration analysis system of claim 18 wherein the adaptor portion being pin engageable with the cable portion.

20. The aircraft engine vibration analysis system of claim 17 wherein the analysis module further comprising:

a memory, wherein a list of predefined vibration analysis sequences is stored and selection of a particular analysis sequence from the stored list being dependent upon a selection signal from the test sequence selection circuity; and

a micro processor is adapted to receive sensor data and operates on the sensor data in accordance with a selected analysis sequence from the memory.

21. The aircraft engine vibration analysis system of claim 17 wherein the multiple pin cable connector at least two of the pins being electrically shorted.

22. The aircraft engine vibration analysis system of claim 17 wherein the multiple pin cable connector at least two of the pins being electrically open.

23. The aircraft engine vibration analysis system of claim 17 wherein said appropriate vibration analysis sequence corresponding to a vibration analysis sequence associated with a dedicated aircraft engine type.