Propeller health monitoring

Patent metadata

Field	Value
Publication number	US-10787275-B2
Application number	US-201815974739-A
Country	US
Kind code	B2
Filing date	May 9, 2018
Priority date	May 10, 2017
Publication date	Sep 29, 2020
Grant date	Sep 29, 2020

Abstract

A method of monitoring the health of an aircraft propeller whilst the propeller is in operation, the propeller having a plurality of blades extending radially outwardly from a central axis extending through the propeller and a propeller drive shaft, is provided. The method includes obtaining measurements representative of strain in the propeller drive shaft using multiple primary strain sensors, each primary strain sensor providing respective measurements representative of strain. The primary strain sensors are located around a circumference of the drive shaft of the propeller, and each strain sensor is located such that it crosses a plane defined by the radial direction of a blade and the central axis, the plane being bounded by the central axis. A corresponding propeller health monitoring system, an aircraft propeller comprising the system and an aircraft comprising the propeller are also provided.

First claim

The inventon claimed is:

1. A method of monitoring the health of an aircraft propeller whilst the propeller is in operation, the propeller having a plurality of blades extending radially outwardly from a central axis extending through the propeller and a propeller drive shaft, the method comprising:
disposing multiple primary strain sensors around a circumference of the drive shaft of the propeller; and
obtaining measurements representative of strain in the propeller drive shaft using multiple primary strain sensors, each primary strain sensor providing a respective measurement representative of strain;
wherein each primary strain sensor is located such that it crosses a plane defined by the radial direction of a blade and the central axis, the plane being bounded by the central axis.

2. The method as claimed in claim 1 , further comprising:
obtaining measurements representative of strain in the propeller drive shaft using multiple secondary strain sensors, each secondary strain sensor being located around the circumference of the drive shaft diametrically opposite to a respective primary strain sensor and forming a sensor pair therewith.

3. The method as claimed in claim 1 , further comprising:
determining a respective steady bending moment of the drive shaft using the respective measurements representative of strain obtained by each primary strain sensor.

4. The method as claimed in claim 3 , further comprising:
comparing the magnitude of the calculated steady bending moments to a threshold.

5. The method as claimed in claim 4 , further comprising:
establishing that the health of the propeller may be impaired if the magnitude of a calculated steady bending moment of the drive shaft is above a threshold.

6. The method as claimed in claim 3 , further comprising:
comparing the magnitude of the calculated steady bending moments to one another.

7. The method as claimed in claim 6 , further comprising:
establishing that the health of the propeller may be impaired if the magnitude of one of the steady bending moments of the drive shaft is outside of a tolerance of the other steady bending moments of the drive shaft.

8. The method as claimed in claim 5 , further comprising:
for a propeller having an odd number of blades, identifying a damaged blade by:
identifying the blade corresponding to the primary sensor which provided the measurements representative of strain which has led to a steady bending moment being calculated which has a magnitude above the threshold; or
for a propeller having an even number of blades, identifying which two diametrically opposed blades may include at least one damaged blade, by:
identifying the blades corresponding to the primary sensor which has provided the measurements representative of strain which has led to a steady bending moment being calculated which has a magnitude above the threshold.

9. The method as claimed in claim 7 , further comprising:
for a propeller having an even number of blades, identifying which two diametrically opposed blades may include at least one damaged blade, by:
identifying the blades corresponding to the primary sensor which has provided the measurements representative of strain which has led to a steady bending moment being calculated which is outside of the tolerance of the other steady bending moments of the drive shaft; or
for a propeller having an odd number of blades, identifying a damaged blade by:
identifying the blade corresponding to the primary sensor which provided the measurements representative of strain which has led to a steady bending moment being calculated which is outside of the tolerance of the other steady bending moments of the drive shaft.

10. The method as claimed in claim 1 , wherein the strain sensors are full bridge strain gauges.

11. An aircraft propeller system comprising:
a propeller and a propeller health monitoring system configured to monitor the health of the propeller while the propeller is in operation, the propeller health monitoring system comprising:
a plurality of primary strain sensors or pairs of primary and secondary strain sensors, the primary strain sensors or strain sensor pairs being configured to provide measurements representative of strain in a drive shaft of a propeller; and
a processor, wherein
the propeller has a plurality of blades extending radially outwardly from hub arms of a propeller hub, which in turn extend radially outwardly from a central axis extending through the propeller and a propeller drive shaft;
the primary strain sensors or pairs of primary and secondary strain sensors are arranged around a circumference of the drive shaft of the propeller;
each primary strain sensor is located such that it crosses a plane defined by the radial direction of a blade and the central axis, the plane being bounded by the central axis; and
in the case in which strain sensor pairs are provided, each secondary strain sensor in the strain sensor pair is located around the circumference of the drive shaft diametrically opposite to its corresponding primary strain sensor.

12. The aircraft propeller system as claimed in claim 11 , wherein the processor is integrated into a FADEC of an aircraft or in a nacelle and the strain sensors are configured to transmit the measured strain to the processor via telemetry, Wi-Fi, or a slip ring.

13. A propeller aircraft comprising the aircraft propeller system as claimed in claim 11 .

14. The aircraft propeller system as claimed in claim 11 , wherein the processor is configured to:
determine a respective steady bending moment of the drive shaft using the respective measurements representative of strain obtained by each primary strain sensor or using the respective measurements representative of strain obtained by each strain sensor pair;
and either compare the magnitude of the calculated steady bending moments to a threshold and establish that the health of the propeller may be impaired if the magnitude of a calculated steady bending moment of the drive shaft is above a threshold; or
compare the magnitude of the calculated steady bending moments to one another and establish that the health of the propeller may be impaired if the magnitude of one of the steady bending moments of the drive shaft is outside of a tolerance of the other steady bending moments of the drive shaft.

15. The method as claimed in claim 2 , further comprising:
determining a respective steady bending moment of the drive shaft using the respective measurements representative of strain obtained by each strain sensor pair.

16. The method as claimed in claim 15 , further comprising:
comparing the magnitude of the calculated steady bending moments to a threshold.

17. The method as claimed in claim 16 , further comprising:
establishing that the health of the propeller may be impaired if the magnitude of a calculated steady bending moment of the drive shaft is above a threshold.

18. The method as claimed in claim 17 , further comprising:
for a propeller having an odd number of blades, identifying a damaged blade by:
identifying the blade corresponding to the sensor pair which provided the measurements representative of strain which has led to a steady bending moment being calculated which has a magnitude above the threshold; or
for a propeller having an even number of blades, identifying which two diametrically opposed blades may include at least one damaged blade, by:
identifying the blades corresponding to the sensor pair which has provided the measurements representative of strain which has led to a st

Assignees

• Ratier Figeac Sas

Inventors

• Huth Brian P
• El Haloui Abdellah

Classifications

• G01M5/0016 Primary

  of aircraft wings or blades · CPC title

• B64C11/04

  Blade mountings · CPC title

• G01L5/133

  for measuring thrust of propulsive devices, e.g. of propellers (aeroplanes B64C; marine propulsion B63H; jet-engines F02K) · CPC title

• G01M5/0041

  by determining deflection or stress · CPC title

• G01M5/0083

  by measuring variation of impedance, e.g. resistance, capacitance, induction · CPC title