Propeller health monitoring

Patent metadata

Field	Value
Publication number	US-11708175-B2
Application number	US-201815974762-A
Country	US
Kind code	B2
Filing date	May 9, 2018
Priority date	May 10, 2017
Publication date	Jul 25, 2023
Grant date	Jul 25, 2023

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 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, is provided. The method comprises obtaining measurements representative of the strain in each of at least some of the hub arms using strain sensors, each of the strain sensors being provided on a respective hub arm. A corresponding propeller health monitoring system, an aircraft propeller comprising the system and an aircraft comprising the propeller are also provided.

First claim

The invention claimed is:

1. A method of monitoring the health of an aircraft propeller whilst the propeller is in operation, the propeller comprising a propeller hub with a plurality of hub arms, the propeller having a plurality of propeller blades connected to the propeller hub via the hub arms, the propeller blades extending radially outwardly from the hub arms with respect to a central rotational axis extending through the propeller and a propeller drive shaft, wherein each of the hub arms also extends radially outwardly from an outer circumferential surface of the hub, each hub arm comprising an external surface, the method comprising:
mounting strain sensors, each of the strain sensors being mounted on a respective hub arm, wherein each strain sensor is provided on the external surface of the respective hub arm on an axially forward side of the hub such that each of the strain sensors is circumferentially aligned with a propeller blade among the plurality of propeller blades and is axially offset from said propeller blade along a line parallel to the central rotational axis of the propeller;
obtaining measurements of the strain at the external surface of the respective hub arm on the axially forward side of the hub in each of the hub arms using the strain sensors, wherein the measurements of strain in each of the hub arms are representative of strain in the respective propeller blade;
calculating, using a processor, amplitudes of the cyclic responses of the strain sensors using the measurements of strain obtained from each of the sensors; and
comparing, using the processor, the amplitude of at least one cyclic response to the amplitude of at least one of the other cyclic responses; and
determining if the amplitudes of the cyclic responses are equal within a defined tolerance; wherein if they are it is established that the propeller is healthy, and if they are not it is established that the health of the propeller may be impaired, wherein if the amplitudes of the cyclic responses are not equal within a defined tolerance, it is established that the blade aligned with the sensor which has the largest difference in amplitude of the cyclic response compared to the amplitudes of the cyclic response of the other sensors is damaged.

2. A method as claimed in claim 1 , wherein each strain sensor is located radially inward of said propeller blade, and along a radial line extending from a central rotational axis of the propeller hub along the blade.

3. A method as claimed in claim 1 , further comprising:
establishing that the health of a blade of the propeller may be impaired if the amplitude of the cyclic response of the sensor provided on the hub arm from which the blade extends is above or below the remainder of the amplitudes by at least 20%.

4. A method as claimed in claim 1 , further comprising indicating an alert for maintenance if it is established that the health of the propeller may be impaired.

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

6. A propeller health monitoring system comprising:
a plurality of strain sensors each configured to measure the strain in a hub arm of a propeller, the propeller comprising a propeller hub with a plurality of hub arms, the propeller having a plurality of propeller blades connected to the propeller hub via the hub arms, the propeller blades extending radially outwardly from the hub arms with respect to a central rotational axis extending through the propeller and a propeller drive shaft, wherein each of the hub arms also extends radially outwardly from an outer circumferential surface of the hub, each hub arm comprising an external surface, and each of the strain sensors is mounted on a respective hub arm and provided on the external surface of the respective hub arm on an axially forward side of the hub such that each of the strain sensors is circumferentially aligned with a propeller blade among the plurality of propeller blades and is axially offset from said propeller blade along a line parallel to the central rotational axis of the propeller; and
a processor configured to carry out steps of:
obtaining measurements of the strain in each of the hub arms using strain sensors, wherein the measurements of strain in each of the hub arms are representative of strain in the respective propeller blade;
calculating amplitudes of the cyclic responses of the strain sensors using the measurements of strain obtained from each of the sensors;
comparing the amplitude of at least one cyclic response to the amplitude of at least one of the other cyclic responses; and
determining if the amplitudes of the cyclic responses are equal within a defined tolerance; wherein if they are it is established that the propeller is healthy, and if they are not it is established that the health of the propeller may be impaired, wherein if the amplitudes of the cyclic responses are not equal within a defined tolerance, it is established that the blade aligned with the sensor which has the largest difference in amplitude of the cyclic response compared to the amplitudes of the cyclic response of the other sensors is damaged.

7. An aircraft propeller system comprising:
a propeller comprising a propeller hub with a plurality of hub arms, the propeller having a plurality of propeller blades connected to the propeller hub via the hub arms, the propeller blades extending radially outwardly from hub arms with respect to a central rotational axis extending through the propeller and a propeller drive shaft, wherein each of the hub arms also extends radially outwardly from an outer circumferential surface of the hub, each hub arm comprising an external surface;
strain sensors mounted on each of at least some of the hub arms configured to measure the strain in the hub arm of the propeller, wherein each strain sensor is provided on the external surface of the respective hub arm on an axially forward side of the hub such that each of the strain sensors is circumferentially aligned with a propeller blade among the plurality of propeller blades and is axially offset from said propeller blade along a line parallel to the central rotational axis of the propeller; and
a propeller health monitoring system that includes:
a processor configured to carry out steps of:
obtaining measurements of the strain in each of the hub arms using strain sensors, wherein the measurements of strain in each of the hub arms are representative of strain in the respective propeller blade;
calculating amplitudes of the cyclic responses of the strain sensors using the measurements of strain obtained from each of the sensors;
comparing the amplitude of at least one cyclic response to the amplitude of at least one of the other cyclic responses; and
determining if the amplitudes of the cyclic responses are equal within a defined tolerance; wherein if they are it is established that the propeller is healthy, and if they are not it is established that the health of the propeller may be impaired, wherein if the amplitudes of the cyclic responses are not equal within a defined tolerance, it is established that the blade aligned with the sensor which has the largest difference in amplitude of the cyclic response compared to the amplitudes of the cyclic response of the other sensors is damaged.

8. An aircraft propeller system as claimed in claim 7 , wherein the processor is integrated into a FADEC of the aircraft or in the nacelle and the strain sensors are configured to transmit the measurements representative of strain to the processor via telemetry, Wi-Fi, or a slip ring.

9. An aircraft propeller system as claimed in claim 8 , wherein the strain sensors are full bridge strain gauges.

10. An aircr

Assignees

• Ratier Figeac Sas

Inventors

• Huth Brian P
• El Haloui Abdellah

Classifications

• B64D45/00 Primary

  Aircraft indicators or protectors not otherwise provided for · CPC title

• G01L1/2262

  involving simple electrical bridges · CPC title

• G01M5/0016 Primary

  of aircraft wings or blades · CPC title

• G01M5/0025

  of elongated objects, e.g. pipes, masts, towers or railways (G01M5/0058 takes precedence) · CPC title

• G01M5/0033

  by determining damage, crack or wear · CPC title