Torque sensor monitoring for gas turbine engine

Patent metadata

Field	Value
Publication number	US-2016178464-A1
Application number	US-201514950822-A
Country	US
Kind code	A1
Filing date	Nov 24, 2015
Priority date	Dec 19, 2014
Publication date	Jun 23, 2016
Grant date	—

Abstract

A gas turbine engine torque monitoring system includes a gas turbine engine and gas turbine engine electronics. The gas turbine engine includes a torque sensor coupled to a rotatable element of the gas turbine engine, such as a drive shaft. The torque monitoring system analyzes torque signals output by the torque sensor, using a combination of frequency domain analysis and time domain analysis, and generates an interpretation of the torque sensor output signals. The gas turbine engine torque monitoring system can initiate a variety of different types of actions in relation to the gas turbine engine based on the interpretation of the torque sensor output signals.

First claim

What is claimed is:

1 . A gas turbine engine system, comprising:
a gas turbine engine comprising:
a rotor;
an output shaft coupled to the rotor, the output shaft having a magnetized portion; and
a high frequency-capable magnetic torque sensor located adjacent the magnetized portion of the output shaft; and
gas turbine engine electronics to, over time during operation of the gas turbine engine:
collect a plurality of data samples from output of the torque sensor, and with the data samples, cause one or more processors to:
perform a frequency response data analysis;
based on the frequency response data analysis, identify one or more frequency-domain torque-related events resulting from torsional vibration of the output shaft;
perform a time response data analysis;
based on the time response data analysis, identify one or more time-domain torque-related events resulting from torsional vibration of the output shaft;
categorize a combination of frequency-domain torque-related events and time-domain torque-related events according to one or more event categorization criteria; and
based on a category of the combination of frequency-domain torque-related events and time-domain torque-related events, initiate a communication from the gas turbine engine system to another device.

2 . The gas turbine engine system of claim 1 , wherein the gas turbine engine comprises a high-pressure (HP) drive train and a low-pressure (LP) drive train, the output shaft is an LP output shaft, and the torque sensor is mounted to the LP output shaft to detect high frequency torque-related events associated with a component of the LP drive train.

3 . The gas turbine engine system of claim 1 , wherein the gas turbine engine comprises a high-pressure (HP) drive train and a low-pressure (LP) drive train, the output shaft is an HP output shaft, and the torque sensor is mounted to the HP output shaft to detect high frequency torque-related events associated with a component of the HP drive train.

4 . The gas turbine engine system of claim 1 , wherein the gas turbine engine comprises a high-pressure (HP) drive train and an auxiliary gearbox (AGB) drive train, the output shaft is an output shaft of the HP drive train, a first torque sensor is mounted to the HP output shaft and a second torque sensor is mounted to an AGB shaft, wherein the AGB shaft couples the HP drive train to the AGB.

5 . The gas turbine engine system of claim 1 , wherein the magnetized portion of the output shaft comprises a portion of a cross section of the output shaft and the magnetized portion has a length that is less than the entire length of the output shaft.

6 . The gas turbine engine system of claim 1 , wherein the torque sensor is mounted to the output shaft in close proximity to but not touching the magnetized portion of the output shaft.

7 . The gas turbine engine system of claim 1 , wherein the gas turbine engine is a turboprop engine comprising a propeller shaft and propeller gearbox, the output shaft is disposed within the propeller gearbox and connected to the propeller shaft, and the torque sensor is mounted to the output shaft in the propeller gearbox.

8 . The gas turbine engine system of claim 1 , wherein the gas turbine engine is a turboshaft engine, the gas turbine engine comprises a power gearbox on the output shaft, and the torque sensor is mounted to a shaft of the power gearbox and disposed within the power gearbox.

9 . The gas turbine engine system of claim 1 , wherein the gas turbine engine electronics are configured to initiate an automatic engine control routine in response to a torque-related event.

10 . The gas turbine engine system of claim 1 , wherein the gas turbine engine system is embodied in an aircraft, and the gas turbine engine electronics are configured to perform at least one of communicating torque-related event data to an on-board display of the aircraft in response to a torque-related event; communicating torque-related event data to an on-ground maintenance system in response to a torque-related event, and storing torque-related event data in a log file in response to a torque-related event.

11 . The gas turbine engine system of claim 1 , wherein the engine electronics are configured to perform a frequency response data analysis by continuously generating a high frequency domain spectrum for a plurality of different high frequencies over a time interval.

12 . The gas turbine engine system of claim 11 , wherein to identify one or more frequency-domain torque-related events comprises to compare one or more characteristics of the high frequency domain spectrum to frequency domain spectrum characteristics of known torque-related events.

13 . The gas turbine engine system of claim 12 , wherein the gas turbine engine electronics are configured to continuously generate a low frequency domain spectrum for a plurality of different low frequencies over a time interval.

14 . The gas turbine engine system of claim 13 , wherein to identify one or more frequency-domain torque-related events comprises to compare one or more characteristics of the low frequency domain spectrum to frequency domain spectrum characteristics of known torque-related events.

15 . The gas turbine engine system of claim 14 , wherein the gas turbine engine electronics are configured to identify torque-related events by tagging frequency analysis summary data with reference time tags.

16 . The gas turbine engine system of claim 15 , wherein the gas turbine engine electronics are to configured use the time response data analysis of an identified torque-related event to determine a time and a spectrum of interest for frequency response analysis.

17 . The gas turbine engine system of claim 16 , wherein the gas turbine engine electronics are configured to receive data indicative of torque-related events from one or more other sensors of the gas turbine engine system, and use the received data to determine a time and a spectrum of interest for frequency response analysis and wherein the gas turbine engine electronics are configured to identify a trend in torsional oscillations based on the spectrum of interest.

18 . The gas turbine engine system of claim 17 , wherein the gas turbine engine electronics are to monitor torsional cycles and compare the torsional cycles to one or more threshold limits including a torsional vibration limit and a high cycle fatigue limit.

19 . The gas turbine engine system of claim 18 , wherein the gas turbine engine electronics are configured to compare a characteristic of a frequency spectrum of interest to one or more characteristics of a known engine health condition.

20 . The gas turbine engine system of claim 19 , wherein the gas turbine engine electronics are to output data indicative of an engine health condition or an engine failure mode.

Assignees

• Rolls Royce Corp

Inventors

• Burns Donald W
• Smith Alan W
• Amshoff Mark

Classifications

• G01L3/10 Primary

  involving electric or magnetic means for indicating · CPC title

• F01D21/003

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title

• G01L3/102

  involving magnetostrictive means (magnetostrictive sensors H10N35/101) · CPC title

• G01L3/101

  involving magnetic or electromagnetic means · CPC title

• F02C3/10

  with another turbine driving an output shaft but not driving the compressor · CPC title