US 11,788,931 B2
Method for monitoring the torsion of a rotary shaft on a turbomachine of an aircraft
Alméric Pierre Louis Garnier, Moissy-Cramayel (FR); Marion Cuny, Moissy-Cramayel (FR); Tony Alain Roger Joël Lhommeau, Moissy-Cramayel (FR); and Claire Marie Figeureu, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/755,984
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Nov. 13, 2020, PCT No. PCT/FR2020/052075
§ 371(c)(1), (2) Date May 13, 2022,
PCT Pub. No. WO2021/094693, PCT Pub. Date May 20, 2021.
Claims priority of application No. 1912727 (FR), filed on Nov. 14, 2019.
Prior Publication US 2022/0390328 A1, Dec. 8, 2022
Int. Cl. G01M 15/14 (2006.01); F01D 21/00 (2006.01); G01L 3/10 (2006.01)
CPC G01M 15/14 (2013.01) [F01D 21/003 (2013.01); G01L 3/109 (2013.01); F05D 2220/323 (2013.01); F05D 2260/83 (2013.01)] 9 Claims
OG exemplary drawing
 
1. A method for monitoring a torsion of a rotary shaft on an aircraft turbomachine based on the measurements from at least three sensor, wherein the at least three sensors include a first sensor, a second sensor, and a third sensor distributed along the rotary shaft to divide the shaft into at least two shaft segments, the method comprising:
a step of measuring, for each sensor, a parameter dependent on the rotation of the shaft,
a step of calculating, for each achievable pair of sensors, a parameter related to the torsion of the shaft, wherein the achievable pair of sensors include the first sensor and the second sensor, the first sensor and the third sensor, and the second sensor and the third sensor,
a step of comparing the different calculated parameters related to the torsion of the shaft with references,
a step of detecting damage on a shaft segment at the end of the comparison step, and
a step of indicating the localization of the damage on the shaft from the shaft segment for which damage has been detected.