Method, device and computer program for monitoring a rotating machine of an aircraft

Patent metadata

Field	Value
Publication number	US-11754435-B2
Application number	US-202017774591-A
Country	US
Kind code	B2
Filing date	Nov 3, 2020
Priority date	Nov 5, 2019
Publication date	Sep 12, 2023
Grant date	Sep 12, 2023

Abstract

The invention relates to a method ( 1 ) for monitoring a rotating machine ( 100 ) of an aircraft, wherein a measurement signal is acquired from the rotating machine. According to the invention, instantaneous frequencies (f K (t)) of sinusoidal components of the measurement signal are estimated, and, using a computing module ( 12 ), a plurality of successive iterations are carried out in each of which: complex envelopes of the components are updated (C 1 ), parameters of a model of a noise of the signal are updated (C 21 ) on the basis of the envelopes, whether the model has converged from the preceding iteration to the present iteration is tested (C 4 ), with a view to: o if not, carrying out a new iteration, o if so, performing a computation (D) of the complex envelopes on the basis of the iterations that have been carried out.

First claim

The invention claimed is:

1. A method for monitoring at least one rotating machine of an aircraft, the mehod comprising the following steps:
acquiring at least one measurement signal of the rotating machine by an acquisition module,
estimating instantaneous frequencies of sinusoidal components of the at least one measurement signal by an estimation module,
executing by a calculation module several successive iterations, each of which comprising:
updating complex envelopes of the sinusoidal components,
updating parameters of a noise model of the at least one measurement signal from the complex envelopes having been updated,
performing a convergence test as to whether the noise model converges from the preceding iteration to the current iteration, to:
in the negative, redo a new iteration,
in the affirmative, perform a calculation of the complex envelopes from the iterations carried out,

updating at each iteration regularisation parameters of the noise model by the calculation module from the complex envelopes having been updated,
and, updating, at each iteration, an auxiliary decoupling variable of the complex envelopes of the components between them in the noise model by the calculation module from the complex envelopes having been updated and from the parameters of the noise model having been updated.

2. The method according to claim 1 , wherein the noise model of the at least one measurement signal comprises a structured interfering noise, whereof a distribution of probability a priori of its spectrum has a heavy-tailed law calculated by the calculation module at each iteration.

3. The method according to claim 1 , wherein the noise model of the at least one measurement signal comprises a non-structured interfering noise, whereof a distribution of probability a priori is given by a third distribution of Gaussian type calculated by the calculation module at each iteration.

4. The method according to claim 1 , wherein the noise model of the at least one measurement signal resulting from a structured interfering noise model and from a non-structured interfering noise model is a convolution of a Gaussian law and of a heavy-tailed law whose parameters are calculated by the calculation module at each iteration.

5. The method according to claim 1 , wherein a conjugated law of probability a priori is allocated to hyperparameters of laws a priori of the parameters of the noise model.

6. The method according to claim 1 , wherein a Gamma law of probability a priori is allocated to at least one of the regularisation parameters and results from a Gamma law a posteriori whose parameters are calculated by the calculation module at each iteration.

7. The method according to claim 1 , wherein the auxiliary decoupling variable is defined by a model having a distribution of probability of a type of circularly symmetrical normal complex law, which is calculated by the calculation module at each iteration.

8. The method according to claim 1 , wherein the convergence test comprises testing by the calculation module at each current iteration that the difference between an absolute value of the complex envelope calculated from the current iteration and the absolute value of the complex envelope calculated from the preceding iteration is less than a prescribed threshold.

9. The method according to claim 1 , comprising analysing by the calculation module the complex envelopes having been calculated, and triggering a communication of an alarm by the calculation module on at least one physical outlet as a function of the complex envelopes having been analysed.

10. A computer program comprising code instructions for executing the monitoring method according to claim 1 , when it is executed on a computer.

11. A monitoring device of at least one rotating machine of an aircraft, the device comprising
a module for acquiring at least one measurement signal of the rotating machine,
wherein the device comprises
a module for estimating instantaneous frequencies of sinusoidal components of the at least one measurement signal,
a calculation module configured, at each of several successive iterations carried out, to:
update complex envelopes of the sinusoidal components,
update parameters of a noise model of the at least one measurement signal from the complex envelopes having been updated,
test whether the noise model converges from the preceding iteration to the current iteration, to:
in the negative, redo a new iteration,
in the affirmative, perform a calculation of the complex envelopes from the iterations carried out,

the calculation module being configured to, at each of the successive iterations carried out:
update regularisation parameters of the noise model from the complex envelopes having been updated,
update an auxiliary decoupling variable of the complex envelopes of the components between them in the noise model, from the complex envelopes having been updated and from the parameters of the noise model having been updated.

12. The monitoring device according to claim 11 , wherein the calculation module is configured to analyse the complex envelopes having been calculated, and is able to trigger a communication of an alarm on at least one physical outlet of the device as a function of the complex envelopes having been analysed.

13. The monitoring device according to claim 11 , wherein the auxiliary decoupling variable is defined by a model having a distribution of probability of a type of circularly symmetrical normal complex law, which is calculated by the calculation module at each iteration.

14. An aircraft comprising at least one rotating machine and a monitoring device of the at least one rotating machine according to claim 11 .

Assignees

• Safran

Inventors

• Marnissi Yosra
• Abboud Dany
• El Badaoui Mohammed

Classifications

• G01R23/16 Primary

  Spectrum analysis; Fourier analysis · CPC title

• G01H1/006 Primary

  of the rotor of turbo machines · CPC title

• G01R23/167

  with digital filters · CPC title

• G01R31/008

  on air- or spacecraft, railway rolling stock or sea-going vessels · CPC title

• G01M1/08

  Instruments for indicating directly the magnitude and phase of the imbalance · CPC title