Method for the detection of failures in a turbomachine by means of a theoretical model of the thermodynamic cycle of the said turbomachine

• US 8,903,692 B2
• Filed: 02/16/2012
• Issued: 12/02/2014
• Est. Priority Date: 02/18/2011
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Beaupel, Benoit, Callot, Stanislas
• Primary Examiner(s): JONES, HUGH M
• Application Number:
  US13/398,182
• Publication Number:
  US 20120215509A1
• Time in Patent Office: 1,020 Days
• Field of Search: 703/8
• US Class Current: 703/8
• CPC Class Codes: G05B 23/0243 model based detection method, e.g. first-principles knowledge model

Abstract

A method for the detection of failure in a turbomachine by monitoring the performance of the turbomachine is provided. The method includes measuring at least one performance parameter of the turbomachine in order to obtain an actual signature for the performance of the turbomachine; comparing the actual signature of the turbomachine with a database of failures associating reference signatures for the performance of the turbomachine with identifiers of failure, the database of failures being obtained by the simulation of failures on the basis of a theoretical model of the thermodynamic cycle of the turbomachine; and determining the identifier of failure of the turbomachine for the actual signature.

Claims

1. A method for the detection of failure for a turbomachine by monitoring the performance of the turbomachine, comprising:

measuring at least one parameter for the performance of the turbomachine;

obtaining an actual signature for the performance of the turbomachine based on the measured at least one parameter;

obtaining a database of failures associating reference signatures for the performance of the turbomachine with identifiers of failure by simulating failures based on a theoretical model of a thermodynamic model of the turbomachine;

comparing the actual signature of the turbomachine with the database of failures;

determining the identifier of failure of the turbomachine for the actual signature,

wherein the obtaining the database of failures comprises;

parameterizing the theoretical model by modifying a definition of a component part of the turbomachine in the theoretical model such that the turbomachine simulates a failure of said component part, the simulated failure being identified by its identifier of failure;

calculating thermodynamic quantities obtained from the thermodynamic cycle of the turbomachine defined by the theoretical model as parameterized;

calculating a reference signature for the said turbomachine on the basis of the thermodynamic quantities; and

associating the calculated reference signature with the identifier of failure in the database of failures.

2. The method according to claim 1, wherein the turbomachine comprises a plurality of component parts, the theoretical model of the turbomachine includes definitions of the component parts of the turbomachine and the state of the thermodynamic cycle of the turbomachine associated with the definitions of the component parts.

3. The method according to claim 2, wherein a reference signature for the database of failures is calculated based on thermodynamic quantities obtained from the thermodynamic cycle of the turbomachine defined by the theoretical model of the turbomachine, at least one component part of the turbomachine being defined in the theoretical model as being defective in order to simulate a failure for which the identifier is determined.

4. The method according to claim 2, wherein each reference signature of the database of failures corresponds to a failure of one of the component parts of the turbomachine.

5. The method according to claim 1, wherein the theoretical model of the turbomachine corresponds to a brochure for the turbomachine.

6. The method according to claim 1, wherein the reference signatures and the actual signatures are each defined in the form of a vector in an orthonormal base of thermodynamic quantities for the turbomachine, a scalar product of the actual signature with the reference signatures is produced in order to identify the one which exhibits the greatest number of similarities with the actual signature and to deduce the identifier of failure of the said turbomachine for the actual signature.

7. The method according to claim 1, wherein the reference signatures are defined for standardized operating conditions of the turbomachine, the actual signature measured under actual operating conditions is standardized in relation to the standardized operating conditions based on the theoretical model of the said turbomachine prior to the comparing with the database of failures.

8. The method according to claim 1, wherein results of the comparing is displayed as a graphical representation.