Method and device for monitoring a turbine engine of an aircraft

• US 8,918,264 B2
• Filed: 06/05/2012
• Issued: 12/23/2014
• Est. Priority Date: 06/09/2011
• Status: Active Grant

• Current Assignee: Airbus, Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Original Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Inventors: Jegu, Patrick, Birnfeld, Manfred
• Primary Examiner(s): Nguyen, Kim T
• Application Number:
  US13/488,574
• Publication Number:
  US 20120316748A1
• Time in Patent Office: 931 Days
• Field of Search: 701/3, 701/14, 701/31, 701/35, 701/100, 701/31.1
• US Class Current: 701/100
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F02C 7/262 Restarting after flame-out
• CPC Class Codes: F02C 9/00 Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2270/092 in particular blow-out and relight
• CPC Class Codes: F05D 2270/303 Temperature
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A method and device aids in monitoring at least one turbine engine in an aircraft. The method includes determining a value illustrating a thermomechanical state of the turbine engine, and comparing the determined value with at least one threshold. The method also includes displaying in the cockpit of the aircraft, at least one indication related to the operation of the turbine engine, according to this comparison. As a result, conditions that could result in mechanical degradation or failure of the turbine engine are identified for a crew of the aircraft.

Claims

1. An aiding method for monitoring at least one turbine engine of an aircraft, the method comprising the following operations, carried out automatically and repeatedly:

(a) measuring, by a parameter measurement device, at least one temperature relating to the turbine engine;

(b) determining, by an information processing unit/calculator, a value illustrating a thermomechanical condition of the turbine engine, the value illustrating the thermomechanical condition being determined by a calculation method and being dependent on thermal conditions identified by the at least one temperature that has been measured, wherein the value illustrating the thermomechanical condition identifies differential expansion between elements of the turbine engine that can lead to undesired frictional contact and damage of the elements and that can also lead to rotor lock;

(c) comparing, by the information processing unit/calculator, the determined value illustrating the thermomechanical condition with at least one predetermined threshold value; and

(d) showing, by a display device, at least one indication on a cockpit viewing screen of the aircraft, depending on the comparison of step (c), the at least one indication relating to operation of the turbine engine and including at least one of the following indications;

an indication relating to a damage risk for the turbine engine;

an indication relating to a lock risk for the turbine engine; and

an indication relating to an operational procedure.

2. The method according to claim 1, wherein at step (b), the value illustrating the thermomechanical condition of the turbine engine is determined by a predetermined calculation method provided to the information processing unit/calculator.

3. The method according to claim 2, further comprising a preliminary step of:

defining the predetermined calculation method by performing a bench test experiment enabling to characterize a thermomechanical response of the turbine engine depending on different speeds being tested.

4. The method according to claim 1, further comprising:

monitoring a current speed of the turbine engine, wherein steps (b) through (d) are implemented when the current speed is higher than a predetermined idle speed.

5. The method according to claim 1, wherein at step (c), the determined value illustrating the thermomechanical condition is compared with a plurality of different predetermined threshold values.

6. The method according to claim 1, wherein when the aircraft is in a ground phase, with the turbine engine in operation, one indication is shown, at step (d) that indicates a pending risk upon a shutdown of the turbine engine.

7. The method according to claim 6, wherein when the shutdown of the turbine engine has just occurred,

one indication is shown at step (d) providing information relating to a possible restarting of the turbine engine and at least a minimum waiting duration being recommended before a restarting of the turbine engine.

8. The method according to claim 1, wherein when the aircraft is in a flight phase, and when a turbine engine shutdown has just occurred,

an indication is presented, at step (d) which provides information relating to a possible restarting of the turbine engine.

9. The method according to claim 8, wherein the indication comprises an optimum speed of the aircraft to restart the turbine engine in windmill.

10. An aiding method for monitoring at least one turbine engine of an aircraft, the method comprising the following operations, carried out automatically and repeatedly:

(a) measuring, by a parameter measurement device, at least one temperature relating to the turbine engine;

(b) determining, by an information processing unit/calculator, a value illustrating a thermomechanical condition of the turbine engine by illustrating expansion of at least one element of the turbine engine, depending on thermal conditions identified by the at least one temperature that has been measured;

(c) comparing, by the information processing unit/calculator, the determined value illustrating the thermomechanical condition with at least one predetermined threshold value; and

(d) showing, by a display device, at least one indication on a cockpit viewing screen of the aircraft, depending on the comparison of step (c), the at least one indication relating to operation of the turbine engine and including at least one of the following indications;

an indication relating to a damage risk for the turbine engine;

an indication relating to a lock risk for the turbine engine; and

an indication relating to an operational procedure,

wherein when the aircraft is in a ground phase, with the turbine engine in operation, one indication is shown, at step (d) that indicates a pending risk upon a shutdown of the turbine engine,

wherein when the shutdown of the turbine engine has just occurred, one indication is shown at step (d) providing information relating to a possible restarting of the turbine engine and at least a minimum waiting duration being recommended before a restarting of the turbine engine, and

wherein at step (c), the determined value illustrating the thermomechanical condition is compared with two threshold values S1 and S2, the threshold value S1 being larger than the threshold value S2, and the method further comprises;

when the determined value is higher than or equal the threshold value S1, the turbine engine presents the thermomechanical condition, for which the shutdown of the turbine engine is to be avoided;

when the determined value is between the threshold values Si and S2, the turbine engine presents the thermomechanical condition, for which the shutdown can cause difficulties upon a subsequent restarting; and

when the determined value is lower than or equal to the threshold value S2, the turbine engine presents the thermomechanical condition making the shutdown possible.

11. An aiding device for automatically monitoring at least one turbine engine of an aircraft, the aiding device comprising—

;

a parameter measurement device on the aircraft which measures at least one temperature relating to the turbine engine;

an information processing unit/calculator which (i) uses the measured at least one temperature to determine a value illustrating a thermomechanical condition of the turbine engine, the value illustrating the thermomechanical condition being determined by a calculation method and being dependent on thermal conditions identified by the at least one temperature that has been measured, wherein the value illustrating the thermomechanical condition identifies differential expansion between elements of the turbine engine that can lead to undesired frictional contact and damage of the elements and that can also lead to rotor lock, and (ii) compares the value illustrating the thermomechanical condition with at least one predetermined threshold value; and

a display device which shows on a cockpit viewing screen, depending on the comparison with at least one predetermined threshold value, at least one indication relating to the operation of the turbine engine and including at least one of the following indications;

an indication relating to a damage risk for the turbine engine;

an indication relating to a lock risk for the turbine engine; and

an indication relating to an operational procedure.

12. The device according to claim 11, wherein the information processing unit/calculator is part of a FADEC control calculator for the turbine engine.

13. The device according to claim 11, wherein the information processing unit/calculator is part of an aircraft calculator.

14. An aircraft system for an aircraft, comprising:

plurality of turbine engines, and

a plurality of aiding devices, each of which is associated with one of said turbine engines and each of which comprises;

a parameter measurement device on the aircraft which measures at least one temperature relating to the turbine engine;

an information processing unit/calculator which (i) uses the measured at least one temperature to determine a value illustrating a thermomechanical condition of the turbine engine, the value illustrating the thermomechanical condition being determined by a calculation method and being dependent on thermal conditions identified by the at least one temperature that has been measured, wherein the value illustrating the thermomechanical condition identifies differential expansion between elements of the turbine engine that can lead to undesired frictional contact and damage of the elements and that can also lead to rotor lock, and (ii) compares the value illustrating the thermomechanical condition with at least one predetermined threshold value; and

a display device which shows on a cockpit viewing screen, depending on the comparison with at least one predetermined threshold value, at least one indication relating to the operation of the turbine engine and including at least one of the following indications;

an indication relating to a damage risk for the turbine engine;

an indication relating to a lock risk for the turbine engine; and

an indication relating to an operational procedure.