Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines

Patent metadata

Field	Value
Publication number	US-11459960-B2
Application number	US-201816500285-A
Country	US
Kind code	B2
Filing date	Mar 30, 2018
Priority date	Apr 3, 2017
Publication date	Oct 4, 2022
Grant date	Oct 4, 2022

Abstract

A method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines configured to operate in parallel and together to supply a necessary power to the aircraft during a flight phase includes: placing one of the turbine engines in a maximum take-off power regime, and adjusting a power supplied by the other turbine engine, such that the turbine engines continue to supply the necessary power to the aircraft during the flight phase; determining a power supplied by the turbine engine placed in the maximum take-off power regime, and processing the supplied power determined in this way, in order to deduce a piece of information relating to the maximum available power.

First claim

The invention claimed is:

1. A method of checking a maximum available power of a turbine engine of an aircraft equipped with two turbine engines configured to operate in parallel and together to supply the aircraft with a necessary power during a flight phase, said method comprising:
placing a first of the two turbine engines in an engine speed equal to an engine speed at maximum take-off power,
adjusting a power supplied by a second of the two turbine engines, so that the two turbine engines keep supplying the aircraft with the necessary power during the flight phase,
determining a power supplied by the first turbine engine while the first turbine engine is being placed in the engine speed at maximum take-off power, and
processing the thus determined supplied power in order to deduce an information pertaining to the maximum available power.

2. The method according to claim 1 , further comprising:
determining a threshold power, said threshold power corresponding to a minimum power to be reached by the turbine engine placed in the engine speed at maximum take-off power in an event of failure of the other turbine engine,
comparing the thus determined supplied power with the threshold power.

3. The method according to claim 1 , wherein the turbine engine placed in the engine speed at maximum take-off power comprises a high pressure turbine and a low pressure turbine, the method further comprising:
measuring a temperature of the gases between the high pressure turbine and the low pressure turbine of the turbine engine placed in the engine speed at maximum take-off power, and
comparing the measured temperature with a predetermined threshold temperature, so as to ensure that the measured temperature is lower than the threshold temperature.

4. The method according to claim 1 , further comprising:
measuring a rotation speed of the turbine engine placed in the engine speed at maximum take-off power, and
comparing the measured rotation speed with a predetermined threshold rotation speed so as to ensure that the measured rotation speed is higher than or equal to the threshold rotation speed.

5. The method according to claim 1 , further comprising:
determining an operating power, said operating power corresponding to a minimum power guaranteeing a re-acceleration of the second of the two turbine engines in an event of failure of the turbine engine placed in the engine speed at maximum take-off power, and
adjusting the power of the turbine engine placed in the engine speed at maximum take-off power such that the power supplied by the second of the two turbine engines remains higher than the determined operating power.

6. The method according to claim 1 , wherein the turbine engine placed in the engine speed at maximum take-off power comprises a high pressure shaft and a low pressure shaft, and wherein the method is automatically interrupted when at least one of the following conditions is fulfilled:
rotation speed of the high pressure shaft is lower than a first threshold rotation speed,
rotation speed of the low pressure shaft is lower than a second threshold rotation speed and higher than a third threshold rotation speed,
a failure is detected on one of the two turbine engines.

7. A non-transitory computer readable medium comprising code instructions for executing the method according to claim 1 when the code instructions are executed by a processor.

8. A controlling device comprising a computer configured to implement the method according to claim 1 , said computer being configured to implement the following steps:
placing the first turbine engine in the engine speed equal to the engine speed at maximum take-off power,
adjusting the power supplied by the second turbine engine, such that the two turbine engines continue supplying the aircraft with the necessary power during the flight phase,
determining the power supplied by the first turbine engine while the first turbine engine is being placed in the engine speed at maximum take-off power, and
processing the thus determined power supplied to deduce the information pertaining to the maximum available power.

9. An assembly comprising two turbine engines configured to operate in parallel and together to supply a necessary power for an aircraft during a flight phase, said assembly comprising the controlling device according to claim 8 .

10. An aircraft comprising two turbine engines configured to operate in parallel and together to supply a necessary power for the aircraft during a flight phase, said aircraft comprising a computer configured to implement the method according to claim 1 .

11. A method of checking a maximum available power of a turbine engine of an aircraft equipped with two turbine engines configured to operate in parallel and together to supply the aircraft with a necessary power during a flight phase, said method comprising:
placing a first of the two turbine engines in an engine speed equal to an engine speed at maximum take-off power,
adjusting a power supplied by a second of the two turbine engines, so that the two turbine engines keep supplying the aircraft with the necessary power during the flight phase,
determining a power supplied by the turbine engine placed in the engine speed at maximum take-off power,
determining a threshold power, said threshold power corresponding to a minimum power to be reached by the turbine engine placed in the engine speed at maximum take-off power in an event of failure of the other turbine engine, and
comparing the thus determined supplied power with the threshold power.

12. A method of checking a maximum available power of a turbine engine of an aircraft equipped with two turbine engines configured to operate in parallel and together to supply the aircraft with a necessary power during a flight phase, said method comprising:
placing a first of the two turbine engines in an engine speed equal to an engine speed at maximum take-off power,
determining an operating power, said operating power corresponding to a minimum power guaranteeing a re-acceleration of a second of the two turbine engines in an event of failure of the turbine engine placed in the engine speed at maximum take-off power,
adjusting a power of the turbine engine placed in the engine speed at maximum take-off power such that a power supplied by the second of the two turbine engines remains higher than the determined operating power,
determining a power supplied by the turbine engine placed in the engine speed at maximum take-off power, and
processing the thus determined supplied power in order to deduce an information pertaining to the maximum available power.

Assignees

• Safran Helicopter Engines

Inventors

• Darfeuil Pierre
• Marconi Patrick
• Seve Caroline

Classifications

• F05D2260/80

  Diagnostics · CPC title

• B64D31/02

  Initiating means · CPC title

• F02C9/42 Primary

  specially adapted for the control of two or more plants simultaneously · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• F02C6/20

  Adaptations of gas-turbine plants for driving vehicles · CPC title