Method and a device for adjusting a setpoint value of a parameter that influences thrust from a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9371779-B2
Application number	US-201314409663-A
Country	US
Kind code	B2
Filing date	Jun 11, 2013
Priority date	Jun 20, 2012
Publication date	Jun 21, 2016
Grant date	Jun 21, 2016

Abstract

A method of adjusting a setpoint value of at least one parameter that has an influence on thrust of a gas turbine engine propelling an aircraft during a stage of flight of the aircraft, the method including: obtaining a current value of at least one operating variable of the engine; extracting from a pre-established table a decrement value for the at least one parameter associated with the current value of the at least one operating variable of the engine; and adjusting the setpoint value of the at least one parameter by applying thereto the decrement value extracted from the table.

First claim

The invention claimed is:

1. A method of adjusting a setpoint value of at least one parameter that has an influence on thrust of a gas turbine engine propelling an aircraft during a stage of flight of the aircraft, the method comprising:
obtaining a current value of at least one operating variable of the engine;
extracting from a pre-established table a decrement value for the at least one parameter associated with the current value of the at least one operating variable of the engine; and
adjusting the setpoint value of the at least one parameter by applying thereto the decrement value extracted from the table.

2. A method according to claim 1 , wherein the at least one operating variable of the engine is selected from:
a temperature at an inlet to the engine; and
an atmospheric pressure at the inlet to the engine.

3. A method according to claim 1 , wherein the engine is a turbojet and the at least one parameter is selected from:
a speed of rotation of a compressor of the turbojet;
a surge margin of the compressor; and
a richness of a combustion mixture of the turbojet.

4. A method according to claim 3 , wherein, during the adjustment, the setpoint value of the speed of rotation of the compressor and the setpoint value of the surge margin are adjusted.

5. A method according to claim 1 , wherein the decrement value extracted from the table for each parameter also depends on a current speed and/or a load of the aircraft.

6. A method according to claim 1 , wherein the stage of flight is a stage of the aircraft taking off and the decrement value extracted from the table for each parameter also depends on a length of a runway used by the aircraft during the takeoff stage.

7. A method according to claim 1 , wherein during the adjustment, the value of the decrement applied to the setpoint value is weighted by a weighting factor of less than 1.

8. A method according to claim 7 , wherein the weighting factor depends on a state of advance of the flight stage.

9. A non-transitory computer readable medium including a computer program including instructions for executing the method according to claim 1 when the program is executed by a computer.

10. Use, for regulating a thrust of a gas turbine engine propelling an aircraft during a stage of flight, of a setpoint value for at least one parameter that influences the thrust that has been adjusted according to the method of claim 1 .

Assignees

• Snecma

Inventors

• Belghagi Hichem
• Clermonte Sylvain
• Garin Laurence

Classifications

• F05D2270/313

  Air temperature · CPC title

• F05D2270/303

  Temperature · CPC title

• F05D2270/708

  with comparison tables · CPC title

• F05D2270/304

  Spool rotational speed · CPC title

• F02C9/28

  Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) · CPC title