Device and method for regulating a motor using a thrust measurement

Patent metadata

Field	Value
Publication number	US-10450966-B2
Application number	US-201514956851-A
Country	US
Kind code	B2
Filing date	Dec 2, 2015
Priority date	Dec 5, 2014
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

A device for regulating the flow rate of fuel supplied to an aircraft engine, configured to produce a fuel flow rate set value according to a thrust set value supplied by a gas control lever and a measurement of actual thrust of the engine. It extends to a control system including the regulation device and a device for measuring the actual thrust of the engine, to an engine equipped with such a control system, to a regulation method and to a computer program for implementing the method.

First claim

The invention claimed is:

1. A device for regulating a flow rate of fuel supplied to an engine in an aircraft, comprising:
an engine speed set value calculator configured to produce an engine speed set value from a thrust set value supplied by a gas control lever, based on a model linking the thrust set value to the engine speed set value, and
a fuel flow rate set value circuit configured to:
produce a fuel flow rate set value from the engine speed set value and a measurement of an actual speed of the engine, and
control a metering unit of the engine based on said fuel flow rate set value so as to regulate the flow rate of fuel supplied to the engine,

wherein the engine speed set value calculator is configured to provide a correction factor to the model linking the thrust set value to the engine speed set value based on non-continuous measurements of actual thrust provided by an actual thrust measuring device configured to make measurements of deformation of a thrust forces absorbing device interposed between the engine and the aircraft, and
wherein the correction factor modifies the model based on the measurements of actual thrust.

2. The device according to claim 1 , wherein the non-continuous measurements of actual thrust are made when attitudes of the aircraft do not vary.

3. The device according to claim 1 , wherein the device is further configured to standardize the actual thrust measurements of the engine to eliminate dependency of said actual thrust measurements vis-a-vis an external context.

4. The device according to claim 3 , wherein attitude data supplied by an inertial unit is used as data representing the external context.

5. A system for controlling an aircraft engine, comprising a regulation device according to claim 1 , wherein the actual thrust measuring device supplies supplying said measurements of actual thrust of the engine to the regulation device.

6. The system according to claim 5 , wherein the thrust forces absorbing device comprises at least one connecting rod and wherein the actual thrust measuring device of the engine comprises at least one deformation sensor arranged on the at least one connecting rod.

7. An aircraft engine equipped with a control system according to claim 5 .

8. A method for regulating a flow rate of fuel supplied to an engine in an aircraft, comprising:
producing an engine speed set value from a thrust set value supplied by a gas control lever, based on a model linking the thrust set value to the engine speed set value;
producing a fuel flow rate set value from the engine speed set value and a measurement of an actual speed of the engine; and
controlling a metering unit of the engine based on said fuel flow rate set value so as to regulate the flow rate of fuel supplied to the engine,
wherein a correction factor is provided to the model linking the thrust set value to the engine speed set value based on non-continuous measurements of actual thrust provided by an actual thrust measuring device configured to make measurements of deformation of a thrust forces absorbing device interposed between the engine and the aircraft, and
wherein the correction factor modifies the model based on the measurements of actual thrust.

9. A non-transitory computer readable medium including a computer program comprising code instructions for implementing a method of regulating a flow rate of fuel supplied to an engine in an aircraft when said program is executed on a computer, said method comprising:
producing an engine speed set value from a thrust set value, based on a model linking the thrust set value to the engine speed set value;
producing a fuel flow rate set value from the engine speed set value and a measurement of an actual speed of the engine;
providing a correction factor to the model linking the thrust set value to the engine speed set value based on non-continuous measurements of actual thrust provided by an actual thrust measuring device configured to make measurements of deformation of a thrust forces absorbing device interposed between the engine and the aircraft; and
controlling a metering unit of the engine based on said fuel flow rate set value so as to regulate the flow rate of fuel supplied to the engine,
wherein the correction factor modifies the model based on the measurements of actual thrust.

10. The device according to claim 1 , wherein the actual thrust measuring device includes a deformation sensor provided on a connecting link.

Assignees

• Safran Aircraft Engines

Inventors

• Blanchard Serge
• Bense William

Classifications

• F05D2270/051

  Thrust · CPC title

• F05D2270/702

  differential · CPC title

• F02C9/32 Primary

  characterised by throttling of fuel (F02C9/38 takes precedence) · CPC title

• F02K3/00

  Plants including a gas turbine driving a compressor or a ducted fan · CPC title

• F05D2270/44

  active, predictive, or anticipative · CPC title