Method and device for determining the capacity of an aircraft pump to deliver a predetermined fuel output

Patent metadata

Field	Value
Publication number	US-9249683-B2
Application number	US-201213372777-A
Country	US
Kind code	B2
Filing date	Feb 14, 2012
Priority date	Feb 16, 2011
Publication date	Feb 2, 2016
Grant date	Feb 2, 2016

Abstract

The invention proposes a method for determining the capacity of an aircraft pump to deliver a predetermined fuel flow rate,
characterised in that it comprises
a step of rotating the pump at a predetermined speed; a step of supplying at least one cylinder with the totality of the fuel coming out of the pump; a step of determining the fuel flow rate supplying said cylinder, and a diagnostic step which consists in determining whether the pump is able to supply a sufficient flow rate as a function of the determined value of the flow rate supplying the cylinder.

The invention also proposes a device implementing the method.

First claim

The invention claimed is:

1. A method for determining the capacity of an aircraft pump to deliver a predetermined fuel flow rate,
in which the pump is able to supply fuel to a combustion chamber of a turbine engine of the aircraft and a fuel distribution circuit to a plurality of cylinders for actuating moving components of the turbine engine,
and in which said predetermined flow rate is a fuel flow rate supplying the combustion chamber making it possible to perform a restart up of the turbine engine after stoppage while the aircraft is in flight,
comprising:
a step of rotating the pump at a predetermined rotation speed;
a supply step including maintaining the rotation speed of the pump at the predetermined rotation speed and supplying at least one of said cylinders with the totality of the fuel coming out of the pump;
a step of determining the fuel flow rate supplying said at least one cylinder, and
a diagnostic step which consists of determining whether the pump is able to supply a sufficient flow rate when the determined value of the flow rate supplying said at least one cylinder is at least equal to the predetermined flow rate value.

2. The method according to claim 1 , wherein the step of determining the fuel flow rate comprises a phase of measuring the displacement speed of said at least one cylinder and a phase of calculating the flow rate as a function of the displacement speed and as a function of the dimensions of said at least one cylinder.

3. The method according to claim 1 , wherein the step of rotating the pump consists of turning the pump at a rotation speed substantially equal to a rotation speed of the pump when the turbine engine is in autorotation.

4. The method according to claim 3 , wherein the step of rotating is implemented by an electric starter of the turbine engine.

5. The method according to claim 3 or 4 , wherein the supply step consists of supplying a single cylinder.

6. The method according to claim 1 , wherein the step of rotating the pump consists of turning the pump at a rotation speed greater than a rotation speed of the pump when the turbine engine is in autorotation.

7. The method according to claim 6 , wherein the step of rotating is implemented by an electric starter of the turbine engine.

8. The method according to claim 6 , wherein the supply step consists of supplying several cylinders.

9. The method according to claim 1 , wherein it is implemented while the aircraft is stopped and is on the ground and in that the step of determining the flow rate comprises a phase of correction of the determined value of the flow rate supplying said at least one cylinder as a function of the ambient pressure and temperature conditions on the ground and the pressure and temperature conditions at altitude.

10. A device implementing a method for determining the capacity of an aircraft pump to deliver a predetermined fuel flow rate, according to claim 1 , comprising:
means of driving the pump up to a predetermined speed;
means of distributing the fluid at the output of the pump to at least one cylinder of the turbine engine;
means of calculating the fuel flow rate supplying said at least one cylinder; and
diagnostic means that determine whether the pump is able to deliver a predetermined fuel flow rate as a function of the fuel flow rate supplying said at least one cylinder.

11. The device according to claim 10 , wherein said means of calculating the fuel flow rate supplying the cylinder comprise means of measuring the displacement speed of the cylinder and means of measuring the position of said at least one cylinder.

12. The device according to claim 10 , wherein the drive means of the pump comprise an electric starter of the turbine engine.

13. The device according to claim 12 , wherein the drive means of the pump comprise means of regulating the drive speed of the electric starter.

14. The device according to claim 10 , wherein the drive means of the pump consist of a pneumatic starter of the turbine engine.

Assignees

• Bader Nicolas Alain
• Snecma

Inventors

• Bader Nicolas Alain

Classifications

• F05D2260/85

  Starting · CPC title

• F04C14/08

  characterised by varying the rotational speed · CPC title

• F05D2260/80

  Diagnostics · CPC title

• F02C7/236

  Fuel delivery systems comprising two or more pumps · CPC title

• F01D21/003 Primary

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title