Control device of a variable section nozzle and the implementation method thereof

Patent metadata

Field	Value
Publication number	US-10787995-B2
Application number	US-201715619858-A
Country	US
Kind code	B2
Filing date	Jun 12, 2017
Priority date	Dec 11, 2014
Publication date	Sep 29, 2020
Grant date	Sep 29, 2020

Abstract

The present disclosure provides a device for controlling a variable section ejection nozzle of a turbojet engine nacelle of an aircraft. The device includes a calculator adapted to determine a position setpoint of the nozzle and a management system of the servo-control of the position of the variable nozzle depending on the flow rate of the fuel supplying the turbojet engine. The management system includes at least one instantaneous flow rate sensor of the fuel and a management unit which is designed to compare the flow rate measured by the flow rate sensor with a theoretical fuel flow rate depending on the parameters of the flight of the aircraft, to determine a correction value of the position of the nozzle depending on the comparison of the measured flow rate and the theoretical fuel flow rate, and to correct the position setpoint of the nozzle according to the correction value.

First claim

What is claimed is:

1. A device for controlling a variable section ejection nozzle of a turbojet engine nacelle of an aircraft, the device comprising:
a calculator that determines a theoretical position setpoint of the nozzle based on flight parameters of the aircraft;
a device configured to actuate the nozzle and associated to said calculator, the device adapted to control a position of the nozzle according to the theoretical position setpoint;
a measuring device for measuring the position of the nozzle; and
a management system including at least one instantaneous flow rate sensor for measuring an actual flow rate of fuel supplied to a turbojet engine and a management unit, wherein the management unit:
compares the actual flow rate measured by the at least one instantaneous flow rate sensor with a theoretical flow rate of fuel corresponding to the theoretical position setpoint of the nozzle;
determines a correction value of the position of the nozzle based on a comparison of the actual flow rate and the theoretical flow rate of fuel; and
corrects a position setpoint of the nozzle according to the correction value such that a difference between the theoretical flow rate and the actual flow rate is reduced to compensate for inaccuracies in the position of the nozzle due to manufacturing tolerance and wear of the nozzle during operation.

2. The control device according to claim 1 , wherein the management unit is operable to vary the position of the nozzle in a plurality of positions and to measure the actual flow rate for the position of the nozzle to determine a position offering improved operation efficiency of the turbojet engine based on the theoretical flow rate such that the difference between the theoretical flow rate and the actual flow rate is reduced.

3. The control device according to claim 1 , wherein the management system further includes a data storage unit which contains a data table of the theoretical flow rate depending on the parameters of flight of the aircraft.

4. The control device according to claim 3 , wherein the data table is adapted to be updated.

5. The control device according to claim 3 , wherein the data storage unit is adapted to record the correction value of the position of the nozzle during several flights.

6. The control device according to claim 1 , wherein the management system further includes an integrator adapted to calculate an integral of the measured actual flow rate over time to refine an accuracy of the measured actual flow rate.

7. A method for implementation of a control device of a variable section ejection nozzle of a turbojet engine nacelle of an aircraft, said device being in accordance with claim 1 , the method comprising:
determining a theoretical position setpoint of the nozzle based on flight parameters of the aircraft;
actuating the nozzle to a position according to the theoretical position setpoint;
measuring the position of the nozzle;
comparing a flow rate measured by a flow rate sensor and a theoretical flow rate;
determining a correction value of the position of the nozzle based on the comparison of the measured flow rate and the theoretical flow rate; and
correcting the position setpoint of the nozzle according to the correction value obtained in the determination step such that a difference between the theoretical flow rate and the measured flow rate is reduced to compensate for inaccuracies in the position of the nozzle due to manufacturing tolerance and wear of the nozzle during operation.

8. The method according to claim 7 further comprising determining an improved operation comprising:
varying the position of the nozzle in a plurality of different positions according to different position setpoints of the nozzle; and
measuring the flow rate corresponding to the position of the nozzle to determine an enhanced efficiency of a turbojet engine based on the theoretical flow rate.

9. The method according to claim 8 , wherein the step of determining an improved operation comprises a recording phase which includes recording a position allowing improved efficiency according to the flight parameters.

Assignees

• Safran Aircraft Engines

Inventors

• Caruel Pierre

Classifications

• F05D2270/114

  by limiting mechanical stresses · CPC title

• F02K3/06 Primary

  with front fan · CPC title

• F05D2270/07

  to improve fuel economy · CPC title

• F05D2270/703

  integral · CPC title

• F05D2270/821

  Displacement measuring means, e.g. inductive · CPC title