Multi-variable fleet optimisation method and system

Patent metadata

Field	Value
Publication number	US-11567459-B2
Application number	US-201916580463-A
Country	US
Kind code	B2
Filing date	Sep 24, 2019
Priority date	Oct 1, 2018
Publication date	Jan 31, 2023
Grant date	Jan 31, 2023

Abstract

A method of optimizing the operation of a fleet of gas turbine engines is provided. The method comprises the steps of: (a) measuring respective values for plural control actuator settings within each of the gas turbine engines; (b) deriving, based on data external to the operation of the gas turbine engines, a desired performance modification of the gas turbine engines; (c) determining, based on the measured control actuator settings, one or more respective trim signals for varying selected of the control actuator settings to achieve the desired performance modification; and (d) transmitting the trim signals to respective electronic controllers of the engines to vary the selected control actuator settings accordingly.

First claim

We claim:

1. A method of optimizing the operation of a fleet of gas turbine engines, the method comprising the steps of:
(a) measuring respective values for plural control actuator settings within each of the gas turbine engines;
(b) deriving, based on data external to the operation of the gas turbine engines, a desired performance modification of the gas turbine engines;
(c) determining, based on the measured control actuator settings, one or more trim signals for respectively varying selected of the control actuator settings to achieve the desired performance modification; and
(d) transmitting the trim signals to respective electronic controllers of the engines to vary the selected control actuator settings accordingly.

2. The method of claim 1 , wherein respective values of three or more control actuator settings are measured within each of the gas turbine engines.

3. The method of claim 1 , wherein the step of determining the one or more trim signals is further based on current values of one or more engine state parameters of one or more of the gas turbine engines.

4. The method of claim 1 , wherein the data external to the operation of the gas turbine engines include data indicative of at least one of: a flight logistics plan for an aircraft including at least one of the gas turbine engines; an availability of service personnel; a service interval time of at least one of the gas turbine engines; and an availability of consumables for the fleet of gas turbine engines.

5. The method of claim 1 , wherein the control actuator settings are selected from the group consisting of: a fuel flow rate; a variable geometry of one or more stators and/or one or more rotors of the gas turbine engine; a variable engine size; a variable nozzle area; and a variable fan pitch.

6. The method of claim 1 , wherein the gas turbine engines are geared turbofan engines.

7. A system for optimizing the operation of a fleet of gas turbine engines, the system comprising:
plural power managers local to and connected to the gas turbine engines, and configured to measure values for plural control actuator settings within each of the gas turbine engines; and
a remote, fleet management computer system in communication with each of the power managers, and configured to derive, based on data external to the operation of the gas turbine engines, a desired performance modification of the gas turbine engines;
wherein either the power managers are further configured to determine or the fleet management computer system is further configured to determine, based on the measured control actuator settings, one or more trim signals for respectively varying selected of the control actuator settings to achieve the desired performance modification; and
wherein the power managers are further configured to transmit the trim signals to respective electronic controllers of the engines to vary the selected control actuator settings accordingly.

8. The system of claim 7 , wherein respective values of three or more control actuator settings are measured within each of the gas turbine engines.

9. The system of claim 7 , wherein one or more of the power managers are further configured to measure current values of one or more engine state parameters of one or more of the gas turbine engines, and the determination of the one or more trim signals is further based on the measured current values of the engine state parameters.

10. The system of claim 7 , wherein the data external to the operation of the gas turbine engines include data indicative of at least one of: a flight logistics plan for an aircraft including at least one of the gas turbine engines; an availability of service personnel; an availability of maintenance equipment; a service interval time of at least one of the gas turbine engines; and an availability of consumables for the fleet of gas turbine engines.

11. The system of claim 7 , wherein the control actuator settings are selected from the group consisting of: a fuel flow rate; a variable geometry of one or more stators and/or one or more rotors of the gas turbine engine; a variable engine size; a variable nozzle area; and a variable fan pitch.

12. The system of claim 8 , wherein the gas turbine engines are geared turbofan engines.

13. A non-transitory computer program comprising code for optimizing the operation of a fleet of gas turbine engines, the code, when run on a computer, causing the computer to perform a method comprising the steps of:
(a) receiving respective measured values for plural control actuator settings within each of the gas turbine engines;
(b) deriving, based on data external to the operation of the gas turbine engines, a desired performance modification of the gas turbine engines;
(c) determining, based on the measured control actuator settings, one or more trim signals for respectively varying selected of the control actuator settings to achieve the desired performance modification; and
(d) transmitting the trim signals to respective electronic controllers of the engines to vary the selected control actuator settings accordingly.

14. The computer program of claim 13 stored on a non-transitory computer readable medium.

Assignees

• Rolls Royce Plc

Inventors

• Wall Derek S
• Goldberg Chana T
• Laskaridis Panagiotis
• Nalianda Devaiah K

Classifications

• G05B13/024 Primary

  in which a parameter or coefficient is automatically adjusted to optimise the performance · CPC title

• F02C9/285

  Mechanical command devices linked to the throttle lever · CPC title

• F02C6/206

  the vehicles being airscrew driven · CPC title

• G08G5/003

  Physics · mapped topic

• G08G5/30

  Flight plan management · CPC title