Automatic engine fuel flow monitoring and alerting fuel leak detection method

• US 20080125930A1
• Filed: 11/29/2006
• Published: 05/29/2008
• Est. Priority Date: 11/29/2006
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Johnson, Richard A.
• Granted Patent: US 7,739,004 B2
• Time in Patent Office: Days
• US Class Current: 701/29
• CPC Class Codes: F02C 9/42 specially adapted for the control of two or more plants simultaneously
• CPC Class Codes: F02C 9/46 Emergency fuel control

Abstract

A method for automatically monitoring and alerting a fuel leak downstream of an engine fuel flow meter in an aircraft is provided. The method uses existing engine sensor data to input into a predetermined parameter model to predict the nominal fuel flow, and also compares fuel flow between a left engine and a right engine.

Claims

1. A method for automatically monitoring and alerting a fuel leak downstream of an engine fuel flow meter in an aircraft, the method comprising the steps of:

obtaining a predicted fuel flow rate for each engine of the aircraft based on a set of predetermined reference operating parameters for each engine;

obtaining a measured fuel flow rate for each engine of the aircraft based on actual operating parameters for each engine;

using an engine monitoring system software to compare the predicted fuel flow rate to the measured fuel flow rate; and

,

automatically providing an alert on a flight deck display if there is a difference above a nuisance threshold between the measured fuel flow rate and the predicted fuel flow rate.

2. The method of claim 1 wherein the alert displayed on the flight deck display is “

ENG FF HIGH L,R”

.

3. The method of claim 1 wherein the predetermined reference operating parameters of the engine include engine thrust, airspeed, altitude, outside air temperature, engine accessory loads, and engine age.

4. The method of claim 1 wherein the aircraft is a multi-engine aircraft.

5. The method of claim 1 wherein the method provides alerts for excessive engine fuel flow, possible engine fuel leaks, secondary engine indications, fuel flow to the affected engine, and expanded fuel quantity indications.

6. The method of claim 1 wherein the nuisance threshold is determined by a numerical probability analysis.

7. The method of claim 1 wherein the alert is an illuminated message displayed on the flight deck display in a cockpit.

8. A method for automatically monitoring and alerting a fuel leak downstream of an engine fuel flow meter in a multi-engine aircraft, the method comprising the steps of:

obtaining a first thrust setting of a first engine and a second thrust setting of a second engine, such that the first thrust setting is equivalent to the second thrust setting;

obtaining a fuel flow rate for the first engine and a fuel flow rate for the second engine;

using an engine monitoring system software to compare the fuel flow rate for the first engine to the fuel flow rate of the second engine; and

,

automatically providing an alert on a flight deck display if there is a difference above a nuisance threshold between the fuel flow rate of the first engine and the fuel flow rate of the second engine.

9. The method of claim 8 wherein the alert displayed on the flight deck display is “

ENG FF DISAGREE”

.

10. The method of claim 8 wherein the aircraft has two engines where a first engine is located on a first side of the aircraft and a second engine is located on a second side of the aircraft.

11. The method of claim 8 wherein the method provides alerts for fuel flow rate disagreement between the first and second engines, the possible engine fuel leaks, secondary engine indications, and expanded fuel quantity indications.

12. The method of claim 8 wherein the nuisance threshold is determined by a numerical probability analysis.

13. The method of claim 8 wherein the alert is an illuminated message displayed on the flight deck display in a cockpit.

14. An automatic engine fuel flow monitoring and alerting fuel leak detection method for use with a two engine aircraft, the method comprising the steps of:

obtaining a predicted fuel flow rate for each engine of the aircraft based on a set of predetermined reference operating parameters for each engine;

obtaining a measured fuel flow rate for each engine of the aircraft based on actual operating parameters for each engine;

using an engine monitoring system software to compare the predicted fuel flow rate to the measured fuel flow rate;

automatically providing an alert on a flight deck display if there is a difference above a nuisance threshold between the measured fuel flow rate and the predicted fuel flow rate;

obtaining a thrust setting for each engine and making sure the thrust setting for each engine is equivalent;

obtaining a fuel flow rate for each engine;

using the engine monitoring system software to compare the fuel flow rate of each engine; and

,

automatically providing an alert on the flight deck display if there is a difference above a nuisance threshold between the fuel flow rate of each engine.

15. The method of claim 14 wherein the method automatically monitors and alerts a fuel leak downstream of an engine fuel flow-meter in the aircraft.

16. The method of claim 14 wherein the predetermined reference operating parameters of the engine include engine thrust, airspeed, altitude, outside air temperature, engine accessory loads, and engine age.

17. The method of claim 14 wherein the method provides alerts for possible engine fuel leaks, secondary engine indications, and expanded fuel quantity indications.

18. The method of claim 14 wherein the nuisance threshold is determined by a numerical probability analysis.

19. The method of claim 14 wherein the alert is an illuminated message displayed on the flight deck display in a cockpit.

20. The method of claim 14 wherein a first engine is located on a first side of the aircraft and a second engine is located on a second side of the aircraft.