Monitoring fluid consumption of gas turbine engine during an engine cycle

Patent metadata

Field	Value
Publication number	US-11959386-B2
Application number	US-202217712882-A
Country	US
Kind code	B2
Filing date	Apr 4, 2022
Priority date	Apr 4, 2022
Publication date	Apr 16, 2024
Grant date	Apr 16, 2024

Abstract

A method is provided for a gas turbine engine. During this method, a first lubricant parameter is determined during a first period of an engine operating cycle. The first lubricant parameter is indicative of a first quantity of lubricant within a reservoir of the gas turbine engine. A second lubricant parameter is determined during a second period of the engine operating cycle. The second lubricant parameter is indicative of a second quantity of the lubricant within the reservoir. The first lubricant parameter and the second lubricant parameter are compared to determine a lubricant consumption parameter. The lubricant consumption parameter is indicative of a quantity of the lubricant consumed by the gas turbine engine during the engine operating cycle.

First claim

What is claimed is:

1. A method for a gas turbine engine, comprising:
determining a first lubricant parameter during a first period of an engine operating cycle, the first lubricant parameter indicative of a first quantity of lubricant within a reservoir of the gas turbine engine, and the engine operating cycle corresponding to operation of the gas turbine engine for a single aircraft flight;
determining a second lubricant parameter during a second period of the engine operating cycle, the second lubricant parameter indicative of a second quantity of the lubricant within the reservoir; and
comparing the first lubricant parameter and the second lubricant parameter to determine a lubricant consumption parameter, the lubricant consumption parameter indicative of a quantity of the lubricant consumed by the gas turbine engine during the engine operating cycle.

2. The method of claim 1 , further comprising:
measuring a parameter of the lubricant within the reservoir at a first point during the first period of the engine operating cycle to provide a first measured parameter; and
normalizing the first measured parameter to provide a normalized first measured parameter;
wherein the first lubricant parameter is determined based on the normalized first measured parameter.

3. The method of claim 2 , further comprising:
measuring the parameter of the lubricant within the reservoir at a second point during the first period of the engine operating cycle to provide a second measured parameter; and
normalizing the second measured parameter to provide a normalized second measured parameter;
wherein the first lubricant parameter is determined further based on the normalized second measured parameter.

4. The method of claim 3 , wherein the determining of the first lubricant parameter comprises processing the normalized first measured parameter and the normalized second measured parameter to determine at least one of
an average normalized measured parameter;
a median normalized measured parameter;
a minimum normalized measured parameter; or
a maximum normalized measured parameter.

5. The method of claim 1 , further comprising communicating information based on the lubricant consumption parameter.

6. The method of claim 5 , wherein the information is communicated to at least one of personnel operating the gas turbine engine or personnel servicing the gas turbine engine.

7. The method of claim 1 , further comprising:
determining a second lubricant consumption parameter, the second lubricant consumption parameter indicative of a quantity of the lubricant consumed by the gas turbine engine during a second engine operating cycle; and
processing at least the lubricant consumption parameter and the second lubricant consumption parameter to determine a lubricant consumption trend over a plurality of operating cycles of the gas turbine engine.

8. The method of claim 1 , wherein the gas turbine engine is operated at idle during the first period of the engine operating cycle and the second period of the engine operating cycle.

9. The method of claim 8 , wherein the gas turbine engine is operated above idle during an intermediate period of the engine operating cycle occurring between the first period of the engine operating cycle and the second period of the engine operating cycle.

10. The method of claim 1 , wherein a first speed of a rotating assembly of the gas turbine engine during the first period of the engine operating cycle is substantially equal to a second speed of the rotating assembly during the second period of the engine operating cycle.

11. The method of claim 1 , wherein
a centerline of the gas turbine engine is at a first position relative to a horizon line during the first period of the engine operating cycle; and
the centerline of the gas turbine engine is at a second position relative to the horizon line during the second period of the engine operating cycle that is substantially equal to the first position.

12. The method of claim 1 , wherein a first temperature of the lubricant during the first period of the engine operating cycle is substantially equal to a second temperature of the lubricant during the second period of the engine operating cycle.

13. The method of claim 1 , wherein
the lubricant flows at a first flowrate during the first period of the engine operating cycle; and
the lubricant flows at a second flowrate during the second period of the engine operating cycle that is substantially equal to the first flowrate.

14. The method of claim 1 , wherein
the gas turbine engine is configured with an aircraft; and
the lubricant consumption parameter is determined onboard the aircraft.

15. The method of claim 1 , wherein
the gas turbine engine is configured with an aircraft; and
the lubricant consumption parameter is determined offboard the aircraft.

16. A method for a gas turbine engine, comprising:
determining a first lubricant parameter at engine idle prior to an aircraft flight, the first lubricant parameter indicative of a first quantity of lubricant within a reservoir of the gas turbine engine;
determining a second lubricant parameter at engine idle after the aircraft flight, the second lubricant parameter indicative of a second quantity of lubricant within the reservoir; and
determining a lubricant consumption parameter based on the first lubricant parameter and the second lubricant parameter, the lubricant consumption parameter indicative of a quantity of the lubricant consumed by the gas turbine engine during the aircraft flight.

17. A system for a gas turbine engine, comprising:
a lubricant system with a lubricant reservoir;
a sensor system configured to monitor lubricant within the lubricant reservoir; and
a monitoring system configured to
determine a first lubricant parameter based on first sensor data received from the sensor system while the gas turbine engine is operating during a first period of an operating cycle of the gas turbine engine, the first lubricant parameter indicative of a first quantity of lubricant within the lubricant reservoir;
determine a second lubricant parameter based on second sensor data received from the sensor system while the gas turbine engine is operating during a second period of the operating cycle of the gas turbine engine, the second lubricant parameter indicative of a second quantity of lubricant within the lubricant reservoir; and
determine a lubricant consumption parameter based on the first lubricant parameter and the second lubricant parameter, the lubricant consumption parameter indicative of a quantity of the lubricant consumed by the gas turbine engine during the operating cycle.

18. The system of claim 17 , wherein
the sensor system is further configured to measure a parameter of the lubricant within the reservoir at a first point during the first period of the operating cycle of the gas turbine engine to provide a first measured parameter;
the monitoring system is further configured to normalize the first measured parameter to provide a normalized first measured parameter; and
the first lubricant parameter is determined based on the normalized first measured parameter.

19. The method of claim 1 , further comprising communicating information to personnel where the lubricant comparison parameter is equal to or greater than a threshold, the information indicative of at least one of:
the quantity of the lubricant consumed by the gas turbine engine during the engine operating cycle;
a quantity of the lubricant remaining within the lubric

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Rocco Edward T
• Carey Grant A
• Schafer Bradley C

Classifications

• F01D21/003 Primary

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

• F01D25/18 Primary

  Lubricating arrangements (of machines or engines in general F01M) · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2260/80

  Diagnostics · CPC title

• F05D2260/98

  Lubrication · CPC title