Systems and methods for operating gas turbine engines

Patent metadata

Field	Value
Publication number	US-11236681-B2
Application number	US-201916665520-A
Country	US
Kind code	B2
Filing date	Oct 28, 2019
Priority date	Sep 25, 2019
Publication date	Feb 1, 2022
Grant date	Feb 1, 2022

Abstract

Methods and systems for operating a gas turbine engine having variable geometry mechanisms are described. The method comprises detecting a failure event associated with the gas turbine engine, identifying a location of the failure event, selecting an aerodynamic load modulation schedule for the variable geometry mechanisms of the gas turbine engine as a function of the location of the failure event, and applying the aerodynamic load modulation schedule as selected to the variable geometry mechanisms during the failure event.

First claim

The invention claimed is:

1. A method for operating a gas turbine engine having variable geometry mechanisms, the method comprising:
detecting a failure event associated with the gas turbine engine;
identifying a location of the failure event from one of a shaft shear location and a fuel control unit location;
selecting an aerodynamic load modulation schedule for the variable geometry mechanisms of the gas turbine engine from a plurality of aerodynamic load modulation schedules as a function of the location of the failure event; and
applying the aerodynamic load modulation schedule as selected to the variable geometry mechanisms during the failure event.

2. The method of claim 1 , wherein selecting the shaft shear location comprises selecting one of a first location, a second location, and a third location.

3. The method of claim 2 , wherein the variable geometry mechanisms comprise a first set of variable guide vanes and a second set of variable guide vanes, and wherein the aerodynamic load modulation schedule assigns a first position to the first set of variable guide vanes and a second position to the second set of variable guide vanes.

4. The method of claim 3 , wherein the aerodynamic load modulation schedule assigns the first set of variable guide vanes and the second set of variable guide vanes to an open position when the shaft shear location is the first location.

5. The method of claim 3 , wherein the aerodynamic load modulation schedule assigns the first set of variable guide vanes to a closed position and the second set of variable guide vanes to an open position when the shaft shear location is the second location.

6. The method of claim 3 , wherein the aerodynamic load modulation schedule assigns the first set of variable guide vanes and the second set of variable guide vanes to a closed position when the shaft shear location is the third location.

7. The method of claim 3 , wherein the aerodynamic load modulation schedule assigns the first set of variable guide vanes and the second set of variable guide vanes to a closed position when the location of the failure event is the fuel control unit location.

8. The method of claim 1 , wherein applying the aerodynamic load modulation schedule comprises applying a control signal to the variable geometry mechanisms to step change a position of the variable geometry mechanisms.

9. A system for operating a gas turbine engine having variable geometry mechanisms, the system comprising:
a processing unit; and
a non-transitory computer-readable medium having stored thereon program instructions executable by the processing unit for:
detecting a failure event associated with the gas turbine engine;
identifying a location of the failure event from one of a shaft shear location and a fuel control unit location;
selecting an aerodynamic load modulation schedule for the variable geometry mechanisms of the gas turbine engine from a plurality of aerodynamic load modulation schedules as a function of the location of the failure event; and
applying the aerodynamic load modulation schedule as selected to the variable geometry mechanisms during the failure event.

10. The system of claim 9 , wherein selecting the shaft shear location comprises selecting one of a first location, a second location, and a third location.

11. The system of claim 10 , wherein the variable geometry mechanisms comprise a first set of variable guide vanes and a second set of variable guide vanes, and wherein the aerodynamic load modulation schedule assigns a first position to the first set of variable guide vanes and a second position to the second set of variable guide vanes.

12. The system of claim 11 , wherein the aerodynamic load modulation schedule assigns the first set of variable guide vanes and the second set of variable guide vanes to an open position when the shaft shear location is the first location.

13. The system of claim 11 , wherein the aerodynamic load modulation schedule assigns the first set of variable guide vanes to a closed position and the second set of variable guide vanes to an open position when the shaft shear location is the second location.

14. The system of claim 11 , wherein the aerodynamic load modulation schedule assigns the first set of variable guide vanes and the second set of variable guide vanes to a closed position when the shaft shear location is the third location.

15. The system of claim 11 , wherein the aerodynamic load modulation schedule assigns the first set of variable guide vanes and the second set of variable guide vanes to a closed position when the location of the failure event is the fuel control unit location.

16. The system of claim 9 , wherein applying the aerodynamic load modulation schedule comprises applying a control signal to the variable guide vanes to step change a position of the variable guide vanes.

17. A system comprising:
a gas turbine engine having variable geometry mechanisms; and
a control system operatively connected to the gas turbine engine and configured for:
detecting a failure event associated with the gas turbine engine;
identifying a location of the failure event from one of a shaft shear location and a fuel control unit location; and
applying an aerodynamic load modulation schedule to the variable geometry mechanisms from a plurality of aerodynamic load modulation schedules during the failure event as a function of the location of the failure event.

18. The system of claim 17 , wherein identifying the location of the failure event comprises determining a position of a shaft shear along at least one shaft of the gas turbine engine.

Assignees

• Pratt & Whitney Canada

Inventors

• Beauchesne-Martel Philippe
• Morgan Keith

Classifications

• F01D17/06

  responsive to speed · CPC title

• F02C9/28

  Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) · CPC title

• F02C9/54

  by throttling the working fluid, by adjusting vanes · CPC title

• F02C9/46

  Emergency fuel control · CPC title

• F04D27/0246

  by varying geometry within the pumps, e.g. by adjusting vanes · CPC title