Systems and methods for operating gas turbine engines
AssigneePratt & Whitney Canada Corp.
InventorsPhilippe Beauchesne-Martel, Keith Morgan
Life of this patent
Estimating the term…
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.
Claims18
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.
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.
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.
Dependencies are inferred from the claim text.