Patent ID: 11913387
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 18:
19. A non-transitory, machine-accessible storage medium having computer instructions and wherein the instructions are configured, when executed by a controller, to cause the controller to:
receive a determined minimum creep life location (MCLL) for a turbine blade design, the MCLL being a location at which minimum creep life occurs on the turbine blade design that fails fastest due to creep;
monitor a temperature of the MCLL on a turbine blade having the turbine blade design in an aircraft engine using at least one sensor; and
when the temperature of the MCLL exceeds a predetermined temperature threshold, adjust a temperature of air flowing about the turbine blade as the aircraft engine is operating.