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

Claim 9:
10. A system, comprising:
at least one sensor;
a turbine blade coupled to a rotating shaft of an aircraft engine; and
a controller, the controller coupled to the at least one sensor, the controller being configured to:
receive a determined minimum creep life location (MCLL) for a turbine blade design, the MCLL being a location as to where minimum creep life occurs on the turbine blade design that fails fastest due to creep;
via the at least one sensor, monitor a temperature of the MCLL for a turbine blade having the turbine blade design; and
when the temperature of the MCLL exceeds a predetermined temperature threshold, send one or more first control signals to cause an adjustment of an operation of a temperature adjustment apparatus, the adjustment of the operation of the temperature adjustment apparatus being effective to cool a temperature of air flowing about the turbine blade as the aircraft engine is operating.