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US 11,913,387 B2Granted
Method and apparatus for cooling turbine blades
AssigneeGeneral Electric Company
InventorsConstantinos Minas, William Morton
Life of this patent
Estimating the term…
Abstract
A minimum creep life location (MCLL) on a blade for a turbine blade design is received. A temperature at the MCLL on the blade is monitored. When the temperature at the MCLL exceeds a predetermined threshold, a cooling air supply is adjusted to lower the temperature below the threshold during engine operation.
Claims20
A method for controlling an operational condition of a turbine blade, the method comprising:
- determining a 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;
- monitoring 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, adjusting a temperature of air flowing about the turbine blade as the aircraft engine is operating.
1 more element
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.
5 more elements
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.
1 more element
Dependencies are inferred from the claim text.