Abstract: A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.

Abstract: A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.

Abstract: A method for reducing a turbine clearance between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. Said method includes determining, with a flight operation controller, that an airplane is in a first flight condition, wherein the first flight condition is associated with a first turbine clearance and a first engine responsiveness level, determining, with the flight operation controller, that the airplane is in a second flight condition, adjusting an engine responsiveness level from the first engine responsiveness level to a second engine responsiveness level based on determining the airplane is in the second flight condition, and adjusting the turbine clearance from the first turbine clearance to a second turbine clearance based on the engine responsiveness level.

Abstract: A precision method is defined for identifying defective sections of a spoolable material for removal. Defective sections are noted during manufacture and the spool containing the material is subsequently unwound to allow removal of the defective sections. The invention uses rotation data corresponding to the location on the spool where the fiber contains defects. A process controller records rotational positioning data from the take-up spool during manufacturing and uses the information to locate the defect when unwinding the spool. In addition, the pitch of winding the fiber onto the spool may be altered during manufacturing to indicate the beginning and end of a defective section. In this instance, the defective portion of the fiber can be determined during unwinding by monitoring the pitch width of the material. Finally, an algorithm for defining cut out bands adjacent to the defective sections aid in ensuring that no remaining defective fiber remains.

Abstract: A precision method is defined for identifying defective sections of a spoolable material for removal. Defective sections are noted during manufacture and the spool containing the material is subsequently unwound to allow removal of the defective sections. The invention uses rotation data corresponding to the location on the spool where the fiber contains defects. A process controller records rotational positioning data from the take-up spool during manufacturing and uses the information to locate the defect when unwinding the spool. In addition, the pitch of winding the fiber onto the spool may be altered during manufacturing to indicate the beginning and end of a defective section. In this instance, the defective portion of the fiber can be determined during unwinding by monitoring the pitch width of the material. Finally, an algorithm for defining cut out bands adjacent to the defective sections aid in ensuring that no remaining defective fiber remains.