초록 ▼

Methods, systems, and apparatus for controlling a turbine clearance in an aircraft engine are provided. A method includes activating a turbine clearance control based on a flight phase of an aircraft using the aircraft engine, and adjusting the turbine clearance based on a preselected turbine cleara

Methods, systems, and apparatus for controlling a turbine clearance in an aircraft engine are provided. A method includes activating a turbine clearance control based on a flight phase of an aircraft using the aircraft engine, and adjusting the turbine clearance based on a preselected turbine clearance value.

대표청구항 ▼

1. A method for controlling a turbine clearance in an aircraft engine, said method comprising: determining a flight phase of an aircraft;measuring at least one engine parameter;determining a rate of change of the at least one measured engine parameter; andcomparing the determined rate of change to a

1. A method for controlling a turbine clearance in an aircraft engine, said method comprising: determining a flight phase of an aircraft;measuring at least one engine parameter;determining a rate of change of the at least one measured engine parameter; andcomparing the determined rate of change to a predetermined rate of change of the measured engine parameter associated with the aircraft being in a stable flight phase;activating the turbine clearance control based on a flight phase of the aircraft using the aircraft engine; andadjusting the turbine clearance based on a preselected turbine clearance value. 2. A method in accordance with claim 1, further comprising enabling a turbine clearance control using a selection switch. 3. A method in accordance with claim 1, wherein activating a turbine clearance control comprises remotely activating the turbine clearance control when the aircraft is determined to be in the stable flight phase. 4. A method in accordance with claim 1, wherein activating a turbine clearance control comprises notifying an operator of the activation status of the turbine clearance control using a notification device. 5. A method in accordance with claim 1, further comprising determining a turbine clearance. 6. A method in accordance with claim 5, wherein adjusting the turbine clearance comprises: comparing the determined turbine clearance to the preselected turbine clearance value; andadjusting the turbine clearance based on the comparison. 7. A method in accordance with claim 1, further comprising deactivating the turbine clearance control at a preselected time prior to an end of the stable flight phase. 8. A turbine clearance control system for use with an aircraft engine, said system comprising: a switch;a notification device; anda controller coupled to said switch and to said notification device, said controller is configured to: activate said turbine clearance control system based on a flight phase of an aircraft using the aircraft engine; andadjust a turbine clearance within the aircraft engine based on a preselected turbine clearance value. 9. A turbine clearance control system in accordance with claim 8, wherein said switch is configured to enable operation of said controller in response to an operator input. 10. A turbine clearance control system in accordance with claim 8, wherein said switch is configured to enable operation of said controller in response to an input received from a remote operator. 11. A turbine clearance control system in accordance with claim 8, wherein said notification device is configured to notify an operator of an activation status of said turbine clearance control system using at least one of a display device and an audio device. 12. A turbine clearance control system in accordance with claim 8, wherein said controller is further configured to: measure at least one aircraft engine parameter;determine a rate of change for the at least one measured aircraft engine parameter;compare the determined rate of change to a predetermined rate of change of the at least one aircraft engine parameter, wherein the predetermined rate of change corresponds to a stable flight phase of the aircraft; andactivate said turbine clearance control system based when the flight phase is a stable flight phase. 13. A turbine clearance control system in accordance with claim 8, wherein said controller is further configured to determine the turbine clearance. 14. A turbine clearance control system in accordance with claim 13, wherein said controller is further configured to compare the determined turbine clearance to the preselected turbine clearance value and adjust the turbine clearance based on the comparison. 15. A turbine clearance control system in accordance with claim 12, wherein said controller is further configured to deactivate said turbine clearance control system at a preselected time prior to an end of the stable flight phase. 16. An apparatus for controlling a turbine clearance in an aircraft engine, said apparatus comprising: a steady-state condition switch configured to receive an input and, in response to the input, transmit a preselected turbine clearance value to a turbine controller that is communicatively coupled to said switch, wherein the controller adjusts the turbine clearance based on the preselected turbine clearance value; anda notification device communicatively coupled to said switch, said notification device is configured to communicate information relating to an operation status of said apparatus based at least partially on a status of said switch. 17. An apparatus in accordance with claim 16, wherein said switch is further configured to receive the input from at least one of a local operator and a remote operator. 18. An apparatus in accordance with claim 16, wherein said notification device comprises a display device. 19. An apparatus in accordance with claim 16, wherein said notification device comprises an audio device.