Devices and methods for balancing a high-pressure spool of a gas turbine engine

Abstract

Devices and methods useful for balancing high-pressure spools of gas turbine engines are disclosed. An exemplary device may comprise: an input shaft configured to be coupled to an output of an accessory gear box driven by a high-pressure spool of a gas turbine engine; a first trigger rotatably coupled to the input shaft at a first speed ratio; and a sensor configured to detect the trigger at each revolution of the trigger. The first speed ratio may permit a rotational speed of the first trigger to be substantially the same as a rotational speed of the high-pressure spool. Upon detection of the trigger, the sensor may generate one or more signals representative of each associated revolution of the high-pressure spool of the gas turbine engine.

1 . A device useful in determining a balancing solution for a high-pressure spool of a gas turbine engine, the device comprising:
 an input shaft configured to be coupled to an output of an accessory gear box driven by the high-pressure spool of the gas turbine engine;   a first trigger rotatably coupled to the input shaft at a first speed ratio, the first speed ratio permitting a rotational speed of the first trigger to be substantially the same as a rotational speed of the high-pressure spool; and   a sensor configured to detect the trigger at each revolution of the trigger and, upon detection of the trigger, generate one or more signals representative of each associated revolution of the high-pressure spool of the gas turbine engine.   
     
     
         2 . The device as defined in  claim 1 , comprising a second trigger rotatably coupled to the input shaft at a second speed ratio, the second speed ratio permitting a rotational speed of the second trigger to be substantially identical to a rotational speed of a high-pressure spool of another gas turbine engine when the device is used with the other gas turbine engine. 
     
     
         3 . A device useful in determining a balancing solution for a high-pressure spool of a gas turbine engine, the device comprising:
 an interface configured to receive rotary input from an accessory gear box driven by the high-pressure spool of the gas turbine engine; and   an output configured to generate one or more signals representative of each revolution of the high-pressure spool of the gas turbine engine associated with the rotary input.   
     
     
         4 . The device as defined in  claim 3 , wherein:
 the interface comprises an input shaft; and   the device comprises a first detectable trigger coupled to the input shaft at a first speed ratio.   
     
     
         5 . The device as defined in  claim 4 , wherein the first speed ratio is configured to permit a rotational speed of the first trigger to be substantially identical to a rotational speed of the high-pressure spool. 
     
     
         6 . The device as defined in  claim 5 , comprising a sensor configured to detect the trigger at each revolution of the trigger and, upon detection of the trigger, generate one or more signals representative of each associated revolution of the high-pressure spool of the gas turbine engine. 
     
     
         7 . The device as defined in  claim 5 , comprising a second detectable trigger coupled to the input shaft at a second speed ratio, the second speed ratio permitting a rotational speed of the second trigger to be substantially identical to a rotational speed of a high-pressure spool of another gas turbine engine when the device is used with the other gas turbine engine. 
     
     
         8 . The device as defined in  claim 3 , comprising a first trigger coupled to the interface and configured to cause the generation of the one or more signals by the output. 
     
     
         9 . The device as defined in  claim 3 , comprising a rotatable trigger coupled to the interface and configured to substantially reproduce a rotational speed of the high-pressure spool based on the rotary input from the accessory gear box. 
     
     
         10 . The device as defined in  claim 9 , comprising a sensor configured detect the trigger at each revolution of the trigger and, upon detection of the trigger, generate one or more signals representative of each associated revolution of the high-pressure spool of the gas turbine engine. 
     
     
         11 .- 20 . (canceled)