Method and system for taxiing an aircraft

Abstract

The system is used for taxiing an aircraft and comprises at least one multi-spool gas turbine engine, the engine having an electrical motor in a torque-driving engagement with a low pressure spool of the engine. The low pressure spool has a propulsor connected thereon to generate thrust when rotated. A controller is connected to the electrical motor and an electrical power source to control an amount of electrical power provided from the power source to the electrical motor so as to drive the propulsor and cause at least a major portion of the thrust to be generated by the propulsor for moving the aircraft during taxiing.

1 . A system for taxiing an aircraft, the system comprising:
 at least one multi-spool gas turbine engine, the engine having an electrical motor in a torque-driving engagement with a low pressure spool of the engine, the low pressure spool having a propulsor connected thereon to generate thrust when rotated; and   a controller connected to the electrical motor and an electrical power source to control an amount of electrical power provided from the power source to the electrical motor so as to drive the propulsor and cause at least a major portion of the thrust to be generated by the propulsor for moving the aircraft during taxiing.   
     
     
         2 . The system as defined in  claim 1 , wherein the gas turbine engine is a turbofan and the propulsor includes a fan. 
     
     
         3 . The system as defined in  claim 1 , wherein the gas turbine engine is a turboprop and the propulsor includes a propeller. 
     
     
         4 . The system as defined in  claim 1 , wherein the electrical motor is coaxially mounted on a shaft of the low pressure spool. 
     
     
         5 . The system as defined in  claim 1 , wherein the electrical motor is provided in an auxiliary gearbox (AGB), and is connected to the low pressure spool through a tower shaft. 
     
     
         6 . The system as defined in  claim 1 , wherein the electrical motor is operatable as a generator while the aircraft is in flight. 
     
     
         7 . The system as defined in  claim 1 , wherein the electrical power is at least partially provided by an electrical battery. 
     
     
         8 . The system as defined in  claim 1 , wherein the electrical power is at least partially provided by an auxiliary power unit (APU). 
     
     
         9 . The system as defined in  claim 1 , wherein the electrical power is at least partially provided by a generator from another engine on the aircraft. 
     
     
         10 . A system to be used on an aircraft during taxiing for generating thrust in a gas turbine engine, the engine having a propulsor mechanically connected to at least one turbine, the propulsor being configured and disposed to receive power from the turbine at least during take-off and in flight, the system comprising:
 an electrical motor mechanically connected to the propulsor of the engine; and   means for supplying sufficient electrical power to the electrical motor so as to rotate the propulsor and move the aircraft during taxiing in replacement of at least a major portion of the power from the turbine of the engine.   
     
     
         11 . The system as defined in  claim 10 , wherein the gas turbine engine is a turbofan and the propulsor includes a fan. 
     
     
         12 . The system as defined in  claim 10 , wherein the gas turbine engine is a turboprop and the propulsor includes a propeller. 
     
     
         13 . The system as defined in  claim 10 , wherein the electrical motor is coaxially mounted on a shaft of the low pressure spool. 
     
     
         14 . The system as defined in  claim 10 , wherein the electrical motor is provided in an auxiliary gearbox (AGB), and is connected to the low pressure spool through a tower shaft. 
     
     
         15 . The system as defined in  claim 10 , wherein the electrical motor is operatable as a generator during take-off and while the aircraft is in flight. 
     
     
         16 . The system as defined in  claim 10 , wherein the electrical power is at least partially provided by an electrical battery. 
     
     
         17 . The system as defined in  claim 10 , wherein the electrical power is at least partially provided by an auxiliary power unit (APU). 
     
     
         18 . The system as defined in  claim 10 , wherein the electrical power is at least partially provided by a generator from another engine on the aircraft. 
     
     
         19 . A method of moving an aircraft during taxiing using thrust generated by a propulsor of a gas turbine engine mounted on the aircraft, the engine comprising an electrical motor in a torque-driving engagement with the propulsor, the method comprising:
 conducting electrical power to the electrical motor for rotating the propulsor; and   generating sufficient thrust by the propulsor using the electrical motor for moving the aircraft.   
     
     
         20 . The method as defined in  claim 19 , wherein the gas turbine engine is a turbofan and the propulsor includes a fan. 
     
     
         21 . The method as defined in  claim 19 , wherein the gas turbine engine is a turboprop and the propulsor includes a propeller. 
     
     
         22 . The method as defined in  claim 19 , wherein the electrical motor is coaxially mounted on a shaft of the low pressure spool. 
     
     
         23 . The method as defined in  claim 19 , wherein the electrical motor is provided in an auxiliary gearbox (AGB), and is connected to the low pressure spool through a tower shaft. 
     
     
         24 . The method as defined in  claim 19 , wherein the electrical motor is operatable as a generator when the engine drives rotation of the low pressure spool. 
     
     
         25 . The method as defined in  claim 19 , wherein the electrical power is at least partially provided by an electrical battery. 
     
     
         26 . The system as defined in  claim 19 , wherein the electrical power is at least partially provided by an auxiliary power unit (APU). 
     
     
         27 . The system as defined in  claim 19 , wherein the electrical power is at least partially provided by a generator from another engine on the aircraft. 
     
     
         28 . A method of generating electrical power from a shutdown gas turbine engine having a propulsor and being mounted on a flying aircraft, the method comprising:
 rotating the propulsor using a windmill effect caused by movement of the flying aircraft through air; and   generating electrical power using torque produced by the windmill effect on the propulsor of the gas turbine engine.   
     
     
         29 . The method as defined in  claim 28 , wherein the gas turbine engine is a turbofan and the propulsor includes a fan. 
     
     
         30 . The method as defined in  claim 28 , wherein the gas turbine engine is a turboprop and the propulsor includes a propeller. 
     
     
         31 . The method as defined in  claim 28 , wherein the electrical motor is coaxially mounted on a shaft of the low pressure spool. 
     
     
         32 . The method as defined in  claim 28 , wherein the electrical motor is provided in an auxiliary gearbox (AGB), and is connected to the low pressure spool through a tower shaft.