One embodiment of the present invention is a unique vehicle. Another embodiment is a unique propulsion system. Yet another embodiment is a unique system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for vehicle propulsions systems. Further embodiments,
One embodiment of the present invention is a unique vehicle. Another embodiment is a unique propulsion system. Yet another embodiment is a unique system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for vehicle propulsions systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
대표청구항▼
1. A propulsion system for an aircraft, comprising: a gas turbine engine including a spool configured to power a propulsor;an auxiliary power unit (APU) comprising a thermodynamic machine configured to be mechanically engaged with the spool to supply power to the propulsor sufficient to taxi the air
1. A propulsion system for an aircraft, comprising: a gas turbine engine including a spool configured to power a propulsor;an auxiliary power unit (APU) comprising a thermodynamic machine configured to be mechanically engaged with the spool to supply power to the propulsor sufficient to taxi the aircraft; anda controller configured to selectively mechanically engage the APU to the spool to taxi the aircraft without starting the gas turbine engine. 2. The propulsion system of claim 1, further comprising a clutch mechanically coupled between the APU and the spool, wherein the clutch is configured to mechanically engage and disengage the APU respectively to and from the spool. 3. The propulsion system of claim 2, wherein the controller is configured to control the clutch to selectively mechanically engage the APU to the spool to power the propulsor to taxi the aircraft without starting the gas turbine engine. 4. The propulsion system of claim 1, wherein the controller is configured to selectively mechanically disengage the APU from the spool during one or more of takeoff, cruise and landing modes. 5. The propulsion system of claim 1, wherein the controller is configured to selectively mechanically engage the APU to the spool during one or more of takeoff, cruise and landing modes, to provide supplemental power to the spool. 6. The propulsion system of claim 1, wherein the controller is configured to selectively mechanically engage the APU to the spool to start or aid in the starting of the gas turbine engine following completion of a taxiing operation. 7. The propulsion system of claim 1, wherein the controller is configured to selectively mechanically engage the APU to the spool to start or aid in the starting of the gas turbine engine and to selectively mechanically disengage the APU from the spool. 8. The propulsion system of claim 1, wherein the APU is configured to start or aid in the starting of the gas turbine engine by one or more of supplying rotational power to the spool or supplying electrical power to an electrical machine coupled to the spool. 9. The propulsion system of claim 1, further comprising a generator coupled to the APU, wherein the generator is configured to supply electrical power to the aircraft when the gas turbine engine is not running. 10. The propulsion system of claim 1, further comprising a generator coupled to the APU, wherein the generator is configured to supply electrical power to the aircraft in a taxiing mode. 11. The propulsion system of claim 1, wherein the APU generates an exhaust, and wherein the exhaust is supplied to the gas turbine engine to warm up the gas turbine engine prior to starting the gas turbine engine. 12. The propulsion system of claim 1, wherein the APU includes an APU intake; wherein the gas turbine engine generates a bleed air flow; and wherein the bleed air flow is supplied to the APU intake. 13. The propulsion system of claim 1, further comprising a reduction gearbox disposed between the APU and the spool, wherein the reduction gearbox is configured to reduce an output speed of the APU. 14. A propulsion system for an aircraft, comprising: a turbofan engine including a turbofan, a high pressure (HP) spool, and a low pressure (LP) spool, wherein the LP spool is configured to rotate the turbofan to impart motion to the aircraft in taxiing, take-off, cruise and landing modes;an auxiliary power unit (APU) engine comprising a thermodynamic machine configured to supply rotational power to the LP spool sufficient to power the turbofan to taxi the aircraft; anda controller configured to selectively mechanically engage the APU engine to the LP spool in the taxiing mode to taxi the aircraft without starting the turbofan engine, and to selectively mechanically disengage the APU from the LP spool in at least one of the take-off, cruise, and landing modes. 15. The propulsion system of claim 14, further comprising an electrical machine coupled to the LP spool that is operative to convert mechanical power to electrical power. 16. The propulsion system of claim 14, further comprising an electrical machine coupled to the HP spool that is operative to convert mechanical power to electrical power. 17. A propulsion system for a vehicle, comprising: a gas turbine engine including a spool configured to power a propulsor, wherein the propulsor is configured to impart motion to the vehicle during normal vehicle moving operations;an auxiliary power unit (APU) comprising a thermodynamic machine operative to supply rotational power to the spool sufficient to power the propulsor to impart motion to the vehicle in a taxiing operation; anda controller configured to selectively mechanically engage the APU to the spool to power the propulsor to impart the motion to the vehicle without starting the gas turbine engine. 18. The propulsion system of claim 17, wherein the gas turbine engine is a single spool engine comprising the spool. 19. The propulsion system of claim 17, wherein the spool comprises a low pressure (LP) spool, and the gas turbine engine further includes a high pressure (HP) spool, and wherein the controller is configured to selectively mechanically engage the APU to the LP spool to power the propulsor to impart the motion to the vehicle without starting the gas turbine engine. 20. The propulsion system of claim 17, wherein the APU comprises a second gas turbine engine.
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이 특허에 인용된 특허 (15)
Snow Barton H. (Wyoming OH) Homan Frank R. (Cincinnati OH), Apparatus for windmill starts in gas turbine engines.
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