[특허]Aircraft and propulsion system

Rolls-Royce Corporation

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Aircraft and propulsion system

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-041/00
미국특허분류(USC)	244/058; 244/057; 244/053R
출원번호	US-0947482 (2010-11-16)
등록번호	US-8690099 (2014-04-08)
발명자 / 주소	Burns, Donald Rajashekara, Kaushik
출원인 / 주소	Rolls-Royce Corporation
대리인 / 주소	Krieg DeVault LLP
인용정보	피인용 횟수 : 0 인용 특허 : 16

초록

One embodiment of the present invention is a unique aircraft. Another embodiment is a unique propulsion system for an aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and aircraft propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

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1. A propulsion system for an aircraft, comprising: a gas turbine engine having a high pressure spool and a low pressure spool, wherein the low pressure spool is operative to drive a propulsor; andan auxiliary power unit (APU) mechanically coupled to both the high pressure spool and the low pressure spool, wherein the APU is a thermodynamic machine configured to generate mechanical power from fuel; and wherein the APU supplies rotational power to both the high pressure spool and the low pressure spool at the same time. 2. The propulsion system of claim 1, further comprising a transmission mechanically disposed between either the high pressure spool and the APU, or between the low pressure spool and the APU. 3. The propulsion system of claim 2, wherein the transmission is a continuously variable transmission. 4. The propulsion system of claim 2, wherein the transmission is mechanically disposed between the high pressure spool and the APU. 5. The propulsion system of claim 2, wherein the transmission is configured to vary the rotational speed as between the high pressure spool and the low pressure spool. 6. 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 engine start. 7. The propulsion system of claim 1, further comprising a clutch mechanically coupled between the APU and the gas turbine engine, wherein the clutch is configured to mechanically disengage the APU from at least one of the high pressure spool and the low pressure spool of the gas turbine engine. 8. The propulsion system of claim 1, wherein the APU includes an APU compressor; wherein the gas turbine engine generates a bleed air flow; and wherein the bleed air flow is supplied to the APU compressor. 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 during ground operations of the aircraft and during flight operations of the aircraft. 10. The propulsion system of claim 1, wherein the APU is configured to start the gas turbine engine by supplying mechanical power to rotate at least one of the low pressure spool and the high pressure spool. 11. The propulsion system of claim 1, wherein the propulsor is a turbofan of the gas turbine engine. 12. An aircraft, comprising: a fuselage;an empennage coupled to the fuselage;a plurality of wings coupled to the fuselage;a gas turbine engine having a high pressure spool and a low pressure spool, wherein the low pressure spool is operative to drive a propulsor; and wherein the gas turbine engine is coupled to at least one of the fuselage, the empennage and at least one of the plurality of wings;an auxiliary power unit (APU) operative to supply mechanical power to the gas turbine engine via a reduction gearbox, wherein the APU is a thermodynamic machine configured to generate mechanical power from fuel; anda shafting system mechanically coupling both the high pressure spool and the low pressure spool to the reduction gearbox, wherein the APU is operative to supply supplies rotational power to both the high pressure spool and the low pressure spool at the same time via the shafting system and reduction gearbox. 13. The aircraft of claim 12 further comprising a transmission mechanically coupled between either the high pressure spool and the APU, or between the low pressure spool and the APU. 14. The aircraft of claim 13, wherein the transmission is a continuously variable transmission. 15. The aircraft of claim 13, wherein the transmission is configured to selectively disengage the APU from either the high pressure spool or the low pressure spool. 16. The aircraft of claim 13, wherein the power mechanically transferred from the APU to the gas turbine engine is configured to supply thrust sufficient for taxiing the aircraft. 17. The aircraft of claim 12, further comprising an engine electrical machine coupled to the high pressure spool; and an APU electrical machine coupled to the APU, wherein the APU is configured to supply electrical power to the engine electrical machine for starting the gas turbine engine. 18. The aircraft of claim 17, wherein the engine electrical machine is configured to provide electrical power to the aircraft during operation of the gas turbine engine. 19. The aircraft of claim 18 further comprising an other engine electrical machine coupled to the low pressure spool, wherein both the engine electrical machine and the other engine electrical machine are configured to provide electrical power to the aircraft during operation of the gas turbine engine. 20. The aircraft of claim 12, further comprising an engine electrical machine coupled to the low pressure spool, wherein the engine electrical machine is configured to provide electrical power to the aircraft during operation of the gas turbine engine. 21. A system, comprising: a gas turbine engine having a high pressure spool and a low pressure spool, wherein the low pressure spool is operative to drive a propulsor; andmeans for supplying mechanical power to both the high pressure spool and the low pressure spool, wherein the means for supplying mechanical power includes means for generating the mechanical power from fuel, and includes means for supplying rotational power to both the high pressure spool and the low pressure spool at the same time. 22. The system of claim 21, further comprising means for varying a rotational speed of one of the high pressure spool and the low pressure spool relative to the rotational speed of the other of the high pressure spool and the low pressure spool.

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