[특허]Turbofan engine assembly and method of assembling same

General Electric Company

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특허 상세정보

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Turbofan engine assembly and method of assembling same

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-003/00
미국특허분류(USC)	060/268; 060/039.162
출원번호	UP-0614585 (2006-12-21)
등록번호	US-7716914 (2010-06-10)
발명자 / 주소	Schilling, Jan Christopher
출원인 / 주소	General Electric Company
대리인 / 주소	Andes, Esq., William Scott
인용정보	피인용 횟수 : 37 인용 특허 : 21

초록
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A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor disposed downstream from the high-pressure compressor, and a high-pressure turbine coupled to the high-pressure compressor using a shaft, counter-rotating booster compressor coupled to the core gas turbine engine, the counter-rotating booster compressor comprising a first rotor section configured to rotate in a first direction and a second rotor section configured to rotate in an opposite second direction, a single stage fan assembly coupled to the first rotor section, a drive shaft coupled between the low-pressure turbine and the fan assembly, and a gearbox coupled between the drive shaft and the second rotor section such that the low-pressure turbine drives the gearbox and such that the gearbox drives the second rotor section. A method of assembling the above turbofan engine assembly is also described herein.

대표
청구항
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What is claimed is: 1. A method of assembling a turbofan engine assembly comprises: coupling a counter-rotating booster compressor upstream from a core gas turbine engine, the counter-rotating booster compressor including a first rotor section configured to rotate in a first direction and a second rotor section configured to rotate in an opposite second direction; coupling the first rotor section to a single stage fan assembly; coupling the second rotor section to a gearbox; coupling the single stage fan assembly to the a low-pressure turbine using a drive shaft; and coupling a gearbox between the drive shaft and the second rotor section such that the low-pressure turbine drives the gearbox and such that the gearbox drives the second rotor section. 2. A method in accordance with claim 1, further comprising: coupling a drive shaft to the low-pressure turbine; and coupling the gearbox between the drive shaft and the second rotor section such that the second rotor section rotates at a rotational speed that is different than the rotational speed of the low-pressure turbine. 3. A method in accordance with claim 1, further comprising: coupling a support structure to a fan frame; and coupling the gearbox to the support structure. 4. A method in accordance with claim 3, further comprising: coupling the second rotor section to the gearbox using a cone; and mounting a first roller bearing assembly to a radially outer surface of the cone such that the first roller bearing assembly in disposed between the cone and the support structure. 5. A method in accordance with claim 4, further comprising mounting a first thrust bearing assembly to a radially inner surface of the cone such that the first thrust bearing assembly in disposed downstream from the gearbox between the cone and the support structure. 6. A method in accordance with claim 4, further comprising: coupling a drive shaft extension between the drive shaft and the fan assembly; and mounting a second thrust bearing assembly to a radially inner surface of the support structure such that the second thrust bearing assembly is disposed downstream from the gearbox between the support structure and the drive shaft extension. 7. A method in accordance with claim 6, further comprising mounting a second roller bearing assembly to a radially outer surface of the drive shaft extension such that the second roller bearing assembly is disposed upstream from the gearbox between the drive shaft extension and the cone. 8. A method in accordance with claim 1, further comprising coupling an epicyclic gearbox having a substantially toroidal cross-sectional profile to the drive shaft such that the gearbox substantially circumscribes the drive shaft. 9. A method in accordance with claim 1, further comprising coupling a first shaft extension between the gearbox and the second rotor assembly such that a first end of the first shaft extension is splined to a cone driving the second rotor assembly and such that a second end of the first shaft extension is splined to the gearbox. 10. A method in accordance with claim 1, further comprising coupling a second shaft extension between the gearbox and the fan assembly such that a first end of the second shaft extension is geared to the gearbox and such that a second end of the second shaft extension is geared to a drive shaft extension coupled between the drive shaft and the fan assembly. 11. A turbofan engine assembly comprising: a core gas turbine engine including a high-pressure compressor, a combustor disposed downstream from said high-pressure compressor, and a high-pressure turbine coupled to said high-pressure compressor using a shaft; counter-rotating booster compressor coupled to said core gas turbine engine, said counter-rotating booster compressor comprising a first rotor section configured to rotate in a first direction and a second rotor section configured to rotate in an opposite second direction; a single stage fan assembly coupled to said first rotor section; a drive shaft coupled between a low-pressure turbine and said fan assembly; and a gearbox coupled between said drive shaft and said second rotor section such that said low-pressure turbine drives said gearbox and such that said gearbox drives said second rotor section. 12. A turbofan engine assembly in accordance with claim 11, wherein said gearbox comprises a plurality of gears, said plurality of gears configured to drive said second rotor section at a rotational speed that is different than a rotational speed of said low-pressure turbine. 13. A turbofan engine assembly in accordance with claim 11, further comprising a support structure coupled to a fan frame, said gearbox coupled to said support structure. 14. A turbofan engine assembly in accordance with claim 13, further comprising: a cone coupled between said gearbox and said second rotor section; and a first roller bearing assembly mounted to a radially outer surface of said cone such that said first roller bearing assembly in disposed between said cone and said support structure. 15. A turbofan engine assembly in accordance with claim 14, further comprising a first thrust bearing assembly mounted to a radially inner surface of said cone such that said first thrust bearing assembly in disposed downstream from said gearbox between said cone and said support structure. 16. A turbofan engine assembly in accordance with claim 14, further comprising: a drive shaft extension coupled between said drive shaft and said fan assembly; and a second thrust bearing assembly mounted to a radially inner surface of said support structure such that said second thrust bearing assembly is disposed downstream from said gearbox between said support structure and said drive shaft extension. 17. A turbofan engine assembly in accordance with claim 16, further comprising a second roller bearing assembly mounted to a radially outer surface of said drive shaft extension such that said second roller bearing assembly is disposed upstream from said gearbox between said drive shaft extension and said cone. 18. A turbofan engine assembly in accordance with claim 11, wherein said gearbox comprises an epicyclic gearbox having a substantially toroidal cross-sectional profile, said gearbox substantially circumscribes said drive shaft. 19. A turbofan engine assembly in accordance with claim 11 further comprising a first shaft extension coupled between said gearbox and said second rotor assembly such that a first end of said first shaft extension is splined to a cone driving said second rotor assembly and such that a second end of said first shaft extension is splined to said gearbox. 20. A turbofan engine assembly in accordance with claim 11 further comprising a second shaft extension coupled between said gearbox and said fan assembly such that a first end of said second shaft extension is splined to said gearbox and such that a second end of said second shaft extension is splined to a drive shaft extension coupled between said drive shaft and said fan assembly.

이 특허에 인용된 특허 (21)

이 특허를 인용한 특허 피인용횟수: 37

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Turbofan engine assembly and method of assembling same

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Turbofan engine assembly and method of assembling same

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이 특허에 인용된 특허 (21)

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