[특허]Gas turbine engine assembly and methods of assembling same

General Electric Company

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Gas turbine engine assembly and methods of assembling same

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-003/02
미국특허분류(USC)	060/268; 060/226.1
출원번호	UP-0254143 (2005-10-19)
등록번호	US-7685808 (2010-04-23)
발명자 / 주소	Orlando, Robert Joseph Moniz, Thomas Ory
출원인 / 주소	General Electric Company
대리인 / 주소	Andes, Esq., William Scott
인용정보	피인용 횟수 : 25 인용 특허 : 33

초록

A method for assembling a gas turbine engine includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, and coupling a counter-rotating fan assembly to the core gas turbine engine such that air discharged from the counter-rotating fan assembly is channeled directly into an inlet of the gas turbine engine compressor.

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What is claimed is: 1. A method of assembling a gas turbine assembly said method comprising: providing a core gas turbine engine including a high-pressure compressor, a combustor, a low-pressure turbine, and a high-pressure turbine; coupling a counter-rotating fan assembly including a first fan assembly and a second fan assembly to the core gas turbine engine such that air discharged from the counter-rotating fan assembly is channeled directly into an inlet of the gas turbine engine compressor via a passage without passing through a booster compressor; coupling a gearbox between the low-pressure turbine and the second fan assembly such that the second fan assembly rotates at a rotational speed that is different than the rotational speed of the first fan assembly; coupling the counter-rotating fan assembly to the low-pressure turbine such that the low-pressure turbine rotates the counter-fan assembly; and coupling a downstream end of the compressor against the combustor such that air discharged from the compressor is channeled to the combustor. 2. A method in accordance with claim 1 wherein coupling a counter-rotating fan assembly further comprises coupling a counter-rotating fan assembly to the core gas turbine engine such that compressed air is discharged from the counter-rotating fan assembly at a first operating pressure and received at the core gas turbine high-pressure compressor at approximately the first operational pressure. 3. A method in accordance with claim 1 wherein coupling a counter-rotating fan assembly further comprises coupling a counter-rotating fan assembly including a first fan assembly and a second fan assembly to the core gas turbine engine such that the first fan assembly rotates in a first direction and the second fan assembly rotates in an opposite second direction. 4. A method in accordance with claim 1 wherein coupling a counter-rotating fan assembly further comprises coupling a counter-rotating fan assembly that discharges a predetermined quantity of air based on the gas turbine engine compression ratio to the core gas turbine engine. 5. A method in accordance with claim 1 wherein providing a core gas turbine engine comprises providing a core gas turbine engine that includes a predetermined quantity of compressor stages based on the quantity of compressed air discharged from the counter-rotating fan assembly. 6. A method in accordance with claim 1 wherein providing a core gas turbine engine comprises providing a core gas turbine engine that includes ten compressor stages and two high-pressure turbine stages. 7. A method in accordance with claim 3 further comprising: coupling a low-pressure turbine to the first fan assembly such that the first fan assembly rotates in a first direction; and coupling a gearbox between the low-pressure turbine assembly and the second fan assembly such that the second fan assembly rotates in a second opposite direction. 8. A method in accordance with claim 3 further comprising coupling a counter-rotating fan assembly including a first fan assembly and a second fan assembly to the low-pressure turbine such that the first fan assembly rotates at a first rotational speed and the second fan assembly rotates at a second different rotational speed. 9. A method in accordance with claim 7 further comprising: coupling a shaft between a low-pressure turbine and the first fan assembly such that the first fan assembly rotates at approximately the same rotational speed as the low-pressure turbine. 10. A method in accordance with claim 1 further comprising coupling a gearbox between the low-pressure turbine assembly and the second fan assembly such that the second fan assembly rotates at a rotational speed that is less than the rotational speed of the first fan assembly. 11. A turbine engine assembly comprising: a core gas turbine engine including a high-pressure compressor, a combustor, a low-pressure turbine, and a high-pressure turbine, said compressor comprising an upstream end and a downstream end, said combustor coupled to said compressor downstream end; a counter-rotating fan assembly comprising a first fan assembly and a second fan assembly, wherein said counter-rotating fan assembly is coupled to said core gas turbine engine such that air discharged from said counter-rotating fan assembly is channeled directly into an inlet of said gas turbine engine compressor via a passage without passing through a booster compressor, said counter-rotating fan assembly coupled to said low-pressure turbine such that said low-pressure turbine rotates said counter-fan assembly; and a gearbox coupled between said low-pressure turbine assembly and said counter-rotating fan assembly configured to facilitate rotation of said second fan assembly at a rotational speed that is different than the rotational speed of said first fan assembly. 12. A turbine engine assembly in accordance with claim 11 wherein said counter-rotating fan assembly is selectively sized to discharge compressed air at a first operating pressure, said core gas turbine engine configured to receive the compressed air at approximately the first operational pressure. 13. A turbine engine assembly in accordance with claim 11 wherein said first fan assembly rotates in a first direction and said second fan assembly that rotates in an opposite second direction. 14. A turbine engine assembly in accordance with claim 11 further comprising coupling a counter-rotating fan assembly that discharges a predetermined quantity of air based on the gas turbine engine compression ratio to the core gas turbine engine. 15. A turbine engine assembly in accordance with claim 11 said core gas turbine engine comprises a predetermined quantity of compressor stages based on the compression ratio of said counter-rotating fan assembly and the overall compression ratio of the gas turbine engine assembly. 16. A turbine engine assembly in accordance with claim 15 wherein said core gas turbine engine comprises a predetermined quantity of high-pressure turbine stages based on the compression ratio of said counter-rotating fan assembly and the overall compression ratio of the gas turbine engine assembly. 17. A turbine engine assembly in accordance with claim 13 wherein said low-pressure turbine is coupled to said first fan assembly such that said first fan assembly rotates in a first direction, said turbine engine assembly further comprising: a gearbox coupled between said low-pressure turbine assembly and said second fan assembly such that said second fan assembly rotates in a second opposite direction. 18. A turbine engine assembly in accordance with claim 13 wherein said counter-rotating fan assembly comprises a first fan assembly configured to rotate at a first rotational speed and a second fan assembly configured to rotate at a second different rotational speed. 19. A turbine engine assembly in accordance with claim 17 further comprising: a shaft coupled between said low-pressure turbine and said first fan assembly such that said first fan assembly rotates at approximately the same rotational speed as said low-pressure turbine. 20. A turbine engine assembly in accordance with claim 19 further comprising a gearbox coupled between said low-pressure turbine assembly and said second fan assembly such that said second fan assembly rotates at a rotational speed that is less than the rotational speed of said first fan assembly; a core turbine engine; a low-pressure turbine coupled to said core turbine engine; and a counter-rotating fan assembly coupled to said low-pressure turbine, said counter-rotating fan assembly comprising a first fan assembly coupled to said low-pressure turbine and configured to rotate in the first direction and a second fan assembly coupled to said low-pressure turbine, said second fan assembly configured to rotate in an opposite second direction.

이 특허에 인용된 특허 (33)

이 특허를 인용한 특허 피인용횟수: 25

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특허 상세정보

Gas turbine engine assembly and methods of assembling same

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Gas turbine engine assembly and methods of assembling same

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이 특허에 인용된 특허 (33)

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