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

General Electric Company

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특허 상세정보

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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; 415/061
출원번호	UP-0553571 (2006-10-27)
등록번호	US-7832193 (2011-01-16)
발명자 / 주소	Orlando, Robert Joseph Moniz, Thomas Ory Schilling, Jan Christopher
출원인 / 주소	General Electric Company
대리인 / 주소	Louke, Marcella R.
인용정보	피인용 횟수 : 38 인용 특허 : 21

초록

A method of assembling a gas turbine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, coupling a low-pressure turbine to the core gas turbine engine, coupling a booster compressor to a gearbox, and coupling the gearbox to the low-pressure turbine such that the booster compressor is driven by the low-pressure turbine.

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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, and a turbine; coupling a low pressure turbine to the core gas turbine engine; coupling a booster compressor to a gearbox; coupling the gearbox to the low-pressure turbine such that the booster compressor is driven by the low-pressure turbine; coupling a drive shaft to the low pressure turbine; and coupling the gearbox between the drive shaft and the booster compressor such that the booster compressor rotates at a rotational speed that is different than the rotational speed of the low-pressure turbine. 2. A method of assembling a gas turbine assembly, said method comprising: providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine; coupling a low pressure turbine to the core gas turbine engine; coupling a booster compressor to a gearbox; coupling the gearbox to the low-pressure turbine such that the booster compressor is driven by the low-pressure turbine; coupling a drive shaft to the low pressure turbine; coupling a fan assembly to the drive shaft such that the fan assembly rotates at a rotational speed that is the same as the rotational speed of the low-pressure turbine; and coupling a thrust bearing assembly between the fan assembly and the low-pressure turbine such that the residual thrust generated by the fan assembly and the low-pressure turbine is transmitted to a stationary structural component. 3. A method of assembling a gas turbine assembly, said method comprising: providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine; coupling a low pressure turbine to the core gas turbine engine; coupling a booster compressor to a gearbox; coupling the gearbox to the low-pressure turbine such that the booster compressor is driven by the low-pressure turbine; coupling a drive shaft to the low pressure turbine; and coupling a thrust bearing assembly between the booster compressor and the gearbox such that the residual thrust loads generated by the booster compressor are transferred to a stationary structural component. 4. A method of assembling a gas turbine assembly, said method comprising: providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine; coupling a low pressure turbine to the core gas turbine engine; coupling a booster compressor to a gearbox; and coupling the gearbox to the low-pressure turbine such that the booster compressor is driven by the low-pressure turbine; wherein coupling said gearbox further comprises coupling a gearbox having a substantially toroidal cross-sectional profile between the booster compressor and the drive shaft such that the gearbox substantially circumscribes the drive shaft. 5. A method of assembling a gas turbine assembly, said method comprising: providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine; coupling a low pressure turbine to the core gas turbine engine; coupling a booster compressor to a gearbox; coupling the gearbox to the low-pressure turbine such that the booster compressor is driven by the low-pressure turbine; and coupling a flex connection between the drive shaft and gearbox. 6. A turbine engine assembly comprising: a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine; a low-pressure turbine coupled to said core gas turbine engine; a booster compressor; a gearbox coupled between said low-pressure turbine and said booster compressor such that the booster compressor is driven by the low-pressure turbine; and a drive shaft coupled between said low-pressure turbine and said gearbox to facilitate driving said booster compressor at a rotational speed that is different than the rotational speed of the low-pressure turbine. 7. A turbine engine assembly comprising: a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine; a low-pressure turbine coupled to said core gas turbine engine; a booster compressor; a gearbox coupled between said low-pressure turbine and said booster compressor such that the booster compressor is driven by the low-pressure turbine; a drive shaft coupled to said low-pressure turbine; a fan assembly coupled to said drive shaft such that said fan assembly rotates at a rotational speed that is the same as the rotational speed of the low pressure turbine; and a thrust bearing assembly coupled between the fan assembly and said low-pressure turbine and configured to transfer residual thrust loads generated by said fan assembly and said low-pressure turbine to a stationary structural component. 8. A turbine engine assembly comprising: a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine; a low-pressure turbine coupled to said core gas turbine engine; a booster compressor; a gearbox coupled between said low-pressure turbine and said booster compressor such that the booster compressor is driven by the low-pressure turbine; and a thrust bearing assembly coupled between said booster and said gearbox and configured to transfer residual thrust loads generated by said booster to a stationary structural component. 9. A turbine engine assembly comprising: a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine; a low-pressure turbine coupled to said core gas turbine engine; a booster compressor; a gearbox coupled between said low-pressure turbine and said booster compressor such that the booster compressor is driven by the low-pressure turbine; wherein said gearbox has a substantially toroidal cross-sectional profile and substantially circumscribes said drive shaft. 10. A turbine engine assembly comprising: a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine; a low-pressure turbine coupled to said core gas turbine engine; a booster compressor; a gearbox coupled between said low-pressure turbine and said booster compressor such that the booster compressor is driven by the low-pressure turbine; and a flex connection coupled between said drive shaft and said gearbox. 11. A turbine engine assembly comprising: a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine; a low-pressure turbine coupled to said core gas turbine engine; a booster compressor; a gearbox coupled between said low-pressure turbine and said booster compressor such that the booster compressor is driven by the low-pressure turbine; and a generator driven by said booster compressor. 12. A turbine engine in accordance with claim 11, further comprising: a drive shaft coupled to an output of said gearbox; a first bevel gear coupled to said drive shaft; a generator drive shaft coupled to said generator; and a second bevel gear coupled to an end of said generator drive shaft, said second bevel gear configured to mesh with said first bevel gear such that said booster compressor drives said generator.

이 특허에 인용된 특허 (21)

이 특허를 인용한 특허 피인용횟수: 38

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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 (21)

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