초록 ▼

A method for assembling a gas turbine engine assembly includes coupling a fan assembly to a core gas turbine engine such that the fan assembly is upstream from the core gas turbine engine, coupling a low-pressure turbine downstream from the core gas turbine engine such, wherein the low-pressure turb

A method for assembling a gas turbine engine assembly includes coupling a fan assembly to a core gas turbine engine such that the fan assembly is upstream from the core gas turbine engine, coupling a low-pressure turbine downstream from the core gas turbine engine such, wherein the low-pressure turbine includes a disk and a plurality of splines formed in the disk, providing a shaft that includes a first end and a second end that includes a plurality of splines, coupling the shaft first end to the fan assembly, and coupling the shaft second end to the low-pressure turbine such that the shaft splines mesh with the disk splines such that torque is transmitted from the low-pressure turbine to the fan assembly via the shaft during engine operation.

대표청구항 ▼

What is claimed is: 1. A method for assembling a gas turbine engine assembly, said method comprising: coupling a fan assembly to a core gas turbine engine such that the fan assembly is upstream from the core gas turbine engine; coupling a low-pressure turbine downstream from the core gas turbine en

What is claimed is: 1. A method for assembling a gas turbine engine assembly, said method comprising: coupling a fan assembly to a core gas turbine engine such that the fan assembly is upstream from the core gas turbine engine; coupling a low-pressure turbine downstream from the core gas turbine engine, wherein the low-pressure turbine includes a disk, a flange formed with said disk, and a plurality of splines formed in the flange; providing a shaft that includes a first end having a first outer diameter and a second end having a second outer diameter that is less than the first outer diameter, said second end further including a plurality of splines; coupling the shaft first end to the fan assembly; and coupling the shaft second end to the low-pressure turbine disk flange such that the shaft splines mesh with the flange splines such that torque is transmitted from the low-pressure turbine to the fan assembly via the shaft during engine operation. 2. A method in accordance with claim 1, wherein the shaft includes a plurality of male splines and the flange includes a plurality of female splines, said method further comprising coupling the shaft second end to the low-pressure turbine such that a plurality of the shaft male splines mesh with the flange female splines. 3. A method in accordance with claim 1, wherein providing a shaft further comprises providing a shaft that includes a first portion having an outer diameter and a second portion having an outer diameter that is less than the first portion outer diameter. 4. A method in accordance with claim 1, wherein providing a shaft further comprises providing a shaft that includes a first portion having a first length and a second portion having a second length that is less than the first length. 5. A method in accordance with claim 4, wherein providing a shaft further comprises providing a shaft that includes a first portion and a second portion that is formed unitarily with the first portion. 6. A method in accordance with claim 4, wherein providing a shaft further comprises providing a shaft includes a first portion having a length that is approximately equal to an axial distance between the fan assembly and a high-pressure turbine. 7. A method in accordance with claim 4, wherein the core gas turbine engine includes a high-pressure turbine including a disk having a bore extending therethrough, said method further comprising providing a shaft that includes a first portion having an outer diameter that is greater than an inner diameter of the disk bore. 8. A method in accordance with claim 1, wherein the core gas turbine engine includes a high-pressure turbine, said method further comprising coupling the high-pressure turbine downstream from the shaft first portion. 9. A method in accordance with claim 1, wherein providing a shaft further comprises providing a shaft that includes a first portion having an outer diameter that is between approximately four and five inches, and a second portion having an outer diameter that is between approximately three and four inches. 10. A gas turbine engine assembly comprising: a core gas turbine engine; a fan assembly coupled to said core gas turbine engine such that said fan assembly is upstream from said core gas turbine engine; a low-pressure turbine coupled to said core gas turbine engine, said low-pressure turbine disposed downstream from said core gas turbine engine, said low-pressure turbine comprising a disk comprising a flange and a plurality of splines formed in said flange; and a shaft comprising a first end coupled to said fan assembly and a second end that comprises a plurality of splines, said shaft splines configured to mesh with said flange splines such that torque is transmitted from said low-pressure turbine to said fan assembly via said shaft, said shaft first end having a first outer diameter and said shaft second end having a second outer diameter that is less than the first outer diameter. 11. A gas turbine engine assembly in accordance with claim 10, wherein said shaft splines comprise a plurality of male splines and said flange splines comprise a plurality of female splines configured to mesh with said male splines. 12. A gas turbine engine assembly in accordance with claim 10, wherein said shaft comprises: a first portion having an outer diameter; and a second portion having an outer diameter that is less than said first portion outer diameter. 13. A gas turbine engine assembly in accordance with claim 12, wherein said first portion has a first length and said second portion has a second length that is less than said first length. 14. A gas turbine engine assembly in accordance with claim 12, wherein said fan assembly and said high-pressure turbine are separated by a distance that is approximately equal to said first length. 15. A gas turbine engine assembly in accordance with claim 12, wherein said first portion and said portion are formed unitarily. 16. A gas turbine engine assembly in accordance with claim 12, wherein said core gas turbine engine comprises a high-pressure turbine comprising a disk having a bore extending therethrough, said bore having an inner diameter that is smaller than said shaft first portion outer diameter. 17. A gas turbine engine assembly in accordance with claim 12, wherein said core gas turbine engine comprises a high-pressure turbine that is coupled downstream said shaft first portion. 18. A gas turbine engine assembly in accordance with claim 10, wherein said shaft comprises: a first portion having an outer diameter that is between approximately four and five inches; and a second portion having an outer diameter that is between approximately three and four inches.