초록 ▼

A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forward fan assembly rotates in a first

A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction, and coupling a booster compressor to the low-pressure turbine such that the booster compressor rotates in the first direction.

대표청구항 ▼

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: coupling a low-pressure turbine to a core turbine engine; coupling a single low-pressure turbine shaft to the low-pressure turbine; coupling a counter-rotating fan assembly including a forward fan assembly

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: coupling a low-pressure turbine to a core turbine engine; coupling a single low-pressure turbine shaft to the low-pressure turbine; coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine via the single low-pressure turbine shaft such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction; and coupling a booster compressor directly to the single low-pressure turbine shaft such that the booster compressor rotates in the first direction. 2. A method in accordance with claim 1 wherein the counter-rotating fan assembly includes a fan frame assembly, said method further comprising coupling the booster compressor to the forward fan assembly such that the booster compressor is positioned axially aft of the fan frame assembly. 3. A method in accordance with claim 1 wherein the counter-rotating fan assembly includes a fan frame assembly, said method further comprising coupling the booster compressor to the forward fan assembly such that the fan frame assembly is positioned axially between the booster compressor and the aft fan assembly. 4. A method in accordance with claim 1 further comprising: coupling a drive shaft between the low-pressure turbine and the forward fan assembly; and coupling a gearbox between the drive shaft and the aft fan assembly such that the aft fan assembly rotates in an opposite second direction than the forward fan assembly. 5. A method in accordance with claim 1 further comprising coupling a counter-rotating fan assembly including a forward fan assembly and a aft fan assembly to the low-pressure turbine such that the forward fan assembly and the booster compressor each rotate at a first rotational speed and the aft fan assembly rotates at a second rotational speed that is different than the first rotational speed. 6. A method in accordance with claim 5 further comprising coupling a counter-rotating fan assembly including a forward fan assembly and a aft fan assembly to the low-pressure turbine such that the forward fan assembly and booster compressor each rotate at a first rotational speed and the aft fan assembly rotates at a second rotational speed that is approximately one-half the first rotational speed. 7. A method in accordance with claim 4 wherein the gearbox is a toroidal shaped gearbox that substantially circumscribes the drive shaft, said method further comprising positioning the gearbox within an engine sump. 8. A counter-rotating fan assembly comprising: a forward fan assembly coupled to a low-pressure turbine via a single low-pressure turbine shaft, said forward fan assembly comprising a disk and a plurality of rotor blades coupled to said disk and configured to rotate in a first rotational direction; an aft fan assembly coupled to the low-pressure turbine via the single low-pressure turbine shaft, said aft fan assembly comprising a disk and a plurality of rotor blades coupled to said disk, said aft fan assembly configured to rotate in a second rotational direction; and a booster compressor coupled directly to the single low-pressure turbine shaft such that said booster compressor rotates in the first direction. 9. A counter-rotating fan assembly in accordance with claim 8 wherein said counter-rotating fan assembly further comprises a fan frame assembly that is coupled axially forward from said booster compressor. 10. A counter-rotating fan assembly in accordance with claim 8 wherein said counter-rotating fan assembly further comprises a fan frame assembly that is coupled between said aft fan assembly and said booster compressor. 11. A counter-rotating fan assembly in accordance with claim 8 further comprising: a drive shaft coupled between said low-pressure turbine and said forward fan assembly; and a gearbox coupled between said drive shaft and said aft fan assembly such that said aft fan assembly rotates in an opposite second direction than said forward fan assembly. 12. A counter-rotating fan assembly in accordance with claim 8 wherein said forward fan assembly and said booster compressor are configured to rotate at a first rotational speed and said aft fan assembly is configured to rotate at a second rotational speed that is different than the first rotational speed. 13. A counter-rotating fan assembly in accordance with claim 8 wherein said aft fan assembly is configured to rotate at a first rotational speed that is approximately one-half the rotational speed of said forward fan assembly and said booster compressor. 14. A counter-rotating fan assembly in accordance with claim 11 wherein said gearbox has a substantially toroidal cross-sectional profile and substantially circumscribes said drive shaft. 15. A turbine engine assembly comprising: a core gas turbine engine; a low-pressure turbine coupled to said core gas turbine engine; a single low-pressure turbine shaft coupled to said low-pressure turbine; a counter-rotating fan assembly coupled to said core gas turbine engine comprising: a forward fan assembly coupled to said low-pressure turbine via said single low-pressure turbine shaft, said forward fan assembly comprising a disk and a plurality of rotor blades coupled to said disk and configured to rotate in a first rotational direction; and an aft fan assembly coupled to the low-pressure turbine via said single low-pressure-turbine shaft, said aft fan assembly comprising a disk and a plurality of rotor blades coupled to said disk, said aft fan assembly configured to rotate in a second rotational direction; and a booster compressor coupled directly to said single low-pressure-turbine shaft such that said booster compressor rotates in the first direction. 16. A turbine engine assembly in accordance with claim 15 wherein said counter-rotating fan assembly further comprises a fan frame assembly that is coupled between said aft fan assembly and said booster compressor. 17. A turbine engine assembly in accordance with claim 15 further comprising: a drive shaft coupled between said low-pressure turbine and said forward fan assembly; and a gearbox coupled between said drive shaft and said aft fan assembly such that said aft fan assembly rotates in an opposite second direction than said forward fan assembly. 18. A turbine engine assembly in accordance with claim 15 wherein said forward fan assembly and said booster compressor are configured to rotate at a first rotational speed and said aft fan assembly is configured to rotate at a second rotational speed that is different than the first rotational speed. 19. A turbine engine assembly in accordance with claim 15 wherein said aft fan assembly is configured to rotate at a first rotational speed that is approximately one-half the rotational speed of said forward fan assembly and said booster compressor. 20. A turbine engine assembly in accordance with claim 17 wherein said gearbox has a substantially toroidal cross-sectional profile and substantially circumscribes said drive shaft.