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A gearbox includes a support structure, at least one sun gear coupled within the support structure, and a plurality of planetary gears coupled within the support structure. The support structure includes a first portion, an axially aft second portion, and a thrust spring coupled between the first an

A gearbox includes a support structure, at least one sun gear coupled within the support structure, and a plurality of planetary gears coupled within the support structure. The support structure includes a first portion, an axially aft second portion, and a thrust spring coupled between the first and second portions.

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What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: providing a core gas turbine engine at least partially defined by a frame and having a drive shaft rotatable about a longitudinal axis of the core gas turbine engine; coupling a low-pressure turbine to the

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: providing a core gas turbine engine at least partially defined by a frame and having a drive shaft rotatable about a longitudinal axis of the core gas turbine engine; coupling a low-pressure turbine to the core gas turbine engine; 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 in a first direction and the second fan assembly rotates in an opposite second direction; coupling a gearbox between the shaft and the counter-rotating fan assembly so that the gear box extends substantially circumferentially about the drive shaft, the gearbox including a support structure including a first portion and a second portion; coupling a gearbox input to the low-pressure turbine; coupling a gearbox output to the counter-rotating fan assembly; and coupling a thrust spring between the gearbox input and the gearbox output to at least partially absorb the thrust generated by the counter-rotating fan assembly the thrust spring formed unitarily with the first and second portions, a plurality of openings formed through the thrust spring to facilitate adjusting the thrust absorbed by the thrust spring. 2. A method in accordance with claim 1 wherein the gearbox includes a support structure including a first portion and a second portion, said method further comprising coupling the thrust spring between the first and second portions. 3. A method in accordance with claim 1 further comprising coupling a thrust bearing within the second portion to at least partially absorb the thrust generated by the counter-rotating fan assembly. 4. A method in accordance with claim 3 further comprising coupling an outer race of the thrust bearing assembly to the frame. 5. A method in accordance with claim 1 further forming a plurality of planetary gear support structures unitarily with the first portion. 6. A gearbox comprising: a support structure; at least one sun gear coupled within said support structure; and a plurality of planetary gears coupled within said support structure, said support structure comprising a first portion, an axially aft second portion, and a thrust spring coupled between said first and second portions, said thrust spring comprising a plurality of openings extending therethrough, at least one of the quantity of openings and the size of the openings based on the thrust absorbed by the thrust spring. 7. A gearbox in accordance with claim 6 wherein said first portion, said second portion, and said thrust spring are formed unitarily. 8. A gearbox in accordance with claim 6 further comprising: an input coupled to a gas turbine engine low-pressure turbine; at least one output coupled to a counter-rotating fan assembly, said thrust spring configured at least partially absorb the thrust generated by the counter-rotating fan assembly. 9. A gearbox in accordance with claim 6 wherein said gearbox further comprises a thrust bearing coupled within said support structure. 10. A gearbox in accordance with claim 6 wherein said support structure further comprises a plurality of planetary gear support structures formed unitarily with said support structure. 11. A gearbox in accordance with claim 10 wherein said thrust bearing comprises an outer race that is coupled to a gas turbine engine frame and a radially inner race that is coupled to said counter-rotating fan assembly. 12. A turbine engine assembly comprising: a core turbine engine; a low-pressure turbine coupled to said core turbine engine; a gearbox coupled to said low-pressure turbine; and a counter-rotating fan assembly coupled to said gearbox, said gearbox comprising a first portion; an axially aft second portion; and a thrust spring coupled between said first and second portions, said thrust spring comprises a plurality of openings extending therethrough, the quantity of openings based on the thrust absorbed by the thrust spring. 13. A turbine engine assembly in accordance with claim 12 wherein said first portion, said second portion, and said thrust spring are formed unitarily. 14. A turbine engine assembly in accordance with claim 12 further comprising: an input coupled to said low-pressure turbine; at least one output coupled to said counter-rotating fan assembly, said thrust spring configured at least partially absorb the thrust generated by the counter-rotating fan assembly. 15. A turbine engine assembly in accordance with claim 12 wherein said gearbox further comprises a thrust bearing coupled within said support structure. 16. A turbine engine assembly in accordance with claim 12 wherein said support structure further comprises a plurality of planetary gear support structures formed unitarily with said support structure.