Flexible support structure for a geared architecture gas turbine engine
View Patent ↗A geared architecture with a flex mount for a Fan Drive Gear System defined by a transverse stiffness relationship.
1. A geared architecture for a gas turbine engine comprising:
a fan shaft;
a frame which supports said fan shaft, said frame defines a frame transverse stiffness;
a gear system which drives said fan shaft;
a flexible support which at least partially supports said gear system, said flexible support defines a flexible support transverse stiffness with respect to said frame transverse stiffness; and
an input coupling to said gear system, said input coupling defines an input coupling transverse stiffness with respect to said frame transverse stiffness.
2. The geared architecture as recited in claim 1 , wherein said frame and said flexible support are mounted to a static structure.
3. The geared architecture as recited in claim 1 , wherein said frame and said flexible support are mounted to a static structure of a gas turbine engine.
4. The geared architecture as recited in claim 1 , wherein said frame and said flexible support are mounted to a front center body of a gas turbine engine.
5. The geared architecture as recited in claim 1 , wherein said flexible support is mounted to a planet carrier of said gear system.
6. The geared architecture as recited in claim 5 , wherein said input coupling is mounted to a sun gear of said gear system.
7. The geared architecture as recited in claim 6 , wherein said fan shaft is mounted to a ring gear of said gear system.
8. The geared architecture as recited in claim 7 , wherein said gear system is a star system.
9. The geared architecture as recited in claim 1 , wherein said flexible support is mounted to a ring gear of said gear system.
10. The geared architecture as recited in claim 9 , wherein said input coupling is mounted to a sun gear of said gear system.
11. The geared architecture as recited in claim 10 , wherein said fan shaft is mounted to a planet carrier of said gear system.
12. The geared architecture as recited in claim 11 , wherein said gear system is a planet system.
13. The geared architecture as recited in claim 1 , further comprising a low speed spool which drives said input coupling.
14. The geared architecture as recited in claim 1 , wherein at least one of said flexible support transverse stiffness and said input coupling transverse stiffness are less than about 20% of said frame transverse stiffness.
15. The geared architecture as recited in claim 1 , wherein said flexible support transverse stiffness and said input coupling transverse stiffness are each less than about 20% of said frame transverse stiffness.
16. The geared architecture as recited in claim 1 , wherein at least one of said flexible support transverse stiffness and said input coupling transverse stiffness are less than about 11% of said frame transverse stiffness.
17. The geared architecture as recited in claim 1 , wherein said flexible support transverse stiffness and said input coupling transverse stiffness are each less than about 11% of said frame transverse stiffness.
18. The geared architecture as recited in claim 1 , wherein said frame which supports said fan shaft and defines said frame transverse stiffness is a K-frame bearing support, said K-frame bearing support supporting a bearing system that supports said fan shaft.
19. A geared architecture for a gas turbine engine comprising:
a fan shaft;
a frame which supports said fan shaft;
a gear system which drives said fan shaft, said gear system includes a gear mesh that defines a gear mesh transverse stiffness;
a flexible support which at least partially supports said gear system, said flexible support defines a flexible support transverse stiffness with respect to said gear mesh transverse stiffness; and
an input coupling to said gear system, said input coupling defines an input coupling transverse stiffness with respect to said gear mesh transverse stiffness.
20. The geared architecture as recited in claim 19 , wherein said flexible support transverse stiffness is less than about 8% of said gear mesh transverse stiffness.
21. The geared architecture as recited in claim 19 , wherein said input coupling transverse stiffness is less than about 5% of said gear mesh transverse stiffness.
22. The geared architecture as recited in claim 19 , wherein a transverse stiffness of a ring gear of said gear system is less than about 20% of said gear mesh transverse stiffness.
23. The geared architecture as recited in claim 19 , wherein a transverse stiffness of a ring gear of said gear system is less than about 12% of said gear mesh transverse stiffness.
24. The geared architecture as recited in claim 19 , wherein a transverse stiffness of a planet journal bearing which supports a planet gear of said gear system is less than or equal to said gear mesh transverse stiffness.
25. The geared architecture as recited in claim 19 , wherein said gear mesh transverse stiffness is defined between a sun gear and a multiple planet gears of said gear system.
26. The geared architecture as recited in claim 19 , wherein said gear system floats with said fan shaft.
27. The geared architecture as recited in claim 19 , wherein a planet journal bearing which supports a planet gear of said gear system defines a transverse stiffness with respect to said gear mesh transverse stiffness.
28. The geared architecture as recited in claim 19 , wherein a ring gear of said gear system defines a transverse stiffness with respect to said gear mesh transverse stiffness.