Flexible support structure for a geared architecture gas turbine engine
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft configured to drive a fan, a support configured to support at least a portion of the fan shaft, the support defining a support transverse stiffness and a support lateral stiffness, a gear system coupled to the fan shaft, and a flexible support configured to at least partially support the gear system. The flexible support defines a flexible support transverse stiffness with respect to the support transverse stiffness and a flexible support lateral stiffness with respect to the support lateral stiffness. The input defines an input transverse stiffness with respect to the support transverse stiffness and an input lateral stiffness with respect to the support lateral stiffness.
1. A gas turbine engine, comprising:
a fan having fan blades;
an outer housing surrounding the fan, and a bypass flow path within said outer housing;
a fan shaft drivingly connected to said fan;
a frame supporting said fan shaft and defining a frame lateral stiffness;
a gear system connected to said fan shaft and driven through an input, said gear system includes a gear mesh defining a gear mesh lateral stiffness; and
a gear system flex mount arrangement, wherein said flex mount arrangement accommodates misalignment of said fan shaft and said input during operation and includes a flexible support which supports said gear system relative to a static structure and defines a flexible support lateral stiffness and said flexible support lateral stiffness is less than 11% of said frame lateral stiffness and said flexible support lateral stiffness is less than 8% of said gear mesh lateral stiffness.
2. The gas turbine engine of claim 1 , and wherein said frame defines a frame transverse stiffness and said flexible support defines a flexible support transverse stiffness that is less than 11% of said frame transverse stiffness.
3. The gas turbine engine of claim 2 , wherein said gear system includes a ring gear defining a ring gear lateral stiffness that is less than 12% of said gear mesh lateral stiffness.
4. The gas turbine engine of claim 3 , further comprising a gear reduction ratio of greater than 2.3, a bypass ratio greater than ten (10), a fan pressure ratio of less than 1.45 measured across said fan blades alone, and a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1, wherein said low pressure turbine pressure ratio is a ratio of a pressure measured prior to said inlet as related to a pressure at said outlet prior to any exhaust nozzle.
5. The gas turbine engine of claim 4 , wherein said gear mesh defines a gear mesh transverse stiffness, and said flexible support transverse stiffness is less than 8% of said gear mesh transverse stiffness.
6. The gas turbine engine of claim 5 , wherein said ring gear defines a ring gear transverse stiffness and said ring gear transverse stiffness is less than 12% of said gear mesh transverse stiffness.
7. The gas turbine engine of claim 6 , further comprising a two stage high pressure turbine.
8. The gas turbine engine of claim 7 , further comprising a three stage low pressure compressor.
9. The gas turbine engine of claim 7 , further comprising a fan tip speed of less than 1150 ft/second.
10. The gas turbine engine of claim 3 , wherein said input to said gear system defines an input lateral stiffness and said input lateral stiffness is less than 11% of said frame lateral stiffness.
11. The gas turbine engine of claim 10 , wherein said input lateral stiffness is less than 5% of said gear mesh lateral stiffness.
12. The gas turbine engine of claim 11 , further comprising a journal bearing defining a journal bearing lateral stiffness that is less than said gear mesh lateral stiffness.
13. The gas turbine engine of claim 10 , wherein said ring gear defines a ring gear transverse stiffness, said gear mesh defines a gear mesh transverse stiffness, said ring gear transverse stiffness is less than 12% of said gear mesh transverse stiffness, and said flexible support transverse stiffness is less than 8% of said gear mesh transverse stiffness.
14. A gas turbine engine, comprising:
a fan having fan blades;
an outer housing surrounding the fan, and a bypass flow path within said outer housing;
a fan shaft drivingly connected to said fan;
a frame supporting said fan shaft and defining a frame lateral stiffness and a frame transverse stiffness;
a gear system connected to said fan shaft and driven through an input to said gear system defining an input lateral stiffness;
a gear system flex mount arrangement, wherein said flex mount arrangement accommodates misalignment of said fan shaft and said input during operation, and includes a flexible support which supports said gear system relative to a static structure and defines a flexible support lateral stiffness that is less than 11% of said frame lateral stiffness and said input lateral stiffness is less than 11% of said frame lateral stiffness; and
a two stage high pressure turbine.
15. The gas turbine engine of claim 14 , further comprising a gear reduction ratio of greater than 2.3, a bypass ratio greater than ten (10), a fan pressure ratio of less than 1.45 measured across said fan blades alone, and a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1, wherein said low pressure turbine pressure ratio is a ratio of a pressure measured prior to said inlet as related to a pressure at said outlet prior to any exhaust nozzle.
16. The gas turbine engine of claim 15 , further comprising a gear mesh defining a gear mesh lateral stiffness and said flexible support lateral stiffness is less than 8% of said gear mesh lateral stiffness.
17. The gas turbine engine of claim 15 , further comprising a gear mesh defining a gear mesh lateral stiffness, a ring gear defining a ring gear lateral stiffness, and said ring gear lateral stiffness is less than 12% of said gear mesh lateral stiffness.
18. The gas turbine engine of claim 17 , wherein said ring gear defines a ring gear transverse stiffness, said gear mesh defines a gear mesh transverse stiffness, said flexible support defines a flexible support transverse stiffness, said ring gear transverse stiffness is less than 12% of said gear mesh transverse stiffness and said flexible support transverse stiffness is less than 8% of said gear mesh transverse stiffness.
19. The gas turbine engine of claim 18 , wherein said flexible support transverse stiffness is less than 11% of said frame transverse stiffness.
20. The gas turbine engine of claim 15 , further comprising a gear mesh defining a gear mesh lateral stiffness and said input lateral stiffness is less than 5% of said gear mesh lateral stiffness.
21. The gas turbine engine of claim 20 , further comprising further comprising a fan tip speed of less than 1150 ft/second.
22. A gas turbine engine, comprising:
a fan having fan blades;
an outer housing surrounding the fan, and a bypass flow path within said outer housing;
a fan shaft driving said fan in operation;
a frame supporting said fan shaft and defining a frame transverse stiffness and a frame lateral stiffness;
a gear system connected to said fan shaft and driven through an input to said gear system, the gear system including a ring gear defining a ring gear lateral stiffness;
a gear system flex mount arrangement, wherein said flex mount arrangement accommodates misalignment of said fan shaft and said input during operation, and includes a gear mesh defining a gear mesh lateral stiffness and a flexible support which supports said gear system relative to a static structure and defines a flexible support transverse stiffness that is less than 11% of said frame transverse stiffness; and
wherein said ring gear lateral stiffness is less than 12% of said gear mesh lateral stiffness.
23. The gas turbine engine of claim 22 , further comprising a two stage high pressure turbine.
24. The gas turbine engine of claim 23 , wherein said flexible support defines a flexible support lateral stiffness that is less than 11% of said frame lateral stiffness.
25. The gas turbine engine of claim 24 , wherein said flexible support lateral stiffness is less than 8% of said gear mesh lateral stiffness.
26. The gas turbine engine of claim 25 , further comprising a gear reduction ratio of greater than 2.3, a bypass ratio greater than ten (10), a fan pressure ratio of less than 1.45 measured across said fan blades alone, and a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1, wherein said low pressure turbine pressure ratio is a ratio of a pressure measured prior to said inlet as related to a pressure at said outlet prior to any exhaust nozzle.
27. The gas turbine engine of claim 26 , wherein said ring gear defines a ring gear transverse stiffness, said gear mesh defines a gear mesh transverse stiffness, said ring gear transverse stiffness is less than 12% of said gear mesh transverse stiffness, and said flexible support transverse stiffness is less than 8% of said gear mesh transverse stiffness.
28. The gas turbine engine of claim 27 , further comprising a fan tip speed of less than 1150 ft/second.
29. The gas turbine engine of claim 28 , wherein said input defines an input lateral stiffness, wherein said input lateral stiffness is less than 11% of said frame lateral stiffness and said input lateral stiffness is less than 5% of said gear mesh lateral stiffness.