GEARED ARCHITECTURE FOR HIGH SPEED AND SMALL VOLUME FAN DRIVE TURBINE
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft drivingly connected to a fan with the fan having fan blades. A fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. A gear system input connected to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness At least one of the gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of the gear mesh lateral stiffness and the gear mesh transverse stiffness.
1 . A gas turbine engine, comprising:
a fan shaft drivingly connected to a fan, said fan having fan blades;
a fan shaft support that supports said fan shaft;
a gear system connected to said fan shaft, said gear system includes a gear mesh defining gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3;
a gear system input to said gear system defining a gear system input lateral stiffness and a gear system input transverse stiffness; and
wherein at least one of said gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.
2 . The gas turbine engine of claim 1 , further comprising a low fan pressure ratio of less than 1.45 and said low fan pressure ratio is measured across the fan blades alone.
3 . The gas turbine engine of claim 2 , further comprising a fan tip speed less than about 1150 ft/second.
4 . The gas turbine engine of claim 3 , further comprising a mid-turbine frame including at least one airfoil extending into a flow path.
5 . The gas turbine engine of claim 3 , further comprising a ring gear in said gear system defining a ring gear lateral stiffness and a ring gear transverse stiffness, wherein at least one of said ring gear lateral stiffness and said ring gear transverse stiffness is less than 12% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.
6 . The gas turbine engine of claim 2 , wherein said gear system input transverse stiffness is less than 5% of said gear mesh transverse stiffness.
7 . The gas turbine engine of claim 6 , further comprising 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.
8 . The gas turbine engine of claim 7 , wherein said gear system input lateral stiffness is less than 5% of said gear mesh lateral stiffness.
9 . The gas turbine engine of claim 8 , further comprising a fan tip speed less than about 1150 ft/second.
10 . The gas turbine engine of claim 9 , further comprising a bypass ratio greater than ten (10).
11 . The gas turbine engine of claim 8 , further comprising a ring gear in said gear system defining a ring gear lateral stiffness and a ring gear transverse stiffness, wherein at least one of said ring gear lateral stiffness and said ring gear transverse stiffness is less than 12% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.
12 . The gas turbine engine of claim 11 , wherein said ring gear transverse stiffness is less than 12% of said gear mesh transverse stiffness.
13 . The gas turbine engine of claim 1 , where said gear system input lateral stiffness is less than 5% of said gear mesh lateral stiffness.
14 . The gas turbine engine of claim 13 , further comprising 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.
15 . The gas turbine engine of claim 14 , further comprising a bypass ratio greater than ten (10).
16 . The gas turbine engine of claim 15 , further comprising a low fan pressure ratio of less than 1.45 and said low fan pressure ratio is measured across said fan blades alone.
17 . The gas turbine engine of claim 14 , further comprising a fan tip speed less than about 1150 ft/second.
18 . The gas turbine engine of claim 17 , further comprising a low fan pressure ratio of less than 1.45 and said low fan pressure ratio is measured across the fan blades alone.
19 . The gas turbine engine of claim 18 , further comprising a mid-turbine frame including at least one airfoil extending into a flow path.
20 . The gas turbine engine of claim 13 , further comprising a ring gear in said gear system defining a ring gear lateral stiffness and a ring gear transverse stiffness, wherein at least one of said ring gear lateral stiffness and said ring gear transverse stiffness is less than 12% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.
21 . The gas turbine engine of claim 11 , wherein said ring gear transverse stiffness is less than 12% of said gear mesh transverse stiffness.
22 . The gas turbine engine of claim 1 , wherein said fan shaft support defines a fan shaft support lateral stiffness and a fan shaft support transverse stiffness, at least one of said gear system input lateral stiffness and said gear system input transverse stiffness is less than 12% of a respective one of said fan shaft support lateral stiffness and said fan shaft support transverse stiffness.
23 . The gas turbine engine of claim 22 , wherein said gear system input transverse stiffness is less than 11% of said fan shaft support transverse stiffness.
24 . The gas turbine engine of claim 23 , further comprising a low fan pressure ratio of less than 1.45 and said low fan pressure ratio is measured across said fan blades alone.
25 . The gas turbine engine of claim 24 , wherein said gear system input transverse stiffness is less than 5% of said gear mesh transverse stiffness.
26 . The gas turbine engine of claim 25 , wherein said gear system input lateral stiffness is less than 5% of said gear mesh lateral stiffness.
27 . The gas turbine engine of claim 26 , further comprising a fan tip speed less than about 1150 ft/second.
28 . The gas turbine engine of claim 26 , further comprising a ring gear in said gear system defining a ring gear lateral stiffness and a ring gear transverse stiffness, wherein at least one of said ring gear lateral stiffness and said ring gear transverse stiffness is less than 12% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.
29 . The gas turbine engine of claim 28 , wherein said ring gear transverse stiffness is less than 12% of said gear mesh transverse stiffness.
30 . The gas turbine engine of claim 22 , wherein said gear system input lateral stiffness is less than 5% of said gear mesh lateral stiffness.