Gas turbine engine with geared architecture
In one exemplary embodiment, a gas turbine engine includes a bypass flow ratio greater than about ten. A fan supported on a fan shaft having a plurality of fan blades and a low fan pressure ratio of less than 1.45 measured across the fan blades alone. A gutter with an annular channel. A gear system connected to the fan shaft having a gear reduction ratio greater than 2.5, planetary gears, and a ring gear with an aperture that is axially aligned with the annular channel. A torque frame at least partially supports the gear system. A low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1.
1. A gas turbine engine comprising:
a bypass ratio greater than about ten (10);
a fan supported on a fan shaft and having a plurality of fan blades, and a low fan pressure ratio of less than 1.45 across the fan blades alone;
a gutter with an annular channel;
a gear system connected to the fan shaft and having a gear reduction ratio of greater than 2.5, a plurality of planetary gears, and a ring gear with an aperture that is axially aligned with the annular channel;
a torque frame at least partially supporting the gear system; and
a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1.
2. The gas turbine engine of claim 1 , further comprising a fan tip speed less than 1150 ft/second.
3. The gas turbine engine of claim 2 , further comprising a front center body facilitating segregation of vibration.
4. The gas turbine engine of claim 3 , further comprising an input to the gear system, the input facilitates segregation of vibrations.
5. The gas turbine engine of claim 4 , wherein the gear system includes a sun gear having a sun gear splined connection.
6. The gas turbine engine of claim 5 , wherein the input includes an input splined connection complementary to the sun gear splined connection.
7. The gas turbine engine of claim 3 , wherein the fan shaft is supported by at least one tapered roller bearing.
8. The gas turbine engine of claim 1 , further comprising a ring gear having a first portion with a first set of opposed angled teeth separated by a trough from a second portion with a second set of opposed angled teeth, wherein the first portion and the second portion of the ring gear each include a radially extending flange that extends radially outward away from a corresponding set of opposed angled teeth.
9. The gas turbine engine of claim 8 , further comprising a fan tip speed less than 1150 ft/second.
10. The gas turbine engine of claim 8 , wherein the fan shaft includes a radially extending flange connected to the radially extending flange on the first portion of the ring gear and the radially extending flange on the second portion of the ring gear.
11. The gas turbine engine of claim 10 , further comprising a seal attached to at least one of the radially extending flanges on the ring gear or the radially extending flange on the fan shaft.
12. The gas turbine engine of claim 11 , wherein the seal includes an oil return passage.
13. The gas turbine engine of claim 12 , wherein the oil return passage includes a slot.
14. The gas turbine engine of claim 13 , wherein the slot is located in the seal.
15. The gas turbine engine of claim 13 , wherein the slot is located in the radially extending flange on the fan shaft.
16. The gas turbine engine of claim 1 , further comprising a gutter for collecting oil expelled from the gear system.
17. The gas turbine engine of claim 16 , further comprising a fan tip speed less than 1150 ft/second.
18. The gas turbine engine of claim 17 , wherein the gutter is formed from a soft material.
19. The gas turbine engine of claim 18 , wherein the soft material is aluminum.
20. A gas turbine engine comprising:
a fan supported on a fan shaft by at least one roller bearing and having a plurality of fan blades;
a fan tip speed less than 1150 ft/second;
a bypass ratio greater than about ten (10);
a low fan pressure ratio of less than 1.45 and the low fan pressure ratio is measured across the fan blades alone;
a gutter with an annular channel;
a planetary gear system connected to the fan shaft, the gear system having a gear reduction ratio of greater than 2.5, a plurality of intermediate gears, and a ring gear a ring gear with an aperture that is axially aligned with the annular channel;
a torque frame as least partially supporting the gear system; and
a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1.
21. The gas turbine engine of claim 20 , further comprising an input to the gear system, the input facilitates segregation of vibrations.
22. The gas turbine engine of claim 21 , wherein the gear system includes a sun gear having a sun gear splined connection and the input includes an input splined connection complementary to the sun gear splined connection.
23. The gas turbine engine of claim 22 , wherein the roller bearing is a tapered roller bearing.
24. The gas turbine engine of claim 21 , further comprising a gutter for collecting oil expelled from the gear system.
25. The gas turbine engine of claim 24 , wherein the gutter is formed from a soft material.
26. The gas turbine engine of claim 25 , wherein the soft material is aluminum.
27. The gas turbine of claim 26 , wherein the ring gear includes a first portion separated from a second portion, the first portion and the second portion each include a radially extending flange that extends radially outward away from a corresponding set of opposed angled teeth.
28. The gas turbine engine of claim 27 , wherein the fan shaft includes a radially extending flange connected to the radially extending flange on the first portion of the ring gear and the radially extending flange on the second portion of the ring gear.
29. The gas turbine engine of claim 28 , further comprising a seal attached to at least one of the radially extending flanges on the ring gear or the radially extending flange on the fan shaft.
30. The gas turbine engine of claim 11 , wherein the seal includes an oil return passage.