Geared architecture for gas turbine engine
A turbofan engine includes a fan section. A turbine section is in driving engagement with the fan section through a planetary gear system. The planetary gear system includes a plurality of planet gears surrounding a sun gear. A carrier supports the plurality of planet gears and includes a first carrier bearing flange. A ring gear surrounds the plurality of planet gears and includes a ring gear bearing flange. At least one ring gear carrier bearing engages the carrier bearing flange and the ring gear bearing flange. A speed change mechanism for a gas turbine is also disclosed.
1. A gas turbine engine comprising:
a fan section; and
a turbine section in driving engagement with the fan section through a planetary gear system, the planetary gear system including:
a plurality of planet gears surrounding a sun gear;
a carrier supporting the plurality of planet gears and including a first carrier bearing flange;
a ring gear surrounding the plurality of planet gears and including a ring gear bearing flange; and
at least one ring gear carrier bearing engaging the first carrier bearing flange and the ring gear bearing flange.
2. The gas turbine engine of claim 1 , wherein the ring gear is fixed from rotation relative to an engine static structure by a rigid support.
3. The gas turbine engine of claim 2 , further comprising a flexible input shaft in driving engagement with the sun gear and wherein the carrier is in driving engagement with a flexible output shaft.
4. The gas turbine engine of claim 1 , wherein the at least one ring gear carrier bearing includes at least one outer race that engages a radially inner side of the ring gear bearing flange and an inner race that engages a radially outer side of the first carrier bearing flange.
5. The gas turbine engine of claim 4 , wherein the ring gear includes an axially forward extending portion extending forward of a forward plate of the carrier and a radially inward extending portion having the ring gear bearing flange.
6. The gas turbine engine of claim 5 , wherein the ring gear bearing flange extends axially downstream from the radially inward extending portion of the ring gear.
7. The gas turbine engine of claim 4 , wherein the carrier includes a second carrier bearing flange on an aft plate of the carrier and at least one carrier sun gear bearing engages the second carrier bearing flange and an axially aft bearing flange on the sun gear.
8. The gas turbine engine of claim 4 , wherein the carrier includes a second carrier bearing flange located radially inward from the first carrier bearing flange with the second carrier bearing flange at least partially axially overlapping the first carrier bearing flange and at least one carrier sun gear bearing engages the second carrier bearing flange and an axially forward bearing flange on the sun gear.
9. The gas turbine engine of claim 4 , wherein the ring gear includes an axially aft extending portion extending downstream of an aft plate of the carrier and a radially inward extending portion having the ring gear bearing flange.
10. The gas turbine of claim 9 , wherein at least one carrier sun gear bearing engages a second carrier bearing flange and an axially aft bearing flange on the sun gear.
11. A speed change mechanism for a gas turbine engine comprising:
a plurality of planet gears surrounding a sun gear;
a carrier supporting the plurality of planet gears and including a first carrier bearing flange and a second carrier bearing flange located radially inward from the first carrier bearing flange and axial overlapping with the first carrier bearing flange;
a ring gear surrounding the plurality of planet gears and including a ring gear bearing flange; and
at least one ring gear carrier bearing with an inner race that engages a radially outer side of the first carrier bearing flange and at least one outer race that engages a radially inner side of the ring gear bearing flange.
12. The speed change mechanism of claim 11 , wherein the ring gear includes an axially forward extending portion extending forward of a forward plate of the carrier and a radially inward extending portion having the ring gear bearing flange.
13. The speed change mechanism of claim 12 , wherein the ring gear bearing flange extends axially downstream from the radially inward extending portion of the ring gear.
14. The speed change mechanism of claim 11 , wherein at least one carrier sun gear bearing engages the second carrier bearing flange and an axially forward bearing flange on the sun gear.
15. The speed change mechanism of claim 11 , wherein the ring gear includes an axially aft extending portion extending downstream of an aft plate of the carrier and a radially inward extending portion having the ring gear bearing flange.
16. The speed change mechanism of claim 15 , wherein the ring gear bearing flange extends axially and perpendicular from the radially inward extending portion of the ring gear.
17. The speed change mechanism of claim 15 , wherein at least one carrier sun gear bearing engages a second carrier bearing flange and an axially aft bearing flange on the sun gear.
18. A speed change mechanism for a gas for a gas turbine engine comprising:
a plurality of planet gears surrounding a sun gear;
a carrier supporting the plurality of planet gears and including a first carrier bearing flange;
a ring gear surrounding the plurality of planet gears and including a ring gear bearing flange; and
at least one ring gear carrier bearing with an inner race that engages a radially outer side of the first carrier bearing flange and at least one outer race that engages a radially inner side of the ring gear bearing flange;
wherein the carrier includes a second carrier bearing flange on an aft plate of the carrier and at least one carrier sun gear bearing engages the second carrier bearing flange and an axially aft bearing flange on the sun gear.