FAN DRIVE GEAR SYSTEM
A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted aft of the speed change mechanism.
1 . A gas turbine engine comprising:
a fan section;
a speed change mechanism for driving the fan section; and
a first fan section support bearing mounted forward of the speed change mechanism and a second fan section bearing mounted aft of the speed change mechanism.
2 . The gas turbine engine of claim 1 , wherein the speed change mechanism is a planetary gear system including a sun gear in communication with a fan drive turbine and a planet carrier in communication with the fan section.
3 . The gas turbine engine of claim 1 , wherein a torque frame surrounds the speed change mechanism.
4 . The gas turbine engine of claim 3 , wherein the torque frame includes a first end for engaging the fan section and second end supporting the second fan section bearing.
5 . The gas turbine engine of claim 4 , wherein the torque frame includes a plurality of fingers that surround a planet carrier of the speed change mechanism.
6 . The gas turbine engine of claim 5 , wherein the second fan section bearing is a fan thrust bearing supported on a bearing support attached to distal ends of the plurality of fingers on the torque frame.
7 . The gas turbine engine of claim 6 , wherein the bearing support includes at least one tang that engages a groove in at least one of the plurality of fingers.
8 . The gas turbine engine of claim 7 , wherein the groove is located on a radially inner side of at least one of the plurality of fingers.
9 . The gas turbine engine of claim 1 , wherein the speed change mechanism is at least partially axially aligned with a compressor section.
10 . The gas turbine engine of claim 1 , further comprising a high pressure compressor with a compression ratio of approximately 20:1 or greater.
11 . The gas turbine engine of claim 1 , further comprising a fan bypass ratio of approximately 10 or greater.
12 . The gas turbine engine of claim 1 , wherein the first fan section support bearing is a roller bearing and the second fan section bearing is a thrust bearing.
13 . A speed change mechanism for a gas turbine engine comprising:
a planetary gear system;
a torque frame surrounding the speed change mechanism; and
a bearing support attached to a downstream end of the torque frame for supporting a fan section bearing.
14 . The mechanism of claim 13 , wherein the planetary gear system includes a sun gear in communication with a fan drive turbine and a planet carrier is in communication with the fan section.
15 . The mechanism of claim 13 , wherein the torque frame includes a plurality of fingers that engage grooves in a planet carrier of the speed change mechanism and the bearing support is attached to a distal end of the plurality of fingers.
16 . The mechanism of claim 15 , wherein the bearing support includes a plurality of tangs that engage grooves on the plurality of fingers.
17 . A method of assembling a gas turbine engine comprising:
supporting a fan section on a first fan section support bearing located forward of a speed change mechanism; and
supporting the fan section on a second fan section support bearing located aft of the speed change mechanism.
18 . The method of claim 17 , wherein the speed change mechanism is a planetary gear system supported by a torque frame including a first end for engaging the fan section and a second end attached to a bearing support for supporting the second fan section support bearing.
19 . The method of claim 18 , wherein the torque frame includes a plurality of fingers that surround a planet carrier of the planetary gear system.
20 . The method of claim 19 , wherein the bearing support includes a plurality of tangs that each engage a groove on each of the plurality of fingers.