Engine mount system for a gas turbine engine

1. A gas turbine engine comprising:

a propulsor section including a rotor having a plurality of blades;

an epicycle gear train;

a low spool and a high spool rotatable about an engine axis of rotation, the low spool including a low pressure compressor and a low pressure turbine, the high spool including a high pressure turbine that drives a high pressure compressor, and wherein the low pressure turbine drives the propulsor section through the gear train;

a combustor between the high pressure compressor and the high pressure turbine;

a static structure that supports a bearing system upon which the low pressure and high pressure turbines, the low pressure and high pressure compressors and the rotor rotate, wherein the static structure includes a plurality of cases, and the plurality of cases includes a first case and a second case positioned aft of the first case with respect to the engine axis of rotation; and

a mount system including a forward mount and an aft mount arranged in a plane containing the engine axis of rotation, wherein the forward mount is secured to the first case, the aft mount is secured to the second case, and the aft mount comprises:

a rear mount platform mountable to an aircraft structure, wherein the aft mount reacts at least a vertical load and a side load in operation;

a whiffle tree assembly including a whiffle link supporting a first sliding ball joint and a second sliding ball joint;

a first A-arm mounted to the rear mount platform through a first ball joint and the whiffle tree assembly through the first sliding ball joint; and

a second A-arm mounted to the rear mount platform through a second ball joint and the whiffle tree assembly through the second sliding ball joint.

2. The gas turbine engine as recited in claim 1 , wherein the aft mount is configured so as to not be connected to the first case by any thrust links when the gas turbine engine is mounted.

3. The gas turbine engine as recited in claim 1 , wherein the second case is a thrust case, the aft mount is secured to a mid-turbine frame at the thrust case, and the mid-turbine frame is axially between the low pressure turbine and the high pressure turbine relative to the engine axis of rotation.

4. The gas turbine engine as recited in claim 3 , wherein the aft mount reacts a thrust vector of a thrust load along the engine axis of rotation at the second case in operation.

5. The gas turbine engine as recited in claim 4 , wherein the first case is an intermediate case.

6. The gas turbine engine as recited in claim 5 , wherein the aft mount includes a drag link that reacts a torque load about the engine axis of rotation in operation, and the drag link includes a pair of ball joints mounted to the thrust case and the rear mount platform.

7. The gas turbine engine as recited in claim 6 , wherein the forward mount reacts a vertical load and a side load in operation.

8. The gas turbine engine as recited in claim 7 , wherein the whiffle link is rotatable about a central ball joint attached to the aircraft structure, and the aircraft structure is a pylon.

9. The gas turbine engine as recited in claim 7 , wherein:

the first and second A-arms mount between the thrust case at case bosses;

the first and second A-arms each include a first link arm, a second link arm and a third link arm;

the first link arm is between a respective one of the case bosses and the rear mount platform;

the second link arm is between the respective one of the case bosses and the whiffle tree assembly;

the third link arm is between the whiffle tree assembly and the rear mount platform; and

the first and second A-arms transmit a thrust load to the rear mount platform in operation.

10. The gas turbine engine as recited in claim 9 , wherein the aft mount is configured so as to not be connected to the first case by any thrust links when the gas turbine engine is mounted.

11. The gas turbine engine as recited in claim 10 , wherein:

the forward mount includes a shackle arrangement which mounts to the intermediate case at two points; and

the whiffle tree assembly reacts only a vertical load in operation.

12. The gas turbine engine as recited in claim 11 , wherein the low pressure turbine is a three to six stage turbine.

13. The gas turbine engine as recited in claim 12 , wherein the bearing system includes a pair of bearings which rotatably support the low and high spools, and the pair of bearings are supported within the mid-turbine frame.

14. The gas turbine engine as recited in claim 13 , wherein the pair of bearings straddle radially extending structural struts preloaded in tension.

15. The gas turbine engine as recited in claim 14 , wherein the bearing system includes a first bearing which rotationally supports the rotor, and the first bearing is a dual bearing preloaded to react a thrust load in operation.

16. The gas turbine engine as recited in claim 15 , wherein the bearing system includes:

a second bearing which rotationally supports the low spool;

a third bearing which rotationally supports the high spool; and

wherein the second and third bearings react a thrust load in operation and are axially located within the intermediate case relative to the engine axis of rotation.

17. The gas turbine engine as recited in claim 16 , wherein the bearing system includes:

a fourth bearing that rotationally supports a rear segment of the low spool and reacts a radial load in operation;

a fifth bearing that rotationally supports the rear segment of the low spool and reacts a radial load in operation;

wherein the fourth bearing is axially located within the thrust case relative to the engine axis of rotation; and

wherein the fifth bearing is axially located aft of the fourth bearing within the thrust case relative to the engine axis of rotation.

18. The gas turbine engine as recited in claim 1 , wherein:

the plurality of cases includes an intermediate case, a combustor case, a high pressure turbine case, a thrust case, a low pressure turbine case; and

the intermediate case includes a multiple of circumferentially spaced radially extending struts.

19. The gas turbine engine as recited in claim 18 , wherein the aft mount reacts a thrust vector of a thrust load along the engine axis of rotation at the second case in operation.

20. The gas turbine engine as recited in claim 19 , wherein:

the first and second A-arms mount between the second case at case bosses;

the first and second A-arms are generally triangular arrangements each including first, second and third link arms;

the first link arm is between a respective one of the case bosses and the rear mount platform;

the second link arm is between the respective one of the case bosses and the whiffle tree assembly; and

the third link arm is between the whiffle tree assembly and the rear mount platform.

21. The gas turbine engine as recited in claim 20 , wherein the aft mount includes a drag link, and the drag link includes a pair of ball joints mounted to respective ones of the thrust case and the rear mount platform.

22. The gas turbine engine as recited in claim 21 , wherein the first and second A-arms transmit a thrust load to the rear mount platform in operation.

23. The gas turbine engine as recited in claim 22 , wherein the drag link reacts a torque load about the engine axis of rotation in operation.

24. The gas turbine engine as recited in claim 23 , wherein the aft mount is configured so as to not be connected to the first case by any thrust links when the gas turbine engine is mounted.

25. The gas turbine engine as recited in claim 24 , wherein the low pressure turbine is a three to six stage turbine.

26. The gas turbine engine as recited in claim 25 , wherein the first case is a high pressure compressor case.

27. The gas turbine engine as recited in claim 25 , wherein the second case is a turbine exhaust case.

28. The gas turbine engine as recited in claim 27 , wherein the high pressure turbine includes two stages.

29. The gas turbine engine as recited in claim 28 , wherein the low pressure compressor and the low pressure turbine include an equal number of stages.

30. The gas turbine engine as recited in claim 29 , wherein the low pressure compressor includes four stages.