Engine mount system for a turbofan gas turbine engine
A gas turbine engine according to an exemplary aspect of the present invention includes a gear train defined along an engine centerline axis, and a spool along the engine centerline axis which drives the gear train, the spool includes a low stage count low pressure turbine.
1. A gas turbine engine comprising:
a turbine section;
a fan section;
an epicyclic gear train;
a spool connecting said turbine section and said epicyclic gear train such that said fan section is rotatable with said turbine section through said epicyclic gear train;
a static structure supporting said turbine section and said fan section;
a mount including a mount platform, a wiffle tree assembly, a first A-arm mounted to said mount platform and said wiffle tree assembly and a second A-arm mounted to said mount platform and said wiffle tree assembly.
2. The gas turbine engine as recited in claim 1 , wherein said wiffle tree assembly includes a wiffle link supporting a ball joint, a first sliding ball joint and a second sliding ball joint.
3. The gas turbine engine as recited in claim 2 , wherein said ball joint is between said first sliding ball joint and said second sliding ball joint.
4. The gas turbine engine as recited in claim 1 , wherein said first A-arm is mounted to said mount platform through a first A-arm first ball joint, and said second A-arm is mounted to said mount platform through a second A-arm ball joint.
5. The gas turbine engine as recited in claim 1 , wherein said first A-arm is mounted to said wiffle tree assembly through a first sliding ball joint, and said second A-arm is mounted to said wiffle tree assembly through a second sliding ball joint.
6. The gas turbine engine as recited in claim 1 , wherein said first A-arm and said second A-arm each comprise rigid generally triangular arrangement.
7. The gas turbine engine as recited in claim 1 , further comprising a drag link including a first ball joint mounted to said static structure and a second ball joint mounted to said mount platform, said drag link reacting torque.
8. The gas turbine engine as recited in claim 1 , wherein said static structure comprises an engine case.
9. The gas turbine engine as recited in claim 1 , wherein said static structure comprises an engine case.
10. The gas turbine engine as recited in claim 1 , wherein said mount is an aft mount, and further comprising a forward mount forward of said aft mount with regard to an engine central axis.
11. The gas turbine engine as recited in claim 1 , wherein said epicyclic gear train has a gear reduction ratio of greater than 2.5:1.
12. The gas turbine engine as recited in claim 1 , further comprising a compressor section, said compressor section being arranged to receive a core airflow, and said fan section defines a bypass ratio with regard to said core airflow that is greater than 10:1.