Engine mounting configuration for a turbofan gas turbine engine
An engine mounting configuration reacts engine thrust at an aft mount. The engine mounting configuration reduces backbone bending of the engine, intermediate case distortion and frees-up space within the core nacelle.
1. A gas turbine engine mounting configuration comprising:
an aft mount which reacts at least a thrust load, said aft mount includes a beam having a first arm and a second arm;
wherein said first arm includes a first attachment fastener and said second arm includes a second attachment fastener, said first attachment fastener and said second attachment fastener defined along a first and second attachment fastener axis which extends radially inward to intersect the engine axis.
2. The gas turbine engine mounting configuration as recited in claim 1 , wherein said aft mount is attachable to a mid-turbine frame.
3. The gas turbine engine mounting configuration as recited in claim 2 , wherein said aft mount is attachable between a first bearing and a second bearing supported by said mid turbine frame.
4. The gas turbine engine mounting configuration as recited in claim 1 , wherein said aft mount is attachable to an engine thrust case.
5. The gas turbine engine mounting configuration as recited in claim 1 , further comprising a forward mount forward of said aft mount along an engine axis, said forward mount reacts at least a vertical load.
6. The gas turbine engine mounting configuration as recited in claim 5 , wherein said forward mount is attachable to an engine intermediate case.
7. The gas turbine engine mounting configuration as recited in claim 5 , wherein said forward mount reacts a side load.
8. The gas turbine engine mounting configuration as recited in claim 5 , wherein said forward mount is a generally planar member transverse to said engine axis.
9. The gas turbine engine mounting configuration as recited in claim 1 , wherein said beam is fixed about a vertical axis which intersects said engine axis.
10. The gas turbine engine mounting configuration as recited in claim 1 , wherein said beam is rotatable about a vertical axis which intersects said engine axis.
11. The gas turbine engine mounting configuration as recited in claim 1 , wherein said beam is a single beam, said first and second arms defined by said beam.
12. The gas turbine engine mounting configuration as recited in claim 1 , further including a pylori, said aft mount extending from said pylori, said pylori suspending an engine.
13. The gas turbine engine mounting configuration as recited in claim 12 , wherein said beam is rotatable relative to said pylori.
14. The gas turbine engine mounting configuration as recited in claim 1 , wherein the gas turbine engine mounting configuration excludes thrust links extending from an intermediate case.
15. The gas turbine engine mounting configuration as recited in claim 1 , wherein said first and second arms are defined by said beam.
16. A gas turbine engine mounting configuration comprising:
a pylori;
an aft mount which reacts at least a thrust load, said aft mount extends from said pylori, said aft mount includes a beam having a first arm and a second arm, wherein said beam is rotatable about a vertical axis which intersects an engine axis; and
a forward mount which reacts at least a vertical load, said forward mount extends from said pylori forward of said aft mount along said engine axis.
17. The gas turbine engine mounting configuration as recited in claim 16 , wherein said forward mount reacts a side load.
18. The gas turbine engine mounting configuration as recited in claim 16 , wherein said first arm includes a first attachment fastener and said second arm includes a second attachment fastener, said first attachment fastener and said second attachment fastener defined along a first and second attachment fastener axis which extend radially inward to intersect the engine axis.
19. The gas turbine engine mounting configuration as recited in claim 16 , wherein said pylori suspends an engine.
20. The gas turbine engine mounting configuration as recited in claim 19 , wherein said aft mount is rotatable relative to said pylori.
21. The gas turbine engine mounting configuration as recited in claim 16 , wherein said beam is a single beam.