Gas turbine engine assembly and method of assembling same

1. A method of reducing gas turbine engine distortion comprising:

coupling a core gas turbine engine to a power turbine;

coupling the power turbine to a thrust bearing through a frusto-conically shaped structural support assembly;

coupling the thrust bearing to a thrust bearing support assembly such that the net axial thrust of the coupled core gas turbine engine and power turbine reacts through the thrust bearing support assembly at engine centerline; and

supporting the thrust bearing support assembly such that all of the remaining thrust generated by the core gas turbine engine and the power turbine is reacted to ground.

2. A method in accordance with claim 1 wherein coupling the thrust bearing to the thrust bearing support assembly comprises coupling the thrust bearing to a thrust bearing support assembly that is substantially trapezoidally shaped.

3. A method in accordance with claim 1 further comprising coupling a pair of support members to opposite sides of the thrust bearing support assembly and to the thrust bearing.

4. A method in accordance with claim 3 further comprising coupling an alignment block to each respective support member to facilitate aligning the power turbine thrust bearing with respect to the power turbine.

5. A method in accordance with claim 3 further comprising coupling the alignment block to each respective support member to facilitate maintaining the power turbine thrust bearing in an axial direction with respect to the gas turbine engine.

6. A method in accordance with claim 1 further comprising

coupling a first pair of structural members to the thrust bearing support assembly; and

coupling a second pair of structural members to an opposite side of the thrust bearing support assembly than the first pair of structural members.

7. A gas turbine engine assembly comprising:

a core gas turbine engine comprising:

a first compressor;

a second compressor downstream from said first compressor;

a turbine coupled in flow communication with said second compressor;

a power turbine coupled to said core gas turbine engine;

a thrust bearing;

a frusto-conically shaped structural support assembly coupling said thrust bearing to said power turbine;

a thrust bearing support assembly supporting said thrust bearing such that the net axial thrust of said coupled core gas turbine engine and power turbine reacts through said thrust bearing support assembly at engine centerline, wherein said thrust bearing is supported such that all of the remaining thrust generated by said core gas turbine engine and said power turbine is reacted to ground.

8. A gas turbine engine assembly in accordance with claim 7 further comprising a base plate coupled to said thrust bearing support assembly.

9. A gas turbine engine assembly in accordance with claim 7 further comprising a pair of support members coupled to opposite sides of said thrust bearing support assembly, said support members coupled to said thrust bearing.

10. A gas turbine engine assembly in accordance with claim 9 further comprising an alignment block coupled to each respective support member to facilitate aligning said thrust bearing with respect to said power turbine.

11. A gas turbine engine assembly in accordance with claim 10 wherein said alignment block is configured to facilitate maintaining said power turbine thrust bearing in an axial direction with respect to said gas turbine engine.

12. A gas turbine engine assembly in accordance with claim 7 further comprising

a first pair of structural members coupled to said thrust bearing support assembly; and

a second pair of structural members coupled to side of said thrust bearing support assembly opposite said first pair of structural members.

13. A gas turbine engine assembly in accordance with claim 12 wherein said first and second pair of structural members are substantially hollow.