Gas turbine engine assembly and method of assembling same
AssigneeGeneral Electric Company
InventorsThomas George Wakeman, Peter Walter Mueller, Stephen Eugene Melton, Michael Todd Summers
Life of this patent
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Abstract
A method of reducing gas turbine engine distortion includes coupling a core gas turbine engine to a power turbine, coupling the power turbine to a thrust bearing support assembly through a frusto-conically shaped structural support 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 to facilitate minimizing distortion of the core gas turbine engine casing, 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.
Claims13
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.
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.
Dependencies are inferred from the claim text.