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A gas turbine engine having at least one spool assembly, the at least one spool assembly including a fan rotor, a compressor disposed downstream of the fan rotor, a turbine and a shaft connecting the fan rotor, compressor and turbine, a joint affixed to an upstream end of the shaft, and including a

A gas turbine engine having at least one spool assembly, the at least one spool assembly including a fan rotor, a compressor disposed downstream of the fan rotor, a turbine and a shaft connecting the fan rotor, compressor and turbine, a joint affixed to an upstream end of the shaft, and including a first link connecting the fan rotor to the shaft and a second link connecting the compressor to the shaft, the second link being less rigid then the first link.

대표청구항 ▼

1. A gas turbine engine having at least one spool assembly, the at least one spool assembly comprising a fan rotor, a compressor disposed downstream of the fan rotor, a turbine and a shaft connecting the fan rotor, compressor and turbine, a joint having first and second links firmly fixed to an upst

1. A gas turbine engine having at least one spool assembly, the at least one spool assembly comprising a fan rotor, a compressor disposed downstream of the fan rotor, a turbine and a shaft connecting the fan rotor, compressor and turbine, a joint having first and second links firmly fixed to an upstream end of the shaft, the first link being connected to the fan rotor by means of first fasteners and the second link being connected to the compressor, by means of second fasteners, the second link being less rigid than the first link wherein the first link comprises an annular front leg extending generally radially outwardly from the shaft, and wherein the second link comprises an annular rear leg extending generally radially outwardly from the shaft. 2. The gas turbine engine as defined in claim 1 wherein the joint comprises an annular body extending radially and outwardly from the upstream end of the shaft, the front leg expanding frustoconically forwardly from the annular body of the shaft end, and the rear leg expanding frustoconically rearwardly from the annular body of the shaft end. 3. The gas turbine engine as defined in claim 2 wherein the annular body with the annular front and rear legs comprises a substantial Y-shaped cross section. 4. The gas turbine engine as defined in claim 2 wherein the annular front leg has a thickness greater than a thickness of the annular rear leg. 5. The gas turbine engine as defined in claim 2 wherein the annular front leg is shorter than the annular rear leg. 6. The gas turbine engine as defined in claim 2 wherein the annular body has a thickness greater than a thickness of either the annular front or rear leg. 7. The gas turbine engine as defined in claim 2 wherein the joint is integrated with the shaft to form an integral part of a single-piece shaft. 8. The gas turbine engine as defined in claim 2 wherein the annular front leg defines a plurality of holes receiving respective fasteners axially extending therethrough to secure the fan rotor to the annular front leg. 9. The gas turbine engine as defined in claim 2 wherein the annular rear leg defines a plurality of holes receiving respective fasteners axially extending therethrough to secure the compressor to the annular rear leg. 10. The gas turbine engine as defined in claim 1 wherein the fan rotor comprises a rearwardly and inwardly extending annular web connected to the first link of the joint and wherein the compressor comprises a forwardly and inwardly extending annular web connected to the second link of the joint. 11. The gas turbine engine as defined in claim 10 wherein the web of the fan rotor has a thickness greater than a thickness of the web of the compressor. 12. The gas turbine engine as defined in claim 10 wherein the annular web of the fan rotor comprises a flange extending radially and inwardly from a rear end of the annular web, the flange defining a plurality of holes receiving respective fasteners extending axially therethrough to secure the first link of the joint to the annular web of the fan rotor. 13. The gas turbine engine as defined in claim 10 wherein the annular web of the compressor comprises a flange extending radially and inwardly from a front end of the annular web, the flange defining a plurality of holes receiving respective fasteners extending axially therethrough to secure the second link of the joint to the annular web of the compressor. 14. A gas turbine engine having at least one spool assembly, the at least one spool assembly comprising a fan rotor, a compressor disposed downstream of the fan rotor, a turbine and a shaft connecting the fan rotor, compressor and turbine, means firmly fixed to an upstream end of the shaft being connected to the fan rotor by means of first fasteners in a first link and connecting being connected to the compressor by means of second fasteners in a second link, the second link being less rigid than the first link. 15. A method for disassociating a fan rotor deflection from a compressor deflection during an undue imbalance event of a fan rotor in a gas turbine engine, the method comprising: a) firmly fixing a fan rotor to an engine shaft by a first link, the link frustoconically extending outwardly of an upstream end of the shaft; andb) firmly fixing a compressor to the engine shaft by a second link, the second link frustoconically extending outwardly of the upstream end of the shaft, the second link being less rigid than the first link. 16. The method as defined in claim 15 wherein steps (a) and (b) are achieved by a joint firmly fixed to the upstream end of the shaft, the joint having the first and second links with a joint body to form a single-piece component having a substantially Y-shaped cross section.