Rotor assembly for a gas turbine engine and method for assembling same
AssigneePratt & Whitney Canada Corp.
InventorsMichael Paolucci, Franco Di Paola
Life of this patent
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Abstract
A rotor assembly for a gas turbine engine includes a turbine shaft disposed about a longitudinal axis, a first rotor and a second rotor configured for rotation about the longitudinal axis, and an intermediate shaft positioned radially between the turbine shaft and the second rotor. The second rotor is mounted to and axially adjacent the first rotor. The intermediate shaft is mounted to the turbine shaft on an inner radial side of the intermediate shaft. The intermediate shaft is mounted to the second rotor on an outer radial side of the intermediate shaft.
Claims17
A rotor assembly for a gas turbine engine, the rotor assembly comprising:
- a turbine shaft disposed about a longitudinal axis;
- a first rotor configured for rotation about the longitudinal axis;
- a second rotor mounted to and axially adjacent the first rotor and configured for rotation about the longitudinal axis;
- and
- an intermediate shaft positioned radially between the turbine shaft and the second rotor, the intermediate shaft mounted to the turbine shaft on an inner radial side of the intermediate shaft and mounted to the second rotor on an outer radial side of the intermediate shaft, the intermediate shaft including at least one bearing assembly mounted on the outer radial side of the intermediate shaft, a first bearing assembly of the at least one bearing assembly mounted to the intermediate shaft axially aft of the second rotor, the first bearing assembly contacting the second rotor at an aft axial end of the second rotor.
A method for assembling a rotor assembly for a gas turbine engine, the method comprising:
- mounting an intermediate shaft to a turbine shaft disposed about a longitudinal axis by axially inserting the intermediate shaft relative to the turbine shaft with an inner radial side of the intermediate shaft mounted to the turbine shaft to form a first splined connection;
- mounting a second rotor to the intermediate shaft by axially inserting the second rotor relative to the intermediate shaft with an outer radial side of the intermediate shaft mounted to the second rotor to form a second splined connection, the first splined connection axially overlapping the second splined connection;
- and
- mounting a first rotor to the second rotor with the first rotor axially adjacent the second rotor.
A rotor assembly for a gas turbine engine, the rotor assembly comprising:
- a turbine shaft disposed about a longitudinal axis;
- a first rotor configured for rotation about the longitudinal axis;
- a second rotor mounted to and axially adjacent the first rotor and configured for rotation about the longitudinal axis;
- and
- an intermediate shaft positioned radially between the turbine shaft and the second rotor, the intermediate shaft mounted to the turbine shaft on an inner radial side of the intermediate shaft and mounted to the second rotor on an outer radial side of the intermediate shaft;
- wherein the turbine shaft and the intermediate shaft define a first splined connection comprising first external splines of the turbine shaft engaged with first internal splines of the intermediate shaft;
- wherein the intermediate shaft and the second rotor define a second splined connection comprising second external splines of the intermediate shaft engaged with second internal splines of the second rotor, and wherein the first splined connection axially overlaps the second splined connection.
Dependencies are inferred from the claim text.