Gas turbine rotor support systems
AssigneeROLLS-ROYCE plc
InventorDerek A. Roberts
Life of this patent
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Abstract
A rotor assembly, particularly for a gas turbine engine, comprising a torsionally stiff drive shaft 16 mounted at two spaced locations in first and second bearings 22,23 which are substantially immovable bodily in radial directions. The drive shaft 16 has a flexible end portion 15 constituted by a shaft 25, projecting beyond the first bearing 23 which is more flexible in bending than the span of the drive shaft 16 between the first and second bearings 22,23. A support means 27 is mounted for rotation in a third bearing 28. The rotor 11 is mounted on the flexible end portion 15 of the drive shaft 16 to be driven thereby and is also mounted on the support means 27 for rotation in the third bearing 28. The third bearing 28 is capable of accommodating radial deflections of the support means 27 when the rotor becomes unbalanced.
Claims9
A rotor assembly comprising a torsionally stiff drive shaft mounted at two spaced locations in first and second bearing means which are substantially immovable bodily in radial directions;
- the drive shaft having a flexible end portion, projecting beyond the first bearing means, which is more flexible in bending than the span of the drive shaft between the first and second bearings;
- a support means mounted for rotation in a third bearing means;
- and a rotor mounted on the flexible end portion of the drive shaft to be driven thereby and also mounted on the support means for rotation in the third bearing means, the third bearing means being capable of accommodating radial deflections of the support means when the rotor becomes unbalanced.
Dependencies are inferred from the claim text.