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US 2025/0052158 A1Published application
Rotor assembly for gas turbine engines with replaceable balance weight bands
AssigneeRolls-Royce North American Technologies Inc.
InventorRyan C. Humes
Life of this patent
Estimating the term…
Abstract
A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight is located in a space radially between the first rotor and the second rotor.
Claims20
A rotor assembly adapted for use in a gas turbine engine, the rotor assembly comprising:
- a first rotor arranged circumferentially about a central axis, the first rotor having a first rotor body that extends circumferentially about the central axis, a first band that extends axially away from the first rotor body at least partway circumferentially about the central axis, a plurality of first splines that extend radially inward from the first band, and a discrete first tab that extends axially away from the first band,
- a second rotor arranged circumferentially about the central axis and located radially inward of the first rotor, the second rotor having a second rotor body that extends circumferentially about the central axis, a second band that extends at least partway circumferentially about the central axis, and a plurality of second splines that extend radially away from the band and engage with the plurality of first splines to couple the second rotor with the first rotor for rotation therewith, and
- a balance weight located radially between the first rotor and the second rotor and configured to balance a weight distribution of the rotor assembly, the balance weight extending circumferentially partway about the central axis and formed to define a groove that receives the first tab of the first rotor to block circumferential movement of the balance weight relative to the first rotor and the second rotor, wherein an outer radial surface of the balance weight is configured to be machined as a sacrificial layer to allow for balance correction of the rotor assembly without machining the first rotor and the second rotor.
A rotor assembly adapted for use in a gas turbine engine, the rotor assembly comprising:
- a first component arranged circumferentially about a central axis, the first component having a first band that extends at least partway circumferentially about the central axis, a discrete first tab that extends away from the first band, and a discrete second tab that extends axially away from the first band,
- a second component arranged circumferentially about the central axis and located radially inward of the first component, the second component having a second band that extends at least partway circumferentially about the central axis,
- a first balance weight located between the first component and the second component and configured to balance a weight distribution of the rotor assembly, the first balance weight extending circumferentially partway about the central axis and formed to define a groove that receives the first tab of the first component to block movement of the first balance weight relative to the first component and the second component, wherein an outer surface of the first balance weight is configured to be machined as a sacrificial layer to allow for balance correction of the rotor assembly without machining the first component and the second component;
- and
- a second balance weight.
2 more elements
(canceled)
A method comprising:
- arranging a first component of a rotor assembly of a gas turbine engine circumferentially about a central axis, the first component having a first band that extends at least partway circumferentially about the central axis, a discrete first tab that extends away from the first band, and a discrete second tab that extends axially away from the first band,
- arranging a second component of the rotor assembly circumferentially about the central axis and radially inward of the first component, the second component having a second band that extends at least partway circumferentially about the central axis and a lip extending radially outward from the second band,
- determining a balance offset of the rotor assembly of the gas turbine engine,
- providing a first balance weight including a weight body and a second balance weight, and
- locating the first balance weight between the first component and the second component to balance a weight distribution of the rotor assembly, the first balance weight extending circumferentially partway about the central axis and formed to define a groove, the first balance weight located so that the groove defined in the first balance weight receives the first tab of the first component to block circumferential movement of the first balance weight relative to the first component and the second component, wherein an outer radial surface of the first balance weight is configured to be machined as a sacrificial layer to allow for balance correction of the rotor assembly without machining the first rotor and the second rotor.
2 more elements
Dependencies are inferred from the claim text.