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US 2006/0130456 A1Published application
Turbine engine rotor stack
AssigneeUnited Technologies Corporation
InventorsGabriel Suciu, James Norris
Life of this patent
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Abstract
A turbine engine has a first disk and a second disk, each extending radially from an inner aperture to an outer periphery. A coupling, transmits a torque and a longitudinal compressive force between the first and second disks. The coupling has first means for transmitting a majority of the torque and a majority of the force and second means, radially outboard of the first means, for vibration stabilizing.
Claims20
A turbine engine comprising:
- a first disk and a second disk, each extending radially from an inner aperture to an outer periphery;
- and
- a coupling, transmitting a torque and a longitudinal compressive force between the first and second disks and comprising:
- first means for transmitting a majority of the torque and a majority of the force;
- and
- second means, radially outboard of the first means for vibration stabilizing of the first and second disks.
3 more elements
A gas turbine engine comprising:
- a central shaft;
- a plurality of blade disks, the disks each having a central aperture surrounding the shaft, and the disks defining annular cavities between adjacent pairs of the disks;
- a plurality of vane stages interspersed with the blade disks;
- a radial spline torque coupling between a first and a second of said disks;
- and
- a spacer having:
- a longitudinally cross-sectional profile having an outward concavity effective to provide an increase in a longitudinal force across the spacer with an increase in rotational speed of the first and second disks;
- and
- at least one radially outwardly extending sealing element for sealing with one of the vane stages.
6 more elements
A turbine engine rotor comprising:
- a plurality of disks, each disk extending radially from an inner aperture to an outer periphery;
- a plurality of stages of blades, each stage borne by an associated one of said disks;
- a plurality of stages of vanes interspersed with said stages of blades;
- a plurality of spacers, each spacer between an adjacent pair of said disks;
- and
- a central shaft carrying the plurality of disks and the plurality of spacers to rotate about an axis with the plurality of disks and the plurality of spacers, wherein:
- a first of the spacers between a first and a second of the disks has first means for sealing with second means of an adjacent one of said stages of vanes;
- and
- interfitting first and second portions of said first and second disks radially inboard of said first spacer transmit longitudinal force and torque between the first and second disks.
6 more elements
Dependencies are inferred from the claim text.