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US 8,540,482 B2Granted
Rotor assembly for gas turbine engine
AssigneeUnited Technologies Corporation
InventorsEric W. Malmborg, Matthew E. Bintz
Life of this patent
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Abstract
A rotor assembly for a gas turbine engine includes a rotor airfoil and a first rotor disk. The rotor airfoil extends along a radial axis. The first rotor disk includes an outer rim, a bore and a web extending between the outer rim and the bore. The first rotor disk is axially offset from the radial axis of the rotor airfoil.
Claims19
A rotor assembly for a gas turbine engine, comprising:
- a bladed ring defining a radial axis and having a plurality of separate components that are spaced apart from one another;
- a rotor airfoil that extends from each of said plurality of separate components along said radial axis;
- a first rotor disk radially supporting said rotor airfoil and having an outer rim, a bore and a web extending between said outer rim and said bore, wherein said first rotor disk is axially offset from said radial axis of said rotor airfoil;
- and
- a second rotor disk radially supporting another rotor airfoil and having an outer rim, a bore and a web extending between said outer rim and said bore, wherein said second rotor disk is axially in-line with a radial axis of said another rotor airfoil.
2 more elements
A gas turbine engine, comprising:
- a section including alternating rows of rotating rotor airfoils and static stator vanes;
- wherein said section includes a first rotor assembly having a first rotor disk and a second rotor assembly having a second rotor disk, and each of said first rotor disk and said second rotor disk radially supporting a plurality of said rotor airfoils, wherein said first rotor disk is axially offset from a first radial axis of said plurality of rotor airfoils of said first rotor disk and said second rotor disk is axially in-line with a second radial axis of said plurality of rotor airfoils of said second rotor disk.
A method for providing a rotor assembly for a gas turbine engine, comprising the steps of:
- positioning a first rotor assembly such that a first rotor disk of the first rotor assembly is axially offset from a first radial axis of a first rotor airfoil of the first rotor assembly;
- and
- positioning a second rotor assembly such that a second rotor disk of the second rotor assembly is axially in-line with a second radial axis of a second rotor airfoil of the second rotor assembly, wherein the first rotor disk radially supports the first rotor airfoil and the second rotor disk radially supports the second rotor airfoil.
Dependencies are inferred from the claim text.