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US 2011/0299992 A1Published application
Rotor assembly for gas turbine engine
AssigneeUnited Technologies Corporation
InventorsEric W. Malmborg, Matthew E. Bintz
Life of this patent
Estimating the term…
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.
Claims20
A rotor assembly for a gas turbine engine, comprising:
- a rotor airfoil that extends along a radial axis;
- and
- a first rotor disk 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.
A gas turbine engine, comprising:
- a section including alternating rows of rotating rotor airfoils and static stator vanes;
- wherein said section includes a rotor assembly having a first rotor disk and a second rotor disk, and each of said first rotor disk and said second rotor disk includes a plurality of said rotor airfoils, wherein each of said rotor airfoils are integrally formed with a bladed ring that is radially trapped between said first rotor disk and said second rotor disk.
A method for providing a rotor assembly for a gas turbine engine, comprising the steps of:
- positioning a rotor disk of the rotor assembly at a position that is axially offset from a radial axis of a rotor airfoil of the rotor assembly.
Dependencies are inferred from the claim text.