Rotor assembly for a gas turbine engine
AssigneeGeneral Electric Company
InventorsMichal Tomasz Kuropatwa, Adam Wojciech Deskiewicz, Robert Kaminski, Adam Kunicki, Nicholas Joseph Kray
Life of this patent
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Abstract
A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.
Claims21
A rotor assembly comprising:
- a spool defining a plurality of apertures spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface;
- and
- a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade of the at least two blades extends through a common aperture of the plurality of apertures such that the platform defines a flow path surface of the rotor assembly, and wherein the blade assembly further comprises a pair of platform wings,
- wherein the platform has a radially outward surface that conforms to the radially inward-facing surface of the spool.
A rotor assembly comprising:
- a spool defining a plurality of apertures spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface;
- and
- a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade of the at least two blades extends through a common aperture of the plurality of apertures such that the platform defines a flow path surface of the rotor assembly, and wherein the blade assembly further comprises a pair of platform wings,
- wherein the blade assembly further comprises a retention device positioned in contact with the blade assembly such that the pair of platform wings are held in contact with the radially inward-facing surface.
A rotor assembly comprising:
- a spool defining a plurality of apertures spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface;
- and
- a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade of the at least two blades extends through a common aperture of the plurality of apertures such that the platform defines a flow path surface of the rotor assembly, and wherein the blade assembly further comprises a pair of platform wings,
- wherein the platform is disposed radially inward of the radially inward-facing surface of the spool and extends circumferentially from a first blade of the at least two blades to a second blade of the at least two blades.
Dependencies are inferred from the claim text.