Rotor for turbo engines

Claim 1

A rotor for gas turbine machines wherein the turbine machines operate at high speeds and temperatures, the rotor comprising: a shaft having first and second ends; a turbine vane wheel consisting of cast, unmachined vanes formed integrally with the shaft by virtue of being cast therewith and projecting radially from the shaft adjacent the first end thereof; a compressor vane wheel consisting of cast, unmachined vanes formed integrally with the shaft by virtue of being cast therewith and projecting radially from the shaft at a location spaced from and inboard of the turbine vaned wheel; a sealing surface disposed between the vaned wheels, the sealing surface being integral with the shaft by virtue of being cast therewith and being machined to provide a smooth surface; a first bearing surface disposed adjacent to and inboard of the compressor vane wheel, the first bearing surface being integral with the shaft by virtue of being cast therewith and being machined to provide a smooth surface; a second bearing surface spaced from the first bearing surface, the second bearing surface being integral with the shaft by virtue of being cast therewith and being machined to provide a smooth surface; a helical thread adjacent to and outboard of the second bearing surface, the helical thread having a machined surface, and a spline positioned adjacent to the helical thread and at the second end of the shaft, the spline having a machined surface for receiving a gear; whereby, a unitary rotor made from a single unit of material is provided, which rotor is relatively inexpensive to manufacture and withstands high thermal stress and high mechanical stress.