Hybrid gas turbine rotor

Claim 1

In a hybrid turbine rotor for a gas turbine engine, the combination comprising, a ceramic turbine wheel portion having a plurality of turbine blades therearound, a hollow ceramic stub shaft integral with said ceramic turbine wheel portion having a first coefficient of thermal expansion and a frustoconical outer surface with a predetermined taper angle and defining in cross section an annulus of predetermined area, said stub shaft being perpendicular to the plane of said turbine wheel portion with said frustoconical outer surface tapering axially away from said turbine wheel portion so that heat flow between said stub shaft and said turbine wheel portion is only through said annulus of predetermined area, an alloy metal shaft portion, and an alloy metal tubular end welded to said alloy metal shaft portion having a second coefficient of thermal expansion exceeding said first coefficient of thermal expansion and a frustoconical inner surface axially tapering toward said shaft at a taper angle corresponding to said outer surface taper angle, said tubular end being shrunk fit over said stub shaft on the opposite side of said annulus of predetermined area from said turbine wheel portion and with predetermined diametral interference between said outer and said inner surfaces at all operating temperatures of said hybrid rotor whereby torque transfer between said stub shaft and said tubular end occurs only at the shrunk fit interface between said outer and said inner surfaces and whereby all heat flow between said alloy metal shaft portion and said turbine wheel portion is through said annulus of predetermined area.