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A hybrid component (30) having a cast single crystal superalloy portion (32) and an attached powder metallurgy material portion (34). The component may be a blade (30) of a gas turbine engine having a single crystal airfoil section and a powder metallurgy material root section. The powder metallurgy

A hybrid component (30) having a cast single crystal superalloy portion (32) and an attached powder metallurgy material portion (34). The component may be a blade (30) of a gas turbine engine having a single crystal airfoil section and a powder metallurgy material root section. The powder metallurgy material may extend to form a core (36) within the airfoil section and may include cooling passages 38. The single crystal portion has a relatively simple geometry so that casting yields are optimized. The powder metallurgical portion includes the lower stressed and more complicated geometry sections of the component. A method of forming such a component includes casting the single crystal superalloy portion, then using that portion to form part of the mold for forming the powder metallurgy material portion.

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1. A hybrid blade for the hot gas pathway portion of a gas turbine engine, the hybrid blade comprising: a cast single crystal superalloy portion comprising an outer surface defining an airfoil and an inner surface defining a cavity; and a superalloy powder metallurgy material portion comprising

1. A hybrid blade for the hot gas pathway portion of a gas turbine engine, the hybrid blade comprising: a cast single crystal superalloy portion comprising an outer surface defining an airfoil and an inner surface defining a cavity; and a superalloy powder metallurgy material portion comprising a core disposed within the cavity and a root extending beyond the cavity, the superalloy powder metallurgy material portion being metallurgically bonded to the cast single crystal superalloy portion along the inner surface. 2. The hybrid blade of claim 1, further comprising a cooling passage formed through the superalloy powder metallurgy material portion. 3. The hybrid blade of claim 1, further comprising a fugitive insert disposed within the superalloy powder metallurgy material portion. 4. A method of fabricating a hybrid component, the method comprising: forming a first portion comprising a cast single crystal material; and using the first portion as at least part of a mold for forming a second portion comprising a powder metallurgy material, the powder metallurgy material becoming bonded to the cast single crystal material during densification of the powder metallurgy material. 5. The method of claim 4, further comprising: casting the first portion to comprise an airfoil having a hollow center; and using the airfoil as a mold for at least partially containing powder during the step of forming a second portion. 6. The method of claim 4, further comprising: applying a melting point suppressant material to a bond surface of the first portion; and forming a metallurgical bond between the first portion and the second portion along the bond surface. 7. The method of claim 4, further comprising forming the second portion to comprise a relatively complex shape compared to the first portion. 8. The method of claim 4, further comprising forming the second portion in a section of the component subjected to a lower level of stress than the first portion during use of the component. 9. The method of claim 4, further comprising forming the first portion of a cast single crystal superalloy material. 10. The method of claim 4, further comprising forming the first portion to comprise an airfoil section and forming the second portion to comprise a root section attached to the airfoil section. 11. The method of claim 4, further comprising forming the second portion to comprise a core for the airfoil section. 12. The method of claim 4, further comprising forming a cooling passage in the second portion. 13. The method of claim 4, further comprising forming the first portion to comprise an airfoil section and forming the second portion to comprise a shroud attached to the airfoil section. 14. The method of claim 4, further comprising forming the first portion of a cast single crystal superalloy material comprising at least 3 wt. % rhenium. 15. The method of claim 4, further comprising forming the second portion to comprise a first composition of powder in a first section of the second portion and a second composition of powder in a second section of the second portion. 16. The method of claim 4, further comprising selecting the first portion to include a surface exposed to a first peak temperature during use of the component and selecting the second portion to include a surface exposed to a second peak temperature during use of the component, the first peak temperature being higher than the second peak temperature. 17. The method of claim 4, further comprising: disposing a ceramic insert within a powder used to form the second portion during the step of forming the second portion; and dissolving the ceramic insert to define a cooling passage through the second portion. 18. The method of claim 4, further comprising densifying the powder metallurgy material at a temperature below a gamma prime solvus temperature of the cast single crystal material.