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Turbine components are provided. In an embodiment, by way of example, a hub and a ring are included. The hub comprises a first material. The ring is bonded to the hub. The ring comprises a plurality of arc segments forming a ring, each arc segment comprising a second material comprising a single cry

Turbine components are provided. In an embodiment, by way of example, a hub and a ring are included. The hub comprises a first material. The ring is bonded to the hub. The ring comprises a plurality of arc segments forming a ring, each arc segment comprising a second material comprising a single crystal superalloy material having a predetermined primary orientation and a predetermined secondary orientation, each predetermined primary orientation of each arc segment being substantially equal, and each predetermined secondary orientation of each arc segment being substantially equal, each arc segment adjacent another arc segment, and the adjacent arc segments having a predetermined crystallographic mismatch therebetween. Methods of manufacturing are also provided.

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1. A method of manufacturing a turbine component, the method comprising the steps of: forming a plurality of arc segments, each arc segment comprising a single crystal material having a predetermined primary orientation and a predetermined secondary orientation, each predetermined primary orientatio

1. A method of manufacturing a turbine component, the method comprising the steps of: forming a plurality of arc segments, each arc segment comprising a single crystal material having a predetermined primary orientation and a predetermined secondary orientation, each predetermined primary orientation of each arc segment being substantially equal, and each predetermined secondary orientation of each arc segment being substantially equal;bonding the plurality of arc segments together into a ring such that each arc segment is adjacent another arc segment, the adjacent arc segments have a bond line therebetween, and the adjacent arc segments have a predetermined crystallographic mismatch therebetween;bonding the ring to a hub to form a disk; andmachining the disk to remove at least a portion of the bond line between adjacent arc segments to thereby form a slot in the disk to form the turbine component. 2. The method of claim 1, wherein the step of forming comprises growing each arc segment from a seed crystal. 3. The method of claim 2, wherein the seed crystal comprises a nickel-based superalloy. 4. The method of claim 1, wherein the step of bonding the plurality of arc segments comprises positioning the plurality of arc segments such that the predetermined crystallographic mismatch between adjacent arc segments is an angle between about 6 degrees and about 18 degrees. 5. The method of claim 1, wherein the plurality of arc segments comprises a first arc segment and a second arc segment and the step of bonding the plurality of arc segments comprises: depositing a transient liquid phase material on a bonding surface of the first arc segment and a bonding surface of the second arc segment;loading the plurality of arc segments into a thermal expansion tooling; andheating the plurality of arc segments to melt a melting point depressant in the transient liquid phase material and to thereby bond the plurality of arc segments together into the ring and to compress the plurality of arc segments. 6. The method of claim 1, wherein the plurality of arc segments comprises a first arc segment and a second arc segment and the step of bonding the plurality of arc segments comprises: depositing a transient liquid melting point depressant on a bonding surface of the first arc segment and a bonding surface of the second arc segment;loading the plurality of arc segments into tooling that places the bonding surfaces of the arc segments into compression; andheating adjacent arc segments to melt a melting point depressant in the transient liquid phase material and to thereby bond the plurality of arc segments together into the ring. 7. The method of claim 1, wherein the step of bonding the plurality of arc segments comprises: inserting a superalloy foil between the bonding surfaces of adjacent arc segments, the superalloy foil including a transient liquid phase material thereon;loading the plurality of arc segments into a thermal expansion tooling; andheating the plurality of arc segments to melt the transient liquid phase material to thereby bond and compress the plurality of arc segments together into a ring. 8. The method of claim 1, wherein the step of bonding the plurality of arc segments comprises: arranging the plurality of arc segments into an investment casting mold;preheating the investment casting mold and the plurality of arc segments to a temperature of about 1100° C.±100° C.; andcasting a molten bonding alloy into a gap between bonding surfaces of at least two adjacent arc segments of the plurality of arc segments. 9. The method of claim 1, wherein the step of bonding the plurality of arc segments comprises: arranging the plurality of arc segments into casting tooling;preheating at least two adjacent arc segments of the plurality of arc segments to a temperature of about 1100° C.±100° C.;casting a molten bonding alloy into a gap between a bonding surface of each arc segment of the at least two adjacent arc segments; andrepeating the preheating and casting steps until all arc segments are bonded into a ring. 10. The method of claim 1, wherein the step of bonding the ring to the hub comprises subjecting the ring and the hub to a hot isostatic pressing process. 11. The method of claim 1, further comprising inserting a turbine blade into the slot in the disk. 12. A method of manufacturing a turbine component, the method comprising the steps of: integrally casting a ring having a plurality of arc segments grown from a plurality of seed crystals, each arc segment comprising a single crystal material having a predetermined primary orientation and a predetermined secondary orientation, each predetermined primary orientation of each arc segment being substantially equal, and each predetermined secondary orientation of each arc segment being substantially equal, each arc segment adjacent another arc segment and having a bond line therebetween, and the adjacent arc segments having a predetermined crystallographic mismatch therebetween;bonding the ring to a hub to form a disk; andmachining the disk to remove at least a portion of the bond line between adjacent arc segments to thereby form a slot in the disk to form the turbine component. 13. The method of claim 12, wherein the step of integrally casting comprises forming each arc segment from at least one nickel-base superalloy seed crystal. 14. The method of claim 12, wherein the step of integrally casting comprises forming the arc segments from between about 24 and about 72 seed crystals. 15. The method of claim 12, wherein the step of bonding comprises subjecting the ring and the hub to a hot isostatic pressing process. 16. The method of claim 12, further comprising inserting a turbine blade into the slot of the disk. 17. A turbine component comprising: a hub comprising a first material;a ring bonded to the hub, the ring comprising a plurality of arc segments, each arc segment comprising a second material comprising a single crystal material having a predetermined primary orientation and a predetermined secondary orientation, each predetermined primary orientation of each arc segment being substantially equal, and each predetermined secondary orientation of each arc segment being substantially equal, each arc segment adjacent another arc segment, and the adjacent arc segments having a predetermined crystallographic mismatch therebetween, the ring having a plurality of slots therein; anda plurality of blades inserted into corresponding plurality of slots, each blade comprising a material having a predetermined primary orientation and a predetermined secondary orientation, each predetermined primary orientation of each blade being substantially equal, each predetermined secondary orientation of each blade being substantially equal, and each predetermined primary orientation and a predetermined secondary orientation of each blade being substantially equal to an adjacent arc segment. 18. The turbine component of claim 17, wherein the hub comprises an equiaxed superalloy material. 19. The turbine component of claim 17, wherein the ring comprises a nickel-based superalloy material.