초록

Embodiments of the present disclosure include a system having a turbomachine blade segment including a blade and a mounting segment coupled to the blade, wherein the mounting segment has a plurality of reinforcement pins laterally extending at least partially through a neck of the mounting segment.

대표청구항 ▼

1. A system, comprising: a turbomachine blade segment, comprising: a blade; anda mounting segment coupled to the blade, wherein the mounting segment has a plurality of reinforcement pins laterally extending at least partially through a neck of the mounting segment, wherein the neck of the mounting s

1. A system, comprising: a turbomachine blade segment, comprising: a blade; anda mounting segment coupled to the blade, wherein the mounting segment has a plurality of reinforcement pins laterally extending at least partially through a neck of the mounting segment, wherein the neck of the mounting segment comprises a portion of the mounting segment that has a smallest thickness of the mounting segment, wherein the smallest thickness extends from a pressure side of the blade to a suction side of the mounting segment, wherein at least one of the plurality of pins extends laterally through the smallest thickness of the mounting segment, and wherein none of the plurality of reinforcement pins extends through an outer surface of the mounting segment. 2. The system of claim 1, wherein the turbomachine blade segment is formed from a plurality of laminated layers. 3. The system of claim 2, wherein each of the plurality of laminated layers comprises a composite material, wherein the composite material comprises a first plurality of ceramic fibers distributed throughout a ceramic matrix material, and wherein each of the first plurality of ceramic fibers extends along a length of the respective laminated layer. 4. The system of claim 3, wherein the plurality of reinforcement pins comprises a second plurality of ceramic fibers. 5. The system of claim 2, wherein each of the plurality of reinforcement pins extends through two or more of the plurality of laminated layers. 6. The system of claim 1, wherein the plurality of reinforcement pins has a staggered arrangement. 7. The system of claim 6, wherein each of the plurality of reinforcement pins at least partially overlaps with adjacent reinforcement pins. 8. The system of claim 1, comprising a turbomachine having a rotor, wherein the turbomachine blade segment is coupled to the rotor via the mounting segment. 9. The system of claim 8, wherein the turbomachine comprises a turbine. 10. A system, comprising: a turbomachine blade mounting segment, comprising: a plurality of layers laminated to one another to form a first portion of a dovetail joint; anda plurality of reinforcement pins, wherein each of the plurality of reinforcement pins extends crosswise through at least two of the plurality of layers within a shank region of the turbomachine blade mounting segment, wherein the shank region of the turbomachine blade mounting segment comprises a portion of the turbomachine blade mounting segment having a smallest thickness extending between a suction side and a pressure side of the turbomachine blade mounting segment, at least one of the plurality of reinforcement pins extends crosswise through the smallest thickness, and none of the plurality of reinforcement pins extends through an outer layer of the plurality of layers. 11. The system of claim 10, wherein each of the plurality of layers comprises a plurality of ceramic fibers embedded within a ceramic matrix material, and each of the plurality of ceramic fibers extends along a length of the respective layer. 12. The system of claim 10, wherein each of the plurality of reinforcement pins comprises a ceramic fiber. 13. The system of claim 10, wherein the plurality of reinforcement pins are staggered, overlapping, crisscrossing, or a combination thereof. 14. The system of claim 10, comprising a turbomachine having a rotor with a second dovetail portion of the dovetail joint, and the turbomachine blade mounting segment is coupled to the rotor with the first and second dovetail portions mated together to define a dovetail joint. 15. A method, comprising: laminating a plurality of layers to form a turbomachine blade mounting segment of a turbomachine blade, wherein each of the plurality of layers comprises a plurality of ceramic fibers distributed within a ceramic matrix material; anddisposing a plurality of reinforcement pins within a neck region of the turbomachine blade mounting segment, wherein the neck region comprises a region of the turbomachine blade mounting segment having a smallest thickness extending from a pressure side to a suction side of the turbomachine blade mounting segment, each of the plurality of reinforcement pins extends crosswise through at least two of the plurality of layers, at least one of the plurality of reinforcement pins extends through the smallest thickness, and none of the plurality of reinforcement pins extends through outer layers of the plurality of layers. 16. The method of claim 15, comprising arranging the plurality of reinforcement pins in a staggered pattern, an overlapping pattern, a crisscrossing pattern, or a combination thereof. 17. The system of claim 15, wherein each of the plurality of reinforcement pins comprises a ceramic fiber.