Thin-walled reinforcement lattice structure for hollow CMC buckets
A hollow ceramic matrix composite (CMC) turbine bucket with an internal reinforcement lattice structure has improved vibration properties and stiffness. The lattice structure is formed of thin-walled plies made of CMC. The wall structures are arranged and located according to high stress areas within the hollow bucket. After the melt infiltration process, the mandrels melt away, leaving the wall structure to become the internal lattice reinforcement structure of the bucket.
1. A mandrel assembly for manufacturing a CMC turbine blade, the mandrel assembly comprising:
a tip section including a pressure side and a suction side;
a root section including a pressure side and a suction side; and
a plurality of ceramic matrix composite (CMC) plies laid up from one side to the other across a cross section of the mandrel assembly and interposed between the tip section and the root section, the plurality of CMC plies defining reinforcement lattice structure within the CMC turbine blade,
wherein the tip section comprises a leading edge part connected to a trailing edge part, and wherein the root section comprises a leading edge part connected to a trailing edge part,
wherein one of the leading edge part of the tip section and the leading edge part of the root section comprises a connector on an end facing the other of the leading edge part of the tip section and the leading edge part of the root section, and wherein the other of the leading edge part of the tip section and the leading edge part of the root section comprises a connector receiver on an end facing the one of the leading edge part of the tip section and the leading edge part of the root section, and
wherein one of the trailing edge part of the tip section and the trailing edge part of the root section comprises a connector on an end facing the other of the trailing edge part of the tip section and the trailing edge part of the root section, and wherein the other of the trailing edge part of the tip section and the trailing edge part of the root section comprises a connector receiver on an end facing the one of the trailing edge part of the tip section and the trailing edge part of the root section,
the plurality of CMC plies each including an alignment opening through which respective ones of the connectors are disposed in engagement with the connector receivers.
2. A mandrel assembly according to claim 1 , wherein each of the leading edge parts and the trailing edge parts includes a perimeter wall that defines a cavity.
3. A mandrel assembly according to claim 1 , comprising a plurality of the CMC plies laid up between both (1) the leading edge parts of the tip section and the root section and (2) the trailing edge parts of the tip section and the root section.
4. A mandrel assembly according to claim 3 , wherein each of the CMC plies is shaped corresponding to a cross-section of the respective parts of the tip section and the root section between which the CMC plies are disposed.
5. A mandrel assembly according to claim 1 , further comprising a middle section including a pressure side and a suction side, the middle section being interposed between the tip section and the root section.
6. A mandrel assembly for manufacturing a CMC turbine blade, the mandrel assembly comprising:
a tip section including a pressure side and a suction side;
a root section including a pressure side and a suction side; and
a plurality of ceramic matrix composite (CMC) plies laid up from one side to the other across a cross section of the mandrel assembly and interposed between the tip section and the root section, the plurality of CMC plies defining reinforcement lattice structure within the CMC turbine blade,
wherein one of the tip section and the root section comprises a connector on an end facing the other of the tip section and the root section, and wherein the other of the tip section and the root section comprises a connector receiver on an end facing the one of the tip section and the root section, the plurality of CMC plies including an alignment opening through which the connector is disposed in engagement with the connector receiver.
7. A mandrel assembly for manufacturing a CMC turbine blade, the mandrel assembly comprising:
a tip section including a pressure side and a suction side:
a root section including a pressure &de and a suction side: and
a plurality of ceramic matrix composite (CMC) plies laid up from one side to the other
across a cross section of the mandrel assembly and interposed between the tip section and the root section, the plurality of CMC plies defining reinforcement lattice structure within the CMC turbine blade,
wherein the tip section and the root section each comprises multiple parts that interlock with each other using a plurality of alignment tabs and a plurality of tab receivers, and wherein the CMC plies comprise a plurality of alignment openings through which the plurality of alignment tabs are disposed.
8. A method of constructing a turbine bucket, the method comprising:
(a) assembling a mandrel including a tip section with a pressure side and a suction side, a root section with a pressure side and a suction side, and a plurality of ceramic matrix composite (CMC) plies laid up from one side to the other across a cross section of the mandrel and interposed between the tip section and the root section;
(b) wrapping the mandrel with CMC layers on the pressure side and the suction side, and securing the pressure side to the suction side; and
(c) removing the mandrel such that the plurality of CMC plies define cross-sectional reinforcement lattice structure within the turbine bucket,
wherein step (a) is practiced by connecting the tip section of the mandrel with the root section of the mandrel via a tab and slot, and by securing the CMC plies using an alignment opening in the CMC plies with the tab extending through the alignment opening.
9. A method according to claim 8 , wherein step (c) is practiced by melting the mandrel through the alignment opening.
10. A method according to claim 8 , wherein step (b) is practiced by forming the CMC layers into an airfoil shape.
11. A method according to claim 8 , wherein step (a) is practiced such that the CMC plies are positioned according to high stress areas of the bucket.
12. A method according to claim 8 , wherein the tip section and the root section of the mandrel include internal cavities, and wherein step (b) is practiced such that the turbine bucket includes hollow cavities separated by internal walls reinforced with the CMC plies.