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US 9,435,209 B2Granted
Turbomachine blade reinforcement
AssigneeGeneral Electric Company
InventorAndres Jose Garcia Crespo
Life of this patent
Estimating the term…
Abstract
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.
Claims17
A system, comprising:
- a turbomachine blade segment, comprising:
- 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, 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.
1 more element
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;
- and
- a 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.
1 more element
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;
- and
- disposing 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.
Dependencies are inferred from the claim text.