An improved method for embedding one or more sensors in SiC is provided. The method includes depositing a binder onto successive layers of a SiC powder feedstock to produce a dimensionally stable green body have a true-sized cavity. A sensor component is then press-fit into the true-sized cavity. Alternatively, the green body is printed around the sensor component. The assembly (the green body and the sensor component) is heated within a chemical vapor infiltration (CVI) chamber for debinding, and a precursor gas is introduced for densifying the SiC matrix material. During infiltration, the sensor component becomes bonded to the densified SiC matrix, the sensor component being selected to be thermodynamically compatible with CVI byproducts at elevated temperatures, including temperatures in excess of 1000? C.

A method for manufacturing a turbomachine blade made of ceramic matrix composite component includes at least a structural part and a functional part secured to the structural part, the method including obtaining an assembly including a first preform of the functional part that is mounted on a second preform of the structural part or on the structural part, the first preform including a fibrous reinforcement of short fibres, and the second preform or the structural part comprising a woven fibrous reinforcement, and densification of the first preform of the assembly by infiltration with a molten composition.

The present invention relates to a method of printing a composite material (1), for example polymeric, carbonaceous, siliconic or metallic comprising steps of: i) providing a plurality of bundles (2) of reinforcement fibers (4), wherein the reinforcement fibers (4) have a length in the range 3-50 mm and are in the number of about 1,000-100,000 in each bundle (2); ii) aligning the bundles (2) along a predetermined path (X, X); iii) incorporating at least part of the bundles (2) into a matrix (6, 8), for example polymeric, carbonaceous, siliconic or metallic, preserving the alignment along said path (X, X); iv) laying and solidifying at least one layer (8) of the matrix (6, 8) of step iii) to make the composite material (1).

A ceramic matrix composite component and a ceramic insert, and a method for producing the same. The ceramic matrix composite component may include an exterior surface comprising silicon fibers in a silicon carbide matrix. The insert may include a continuous porosity bonded to the exterior surface of the ceramic matrix composite component. The silicon carbide matrix of the ceramic matrix composite component may extend into the porosity of the ceramic insert to bond the ceramic insert to the ceramic matrix composite component.

A process of producing a hot gas path turbine component. The process includes forming a void in a first ceramic matrix composite ply and forming a void in a second ceramic matrix composite ply. The second ceramic matrix composite ply is positioned on the first ceramic matrix composite ply such that the positioning aligns the voids to at least partially define a cavity in the component. A third ceramic matrix composite ply is positioned on the first ceramic matrix composite ply and the first ceramic matrix composite ply, the second ceramic matrix composite ply and the third ceramic matrix composite ply are densified to form a densified body. The cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.

A method of forming a ceramic matrix composite turbine blade with squealer tip and with tip flare is provided. The tip flare may be located at either or both of the pressure side and the suction side. The method provides a mandrel which is placed in the pre-form tooling to create the cavity and aid in formation of the pressure side flare.

Disclosed are an inorganic nanofiber characterized in that the average fiber diameter is 2 m or less, the average fiber length is 200 m or less, and the CV value of the fiber length is 0.7 or less; and a method of manufacturing the same. In the manufacturing method, an inorganic nanofiber sheet consisting of inorganic nanofibers having an average fiber diameter of 2 m or less is formed by electrospinning, and then, the inorganic nanofiber sheet is pressed using a press machine and crushed so that the average fiber length becomes 200 m or less, and the CV value of the fiber length becomes 0.7 or less.

Methods for forming ceramic matrix composite (CMC) components are provided. In one exemplary embodiment, a method comprises automatically laying up CMC plies. Laying up plies includes transferring a CMC ply to a layup tool; applying heat to the CMC ply; and stacking the CMC ply with at least one other CMC ply. In various embodiments, CMC plies may be laid up using an automated machine. In some embodiments, a CMC ply may be transferred to a layup tool using an automated machine and the CMC ply may be stacked with at least one other CMC ply using the automated machine.

An article includes a ceramic wall that defines at least a side of a passage. The ceramic wall includes a flow turbulator that projects into the passage. The flow turbulator is formed of ceramic matrix composite. A gas turbine engine is also disclosed. The gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. At least one of the turbine section or the compressor section including the article.

A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.