A turbine vane assembly adapted for use in a gas turbine engine includes a spar, a turbine vane, and load transfer pins. The spar comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly.

An article and a method of manufacturing the article is disclosed. The method includes providing the article including a substrate and a coating at least partially disposed on the substrate. The coating includes an outer surface. The coating further includes platinum and chromium. The method further includes applying cold work to the outer surface of the coating to produce a cold-worked layer extending from the outer surface of the coating to a cold work depth. The cold-worked layer includes approximately 45% cold work. The cold work depth is between about 30 microns to about 150 microns from the outer surface of the coating.

A method for manufacturing a composite part reinforced with nanotubes, includes stacking a plurality of composite plies of prepreg and at least one composite ply integrating nanotubes, the at least one composite ply integrating nanotubes being positioned in an inter-ply space between two composite plies of prepreg, wherein the at least one composite ply integrating nanotubes is a ply having a thermoplastic component, the nanotubes being integrated in the thermoplastic component.

A steam turbine according to the present invention comprises: a shaft which rotates about the rotation axis thereof; a plurality of moving blades which extend in the radial direction from the outer peripheral surface of the shaft and which are arranged along the circumferential direction; a casing main body which covers the shaft and the moving blades from the outer peripheral side; a plurality of stationary blades which are arranged on the inner circumferential surface of the casing main body; and a substance supply unit which supplies, to the surfaces of the moving blades and/or the surfaces of the stationary blades, a film forming substance that is hydrophobic, wherein the substance supply unit has a storage unit, a supply passage which is formed inside the casing and through which the film forming substance flows, and discharge units which are formed inside the moving blades and/or the stationary blades and which guide the film forming substance to the surfaces.

A steam turbine according to the present invention comprises: a shaft which rotates about the rotation axis thereof; a plurality of moving blades which extend in the radial direction from the outer peripheral surface of the shaft and which are arranged along the circumferential direction; a casing main body which covers the shaft and the moving blades from the outer peripheral side; a plurality of stationary blades which are arranged on the inner circumferential surface of the casing main body; and a substance supply unit which supplies, to the surfaces of the moving blades and/or the surfaces of the stationary blades, a film forming substance that is hydrophobic, wherein the substance supply unit has a storage unit, a supply passage which is formed inside the casing and through which the film forming substance flows, and discharge units which are formed inside the moving blades and/or the stationary blades and which guide the film forming substance to the surfaces.

An airfoil assembly includes first and second fiber-reinforced composite airfoil rings that each have inner and outer platform sections, a suction side wall extending between the inner and outer platforms, a pressure side wall extending between the inner and outer platforms, and suction and pressure side mate faces along, respectively, edges of the suction and pressure side walls. The suction side mate face of the first fiber-reinforced composite airfoil ring and the pressure side mate face of the second fiber-reinforced composite airfoil ring mate at an interface to form an airfoil that circumscribes an internal cavity. A least one of the suction or pressure side mate faces includes protrusions along a trailing edge of the airfoil. The protrusions define a toothed exit slot for emitting cooling air from the internal cavity.

A fan platform for gas turbine engine is provided. The fan platform incudes a body portion and a flow path surface coupled to the body portion. The body portion and the flow path surface define at least a portion of a flow path extending through the engine. The body portion and/or the flow path surface include an impact region including hybrid composite plies including one or more metallic tows. A gas turbine engine including the fan platform and methods for forming the fan platform are also disclosed.

Articles coated with a porous, segmented thermal barrier coating. The coating described has a density less than about 88% of the theoretical density. Multi-layer articles and methods of applying the thermal barrier coatings to an article are also described.

A gas turbine engine article includes a substrate and a silicate-resistant barrier coating disposed on the substrate. The silicate-resistant barrier coating is composed of a refractory matrix and a calcium aluminosilicate additive (CAS additive) dispersed in the refractory matrix.

A gas turbine engine component includes a ceramic matrix composite (CMC) body that includes an interior surface that defines a blind cavity. A barrier coating is disposed on an exterior of the CMC body. A ceramic body in the blind cavity lines at least a portion of the interior surface of the CMC body. The ceramic body defines an open, interconnected network of pores.