A doped SiOC liquid starting material provides a p-type polymer derived ceramic SiC crystalline materials, including boules and wafers. P-type SiC electronic devices. Low resistivity SiC crystals, wafers and boules, having phosphorous as a dopant. Polymer derived ceramic doped SiC shaped charge source materials for vapor deposition growth of doped SiC crystals.

A doped SiOC liquid starting material provides a p-type polymer derived ceramic SiC crystalline materials, including boules and wafers. P-type SiC electronic devices. Low resistivity SiC crystals, wafers and boules, having phosphorous as a dopant. Polymer derived ceramic doped SiC shaped charge source materials for vapor deposition growth of doped SiC crystals.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof.

Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof.

Flow path assemblies and methods for forming such flow path assemblies for gas turbine engines are provided. For example, a flow path assembly for a gas turbine engine has a boundary structure, an airfoil, and a locking feature. The boundary structure and the airfoil are formed from a composite material. The boundary structure defines an opening and a cutout proximate the opening, and the airfoil is sized to fit within the opening of the boundary structure. The locking feature is received within the cutout defined by the boundary structure to interlock the airfoil with the boundary structure.

Flow path assemblies and methods for forming such flow path assemblies for gas turbine engines are provided. For example, a flow path assembly for a gas turbine engine has a boundary structure, an airfoil, and a locking feature. The boundary structure and the airfoil are formed from a composite material. The boundary structure defines an opening and a cutout proximate the opening, and the airfoil is sized to fit within the opening of the boundary structure. The locking feature is received within the cutout defined by the boundary structure to interlock the airfoil with the boundary structure.

A filter including a porous support defining one or more channels therethrough, and a porous ceramic membrane layer on a surface of the porous support defining at least one of the one or more channels. The ceramic membrane layer includes an inorganic ceramic composition having the formula SiM.sup.p.sub.xpC.sub.yN.sub.zO.sub.mH.sub.n, where each M.sup.p present is independently selected from a p-block element or a d-block element; p is an integer from 1 to 5; for each M.sup.p present, xp is independently from about 0 to about 60; y is from about 0 to about 60; z is from about 0 to about 60; m is from about 0 to about 40; and n is zero or nonzero. At least one of y and z is nonzero when p is zero, and p is nonzero when y and z are both zero.

A filter including a porous support defining one or more channels therethrough, and a porous ceramic membrane layer on a surface of the porous support defining at least one of the one or more channels. The ceramic membrane layer includes an inorganic ceramic composition having the formula SiM.sup.p.sub.xpC.sub.yN.sub.zO.sub.mH.sub.n, where each M.sup.p present is independently selected from a p-block element or a d-block element; p is an integer from 1 to 5; for each M.sup.p present, xp is independently from about 0 to about 60; y is from about 0 to about 60; z is from about 0 to about 60; m is from about 0 to about 40; and n is zero or nonzero. At least one of y and z is nonzero when p is zero, and p is nonzero when y and z are both zero.