A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of disk mounts. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is mounted to the first rotor disk and to the second rotor disk. The rotor blades include a first rotor blade. Each of the disk mounts connects the first rotor disk and the second rotor disk together. The disk mounts include a first disk mount that further supports the first rotor blade.

A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of vanes. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The vanes are arranged circumferentially around the rotational axis. The vanes include a first vane that is integral with the first rotor disk and projects axially to the second rotor disk.

A ceramic structural body includes a substrate that is composed of a ceramic(s), a hole that is opened on a surface of the substrate, and a seal material that is positioned at an opening portion of the hole.

A method of forming a composite component. The method includes laying up a plurality of composite plies to form a composite ply core. Another step of the method includes partially processing the composite ply core to form a green state core. The method further includes machining a cooling cavity on an exterior surface of the green state core. Additionally, the method includes inserting a filler material within the cooling cavity. A further step includes wrapping composite plies around the green state core and filler material to secure the filler material and form an outer enclosure. In one step, the method includes processing the green state core and outer enclosure to form the composite component.

A method of producing a ceramic matrix composite component. The method includes positioning a first plurality of ceramic matrix composite plies on top of one another, disposing a filler pack on the first plurality of ceramic matrix composite plies, and positioning a second plurality of ceramic matrix composite plies on top of the filler pack. One of the first plurality of ceramic composite plies or the second plurality of ceramic composite plies includes a bend angle, to define an interstice between the plurality of ceramic matrix composite plies with the filler pack disposed in the interstice. The filler pack includes one or more sacrificial fibers disposed therein, that subsequent to removal provide a functional feature, such as a cooling manifold in the filler pack. The method further includes forming one or more channels coupled to the one or more functional features for the flow of a cooling fluid therethrough. A ceramic matrix composite is also disclosed.

An apparatus contains at least one pressure-rated apparatus shell and at least one modular framework system containing ceramic fiber composite materials and arranged within the apparatus shell. A modular lining apparatus includes the modular framework system and. refractory bricks. The apparatus can be used for high-temperature reactors, especially electrically heated high-temperature reactors.

A lattice structure includes multiple identical unit cells formed from joined plates. In the lattice structure, some of the plates are rectangular plates, some of the plates are triangular plates, and some of the plates are trapezoidal plates. Further, any two of the joined rectangular plates have corresponding surface normals perpendicular to each other and at least two edges of each one of the triangular plates are joined to one of a surface or an edge of one of the plurality of joined plates. Further, at least three edges of each one of the trapezoidal plates are joined to one of a surface or an edge of one of the plurality of joined plates, and any one of a plurality of surface normals for the triangular plates and the trapezoidal plates are nonparallel to any one of a plurality of surface normals of rectangular plates.

Methods of forming ceramic matrix composite structures include joining at least two lamina together to form a flexible ceramic matrix composite structure. Ceramic matrix composite structures include at least one region of reduced inter-laminar bonding at a selected location between lamina thereof. Thermal protection systems include at least one seal comprising a ceramic matrix composite material and have at least one region of reduced inter-laminar bonding at a selected location between lamina used to form the seal. Methods of forming thermal protection systems include providing one or more such seals between adjacent panels of a thermal protection system.

A crucible includes an outer element and an inner element. The outer element includes a first portion that is horizontal at a bottom end of the crucible and a second portion that ascends radially outwardly from the bottom end of the crucible to a top end of the crucible at a first acute angle to a vertical axis. The inner element includes a conus with a cylinder at a base of the conus. The conus descends radially outwardly from the top end of the crucible to the bottom end of the crucible at a second acute angle to the vertical axis. The inner element includes a base portion of the cylinder attached to the first portion of the outer element using a sealant to form a hollow mold between an inner portion of the outer element and an outer portion of the inner element.

Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine and an airfoil having a root and a tip. The root is coupled to the rotary structure and has a bulbous shape. The airfoil is formed from a plurality of composite plies, a portion of which defines at the root first and second end surfaces, which are in contact with the rotary structure and together define a chisel-shaped end of the root. In another embodiment, a rotor assembly comprises an outer rotor extending circumferentially about an axial centerline of a gas turbine engine and a composite outer rotor blade having a root and a tip. The blade root is coupled to the outer rotor and extends inward along a radial direction toward the axial centerline.