The present disclosure relates to a method of fabricating a ceramic composite components. The method may include providing at least a first layer of reinforcing fiber material which may be a pre-impregnated fiber. An additively manufactured component may be provided on or near the first layer. A second layer of reinforcing fiber, which may be a pre-impregnated fiber may be formed on top the additively manufactured component. A precursor is densified to consolidates at least the first and second layer into a densified composite, wherein the additively manufactured material defines at least one cooling passage in the densified composite component.

Provided is a tubular body containing SiC fibers having high thermal conductivity. The tubular body containing SiC fibers includes a SiC fiber layer wound in a tubular form, an inner SiC coating layer covering an inner surface of the SiC fiber layer, and an outer SiC coating layer covering an outer surface of the SiC fiber layer. The inner and outer SiC coating layers are bound to each other in gaps provided in the SiC fiber layer.

A method of forming one or more high temperature co-fired ceramic articles, comprising the steps of:— a) forming a plurality of green compacts, by a process comprising dry pressing a powder comprising ceramic and organic binder to form a green compact; b) disposing a conductor or conductor precursor to at least one surface of at least one of the plurality of green compacts to form at least one patterned green compact; c) assembling the at least one patterned green compact with one or more of the plurality of green compacts or patterned green compacts or both to form a laminated assembly; d) isostatically pressing the laminated assembly to form a pressed laminated assembly; e) firing the pressed laminated assembly at a temperature sufficient to sinter the ceramic layers together.

The disclosure relates to microchemical (or microfluidic) apparatus as well as related methods for making the same. The methods generally include partial sintering of sintering powder (e.g., binderless or otherwise free-flowing sintering powder) that encloses a fugitive phase material having a shape corresponding to a desired cavity structure in the formed apparatus. Partial sintering removes the fugitive phase and produces a porous compact, which can then be machined if desired and then further fully sintered to form the final apparatus. The process can produce apparatus with small, controllable cavities shaped as desired for various microchemical or microfluidic unit operations, with a generally smooth interior cavity finish, and with materials (e.g., ceramics) able to withstand harsh environments for such unit operations.

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 ceramic matrix composite turbine nozzle includes a primary outer nozzle platform; a primary inner nozzle platform; and an airfoil-shaped body extending between the primary inner and primary outer nozzle platforms. The body includes core plies defining a cavity; composite wrap plies circumscribing the core plies and defining an airfoil shape; a secondary outer nozzle platform in contact with the primary outer nozzle platform; and a secondary inner nozzle platform in contact with the primary inner nozzle platform. Each composite wrap ply has two layers of unidirectional fibers oriented transverse to each other and has first and second longitudinal edges. The first and second longitudinal edges are cut into fingers, which are folded in a transverse direction away from a turbine nozzle longitudinal axis and are interleaved between platform plies to define the secondary inner nozzle platform and the secondary outer nozzle platform.

A method for producing, by a metal powder injection moulding (MIM) technique, a part formed of at least one metal and/or at least one metal alloy including at least one internal cavity. A green core of a mixture of at least one powder of at least one ceramic and of a thermoplastic binder is used.

Moulded insulation bodies, processes for the production thereof and use thereof consisting essentially of ceramic material comprising SiO.sub.2 fibers and Al.sub.2O.sub.3 fibers which has been produced using Al.sub.2O.sub.3 sol as a binder and kilned at a temperature of above 800° C. for insulation of the ends of cracking tubes of a tubular reactor for performing a steam reforming process for generating synthesis gas which project out of the reactor heating space.

A method for forming a hole within a ceramic matrix composite component includes forming a first core portion for a ceramic matrix composite component; embedding a hollow member into the first core portion at a desired location; wrapping the first core portion with a first ceramic matrix composite material; inserting a rod through the hollow member and into the first core portion; removing the hollow member; assembling a second core portion to the first core portion such that the rod extends into the second core portion; and wrapping the first core portion and the second core portion with a second ceramic matrix composite material.

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.