A combustion assembly for a gas turbine engine may be provided. The combustion assembly may include a ceramic matrix composite combustor shell, which may include a chamber defined by a wall of the ceramic matrix composite combustor shell, and the ceramic matrix composite combustor shell may include a ceramic matrix composite chute integral with the ceramic matrix composite combustor shell. The ceramic matrix composite chute may extend towards a midline of the chamber. A method for fabricating a ceramic matrix composite chute may be provided. At least one chute may be woven in three dimensions into a ceramic preform. A layup tool may be inserted into the chute. The chute may be enlarged with the layup tool. The ceramic preform may be formed into a ceramic matrix composite body, which includes a combustor shell and the chute.

A porous ceramic particle (16) has a pair of main surfaces (161, 162) in parallel with each other. An average porosity in a range (633) extending from one main surface (161) toward the other main surface (162) and having a thickness which is one fourth of a particle thickness that is a distance between the main surfaces is higher than that in a range (632) which is positioned in the center between the pair of main surfaces and has a thickness which is half of the particle thickness. The upper main surface (161) is a surface to be placed on an object. By limiting an area having a high porosity to the vicinity of the one main surface (161), it is possible to cause the porous ceramic particle (16) to have low thermal conductivity and low heat capacity and suppress a decrease in the mechanical strength.

A shape-stable structure that is configured to provide ablative cooling. The structure is used to form a component that includes shape-stable bulk structure and an ablative material. The bulk structure is infiltrated with the ablative material so that the ablative material is disposed in pathways defined by the bulk structure.

Provided herein are methods for making a freeze-cast material having a internal structure, the methods comprising steps of: determining the internal structure of the material, the internal structure having a plurality of pores, wherein: each of the plurality of pores has directionality; and the step of determining comprises: selecting a temperature gradient and a freezing front velocity to obtain the determined internal structure based on the selected temperature gradient and the selected freezing front velocity; directionally freezing a liquid formulation to form a frozen solid, the step of directionally freezing comprising: controlling the temperature gradient and the freezing front velocity to match the selected temperature gradient and the selected freezing front velocity during directionally freezing; wherein the liquid formulation comprises at least one solvent and at least one dispersed species; and subliming the at least one solvent out of the frozen solid to form the material.

An arrangement for producing a bulk material consisting substantially of foamed or blown mineral or oxide particles by thermal treatment of a bulk material of basic particles. The arrangement includes NIR halogen radiators for generating a NIR radiation field of radiation with an active component in a near infrared, NIR, range having a wavelength in a range between 0.8 m and 1.5 m and which has a power density of at least 50 kW/m.sup.2 for thermally treating the basic particles, a conveying device for transporting a layer or stream of the bed of basic particles through the radiation field, and a controller that controls heating of the bed of basic particles such that a maximum temperature in the layer or stream is in a temperature range between 600 and 1500 C.

An arrangement for producing a bulk material consisting substantially of foamed or blown mineral or oxide particles by thermal treatment of a bulk material of basic particles. The arrangement includes NIR halogen radiators for generating a NIR radiation field of radiation with an active component in a near infrared, NIR, range having a wavelength in a range between 0.8 ?m and 1.5 ?m and which has a power density of at least 50 kW/m.sup.2 for thermally treating the basic particles, a conveying device for transporting a layer or stream of the bed of basic particles through the radiation field, and a controller that controls heating of the bed of basic particles such that a maximum temperature in the layer or stream is in a temperature range between 600 and 1500? C.

Disclosed are a ceramic nanoparticle-carbon allotrope composite having a pore structure, and a method of manufacturing the same. According to an embodiment of the present invention, by modifying the surface of ceramic nanoparticles using a polymer containing a polar functional group, a porous-structured ceramic nanoparticle-carbon allotrope composite in which the particles are evenly distributed in a carbon allotrope can be provided.

Provided herein are methods for making a freeze-cast material having a internal structure, the methods comprising steps of: determining the internal structure of the material, the internal structure having a plurality of pores, wherein: each of the plurality of pores has directionality; and the step of determining comprises: selecting a temperature gradient and a freezing front velocity to obtain the determined internal structure based on the selected temperature gradient and the selected freezing front velocity; directionally freezing a liquid formulation to form a frozen solid, the step of directionally freezing comprising: controlling the temperature gradient and the freezing front velocity to match the selected temperature gradient and the selected freezing front velocity during directionally freezing; wherein the liquid formulation comprises at least one solvent and at least one dispersed species; and subliming the at least one solvent out of the frozen solid to form the material.

A combustion assembly for a gas turbine engine may be provided. The combustion assembly may include a ceramic matrix composite combustor shell, which may include a chamber defined by a wall of the ceramic matrix composite combustor shell, and the ceramic matrix composite combustor shell may include a ceramic matrix composite chute integral with the ceramic matrix composite combustor shell. The ceramic matrix composite chute may extend towards a midline of the chamber. A method for fabricating a ceramic matrix composite chute may be provided. At least one chute may be woven in three dimensions into a ceramic preform. A layup tool may be inserted into the chute. The chute may be enlarged with the layup tool. The ceramic preform may be formed into a ceramic matrix composite body, which includes a combustor shell and the chute.

A method for densifying porous annular substrates having a central passage by chemical vapor infiltration, the method including providing stacks of porous annular substrates, providing a plurality of individual modules including stacks disposed on a support plate having a perforated injection tube each mounted on a gas inlet opening, forming a stack of individual modules, aligning the individual modules of the stack in a sealed manner by means of an annular seal disposed between the injection tubes of a second individual module and the gas inlet openings of a first individual module with which it cooperates, and injecting into the internal volume of each stack of porous annular substrates a gas phase including a gaseous precursor of a matrix material to be deposited within the porosities of the substrates.