A ceramic matrix composite laminate comprises a ceramic matrix that encapsulates a plurality of layers. Each layer comprises fibers. Each layer comprises a plurality of fill fibers and a plurality of warp fibers or a plurality of bias fibers. The outermost layer contains a different concentration of fibers per unit volume than a layer located near an interior of the ceramic matrix composite laminate. A gradient in the number of fibers exists between the outermost layer and the layer located at the interior of the ceramic matrix composite laminate, or a combination thereof. A combined ceramic matrix composite comprises a plurality of composite laminates; wherein each laminate has a different fiber concentration gradient from another laminate that it is in contact with.

A preform comprising a first sub-laminate comprising a plurality of layers and a second sub-laminate comprising a plurality of layers. The first sub-laminate comprises a first unit cell comprising a first volume fraction of tows, where the first volume fraction of tows comprise first tows having a first tow spacing between successive first tows. The second sub-laminate comprises a second unit cell comprising a second volume fraction of tows, where the second volume fraction of tows comprise second tows having a second tow spacing between successive second tows. The first volume fraction of tows in the first unit cell is equal to the second volume fraction of tows in the second unit cell. The second tow spacing is less than the first tow spacing.

According to a method set forth herein a plurality of preform plies having first and second preform plies can be associated together to define a preform. The preform can be subject to chemical vapor infiltration (CVI) processing to define a ceramic matrix composite (CMC) structure.

A particulate matter measuring device component includes: a base portion formed of ceramics, the base portion being internally provided with a flow channel through which gas flows; a filter portion formed of porous ceramics, the filter portion being disposed within the flow channel so as to divide the flow channel into a plurality of portions; and a pair of electrodes for formation of electrostatic capacitance, disposed in the base portion so that the filter portion is sandwiched between the pair of electrodes, a wall surface of the flow channel of the base portion being denser than a surface of the filter portion.

Provided are a composite ceramic member and a method for preparation thereof, a vaporization assembly, and an electronic cigarette. The composite ceramic member comprises a first ceramic layer, a second ceramic layer, and a third ceramic layer stacked in sequence; in the first ceramic layer, the second ceramic layer, and the third ceramic layer, the first ceramic layer has the smallest pore size and the highest thermal conductivity, the second ceramic layer has the largest porosity, and the third ceramic layer has the highest compressive strength.

A gas inlet suitable in particular for use in an ion thruster includes a housing which is made of a gas-tight ceramics material, and an insert which is arranged in the housing and is made of a porous ceramics material. The geometry and pore structure of the insert are such that the insert forms a desired flow resistance for a gas stream flowing through the insert.

A method of forming a ceramic matrix composite includes preparing a plurality of fibrous ceramic plies by applying a binder solution loaded with ceramic particles to each of a first subset of plies, and applying the binder solution without ceramic particles to each of a second subset of plies. The method further includes arranging the plurality of plies to form a preform with a gradient along a thickness direction of the preform by stacking the first subset of plies to form a first zone of the preform, and stacking individual ones of the second subset of the plies on both sides of the first zone to form a second zone on each side of the first zone. Loading of the ceramic particles is higher in the first zone than in the second zones. The method further includes densifying the preform with a ceramic matrix.

In some examples, a method including depositing a resin and a plurality of carbon fibers via a print head of a three-dimensional printing system to form a carbon fiber preform including a plurality of individual carbon fiber layers, wherein each individual layer of the plurality of individual carbon fiber layers includes the resin and carbon fibers, and wherein the carbon fiber preform exhibits at least one of a non-uniform composition of the resin within the preform, different types of the carbon fibers within the preform, or non-uniform fiber orientation within the preform.

The present disclosure provides a composite heat-dissipation substrate and a method of manufacturing the same. The composite heat-dissipation substrate includes a first ceramic layer having insulating properties, a second porous ceramic layer and a metal layer, wherein the first ceramic layer and the second ceramic layer are continuously connected to each other so as not to form an interface therebetween, and the metal layer is infiltrated into plural pores of the second ceramic layer to be coupled to the ceramic layers, whereby interfacial coupling force between the ceramic layers and the metal layer is very high, thereby providing significantly improved heat dissipation characteristics.

Components for a gas turbine engine and method for producing the components are provided. The components may include a substrate and a thermal barrier coating (TBC) having at least a first layer secured to a surface of the substrate. The first layer is formed of a ceramic material with a first microstructure that includes a plurality of interconnected unit cells having struts that have a relative density of greater than 98 percent and a closed cell porosity of 10 percent or greater. The TBC is secured to the substrate subsequent to formation of the TBC.