1282 results about "Ceramic matrix composite" patented technology

The invention discloses an intelligent segmentation method and device for ceramic matrix composite CT image defects, and belongs to the technical field of image detection. The method comprises the following steps: inputting preprocessed CT image data into a preset double-branch collaborative segmentation model, and respectively outputting to obtain a local texture feature map and a global relation feature map; performing three-branch material perception fusion processing on the local texture feature map and the global relation feature map according to a preset perception fusion model to obtain a fusion feature map containing local detail accuracy and global consistency; sequentially carrying out progressive decoding and refined reconstruction processing on the fused feature graph to obtain a defect probability graph; and calculating a loss function of the defect probability graph and a manually pre-labeled real defect segmentation graph, and dynamically adjusting the loss weight of the initial model according to a calculation result to obtain a CT image defect segmentation model meeting a preset convergence condition. The method can meet the detection requirements of industrial scenes on the defects of the ceramic-based composite material.

The invention belongs to the field of aero-engines, relates to an engine main combustion chamber design technology, and provides a ceramic matrix composite material flame tube matching design method and system.The method comprises the steps that a flame tube wall temperature interval of a main working state point is obtained; determining the thermal-state radial dimensions of the feature points on the ceramic-based component and the metal component; converting the hot-state radial size into a cold-state radial size; carrying out two-dimensional cold-state flame tube profile design; and the cold-state radial size of the two-dimensional cold-state flame tube molded surface is converted into the hot-state size to obtain a two-dimensional hot-state flame tube molded surface, and a three-dimensional hot-state model is constructed and evaluated and iteratively optimized. According to the method, matching structure characteristic parameters of the ceramic-based component and the metal component are designed, and the molded surface of the flame tube made of the different materials is self-adaptively formed into smooth transition at main working state points, so that a backflow area is actively controlled, and the problems that the stability of a flow field of a main combustion chamber is influenced and pressure is lost due to different and relative displacement changes in the working process are solved.

The invention provides a high-bearing-capacity double-cavity ceramic matrix composite material blade assembly, and belongs to the technical field of aero-engines, the ceramic matrix composite material blade assembly comprises a ceramic matrix composite material blade, the ceramic matrix composite material blade comprises a blade body with a cavity, a blade upper edge plate and a blade lower edge plate, and the blade upper edge plate and the blade lower edge plate are located on the two sides of the blade body; a partition rib is arranged in the cavity of the blade body and divides the cavity into a front cavity and a rear cavity; the front cavity metal framework is integrally connected with a metal lower edge plate, the rear cavity metal framework is integrally connected with a metal upper edge plate, the metal lower edge plate and the metal upper edge plate are connected with an engine bearing structure, the front cavity metal framework is arranged in a front cavity of the blade body, and the rear cavity metal framework is arranged in a rear cavity of the blade body. The rear cavity metal framework is arranged in a rear cavity of the blade body, the front cavity metal framework is connected with the upper metal edge plate through a connecting piece, and the rear cavity metal framework is connected with the lower metal edge plate through a connecting piece.

A method of forming a ceramic matrix composite component includes forming a fiber preform, the fiber preform including a plurality of ceramic fiber plies, a non-reduced fiber region having an areal weight, and a reduced fiber region characterized by a reduced areal weight less than the areal weight of the non-reduced fiber region by at least 5 percent. The method further includes selectively applying ceramic particles to the reduced fiber region in such manner as to avoid applying the ceramic particles to the non-reduced fiber region, and subsequently densifying the preform.

Disclosed is a collaborative design system and method for a thermophysical property gradient distribution and a braided structure of a CMC and a storage medium. The system comprises at least one storage medium and at least one processor. The at least one processor is configured to: generate a temperature field parameter of a surface of a CMC turbine blade under a non-uniform inflow condition based on a simulation analysis platform, and extract a convective heat transfer coefficient; partition the CMC turbine blade and import an extracted fluid-solid heat transfer boundary condition into an optimization platform; perform multi-objective optimization on the thermophysical property gradient distribution of the CMC turbine blade under the non-uniform inflow condition based on an optimization simulation tool; and generate C nanotube contents of different regions of the CMC turbine blade based on a correspondence function and values of material thermal conductivities of the different regions of the CMC turbine blade to realize the collaborative design of the thermophysical property gradient distribution and the braided structure of the CMC.

A method of manufacturing ceramic matrix composites includes producing chemical vapor deposition functionalized ceramic particles before injecting the functionalized ceramic particles into the CMC fabric. The functionalized ceramic particles are mixed with a binder solution and then dispensed into voids present between adjacent tows of the CMC fabric. Injecting the particles in the center of the voids reduces the size and volume fraction of the voids / defects, improving the homogeneity of surface texture, homogeneity of microstructure, and part model shape conformity.

The invention discloses a nanostructure thermal protection coating resistant to long-time high-temperature oxidation and a preparation method thereof.The nanostructure thermal protection coating takes a ceramic matrix composite material as a matrix, and a bonding layer and a composite component coating are sequentially sprayed to the surface of the matrix. Preparing a nano-structure self-healing additive / Re2Si2O7 spherical powder body; preparing a bonding layer on the surface of the ceramic-based composite material serving as a matrix; and 3, depositing the nano-structure self-healing additive / Re2Si2O7 spherical powder on the surface of the bonding layer to form the composite component coating. According to the preparation method, the self-healing additive / Re2Si2O7 is prepared into the nano-structure spherical powder suitable for thermal spraying for the first time, and a method is provided for implementation of the high-performance material on a thermal spraying nano-structure coating. The prepared coating is stable in phase structure at high temperature, phase change of powder is avoided in the spraying process, and the coating has good thermal expansion coefficient matching performance with a base body.

The invention provides a novel ceramic matrix composite material and metal material combined adjustable turbine blade, and belongs to the technical field of aerospace, the novel ceramic matrix composite material and metal material combined adjustable turbine blade specifically comprises a metal upper edge plate and a metal lower edge plate; the ceramic matrix composite material front edge assembly is fixedly installed between the metal upper edge plate and the metal lower edge plate, and the ceramic matrix composite material front edge assembly serves as a front edge area of the blade; the adjustable metal blade body is rotationally mounted between the metal upper edge plate and the metal lower edge plate; the rear end of the blade body part of the ceramic matrix composite material front edge assembly is in butt joint with the front end of the adjustable metal blade body to form a complete turbine blade body structure. Through the treatment scheme, the problem that in the prior art, cooling of the front edge of the metal blade consumes a large amount of cold air is solved, and the service life of the adjustable turbine blade is prolonged.

The invention provides a laser-induced composite material surface multi-scale micro-texture assisted brazing method which comprises the following steps: step 3, carrying out surface texturing treatment on a to-be-welded surface of a fiber reinforced ceramic matrix composite obtained in step 2 by using a laser in air, and in the laser texturing process, carrying out surface texturing treatment on the to-be-welded surface of the fiber reinforced ceramic matrix composite, the fiber-reinforced ceramic matrix composite material is placed in the center of a laser objective table, then laser with the defocusing amount being-5-5 mm, the laser power being 0-300 W and the laser scanning speed being 5-100 mm s <-1 > is adopted for vertical irradiation, and the textured fiber-reinforced ceramic matrix composite material is obtained; and fourthly, active brazing filler metal is placed between the textured fiber-reinforced ceramic matrix composite obtained in the third step and the to-be-welded face of metal, and brazing assembly is completed. According to the method, the original straight interface reaction layer is textured through a surface material reduction method, and compared with a surface material increase method which is complex in process, harsh in process condition and high in process cost, the economic cost and the labor cost of the process are greatly reduced through the method.

A method of preparing a ceramic fabric and ceramic matrix composite components constructed from the ceramic fabric include transforming ceramic tows, or ceramic fabrics, to varying degrees from a first tow geometry to a second tow geometry, thereby reducing a first dimension of the ceramic tows and increasing a second dimension of the ceramic tows orthogonal to the first dimension. Plies constructed with flattened tows, or as-received tows, have various inter-tow pore sizes that are arranged with increasing inter-tow pore size towards exterior surfaces of the preform structure.

The invention discloses a silicon nitride ceramic-based composite material and a preparation method thereof, and relates to the technical field of silicon nitride ceramics. The silicon nitride ceramic-based composite material is prepared from silicon dioxide coated modified boron nitride and resin composite phase change microcapsules, Si3N4-C coated Al2O3 core-shell fiber aerogel, nano yttrium oxide and polyvinyl butyral, the silicon dioxide coated modified boron nitride and resin composite phase change microcapsules are stably attached to the surface of the Si3N4-C coated Al2O3 core-shell fiber aerogel in a chemical bonding and mechanical interlocking mode, the interface bonding strength is enhanced, the risk of phase separation is reduced, the combination effect of the silicon dioxide coated modified boron nitride and resin composite phase change microcapsules and the Si3N4-C coated Al2O3 core-shell fiber aerogel is better exerted, and the composite phase change effect of the silicon dioxide coated modified boron nitride and resin composite phase change microcapsules is improved. According to the present invention, the fracture toughness can be improved through fiber toughening, aerogel pore and microcapsule stress dispersion, the high temperature resistance can be improved through the low thermal conductivity of the aerogel and the heat absorption effect of the microcapsule, the mechanical property of the silicon nitride can be significantly improved through multiple ways and multiple modes, and the high temperature resistance can be effectively enhanced.

The invention relates to a gradient carbon nanotube fiber needled preform heat dredging ceramic-based composite material and a preparation method thereof. The method includes; preparing a plurality of carbon nano tube fiber web tire layers and carbon nano tube fiber cloth layers which are alternately laminated with the carbon nano tube fiber web tire layers and are compounded by needling, wherein the carbon nano tube fiber web tire layers comprise carbon nano tube fibers and organic fibers, and the content of the organic fibers is gradually changed layer by layer along the thickness direction of the prefabricated body; forming a carbon interface layer by using a carbon source; decomposing the organic fibers through high-temperature treatment to form pores in gradient distribution; and carrying out impregnation and cracking by using a ceramic precursor to obtain the heat-conducting ceramic-based composite material. According to the pure carbon nanotube fiber needled preform prepared by the method, organic fibers are decomposed through high-temperature treatment, pores in gradient distribution are formed while the heat conductivity is improved, closed pores are avoided, carbon interface deposition and ceramic densification are facilitated, mechanics is improved, the preparation period is shortened, and the cost is reduced.

The invention relates to the technical field of ceramic matrix composite material forming, in particular to a forming die and method for a thin-wall R-arc reinforced structure composite material component, and the forming die comprises a bottom die, an outer die, an inner die and a top cover; the inner mold is located in an R-arc inner cavity of the thin-wall R-arc reinforced structure composite material component and connected to the bottom mold, the outer mold is connected to the bottom mold, the top cover is connected to the bottom mold and the outer mold, and a cavity used for forming the thin-wall R-arc reinforced structure composite material component is defined by the bottom mold, the outer mold, the inner mold and the top cover; a gasket used for enabling the R-arc outer molded surface of the component prefabricated body to be attached to the outer mold and the top cover is arranged at the position, making contact with the component prefabricated body, of the bottom mold, and a supporting cushion rope used for assisting in forming of the R-arc tip is arranged at the tip of the inner mold. The forming die and method of the thin-wall R-arc reinforced structure composite material component aim at solving the problem that the forming difficulty of the R-arc position of a thin-wall R-arc reinforced structure is large.

The invention discloses a milling cutter for processing a ceramic matrix composite material, a cutting edge comprises a wave-shaped cutting edge and a tooth-shaped cutting edge, the wave-shaped cutting edge and the tooth-shaped cutting edge are positioned on different edge sections and are alternately arranged, the waveform of the wave-shaped cutting edge is a sine curve waveform, and the sine curve waveform is periodically arranged along the axial direction of the milling cutter; chip separating grooves are periodically formed in the tooth-shaped cutting edge in the axial direction of the milling cutter at intervals, and the chip separating grooves correspond to wave crests and wave troughs of the sine curve waveform. The wave-shaped cutting edge is in a sine curve wave shape, so that the length of the cutting edge is increased, the load in unit length is reduced, the machining cutting force is effectively reduced, heat dissipation is accelerated, vibration and deformation are reduced, the tooth-shaped cutting edge is divided by the chip dividing grooves of the tooth-shaped cutting edge, and chip removal and heat dissipation are facilitated while cutting force distribution is optimized; and in the machining process, discontinuous parts are cut through the tooth-shaped cutting edges, machining is conducted through the wave crests or the wave troughs of the wave-shaped cutting edges, and the cutting service life of the cutter is long.

The invention discloses a method for testing interlayer tensile strength of a ceramic matrix composite material. Comprising the following steps: acquiring the geometric dimension of a sample, performing surface treatment on a test surface of the sample, marking a test section of the sample, acquiring the geometric dimension of a four-point bending clamp, determining a placement mode of the sample and a camera, and capturing a displacement field of the test surface of the sample by using the camera while performing a curved beam four-point bending test. Obtaining the load value and stroke of the first load drop, extracting the in-situ strain of the sample by using a camera, deducing a formula for calculating the interlayer radial and tangential modulus ratio of the sample, carrying out calculation, and calculating the interlayer tensile strength of the sample by using the existing formula. According to the method disclosed by the invention, the modulus ratio of the interlayer radial direction to the interlayer tangential direction is obtained by using in-situ strain, the problem that the interlayer radial modulus is difficult to accurately determine directly through the test is solved, and the accuracy of the interlayer tensile strength of the ceramic matrix composite material measured through the curved beam four-point bending test is improved.

The invention relates to the technical field of aero-engine part machining, in particular to a machining method for a ceramic matrix composite turbine outer ring. The method specifically comprises the following steps: polishing a blank; blank detection; cutting the silicon shell; trimming is conducted; bonding is conducted; milling is conducted; repairing and cleaning by pincers; and inspecting. According to the method, a bonding clamping mode is adopted, a traditional pressing plate and bolt pressing structure is omitted, the structure of a tool clamp is simplified, the operation complexity of the clamp is reduced, and large machining and tool cost is saved; after the blank benchmark of the part is determined, the part is directly machined to the final size at a time, benchmark conversion is not needed, machining errors caused by clamping and benchmark conversion are reduced, the size precision and stability are guaranteed, and meanwhile the production efficiency is improved.

The invention discloses a morphology reconstruction method for a deposition layer of a ceramic matrix composite air film cooling structure, and belongs to the field of engineering thermophysics. According to the method, on the basis of traditional fluid-solid coupling heat transfer simulation, a track of dust particles on the surface of the ceramic-based composite material air film cooling structure is simulated in combination with a dispersed phase model, deposition layer thickness distribution characteristics are obtained, and after coordinate positions and normal vectors on surface grids are obtained through a user-defined function, the deposition layer thickness distribution characteristics are obtained. And directionally moving the coordinates at different positions of the component along the normal direction by the distance of the deposition thickness to obtain coordinate values of the surface of the sediment, and sequentially reconstructing the obtained coordinate point clouds into a polygonal mesh surface and a geometric model to obtain the geometric morphology of the reconstructed deposition layer. Therefore, the comprehensive cooling efficiency and attenuation characteristics of the ceramic-based composite material air film cooling structure under the influence of the deposited particles can be accurately calculated by simulating and analyzing the influence of the deposited layer on parameters such as flow characteristics and temperature distribution on the wall surface.

An airfoil includes an airfoil section that defines a trailing edge region that includes a trailing edge. The airfoil section is formed of a ceramic matrix composite that includes core fiber plies and skin fiber plies. The core fiber plies define a radial tube that has a radiused end in the trailing edge region. The skin fiber plies wrap around the core fiber plies and a filler element in the trailing edge region is aft of the internal cavity and is sandwiched between the skin fiber plies on the pressure side and the skin fiber plies on the suction side. There is at least one cooling passage that includes a first, inlet orifice section that opens to the internal cavity at a location forward of the radiused end and that extends through the core fiber plies, and a second, outlet orifice section that extends through the trailing edge.

The invention provides a multi-scale calculation method and system for mechanical properties of a unidirectional fiber reinforced ceramic matrix composite material. According to the method, a sequential multi-scale method is adopted, the surface energy of a matrix material is obtained through molecular dynamics on the nanoscale scale, and the molecular dynamics-discrete element coupled unidirectional fiber reinforced ceramic matrix composite material multi-scale calculation method and system are provided on the basis of the periodic damage characteristic of the material under the microscale. Compared with the prior art, the method has the advantages that the nanoscale damage behavior of the ceramic matrix composite matrix and the aggregation characteristic of the microcracks are fully considered, and the calculation precision of a microscopic result is remarkably improved. The method is suitable for component design, structure optimization and mechanical property prediction of the ceramic-based composite material in the aerospace field.

The invention provides a silicon carbide fiber reinforced ceramic-based composite material as well as a preparation method and application thereof, and belongs to the technical field of ceramic-based composite materials. The composite material comprises a silicon carbide fiber reinforced phase, a boron nitride interface layer and a silicon-based multiphase ceramic matrix from inside to outside, the silicon-based multiphase ceramic matrix comprises an infiltration reaction generation phase, an introduced ceramic particle phase and a silicon-containing binary alloy phase, and the infiltration reaction generation phase comprises a water-oxygen corrosion resistant phase, a silicon phase, a silicon carbide phase and a boride phase. The water oxygen corrosion resistant phase comprises a compound of boron and any element of yttrium, ytterbium, hafnium, molybdenum and aluminum, the boride phase comprises B12 (C, Si, B) 3, the bending strength of the composite material is larger than or equal to 600 MPa, and the fracture toughness of the composite material is larger than or equal to 19 MPa.m < 1 / 2 >. According to the preparation method, the matching property among the components of the composite material is optimized, the mechanical property of the composite material is improved, and a new thought and a process method are provided for preparing the high-strength and water-oxygen-corrosion-resistant ceramic matrix composite material.

The invention discloses direct writing forming equipment and method for a continuous fiber reinforced ceramic matrix composite, the direct writing forming equipment comprises an XYZ-axis motion platform, an extrusion nozzle, an ultrasonic transducer, a screw propeller, a wire feeder, a forming table and a curing mechanism, the extrusion nozzle is mounted on the XYZ-axis motion platform, and an outlet is formed in the bottom of the extrusion nozzle; the screw propeller comprises a motor and a screw, the motor is mounted on the extrusion nozzle and connected with the screw to drive the screw to rotate, so that the screw shears ceramic slurry in the extrusion nozzle and extrudes the ceramic slurry from an outlet of the extrusion nozzle, and a through hole is formed in the screw. Continuous fibers sent out by the wire feeder penetrate through the screw rod and then are discharged from an outlet of the extrusion nozzle; and the curing mechanism is used for curing the ceramic slurry on the forming table. The viscosity of the ceramic slurry is reduced through the shearing effect of the screw rod, blockage is prevented, and the extrusion nozzle can disperse nano-particle aggregates in the ceramic slurry through the vibration effect of ultrasonic waves.

The invention discloses a preparation method of a low-cost in-situ doped silicon nitride fiber, which comprises the following steps: taking one or two of vinyl liquid polycarbosilane and vinyl polysilazane as a precursor, adding a boron monomer, an organic solvent and metallocene, and doping to prepare a doped silicon nitride fiber containing boron, titanium, hafnium, zirconium and other elements; carrying out melt spinning on the doped precursor to obtain a doped precursor; then boron-containing active gas introduced in the crosslinking process can be combined with active sites on the surface of the protofilament fiber or directly deposited on the surface of the fiber; and finally, the boron-containing active gas reacts with ammonia gas in the high-temperature sintering process to generate a boron nitride (BN) surface coating. Thus, the temperature resistance of the silicon nitride fiber is improved, the problem that a coating of a prefabricated body of a silicon nitride fiber ceramic matrix composite material with a complex structure is not uniform is solved, meanwhile, high cost of a secondary coating and large damage to the fiber are avoided, the composite material preparation process flow is simplified, and the invention provides the low-cost preparation method for in-situ doping of the silicon nitride fiber.

The invention relates to the field of ceramic matrix composite bolt preparation, in particular to a high-strength ceramic matrix composite bolt production and processing technology which comprises the following steps: obtaining a rod-shaped preform with a cladding structure and a core structure, hanging the rod-shaped preform in a vapor deposition furnace, and depositing a pyrolytic carbon interface layer on the fiber surface of the rod-shaped preform to obtain the high-strength ceramic matrix composite bolt. Carrying out high-temperature treatment; placing the treated rod-shaped prefabricated body in a vacuum dipping barrel; pumping the ceramic precursor slurry into a barrel, carrying out argon pressurization, heating, heat preservation and furnace cooling, then taking out the ceramic precursor slurry, respectively carrying out vacuum cracking treatment under low-temperature and high-temperature conditions, and after heat preservation, naturally cooling the ceramic precursor slurry to room temperature in an argon atmosphere; preparing a silicon carbide matrix to obtain segmented bars; the segmented bars are ground and machined; and a ceramic coating is prepared on the surface of the bolt with the outer threads machined, the ceramic coating is silicon carbide, and the ceramic-based composite material bolt is obtained. The method aims at optimizing the cracking temperature in the cracking treatment process of the ceramic matrix composite bolt.

A gas turbine engine is provided. The gas turbine engine includes a stage of airfoil segments having a first ceramic matrix composite (CMC) airfoil segment, the first CMC airfoil segment includes: an end band having a radial surface defining a cold side surface area, ACS; and an airfoil coupled to or formed with the end band, the airfoil and the end band defining a joint therebetween, the joint including one or more radial interfaces defining a total radial interface surface area, ARI, and one or more axial interfaces defining a total axial interface surface area, AAI. The first CMC airfoil segment defines a first ratio of the cold side surface area, ACS, to the total axial interface surface area, AAI, and a second ratio of the total axial interface surface area, AAI to the total radial interface surface area, ARI.

A ceramic matrix composite (CMC) blade outer air seal (BOAS) assembly includes a CMC BOAS including a base and a pair of rails having a substantially π-shaped cross-section. The pair of rails include a first pair of aligned holes at a first end and second pair of aligned holes at a second end. A first pair of parallel metallic pins have a first end connected to a first central support pin and a second end connected to a second central support pin, respectively, wherein the first pair of parallel metallic pins are configured to engage the first pair of aligned holes. A second pair of parallel metallic pins also have a first end connected to a first central support pin and a second end connected to a second central support pin, respectively, wherein the second pair of parallel metallic pins are configured to engage the second pair of aligned holes.

An ultrahigh-temperature-resistant full ball bearing comprises a bearing outer ring, a bearing inner ring and a roller, the roller is spherical and is arranged in a roller path in a full complement mode, and the bearing outer ring, the bearing inner ring and the roller are all made of carbon fiber reinforced ceramic matrix composite materials. The design method comprises the following steps: S1, determining the inner diameter d, the outer diameter D and the width B of the bearing; and S2, determining an inner groove curvature radius coefficient fi and an outer groove curvature radius coefficient fe of the bearing based on a principle of reducing the working contact stress of the bearing and prolonging the fatigue relieving life of the bearing. And S3, the value ranges of the roller diameter DW, the center diameter DWP and the roller number Z of the bearing are determined. And S4, optimizing and determining the roller diameter DW, the center diameter DWP and the roller number Z of the bearing by taking the principle of obtaining the maximum radial basic rated static load. By applying the high-temperature-resistant bearing, the technical problems that an existing bearing loses efficacy quickly due to high temperature and insufficient lubrication in a high-temperature environment for a long time, and a bearing made of a ceramic material is low in fracture toughness and thermal shock resistance can be solved.

The invention relates to a water jet-laser / mechanical energy field cooperative precision machining method for a ceramic base material, and belongs to the field of laser-mechanical cooperative machining. During the execution period, the method comprises the following steps in sequence: firstly, carrying out rapid and low-damage precise material reduction on the ceramic matrix composite material through water jet assisted laser; and then, a superhard forming grinding wheel on the same machine tool is matched with mixed grinding fluid to conduct in-situ finishing and polishing on the surface obtained after material reduction. Wherein the surface quality can be improved while high-efficiency machining is ensured through the synergistic combination of laser and machinery. Through the in-situ grinding and polishing effect of the grinding wheel and the mixed grinding fluid, the precision of a formed surface is higher, and a damaged layer is thinner and even completely removed. Based on a water jet assisted laser milling / mechanical grinding and polishing collaborative machining strategy, rough machining, finish machining and fine polishing of the ceramic matrix composite can be completed on the same equipment, and the method has the characteristics of being high in precision, high in efficiency, high in quality and extremely low in surface damage.

An apparatus for controlling a layer of a composite material includes a robotic arm (18) and an end effector (100) mounted on the robotic arm.The end effector (100) comprises a base (112) attached to the robotic arm (18), the base (112) comprising a base track (116) extending along a first translational dimension, a platform (114) supported by the base (112) and movable along the base track (116), the platform (114) comprising a platform track (124) extending along a second translational dimension, a disk (134) supported by the platform (114) and movable along the platform track (124), the disk (134) being rotatable about a first rotational dimension, an arcuate track (136) supported by the disk (134), the arcuate track (136) extending along a second rotational dimension, and a layer manipulator (102) extending from the arcuate track (136) and movable along the arcuate track (136).

A method for fabricating a metal-infiltrated ceramic matrix composite, comprises: providing a ceramic fiber preform comprising a fiber tow; depositing an interface coating material around the fiber tow to form an interface coating therearound, and form an interfaced coated ceramic preform containing the interface coated fiber tows; depositing a silicon carbide layer around the interface coated fiber tow; depositing a reaction-barrier coating around the interface coated, silicon carbide coated fiber tow of the interface coated, silicon carbide coated ceramic preform; infiltrating the interface coated, silicon carbide coated ceramic preform with a slurry comprising a carbon source; drying the slurry infiltrated interface coated, silicon carbide coated ceramic preform; and infiltrating the dried slurry infiltrated interface coated, silicon carbide coated ceramic preform with a molten ternary metal alloy, a molten ternary metalloid alloy, a molten ternary metal alloy comprising boron as a constituent, a molten ternary metalloid alloy comprising boron as a constituent, a ternary metal melt, a ternary metalloid melt, a ternary metal melt comprising boron as a constituent, or a ternary metalloid melt comprising boron as a constituent, combinations comprising at least one of the foregoing; to form a melt-infiltrated ceramic matrix composite.

Systems, structures, devices, and fabrication processes for ceramic matrix composites suitable for use in a nuclear reactor environment and other applications requiring materials that can withstand high temperatures and / or highly corrosive environments are disclosed. In one aspect, a ceramic composite structure is provided. The structure comprises a chamber including an external shell and a hollow space inside the external shell. The external shell includes an inner composite layer including a first composite structure, a middle composite layer placed outside of the inner composite layer, the middle composite layer including a second composite structure that is different from the first composite structure, and an outer monolithic layer that has a spatially uniform material property and placed outside of the middle composite layer.