691 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 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 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.

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.

The invention relates to a preparation method of a ceramic-based composite material, in particular to a preparation method of a ceramic-based composite material with a pyrolytic carbon-carbon nanotube interface, which is used for solving the problem that in the aspect of improving the thermal conductivity of an interface layer, metals such as Fe, Co, Ni and the like are widely used as catalysts for growing carbon nanotubes at present, so that the thermal conductivity of the interface layer is improved. Carbon nanotubes obtained through a traditional preparation method are prone to agglomeration and uneven in distribution, the risk of the preparation process is high, the carbon nanotubes are not suitable for large-scale production, although metal particles can be reduced through a chemical plating method, the particle sizes of the metal particles are not controlled, the distribution of the metal particles is uneven, and the requirement of a chemical vapor reduction method for distribution of an earlier-stage metal salt solution is high. And the defect is difficult to realize easily. According to the preparation method of the ceramic-based composite material with the pyrolytic carbon-carbon nanotube interface, the ceramic-based composite material with the pyrolytic carbon-carbon nanotube interface is finally obtained through pretreatment, solution A preparation, metal salt solution in-situ reduction and chemical vapor deposition in sequence.

A gas turbine engine component, comprises a densified three-dimensional woven ceramic matrix composite comprising the shape of the gas turbine engine component, the densified three-dimensional woven ceramic matrix composite further comprises a three-dimensional woven structure comprising a densified ceramic matrix disposed on, within and throughout a three-dimensional weave comprising at least one inorganic fiber comprising at least one multilayer coating material structure disposed thereupon, wherein the at least one multilayer coating material structure comprises at least one first interface coating material layer comprising a boron nitride; at least one coating material layer comprising a silicon nitride; at least one second interface coating material layer comprising the boron nitride; and at least one third interface coating material layer comprising a Si3N4-BN multilayer coating having one or more alternating layers comprising at least one layer of silicon nitride at a first thickness; and at least one layer of boron nitride at a second thickness.

The invention belongs to the technical field of ceramic materials, and particularly discloses whisker toughened zirconium oxide-aluminum oxide composite ceramic and an additive manufacturing method thereof, the composite ceramic comprises the following components by mass: 94 parts of zirconium oxide toughened aluminum oxide ceramic and 5 parts of silicon carbide whisker; the zirconium oxide toughened aluminum oxide ceramic is prepared from the following components in parts by mass: 76 parts of aluminum oxide and 24 parts of zirconium oxide, and 3mol% of yttrium oxide is added into the zirconium oxide. According to the whisker toughened zirconium oxide-aluminum oxide composite ceramic and the additive manufacturing method thereof, the preparation method has unique design of components and process, and the preparation of a high-density and high-performance ceramic-based composite material part based on a fused deposition modeling technology is successfully realized. Further, the prepared silicon carbide whisker toughened zirconium oxide-aluminum oxide-based composite ceramic has relatively high density and excellent obdurability.

A cooling flow arrangement for a ceramic matrix composite (CMC) component of a turbine engine, wherein the CMC component includes a hot side configured for exposure to a hot gas path of the turbine engine and an opposing cold side. At least one cavity is provided in the CMC component, the at least one cavity having an entrance disposed on the cold side that is configured for receiving a cooling flow. A seal is disposed adjacent the at least one cavity and the cold side of the CMC component and is configured to provide a seal between the CMC component and an upstream turbine component. At least one hole extends through the seal and is positioned to provide the cooling flow to the at least one cavity of the CMC component.

The invention relates to a low-expansion, ablation-resistant and heat-insulating integrated composite material and a preparation method thereof, and belongs to the field of ceramic-based composite materials. Comprising the following steps: putting a fiber reinforcement into a high-temperature furnace, and carrying out glue removal treatment in a vacuum state to remove a surface glue layer; adding low-expansion ceramic powder and ultrahigh-temperature ceramic powder into the ceramic precursor, and carrying out ball milling and uniform mixing to obtain a mixed solution; introducing the mixed solution into the central area of the fiber preform by adopting an injection mode, soaking the fiber preform in the mixed solution, soaking the mixed solution into the fiber preform by adopting a vacuum impregnation and pressure impregnation mode, and fully impregnating, compounding and curing; and putting the cured green body into a high-temperature atmosphere furnace for cracking, and obtaining composite materials with different densities by controlling the number of times of impregnation and cracking. The prepared composite material has excellent heat insulation, ablation resistance and bearing performance, has more reliable thermal stability and reliability, is simple in process and short in period, and can be applied to the fields of ultra-high-speed aircrafts and the like.

The invention relates to a high-performance hafnium-based ultrahigh-temperature ceramic-based composite material and a preparation method thereof. The method comprises the following steps: depositing pyrolytic carbon on the carbon fiber surface of a carbon fiber preform through a CVD (Chemical Vapor Deposition) method; preparing a hafnium oxide interface layer on the surface of the pyrolytic carbon through an atomic layer deposition method, and performing ultra-fast annealing treatment to form a pyrolytic carbon-hafnium oxide composite interface layer; carrying out a reaction with a matrix containing a pyrolytic carbon-hafnium oxide composite interface layer through an impregnation pyrolysis method; a hafnium carbide coating is prepared on the surface of the composite material matrix through a CVD method; and preparing a hafnium oxide coating on the surface of the hafnium carbide coating through an atomic layer deposition method, and carrying out ultra-fast annealing treatment to prepare the high-performance hafnium-based ultra-high-temperature ceramic-based composite material. According to the preparation method, the pyrolytic carbon-hafnium oxide composite interface layer is prepared by adopting an atomic layer deposition process and depending on ultra-fast annealing treatment, and meanwhile, the hafnium carbide-hafnium oxide composite coating is prepared, so that the mechanical property of the composite material in a high-temperature aerobic environment is remarkably improved.

The invention discloses a method for predicting high-temperature and complex stress of a ceramic-based composite material based on strain control damage evolution, and belongs to the technical field of stress prediction of ceramic-based composite materials. The method comprises the following steps: determining material high-temperature performance degradation conditions according to temperature; the total strain (mechanical strain and thermal strain) of the material is calculated, and then based on a three-dimensional failure criterion of strain control, six damage initial criterion equations including stretching and compression in the warp direction, the weft direction and the out-of-plane direction are constructed; establishing an evolution model of damage coefficients by introducing a coupling mechanism of damage factors in different directions; combining a multi-linear constitutive relation of the ceramic matrix composite material to construct a rigidity degradation matrix, and realizing rigidity adjustment of the failure unit; and finally deducing a stress-strain relation equation to complete stress prediction of the material under the conditions of high temperature and complex load. The prediction method provided by the invention can accurately predict the complex stress state of the ceramic matrix composite material under the combined action of the high temperature and the mechanical load.

The invention belongs to the technical field of ceramic matrix composite material laser processing, and discloses a ceramic matrix composite material component large depth-diameter ratio micropore long pulse laser processing method, which comprises the following steps: cleaning the surface of a pretreatment component, and finishing initial alignment of processing; then drilling in three stages: in the first stage, using a first group of parameters to make a laser focus defocus, and releasing a preset pulse; in the second stage, the pulse width and frequency are kept unchanged, the laser power is maintained, the focus is adjusted to be zero defocus, and the pulse is released; and in the third stage, the first two parameters are kept unchanged, the laser power is reduced, the focus is adjusted to be negative defocus, and the pulse is released. And repeating the preset times according to the depth-diameter ratio requirement, and finally cleaning impurities at the orifice. The invention aims to solve the problems of low processing efficiency and precision caused by complex film hole angle, small hole diameter and large depth-diameter ratio of a ceramic matrix composite component.

The invention discloses a field plowing rotary cultivator, which relates to the technical field of agricultural machinery and comprises a machine body frame, a gearbox is fixedly connected to the interior of the machine body frame, and two connecting seats are fixedly connected to the surface of one side of the machine body frame. In the embodiment, the machine body frame is in three-point suspension connection with the tail of a tractor through the connecting seat, the input end of the gearbox is connected with the output end of the tractor, the transmission shaft drives the rotary blade to turn soil, the bearing seat supports the transmission shaft to avoid vibration, the baffle prevents soil from splashing, and the rotary blade is made of silicon nitride ceramic matrix composite materials and is reinforced by adding carbon fibers. The machine body frame is made of a high-performance resin-based composite material and a mixed reinforced material of modified epoxy resin, modified glass fibers and modified aramid fibers, and compared with a traditional metal frame, the machine body frame has the advantages that the weight is reduced, excellent corrosion resistance is achieved, rust-proof treatment is not needed, and the service life is prolonged. The device can be used for a long time in a humid and muddy field environment without being damaged.

A brush seal for use with a ceramic matrix composite (CMC) component of a gas turbine engine may feed a cooling flow to the CMC component, which has a hot side configured for exposure to a hot gas path of the gas turbine engine and an opposing cold side having a cavity for feeding a cooling flow to at least one film cooling hole of the CMC component. The brush seal includes: an outer diameter (OD) backing plate; an inner diameter (ID) backing plate; a plurality of brush seal bristles sandwiched between the OD backing plate and the ID backing plate; at least one hole forming a passage extending through the OD backing plate, the brush seal bristles, and the ID backing plate; and a cover plate attached to an inner surface of the ID backing plate and configured to extend into the cavity of the CMC component.

The invention relates to a structural wave-absorbing integrated ceramic-based composite material prepared based on 3D printing and a preparation method of the structural wave-absorbing integrated ceramic-based composite material. The preparation method of the structural wave-absorbing integrated ceramic matrix composite material comprises the following steps: mixing chopped silicon carbide fibers, a dispersant, a binder, a catalyst and a solvent to obtain chopped silicon carbide fiber slurry; the slurry is subjected to periodic array arrangement, printing and forming through 3D printing, and a silicon carbide fiber preform of a periodic structure is obtained through drying and glue discharging; inducing in-situ growth of the silicon carbide nanowire on the surface of the preform by using a catalyst introduced into the slurry by adopting CVI, and depositing a BN interface phase on the surface of the silicon carbide nanowire by adopting CVI to form a SiC / BN core-shell structure nanowire; dipping the prefabricated body into a polysilazane precursor, curing and cracking, and introducing a Si3N4 ceramic matrix into the prefabricated body; and repeating dipping, curing and cracking for 5-10 times to densify the composite material, thereby obtaining the structural wave-absorbing integrated ceramic matrix composite material.

The invention discloses a self-healing high-temperature anti-oxidation carbon-ceramic composite material, belongs to the technical field of ceramic-based composite materials, and particularly relates to a method for introducing a self-healing metal-element-free high-temperature anti-oxidation ceramic matrix into a carbon fiber preform. Then introducing a resin carbon matrix and a self-healing inorganic filler through two times of vacuum impregnation and high-temperature cracking, and finally preparing the SiC matrix by adopting high-temperature siliconizing. The carbon-ceramic composite material prepared by the invention does not contain metal impurities, has a self-healing function, and has a long-life anti-oxidation function in a range of 700-1000 DEG C.

The invention discloses a ceramic precursor efficient impregnation and solidification integrated device and method, belongs to the technical field of ceramic matrix composite material preparation, and solves the problems of low production efficiency, large raw material loss and poor impregnation effect caused by step-by-step impregnation and solidification of a ceramic precursor in the prior art. The device specifically comprises an integrated furnace body, an ultrasonic vibration assembly, a vacuum system, a temperature control system and a precursor storage tank, and an objective table for placing a workpiece to be impregnated is arranged in the integrated furnace body. During precursor solution impregnation, the vacuum system extracts air in the integrated furnace body to form negative pressure, and the precursor solution in the precursor storage tank is extracted into the furnace body through the negative pressure to impregnate the workpiece; after impregnation is finished, the workpieces are directly heated and cured in the integrated furnace body, the process of transferring the workpieces from the impregnation tank to a curing furnace is omitted, and the production efficiency is improved; and meanwhile, poor impregnation effect caused by re-permeation of air into pores of the workpiece after the workpiece is in contact with the air in the transfer process is prevented.

The invention relates to the field of advanced ceramic materials, in particular to a ceramic matrix composite (CMC) and a preparation method thereof. The technical problems that a traditional CMC preparation technology is long in period, poor in structural uniformity and insufficient in toughness are solved. According to the method, surface-modified aluminum oxide ceramic microspheres are used as reinforcements, the surfaces of the microspheres are sequentially modified with hexagonal boron nitride nanosheets and a metal nickel catalyst, the microspheres, silicon carbide nanoparticles and a polycarbosilane precursor are mixed to form slurry, and a complex component is formed through multi-material additive manufacturing. A green body is prepared by using a 3D printing technology combining photocuring and material extrusion; carrying out ultraviolet curing on the green body, and carrying out staged heat treatment in an inert atmosphere, so that the precursor polymer is subjected to cross-linking curing, and meanwhile, carbon nanowires grow through in-situ catalysis; and finally, sintering under a pressurizing condition to realize matrix densification. The preparation period is greatly shortened, and the obtained composite material is uniform in structure, compact in matrix and excellent in mechanical property.

The invention discloses a machining method for multi-stage laser composite modified auxiliary grinding, and belongs to the technical field of material machining. According to the method, a multi-step synergistic process of ultraviolet activation (cleaning / absorption increasing), infrared-induced loosening (oxidation channel construction / surface macroscopic removal difficulty reduction) and ultraviolet amorphous oxidation (brittle-plastic transition promotion / subsurface layer heat affected zone repair) is adopted, and selective ablation of infrared laser and photochemical action of ultraviolet laser are synergistically complemented; a composite modified layer which is composed of a porous deformation layer and an amorphous oxide layer and has a small subsurface layer heat affected zone is constructed on the surface of the fiber reinforced ceramic matrix composite material, and the modified layer has the three functions of being loose and easy to remove, promoting abrasive dust to be discharged and visualizing a thickness scale, so that follow-up fine grinding machining is guided and optimized, and the service life of the fiber reinforced ceramic matrix composite material is prolonged. And finally, high-efficiency, high-quality and low-damage surface precision machining of the material is achieved.

Carbide-based fuel assembly includes outer structural member of ceramic matrix composite material, the interior surface of which is lined in higher temperature regions with an insulation layer of porous refractory ceramic material. A continuous insulation layer extends the length of the fuel assembly or separate insulation layer sections have a thickness increasing step-wise along the length of the fuel assembly from upper (inlet) section towards bottom (outlet) section. Fuel element positioned inward of the insulation layer and between support meshes has a fuel composition including HALEU and the form of a plurality of individual elongated fuel bodies or one or more fuel monolith bodies containing coolant flow channels. Fuel assemblies are distributively arranged in a moderator block, with upper end of the outer structural member attached to an inlet for propellant and lower end of the outer structural member operatively interfaced with a nozzle forming a nuclear thermal propulsion reactor.

The invention relates to a method for strengthening and toughening a ceramic matrix composite material brazed joint through a laser-induced surface texturing structure. The method is mainly used for preparing a fiber reinforced composite material and brazed connection of the fiber reinforced composite material and metal. The method solves the problems of high residual stress and poor strength and toughness of the fiber reinforced composite material and metal brazed joint. The method comprises the following specific steps: processing the fiber reinforced composite material into a required size, polishing and cleaning the fiber reinforced composite material, and performing surface ablation treatment on a to-be-welded surface of the fiber reinforced composite material by using a laser to obtain the textured fiber reinforced composite material; and then the alloy is used as base metal to be in brazed connection with metal. A sawtooth structure is formed on the surface of a material and pores are opened through laser irradiation by utilizing the ablation difference between fibers and a matrix material, so that a mechanically interlocked pinning structure is constructed in a brazed joint, and the modification of an interface microstructure is realized. When the structure is stressed, crack bridging, deflection and fiber pulling-out can be induced, crack propagation energy is effectively consumed, and the mechanical property of a joint is improved. In addition, a uniform eutectic phase generated by laser ablation is beneficial to improving the thermal physical property and the plasticity and toughness of a welding seam, and a joint is further strengthened. According to the method, the interface microstructure can be effectively regulated and controlled, and the comprehensive mechanical property of the fiber reinforced composite material and the metal joint is remarkably improved.

The invention discloses a method for predicting residual mechanical properties of a ceramic-based composite material based on deep learning, and belongs to the field of mechanical analysis of ceramic-based composites.The method comprises the steps that a cyclic load test is conducted on a plurality of ceramic-based composite material test pieces, and mechanical data and acoustic emission signals of the whole life cycle are recorded; respectively analyzing the mechanical data and the acoustic emission signal of each ceramic matrix composite material test piece, and determining a macromechanical response characteristic sequence and a microcosmic acoustic emission response characteristic sequence; training a deep learning network model according to the macroscopic mechanical response feature sequence and the microscopic acoustic emission response feature sequence of each ceramic matrix composite test piece to obtain a residual mechanical property prediction model; and according to the residual mechanical property prediction model, predicting and analyzing the residual mechanical properties of the ceramic matrix composite to-be-tested piece. The method solves the technical problem of low reliability of residual mechanical property analysis of the ceramic-based composite material under the condition of repeated use.

The invention relates to the technical field of high-temperature-resistant coatings, in particular to a method for repairing a high-temperature-resistant environmental barrier coating, which comprises the following steps of: pretreating a to-be-repaired area on the surface of a ceramic matrix composite material; the surface to-be-repaired area is coated with prepared bonding layer slurry, curing treatment is carried out, and a first bonding layer is obtained; coating the outer surface of the first bonding layer with the bonding layer slurry, and performing curing treatment to obtain a second bonding layer; the outer surface of the second bonding layer is coated with prepared middle layer slurry, curing treatment is conducted, and a middle layer is obtained; coating the outer surface of the middle layer with prepared surface layer slurry, and performing curing treatment to obtain a surface layer; and carrying out surface heat treatment on the ceramic-based composite material coated with the surface layer to obtain the high-temperature-resistant environmental barrier repair coating. The repairing method of the high-temperature-resistant environmental barrier coating aims at solving the problem that the external field repairing difficulty of the local damaged area of the environmental barrier coating on the surface of the ceramic matrix composite is large.

The application discloses a kind of multi-element ultra-high temperature nanocomposite ceramic matrix composites and preparation method thereof, the multi-element ultra-high temperature nanocomposite ceramic matrix composites are composed of multi-element ultra-high temperature nanocomposite ceramic and porous fiber body, wherein multi-element ultra-high temperature nanocomposite ceramic is composed of oxygen-free silicon-based ceramic and multi-element transition metal carbonitride uniformly distributed therein, and the preparation method is: at least two metal element complexes are reacted with silicon-based polymer to obtain single-source precursor polymer;Then porous fiber body is placed in single-source precursor polymer solution for multiple times of impregnation pyrolysis, and the composite material provided by the application has a nanocomposite structure, an ultra-high temperature ceramic multi-element single-phase solid solution, the type, content and ratio of metal elements can be adjusted, the ultra-high temperature ceramic in the matrix is uniformly distributed and has a nanoscale grain size, and the method can avoid damage to the fiber during preparation, thereby achieving simultaneous improvement of the mechanical properties and oxidation ablation resistance of the composite material.

The application is a kind of fiber reinforced ceramic matrix composite surface three-dimensional roughness detection method and system, belongs to the technical field of material processing surface quality detection;Method is, first scanning fiber reinforced ceramic matrix composite processing surface to get the original processing surface three-dimensional model, and export point cloud data;Secondly, the coordinate transformation processing is carried out to the original three-dimensional model point cloud data, and the model is put right, the height difference of adjacent point cloud data is taken as the feature, the abnormal data points are screened and removed, the internal hole exposed on the processing surface is removed, the processing surface is reconstructed and the three-dimensional roughness S a Is calculated;Then determine the measurement area;Finally, according to the determined measurement area, the above scanning, hole removal, model reconstruction, S a The calculation work, namely the three-dimensional roughness of the processing surface is determined. The three-dimensional surface roughness value calculated by the application is no longer affected by the hole data, which ensures the effectiveness of the data.

The utility model discloses a high-temperature cracking shaping tool for a ceramic-based composite sheet, relates to the technical field of ceramic-based composites, and can solve the problems that a shaping tool in the prior art cannot shape a product at one time and is troublesome to disassemble and assemble. The high-temperature cracking shaping tool for the ceramic-based composite sheet comprises an upper die and a lower die which are detachably connected, and the upper die comprises a cover plate and a first forming structure arranged at the bottom of the cover plate; the lower die comprises a base and a containing groove formed in the center of the top face of the base, and the bottom of the containing groove is provided with a second forming structure used for being matched with the first forming structure to enable the circular arch structure of the ceramic-based composite to be formed.

The invention discloses a single-crystal high-temperature alloy and ceramic matrix composite material-based functional partition type composite blade design method, which comprises the following steps of defining a temperature bearing area and a force bearing area of a blade through heat and force simulation; the brazing residual stress is predicted, and the optimal assembly gap between the two partition interfaces of the temperature bearing area and the force bearing area of the composite blade is optimized and determined; predicting peak stress, and optimizing and determining the optimal position and size of a mechanical locking structure between two partition interfaces of a temperature bearing area and a force bearing area of the composite blade; and through heat-force-flow coupling simulation, the maximum equivalent stress of the composite blade and the bonding strength between partition interfaces are evaluated, and then the design of the composite blade is completed. According to the method, through heat-force-flow coupling simulation and iterative optimization, precise definition of function partitions and cooperative compatibility of mechanical locking and the process are achieved, and the low-stress and high-strength performance of the composite blade in the high-temperature and high-pressure environment is ensured.

The invention relates to the technical field of aero-engine high-temperature and high-pressure testing, and particularly discloses a double-working-condition high-temperature-resistant total temperature sensing part which is suitable for a cooling-free working condition and a cooling working condition and comprises a shell, a lead device, a mounting base and a supporting framework. The shell comprises a front test piece and a rear protective sleeve which are formed by integrally weaving a ceramic matrix composite material; the windward side of the front test piece is semi-cylindrical, a temperature taking cavity is formed in the front test piece, an air leakage hole is formed in the outer wall, and a thermocouple is mounted in the temperature taking cavity; the lead device comprises a ceramic tube, a lead tube and a shielding cable accessory; the front test piece and the rear protective sleeve are connected by the support framework through a stepped combined groove, and a bent water cooling pipeline is formed in the support framework; and a cavity between the supporting framework and the front test piece is filled and sealed by high-temperature cement. According to the invention, short-time high-temperature measurement can be realized under a non-cooling condition, and long-time stable total temperature acquisition capability can be obtained under a cooling condition, so that structural reliability and temperature measurement precision in an extreme gas environment are both considered.

The present application relates to a kind of high electrochemical performance porous ceramic matrix composite and its preparation method, porous ceramic matrix composite includes: porous ceramic composite, carbon coating layer is coated in the outer surface of porous ceramic composite;Porous ceramic composite: porous ceramic matrix, dispersing carbon layer is dispersedly distributed on the outer surface and pore wall of porous ceramic matrix, and silicon nanolayer is deposited on dispersing carbon layer;Silicon nanolayer is made of closely arranged nanometer silicon crystal grain;The average particle size of nanometer silicon crystal grain is between 1nm and 5nm;Silicon element in porous ceramic matrix composite accounts for 20wt% to 70wt%;The thickness of dispersing carbon layer is between 1nm and 20nm;The porous ceramic matrix composite of the present application is used to prepare negative pole piece and is applied in lithium ion battery, can improve the first cycle coulomb efficiency and safety performance of lithium ion battery.

The invention relates to a carbon nano tube fiber-carbon nano tube-pitch-based fiber profiling heat dredging ceramic matrix composite material and a preparation method of the carbon nano tube fiber-carbon nano tube-pitch-based fiber profiling heat dredging ceramic matrix composite material. The preparation method comprises the following steps: cutting carbon nano tube fiber cloth into an expected shape, paving layers, and implementing primary PIP by using a carbon nano tube resin dispersion liquid; an asphalt-based fiber resin composite material bar is implanted in the Z direction, and secondary PIP is carried out; and siliconizing treatment. The invention also provides the heat-conducting ceramic-based composite material prepared by the method. The carbon nanotube fibers, the carbon nanotubes and the high-brittleness asphalt-based fibers are adopted to realize the thermal dredging ceramic-based composite material with excellent mechanical properties and thermal conductivity, and the thermal dredging ceramic-based composite material has a wide application prospect.