517 results about "Thermal barrier coating" patented technology

The invention relates to the technical field of aero-engines, in particular to an aero-engine thermal barrier coating working condition simulation experiment system which comprises a high-temperature thermal cycle module, a high-speed airflow scouring module, a high-pressure loading module, an atmosphere control module and a data monitoring and collecting module. The high-temperature thermal cycle module is used for realizing rapid heating and cooling so as to simulate a thermal environment; the high-speed airflow scouring module is used for generating high-speed airflow to simulate gas scouring; the coating performance can be accurately evaluated through the multi-working-condition high-precision simulation capability, research and development personnel can be assisted to optimize components and structures, coating defects and weak points can be rapidly and accurately found through strict working condition simulation in the aspect of quality detection, the product quality is guaranteed, the defective rate is reduced, and the method has good application prospects from cost benefit consideration. The test frequency and the part replacement cost caused by the coating problem in engine research and development are reduced, the research and development period is shortened, the performance and reliability of the aero-engine are greatly improved, the development of the aerospace industry is powerfully promoted, and a solid foundation is laid for advanced engine research and development.

The invention discloses a thermal shock failure prediction and laser repair device for a thermal barrier coating and an application method. The device comprises a multi-physics field coupling simulation analysis module, a thermal shock experiment loading module, an online damage monitoring and failure diagnosis module, a robot laser repair execution module and a central control and data processing core unit. A thermal-mechanical-chemical coupling model is established to predict a coating failure behavior, a high-frequency induction heating and gas quenching system is adopted to simulate an extreme thermal shock environment, a multi-band thermal infrared imager, an ultrasonic probe and a digital image related system are integrated to monitor damage evolution in real time, and in-situ repair of a damaged area is realized based on a six-degree-of-freedom industrial robot. According to the method, the whole-process closed-loop control from failure prediction to repair regeneration is realized, the problems of single function and lack of multi-field coupling analysis and real-time repair capability in the prior art are solved, and the service reliability evaluation precision and the remanufacturing efficiency of the thermal barrier coating are remarkably improved.

The invention provides a thermal barrier coating defect analysis method based on terahertz multi-domain imaging weighted fusion, which comprises the following steps: according to different positions of defects in a thermal barrier coating, respectively intercepting signals of imaging modes of the surface, the interior, the lower interface and the integral structure of the thermal barrier coating from thermal barrier coating signals; calculating a time domain index value and a statistical domain index value in each signal, arranging the index values into a two-dimensional matrix, and drawing a two-dimensional imaging graph; carrying out fusion imaging on the two-dimensional image by adopting a weighted fusion method to obtain a terahertz fusion image; segmenting and identifying defect features in the terahertz fusion image to obtain defect type and size information; according to the thermal barrier coating falling failure judgment criterion, the failure state of the thermal barrier coating is evaluated according to the defect area proportion; according to the method, the terahertz multi-domain imaging graph is adopted to effectively extract the early internal defect characteristics of the thermal barrier coating, the defect characteristics are enhanced through weighted fusion imaging, and finally early internal defect detection and failure evaluation are achieved.

The invention discloses an infrared temperature measurement calibration method and device for a CMAS high-temperature corrosion thermal barrier coating. The method comprises the following steps: preparing a thermal barrier coating sample coated with CMAS and provided with holes in the side surface; placing the sample in a high-temperature furnace, and inserting a high-temperature thermocouple into the sample temperature measuring hole; adjusting the high-temperature infrared thermometer to align a temperature measuring light path of the high-temperature infrared thermometer with a to-be-measured area on the surface of the sample; heating the high-temperature furnace to a preset temperature and preserving heat; and comparing thermocouple and infrared temperature measurement data in real time, adjusting the infrared emissivity to enable the difference between the thermocouple and the infrared temperature measurement data to be within a preset error range, and determining the infrared emissivity parameter of the sample at the temperature. According to the method provided by the invention, the infrared temperature measurement parameters of the thermal barrier coating under different CMAS corrosion conditions can be accurately calibrated, so that the corresponding infrared emissivity is obtained, and a key technical support is provided for checking and evaluating the high-temperature CMAS corrosion service life of the thermal barrier coating and testing the reliability of the service life. Meanwhile, the device adopted by the invention is simple in structure, simple and convenient to operate, accurate and effective in test result and good in application value.

The invention discloses a method for quantitatively evaluating the CMAS corrosion resistance of a thermal barrier coating, which comprises the following steps: uniformly coating CMAS on the surface of the thermal barrier coating, and carrying out corrosion treatment according to set temperature and time; the corroded thermal barrier coating is subjected to longitudinal linear cutting, and the cut section is gradually ground and polished; sEM characterization is conducted on the polished cutting section, and an SEM image is shot for further quantitative analysis; based on the obtained SEM image, the corrosion depth of the CMAS in the thermal barrier coating is measured; selecting at least one identification area in the CMAS corrosion area, and calculating the area of the CMAS phase in each identification area; and calculating the corrosion degree C of the CMAS to the thermal barrier coating based on the proportion of the CMAS phase area in the identification area. The method is simple and easy to operate, the proportion of the area corroded by the CMAS in the corrosion area is introduced as a key evaluation index on the basis of corrosion depth measurement, and a unified, reliable and quantifiable standard is provided for objectively and quantitatively evaluating the CMAS corrosion resistance of the thermal barrier coating.

The invention provides a turbine blade thermal barrier coating thickness distribution optimization method, electronic equipment and a medium, and the method comprises the following steps: dividing a turbine blade thermal barrier coating into a plurality of areas, and changing the thermal barrier coating thickness of at least one area to obtain a plurality of different thermal barrier coating thickness distributions; a machine learning network model is adopted to construct a prediction model of a target value, the multiple different thermal barrier coating thickness distributions serve as input of the machine learning network model, the machine learning network model is trained, and a target value prediction model is obtained; and adopting a multi-target genetic algorithm to obtain a Pareto optimal solution of the thickness distribution of the thermal barrier coating. The thickness distribution of the thermal barrier coating is reasonably optimized to optimize the thermal load distribution on the surface of the coating, so that the comprehensive cooling effect of the turbine blade is improved; according to the method, the high comprehensive cooling efficiency and the low pressure loss coefficient are both considered, and the service performance and economical efficiency of the turbine blade are improved.

The invention discloses an ultralow-thermal-conductivity high-entropy rare earth disilicate ceramic material and a preparation method thereof, and belongs to the technical field of high-performance ceramics. Through a high-entropy engineering strategy, aiming at the problems of poor phase stability, high thermal conductivity and insufficient calcium-magnesium-aluminum silicate corrosion resistance of a traditional rare earth bisilicate material, a Ho-Yb-Lu-X multi-element rare earth composite system high-entropy effect regulation and control component strategy is innovatively adopted, and based on atomic radius difference, electronegativity matching and a mixed entropy effect, the high-entropy composite material is prepared. The high-entropy ceramic with the beta-type RE2Si2O7 phase structure is successfully prepared, generation of impure phases is effectively inhibited, and a compact material is obtained. The obtained material shows the ultralow thermal conductivity of 0.841 W / m.K at the temperature of 1400 DEG C, wherein the thermal conductivity is reduced by about 46% compared with that of traditional Yb2Si2O7. According to the preparation process, the sintering temperature is reduced by 50 DEG C through high-entropy component design, no complex post-treatment procedure is needed, the preparation process has the advantages of simplified process, high yield and the like, and an ideal candidate material is provided for a new generation of aero-engine thermal barrier coating.

The invention discloses an automatic grading device for thermal shock cracks of a coating and an application method. Comprising a terahertz wave detection module, a laser ultrasonic excitation and detection module, a high-precision three-dimensional motion control platform, a multi-mode signal synchronous acquisition and processing unit, a crack intelligent grading evaluation unit, an environment simulation and temperature control unit, a protective shell and a human-computer interaction interface. The near-surface dielectric property change of the coating is represented through the terahertz technology, the deep mechanical property evolution is detected through the laser ultrasonic technology, the thermal shock service condition is reproduced in combination with a high-temperature environment simulation unit, and a multi-modal feature fusion algorithm and a physical model and machine learning collaborative inversion model are adopted to obtain the thermal shock resistance of the coating. And automatic quantitative evaluation and severity grading of the depth, density, length and network connectivity of the thermal shock cracks of the thermal barrier coating are realized. The problems that an existing single detection method is insensitive to vertical cracks, poor in high-temperature environment adaptability and low in manual evaluation efficiency are solved.

The invention relates to an aero-engine thermal barrier coating quality evaluation method based on a terahertz technology. The method comprises the following steps: performing terahertz wave scanning on the surface of a target hot end component, and collecting a terahertz wave reflection time-domain spectrum generated by terahertz waves at a scanning position; determining a peak value region corresponding to the surface of the coating and a peak value region corresponding to the bottom surface of the coating in the terahertz wave reflection time-domain spectrum, determining the thickness of the coating corresponding to the scanning position based on the acquisition time difference of each peak value region, and determining the porosity of the coating corresponding to the scanning position according to the amplitude and phase of each peak value region; target area division is carried out on the surface of the target hot end component, and the coating uniformity corresponding to a target area is determined based on the coating thickness corresponding to each scanning position contained in the target area; and determining a coating quality index of the target hot end component according to the coating thickness and the coating porosity corresponding to each scanning position and the coating uniformity corresponding to each target area. By adopting the method, the coating evaluation cost can be reduced.

The invention discloses a data-driven high-infrared-radiation-characteristic high-entropy rare earth tantalate material screening method and application, and belongs to the technical field of thermal barrier coating materials. The method aims at breaking through the infrared radiation performance bottleneck of a traditional rare earth tantalate ceramic material, a high-precision prediction model of the infrared emissivity of the rare earth tantalate is innovatively developed by constructing a multi-system common data set, and rapid evaluation of the infrared spectral characteristics of the A-site high-entropy rare earth tantalate RE3TaO7 material is achieved. On the basis of the model, a multi-element rare earth tantalate system which comprises (Y < 0.2 > Dy < 0.2 > Gd < 0.2 > Sm < 0.2 > Nd < 0.2 >) < 3 > TaO7 and (Nd < 0.2 > Eu < 0.2 > Dy < 0.2 > Er < 0.2 > Yb < 0.2 >) < 3 > TaO7 and has excellent infrared radiation characteristics is successfully screened out. According to the method, the limitation of traditional small sample material research is broken through through big data modeling, and an efficient theoretical design normal form is provided for developing a novel high-entropy infrared radiation material.

A preparation method of an integrated thermal barrier ceramic coating with high strength and toughness / low thermal conductivity / anti-thermal radiation penetration belongs to the technical field of thermal barrier coating materials. The purpose of the present invention is to solve the problems that the anti-thermal radiation penetration thermal barrier coating materials prepared by the existing methods have precious metal second phases which are not only expensive but also have a large difference in thermal expansion coefficients between the metal-doped second phases and the ceramic matrix phases, resulting in the failure of thermal expansion matching of the materials at high temperatures, the metal-doped second phases have high thermal conductivities, which will increase the thermal conductivity of the composite materials and reduce their thermal protection effects during high-temperature service, and there are potential problems of interface failure in the multi-layer structure coatings. Method: First, surface pretreatment of the substrate; second, preparation of the bonding layer; third, preparation of the ceramic matrix phase components and the dispersed phase functional ceramic components; fourth, mixing and spherical granulation; fifth, preparation of the functional surface layer. The present invention can obtain an integrated thermal barrier ceramic coating with high strength and toughness / low thermal conductivity / anti-thermal radiation penetration.

Disclosed in the present invention is a spraying fixture for a combustion liner of a combustion chamber of a gas turbine, relating to the technical field of spray tooling. The spraying fixture comprises a clamping unit comprising an abutting component abutting against a port of the combustion liner, a grating component arranged at the circle center position of the abutting component, the lower end of the grating component extending to a position below the abutting component, and eight clamping members arranged on the abutting component and annularly distributed using the grating component as the circle center. The present invention can achieve stable and effective clamping of the combustion liner of the combustion chamber of the gas turbine during manufacturing for an inner surface thermal barrier coating layer, ensuring the stability thereof during spraying; furthermore, by means of a grating design, a channel for communicating the interior of the combustion liner with external air is increased, the efficiency of cooling the wall of the combustion liner is improved, and the clamping and fixing range of the device can be adjusted on the basis of the actual size of the port of the combustion liner, thereby meeting more use requirements.

The invention belongs to the technical field of nuclear power, and particularly relates to a nuclear power plant equipment coating heat conductivity coefficient prediction method and device. According to the model building disclosed by the invention, the common defects of pores and macroscopic horizontal cracks in the coating are considered, the coating is used as a tight skeleton, pore and crack three-phase composite system, and after one defect is gradually added into the substrate, the formed system becomes a new substrate in the next step. And repeating the compounding process until the two defects of pores and cracks are added into the system. Therefore, the actual operation state of the thermal barrier coating of the nuclear power equipment can be simulated more vividly. Furthermore, pore shape influence factors and crack shape influence factors corresponding to different porosities and crack rates can be determined through modeling and heat conductivity coefficient simulation calculation, and the actual heat conductivity coefficient of the coating is further predicted. And a theoretical basis is provided for researching the failure behavior of the service thermal barrier coating.

The invention discloses a double-probe film thickness and defect collaborative decoupling method. The method comprises the steps that microwave reflection signals of a thermal barrier coating are synchronously collected through a coaxial resonance probe and a CSRR resonance ring probe; the microwave reflection signal comprises reflection coefficient amplitude, reflection coefficient phase and resonant frequency; constructing a frequency deviation model based on the microwave reflection signal; training the dual-channel deep learning network based on the frequency deviation model to obtain a trained dual-channel deep learning network; and obtaining film thickness information and a defect positioning result based on the trained dual-channel deep learning network. According to the method, collaborative decoupling of the film thickness and the defect signal is achieved through a physical-data fusion method, effective decoupling and independent recognition of the coating film thickness change and the defect response signal are achieved, and the resolution ratio, the accuracy rate and the practicability of a detection system are improved.

The invention relates to the technical field of mold machining, and discloses a metal surface pretreatment system for thermal barrier coating metal mold machining, which comprises a placing part, the placing part comprises a support, and two rotating frames are rotationally connected to the support in a front-back symmetrical manner; the two rotating frames are jointly provided with a placing mechanism and an overturning part, the placing mechanism can be used for placing a mold and centering and positioning the mold, the overturning part comprises an overturning mechanism, and the overturning mechanism is installed on the support and connected with the rotating frame on the front side. The metal surface pretreatment system for thermal barrier coating metal mold machining can effectively solve the problems that in the prior art, in a continuous industrial production scene, in the process of frequently placing and positioning a mold, taking down a cleaned mold, installing a new mold and repositioning, a large amount of time is consumed, and the production efficiency is high. And the cleaning period of a single metal mold is prolonged, so that the number of the metal molds which can be cleaned within unit time and enter a thermal barrier coating spraying procedure is limited.

The invention relates to the field of suspension plasma spraying, in particular to a long-service-life suspension plasma spraying thermal barrier coating based on a platinum-aluminum coating and a preparation method of the long-service-life suspension plasma spraying thermal barrier coating. The preparation method comprises the following steps: preparing a vertical crack or columnar-like structure ceramic layer on the surface of a platinum modified aluminide bonding layer with lower roughness by using suspension slurry prepared from fully-stable tetragonal phase yttrium oxide stabilized zirconium oxide powder and adopting suspension plasma spraying suspension, so as to obtain a thermal barrier coating system with long service life. The problems that in the prior art, due to stress existing between a ceramic layer prepared through plasma spraying and a low-roughness platinum modified aluminide bonding layer, cracks are continuously formed and expanded at an interface, and the service life of a thermal barrier coating system is short are solved. The long-life thermal barrier coating system can be prepared on the platinum modified aluminide bonding layer through suspension plasma spraying.

The invention provides a CMAS corrosion resistant thermal barrier coating and a preparation method thereof.The CMAS corrosion resistant thermal barrier coating comprises a metal bonding layer, an yttria-stabilized zirconia layer and a multi-component rare earth zirconate layer, and the yttria-stabilized zirconia layer and the multi-component rare earth zirconate layer are sequentially arranged on the metal bonding layer. The multi-component rare earth cerate layer and / or the CMAS barrier layer are / is sequentially arranged on the multi-component rare earth zirconate layer; the multi-component rare earth zirconate layer comprises multi-component rare earth zirconate, the chemical formula of the multi-component rare earth zirconate is (nRE1 / n) 2Zr2O7, RE is any n of Sc, Y, La, Ce, Pr, Nd, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb and Lu, and n is not smaller than 10; the CMAS barrier layer includes an anti-corrosion oxide having an optical basicity of 0.55 to 0.68. The CMAS corrosion resistant thermal barrier coating disclosed by the invention realizes high thermal insulation, sintering resistance and CMAS corrosion resistance, reduces the surface temperature of a matrix alloy, and improves the sintering resistance and CMAS corrosion resistance of ceramics.

A thermal barrier coating (TBC) material with high fracture toughness, calcia-magnesia-alumino silicate (CMAS) corrosion resistance, and ultra-high-temperature sintering resistance, and a preparation and use thereof are provided, belonging to the technical field of high-temperature / ultra-high-temperature TBCs. In the TBC material, ZrO2 is co-doped with different rare earth oxides and a crystal defect concentration and a lattice distortion degree are controlled by a doping amount of the rare earth oxides, resulting in a fully-stabilized cubic fluorite crystal structure showing no phase change at a room temperature to 1,600° C. Moreover, the material exhibits high toughness, CMAS corrosion resistance, ultra-high-temperature sintering resistance, and long service life.

A method for testing the heat insulation performance of a thermal barrier coating comprises the following steps: preparing a set of plasma flame spraying equipment, preparing a metal sheet, and spraying the thermal barrier coating on the surface of the metal sheet to prepare a coating sample; preparing a high-temperature electric furnace and an aluminum oxide fiberboard with the same size as a furnace door brick, embedding the metal sheet into the aluminum oxide fiberboard, and exposing the coating surface and the back surface of the metal sheet; opening a furnace door of the high-temperature electric furnace, sealing the furnace door by using the cut aluminum oxide fiber plate as a furnace door brick, and embedding the metal sheet into the aluminum oxide fiber plate in the direction that the coating surface faces the interior of the furnace; setting a heating program of the electric furnace to heat the electric furnace to a temperature required to be tested; testing the temperature of the back surface, exposed in the air, of the metal sheet by using a laser thermometer; the steps are repeated for multiple times, the difference value between the furnace temperature and the back temperature is recorded, and the average value is calculated and can serve as the judgment basis of the heat insulation performance of the thermal barrier coating. The method is simple and convenient to operate, accurate in test condition and high in practical application value.

The invention discloses a high-entropy rare earth tantalate ceramic with ultralow transmittance / broadband high emissivity and a preparation method of the high-entropy rare earth tantalate ceramic, and belongs to the technical field of thermal barrier coating materials. The invention aims to solve the problems that the existing rare earth tantalate ceramic material is insufficient in thermal radiation penetration resistance and poor in infrared radiation performance, and the thermal conductivity is too high due to doping of transition group ions and a second phase. The phase composition of the high-entropy rare earth tantalate ceramic with ultralow transmittance / broadband high emissivity is (4RE < 0.2 > Gd < 0.2 >) 3TaO7, RE is a combination of any four elements of Pr, Nd, Sm, Eu, Tb, Dy and Y, and the molar ratio of the four elements to Gd is 1: 1: 1: 1: 1. According to the prepared high-entropy rare earth tantalate ceramic, the near-infrared band transmittance is smaller than 3%, the emissivity is larger than 0.9, the high-temperature emissivity is larger than 0.75, and the heat conductivity at the high temperature is smaller than 1.3 W.m <-1 >. K <-1 >.

The invention discloses an electron beam physical vapor deposition device for preparing a thermal barrier coating and a method for preparing the thermal barrier coating, the device has the advantages of being simple in structure, easy to overhaul, long in service life and high in power density, and the thermal barrier coating which is uniform in columnar microstructure and excellent in overall performance can be prepared through the device. And the preparation requirements of high performance and high stability of the thermal barrier coating are met.

The invention discloses a thermal barrier coating anti-CMAS method and system based on a double-hybrid data model, and the method comprises the steps: building a simulated rare earth element doped thermal barrier coating, and manufacturing a rare earth element doped thermal barrier coating with the same content; performing high-temperature simulation on the simulation coating, performing high-temperature treatment on the real coating, and obtaining time-domain data representing the corrosion degree of the thermal barrier coating CMAS through a terahertz time-domain spectroscopy technology; performing data preprocessing on the terahertz time-domain spectroscopy data set, and performing feature extraction on the preprocessed data by using a machine learning and signal processing combined method to obtain a double-hybrid data feature set; and importing machine learning according to the data contribution degree on the basis of the obtained double-mixed data feature group, constructing an anti-CMAS performance characterization model of the rare earth element doped thermal barrier coating, and reducing errors caused by data by using a model loss function. The double-mixed data model is used for representing the CMAS corrosion resistance of the thermal barrier coating in the high-temperature service environment.

The invention discloses a double-ceramic-layer thermal barrier coating of a differentiated columnar crystal structure and a preparation method, and belongs to the technical field of thermal barrier coating corrosion and protection. The invention innovatively discovers and utilizes the double influence of the columnar crystal size on the performance of the coating; the YSZ layer adopts a fine grain structure of 1-1.5 microns, so that the bonding strength and thermal shock resistance of the coating can be obviously improved; and the modified gadolinium zirconate layer adopts a 2-3 [mu] m coarse grain structure, so that the heat conductivity can be reduced, the permeation path of CMAS along a grain boundary can be effectively inhibited, and meanwhile, the modified gadolinium zirconate layer reacts with CMAS to form a compact barrier layer to prevent further permeation of CMAS. Through accurate regulation and control of electron beam physical vapor deposition (EB-PVD) process parameters, differential control of the sizes of the two layers of ceramic columnar crystals is realized, and under the synergistic effect of the two columnar crystal structures with different sizes, the thermal cycle life and CMAS corrosion resistance of the whole coating system in an ultra-high-temperature environment are remarkably prolonged and improved.

The invention relates to the technical field of thermal barrier coatings, in particular to a gadolinium oxide and aluminum oxide co-doped modified YSZ: Dy thermal barrier sensing coating material as well as a preparation method and application thereof. The invention provides a thermal barrier sensing coating material. The chemical composition of the thermal barrier sensing coating material is Y Gd Al < c > Zr < d > DeyOf, wherein a is equal to 0.01 to 0.04, b is equal to 0.15 to 0.35, c is equal to 0.40 to 0.60, d is equal to 0.35 to 0.70, e is equal to 0.01 to 0.02, and f is equal to 1.50 to 1.70. The temperature measurement upper limit of the thermal barrier sensing coating material is 1200 DEG C, and the average thermal expansion coefficient is increased by 18% at the room temperature of 1200 DEG C, so that the thermal shock resistance of the thermal barrier sensing coating is effectively improved, and the service life of the thermal barrier sensing coating is prolonged.

The application belongs to the field of turbine blade thermal barrier coating of an aero-engine. Specifically, it is a structure design, a preparation method and a prepared coating of a double-layer radiation-resistant thermal barrier coating with a high-reflection layer and a high-absorption layer. The coating comprises a high-absorption layer and a high-reflection layer. The high-absorption layer can absorb part of the energy of photon radiation and re-emit it into the environment, while relying on a cooling gas film to quickly remove heat. Part of the energy of the photon radiation is reflected by the high-reflection layer again to the high-absorption layer after passing through the high-absorption layer, and the process of absorption-emission-cooling gas film heat dissipation is repeated. Within a set temperature range, the absorption rate of the high-absorption layer is determined based on the temperature difference requirement between the inner and outer surfaces of the thermal barrier coating, and the high-absorption layer material is determined based on the absorption rate. The application greatly reduces the radiation heat flow penetrating the coating, avoids the direct heating of the high-temperature alloy by infrared radiation, and significantly improves the heat insulation capacity of the thermal barrier coating and the service life of the turbine blade.

The utility model discloses a thermal barrier coating material fixing device which comprises a fixing device body, a fixing frame is arranged at the top of the fixing device body, a fixing piece is fixedly installed at the end of the fixing frame, a fixing block covers the surface of the fixing piece, and meanwhile a first support is fixedly welded to the bottom of the fixing frame. Supporting columns are fixedly welded to the ends, away from the fixing frame, of the first supports. According to the thermal barrier coating material fixing device, the thermal barrier coating material covers the three groups of fixing pieces on the surface of the fixing frame, and the thermal barrier coating is adsorbed and fixed on the surface of the fixing frame through the three groups of fixing blocks, so that the thermal barrier coating cannot fall off from the surface of the fixing frame when being tested; the fixing device bodies can be combined together to test a plurality of groups of thermal barrier coating samples, and the plurality of groups of fixing device bodies can be tightly concentrated together, so that more space is saved, and centralized management is facilitated.

The application provides a heat insulation performance testing device for thermal barrier coating, which comprises a hollow cavity with a through mold loading groove, a cylindrical graphite mold placed in the mold loading groove, and a temperature rising device and a first temperature measuring device which are opposite to each other and face one end surface of the cylindrical graphite mold; wherein one end surface of the cylindrical graphite mold is sprayed with a thermal barrier coating to be measured, and the side surface of the cylindrical graphite mold is sprayed with a heat insulation coating. The heat insulation condition of the heat insulation performance testing device for thermal barrier coating is set by spraying the heat insulation coating on the side surface of the graphite mold, and the heat insulation condition is set ingeniously so that the device can meet the Fourier heat transfer law under one-dimensional condition as much as possible, unnecessary heat escape is avoided, the heat flow on the coating surface completely realizes conduction to the back of the substrate, and thus, the measurement error caused by neglecting is avoided, and the result is accurate and reliable.

The invention discloses a method for predicting surface erosion characteristics and temperature distribution of a thermal barrier coating based on numerical simulation. The method comprises the steps of establishing a grid model, establishing an erosion model considering dynamic physical property changes of the coating, establishing a thin-wall thermal resistance model supporting the dynamic thickness of the coating, setting a time amplification factor and the like. The characteristics that the porosity, Young modulus, Vickers hardness and other physical properties of the coating change along with the service time are considered. And in combination with a thin-wall thermal resistance model considering the dynamic thickness of the coating, the erosion characteristic of the coating surface and the temperature distribution condition of the coating surface at any moment in the future are quickly predicted and obtained. The method has the advantage of high simulation precision in coating erosion prediction. According to the method, the wall surface erosion characteristics and thermal barrier coating surface temperature distribution caused after erosion can be predicted, so that the service life conditions of different device surface coatings are effectively predicted, and reliable data support and guidance are provided for design of a thermal protection system and timely replacement of equipment.

The invention relates to a combustion system, an engine and a vehicle. The combustion system comprises an air inlet channel, an exhaust channel, an air inlet valve, an exhaust valve, a cylinder cover, a cylinder sleeve and a piston, a cylinder cover combustion chamber is arranged in the combustion system, and at least one of the inner surface of the cylinder cover combustion chamber, the surface, facing the interior of the combustion system, of the air inlet valve, the surface, facing the interior of the combustion system, of the exhaust valve and the top surface of the piston is provided with a thermal barrier coating.

The invention discloses a high-entropy ceramic thermal barrier coating and a preparation method thereof, and relates to the technical field of thermal barrier coating materials. The method comprises the following steps: mixing ZrO2, HfO2, Ta2O5 and various rare earth oxides, and carrying out high-energy wet ball milling, drying, solid solution sintering and crushing to prepare submicron high-entropy ceramic powder; mixing the modified powder with aluminum sol obtained by hydrolyzing aluminum isopropoxide, rare earth nitrate and the like, dispersing, drying and carrying out heat treatment to obtain modified powder coated with aluminum oxide nanoparticles on the surface; carrying out spray drying granulation to obtain spherical agglomerated powder; and finally, a DD6 single-crystal high-temperature alloy matrix is subjected to sand blasting and pre-oxidation treatment, agglomerated powder is deposited on the surface of the matrix through a plasma spraying vapor deposition technology, a columnar crystal coating is formed, and a finished product is obtained through vacuum annealing. The coating prepared through the method is uniform in structure and high in bonding strength, thermal shock resistance and high-temperature phase stability are remarkably improved, and the coating is suitable for surface protection of aero-engine hot end components.