626 results about "Thermal barrier coating" patented technology

The invention discloses a terahertz-based curved surface thermal barrier coating nondestructive thickness measurement system and method, and the method comprises the steps: firstly carrying out the coordinate calibration and reverse reconstruction of a sample piece and a mechanical arm through an optical scanning and trinocular vision measurement system, and building a virtual space; then matching the virtual space with the actual space, extracting a normal vector of the curved surface of the sample piece, performing path planning on the mechanical arms to generate a control script, and controlling the double mechanical arms to carry a terahertz measuring head to scan the sample piece in a manner of being vertical to the surface of the sample piece to obtain a terahertz signal; and finally, constructing a terahertz signal analytical model, optimizing terahertz simulation signal parameters through a self-adaptive teaching and learning optimization algorithm, and fitting a detection signal until an optimal solution is obtained, namely the thickness of the thermal barrier coating. According to the invention, through cooperation of the two mechanical arms and path planning, rapid detection of a complex curved surface structure is adapted; by establishing an analytical model and combining with an optimization algorithm, the detection precision is improved, and high-precision nondestructive detection suitable for a complex curved surface structure is realized.

The invention discloses a thermal barrier coating multi-dimensional terahertz nondestructive testing method and system based on an adaptive optimization mechanism, and the method comprises the steps: constructing a matrix sample library, and preparing thermal barrier coating samples with different thicknesses, porosities and uniformity; obtaining terahertz detection data of three dimensions of geometric dimension stability, microstructure integrity and material structure uniformity of the thermal barrier coating; establishing a multi-parameter correction model based on surface roughness, and performing feature extraction, fusion analysis and error compensation on the detection data by adopting a multi-modal integration algorithm; an adaptive optimization model is established through a deep learning algorithm, and continuous iterative optimization of the detection system is realized in combination with a feedback correction mechanism; the method is applied to an engine blade thermal barrier coating, an actual blade coating is detected, detection data are collected for system optimization, system parameters and models are updated, and system applicability and robustness are improved. The method can be widely applied to the field of nondestructive testing of coating structures such as aero-engine blade thermal barrier coatings.

The invention discloses a crack propagation simulation analysis method based on a real-structure thermal barrier coating under cyclic load, which comprises the following steps: creating a finite element model according to a thermal barrier coating sample; setting material attributes and section characteristics in the finite element model; after parameters are set, a thermal cycle load is applied to the surface of the finite element model, analysis is carried out after grid division, and an Odb file is obtained; and copying the finite element model, taking the Odb file as a boundary condition, and carrying out thermal-mechanical coupling to obtain thermal stress and crack expansion conditions after thermal circulation. The analysis method is simple, the real service condition and the microstructure are fitted, the expected research effect is achieved for finite element simulation, and accurate simulation data can be obtained.

The invention belongs to the technical field of thermal barrier coatings, and provides an artificial preparation method of multi-scale aero-engine environment sediment particles. The preparation method comprises the following steps: grinding CMAS original powder into mixture powder; calculating the mass of the required mixture powder according to the powder density of the CMAS original powder and the particle size of the target sediment particles; weighing the mixture powder, and pressing the mixture powder into sheets; in an air suspension furnace, tabletting and melting the mixture powder into balls by adopting a laser; and rapidly cooling to normal temperature to obtain the target sediment particles with the target particle size. The melting process of the CMAS powder is greatly improved, the gas suspension furnace and the laser are used for heating, single CMAS particles with the designed size can be obtained in a short time, the preparation time is shortened, and the preparation cost is effectively reduced.

The invention discloses an in-situ characterization method for fracture toughness of a high-temperature interface of a thermal barrier coating, which comprises the following steps: taking a metal test piece with the thermal barrier coating as a sample to be tested, spraying NiAl on the surface of a ceramic layer in the thermal barrier coating to serve as a buffer layer, then spraying a reinforcing layer, and forming a mixed reinforcing layer with the buffer layer; a three-point bending experiment is carried out on a to-be-tested sample at 1000-1400 DEG C by using a three-point bending device with a digital image correlation method in-situ observation function, and the three-point bending process is recorded in real time. A strain cloud picture of an observation area is obtained through a digital image correlation method, parameters are obtained from the strain cloud picture, and the interface critical energy release rate and the stress intensity factor of a three-point bending experiment are calculated and are both in direct proportion to the high-temperature interface fracture toughness of the thermal barrier coating. Therefore, in-situ characterization of the interface fracture toughness of the thermal barrier coating can be realized in a high-temperature environment of real service of the thermal barrier coating, test data can be accurately acquired in real time, and the test period is short.

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 discloses a system and a method for evaluating the thermal insulation effect of a thermal barrier coating of a turbine blade in a rotating state, the system comprises a service environment simulation unit, a temperature field measurement unit and an evaluation unit, and the service environment simulation unit comprises a turbine blade test piece and a gas spray gun; the temperature field measuring unit comprises an infrared thermal imaging module and a thermocouple module, the thermocouple module comprises a thin film thermocouple and a miniature thermocouple, and the thin film thermocouple is arranged between the blade and the thermal barrier coating and used for obtaining a temperature field of an interface; the micro thermocouple is arranged on the surface, away from the blade, of the thermal barrier coating and used for obtaining a temperature field of the surface of the thermal barrier coating; the evaluation unit evaluates the thermal insulation effect of the thermal barrier coating according to the temperature measurement result. The real service environment of high-temperature and high-speed rotation of the thermal barrier coating of the turbine blade can be simulated, the surface of the thermal barrier coating is heated in an annular gas flame mode, the high-power and high-speed motor is adopted to drive the turbine blade to rotate at a high speed, and real-time temperature measurement in the high-speed rotation state is achieved.

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 a method for predicting the penetration behavior of fused CMAS of a zirconia-based thermal barrier coating, and the method is used for predicting the penetration behavior of the fused CMAS in the coating based on the microstructure characteristics of the coating. Comprising the following steps: preparing a thermal barrier coating and summarizing microstructure characteristics of the coating; establishing a numerical model on the basis of the microstructure characteristics of the coating, and carrying out grid division in COMSOL Multiphysics; establishing a constitutive equation for reflecting the relationship among the permeation time-porosity-permeation path complexity-permeation contact angle of the internal fusion CMAS of the coating; the constitutive equation is substituted into COMSOL Multiphysics, and parameter setting is carried out on the constitutive equation; and calculating a structure and post-processing. According to the method, the dynamic permeation process of the thermal barrier coating under CMAS corrosion can be nondestructively detected, and guidance is provided for improving the CMAS permeation resistance of the thermal barrier coating through microstructure regulation and control.

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 relates to a thermal barrier coating thermodynamic coupling field synchrotron radiation in-situ characterization device which comprises a base and a stretching instrument, a heating device, a cooling device and a powder feeding device which are arranged on the base, the stretching instrument is used for applying a stretching load to a sample, the heating device is used for heating the sample, and the cooling device is used for cooling the sample. The cooling device is used for cooling the back surface of the sample, so that the temperature of the back surface of the sample is lower than that of the front surface of the sample, and the interior of the sample has a temperature gradient; the powder feeding device is used for providing powder for the sample, so that the sample is in a powder corrosion state. According to the thermal barrier coating thermodynamic coupling field synchrotron radiation in-situ characterization device, the high temperature, thermal gradient, tensile load and corrosion service environment of a thermal barrier coating can be simulated at the same time, and the thermal barrier coating thermodynamic coupling field synchrotron radiation in-situ characterization device is very close to the real service environment.

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.

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

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.

There is provided a method of manufacturing a component of a gas turbine engine, comprising: providing a precursor component having at least one internal cooling passage configured to receive a flow of cooling air therethrough; estimating a predicted temperature profile for the component based on one or more operating parameters of the gas turbine engine, the predicted temperature profile indicating a predicted operating temperature of at least one gas-washed surface of the component; determining a thermal barrier coating (TBC) configuration for the component based on the predicted temperature profile, comprising setting a TBC thickness to be below a threshold thickness in a region of the at least one gas-washed surface of the component based on the predicted operating temperature of the at least one gas-washed surface of the component exceeding a threshold temperature; and applying a TBC to the precursor component according to the TBC configuration.

The invention provides a film hole machining method and device for a blade with a thermal barrier coating, and the machining method comprises the following steps: S1, the blade with the thermal barrier coating is fixed, the thermal barrier coating at the punching part is removed by using femtosecond laser, the surface of a blade body is exposed, the incident angle alpha of the femtosecond laser is larger than or equal to 30 degrees and larger than or equal to 15 degrees; s2, direct punching is conducted on the punching part through millisecond laser, a blind hole is formed in the blade body, the incident angle of the millisecond laser is beta, and beta-alpha is larger than or equal to 5 degrees and smaller than or equal to 20 degrees; s3, the bottom hole is punched in a mechanical drilling mode, and a through hole is formed; and S4, the hole wall is trimmed through an electro-hydraulic beam, and the air film hole is obtained through machining. According to the air film hole machining device, the technology of double-laser machining, mechanical drilling and electro-hydraulic beam hole repairing is adopted, the machining efficiency and quality of the air film hole are effectively improved, it is ensured that the machined air film hole meets the requirements in the aspects of size precision, surface quality and the like, and the high-quality air film hole can be efficiently obtained.

The invention discloses a thermal barrier coating resistant to high-temperature oxidation and a preparation method thereof, and relates to the technical field of thermal barrier coating materials. According to the preparation method, a NiCoCrAlYHfRu coated coating is prepared on a high-temperature alloy by adopting arc ion plating equipment, and a YSZ / LaZrCeO ceramic surface layer is prepared by adopting electron beam physical vapor deposition equipment. The thermal barrier coating prepared through the technology has a unique columnar crystal structure and meanwhile has good thermal cycle performance. Finally, the anti-oxidation and anti-corrosion requirements of the turbine blade can be met; and the process is simple, industrial production is easy to achieve, and the composite coating is excellent in performance, has application prospects and is suitable for the high-temperature alloy.

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 provides a self-repairing thermal barrier coating for a gas turbine working blade. The coating structurally comprises an MCrAlY metal bonding layer, a TiC-Al2O3-YSZ self-repairing transition layer and a YSZ ceramic layer. The thermal barrier coating not only has a high thermal insulation effect and good high-temperature oxidation resistance, but also has very good capability of resisting rapid diffusion of cracks. The preparation method comprises the following steps: preparing the MCrAlY coating by adopting a hypersonic flame spraying method, preparing the TiC-Al2O3-YSZ self-repairing transition layer by adopting a plasma spraying method, and preparing the YSZ ceramic layer by adopting the plasma spraying method or an electron beam physical vapor deposition method. The method is simple, and the uniform and stable thermal barrier coating can be prepared. The thermal barrier coating is applied to the surface of the turbine working blade of the gas turbine, the surface temperature of the turbine blade can be effectively reduced, the service life of the blade is prolonged, and the overhaul and replacement cost caused by early falling of the coating is reduced.

The invention relates to the field of nondestructive testing, and discloses an aero-engine blade in-service in-situ video eddy current infrared detection system and a detection method, which are characterized in that a multi-mode detector and an integrated detection probe are designed, an endoscopic video head is adopted to acquire complex internal conditions of an engine, the probe is assisted to stretch in, and an eddy current detection coil assembly works in a time-sharing and multi-mode manner; different detection modes and heating functions are switched by applying a combined excitation signal, the eddy current detection coil and the eddy current heating coil which are in a flat transparent flexible film shape are adopted to conformally fit the surface of a to-be-detected blade for eddy current detection, the shielding influence of the coils on infrared thermal imaging signals obtained by a miniature infrared camera is reduced, and the detection accuracy is improved. And the precision of an infrared thermal imaging signal is improved. According to the invention, high integration of video, eddy current and infrared sensors is realized, the probe is miniaturized, and in-service in-situ detection of various defects at the same fixed point position on a thermal barrier coating of an aero-engine blade is realized.

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 discloses a low-thermal-conductivity anti-sintering thermal barrier coating material as well as a preparation method and application thereof, and belongs to the technical field of coating materials. The low-thermal-conductivity anti-sintering thermal barrier coating material comprises a base phase oxide (ZrO2), four groups of solid solution doped rare earth oxides (Y2O3, Yb2O3, Gd2O3 and Nd2O3) and a group of second phase doped oxides (Al2O3), the four groups of solid solution doped rare earth oxides exist in ZrO2 in a solid solution form to form a ZrO2 solid solution, and Al2O3 is doped in the ZrO2 solid solution in a second phase form; wherein the ion radiuses and cation valences of Yb2O3, Gd2O3 and Nd2O3 are different from the cation radiuses and valences of the base phase oxide or the main stable oxide (Y2O3). The low-heat-conduction anti-sintering thermal barrier coating material is sprayed on the surface of a base body or other coatings, and compared with a coating formed by a traditional YSZ material, the formed thermal barrier coating has the low heat conduction performance and the anti-sintering performance.