CN102788811B - Method for predicting temperature range of high-temperature alloy coating of segment of blading of gas turbine - Google Patents
Method for predicting temperature range of high-temperature alloy coating of segment of blading of gas turbine Download PDFInfo
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Abstract
A method for predicting temperature range of a high-temperature alloy coating of a segment of blading of a gas turbine belongs to the technical fields of service life prediction of hot parts of gas turbine and service state monitoring of surface coating. According to the invention, experiments and numerical calculation are combined to determine tissue change of the coating, so as to obtain a size L of an internal diffusion tissue in the coating; the L is substituted into a life prediction calculation model to predict a temperature, so as to carrying out temperature prediction on surface coating of the segment of blading of the gas turbine after service; meanwhile, temperature of the high temperature alloy matrix material is calculated out according to an aerodynamic heat value, a transfer value and a strength value; and a coating calculation temperature is obtained by temperature correction, and is then compared with an experimental temperature of the coating, so as to obtain a coating temperature closer to an actual working environment, and provide temperature parameters for further life prediction.
Description
Technical field
The present invention relates to the Forecasting Methodology in rear alloy coating at high temperature life-span of a kind of gas turbine hot-end component military service, relate in particular to operation and the disposal route of temperature prediction.
Background technology
In turbine blade of gas turbine, moving vane adopts Ni based high-temperature alloy, in several large mainly E levels that Ran Ji manufacturer manufactures, F level unit, on movable vane, has used anti-oxidation and antisepsis erosion resisting coating.Coating is mainly MCrAlY high-temperature oxidation resistant tack coat, play anti-oxidant and etch-proof effect, along with gas turbine unit inlet temperature rising turbine blade surface also can apply YSZ (yttria-stabilized zirconia) coating, play the effect of isolated temperature, part of generating units floating coat also can apply aluminized coating, improves oxidation resistance.Typical thermal barrier coating system is by being coated on MCrAlY on matrix (M=Ni, Co or the two have concurrently) high-temperature oxidation resistant tack coat and with Y
2o
3partially stabilized ZrO
2for the ceramic with heat resistance top layer composition (as shown in Figure 5) of principal ingredient.In high-temperature oxidation process, between high-temperature oxidation resistant tack coat and ceramic with heat resistance layer, can form one deck thermal growth oxide (TGO), stop oxygen further to spread, play the effect that protection matrix material does not weather.But TGO thickness increases the stress producing and will directly cause germinating and the expansion of crackle, cause disbonding to lose efficacy, and coating disappear effectively mutually and lose the function that anti-oxidation and antisepsis loses.Therefore, the oxidation rate of tack coat becomes affects one of the key issue in coating serviceable life.Gas turbine is in order to obtain more high-level efficiency, the temperature of turbine and cooling technology development, the Service Environment of moving vane is more and more severe, high maintenance and renewal cost make user more and more be concerned about the military service situation of unit, wish forwardly to obtain more advanced coating, the Forecasting Methodology of substrate temperature and Prediction Method of Coating Film Life more accurately.
In military service process, turbine blade need to keep certain intensity and mechanical property, and along with fuel gas temperature raises, metal temperature of being on active service steady in a long-term has reached ultimate value, reach and reduce blade surface and inner serviceability temperature by the different types of cooling, keep the superior function of metal; In order to improve its resistance to high temperature oxidation and corrosion resistance, the each main production of gas turbine and design manufacturer carry out Cooling Design and coating protection to blade, and the cooling effect of part of generating units has reached requirement, is coated with high-temperature oxidation resistant tack coat on surface.
All there is the inside and outside diffusion of aluminium element in process in high-temperature oxidation resistant tack coat, forms the aluminium oxide of one deck densification under arms on top layer, stops oxygen atom to continue diffusion, the proportional routine relation of the variation in thickness of aluminium oxide and the time of military service and temperature.Oxide components and oxidated layer thickness be two of coating service life important affect parameter, therefore obtain the actual service temperature of coating more accurately and just can obtain the safety in utilization of coating, have great importance for research coating life.
Summary of the invention
The object of this invention is to provide a kind of Forecasting Methodology of gas turbine turbine blade alloy coating at high temperature service temperature, solve the oxidation deactivation monitoring problem that alloy coating at high temperature easily appears in process in turbine engine high-temperature component under arms, obtain the actual service temperature of alloy coating at high temperature more accurately, thereby improve the security of alloy coating at high temperature and unit use.
In order to realize above-mentioned object, technical scheme of the present invention is as follows;
A Forecasting Methodology for gas turbine turbine blade alloy coating at high temperature service temperature, is characterized in that the method comprises the following steps:
1) need the enterprising line cutting of predicted temperature place xsect at turbine blade blade position, prepare sample, adopt destructive metallographic analysing method to obtain the rear internal divergence layer tissue size L of sample location coating military service;
2) by life prediction formula
Obtain the coating experimental temperature T of diffusion layer interface in alloy coating at high temperature
o, in formula: Q is energy of activation constant, K
0for chemical reaction rate constant, Q and K
0relevant with coating service state with coating composition, preparation technology, obtain parameter by oxidation experiment under different temperatures; R is gas law constant; T is the T.T. of unit operation after being on active service, L
0for diffusion layer in the coating of original state before being on active service is organized size;
3) for turbine blade Service Environment and thermal boundary condition, by means of ABAQUS finite element analysis software, blade is carried out to temperature field analysis, obtain any position high temperature alloy matrix mother metal temperature distribution history, thereby obtain arbitrfary point matrix accounting temperature T
1;
4) utilize T
0'=T
1+ δ, to matrix accounting temperature T
1revise, obtain alloy coating at high temperature accounting temperature T
0', wherein δ span is 2～10 DEG C;
5) alloy coating at high temperature accounting temperature T
0' and alloy coating at high temperature experimental temperature T
0compare, if T
0<T
0', experimental temperature herein will be lower than coating accounting temperature, and coating is in safety zone, with T
0' as alloy coating at high temperature service temperature; If T
0≤ T
0', experimental temperature will be higher than coating accounting temperature herein, and coating is under higher service temperature, with T
0as alloy coating at high temperature service temperature.
Alloy coating at high temperature of the present invention is the nearly surface coating of matrix, and alloy coating at high temperature experimental temperature is alloy coating at high temperature and basal body interface place temperature; For coating, ablation or hot corrosion phenomenon have occurred, when in coating, diffusion layer organizes size to measure, alloy coating at high temperature experimental temperature adopts the alloy coating at high temperature at alloy coating at high temperature close positions place and the experimental temperature at basal body interface place to be replaced.
Internal divergence layer tissue size L of the present invention, refer to the region of aluminium element, chromium Elements Diffusion and variation in complete reservation coating, wherein L is of a size of to adopt and in 5mm length range, takes continuously 5～10 metallographs, measures 50～100 measured values and gets its mean value.
Alloy coating at high temperature of the present invention is MCrAlY coating, MCrAlY+ aluminized coating or MCrAlY+TBC layer.
The present invention has the following advantages and high-lighting effect: 1. unit is under arms in process, due to turbine blade operation characteristic, be difficult to realize real time temperature monitoring, be difficult to turbine blade life-span and running status to assess, and the height of coating service temperature directly affects the oxidation of turbine blade surface high-temp alloy coat, hot corrosion and matrix mechanical property to change, therefore, obtain turbines vane alloy coating at high temperature service temperature accurately, have great importance for the life prediction of blade.The alloy coating at high temperature temperature that experimental technique and computing method obtain, by mutual contrast, finds the numerical value that more can represent the actual service temperature of blade and coating, can provide service temperature more accurately for coating life prediction.2. in document and patented technology in the past, to the service temperature of alloy coating at high temperature, means by metallographic examination obtain accounting temperature, its accuracy is not analyzed, cannot prove the service temperature that it represents blade alloy coating at high temperature reality, by operation of the present invention, introduce modified value δ, utilize alloy substrate accounting temperature prediction alloy coating at high temperature accounting temperature, the accounting temperature of coating and experimental temperature are contrasted, can obtain the temperature closer to actual service state, judge the security of alloy coating at high temperature.3. determining about modified value δ, heat conduction based on alloy coating at high temperature is uniform, under identical Service Environment, the Temperature Distribution of coating is similar, by summary of experience and data accumulation, can adjust δ value, there is different δ values in different temperature prediction points, monitors by the temperature prediction position of key area, ensure that damaging does not appear in blade position dangerous position, can ensure that other position of blade is not dangerous.
Brief description of the drawings
The MCrAlY coating of Fig. 1 band aluminized coating is organized and is changed schematic diagram after being on active service.
Fig. 2 model gas turbine Bucket1 one-level movable vane coating electromicroscopic photograph.
Fig. 3 model gas turbine Bucket2 one-level movable vane coating electromicroscopic photograph.
Fig. 4 model blade matrix accounting temperature and coating experimental temperature comparison diagram.
The temperature contrast schematic diagram of Fig. 5 Heat insulation with ceramic coatings effect and matrix and coating.
Embodiment
The Forecasting Methodology of a kind of gas turbine turbine blade alloy coating at high temperature service temperature provided by the invention, it is below embodiment:
1) need the enterprising line cutting of predicted temperature place xsect at turbine blade blade position, can carry out sample analysis to turbine blade blade optional position, prepare sample, what adopt that destructive metallographic analysing method obtains internal divergence layer in sample location coating organizes size L;
In order to realize above-mentioned target, blade height is chosen and should be followed using platform area surface level as datum line, platform area leading edge locus is as initial point, carry out vertical survey along leading edges line to leaf top leading edge, to highly carrying out ten deciles, integral shroud is as blade 100% position, choose equally trailing edge position, platform area as initial point, carry out vertical survey along trailing edge edge line to leaf top trailing edge, same decile height, the sampling spot of equal height is connected with straight line, as the cutting planes of line cutting, can obtain the sampling cross section of arbitrary height, in sampling cross section, choose diverse location and carry out temperature prediction, generally, at least to get 4 positions, comprise leading edge, trailing edge, in the middle of pressure face and in the middle of suction surface.The predicted temperature of coating sampling is regional area, for ensureing the accuracy of its prediction, and the coating surface of the scope of measurement within the scope of 5mm.Prepare sample, by the internal divergence layer tissue size at backward scattering scanning electron microscope observation alloy coating at high temperature and basal body interface place, adopt statistical method to measure the mean value of internal divergence layer L.Internal divergence layer tissue size L, refers to the region of aluminium element, chromium Elements Diffusion and variation in complete reservation coating, and wherein L is of a size of to adopt and in 5mm length range, takes continuously 5～10 metallographs, measures 50～100 measured values and gets its mean value.
2) by life prediction formula
wherein Q is energy of activation constant, K
0for chemical reaction rate constant, derive coating service temperature, Q and K
0with coating composition, preparation technology is relevant with coating service state, can obtain by high-temperature oxydation experiment under different temperatures; R is gas law constant; T is the T.T. of unit operation after being on active service, L
0for thickness of diffusion layer in the coating of original state before being on active service.
In order to realize above-mentioned target, need to characterize the alloy coating at high temperature metallographic structure of military service rear blade, with reference to the requirement of technical scheme 1, obtain internal divergence layer tissue size L, secondly determine the character of alloy coating at high temperature, comprise kind and the tissue inter-variable of alloy coating at high temperature, and the preparation technology of alloy coating at high temperature, determine Q value and the K of alloy coating at high temperature
0value, coating performance difference, preparation technology's difference, Q value and K
0value differs greatly.Alloy coating at high temperature after part is on active service is owing to being subject to the situations such as hot corrosion, oxidation and ablation, feature organization is destroyed, cannot carry out experimental temperature prediction, more than temperature herein may be defined as dangerous temperature, coating lost efficacy, also can adopt following principle, organize size to measure for diffusion layer in alloy coating at high temperature, alloy coating at high temperature predicted temperature adopts the alloy coating at high temperature at alloy coating at high temperature close positions place and the experimental temperature at basal body interface place to be replaced.
3) in order to obtain substrate temperature distribution curve, need to carry out following steps: calculate thermal boundary condition by CFD flow field analysis software, comprise near the fluid temperature (F.T.) of blade wall and convection transfer rate, utilize interpolation software FSI that the grid of CFD flow field analysis is corresponding with CALCULATION OF THERMAL grid in ABAQUS, after coordinate conversion, near fluid node temperature the data a large amount of wall that CFD flow field analysis is obtained are converted into surface temperature value, by ABAQUS finite element analysis software, blade is carried out to temperature field analysis, obtain the Temperature Distribution cloud atlas of blade surface, pass through value, can obtain the temperature distribution history of the high temperature alloy matrix mother metal of optional position or arbitrary section, thereby obtain the matrix accounting temperature T of arbitrfary point
1.
4) in order to obtain the accounting temperature T of alloy coating at high temperature
0', according to formula T
0'=T
1+ δ, to matrix accounting temperature T
1revise, obtain alloy coating at high temperature accounting temperature T
0', wherein δ span is 2～10 DEG C.δ is the difference of the accounting temperature of matrix accounting temperature and alloy coating at high temperature, the principle of determining this difference is between alloy coating at high temperature and matrix, to have heat conduction uniformly, consider the effect of heat insulating coat and combustion gas in actual service state simultaneously, try to achieve δ difference in the reasonable scope, obtain the alloy coating at high temperature temperature after prediction, measure coating temperature with metallographic destructive test and compare;
5) in order to obtain the actual service temperature of alloy coating at high temperature, need to be by alloy coating at high temperature accounting temperature T
0' and alloy coating at high temperature experimental temperature T
0compare, if the alloy coating at high temperature temperature T obtaining
0<T
0', showing that experimental temperature will be lower than calculating coating temperature herein, coating is in safety zone, with T
0' as predicted temperature, bring Life Prediction Model into, prediction coating residual life, can obtain minimum safe range; If there is T between alloy coating at high temperature experimental temperature and accounting temperature
0≤ T
0', show that coating experimental temperature will be higher than coating accounting temperature, with coating experimental temperature T herein
0bring in Life Prediction Model, the life prediction result of acquisition is used residual life closer to alloy coating at high temperature.
Different turbines vane alloy coating at high temperature differences, revise δ difference difference, for there being the alloy coating at high temperature destroying, if adopt nearby principle and measurable principle to obtain approaching coating experimental temperature, generally, leading edge locus is selected the coating test temperature near pressure face one side, and trailing edge position selects a side coating experimental temperature of close suction surface as danger position coating experimental temperature.
6) described alloy coating at high temperature is MCrAlY coating, MCrAlY+ aluminized coating or MCrAlY+TBC layer.
Feature of the present invention and advantage will be elaborated by embodiment and accompanying drawing.Carry out verification experimental verification for certain model gas turbine turbine one-level movable vane after being on active service, choosing blade 60% position sample is example, and this model unit one-level movable vane surface coating is MCrAlY high temperature alloy layer, outer one deck aluminized coating that applies.
EXAMPLE l:
The history run record of blade Bucket1, total run time is more than 30500 hours, and heavy oil operation is more than 25000 hours, and after 24000 hours, coating is repaired again, ignition trigger 1798 times, blade unloads after being on active service, and effects on surface carries out macro check, and blade surface forms serious dirt because of burning heavy oil, after cleaning, find, there is ablation vestige in the trailing edge of blade 50%～60% position, for the tissue of further analyzing coating changes and predicted temperature, has carried out destructive detection.
For protection alloy coating at high temperature primary morphology is not destroyed in preparation process, adopt gentle chemical nickel plating method to protect coating, after surface deposition nickel coating, heat edge sample, prepare polishing after sample, be dried and the processing of spray carbon, backward scattering observation alloy coating at high temperature pattern as shown in Figure 2, top layer is chemical Ni-plating layer, lower floor is oxide skin(coating), be inwardly aluminized coating, between inside and matrix, there is Elements Diffusion and occur internal divergence layer, there is sharp interface with matrix in this layer, along with service temperature raises and military service time lengthening, interior diffusion layer increases gradually, until coating consumes and loses protective effect completely effectively mutually.
Obtain diffusion group in alloy coating at high temperature by electron microscopy observation and knit metallograph, 5～10 photos of each sample position picked-up, every photo is equidistant evenly chooses 10 positions, obtain alloy coating at high temperature internal divergence layer tissue size L by statistical computation, determine character and the preparation technology of coating simultaneously, determine Q value and K0 value, in substitution formula
calculate temperature value (coating test temperature) T of diffusion layer interface in alloy coating at high temperature
0.
In order to obtain the accounting temperature distribution curve of matrix, calculate thermal boundary condition by CFD flow field analysis software, comprise near the fluid temperature (F.T.) of blade wall and convection transfer rate, utilize interpolation software FSI that the grid of CFD flow field analysis is corresponding with CALCULATION OF THERMAL grid in ABAQUS, after coordinate conversion, near fluid node temperature the data a large amount of wall that CFD flow field analysis is obtained are converted into surface temperature value, by ABAQUS finite element analysis software, blade is carried out to temperature field analysis, obtain the Temperature Distribution cloud atlas of blade surface, pass through value, can obtain the temperature distribution history of the high temperature alloy matrix mother metal of optional position or arbitrary section, temperature value is carried out in blade 60% cross section, obtain temperature distribution history as shown in Figure 4, can obtain to any value of curved portion the matrix accounting temperature T of the optional position of blade height 60% position
1.
In order to obtain the alloy coating at high temperature accounting temperature T of nearly matrix
0', utilize correction formula T
0'=T
1+ δ, wherein δ is determined by empirical value, span is 2～10 DEG C, if obtain coating temperature T
0<T
0', showing that alloy coating at high temperature experimental temperature will be lower than accounting temperature herein, coating is in safety zone, with T
0' as coating actual prediction temperature, bring Life Prediction Model into, predict coating residual life, can obtain being not less than the safe handling scope of residual life; If alloy coating at high temperature accounting temperature is lower than measuring temperature T
0> T
0', surperficial turbine blade moves use at higher temperature, alloy coating at high temperature in unsafe running environment, T
0bring in Life Prediction Model as coating actual prediction temperature, the result of acquisition more can represent alloy coating at high temperature service condition and residual life.Wherein Fig. 4 has enumerated blade Bucket1 blade substrate temperature and the military service rear blade coating temperature correlation curve figure of several positions.The experimental temperature obtaining taking the position metallographic examination of Bucket1 blade trailing edge is 923 DEG C, calculating substrate temperature is 956 DEG C, empirical value δ value is got 8 DEG C, accounting temperature is herein 964 DEG C, 923 DEG C of <964 DEG C, 964 DEG C of life prediction service temperatures as blade trailing edge position should getting, bring Life Prediction Model into
in, in alloy coating at high temperature, diffusion layer organizes size L to choose the critical dimension that calculates inefficacy, determines Q value and K
0value, the residual life that result of calculation obtains high-temperature service coating is 2000h, other blades of unit have continued safe operations 2000h, coating reaches service life, need to be from new spraying, for lengthening the life of unit made guidance.
The operation history data of blade Bucket2 is that total run time is 72000 hours, and after 48000 hours, coating was repaired again, and be 200 hours total duration of ignition, start and stop in a year 2～3 times, and fuel is rock gas.Identical with the project organization of Bucket1 blade, adopt the 12 cooling blades in upright cooling duct, hole.
Effects on surface carries out macroscopic view observation, blade surface burns rock gas, there is not corrosion fouling, being mainly oxidation product generates, after cleaning, carry out macroscopic view observation, blade 50%～60% position trailing edge, without ablation problem, changes and predicted temperature in order further to analyze coating structure, carries out destructive metallographic detection.
For the primary morphology of protective finish is not destroyed in preparation process; adopt the disposal route identical with Bucket1 to carry out sample preparation; in backward scattering observation acquisition alloy coating at high temperature, diffusion layer is organized the numerical value of size L; the composition of determining coating is identical with Bucket1 with preparation technology; Q value, K0 value and L0 value are identical, in substitution formula
calculate the experimental temperature T0 at diffusion layer place in coating, because blade material is identical with project organization, therefore utilize the data such as pneumatic, heat transfer, intensity to carry out the boundary condition of finite element analysis identical, the matrix accounting temperature curve of two groups of blades is identical, chooses equally the matrix accounting temperature value T on the curve of blade trailing edge position
1, bring the correction formula T of coating accounting temperature into
0'=T
1+ δ, wherein δ is determined by empirical value, defines consistent with the former.Wherein Fig. 4 has enumerated the relativity figure of the several position of blade Bucket2 alloy coating at high temperature experimental temperature and matrix accounting temperature, taking Bucket2 trailing edge position as example, the experimental temperature that metallographic examination obtains is 988 DEG C, matrix accounting temperature is 956 DEG C, modified value δ gets 8 DEG C, and trailing edge position coating accounting temperature is 964 DEG C, wherein 964 DEG C of 988 DEG C of >, therefore get 988 DEG C of actual service temperatures as blade trailing edge position coating, bring Life Prediction Model into
in, in alloy coating at high temperature, diffusion layer organizes size L to choose the critical dimension that calculates inefficacy, determines Q value and K
0value, the residual life that result of calculation obtains high-temperature service coating is 120h, consider the operation conditions of unit, think that coating reaches the service life time limit substantially, need to be from new spraying, the safe operation of guarantee unit, simultaneously, by the situation of change of trailing edge position metallographic structure, effective minimizing of alloy coating at high temperature, coating surface oxide layer thickens, there is the phenomenon that effective item disappears completely in coating layer portion position, can judge that coating is inefficacy coating, therefore comprehensively analyzing blade alloy coating at high temperature needs repairing, for the user of power plant detects and has made guidance the service state of unit.
Claims (3)
1. a Forecasting Methodology for gas turbine turbine blade alloy coating at high temperature service temperature, described alloy coating at high temperature is MCrAlY coating, MCrAlY+ aluminized coating or MCrAlY+TBC layer, it is characterized in that the method comprises the following steps:
1) need the enterprising line cutting of predicted temperature place xsect at turbine blade blade position, prepare sample, adopt destructive metallographic analysing method to obtain the rear coating internal divergence layer tissue size L of sample location military service;
2) by life prediction formula
Calculate the coating experimental temperature T of diffusion layer interface in alloy coating at high temperature
0, in formula: Q is energy of activation constant, K
0for chemical reaction rate constant, Q and K
0relevant with coating service state with coating composition, preparation technology; R is gas law constant; T is the T.T. of unit operation after being on active service, L
0for diffusion layer in the coating of original state before being on active service is organized size;
3) for turbine blade Service Environment and thermal boundary condition, by means of ABAQUS finite element analysis software, blade is carried out to temperature field analysis, obtain any position high temperature alloy matrix mother metal temperature distribution history, thereby obtain arbitrfary point matrix accounting temperature T
1;
4) utilize T
0'=T
1+ δ, to matrix accounting temperature T
1revise, obtain alloy coating at high temperature accounting temperature T
0', wherein δ span is 2～10 DEG C;
5) alloy coating at high temperature accounting temperature T
0' and alloy coating at high temperature experimental temperature T
0compare, if T
0<T
0', experimental temperature herein will be lower than coating accounting temperature, and coating is in safety zone, with T
0' as alloy coating at high temperature service temperature; If T
0≤ T
0', experimental temperature will be higher than coating accounting temperature herein, and coating is under higher service temperature, with T
0as alloy coating at high temperature service temperature.
2. a kind of Forecasting Methodology of gas turbine turbine blade alloy coating at high temperature service temperature as claimed in claim 1, it is characterized in that: described alloy coating at high temperature is the nearly surface coating of matrix, alloy coating at high temperature experimental temperature is alloy coating at high temperature and basal body interface place temperature; For coating, ablation or hot corrosion phenomenon have occurred, when coating internal divergence layer tissue size cannot be measured, alloy coating at high temperature experimental temperature adopts the alloy coating at high temperature at alloy coating at high temperature close positions place and the experimental temperature at basal body interface place to be replaced.
3. a kind of Forecasting Methodology of gas turbine turbine blade alloy coating at high temperature service temperature as claimed in claim 1, it is characterized in that: internal divergence layer tissue size L, refer to the region of aluminium element, chromium Elements Diffusion and variation in complete reservation coating, wherein L is of a size of to adopt and in 5mm length range, takes continuously 5～10 metallographs, measures 50～100 measured values and gets its mean value.
Priority Applications (1)
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| CN105354627B (en) * | 2015-10-15 | 2018-11-27 | 北京科技大学 | A kind of prediction technique of high Nb type GH4169 alloy Long-term Aging performance degradation |
| CN105403502B (en) * | 2015-12-28 | 2018-08-03 | 北京科技大学 | A kind of experimental evaluation method of high-temperature alloy turbine blade service temperature |
| CN106681293A (en) * | 2016-03-04 | 2017-05-17 | 浙江大学 | Condition-based maintenance decision making system for gas turbines |
| CN109613058B (en) * | 2018-12-27 | 2021-07-13 | 上海海事大学 | Steel adheres to hot feedback heat transfer effect testing arrangement of combustible material burning |
| CN113063793B (en) * | 2021-03-25 | 2022-01-07 | 中山大学 | Graphical processing analysis method for service condition of titanium alloy surface coating and application thereof |
| CN113094888B (en) * | 2021-03-31 | 2024-01-30 | 西安电子科技大学 | Method and device for predicting service life of thermal barrier coating of high-speed rotating turbine blade |
| CN113704915B (en) * | 2021-08-26 | 2023-09-19 | 华能国际电力股份有限公司 | Thermal barrier coating thermal fatigue life prediction method for turbine blade of heavy-duty gas turbine |
| CN113758968B (en) * | 2021-09-30 | 2022-08-05 | 西安交通大学 | Experimental system and steady-state experimental method for measuring turbine movable blade top heat exchange coefficient |
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| CN101008324A (en) * | 2006-12-22 | 2007-08-01 | 陕西鼓风机（集团）有限公司 | Surface composite coating of turbomachine rotor blade and preparation method thereof |
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