热障涂层破坏理论与评价技术(英文版)

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作者：周益春，杨丽，朱旺

出版社：科学出版社

本类榜单：工业技术

分类：工业技术 > 一般工业技术

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ISBN：9787030733290
装帧：一般胶版纸
册数：暂无
重量：暂无
开本：B5
页数：952
出版时间：2022-10-01
条形码：9787030733290 ; 978-7-03-073329-0

本书特色

国家航发系统的所有企事业单位一线的科研人员和管理人员，高等学校力学学科固体力学学科、材料学科的教师和博士生、硕士生，个别高年级的本科生。

内容简介

本书内容是开始基于航空发动机热障涂层剥落瓶颈亟待解决的重大需求，从工程中提炼科学问题，致力于特别环境下涂层性能损伤表征、热-力-化耦合模型及环境模拟装置等物理力学应用基础研究，并将研究成果应用到工程解决实际问题。提出的界面断裂韧性屈曲表征与高温裂纹声发射实时检测方法，解决了界面性能不能科学表征、失效模式与过程接近未知的黑匣子问题；建立的热-力-化耦合氧化与CMAS腐蚀本构模型，打破了长期以来基于失效现象的定性分析模式；自主研制的CMAS高温接触角、高温振动、航空煤油式燃气冲击与实时测试、高速旋转与实时测试等装置，极大程度上解决了试车前接近没有考核设备的问题。

目录
Contents
1　Introduction　1
1.1　TBCs and the Corresponding Preparation Methods　2
1.1.1　TBC Materialsand Structures　2
1.1.2　TBC Preparation Methods　4
1.2　TBC Spallation Failure and Its MainIn.uencingFactors　9
1.2.1　Service Conditions for TBCs　9
1.2.2　TBC Spallation Failure and Its MainIn.uencing Factors　10
1.3　Solid Mechanics Requirements and Challenges Generated by TBC Failure　14
1.3.1　Solid Mechanics Requirements Generated by TBC Failure　14
1.3.2　Solid Mechanics Challenges Presented by TBC Failure　17
1.4　Content Overview　21
References　23
2　Basic Theoretical Frameworks for Thermo–Mechano-Chemical Coupling in TBCs　27
2.1　Continuum Mechanics　27
2.2　Theoretical Frameworkfor Thermo–Mechano-Chemical Coupling Basedon Small Deformation　30
2.2.1　Strain and Stress Measures BasedonSmall Deformation[5，6]　30
2.2.2　Stress–Strain Constitutive Relations Based onSmall Deformation[5，6]　47
2.2.3　Constitutive Theoryfor Thermomechanical CouplingBased on Small Deformation[11]　52
2.2.4　Constitutive Theory forThermo–Mechano-Chemical Coupling Basedon Small Deformation[16]　61
2.3　Theoretical Frameworkfor Thermo–Mechano-Chemical Coupling BasedonLarge Deformation　68
2.3.1　Kinematic Description[9]　68
2.3.2　Stressand StrainMeasures　71
2.3.3　Mass Conservation and Force Equilibrium Equations　74
2.3.4　Constitutive Theoryfor Thermomechanical Coupling Basedon Large Deformation[18，25，26]　80
2.3.5　Constitutive Theory for Thermo–Mechano-Chemical Coupling BasedonLarge Deformation　85
2.4　Summary and Out look　93
References　97
3　Nonlinear FEA of TBCs on Turbine Blades　99
3.1　FEAPrinciples　100
3.1.1　Functional Variational Principle　100
3.1.2　WeakFormof theEulerianFormulation　105
3.1.3　FEDiscretizati on of the Eulerian Formulation　108
3.1.4　WeakFormof theLagrangian Formulation　111
3.1.5　FE Discretizati on of the Lagrangian Formulation　113
3.1.6　WeakFormof the Arbitrary Lagrangian–Eulerian Formulation　116
3.1.7　Initial and Boundary Conditions　121
3.2　FE Modeling of TBCs on Turbine Blades　122
3.2.1　Geometric Characteristicsof Turbine Blades　122
3.2.2　Parametric Modelingof Turbine Blades　124
3.3　Mesh Generationfor Turbine Blades　140
3.3.1　Generationof Unstructured Meshes　141
3.3.2　Structured Meshes for Turbine Blades　145
3.4　Image-Based FE Modeling　150
3.4.1　Image-BasedFEM　151
3.4.2　2D TGO Interface Modeling　153
3.4.3　Porous Ceramic Layer Modeling　156
3.4.4　D3TGO Interface Modeling Method　157
3.5　Summaryand Outlook　158
References　159
4　Geometric Nonlinearity Theory for the Interfacial Oxidation of TBCs　163
4.1　Interfacial Oxidation Phenomenon andFailure　164
4.1.1　Characteristics and Patterns of Interfacial Oxidation　164
4.1.2　StressField Inducedby Interfacial Oxidation　167
4.1.3　Coating SpallationInducedby Interfacial Oxidation　170
4.2　TGO Growth Model Basedon Diffusion Reaction　172
4.2.1　Governing Equations　172
4.2.2　FESimulation　178
4.3　Thermo–Chemo–Mechanical CouplingAnalytical Model forInterfacial OxidationofTBCs　188
4.3.1　Thermo–Chemo–Mechanical Coupling Analytical Growth Model forInterfacial Oxidation　188
4.3.2　Thermo–Chemo–Mechanical Coupling Growth Constitutive Relations forInterfacial Oxidation　201
4.3.3　Analysis of theThermo–Mechano-Chemical CouplingGrowthPatterns and Mechanisms DuringInterfacialOxidation　222 References　232
5　Physically Nonlinear Coupling Growth and Damage Caused by Interfacial Oxidation in TBCs　235
5.1　Physically Nonlinear Model forThermo–Mechano–Chemical Coupling Growth Causedby Interfacial Oxidationin TBCs　236
5.1.1　Model Framework　236
5.1.2　Numerical Implementation　243
5.1.3　Resultsand Discussion　246
5.1.4　Analytical Coupling Model for Interfacial Oxidation　252
5.1.5　Comparison with Experimental Results　256
5.2　Interfacial Oxidation Failure Theorythat Integrates the CZM and PFM　262
5.2.1　Integrated CZM and PFM Framework　262
5.2.2　Introductionto PFM　263
5.2.3　Introductionto CZM for Phase-FieldCrack Interactions　267
5.2.4　Numerical Implementation　271
5.2.5　Resultsand Discussion　273
5.3　Summary and Out look　281
5.3.1　Summary　281
5.3.2　Outlook　283
References　283
6　Thermo–Mechano–Chemical Coupling During CMAS Corrosion in TBCs　287
6.1　Correlation Analysisof Molten CMASIn.ltration and Its KeyIn.uencingFactors　288
6.1.1　Theoretical Model for Mol ten CMASIn.ltration Depthin EB-PVD TBCs　288
6.1.2　Experimentsonthe MoltenCMASIn.ltration Depthinan EB-PVD TBC and Its In.uencing Factors　298
6.1.3　CMASIn.ltration Depthinthe EB-PVD TBC and ItsIn.uencing Factors　299
6.1.4　In.ltration of CMAS Meltsin an APS TBC　308
6.2　Microstructural Evolution， Deformation， and Composition Loss of Coatings Dueto Corrosion　312
6.2.1　Microstructural Evolution and Deformation ofCoatings　312
6.2.2　Thermo–Mechano–Che

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Chapter 1 Introduction 　　The aeroengine is the “heart” of an aircraft， and these national treasures are an important indicators of national core competitiveness. The turbine inlet tempera-tures in both third-and fourth-generation aeroengines exceed the melting points of high-temperature metallic materials.A new generationof materials can yielda new generation of equipment. As the most feasible technology for improving the service temperature of gas turbine engines， thermal barrier coatings (TBCs) have becomeanindispensablethermalprotection materialfor hot-end components(e.g.， high-pressure turbinebladesin aeroenginesandgasturbines)and，toaremarkable extent， determine engine performance anddevelopmentlevels. All theworld’savia-tionpowershave listedTBCsasakey coretechnologyin theirmajoradvancement plans.Likewise， China has categorized TBCs asakeytechnology urgently needed for aeroengines andgasturbines. 　　Operating in hot-end components such as engine turbine blades， TBCs are subjected to long-termextreme conditions such as impactsfrom 2000Kgas near the critical Mach number， centrifugal forces generated by rotations at 10，000– 50，000 rpm，fatigue， creep， calcium-magnesium-aluminosilicate(CMAS) corrosion， solid particle erosion，and oxidation， accompaniedbychemical reactions.Asaresult ofextremeadverse conditions， coatingsspallandfailbyavarietyofcomplexmech-anisms， posinga multitudeofnew challengesto research onfailure theories.For example， oxidation， thermal mismatch， growth stress， and high temperature， which are involved in the interfacial oxidation failure of TBCs， affect one another. The oxidation process and the resulting coating spallation are both a typical thermo-mechano-chemical couplingphysical nonlinear problem anda geometric nonlinear problemwithstrainupto10%.As anotherexample，TBCmelts(CMAS) corrodeat high temperatures， and theirrelevant in.ltration and performanceevolution patterns and thermo-mechano-chemical coupling mechanismsare allnewfailure phenomena exhibitedbyTBCs，the mechanical natureofwhich has been poorlyexplained sofar. 　　Turbine blades are geometrically complex， and TBCs with defects and multi-layer systemshaveacomplexmicrostructure. During service， coatings and interfaces evolve in terms of composition， microstructure， and performance. Their nonlinear physical and geometricpropertiescreatenew problemsfor mechanical performance characterization and numerical simulation techniques. In addition， high tempera-turesare inevitableservice conditions for TBCs.The characterizationofthe coating performance at high temperatures and the accurate descriptionofthe loading condi-tions in complex high-temperature environments are issues to be considered in the failure analysis of TBCs. 　　Performanceevaluationand service lifepredictionarethemosturgent issuesof the TBC applicationsector.The associationofthe service lifewith thematerial and service-environment parametersoffersthe most direct basis forthe TBC production sector.Understanding this associationisthe ultimategoalofinvestigationintofailure mechanisms and， more importantly， is the most dif.cult scienti.c problem at the forefrontof theresearchin this .eld. Moreover， simulation andevaluationdevices canofferthe most reliable， directexperimental basis.They are thetopical andkey areasof researchonTBCfailure mechanism analysisandevaluationtechniques，but technological embargos are often imposed by relevant countries. 　　Thus，spallationfailure theories， numerical computational methods， mechanical performance characterizations， performance and service life evaluations， and pre-test-run simulation and evaluation devices all merit investigation in the study of TBCfailure mechanisms and performanceevaluation. 　　1.1 TBCs and the Corresponding Preparation Methods 　　1.1.1 TBC Materials and Structures 　　To meetthe demandforincreasingservice temperaturesingasturbine engines，the National Aeronautics and Space Administration(NASA)of the UnitedStates put forwardthe conceptof TBCsin 1953 [1–3]. TBCsofferthermalprotection based on thefollowing principle. Ceramicmaterials are characterizedby high-temperature resistance， high thermalstability，lowthermal conductivity，and high corrosion resis-tance. Because of these properties， ceramic materials are combined with metallic substrates in the form of coatings to insulate high-temperature metallic substrate materialsfromhigh-temperaturegas，withthegoalof reducingsurface temperatures in hot-end metallic components and simultaneously enhancing their resistance to high-temperature oxidation and hot corrosion [4，5]. TBCs have been satisfactorily appliedinhot-end componentssuch as turbine blades in aeroengines and gas turbines. 　　A typical TBC has a two-layer structure [8]. Figure 1.1 shows the geometry an structureof a TBC onaturbine blade. Theblade substrateis generally madeofa Ni-based high-temperaturealloy(adirectionally solidi.ed alloy ora single-crystal alloy).The TBC containsa metallic bond c

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