Tensile and Fracture Behavior of DZ68 Ni-base Superalloy

The tensile and fracture behavior of DZ68 directionally solidified Ni-base superalloy was studied in the temperature range of room temperature (RT) to 1000°C. The fracture mode was examined by scanning electron microscopy (SEM) and transmission electron microscopy (TEM). The results show the tensile strength and yield strength of DZ68 alloy increase slightly with increasing temperature, so that at 760°C its reach maxima value: 1214 and 1019 MPa, respectively. When the experimental temperature is higher than...     

Tensile,creep behavior and microstructure evolution of an as-cast Ni-based K417G polycrystalline superalloy

The Ni-based K417G superalloy is extensively applied as aeroengine components for its low cost and good mid-temperature (600–900 °C) properties. Since used in as-cast state, the comprehensive understanding on its mechanical properties and microstructure evolution is necessary. In the present research, the tensile, creep behavior and microstructure evolution of the as-cast K417G superalloy under different conditions were investigated. The results exhibit that tensile cracks tend to initiate at MC carbide and γ/γ′ eutectic structure and then propagate along grain boundary. As the temperature for tensile tests increases from 21 °C to 700 °C, the yield strength and ultimate tensile strength of K417G superalloy decreases slightly, while the elongation to failure decreases greatly because of the intermediate temperature embrittlement. When the temperature rises to 900 °C, the yield strength and ultimate tensile strength would decrease significantly. The creep deformation mechanism varies under different testing conditions. At 760 °C/645 MPa, the creep cracks initiate at MC carbides and γ/γ′ eutectic structures, and propagate transgranularly. While at 900 °C/315 MPa and 950 °C/235 MPa, the creep cracks initiate at grain boundary and propagate intergranularly. As the creep condition changes from 760 °C/645 MPa to 900 °C/315 MPa and 950 °C/235 MPa, the γ′ phase starts to raft, which reduces the creep deformation resistance and increases the steady-state deformation rate.     

影响单晶Ni基高温合金持久性能的因素

本文研究了一些直接影响单晶 Ni 基高温合金持久强度的因素。原始晶界和由机械加工引起的再结晶对性能的危害极大。在经高温持久试验后的单晶中,往往形成亚结构和微孪晶。单晶合金的[001]方向平行应力轴时,持久性能最佳。当[001]方向与应力轴夹角大于10°时,持久强度大幅度下降。单晶合金中碳化物的含量越多,尺寸越大,对持久性能损害越大。初生γ′和共晶相区是单晶合金中的低强度区域,应通过固溶热处理消除。单晶高温合金经组织结构和晶体取向的一系列优化后,持久强度比普通铸造和定向凝固合金显著提高。     

Creep–fatigue crack growth behaviour based on EBSD observations for notched specimen made of directionally solidified Ni-base superalloy

Abstract

In order to characterise the creep–fatigue crack growth behaviour of a directionally solidified Ni-base superalloy, an investigation into damage behaviour based on the electron backscattered diffraction (EBSD) method using notched specimens has been carried out. The average misorientation in the vicinity of notches increases linearly up to the initiation of cracks with the increasing creep strains under creep or creep–fatigue conditions, whereas under fatigue conditions fatigue cracks grew without an increase in misorientation. The stress holding time clearly influenced the growth behaviour of creep–fatigue cracks and the appearance of misorientation development. However, it was shown that the relationship between the average misorientation and the relative notch opening displacement was independent of test conditions such as temperatures, stresses and stress wave forms.

It is concluded that the misorientation analysis of damaged samples based on the EBSD method allows the prediction of the initiation of creep–fatigue cracks and their growth behaviours.     

HIGH-TEMPERATURE LOW-CYCLE FATIGUE AND CREEP BEHAVIOUR OF NICKEL-BASED SUPERALLOYS WITH HEAT-RESISTANT COATINGS

The problems associated with nickel-based superalloys with heat-resisting coatings, as used in aerospace, have been addressed in this paper. The influence of the heat-resisting coating technology on both the fatigue and creep behaviour of the alloys has been shown. Low-cycle fatigue and creep tests have been performed. Lifetime conditions have been determined in relation to low-cycle fatigue, isothermal creep and creep at cyclically variable temperatures, as a function of the chemical composition of the coating, parameters of the thermal treatment and thickness of the coating. Possible processes and mechanisms of fracture are discussed.     

涡轮叶片Bi─Sn致脆研究

研究了Ｋ４０５高温合金精铸涡轮叶片断裂失效的性质与原因。结果表明，叶片制造过程中表面遭受Ｂｉ－Ｓｎ低熔点合金污染，在使用温度与拉应力作用下出现脆性开裂，从而导致早期疲劳断裂失效。     

Intergrowth of C phase within μ phase in a Re-containing Ni-base single crystal superalloy

Precipitation of topologically close-packed phases in a Re-containing Ni-base single crystal superalloy was studied under elevated temperature by in situ transmission electron microscopy.Above 1150?C,a new intergrowth structure called C phase was found within μ phase with a defined crystallographic orientation relationship.Elements mapping analysis reveals that C phase has a similar element composition as μ phase,but contains a lower level of Cr,W and Re.With increasing temperature,the proportion of C phase increases gradually.At 1250?C,C phase becomes the dominant precipitate.It is demonstrated that C phase is more thermodynamically stable than μ phase above 1150?C that leads to an intergrowth pathway from μ phase to C phase.     

FATIGUE, CREEP AND CREEP/FATIGUE BEHAVIOUR OF A NICKEL BASE SUPERALLOY AT 700°C

Abstract— This paper presents the results of an experimental testing programme to examine the uniaxial creep, low cycle fatigue and creep/fatigue interaction behaviour of a Ni-base superalloy at 700°C. The material is used in the manufacture of aeroengine turbine discs. A creep continuum damage mechanics model is shown to be capable of accurately predicting the creep and creep rupture behaviour of the material. A healing term has been incorporated into the damage mechanics model to allow the behaviour under creep/fatigue conditions to be described.     

涡轮叶片Bi─Sn致脆研究

研究了Ｋ４０５高温合金精铸涡轮叶片断裂失效的性质与原因,结果表明,叶片制造过程中表面遭受Ｂｉ－Ｓｎ低熔点合金污染,在使用温度与拉应力作用下出现脆性开裂,从而导致早期疲劳断裂失效。     

The Behaviour of Mg in γ-phase in a Ni-base Superalloy

1.IntroductionSince the biginning of 1960s,the effectof Mg upon superalloy has been studiedand some satisfactory developments havebeen achieved.The role of Mg on the alloycan be summarized as follows:(1)Themechanical plasticity of Ni-base superalloycan be improved by adding Mg asdesulphurizer,because of forming insolubleMgS instead of other low melting eutectic     

Modification of Sn58Bi solder based on graphite

Abstract

A novel composite solder paste with 0·07 wt-% graphite addition was fabricated. The mechanical properties of matrix solder and composite solder alloys were tested using a kind of miniature joint. The results showed that the tensile strength of the Sn58Bi+graphite composite solder joint declined slightly compared with the Sn58Bi solder joint. However, the elongation of the Sn58Bi+graphite composite solder joint was ～13 times as much as that of the Sn58Bi solder joint. Stress relaxation method, which was used to test the creep performance, was verified by nanoindentation method. The result showed that the stress relaxation method was suitable for creep testing. The creep testing results of Sn58Bi and Sn58Bi+0·07 wt-% graphite solder alloys showed that the anticreep performance of Sn58Bi was improved by the addition of graphite.     

不同Ru含量的镍基高温合金热腐蚀研究

为了解Ru对高温合金热腐蚀性能影响规律,采用了浸盐方法研究了不同Ru含量镍基高温合金的热腐蚀过程,采用扫描电镜观察了合金腐蚀层截面的微观组织,并利用X-射线衍射仪确定相结构.结果表明:在900℃浸盐条件下,Ni基高温合金中加入质量分数3%的Ru可以显著提高合金自身的热腐蚀抗力,并且随着Ru含量增加,合金的热腐蚀抗力进一步增强;合金中加入Ru后,能促使合金表层腐蚀层变薄且与基体结合力好,从而提高了合金的热腐蚀抗力.     

Effects of microstructure evolution on the deformation mechanisms and tensile properties of a new Ni-base superalloy during aging at 800℃

Tensile properties at room temperature of a new casting Ni-base superalloy during aging at 800℃ for0-1000 h were investigated.During aging,granular M23C6 carbides presented at grain boundaries and kept growing from dispersed particles to continuous networks.The γ’ phase significantly coarsened,with the morphology of some γ’ phase changed from spherical to rounded cubic shape after 1000 h.Three deformation mechanisms in relation to the γ’ diameter(dγ’) were identified:(ⅰ) weakly coupled dislocations(WCD) connected by anti-phase boundary(APB) traveled in pair across the γ/γ’ structure when dγ’ was small in the under-aged alloys;(ⅱ) strongly coupled dislocations(SCD) with reduced spacing compared to(ⅰ) sheared γ’ phase when dγ’ increased in the over-aged alloys;(ⅲ) dislocations occasionally by-passed γ’ phase when dγ’ was larger than 97 nm after aging for more than 300 h.The alloy obtained the peak strength when 20 h-aged with dγ’=44 nm which was in the transition between(ⅰ) and(ⅱ).The aginginduced variation in yield strength was correlated to the coarsening of γ’ phase using a theoretical model of precipitation strengthening in terms of the formation of APB.The calculated results suggested that the γ’ phase with a volume fraction of 23% contributed more than 61% of the peak-aged yield strength.Observation after fracture revealed that the alloys usually fractured at grain boundaries.High stress concentration around carbides resulted in cracks by carbides self-cracking and the initiation of cavities.The undesirable agglomeration of M23C6 at grain boundaries was harmful to the properties of the overaged alloys.     

Estimating fatigue sensitivity to polycrystalline Ni-base superalloy microstructures using a computational approach

A computational study is conducted to determine the influence of microstructure attributes and properties on driving forces for fatigue crack formation and microstructurally small crack growth in a polycrystalline Ni‐base superalloy, IN100, a turbine disk alloy. A principal objective is to obtain quantitative estimates of the effect of variability of microstructure features on scatter in fatigue life or fatigue strength for a given life. Understanding is sought regarding sensitivity of driving forces to various microstructure attributes that may guide selection of the process route to tailor microstructure to achieve fatigue resistance. A microstructure‐sensitive crystal plasticity model is used to explicitly model individual grains and polycrystals, which is then used to explore effects of: (a) grain size distribution and (b) secondary and tertiary coherent γ′ precipitate size distributions and volume fractions on the cyclic inelastic strain distribution. Multiple statistical volume elements (SVEs) are subjected to random periodic boundary conditions to build up statistically significant measures of distributions of cyclic microplasticity. Multiaxial fatigue criteria with critical plane approaches are used to estimate the crack initiation life. Methods are developed for assessing crack formation and microstructurally small crack growth as a function of microstructure attributes.     

镍基高温合金脱氧的研究

氧在高温合金中是作为有害杂质元素存在的,通常是疲劳裂纹的萌生地及扩展通道,从而影响高温合金的蠕变、持久强度等性能.本研究在现有条件下,确定了氧在镍基高温合金中存在主要形态为氧化铝夹杂,根据得到的实验数据分析和计算,初步研究了真空感应熔炼条件下碳和铝对镍基高温合金的脱氧机理, 实验中氧含量最低为0.0006%,达到了小于0.001%的目标值.