Al元素对Ti40阻燃钛合金550℃热稳定性的影响

研究Ti-25V-15Cr-0.2Si和Ti-25V-15Cr-2Al-0.2Si两种阻燃钛合金在550℃热暴露不同时间后的力学性能，并应用光学显微镜、X射线衍射、透射电镜对合金组织进行分析。结果表明，Al元素使Ti40阻燃钛合金在550℃的热稳定性能显著降低；对相的分析表明，Al元素可促进合金中Ti5si3和α相的形成。在550℃热暴露200h条件下，出现明显的TiCr2有序相。降低组织的稳定性及使合金在热暴露过程中生成过多的第二相是Al元素降低合金热稳定性能的主要原因。     

Cr元素对Ti-V-Cr系阻燃钛合金热暴露力学性能的影响

研究了Ti-25V-15Cr-0.2Si和Ti-25V-10Cr-0.2Si两种阻燃钛合金在不同热暴露条件下的热稳定性能.结果表明:Cr元素对Ti-V-Cr系阻燃钛合金的组织有较强细化作用,强化合金室温力学性能;随Cr元素含量的降低,合金在热暴露过程中析出的第二相减少,合金热稳定性能优化.此实验现象与Cr元素在钛合金中属于共析元素的性质有关.     

V元素对Ti-V-Cr系阻燃钛合金热强性的影响

配制不同V含量的3种阻燃钛合金，分别测试其在不同热暴露和蠕变工艺下的热稳定性能和蠕变性能，并观察其显微组织。结果表明，随V元素含量的增加，合金热稳定性能和抗蠕变性能提高，并且V元素的含量对热稳定性能和蠕变性能的影响存在一个最佳含量，小于该含量时，V元素含量对热稳定性能和抗蠕变性能影响较大，大于该含量时，含量增加对其性能影响不大。在讨论中指出，V元素对热稳定性能和蠕变性能的影响主要表现在对β相稳定性的影响，对TiCr2相形成过程的影响和与空位的相互作用三个方面，并详细论述了其机理。     

β型Ti40阻燃钛合金高温长期作用的第二相及其对性能的影响

研究了β型Ti40阻燃钛合金高温长期作用的第二相及其对性能影响，Ti40合金高温长期作用后，从β相中析出Ti5Si3相和α相，采用常规锻造工艺不高于540℃热暴露100h,Ti5Si3相沿晶界不连续分布，降低合金热稳定性能，700℃热暴露100h，Ti5Si3相明显，大大降低合金热稳定性能，合金呈脆性沿晶界断裂，采用等温锻造工艺540℃热暴露100h，晶内析出粗大的Ti5Si3相和α相，热稳定性能严重降低，呈宏观脆性断裂，采用常规锻造工艺合适的热处理制度，540℃，100h,250MPa蠕变作用后Ti5Si3相沿晶界不连续分布，合金有较好的蠕变性能，若热处理工艺不当，合金中有大量粗大的棒状Ti5Si3相和α相析出，Ti5Si3 相沿晶界连续分布，合金的蠕变抗力明显降低，采用等温锻造工艺蠕变作用后，合金中析出大量粗大的α相，合金蠕变抗力也明显降低。     

Ti-25V-15Cr-2Al-2Mo-0.2C阻燃β钛合金的蠕变变形结构研究

采用TEM技术研究了具有不同热处理组织的Ti-25V-15Cr-2A1-2Mo-0．2C合金存在540℃，250MPa，100h蠕变作用后的变形结构。结果表明：位错环组是合金蠕变变形结构中的典型位错组态；合金的蠕变抗力随β基本上弥散分布的第二相析出数量的增加而提高。添加微量能提高蠕变抗力的合金元素，如Si元素等，是改善合金蠕变性能的可行途径。     

Ti—40阻燃钛合金中的第二相

研究了Ti-40(Ti-25V-15Cr-0.2Si)阻燃钛合金中的第二相及其对合金性能的影响。研究结果表明：固溶温度升高,Ti40合金析出第二相的趋势增大;低于850℃固溶,合金中没有第二相析出,高于850℃固溶,合金中析出棒状α相和少量Ti5Si3相;910℃固溶＋600℃时效,合金存在第二相有α和Ti5Si3相;860℃固溶＋600℃时效,合金仅存在Ti5Si3相,固溶时效态存在的第二相对合金的性能没有明显影响,540℃,100h热暴露,合金中存在的各种形态的α相和Ti5Si3析出物,明显降低合金的热稳定性能。     

Ti-25V-15Cr-2Al-0.2C合金微观组织和相组成研究

通过OM，XRD，SEM和TEM等多种分析手段对Ti-25V-15Cr-2Al-0.2C阻燃β钛合金的微观组织和相组成进行了研究。结果表明，α和(Ti，V)C是β基体上的2种主要析出相，合金在高温长时间热暴露(540℃，100h)后会析出金属间化合物TiCr2相。此外，也有极少量α相在热暴露期间发生了短程有序化(SRO)转变。     

Ti40合金热稳定性能的初步研究

研究了热处理制度和少量合金元素Si对β型阻燃钛合金Ti40热稳定性的影响.结果表明含0.2%Si的合金,固溶温度越高,热暴露后析出的Ti5Si3相越粗大,明显降低合金热稳定性能.820℃/0.5 h,WQ+600℃/5 h,AC热处理后,与无暴露相比,含0.2%Si的合金热暴露后析出的Ti5Si3相使合金塑性明显下降;与不含Si的合金相比,含0.2%Si的合金热稳定性能较差.     

碳化物分布状态对Ti-25V-15Cr-2Al-0．2C-x合金微观组织的影响

碳化物和α相是Ti-25V-15Cr-2Al-0．2C-x（x=0.2%Mo,2%Nb等）阻燃β钛合金基体上的2种主要析出相。采用OM，SEM，TEM等方法研究了具有不同碳化物分布状态的Ti-25V-15Cr-2Al-0．2C-x合金的热处理及热暴露后的微观组织。结果表明，细小、弥散分布的碳化物颗粒不仅能细化合金的β晶粒，而且能明显抑制对合金组织稳定性有害的α沉淀相的析出，碳化物颗粒越细小、弥散，抑制α相析出的作用就越强，合金的组织稳定性也越高。     

第二相对Ti-V-Cr系阻燃钛合金高温蠕变行为的影响

在相同的实验条件下,Ti-25V-15Cr-0.2Si合金的蠕变性能优于Ti-35V-15Cr合金.蠕变过程中,前者在晶界和晶内析出硅化物和少量α相;后者析出长条状α相连续分布于晶界.同种合金相比较时,Ti-35V-15Cr合金经870℃/0.5 h,WQ+600℃/5 h,AC处理的蠕变性能比锻态稍好,主要是因为锻态中除晶界分布有连续α相外,晶内还有一些不均匀的α相;而固溶时效处理的试样,其析出相大都连续分布于晶界.研究表明,硅化物可钉扎位错,阻碍位错运动;晶界处连续的α相起到晶界强化作用,提高了蠕变抗力;而弥散的α相降低蠕变抗力.     

Creep behavior of nonburning Ti-35V-15Cr-<Emphasis Type="Italic">x</Emphasis>C alloys

A comparison is made between the creep behavior of the Ti-35V-15Cr and Ti-35V-15Cr-0.2C alloys at 500 to 580 °C within the stress range of 200 to 300 MPa. The creep resistance of Ti-35V-15Cr-0.2C is considerably improved by the incorporation of Ti₂C particulates into the Ti-35V-15Cr-0.2C matrix. This paper was presented at the Beta Titanium Alloys of the 00’s Symposium sponsored by the Titanium Committee of TMS, held during the 2005 TMS Annual Meeting & Exhibition, February 13–16, 2005 in San Francisco, CA.     

Effect of size and distribution of titanium carbide on microstructure and mechanical properties of Ti-25V-15Cr-2Al-0.2C-0.2Si alloy

The effect of size and distribution of titanium carbide on the microstructure and mechanical properties of non-burning β titanium alloy Ti-25V-15Cr-2Al-0.2C-0. 2Si （mass fraction, %） was investigated. The microstructure of the heat-treated and exposed alloy was studied using optical microscopy（OM）, scanning electron microscopy （SEM） and transmission electron microscopy（TEM）. It is found that carbides with finer size and more uniform distribution can suppress the formation of α precipitates more effectively, and can especially decrease the amount of grain boundary α precipitates after long-term exposure at 540 ℃ （the expected application temperature）. Thus, significant improvement in thermal stability can be achieved by refining carbide particles in the matrix of the alloy.     

一种新型低成本阻燃钛合金的微观组织与力学性能

研究了一种名义成分为Ti-25V-15Cr-5Mo-0.25Si-0.08C的新型低成本阻燃钛合金TF-X,通过三次真空自耗熔炼制备了φ120mm铸锭,经包套挤压得到φ25mm棒材,观察了铸锭和挤压棒材的微观组织,测试并分析了挤压棒材的室温和高温拉伸性能、热稳定性能、高温蠕变性能。结果表明：TF-X合金具有与TF550合金大致相同的微观组织;TF-X合金室温及高温拉伸强度高于TF550合金,并且具有很好的塑性;试验条件下,TF-X合金的热稳定性能低于TF550合金,熔炼过程中应该严格控制氧含量;TF-X合金在540℃/250MPa/100h条件下蠕变性能与TF550合金相当,显著高于Ti40合金。     

The use of β titanium alloys in the aerospace industry

Beta titanium alloys have been available since the 1950s (Ti-13V-11Cr-3Mo or B120VCA), but significant applications of these alloys, beyond the SR-71 Blackbird, have been slow in coming. The next significant usage of a β alloy did not occur until the mid-1980s on the B-1B bomber. This aircraft used Ti-15V-3Cr-3Al-3Sn sheet due to its capability for strip rolling, improved formability, and higher strength than Ti-6Al-4V. The next major usage was on a commercial aircraft, the Boeing 777, which made extensive use of Ti-10V-2Fe-3Al high-strength forgings. Ti-15V-3Cr-3Al-3Sn environmental control system ducting, castings, and springs were also used, along with Ti-3Al-8V-6Cr-4Mo-4Zr (β-C) springs. Beta-21S was also introduced for high-temperature usage. More recent work at Boeing has focused on the development of Ti-5Al-5Mo-5V-3Cr, a high-strength alloy that can be used at higher strength than Ti-10V-2Fe-3Al and is much more robust; it has a much wider, or friendlier, processing window. This, along with additional studies at Boeing, and from within the aerospace industry in general will be discussed in detail, summarizing applications and the rationale for the selection of this alloy system for aerospace applications. This paper was presented at the Beta Titanium Alloys of the 00’s Symposium sponsored by the Titanium Committee of TMS, held during the 2005 TMS Annual Meeting & Exhibition, February 13–16, 2005 in San Francisco, CA.     

HYDROGEN EFFECT ON DEFORMATION BEHMIOR OF TITANIUM ALLOY AT HIGH TEMPERATURE

1.IntroductionContinuousfiberreinforcedtitaniummatrixcompositeshavepotentialapplicationatelevatedtemperature.Anewmethodhajsbeentriedbyoneofthepresentautho.s[1'21toalleviatethedeleteriousinterfacereactionbetweenthefiberandthematrix,whichislikelytooccurinthiscompositeduringfabrication.Previous.orb[llshowedthattitaniummatrixcompositecanachievefullconsolidationatrelativelylowtemperaturewiththeaidofhydrogenasatemporaryalloyingelement.Furtherstudyalongthisdirectionshouldbebasedonacomprehensiveunders…     

Dynamic recovery and recrystallization in titanium alloys by hot deformation

The microstructural change of β titanium alloys, Ti-15V-3Cr-3Sn-3Al and Ti-10V-2Fe-3Al, and an (α+β) titanium alloy, Ti-6Al-4V, during hot deformation at temperatures in β single-phase and (α+β) two-phase regions was studied. For the β titanium alloys, dynamic recovery takes place dominantly within β grains during deformation in the β single-phase region although some discontinuous dynamic recrystallization occurs along β grain boundaries. The size and fraction of recrystallized β grains increase as strain rate decreases or the deformation temperature rises.     

Spark anodizing behaviour of titanium and its alloys in alkaline aluminate electrolyte

Spark anodizing of titanium, Ti-6Al-4V and Ti-15V-3Al-3Cr-3Sn in alkaline aluminate electrolyte produces highly crystalline anodic films consisting mainly of Al₂TiO₅ with α- and γ-Al₂O₃ as minor oxide phases, irrespective of substrate composition. However, the apparent efficiency for film formation decreases in the following order: Ti-6Al-4V, titanium and Ti-15V-3Al-3Cr-3Sn. A large amount of aluminium species are incorporated from the electrolyte, probably by plasma-chemical reaction, and become distributed throughout the film thickness. This distribution indicates that the electrolyte penetrates near to the film/substrate interface through the discharge channels. Thus, the outwardly migrating aluminium ions under a high electric field can be present even in the inner part of the anodic films. Voids are developed at the film/substrate interface, particularly on the vanadium-containing alloys, reducing the adhesion of the anodic film to the substrate.     

Aerospace applications of beta titanium alloys

Beta alloys are beginning to play a significant role in both military and commercial aircraft. Ti-10V-2Fe-3Al forgings, for example, play major roles in the McDonnell Douglas C-17 and the Boeing 777. The attractive properties of Beta-C are increasing the use of titanium, rather than steel, in aircraft springs. Ti-15V-3Cr-3Al-3Sn is subject to increasing usage primarily because of its strip producibility and formability. Beta-21S is gaining importance for high-temperature applications. New alloys such as β-CEZ, SP-700, and Timetal® LCB could become important because of advantageous costs, processing, and/or properties. In the past, the use of beta alloys has largely been driven by their superior properties and weight-savings potential. In the future, cost will become more important. As a result, a greater emphasis will be placed on lower cost alloys and/or taking advantage of the improved processing capabilities of these alloys to minimize final component costs.