1)  titanium alloy Ti6A14V
钛合金Ti6A14V
2)  titanium alloy
钛合金
1.
Finite element analysis of adiabatic shear band formation in titanium alloy cutting process;
钛合金切削绝热剪切带形成过程的有限元分析
2.
Reactive electric-spark deposition Ti(C N)-based ceramets coating on titanium alloy;
钛合金表面反应电火花沉积Ti(CN)涂层研究
3.
Numerical simulation of vacuum hot bulge forming of titanium alloy cylindrical workpiece;
钛合金筒形件真空热胀形过程数值模拟
3)  TG6 Titanium Alloy
TG6钛合金
1.
Analysis of the Uncertainty for the Determination of Trace Nickel in TG6 Titanium Alloy by AAS;
原子吸收光谱法测定TG6钛合金中痕量镍不确定度的分析
2.
The influences of the amount of HCl(1+1) and HBF_4(1+4),and titamium and coexisting elements on the determination of Ni in TG6 titanium alloy have been investigated.
采用原子吸收光谱测定TG6钛合金中痕量镍。
4)  titanium alloy
TC11钛合金
1.
The corrosion wear behavior of titanium alloy TC11 flat was investigated in artificial sea water and distilled water by using ball-on-flat configuration with 5 mm reciprocating amplitude.
采用球-面接触方式,在振幅为5 mm条件下研究了TC11钛合金在人造海水和纯净水中的往复滑动腐蚀磨损行为,采用扫描电子显微镜观察磨屑和磨痕表面形貌,用能谱仪测试微区元素分布,用非接触式表面形貌仪测定磨痕的三维表面形貌及其磨损体积损失,研究了载荷、滑动频率以及介质对TC11钛合金摩擦系数和磨损量的影响,并用动电位扫描法分析TC11在腐蚀磨损前后的电化学行为。
5)  TC11 Alloy
TC11钛合金
1.
Establishment of a ductile damage evolution model for TC11 alloy during hot forging process;
TC11钛合金热锻成形过程中延性损伤演化模型的建立
2.
Thermo-mechanical modeling tests of TC11 alloy with original β-transformed microstructure were carried out by hot compression in strain rate range 10-3-10-1 s-1 at the temperature range 1090-800°C.
对具有原始β转变组织的TC11钛合金在温度1090~800℃,应变速率10-3~10-1s-1条件下进行了热力模拟压缩实验,获得了该合金不同热变形条件下的应力-应变曲线。
3.
The adjustment experimental result indicates that TC11 alloy blade which adopts adjustment and solution plus aging heat treatment have better transmissivity of blade profile,the mechanical property and microstruture than that blade which only adopts solution heat processing technical scheme;In the isothermal adjustment,the improvement of blade profile becom.
针对TC11钛合金叶片锻造变形后的残余应力和冷却时的温度应力叠加造成的叶身型面翘曲问题,采用等温校正的方法来释放残余应力,使翘曲变形减轻,叶片尺寸达到合格,同时保证叶片的金相组织和力学性能得到改善。
6)  TA6V titanium alloy
TA6V钛合金
1.
On the base of the fatigue small cracks growth test in TA6V titanium alloy,the fatigue fracture of TA6V titanium alloy SENT specimen is analyzed.
在进行TA6V钛合金疲劳小裂纹实验的基础上,使用KYKY2800B型扫描电镜(SEM)对TA6V钛合金疲劳断口形貌进行疲劳源区及其裂纹扩展形状、扩展区、瞬断区形貌的观察,分析TA6V钛合金疲劳断口形貌形成的原因,为其结构疲劳安全设计及可靠性分析提供科学依据,为今后TA6V钛合金在我国的使用提供参考。
2.
Firstly, in the paper, according to aerial standard HB7705-2001 "Standard test method for fatigue small crack growth rates of metallic materials", the test of fatigue small cracks growth has been made in the single-edge-notch tension (SENT) specimen of TA6V titanium alloy by applying the replica methods.
本文首先根据航空标准HB7705-2001《金属材料疲劳小裂纹扩展速率试验方法》，采用复型法对TA6V钛合金SENT试样进行疲劳小裂纹试验，根据试验结果分析TA6V钛合金在应力比R=-1和R=0时不同应力水平下的疲劳小裂纹扩展规律。
参考词条
补充资料：Ti-55高温钛合金显微组织


Ti-55高温钛合金显微组织


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说明：补充资料仅用于学习参考，请勿用于其它任何用途。