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1)  cracking in structural weld
结构焊缝中的开裂
2)  weld seam cracking
焊缝开裂
1.
The occurrence of weld seam cracking is considered to be mainly caused by the crassitude elongated grains,the porosity,slag inclusion,inclusion,the Cl-corrosion because of the carbide precipitation along the grain boundary.
采用扫描电镜及电子探针、金相组织、化学成分、力学性能等方法,系统分析了Inconel 600氯化反应器焊缝开裂原因,认为焊缝开裂的原因是焊缝柱状晶粗大,存在气孔、夹渣、缩松和夹杂缺陷,焊缝强度较低;铬的碳化物沿晶界析出,使晶界处贫铬,产生氯离子晶间腐蚀,使焊缝强度急剧降低,导致焊缝在设备运行时开裂。
2.
It is considered that the occurrence of weld seam cracking is mainly caused by the crassitude elongated grains and that there exist porosities,slag inclusions,inclusions and that the water is not throughly desiccated from.
采用扫描电镜及电子探针、金相组织、化学成分、力学性能等分析方法,系统分析了Inconel600氯化反应器焊缝开裂原因。
3)  welded seam burst
焊缝裂开
4)  construction joint
结构焊缝
5)  Structure crack
结构裂缝
1.
Prevention analysis and treatment measures of steel bar concrete structure crack;
钢筋混凝土结构裂缝预防分析与处理措施
2.
Has summarized the concrete structure crack present situation, analyzed it to have the reason, proposed the concrete structure crack prevention as well as the control strategy.
本文简述了混凝土结构裂缝现状,分析了其产生原因,提出了混凝土结构裂缝的预防以及控制策略。
6)  structural crack
结构裂缝
1.
Study on the causes of structural cracks of buildings and quality control measures;
建筑结构裂缝产生的原因及质量控制
2.
The control solution of the structural crack for mass concrete;
大体积混凝土结构裂缝的控制措施
3.
Based on the practice, this paper advances some measures for treating the structural cracks on the reinforced concrete, including the surface patching method and the internal patching method.
在实践的基础上,提出了钢筋混凝土结构裂缝的治理方法,包括表面修补法和内部修补法。
补充资料:ANSYS工字梁焊缝初应力例子

建立好模型
…..
/SOLU
!*
ANTYPE,0
/INPUT,'input','txt',
/INPUT,'output1','txt',
!*
ISFILE,READ,1,txt, ,0
SOLVE
=====================
!定义残余应力矩阵
I=1
fy=310e6
!定义单元中心坐标数组,初应力数组
*DIM,EleCenter,ARRAY,NumNode,3,1, , ,
*DIM,EleIS,ARRAY,NumNode,1,1, , ,
*DO,I, 1, NumNode,1
!得到单元中心坐标
*GET,EleCenter(I,1,1),ELEM,I,CENT,X
*GET,EleCenter(I,2,1),ELEM,I,CENT,Y
*GET,EleCenter(I,3,1),ELEM,I,CENT,Z
!焊缝位置在X=1.0 到1.05 之间
*IF,EleCenter(I,1,1),GT,1,THEN
*IF,EleCenter(I,1,1),LT,1.05,THEN
*IF,EleCenter(I,2,1),GT,0.5,THEN
!上翼缘初始应力
EleIS(I,1,1)=-20*fy*EleCenter(I,3,1)**2+0.3*fy
*endif
*IF,EleCenter(I,2,1),LT,0.0,THEN
!下翼缘初始应力
EleIS(I,1,1)=-20*fy*EleCenter(I,3,1)**2+0.3*fy
*endif
!腹板初始应力
*if,EleCenter(I,2,1),GE,0.0,THEN
*IF,ELECENTER(I,2,1),LE,0.5,THEN
EleIS(I,1,1)=4.076*fy*(EleCenter(I,2,1)-0.5)**2
EleIS(I,1,1)=EleIS(I,1,1)-0.719*fy
*IF,EleIS(I,1,1),LT,-0.3*fy,THEN
ELeIS(I,1,1)=-0.3*fy
*ENDIF


*ENDIF
*ENDIF
*ENDIF
*ENDIF
*ENDDO
===============
!输出应力数值
*CFOPEN,'1','txt',' '
*DO,I,1,3840
!*IF,EleIS(I,1,1),ne,0.,then
*VWRITE,'!'
(A)
*VWRITE,'! Stress for element',
(A,F)
*VWRITE,'!'
(A)
*VWRITE,'eis,',I
(A,F)
P=EleIS(I,1,1)
*VWRITE,P,0.,0.,0.,0.,0.
(E,E,E,E,E,E)
!*ENDIF
*ENDDO
*CFCLOS

说明:补充资料仅用于学习参考,请勿用于其它任何用途。
参考词条