CN1891392B - 结合燃气涡轮机应用的超级合金的带垫片激光束焊接工艺 - Google Patents

结合燃气涡轮机应用的超级合金的带垫片激光束焊接工艺 Download PDF

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CN1891392B
CN1891392B CN2006101001914A CN200610100191A CN1891392B CN 1891392 B CN1891392 B CN 1891392B CN 2006101001914 A CN2006101001914 A CN 2006101001914A CN 200610100191 A CN200610100191 A CN 200610100191A CN 1891392 B CN1891392 B CN 1891392B
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D·A·诺沃克
G·冯
L·B·斯皮格尔
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    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
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Abstract

激光束焊接至少两个邻近的超级合金部件(12，14)的方法，其包括(a)沿着一对接合面(18，20)对齐部件，但没有支承板；(b)把超级合金垫片(16)放置在接合面之间；(c)使用激光束把部件焊接在一起，使沿着接合面的超级合金部件的部分与超级合金垫片混合；以及冷却部件以在部件之间产生对接焊缝(22)。

Description

结合燃气涡轮机应用的超级合金的带垫片激光束焊接工艺
技术领域
本发明总的涉及燃气涡轮机技术，更具体地，涉及用于结合镍，钴，和铁基超级合金的激光束焊接工艺。
背景技术
类似Rene N5的镍基超级合金，典型地包含大于10％的难熔元素，并且通常看作不可焊接的。然而，诸如激光来或电子束之类的低热输入焊接工艺的使用在很窄范围的焊接条件内产生无裂纹的焊接接缝。这些束工艺的一个缺点为在熔化区内的定向晶粒长大，其在焊接区域的中心形成清楚的树枝状边界。这种类型的晶粒结构使得接缝容易中心线裂纹并且导致很差的疲劳强度。例如，电子束焊接的N5/GTD-222接缝的疲劳寿命在1200和0.9％的应变下在大约100个循环时破坏，这比较低强度GTD-222基础金属的疲劳寿命低5倍。在这个范围的焊接性能水平导致燃气涡轮机运行期间焊接接缝的灾难性的破坏。
为了克服中心线裂纹问题，已经为焊接超级合金开发了几种可选的工艺。在它们之中，送丝电子束工艺(送丝EB)，预置垫片电子束工艺(垫片EB)和气钨弧工艺(TIG)已经证明在改进接缝的疲劳寿命中是最好的执行者。送丝EB工艺通过电子束焊接期间的自动送丝器加入可延展的超级合金填充金属。因为焊接金属延展性的增加，送丝EB接缝的疲劳寿命改进至在1200和0.9％的应变下1000个循环。然而，这个工艺受接缝厚度的限制。并且，当接缝厚度增加超过0.1英寸时未焊透(LOP)的缺陷经常发生。严重的LOP缺陷降低疲劳寿命至小于10个循环。然而，垫片EB工艺极大地增加接缝厚度，焊接接缝需要必需的垫板以停止电子束。这个垫板导致在接缝根部应力上升源。
另一个追求的可选的工艺是使用可延展的超级合金填充金属的TIG焊接。这个多道弧焊接工艺彻底改变了焊接区域内的定向晶粒结构，把延展性引入焊接金属，并且消除了必需的垫板。结果，TIG焊接接缝的疲劳寿命增加至在1200和0.9％的应变下1300个循环。然而，与弧焊接相关的高热输入造成相对大的翼片变形并增加了焊接内熔化不足缺陷的危险。变形的量时常禁止TIG工艺作为用于复杂的翼片结构的主要焊接工艺的使用。
发明内容
本发明提供改良的激光束焊接工艺以促进无缺陷超级合金焊接接缝的开发，其将改进高温和高应变范围的低循环疲劳寿命。该工艺也设计为实现完全的焊透焊接至0.5英寸深，消除了对必需的垫板的需要，降低了未焊透缺陷的倾向，并减少了熔化不足缺陷的危险。该工艺也降低了零件的变形并允许在复杂的翼片结构的生产接缝内的装配间隙变化。
更具体地，在一个示例性的实施例中，0.010-0.040英寸厚的镍基或钴基垫片预置并***镍基，钴基和铁基超级合金(例如，GTD-222，GTD-111，A286，FSX-414和Rene N5)的试样块之间。垫片的高度延伸超过接缝深度大约0.010英寸-0.150英寸。换句话说，垫片在接缝表面上向外突起0.010-0.150英寸。基础材料焊接到自身和其他候选超级合金的每个，不使用支承板。
因此，一方面，本发明涉及激光束焊接至少两个邻近的超级合金部件的方法，其包括：(a)沿着一对接合面对齐部件，但没有支承板；(b)把超级合金垫片放置在接合面之间；(c)使用激光束把部件焊接在一起，使沿着接合面的超级合金部件的部分与超级合金垫片混合；以及冷却部件以在部件之间产生对接焊缝。
另一方面，本发明涉及激光束焊接至少两个超级合金部件的方法，其包括沿着一对接合面对齐部件，但没有支承板；把超级合金垫片放置在接合面之间；使用激光束把部件焊接在一起，使沿着接合面的超级合金部件的部分与超级合金垫片混合；以及冷却部件以在部件之间产生对接焊缝；其中垫片在邻近部件上突出大约0.010至0.150°；并且其中用于激光焊接的参数包括：
瓦特数：1000-3500
速度：8至30ipm(英寸每分钟)
焦距：7
Figure 10003_0
英寸
垫片厚度：0.010至0.040英寸
间隙：在垫片和接合面之间0至0.010英寸
现在连同下面的附图详细地描述本发明。
附图说明
图1为焊接之前的激光垫片焊接装置的示意图；以及
图2为完成的激光垫片焊件的示意图。
具体实施方式
参考图1，激光垫片焊接装置10包括一对镍基超级合金(例如，GTD-222)试样块12，14，垫片16***位于镍基或钴基垫片16的每一侧上的相对的接合面18，20之间。在批露的例子中，垫片16为0.010和0.040英寸之间的厚度，并且注意垫片的高度延伸超过接缝深度，即，超过试样块12和14的高度或厚度大约0.10至0.150英寸。焊接接缝模型装配有从0至0.010英寸的焊接接缝间隙(在垫片16和接合面18，20之间)，并且通过激光束使用较低的功率设置定位焊接。沿着接缝的长度可以每二分之一英寸进行点定位焊。
在批露的例子中，用于激光垫片焊接工艺的焊接参数如下：
瓦特数：1000-3500
速度：8至30ipm(英寸每分钟)
焦距：7
Figure 10003_1
英寸
垫片厚度：0.010至0.040英寸
间隙：0至0.010英寸
注意在激光束焊接中，束自身沿着焊接接缝移动，不管其为平面或圆形。
图2示出了产生的对接焊缝22，在冷却后，把超级合金试样块12和14结合在一起，接合面18，20与垫片16的材料混合。注意，即使没有支承板，焊接材料仅在各个试样块12，14的下表面的下面稍微突出并且如果需要，可以机械加工齐平。类似地，焊缝的上不规则表面也可以机械加工与试样块齐平。
应意识到，上面描述的激光垫片焊接工艺也适于钴基和铁基超级合金的使用，例如，GTD-111，A286，FSX-414，和Rene N5。
改良的激光束焊接工艺产生直到0.5英寸深的完全的焊透焊接，消除了必需的支承板的需要，降低了未焊透缺陷的倾向，并减少了熔化不足缺陷的危险。
尽管以部件或试样块的形式描述，应意识到，焊接的部件可以为许多涡轮机零件的任何一个，例如，蒸汽出口烟道至喷嘴接缝；叶片至叶片顶端罩子，等等。
尽管连同当前认为最实际和优选的实施例描述了本发明，将理解本发明不限于批露的实施例，而是相反，意在覆盖包括在所附权利要求书精神和范围内的各种更改和等价布置。
部件列表
激光垫片焊接装置10
试样块对12，14
垫片16
相对的接合面18，20
对接焊缝22

Claims (7)

1.一种激光束焊接至少两个邻近的超级合金部件(12，14)的方法，其包括：
(a)沿着一对接合面(18，20)对齐部件，但没有支承板；
(b)把超级合金垫片(16)放置在接合面之间；
(c)使用激光束把部件焊接在一起，使沿着接合面的超级合金部件的部分与超级合金垫片混合；以及冷却部件以在部件之间产生对接焊缝(22)，
其特征在于，
沿着接缝的长度以每二分之一英寸进行点定位焊，并且，
其中用于实施步骤(c)的参数包括：
瓦特数：1000-3500瓦
速度：8至30ipm
焦距：71/2英寸
垫片厚度：0.010至0.040英寸
间隙：在垫片和接合面之间为0至0.010英寸，使得激光工艺产生直到0.5英寸深的完全的焊透焊接。
2.根据权利要求1所述的方法，其中超级合金部件(12，14)为镍基，钴基或铁基超级合金。
3.根据权利要求1所述的方法，其中所述垫片(16)为镍基或钴基超级合金。
4.根据权利要求1所述的方法，其中垫片(16)在邻近部件上面突出。
5.根据权利要求4所述的方法，其中垫片(16)在邻近部件上面突出大约0.010至0.150英寸。
6.根据权利要求1所述的方法，其中垫片(16)延伸超出邻近接合面。
7.一种激光束焊接至少两个超级合金部件(12，14)的方法，其包括：
沿着一对接合面(18，20)对齐部件，但没有支承板；
把超级合金垫片(16)放置在接合面之间；
使用激光束把部件焊接在一起，使沿着接合面的超级合金部件的部分与超级合金垫片混合；以及冷却部件以在部件之间产生对接焊缝(22)；
其特征在于，
沿着接缝的长度以每二分之一英寸进行点定位焊，并且，
其中垫片(16)在邻近部件(12，14)上面突出大约0.010至0.150英寸；并且其中用于激光焊接的参数包括：
瓦特数：1000-3500瓦
速度：8至30ipm
焦距：71/2英寸
垫片厚度：0.010至0.040英寸
间隙：在垫片和接合面之间为0至0.010英寸，使得激光工艺产生直到0.5英寸深的完全的焊透焊接。
CN2006101001914A 2005-06-30 2006-06-30 结合燃气涡轮机应用的超级合金的带垫片激光束焊接工艺 Expired - Fee Related CN1891392B (zh)

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