CN104313600B - Impaired titanium alloy forging continuous point type forging and stamping Laser forming repair method - Google Patents
Impaired titanium alloy forging continuous point type forging and stamping Laser forming repair method Download PDFInfo
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- 238000005242 forging Methods 0.000 title claims abstract description 76
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 62
- 230000008439 repair process Effects 0.000 title claims abstract description 26
- 238000000034 method Methods 0.000 title claims abstract description 14
- 230000001771 impaired effect Effects 0.000 title claims 4
- 230000008021 deposition Effects 0.000 claims abstract description 22
- 239000000956 alloy Substances 0.000 claims abstract description 13
- 238000010438 heat treatment Methods 0.000 claims abstract description 10
- 239000000843 powder Substances 0.000 claims abstract description 10
- 238000001953 recrystallisation Methods 0.000 claims abstract description 10
- 238000001816 cooling Methods 0.000 claims abstract 2
- 238000005253 cladding Methods 0.000 claims description 13
- 239000000463 material Substances 0.000 claims description 9
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 4
- 229910052786 argon Inorganic materials 0.000 claims description 2
- 230000014759 maintenance of location Effects 0.000 claims 2
- 238000007789 sealing Methods 0.000 claims 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 abstract description 5
- 239000001301 oxygen Substances 0.000 abstract description 5
- 229910052760 oxygen Inorganic materials 0.000 abstract description 5
- 230000009467 reduction Effects 0.000 abstract description 5
- 238000003825 pressing Methods 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 9
- 230000008569 process Effects 0.000 description 7
- 229910045601 alloy Inorganic materials 0.000 description 6
- 229910052751 metal Inorganic materials 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- 230000035882 stress Effects 0.000 description 6
- 238000002844 melting Methods 0.000 description 5
- 230000008018 melting Effects 0.000 description 4
- 238000007712 rapid solidification Methods 0.000 description 4
- 229910000883 Ti6Al4V Inorganic materials 0.000 description 3
- 230000007123 defense Effects 0.000 description 3
- 239000000758 substrate Substances 0.000 description 3
- 239000010936 titanium Substances 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001513 hot isostatic pressing Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 229910052758 niobium Inorganic materials 0.000 description 1
- 230000006911 nucleation Effects 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 239000003870 refractory metal Substances 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 229910052715 tantalum Inorganic materials 0.000 description 1
- 230000003685 thermal hair damage Effects 0.000 description 1
- 238000007751 thermal spraying Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
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Abstract
一种受损钛合金锻件连续点式锻压激光成形修复方法，其主要是将受损钛合金锻件置入惰性气氛保护箱，控制氧体积分数含量小于5×10‑5；采用高精度双路同轴送粉系统进行钛合金激光沉积修复，激光功率：1800‑5000W；扫描速度：3‑10mm/s；光斑直径：3‑6mm；搭接率：30‑50％；送粉速率：5‑15g/min；对上述经过激光修复的钛合金锻件进行锻压，压下量为4‑12吨；在计算机控制下，沿激光沉积修复钛合金材料上表面，逐点连续实施小面积锻压，重复进行上述步骤，直至达到修复锻件合格的标准尺寸；对上述经过修复的钛合金锻件进行再结晶热处理，温度为850‑960℃，保温时间为1h‑3h，空冷至室温。本发明可以实现对成形修复钛合金局部结构内部再结晶组织结构和晶粒尺寸的主动控制。
A method for repairing damaged titanium alloy forgings by continuous point-type forging laser forming, which mainly includes placing the damaged titanium alloy forgings in an inert atmosphere protection box, and controlling the oxygen volume fraction to less than 5×10-5; Shaft powder feeding system for titanium alloy laser deposition repair, laser power: 1800‑5000W; scanning speed: 3‑10mm/s; spot diameter: 3‑6mm; lap rate: 30‑50%; powder feeding rate: 5‑15g /min; carry out forging and pressing on the above-mentioned laser repaired titanium alloy forgings, the reduction is 4-12 tons; under the control of the computer, along the laser deposition and repairing the upper surface of the titanium alloy material, small-area forging is continuously implemented point by point, and the above steps are repeated. Steps, until the qualified standard size of the repaired forging is reached; the above repaired titanium alloy forging is subjected to recrystallization heat treatment at a temperature of 850-960°C, holding time of 1h-3h, and air cooling to room temperature. The invention can realize the active control of the internal recrystallization structure and grain size of the local structure of the formed and repaired titanium alloy.
Description
技术领域technical field
本发明涉及一种金属锻件的修复方法。The invention relates to a method for repairing metal forgings.
背景技术：Background technique:
激光成形修复是一种先进的金属零件修复与再制造技术，该技术利用快速原型制造(Rapid Prototype Manufacturing,RPM)技术的基本原理，计算机数控系统在受损金属零件局部结构CAD数字模型分层切片数据驱动下，通过逐层添加激光熔化/快速凝固金属材料，快速恢复金属零件局部损伤结构的几何特性及零件的服役性能，与一些传统的修复和再制造技术(热喷涂、电刷镀、钎焊、TIG焊、MIG焊)相比，该技术存在以下突出优点：(1)激光束能量集中，热影响区极小，激光成形修复过程对金属零件基材几乎无热损伤；(2)柔性高，在无需任何模具和工装条件下快速实现金属零件任意形状局部损伤结构的近终成形；(3)材料适用范围宽，可以实现对包括W、Mo、Nb、Ta等难熔金属及合金、高熔点金属间化合物合金以及Ti基等各种高活性合金等在内的各类高性能金属材料零件的修复与再制造。正是由于其上述独特特点，使之在航空、航天等国防装备中高附加值重点零部件修复与再制造上具有极为广阔的应用前景。Laser forming repair is an advanced metal parts repair and remanufacturing technology. This technology uses the basic principle of Rapid Prototype Manufacturing (RPM) technology. Driven by data, by adding laser melting/rapid solidification metal materials layer by layer, the geometric characteristics of the local damaged structure of the metal parts and the service performance of the parts can be quickly restored, and some traditional repair and remanufacturing technologies (thermal spraying, brush plating, brazing Compared with welding, TIG welding, MIG welding), this technology has the following outstanding advantages: (1) The energy of the laser beam is concentrated, the heat-affected zone is extremely small, and the laser forming repair process has almost no thermal damage to the base material of the metal part; (2) Flexible High, without any molds and tooling, the near-net forming of metal parts with arbitrary shapes and local damage structures can be quickly realized; (3) The material has a wide range of applications, and can realize refractory metals and alloys including W, Mo, Nb, Ta, etc. Repair and remanufacture of various high-performance metal material parts including high-melting point intermetallic compound alloys and Ti-based and other high-activity alloys. It is precisely because of the above-mentioned unique characteristics that it has a very broad application prospect in the repair and remanufacturing of high value-added key components in aviation, aerospace and other national defense equipment.
1995-1997年，美国约翰哈普金斯大学、宾夕法尼亚州立大学、MTS公司及波音公司在美国国防部国防先进研究计划署(DARPA)和国防部海军研究办公室(ONR)联合资助下，研发出名为LasformTM的飞机钛合金结构件激光快速成形与修复技术，1998年MTS公司独资建立了AeroMet子公司，专门从事LasformTM技术的工程化应用。LasformTM的技术原理是：以钛合金热轧件或锻件为基板，计算机控制激光熔化钛合金粉末/快速凝固逐层堆积，在钛合金基板上以添加的方式“生长成形”出加强筋、连接接头等结构，因此，LasformTM技术实质上制造的是一种内部具有混合组织的钛合金结构件。在激光熔化沉积成形过程中，激光移动熔池超常冶金动力学行为及其在超高温度梯度作用下非平衡快速凝固形核和长大过程，决定了激光熔化沉积成形“添加”的加强筋及连接接头，其内部晶粒形态、尺寸、晶体取向、晶界结构等与钛合金基板组织间存在极为显著的差异，并直接导致两者间力学性能不一致，即使再经热等静压(HIP)、开模锻造(Open Die Forging)加工，AeroMet公司制造的Ti6Al4V钛合金结构件，其疲劳力学性能仍然显著低于钛合金锻件，难以实现其在飞机结构件上的应用，AeroMet公司最终于2005年12月被迫停业关闭。From 1995 to 1997, under the joint funding of the US Defense Advanced Research Projects Agency (DARPA) and the Department of Defense Office of Naval Research (ONR), John Hupkins University, Pennsylvania State University, MTS and Boeing developed the famous For Lasform TM 's laser rapid prototyping and repair technology for aircraft titanium alloy structural parts, in 1998, MTS Corporation established AeroMet, a wholly-owned subsidiary, specializing in the engineering application of Lasform TM technology. The technical principle of Lasform TM is: using titanium alloy hot-rolled parts or forgings as the substrate, computer-controlled laser melting titanium alloy powder/rapid solidification is accumulated layer by layer, and "grows and forms" reinforcement ribs and connections on the titanium alloy substrate in an additive manner. Therefore, Lasform TM technology essentially manufactures a titanium alloy structure with a mixed structure inside. In the laser melting deposition forming process, the ultra-metallurgical dynamic behavior of the laser moving molten pool and the non-equilibrium rapid solidification nucleation and growth process under the action of an ultra-high temperature gradient determine the "addition" of the laser melting deposition forming. There are extremely significant differences between the internal grain morphology, size, crystal orientation, grain boundary structure, etc. of the connection joint and the structure of the titanium alloy substrate, which directly leads to inconsistent mechanical properties between the two, even after hot isostatic pressing (HIP) , Open Die Forging (Open Die Forging) processing, Ti6Al4V titanium alloy structural parts manufactured by AeroMet, its fatigue mechanical properties are still significantly lower than titanium alloy forgings, it is difficult to realize its application in aircraft structural parts, AeroMet finally in 2005 It was forced to close down in December.
西北工业大学采用激光立体成形技术对Ti6Al4V和Ti17两种钛合金锻件进行激光成形修复，由于激光修复钛合金材料非平衡快速凝固组织与钛合金锻件基体锻造退火组织间的差异，以及两者间力学性能不一致，激光成形修复Ti6Al4V、Ti17锻件，其疲劳性能远低于钛合金锻件；北京有色金属研究总院研究了激光修复TC11钛合金锻件内部组织及其力学性能，结果表明，激光修复TC11钛合金材料组织与锻件基体组织显著不同，且塑性明显低于钛合金锻件，修复的TC11钛合金锻件的整体力学性能达不到航空服役力学性能标准。Northwestern Polytechnical University used laser stereoforming technology to repair Ti6Al4V and Ti17 titanium alloy forgings by laser forming. Due to the difference between the non-equilibrium rapid solidification structure of the laser repaired titanium alloy material and the forging and annealing structure of the titanium alloy forging matrix, and the mechanical properties between the two The performance is inconsistent, and the fatigue performance of Ti6Al4V and Ti17 forgings repaired by laser forming is much lower than that of titanium alloy forgings; Beijing Nonferrous Metals Research Institute has studied the internal structure and mechanical properties of laser repaired TC11 titanium alloy forgings. The material structure is significantly different from the matrix structure of the forging, and the plasticity is significantly lower than that of the titanium alloy forging. The overall mechanical properties of the repaired TC11 titanium alloy forging cannot meet the mechanical performance standards for aviation service.
发明内容：Invention content:
为了解决激光成形修复钛合金锻件，其力学性能远低于钛合金锻件等问题，本发明提供一种受损钛合金锻件连续点式锻压激光成形修复方法。In order to solve the problem that the mechanical properties of titanium alloy forgings repaired by laser forming are far lower than those of titanium alloy forgings, the present invention provides a continuous point forging laser forming repair method for damaged titanium alloy forgings.
本发明的技术方案如下：Technical scheme of the present invention is as follows:
(1)将受损大型复杂航空钛合金锻件置入惰性气氛保护箱，装卡后，封箱，为防止钛合金在激光快速成形过程中氧化，使用氩气保护，控制氧体积分数含量小于5×10-5；然后采用高精度双路同轴送粉系统进行钛合金激光沉积修复，按照沉积轨迹直到第一层熔覆完成；激光工艺参数为激光功率：1800-5000W；扫描速度：3-10mm/s；光斑直径：3-6mm；搭接率：30-50％；送粉速率：5-15g/min；(1) Put the damaged large and complex aerospace titanium alloy forgings into an inert atmosphere protection box. After loading the card, seal the box. In order to prevent the titanium alloy from being oxidized during the laser rapid forming process, use argon protection to control the oxygen volume fraction to less than 5 ×10-5; Then use high-precision dual-channel coaxial powder feeding system for titanium alloy laser deposition repair, follow the deposition track until the first layer of cladding is completed; laser process parameters are laser power: 1800-5000W; scanning speed: 3- 10mm/s; spot diameter: 3-6mm; lap rate: 30-50%; powder feeding rate: 5-15g/min;
(2)对上述经过激光修复的钛合金锻件进行锻压，选用弧面点式压头，设置压力机压头的压下量为4-12吨；，在计算机控制下，沿激光沉积修复钛合金材料上表面，逐点连续实施小面积锻压，将第一层熔覆材料全部锻压完成，迫使激光沉积修复钛合金材料发生由表及里剧烈塑性冷变形，使激光沉积修复钛合金材料非平衡快速凝固组织转变为锻造组织；由于点式锻压具有变形区小、无变形死区、变形区内的应力状态为三向压应力的特点，因此，一方面，连续点式锻压易于实现激光修复钛合金层的逐点均匀塑性变形，有效保证激光沉积修复钛合金锻造组织的均匀性；另一方面，经过连续点式锻压后，前一激光沉积修复钛合金材料中的残余拉应力将转变为残余压应力。(2) Forging and pressing the above-mentioned titanium alloy forgings repaired by laser, using arc point indenter, setting the reduction amount of the indenter of the press to 4-12 tons; under the control of the computer, repairing the titanium alloy along the laser deposition On the upper surface of the material, small-area forging is carried out point by point continuously, and the first layer of cladding material is completely forged, forcing the laser deposition repair titanium alloy material to undergo severe plastic cold deformation from the surface to the inside, so that the laser deposition repair titanium alloy material is unbalanced and fast The solidified structure is transformed into a forged structure; because point-type forging has the characteristics of small deformation zone, no deformation dead zone, and the stress state in the deformation zone is three-dimensional compressive stress, therefore, on the one hand, continuous point-type forging is easy to achieve laser repair of titanium alloys. The point-by-point uniform plastic deformation of the layer can effectively ensure the uniformity of the forged structure of the laser deposition repaired titanium alloy; stress.
重复进行上述(1)、(2)步骤，直至达到修复锻件合格的标准尺寸。Repeat the above steps (1) and (2) until the standard size of the repaired forging is reached.
(3)将上述经过修复的钛合金锻件放入热处理炉中进行再结晶热处理，温度为850-960℃，最优温度为920-940℃；保温时间为1-3h，最优保温时间为1h；空冷至室温。(3) Put the above-mentioned repaired titanium alloy forging into a heat treatment furnace for recrystallization heat treatment, the temperature is 850-960°C, the optimal temperature is 920-940°C; the holding time is 1-3h, and the optimal holding time is 1h ; Air cool to room temperature.
本发明与现有技术相比具有如下优点：Compared with the prior art, the present invention has the following advantages:
可以实现对成形修复钛合金锻件局部结构内部再结晶组织结构、再结晶晶粒尺寸的主动控制，避免了在新的激光沉积修复过程中，由于瞬态热应力与前一激光沉积修复钛合金材料中的残余拉应力交互作用而引起应力强度增大，同时避免了由于应力强度超过钛合金材料屈服强度而引起钛合金锻件产生塑性变形；并有效地防止了由于热应力强度循环累积所引起的钛合金锻件变形累积效应。It can realize the active control of recrystallization structure and recrystallization grain size in the local structure of forming and repairing titanium alloy forgings, avoiding the problems caused by transient thermal stress and previous laser deposition repairing titanium alloy materials in the new laser deposition repair process. The residual tensile stress in the interaction causes the stress intensity to increase, and at the same time avoids the plastic deformation of the titanium alloy forging caused by the stress intensity exceeding the yield strength of the titanium alloy material; and effectively prevents the titanium alloy forging caused by the thermal stress intensity cycle accumulation. Cumulative effects of deformation in alloy forgings.
附图说明Description of drawings
图1是本发明连续点式锻压激光成形修复过程示意图。Fig. 1 is a schematic diagram of the continuous point forging laser forming repair process of the present invention.
具体实施方式：detailed description:
实施例1Example 1
如图1所示，将受损大型复杂航空钛合金锻件1置入惰性气氛保护箱6，装卡后，安装上盖5封箱，将箱内气氛中的氧含量降至50PPm后，通过激光头2，采用高精度双路同轴送粉系统进行钛合金激光沉积修复，按照沉积轨迹直到第一层熔覆完成。激光工艺参数为激光功率：1800W；扫描速度：3mm/s；光斑直径：3mm；搭接率：30％；送粉速率：5g/min，在钛合金锻件表面形成钛合金激光沉积修复层7；对上述经过激光修复的钛合金锻件进行锻压，与压杆3连接的压力机压头4为弧面点式压头，设置压头的压下量为4吨，在计算机控制下，沿激光沉积修复钛合金锻件上表面，逐点连续实施小面积锻压，将第一层熔覆材料全部锻压完成。重复上述熔覆和锻压步骤直至达到原锻件尺寸，将上述经过修复的钛合金锻件放入热处理炉中进行再结晶热处理，温度为850℃，保温时间为2h，空冷至室温。As shown in Figure 1, put the damaged large and complex aerospace titanium alloy forging 1 into the inert atmosphere protection box 6, install the upper cover 5 to seal the box after loading, and reduce the oxygen content in the atmosphere in the box to 50PPm. Head 2, using a high-precision two-way coaxial powder feeding system for titanium alloy laser deposition repair, follow the deposition trajectory until the first layer of cladding is completed. Laser process parameters are laser power: 1800W; scanning speed: 3mm/s; spot diameter: 3mm; Forging the above-mentioned titanium alloy forging that has been repaired by laser, the press head 4 connected with the pressure rod 3 is an arc point type indenter, and the reduction amount of the indenter is set to 4 tons. Repair the upper surface of the titanium alloy forging, and carry out small-area forging point by point continuously, and complete the forging of the first layer of cladding material. Repeat the cladding and forging steps above until the size of the original forging is reached, then put the repaired titanium alloy forging into a heat treatment furnace for recrystallization heat treatment at a temperature of 850°C, holding time for 2 hours, and air-cool to room temperature.
实施例2Example 2
将受损大型复杂航空钛合金锻件置入惰性气氛保护箱，装卡后，改善上盖封箱，将箱内气氛中的氧含量降至50PPm后，通过激光头，采用高精度双路同轴送粉系统进行钛合金激光沉积修复，按照沉积轨迹直到第一层熔覆完成。调整激光工艺参数为激光功率：5500W；扫描速度：7mm/s；光斑直径：4mm；搭接率：40％；送粉速率：10g/min；在钛合金锻件表面形成钛合金激光沉积修复层；对上述经过激光修复的钛合金锻件进行锻压，与压杆连接的压力机压头为弧面点式压头，设置压头的压下量为8吨，在计算机控制下，沿激光沉积修复钛合金锻件上表面，逐点连续实施小面积锻压，将第一层熔覆材料全部锻压完成。重复上述熔覆和锻压步骤直至达到原锻件尺寸，将上述经过修复的钛合金锻件放入热处理炉中进行再结晶热处理，温度为920℃，保温时间为1h，空冷至室温。Put the damaged large and complex aviation titanium alloy forgings into the inert atmosphere protection box. After loading the card, improve the upper cover to seal the box, and reduce the oxygen content in the atmosphere in the box to 50PPm. After passing through the laser head, adopt high-precision two-way coaxial The powder feeding system performs titanium alloy laser deposition repair, following the deposition track until the first layer of cladding is completed. Adjust the laser process parameters to laser power: 5500W; scanning speed: 7mm/s; spot diameter: 4mm; Forging and pressing the above-mentioned titanium alloy forgings repaired by laser, the press head connected to the pressure rod is an arc point type indenter, and the reduction amount of the indenter is set to 8 tons. Under the control of the computer, along the laser deposition repair titanium On the upper surface of the alloy forging, small-area forging is carried out point by point continuously, and the first layer of cladding material is completely forged. Repeat the cladding and forging steps above until the size of the original forging is reached, then put the repaired titanium alloy forging into a heat treatment furnace for recrystallization heat treatment at a temperature of 920°C for 1 hour, and air cool to room temperature.
实施例3Example 3
将受损大型复杂航空钛合金锻件置入惰性气氛保护箱，装卡后，改善上盖封箱，将箱内气氛中的氧含量降至50PPm后，通过激光头，采用高精度双路同轴送粉系统进行钛合金激光沉积修复，按照沉积轨迹直到第一层熔覆完成。调整激光工艺参数为激光功率：10000W；扫描速度：10mm/s；光斑直径：6mm；搭接率：50％；送粉速率：15g/min；在钛合金锻件表面形成钛合金激光沉积修复层；对上述经过激光修复的钛合金锻件进行锻压，与压杆连接的压力机压头为弧面点式压头，设置压头的压下量为12吨，在计算机控制下，沿激光沉积修复钛合金锻件上表面，逐点连续实施小面积锻压，将第一层熔覆材料全部锻压完成。重复上述熔覆和锻压步骤直至达到原锻件尺寸，将上述经过修复的钛合金锻件放入热处理炉中进行再结晶热处理，温度为960℃，保温时间为3h，空冷至室温。Put the damaged large and complex aviation titanium alloy forgings into the inert atmosphere protection box. After loading the card, improve the upper cover to seal the box, and reduce the oxygen content in the atmosphere in the box to 50PPm. After passing through the laser head, adopt high-precision two-way coaxial The powder feeding system performs titanium alloy laser deposition repair, following the deposition track until the first layer of cladding is completed. Adjust the laser process parameters as laser power: 10000W; scanning speed: 10mm/s; spot diameter: 6mm; Forging the above laser repaired titanium alloy forgings, the press head connected to the pressure rod is an arc point type indenter, and the reduction amount of the indenter is set to 12 tons. Under the control of the computer, the laser deposition repair titanium On the upper surface of the alloy forging, small-area forging is carried out point by point continuously, and the first layer of cladding material is completely forged. Repeat the cladding and forging steps above until the size of the original forging is reached, then put the repaired titanium alloy forging into a heat treatment furnace for recrystallization heat treatment at a temperature of 960°C, holding time for 3 hours, and air-cool to room temperature.
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