CN102941396A - Anti-deformation repair welding method for shell of aero-engine ignition device - Google Patents
Anti-deformation repair welding method for shell of aero-engine ignition device Download PDFInfo
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- CN102941396A CN102941396A CN2012103755150A CN201210375515A CN102941396A CN 102941396 A CN102941396 A CN 102941396A CN 2012103755150 A CN2012103755150 A CN 2012103755150A CN 201210375515 A CN201210375515 A CN 201210375515A CN 102941396 A CN102941396 A CN 102941396A
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Abstract
The invention aims to provide an anti-deformation repair welding method for a shell of an aero-engine ignition device, which comprises the steps of: fixing the ignition device onto an anti-deformation fixture to shape, drilling a stopper hole at the crack end of a crack portion, using an alloy rotary file to groove the crack portion and polish surroundings of the crack portion, adopting an argon arc welding method to repair and weld the crack, and using ultrasonic wave to eliminate the stress at the welded seam, at last, performing dye check, if the check result can meet the technical requirement to engine overhaul, installing the shell to the ignition device to be used. The method lays a foundation for elimination of the crack fault for the aero-engine ignition device.
Description
Technical field
The present invention relates to the engine overhaul technology, a kind of aero-engine igniter housing anti-deformation repair method is provided especially.
Background technology
The engine ignitor housing is the main seal member of engine by-pass air duct, engine finds that in the overhaul process igniter is owing to the reasons such as vibration in long-term the use cause root crack, cause whole igniter not use, still there are not at present method for repairing crack and interchangeable self-made components, if igniter cracked housing and transaxle, just can only scrap, cause huge economic waste.
Summary of the invention
The object of the present invention is to provide a kind of aero-engine igniter housing anti-deformation repair method, formalize by igniter being fixed on the anti-deformation tool, and crack site beaten stop hole at crack-tip, then with the alloy rotary file crack site is slotted and polished on every side, adopt the argon arc welding repair method that crackle is carried out repair welding, and eliminate stress with the ultrasonic wave butt welded seam, last dyeing inspection, check result can satisfy the specification requirement of engine overhaul, the use of can installing.The method is that the eliminating of engine ignitor crack fault is laid a good foundation.
The present invention specifically provides a kind of aero-engine igniter housing anti-deformation repair method, and it is characterized in that: step is as follows:
(1), the engine ignitor housing is fixed on the anti-deformation tool;
(2), determine crack length with the coloration detection method, then beat the stop hole of φ 2 ~ 3mm at the end of crack site, with the alloy rotary file crackle is slotted, and polish to around the crackle, polishing is to metallic luster occurring;
(3), with the argon arc welding repair method crack site is carried out repair welding, welding parameter is:
Electric current kind: direct current, positive polarity;
Electric current: 40 ~ 50A;
Argon flow amount: welding gun, 14 ~ 16L/min;
Back side blowing argon gas: 8 ~ 10L/min;
Electrode: lanthanide tungsten φ 2.0;
Scolder: BT20-ICB or TA1, φ 1.2-φ 1.6;
(4), overlap is polished, make overlap not be higher than matrix surface 0.3mm;
(5), the butt welded seam zone carries out ultrasonic wave and eliminates stress, technological parameter is as follows:
Impact amplitude no-load current: 1.0 ~ 1.6A;
Precompression: rifle deadweight 100N;
Impact velocity: 300 ~ 500mm/min;
Impact number of times: 3 times;
Frequency of impact: 20KHz;
(6), check with the colouring butt welded seam, it is qualified not having crackle;
(7), the igniter housing is carried out the factory test checking, butt welded seam dyeing inspection after the checking, the qualified permission installation of dyeing inspection use.
Aero-engine igniter housing anti-deformation repair method provided by the invention, it is characterized in that: described anti-deformation tool is circular ring type fixing tool 1,12 through holes (as shown in Figure 1, 2) have evenly distributed on this fixing tool 1.
Aero-engine igniter housing anti-deformation repair method provided by the invention, it is characterized in that: be the part deformation that prevents that thermal stress causes in the argon arc welding process of patch weld, in welding process, adopt the segmentation welding manner: with weld seam since an end, weld one section, separate one section and weld again, after then equitemperature drops to below 100 ℃, to weld less than the place of welding, welding can prevent part deformation so again.
Adopt method provided by the invention successfully to repair and finish 10 igniters, and the use of having installed, create approximately 500,000 RMB of economic worth, the method can be applied to the repairing of other correlated parts, has broad application prospects.
Description of drawings
Fig. 1 anti-deformation tool cutaway view;
Fig. 2 anti-deformation tool top view;
Fig. 3 igniter is fixed on the cutaway view on the anti-deformation tool;
Fig. 4 igniter is fixed on the local enlarged diagram on the anti-deformation tool.
The specific embodiment
For the igniter housing that root cracks, adopt repair method reparation of the present invention, its concrete steps are as follows:
(1), the engine ignitor housing is fixed on (shown in Fig. 3,4) on the fixing tool 1;
(2), determine crack length with the coloration detection method, then beat the stop hole of φ 2mm at the end of crack site, with the alloy rotary file crackle is slotted, and polish to around the crackle, polishing is to metallic luster occurring;
(3), with the argon arc welding repair method crack site is carried out repair welding, in welding process, adopt the segmentation welding manner: with weld seam since an end, weld one section, separating one section welds again, then after equitemperature drops to below 100 ℃, will weld less than the place of welding, welding parameter is again:
Electric current kind: direct current, positive polarity;
Electric current: 40 ~ 50A;
Argon flow amount: welding gun, 14L/min;
Back side blowing argon gas: 8L/min;
Electrode: lanthanide tungsten φ 2.0;
The BT20-ICB of scolder: φ 1.6;
(4), overlap is polished with emery wheel, do not allow the matrix material of damaging during polishing, overlap is not higher than matrix surface 0.3mm after the polishing;
(5), carrying out ultrasonic wave with HY2050 type ultrasonic impact device butt welded seam zone eliminates stress, the impact head butt welded seam of selecting to adapt with the part weld seam carries out shock treatment processing, swing on the direction of the impact head of impact gun perpendicular to weld seam, and move around along the fusion length direction, technological parameter is as follows:
Impact amplitude no-load current: 1.0 ~ 1.6A;
Precompression: rifle deadweight 100N;
Impact velocity: 300 ~ 500mm/min;
Impact number of times: 3 times;
Frequency of impact: 20KHz;
(6), check with the colouring butt welded seam, it is qualified not having crackle;
(7), the igniter housing is carried out the factory test checking, butt welded seam dyeing inspection after the checking, the qualified permission installation of dyeing inspection use.
Technological process is with embodiment 1, and difference is: beat the stop hole of φ 3mm at the end of crack site, when with the argon arc welding repair method crack site being carried out repair welding, argon flow amount is welding gun 16L/min; Back side blowing argon gas 9L/min; The TA1 of scolder: φ 1.2.
The postwelding result of the test
By choosing 10 components parts for assembly of a machine the igniter housing of scrapping from crackle, carry out repair welding, repair welding result such as table 1 according to embodiment 1,2 step:
Table 1 repair welding result
By 10 welding result inspections, although there are two components parts for assembly of a machine to be welded with slight deformation, not super repairing standards, it is qualified to repair.
Choose two and participated in factory test, behind factory test, the igniter housing is carried out dyeing inspection qualified, and the igniter housing do not have buckling deformation, so passed through long examination examination, allow installation to use.
Claims (3)
1. aero-engine igniter housing anti-deformation repair method, it is characterized in that: step is as follows:
(1), the engine ignitor housing is fixed on the anti-deformation tool;
(2), determine crack length with the coloration detection method, then beat the stop hole of φ 2 ~ 3mm at the end of crack site, with the alloy rotary file crackle is slotted, and polish to around the crackle, polishing is to metallic luster occurring;
(3), with the argon arc welding repair method crack site is carried out repair welding, welding parameter is:
Electric current kind: direct current, positive polarity;
Electric current: 40 ~ 50A;
Argon flow amount: welding gun, 14 ~ 16L/min;
Back side blowing argon gas: 8 ~ 10L/min;
Electrode: lanthanide tungsten φ 2.0;
Scolder: BT20-ICB or TA1, φ 1.2-φ 1.6;
(4), overlap is polished, make overlap not be higher than matrix surface 0.3mm;
(5), the butt welded seam zone carries out ultrasonic wave and eliminates stress, technological parameter is as follows:
Impact amplitude no-load current: 1.0 ~ 1.6A;
Precompression: rifle deadweight 100N;
Impact velocity: 300 ~ 500mm/min;
Impact number of times: 3 times;
Frequency of impact: 20KHz;
(6), check with the colouring butt welded seam, it is qualified not having crackle;
(7), the igniter housing is carried out the factory test checking, butt welded seam dyeing inspection after the checking, the qualified permission installation of dyeing inspection use.
2. according to the described aero-engine igniter of claim 1 housing anti-deformation repair method, it is characterized in that: described anti-deformation tool is circular ring type fixing tool (1), and 12 through holes have evenly distributed on this fixing tool (1).
3. according to the described aero-engine igniter of claim 1 housing anti-deformation repair method, it is characterized in that: be the part deformation that prevents that thermal stress causes in the argon arc welding process of patch weld, in welding process, adopt the segmentation welding manner: with weld seam since an end, weld one section, separate one section and weld again, after then equitemperature drops to below 100 ℃, will weld less than the place of welding again.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012103755150A CN102941396A (en) | 2012-09-29 | 2012-09-29 | Anti-deformation repair welding method for shell of aero-engine ignition device |
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| CN2012103755150A CN102941396A (en) | 2012-09-29 | 2012-09-29 | Anti-deformation repair welding method for shell of aero-engine ignition device |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103586560A (en) * | 2013-11-12 | 2014-02-19 | 哈尔滨东安发动机（集团）有限公司 | Method for repairing cracks in installing support of combustion box |
| CN104384816A (en) * | 2014-10-21 | 2015-03-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Welding method for box type part of air intake machine |
| CN106493450A (en) * | 2016-11-17 | 2017-03-15 | 中国华冶科工集团有限公司 | Cleft welding method |
| CN106808165A (en) * | 2017-02-28 | 2017-06-09 | 中航湖南通用航空发动机有限公司 | The processing method of impeller outer cover in a kind of aero-engine |
| CN109531046A (en) * | 2018-11-27 | 2019-03-29 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine shunting shaped part spot welding method for repairing crack |
| CN110465728A (en) * | 2019-08-05 | 2019-11-19 | 大连理工大学 | High-power protected type core main pump c-type sealing structural component repeats welding procedure |
| CN110977106A (en) * | 2019-11-11 | 2020-04-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Repair welding repairing method for cracks of titanium alloy fan case |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1288797A (en) * | 2000-10-27 | 2001-03-28 | 重庆大学 | Crack welding and repairing process for ferrous metal parts |
| US6338765B1 (en) * | 1998-09-03 | 2002-01-15 | Uit, L.L.C. | Ultrasonic impact methods for treatment of welded structures |
| CN102430889A (en) * | 2011-09-09 | 2012-05-02 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for repairing crack and chipping of shunt ring of case |
-
2012
- 2012-09-29 CN CN2012103755150A patent/CN102941396A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6338765B1 (en) * | 1998-09-03 | 2002-01-15 | Uit, L.L.C. | Ultrasonic impact methods for treatment of welded structures |
| CN1288797A (en) * | 2000-10-27 | 2001-03-28 | 重庆大学 | Crack welding and repairing process for ferrous metal parts |
| CN102430889A (en) * | 2011-09-09 | 2012-05-02 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for repairing crack and chipping of shunt ring of case |
Non-Patent Citations (3)
| Title |
|---|
| 常敏等: "发动机高压涡轮工作叶片叶尖裂纹修复研究", 《中国航空学会第三届航空发动机可靠性学术交流会》, 1 November 2005 (2005-11-01), pages 244 - 250 * |
| 杨苹等: "氩弧焊修复尾喷管裂纹", 《机械制造》, vol. 41, no. 466, 30 June 2003 (2003-06-30), pages 57 * |
| 陈爱国: "船用螺旋浆裂纹氩弧焊修复工艺探讨", 《中国水运》, no. 5, 31 May 2006 (2006-05-31), pages 42 - 43 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103586560A (en) * | 2013-11-12 | 2014-02-19 | 哈尔滨东安发动机（集团）有限公司 | Method for repairing cracks in installing support of combustion box |
| CN103586560B (en) * | 2013-11-12 | 2018-01-23 | 哈尔滨东安发动机（集团）有限公司 | The repair method of crackle at a kind of combustion box mounting bracket |
| CN104384816A (en) * | 2014-10-21 | 2015-03-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Welding method for box type part of air intake machine |
| CN106493450A (en) * | 2016-11-17 | 2017-03-15 | 中国华冶科工集团有限公司 | Cleft welding method |
| CN106493450B (en) * | 2016-11-17 | 2019-08-02 | 中国华冶科工集团有限公司 | Cleft welding method |
| CN106808165A (en) * | 2017-02-28 | 2017-06-09 | 中航湖南通用航空发动机有限公司 | The processing method of impeller outer cover in a kind of aero-engine |
| CN109531046A (en) * | 2018-11-27 | 2019-03-29 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine shunting shaped part spot welding method for repairing crack |
| CN109531046B (en) * | 2018-11-27 | 2020-12-04 | 中国航发沈阳黎明航空发动机有限责任公司 | Spot welding crack repairing method for aeroengine shunt ring part |
| CN110465728A (en) * | 2019-08-05 | 2019-11-19 | 大连理工大学 | High-power protected type core main pump c-type sealing structural component repeats welding procedure |
| CN110977106A (en) * | 2019-11-11 | 2020-04-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Repair welding repairing method for cracks of titanium alloy fan case |
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Application publication date: 20130227 |