CN106048597A - Method for repairing damaged surface of stator blade of large fan casing weld assembly - Google Patents
Method for repairing damaged surface of stator blade of large fan casing weld assembly Download PDFInfo
- Publication number
- CN106048597A CN106048597A CN201610464947.7A CN201610464947A CN106048597A CN 106048597 A CN106048597 A CN 106048597A CN 201610464947 A CN201610464947 A CN 201610464947A CN 106048597 A CN106048597 A CN 106048597A
- Authority
- CN
- China
- Prior art keywords
- cladding
- stator blade
- weld assembly
- glove box
- carried out
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
Landscapes
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a method for repairing the foreign matter damage surface of a stator blade of a large fan casing weld assembly. The repair method is low in repair cost and short in repair period. The method is realized according to the following technical scheme that firstly, a foreign matter damage defect is ground to be removed, then, a part is encased in an atmosphere glove box, vacuum pumping is carried out, and argon is fed in for cleaning after vacuum pumping is carried out; then, path planning is carried out on the complex surface of the ground part, and a short distance Z-shaped cladding path is adopted for path planning; a laser cladding apparatus provided with the atmosphere glove box and a six-axis mechanical arm multi-degree-of-freedom robot is used for carrying out laser cladding on the ground area of the part; in the cladding process, titanium alloy cladding powder with the granularity of -100 meshes to +325 meshes is adopted, the adopted cladding technological parameters are that the laser cladding power is 300 W to 500 W, the defocusing amount is 4 mm to 6 mm, the powder feeding amount is 5 g/min to 8 g/min, and the layer height is 0.2 mm to 0.5 mm, and laser cladding is carried out on each layer of cladding powder in the progressive decrease manner that the progressive decrease amount of each single layer is 30 W.
Description
Technical field
The invention belongs to aircraft engine maintenance field.Relate generally to the large-scale fan of more than a kind of aero-engine 1000mm
The restorative procedure of casing weld assembly stator blade foreign object damage.
Technical background
Aerial engine fan casing weld assembly stator blade is one of vitals in compressor, plays rectification and expands
Pressure, improves the effect of engine efficiency.It is for a long time by airflow scouring and bear the risk injured by foreign body.Casing welding group
Component belongs to large thin-wall casing, and structure is complex, has multiple tracks groove, cell body side to have U-type groove inside casing, and outside is welded
Multiple boss, forward and backward installation limit is drilled with hole.What large-scale casing shown in Fig. 1 and Thin-Wall Outer Casing work in-process faced most important asks
In topic processing exactly, sidewall and forward and backward installation limit easily cause deformation；Part the most also can cause deformation.Casing
Inside be furnished with multiple tracks abnormal shape annular groove, and size is less, precision is higher.Casing material hardness is relatively big, processing difficulties, fault rate
High.Main damage pattern is that foreign body is injured.Owing to blade is welded as a whole with casing, largest outside diameter size reaches 1000mm, should
Stator blade material is titanium alloy TC 4, and damage is main at blade leading edge everywhere, and leading edge belongs to complex space curved surfaces structure,
Adjacent blades distance is less than 50mm, and vane thickness thinnest part about 0.5mm, and conventional argon arc welding can not be adjusted in welding process in real time
Whole heat inputs, it is difficult to realizes space curved surface welding, and occurs the phenomenons such as undercut in welding process.For complex space curved surfaces structure
The profiling reparation of the stator blade made, mainly uses laser melting and coating technique, the compressor of the openest report
The repairing of blade, mainly for the repairing of individual blade, there is no open aircraft electromotor large-scale fancase weld assembly quiet
The repairing that blades foreign body is injured.Large-scale fancase weld assembly stator blade is repaired to repair with individual blade to be had the most not
With: first, large-scale fancase weld assembly stator blade is repaired, and needs to formulate the atmosphere protection case of specific dimensions, it is achieved
Laser melting coating is carried out under atmosphere protection；Second, large-scale fancase weld assembly stator blade has been fixed relative to position, some
Position accessibility is poor, needs have multivariant laser cladding equipment material and realizes cladding.Therefore, tradition single shaft or three axle controls
The laser cladding equipment of system processed is difficult to the laser melting coating of large-scale fancase weld assembly.
Summary of the invention
The present invention is directed to the deficiency that above-mentioned prior art exists, it is provided that a kind of rehabilitation cost is low, the cycle is short, repairs large-scale wind
The method that fan casing weld assembly stator blade foreign body is injured.
The above-mentioned purpose of the present invention can be reached by following measures, and the large-scale fancase weld assembly of a kind of reparation is quiet
The method in blades foreign object damage face, it is characterised in that comprise the steps: to remove foreign object damage portion initially with manual grinding
Position carries out polishing to remove oxide, then is loaded by the part at above-mentioned removal foreign object damage position in atmosphere glove box, opens hands
The air-extractor of casing, evacuation, after the oxygen content in glove box is less than 10ppm, stops evacuation, is filled with at least 1 air
The argon of pressure, uses argon to be carried out；Then the complex profile for polishing position carries out path planning, and path planning uses
Short distance zigzag cladding path；Employing is furnished with atmosphere glove box and multi-freedom robot six axis robot laser cladding equipment,
Part polishing region is carried out laser melting coating；In cladding process, with the titanium alloy cladding powder that granularity is-100～+325 mesh, adopt
With 300W～500W laser melting coating power, defocusing amount is 4mm～6mm, and powder sending quantity is g/min 5～8g/min, and scanning speed is
35mm/s～5mm/s, the monolayer height of cladding is 0.2mm～0.5mm/ layer, and overlapping rate is 40%～60% melting and coating process parameter,
Successively cladding is carried out by the decline mode that monolayer decrement is 30W.
Layer in the present invention refers to be perpendicular to the height of single track cladding on matrix direction.
The present invention uses the reparation flow process of defect polishing → evacuation → path planning → laser melting coating → manual grinding, right
The stator blade of electromotor weld assembly stator casing is repaired, and rehabilitation cost is low, the cycle is short.It is 30W by monolayer decrement
Decline mode successively cladding, by using the laser melting coating of little energy input and multi-freedom robot, effectively prevent
The problems such as the undercut that occurs in conventional repair mode, poor performance, reparation accessibility difference, substantially increase weld assembly stator blade
Repair capability, qualification rate reaches more than 95%, and repair cost is low, the cycle is short.
The composite can be widely applied to the repairing of TC4 titanium alloy aero-engine weld assembly stator blade.
Accompanying drawing explanation
Fig. 1 is the section structure schematic diagram of large-scale fancase weld assembly stator blade.
In figure: 1 is stator blade, 2 is casing outer shroud, and 3 is casing internal ring.
Detailed description of the invention
In embodiment described below, for the stator blade of aero-engine weld assembly stator casing on inspection,
There are 5 to damage for leading edge, damage at totally 11, exceed therefore examine requirement, the example that may scrap.According to the present invention, beat by defect
The reparation flow process of mill → evacuation → path planning → laser melting coating → manual grinding, removes foreign body initially with manual grinding and damages
Position, traumatic part, then the part at above-mentioned removal foreign object damage position is loaded in atmosphere glove box, open the air-extractor of glove box, take out
Vacuum, stops evacuation after the oxygen content in glove box is less than 10ppm, is then charged with the argon of 1 atmospheric pressure, use argon
It is carried out；Employing is used to be furnished with atmosphere glove box and six axis robot multi-freedom robot laser cladding equipment, to blade
The complex profile at polishing position carries out path planning, and path planning uses short distance zigzag cladding path, to reduce cladding layer
Thermal stress；Part polishing region is carried out laser melting coating, and cladding powder is titanium alloy TC 4 powder, and granularity is (-100～+325)
Mesh.Melting and coating process parameter: the power of laser melting coating is (300～500) W, defocusing amount is (4～6) mm, and powder sending quantity is (5～8) g/
Min, scanning speed is (3～5) mm/s, and the monolayer height of cladding is (0.2～0.5) mm/ layer, and overlapping rate is (40～60) %.
In cladding process, the power of every layer carries out decline mode, and monolayer decrement is 30W.Manual grinding cladding surface, meets surface thick
Rugosity is not less than Ra0.5.Flawless, satisfied repairing requirement after fluoroscopy after repairing.
Claims (2)
1. the method repairing large-scale fancase weld assembly stator blade foreign object damage face, it is characterised in that include as follows
Step: remove foreign object damage position initially with manual grinding and carry out polishing to remove oxide, more above-mentioned removal foreign body is damaged
The part of position, traumatic part loads in atmosphere glove box, opens the air-extractor of glove box, and evacuation, when the oxygen content in glove box is little
After 10ppm, stop evacuation, be filled with the argon of at least 1 atmospheric pressure, use argon to be carried out；Then for polishing position
Complex profile carry out path planning, path planning uses short distance zigzag cladding path；Employing is furnished with atmosphere glove box with many
Degree of freedom robot six axis robot laser cladding equipment, carries out laser melting coating to part polishing region；In cladding process, with grain
Degree is the titanium alloy cladding powder of-100～+325 mesh, uses 300W～500W laser melting coating power, and defocusing amount is 4mm～6mm,
Powder sending quantity is g/min 5～8g/min, and scanning speed is 35mm/s～5mm/s, and the monolayer height of cladding is 0.2mm～0.5mm/
Layer, overlapping rate is 40%～60% melting and coating process parameter, carries out successively cladding by the decline mode that monolayer decrement is 30W.
2. the method repairing large-scale fancase weld assembly stator blade foreign object damage face as claimed in claim 1, it is special
Levy and be: by the reparation flow process of defect polishing → evacuation → path planning → laser melting coating → manual grinding, to large-scale fan
Casing weld assembly stator blade foreign object damage face is repaired.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610464947.7A CN106048597A (en) | 2016-06-23 | 2016-06-23 | Method for repairing damaged surface of stator blade of large fan casing weld assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610464947.7A CN106048597A (en) | 2016-06-23 | 2016-06-23 | Method for repairing damaged surface of stator blade of large fan casing weld assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106048597A true CN106048597A (en) | 2016-10-26 |
Family
ID=57165543
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610464947.7A Pending CN106048597A (en) | 2016-06-23 | 2016-06-23 | Method for repairing damaged surface of stator blade of large fan casing weld assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106048597A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106637187A (en) * | 2016-11-16 | 2017-05-10 | 中国人民解放军第五七九工厂 | Laser cladding restoration method for damage of stator blade of welding assembly of large fan casing of aeroengine |
| CN107116336A (en) * | 2017-06-16 | 2017-09-01 | 中国人民解放军第五七九工厂 | A kind of aero-engine composite casing restorative procedure |
| CN109128135A (en) * | 2018-08-23 | 2019-01-04 | 江苏理工学院 | A kind of self-fluxing alloy powder and titanium alloy blade pulse laser remanufacture forming technology |
| CN109623575A (en) * | 2018-12-17 | 2019-04-16 | 中国航发动力股份有限公司 | A kind of sbrasive belt grinding method of reblading |
| CN111331136A (en) * | 2020-02-10 | 2020-06-26 | 中国科学院金属研究所 | Powder feeding laser 3D printing method for metal thin-wall parts with uniform performance |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102031513A (en) * | 2009-09-28 | 2011-04-27 | 沈阳大陆激光技术有限公司 | Restoring method of last-stage blade of steam turbine |
| CN103753098A (en) * | 2013-12-31 | 2014-04-30 | 上海彩石激光科技有限公司 | Turbine engine blade automatic repairing device and method |
-
2016
- 2016-06-23 CN CN201610464947.7A patent/CN106048597A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102031513A (en) * | 2009-09-28 | 2011-04-27 | 沈阳大陆激光技术有限公司 | Restoring method of last-stage blade of steam turbine |
| CN103753098A (en) * | 2013-12-31 | 2014-04-30 | 上海彩石激光科技有限公司 | Turbine engine blade automatic repairing device and method |
Non-Patent Citations (1)
| Title |
|---|
| 罗奎林等: "激光熔覆修复航空发动机风扇机匣TC4钛合金静子叶片", 《中国表面工程》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106637187A (en) * | 2016-11-16 | 2017-05-10 | 中国人民解放军第五七九工厂 | Laser cladding restoration method for damage of stator blade of welding assembly of large fan casing of aeroengine |
| CN107116336A (en) * | 2017-06-16 | 2017-09-01 | 中国人民解放军第五七九工厂 | A kind of aero-engine composite casing restorative procedure |
| CN107116336B (en) * | 2017-06-16 | 2019-01-04 | 中国人民解放军第五七一九工厂 | A kind of aero-engine composite material casing restorative procedure |
| CN109128135A (en) * | 2018-08-23 | 2019-01-04 | 江苏理工学院 | A kind of self-fluxing alloy powder and titanium alloy blade pulse laser remanufacture forming technology |
| CN109128135B (en) * | 2018-08-23 | 2021-04-20 | 江苏理工学院 | Pulse laser remanufacturing and forming process for self-fluxing alloy powder and titanium alloy blade |
| CN109623575A (en) * | 2018-12-17 | 2019-04-16 | 中国航发动力股份有限公司 | A kind of sbrasive belt grinding method of reblading |
| CN111331136A (en) * | 2020-02-10 | 2020-06-26 | 中国科学院金属研究所 | Powder feeding laser 3D printing method for metal thin-wall parts with uniform performance |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106048597A (en) | Method for repairing damaged surface of stator blade of large fan casing weld assembly | |
| CN106637187A (en) | Laser cladding restoration method for damage of stator blade of welding assembly of large fan casing of aeroengine | |
| US9085980B2 (en) | Methods for repairing turbine components | |
| US9328614B2 (en) | Method of making a metal reinforcing piece | |
| JP5322371B2 (en) | How to repair a disk with an integrated blade, test piece at the start and end of work | |
| US20180216464A1 (en) | Method of repairing a blisk | |
| US20070111119A1 (en) | Method for repairing gas turbine engine compressor components | |
| US20110099810A1 (en) | Method for repairing a gas turbine component | |
| CN106521487B (en) | A kind of reproducing method of military service mid-term titanium alloy compressor blade | |
| EP2236235A1 (en) | A high temperature additive manufacturing system for making near net shape airfoil leading edge protection with a cladded mandrel | |
| JP4000075B2 (en) | Rotor repair method | |
| US20050029235A1 (en) | Method for the restoration of damaged areal components | |
| CN110539080A (en) | double-mechanical-arm laser-plasma composite milling material-increasing and material-decreasing manufacturing equipment and method | |
| CN109746453B (en) | Laser repair method and device | |
| US8906221B2 (en) | Electrochemical grinding tool and method | |
| CN105821408A (en) | Method for adopting laser cladding to repair TC4-DT titanium alloys | |
| CN102712066A (en) | Method for repairing a titanium blade by laser recharging and moderate hip pressing | |
| US20170081752A1 (en) | Method for Producing a Near Net Shape Metallic Leading Edge | |
| CN104004982B (en) | A kind of titanium alloy component stablizes heat treatment process method | |
| EP1807237A2 (en) | Weld shielding device for automated welding of impellers and blisks | |
| CN104010762A (en) | A method of repairing rotating machine components | |
| CN112621103B (en) | Repair method for titanium alloy blade of aircraft engine compressor | |
| CN211102162U (en) | Double-mechanical-arm laser-plasma composite milling material increase and decrease manufacturing equipment | |
| EP2617513B1 (en) | Apparatus and method for on line surface enhancement of a workpiece | |
| CN110202158A (en) | A kind of monoblock type restorative procedure of aero-turbine rotor blade integral shroud longitudinal direction heavy break |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20161026 |
|
| WD01 | Invention patent application deemed withdrawn after publication |