CN108031934A - A kind of electrolysis correction method of TC4 titanium alloys turbo blade repair layer - Google Patents
A kind of electrolysis correction method of TC4 titanium alloys turbo blade repair layer Download PDFInfo
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- CN108031934A CN108031934A CN201711349221.XA CN201711349221A CN108031934A CN 108031934 A CN108031934 A CN 108031934A CN 201711349221 A CN201711349221 A CN 201711349221A CN 108031934 A CN108031934 A CN 108031934A
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- electrolyte
- turbo blade
- electrolysis
- correction method
- cathod
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H3/00—Electrochemical machining, i.e. removing metal by passing current between an electrode and a workpiece in the presence of an electrolyte
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
- B23H9/10—Working turbine blades or nozzles
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
Abstract
The invention discloses a kind of electrolysis correction method of TC4 titanium alloys turbo blade repair layer, include the following steps：S1, establish electrochemical machining system, the electrochemical machining system of foundation, including power-supply system, electrolyte circulation system, electrolytic cell, displacement platform, cathod system and control system, the electrolyte inlet and electrolyte channel of the circulation pipe connection cathod system of the electrolyte circulation system, the positive and negative electrode of power-supply system connect cathod system respectively；The electrolyte is 18% sodium chloride solution, and the rotating speed of electrolyte circulating pump is 1800r/min；S2, processing, turbo blade sample use the TC4 titanium-alloy thin-plates after edges of boards pile up welding in element of arc, and the non-repair face of turbo blade is protected using epoxy resin insulating layers, are placed in be electrolysed in the runner of cathod system and repair.The present invention carries out Bead weld repair blade tip electrolysis correction of the flank shape using cathode technique is improved, and the correction of the flank shape time 80s of single group blade, has good reliability.
Description
Technical field
The present invention relates to a kind of electrolysis correction method of TC4 titanium alloys turbo blade repair layer.
Background technology
For the core component of aero-engine, the damaged condition of turbo blade directly affect the efficiency of aircraft operation with
Safety, therefore the turbo blade damaged must be replaced or repaired.Since turbo blade material is high-strength hardened material, cost
It is higher, therefore the turbo blade of damage is carried out maintenance, there is high technology and economic value.At present, turbo blade reparation
Technology chain mainly fills up defect and follow-up two steps of correction of the flank shape restoration designing precision including built-up welding.Forefathers using technique for overlaying to being repaiied
Multiple aviation component has carried out numerous studies, and is studied on follow-up correction of the flank shape, focuses primarily upon to traditional correction of the flank shape technology (grinding, milling
Cut or electrical discharge machining) equipment and technology improvement.And traditional correction of the flank shape technology is due to cutting force in process, cutting or electricity
The influence of spark, the surface processed is there are residual stress, the defects of heat affected layer, easily causes microcrack, and be expanded into grand
See defect.Therefore, traditional correction of the flank shape technology has been difficult to the requirement for meeting the follow-up correction of the flank shape in repairing of modern turbo blade.Electrolyzed Processing is
A kind of special processing technology, with no cutting force and cutting heat affecting, high in machining efficiency, finished surface without residual stress and tool marks
The advantages that.Electrochemical Machining Technology applied in the directly manufacture of turbo blade, has high efficiency and reliable precision, because
This, Electrolyzed Processing is introduced into the follow-up correction of the flank shape of turbo blade reparation, has potential technical advantage.But compared to tradition
Vane manufacturing, carry out electrolysis correction of the flank shape for turbo blade after Bead weld repair, there are its distinctive technological difficulties.On the one hand, heap
Repair welding is nearly whole manufacturing technology again, and Bead weld repair layer pattern is influenced by metal freezing rule, easily forms thin edge, thick middle
Shape characteristic.On the other hand, Electrolyzed Processing has an inherited error effect, non-uniform pattern after Bead weld repair, largely
It has impact on the final precision after workpiece correction of the flank shape.Therefore, using the cathode of traditional design, electrolysis is carried out to non-uniform overlay cladding and is repaiied
During shape, occurred that incised notch was fallen at overlay cladding edge, precision is repaired in deterioration.As it can be seen that the special several of overlay cladding must be considered
The technology characteristics of what pattern and Electrolyzed Processing, are improved conventional design cathode, are cut with eliminating, and improve correction of the flank shape precision.Cause
This, has originally researched and proposed the improvement cathode of edge retraction.The cathode of edge retraction adds the processing gap of edge, so as to subtract
The small electric field strength of edge, and then the metal ablation amount at overlay cladding edge is reduced, avoid over-cutting.
The content of the invention
The technical problems to be solved by the invention, exactly propose that a kind of electrolysis of TC4 titanium alloys turbo blade repair layer is repaiied
Shape method.
In order to solve the above technical problems, the present invention is achieved by the following scheme：
A kind of electrolysis correction method of TC4 titanium alloys turbo blade repair layer, includes the following steps：
S1, establish electrochemical machining system
The electrochemical machining system of foundation, including power-supply system, electrolyte circulation system, electrolytic cell, displacement platform, cathode system
System and control system, the electrolyte inlet and electrolyte channel of the circulation pipe connection cathod system of the electrolyte circulation system,
The positive and negative electrode of power-supply system connects cathod system respectively；The electrolyte is 18% sodium chloride solution, electrolyte circulating pump
Rotating speed is 1800r/min；
S2, processing
Turbo blade sample uses the TC4 titanium-alloy thin-plates after edges of boards pile up welding in element of arc, and the non-repair face of turbo blade is adopted
Protected with epoxy resin insulating layers, be placed in be electrolysed in the runner of cathod system and repair.
Preferably, to obtain uniform Flow Field Distribution, the cathode in the cathod system, which has, laterally supplies propulsive cathode
Runner.
Preferably, the cathode material is brass, and cathode feed speed is 0.6mm/min.
Preferably, the process time is 80 seconds.
Preferably, machining voltage 24V, and electrolysis temperature is 35 ± 2 DEG C.
Compared with prior art, the device have the advantages that being：The present invention is effectively eliminated using cathode is improved
Over-cutting, so as to obtain higher correction of the flank shape precision；Correction of the flank shape rear blade cross section profile uniform ground is electrolysed, non-processing face is still kept
Original precision, edge transition is gentle, meets blade shape requirement；In addition, the result relative error of Continuous maching experiment is smaller,
Improving cathode has preferable repeatable accuracy and reliability.Electrolysis is carried out using improvement cathode technique to Bead weld repair blade tip to repair
Shape, the correction of the flank shape time 80s of single group blade, has good reliability.Blade tip form accuracy after correction of the flank shape is higher, surface roughness
Ra≤0.8 μm, meets the requirement of blade tip correction of the flank shape.
Brief description of the drawings
Fig. 1 is the structure diagram of the electrochemical machining system of the present invention；
Fig. 2 is the structure diagram of the cathod system of the present invention.
Embodiment
To allow those skilled in the art to become apparent from getting information about the present invention, below in conjunction with attached drawing, to the present invention
It is further described.
It is the preferred embodiment of the present invention as shown in Figs. 1-2.
A kind of electrolysis correction method of TC4 titanium alloys turbo blade repair layer, includes the following steps：
S1, establish electrochemical machining system
Using electrochemical machining system is made by oneself in experiment, as shown in Figure 1.The system is furnished with the power-supply system 1 of direct current processing, defeated
It is 0-24V, maximum output current 2000A to go out voltage, has short-circuit protection control function.Power-supply system 1, electrolyte cyclic system
System 2 is with 3 integrated control of lathe displacement platform system, it can be achieved that the parameter such as voltage, electric current, electrolyte pressure is automatically controlled and believed
Number collection；
S2, processing
The demand of correction of the flank shape is electrolysed according to blade tip, design cathod system 4 is as shown in Figure 2.Wherein, conventional cathode is according to cos θ methods
Design.To obtain uniform Flow Field Distribution, the cathod system 4 of the present embodiment devises lateral feed flow cathode flow channels 5.Turbo blade
Sample 6 is carried out using the TC4 titanium-alloy thin-plates (50 × 30 × 2mm) after edges of boards pile up welding in element of arc, non-repair face using epoxy resin
Insulation protection.
According to the Electrolyzed Processing characteristic of TC4, the Optimizing Technical obtained in early-stage study is used in experiment, such as the institute of table 1
Show.
Table 1：Test parameters
| Workpiece material | TC4 titanium alloys |
| Cathode material | Brass |
| Electrolyte | 18%NaCl |
| Test temperature | 35±2℃ |
| Electrolyte circulating pump rotating speed | 1800r/min |
| Machining voltage | 24V |
| Cathode feed speed | 0.6mm/min |
| Process time | 80s |
| Insulating layer material | Epoxy resin |
For the correction of the flank shape effect of exact evaluation different process, the three-dimensional micro- sem observation blade tip tables of Leica DVM5000 HD are utilized
Face part pattern, and absorb the blade tip two-dimensional silhouette after correction of the flank shape.In addition, to ensure improved reliability, continuously 6 groups of blade tips are tried
The both sides of sample carry out correction of the flank shape respectively, using the micro- sem observation microscopic appearance of Olympus SZX12 shapes.Meanwhile pass through Form
Roughness among Talysurf roughmeters measurement correction of the flank shape face with fringe region.
Results and discussion
(1) Bead weld repair TC4 turbo blade blade tips are directed to, carry out electrolysis correction of the flank shape research, it is cloudy with improving by conventional cathode
The contrast of pole result of the test, with reference to numerical Analysis, demonstrates using cathode is improved, is fallen into incised notch was eliminated, optimization adds
The effect of work precision.
2) numerical computations show：There is over-cutting in conventional cathode processing, be due to overlay cladding marginal position, electric field collection
Caused by current density rise caused by.The spatial abnormal feature of current density can be effectively eliminated by improving cathode technique, so that
To good correction of the flank shape effect.
(3) result of the test shows：Electrolysis correction of the flank shape is carried out to Bead weld repair blade tip using cathode technique is improved, single group blade
Correction of the flank shape time 80s, has good reliability.Blade tip form accuracy after correction of the flank shape is higher, surface roughness Ra≤0.8 μm, full
The requirement of sufficient blade tip correction of the flank shape.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
With within principle, any modification, equivalent replacement, improvement and so on, should all be included in the protection scope of the present invention god.
Claims (5)
1. a kind of electrolysis correction method of TC4 titanium alloys turbo blade repair layer, it is characterised in that include the following steps：
S1, establish electrochemical machining system
The electrochemical machining system of foundation, including power-supply system, electrolyte circulation system, electrolytic cell, displacement platform, cathod system and
Control system, the electrolyte inlet and electrolyte channel of the circulation pipe connection cathod system of the electrolyte circulation system, power supply
The positive and negative electrode of system connects cathod system respectively；The electrolyte be 18% sodium chloride solution, the rotating speed of electrolyte circulating pump
For 1800r/min；
S2, processing
Turbo blade sample uses the TC4 titanium-alloy thin-plates after edges of boards pile up welding in element of arc, and ring is used to the non-repair face of turbo blade
Oxygen tree fat dielectric protection layer, is placed in be electrolysed in the runner of cathod system and repairs.
2. the electrolysis correction method of TC4 titanium alloys turbo blade repair layer according to claim 1, it is characterised in that be
Obtain uniform Flow Field Distribution, the cathode in the cathod system has lateral feed flow cathode flow channels.
3. the electrolysis correction method of TC4 titanium alloys turbo blade repair layer according to claim 1, it is characterised in that institute
It is brass to state cathode material, and cathode feed speed is 0.6mm/min.
4. the electrolysis correction method of TC4 titanium alloys turbo blade repair layer according to claim 1, it is characterised in that institute
Process time is stated as 80 seconds.
5. the electrolysis correction method of TC4 titanium alloys turbo blade repair layer according to claim 1, it is characterised in that add
Work voltage is 24V, and electrolysis temperature is 35 ± 2 DEG C.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711349221.XA CN108031934A (en) | 2017-12-15 | 2017-12-15 | A kind of electrolysis correction method of TC4 titanium alloys turbo blade repair layer |
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| CN201711349221.XA CN108031934A (en) | 2017-12-15 | 2017-12-15 | A kind of electrolysis correction method of TC4 titanium alloys turbo blade repair layer |
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| CN201711349221.XA Pending CN108031934A (en) | 2017-12-15 | 2017-12-15 | A kind of electrolysis correction method of TC4 titanium alloys turbo blade repair layer |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111037012A (en) * | 2019-12-06 | 2020-04-21 | 西安铂力特增材技术股份有限公司 | Subsequent electrolytic machining device and method for titanium alloy workpiece manufactured by laser additive manufacturing |
| CN112621103A (en) * | 2020-12-17 | 2021-04-09 | 中国民航大学 | Repair method for titanium alloy blade of aircraft engine compressor |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1400076A (en) * | 2001-07-27 | 2003-03-05 | 株式会社三协精机制作所 | Electrolytic machining process, dynamic pressure bearing and its machining process |
| CN1857858A (en) * | 2006-05-24 | 2006-11-08 | 南京航空航天大学 | Fixture for electrolytic forming of three-head flexible feeding vane |
| KR20090070019A (en) * | 2007-12-26 | 2009-07-01 | 한전케이피에스 주식회사 | Cooling hole processing device of gas turbine blade |
| CN101502901A (en) * | 2009-03-10 | 2009-08-12 | 南京航空航天大学 | Thin electrode for electrolytic machining of integral wheel |
-
2017
- 2017-12-15 CN CN201711349221.XA patent/CN108031934A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1400076A (en) * | 2001-07-27 | 2003-03-05 | 株式会社三协精机制作所 | Electrolytic machining process, dynamic pressure bearing and its machining process |
| CN1857858A (en) * | 2006-05-24 | 2006-11-08 | 南京航空航天大学 | Fixture for electrolytic forming of three-head flexible feeding vane |
| KR20090070019A (en) * | 2007-12-26 | 2009-07-01 | 한전케이피에스 주식회사 | Cooling hole processing device of gas turbine blade |
| CN101502901A (en) * | 2009-03-10 | 2009-08-12 | 南京航空航天大学 | Thin electrode for electrolytic machining of integral wheel |
Non-Patent Citations (1)
| Title |
|---|
| 刘为东等: "TC4钛合金涡轮叶片修复层的电解修形技术", 《天津大学学报(自然科学与工程技术版)》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111037012A (en) * | 2019-12-06 | 2020-04-21 | 西安铂力特增材技术股份有限公司 | Subsequent electrolytic machining device and method for titanium alloy workpiece manufactured by laser additive manufacturing |
| CN112621103A (en) * | 2020-12-17 | 2021-04-09 | 中国民航大学 | Repair method for titanium alloy blade of aircraft engine compressor |
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Application publication date: 20180515 |