CN103014278A - Method for improving blade fatigue strength through comprehensive means - Google Patents
Method for improving blade fatigue strength through comprehensive means Download PDFInfo
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- CN103014278A CN103014278A CN2012105714140A CN201210571414A CN103014278A CN 103014278 A CN103014278 A CN 103014278A CN 2012105714140 A CN2012105714140 A CN 2012105714140A CN 201210571414 A CN201210571414 A CN 201210571414A CN 103014278 A CN103014278 A CN 103014278A
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Abstract
The invention relates to a method for improving blade fatigue strength through comprehensive means. The method comprises the following steps of: performing laser shock processing on an area which takes a first order vibration pitch line in the middle of a blade as the center, performing shot blasting and laser shock overlap processing adjacent to the area, and performing shot blasting shock processing, wherein mixed vibration burnishing process treatment is performed in the whole treatment process. By adoption of the treatment process of combining the laser shock enhancement, shot blasting and vibration burnishing for enhancement, the respective defects are offset between the processes, and respective advantages are exerted, so that the blade fatigue strength is further improved.
Description
Technical field
The invention belongs to surface engineering technology and field of laser processing, relate to and a kind ofly improve the method for blade fatigue strength with comprehensive means, be specially the applied in any combination of utilizing laser impact intensified, vibration finishing and shot-peening, further improve the fatigue strength of blade.
Background technology
In the aircraft engine working process, working order changes many, pneumatic excited frequency is wide, cause easily the engine blade high-frequency vibration, thereby cause leaf development high cycle fatigue fracture, often adopt surface strengthening technology (such as shot-peening, laser impact intensified and vibration finishing etc.) to improve the workpiece anti-fatigue performance.
Laser impact intensified and Shot Peening Technology all is a kind of at material surface generation stress, crystal grain thinning, thereby improves the method for hardware fatigue strength.Shot-peening adopts bullet high-speed impact component surface, makes top layer metal generation plastic flow, improves the weave construction of top layer metal, and grain shape and orientation are changed, and produces residual tension.It is less that its shortcoming is that unrelieved stress affects the degree of depth, and surfaceness is difficult to control.
Laser impact intensified short pulse (ns), the high power density (〉 1GW/cm of then utilizing
2) laser irradiation, induce to form plasma body high pressure (〉 1GPa) shockwave, act on workpiece surface and to internal communication, high strain rate dynamic response occurs material, cause that microtexture changes, and produces residual compressive stress in darker thickness.Therefore, laser impact intensified employing shockwave is realized the propagation of energy, degree of grain refinement and affect layer depth and all be better than shot-peening, and its strengthening effect is better.At present, the laser impact intensified fatigue strength that is mainly used in improving aircraft engine key member key position.
Vibration finishing is a kind of complete processing that improves surface integrity, is widely used in deburring and the rounding of the members such as blade of aviation engine, can improve to a certain extent the surface integrity of workpiece.It is that blade and abrasive material are packed in the same container, and the motion by container is ground blade and abrasive material mutually, reaches the purpose of blade surface leveling or polishing.In the vibration finishing process, there is the grinding in the similar polishing process, abrading block is to effects such as the impact of workpiece, scratchings, but the effects on surface sclerization is less.
Summary of the invention
The technical problem that solves
For fear of the deficiencies in the prior art part, the present invention proposes a kind of method that improves blade fatigue strength with comprehensive means, according to blade construction and stress characteristic, adopt laser impact intensified, shot-peening and vibration finishing in conjunction with strengthening, mutually remedy deficiency separately, thereby further improve the fatigue strength of blade.
Technical scheme
A kind of method with comprehensive means raising blade fatigue strength is characterized in that step is as follows:
Step 1: the single order take the blade middle part vibrates nodel line as benchmark, the zone of 20 ~ 50mm is the laser-impact zone up and down centered by single order vibration nodel line, be close to this zone up and down be shot-peening and laser-impact overlapping region, greater than 5mm, what be close to shot-peening and laser-impact overlapping region is the shot-peening shock zone, greater than 5mm;
Step 2: determine shot-blast process parameter and shot peening strength according to material behavior, the shot peening strength with 1/2nd carries out the shot-peening shock treatment first time to the shot-peening shock zone of 8 ~ 12mm and shot-peening and the laser-impact overlapping region of 8 ~ 12mm;
Step 3: determine laser impact intensified parameter according to material behavior: optical maser wavelength, pulsewidth and power density, the laser reinforcing processing is carried out in laser-impact zone and 8 ~ 12mm shot-peening and laser-impact overlapping region up and down, this zone of next-door neighbour to 20 ~ 50mm, and the hot spot overlapping rate when laser reinforcing is processed is 70%;
Step 4: repeating step 2 carries out the shot-peening shock treatment to carrying out the shot-peening shock zone again;
Step 5: determine the vibration finishing processing parameter according to material behavior, blade integral is carried out the vibration finishing art breading, so that blade fatigue strength effectively improves.
When processed blade belongs to without the blade that polishes, when processed blade belongs to without the blade that polishes, the vibration finishing art breading is carried out before the shot-peening shock treatment for the first time in step 2, or before step 2, carry out the vibration finishing art breading one time.
When the surfaceness after each shot-peening shock treatment is undesirable, after implementing the shot-peening shock treatment, carry out the vibration finishing art breading one time.
Beneficial effect
A kind of method that improves blade fatigue strength with comprehensive means that the present invention proposes, zone centered by the single order vibration nodel line at blade middle part is carried out laser-impact and is processed, be close to this zone and carry out shot-peening and the overlapping processing of laser-impact, then be the shot-peening shock treatment, in whole treating processes, be mingled with the vibration finishing art breading.Because the treatment process that has adopted laser impact intensified, shot-peening and vibration finishing to combine and strengthen, so that mutually remedy separately deficiency between each art breading, thereby performance advantage separately further improves the fatigue strength of blade among the present invention.
The present invention's outstanding effect compared to existing technology is:
(1) can remedy shot peening strengthening and affect the problems such as inadequate, the laser impact intensified zone of transition residual tension of the degree of depth;
(2) laser-impact and not the residual stress gradient of shock zone intersection change obviously, and have the balance tensile stress.By near the shot peening the laser-impact zone, can effectively eliminate the balance tensile stress, slow down impact zone rim stress variable gradient;
(3) after the employing combination process was processed blade, the unrelieved stress field distribution was more even, and variation tendency is mild, and blade fatigue life significantly improves.
Description of drawings
Fig. 1: blade subregion and reinforcement combination synoptic diagram,
1 is blade, and 2 is the blade leading edge, and 3 is blade exhaust limit, 4 is blade root, 5 is laser-impact and shot-peening overlap, and 6 is the shot-peening district, and 7 is laser-impact and shot-peening overlap, 8 is the shot-peening district, 9 is the laser-impact zone, and 10 are single order vibration nodel line, and 11 is laser facula, 12 is the laser-impact path, and 13 is blade.
Embodiment
Now in conjunction with the embodiments, the invention will be further described for accompanying drawing:
Among the embodiment of the present invention, adopt certain engine stainless steel blade to process, the implementation step is:
Step 1: take blade middle part, vibrate nodel line as benchmark apart from the about 40mm single order of root, the zone of 20mm is the laser-impact zone up and down take single order vibration nodel line center, being close to this zone 10mm up and down is shot-peening and laser-impact overlapping region, and the 10mm of next-door neighbour's shot-peening and laser-impact overlapping region is the shot-peening shock zone;
Step 2: determine that according to material behavior the shot-blast process parameter is the cutting steel wire ball, shot peening strength is 0.4A, and the shot peening strength 0.2A with 1/2nd carries out the shot-peening shock treatment first time to the shot-peening shock zone of 10mm and shot-peening and the laser-impact overlapping region of 10mm;
Step 3: determine laser impact intensified parameter according to material behavior: optical maser wavelength is 1064nm, and pulsewidth is 20ns, and power density is 4.2GW/cm
2, the laser reinforcing processing is carried out in laser-impact zone and 10mm shot-peening and the laser-impact overlapping region up and down, this zone of next-door neighbour of 20mm, the hot spot overlapping rate when laser reinforcing is processed is 70%; The laser energy of the described pulsewidth power density of root is 6J, and the light spot shape of laser is circular, and the diameter of hot spot is 3mm;
Step 4: repeating step 2 carries out the shot-peening shock treatment to carrying out the shot-peening shock zone again;
Step 5: determine that according to material behavior the vibration finishing processing parameter is that abrasive material adopts resin particle, blade integral is carried out the vibration finishing art breading, the time is 30 minutes, so that blade fatigue strength effectively improves.
Through aforesaid method stainless steel blade is carried out intensive treatment, in upper shot-peening and laser-impact overlapping region 5 and lower shot-peening and laser-impact overlapping region 7 formation zone of transition, realized seamlessly transitting of blade surface residual stress distribution.
The order that laser impact intensified, shot-peening and vibration finishing are processed can be according to the motor-driven adjustment of workpiece practical situation.Such as workpiece surface roughness large (without the workpiece of polishing), vibration finishing can be processed and advance to step 3 position; Higher or material hardness is lower (such as aluminium alloy) such as shot peening strength, shot-peening rear surface roughness is larger, can adopt the laser impact intensified process sequence of whole shot-peening-vibration finishings-key position; For breach sensitive material and workpiece (such as titanium alloy blade), should guarantee that vibration finishing is arranged in last procedure, to guarantee the surface integrity of blade, reduce the possibility that breach occurs.
Claims (3)
1. one kind is improved the method for blade fatigue strength with comprehensive means, it is characterized in that step is as follows:
Step 1: the single order take the blade middle part vibrates nodel line as benchmark, the zone of 20 ~ 50mm is the laser-impact zone up and down centered by single order vibration nodel line, be close to this zone up and down be shot-peening and laser-impact overlapping region, greater than 5mm, what be close to shot-peening and laser-impact overlapping region is the shot-peening shock zone, greater than 5mm;
Step 2: determine shot-blast process parameter and shot peening strength according to material behavior, the shot peening strength with 1/2nd carries out the shot-peening shock treatment first time to the shot-peening shock zone of 8 ~ 12mm and shot-peening and the laser-impact overlapping region of 8 ~ 12mm;
Step 3: determine laser impact intensified parameter according to material behavior: optical maser wavelength, pulsewidth and power density, the laser reinforcing processing is carried out in laser-impact zone and 8 ~ 12mm shot-peening and laser-impact overlapping region up and down, this zone of next-door neighbour to 20 ~ 50mm, and the hot spot overlapping rate when laser reinforcing is processed is 70%;
Step 4: repeating step 2 carries out the shot-peening shock treatment to carrying out the shot-peening shock zone again;
Step 5: determine the vibration finishing processing parameter according to material behavior, blade integral is carried out the vibration finishing art breading, so that blade fatigue strength effectively improves.
2. the method that improves blade fatigue strength with comprehensive means according to claim 1, it is characterized in that: when processed blade belongs to without the blade that polishes, the vibration finishing art breading is carried out before the shot-peening shock treatment for the first time in step 2, or before step 2, carry out the vibration finishing art breading one time.
3. the method that improves blade fatigue strength with comprehensive means according to claim 1, it is characterized in that: when the surfaceness after each shot-peening shock treatment is undesirable, after implementing the shot-peening shock treatment, carry out the vibration finishing art breading one time.
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| CN2012105714140A CN103014278A (en) | 2012-12-25 | 2012-12-25 | Method for improving blade fatigue strength through comprehensive means |
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| CN2012105714140A CN103014278A (en) | 2012-12-25 | 2012-12-25 | Method for improving blade fatigue strength through comprehensive means |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106636589A (en) * | 2016-10-08 | 2017-05-10 | 中国航空工业集团公司北京航空制造工程研究所 | Shot peening strengthening method for controlling hollow blade deformation |
| CN107099655A (en) * | 2017-03-23 | 2017-08-29 | 杭州四鑫工业泵制造有限公司 | The laser reinforcing process of vavuum pump compressor blade |
| CN107858500A (en) * | 2017-09-30 | 2018-03-30 | 广东工业大学 | A kind of blade laser peening intensifying method for becoming the controllable residual stress of pulse width |
| CN107937706A (en) * | 2017-11-28 | 2018-04-20 | 广东工业大学 | A kind of method and system of pulse laser reinforced metal part |
| CN109093453A (en) * | 2018-09-27 | 2018-12-28 | 中国航发哈尔滨轴承有限公司 | A kind of surface quality method for improving of non-ferrous metal retainer |
| CN109885882A (en) * | 2019-01-21 | 2019-06-14 | 北京航空航天大学 | A kind of design method of blade of aviation engine simulating piece |
| CN110438425A (en) * | 2019-09-19 | 2019-11-12 | 中国人民解放军空军工程大学 | A kind of laser impact intensified intensifying method with shot peening strengthening optimum organization |
| CN111850442A (en) * | 2020-07-06 | 2020-10-30 | 中国人民解放军空军工程大学 | Strengthening method for preventing high-order vibration type induced blade tip block dropping of titanium alloy blisk blade |
| CN112404913A (en) * | 2020-10-13 | 2021-02-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Titanium alloy blisk blade processing technology method |
-
2012
- 2012-12-25 CN CN2012105714140A patent/CN103014278A/en active Pending
Non-Patent Citations (2)
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| 周磊等: "航空发动机风扇叶片两种表面处理方法对比", 《航空精密制造技术》 * |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106636589B (en) * | 2016-10-08 | 2018-07-24 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of stress peening method of control hollow blade deformation |
| CN106636589A (en) * | 2016-10-08 | 2017-05-10 | 中国航空工业集团公司北京航空制造工程研究所 | Shot peening strengthening method for controlling hollow blade deformation |
| CN107099655A (en) * | 2017-03-23 | 2017-08-29 | 杭州四鑫工业泵制造有限公司 | The laser reinforcing process of vavuum pump compressor blade |
| CN107099655B (en) * | 2017-03-23 | 2018-09-07 | 杭州四鑫工业泵制造有限公司 | The laser reinforcing process of vacuum pump compressor blade |
| CN107858500B (en) * | 2017-09-30 | 2019-06-14 | 广东工业大学 | A kind of blade laser peening intensifying method becoming the controllable residual stress of pulse width |
| CN107858500A (en) * | 2017-09-30 | 2018-03-30 | 广东工业大学 | A kind of blade laser peening intensifying method for becoming the controllable residual stress of pulse width |
| CN107937706A (en) * | 2017-11-28 | 2018-04-20 | 广东工业大学 | A kind of method and system of pulse laser reinforced metal part |
| CN109093453A (en) * | 2018-09-27 | 2018-12-28 | 中国航发哈尔滨轴承有限公司 | A kind of surface quality method for improving of non-ferrous metal retainer |
| CN109885882A (en) * | 2019-01-21 | 2019-06-14 | 北京航空航天大学 | A kind of design method of blade of aviation engine simulating piece |
| CN109885882B (en) * | 2019-01-21 | 2020-08-11 | 北京航空航天大学 | Design method of aero-engine blade simulation piece |
| CN110438425A (en) * | 2019-09-19 | 2019-11-12 | 中国人民解放军空军工程大学 | A kind of laser impact intensified intensifying method with shot peening strengthening optimum organization |
| CN110438425B (en) * | 2019-09-19 | 2021-08-31 | 中国人民解放军空军工程大学 | Strengthening method for optimally combining laser shock strengthening and shot peening strengthening |
| CN111850442A (en) * | 2020-07-06 | 2020-10-30 | 中国人民解放军空军工程大学 | Strengthening method for preventing high-order vibration type induced blade tip block dropping of titanium alloy blisk blade |
| CN111850442B (en) * | 2020-07-06 | 2022-06-10 | 中国人民解放军空军工程大学 | Strengthening method for preventing high-order vibration type induced blade tip block dropping of titanium alloy blisk blade |
| CN112404913A (en) * | 2020-10-13 | 2021-02-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Titanium alloy blisk blade processing technology method |
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Application publication date: 20130403 |