CN109583037A - A kind of parameter control method of blade of aviation engine shot-peening machining deformation - Google Patents
A kind of parameter control method of blade of aviation engine shot-peening machining deformation Download PDFInfo
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Abstract
The invention discloses a kind of parameter control methods of blade of aviation engine shot-peening machining deformation, and the blade after selecting a shot-peening measures its first deflection and the first residual stress；Using the blade simulation model with feasibility, the deflection of the blade simulation model of multiple groups orthogonal test is measured, the absolute value for the blade simulation model deflection that must send as an envoy to is less than the residual stress value condition of preset threshold；Blade shot-peening machining simulation model is established, shot-peening l-G simulation test is carried out by blade shot-peening machining simulation model, show that optimal shot-peening parameter, optimal shot-peening parameter are to meet the shot-peening parameter of residual stress value condition；The present invention can avoid the accuracy of form and position and dimension overproof after blade processing, reduce the scrappage of blade.
Description
[technical field]
The invention belongs to metal material blade mechanism processing technique fields, and in particular to a kind of blade of aviation engine shot-peening
The parameter control method of machining deformation.
[background technique]
The developing direction of modern aeroengine is to make its weight saving, thrust increase, fuel consumption reduction and noise drop
It is low, to meet this requirement, develop fanjet.Important component of the fan blade as turbofan,
Have the characteristics that long blade, big torsional angle and wide chord of foil.
Due to the effect and working characteristics of blade within the engine, so that blade be made to become size span in engine
Greatly, stress and the part that bearing capacity is most strong, shape is most complicated.In order to meet the safety of engine, high-performance, reliability and
The requirement of service life, it is necessary to assure the stringency of the accuracy of blade shape, the accuracy of size and surface integrity.
Fan blade processing is mainly using techniques such as milling, polishing, heat treatment, vibration finishing, shot-peenings.Up to now, it is
It can be improved the surface integrity, durability and reliability of airplane component, in aerospace field mostly use shot-peening
Method improves the fretting fatigue drag and anti-fatigue performance of titanium alloy component.
Since blade is typical thin-wall member, have the characteristics that wide chord length, type face flexion torsion and poor rigidity, moreover,
Deformation caused by shot-peening is to impact a plastic elongation layer of generation jointly due to many bullets, and then make plastic deformation in blade
The regional area on surface layer generates, and finally causes the bending deformation of blade, and then lead to the accuracy of form and position after blade processing and size
Precision is overproof, so that blade rejection.
[summary of the invention]
The object of the present invention is to provide a kind of parameter control methods of blade of aviation engine shot-peening machining deformation, so that leaf
Piece deflection during shot-peening is controllable, avoids the accuracy of form and position and dimension overproof after blade processing, reduces the scrappage of blade.
The invention adopts the following technical scheme: a kind of parameter control method of blade of aviation engine shot-peening machining deformation,
The following steps are included:
Blade after selecting shot-peening processing, measures its first deflection and the first residual stress；
Using blade simulation model, multiple groups orthogonal test is carried out, and measure the blade simulation model of multiple groups orthogonal test
Deflection, the absolute value for the blade simulation model deflection that must send as an envoy to are less than the residual stress value condition of preset threshold；
Blade shot-peening machining simulation model is established, shot-peening l-G simulation test is carried out by blade shot-peening machining simulation model, is obtained
Optimal shot-peening parameter out, optimal shot-peening parameter are to meet the shot-peening parameter of residual stress value condition.
Further, preset threshold 0.36mm；
Residual stress value condition are as follows: the remnants of the residual stress and leaf basin Z-direction of blade simulation model blade back Z-direction are answered
The difference of value is -60MPa~-80MPa, and Z-direction is direction of the blade root to blade tip.
Further, it establishes after blade shot-peening machining simulation model, blade shot-peening machining simulation model is carried out feasible
Property verifying, feasibility verification method are as follows:
Simulation calculating is carried out to blade shot-peening machining simulation model, the second residual stress after obtaining operation is residual by second
Residue stress and the first residual stress do difference operation；
As the operation difference≤first residual-stress value * 10%, it is feasible to determine that blade shot-peening machining simulation model has
Property；
As operation difference > the first residual-stress value * 10%, judgement blade shot-peening machining simulation model does not have can
Row.
Further, in multiple groups orthogonal test, residual-stress value is tested to fixed blade simulation model multiple groups, multiple groups test is residual
The value range of residue stress value is the value range of the first residual stress.
Further, multi-section measurement method is used when measuring the first deflection, multi-section measurement method is specifically in leaf
Section is chosen respectively and is measured with blade tip in piece blade root, leaf.
Further, multi-point measurement method is used when measuring the first residual stress, multi-point measurement method is specifically to exist
It is measured on blade blade back and leaf basin using multiple points.
The beneficial effects of the present invention are: comprehensively consider deformation caused by shot peening strengthening and shot-peening, it could be in the shot-peening of blade
Real strengthening effect is realized in technique application, and the present invention is based on finite element simulation and reality using titanium alloy thin wall blade as object
The method combined is tested, influence of the residual stress field after studying thin wall vane shot-peening to deformation is soft based on ABAQUS finite element
Part emulates the deformation after blade shot-peening, while carrying out simulation analysis to deformation caused by residual stress after its shot-peening；Leaf
After the completion of piece residual stress deformation simulation, the relationship of residual stress field and deformation is analyzed, further shot-peening parameter is optimized
To reach the control to deforming after thin wall vane shot-peening, so that obtaining the dimensional accuracy and shape of design requirement after thin wall vane shot-peening
Shape precision has certain research significance to the control of thin-wall construction shot-peening deformation.
[Detailed description of the invention]
Fig. 1 is the blade residual stress measurement region division schematic diagram in the embodiment of the present invention；
Fig. 2 is the blade residual stress deformation simulation model schematic in the embodiment of the present invention；
Fig. 3 is the blade emulation deformation schematic diagram in the embodiment of the present invention；
Fig. 3-a is blade emulation deformation overall effect schematic diagram；
Fig. 3-b is blade X-direction deformation schematic diagram；
Fig. 3-c is blade Y-direction deformation schematic diagram；
Fig. 4 is the orthogonal simulating scheme simulation analysis result schematic diagram in the embodiment of the present invention；
Fig. 4-a is the relation schematic diagram of blade X-direction deflection and residual stress difference；
Fig. 4-b is the relation schematic diagram of blade Y-direction deflection and residual stress difference.
Fig. 5 is more bullet shot-peening simulation model schematic diagrames in the embodiment of the present invention.
[specific embodiment]
The following describes the present invention in detail with reference to the accompanying drawings and specific embodiments.
The invention discloses a kind of parameter control methods of blade of aviation engine shot-peening machining deformation, including following step
It is rapid:
Blade after selecting shot-peening processing, measures its first deflection and the first residual stress, the first deflection refers to
Deformable blade amount after the blade shot-peening processing of the selection.
Blade simulation model is established in Abaqus software, method particularly includes:
Blade 3-D geometric model is imported into Abaqus software；In material properties module, by Poisson's ratio, elasticity modulus, close
The parameters write-in such as degree and material constitutive, and assign corresponding material properties to blade entity；Then is assembled and be arranged general
Static analysis step；And then complete addition constraint link；Residual stress then is applied to blade；Then by blade back and leaf basin sheet body and
The suitable grid of blade entity division；It can be obtained blade simulation model after establishing working document analytic operation.
First residual stress is loaded on blade simulation model, simulation calculating is carried out, obtains the of blade simulation model
Two deflections, the second deflection are the deformable blade amount of blade simulation model shot-peening processing front and back.
Using blade simulation model, multiple groups orthogonal test is carried out, in multiple groups orthogonal test, give fixed blade simulation model multiple groups
Residual-stress value is tested, the value range that multiple groups test residual-stress value is the value range of the first residual stress.And it measures more
The absolute value of the deflection of the blade simulation model of group orthogonal test, the blade simulation model deflection that must send as an envoy to is less than preset threshold
Residual stress value condition.
Preset threshold is preferably 0.36mm；Residual stress value condition are as follows: the remnants of blade simulation model blade back Z-direction are answered
The difference that the remnants of power and leaf basin Z-direction should be worth is -60MPa~-80MPa.
Blade shot-peening machining simulation model is established in Abaqus software, method particularly includes:
Bullet model is established in Abaqus software and by spray testpieces model；In material properties module, by Poisson's ratio, bullet
Property the parameters write-in such as modulus, density and material constitutive, and assign corresponding material properties to bullet model and by spray testpieces mould
Type；It is then assembled and display kinematic analysis step is set；And then complete addition constraint link；Speed ginseng then is applied to bullet
Number；Then by bullet model and by the spray suitable grid of testpieces model partition；It can be obtained after establishing working document analytic operation
Obtain blade shot-peening machining simulation model.
It establishes after blade shot-peening machining simulation model, blade shot-peening machining simulation model is verified, verification method
Are as follows:
Simulation calculating is carried out to blade shot-peening machining simulation model, the second residual stress after obtaining operation is residual by second
Residue stress and the first residual stress do difference operation；
As the operation difference≤first residual-stress value * 10%, it is feasible to determine that blade shot-peening machining simulation model has
Property；
As operation difference > the first residual-stress value * 10%, judgement blade shot-peening machining simulation model does not have can
Row.
Shot-peening l-G simulation test is carried out by blade shot-peening machining simulation model, obtains optimal shot-peening parameter, optimal shot-peening ginseng
Number is the shot-peening parameter for meeting residual stress value condition.After obtaining optimal shot-peening parameter, optimal shot-peening Verification is carried out
Test is the optimal shot-peening parameter finally determined by the optimal shot-peening parameter after verification test.
Using multi-section measurement method when measuring the first deflection and the second deflection, multi-section measurement method is specifically to exist
Section is chosen respectively and is measured with blade tip in blade root, leaf；
Using multi-point measurement method when measuring the first residual stress, multi-point measurement method be specifically in blade blade back and
It is measured on leaf basin using multiple points, each can also put the residual stress for measuring multiple depth when measurement.
Embodiment
Following steps are specifically used in this implementation:
Step 1: planning shot-peening deformable blade data test
When measurement using with the consistent coordinate system that designs a model, i.e., using tenon root bottom part midpoint as origin, leading edge is to exhaust
The direction on side is X-direction, and blade back is Y-direction to the direction of leaf basin, and blade root is Z-direction to the direction of blade tip, establishes coordinate system, and
X-axis is parallel to tenon root sideline.
The characterization accuracy for comprehensively considering deformable blade Data Detection cost and deformable blade amount, blade root, leaf in blade
In and blade tip position select three sections, test-schedule is carried out to the overall deformation situation of blade.
Step 2: the test of existing shot-peening deformable blade amount
According to the planning situation that blade deformation data in step 1 is tested, using three coordinate measuring machine to blade root, Ye Zhong
And the deflection situation in three sections of blade tip is tested.
Step 3: planning shot-peening blade residual stress numerical value test
Comprehensively consider residual stress testing cost and the characterization accuracy of blade residual stress, respectively plans 9 on blade two sides
Region carries out the test of residual stress distribution condition, and test zone is as shown in Figure 1.
Step 4: the test of existing shot-peening blade residual stress
According to the planning situation of blade residual stress test, using X-ray diffractometer to the residual stress in 9 regions of blade
Distribution situation is tested.
Residual stress is tested using Proto LXRD MG2000 residual stress test analysis system, tests target Cu
Target, 141.88 ° of the angle of diffraction, { 213 } crystal face tests electric current 20mA, test voltage 25kV.
Step 5: the relationship of coarse analysis blade residual stresses and deformations
According to the blade residual stress data and deformation data measured, comparative analysis blade blade back and leaf basin corresponding region
The residual-stress value difference that residual stress, blade back and leaf basin correspond to measurement point is larger, discovery deformable blade and blade blade back and leaf
The whole residual stress difference of basin is related.
Step 6: causing deformation to carry out simulation calculating blade residual stress (soft by executing finite element simulation on computer
Part carries out)
As shown in Fig. 2, establishing leaf model in finite element emulation software, and the blade residual stress data measured are added
It is downloaded on the leaf model, carries out simulation calculating after the completion of residual stress load, as shown in figure 3, after obtaining analogue simulation operation
The deformation of leaf model.
Step 7: the relationship of Orthogonal Analysis blade residual stresses and deformations
According to the residual stress situation that step 4 measures, the residual-stress value range of load is determined, take Orthogonal Method to carry out big
Measure emulation experiment, experimental program is as shown in table 6, analyze blade residual stresses and deformations relationship, analysis result as shown in figure 4,
The result shows that when blade blade back Z-direction residual-stress value and leaf basin Z-direction residual-stress value only it is poor for -60MPa~-
When 80MPa, the deformation of blade x-direction and y-direction is all minimum；And the difference of the residual-stress value of the X-direction of blade is to deformable blade
Influence it is little.
The orthogonal simulating scheme of table 6
Step 8: establishing more bullet shot-peening simulation models
The shot-peening simulation model of multiple bullet impacts is established according to the parameter of blade shot-peening, as shown in figure 5, and being emulated
Operation (simulation calculating is that finite element emulation software is used to carry out analogue simulation on computers).
Step 9: the feasibility of verifying shot-peening simulation model
The residual stress data of residual-stress value and the shot-peening blade measured after shot-peening simulation model operation are compared
Compared with analysis, feasibility verification method are as follows:
Simulation calculating is carried out to blade shot-peening machining simulation model, the second residual stress (emulation knot after obtaining operation
Fruit), the second residual stress and the first residual stress (measured result) are done into difference operation；
As the operation difference≤first residual-stress value * 10%, it is feasible to determine that blade shot-peening machining simulation model has
Property；
As operation difference > the first residual-stress value * 10%, judgement blade shot-peening machining simulation model does not have can
Row.
Shot-peening residual stress data are as shown in table 7, and the shot-peening actual measurement for randomly selecting 9 points corresponding with table 2 and table 3 is residual
Residue stress and shot-peening emulation residual stress meet feasibility, demonstrate shot-peening simulation model feasibility.
7 shot-peening residual-stress value of table compares
Step 10: optimization shot-peening parameter
According to the analysis of the residual stresses and deformations relationship of step 8 as a result, being emulated in conjunction with shot-peening, emulated by multiple shot-peening
Experiment, by the residual stress of control shot-peening gain of parameter anticipation as a result, optimum results are as shown in table 8, and then are answered by remnants
The deflection of power control blade.
8 shot-peening Optimal Parameters of table
Step 11: the application and verifying of optimization shot-peening parameter
Since the optimal shot-peening parameter obtained is obtained using blade shot-peening machining simulation model, need to verify practical spray
Its validity when ball is processed.Therefore, shot-peening processing is carried out to blade using the shot-peening parameter after optimization, while is sprayed according to optimization
Ball parameter carries out analog simulation again, and carries out the measurement of deformable blade amount, verifying thin-wall construction shot-peening machining deformation control
Feasibility, verification result are as shown in table 9.
9 blade optimization deformation result of table
As shown in table 9, actual processing and analog simulation are carried out to blade using the shot-peening parameter after optimization, while according to survey
The deflection for obtaining blade show, blade residual stress deformation simulation result is consistent with measured result very high after being compared, spray
After ball machining parameters optimization, the deflection of shot-peening processing rear blade, which has, obviously to be reduced, and has been reached Element Design requirement, has been tested
Demonstrate,prove the feasibility of thin-wall construction shot-peening machining deformation control.
A kind of control method of the shot-peening machining deformation of blade of aviation engine of the present embodiment, feature are as follows: pass through survey
The residual stress distribution and deformable blade situation of the shot-peening blade obtained, analyze the relationship of residual stresses and deformations, obtain blade and blade
Back is the main reason for causing deformable blade with leaf basin residual stress difference, then by shot-peening simulation study shot-peening parameter with it is residual
The relationship of residue stress.Under the premise of guaranteeing shot-peening effect, the residual stress determined by control shot-peening gain of parameter, into
And pass through the deformation of residual stress control blade, achieve the purpose that inhibit the deformation of blade shot-peening.
The embodiment of the present invention carries out test analysis to the residual stress of shot-peening processing rear blade.In the blade surface measured and
On the basis of surface residual stress data, analyze leaf surface residual stress distribution and residual stress along depth direction point
Cloth.It is loaded based on blade design model residual stress, establishes blade residual stress deformation simulation model.In simulation analysis result
On the basis of, analyze the relationship of residual-stress value and deformable blade.
Using more bullet shot-peening emulation modes, the variation of average velocity of projectile is had studied to surface and surface residual stress point
The influence of cloth, selective analysis distribution situation of the residual stress along depth direction；On this basis, it has studied based on blade minimum
Deform the shot-peening parameter optimization of constraint；Simulation study shows: when blade back pressure is 2bar, leaf basin pressure is
It is deformed when 1.418bar, after blade shot-peening minimum.This example carries out blade processing using the shot-peening parameter after optimization, X-direction
Deformation becomes 0.19mm from 0.65mm, and the deformation of Y-direction becomes 0.17mm from 0.48mm, demonstrates having for the shot-peening parameter of optimization
Effect property.
Claims (6)
1. a kind of parameter control method of blade of aviation engine shot-peening machining deformation, which comprises the following steps:
Blade after selecting shot-peening processing, measures its first deflection and the first residual stress；
Using blade simulation model, multiple groups orthogonal test is carried out, and measure the blade simulation model of the multiple groups orthogonal test
Deflection, the absolute value for the blade simulation model deflection that must send as an envoy to are less than the residual stress value condition of preset threshold；
Blade shot-peening machining simulation model is established, shot-peening l-G simulation test is carried out by the blade shot-peening machining simulation model, is obtained
Optimal shot-peening parameter out, the optimal shot-peening parameter are to meet the shot-peening parameter of the residual stress value condition.
2. a kind of parameter control method of blade of aviation engine shot-peening machining deformation as described in claim 1, feature exist
In the preset threshold is 0.36mm；
The residual stress value condition are as follows: the residual stress of the blade simulation model blade back Z-direction is residual with leaf basin Z-direction
The remaining difference that should be worth is -60MPa~-80MPa, and the Z-direction is direction of the blade root to blade tip.
3. a kind of parameter control method of blade of aviation engine shot-peening machining deformation as claimed in claim 1 or 2, feature
It is, establishes after blade shot-peening machining simulation model, feasibility verifying, institute is carried out to the blade shot-peening machining simulation model
State feasibility verification method are as follows:
Simulation calculating carried out to the blade shot-peening machining simulation model, the second residual stress after obtaining operation, by described the
Two residual stress and the first residual stress do difference operation；
As the operation difference≤first residual-stress value * 10%, it is feasible to determine that the blade shot-peening machining simulation model has
Property；
As operation difference > the first residual-stress value * 10%, determine the blade shot-peening machining simulation model do not have can
Row.
4. a kind of parameter control method of blade of aviation engine shot-peening machining deformation as claimed in claim 3, feature exist
In in the multiple groups orthogonal test, giving blade simulation model multiple groups test residual-stress value, the multiple groups test is remaining
The value range of stress value is the value range of the first residual stress.
5. a kind of parameter control method of blade of aviation engine shot-peening machining deformation as claimed in claim 4, feature exist
In, measure first deflection when use multi-section measurement method, the multi-section measurement method be specifically blade root,
Section is chosen respectively and is measured with blade tip in leaf.
6. a kind of parameter control method of blade of aviation engine shot-peening machining deformation as described in claim 4 or 5, feature
It is, multi-point measurement method is used when measuring first residual stress, and the multi-point measurement method is specifically in blade
It is measured on blade back and leaf basin using multiple points.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110877295A (en) * | 2019-11-13 | 2020-03-13 | 中国航发南方工业有限公司 | Method for processing blade disc wet shot blasting and blade disc |
| CN111062094A (en) * | 2019-10-08 | 2020-04-24 | 珠海格力电器股份有限公司 | Topological optimization design method of spindle box of machining center |
| CN111475891A (en) * | 2020-03-26 | 2020-07-31 | 青岛海尔空调器有限总公司 | Design method and device for air conditioner movement mechanism |
| CN112651157A (en) * | 2020-12-24 | 2021-04-13 | 北京星航机电装备有限公司 | Aviation thin-walled part plasma spraying deformation control method |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004045115A (en) * | 2002-07-10 | 2004-02-12 | Ishikawajima Harima Heavy Ind Co Ltd | Peening intensity measuring method |
| EP1485510A1 (en) * | 2002-03-18 | 2004-12-15 | Surface Technology Holdings, Ltd. | Method and apparatus for providing a layer of compressive residual stress |
| JP2006110634A (en) * | 2004-10-12 | 2006-04-27 | Sintokogio Ltd | Method for selecting peening strength to steel component |
| US20130138363A1 (en) * | 2010-10-26 | 2013-05-30 | Sintokogio, Ltd. | Evaluation method and evaluation system for impact force of laser irradiation during laser peening and laser peening method and laser peening system |
| CN104484538A (en) * | 2014-12-29 | 2015-04-01 | 滁州汽车与家电技术及装备研究院 | Shot peening strengthening treatment process parameter determination method based on finite element analysis |
| CN104866652A (en) * | 2015-04-29 | 2015-08-26 | 西北工业大学 | Finite element simulation method for shot-peening strengthening deformation based on ABAQUS |
| CN106649994A (en) * | 2016-11-16 | 2017-05-10 | 西北工业大学 | Predicting method of titanium alloy shot peening strengthening remnant stress field |
| CN106636563A (en) * | 2016-11-04 | 2017-05-10 | 广东工业大学 | Multiple-unit control method and multiple-unit control device for reverse laser shot peening |
| CN107229783A (en) * | 2017-05-22 | 2017-10-03 | 济南大学 | A kind of potassium steel shot blast machine blade stress peening process determination method for parameter |
| CN108614418A (en) * | 2018-03-27 | 2018-10-02 | 西北工业大学 | Titanium alloy milling-polishing-shot peening strengthening residual stress field process control method |
-
2018
- 2018-11-06 CN CN201811312755.XA patent/CN109583037A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1485510A1 (en) * | 2002-03-18 | 2004-12-15 | Surface Technology Holdings, Ltd. | Method and apparatus for providing a layer of compressive residual stress |
| JP2004045115A (en) * | 2002-07-10 | 2004-02-12 | Ishikawajima Harima Heavy Ind Co Ltd | Peening intensity measuring method |
| JP2006110634A (en) * | 2004-10-12 | 2006-04-27 | Sintokogio Ltd | Method for selecting peening strength to steel component |
| US20130138363A1 (en) * | 2010-10-26 | 2013-05-30 | Sintokogio, Ltd. | Evaluation method and evaluation system for impact force of laser irradiation during laser peening and laser peening method and laser peening system |
| CN104484538A (en) * | 2014-12-29 | 2015-04-01 | 滁州汽车与家电技术及装备研究院 | Shot peening strengthening treatment process parameter determination method based on finite element analysis |
| CN104866652A (en) * | 2015-04-29 | 2015-08-26 | 西北工业大学 | Finite element simulation method for shot-peening strengthening deformation based on ABAQUS |
| CN106636563A (en) * | 2016-11-04 | 2017-05-10 | 广东工业大学 | Multiple-unit control method and multiple-unit control device for reverse laser shot peening |
| CN106649994A (en) * | 2016-11-16 | 2017-05-10 | 西北工业大学 | Predicting method of titanium alloy shot peening strengthening remnant stress field |
| CN107229783A (en) * | 2017-05-22 | 2017-10-03 | 济南大学 | A kind of potassium steel shot blast machine blade stress peening process determination method for parameter |
| CN108614418A (en) * | 2018-03-27 | 2018-10-02 | 西北工业大学 | Titanium alloy milling-polishing-shot peening strengthening residual stress field process control method |
Non-Patent Citations (6)
| Title |
|---|
| JINXIANG LIU 等: "Simulation of Shot Peening Process Using Combined Hardening Model", 《2010 INTERNATIONAL CONFERENCE ON E-PRODUCT E-SERVICE AND E-ENTERTAINMENT》 * |
| NEWBY, M 等: "Finite element modelling of residual stresses in shot-peened steam turbine blades", 《FATIGUE & FRACTURE OF ENGINEERING MATERIALS & STRUCTURES》 * |
| WU, DAOXIA 等: "Surface characterization of Ti1023 alloy shot peened by cast steel and ceramic shot", 《ADVANCES IN MECHANICAL ENGINEERING 》 * |
| 张少平 等: "喷丸强化对TC17钛合金表面完整性及疲劳寿命的影响", 《航空制造技术》 * |
| 张炜 等: "机翼缘条喷丸强化变形模拟与参数优化", 《航空制造技术》 * |
| 蒋聪盈 等: "TC4钛合金激光冲击强化与喷丸强化的残余应力模拟分析", 《表面技术》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111062094A (en) * | 2019-10-08 | 2020-04-24 | 珠海格力电器股份有限公司 | Topological optimization design method of spindle box of machining center |
| CN110877295A (en) * | 2019-11-13 | 2020-03-13 | 中国航发南方工业有限公司 | Method for processing blade disc wet shot blasting and blade disc |
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