CN102169518A - Accurate forming method for precise-casting turbine blade die cavity - Google Patents
Accurate forming method for precise-casting turbine blade die cavity Download PDFInfo
- Publication number
- CN102169518A CN102169518A CN 201110072878 CN201110072878A CN102169518A CN 102169518 A CN102169518 A CN 102169518A CN 201110072878 CN201110072878 CN 201110072878 CN 201110072878 A CN201110072878 A CN 201110072878A CN 102169518 A CN102169518 A CN 102169518A
- Authority
- CN
- China
- Prior art keywords
- model
- casting
- blade
- turbine blade
- numerical simulation
- 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
Images
Abstract
The invention discloses an accurate forming method for a precise-casting turbine blade die cavity, which comprises the following steps: the casting system model of a turbine blade is designed according to the casting technique of the turbine blade and a casting test is implemented; a thermoelectric couple is adopted for measuring the actual temperatures of the front edge and back edge of the blade, a blade back and a blade cabin during casting and condensing processes, determining the heat exchange coefficients of an interface, implementing numerical simulation on the casting process, obtaining the deformation situations of turbine blade castings during the casting process, implementing numerical simulation on precise casting process after the anti-deformation treatment of the casting model, and finally whether a molded surface deviation value meets the precision requirements on the size tolerance of the castings or not is judged. The accurate forming method for a precise-casting turbine blade die cavity greatly improves the finished product rate of the turbine blade, and reduces the periods and times of die trial.
Description
Technical field
The present invention relates to a kind of method for shaping of mold cavity.
Background technology
Complicated hollow turbine vane is the core technology of high thrust-weight ratio engine, and this class turbo blade is because inner cooling structure complexity, aerodynamic configuration and the strictness of blade wall thickness dimension precision requirement, and the condition of work harshness is the key of aeromotor development.At present, hollow turbine vane generally adopts monocrystalline or crystallographic orientation not to have the surplus hot investment casting, and after high temperature alloy injected formwork, reducing with temperature can the generation drawdown deformation.The mold cavity that investment pattern precision casting adopts must be considered the compensation to the foundry goods drawdown deformation.Because turbo blade is the ill structure that a large amount of free form surfaces and complicated inner cavity are formed, it is non-linear that the inequality of dispelling the heat when therefore cooling off causes the contraction of foundry goods, heterogeneous.Thus, making the used precision casting mould of turbo blade becomes reseach of engine production and manufactures and designs the blade frock that the cycle is the longest, technical difficulty is maximum in preparing, and the cavity design of precision casting mould is to solve the accurately key link of control shape.
The principle of design of mold cavity be deformation place give an amount of anti-deformation with offset foundry goods solidifying with cooling procedure in drawdown deformation.The drawdown deformation of foundry goods is non-linear, and embodies in the mode of displacement field (distribution of blade casting deformation amount).How to obtain the displacement field of foundry goods, and with serve as according to the die cavity of optimizing mould, be a key that guarantees the smart contraction rule cun precision of blade.At present, the design of mold cavity is still adopted in X, Y, three directions of Z and is calculated profile according to the comprehensive shrinkage factor that linear method simply provides.Obvious this method has unreasonable part, because blade is complex-shaped, heat radiation inequality when causing the foundry goods cooling, thereby the distortion of blade each point and inconsistent must could obtain to meet the product of accuracy requirement through after the die trial that repairs a die repeatedly repeatedly.So the die trial of this coarse reversible deformation Treatment Design mold cavity often, the manufacturing cycle of mould is long, can not satisfy mould and produce short period, high-precision requirement.Along with software ANSYS is used for actual processing, the at present existing method for designing mould cavity that the reversible deformation of the numerical simulation means quantification handles (Chinese patent application number: 200710028749.7 of utilizing, June 22 2007 applying date), for improving the mould design efficiency, the minimizing manufacturing cycle plays a role.But still employing experience of the employed relaxation factor of reversible deformation algorithm determines that this kind method still is difficult to effectively be directly used in the process of manufacture.
Summary of the invention
In order to overcome the accurately deficiency of designing mould die cavity of prior art, the invention provides a kind of precision casting mould cavity design method based on numerical simulation, its result can be directly used in the design of turbo blade precision casting mould die cavity, solves the problem that the cycle is long, efficient is low, precision is low of present similar mould design.
The technical solution adopted for the present invention to solve the technical problems may further comprise the steps:
Design the running gate system model of turbo blade according to the pouring technology of turbo blade.
The running gate system model that adopts finite element method that step 1 is set up carries out dividing elements.
The running gate system model that adopts step 1 to set up is poured into a mould experiment.Adopt the actual temperature at thermocouple measurement blade front and rear edge, blade back and leaf basin place in cast and process of setting, introduce formula
As the mathematical model of finding the solution interface heat exchange coefficient.In the formula: T (h
c) be the simulated temperature value,
T 'For with T (h
c) corresponding measurement temperature value, the thermocouple number of n for arranging, promptly unknown interface heat exchange coefficient number.Set up iterative relation formula T
K+1=T
k+ Δ T.In the formula: T
K+1Be the k+1 time iteration result, T
kBe the result of the k time iteration, the modified value when Δ T is the k time iteration is as the accounting temperature value T of numerical simulation (h
c) with the absolute value of the difference of measuring temperature value | T
k-T ' | require (can be taken as 10 less than specified accuracy
-3) time, when promptly the iteration result levels off to the point for measuring temperature temperature, have
, think that then the heat exchange situation in numerical simulation this moment conforms to actual, and then definite interface heat exchange coefficient h
c
Obtain accurate interface heat exchange coefficient by step 3, carry out the numerical simulation of casting process then, to obtain the turbo blade casting deformation situation in the casting process.At first apply the numerical simulation boundary condition, comprise the thermal physical property parameter of alloy material and formwork material, initial cast alloy temperature, end the interface heat exchange coefficient between alloy temperature, alloy material and the finish cast die shell of numerical evaluation, the constraint condition of model displacement.By finding the solution of essence casting process stress field, draw the stress distribution of smart each node of casting process turbo blade grid model, and then derive the displacement of each node, can set up the displacement field model.
Based on the reversible deformation iterative formula
Cast model is carried out reversible deformation to be handled.P in the formula
0(x
0, y
0) any coordinate of discrete point on the initial blade surface of expression,
Expression any one discrete point coordinate on the mold cavity, K represents the shrinkage factor of discrete point correspondence, the used K of shrinkage by inspection is 1.012 in the time of can being taken as Mould Cavity for Turbine Blade here and repairing a die,
The coordinate difference ratio of two discrete points on the section of the foundry goods sustained height of expression cast direction, W
Xy(x
1, y
1) displacement variable between two discrete points of expression.
Discrete point after obtaining the cast model discrete point carried out reversible deformation and handle in step 5 carries out obtaining the reversible deformation model behind the surface reconstruction, just the mold cavity model.In order to verify whether the mold cavity model meets the demands, under the prerequisite of process conditions identical and mould structure, carry out the numerical simulation of smart casting process with step 4.
Reversible deformation model that step 6 is obtained and foundry goods design a model and obtain the profile departure of reversible deformation model behind the registration, judge whether the profile departure meets the accuracy requirement of the dimensional tolerance of casting.As meeting accuracy requirement, then final reversible deformation model is the die cavity of precision casting mould.As do not meet accuracy requirement, and repeating step 4～step 7 then, the model behind final reversible deformation model deformation meets accuracy requirement.
The invention has the beneficial effects as follows:, significantly improved the yield rate of turbo blade by optimal design to essence casting Mould Cavity for Turbine Blade; The cycle and the number of times of die trial have been reduced.This method has important significance for theories and using value to the design of mold cavity, this method has been avoided the shortcoming of traditional empirical design, have the advantages that the design cycle is short, precision is high, efficient is high, and the defective of mould design can be found and correct in real time on computers, shortened the cycle of mould development, reduce the mould design cost significantly, be particularly useful for not having the governed new product development of experience.This method is applicable to the design of aeromotor with the outer die cavity of turbo blade precision casting mould.With respect to the technology of patent 200710028749.7, it is unreliable to the invention solves present numerical simulation result, can only be qualitative and problem that can't be quantitative.Simultaneously all used different relaxation factors, improved the precision of reversible deformation compensation for each grid node.
The present invention is further described below in conjunction with drawings and Examples.
Description of drawings
Fig. 1 is a process flow diagram of the present invention.
Fig. 2 is smart casting Turbine Blade Model.
Fig. 3 is the running gate system model.
Fig. 4 is the thermopair distribution schematic diagram.
Embodiment
Below in conjunction with accompanying drawing embodiments of the invention are elaborated: present embodiment has provided detailed embodiment and process being to implement under the prerequisite with the technical solution of the present invention.But protection scope of the present invention is not limited to following embodiment.
Produce the design of the shaper die cavity of certain type aeroturbine blade, the embodiment step as shown in Figure 1:
Adopt certain type turbo-power blade to carry out numerical simulation, as shown in Figure 2.Its major parameter is the long 101mm of blade, maximum chord length 59.21mm, maximum inscribed circle radius 5.67mm, leading-edge radius 4.22mm, trailing edge radius 1.27mm.Blade is selected second generation single crystal super alloy DD6 for use, and formwork is selected silica sand for use.According to casting feeding theory and practical production experience,, adopt the teeming formula, 3 one group at power blade design blade casting technique and running gate system.As shown in Figure 3.
Adopt commercial finite element pre-processing software Hypermesh (product of U.S. Altair company) model to be carried out dividing elements based on non-uniform grid subdivision technology, at first the running gate system model is imported among the Hypermesh, it is dispersed is tetrahedron element, element quality satisfies general enterprise finite element analysis quality requirements, in the present embodiment, require the element quality more than 95% to satisfy: the unit warpage less than 5.0, length limit, unit ratio less than 5.0, deflection less than 60.0, the unit Jacobi is greater than 0.7.Tetrahedron element sum 1,640,000 5 thousand.
The running gate system of utilizing step 1 to set up is provided with a temperature field experiment, and the actual measurement turbo blade is in the temperature field of cast and process of setting.Utilize peg wood to substitute the thermopair fixed position after wax-pattern makes, then reserve the preset holes of thermopair behind the system shell in the fixed position.The riding position of thermopair as shown in Figure 4.Experiment is provided with 14 groups of thermopairs of common layout, measures the temperature variation data of blade tenon, blade, seeding section respectively.Wherein, the seeding section is laid 4 groups of thermopairs altogether, 1,5,6, No. 10 thermopair as shown in Figure 4, and 1, No. 10 thermocouple measurement seeding section bottom temp is measured seeding section spiral place temperature No. 5, measures seeding section and blade junction temperature No. 6.The blade section is laid 7 groups of thermopairs, and 2, No. 3 thermopairs are placed in blade leaf basin axis as shown in Figure 4, and 7,8, No. 9 thermopair is positioned at the trailing edge place, and 11, No. 12 thermopair is positioned at blade blade back axis.Tenon is laid 3 groups of thermopairs, and No. 4 thermopairs as shown in Figure 4 are positioned at the blade axis, is positioned at same horizontal line with No. 4 thermopairs 13, No. 14, and two groups of thermopair institute locations put identically, but No. 13 depth positions are shallow than No. 14 thermocouples.According to the thermocouple location arrangement that experiment is adopted, can measure the thermograde of blade process of setting, the temperature contrast of going back the same level height diverse location of energy measurement (leaf basin, blade back, trailing edge) simultaneously.Adopt the gravity-assist pouring mode.Pouring temperature is 1550 ℃, and experiment has been carried out the temperature field actual measurement to six groups of blades.Data acquisition time 4000 seconds, collecting temperature variation range are 1550 ℃-600 ℃.The anti-module of asking based on ProCAST (product of French ESI Group), the input measured value, through 15 iteration, the counter curve of asking the coefficient of heat transfer t conversion in time that obtains foundry goods and formwork, the function that obtains the interface coefficient of heat transfer between foundry goods and formwork through the curve match is expressed: h
Foundry goods-formwork=12160.36+1245.61t
-0.52
Adopt ProCAST that turbo blade is carried out smart casting process numerical simulation, alloy is selected the DD6 high-temperature nickel-base alloy for use, and its liquidus temperature is 1380 ℃, and solidus temperature is 1310 ℃.Its pyroconductivity is 33.2W/mK, and density is 8780kg/m
3, specific heat is 99.0KJ/Kg/K.Formwork is selected silica sand for use, and its pyroconductivity is 0.59W/mK, and density is 1520kg/m
3, specific heat is 1.20KJ/Kg/K.The alloy initial temperature of numerical simulation is 1550 ℃, and the alloy temperature of numerical simulation termination of computations is 600 ℃.Interface heat exchange coefficient between alloy and the formwork is selected the calculated value of embodiment step 3.Displacement constrains is that running channel bottom and blade seeding section bottom fixing and cold copper bottom is fixing.
Based on the reversible deformation iterative formula
Cast model is carried out reversible deformation to be handled.In the formula
Discrete point on the expression mold cavity, K represents the shrinkage factor of each discrete point correspondence.Be 1.012,
The coordinate difference ratio of two discrete points on the expression section line, W
Xy(x
1, y
1) expression discrete point displacement variable, P
0(x
0, y
0) expression initial blade profile discrete point coordinate.
Discrete point after pin obtains the cast model discrete point carried out reversible deformation and handle in step 5 obtains the reversible deformation model after using the surface reconstruction function under the UG (product of Siemens), just the mold cavity model.In order to verify whether the mold cavity model meets the demands, under the prerequisite of process conditions identical and mould structure, carry out the numerical simulation of smart casting process with step 4.
The reversible deformation model that step 6 is obtained is by UG software File menu " importing " function importing UG platform down, designs a model with foundry goods and obtains the profile departure of reversible deformation model behind the registration.Whether the model behind the detection reversible deformation model deformation meets the foundry goods accuracy requirement.As meet accuracy requirement, then according to final reversible deformation distorted pattern, design the die cavity of precision casting mould.As do not meet accuracy requirement, and then proceed foundry goods reversible deformation processing and numerical simulation, the model behind final reversible deformation model deformation meets accuracy requirement.
Claims (1)
1. the accurate method for shaping of smart casting Mould Cavity for Turbine Blade is characterized in that comprising the steps:
Step 1
Design the running gate system model of turbo blade according to the pouring technology of turbo blade;
Step 2
The running gate system model that adopts finite element method that step 1 is set up carries out dividing elements;
Step 3
The running gate system model that adopts step 1 to set up is poured into a mould experiment; Adopt the actual temperature at thermocouple measurement blade front and rear edge, blade back and leaf basin place in cast and process of setting, introduce formula
As the mathematical model of finding the solution interface heat exchange coefficient, in the formula: T (h
c) be the simulated temperature value,
T 'For with T (h
c) corresponding measurement temperature value, the thermocouple number of n for arranging; Set up iterative relation formula T
K+1=T
k+ Δ T is in the formula: T
K+1Be the k+1 time iteration result, T
kBe the result of the k time iteration, the modified value when Δ T is the k time iteration is as the accounting temperature value T of numerical simulation (h
c) with the absolute value of the difference of measuring temperature value | T
k-T ' | when requiring, T is arranged less than specified accuracy
K+1=T ' thinks that then the heat exchange situation in numerical simulation this moment conforms to actual, and then definite interface heat exchange coefficient h
c
Step 4
Obtain accurate interface heat exchange coefficient by step 3, carry out the numerical simulation of casting process then, to obtain the turbo blade casting deformation situation in the casting process: at first apply the numerical simulation boundary condition, comprise the thermal physical property parameter of alloy material and formwork material, initial cast alloy temperature, end the interface heat exchange coefficient between alloy temperature, alloy material and the finish cast die shell of numerical evaluation, the constraint condition of model displacement; By finding the solution of essence casting process stress field, draw the stress distribution of smart each node of casting process turbo blade grid model, and then derive the displacement of each node, can set up the displacement field model.
Step 5
Based on the reversible deformation iterative formula
Cast model is carried out reversible deformation handle P in the formula
0(x
0, y
0) any coordinate of discrete point on the initial blade surface of expression,
Any one discrete point coordinate on the expression mold cavity, K represents the shrinkage factor of discrete point correspondence, getting K is 1.012,
The coordinate difference ratio of two discrete points on the section of the foundry goods sustained height of expression cast direction, W
Xy(x
1, y
1) displacement variable between two discrete points of expression;
Step 6
Discrete point after obtaining the cast model discrete point carried out reversible deformation and handle in step 5 carries out obtaining the mold cavity model behind the surface reconstruction; Under the prerequisite of process conditions identical and mould structure, carry out the numerical simulation of smart casting process with step 4;
Step 7
Reversible deformation model that step 6 is obtained and foundry goods design a model and obtain the profile departure of reversible deformation model behind the registration, judge whether the profile departure meets the accuracy requirement of the dimensional tolerance of casting; As meeting accuracy requirement, then final reversible deformation model is the die cavity of precision casting mould; As do not meet accuracy requirement, and repeating step 4～step 7 then, the model behind final reversible deformation model deformation meets accuracy requirement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110072878 CN102169518A (en) | 2011-03-24 | 2011-03-24 | Accurate forming method for precise-casting turbine blade die cavity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110072878 CN102169518A (en) | 2011-03-24 | 2011-03-24 | Accurate forming method for precise-casting turbine blade die cavity |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102169518A true CN102169518A (en) | 2011-08-31 |
Family
ID=44490679
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110072878 Pending CN102169518A (en) | 2011-03-24 | 2011-03-24 | Accurate forming method for precise-casting turbine blade die cavity |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102169518A (en) |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102426622A (en) * | 2011-11-15 | 2012-04-25 | 清华大学 | Adaptive variable-speed drawing simulation method for production of single-crystal blade |
| CN102507636A (en) * | 2011-09-30 | 2012-06-20 | 中国科学院金属研究所 | Method for measuring interfacial heat transfer coefficient of rapid cooling process of steel |
| CN102819651A (en) * | 2012-08-20 | 2012-12-12 | 西北工业大学 | Simulation-based parameter optimizing method for precise casting process of single crystal turbine blade |
| CN103826776A (en) * | 2011-09-27 | 2014-05-28 | 株式会社神户制钢所 | Mold designing method, and mold |
| CN104325083A (en) * | 2014-11-24 | 2015-02-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Pouring technique of directional turbine blade with block cast cover board structure |
| CN105300695A (en) * | 2015-09-22 | 2016-02-03 | 中国航空工业集团公司沈阳发动机设计研究所 | Turbine rotating disc cavity flow heat exchange formula correction coefficient determination method |
| CN105305089A (en) * | 2015-11-19 | 2016-02-03 | 西安空间无线电技术研究所 | Design device and design method of adjustable composite-material mold |
| JP2016503729A (en) * | 2013-01-17 | 2016-02-08 | スネクマ | Part manufacturing method using lost wax casting method with directional cooling |
| CN106777561A (en) * | 2016-11-29 | 2017-05-31 | 朱金焰 | A kind of layout method of turbo blade essence casting wax pattern Tao Xin clamping elements |
| CN107037779A (en) * | 2017-05-09 | 2017-08-11 | 西北工业大学 | Free form surface NC process tool track optimizing methods under non-homogeneous tolerance |
| CN107506519A (en) * | 2017-07-07 | 2017-12-22 | 厦门大学 | A kind of parametrization processing method of essence casting turbine blade air film Cooling Holes |
| CN107577874A (en) * | 2017-09-06 | 2018-01-12 | 厦门大学 | A kind of determination method of hollow turbine vane investment casting mould design shrinkage factor |
| CN107755636A (en) * | 2017-09-12 | 2018-03-06 | 东方电气集团东方汽轮机有限公司 | A kind of quick method for solving the casting deformation of combustion engine blade |
| CN109338456A (en) * | 2018-12-03 | 2019-02-15 | 上海交通大学 | Single crystal articles production of intelligent control technology based on numerical simulation and neural network judgement |
| CN110760715A (en) * | 2019-11-29 | 2020-02-07 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for accurately detecting size of inner cavity of shell of high-temperature alloy precision casting |
| CN111872324A (en) * | 2020-06-23 | 2020-11-03 | 上海交通大学 | Parameter acquisition method for casting solidification simulation and gridding design method of casting system |
| CN112642997A (en) * | 2020-12-16 | 2021-04-13 | 南通海泰科特精密材料有限公司 | Method for confirming boundary heat exchange system in casting |
| CN113414347A (en) * | 2021-07-01 | 2021-09-21 | 上海万泽精密铸造有限公司 | Method for controlling dimensional accuracy of hollow blade wax mold |
| CN115047160A (en) * | 2022-04-28 | 2022-09-13 | 上海交通大学 | Device and method for evaluating casting performance of single crystal high-temperature alloy |
| CN116638061A (en) * | 2023-06-14 | 2023-08-25 | 广州市型腔模具制造有限公司 | Die casting size deformation control method for new energy automobile |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0787547A1 (en) * | 1996-01-31 | 1997-08-06 | ROLLS-ROYCE plc | A method of investment casting and a method of making an investment casting mould |
| CN1916917A (en) * | 2006-09-04 | 2007-02-21 | 大连理工大学 | Method for designing determinatus model cavity based on heating power coupling |
| CN101075269A (en) * | 2007-06-22 | 2007-11-21 | 广东工业大学 | Method for designing mould cavity |
-
2011
- 2011-03-24 CN CN 201110072878 patent/CN102169518A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0787547A1 (en) * | 1996-01-31 | 1997-08-06 | ROLLS-ROYCE plc | A method of investment casting and a method of making an investment casting mould |
| CN1916917A (en) * | 2006-09-04 | 2007-02-21 | 大连理工大学 | Method for designing determinatus model cavity based on heating power coupling |
| CN101075269A (en) * | 2007-06-22 | 2007-11-21 | 广东工业大学 | Method for designing mould cavity |
Non-Patent Citations (2)
| Title |
|---|
| 《Transactions of Nonferrous Metals Society of China》 20110228 Yiwei Dong etc Determination of wax pattern die profile for investment casting of turbine blades 第21卷, 第2期 * |
| 《中国制造业信息化》 20060331 卜昆 等 基于位移场的涡轮叶片模具设计中的反变形技术研究 , * |
Cited By (34)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103826776A (en) * | 2011-09-27 | 2014-05-28 | 株式会社神户制钢所 | Mold designing method, and mold |
| US20150231692A1 (en) * | 2011-09-27 | 2015-08-20 | Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.) | Mold designing method and mold |
| CN102507636A (en) * | 2011-09-30 | 2012-06-20 | 中国科学院金属研究所 | Method for measuring interfacial heat transfer coefficient of rapid cooling process of steel |
| CN102507636B (en) * | 2011-09-30 | 2013-11-06 | 中国科学院金属研究所 | Method for measuring interfacial heat transfer coefficient of rapid cooling process of steel |
| CN102426622B (en) * | 2011-11-15 | 2013-05-22 | 清华大学 | Adaptive variable-speed drawing simulation method for production of single-crystal blade |
| CN102426622A (en) * | 2011-11-15 | 2012-04-25 | 清华大学 | Adaptive variable-speed drawing simulation method for production of single-crystal blade |
| CN102819651A (en) * | 2012-08-20 | 2012-12-12 | 西北工业大学 | Simulation-based parameter optimizing method for precise casting process of single crystal turbine blade |
| US10717128B2 (en) | 2013-01-17 | 2020-07-21 | Safran Aircraft Engines | Method for manufacturing a component using the lost-wax casting method with directed cooling |
| JP2016503729A (en) * | 2013-01-17 | 2016-02-08 | スネクマ | Part manufacturing method using lost wax casting method with directional cooling |
| CN104325083B (en) * | 2014-11-24 | 2016-06-29 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of block cast covering plate structure orientation turbo blade pouring technology method |
| CN104325083A (en) * | 2014-11-24 | 2015-02-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Pouring technique of directional turbine blade with block cast cover board structure |
| CN105300695A (en) * | 2015-09-22 | 2016-02-03 | 中国航空工业集团公司沈阳发动机设计研究所 | Turbine rotating disc cavity flow heat exchange formula correction coefficient determination method |
| CN105300695B (en) * | 2015-09-22 | 2018-04-13 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of turbine inside rotating disc cavities fluid interchange formula correction factor determines method |
| CN105305089A (en) * | 2015-11-19 | 2016-02-03 | 西安空间无线电技术研究所 | Design device and design method of adjustable composite-material mold |
| CN105305089B (en) * | 2015-11-19 | 2018-04-10 | 西安空间无线电技术研究所 | A kind of adjustable composite material mould design device and design method |
| CN106777561A (en) * | 2016-11-29 | 2017-05-31 | 朱金焰 | A kind of layout method of turbo blade essence casting wax pattern Tao Xin clamping elements |
| CN107037779A (en) * | 2017-05-09 | 2017-08-11 | 西北工业大学 | Free form surface NC process tool track optimizing methods under non-homogeneous tolerance |
| CN107037779B (en) * | 2017-05-09 | 2019-03-05 | 西北工业大学 | Free form surface NC process tool track optimizing method under non-homogeneous tolerance |
| CN107506519A (en) * | 2017-07-07 | 2017-12-22 | 厦门大学 | A kind of parametrization processing method of essence casting turbine blade air film Cooling Holes |
| CN107506519B (en) * | 2017-07-07 | 2020-07-03 | 厦门大学 | Parametric machining method for gas film cooling hole of precision-cast turbine blade |
| CN107577874A (en) * | 2017-09-06 | 2018-01-12 | 厦门大学 | A kind of determination method of hollow turbine vane investment casting mould design shrinkage factor |
| CN107577874B (en) * | 2017-09-06 | 2019-07-19 | 厦门大学 | A kind of determination method of hollow turbine vane investment casting mould design shrinking percentage |
| CN107755636A (en) * | 2017-09-12 | 2018-03-06 | 东方电气集团东方汽轮机有限公司 | A kind of quick method for solving the casting deformation of combustion engine blade |
| CN109338456A (en) * | 2018-12-03 | 2019-02-15 | 上海交通大学 | Single crystal articles production of intelligent control technology based on numerical simulation and neural network judgement |
| CN110760715A (en) * | 2019-11-29 | 2020-02-07 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for accurately detecting size of inner cavity of shell of high-temperature alloy precision casting |
| CN111872324A (en) * | 2020-06-23 | 2020-11-03 | 上海交通大学 | Parameter acquisition method for casting solidification simulation and gridding design method of casting system |
| WO2021259386A1 (en) * | 2020-06-23 | 2021-12-30 | 上海交通大学 | Parameter acquisition method for cast-piece solidification simulation and cast-in-place system gridding design method |
| US11638953B2 (en) | 2020-06-23 | 2023-05-02 | Shanghai Jiao Tong University | Method for collecting parameters for casting solidification simulation and gridded design method for pouring and riser system |
| CN112642997A (en) * | 2020-12-16 | 2021-04-13 | 南通海泰科特精密材料有限公司 | Method for confirming boundary heat exchange system in casting |
| CN113414347A (en) * | 2021-07-01 | 2021-09-21 | 上海万泽精密铸造有限公司 | Method for controlling dimensional accuracy of hollow blade wax mold |
| CN115047160A (en) * | 2022-04-28 | 2022-09-13 | 上海交通大学 | Device and method for evaluating casting performance of single crystal high-temperature alloy |
| CN115047160B (en) * | 2022-04-28 | 2023-11-03 | 上海交通大学 | Device and method for evaluating casting performance of monocrystal superalloy |
| CN116638061A (en) * | 2023-06-14 | 2023-08-25 | 广州市型腔模具制造有限公司 | Die casting size deformation control method for new energy automobile |
| CN116638061B (en) * | 2023-06-14 | 2023-11-21 | 广州市型腔模具制造有限公司 | Die casting size deformation control method for new energy automobile |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102169518A (en) | Accurate forming method for precise-casting turbine blade die cavity | |
| Dong et al. | Modeling of shrinkage during investment casting of thin-walled hollow turbine blades | |
| CN101767185B (en) | Quantitative reverse deformation arrangement based method for designing cast model | |
| CN102231170B (en) | Parameterized sizing method for turbine blade mould cavity | |
| CN103310068B (en) | A kind of quick sand casting mold molding methods based on SLA prototype | |
| CN108304657A (en) | The continuous modeling and simulating method of lathe important Parts residual stress multi-process based on finite element | |
| Yarlagadda et al. | Statistical analysis on accuracy of wax patterns used in investment casting process | |
| CN107577874B (en) | A kind of determination method of hollow turbine vane investment casting mould design shrinking percentage | |
| CN102567582B (en) | Finite-element analysis-based method for designing profile of autoclave molding fixture of composite material member | |
| CN105335568B (en) | A kind of superplastic forming die design method considering thermal expansion based on finite element technique | |
| Liu et al. | Influence of complex structure on the shrinkage of part in investment casting process | |
| CN112207233A (en) | Mold manufacturing process based on 3D printing technology | |
| Dong et al. | Determination of wax pattern die profile for investment casting of turbine blades | |
| Dong et al. | Deformation characterization method of typical double-walled turbine blade structure during casting process | |
| CN110788279A (en) | Preparation method of ceramic mould shell of single crystal high-temperature alloy turbine blade | |
| CN109815527A (en) | A kind of die face optimization method of hot stamping die | |
| CN110076974A (en) | The design method of injection mold conformal cooling channel based on increases material manufacturing technology | |
| CN109702931B (en) | Method for designing mold surface of computer-aided large-scale component precise hot forming mold | |
| CN109676001B (en) | method for preparing aluminum alloy component product by forming | |
| Ren et al. | Control of dimensional accuracy of hollow turbine blades during investment casting | |
| CN109702930B (en) | Solid mold design method for accurate thermal forming of component | |
| CN109732815B (en) | Method for forming and preparing fiber resin composite material component product | |
| CN108296402A (en) | A kind of manufacturing process of welding covering entirety isothermal thermal forming mold | |
| CN106407547A (en) | Numerical simulation method for aiming at casting residual stress of anisotropic material | |
| Pancholi et al. | Design and Analysis of Die Casting Die with Conformal Cooling Channel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20110831 |