CN107838372A - One kind is without surplus essence casting turborotor dimension control method - Google Patents
One kind is without surplus essence casting turborotor dimension control method Download PDFInfo
- Publication number
- CN107838372A CN107838372A CN201711010716.XA CN201711010716A CN107838372A CN 107838372 A CN107838372 A CN 107838372A CN 201711010716 A CN201711010716 A CN 201711010716A CN 107838372 A CN107838372 A CN 107838372A
- Authority
- CN
- China
- Prior art keywords
- guide vane
- blade profile
- size
- turborotor
- dimension
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000005266 casting Methods 0.000 title claims abstract description 17
- 230000008602 contraction Effects 0.000 claims description 5
- 230000003321 amplification Effects 0.000 claims 1
- 238000003199 nucleic acid amplification method Methods 0.000 claims 1
- 238000005495 investment casting Methods 0.000 abstract description 5
- 238000004513 sizing Methods 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000005498 polishing Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
- B22C7/02—Lost patterns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D5/00—Control of dimensions of material
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to precision casting technology, is related to one kind without surplus essence casting turborotor dimension control method.Characterized in that, the step of guide vane dimension control, is as follows：To the precision controlling of guide vane blade profile size；To the precision controlling of guide vane exhaust side size.The present invention proposes one kind without surplus essence casting turborotor dimension control method, in view of influence of the subsequent treatment to blade dimensions, the dimensional accuracy of guide vane is met design requirement, shorten the sizing cycle of guide vane mould, ensure that the uniformity of guide vane quality.
Description
Technical field
The invention belongs to precision casting technology, is related to one kind without surplus essence casting turborotor dimension control side
Method.
Background technology
The part that aero-turbine guide vane is made up of a large amount of free form surfaces and listrium, its aerodynamic configuration, chi
Very little precision, listrium profile tolerance, forming accuracy require very high.At present, aero-turbine guide vane is by precision casting mould, material
The influence of many factors such as material, precision casting technology, guide vane formed precision is relatively low, quality is unstable, weight is overproof, percent defective compared with
Height, turn into the technology barrier for restricting the new aero-engine development in China.Turborotor dimensional accuracy relies primarily on essence casting
Wax mold guarantee, a kind of application for a patent for invention " shrinkage factor design method of leafy group of stator precision casting mould " (application number
201410604620.6) a kind of control method of turborotor dimensional accuracy is disclosed, this method only accounts for directing vane
Theoretical amount of contraction of the piece on three dimension directions, does not account for influence of the subsequent treatment to guide vane size, and use is this
The guide vane dimensional accuracy that the Wax mold of method design is produced can not meet design requirement, and guide vane delivers processing
Afterwards, if it find that guide vane dimension overproof, can only repairing die or polishing casting so that the sizing week of guide vane mould
Phase greatly prolongs, and increases worker's amount of labour, it is impossible to ensure the uniformity of guide vane quality, even result in mould and scrap.
The content of the invention
The purpose of the present invention is：One kind is proposed without surplus essence casting turborotor dimension control method, to examine
Consider influence of the subsequent treatment to blade dimensions, the dimensional accuracy of guide vane is met design requirement, shorten guide vane mould
In the sizing cycle of tool, ensure the uniformity of guide vane quality.
The technical scheme is that：One kind is designing without surplus essence casting turborotor dimension control method
During the cavity dimension of Wax mold, different contraction rate scores is employed on three dimension directions of three-dimensional cartesian coordinate system；
Characterized in that, the step of guide vane dimension control, is as follows：
1st, to the precision controlling of guide vane blade profile size：The die cavity of Wax mold is being amplified into the base of nonlinear shrinkage rate
On plinth, blade profile type face is outwards expanded along normal direction to the λ of the λ of δ mm, δ=0.4~0.6, λ is the upper tolerance of blade profile size；
2nd, the precision controlling of side size is vented to guide vane：Side is vented for guide vane of the thickness less than 1mm, along certainly
Extend τ mm, τ=0.15mm~0.45mm from curved surface blade profile to discharge directions, exhaust side is thinner, and τ value is bigger.
It is an advantage of the invention that：Propose a kind of without surplus essence casting turborotor dimension control method, consideration
Influence to subsequent treatment to blade dimensions, the dimensional accuracy of guide vane is met design requirement, shorten guide vane
In the sizing cycle of mould, it ensure that the uniformity of guide vane quality.
Brief description of the drawings
Fig. 1 is schematic diagram of the present invention to guide vane blade profile dimension control.
Fig. 2 is the schematic diagram that the present invention is vented side dimension control to guide vane.
Embodiment
The present invention is described in further details below.Referring to Fig. 1,2, one kind is without surplus essence casting turborotor size
Accuracy control method, when designing the cavity dimension of Wax mold, used on three dimension directions of three-dimensional cartesian coordinate system
Different contraction rate score；Characterized in that, the step of guide vane dimension control, is as follows：
1st, to the precision controlling of guide vane blade profile size：The die cavity of Wax mold is being amplified into the base of nonlinear shrinkage rate
On plinth, blade profile type face is outwards expanded along normal direction to the λ of the λ of δ mm, δ=0.4~0.6, λ is the upper tolerance of blade profile size；By blade profile
After type face outwards expands δ mm along normal direction, the casting blade profile actual size produced with the Wax mold is compared with theoretical size
Big δ mm, post-treated process such as blast, polishing burr etc. go surplus to operate on a small quantity, can make casting final size fitting design reason
By size.
2nd, the precision controlling of side size is vented to guide vane：Side is vented for guide vane of the thickness less than 1mm, along certainly
Extend τ mm, τ=0.15mm~0.45mm from curved surface blade profile to discharge directions, exhaust side is thinner, and τ value is bigger.
It is less than 1mm guide vane for blade exhaust side thickness, it is vented side and is very easy to owe casting, after casting is owed on exhaust side
Each section chord width size of blade can not ensure, therefore, when designing the cavity dimension of Wax mold, first in three-dimensional cartesian coordinate system
Three dimension directions on use different contraction rate scores, then vane foil is outwards expanded to δ mm, last edge along normal direction
Free form surface blade profile extends τ mm to discharge directions, owes blade exhaust side to casting part and guides to prolongation τ mm, to ensure blade
Each section chord width size.
Embodiment 1：
Certain machine high-pressure turbine guide vane, blade profile tolerance+0.12mm, it is vented side thickness 0.8mm, its size Control precision
Method is as follows：
1st, to the precision controlling of certain high-pressure turbine guide vane blade profile size：The die cavity of Wax mold is put in X and Y-direction
It is big by 1.8%, amplify 2.2% in z-direction, blade profile type face is outwards expanded into 0.048mm along normal direction.
2nd, the precision controlling of side size is vented to certain high-pressure turbine guide vane：Prolong along free form surface blade profile to discharge directions
Long 0.15mm.
Certain the machine high-pressure turbine guide vane produced using above method, blade profile size meet design drawing requirement, leaf
Each section chord width of piece meets design drawing requirement.
Embodiment 2：
Certain machine low-pressure turbine guide vane, blade profile tolerance+0.14mm, it is vented side thickness 0.6mm, its size Control precision
Method is as follows：
1st, to the precision controlling of certain high-pressure turbine guide vane blade profile size：The die cavity of Wax mold is put in X and Y-direction
It is big by 2.0%, amplify 2.3% in z-direction, blade profile type face is outwards expanded into 0.07mm along normal direction.
2nd, the precision controlling of side size is vented to certain high-pressure turbine guide vane：Prolong along free form surface blade profile to discharge directions
Long 0.30mm.
Certain the machine low-pressure turbine guide vane produced using above method, blade profile size meet design drawing requirement, leaf
Each section chord width of piece meets design drawing requirement.
Embodiment 3：
Certain machine low-pressure turbine guide vane, blade profile tolerance+0.12mm, it is vented side thickness 0.4mm, its size Control precision
Method is as follows：
1st, to the precision controlling of certain high-pressure turbine guide vane blade profile size：The die cavity of Wax mold is put in X and Y-direction
It is big by 2.0%, amplify 2.4% in z-direction, blade profile type face is outwards expanded into 0.072mm along normal direction.
2nd, the precision controlling of side size is vented to certain high-pressure turbine guide vane：Prolong along free form surface blade profile to discharge directions
Long 0.45mm.
Certain the machine low-pressure turbine guide vane produced using above method, blade profile size meet design drawing requirement, leaf
Each section chord width of piece meets design drawing requirement.
Claims (1)
1. it is a kind of without surplus essence casting turborotor dimension control method, when designing the cavity dimension of Wax mold,
Different contraction rate scores is employed on three dimension directions of three-dimensional cartesian coordinate system；Characterized in that, guide vane chi
The step of very little precision controlling, is as follows：
1.1st, to the precision controlling of guide vane blade profile size：By the die cavity of Wax mold on the basis of amplification nonlinear shrinkage rate
On, blade profile type face is outwards expanded along normal direction to the λ of the λ of δ mm, δ=0.4~0.6, λ is the upper tolerance of blade profile size；
1.2nd, the precision controlling of side size is vented to guide vane：Side is vented for guide vane of the thickness less than 1mm, along freedom
Curved surface blade profile extends τ mm, τ=0.15mm~0.45mm to discharge directions, and exhaust side is thinner, and τ value is bigger.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711010716.XA CN107838372B8 (en) | 2017-10-25 | 2017-10-25 | Method for controlling dimensional precision of guide blade of allowance-free precision casting turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711010716.XA CN107838372B8 (en) | 2017-10-25 | 2017-10-25 | Method for controlling dimensional precision of guide blade of allowance-free precision casting turbine |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| CN107838372A true CN107838372A (en) | 2018-03-27 |
| CN107838372B CN107838372B (en) | 2019-05-21 |
| CN107838372B8 CN107838372B8 (en) | 2022-02-11 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711010716.XA Active CN107838372B8 (en) | 2017-10-25 | 2017-10-25 | Method for controlling dimensional precision of guide blade of allowance-free precision casting turbine |
Country Status (1)
| Country | Link |
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| CN (1) | CN107838372B8 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110523929A (en) * | 2019-08-30 | 2019-12-03 | 中国航发动力股份有限公司 | A kind of vane foil dimensional control methods |
| CN111390113A (en) * | 2020-04-17 | 2020-07-10 | 中国航发北京航空材料研究院 | Method for accurately controlling outline dimension of hollow single crystal turbine working blade |
| CN111570726A (en) * | 2020-06-30 | 2020-08-25 | 中国航发动力股份有限公司 | Guide blade mold and shrinkage design method thereof |
| CN113859764A (en) * | 2021-09-29 | 2021-12-31 | 中国航发动力股份有限公司 | Protection device for guide blade cavity of turbine guide assembly and preparation method |
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| US20060052499A1 (en) * | 2003-02-25 | 2006-03-09 | Dow Global Technologies Inc. | Fugitive pattern for casting |
| CN102125998A (en) * | 2010-12-31 | 2011-07-20 | 大同北方天力增压技术有限公司 | Method for manufacturing impeller mould for gas compressor of turbocharger |
| CN104504195A (en) * | 2014-12-18 | 2015-04-08 | 上海交通大学 | Method for determining shrinking percentages of investment pattern precision casting mold |
| CN106734867A (en) * | 2016-11-28 | 2017-05-31 | 江苏雨燕模业科技有限公司 | A kind of preparation method of turbo-charger impeller mould |
| CN107199311A (en) * | 2017-06-08 | 2017-09-26 | 西安工业大学 | A kind of combination is towards turbo blade rapid shaping and the molten mistake fusible pattern method of model casting |
-
2017
- 2017-10-25 CN CN201711010716.XA patent/CN107838372B8/en active Active
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| US20060052499A1 (en) * | 2003-02-25 | 2006-03-09 | Dow Global Technologies Inc. | Fugitive pattern for casting |
| CN102125998A (en) * | 2010-12-31 | 2011-07-20 | 大同北方天力增压技术有限公司 | Method for manufacturing impeller mould for gas compressor of turbocharger |
| CN104504195A (en) * | 2014-12-18 | 2015-04-08 | 上海交通大学 | Method for determining shrinking percentages of investment pattern precision casting mold |
| CN106734867A (en) * | 2016-11-28 | 2017-05-31 | 江苏雨燕模业科技有限公司 | A kind of preparation method of turbo-charger impeller mould |
| CN107199311A (en) * | 2017-06-08 | 2017-09-26 | 西安工业大学 | A kind of combination is towards turbo blade rapid shaping and the molten mistake fusible pattern method of model casting |
Non-Patent Citations (1)
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| 白喜波: "《江苏省暨南京市航空航天学会第四次代表大会综合学术交流会 论文集》", 30 November 1989, 江苏省暨南京市航空航天学会 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110523929A (en) * | 2019-08-30 | 2019-12-03 | 中国航发动力股份有限公司 | A kind of vane foil dimensional control methods |
| CN111390113A (en) * | 2020-04-17 | 2020-07-10 | 中国航发北京航空材料研究院 | Method for accurately controlling outline dimension of hollow single crystal turbine working blade |
| CN111570726A (en) * | 2020-06-30 | 2020-08-25 | 中国航发动力股份有限公司 | Guide blade mold and shrinkage design method thereof |
| CN113859764A (en) * | 2021-09-29 | 2021-12-31 | 中国航发动力股份有限公司 | Protection device for guide blade cavity of turbine guide assembly and preparation method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107838372B (en) | 2019-05-21 |
| CN107838372B8 (en) | 2022-02-11 |
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| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CI03 | Correction of invention patent |
Correction item: Patentee|Address Correct: China Hangfa Power Co., Ltd.|710021 sub box 93, P.O. Box 13, Xi'an City, Shaanxi Province False: China Hangfa Aviation Power Co., Ltd.|710021 sub box 93, P.O. Box 13, xujiawan and Xi'an, Weiyang District, Xi'an City, Shaanxi Province Number: 21-01 Page: The title page Volume: 35 Correction item: Patentee|Address Correct: China Hangfa Power Co., Ltd.|710021 sub box 93, P.O. Box 13, Xi'an City, Shaanxi Province False: China Hangfa Aviation Power Co., Ltd.|710021 sub box 93, P.O. Box 13, xujiawan and Xi'an, Weiyang District, Xi'an City, Shaanxi Province Number: 21-01 Volume: 35 |
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| CI03 | Correction of invention patent |