CN107838372B - A kind of no surplus essence casting turborotor dimension control method - Google Patents
A kind of no surplus essence casting turborotor dimension control method Download PDFInfo
- Publication number
- CN107838372B CN107838372B CN201711010716.XA CN201711010716A CN107838372B CN 107838372 B CN107838372 B CN 107838372B CN 201711010716 A CN201711010716 A CN 201711010716A CN 107838372 B CN107838372 B CN 107838372B
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- CN
- China
- Prior art keywords
- guide vane
- blade profile
- size
- turborotor
- dimension
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- 238000000034 method Methods 0.000 title claims abstract description 22
- 238000005266 casting Methods 0.000 title claims abstract description 17
- 230000008602 contraction Effects 0.000 claims description 4
- 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
- 238000005516 engineering process Methods 0.000 abstract description 4
- 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
- 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 technologies, are related to a kind of no surplus essence casting turborotor dimension control method.It is 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 invention proposes a kind of no surplus essence casting turborotor dimension control methods, influence in view of subsequent processing to blade dimensions, so that the dimensional accuracy of guide vane is met design requirement, shortens the sizing period of guide vane mold, ensure that the consistency of guide vane quality.
Description
Technical field
The invention belongs to precision casting technologies, are related to a kind of no surplus essence casting turborotor dimension control side
Method.
Background technique
The part that aero-turbine guide vane is made of a large amount of free form surfaces and listrium, aerodynamic configuration, ruler
Very little precision, listrium profile tolerance, forming accuracy require very high.Currently, 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, rejection rate compared with
Height becomes the technology barrier for restricting the novel 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 " shrinking percentage design method of leafy group of guide vane 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 shrinkage of the piece on three dimension directions, does not account for influence of the subsequent processing to guide vane size, and use is this
The guide vane dimensional accuracy that the Wax mold of method design is produced is not able to satisfy design requirement, and guide vane delivers processing
Afterwards, if it find that guide vane dimension overproof, can only repairing die or polishing casting, to make the sizing week of guide vane mold
Phase greatly prolongs, and increases worker's amount of labour, it cannot be guaranteed that the consistency of guide vane quality, even results in mold and scrap.
Summary of the invention
The purpose of the present invention is: a kind of no surplus essence casting turborotor dimension control method is proposed, to examine
Consider influence of the subsequent processing to blade dimensions, the dimensional accuracy of guide vane is made to meet design requirement, shortens guide vane mould
The sizing period of tool guarantees the consistency of guide vane quality.
The technical scheme is that a kind of no surplus essence casting turborotor dimension control method, is being designed
When the cavity dimension of Wax mold, different contraction rate scores is used on three dimension directions of three-dimensional cartesian coordinate system；
It is characterized in that, the step of guide vane dimension control, is as follows:
1, to the precision controlling of guide vane blade profile size: by the type chamber of Wax mold in the base for amplifying nonlinear shrinkage rate
On plinth, blade profile type face is expanded into δ mm along normal direction outward, the λ~0.6 of δ=0.4 λ, λ are the upper tolerances of blade profile size；
2, the precision controlling in size is vented to guide vane: when the guide vane for thickness less than 1mm is vented, along certainly
Extend τ mm, τ=0.15mm~0.45mm from curved surface blade profile to discharge directions, exhaust side is thinner, and the value of τ is bigger.
The invention has the advantages that proposing a kind of no surplus essence casting turborotor dimension control method, consider
Influence to subsequent processing to blade dimensions makes the dimensional accuracy of guide vane meet design requirement, shortens guide vane
In the sizing period of mold, it ensure that the consistency of guide vane quality.
Detailed description of the invention
Fig. 1 is schematic diagram of the present invention to guide vane blade profile dimension control.
Fig. 2 is schematic diagram of the present invention to guide vane exhaust side dimension control.
Specific embodiment
The present invention is described in further details below.Referring to Fig. 1,2, a kind of no surplus essence casting turborotor size
Accuracy control method uses on three dimension directions of three-dimensional cartesian coordinate system when designing the cavity dimension of Wax mold
Different contraction rate score；It is characterized in that, the step of guide vane dimension control, is as follows:
1, to the precision controlling of guide vane blade profile size: by the type chamber of Wax mold in the base for amplifying nonlinear shrinkage rate
On plinth, blade profile type face is expanded into δ mm along normal direction outward, the λ~0.6 of δ=0.4 λ, λ are the upper tolerances of blade profile size；By blade profile
After type face expands δ mm along normal direction outward, 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.
2, the precision controlling in size is vented to guide vane: when the guide vane for thickness less than 1mm is vented, along certainly
Extend τ mm, τ=0.15mm~0.45mm from curved surface blade profile to discharge directions, exhaust side is thinner, and the value of τ is bigger.
It is less than the guide vane of 1mm for blade exhaust side thickness, exhaust side is very easy to owe casting, after casting is owed on exhaust side
Each section chord width size of blade not can guarantee, 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 expanded into δ mm, last edge along normal direction outward
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 guarantee blade
Each section chord width size.
Embodiment 1:
Certain machine guide vane of high pressure turbine, blade profile tolerance+0.12mm are vented side thickness 0.8mm, size Control precision
Method is as follows:
1, to the precision controlling of certain guide vane of high pressure turbine blade profile size: the type chamber 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 expanded into 0.048mm along normal direction outward.
2, to the precision controlling of certain guide vane of high pressure turbine exhaust side size: prolonging along free form surface blade profile to discharge directions
Long 0.15mm.
Certain the machine guide vane of high pressure turbine 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 are vented side thickness 0.6mm, size Control precision
Method is as follows:
1, to the precision controlling of certain guide vane of high pressure turbine blade profile size: the type chamber 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 expanded into 0.07mm along normal direction outward.
2, to the precision controlling of certain guide vane of high pressure turbine exhaust side size: prolonging 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 are vented side thickness 0.4mm, size Control precision
Method is as follows:
1, to the precision controlling of certain guide vane of high pressure turbine blade profile size: the type chamber 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 expanded into 0.072mm along normal direction outward.
2, to the precision controlling of certain guide vane of high pressure turbine exhaust side size: prolonging 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. a kind of no surplus essence casting turborotor dimension control method, when designing the cavity dimension of Wax mold,
Different contraction rate scores is used on three dimension directions of three-dimensional cartesian coordinate system；It is characterized in that, guide vane ruler
The step of very little precision controlling, is as follows:
1.1, to the precision controlling of guide vane blade profile size: by the type chamber of Wax mold on the basis of amplification nonlinear shrinkage rate
On, blade profile type face is expanded into δ mm along normal direction outward, the λ~0.6 of δ=0.4 λ, λ are the upper tolerances of blade profile size；
1.2, the precision controlling in size is vented to guide vane: when the guide vane for thickness less than 1mm is vented, along freedom
Curved surface blade profile extends τ mm, τ=0.15mm~0.45mm to discharge directions, and exhaust side is thinner, and the value of τ 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 CN107838372A (en) | 2018-03-27 |
| CN107838372B true CN107838372B (en) | 2019-05-21 |
| CN107838372B8 CN107838372B8 (en) | 2022-02-11 |
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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 |
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| CN (1) | CN107838372B8 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110523929B (en) * | 2019-08-30 | 2020-12-29 | 中国航发动力股份有限公司 | Blade profile size control method |
| 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 |
| CN111570726B (en) * | 2020-06-30 | 2021-06-08 | 中国航发动力股份有限公司 | Guide blade mold and shrinkage design method thereof |
| CN113859764B (en) * | 2021-09-29 | 2023-04-07 | 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040167270A1 (en) * | 2003-02-25 | 2004-08-26 | Dane Chang | Fugitive pattern for casting |
-
2017
- 2017-10-25 CN CN201711010716.XA patent/CN107838372B8/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107838372A (en) | 2018-03-27 |
| CN107838372B8 (en) | 2022-02-11 |
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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 |