CN104368756B - By the method for contoured chill model casting aero-engine complex structure thick and large casting - Google Patents
By the method for contoured chill model casting aero-engine complex structure thick and large casting Download PDFInfo
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- CN104368756B CN104368756B CN201410623969.4A CN201410623969A CN104368756B CN 104368756 B CN104368756 B CN 104368756B CN 201410623969 A CN201410623969 A CN 201410623969A CN 104368756 B CN104368756 B CN 104368756B
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- 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
- B22C9/043—Removing the consumable pattern
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- Mechanical Engineering (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
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Abstract
A method for contoured chill model casting aero-engine complex structure thick and large casting, its step comprises: make contoured chill with full form casting process; Casting die is utilized to make wax-pattern; Wax-pattern is utilized to make shell, paint slurry is made up of the Ludox of dioxide-containing silica 25%-30% and schmigel, proportioning adds 3-4Kg schmigel by every Kg Ludox, the stucco of 80#-100# emergy is used after being coated with slurry, coating to three is to after five layers, shell needs to the position iron wire of foundry goods cooling, contoured chill is fixed on shell, then continue coating and obtain shell; Obtained shell is utilized to pour into a mould, shell preheat temperature 900 DEG C-1000 DEG C during cast, cast temperature 1560 DEG C-1610 DEG C; Carry out after cast shelling, cut and clear up obtained foundry goods.The short texture problem at the complicated dark position, chamber of foundry goods can be solved by the method.
Description
Technical field
The present invention relates to precision-investment casting, particularly a kind of method utilizing contoured chill model casting aero-engine complex structure thick and large casting.
Background technology
The baroque thick and large casting of aero-engine is prepared with full form casting process, short texture problem is easily there is at position, the complexity of foundry goods dark chamber, due to complex structure, cannot be addressed this problem by pouring and riser systems preferably, traditional solution is corresponding site chill being directly installed to wax-pattern, utilize chill to absorb the heat of molten steel, make the region of placement chill not produce loose phenomenon.There are two defects in the method: one is in casting process, and chill can react with casting material, causes certain pollution to foundry goods itself; Two is that so chill can only be installed to foundry goods the surface of allowance (removing when following process), can not place chill at the non-machined surface place of foundry goods, the scope of application of chill is restricted because chill can be molten on foundry goods body.
Summary of the invention
The object of the invention is to provide a kind of method utilizing contoured chill model casting aero-engine complex structure thick and large casting for the defect of above-mentioned prior art, to solve the short texture problem that the complicated dark position, chamber of foundry goods easily occurs.
For achieving the above object, the method for contoured chill model casting aero-engine complex structure thick and large casting that utilizes provided by the invention comprises the following steps:
Step one: make contoured chill with full form casting process
According to foundry goods cavity body structure, UG software offset 3mm ~ 8mm is used to design contoured chill structure; Then manufacture and design shaping chill Wax mold according to contoured chill, adopt full form casting process to produce contoured chill stand-by;
Step 2: utilize casting die to make wax-pattern;
Step 3: utilize wax-pattern to make shell
Carry out coating after completing wax-pattern combination, institute is coated with slurry and is made up of the Ludox of dioxide-containing silica 25% ~ 30% and schmigel, and proportioning adds 3 ~ 4Kg schmigel by every Kg Ludox, use 80# ~ 100# emergy stucco after painting slurry; After coating three to five layers, shell needs to the position of foundry goods cooling, the contoured chill that step one is obtained is fixed on shell, then continue coating, continue coating 46# ~ 60# emergy, obtained shell;
Step 4: utilize the obtained shell of step 3 to pour into a mould, shell preheat temperature 900 DEG C ~ 1000 DEG C in casting process, cast temperature 1560 DEG C ~ 1610 DEG C;
Step 5: carry out after cast shelling, cut and clearing up, obtained foundry goods.
Contoured chill is placed in shell by the present invention, and when molten steel injects after in shell, chill can absorb the heat of molten steel fast, thus makes the region of the corresponding chill of foundry goods not produce loose.
Compared with prior art, advantage of the present invention is:
1, because contoured chill is placed in shell, do not contact with cast(ing) surface, avoid chill to the pollution of cast(ing) surface with break.
2, contoured chill can be arranged on any position of foundry goods, and can only not be installed to foundry goods when wax-pattern combines by traditional chill has restriction on allowance face.
Accompanying drawing explanation
Fig. 1 is the 3 dimensional drawing of certain type Aero-engine Bearing seat;
Fig. 2 is with the contoured chill scheme of installation (broken section) during the inventive method model casting Fig. 1 bearing block.
In figure: 1-bear-sleeve casting, 2-(after three to five layers) shell, 3-contoured chill, 4-iron wire.
Detailed description of the invention
Below in conjunction with drawings and Examples, the invention will be further described.
The present embodiment adopts the inventive method to carry out model casting to certain type Aero-engine Bearing seat shown in Fig. 1.This bear-sleeve casting material is ZG0Cr17Ni4Cu3Nb, and maximum diameter is about 500mm, the groove that mount pad place has a circle dark, and depth of groove is about 50mm, and in casting process, this groove easily produces the defects such as loose.
Composition graphs 1 and Fig. 2, this bear-sleeve casting 1 of model casting comprises the following steps:
Step one: make contoured chill 3
Mount pad groove based on casting process bottom bracket foundry goods 1 easily produces rarefaction defect, needs to use chill at this place during model casting.According to the shape of groove, UG software offset 5mm is used to design the structure of contoured chill 3; Then manufacture and design shaping chill Wax mold according to contoured chill, adopt conventional full form casting process to produce contoured chill 3 stand-by, the material of contoured chill 3 adopts ZG0Cr17Ni4Cu3Nb;
Step 2: utilize casting die to make wax-pattern;
Step 3: utilize wax-pattern to make shell
Foundry goods carries out coating after completing wax-pattern combination, and paint slurry is made up of Ludox and schmigel, and in Ludox, dioxide-containing silica is 28%, and proportioning adds 3.5Kg schmigel by per kilogram Ludox, uses the stucco of 100# emergy after being coated with slurry; After being applied to three layers, position above the groove that the contoured chill 3 that step one is obtained to be fixed to the iron wire 4 of diameter 1mm bear-sleeve casting 1 by the shell 2 formed, then continues coating with 60# emergy, is coated with Floor 12 altogether, obtain shell;
Step 4: utilize the obtained shell of step 3 to pour into a mould, shell preheat temperature 980 DEG C in casting process, cast temperature 1600 DEG C;
Step 5: after cast, technique is carried out shelling, cuts, cleared up routinely, obtained bear-sleeve casting.
Detect obtained bear-sleeve casting with detection method of X-ray and fluorescence detection method, groove is without loose metallurgical imperfection.
Above embodiment is for explaining the present invention, and protection scope of the present invention is not limited to this embodiment, and all the inventive method model casting aero-engine complex structure thick and large castings are all in protection scope of the present invention.
Claims (1)
1., by a method for contoured chill model casting aero-engine complex structure thick and large casting, it is characterized in that comprising the following steps:
Step one: make contoured chill (3) with full form casting process
According to foundry goods cavity body structure, UG software offset 3mm ~ 8mm is used to design contoured chill structure; Then manufacture and design shaping chill Wax mold according to contoured chill, adopt full form casting process to produce contoured chill (3) stand-by;
Step 2: utilize casting die to make wax-pattern;
Step 3: utilize wax-pattern to make shell
Carry out coating after completing wax-pattern combination, institute is coated with slurry and is made up of the Ludox of dioxide-containing silica 25%-30% and schmigel, and proportioning adds 3-4Kg schmigel by every Kg Ludox, use 80#-100# emergy stucco after painting slurry; After coating three to five layers, shell needs to the position of foundry goods cooling, the contoured chill that step one is obtained is fixed on shell, then continue coating, continue coating 46#-60# emergy, obtained shell;
Step 4: utilize the obtained shell of step 3 to pour into a mould, shell preheat temperature 900 DEG C-1000 DEG C in casting process, cast temperature 1560 DEG C-1610 DEG C;
Step 5: carry out after cast shelling, cut and clearing up, obtained foundry goods.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410623969.4A CN104368756B (en) | 2014-11-07 | 2014-11-07 | By the method for contoured chill model casting aero-engine complex structure thick and large casting |
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| CN201410623969.4A CN104368756B (en) | 2014-11-07 | 2014-11-07 | By the method for contoured chill model casting aero-engine complex structure thick and large casting |
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| Publication Number | Publication Date |
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| CN104368756A CN104368756A (en) | 2015-02-25 |
| CN104368756B true CN104368756B (en) | 2016-04-20 |
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| CN201410623969.4A Active CN104368756B (en) | 2014-11-07 | 2014-11-07 | By the method for contoured chill model casting aero-engine complex structure thick and large casting |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105364002B (en) * | 2015-10-22 | 2017-08-25 | 贵州安吉航空精密铸造有限责任公司 | A kind of full form casting process for accelerating casting solidification to cool down |
| CN105397027A (en) * | 2015-12-02 | 2016-03-16 | 株洲中航动力精密铸造有限公司 | Casting method of casting |
| CN105945225B (en) * | 2016-07-11 | 2017-12-19 | 山东美陵化工设备股份有限公司 | Automobile brake base plate class casting descends chilling block device and Mechanical processing of casting method automatically |
| CN106623785A (en) * | 2016-12-19 | 2017-05-10 | 洛阳市金峰铸造有限公司 | Casting structure for silica sol investment casting |
| CN107150106B (en) * | 2017-06-29 | 2024-04-16 | 大连金河铸造有限公司 | Casting process for improving quality of sand sharp corner part and prefabricated sand core structure |
| CN108672657A (en) * | 2018-05-24 | 2018-10-19 | 哈尔滨鑫润工业有限公司 | Improve the process of the hot investment casting of extraordinary combustion engine rectification pillar high temperature resistance |
| CN113373502B (en) * | 2021-04-28 | 2022-11-18 | 潍坊科技学院 | Process method for controlling freckle defect in single crystal casting |
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| CN101758181A (en) * | 2009-08-31 | 2010-06-30 | 滨海县万恒铸业有限公司 | Novel process for adding chill modeling on wax mold |
| CN101767193A (en) * | 2009-12-25 | 2010-07-07 | 沈阳工业大学 | Process method for eliminating loose of thick and large casting of high-temperature alloy |
| CN102091757A (en) * | 2010-12-30 | 2011-06-15 | 沈阳黎明航空发动机(集团)有限责任公司 | Integral precision casting method for large thin-wall casing part |
| CN103192027A (en) * | 2013-03-28 | 2013-07-10 | 清华大学 | Partial cooling method of cold iron in investment casting |
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2014
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Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB2150875B (en) * | 1983-12-07 | 1986-07-02 | Rolls Royce | Investment casting |
| CN101138781A (en) * | 2007-09-24 | 2008-03-12 | 中国南车集团戚墅堰机车车辆工艺研究所 | Investment casting formwork and method of producing the same |
| CN101406932A (en) * | 2008-11-10 | 2009-04-15 | 泉州腾达精铸有限公司 | Precision-investment casting method |
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Effective date of registration: 20160905 Address after: 110043 Liaoning Province, Shenyang City District East Street No. six Patentee after: Shenyang AVIC Dynamic Precision Casting Technology Co., Ltd. Address before: 110043 Liaoning Province, Shenyang City District East Street No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
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Address after: 110000 No. 6 Dongta Street, Dadong District, Shenyang City, Liaoning Province Patentee after: Shenyang Hangfa Precision Casting Co., Ltd. Address before: 110043 Liaoning Province, Shenyang City District East Street No. six Patentee before: Shenyang AVIC Dynamic Precision Casting Technology Co., Ltd. |
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Effective date of registration: 20190827 Address after: 110043 Liaoning Province, Shenyang City District East Street No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110000 No. 6 Dongta Street, Dadong District, Shenyang City, Liaoning Province Patentee before: Shenyang Hangfa Precision Casting Co., Ltd. |