CN107755635A - A kind of method for solving combustion engine shrouded blade leaf top R angles fire check - Google Patents
A kind of method for solving combustion engine shrouded blade leaf top R angles fire check Download PDFInfo
- Publication number
- CN107755635A CN107755635A CN201710817839.8A CN201710817839A CN107755635A CN 107755635 A CN107755635 A CN 107755635A CN 201710817839 A CN201710817839 A CN 201710817839A CN 107755635 A CN107755635 A CN 107755635A
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- CN
- China
- Prior art keywords
- combustion engine
- formwork
- angles
- blade
- leaf top
- 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
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 32
- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000009415 formwork Methods 0.000 claims abstract description 30
- 229920000742 Cotton Polymers 0.000 claims abstract description 29
- 239000000919 ceramic Substances 0.000 claims abstract description 27
- 238000009413 insulation Methods 0.000 claims abstract description 24
- 230000007423 decrease Effects 0.000 claims abstract description 8
- 239000004576 sand Substances 0.000 claims abstract description 7
- 239000011248 coating agent Substances 0.000 claims abstract description 5
- 238000000576 coating method Methods 0.000 claims abstract description 5
- 238000001816 cooling Methods 0.000 claims abstract description 5
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 8
- 238000004321 preservation Methods 0.000 claims description 5
- 239000004927 clay Substances 0.000 claims description 4
- 229910052759 nickel Inorganic materials 0.000 claims description 4
- 239000003795 chemical substances by application Substances 0.000 claims 1
- 238000005266 casting Methods 0.000 abstract description 8
- 238000005495 investment casting Methods 0.000 abstract description 6
- 238000012797 qualification Methods 0.000 abstract description 3
- 238000007711 solidification Methods 0.000 description 7
- 230000008023 solidification Effects 0.000 description 7
- 239000011230 binding agent Substances 0.000 description 2
- 238000013467 fragmentation Methods 0.000 description 2
- 238000006062 fragmentation reaction Methods 0.000 description 2
- 229910052573 porcelain Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 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
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
- B22D27/04—Influencing the temperature of the metal, e.g. by heating or cooling the mould
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Solid Fuels And Fuel-Associated Substances (AREA)
Abstract
The invention discloses a kind of method for solving combustion engine shrouded blade leaf top R angles fire check, it is characterised in that follows the steps below successively：（1）Wax-pattern module corresponding with combustion engine shrouded blade is taken, coating is coated with the surface of the wax-pattern module, and is dewaxed, is calcined successively, after cooling treatment, obtains formwork；（2）In the ceramic thermal insulation cotton that on formwork, Jacket thickness successively decreases successively corresponding to dead head, combustion engine blade root, the thick big position of blade, leaf top R angles thin-walled position and integral shroud do not wrap up ceramic thermal insulation cotton；（3）The formwork wrapped is calcined；（4）Roasting formwork is taken out to be poured into a mould or be placed on shot sand after roasting formwork is taken out and poured into a mould.The present invention improves the qualification rate of combustion engine shrouded blade hot investment casting casting, easy to operation.
Description
Technical field
It is specifically a kind of to solve the top R angles hot tearing of shrouded blade leaf the present invention relates to combustion engine blade hot investment casting field
The method of line.
Background technology
Casting is in process of setting, and when alloy temperature is dropped to close to actual solidus, its intensity and plasticity are extremely low, and one
Denier shrinkage stress exceedes strength degree, easily produces fire check.Generally occur in casting thickness, thin-walled handing-over, thermal center or corner.
Combustion engine shrouded blade leaf top R angles are the transitional regions on air flue face and leaf top, and wall thickness differs greatly, and easily produces fire check.
The content of the invention
The invention aims to solve above-mentioned technical problem, there is provided one kind solves shrouded blade leaf top R angles fire check
Method, the method can accelerate leaf top R angles thin-walled position to solidify, improve resistance energy of the leaf top R angles thin-walled position to shrinkage stress
Power, reduce leaf top R angles thin-walled position and solidified slow and caused fire check, and it is easy to operation, casting qualified rate can be improved.
Realize the technical scheme is that：A kind of method for solving combustion engine shrouded blade leaf top R angles fire check, its feature
It is, follows the steps below successively：
（1）Wax-pattern module corresponding with combustion engine shrouded blade is taken, is coated with coating on the surface of the wax-pattern module, and carry out successively
After dewaxing, roasting, cooling treatment, formwork is obtained；
（2）In the ceramics that on formwork, Jacket thickness successively decreases successively corresponding to dead head, combustion engine blade root, the thick big position of blade
Heat-preservation cotton, leaf top R angles thin-walled position and integral shroud do not wrap up ceramic thermal insulation cotton；
（3）The formwork wrapped is calcined；
（4）Roasting formwork is taken out to be poured into a mould or be placed on shot sand after roasting formwork is taken out and poured into a mould.
The step（2）In, on formwork, wrapped up successively corresponding to dead head, combustion engine blade root, the thick big position of blade
The ceramic thermal insulation cotton of thickness-tapered, it is wound on outside ceramic thermal insulation cotton and is fixed with nickel filament, or in ceramic thermal insulation cotton interface
Position high-temperature agglomerant or high temperature clay bond；Leaf top R angles thin-walled position and integral shroud do not wrap up ceramic thermal insulation cotton.
The beneficial effects of the invention are as follows：
1st, the present invention further extends thick big position setting time using ceramic thermal insulation cotton, while using in leaf top R angles thinner wall section
Position does not wrap up ceramic thermal insulation cotton, further shortens setting time, accelerates the solidification of leaf top R angles thin-walled position, improves leaf top R angles thin-walled
Is reduced at position by leaf top R angles thin-walled position and solidified slow and caused fire check for the resistivity of shrinkage stress.
2nd, the present invention is used for combustion engine shrouded blade precision casting.First, it is thick big in dead head, combustion engine blade root, blade
Corresponding to position on formwork, Jacket thickness successively decreases successively ceramic thermal insulation cotton, a kind of top-down solidification side is on the one hand formed
Formula（Consecutive solidification）, the further setting time for extending thick big position of another aspect；Secondly, in leaf top R angles thin-walled position and leaf
Hat does not wrap up ceramic thermal insulation cotton, and roasting formwork is taken out to be placed on shot sand and poured into a mould, it is thin to further speed up leaf top R angles
The solidification of wall site, shorten setting time, increase leaf top R angles thin-walled position intensity, improving leaf top R angles thin-walled position should to shrinking
The resistivity of power, can effectively solve the fire check caused by shrinkage stress.
3rd, the present invention improves the qualification rate of combustion engine shrouded blade hot investment casting casting, easy to operation, is to solve combustion engine band
Shroud blade leaf top R angles produce a kind of effective ways of casting thermal fragmentation line because of shrinkage stress.
Brief description of the drawings
Fig. 1 be with 1 corresponding structural representation of the embodiment of the present invention,
Fig. 2 be and 2 corresponding structural representation of the embodiment of the present invention.
Label in figure：1-formwork, 2-ceramic thermal insulation cotton, 3-shot sand, 4-dead head, 5-combustion engine blade root,
The thick big position of 6-blade, 7-leaf top R angles thin-walled position, 8-integral shroud.
Embodiment
Implement example 1：
As shown in figure 1, a kind of method for solving combustion engine shrouded blade leaf top R angles fire check, is followed the steps below successively：
（1）Wax-pattern module corresponding with combustion engine shrouded blade is taken, is coated with coating on the surface of the wax-pattern module, and carry out successively
After dewaxing, roasting, cooling treatment, formwork 1 is obtained；
（2）At the thick big position 6 of dead head 4, combustion engine blade root 5, blade corresponding to formwork 1, the pottery that Jacket thickness successively decreases successively
Porcelain heat-preservation cotton 2, it is wound on outside ceramic thermal insulation cotton 2 and is fixed with nickel filament, or the position high temperature in the interface of ceramic thermal insulation cotton 2
Binding agent or high temperature clay bond；Leaf top R angles thin-walled position 7 and integral shroud 8 do not wrap up ceramic thermal insulation cotton；
（3）The formwork 1 wrapped is put into roaster and is calcined；
（4）Roasting formwork 1 is taken out and poured into a mould, you can.
Implement example 2：
As shown in Fig. 2 a kind of method for solving combustion engine shrouded blade leaf top R angles fire check, is followed the steps below successively：
（1）Wax-pattern module corresponding with combustion engine shrouded blade is taken, is coated with coating on the surface of the wax-pattern module, and carry out successively
After dewaxing, roasting, cooling treatment, formwork 1 is obtained；
（2）At the thick big position 6 of dead head 4, combustion engine blade root 5, blade corresponding to formwork 1, the pottery that Jacket thickness successively decreases successively
Porcelain heat-preservation cotton 2, it is wound on outside ceramic thermal insulation cotton 2 and is fixed with nickel filament, or the position high temperature in the interface of ceramic thermal insulation cotton 2
Binding agent or high temperature clay bond；Leaf top R angles thin-walled position 7 and integral shroud 8 do not wrap up ceramic thermal insulation cotton；
（3）The formwork 1 wrapped is put into roaster and is calcined；
（4）Roasting formwork 1 is taken out, is placed on shot sand 3 and is poured into a mould, you can.
The present invention is used for combustion engine shrouded blade precision casting.First, in dead head, combustion engine blade root, the thick big portion of blade
Corresponding to position on formwork, on the one hand Jacket thickness successively decreases successively ceramic thermal insulation cotton forms a kind of top-down solidification mode
（Consecutive solidification）, the further setting time for extending thick big position of another aspect；Secondly, in leaf top R angles thin-walled position and integral shroud
Ceramic thermal insulation cotton is not wrapped up, and roasting formwork is taken out to be placed on shot sand and poured into a mould, further speeds up leaf top R angles thin-walled
The solidification at position, shorten setting time, increase leaf top R angles thin-walled position intensity, improve leaf top R angles thin-walled position to shrinkage stress
Resistivity, can effectively solve the fire check caused by shrinkage stress.
The present invention improves the qualification rate of combustion engine shrouded blade hot investment casting casting, easy to operation, is to solve combustion engine band hat
Blade and blade top R angles produce a kind of effective ways of casting thermal fragmentation line because of shrinkage stress.
Claims (2)
- A kind of 1. method for solving combustion engine shrouded blade leaf top R angles fire check, it is characterised in that enter successively according to following steps OK：（1）Wax-pattern module corresponding with combustion engine shrouded blade is taken, is coated with coating on the surface of the wax-pattern module, and carry out successively After dewaxing, roasting, cooling treatment, formwork is obtained；（2）In the ceramics that on formwork, Jacket thickness successively decreases successively corresponding to dead head, combustion engine blade root, the thick big position of blade Heat-preservation cotton, leaf top R angles thin-walled position and integral shroud do not wrap up ceramic thermal insulation cotton；（3）The formwork wrapped is calcined；（4）Roasting formwork is taken out to be poured into a mould or be placed on shot sand after roasting formwork is taken out and poured into a mould.
- 2. solve the method for combustion engine shrouded blade leaf top R angles fire check according to claim 1, it is characterised in that：The step Suddenly（2）In, in the ceramics that on formwork, Jacket thickness successively decreases successively corresponding to dead head, combustion engine blade root, the thick big position of blade Heat-preservation cotton, it is wound on outside ceramic thermal insulation cotton and is fixed with nickel filament, or the position high temperature bond in ceramic thermal insulation cotton interface Agent or high temperature clay bond；Leaf top R angles thin-walled position and integral shroud do not wrap up ceramic thermal insulation cotton.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817839.8A CN107755635A (en) | 2017-09-12 | 2017-09-12 | A kind of method for solving combustion engine shrouded blade leaf top R angles fire check |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817839.8A CN107755635A (en) | 2017-09-12 | 2017-09-12 | A kind of method for solving combustion engine shrouded blade leaf top R angles fire check |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107755635A true CN107755635A (en) | 2018-03-06 |
Family
ID=61265437
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710817839.8A Pending CN107755635A (en) | 2017-09-12 | 2017-09-12 | A kind of method for solving combustion engine shrouded blade leaf top R angles fire check |
Country Status (1)
| Country | Link |
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| CN (1) | CN107755635A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108941459A (en) * | 2018-09-05 | 2018-12-07 | 中国航发动力股份有限公司 | A method of it is loose to reduce combustion engine turbine blade |
| CN109434025A (en) * | 2018-11-29 | 2019-03-08 | 沈阳航发精密铸造有限公司 | A kind of process for eliminating supramarginal plate crackle metallurgical imperfection |
| CN109622888A (en) * | 2018-12-20 | 2019-04-16 | 航天海鹰(哈尔滨)钛业有限公司 | A kind of cast shaping process of the multi-joint guide vane casting of complexity high temperature alloy |
| CN112453325A (en) * | 2020-11-03 | 2021-03-09 | 哈尔滨工业大学 | Casting forming method of wing rudder with high-temperature alloy dot matrix sandwich structure |
| CN115255274A (en) * | 2022-07-29 | 2022-11-01 | 贵州安吉航空精密铸造有限责任公司 | Investment casting method of stainless steel casting with bracket structure |
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| CN101954454A (en) * | 2010-10-14 | 2011-01-26 | 安徽应流集团霍山铸造有限公司 | Method for eliminating casting heating cracks |
| CN103212670A (en) * | 2012-01-24 | 2013-07-24 | 斯奈克玛 | Shell mold for manufacturing aircraft turbine blade element by lost wax casting |
| CN104308076A (en) * | 2014-10-29 | 2015-01-28 | 西安航空动力股份有限公司 | Wax mold combination of four-connection hollow turbine guide vane and precision casting method of wax mold combination |
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Patent Citations (7)
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| US7231955B1 (en) * | 2006-01-30 | 2007-06-19 | United Technologies Corporation | Investment casting mold design and method for investment casting using the same |
| CN101168184A (en) * | 2006-10-26 | 2008-04-30 | 沈阳黎明航空发动机(集团)有限责任公司 | Casting method for heavy combustion engine II-stage diverter blade |
| CN101954454A (en) * | 2010-10-14 | 2011-01-26 | 安徽应流集团霍山铸造有限公司 | Method for eliminating casting heating cracks |
| CN103212670A (en) * | 2012-01-24 | 2013-07-24 | 斯奈克玛 | Shell mold for manufacturing aircraft turbine blade element by lost wax casting |
| CN104308076A (en) * | 2014-10-29 | 2015-01-28 | 西安航空动力股份有限公司 | Wax mold combination of four-connection hollow turbine guide vane and precision casting method of wax mold combination |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108941459A (en) * | 2018-09-05 | 2018-12-07 | 中国航发动力股份有限公司 | A method of it is loose to reduce combustion engine turbine blade |
| CN109434025A (en) * | 2018-11-29 | 2019-03-08 | 沈阳航发精密铸造有限公司 | A kind of process for eliminating supramarginal plate crackle metallurgical imperfection |
| CN109622888A (en) * | 2018-12-20 | 2019-04-16 | 航天海鹰(哈尔滨)钛业有限公司 | A kind of cast shaping process of the multi-joint guide vane casting of complexity high temperature alloy |
| CN112453325A (en) * | 2020-11-03 | 2021-03-09 | 哈尔滨工业大学 | Casting forming method of wing rudder with high-temperature alloy dot matrix sandwich structure |
| CN115255274A (en) * | 2022-07-29 | 2022-11-01 | 贵州安吉航空精密铸造有限责任公司 | Investment casting method of stainless steel casting with bracket structure |
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Application publication date: 20180306 |