CN108971438A - A kind of localization method of single crystal turbine working-blade ceramic core - Google Patents
A kind of localization method of single crystal turbine working-blade ceramic core Download PDFInfo
- Publication number
- CN108971438A CN108971438A CN201810948495.9A CN201810948495A CN108971438A CN 108971438 A CN108971438 A CN 108971438A CN 201810948495 A CN201810948495 A CN 201810948495A CN 108971438 A CN108971438 A CN 108971438A
- Authority
- CN
- China
- Prior art keywords
- blade
- extended segment
- tenon
- single crystal
- localization method
- 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 48
- 239000013078 crystal Substances 0.000 title claims abstract description 46
- 230000004807 localization Effects 0.000 title claims abstract description 28
- 239000000919 ceramic Substances 0.000 title claims abstract description 19
- 238000004519 manufacturing process Methods 0.000 claims description 6
- 238000005266 casting Methods 0.000 abstract description 10
- 229910045601 alloy Inorganic materials 0.000 abstract description 5
- 239000000956 alloy Substances 0.000 abstract description 5
- 238000005516 engineering process Methods 0.000 abstract description 4
- 229910000601 superalloy Inorganic materials 0.000 abstract description 3
- 230000007547 defect Effects 0.000 abstract description 2
- 238000012797 qualification Methods 0.000 description 5
- PNEYBMLMFCGWSK-UHFFFAOYSA-N Alumina Chemical compound [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical group O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 239000003973 paint Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000005495 investment casting Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
- B22C9/108—Installation of cores
-
- 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
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
- B22C9/24—Moulds for peculiarly-shaped castings for hollow articles
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to high temperature alloy melted module precise casting technology field, specially a kind of localization method of single crystal turbine working-blade ceramic core.During making blade wax part, tenon extended segment fixing end is used as using tenon extended segment outside, and location hole is set at the fixing end of tenon extended segment for fixing axial position, the exhaust method that free end is done in side extended segment, free end is done in blade tip extended segment, mold core blade basin is identical as blade back localization method, and locating point position is full symmetric.The method of the present invention has the characteristics that location structure is stable, blade forming rate is high, especially to the single crystal turbine working-blade of complicated inner cavity structure, can greatly improve the integrality of casting.The present invention can reduce core shift in later period casting process, disconnected core defect, reduce the deviation of Blade roughcast wall thickness, improve the yield rate of single crystal super alloy casting.
Description
Technical field
The present invention relates to high temperature alloy melted module precise casting technology field, specially a kind of single crystal turbine working-blade ceramics
The localization method of type core.
Background technique
In order to meet the thrust of aero-engine continuous improvement and the demand of operating temperature, nickel-base high-temperature single crystal alloy is still
The preferred material of blade.But the temperature capability of single crystal alloy is no more than 1150 DEG C, and the fuel gas temperature of turbine inlet is up to 1500
DEG C or more.In addition in blade surface applying coating, designing complicated inner cavity cooling structure is also a kind of effective method.Therefore, multiple
The single crystal blade of miscellaneous inner-cavity structure has become the mark of advanced aero engine.But the technology difficulty of casting is thus also increased,
The especially control problem of blade forming and wall thickness dimension.
In the production and use process of single crystal super alloy blade, pass through the alloy being poured in the cavity of type core and shell
Directional solidification obtains single crystal casting.Domestic common type core is silica, and shell is aluminium oxide, this results in type at high temperature
The mismatch of the shell mould core coefficient of expansion, and then influence molding.In order to solve this problem, determined in shell using setting type core
Position technology, realizes the molding of hollow single crystal blade.Therefore, the localization method of ceramic core is most important for single crystal blade, directly
Connect the ratio of briquetting and wall thickness qualification rate for determining single crystal blade.
By the Searches of Patent Literature, has the report to single crystal blade ceramic core localization method.Chinese invention patent Shen
Please (publication number CN103286275A) then proposes the localization method of monocrystalline directing vane slab core, the small end of type core as fixing end not
Brush wax, and the big end of type core be designed as it is rectangular, after brush wax four faces make basal diameter be 3mm taper anchor point, together
When brush the wax of 1~2mm thickness in the longitudinal direction as free end, square groove brush also uniform brush wax and is locally made in the exhaust side of back cavity
Coating is as free end.This method is more suitable for the positioning of Single crystal guide vane ceramic mould core, it is impossible to be used in monocrystalline working-blade
The positioning of Tao Xin.Chinese invention patent application (publication number CN101695741A) provides a kind of type suitable for hollow blade casting
Blade tip anchor point is arranged in core method, specially blade tip extended segment, and the blade tip extended segment where blade tip anchor point is adopted as fixing end
With face direct contact type；The extended segment of tenon also uses point location, two tower anchor points is made in tenon extended segment, using point
Direct contact type；It is vented side and applies free end, and make two anchor points on free end, type core and shell use point contact herein
Formula；Mold core blade basin is identical as blade back localization method, and locating point position is symmetrical.Chinese invention patent application (publication number
CN104325090A it) proposes to do free end as fixing end, blade exhaust side and tenon using blade tip to monocrystalline working-blade
Method, wherein fixing end uses rectangular slot.Therefore, to monocrystalline working-blade more in such a way that blade tip is as positioning end,
This mode is simple suitable for tip structure, and inner cavity is positioned without the type core of weak structure, and is not suitable for inner-cavity structure complexity, and
Type core positioning with local weak structure.
Summary of the invention
The purpose of the present invention is to provide a kind of localization methods of single crystal turbine working-blade ceramic core, are primarily adapted for use in
Inner-cavity structure is complicated, and the type core with local weak structure positions, while being also applied for the single crystal hollow work of ordinary construction
The type core of blade positions.
The technical scheme is that
A kind of localization method of single crystal turbine working-blade ceramic core, during making blade wax part, using tenon
Head is used as tenon extended segment fixing end on the outside of extended segment, and location hole is arranged when mold design at the fixing end of tenon extended segment, makees
It is tenon extended segment fixing end for fixing axial position, other directions are fixed end by the extended segment of tenon, the extension of exhaust side
Free end is done in section and blade tip extended segment, and mold core blade basin is identical as blade back localization method, and locating point position is full symmetric；
Alternatively, being used as tenon extended segment fixing end, mould using tenon extended segment outside during making blade wax part
Location hole is set at the fixing end of tenon extended segment when tool design, as tenon extended segment fixing end for fixing axial position,
Other directions are fixed end by the extended segment of tenon, and free end is done in blade tip extended segment, and mold core blade basin is identical as blade back localization method,
Locating point position is full symmetric, and exhaust side is closed channel without exhaust passage.
The localization method of the single crystal turbine working-blade ceramic core, the width of blade tenon are 15~100mm, tenon
The height of head is 10~100mm, and for tenon extended segment fixing end along short transverse having a size of 10~40mm, width is 10~70mm,
The diameter of location hole is 3~20mm.
The localization method of the single crystal turbine working-blade ceramic core, blade exhaust side extended segment free end width are
1.5~20mm, is vented 1~2mm of the uniform brush wax in side extended segment, and the diameter of anchor point is 1~15mm, and the spacing of anchor point is 5~
90mm, basin back two sides are symmetrical, the uniform 0.02~0.1mm of mopping of locating point position.
The localization method of the single crystal turbine working-blade ceramic core, blade tip extended segment free end width are 10
~100mm, length are 5~20mm, and blade tip extended segment external form is extended to form by blade type face, and the diameter of free end anchor point is 2
~15mm, the spacing of anchor point are 5~30mm, and basin back two sides are symmetrical, the uniform 0.02~0.1mm of mopping of locating point position.
Design philosophy of the invention is:
It is fixed end using the thicker big position of tenon, it is ensured that the positioning in the direction XY, and increase in the fixing end of tenon extended segment
Add location hole, preferably guarantees Z-direction positioning, by the fixation to three directions of tenon fixing end, guarantee type core is in shell
Position stabilization does not deviate, and the free end guarantee type core using blade tip and exhaust side can have certain free gap in shell, in height
Forced breakage, guarantee disconnected leakage core will not occur due to differential expansion during temperature expansion.
The invention has the following advantages and beneficial effects:
1, the present invention easily manipulation, blade fragment leakage core rate is low.
2, the present invention can be positioned by accurately type core, reduced the core shift in later period casting process, core defect of breaking, guaranteed
Control to blade wall thickness size reduces the deviation of Blade roughcast wall thickness, increases the yield rate of single crystal super alloy precision castings.
3, the method for the present invention has the characteristics that location structure is stable, blade forming rate is high, especially to complicated inner cavity structure
Single crystal turbine working-blade, the integrality of casting can be greatly improved.
4, the present invention is mainly suitable for having the ceramic core of the single crystal turbine working-blade of complex-shaped surface mould to position, and can both use
In the blade of exhaust side window mouth structure, it is also applied for the blade of the exhaust windowless mouth structure in side.
Detailed description of the invention
Fig. 1 is single crystal turbine working-blade anchor point schematic diagram of the present invention.
In figure: 1 tenon extended segment location hole, 2 blade tip extended segment anchor points, 3 exhaust side extended segment anchor points, 4 tenons prolong
Stretch a section fixing end, 5 tenon extended segments, 6 exhaust side extended segments, 7 blade tip extended segments, 8 tenons, 9 blades.
Specific embodiment
In the specific implementation process, as shown in Figure 1, the localization method of single crystal turbine working-blade ceramic core are as follows: making
During making blade wax part, using being used as (the position shown in dotted line in figure of tenon extended segment fixing end 4 on the outside of tenon extended segment 5
Set), and tenon extended segment location hole 1 is set at tenon extended segment fixing end 4, for fixing axial position, using exhaust side
The method that free end is done in extended segment 6, free end is done in blade tip extended segment 7, extended segment positions when exhaust is arranged in exhaust at extended segment 6
3 are put, blade tip extended segment anchor point 2 is set at blade tip extended segment 7, mold core blade basin is identical as blade back localization method, locating point position
It is full symmetric.Furthermore it is possible to fix end only with tenon extended segment, free end is done in blade tip extended segment, is vented the complete packet wax in side,
Anchor point is not added.
8 width of single crystal turbine working-blade tenon is 15~100mm, and 8 height of tenon is 10~100mm；Tenon extended segment
For fixing end 4 along short transverse having a size of 10~40mm, fixing end 4 width in tenon extended segment is 10~70mm, and tenon extended segment is fixed
The diameter in position hole 1 is 3~20mm.
The free end width that single crystal turbine working-blade is vented side extended segment 6 is 1.5~20mm, and exhaust side extended segment 6 is equal
1~2mm of even brush wax, the diameter of exhaust side extended segment anchor point 3 are 1~15mm, and the spacing of exhaust side extended segment anchor point 3 is 5
The basin back two sides of~90mm, mold core blade basin are symmetrical, are vented the position uniform brush blade paint 0.02 of side extended segment anchor point 3
~0.1mm.
The free end width of single crystal turbine blade blade tip extended segment 7 is 10~100mm, and length is 5~20mm, and blade tip extends
The external form of section 7 is extended to form by 9 type face of blade, and the diameter of free end blade tip extended segment anchor point 2 is 2~15mm, and blade tip prolongs
The spacing for stretching section anchor point 2 is 5~30mm, and the basin back two sides of mold core blade basin are symmetrical, the position of blade tip extended segment anchor point 2
Uniform brush blade 0.02~0.1mm of paint.
In the following, the present invention is described in further detail by embodiment.
Embodiment 1
The present embodiment designs a kind of type core positioning method of monocrystalline high-pressure turbine working blade, in the mistake of production blade wax part
Cheng Zhong, using being used as tenon extended segment fixing end on the outside of tenon extended segment, when mold design, sets at the fixing end of tenon extended segment
Location hole is set, as tenon extended segment fixing end for fixing axial position, other directions are fixed end by the extended segment of tenon,
Free end is done in exhaust side extended segment and blade tip extended segment, and mold core blade basin is identical as blade back localization method, and locating point position is completely right
Claim.
The width of single crystal turbine working-blade tenon is 36mm, and the height of tenon is 30mm, tenon extended segment fixing end edge
Short transverse is 5mm having a size of 14mm, width 28mm, the diameter of location hole.The extended segment of tenon and position of positioning hole are direct
Fix end.
It is 5mm that single crystal turbine working-blade, which is vented side extended segment free end width, is vented the uniform brush wax 1mm in side extended segment,
The diameter of anchor point is 3mm, and the spacing of anchor point is 30mm, and basin back two sides are symmetrical, the uniform mopping of locating point position
0.05mm。
Single crystal turbine blade blade tip extended segment free end width is 30mm, and length 10mm, blade tip extended segment external form is by leaf
Body type face extends to form, and the diameter of free end anchor point is 3mm, and the spacing of anchor point is 8mm, and basin back two sides are symmetrical, fixed
The uniform mopping 0.05mm in site location.
It will be poured after the wax part that the positioning method is handled combines shell processed, the cored rate that blade is observed after depoling reaches
To 95%, the qualification rate of wall thickness reaches 90%.
Embodiment 2
The present embodiment designs a kind of type core positioning method of monocrystalline high-pressure turbine working blade, in the mistake of production blade wax part
Cheng Zhong, using being used as tenon extended segment fixing end on the outside of tenon extended segment, when mold design, sets at the fixing end of tenon extended segment
Location hole is set, as tenon extended segment fixing end for fixing axial position, other directions are fixed end by the extended segment of tenon,
Free end is done in exhaust side extended segment and blade tip extended segment, and mold core blade basin is identical as blade back localization method, and locating point position is completely right
Claim.
The width of single crystal turbine working-blade tenon is 19mm, and the height of tenon is 12mm, tenon extended segment fixing end edge
Short transverse is 4mm having a size of 15mm, width 14mm, the diameter of location hole.The extended segment of tenon and position of positioning hole are direct
Fix end.
It is 3mm that single crystal turbine working-blade, which is vented side extended segment free end width, is vented the uniform brush wax 1mm in side extended segment,
The diameter of anchor point is 2mm, and the spacing of anchor point is 9mm, and basin back two sides are symmetrical, the uniform mopping of locating point position
0.03mm。
Single crystal turbine blade blade tip extended segment free end width is 16mm, and length 6.5mm, blade tip extended segment external form is by leaf
Body type face extends to form, and the diameter of free end anchor point is 2mm, and the spacing of anchor point is 6mm, and basin back two sides are symmetrical, fixed
The uniform mopping 0.03mm in site location.
It will be poured after the wax part that the positioning method is handled combines shell processed, the cored rate that blade is observed after depoling reaches
To 96%, the qualification rate of wall thickness reaches 95%.
Embodiment 3
The present embodiment designs a kind of type core positioning method of monocrystalline high-pressure turbine working blade, in the mistake of production blade wax part
Cheng Zhong, using being used as tenon extended segment fixing end on the outside of tenon extended segment, when mold design, sets at the fixing end of tenon extended segment
Location hole is set, as tenon extended segment fixing end for fixing axial position, other directions are fixed end by the extended segment of tenon,
Free end is done in blade tip extended segment, and mold core blade basin is identical as blade back localization method, and locating point position is full symmetric, is vented side without exhaust
Channel is closed channel.
The width of single crystal turbine working-blade tenon is 70mm, and the height of tenon is 54mm, tenon extended segment fixing end edge
Short transverse is 14mm having a size of 19mm, width 65mm, the diameter of location hole.
Single crystal turbine working-blade exhaust side is that closed channel is not processed by mold compression moulding.
Single crystal turbine blade blade tip extended segment free end width is 58mm, and length 15mm, blade tip extended segment external form is by leaf
Body type face extends to form, and the diameter of free end anchor point is 8mm, and the spacing of anchor point is 24mm, and basin back two sides are symmetrical, fixed
The uniform mopping 0.1mm in site location.
It will be poured after the wax part that the positioning method is handled combines shell processed, the cored rate that blade is observed after depoling reaches
To 92%, the qualification rate of wall thickness reaches 93%.
Embodiment 4
The present embodiment designs a kind of type core positioning method of monocrystalline high-pressure turbine working blade, in the mistake of production blade wax part
Cheng Zhong, using being used as tenon extended segment fixing end on the outside of tenon extended segment, when mold design, sets at the fixing end of tenon extended segment
Location hole is set, as tenon extended segment fixing end for fixing axial position, other directions are fixed end by the extended segment of tenon,
Free end is done in exhaust side extended segment and blade tip extended segment, and mold core blade basin is identical as blade back localization method, and locating point position is completely right
Claim.
The width of single crystal turbine working-blade tenon is 48mm, and the height of tenon is 32mm, tenon extended segment fixing end edge
Short transverse is 6mm having a size of 12mm, width 44mm, the diameter of location hole.
It is 10mm that single crystal turbine working-blade, which is vented side extended segment free end width, is vented the uniform brush wax 2mm in side extended segment,
The diameter of anchor point is 8mm, and the spacing of anchor point is 40mm, and basin back two sides are symmetrical, the uniform mopping of locating point position
0.05mm。
Single crystal turbine blade blade tip extended segment free end width is 37mm, and length 16mm, blade tip extended segment external form is by leaf
Body type face extends to form, and the diameter of free end anchor point is 10mm, and the spacing of anchor point is 16mm, and basin back two sides are symmetrical,
The uniform mopping 0.05mm of locating point position.
It will be poured after the wax part that the positioning method is handled combines shell processed, the cored rate that blade is observed after depoling reaches
To 90%, the qualification rate of wall thickness reaches 90%.
Embodiment the result shows that, the present invention be mainly suitable for complex-shaped surface mould monocrystalline working-blade ceramic core positioning, both made
For being vented the blade of side window mouth structure, it is also applied for the blade of the exhaust windowless mouth structure in side.
Claims (4)
1. a kind of localization method of single crystal turbine working-blade ceramic core, which is characterized in that in the process of production blade wax part
In, using being used as tenon extended segment fixing end on the outside of tenon extended segment, when mold design, is arranged at the fixing end of tenon extended segment
Location hole, as tenon extended segment fixing end for fixing axial position, other directions are fixed end by the extended segment of tenon, are arranged
Free end is done in gas side extended segment and blade tip extended segment, and mold core blade basin is identical as blade back localization method, and locating point position is full symmetric；
Alternatively, using tenon extended segment fixing end is used as on the outside of tenon extended segment, mold is set during making blade wax part
Location hole is arranged in timing at the fixing end of tenon extended segment, other as tenon extended segment fixing end for fixing axial position
Direction is fixed end by the extended segment of tenon, and free end is done in blade tip extended segment, and mold core blade basin is identical as blade back localization method, positioning
Point position is full symmetric, and exhaust side is closed channel without exhaust passage.
2. the localization method of single crystal turbine working-blade ceramic core described in accordance with the claim 1, which is characterized in that blade tenon
The width of head is 15~100mm, and the height of tenon is 10~100mm, and tenon extended segment fixing end is along short transverse having a size of 10
~40mm, width are 10~70mm, and the diameter of location hole is 3~20mm.
3. the localization method of single crystal turbine working-blade ceramic core described in accordance with the claim 1, which is characterized in that blade row
Gas side extended segment free end width is 1.5~20mm, is vented 1~2mm of the uniform brush wax in side extended segment, the diameter of anchor point is 1~
15mm, the spacing of anchor point are 5~90mm, and basin back two sides are symmetrical, the uniform 0.02~0.1mm of mopping of locating point position.
4. the localization method of single crystal turbine working-blade ceramic core described in accordance with the claim 1, which is characterized in that blade and blade
Sharp extended segment free end width is 10~100mm, and length is 5~20mm, and blade tip extended segment external form is extended to form by blade type face,
The diameter of free end anchor point is 2~15mm, and the spacing of anchor point is 5~30mm, and basin back two sides are symmetrical, locating point position
0.02~0.1mm of uniform mopping.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810948495.9A CN108971438B (en) | 2018-08-20 | 2018-08-20 | Method for positioning ceramic core of working blade of single crystal turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810948495.9A CN108971438B (en) | 2018-08-20 | 2018-08-20 | Method for positioning ceramic core of working blade of single crystal turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108971438A true CN108971438A (en) | 2018-12-11 |
| CN108971438B CN108971438B (en) | 2020-05-15 |
Family
ID=64554363
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810948495.9A Active CN108971438B (en) | 2018-08-20 | 2018-08-20 | Method for positioning ceramic core of working blade of single crystal turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108971438B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111085661A (en) * | 2020-01-13 | 2020-05-01 | 成都航宇超合金技术有限公司 | Investment mold and method for manufacturing blade with complex cavity |
| CN112548035A (en) * | 2020-11-17 | 2021-03-26 | 中国航发北京航空材料研究院 | Cast hollow blade wall thickness control method based on core self-adaptive positioning |
| CN112705671A (en) * | 2020-12-10 | 2021-04-27 | 中国科学院金属研究所 | Wax module structure of cover plate block casting cantilever structure single crystal blade |
| CN114632914A (en) * | 2022-04-19 | 2022-06-17 | 中国航发动力股份有限公司 | Method for positioning ceramic core of working blade of single crystal turbine |
| CN115625286A (en) * | 2022-10-13 | 2023-01-20 | 中国航发北京航空材料研究院 | External mold of single crystal hollow guide blade and positioning method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1927414A2 (en) * | 2006-11-30 | 2008-06-04 | United Technologies Corporation | RMC-Defined tip blowing slots for turbine blades |
| CN101695741A (en) * | 2009-10-30 | 2010-04-21 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for positioning mold core and mold shell of hollow blade |
| CN101767187A (en) * | 2008-12-30 | 2010-07-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Positioning process method of complex and hollow high vortex blade ceramic core |
| CN103317087A (en) * | 2013-05-24 | 2013-09-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Tapered embedded locating method for silicon-based ceramic core and aluminium-based ceramic shell |
| CN104325090A (en) * | 2014-11-24 | 2015-02-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Positioning method of ceramic core of turbine blade with block-cast cover plate structure |
| US20180178278A1 (en) * | 2016-12-28 | 2018-06-28 | Mapna Group | Method for positioning core by soluble wax in investment casting |
-
2018
- 2018-08-20 CN CN201810948495.9A patent/CN108971438B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1927414A2 (en) * | 2006-11-30 | 2008-06-04 | United Technologies Corporation | RMC-Defined tip blowing slots for turbine blades |
| CN101767187A (en) * | 2008-12-30 | 2010-07-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Positioning process method of complex and hollow high vortex blade ceramic core |
| CN101695741A (en) * | 2009-10-30 | 2010-04-21 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for positioning mold core and mold shell of hollow blade |
| CN103317087A (en) * | 2013-05-24 | 2013-09-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Tapered embedded locating method for silicon-based ceramic core and aluminium-based ceramic shell |
| CN104325090A (en) * | 2014-11-24 | 2015-02-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Positioning method of ceramic core of turbine blade with block-cast cover plate structure |
| US20180178278A1 (en) * | 2016-12-28 | 2018-06-28 | Mapna Group | Method for positioning core by soluble wax in investment casting |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111085661A (en) * | 2020-01-13 | 2020-05-01 | 成都航宇超合金技术有限公司 | Investment mold and method for manufacturing blade with complex cavity |
| CN112548035A (en) * | 2020-11-17 | 2021-03-26 | 中国航发北京航空材料研究院 | Cast hollow blade wall thickness control method based on core self-adaptive positioning |
| CN112705671A (en) * | 2020-12-10 | 2021-04-27 | 中国科学院金属研究所 | Wax module structure of cover plate block casting cantilever structure single crystal blade |
| CN112705671B (en) * | 2020-12-10 | 2022-03-15 | 中国科学院金属研究所 | Wax module structure of cover plate block casting cantilever structure single crystal blade |
| CN114632914A (en) * | 2022-04-19 | 2022-06-17 | 中国航发动力股份有限公司 | Method for positioning ceramic core of working blade of single crystal turbine |
| CN115625286A (en) * | 2022-10-13 | 2023-01-20 | 中国航发北京航空材料研究院 | External mold of single crystal hollow guide blade and positioning method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108971438B (en) | 2020-05-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108971438A (en) | A kind of localization method of single crystal turbine working-blade ceramic core | |
| CN101695741B (en) | Method for positioning mold core and mold shell of hollow blade | |
| US8317475B1 (en) | Turbine airfoil with micro cooling channels | |
| US6627054B2 (en) | Electrode for electrochemical machining | |
| EP1634665B1 (en) | Composite core for use in precision investment casting | |
| CN104550731B (en) | The preparation technology that the anti-surface stray crystal of single crystal hollow turbo blade is formed with recrystallization | |
| EP2511024B1 (en) | Contoured metallic casting core | |
| US10465532B2 (en) | Core positioning | |
| US7918647B1 (en) | Turbine airfoil with flow blocking insert | |
| CN104841619B (en) | Coating method and template for being used together with the coating method | |
| CN109175369A (en) | A kind of metal winding pipe selective laser fusing manufacturing process | |
| CN104646633A (en) | Locally-free-telescopic single crystal blade-used complex-structured ceramic core preparation technology | |
| CN103143682A (en) | Mold core for manufacturing high-temperature alloy hollow blade | |
| CN104014737A (en) | Preparation technology for complex ceramic core with embedded cavity structure | |
| JP2005120995A (en) | Partition plate for intake port, sand core for molding intake port and cylinder head | |
| EP3002070B1 (en) | Casting of engine parts | |
| CN204419278U (en) | Nozzle ring | |
| CN112705671B (en) | Wax module structure of cover plate block casting cantilever structure single crystal blade | |
| CN105290324B (en) | Large scale turborotor anti-deformation preparation technology | |
| CN108097888A (en) | A kind of preparation method of high temperature alloy tubulose sample | |
| CN104647586A (en) | Production method of composite ceramic core for single crystal hollow blade of complex structure | |
| CN114523070A (en) | Deformation prevention control method for crown turbine blade casting | |
| CN104385440B (en) | A kind of method of embedded glass tube/earthenware forming ceramic core | |
| JP2005074748A (en) | Injection mold | |
| EP2095894A1 (en) | Method for manufacturing a turbine blade that is internally cooled |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210804 Address after: 110172 block C12, south of Shendong Sixth Road, west of Zhongxing Street, Shenfu new area, Shenyang City, Liaoning Province Patentee after: Liaoning Hongyin Metal Co.,Ltd. Address before: 110016 No. 72, Wenhua Road, Shenhe District, Liaoning, Shenyang Patentee before: INSTITUTE OF METAL RESEARCH CHINESE ACADEMY OF SCIENCES |
|
| TR01 | Transfer of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: A positioning method for ceramic core of single crystal turbine working blade Effective date of registration: 20220225 Granted publication date: 20200515 Pledgee: Fushun Bank Co.,Ltd. Development Zone sub branch Pledgor: Liaoning Hongyin Metal Co.,Ltd. Registration number: Y2022210000012 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |