CN110076292A - A kind of investment casting method of duplex block cast directional solidification turborotor - Google Patents
A kind of investment casting method of duplex block cast directional solidification turborotor Download PDFInfo
- Publication number
- CN110076292A CN110076292A CN201910448470.7A CN201910448470A CN110076292A CN 110076292 A CN110076292 A CN 110076292A CN 201910448470 A CN201910448470 A CN 201910448470A CN 110076292 A CN110076292 A CN 110076292A
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- core
- turborotor
- blade
- casting method
- investment casting
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Classifications
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- 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
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
- B22C9/043—Removing the consumable pattern
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/08—Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
- B22C9/082—Sprues, pouring cups
-
- 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
-
- 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
Abstract
The present invention is a kind of investment casting method of duplex block cast directional solidification turborotor, the step of this method includes preparing ceramic core, it is put it into shape mold again and suppresses blade wax mould, shell is coated after group mould and the roasting that dewaxes, then smelting and pouring, shelling, depoling, cut off running channel redundance, the method of the present invention is simple for process, it can effectively reduce being mingled with for blade, it is loose, the metallurgical imperfections scrappages such as crystal orientation deviation, and improve casting dimension accuracy, and then greatly improve product qualification rate, reduce economic loss, large-scale production demand can be met.
Description
Technical field
The present invention is a kind of investment casting method of duplex block cast directional solidification turborotor, belongs to precision-investment casting
Make technical field of high temperature alloy.
Background technique
The promotion of turbine inlet temperature is most important to the promotion of engine thrust-weight ratio, and guide vane of high pressure turbine is directly held
By the impact of high-temperature fuel gas, high requirement is proposed to its temperature capability and reliability.On the one hand the promotion of temperature capability comes
Derived from the optimization of alloying component and microscopic structure, compared to traditional equiax crystal blade, column crystal eliminates the cross for being also easy to produce crackle
To crystal boundary, blade fatigue performance is made to have obtained the raising of high degree；On the other hand then from the optimization of structure design, including
The gaseous film control mode of hollow lumen, and the multi-joint block cast structure accurately controlled is realized for access points and throat area.
The directional solidification column crystal blade of certain guide vane of high pressure turbine category duplex block cast structure, shape are (double by blade
Connection), inner platform, curtain plate composition.Traditional preparation process mainly takes listrium seeding mode, the control to blade grain growth
Ability is limited, when process of setting is by extraneous factor influence of fluctuations, be also easy to produce leading edge transverse grain boundaries, exhaust side appear it is brilliant, miscellaneous
The metallurgical imperfections such as brilliant, crystal orientation deviation.In addition, the seeding strip quantity of traditional listrium seeding mode is more and spacing is excessively close, lead
It causes shell local desiccation situation poor, being mingled with for blade is easily caused to scrap.Therefore, a kind of duplex block cast hollow guiding blade is studied
Preparation process, the problem of to promote Blade roughcast qualification rate, be current melted module precise casting technology field urgent need to resolve.
Summary of the invention
It is an object of the invention to press from both sides existing for the preparation process for the existing hollow turborotor of duplex block cast
Miscellaneous, loose, stray crystal, transverse grain boundaries, appear metallurgical imperfections and the overproof equidimension problems of wall thickness such as brilliant, crystal orientation deviation, mention
For a kind of investment casting method of duplex block cast directional solidification turborotor, the purpose is to improve blade qualification rate and production
Efficiency shortens the blade development and production period.
The technical solution of the invention is as follows:
The step of investment casting method of this kind of duplex block cast directional solidification turborotor, this method includes preparation pottery
Porcelain type core, then put it into shape mold and suppress blade wax mould, shell is coated after group mould and the roasting that dewaxes, then melting is poured
Note, shelling, depoling, excision running channel redundance, it is characterised in that:
A, it when preparing ceramic core, first suppresses and is sintered a, circumferential size consistent with ceramic core shape than ceramics
Then the small cold core of the design size of type core covers and is sintered crust in the outside of cold core, forms complete ceramic core；
B, group mould includes sprue cup 1, cross gate 2, blade wax mould, seeding section 3, disk 4, the rectangular item 5 of feeding, feeding bending
6, feeding piece connection running channel 7 and exhaust side wax disk(-sc) 8, wherein blade wax mould includes blade 9, inner platform 10 and curtain plate 11；It is described
1 lower plane of sprue cup connects cross gate 2, and cross gate 2 is installed side with blade wax mould inner platform 10 by the rectangular item 5 of feeding and is connected to,
Disk 4 positioned at bottom will be connected after type core core print package with blade wax mould curtain plate 11 by seeding section 3, then in type core core
Head basin side and back side respectively dig rectangular or diameter 2mm~5mm the round positioning end of a side length 2mm~5mm, the feeding bending
6 is identical as 9 bending shape of blade, and places it between two blades 9 and connect with the curtain plate 11 of lower section, and 6 liang of feeding bending
End connects running channel 7 by feeding piece and is connected to the installation of inner platform 10 side, and the exhaust is in wax disk(-sc) 8 when duplex blade is respectively vented
Corresponding position connects inner platform 10 and curtain plate 11 installs side.
Further, the circumferential size of cold core is 0.5~2mm smaller than ceramic core design size.
Further, the material of cold core is identical as ceramic slurry used by ceramic core shell is prepared.
Further, 3 coated core core print of seeding section with a thickness of 0.5~2mm.
Further, feeding bending 6 with a thickness of 1~5mm, be highly 5~20mm, length be 10~50mm.
Further, the 3~20mm of width, 1~5mm of thickness of side wax disk(-sc) 8 are vented.
Further, the blade 9 in blade wax mould, inner platform 10 and curtain plate 11 use integral injection molding, injection temperature
63~70 DEG C, injection pressure is 6~10bar, and injection time is 10~30s, 20~60s of dwell time.
Further, the material for preparing shell is Al2O3-SiO2It is ceramic shell material, the number of plies for applying shell is controlled at 5-8 layers.
Further, the master alloy used in the model casting of the duplex block cast turborotor is directional solidification high temperature
Alloy.
Further, during the smelting and pouring, using the vacuum oriented consolidation furnace of high-temperature gradient, upper heater temperature
It is 1480 DEG C~1510 DEG C, lower heater temperature is 1490 DEG C~1520 DEG C, and shell soaking time is 10~30min, casting temperature
Degree is 1480 DEG C~1520 DEG C, and withdrawing rate is 3~8mm/min.
The beneficial effects of the present invention are:
It is greater than the turborotor of 8mm, for lumen thickness direction full-size for the accurate control for realizing interior chamber size
System, need to suppress first cold core in type core preparation process, and cold core size compares the unilateral small 0.5~2mm of type core, thereafter puts cold core
Enter core mold press ceramic type core with control type core dimensional contraction, provides basis for the accurate control of wall thickness dimension.
Blade wax mould 2 uses wax injector injection moulding mode, and pressing process controls 63~70 DEG C of injection temperature, injection pressure
For 6~10bar, injection time is 10~30s, 20~60s of dwell time, can avoid ceramic core break core while effectively protect
Demonstrate,prove wax-pattern wall thickness dimension precision.It is controlled and is required according to the grain size of directional columnargrain, using the mould group combination of vertical direction, and
Connect feeding piece and running channel in two inter-blade channel regions, by passage area it is loose, be mingled with etc. and to lead to feeding structure, can be effective
Blade casting qualification rate is substantially improved in the generation for avoiding metallurgical imperfection.Seeding mode of the invention is " curtain plate side core core
Head seeding " is designed using the seeding structure of packaging type, to the seeding of blade apart from shorter and more direct, therefore seeding efficiency
It is higher, it can significantly reduce the probability of occurrence of blade transverse grain boundaries, the abnormal grains such as crystalline substance, high-angle boundary of appearing, while compared to
Traditional listrium seeding mode, local space seeding planform is simple, and quantity is less, therefore seeding structure relative distance is bigger,
Be conducive to the dry consistency of ceramic shell and uniformity, shell breakout ratio is made to reduce by 30%.To sum up, technology is answered in the present invention
With providing strong guarantee for research and production, provide technical support for multi-joint block cast large scale hollow blade.
Detailed description of the invention
Fig. 1 is duplex block cast structure turborotor wax-pattern mould group schematic diagram.In figure:
Specific embodiment
Detailed description is further said to technical solution of the present invention work below with reference to drawings and examples:
Embodiment 1
When preparing ceramic core, first suppresses and be sintered that one consistent with ceramic core shape, circumferential size compares ceramic mould
The small 0.5mm of the design size of core, is then preset in core mold, in the outside drawn-shell case of cold core, is formed after sintering
Complete ceramic core；The material of cold core is identical as ceramic slurry used by ceramic core shell is prepared；
The ceramic core system of completion suppresses blade wax mould after making every effort to, feeding bending 6 is long 30mm, and high 10mm, thickness is by 1mm mistake
It crosses to the wedge block of 3mm；
3 coated core core print of seeding section with a thickness of 0.5~2mm；
It is vented the width 5mm, thickness 3mm of side wax disk(-sc) 8；
Blade 9, inner platform 10 and curtain plate 11 in blade wax mould use integral injection molding, injection temperature 63~70
DEG C, injection pressure is 6~10bar, and injection time is 10~30s, 20~60s of dwell time.
Wax-pattern combination used in the present invention is as shown in Figure 1,1 lower plane of the sprue cup connects cross gate 2, cross gate 2
Side is installed with blade wax mould inner platform 10 by the rectangular item 5 of feeding to be connected to, the disk 4 positioned at bottom passes through seeding section 3 for type core
Connect after core print package with blade wax mould curtain plate 11, then respectively digs a side length 2mm~5mm in type core core print basin side and back side
Rectangular or diameter 2mm~5mm round positioning end, the feeding bending 6 is identical as 9 bending shape of blade, and places it in
It is connect between two blades 9 with the curtain plate 11 of lower section, 6 both ends of feeding bending connect running channel 7 and inner platform 10 by feeding piece
Side connection, the exhaust corresponding position connection inner platform 10 and curtain plate 11 when duplex blade is respectively vented in wax disk(-sc) 8 are installed
Side is installed.
The material for preparing shell is Al2O3-SiO2It is ceramic shell material, it is 5 layers that shell, which coats the number of plies, and last slurry seal is adopted
With surface layer slurry, shell is cleaned after dewaxing roasting and prepares casting.
Smelting and pouring equipment is vacuum induction directional solidification furnace, and 10min is kept the temperature after shell to temperature, and IC10 alloy is selected to exist
It is refined at 1545 DEG C, controls 1510 DEG C of upper heater temperature thereafter, 1520 DEG C of lower heater temperature, 1520 DEG C of pouring temperature, take out
Pulling rate rate 3mm/min.
Casting uses the clear shell of high pressure water after coming out of the stove, and corrodes in ferric trichloride aqueous hydrochloric acid solution after cutting off running channel, through examining
Blade grain size meets design requirement.Through surface visually, fluorescence, x-ray examination, blade without sand holes, be mingled with, the metallurgy such as loose lacks
It falls into.Casting section thickness is measured by ultrasonic method, meets design size requirement.
Embodiment 2
The present embodiment compared with Example 1, difference are as follows:
Cold core size compares the unilateral small 2mm of type core；
Feeding bending (6) is long 20mm, high 15mm, and thickness transits to the wedge block of 4mm by 2mm；
It is vented the width 3mm, thickness 2mm of side wax disk(-sc) (8)；
It is 8 layers that shell, which coats the number of plies,；
Smelting and pouring equipment is vacuum induction directional solidification furnace, and 30min is kept the temperature after shell to temperature, and IC10 alloy is selected to exist
It is refined at 1535 DEG C, controls 1480 DEG C of upper heater temperature thereafter, 1490 DEG C of lower heater temperature, 1480 DEG C of pouring temperature, take out
Pulling rate rate 8mm/min.
Casting uses the clear shell of high pressure water after coming out of the stove, and corrodes in ferric trichloride aqueous hydrochloric acid solution after cutting off running channel, through examining
Blade grain size meets design requirement.Through surface visually, fluorescence, x-ray examination, blade without sand holes, be mingled with, the metallurgy such as loose lacks
It falls into.Casting section thickness is measured by ultrasonic method, meets design size requirement.
Claims (10)
1. a kind of the step of investment casting method of duplex block cast directional solidification turborotor, this method includes preparation ceramics
Type core, then put it into shape mold and suppress blade wax mould, shell is coated after group mould and the roasting that dewaxes, then melting is poured
Note, shelling, depoling, excision running channel redundance, it is characterised in that:
A, it when preparing ceramic core, first suppresses and is sintered that one consistent with ceramic core shape, circumferential size compares ceramic core
The small cold core of design size, cold core is then placed in compacting hygrometric state ceramic core in core mold, is formed after sintering complete
Ceramic core；
B, group mould includes sprue cup (1), cross gate (2), blade wax mould, seeding section (3), disk (4), the rectangular item of feeding (5), mends
Contracting bending (6), feeding piece connection running channel (7) and exhaust side wax disk(-sc) (8), wherein blade wax mould includes blade (9), inner platform
(10) and curtain plate (11)；Sprue cup (1) lower plane connects cross gate (2), and cross gate (2) passes through the rectangular item of feeding (5)
It is connected to blade wax mould inner platform (10) installation side, the disk (4) positioned at bottom will be after type core core print package by seeding section (3)
Connect with blade wax mould curtain plate (11), then type core core print basin side and back side respectively dig the rectangular of a side length 2mm~5mm or
The round positioning end of diameter 2mm~5mm, the feeding bending (6) is identical as blade (9) bending shape, and places it in two
It is connect between blade (9) with the curtain plate (11) of lower section, feeding bending (6) both ends pass through feeding piece connection running channel (7) and inner edge
Plate (10) installs side connection, exhaust corresponding position connection inner platform (10) when duplex blade is respectively vented in wax disk(-sc) (8)
And curtain plate (11) installs side.
2. the investment casting method of duplex block cast directional solidification turborotor according to claim 1, feature exist
In: the circumferential size of cold core is 0.5~2mm smaller than ceramic core design size.
3. the investment casting method of duplex block cast directional solidification turborotor according to claim 1, feature exist
In: the material of cold core is identical as ceramic slurry used by ceramic core shell is prepared.
4. the investment casting method of duplex block cast directional solidification turborotor according to claim 1, feature exist
In: seeding section (3) coated core core print with a thickness of 0.5~2mm.
5. the investment casting method of duplex block cast directional solidification turborotor according to claim 1, feature exist
It is highly 5~20mm in: feeding bending (6) with a thickness of 1~5mm, length is 10~50mm.
6. the investment casting method of duplex block cast turborotor according to claim 1, it is characterised in that: exhaust side
3~20mm of width of wax disk(-sc) (8), 1~5mm of thickness.
7. the investment casting method of duplex block cast directional solidification turborotor according to claim 1, feature exist
In: blade (9), inner platform (10) and curtain plate (11) in blade wax mould use integral injection molding, injection temperature 63~70
DEG C, injection pressure is 6~10bar, and injection time is 10~30s, 20~60s of dwell time.
8. the investment casting method of duplex block cast directional solidification turborotor according to claim 1, feature exist
In: the material for preparing shell is Al2O3-SiO2It is ceramic shell material, the number of plies for applying shell is controlled at 5-8 layers.
9. the investment casting method of duplex block cast directional solidification turborotor according to claim 1, feature exist
In: the master alloy used in the model casting of the duplex block cast turborotor is directionally solidified superalloy, DS superalloy.
10. the investment casting method of duplex block cast directional solidification turborotor according to claim 1, feature exist
In: during the smelting and pouring, using the vacuum oriented consolidation furnace of high-temperature gradient, upper heater temperature is 1480 DEG C~
1510 DEG C, lower heater temperature is 1490 DEG C~1520 DEG C, and shell soaking time is 10~30min, and pouring temperature is 1480 DEG C
~1520 DEG C, withdrawing rate is 3~8mm/min.
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| CN201910448470.7A CN110076292B (en) | 2019-05-27 | 2019-05-27 | Investment casting method for duplex block casting directional solidification turbine guide blade |
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| CN201910448470.7A CN110076292B (en) | 2019-05-27 | 2019-05-27 | Investment casting method for duplex block casting directional solidification turbine guide blade |
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| CN110076292B CN110076292B (en) | 2020-08-11 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111496190A (en) * | 2020-05-11 | 2020-08-07 | 中国航发北京航空材料研究院 | Pouring system of triple block casting directional solidification hollow guide vane |
| CN111618279A (en) * | 2020-06-24 | 2020-09-04 | 中国航发北京航空材料研究院 | Precision casting method for quintuplet directional columnar crystal blade |
| CN111940679A (en) * | 2020-09-17 | 2020-11-17 | 中国航发沈阳黎明航空发动机有限责任公司 | Design method of double-linkage directional hollow blade gating system |
| CN113070454A (en) * | 2021-03-16 | 2021-07-06 | 贵阳航发精密铸造有限公司 | Casting device and method for non-preferred orientation single crystal guide hollow blade |
| CN115106482A (en) * | 2022-07-28 | 2022-09-27 | 中国科学院金属研究所 | Inner cavity forming and wall thickness size control process method for large-size hollow guide blade |
| CN115283650A (en) * | 2022-07-14 | 2022-11-04 | 中国科学院金属研究所 | Method for preventing blade body of single crystal duplex integral casting turbine guide blade from being mixed with crystals |
| CN115570105A (en) * | 2022-11-21 | 2023-01-06 | 中国航发四川燃气涡轮研究院 | Method for manufacturing double-wall turbine blade |
| CN116174649A (en) * | 2023-02-28 | 2023-05-30 | 中国航发北京航空材料研究院 | Preparation method of air inlet side precision casting for maintaining high-temperature alloy guide vane |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105170909A (en) * | 2015-10-10 | 2015-12-23 | 贵阳中航动力精密铸造有限公司 | Pouring system for hollow single crystal blade |
| CN105290337A (en) * | 2015-11-16 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Multiple-connection-blade precision casting method |
| CN106734907A (en) * | 2016-11-25 | 2017-05-31 | 中航动力股份有限公司 | A kind of directional solidification cylindrulite and single crystal blade casting method |
| CN107598097A (en) * | 2017-11-10 | 2018-01-19 | 东方电气集团东方汽轮机有限公司 | A kind of wax-pattern combination of turborotor and its fine casting method |
| CN108941455A (en) * | 2018-07-27 | 2018-12-07 | 沈阳中科三耐新材料股份有限公司 | A kind of casting method of gas turbine duplex turborotor |
-
2019
- 2019-05-27 CN CN201910448470.7A patent/CN110076292B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105170909A (en) * | 2015-10-10 | 2015-12-23 | 贵阳中航动力精密铸造有限公司 | Pouring system for hollow single crystal blade |
| CN105290337A (en) * | 2015-11-16 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Multiple-connection-blade precision casting method |
| CN106734907A (en) * | 2016-11-25 | 2017-05-31 | 中航动力股份有限公司 | A kind of directional solidification cylindrulite and single crystal blade casting method |
| CN107598097A (en) * | 2017-11-10 | 2018-01-19 | 东方电气集团东方汽轮机有限公司 | A kind of wax-pattern combination of turborotor and its fine casting method |
| CN108941455A (en) * | 2018-07-27 | 2018-12-07 | 沈阳中科三耐新材料股份有限公司 | A kind of casting method of gas turbine duplex turborotor |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111496190A (en) * | 2020-05-11 | 2020-08-07 | 中国航发北京航空材料研究院 | Pouring system of triple block casting directional solidification hollow guide vane |
| CN111496190B (en) * | 2020-05-11 | 2021-10-15 | 中国航发北京航空材料研究院 | Module structure of pouring triple-block-casting directional solidification hollow guide vane |
| CN111618279A (en) * | 2020-06-24 | 2020-09-04 | 中国航发北京航空材料研究院 | Precision casting method for quintuplet directional columnar crystal blade |
| CN111618279B (en) * | 2020-06-24 | 2021-08-03 | 中国航发北京航空材料研究院 | Precision casting method for quintuplet directional columnar crystal blade |
| CN111940679B (en) * | 2020-09-17 | 2021-10-22 | 中国航发沈阳黎明航空发动机有限责任公司 | Design method of double-linkage directional hollow blade gating system |
| CN111940679A (en) * | 2020-09-17 | 2020-11-17 | 中国航发沈阳黎明航空发动机有限责任公司 | Design method of double-linkage directional hollow blade gating system |
| CN113070454A (en) * | 2021-03-16 | 2021-07-06 | 贵阳航发精密铸造有限公司 | Casting device and method for non-preferred orientation single crystal guide hollow blade |
| CN115283650A (en) * | 2022-07-14 | 2022-11-04 | 中国科学院金属研究所 | Method for preventing blade body of single crystal duplex integral casting turbine guide blade from being mixed with crystals |
| CN115283650B (en) * | 2022-07-14 | 2024-03-22 | 中国科学院金属研究所 | Method for preventing blade body of single crystal twin cast turbine guide blade from being mixed |
| CN115106482A (en) * | 2022-07-28 | 2022-09-27 | 中国科学院金属研究所 | Inner cavity forming and wall thickness size control process method for large-size hollow guide blade |
| CN115570105A (en) * | 2022-11-21 | 2023-01-06 | 中国航发四川燃气涡轮研究院 | Method for manufacturing double-wall turbine blade |
| CN116174649A (en) * | 2023-02-28 | 2023-05-30 | 中国航发北京航空材料研究院 | Preparation method of air inlet side precision casting for maintaining high-temperature alloy guide vane |
| CN116174649B (en) * | 2023-02-28 | 2024-04-16 | 中国航发北京航空材料研究院 | Preparation method of air inlet side precision casting for maintaining high-temperature alloy turbine guide vane |
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