CN101168485A - Silicon-base ceramic core and preparation thereof - Google Patents
Silicon-base ceramic core and preparation thereof Download PDFInfo
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Abstract
A silicon-based ceramic core is characterized in that the core is prepared from following materials at mass percentages as 30-50% porous quartz glass powder, 10-15% mullite mineralizer, 18-22% plasticizer, and quartz glass powder at left amount, wherein the porosity of the porous quartz glass powder is 10-20%, which granularity is 150-180, the granularity of the mullite mineralizer is lower than 320, the granularity of the quartz glass powder is 180-240, the plasticizer is the mixture of 10-15% wax, 3-5% polythene, and mineral wax at left amount. The preparation comprises that uniformly mixes materials, to be pressed and shaped on a core press via moulds, to be baked, while the bake temperature is 200+-10DEG C for 4-8h, 400+-10DEG C for 4-8h, 600+-10DEG C for 1h, 900+-10DEG C for 1h, and 1200+-10DEG C for 6-10h, to be strengthened at high and low temperatures. The invention can produce ceramic core with demanded requirements, to support the production of R0110 heavy combustion engine II-stage guider blade.
Description
Technical field:
The present invention relates to the technology of preparing of R0110 heavy combustion engine II stage diverter blade, particularly, silicon-base ceramic core and the preparation thereof of casting with R0110 heavy combustion engine II stage diverter blade is provided, the casting manufacture method of R0110 heavy combustion engine II stage diverter blade shell, the pouring procedure of R0110 heavy combustion engine II stage diverter blade.
Background technology:
R0110 heavy combustion engine II stage diverter blade is that large complicated inner-cavity structure equiax crystal does not have the hollow investment pattern precision casting blade of surplus, physical dimension is big (to be of a size of 2～3 times of turning vane in the past, volume is its 6～9 times), its upper and lower listrium area is big, and inner chamber is staggered-mesh shape complex construction (as Fig. 1,2), the dimension precision requirement height.The structure design of this blade still belongs to initiative, aspect the casting preparation of blade, no matter is on the processing condition of the preparation of ceramic core, shell from inner chamber and cast, also all have higher requirement,
At first no matter to be on dimension volume, or on the complexity, R0110 heavy combustion engine II stage diverter blade form the ceramic core of inner chamber all considerably beyond existing homemade engine turning vane ceramic core (see figure 1).Because the large size and the baroque fact of ceramic core have determined and can not produce this core with traditional technique for making ceramic moulding core, also to consider the problem that removes after blade is poured into a mould simultaneously.If adopt traditional silicon-base ceramic core manufacturing process, what at first face is the problem of burning till of core, and this problem mainly is the crackle and the distortion of core.If crack in the core roasting process; can not obtain complete core (core just ruptures when taking out or can not get at all) from roasting pot after roasting; also might on core, produce small crackle; in the process of system wax-pattern or cast,, cause ceramic core to use because of undercapacity ruptures.Even adopt the traditional method core after roasting, not rupture, also might produce distortion, when deflection is big, ceramic core can't use, in the process of system wax-pattern, just rupture in Wax mold at ceramic core, the core fracture can't be used behind the extrusion wax-pattern.The major cause that crackle and distortion produce is excessive the causing of the shrinking percentage of ceramic core in roasting process.Traditional silicon fundamental mode core will produce about 0.4～1.2% the contraction of burning till in roasting process, in roasting process, can produce bigger internal stress like this, cause the fracture of core, if the way by not jolt ramming of filler before roasting reduces crackle, can cause the bigger problem of deflection so, will produce a pair of contradiction between crackle and distortion like this, attend to one thing and lose sight of another, perhaps both exist simultaneously.Because R0110 heavy combustion engine II stage diverter blade is with the singularity of ceramic core, so traditional technology can't satisfy the production of this core at all.Secondly the ceramic core of traditional technology production also is faced with blade and pours the problem that the back ceramic core removes from blade.Because the constructional feature of this blade, inner chamber air cooling passage is intricate, and removing of ceramic core is mouthful narrow and small, this has just determined that ceramic core removing from blade is extremely difficult, if it is long-time that blade soaked in corrosive fluid, can cause corrosion to the metallic substance of blade, serious meeting influences the normal use of blade and must scrap.The voidage that traditional technology is made silicon-base ceramic core is lower, is generally 23～30%, therefore is unfavorable for the infiltration of corrosive fluid to ceramic core inside, so influence depoling speed.
In addition, R0110 heavy combustion engine II stage diverter blade physical dimension is big, the dimension precision requirement height, and its upper and lower listrium area is big, and leaf weight is heavy, and the (see figure 2)s such as the groove of obturaging of 5mm are arranged on the listrium.Above constructional feature makes R0110 heavy combustion engine II stage diverter blade have great difficulty in casting, its investment casting shell there is special requirement, require shell that enough hot strengths and high high temperature amount of deflection and good deformability are arranged, require the deadweight deflection of shell little, traditional shell manufacture method can not meet the demands.
At last, for turbine stator blade in the past, according to its constructional feature, traditional pouring and riser systems and assembled scheme are that side is annotated formula, though have that venting quality is good, molten metal is to advantages such as the impact of casting mold are less, for R0110 heavy combustion engine II stage diverter blade and inapplicable.This is because the inner chamber of R0110 heavy combustion engine II stage diverter blade is complicated grid structure, and wall thickness is thinner, feeding to metal plays barrier effect to ceramic core in inside, cause feeding not smooth, cause side to annotate the formula scheme thus and make the thick large part of blade blade place produce big shrinkage cavity defect, and cause cold shut and the appearance of owing to cast defective easily.
Summary of the invention:
One of purpose of the present invention is to provide a kind of silicon-base ceramic core and technology of preparing thereof, and the silicon-base ceramic core for preparing by this method does not have crackle and distortion, and is easy to remove.
Another purpose of the present invention is to provide the manufacture method of a kind of R0110 heavy combustion engine II stage diverter blade with shell, R0110 heavy combustion engine II stage diverter blade by the preparation of this method possesses enough hot strengths and high high temperature amount of deflection and good deformability with shell, and the deadweight deflection is little, can satisfy the service requirements of casting R0110 heavy combustion engine II stage diverter blade.
The 3rd purpose of the present invention is to provide a kind of casting process of R0110 heavy combustion engine II stage diverter blade, this method have good cavity filling can, and be easy to form consecutive solidification and the foundry goods that obtains dense structure.
The present invention specifically provides a kind of silicon-base ceramic core, it is characterized in that: the feedstock production that described core is made up of following weight per-cent forms:
Porous silica glass powder 30～50%;
Mullite mineralizer 10～15%;
Softening agent 18～22%;
The fused silica powder surplus;
Wherein
The porosity of porous silica glass powder is 10～20%, and granularity is between 150 orders～180 orders;
The granularity of mullite mineralizer is less than 320 orders;
The granularity of fused silica powder is between 180 orders～240 orders;
Softening agent is 10～15% beeswax, 3～5% polyethylene, all the other are the mixture of paraffin.
The present invention also provides the preparation method of above-mentioned silicon-base ceramic core, it is characterized in that: with the raw material thorough mixing, after using mould compression moulding on the pressure core machine, carry out roasting, maturing temperature is 200 ± 10 ℃, 4～8h+400 ± 10 ℃, 4～8h+600 ± 10 ℃, 1h+900 ± 10 ℃, 1h+1200 ± 10 ℃, 6～10h; Carrying out conventional high and low temperature again strengthens.
In order to guarantee that ceramic core can remove fast, has adopted following removing process from R0110 heavy combustion engine II stage diverter blade after cast:
Adopting weight is the aqueous solution of 35%～40% NaOH, in High Temperature High Pressure depoling still, under the pressure of 0.4～0.5MPa, under 180～200 ℃ temperature, through mechanical stirring and ultrasonic vibration, ceramic core can be removed from blade totally through 24～48 hours.
Silicon-base ceramic core of the present invention and preparation method thereof, by manufacturing of traditional silicon base ceramic core and removing process are improved, solved the manufacturing issue of R0110 heavy combustion engine II stage diverter blade with ceramic core, produced the ceramic core that meets the demands, and realized removing fast of ceramic core, for the precision casting of this blade is laid a good foundation.In order to solve the contradiction that ceramic core cracks and is out of shape in roasting process, the present invention has added a certain amount of porous shape fused silica powder to replace the use of parts of traditional fused silica powder in traditional fused silica powder.
Silicon-base ceramic core by the present invention's manufacturing, owing to added a certain amount of porous shape fused silica powder, and adopt the thickness of powder particles to arrange in pairs or groups, and the time of proper extension low temperature de-waxing phase and the whole temperature-time that burns, make to burn till to shrink to be controlled between 0～0.2%, solved the contradictory problems of crackle and distortion like this.Because the adding of porous shape fused silica powder, can effectively absorb the roasting stress in the roasting process, have a certain proportion of simultaneously than meal material formation framework, can reduce to burn till contraction like this, avoided the generation of crackle, also effectively control the distortion of core simultaneously, made satisfactory ceramic core.The porosity of the silicon-base ceramic core that this prepared goes out can reach 35～45%.
Traditional depoling technology does not have machinery and stirs and ultrasonic vibration.Because the porosity of silicon-base ceramic core of the present invention wants high than the porosity of traditional silicon base ceramic core, so help the quick infiltration of corrosive fluid, improved depoling speed, depoling technology of the present invention has increased mechanical stirring and ultrasonic vibration simultaneously, and High Temperature High Pressure all can accelerate depoling speed, can guarantee that R0110 heavy combustion engine II stage diverter blade ceramic core removes fast.
In a word, by to the improvement of traditional technology and the application of novel material novel method, invented this silicon-base ceramic core manufacturing process and quick removing process, produced satisfactory ceramic core, for the manufacturing of R0110 heavy combustion engine II stage diverter blade is laid a good foundation.
In addition, the invention provides the manufacture method of a kind of R0110 heavy combustion engine II stage diverter blade,, it is characterized in that processing parameter is by on wax-pattern, successively carrying out hanging, stucco, drying step acquisition repeatedly with shell:
Carry out roasting after the shell dewaxing that coating finishes, maturing temperature is 950 ℃～980 ℃, and soaking time is come out of the stove greater than 3h.
The difference and the advantage of process for making shell of the present invention and traditional process for making shell are:
1. technology of the present invention only adopts the tetraethyl silicate caking agent at the second layer, and traditional shell or all adopt the tetraethyl silicate caking agent, adopt alternative method (one deck tetraethyl silicate, one deck silicon sol), the purpose that technology of the present invention only adopts tetraethyl silicate caking agent and ammonia to do at the second layer is that the traditional shell of solution is to be penetrated into the first layer because of caking agent being coated with second and third layer, reach the first layer and wax-pattern because of wetting bad, and the shell that causes is heaved problem.Remainder layer can improve the hot strength of shell for the silicon sol caking agent.
2. technology of the present invention has twice reinforcement in the coating process, and is the tetraethyl silicate reinforcement, and traditional shell is the silicon sol reinforcement.Adopt twice reinforcement can improve the wet tenacity and the hot strength of shell, reduce shell rimose possibility in dewaxing and casting process.The employing tetraethyl silicate is strengthened, and can make the easier shell inside that is penetrated into of reinforcer, improves strengthening effect.
3. the preceding 8 layers of sanding material of technology of the present invention are emergy, and the back is two-layer to be the bastard coal stone sand, and purpose is to improve the high temperature amount of deflection and the intensity of shell, with the distortion at high temperature of control shell, guarantee to obtain the qualified blade of size.The back is two-layer to be to make the too high of the unlikely raising of intensity and make foundry goods generation decrepitation with the bastard coal stone sand, to obtain deformability preferably.
4. technology of the present invention is fine sand and medium sand for preceding 5 layers, and purpose is that the groove place of blade can be coated with completely fully, prevents because of the not fine and close phenomenon that runout takes place in the process of cast of this place's shell.And traditional shell directly is coated with the extension coarse sand since the 3rd, 4 layer, causes shell to be put up a bridge at the groove place, reduces intensity.
5. in the roasting stage of shell, the general soaking time of traditional shell gets final product greater than 30min, because the characteristics that II guide vane structure is special and size is big make the inner insufficient oxidizing fire of remaining wax material during easily because of dewaxing of shell form the generation of carbon distribution phenomenon.And processing requirement soaking time of the present invention is greater than 3h, and purpose is the abundant voloxidation of carbon distribution that makes shell inside, prevents from because of the carbon distribution moisture absorption on the core in inner surface of shell and shell expands shell and inner core to be cracked, and reduces intensity.
By the equiax crystal blade shell of prepared of the present invention, can obtain enough hot strengths and high high temperature amount of deflection and good deformability, remedied the deficiency of traditional shell, obtained the qualified II level guide vane of size.
On the basis that provides above-mentioned casting with R0110 heavy combustion engine II stage diverter blade core and shell, the present invention provides a kind of casting process of R0110 heavy combustion engine II stage diverter blade again, adopts teeming formula casting scheme, it is characterized in that:
--the insulation quilt thickness of blade shell outside thickens from the bottom up successively, by 10 ± 2mm to 40 ± 5mm, is coated with one deck shot in the bottom of blade shell, thickness 20～30mm simultaneously;
--a huge rising head has been adopted on the top of teeming formula pouring and riser systems, rising head volume 500～600cm
3, height 110～120mm;
--teeming temperature is controlled at 1450～1480 ℃, 6～8 seconds durations of pouring.
The present invention has changed the traditional direction blade and has adopted side to annotate the pouring and riser systems design concept of formulas, adopt have good cavity filling can, be easy to form consecutive solidification and the teeming formula scheme that obtains sound casting.When adopting the teeming scheme, method to traditional shell bag insulation quilt is improved, change bag insulation quilt mode in the past, insulation quilt thickness is thickened from the bottom up successively, so artificial formation consecutive solidification, avoided the bad formation big area of feeding shrinkage cavity that the constructional feature because of R0110 heavy combustion engine II stage diverter blade causes shortcoming.Be coated with the certain thickness shot of one deck simultaneously in the bottom of blade shell, form and force cooling, strengthen the effect of consecutive solidification from the bottom up.A huge rising head has been adopted on the top of teeming formula pouring and riser systems of the present invention, and huge metals capacity is arranged, and makes its final set, and increases pressure, increases the effect of feeding.By above measure, make blade cooling successively from bottom to up, strengthened the feeding effect.If Fig. 3.In order to make it produce good feeding effect, teeming temperature is controlled at 1450～1480 ℃, and temperature is crossed to hang down and caused cold shut easily and owe to cast defective, and the too high meeting of temperature causes large-area shrinkage cavity and loose.Need strict control the duration of pouring, when being lower than 6 seconds, ceramic core is fractureed, cause easily when being higher than 8 seconds and owe casting.By above to traditional direction blade pouring and riser systems design change and to the improvement of traditional technology, can produce the directional solidification castings of dense structure.
Description of drawings:
Fig. 1 forms the silicon-base ceramic core of its inner chamber for R0110 heavy combustion engine II stage diverter blade;
Fig. 2 is the profile of R0110 heavy combustion engine II stage diverter blade wax-pattern;
Fig. 3 is casting vanning signal.
Embodiment:
Embodiment 1
Porous shape fused silica powder porosity is 10～20%, and too thinless, and between 150 orders～180 orders, consumption is 30%.Adding granularity simultaneously is that consumption is 10% less than 320 purpose mullite mineralizers.The usage quantity of softening agent (10% beeswax, 3% polyethylene, all the other be the mixture of paraffin) is 18%.The granularity of using traditional fused silica powder is between 180 orders～240 orders.
With the above-mentioned raw materials thorough mixing, after pressing on the core machine, carry out roasting according to shape compression moulding shown in Figure 1, the ceramic core of hygrometric state will fully jolt ramming in filler before the roasting.Maturing temperature is 200 ± 10 ℃, 8h+400 ± 10 ℃, 8h+600 ± 10 ℃, 1h+900 ± 10 ℃, 1h+1200 ± 10 ℃, 10h.
Come out of the stove after the tetraethyl silicate High-Temperature Strengthening, phenolic aldehyde alcohol varnish low-temperature reinforcement, the prepared silicon-base ceramic core flawless that goes out does not have distortion.
Embodiment 2
Porous shape fused silica powder porosity is 10～20%, and too thinless, and between 150 orders～180 orders, consumption is 35%.Adding granularity simultaneously is that consumption is 15% less than 320 purpose mullite mineralizers.The usage quantity of softening agent (12% beeswax, 3% polyethylene, all the other be the mixture of paraffin) is 20% of a powder proportion.The granularity of using traditional fused silica powder is between 180 orders～240 orders.
With the above-mentioned raw materials thorough mixing, after pressing on the core machine, carry out roasting according to shape compression moulding shown in Figure 1, the ceramic core of hygrometric state will fully jolt ramming in filler before the roasting.Maturing temperature is 200 ± 10 ℃, 6h+400 ± 10 ℃, 6h+600 ± 10 ℃, 1h+900 ± 10 ℃, 1h+1200 ± 10 ℃, 8h.
Come out of the stove after the tetraethyl silicate High-Temperature Strengthening, phenolic aldehyde alcohol varnish low-temperature reinforcement, the prepared silicon-base ceramic core flawless that goes out does not have distortion.
Embodiment 3
Porous shape fused silica powder porosity is 10～20%, and too thinless, and between 150 orders～180 orders, consumption is 40%.Adding granularity simultaneously is that consumption is 10% less than 320 purpose mullite mineralizers.The usage quantity of softening agent (15% beeswax, 4% polyethylene, all the other be the mixture of paraffin) is 22% of a powder proportion.The granularity of using traditional fused silica powder is between 180 orders～240 orders.
With the above-mentioned raw materials thorough mixing, after pressing on the core machine, carry out roasting according to shape compression moulding shown in Figure 1, the ceramic core of hygrometric state will fully jolt ramming in filler before the roasting.Maturing temperature is 200 ± 10 ℃, 8h+400 ± 10 ℃, 8h+600 ± 10 ℃, 1h+900 ± 10 ℃, 1h+1200 ± 10 ℃, 10h.
Come out of the stove after the tetraethyl silicate High-Temperature Strengthening, phenolic aldehyde alcohol varnish low-temperature reinforcement, the prepared silicon-base ceramic core flawless that goes out does not have distortion.
Embodiment 4
Porous shape fused silica powder porosity is 10～20%, and too thinless, and between 150 orders～180 orders, consumption is 50%.Adding granularity simultaneously is that consumption is 15% less than 320 purpose mullite mineralizers.The usage quantity of softening agent (13% beeswax, 5% polyethylene, all the other be the mixture of paraffin) is 22% of a powder proportion.The granularity of using traditional fused silica powder is between 180 orders～240 orders.
With the above-mentioned raw materials thorough mixing, after pressing on the core machine, carry out roasting according to shape compression moulding shown in Figure 1, the ceramic core of hygrometric state will fully jolt ramming in filler before the roasting.Maturing temperature is 200 ± 10 ℃, 8h+400 ± 10 ℃, 8h+600 ± 10 ℃, 1h+900 ± 10 ℃, 1h+1200 ± 10 ℃, 10h.
Come out of the stove after the tetraethyl silicate High-Temperature Strengthening, phenolic aldehyde alcohol varnish low-temperature reinforcement, the prepared silicon-base ceramic core flawless that goes out does not have distortion.
Embodiment 5～8
On embodiment 1～4 silicon-base ceramic core basis, prepare R0110 heavy combustion engine II stage diverter blade wax-pattern by profile shown in Figure 2, with rising head and sprue cup combination; On the wax-pattern after the combination, make shell; Its coating process parameter is as table.
Carry out roasting after the shell dewaxing that coating finishes, maturing temperature is 950 ℃～980 ℃, and soaking time is come out of the stove greater than 3h.
Embodiment 9～12
Embodiment 5～8 is prepared shells according to vanning shown in Figure 3.
Material is the K4104 superalloy, refining temperature is 1550 ℃～1560 ℃, the formwork preheating temperature is 950 ℃～980 ℃, pour into a mould under the vacuum, vacuum tightness＜6.67Pa adopts teeming formula casting scheme, the insulation quilt thickness of blade shell outside thickens from the bottom up successively, by 10 ± 2mm to 40 ± 5mm, be coated with one deck shot in the bottom of blade shell, thickness 20mm simultaneously; A huge rising head has been adopted on the top of teeming formula pouring and riser systems, rising head volume 500cm
3, height 110mm; Teeming temperature is controlled at 1450～1480 ℃, 6 seconds durations of pouring.Leaf quality all reaches design requirements.
Embodiment 13～16
Embodiment 5～8 is prepared shells according to vanning shown in Figure 3.
Material is the K4104 superalloy, refining temperature is 1550 ℃～1560 ℃, the formwork preheating temperature is 950 ℃～980 ℃, pour into a mould under the vacuum, vacuum tightness＜6.67Pa adopts teeming formula casting scheme, the insulation quilt thickness of blade shell outside thickens from the bottom up successively, by 10 ± 2mm to 40 ± 5mm, be coated with one deck shot in the bottom of blade shell, thickness 30mm simultaneously; A huge rising head has been adopted on the top of teeming formula pouring and riser systems, rising head volume 600cm
3, height 120mm; Teeming temperature is controlled at 1450～1480 ℃, 8 seconds durations of pouring.Leaf quality all reaches design requirements.
Claims (2)
1. silicon-base ceramic core, it is characterized in that: the feedstock production that described core is made up of following weight per-cent forms:
Porous silica glass powder 30～50%;
Mullite mineralizer 10～15%;
Softening agent 18～22%;
The fused silica powder surplus;
Wherein
The porosity of porous silica glass powder is 10～20%, and granularity is between 150 orders～180 orders;
The granularity of mullite mineralizer is less than 320 orders;
The granularity of fused silica powder is between 180 orders～240 orders;
Softening agent is 10～15% beeswax, 3～5% polyethylene, all the other are the mixture of paraffin.
2. the preparation method of the described silicon-base ceramic core of claim 2, it is characterized in that: with the raw material thorough mixing, after using mould compression moulding on the pressure core machine, carry out roasting, maturing temperature is 200 ± 10 ℃, 4～8h+400 ± 10 ℃, 4～8h+600 ± 10 ℃, 1h+900 ± 10 ℃, 1h+1200 ± 10 ℃, 6～10h; Carrying out high and low temperature again strengthens.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103265296A (en) * | 2013-05-13 | 2013-08-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for reducing thermal deformation silicon-based ceramic core |
| CN104384452A (en) * | 2014-10-24 | 2015-03-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Preparation technique for thin-walled silica-based ceramic mold core |
| CN105499480A (en) * | 2015-11-30 | 2016-04-20 | 江苏金汇精铸陶瓷股份有限公司 | High-collapsibility ceramic mould core and preparation method thereof |
| CN106083005A (en) * | 2016-06-06 | 2016-11-09 | 上海交通大学 | High porosity easily removes silicon-base ceramic core preparation method |
| CN109734430A (en) * | 2019-03-20 | 2019-05-10 | 上海大学 | A kind of porous silicon-base ceramic core and preparation method thereof suitable for double wall blade |
| CN112250473A (en) * | 2020-10-20 | 2021-01-22 | 西安工程大学 | Gradient porous ceramic core and preparation method thereof |
| CN114656247A (en) * | 2020-12-23 | 2022-06-24 | 兴化市兴东铸钢有限公司 | Silicon-based ceramic core reinforcing method with excellent mechanical properties |
| CN114951551A (en) * | 2022-06-07 | 2022-08-30 | 中国航发航空科技股份有限公司 | Alternate hardening composite ceramic shell manufacturing method for aviation investment precision casting |
| CN115947606A (en) * | 2022-12-16 | 2023-04-11 | 中航装甲科技有限公司 | Water-soluble enhancer for silicon-based ceramic core and enhancing method |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103265296A (en) * | 2013-05-13 | 2013-08-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for reducing thermal deformation silicon-based ceramic core |
| CN104384452A (en) * | 2014-10-24 | 2015-03-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Preparation technique for thin-walled silica-based ceramic mold core |
| CN105499480A (en) * | 2015-11-30 | 2016-04-20 | 江苏金汇精铸陶瓷股份有限公司 | High-collapsibility ceramic mould core and preparation method thereof |
| CN106083005A (en) * | 2016-06-06 | 2016-11-09 | 上海交通大学 | High porosity easily removes silicon-base ceramic core preparation method |
| CN106083005B (en) * | 2016-06-06 | 2018-10-26 | 上海交通大学 | High porosity easily removes silicon-base ceramic core preparation method |
| CN109734430A (en) * | 2019-03-20 | 2019-05-10 | 上海大学 | A kind of porous silicon-base ceramic core and preparation method thereof suitable for double wall blade |
| CN112250473A (en) * | 2020-10-20 | 2021-01-22 | 西安工程大学 | Gradient porous ceramic core and preparation method thereof |
| CN114656247A (en) * | 2020-12-23 | 2022-06-24 | 兴化市兴东铸钢有限公司 | Silicon-based ceramic core reinforcing method with excellent mechanical properties |
| CN114951551A (en) * | 2022-06-07 | 2022-08-30 | 中国航发航空科技股份有限公司 | Alternate hardening composite ceramic shell manufacturing method for aviation investment precision casting |
| CN115947606A (en) * | 2022-12-16 | 2023-04-11 | 中航装甲科技有限公司 | Water-soluble enhancer for silicon-based ceramic core and enhancing method |
| CN115947606B (en) * | 2022-12-16 | 2024-03-12 | 中航装甲科技有限公司 | Water-soluble strengthening agent and strengthening method for silicon-based ceramic core |
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