CN100577324C - Casting method for heavy combustion engine II-stage diverter blade - Google Patents
Casting method for heavy combustion engine II-stage diverter blade Download PDFInfo
- Publication number
- CN100577324C CN100577324C CN200610134053A CN200610134053A CN100577324C CN 100577324 C CN100577324 C CN 100577324C CN 200610134053 A CN200610134053 A CN 200610134053A CN 200610134053 A CN200610134053 A CN 200610134053A CN 100577324 C CN100577324 C CN 100577324C
- Authority
- CN
- China
- Prior art keywords
- blade
- combustion engine
- shell
- ceramic core
- core
- 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.)
- Expired - Fee Related
Links
- 238000000034 method Methods 0.000 title claims abstract description 33
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 30
- 238000005266 casting Methods 0.000 title claims description 21
- 230000000630 rising effect Effects 0.000 claims description 10
- 238000009413 insulation Methods 0.000 claims description 7
- 238000000465 moulding Methods 0.000 abstract description 5
- 230000008859 change Effects 0.000 abstract description 3
- 230000006872 improvement Effects 0.000 abstract description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 abstract 2
- 229910052742 iron Inorganic materials 0.000 abstract 1
- 239000000919 ceramic Substances 0.000 description 50
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 24
- 239000000843 powder Substances 0.000 description 21
- 239000005350 fused silica glass Substances 0.000 description 15
- 230000008569 process Effects 0.000 description 15
- 238000005516 engineering process Methods 0.000 description 13
- 238000004519 manufacturing process Methods 0.000 description 13
- 208000037656 Respiratory Sounds Diseases 0.000 description 8
- 230000002787 reinforcement Effects 0.000 description 8
- 238000002360 preparation method Methods 0.000 description 7
- 238000005245 sintering Methods 0.000 description 7
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- 229910052863 mullite Inorganic materials 0.000 description 6
- 239000004014 plasticizer Substances 0.000 description 6
- 239000004698 Polyethylene Substances 0.000 description 5
- 235000013871 bee wax Nutrition 0.000 description 5
- 239000012166 beeswax Substances 0.000 description 5
- 239000007767 bonding agent Substances 0.000 description 5
- 238000000748 compression moulding Methods 0.000 description 5
- 239000000945 filler Substances 0.000 description 5
- 239000000203 mixture Substances 0.000 description 5
- 239000012188 paraffin wax Substances 0.000 description 5
- -1 polyethylene Polymers 0.000 description 5
- 229920000573 polyethylene Polymers 0.000 description 5
- 239000002994 raw material Substances 0.000 description 5
- 239000004576 sand Substances 0.000 description 5
- 238000007711 solidification Methods 0.000 description 5
- 230000008023 solidification Effects 0.000 description 5
- 238000005728 strengthening Methods 0.000 description 5
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 125000002485 formyl group Chemical class [H]C(*)=O 0.000 description 4
- 230000014759 maintenance of location Effects 0.000 description 4
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 description 4
- 238000003825 pressing Methods 0.000 description 4
- 239000002966 varnish Substances 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 3
- HEMHJVSKTPXQMS-UHFFFAOYSA-M Sodium hydroxide Chemical compound [OH-].[Na+] HEMHJVSKTPXQMS-UHFFFAOYSA-M 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 238000009826 distribution Methods 0.000 description 3
- 238000005495 investment casting Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 229910052710 silicon Inorganic materials 0.000 description 3
- 239000010703 silicon Substances 0.000 description 3
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 2
- 238000013019 agitation Methods 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 239000003245 coal Substances 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 230000002950 deficient Effects 0.000 description 2
- 230000003031 feeding effect Effects 0.000 description 2
- 238000011049 filling Methods 0.000 description 2
- 238000009415 formwork Methods 0.000 description 2
- 230000008595 infiltration Effects 0.000 description 2
- 238000001764 infiltration Methods 0.000 description 2
- 238000007670 refining Methods 0.000 description 2
- 239000004575 stone Substances 0.000 description 2
- 239000001993 wax Substances 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 229910021529 ammonia Inorganic materials 0.000 description 1
- 239000007864 aqueous solution Substances 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- IXSZQYVWNJNRAL-UHFFFAOYSA-N etoxazole Chemical compound CCOC1=CC(C(C)(C)C)=CC=C1C1N=C(C=2C(=CC=CC=2F)F)OC1 IXSZQYVWNJNRAL-UHFFFAOYSA-N 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 235000012054 meals Nutrition 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- 238000013022 venting Methods 0.000 description 1
- 238000004018 waxing Methods 0.000 description 1
- 238000009736 wetting Methods 0.000 description 1
Images
Landscapes
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
A molding method of II level diverter fins of a R0110 heavy combustion engine utilizes roof pouring style molding scheme, which is characterized in that the insulating blanket thickness of the outer portion of the fin shape casing is thickened from top to bottom, from 10+-2mm to 40+-5mm, simultaneously the bottom of the fin shape casing is covered with a layer of iron bolus at a thickness of 20-30mm, a roof pouring style dead system utilizes a huge dead head, the volume of the dead head is 500 to 600cm3, and the height of the dead head is 110-120mm, the molding temperature is controlled at 1405-1480 DEG C and the molding time is 6-8 seconds. Through the design change of a prior guiding fin dead system and the improvement of a prior craft, the invention is capable of producing casts with fine and close organizations.
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, appearance and size is big (to be of a size of 2～3 times of guide 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 labyrinth (as Fig. 1,2), the dimension precision requirement height.The structural design of this blade still belongs to initiative, aspect the casting preparation of blade, no matter is on the process conditions 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 guide vane ceramic core (see figure 1).Because the large scale 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 conventional 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 main cause that crackle and distortion produce is excessive the causing of the shrinkage factor 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 particularity of ceramic core, so traditional handicraft can't satisfy the production of this core at all.Secondly the ceramic core of traditional handicraft production also is faced with blade and pours the problem that the back ceramic core removes from blade.Because the design 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 liquid, can cause corrosion to the metal material 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 liquid to ceramic core inside, so influence depoling speed.
In addition, R0110 heavy combustion engine II stage diverter blade appearance and size 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 design 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 elevated temperature 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 design 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 elevated temperature strengths and high high temperature amount of deflection and good deformability with shell, and the deadweight deflection is little, can satisfy the instructions for use of casting R0110 heavy combustion engine II stage diverter blade.
The 3rd purpose of the present invention is to provide a kind of casting method 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 percentage forms:
Porous silica glass powder 30～50%;
Mullite mineralizer 10～15%;
Plasticizer 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;
Plasticizer 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: raw material is fully mixed, after using mould compression moulding on the pressure core machine, carry out roasting, sintering 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 HTHP depoling still, under the pressure of 0.4～0.5MPa, under 180～200 ℃ temperature, through mechanical agitation 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 hot investment 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 technology is prepared 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 liquid, improved depoling speed, depoling technology of the present invention has increased mechanical agitation and ultrasonic vibration simultaneously, and HTHP 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 handicraft and the application of new material new 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 technological parameter is by on wax-pattern, successively carrying out hanging, stucco, drying steps acquisition repeatedly with shell:
Carry out roasting after the shell dewaxing that coating finishes, sintering temperature is 950 ℃～980 ℃, and temperature retention 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 silester bonding agent at the second layer, and traditional shell or all adopt the silester bonding agent, adopt alternative method (one deck silester, one deck Ludox), the purpose that technology of the present invention only adopts silester bonding agent and ammonia to do at the second layer is that the traditional shell of solution is to be penetrated into ground floor because of bonding agent being coated with second and third layer, reach ground floor and wax-pattern because of wetting bad, and the shell that causes is heaved problem.Remainder layer can improve the elevated temperature strength of shell for the Ludox bonding agent.
2. technology of the present invention has twice reinforcement in the coating process, and is the silester reinforcement, and traditional shell is the Ludox reinforcement.Adopt twice reinforcement can improve the wet strength and the elevated temperature strength of shell, reduce the possibility that shell ftractures in dewaxing and casting process.The employing silester is strengthened, and can make the easier shell inside that is penetrated into of hardening agent, 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 temperature retention 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 technological requirement temperature retention 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 technology of the present invention preparation, can obtain enough elevated temperature 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 method 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 rising head has been adopted on the top of teeming formula pouring and riser systems, rising head volume 500～600cm
3, height 110～120mm;
---pouring 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 large tracts of land of feeding shrinkage cavity that the design 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, pouring 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 handicraft, 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.
The specific 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 use amount of plasticizer (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.
Above-mentioned raw materials is fully mixed, after pressing on the core machine according to shape compression moulding shown in Figure 1, carry out roasting, the ceramic core of hygrometric state will fully jolt ramming in filler before the roasting.Sintering temperature is 200 ± 10 ℃, 8h+400 ± 10 ℃, 8h+600 ± 10 ℃, 1h+900 ± 10 ℃, 1h+1200 ± 10 ℃, 10h.
Come out of the stove after the silester 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 use amount of plasticizer (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.
Above-mentioned raw materials is fully mixed, after pressing on the core machine according to shape compression moulding shown in Figure 1, carry out roasting, the ceramic core of hygrometric state will fully jolt ramming in filler before the roasting.Sintering temperature is 200 ± 10 ℃, 6h+400 ± 10 ℃, 6h+600 ± 10 ℃, 1h+900 ± 10 ℃, 1h+1200 ± 10 ℃, 8h.
Come out of the stove after the silester 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 use amount of plasticizer (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.
Above-mentioned raw materials is fully mixed, after pressing on the core machine according to shape compression moulding shown in Figure 1, carry out roasting, the ceramic core of hygrometric state will fully jolt ramming in filler before the roasting.Sintering temperature is 200 ± 10 ℃, 8h+400 ± 10 ℃, 8h+600 ± 10 ℃, 1h+900 ± 10 ℃, 1h+1200 ± 10 ℃, 10h.
Come out of the stove after the silester 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 use amount of plasticizer (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.
Above-mentioned raw materials is fully mixed, after pressing on the core machine according to shape compression moulding shown in Figure 1, carry out roasting, the ceramic core of hygrometric state will fully jolt ramming in filler before the roasting.Sintering temperature is 200 ± 10 ℃, 8h+400 ± 10 ℃, 8h+600 ± 10 ℃, 1h+900 ± 10 ℃, 1h+1200 ± 10 ℃, 10h.
Come out of the stove after the silester 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 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, sintering temperature is 950 ℃～980 ℃, and temperature retention 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 high temperature alloy, refining temperature is 1550 ℃～1560 ℃, the formwork preheat temperature is 950 ℃～980 ℃, pour into a mould under the vacuum, vacuum＜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 rising head has been adopted on the top of teeming formula pouring and riser systems, rising head volume 500cm
3, height 110mm; Pouring temperature is controlled at 1450～1480 ℃, 6 seconds durations of pouring.Leaf quality all reaches designing requirement.
Embodiment 13～16
Embodiment 5～8 is prepared shells according to vanning shown in Figure 3.
Material is the K4104 high temperature alloy, refining temperature is 1550 ℃～1560 ℃, the formwork preheat temperature is 950 ℃～980 ℃, pour into a mould under the vacuum, vacuum＜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 rising head has been adopted on the top of teeming formula pouring and riser systems, rising head volume 600cm
3, height 120mm; Pouring temperature is controlled at 1450～1480 ℃, 8 seconds durations of pouring.Leaf quality all reaches designing requirement.
Claims (1)
1, a kind of casting method of R0110 heavy combustion engine II stage diverter blade 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 rising head has been adopted on the top of teeming formula pouring and riser systems, rising head volume 500～600cm
3, height 110～120mm;
---pouring temperature is controlled at 1450～1480 ℃, 6～8 seconds durations of pouring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200610134053A CN100577324C (en) | 2006-10-26 | 2006-10-26 | Casting method for heavy combustion engine II-stage diverter blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200610134053A CN100577324C (en) | 2006-10-26 | 2006-10-26 | Casting method for heavy combustion engine II-stage diverter blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101168184A CN101168184A (en) | 2008-04-30 |
| CN100577324C true CN100577324C (en) | 2010-01-06 |
Family
ID=39389028
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200610134053A Expired - Fee Related CN100577324C (en) | 2006-10-26 | 2006-10-26 | Casting method for heavy combustion engine II-stage diverter blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100577324C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102836964A (en) * | 2012-08-23 | 2012-12-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Pouring system for blade casting with thin core and crown |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102784904B (en) * | 2012-07-27 | 2014-07-02 | 中国航空工业集团公司北京航空材料研究院 | Method for determining heat cracking tendency of directionally solidified column crystal high-temperature alloy |
| CN103551521B (en) * | 2013-11-14 | 2015-07-29 | 宁夏共享集团有限责任公司 | A kind of casting method of guide vane foundry goods |
| CN104308082B (en) * | 2014-10-29 | 2016-05-18 | 西安航空动力股份有限公司 | A kind of pouring procedure of hollow turborotor |
| CN104308076B (en) * | 2014-10-29 | 2016-09-07 | 西安航空动力股份有限公司 | The wax-pattern combination of the hollow turborotor of a kind of tetrad and fine casting method thereof |
| CN104439097A (en) * | 2014-11-10 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for solving penetrative porosity defect of high-temperature alloy expansion regulation sheet base plate |
| CN104999037B (en) * | 2015-08-21 | 2017-12-19 | 东方电气集团东方汽轮机有限公司 | A kind of running gate system and its precision casting molding method for thin-walled tubular piece |
| CN105499480B (en) * | 2015-11-30 | 2018-03-16 | 江苏金汇精铸陶瓷股份有限公司 | A kind of high collapsibility ceramic core and preparation method thereof |
| CN107755635A (en) * | 2017-09-12 | 2018-03-06 | 东方电气集团东方汽轮机有限公司 | A kind of method for solving combustion engine shrouded blade leaf top R angles fire check |
| CN107999691B (en) * | 2017-10-31 | 2019-11-22 | 中国航发北京航空材料研究院 | A Method for Preventing Deformation of Large Superalloy Castings |
| CN108246976B (en) * | 2017-12-22 | 2020-06-16 | 东方电气集团东方汽轮机有限公司 | Dewaxing method for ceramic shell |
| CN108176817B (en) * | 2018-01-10 | 2019-09-03 | 中国航发北京航空材料研究院 | A porosity control method for a slender thin-wall crowned equiaxed grain cast turbine blade |
| CN109550897A (en) * | 2018-11-22 | 2019-04-02 | 沈阳航发精密铸造有限公司 | A method of it eliminating large-scale conjuncted blade blade and listrium switching R part is loose |
| 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 |
| CN114160758B (en) * | 2021-12-08 | 2024-01-23 | 中国航发南方工业有限公司 | Pouring system of double-layer bidirectional integral director casting and casting forming method thereof |
| CN114216426B (en) * | 2021-12-08 | 2024-07-12 | 中国航发南方工业有限公司 | Virtual calculation and assembly device and method for throat area of aeroengine guider |
-
2006
- 2006-10-26 CN CN200610134053A patent/CN100577324C/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102836964A (en) * | 2012-08-23 | 2012-12-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Pouring system for blade casting with thin core and crown |
| CN102836964B (en) * | 2012-08-23 | 2014-08-06 | 沈阳黎明航空发动机(集团)有限责任公司 | Pouring system for blade casting with thin core and crown |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101168184A (en) | 2008-04-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100577324C (en) | Casting method for heavy combustion engine II-stage diverter blade | |
| CN101168485A (en) | Silicon-base ceramic core and preparation thereof | |
| CN104475682B (en) | A kind of heat resisting cast steel thin-walled turbine case investment pattern precision casting method based on combination type wax-pattern | |
| CN100506428C (en) | A method of directly making cores in narrow slots and blind holes of wax models | |
| CN107245640B (en) | Preparation method and pouring system of conical main shaft for wind power | |
| CN109175307B (en) | 3D printing sand mold antigravity casting forming method | |
| CN100497246C (en) | Method for manufacturing casing of heavy combustion engine II-stage diverter blade | |
| CN102717032B (en) | A precision casting method for automobile turbocharger housing parts | |
| CN101767193B (en) | A Process Method for Eliminating Porosity of Superalloy Thick and Large Castings | |
| KR100801970B1 (en) | Tools for the production of casting components, methods of producing the tools and methods of producing the casting components | |
| CN103212672A (en) | Method for casting low speed diesel engine cylinder cap for large cylinder diameter boat | |
| CN101693282A (en) | Method for producing voltage-bearing aluminum alloy tank body of ultra-high voltage switch by V-process | |
| CN103464690A (en) | Manufacturing method of ceramic mold of monocrystal turbine blade | |
| CN102974748A (en) | Precise casting method of ceramic mould of turbine casing, namely critical component of heavy-duty gas turbine | |
| CN105057593A (en) | Investment casting technology for copper alloy casting | |
| CN103008547A (en) | Resin sand shell mold casting method of automotive turbocharger shell | |
| CN109365749A (en) | Precision-investment manufactures vacuum-thermoform production technology | |
| CN113967722A (en) | Casting method of hydraulic casting | |
| CN108015225A (en) | A kind of method for casting aluminium alloy of composite mould | |
| CN110640085A (en) | Investment casting process for hollow casting | |
| US11654476B2 (en) | Hybrid core for manufacturing of castings | |
| CN113976824A (en) | Method for preventing mixed crystals from being generated at free end of core of conjoined single crystal guide blade | |
| CN105537526A (en) | Forming method of flame-retarding insulating riser | |
| CN102397986A (en) | Method for preparing metal grinding ball die by using ceramic model | |
| US4605057A (en) | Process for producing core for casting |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100106 Termination date: 20141026 |
|
| EXPY | Termination of patent right or utility model |