CN104353785B - A kind of directional solidification blade wax-pattern combination inserted chassis and preparation method thereof - Google Patents
A kind of directional solidification blade wax-pattern combination inserted chassis and preparation method thereof Download PDFInfo
- Publication number
- CN104353785B CN104353785B CN201410611972.4A CN201410611972A CN104353785B CN 104353785 B CN104353785 B CN 104353785B CN 201410611972 A CN201410611972 A CN 201410611972A CN 104353785 B CN104353785 B CN 104353785B
- Authority
- CN
- China
- Prior art keywords
- wax
- rosette
- chassis
- nonmetal
- directional solidification
- 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.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
- B22C7/02—Lost patterns
Abstract
It is an object of the invention to the deficiency existed for existing directional solidification blade wax-pattern combination chassis technology of preparing, it is provided that a kind of directional solidification blade wax-pattern combination inserted chassis and preparation method thereof.This chassis is the nonmetal disk identical by diameter and rosette forms；Uniform 6～36 the column type projections of nonmetal lower disk surface, are provided with through hole in nonmetal disc centre；Rosette is the cylinder that a diameter is identical with above-mentioned nonmetal disk diameter, and lower surface is provided with 6～36 petal-shaped grooves, annulus and reinforcement, and center is provided with through the screw thread of rosette, and rosette is additionally provided with several through hole.The preparation method simultaneously additionally providing this chassis.The chassis deformation of this directional solidification blade wax-pattern combination is little, dewaxing is fast, environmental protection, lean.In addition the shell prepared by this chassis, need not polish bottom shell before shell shove charge is poured into a mould, operating efficiency and environmental protection can be greatly improved, and shell does not rise shell, not easily bleed-out simultaneously, can improve casting pouring qualification rate.
Description
Technical field
The invention belongs to model casting field, particularly to a kind of directional solidification blade wax-pattern combination metal and nonmetal inlaid formula chassis and preparation method thereof.
Background technology
For adapting to the growth requirement of aviation aircraft, the thrust-weight ratio of aero-engine need to be improved constantly.Current settling mode is fuel gas temperature and the cooling structure improving blade before raising aero-turbine.Manufacturing from initial isometry polycrystalline developer blade to directional solidification cylindrulite blade and the single crystal blade with complicated air cooling passage of blade.It is known that, the commonly used HRS method of directional solidification blade of China's present stage is prepared, its process underdraws as follows: be placed on by directional solidification blade shell on cylindrical water mold, poured into a mould by upper shifting after shell is put into heater and is heated to uniform temperature by cylindrical water mold, after static a period of time, by moving down cylindrical water mold, shell is moved to from heater and baffle plate casting mold room, take out casting mold, directional solidification blade after shelling, can be obtained.When generally carrying out wax-pattern combination in directional solidification blade wax-pattern clustered operation, employing is the solid chassis prepared by F102 Colophonium powder mould material.There is a lot of shortcoming in this chassis, as 1. this chassis is all produced in batches, the resting period is long, yielding；2. this chassis is solid chassis prepared by F102 Colophonium powder mould material, easily occurs the shell phenomenon that rises during dewaxing.And the top planes on the chassis that directional solidification blade ceramic shell base plane uses when just being combined by wax-pattern is formed, if chassis top planes is uneven, the base plane of the shell after then preparing also can be uneven, the shell that now bottom is uneven is placed on the water mold of directional crystallization furnace, gap will be produced, during cast, the easy bleed-out of shell.In order to avoid the generation of this situation, production scene is intended on grinding table to polish bottom shell before shell shove charge is poured into a mould, gapless or small-gap suture between shell base plane and water mold upper surface during to reach to be arranged on water mold shell.But, substantial amounts of dust can be brought in production scene by this operational approach, thus causing site environment to pollute, if grind not in place bottom shell, little, damage when shell is greatly then poured into a mould and bleed-out often occurs, in addition, the manufacturing expense of directional solidification blade is expensive, any one little details goes wrong, and all can bring bigger economic loss, it is therefore desirable to the chassis of existing directional solidification blade wax-pattern combination is carried out creationary technological improvement.
Summary of the invention
It is an object of the invention to the deficiency existed for existing directional solidification blade wax-pattern combination chassis technology of preparing, it is provided that a kind of directional solidification blade wax-pattern combination inserted chassis and preparation method thereof.This chassis is metal and nonmetal inlaid structure, and preparation method is simple to operation so that the chassis deformation of directional solidification blade wax-pattern combination is little, dewaxing is fast, environmental protection, lean.In addition the shell prepared by this chassis, need not polish bottom shell before shell shove charge is poured into a mould, operating efficiency and environmental protection can be greatly improved, and shell does not rise shell, not easily bleed-out simultaneously, can improve casting pouring qualification rate.
Inserted chassis is used in a kind of directional solidification blade wax-pattern combination, is a diameterThe cylinder of high 8mm～15mm, this cylinder is made up of the identical nonmetal disk of diameter and rosette；
Wherein, described nonmetal disk is a diameterThe cylinder of high 0.5mm～3mm；Nonmetal disk upper surface is plane, lower surface keep to the side 15mm～25mm place, along disc radius direction, uniform 6～36 diameters areThe column type that height is 4mm～6mm is protruding, and being provided with diameter in nonmetal disc centre isThrough hole；Optimum is and nonmetal lower disk surface joint rounding R0.5～R1 protruding at column type；
Described rosette is that diameter is identical with above-mentioned nonmetal disk diameter, the cylinder of high 6.5mm～12mm；Rosette upper surface is plane, lower surface is provided with 6～36 petal-shaped grooves, it it is the annulus that external diameter is identical with metal disc diameter outside groove, annular width 10mm～14mm, it it is reinforcement between adjacent grooves, reinforcement width 5mm～7mm, height 6mm～7mm, optimum mode is the intersection rounding R1～R5 of the intersection at reinforcement and annulus and adjacent said rib；Rosette center is provided with through M6～M10 screw thread of disk, rosette is additionally provided with several through hole, the diameter of through hole, number are corresponding with the diameter of the column type of above-mentioned nonmetal disk projection, number and position with position, optimum is described through hole has a rounding at rosette upper surface, and rounding angle is protruding with above-mentioned column type and nonmetal lower disk surface joint rounding angle is identical；
Described nonmetal disk embeds through hole from the upper surface of described rosette by the column type of lower surface is protruding, makes the two combine；
Wherein, the material of described nonmetal disk be F28-44B, F102 Colophonium powder mould material, 66#、62#、58#、60#、52#In filling wax；
The material of described rosette is described metal material is the light metals such as aluminum alloy series, magnesium alloy series and almag series, such as commercial-purity aluminium: 1A99,1A97,1A95,1A80,1A50；Rust-preventing aluminum alloy 5A02,5A03,5A05,5A30；Duralumin: 2A01,2A11,2A12,2B16；Wrought aluminium: LD2 (6A02), LD2-1 (6B02), LD2-2 (6070), LD30 (6061), LD31 (6063), LD11 (4A11), LD9 (2A90), LD8 (2A80), LD7 (2A70), LD10 (2A14), LD5 (2A50) etc.；Superduralumin 7A09；Cast aluminium alloy gold: ZAlSi7Mn, ZAlSi12, ZAlSi2Cu2Mg1, ZAlSi5Cu1Mg, ZAlCu5Mn, ZAlCu5MnCdVA, ZAlMg10, ZAlMg5Si；Mg-Al system, Mg-Zn system, Mg-Re system alloy, such as cast magnesium alloy: ZM2, ZM5, ZM6 etc.；And wrought magnesium alloy and the same standard GB/T of magnesium base composite material, its trade mark and chemical composition/T5153-2003 record.
Present invention also offers a kind of directional solidification blade wax-pattern combination preparation method on inserted chassis, comprise the steps:
1, will be placed in wax injection mould by the rosette of metal material said structure after Precision Machining, and by mould and die preheating to 25 DEG C～35 DEG C, wax injection mould inner wall size is diameterHigh 8mm～15mm；
2, filling wax is put in the wax storage of wax injector and be heated to 75 DEG C～85 DEG C, stir, and the processing parameter setting that wax injector is suppressed wax-pattern is: clamping pressure is 4MPa～5MPa, template preheating temperature is 31 DEG C～34 DEG C, casting temperature is 68 DEG C～80 DEG C, injection pressure is 0.6MPa～2.0MPa, the dwell time is 50s～100s；
3, wax injection mould is placed in the template of wax injector, wax injector will fill wax injection in the upper surface and 6～36 through holes of the rosette in wax injection mould, and avoid being filled into bottom rosette by filling wax, side and middle part are threaded part, end-of-fill starts pressurize；After the dwell time of setting to be achieved, taking out rosette and be compressed on wax-pattern thereon, can obtain above-mentioned directional solidification blade wax-pattern combination and use inserted chassis, namely wax-pattern is the nonmetal integrated disc portions on chassis；
Wherein, described metal material is the light metals such as aluminum alloy series, magnesium alloy series and almag series, such as commercial-purity aluminium: 1A99,1A97,1A95,1A80,1A50；Rust-preventing aluminum alloy 5A02,5A03,5A05,5A30；Duralumin: 2A01,2A11,2A12,2B16；Wrought aluminium: LD2 (6A02), LD2-1 (6B02), LD2-2 (6070), LD30 (6061), LD31 (6063), LD11 (4A11), LD9 (2A90), LD8 (2A80), LD7 (2A70), LD10 (2A14), LD5 (2A50) etc.；Superduralumin 7A09；Cast aluminium alloy gold: ZAlSi7Mn, ZAlSi12, ZAlSi2Cu2Mg1, ZAlSi5Cu1Mg, ZAlCu5Mn, ZAlCu5MnCdVA, ZAlMg10, ZAlMg5Si；Mg-Al system, Mg-Zn system, Mg-Re system alloy, such as cast magnesium alloy: ZM2, ZM5, ZM6 etc.；And wrought magnesium alloy and the same standard GB/T of magnesium base composite material, its trade mark and chemical composition/T5153-2003 record；Fill wax be F28-44B, F102 Colophonium powder mould material, 66#、62#、58#、60#、52#Deng in temperature wax, high temperature wax.
Accompanying drawing explanation
Fig. 1 is the directional solidification blade wax-pattern combination schematic perspective view on inserted chassis；
Wherein, 1. nonmetal disk, 2. rosette；
Fig. 2 is the directional solidification blade wax-pattern combination structure chart on inserted chassis；
Wherein, the top view that Fig. 2 (a) is chassis；The upward view that Fig. 2 (b) is chassis；
Fig. 3 is the top view sectional view along E-E direction on Fig. 2 (a) chassis；
Fig. 4 is the upward view sectional view along F-F direction on Fig. 2 (b) chassis；
Fig. 5 is the structure chart of nonmetal disk；
Wherein, Fig. 5 (c) is the top view of nonmetal disk；Fig. 5 (d) is the upward view of nonmetal disk；
3. column type is protruding, 4. center through hole；
Fig. 6 is the top view sectional view along C-C direction of the nonmetal disk of Fig. 5 (c)；
Fig. 7 is the upward view sectional view along D-D direction of the nonmetal disk of Fig. 5 (d)；
Fig. 8 is the structure chart of rosette；
Wherein, the top view that Fig. 8 (e) is rosette；The upward view that Fig. 8 (f) is rosette；
5. groove, 6. annulus, 7. reinforcement, 8. center screw thread, 9. through hole；
Fig. 9 is the top view sectional view along A-A direction of Fig. 8 (e) rosette；
Figure 10 is the top view sectional view along B-B direction of Fig. 8 (e) rosette；
Figure 11 is the schematic perspective view of rosette.
Detailed description of the invention
Wax injector used in embodiment is that MPI company of the U.S. produces, model MPI55Series, 55-40-30.
Embodiment 1
Inserted chassis is used in a kind of directional solidification blade wax-pattern combination, as shown in Fig. 1～11, is a diameterThe cylinder of high 8mm～15mm, this cylinder is made up of the identical nonmetal disk 1 of diameter and rosette 2；
Wherein, described nonmetal disk 1 is diameterThe cylinder of high 0.5mm～3mm；Nonmetal disk upper surface is plane, lower surface keep to the side 15mm～25mm place, along disc radius direction, uniform 6～36 diameters areHeight is the column type projection 3 of 4mm～6mm, is provided with diameter at nonmetal disk 1 center and isCenter through hole 4, at column type protruding 3 and nonmetal lower disk surface joint rounding R0.5～R1；
Described rosette 2 is that diameter is identical with nonmetal disk 1 diameter, the cylinder of high 6.5mm～12mm；Rosette upper surface is plane, rosette lower surface has 6～36 petal-shaped grooves 5, it it is the annulus 6 that external diameter is identical with rosette 2 diameter outside groove 5, width 10mm～the 14mm of annulus 6, it it is reinforcement 7 between adjacent grooves, width 5mm～the 7mm of reinforcement 7, height 6mm～7mm, at the intersection rounding R1～R5 of the intersection of reinforcement 7 and annulus 6 and adjacent said rib；Rosette 2 center is provided with through M6～M10 center screw thread 8 of rosette, rosette is additionally provided with several through hole 9, the diameter of through hole, number are corresponding with the diameter of column type projection 3 of nonmetal disk 1, number and position with position, through hole 9 has rounding at the upper surface place of rosette 2, and rounding angle is identical with nonmetal disk 1 lower surface joint rounding angle with above-mentioned column type protruding 3；
Described nonmetal disk 1 is embedded through hole 9 from the upper surface of described rosette 2 by the column type projection 3 of lower surface, makes the two combine；
The material of described nonmetal disk be F28-44B, F102 Colophonium powder mould material, 66#、62#、58#、60#、52#In filling wax；
The material of described rosette is described metal material is the light metals such as aluminum alloy series, magnesium alloy series and almag series, such as commercial-purity aluminium: 1A99,1A97,1A95,1A80,1A50；Rust-preventing aluminum alloy 5A02,5A03,5A05,5A30；Duralumin: 2A01,2A11,2A12,2B16；Wrought aluminium: LD2 (6A02), LD2-1 (6B02), LD2-2 (6070), LD30 (6061), LD31 (6063), LD11 (4A11), LD9 (2A90), LD8 (2A80), LD7 (2A70), LD10 (2A14), LD5 (2A50) etc.；Superduralumin 7A09；Cast aluminium alloy gold: ZAlSi7Mn, ZAlSi12, ZAlSi2Cu2Mg1, ZAlSi5Cu1Mg, ZAlCu5Mn, ZAlCu5MnCdVA, ZAlMg10, ZAlMg5Si；Mg-Al system, Mg-Zn system, Mg-Re system alloy, such as cast magnesium alloy: ZM2, ZM5, ZM6 etc.；And wrought magnesium alloy and the same standard GB/T of magnesium base composite material, its trade mark and chemical composition/T5153-2003 record.
The using method on this chassis is identical with common wax-pattern chassis, the graining section of directional solidification blade wax-pattern is distributed on chassis according to the number of the uniform through hole of chassis lower surface in embodiment 1, then graining section is welded on the nonmetal disk upper surface on chassis, the bottom position of graining section must above the surface of through hole or adjacent through-holes, the other end of blade module is burn-on corresponding running channel and cup wax-pattern, namely one group of directional solidification blade wax-pattern module it is combined into, then carry out module and clean oil removing, finally it is oriented solidification blade shell manufacturing process, when coating shell, only coat the nonmetal disk upper surface part on chassis, do not coat the rosette part on chassis.After Shell Preparation completes, dewaxing, now the non-metallic part on chassis removes because of thawing, and metal part is because of non-metallic part elimination thus producing gap with shell simultaneously, also comes off in the lump and takes out, and the rosette part on chassis is reusable after taking out.Finally the bottom of shell is directly placed on water mold, poured into a mould by upper shifting after shell is put into heater and is heated to uniform temperature by cylindrical water mold, after static a period of time, by moving down cylindrical water mold, shell is moved to from heater and baffle plate casting mold room, take out casting mold, directional solidification blade after shelling, can be obtained.Owing to shell is to make on covert very little chassis, therefore shell base plane is also flat, without producing gap when being placed on water mold, it is not necessary to what carry out routine polishes the operation bottom shell at grinding table, and when pouring into a mould, shell will not bleed-out.
Embodiment 2
The directional solidification blade wax-pattern combination of embodiment 1 by the preparation method on inserted chassis is:
1, will be placed in wax injection mould by wrought aluminium LD8 rosette 1 after Precision Machining, and by mould and die preheating to 25 DEG C～35 DEG C, wax injection mould inner wall size is diameterHigh 8mm～15mm；
2, filling wax F28-44B is put into MPI wax injector wax storage is heated to 75 DEG C～85 DEG C, stir, and the processing parameter setting that MPI wax injector is suppressed wax-pattern is: clamping pressure is 4MPa～5MPa, template preheating temperature is 31 DEG C～34 DEG C, casting temperature is 68 DEG C～80 DEG C, injection pressure is 0.6MPa～2.0MPa, the dwell time is 50s～100s；
3, soak with appropriate methyl-silicone oil parting compound with gauze or hairbrush, uniformly embrocate on the inner surface of wax injection mould, rosette 1 outer surface and uniform through-hole inner surface not brush methyl-silicone oil parting compound；Wax injection mould is placed in the template of MPI wax injector, wax injector will fill wax injection in the upper surface and 6～36 through holes of the rosette in wax injection mould, and avoid being filled into bottom rosette by filling wax, rosette side and middle part are threaded part, end-of-fill starts pressurize；After the dwell time of setting to be achieved, taking out rosette and be compressed on wax-pattern thereon, can obtain above-mentioned directional solidification blade wax-pattern combination and use inserted chassis, namely wax-pattern is the nonmetal integrated disc portions on chassis.
Embodiment 3
1, by by cast magnesium alloy ZM5 diameter after Precision MachiningThe rosette of high 12mm is placed in wax injection mould, and by mould and die preheating to 25 DEG C～28 DEG C, wax injection mould inner wall size is diameterHigh 15mm；
2, filling wax F102 Colophonium powder mould material is put into MPI wax injector wax storage is heated to 75 DEG C～80 DEG C, stir, and the processing parameter setting that MPI wax injector is suppressed wax-pattern is: clamping pressure is 5MPa, template preheating temperature is 31 DEG C～32 DEG C, casting temperature is 68 DEG C～75 DEG C, injection pressure is 1.5MPa～2.0MPa, the dwell time is 50s；
3, soak with appropriate methyl-silicone oil parting compound with gauze or hairbrush, uniformly embrocate on the inner surface of wax injection mould, rosette outer surface and uniform through-hole inner surface not brush methyl-silicone oil parting compound；Wax injection mould is placed in the template of MPI wax injector, wax injector will fill wax injection in the upper surface and 6～36 through holes of the rosette in wax injection mould, and avoid being filled into bottom rosette by filling wax, side and middle part are threaded part, end-of-fill starts pressurize；After the dwell time of setting to be achieved, taking out rosette and be compressed on wax-pattern thereon, can obtain above-mentioned directional solidification blade wax-pattern combination and use inserted chassis, namely wax-pattern is the nonmetal integrated disc portions on chassis.
Embodiment 4
1, by by Cast aluminium alloy gold ZAlSi7Mn diameter after Precision MachiningThe rosette of high 7mm is placed in wax injection mould, and by mould and die preheating to 32 DEG C～35 DEG C, wax injection mould inner wall size is diameterHigh 8mm；
2, wax 58 will be filled#Put into and MPI wax injector wax storage is heated to 80 DEG C～85 DEG C, stir, and the processing parameter setting that MPI wax injector is suppressed wax-pattern is: clamping pressure is 4MPa, template preheating temperature is 33 DEG C～34 DEG C, casting temperature is 75 DEG C～80 DEG C, injection pressure is 0.6MPa～1.0MPa, the dwell time is 100s；
3, soak with appropriate methyl-silicone oil parting compound with gauze or hairbrush, uniformly embrocate on the inner surface of wax injection mould, rosette outer surface and uniform through-hole inner surface not brush methyl-silicone oil parting compound；Wax injection mould is placed in the template of MPI wax injector, wax injector will fill wax injection in the upper surface and 6～36 through holes of the rosette in wax injection mould, and avoid being filled into bottom rosette by filling wax, side and middle part are threaded part, end-of-fill starts pressurize；After the dwell time of setting to be achieved, taking out rosette and be compressed on wax-pattern thereon, can obtain above-mentioned directional solidification blade wax-pattern combination and use inserted chassis, namely wax-pattern is the nonmetal integrated disc portions on chassis.
The metal material of rosette can also be the light metals such as other aluminum alloy series, magnesium alloy series and almag series, such as commercial-purity aluminium: 1A99,1A97,1A95,1A80,1A50；Rust-preventing aluminum alloy 5A02,5A03,5A05,5A30；Duralumin: 2A01,2A11,2A12,2B16；Wrought aluminium: LD2 (6A02), LD2-1 (6B02), LD2-2 (6070), LD30 (6061), LD31 (6063), LD11 (4A11), LD9 (2A90), LD7 (2A70), LD10 (2A14), LD5 (2A50) etc.；Superduralumin 7A09；Cast aluminium alloy gold: ZAlSi12, ZAlSi2Cu2Mg1, ZAlSi5Cu1Mg, ZAlCu5Mn, ZAlCu5MnCdVA, ZAlMg10, ZAlMg5Si；Mg-Al system, Mg-Zn system, Mg-Re system alloy, such as cast magnesium alloy: ZM2, ZM6 etc.；And wrought magnesium alloy and the same standard GB/T of magnesium base composite material, its trade mark and chemical composition/T5153-2003 record；
Filling wax can also be 66#、62#、60#、52#Deng in temperature wax, high temperature wax.
Claims (10)
1. inserted chassis is used in directional solidification blade wax-pattern combination, it is characterised in that this chassis is a cylinder, and this cylinder is made up of the identical nonmetal disk of diameter and rosette；
Wherein, described nonmetal disk is a cylinder；Nonmetal disk upper surface is plane, lower surface keep to the side place, along disc radius direction, uniform several column types are protruding, and are provided with through hole in nonmetal disc centre；
Described rosette is the cylinder that a diameter is identical with above-mentioned nonmetal disk diameter；Rosette upper surface is plane, and lower surface is provided with 6～36 petal-shaped grooves, is the annulus that external diameter is identical with metal disc diameter outside groove, is reinforcement between adjacent grooves；The screw thread of disk it is provided with through at rosette center；Rosette is additionally provided with several through hole；
Described nonmetal disk embeds through hole from the upper surface of described rosette by the column type of lower surface is protruding, makes the two combine.
2. inserted chassis is used in a kind of directional solidification blade wax-pattern combination according to claim 1, it is characterised in that described chassis is of a size of diameterHigh 8mm～15mm；Described nonmetal disk size is diameterHigh 0.5mm～3mm；Described rosette is of a size of diameterHigh 6.5mm～12mm.
3. inserted chassis is used in a kind of directional solidification blade wax-pattern combination according to claim 1, it is characterised in that the described column type projection on nonmetal disk is 6～36, and submarginal distance is 15mm～25mm, and it is of a size of diameterHigh 4mm～6mm；The through-hole diameter of described nonmetal disc centre is
4. inserted chassis is used in a kind of directional solidification blade wax-pattern combination according to claim 1, it is characterised in that the described annular width on rosette is 10mm～14mm；Reinforcement width 5mm～7mm, height 6mm～7mm.
5. inserted chassis is used in a kind of directional solidification blade wax-pattern combination according to claim 1, it is characterised in that the screw thread at described rosette center is M6～M10；Through hole on described rosette is corresponding with the column type projection of above-mentioned nonmetal disk.
6. inserted chassis is used in a kind of directional solidification blade wax-pattern combination according to claim 1, it is characterised in that protruding and nonmetal lower disk surface joint rounding R0.5～R1 at described column type；The described through hole on rosette has a rounding at rosette upper surface, and rounding angle is protruding with above-mentioned column type and nonmetal lower disk surface joint rounding angle is identical.
7. inserted chassis is used in a kind of directional solidification blade wax-pattern combination according to claim 1, it is characterised in that at the intersection rounding R1～R5 of the intersection of described reinforcement and annulus and adjacent said rib.
8. inserted chassis is used in a kind of directional solidification blade wax-pattern combination according to claim 1, it is characterised in that the material of described rosette is the light metal of aluminum alloy series, magnesium alloy series or almag series；The material of described nonmetal disk be F28-44B, F102 Colophonium powder mould material, 66#、62#、58#、60#Or 52#Fill wax.
9. the directional solidification blade wax-pattern combination preparation method on inserted chassis, it is characterised in that comprise the steps:
(1) will be placed in wax injection mould by metal material rosette after Precision Machining, and by mould and die preheating to 25 DEG C～35 DEG C, wax injection mould inner wall size is diameterHigh 8mm～15mm；
(2) filling wax is put in the wax storage of wax injector and be heated to 75 DEG C～85 DEG C, stir, and set the technological parameter of wax injector compacting wax-pattern；
(3) wax injection mould is placed in the template of wax injector, wax injector will fill wax injection in the upper surface and 6～36 through holes of the rosette in wax injection mould, and avoid being filled into bottom rosette by filling wax, side and middle part are threaded part, start pressurize after end-of-fill；After the dwell time of setting to be achieved, take out rosette and be compressed on wax-pattern thereon, the combination of directional solidification blade wax-pattern can be obtained and use inserted chassis.
10. a kind of directional solidification blade wax-pattern according to claim 9 combination preparation method on inserted chassis, it is characterized in that, the processing parameter setting described in step (2) is: clamping pressure is 4MPa～5MPa, template preheating temperature is 31 DEG C～34 DEG C, casting temperature is 68 DEG C～80 DEG C, injection pressure is 0.6MPa～2.0MPa, the dwell time is 50s～100s.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410611972.4A CN104353785B (en) | 2014-10-31 | 2014-10-31 | A kind of directional solidification blade wax-pattern combination inserted chassis and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410611972.4A CN104353785B (en) | 2014-10-31 | 2014-10-31 | A kind of directional solidification blade wax-pattern combination inserted chassis and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104353785A CN104353785A (en) | 2015-02-18 |
| CN104353785B true CN104353785B (en) | 2016-06-29 |
Family
ID=52521143
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410611972.4A Active CN104353785B (en) | 2014-10-31 | 2014-10-31 | A kind of directional solidification blade wax-pattern combination inserted chassis and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104353785B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106392008B (en) * | 2016-10-17 | 2018-09-25 | 株洲中航动力精密铸造有限公司 | Multichannel casting runner mould |
| CN107790623B (en) * | 2017-10-27 | 2019-03-22 | 中国航发南方工业有限公司 | A kind of combined method of hot investment casting assembling wax pattern |
| CN107877807A (en) * | 2017-11-10 | 2018-04-06 | 中国航发动力股份有限公司 | A kind of directional solidification casting crystallization chassis manufacture method |
| CN109317613B (en) * | 2018-11-16 | 2020-09-29 | 中国科学院金属研究所 | Shell preparation method for preventing bending deformation of directional test bar |
| CN111992677A (en) * | 2020-08-25 | 2020-11-27 | 贵州安吉航空精密铸造有限责任公司 | Integral casting forming method for special-shaped part |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8347947B2 (en) * | 2009-02-17 | 2013-01-08 | United Technologies Corporation | Process and refractory metal core for creating varying thickness microcircuits for turbine engine components |
| CN202963369U (en) * | 2012-02-01 | 2013-06-05 | 大同北方天力增压技术有限公司 | Split type wax mold die of integral nozzle ring |
| CN103143678B (en) * | 2013-04-01 | 2015-02-18 | 东方电气集团东方汽轮机有限公司 | Formwork for optimizing directional columnar crystal structure of high-temperature alloy blade |
| CN103894547B (en) * | 2014-03-26 | 2016-03-23 | 东方电气集团东方汽轮机有限公司 | With the casting method of listrium Blade roughcast |
| CN204247909U (en) * | 2014-10-31 | 2015-04-08 | 沈阳黎明航空发动机(集团)有限责任公司 | Inserted chassis is used in a kind of directional solidification blade wax-pattern combination |
-
2014
- 2014-10-31 CN CN201410611972.4A patent/CN104353785B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN104353785A (en) | 2015-02-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104353785B (en) | A kind of directional solidification blade wax-pattern combination inserted chassis and preparation method thereof | |
| CN204247909U (en) | Inserted chassis is used in a kind of directional solidification blade wax-pattern combination | |
| CN104907492A (en) | Making method of surface double-walled hollow turbine blade | |
| US20130266816A1 (en) | Additive manufacturing hybrid core | |
| CN109175307B (en) | 3D printing sand mold antigravity casting forming method | |
| CN110732637A (en) | turbine blade air film hole precision forming method | |
| CN101301677A (en) | Method for quickly and precisely casting complex parts | |
| RU2652672C2 (en) | Monocrystalline smelting mould | |
| CN103990761A (en) | Manufacturing method of hollow turbine blade provided with impact hole structure | |
| CN103861999A (en) | Method for improving bottom deformation of multi-cavity ceramic die shell in directional solidification process | |
| CN103143678A (en) | Formwork for optimizing directional columnar crystal structure of high-temperature alloy blade | |
| CN103394644B (en) | Casting method capable of preventing precise investment casting from generating hot-spot shrinkage holes | |
| CN103658545A (en) | Cross beam type salt-core pressing die and salt core production method adopting pressing die | |
| CN104439068A (en) | Manufacturing process of convex lug alloy part with convex lug hole | |
| CN103691916A (en) | Casting method for protecting thin-wall casting from local isolated hot spot shrinkage | |
| CN109047670B (en) | Salt core preparation method | |
| CN202715766U (en) | Core box | |
| CN106623787B (en) | A kind of preparation method of aluminium alloy Melt casting and its binder used | |
| CN210648388U (en) | Casting device for brake disc | |
| CN110860658B (en) | Preparation method of wax mold gypsum core of cylindrical thin-wall complex component | |
| CN109093069B (en) | Wax mold preparation method for precision investment casting | |
| CN101733387B (en) | Low pressure casting method of aluminium alloy lost foam | |
| CN111230043A (en) | Precision casting complex core mold and using method thereof | |
| CN203155986U (en) | Buffering type aluminum die-casting die | |
| CN112222363A (en) | Ceramic salt core formed by one-step die-casting through molten liquid and preparation method thereof |
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 | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
|
| CP01 | Change in the name or title of a patent holder |