CN110090927A - A method of solving aviation stainless steel investment-casting stress cracking - Google Patents
A method of solving aviation stainless steel investment-casting stress cracking Download PDFInfo
- Publication number
- CN110090927A CN110090927A CN201910503916.1A CN201910503916A CN110090927A CN 110090927 A CN110090927 A CN 110090927A CN 201910503916 A CN201910503916 A CN 201910503916A CN 110090927 A CN110090927 A CN 110090927A
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- casting
- ingate
- stress
- beam structure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
- B22C9/046—Use of patterns which are eliminated by the liquid metal in the mould
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/08—Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
Abstract
The present invention provides a kind of methods for solving aviation stainless steel investment-casting stress cracking, comprising the following steps: step 1: opens up new ingate: opening up a transition arc in former ingate two sides and form new ingate；Step 2: it opens up cast gate stress slot: cutting one section of arc groove near new ingate upper stress concentrated part；Step 3: group tree: group sets the center that stylish ingate is bonded in casting beam structure, has the side of transition arc to be connected with beam structure, the other side is mutually be bonded with riser.Step 4: shell processed: using silica-sol wash shell when shell processed, shell number processed is 7-8 layers；Step 5: it casting: is poured when casting using intermediate frequency furnace.The contacting section product of the new ingate that this method uses and casting beam structure is constant, it is ensured that the feeding of casting beam structure.Using bottom gating scheme, by reasonably casting parameter, it is ensured that obtain the casting without shrinkage porosity defect of contraction cavity.
Description
Technical field
The present invention relates to technical field of aerospace, specifically a kind of side for solving aviation stainless steel investment-casting stress cracking
Method.
Background technique
Our factory produces a kind of tube-like thin-wall class aviation 17-4PH material stainless cast steel part at present, wall thickness 2.78-4.25mm, and zero
Part substance 2.8kg.There are the non-destructive testing and size tolerance requirements of stringent Aerial-casting standard.
17-4PH is in aviation model casting, and a kind of common martensitic precipitation hardening type being made of copper, niobium/columbium is not
Become rusty steel, and phosphorus content is low, and chemical analysis is similar to country trade mark 0Cr17Ni4Cu4Nb.The material casting character is poor, shrinkage
Greatly, with greater need for tending to consecutive solidification when casting, it is not easy to feeding.
The barrel structure castings have a beam structure, long 120.5mm, wide 12.5mm, high 9.8mm.The structure generates in order to prevent
Shrinkage porosity defect of contraction cavity needs to place a rectangular ingate in the center of crossbeam.But since the ingate and beam structure shape are big
Small inconsistent, ingate cooling velocity is slower, and free linear shrinkage speed is less than beam structure, so that ingate and beam structure
The stress of joint is excessively concentrated, and has been more than the Material Strength limit under high temperature, is ultimately caused the two joint and is cracked,
At 5 as shown in figure 1, it is unable to satisfy fluorescent inspection acceptance requirement, crack defect ratio is up to 65%-75%, and a large amount of parts is caused to return
It repairs and scraps, seriously affected the casting cost and shipping requires.
Summary of the invention
Technical problem to be solved by the invention is to provide a kind of sides for solving aviation stainless steel investment-casting stress cracking
Method,
The technical scheme is that
A method of solving aviation stainless steel investment-casting stress cracking, which comprises the following steps:
Step 1: new ingate is opened up: under the premise of keeping former ingate and constant beam structure contacting section product, in original
Ingate two sides open up a transition arc and form new ingate；
Step 2: it opens up cast gate stress slot: cutting one section of arc groove, these circular arcs near new ingate upper stress concentrated part
It will form new stress concentration point at the top of slot, the stress excessively concentrated originally spread out；
Step 3: group tree: group sets the center that stylish ingate is bonded in casting beam structure, there is side and the crossbeam of transition arc
Structure is connected, and the other side is mutually be bonded with riser；The two joint is brushed using bonding wax, makes ingate and beam structure joint
It is more round and smooth, no visible wax seam.
Step 4: shell processed: using silica-sol wash shell when shell processed, shell number processed is 7-8 layers；
Step 5: casting: being poured when casting using intermediate frequency furnace, is first steadily injected aluminium alloy from side gate with teapot packet, until
It when aluminium alloy fills with casting type chamber, then from riser carries out mending to full sprue cup is poured, be added on dead head after casting few
Perhaps covering flux.
Further improvement of these options, in step 2, the radius of the radian of transition arc is controlled in R40-50mm.Cast gate
Stress slot it is deep-controlled in 3-5mm.
Further improvement of these options, in step 5, formwork roasting and holding temperature control exist: 900-1000 DEG C,
Alloy tapping temperature is controlled at 1610-1640 DEG C.
Beneficial effect
1, new gate form.Under the premise of keeping ingate and beam structure contacting section product is constant, in ingate two sides
Open up biggish transition arc, keep ingate and beam structure joint more round and smooth, reduce thermal center, be conducive to feeding a casting and
Stress dispersion.
2, cast gate stress slot is opened up.One section of arc groove, these circular arcs are cut near new ingate upper stress concentrated part
It will form new stress concentration point at the top of slot, the stress excessively concentrated originally spread out, to reduce and avoid original
Stress excessively to concentrate is destroyed and is deformed caused by casting beam structure.
Detailed description of the invention
Fig. 1 is that the present invention is new ingate structure chart.
Fig. 2 is the schematic diagram that the present invention is new running gate system.
Fig. 3 is casting stress figure of the invention.
Specific embodiment
The present invention is further explained in the light of specific embodiments.
As shown in Figure 1-3, the novel ingate of 1-, 2- transition arc, 3- stress slot, 5- primary fissure line point, 6- side gate,
7- riser, 8- casting；
A method of solving aviation stainless steel investment-casting stress cracking, which comprises the following steps:
Step 1: new ingate is opened up: under the premise of keeping former ingate and constant beam structure contacting section product, in original
Ingate two sides open up a transition arc 2, form new ingate, keep new ingate and beam structure joint more round and smooth,
Thermal center is reduced, feeding a casting and stress dispersion are conducive to.
Step 2: it opens up cast gate stress slot: cutting one section of arc groove near new ingate upper stress concentrated part, these
It will form new stress concentration point at the top of arc groove, the stress excessively concentrated originally spread out, to reduce and avoid
Originally the stress excessively concentrated caused by casting beam structure is destroyed and is deformed.
Step 3: group tree: group sets the center that stylish ingate is bonded in casting beam structure, have the side of transition arc with
Beam structure is connected, and the other side is mutually be bonded with riser；The two joint is brushed using bonding wax, makes ingate and beam structure phase
It is more round and smooth to meet place, no visible wax seam.
Step 4: shell processed: using silica-sol wash shell when shell processed, shell number processed is 7-8 layers；
Step 5: casting: being poured when casting using intermediate frequency furnace, is first steadily injected aluminium alloy from side gate with teapot packet, until
It when aluminium alloy fills with casting type chamber, then from riser carries out mending to full sprue cup is poured, be added on dead head after casting few
Perhaps covering flux.
Further improvement of these options, in step 2, the radius of the radian of transition arc 2 is controlled in R40-50mm.It pours
Mouthful stress slot it is deep-controlled in 3-5mm.
Further improvement of these options, in step 5, formwork roasting and holding temperature control exist: 900-1000 DEG C,
Alloy tapping temperature is controlled at 1610-1640 DEG C.
Working principle:
Cause Analysis on Crack
After being cast, the intracavitary aluminium alloy elder generation cooled and solidified of casting type, ingate and running channel because package refractory cotton cooled and solidified compared with
Slowly.In the cooling procedure of casting after solidification, each section and ingate cooling velocity are inconsistent, and beam structure starts linear shrinkage,
But the ingate being attached thereto also is in early solidification, and the deformation of casting beam structure is determined by itself completely at this time, casting
Beam structure drives ingate to shrink together, and casting does not generate thermal stress at this time.
With the growth of cooling time, the two temperature difference is gradually increased, and casting beam structure solid phase has formed complete skeleton.
The shrinkage of ingate is greater than casting beam structure gradually, and since the two is connected with each other, and ingate connects riser, so at this time
Ingate is compressed, and casting beam structure is elongated, and compression is generated in ingate, and casting beam structure generates tensile stress,
When the two temperature difference maximum, stress value is maximum.When stress value has been more than the strength degree of the castings material at these elevated temperatures, just
It can crack.
Novel ingate principle
The transition arc of novel ingate can reduce the thermal center point between ingate and casting, reduce and concentrate deformation, and dilution is poured
Mouth shrinks obstacle, while facilitating the feeding of casting beam structure.And cast gate stress slot can shrink the later period in casting solidification, it will
The tensile stress that ingate is excessively concentrated spreads out, and the top of these arc grooves is made to form new stress concentration point, makes directly to make
Stress used in beam structure becomes smaller, so as to avoid its crackle or the generation of deformation.
The contacting section product of new ingate and casting beam structure is constant, it is ensured that the feeding of casting beam structure.
Bottom gating scheme is all used, by reasonably casting parameter, it is ensured that obtain the casting without shrinkage porosity defect of contraction cavity.
Finally it should be noted that the above specific embodiment is only used to illustrate the technical scheme of the present invention and not to limit it, to the greatest extent
Pipe is described the invention in detail referring to example, those skilled in the art should understand that, it can be to of the invention
Technical solution is modified or replaced equivalently, and without departing from the spirit and scope of the technical solution of the present invention, should all be covered
In scope of the presently claimed invention.
Claims (3)
1. a kind of method for solving aviation stainless steel investment-casting stress cracking, which comprises the following steps:
Step 1 opens up new ingate: under the premise of keeping former ingate and constant beam structure contacting section product, in original
Ingate two sides open up a transition arc (2) and form new ingate (1)；
Step 2 opens up cast gate stress slot (3): one section of arc groove is cut near new ingate upper stress concentrated part, these
It will form new stress concentration point at the top of arc groove, the stress excessively concentrated originally spread out；
Step 3, group tree: group sets the center that stylish ingate is bonded in casting beam structure, there is side and the crossbeam of transition arc
Structure is connected, and the other side is mutually be bonded with riser (7)；The two joint is brushed using bonding wax, makes ingate and beam structure phase
It is more round and smooth to meet place, no visible wax seam；
Step 4, shell processed: using silica-sol wash shell when shell processed, shell number processed is 7-8 layers；
Step 5, casting: being poured when casting using intermediate frequency furnace, is first steadily injected aluminium alloy from side gate with teapot packet, until
It when aluminium alloy fills with casting type chamber, then from riser carries out mending to full sprue cup is poured, be added on dead head after casting few
Perhaps covering flux.
2. solving the method for aviation stainless steel investment-casting stress cracking according to claim 1, it is characterised in that:
In step 2, cast gate is opened up transition arc (2), and radius of the radian is controlled in R40-50mm.
Cast gate opens up cast gate stress slot (3), and stress groove deep degree is controlled in 3-5mm.
3. solving the method for aviation stainless steel investment-casting stress cracking according to claim 1, it is characterised in that:
In step 5, formwork roasting and holding temperature control exist: 900-1000 DEG C, alloy tapping temperature is controlled in 1610-1640
℃。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910503916.1A CN110090927B (en) | 2019-06-12 | 2019-06-12 | Method for solving stress cracks of aviation stainless steel investment casting |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910503916.1A CN110090927B (en) | 2019-06-12 | 2019-06-12 | Method for solving stress cracks of aviation stainless steel investment casting |
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| CN110090927B CN110090927B (en) | 2020-12-25 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111054901A (en) * | 2019-12-31 | 2020-04-24 | 西安西工大超晶科技发展有限责任公司 | Method for solving streamline defect at lower end of ZL210A alloy casting linear chilling block |
| CN112893773A (en) * | 2021-02-23 | 2021-06-04 | 天长市兴宇铸造有限公司 | Module wax part structure for upper and lower shell castings in coupler and draft gear and tree assembling process thereof |
| CN113458514A (en) * | 2021-08-17 | 2021-10-01 | 青岛青特众力车桥有限公司 | Hydrogen embrittlement device and method for bearing seat of middle-rear axle speed reducer |
| CN113547082A (en) * | 2021-07-20 | 2021-10-26 | 上海电气集团上海电机厂有限公司 | Casting method of flame-proof motor fan |
| CN113828735A (en) * | 2021-09-18 | 2021-12-24 | 江苏金诺炉辊有限公司 | Gating system and investment casting process of high-temperature alloy elbow |
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| JPS58159967A (en) * | 1982-03-19 | 1983-09-22 | Akebono Brake Ind Co Ltd | Casting device |
| CN201711494U (en) * | 2010-06-30 | 2011-01-19 | 浙江红马铸造有限公司 | Ingate for precision casting |
| CN204413057U (en) * | 2014-12-31 | 2015-06-24 | 鹰普航空零部件（无锡）有限公司 | Model casting is clear cup cover plate easily |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111054901A (en) * | 2019-12-31 | 2020-04-24 | 西安西工大超晶科技发展有限责任公司 | Method for solving streamline defect at lower end of ZL210A alloy casting linear chilling block |
| CN112893773A (en) * | 2021-02-23 | 2021-06-04 | 天长市兴宇铸造有限公司 | Module wax part structure for upper and lower shell castings in coupler and draft gear and tree assembling process thereof |
| CN112893773B (en) * | 2021-02-23 | 2024-01-26 | 天长市兴宇铸造有限公司 | Module wax component structure for upper and lower shell castings in hook buffer device and tree assembling process thereof |
| CN113547082A (en) * | 2021-07-20 | 2021-10-26 | 上海电气集团上海电机厂有限公司 | Casting method of flame-proof motor fan |
| CN113458514A (en) * | 2021-08-17 | 2021-10-01 | 青岛青特众力车桥有限公司 | Hydrogen embrittlement device and method for bearing seat of middle-rear axle speed reducer |
| CN113828735A (en) * | 2021-09-18 | 2021-12-24 | 江苏金诺炉辊有限公司 | Gating system and investment casting process of high-temperature alloy elbow |
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| Publication number | Publication date |
|---|---|
| CN110090927B (en) | 2020-12-25 |
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Address after: No.18 Furong 5th Road, Xishan Economic Development Zone, Wuxi City, Jiangsu Province Applicant after: Yingpu Aviation Technology Co., Ltd Address before: No.18 Furong 5th Road, Xishan Economic Development Zone, Wuxi City, Jiangsu Province Applicant before: IMPRO AVIATION COMPONENTS (WUXI) Co.,Ltd. |
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