CN104308082A - Pouring method of hollow turbine guide vane - Google Patents
Pouring method of hollow turbine guide vane Download PDFInfo
- Publication number
- CN104308082A CN104308082A CN201410594148.2A CN201410594148A CN104308082A CN 104308082 A CN104308082 A CN 104308082A CN 201410594148 A CN201410594148 A CN 201410594148A CN 104308082 A CN104308082 A CN 104308082A
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- shell
- ingate
- hollow
- casting
- temperature
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/08—Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
- B22C9/082—Sprues, pouring cups
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
The invention provides a pouring method of a hollow turbine guide vane. The pouring method comprises the following steps: (1) manufacturing a wax mold combination; (2) carrying out shell making on the wax mold combination to obtain a hollow turbine guide vane shell; (3) covering one layer of ceramic heat-preservation cotton on a shell vane body part; covering two layers of ceramic cotton on the whole shell; and putting the treated shell into a roasting furnace and carrying out casting, wherein in a casting process, the temperature of casting the shell is 1065-1085 DEG C and the pouring temperature is 1460-1480 DEG C. According to the pouring method of the hollow turbine guide vane, a pouring system of the hollow turbine guide vane is not changed and the shell temperature and the pouring temperature are adjusted so that the casting temperature field is changed; the two layers of ceramic cotton on the whole body and one layer of the ceramic heat-preservation cotton on the vane body part are matched so that after the temperature of the whole shell is improved, the temperature field is uniform, the casting stress is eliminated and the casting temperature is reduced; and furthermore, the temperature field on a casting vane body and an edge plate keeps uniform, the shell is effectively insulated and the casting stress is eliminated.
Description
Technical field
The present invention relates to precision casting technology field, be specially a kind of pouring procedure of hollow turborotor.
Background technology
In prior art, marginless melted module precise casting is the best means of turbo blade manufacture at present.Its technological process mainly comprises the design and manufaction of core mold, suppresses the link such as design and manufaction, assembling casting, pasting shell, dry shell, dewaxing, sintering, casting metal, shelling depoling, laser boring of core, Wax mold.The assembled scheme that hollow turborotor adopts teeming to add rising pouring produces such foundry goods, after wax-pattern module shell, whole shell wraps up one deck ceramic wool, foundry goods is carried out in the temperature field of setting, because shell limits during foundry goods, need the temperature limiting shell, and improve pouring temperature, although this process program can alleviate the porousness of foundry goods and reduce the quantity of casting thermal fragmentation, casting thermal fragmentation and rarefaction defect can not be eliminated completely.Simultaneously in the combination of teeming and rising pouring, hollow turborotor listrium and blade R place hot tearing problem of transferring also cannot solve, and percent defective is high.And Stress non-homogeneity in the technique in pasting shell, easily produces thermal fragmentation defect.
Summary of the invention
For problems of the prior art, the invention provides a kind of product quality high, listrium and blade can be solved completely and to transfer the pouring procedure of hollow turborotor of R place hot tearing.
The present invention is achieved through the following technical solutions:
A kind of hollow turborotor pouring procedure, comprises the steps,
1) wax-pattern combination is manufactured;
2) shell processed is carried out to wax-pattern combination, obtain hollow turborotor shell;
3) shell blade position is wrapped up one deck ceramic thermal insulation cotton, whole shell parcel two-layer ceramic is cotton more afterwards; Shell after process is entered roaster and carries out foundry goods, during foundry goods, casting shell molds temperature is 1065-1085 DEG C, and pouring temperature is 1460-1480 DEG C.
Preferably, the thickness of ceramic thermal insulation cotton is 6-9mm.
Preferably, wax-pattern combination comprises cup, and is communicated with the sprue being arranged on the cup port of export; The sidewall of straight channel is arranged ingate assembly; Each ingate assembly comprises the lower edge ingate be communicated with blade inframarginal die cavity side, and the upper limb ingate be communicated with blade supramarginal plate die cavity side; Lower edge ingate and upper limb ingate are arranged along the flow direction of straight channel successively.
Further, ingate assembly also comprises the cross gate being communicated with and being arranged in straight channel; Cross gate walks abreast and is arranged on the side of lower edge ingate near upstream, and the cross gate port of export is communicated with in the middle part of blade inframarginal die cavity by auxiliary ingate.
Further, the ingate assembly of some groups axially sets gradually along straight channel and/or axis along straight channel is symmetrical set.
Compared with prior art, the present invention has following useful technique effect:
The present invention is not while changing hollow turborotor running gate system, by regulating shell temperature and pouring temperature, thus change casting temperature field, by coordinating the two-layer ceramic of overall parcel cotton and cotton at one deck ceramic thermal insulation of blade position parcel, can after raising shell temperature, ensure the even of temperature field, eliminate casting stress, supplement the pouring temperature of reduction, the temperature field at foundry goods blade and listrium place is made to keep evenly, shell is effectively incubated, eliminate casting stress, the hollow turborotor listrium of thorough solution and blade are transferred R place hot tearing problem, improve product quality.
Further, be optimized the thickness of ceramic thermal insulation cotton, can not only improve the heat insulating ability of shell, make the stable molding of cast rear blade, and can not affect the speed of solidifying, keep rational solid-liquid siding-to-siding block length, it is all even stable that guarantee is solidified.
Further, by arranging the wax-pattern combination of ingate assembly, lower edge ingate in utilization, realize noting the survey of hollow turborotor, can make aluminium alloy smooth outflow in shell, foundry goods not easily owes casting, assembled scheme compared to existing technology, do not form frame structure, casting stress is little, and foundry goods not easily cracks.
Further, whole hollow turborotor can be made when pouring into a mould by the cross gate arranged in the upstream direction, carry out auxiliary feeding from the porous spot of upstream to inframarginal and supramarginal plate of cast, thus its metallurgical imperfection can be avoided better, and the uneven hot tearing caused of cast.
Further, by the reasonable Arrangement of internal sprue component, while guarantee cast effect, the efficiency of cast can be improved, once completes the making of multiple part, and can not affect each other.
Accompanying drawing explanation
Fig. 1 is step 2 in method described in example of the present invention) in shell schematic diagram.
Fig. 2 is step 3 in method described in example of the present invention) in shell schematic diagram.
What Fig. 3 combined for wax-pattern described in example of the present invention partly cuts open structural representation.
Fig. 4 is the schematic enlarged-scale view at I place in Fig. 3.
In figure: 1 is upper limb ingate; 2 is hollow turborotor; 3 is auxiliary ingate 2; 4 is lower edge ingate; 5 is cross gate; 6 is cup; 7 is sprue; 21 is a blade; 22 is No. two blades; 23 is No. three blades; 24 is No. four blades; 25 is inframarginal; 26 is supramarginal plate; 27 is blade.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in further detail, and the explanation of the invention is not limited.
A kind of hollow turborotor pouring procedure of the present invention, comprises the steps,
1) wax-pattern combination is manufactured;
2) shell processed is carried out to wax-pattern combination, obtain hollow turborotor shell, as shown in Figure 1;
3) shell blade position is wrapped up one deck ceramic thermal insulation cotton, whole shell parcel two-layer ceramic is cotton more afterwards, and structure as shown in Figure 2; Shell after process is entered roaster and carries out foundry goods; During cast, casting shell molds temperature is 1065-1085 DEG C, and pouring temperature is 1460-1480 DEG C.Wherein, the thickness of ceramic thermal insulation cotton is 6-9mm, and this preferred embodiment is described for 6mm.Temperature field when the cast parameter adopted during this preferred embodiment medium casting and foundry goods is 1075 DEG C with casting shell molds temperature during foundry goods, and pouring temperature is 1470 DEG C and is described for example.
Wherein, as shown in Figure 3, it comprises cup 6 in wax-pattern combination, and is communicated with the sprue 7 being arranged on cup 6 port of export; The sidewall of straight channel 7 is arranged ingate assembly; Each ingate assembly comprises the lower edge ingate 4 be communicated with blade inframarginal die cavity side, and the upper limb ingate 1 be communicated with blade supramarginal plate die cavity side; Lower edge ingate 4 and upper limb ingate 1 are arranged along the flow direction of straight channel 7 successively.In this preferred embodiment, be described for the symmetrically arranged ingate assembly in axis with two groups, namely adopt the combination of one group of two pieces; Ingate assembly also comprises the cross gate 5 being communicated with and being arranged in straight channel 7; Cross gate 5 is parallel is arranged on the side of lower edge ingate 4 near upstream, and cross gate 5 port of export is communicated with in the middle part of blade inframarginal die cavity by auxiliary ingate 3.
When adopting wax-pattern as above combination and pouring procedure, as shown in Figure 4, the R of blade and listrium switching place, because vane foil divides leading edge and exhaust limit, air inlet R refers to the R of switching place near leading edge to the hollow turborotor of essence casting.It comprises two ends respectively by a blade 21, No. two blades 22, No. three blades 23 of inframarginal 25 and supramarginal plate 26 parallel connection and No. four blades 24, thus forms blade 27; Aluminium alloy is injected in cup 6, aluminium alloy injects downwards along sprue 7, and inject from cross gate 5, the lower edge ingate 4 simultaneously arranged from the same side and upper limb ingate 1 inject inframarginal die cavity and the supramarginal plate die cavity of hollow turborotor 2 simultaneously, and aluminium alloy also injects from auxiliary ingate 3 simultaneously and carries out auxiliary feeding in the middle part of inframarginal die cavity simultaneously.Compare with existing solution hollow turborotor precision castings metallurgical imperfection technology, the program thoroughly can solve hollow turborotor listrium and blade and to transfer R place hot tearing problem, improves the quality of products.
Claims (5)
1. a hollow turborotor pouring procedure, is characterized in that, comprise the steps,
1) wax-pattern combination is manufactured;
2) shell processed is carried out to wax-pattern combination, obtain hollow turborotor shell;
3) shell blade position is wrapped up one deck ceramic thermal insulation cotton, whole shell parcel two-layer ceramic is cotton more afterwards; Shell after process is entered roaster and carries out foundry goods, during foundry goods, casting shell molds temperature is 1065-1085 DEG C, and pouring temperature is 1460-1480 DEG C.
2. the hollow turborotor pouring procedure of one according to claim 1, is characterized in that, the thickness of ceramic thermal insulation cotton is 6-9mm.
3. the hollow turborotor pouring procedure of one according to claim 1, is characterized in that, described wax-pattern combination comprises cup (6), and is communicated with the sprue (7) being arranged on cup (6) port of export; The sidewall of straight channel (7) arranges ingate assembly; Each ingate assembly comprises the lower edge ingate (4) be communicated with blade inframarginal die cavity side, and the upper limb ingate (1) be communicated with blade supramarginal plate die cavity side; Lower edge ingate (4) and upper limb ingate (1) are arranged along the flow direction of straight channel (7) successively.
4. the hollow turborotor pouring procedure of one according to claim 3, is characterized in that, ingate assembly also comprises connection and is arranged on cross gate (5) in straight channel (7); Cross gate (5) is parallel is arranged on the side of lower edge ingate (4) near upstream, and cross gate (5) port of export is communicated with in the middle part of blade inframarginal die cavity by auxiliary ingate (3).
5. the hollow turborotor pouring procedure of one according to claim 3, is characterized in that, the ingate assembly of some groups axially sets gradually along straight channel (7) and/or axis along straight channel (7) is symmetrical set.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410594148.2A CN104308082B (en) | 2014-10-29 | 2014-10-29 | A kind of pouring procedure of hollow turborotor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410594148.2A CN104308082B (en) | 2014-10-29 | 2014-10-29 | A kind of pouring procedure of hollow turborotor |
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| CN104308082A true CN104308082A (en) | 2015-01-28 |
| CN104308082B CN104308082B (en) | 2016-05-18 |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104550735A (en) * | 2015-02-08 | 2015-04-29 | 哈尔滨鑫润工业有限公司 | Precision casting method of last stage extra-long guide blade for million-kilowatt nuclear power unit |
| CN105772633A (en) * | 2015-12-28 | 2016-07-20 | 浙江亚辰新材料科技有限公司 | Mold filling device for directional solidification of turbine blades and preparation method |
| 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 |
| CN108941459A (en) * | 2018-09-05 | 2018-12-07 | 中国航发动力股份有限公司 | A method of it is loose to reduce combustion engine turbine blade |
| CN109093072A (en) * | 2018-07-27 | 2018-12-28 | 沈阳中科三耐新材料股份有限公司 | A kind of casting technique of gas turbine turbo blade |
| CN110052583A (en) * | 2019-03-15 | 2019-07-26 | 启东市聚旺铸造有限公司 | Precise casting process of hollow guide blade |
| US10449601B2 (en) | 2016-12-26 | 2019-10-22 | Safran Aircraft Engines | Shell mold for a sector of a 360°-set of guide vanes |
| CN111659856A (en) * | 2020-05-22 | 2020-09-15 | 东方电气集团东方汽轮机有限公司 | Concatemer solid blade pouring system and pouring method |
| CN111774528A (en) * | 2020-06-19 | 2020-10-16 | 内蒙古第一机械集团股份有限公司 | Manufacturing method of high manganese steel track shoe shell |
| CN112453325A (en) * | 2020-11-03 | 2021-03-09 | 哈尔滨工业大学 | Casting forming method of wing rudder with high-temperature alloy dot matrix sandwich structure |
| CN112548039A (en) * | 2020-11-20 | 2021-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Tenon-and-mortise combined casting system and manufacturing method for high-temperature alloy thin-wall part |
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| US5465780A (en) * | 1993-11-23 | 1995-11-14 | Alliedsignal Inc. | Laser machining of ceramic cores |
| JP2004276109A (en) * | 2003-03-19 | 2004-10-07 | Daido Steel Co Ltd | Lost wax pattern for lost wax casting method |
| CN101168184A (en) * | 2006-10-26 | 2008-04-30 | 沈阳黎明航空发动机(集团)有限责任公司 | Casting method for heavy combustion engine II-stage diverter blade |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104550735A (en) * | 2015-02-08 | 2015-04-29 | 哈尔滨鑫润工业有限公司 | Precision casting method of last stage extra-long guide blade for million-kilowatt nuclear power unit |
| CN105772633A (en) * | 2015-12-28 | 2016-07-20 | 浙江亚辰新材料科技有限公司 | Mold filling device for directional solidification of turbine blades and preparation method |
| CN105772633B (en) * | 2015-12-28 | 2018-05-11 | 浙江亚辰新材料科技有限公司 | A kind of turbo blade hot investment casting directional freeze method |
| US10449601B2 (en) | 2016-12-26 | 2019-10-22 | Safran Aircraft Engines | Shell mold for a sector of a 360°-set of guide vanes |
| 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 |
| CN109093072A (en) * | 2018-07-27 | 2018-12-28 | 沈阳中科三耐新材料股份有限公司 | A kind of casting technique of gas turbine turbo blade |
| CN108941459A (en) * | 2018-09-05 | 2018-12-07 | 中国航发动力股份有限公司 | A method of it is loose to reduce combustion engine turbine blade |
| CN110052583A (en) * | 2019-03-15 | 2019-07-26 | 启东市聚旺铸造有限公司 | Precise casting process of hollow guide blade |
| CN111659856A (en) * | 2020-05-22 | 2020-09-15 | 东方电气集团东方汽轮机有限公司 | Concatemer solid blade pouring system and pouring method |
| CN111659856B (en) * | 2020-05-22 | 2022-03-29 | 东方电气集团东方汽轮机有限公司 | Concatemer solid blade pouring system and pouring method |
| CN111774528A (en) * | 2020-06-19 | 2020-10-16 | 内蒙古第一机械集团股份有限公司 | Manufacturing method of high manganese steel track shoe shell |
| CN112453325A (en) * | 2020-11-03 | 2021-03-09 | 哈尔滨工业大学 | Casting forming method of wing rudder with high-temperature alloy dot matrix sandwich structure |
| CN112548039A (en) * | 2020-11-20 | 2021-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Tenon-and-mortise combined casting system and manufacturing method for high-temperature alloy thin-wall part |
| CN112548039B (en) * | 2020-11-20 | 2022-03-29 | 中国航发沈阳黎明航空发动机有限责任公司 | Tenon-and-mortise combined casting system and manufacturing method for high-temperature alloy thin-wall part |
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|---|---|
| CN104308082B (en) | 2016-05-18 |
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Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO,LTD. Address before: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE Corp.,PLC |
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Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: XI'AN AVIATION POWER Co.,Ltd. |
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