CN103406497A - Method for casting aluminum-magnesium alloy aeroengine box - Google Patents
Method for casting aluminum-magnesium alloy aeroengine box Download PDFInfo
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- CN103406497A CN103406497A CN201310389098XA CN201310389098A CN103406497A CN 103406497 A CN103406497 A CN 103406497A CN 201310389098X A CN201310389098X A CN 201310389098XA CN 201310389098 A CN201310389098 A CN 201310389098A CN 103406497 A CN103406497 A CN 103406497A
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Abstract
The invention relates to a method for casting an aluminum-magnesium alloy aeroengine box. The aeroengine box is of a spiral cone shape and has a big head and a small head, wherein the diameter of the big-head end is 900-1,200 mm, the average wall thickness is about 2.5-3 mm, and the aeroengine box is formed through integral casting of aluminum-magnesium alloy. The method is used for solving the problem that the aeroengine box can not be cast by the traditional casting methods due to the structural features of the aeroengine box. According to the method, during the combination and assembly of a casting form, the casting form is combined in a manner that the big head is located at the downside, then, the small head is enabled to face downwards through inverting, and finally, aluminum-magnesium alloy is cast from a casting port of the small-head end from bottom to top. According to the method disclosed by the invention, a novel casting form combining and casting manner is provided, the defects that the existing casting methods can not be applied to casting are overcome, and the bottleneck in development of aeroengine box cast parts is solved.
Description
Technical field
The present invention relates to a kind of casting method of aerial motor spare part, especially a kind of casting method of aero-engine major diameter complex thin-wall casing, this aero-engine casing is formed by aluminium, magnesium alloy cast.
Background technology
Casing class part in aero-engine, such as front housing etc., its size is generally larger, diameter is generally more than Φ 800mm, and wall thickness is thinner, complex structure, mainly be shaped as the screw cone structure, constituent material is generally the high temperature non-ferrous alloy, for example aluminium alloy or magnesium alloy.Adopt traditional non-ferrous alloy sand casting casting mold combination and moulding by casting very difficult, especially moulding difficulty in blade position is very large.
For example, certain aluminium, magnesium alloy casing foundry goods overall size are Φ 900mm, the main body wall thickness is 2.5-3mm, inside and outside, ring is connected by the thick oblique support plate of a plurality of 2-3mm, and with the thick lug of a plurality of 15～40mm, boss, wall unevenness, complex structure, foundry goods one-time cast-forming, internal metallurgical quality are controlled, the technology difficulty such as Assurance of Size of large thin-wall element are quite large.
The traditional manufacturing process of such part is: adopt different processing technologys to process each single part, then use welding processing, assembly welding becomes integral casing.This casing processing molding method, take the resources of production in a large number, and the process-cycle is long, and the metal material waste is large, and cost is high, the pts wt weight.
Summary of the invention
The technical problem to be solved in the present invention is to provide the casting method of a kind of aluminium, magnesium alloy aero-engine casing, to reduce or to avoid problem noted earlier.
Specifically, for solving the problems of the technologies described above, in the casting method of aluminium of the present invention, magnesium alloy aero-engine casing, described aero-engine casing is the screw cone shape, one large one small, the diameter of its large first end is 900-1200mm, and average wall thickness is about 2.8mm, by aluminium, magnesium alloy integrally cast, formed, described casting method comprises the steps:
Steps A: the major part sandbox that a horizontal positioned is provided, directly over described major part sandbox, be fixed for forming the interior core of the die cavity inboard of described aero-engine casing, described interior core is the centrum shape, the end that the centrum shape of this interior core is large contacts with described major part sandbox, and the little end of shape upward;
Step B: at symmetrical a pair of check lock lever and a pair of backstay installed in the described major part sandbox outside, described check lock lever and described backstay space are arranged;
Step C: microcephaly's sandbox of a plurality of horizontal positioned is provided, forms therein respectively a plurality of outside core in the die cavity outside of described aero-engine casing by molding sand, form the horn-like opening upwards enlarged in the middle of described outside core; Described each microcephaly's sandbox outside is formed with locking hole auricle and the locating hole auricle that can supply described check lock lever and backstay to pass corresponding to the position of above-mentioned check lock lever and backstay;
Step D: after a plurality of microcephaly's sandboxes that are formed with outside core in step C are turned over to turnback, make successively locking hole auricle and the locating hole auricle of described a plurality of microcephaly's sandboxes pass described check lock lever and backstay, after described backstay is accurately located the relative position of described a plurality of microcephaly's sandboxes and major part sandbox, by locking member, described check lock lever is locked the casting mold combination that described a plurality of microcephaly's sandboxes and major part sandbox are rigidly connected and are integral;
Step e: after the described casting mold combination obtained in step C is turned over to turnback, attach it on the counter-pressure casting machine, from bottom pouring mouth cast aluminum, the liquid magnesium alloy of described casting mold combination, pour into a mould from bottom to top and form described aluminium, magnesium alloy aero-engine casing by the counter-pressure casting machine.
Preferably, the end that described backstay coordinates with the installing hole auricle of described major part sandbox arranged outside is that end is gradually thin coniform, is provided with installation sleeve in this installing hole auricle, and the internal diameter of described installation sleeve is less than the maximum outside diameter of described backstay.
Preferably, in described step e, before described casting mold combination upset, in a flat slotted hole that need to arrange at the end that described backstay coordinates with described major part sandbox, insert a wedged plate, so that described backstay is stuck on described major part sandbox.
Preferably, each described microcephaly's sandbox outside is provided with the locating hole auricle, is provided with a positioning sleeve in each described locating hole auricle, and the diameter of these positioning sleeves is greater than the maximum gauge of described backstay.
Preferably, described backstay is that end is gradually thin coniform away from an end of described major part sandbox.
Because the design feature of aero-engine casing of the present invention causes traditional casting method to cast, method of the present invention is in casting mold combination assembling, adopt major part under mode combine, then be inverted come to make upside down little, finally cast aluminum, magnesium alloy from bottom to top from the sprue gate of this end of microcephaly.Casting method of the present invention provides a kind of new casting mold combination and pouring type, has overcome the defect that existing pouring procedure can't be cast, and has solved aero-engine casing foundry goods development bottleneck.
The accompanying drawing explanation
The following drawings only is intended to the present invention is done and schematically illustrates and explain, not delimit the scope of the invention.Wherein,
Shown in Figure 1 is a kind of partial schematic sectional view of aero-engine casing;
Fig. 2 shows is the decomposition diagram of the casting mold combination of aero-engine aluminium, magnesium alloy casing according to a specific embodiment of the present invention;
Fig. 3 shows is the structural representation of interior core that is fixed for forming the die cavity inboard of described aero-engine casing directly over the major part sandbox;
What Fig. 4 showed is the schematic cross-section of casting mold combination shown in Figure 2;
What Fig. 5 showed is the perspective view of combination casting mold combination afterwards.
The specific embodiment
For technical characterictic of the present invention, purpose and effect being had more clearly, understand, now contrast accompanying drawing explanation the specific embodiment of the present invention.Wherein, identical parts adopt identical label.
Just as described in the background section, aero-engine casing type component diameter is large, wall thickness, complex structure, is difficult to by the traditional combination of non-ferrous alloy sand casting casting mold and moulding by casting.
For example, shown in Figure 1 is a kind of partial schematic sectional view of aero-engine casing, this aero-engine casing is the spiral cone shape on the whole, namely one large one small, the diameter of its large first end can reach 900-1200mm usually, and casing main body wall thickness is very thin, and average wall thickness is 2.5-3mm, the casing medial and lateral are distributed with various labyrinths, such as outer surface usually around the structures such as blade that are distributed with a plurality of screw twisted.
In the combination of conventional aluminum alloy or magnesium alloy (hereinafter to be referred as aluminium, magnesium alloy) sand casting casting mold and pouring forming technology, at first need aluminium, the combination of magnesium alloy casing design casting mold according to this aero-engine major diameter complex thin-wall structure, then core is manufactured in combination according to casting mold, afterwards core and set of molds are dressed up to one and pour into a mould, finally obtain required foundry goods.
Yet, as shown in Figure 1, because the case structure that is on the whole the spiral cone shape is very complicated, simply by a set of core, coordinate mould can't form the cast passage of labyrinth like this at all.Therefore, as shown in Figure 2, the invention provides a kind of casting method, in order to the core composite pouring by different, complete aluminium, the magnesium alloy casing of this aero-engine major diameter complex thin-wall structure.
As shown in Figure 2, what wherein show is the decomposition diagram of the casting mold combination of a kind of aero-engine aluminium, magnesium alloy casing, visible in figure, casting mold combination of the present invention provides two-layer at least sand core structure, the interior core 1 that comprises the die cavity inboard that forms aero-engine casing, and the outside core 2 that forms the die cavity outside of aero-engine casing.
As shown in the figure, because the casing internal structure is relatively simple, therefore the above-mentioned interior core 1 that is used to form the die cavity inboard of casing can be combined into the centrum shape by a plurality of cores, these a plurality of core combinations inside are formed with fastening structure, such as being embedded with swivel nut etc., thereby can in assembling, be fixed by bolt.What Fig. 4 showed is the schematic cross-section of casting mold combination shown in Figure 2, can know and find out that a plurality of structures that form interior core 1 mechanically are fixed together by bolt 11 and pre-buried swivel nut 12 each other.
On the other hand, because the casing external structure is very complicated, therefore the said external core 2 that is used to form the die cavity outside of casing is difficult to be combined to form by simple core, therefore, in the present invention, adopted the form of many casees to form described outside core 2, that is to say, a plurality of sandboxes 21 are provided, have formed therein respectively a part of outside core 2.
Specifically describe with reference to the accompanying drawings casting method of the present invention, described casting method comprises the steps:
Steps A: the major part sandbox 13 that a horizontal positioned is provided, directly over described major part sandbox 13, be fixed for forming the interior core 1 of the die cavity inboard of described aero-engine casing, described interior core 1 is the centrum shape, the end that the centrum shape of this interior core 1 is large contacts with described major part sandbox 13, and the little end of shape upward.Described step can be referring to Fig. 3, and what wherein show is the structural representation of interior core 1 that is fixed for forming the die cavity inboard of described aero-engine casing directly over major part sandbox 13.
What Fig. 4 showed is the schematic cross-section of casting mold combination shown in Figure 2, can know and find out that a plurality of structures that form interior core 1 mechanically have been fixedly connected on directly over the major part sandbox by bolt 11 and pre-buried swivel nut 12 each other.
Step B: at symmetrical a pair of check lock lever 14 and a pair of backstay 15 installed in described major part sandbox 13 outsides, described check lock lever 14 and described backstay 15 spaces are arranged.
What in figure, the diameter demonstration was thinner is check lock lever 14, and what the diameter demonstration was thicker is backstay 15.In the figure of Fig. 4 middle section, only show a pair of backstay 15, check lock lever 14 is screw rod, can carry out locking operation by the cooperation of screw rod and nut.
As shown in Figure 4, the end that backstay 15 coordinates with the installing hole auricle 30 of described major part sandbox 13 arranged outside is that end is gradually thin coniform, in this installing hole auricle 30, be provided with installation sleeve 20, the internal diameter of installation sleeve 20 is less than the maximum outside diameter of backstay 15, therefore as seen from the figure, after backstay 15 inserts in installation sleeve 20 from the top down, do not need extra fixed structure just can remain on by the gravity of backstay 15 in installation sleeve 20 and can not skid off installation sleeve 20 downwards.
Step C: microcephaly's sandbox 21 of a plurality of horizontal positioned is provided, forms therein respectively a plurality of outside core 2 in the die cavity outside of described aero-engine casing by molding sand, form the horn-like opening upwards enlarged in the middle of described outside core 2; Each described microcephaly's sandbox 21 outside is formed with the locating hole auricle 16 that can supply described backstay 15 to pass corresponding to the position of above-mentioned backstay 15, from described major part sandbox 13 described microcephaly's sandbox 21 outsides farthest, is formed with the locking hole auricle 18 that can supply described check lock lever 14 to pass corresponding to the position of above-mentioned check lock lever 14 at least.
A plurality of microcephaly's sandboxes 21 that show in casting mold combination decomposing schematic representation in Fig. 2 be in this step with figure in the opposite direction that shows, namely in a plurality of microcephaly's sandboxes 21 of this step and Fig. 2, compare to be and be inverted shape, Fig. 2 means is the situation after combination.Why this step will adopt inverted mode when forming outside core 2, because aero-engine casing of the present invention is one large one small spiral cone shape, if form each outside core 2 with the horn-like opening form enlarged downwards, especially easily in the process of founding, form avalanche, cause the founding failure, and because aero-engine casing diameter of the present invention is very large, if traditional founding mode does not take special molding sand material to be difficult to accomplish that the horn-like opening form enlarged forms each outside core 2 downwards, and the method in this step can adopt traditional mode to construct, greatly saved cost.
Step D: after a plurality of microcephaly's sandboxes 21 that are formed with outside core 2 in step C are turned over to turnback, make successively locking hole auricle 18 and the locating hole auricle 16 of described a plurality of microcephaly's sandboxes 21 pass described check lock lever 14 and backstay 15, after the relative position of 15 pairs of described a plurality of microcephaly's sandboxes 21 of described backstay and major part sandbox 13 is accurately located, by locking member, described check lock lever 14 is locked the casting mold combination that described a plurality of microcephaly's sandboxes 21 and major part sandbox 13 are rigidly connected and are integral.
Wherein check lock lever 14 is common screw rod, and locking member is nut.The cross sectional view of the casting mold combination after combination can be referring to Fig. 4, what Fig. 5 showed is the perspective view of combination casting mold combination afterwards, in figure, visible each microcephaly's sandbox 21 outsides can arrange locking hole auricle 18, perhaps only at microcephaly's sandbox 21 arranged outside locking hole auricles 18 of outermost one deck, after for the most whole casting mold, assembling, locking is just passable.
But in the present invention, each microcephaly's sandbox 21 outside must arrange locating hole auricle 16, is provided with positioning sleeve 17 in each locating hole auricle 16, the slightly larger in diameter of these positioning sleeves 17 is in the maximum gauge of described backstay 15.For ease of backstay 15, can pass easily the positioning sleeve 17 in the locating hole auricle 16 of each microcephaly's sandbox 21, backstay 15 is that end is gradually thin coniform away from an end of described major part sandbox 13.
Step e: by the described casting mold combination upset 180 obtained in step C, attach it to afterwards on the counter-pressure casting machine, from bottom pouring mouth cast aluminum, the liquid magnesium alloy of described casting mold combination, pour into a mould from bottom to top and form described aluminium, magnesium alloy aero-engine casing by the counter-pressure casting machine.
It should be noted that this step belongs to key of the present invention, namely why will after forming the casting mold combination, be inverted 180 degree cast.This is because aero-engine casing of the present invention is the spiral cone shape, must cause interior core 1 to be the centrum shape, and forms horn-like opening in the middle of outside core 2.And, because the diameter of the large first end of casing is 900-1200mm, be too large really, can only adopt major part lower and the microcephaly assembles in upper mode.But because aero-engine casing average wall thickness of the present invention only has 2.5-3mm, thin especially, required precision is also large especially, in order to obtain high-quality foundry goods, must be by counter-pressure casting machine cast aluminum, magnesium alloy from bottom to top during cast, and must the cast from the foundry goods microcephaly toward the major part direction.
That is to say, when casting mold is combined in assembling, can only adopt major part under mode combine, then be inverted come to make upside down little, finally cast aluminum, magnesium alloy from bottom to top from the sprue gate of this end of microcephaly.Because the reasons in structure of this major diameter complex thin-wall of aero-engine casing of the present invention parts equally, cause the interior core volume, weight is all very large, can only be that interior core is assembled to the positioning and locking of afterwards outside core button being come greatly upside down, interior core inversion 180 degree that will turn separately else if after joining are detained on outside core, large due to the interior core volume and weight equally and casing average wall thickness only has 2.5-3mm, space between interior core and outside core is too little, be easy in assembling, outside core be broken, can not adopt the mode of backstay 15 of the present invention and check lock lever 14 to position locking fully.
Visible from top analysis, due to the aero-engine casing structure, the present invention can only first adopt major part under mode combine, then be inverted come to make upside down little.While so just requiring to install, need accurately location, namely the present invention is provided with backstay 15 in this process, need to lock by check lock lever 14 during inversion.
As shown in Figure 2-5, in the process that prevents casting mold combination upset 180, backstay 15 is from landing the installation sleeve 20 of major part sandbox 13, this end that backstay 15 coordinates with major part sandbox 13 is provided with a flat slotted hole 151, before casting mold combination upset, need in described slotted hole 18, insert a wedged plate 19, in order to backstay 15 is stuck on major part sandbox 13, when overturning like this, backstay 15 just can not skid off installation sleeve 20.
In sum, because the design feature of aero-engine casing of the present invention causes traditional casting method to cast, method of the present invention is in casting mold combination assembling, adopt major part under mode combine, then be inverted come to make upside down little, finally cast aluminum, magnesium alloy from bottom to top from the sprue gate of this end of microcephaly.Casting method of the present invention provides a kind of new casting mold combination and pouring type, has overcome the defect that existing pouring procedure can't be cast, and has solved aero-engine casing foundry goods development bottleneck.
The foregoing is only the schematic specific embodiment of the present invention, not in order to limit scope of the present invention.Any those skilled in the art, the equivalent variations of doing under the prerequisite that does not break away from design of the present invention and principle, modification and combination, all should belong to the scope of protection of the invention.
Claims (5)
1. the casting method of an aluminium, magnesium alloy aero-engine casing, described aero-engine casing is the screw cone shape, one large one small, the diameter of its large first end is 900-1200mm, average wall thickness 2.5-3mm, by aluminium, magnesium alloy integrally cast, formed, described casting method comprises the steps:
Steps A: the major part sandbox that a horizontal positioned is provided, directly over described major part sandbox, be fixed for forming the interior core of the die cavity inboard of described aero-engine casing, described interior core is the centrum shape, the end that the centrum shape of this interior core is large contacts with described major part sandbox, and the little end of shape upward;
Step B: at symmetrical a pair of check lock lever and a pair of backstay installed in the described major part sandbox outside, described check lock lever and described backstay space are arranged;
Step C: microcephaly's sandbox of a plurality of horizontal positioned is provided, forms therein respectively a plurality of outside core in the die cavity outside of described aero-engine casing by molding sand, form the horn-like opening upwards enlarged in the middle of described outside core; Described each microcephaly's sandbox outside is formed with locking hole auricle and the locating hole auricle that can supply described check lock lever and backstay to pass corresponding to the position of above-mentioned check lock lever and backstay;
Step D: after a plurality of microcephaly's sandboxes that are formed with outside core in step C are turned over to turnback, make successively locking hole auricle and the locating hole auricle of described a plurality of microcephaly's sandboxes pass described check lock lever and backstay, after described backstay is accurately located the relative position of described a plurality of microcephaly's sandboxes and major part sandbox, by locking member, described check lock lever is locked the casting mold combination that described a plurality of microcephaly's sandboxes and major part sandbox are rigidly connected and are integral;
Step e: after the described casting mold combination obtained in step C is turned over to turnback, attach it on the counter-pressure casting machine, from bottom pouring mouth cast aluminum, the liquid magnesium alloy of described casting mold combination, pour into a mould from bottom to top and form described aluminium, magnesium alloy aero-engine casing by the counter-pressure casting machine.
2. casting method as claimed in claim 1, it is characterized in that, the end that described backstay coordinates with the installing hole auricle of described major part sandbox arranged outside is that end is gradually thin coniform, in this installing hole auricle, be provided with installation sleeve, the internal diameter of described installation sleeve is less than the maximum outside diameter of described backstay.
3. casting method as claimed in claim 1, it is characterized in that, in described step e, before described casting mold combination upset, in a flat slotted hole that need to arrange at the end that described backstay coordinates with described major part sandbox, insert a wedged plate, so that described backstay is stuck on described major part sandbox.
4. casting method as claimed in claim 1, is characterized in that, each described microcephaly's sandbox outside is provided with the locating hole auricle, is provided with a positioning sleeve in each described locating hole auricle, and the diameter of these positioning sleeves is greater than the maximum gauge of described backstay.
5. casting method as claimed in claim 1, is characterized in that, described backstay is that end is gradually thin coniform away from an end of described major part sandbox.
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| CN201310389098.XA CN103406497B (en) | 2013-08-30 | 2013-08-30 | Method for casting aluminum-magnesium alloy aeroengine box |
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| CN201310389098.XA CN103406497B (en) | 2013-08-30 | 2013-08-30 | Method for casting aluminum-magnesium alloy aeroengine box |
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| CN103406497A true CN103406497A (en) | 2013-11-27 |
| CN103406497B CN103406497B (en) | 2015-02-04 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105583374A (en) * | 2014-10-21 | 2016-05-18 | 沈阳黎明航空发动机(集团)有限责任公司 | Production method for large-size aluminum alloy sealing casing |
| CN113566677A (en) * | 2021-08-25 | 2021-10-29 | 贵州安吉航空精密铸造有限责任公司 | Method for inspecting bosses on circumferential surface of large double-ring casting |
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| JP2000288688A (en) * | 1999-04-05 | 2000-10-17 | Kubota Corp | Method for casting pump casing having guide vane |
| CN1666830A (en) * | 2005-04-07 | 2005-09-14 | 中国南方航空动力机械公司 | Method for casting large-scale complex thin-wall Mg alloy castings |
| KR20110096740A (en) * | 2010-02-23 | 2011-08-31 | 서충배 | Mold for piston of vehicle |
| CN102407285A (en) * | 2011-11-18 | 2012-04-11 | 南京六合金盛机械配件厂 | Casting method of stack sand splicing mold |
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2013
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5668549A (en) * | 1979-11-06 | 1981-06-09 | Kubota Ltd | Casting method of casing for axial-flow and oblique-flow pump |
| JP2000288688A (en) * | 1999-04-05 | 2000-10-17 | Kubota Corp | Method for casting pump casing having guide vane |
| CN1666830A (en) * | 2005-04-07 | 2005-09-14 | 中国南方航空动力机械公司 | Method for casting large-scale complex thin-wall Mg alloy castings |
| KR20110096740A (en) * | 2010-02-23 | 2011-08-31 | 서충배 | Mold for piston of vehicle |
| CN102407285A (en) * | 2011-11-18 | 2012-04-11 | 南京六合金盛机械配件厂 | Casting method of stack sand splicing mold |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105583374A (en) * | 2014-10-21 | 2016-05-18 | 沈阳黎明航空发动机(集团)有限责任公司 | Production method for large-size aluminum alloy sealing casing |
| CN105583374B (en) * | 2014-10-21 | 2018-09-04 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of method of production of large aluminum alloy closing casing |
| CN113566677A (en) * | 2021-08-25 | 2021-10-29 | 贵州安吉航空精密铸造有限责任公司 | Method for inspecting bosses on circumferential surface of large double-ring casting |
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| CN103406497B (en) | 2015-02-04 |
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Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |