CN105363975A - Method for forming high-temperature alloy flange for aeroengine - Google Patents
Method for forming high-temperature alloy flange for aeroengine Download PDFInfo
- Publication number
- CN105363975A CN105363975A CN201510867745.2A CN201510867745A CN105363975A CN 105363975 A CN105363975 A CN 105363975A CN 201510867745 A CN201510867745 A CN 201510867745A CN 105363975 A CN105363975 A CN 105363975A
- Authority
- CN
- China
- Prior art keywords
- bulging
- base
- pass
- section
- mounting edge
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21H—MAKING PARTICULAR METAL OBJECTS BY ROLLING, e.g. SCREWS, WHEELS, RINGS, BARRELS, BALLS
- B21H1/00—Making articles shaped as bodies of revolution
- B21H1/06—Making articles shaped as bodies of revolution rings of restricted axial length
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D37/00—Tools as parts of machines covered by this subclass
- B21D37/10—Die sets; Pillar guides
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D37/00—Tools as parts of machines covered by this subclass
- B21D37/16—Heating or cooling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D39/00—Application of procedures in order to connect objects or parts, e.g. coating with sheet metal otherwise than by plating; Tube expanders
- B21D39/08—Tube expanders
- B21D39/20—Tube expanders with mandrels, e.g. expandable
Abstract
The invention discloses a method for forming a high-temperature alloy flange for an aeroengine. The method comprises the following steps: firstly, heating a high-temperature alloy blanked according to specifications until a deformation temperature, carrying out upsetting and punching, and then carrying out rolling to form a ring blank; secondly, dividing and marking the ring blank to divide the ring blank into arc sections corresponding to various edges of the flange, next, performing local bulging on each arc section to obtain a corresponding deflection, and further carrying out pre-budging and finish bulging to obtain the desired flange. The flange prepared by use of the method is relatively high in structure properties, dimensional accuracy and material utilization rate, and good in quality consistency and reliability. The method is mainly used for producing the high-temperature alloy flanges for the aeroengines .
Description
Technical field
The present invention relates to a kind of manufacturing process of mounting edge, particularly relate to a kind of manufacturing process of aero-engine high temperature alloy mounting edge.
Background technology
Mounting edge is a kind of part common in aero-engine, and be a kind of fan-shape polygon frame Structure type part, the sectional area of its each frame is all not identical, eachly belongs to complex class structural member.Because the cross section difference of mounting edge is large, shaping difficulty is very large, and production efficiency is low, and material consumption is very large.For a long time, all continue to use head of a bed manufacturing process to the making of such part both at home and abroad, waste of raw materials is serious, production efficiency is low, and series-produced mounting edge uniformity is poor.
Disclosed in 5 days Mays in 2010, Chinese invention patent description CN101700557A discloses a kind of mounting edge vertical forging and forming technology, its basic craft course is: blanking → jumping-up → punching → reaming → head-stamp → monolateral elongation → button angle → shaping → school shape, its whole process is mainly carried out on flat-die hammer, and the vertical forging achieving mounting edge is shaped.But adopt when producing mounting edge in this way, due to the difference of mounting edge cross section and arc length, when carrying out flat-die hammer pulling to the upper and lower segmental arc of mounting edge, be difficult to precisely control; And the method needs surplus very large, not easily beats and leans on; Owing to needing the artificial subjective size controlling mounting edge, its precision can not get effective control; And stock utilization is very low.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of manufacturing process of aero-engine high temperature alloy mounting edge, by the forming mode adopting looping mill rolling to combine with bulging, effectively can control the size of mounting edge, obtain the mounting edge meeting tissue, performance and dimensional requirement, and improve stock utilization.
For solving the problems of the technologies described above, the manufacturing process of aero-engine high temperature alloy mounting edge of the present invention, its technical scheme comprises the following steps:
High temperature alloy by specification blanking is heated to deformation temperature, after jumping-up jumping-up, punching, is rolled into ring base;
Described ring base is divided, head-stamp, described ring base is divided into ab, bc, cd, ad tetra-sections, and wherein, the arc chord angle corresponding to ab section is 128 DEG C, and the arc chord angle corresponding to cd section is 114 DEG C, and ad section and the arc chord angle corresponding to bc section are respectively 59 DEG C;
Ring base good for described head-stamp being heated to bulging temperature loads on the bulging device of local, and this device is by base, two base fixture blocks, 3 front bulging blocks, bulging block, two core fixture blocks and mandrel slide block form after 3; Forward and backward bulging block is different from mandrel slider contact surface gradient, and its ratio is α: β=2:3; Drive the core fixture block on the bulging device of local and base fixture block that the ad section of ring base and bc section are clamped and fixed; Mandrel slide block is driven to move down, and promote front bulging block, rear bulging block and respectively bulging is carried out to the ab section of ring base and cd section, in Bulging Process, by cooling water pipe to clamped ad section and bc section water-spraying control, to improve this resistance of deformation of two sections, make these the two sections shapes that substantially remain unchanged in Bulging Process; After bulging completes, obtain local bulging base;
Between upper and lower two metal baffle local bulging base being put into pre-expanding die former, and align with the pass of metal baffle, with fastening spring, local bulging base is fixed; Again the microcephaly of formpiston is inserted in the pass of pre-bulging former, from top to bottom, through local bulging base, and pre-bulging is carried out to it, obtain pre-bulging base;
Between upper and lower two metal baffle pre-bulging ring base being put into whole expanding die former, and align with the pass of metal baffle, then the microcephaly of formpiston is inserted in the pass of whole bulging former, from top to bottom, through pre-bulging base, and whole bulging is carried out to it, obtain mounting edge.
The formpiston of described pre-expanding die is a drift, and its shape is similar to the pass of mounting edge, and from top to bottom, its cross-sectional area reduces gradually; Former is made up of the metal baffle of upper and lower two-layer band pass and the rectangular metal contiguous block that connects them, and lower baffle plate has 4 for fastening spring, the pass of upper and lower baffle plate is all similar to the pass of mounting edge.
The formpiston of described whole expanding die is a drift, and its shape is similar to the pass of mounting edge, and from top to bottom, its cross-sectional area reduces gradually; Former is made up of the metal baffle of upper and lower two-layer band pass and the rectangular metal contiguous block that connects them, lower baffle plate there are 4 for fastening spring, the pass of upper and lower baffle plate is all similar to the pass of mounting edge, and the limit shape of metal contiguous block is consistent with the lower arc limit of mounting edge.
Compared with prior art, beneficial effect of the present invention is as follows:
The manufacturing process of aero-engine high temperature alloy mounting edge of the present invention, the forming mode adopting looping mill rolling to combine with bulging instead of free forging mode, improve the quality conformance of product, reliability, improve production efficiency, reduce raw materials consumption.For the shaped as frame that changes of section is larger, adopt local bulging to reduce sectional area, the open die forging pulling mode before instead of, this process is easy to control.Local bulging adopts water-cooling pattern, increases the resistance of deformation of this position after making the Local cooling of ring base, ensure that two arc limits are indeformable or only produce small deformation in Bulging Process.On the other hand, local expanding die adopts bielliptic(al) structure, because front bulging block is different from the gradient of rear bulging block, is out of shape different bielliptic(al) blanks.The former of pre-bulging device and whole bulging device all adopts double-decker, and formpiston can be facilitated to extract, and can prevent blank from Bulging Process, the defects such as warpage occurring.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
Fig. 1 is the ring base schematic diagram rolling rear acquisition in advance.
Fig. 2 is division, the head-stamp schematic diagram of ring base.
Fig. 3 is local shape expanding machine apparatus structure schematic diagram.
Fig. 4 is the installation schematic diagram of local Bulging Process.
Fig. 5 is the gradient structural representation of front bulging block and rear bulging block.
Fig. 6 is the vesica piscis base schematic diagram that local bulging obtains.
Fig. 7 is the formpiston structural representation of pre-bulging device, whole bulging device.
Fig. 8 is the former perspective view of pre-bulging device.
Fig. 9 is the former stereochemical structure sectional view of pre-bulging device.
Figure 10 is the installation schematic diagram of pre-Bulging Process.
Figure 11 is the pre-bulging base schematic diagram that pre-bulging obtains.
Figure 12 is the former stereochemical structure sectional view of whole bulging device.
Figure 13 is the view at the end of whole bulging.
Figure 14 is the structural representation of mounting edge.
Detailed description of the invention
This aero-engine manufacturing process of high temperature alloy mounting edge, its concrete operation step is as follows:
1 blanking.Bar is cutting into by specification, the material used is the nickel base superalloy of Britain material trademark C263, its main chemical elements content (percentage by weight) is: C content 0.04% ~ 0.08%, containing Cr amount 19.0% ~ 21.0%, containing Co amount 19.0% ~ 21.0%, containing Mo amount 5.60% ~ 6.10%, containing Al amount 0.30% ~ 0.60%, containing Ti amount 1.90% ~ 2.40%, containing Al+Ni amount 2.4% ~ 2.8%, containing Fe amount≤0.70%, containing B amount≤0.0050%, containing Mn amount≤0.60%, si content≤0.40%, containing S amount≤0.007%, containing Cu amount≤0.20%, containing Ag amount≤0.0005%, containing Bi amount≤0.0001%, containing Pb amount≤0.0020%, surplus is Ni.
2, ring base processed.C263 bar is loaded in high-temperature electric resistance furnace and is heated to 1120 DEG C ± 10 DEG C, through jumping-up, punching, roll in advance after obtain ring base 10, as shown in Figure 1.
3, division, head-stamp.Ring base 10 is divided, head-stamp, ring 10 is divided into ab, bc, cd, ad tetra-sections, as shown in Figure 2.Arc chord angle corresponding to ab section is 128 DEG C, and the arc chord angle corresponding to cd section is 114 DEG C, and ad section and the arc chord angle corresponding to bc section circular arc are respectively 59 DEG C.
4, local bulging.This process need uses local bulging device, and this device is made up of bulging block 42, two core fixture blocks 50 and mandrel slide block 100 after base 20, two base fixture blocks 30,3 front bulging blocks 41,3, as shown in Figure 3.Front bulging block 41, rear bulging block 42 are different from mandrel slide block 100 contact face slope, and its ratio is α: β=2:3, as shown in Figure 5.
After ring base 10 good for head-stamp is heated to bulging temperature, load on the bulging device of local; Drive the core fixture block 50 on the bulging device of local and base fixture block 30 that the ad section of ring base 10 and bc section are clamped and fixed, as shown in Figure 4; Mandrel slide block 100 is driven to move down, and promote front bulging block 41, rear bulging block 42 and respectively bulging is carried out to the ab section of ring base and cd section, in Bulging Process, by cooling water pipe to clamped ad section and bc section water-spraying control, to improve this resistance of deformation of two sections, make these the two sections shapes that substantially remain unchanged in Bulging Process; After bulging completes, obtain local bulging base 11, as shown in Figure 6.
5, pre-bulging.This process need uses pre-bulging device, and the formpiston 60 of this device is a drift, and its shape is similar to the pass of mounting edge, and from top to bottom, its cross-sectional area reduces gradually, as shown in Figure 7.Former 70 is made up of the metal baffle of upper and lower two-layer band pass and the rectangular metal contiguous block that connects them, and lower baffle plate has 4 for fastening spring 71, the pass of upper and lower baffle plate is all similar to the pass of mounting edge, as shown in Figure 8, Figure 9.
After vesica piscis base 11 is heated to bulging temperature, between upper and lower two metal baffle putting into pre-bulging former 70, and aligns with the pass of metal baffle, with fastening spring 71, vesica piscis base 11 is fixed, as shown in Figure 10; Again the microcephaly of formpiston 60 is inserted in the pass of pre-bulging former 70, from top to bottom, through vesica piscis base 11, and pre-bulging is carried out to it; After pre-bulging, obtain pre-bulging base 12, the lower arc limit of pre-bulging base 12 is a cambered outwards arc limit, as shown in figure 11.
6, whole bulging.This process need uses whole bulging device, and the formpiston of this device and the formpiston of pre-bulging device are same mould; The former of this device is similar to the former of pre-bulging device, and just the metal contiguous block of connection two baffle plates changes to some extent, and the limit shape of its metal contiguous block is consistent with the lower arc limit of mounting edge, as shown in figure 12.
After pre-bulging base 12 is heated to bulging temperature, between upper and lower two metal baffle putting into whole bulging former 80, and align with the pass of metal baffle, again the microcephaly of formpiston 60 is inserted in the pass of whole bulging former 80, from top to bottom, through pre-bulging base 12, and whole bulging is carried out to it, as shown in figure 13.Obtain final mounting edge 13, as shown in figure 14.
Claims (3)
1. an aero-engine manufacturing process for high temperature alloy mounting edge, is characterized in that, comprise the following steps:
High temperature alloy by specification blanking is heated to deformation temperature, after jumping-up jumping-up, punching, is rolled into ring base;
Described ring base is divided, head-stamp, described ring base is divided into ab, bc, cd, ad tetra-sections, and wherein, the arc chord angle corresponding to ab section is 128 DEG C, and the arc chord angle corresponding to cd section is 114 DEG C, and ad section and the arc chord angle corresponding to bc section are respectively 59 DEG C;
Ring base good for described head-stamp being heated to bulging temperature loads on the bulging device of local, and this device is by base, two base fixture blocks, 3 front bulging blocks, bulging block, two core fixture blocks and mandrel slide block form after 3; Forward and backward bulging block is different from mandrel slider contact surface gradient, and its ratio is α: β=2:3; Drive the core fixture block on the bulging device of local and base fixture block that the ad section of ring base and bc section are clamped and fixed; Mandrel slide block is driven to move down, and promote front bulging block, rear bulging block and respectively bulging is carried out to the ab section of ring base and cd section, in Bulging Process, by cooling water pipe to clamped ad section and bc section water-spraying control, to improve this resistance of deformation of two sections, make these the two sections shapes that substantially remain unchanged in Bulging Process; After bulging completes, obtain local bulging base;
Between upper and lower two metal baffle local bulging base being put into pre-expanding die former, and align with the pass of metal baffle, with fastening spring, local bulging base is fixed; Again the microcephaly of formpiston is inserted in the pass of pre-bulging former, from top to bottom, through local bulging base, and pre-bulging is carried out to it, obtain pre-bulging base;
Between upper and lower two metal baffle pre-bulging ring base being put into whole expanding die former, and align with the pass of metal baffle, then the microcephaly of formpiston is inserted in the pass of whole bulging former, from top to bottom, through pre-bulging base, and whole bulging is carried out to it, obtain mounting edge.
2. according to the manufacturing process of claim 1 aero-engine with high temperature alloy mounting edge, it is characterized in that, the formpiston of described pre-expanding die is a drift, and its shape is similar to the pass of mounting edge, and from top to bottom, its cross-sectional area reduces gradually; Former is made up of the metal baffle of upper and lower two-layer band pass and the rectangular metal contiguous block that connects them, and lower baffle plate has 4 for fastening spring, the pass of upper and lower baffle plate is all similar to the pass of mounting edge.
3. according to the manufacturing process of claim 1 aero-engine with high temperature alloy mounting edge, it is characterized in that, the formpiston of described whole expanding die is a drift, and its shape is similar to the pass of mounting edge, and from top to bottom, its cross-sectional area reduces gradually; Former is made up of the metal baffle of upper and lower two-layer band pass and the rectangular metal contiguous block that connects them, lower baffle plate there are 4 for fastening spring, the pass of upper and lower baffle plate is all similar to the pass of mounting edge, and the limit shape of metal contiguous block is consistent with the lower arc limit of mounting edge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510867745.2A CN105363975A (en) | 2015-12-02 | 2015-12-02 | Method for forming high-temperature alloy flange for aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510867745.2A CN105363975A (en) | 2015-12-02 | 2015-12-02 | Method for forming high-temperature alloy flange for aeroengine |
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| Publication Number | Publication Date |
|---|---|
| CN105363975A true CN105363975A (en) | 2016-03-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510867745.2A Pending CN105363975A (en) | 2015-12-02 | 2015-12-02 | Method for forming high-temperature alloy flange for aeroengine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109434397A (en) * | 2018-12-11 | 2019-03-08 | 陕西宏远航空锻造有限责任公司 | A kind of preparation method of superalloy annular forging expanding die |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1031592A1 (en) * | 1982-04-28 | 1983-07-30 | Предприятие П/Я М-5953 | Die for expanding shells |
| CN102489596A (en) * | 2011-11-24 | 2012-06-13 | 贵州安大航空锻造有限责任公司 | Hot bulging method for forming rectangular titanium alloy rolled ring into special-shaped ring |
| CN204171159U (en) * | 2014-09-01 | 2015-02-25 | 福瑞盛航空机件（苏州）有限公司 | A kind of high temperature alloy shaped as frame ring forming frock |
| CN104550583A (en) * | 2014-12-15 | 2015-04-29 | 贵州安大航空锻造有限责任公司 | Method for rolling and forming alpha-phase titanium alloy thick-wall ring forging |
| CN104624879A (en) * | 2014-12-15 | 2015-05-20 | 贵州安大航空锻造有限责任公司 | Roll forming method for thick-wall ring forging of bearing steel |
| CN104801598A (en) * | 2015-04-23 | 2015-07-29 | 西北工业大学 | Bulging die for titanium-alloy thin-walled complicated irregular annular workpieces |
-
2015
- 2015-12-02 CN CN201510867745.2A patent/CN105363975A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1031592A1 (en) * | 1982-04-28 | 1983-07-30 | Предприятие П/Я М-5953 | Die for expanding shells |
| CN102489596A (en) * | 2011-11-24 | 2012-06-13 | 贵州安大航空锻造有限责任公司 | Hot bulging method for forming rectangular titanium alloy rolled ring into special-shaped ring |
| CN204171159U (en) * | 2014-09-01 | 2015-02-25 | 福瑞盛航空机件（苏州）有限公司 | A kind of high temperature alloy shaped as frame ring forming frock |
| CN104550583A (en) * | 2014-12-15 | 2015-04-29 | 贵州安大航空锻造有限责任公司 | Method for rolling and forming alpha-phase titanium alloy thick-wall ring forging |
| CN104624879A (en) * | 2014-12-15 | 2015-05-20 | 贵州安大航空锻造有限责任公司 | Roll forming method for thick-wall ring forging of bearing steel |
| CN104801598A (en) * | 2015-04-23 | 2015-07-29 | 西北工业大学 | Bulging die for titanium-alloy thin-walled complicated irregular annular workpieces |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109434397A (en) * | 2018-12-11 | 2019-03-08 | 陕西宏远航空锻造有限责任公司 | A kind of preparation method of superalloy annular forging expanding die |
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Application publication date: 20160302 |