CN104259285A - Forming method and fixture of check ring of combustion chamber of aero-engine - Google Patents
Forming method and fixture of check ring of combustion chamber of aero-engine Download PDFInfo
- Publication number
- CN104259285A CN104259285A CN201410361562.9A CN201410361562A CN104259285A CN 104259285 A CN104259285 A CN 104259285A CN 201410361562 A CN201410361562 A CN 201410361562A CN 104259285 A CN104259285 A CN 104259285A
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- Prior art keywords
- cavity
- degree
- ring
- bracer
- mandrel
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Classifications
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- 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
- B21D22/00—Shaping without cutting, by stamping, spinning, or deep-drawing
- B21D22/02—Stamping using rigid devices or tools
-
- 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
- B21D43/00—Feeding, positioning or storing devices combined with, or arranged in, or specially adapted for use in connection with, apparatus for working or processing sheet metal, metal tubes or metal profiles; Associations therewith of cutting devices
- B21D43/003—Positioning devices
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Punching Or Piercing (AREA)
Abstract
A forming method of a check ring of a combustion chamber of an aero-engine comprises the following steps of forming a cavity through punching for constituting the check ring, punching an opening part at 60 degrees, 30 degrees and 0 degree after the cavity is positioned by a fixture to achieve forming of a flange of the opening part, and taking the formed check ring out of the fixture finally. The invention provides the forming method and the fixture of the check ring of the combustion chamber of the aero-engine to solve the problem that a flange of the opening part of the check ring of the combustion chamber of the aero-engine is difficult to machine and form, and the flange of the opening part of check ring of the combustion chamber of the aero-engine can be formed by punching at 60 degrees, 30 degrees and 0 degree via ordinary punch forming equipment. The method is simple to implement, low in cost and suitable for small batch or single-piece production and does not require special equipment. The invention further provides the fixture for the method.
Description
Technical field
The present invention relates to a kind of processing method of aircraft engine parts, especially a kind of forming method of the opening portion for aeroengine combustor buring room back-up ring, present invention also offers a kind of special fixture for above-mentioned forming method.
Background technology
Fig. 1 display be a kind of sectional structure schematic diagram of the combustion chamber back-up ring 1 for aero-engine, it has the tubaeform cavity 12 with, and its upper opening portion inwardly has and the angle of vertical direction is the crimp 11 of 90 degree.Because the combustion chamber back-up ring 1 for aero-engine is thin-wall construction, wall thickness is generally 0.8-2mm, and therefore this combustion chamber back-up ring 1 adopts dedicated liquid forming machine monolithic extruded shaping usually, although simply shaping, but equipment price is higher, is suitable for producing in enormous quantities and still can.
And if general experimental single-piece production adopts this special equipment, buying expenses is higher, is difficult to recoup capital outlay.For saving of purchase cost, the invention provides the technical scheme adopting impact style machine-shaping.As shown in Figure 2, do not form the sectional structure schematic diagram of the described cavity 12 before described crimp 11 for the combustion chamber back-up ring 1 of aero-engine shown in the Fig. 1 wherein shown, that is first the present invention makes the tubaeform cavity 12 of part 1 by the mode such as punching press or casting, then forms described crimp 11 in opening portion at an upper portion thereof by special fixture.
Therefore key point of the present invention is how can by impact style fast and accurately at the crimp of the opening portion of thin-walled tubaeform hollow cavity formation 90 degree, and this is the content do not related in prior art.
Summary of the invention
The technical problem to be solved in the present invention is to provide forming method and the fixture thereof of a kind of aeroengine combustor buring room back-up ring, to reduce or to avoid problem noted earlier.
For solving the problems of the technologies described above, the invention provides the forming method of a kind of aeroengine combustor buring room back-up ring, described part comprises a tubaeform cavity; The upper opening portion of described cavity has the crimp that angle that is inside and vertical direction is 90 degree, and described forming method comprises the steps:
Punching press forms described cavity;
The base plate of a horizontal positioned is provided, described base plate is fixedly connected with a mandrel and a fixed support ring; Multiple movable bracer is placed around described mandrel;
Described cavity is positioned on described base plate around described movable bracer, utilizes described fixed support ring to carry out pre-determined bit to described cavity;
Place an annulus skewback along described mandrel, utilize the conical surface of described annulus skewback outwards to be extruded by described movable bracer and the madial wall of described cavity is blocked location, then described annulus skewback is fixed on described mandrel by nut; Afterwards described movable bracer is fixedly connected with described base plate;
Arrange an installing plate along described mandrel, described installing plate has a U-shaped draw-in groove, by described draw-in groove install side inwall have 60 degree of inclination angles first on modular ring, utilize modular ring on described first to carry out first time 60 degree of punch formings to described cavity;
Modular ring on described first is taken off, described installing plate is installed side inwall have 30 degree of inclination angles second on modular ring, utilize modular ring on described second to carry out second time 30 degree of punch formings to described cavity;
Modular ring upset on modular ring or first on described second is installed by described installing plate, utilizes the flat bottom surface of modular ring on modular ring or described first on described second to carry out third time 0 degree of punch forming to described cavity;
Pull down annulus skewback, unclamp the connection of described movable bracer and described base plate, take out after being drawn in by described movable bracer afterwards to centre, finally stamping forming described part can be taken out, whole punching course terminates.
Present invention also offers a kind of fixture for said method, for positioning with shaping in the back-up ring part punching process of described aeroengine combustor buring room, described part comprises a tubaeform cavity; The upper opening portion of described cavity has the crimp that angle that is inside and vertical direction is 90 degree, and described fixture comprises a base plate; A mandrel be fixedly connected with described base plate; A fixed support ring be fixedly connected with described base plate, multiple movable bracer can placed around described mandrel; An annulus skewback can placed along described mandrel, described movable bracer outwards can extrude and the madial wall of described cavity is blocked location by the conical surface of described annulus skewback; An installing plate with U-shaped draw-in groove; side inwall be fixedly connected with described installing plate by described draw-in groove have 60 degree of inclination angles first on modular ring, side inwall be fixedly connected with described installing plate by described draw-in groove have 30 degree of inclination angles second on modular ring.
The opening portion crimp that the present invention is directed to aeroengine combustor buring room back-up ring part is difficult to the problem of machine-shaping, propose forming method and the fixture thereof of a kind of aeroengine combustor buring room back-up ring, it utilizes common punching press shaping equipment to divide 60 degree, 30 degree, 0 degree three punching press, and the opening portion crimp that can complete aeroengine combustor buring room back-up ring part is shaping.Described method is simple to operate, without the need to special equipment, with low cost, is suitable for small lot or single-piece production.
Accompanying drawing explanation
The following drawings is only intended to schematically illustrate the present invention and explain, not delimit the scope of the invention.Wherein,
Fig. 1 display be a kind of sectional structure schematic diagram of the combustion chamber back-up ring for aero-engine;
What Fig. 2 showed is the sectional structure schematic diagram not forming the cavity before crimp shown in Fig. 1 for the combustion chamber back-up ring of aero-engine;
Fig. 3 display be the perspective exploded view of fixture according to a specific embodiment of the present invention;
Fig. 4 display be the perspective view of the annexation of installing plate shown in Fig. 3 and upper modular ring;
Fig. 5 display be the perspective view of another angle of the annexation of installing plate shown in Fig. 3 and upper modular ring;
Fig. 6 display be that the duty of the fixture shown in Fig. 3 partly cuts open schematic diagram.
Detailed description of the invention
In order to there be understanding clearly to technical characteristic of the present invention, object and effect, now contrast accompanying drawing and the specific embodiment of the present invention is described.Wherein, identical parts adopt identical label.
Just as described in the background section, the invention provides the forming method of a kind of aeroengine combustor buring room back-up ring part 1, its essence is when combustion chamber back-up ring part 1 described in small lot or single-piece production, because cost reason cannot use shaping equipment global formation, and have to adopt a kind of punch forming scheme of simplification.
This impact forming method faced by problem be, because described combustion chamber its wall thickness of back-up ring part 1 is very thin, only has 0.8 ~ 2mm, and maximum gauge reaches 300 ~ 500mm on the whole, and described crimp 11 is 90 degree with the fixture of vertical direction, if therefore with common impact style, be difficult to one-shot forming, and the kink be easy between described cavity 12 and described crimp 11 causes defect, be difficult to the Forming Quality ensureing described crimp 11, therefore key point of the present invention is how to crimp 11 described in substep punch forming, and how to shorten process time, enhance productivity.
Fig. 3 display be the perspective exploded view of fixture according to a specific embodiment of the present invention; Fig. 4 display be the perspective view of the annexation of installing plate shown in Fig. 3 and upper modular ring; Fig. 5 display be the perspective view of another angle of the annexation of installing plate shown in Fig. 3 and upper modular ring; Fig. 6 display be that the duty of the fixture shown in Fig. 3 partly cuts open schematic diagram.
Shown in Fig. 3-6, be institute's problems faced in the forming process of solution part 1, the invention provides the forming method of a kind of aeroengine combustor buring room back-up ring, it comprises the steps:
First, punching press forms the described cavity 12 of described part 1; Can first manufacture respectively by conventional punch forming mode.
Then, provide the base plate 2 of a horizontal positioned, described base plate 2 is fixedly connected with a mandrel 3 and a fixed support ring 4; Multiple movable bracer 5 is placed around described mandrel 3;
In figure, the setting of base plate 2 is mainly gone for the ease of the described cavity 12 of having good positioning is moved to press (not shown) position, therefore as seen from the figure the periphery of base plate 2 is provided with handle 21, so that mobile.Mandrel 3 and base plate 2 junction have a head 31, can be connected by bolt 32 through described head 31 with base plate 2, thus are fixed on a base plate 2 by mandrel 3.
As shown in Figure 3, described movable bracer 5 always has six to the shape of movable bracer 5, comprises four fan-shaped bracers and two wedge shape bracers.These six movable bracers 5 are separate, can move each other, six shapes formed as shown in Figure 3 that are stitched together.
Afterwards, described cavity 12 is positioned on described base plate 2 around described movable bracer 5, utilizes described fixed support ring 4 to carry out pre-determined bit to described cavity 12; Certainly, this location inaccuracy, need follow-up step to correct.
In this step, when putting described movable bracer 5, six movable bracers 5 draw in around mandrel 3, such as first the wedge shape bracer in movable bracer 5 can be drawn close placement to mandrel 3, just can reduce spacing between fan-shaped bracer to draw in together, make the volume-diminished that movable bracer 5 entirety occupies, thus the reducing part of described cavity 12 can be made can to place around described movable bracer 5.
Certainly, if the reducing part of described cavity 12 is very little, how no matter movable bracer 5 draw in, when described cavity 12 still cannot put down, can first rely on described fixed support ring 4 to put well described cavity 12, then six movable bracers 5 be put into successively in the middle of fixed support ring 4 and set.
In addition after, place an annulus skewback 6 along described mandrel 3, utilize the conical surface of described annulus skewback 6 outwards to be extruded by described movable bracer 5 and the madial wall of described cavity 12 is blocked location, then described annulus skewback is fixed on described mandrel by nut; Afterwards described movable bracer 5 is fixedly connected with described base plate 2;
This step is exactly utilize circular skewback 6 to the accurate correction process of location.Wherein, the conical surface 61 of annulus skewback 6 adapts with the internal side surface shape of each movable bracer 5, along with annulus skewback 6 moves down along mandrel 3, movable bracer 5 can be against the conical surface 61 outwards thruster of annulus skewback 6, until the madial wall of cavity 12 firmly withstands motionless by each movable bracer 5, then further by after nut screwing clamping, annulus skewback 6 just can make movable bracer 5 and described fixed support ring 4 form held tight to described cavity 12, this addresses the problem orientation problem.
Emphasis of the present invention when extrusion mo(u)lding carried out to the straight flange of described cavity 12, the crimp 11 of the present invention in order to the straight flange of described cavity 12 being bent to 90 degree, devise the closing-in mould of a set of fast demountable especially, divide 60 degree, 30 degree, 0 degree three punching press, thus make described crimp 11 shaping, the following detailed description of closing-in mould provided by the present invention and the course of work thereof.
After location is completed to described cavity 12, along described mandrel, an installing plate 7 is set, described installing plate 7 has a U-shaped draw-in groove 711, by described draw-in groove 711 install side inwall 811 have 60 degree of inclination alpha first on modular ring 81, utilize modular ring 81 on described first to carry out first time 60 degree of punch formings to described cavity 12;
Described U-shaped draw-in groove 711 can be on one piece of substrate 71, fixedly mount a U-shaped part 72 with L tee section formed.The production technology of described installing plate 7 can be simplified like this.
On described first, the two ends up and down of modular ring 81 all can be provided with flange 812, like this can so that modular ring 81 on described first is inserted or take out described U-shaped draw-in groove 711, thus realize modular ring 81 on described first and dismantle with the Fast Installation of described installing plate 7.
On described first, the inwall 811 of modular ring 81 has 60 degree of inclination alpha, like this, when described installing plate 7 extrudes described cavity 12 under press effect, can form the crimp of 60 degree in the opening portion of described cavity 12.
In addition, after, modular ring 81 on described first is taken off, described installing plate is installed side inwall have 30 degree of inclination angles second on modular ring (not shown), utilize modular ring on described second to carry out second time 30 degree of punch formings to described cavity;
On described second, the structure of modular ring is identical with modular ring 81 on described first; the inclination angle being only its side is different; on described second, the upper and lower two ends of modular ring are provided with flange equally; like this can so that modular ring on described second be inserted or take out described U-shaped draw-in groove 711, thus the Fast Installation realizing modular ring and described installing plate 7 on described second is dismantled.
On described second, the side inwall of modular ring has 30 degree of inclination alpha, like this, when described installing plate 7 extrudes described cavity 12 under press effect, the crimp of 60 degree of the opening portion of described cavity 12 can be squeezed into further the crimp of 30 degree.
In addition after, modular ring 81 on modular ring or first on described second is overturn installation by described installing plate 7, utilize the flat bottom surface of modular ring 81 on modular ring or described first on described second to carry out third time 0 degree of punch forming to described cavity 11;
Form the crimp of 60 degree in the opening portion of described cavity 12 after; modular ring 81 on modular ring or first on described second is overturn installation on described installing plate 7; the flat bottom surface of modular ring 81 on modular ring or first on described second can be utilized to carry out third time 0 degree of punch forming to described cavity 11, thus form described crimp 11.
After described crimp 11 is shaping, pull down described annulus skewback 6, unclamp the connection of described movable bracer 5 and described base plate 2, take out after being drawn in centre by described movable bracer 5 afterwards, finally stamping forming described part 1 can be taken out, whole punching course terminates.
By the explanation of above-mentioned forming method, present invention also offers a kind of fixture for preceding method, for positioning with shaping in back-up ring part 1 punching course of described aeroengine combustor buring room, described part 1 comprises a tubaeform cavity 12; The upper opening portion of described cavity 12 has the crimp 11 that angle that is inside and vertical direction is 90 degree, and described fixture comprises a base plate 2; A mandrel 3 be fixedly connected with described base plate 2; A fixed support ring 4 be fixedly connected with described base plate 2, multiple movable bracer 5 can placed around described mandrel 3; An annulus skewback 6 can placed along described mandrel 3, described movable bracer 5 outwards can extrude and the madial wall of described cavity 12 is blocked location by the conical surface 61 of described annulus skewback 6; An installing plate 7 with U-shaped draw-in groove 711; side inwall 811 removably connected by described draw-in groove 711 and described installing plate 7 have 60 degree of inclination alpha first on modular ring 81, by the side inwall that described draw-in groove 711 is fixedly connected with described installing plate 7 have 30 degree of inclination angles second on modular ring.
The opening portion crimp that the present invention is directed to aeroengine combustor buring room back-up ring part is difficult to the problem of machine-shaping, propose forming method and the fixture thereof of a kind of aeroengine combustor buring room back-up ring, it utilizes common punching press shaping equipment to divide 60 degree, 30 degree, 0 degree three punching press, and the opening portion crimp that can complete aeroengine combustor buring room back-up ring part is shaping.Described method is simple to operate, without the need to special equipment, with low cost, is suitable for small lot or single-piece production.
Although it will be appreciated by those skilled in the art that the present invention is described according to the mode of multiple embodiment, not each embodiment only comprises an independently technical scheme.So describe in description be only used to clear for the purpose of; description should integrally be understood by those skilled in the art, and regards technical scheme involved in each embodiment as the mode that mutually can be combined into different embodiment to understand protection scope of the present invention.
The foregoing is only the schematic detailed description of the invention of the present invention, and be not used to limit scope of the present invention.Any those skilled in the art, the equivalent variations done under the prerequisite not departing from design of the present invention and principle, amendment and combination, all should belong to the scope of protection of the invention.
Claims (2)
1. a forming method for aeroengine combustor buring room back-up ring, described part comprises a tubaeform cavity; The upper opening portion of described cavity has the crimp that angle that is inside and vertical direction is 90 degree, and it is characterized in that, described forming method comprises the steps:
Punching press forms described cavity;
The base plate of a horizontal positioned is provided, described base plate is fixedly connected with a mandrel and a fixed support ring; Multiple movable bracer is placed around described mandrel;
Described cavity is positioned on described base plate around described movable bracer, utilizes described fixed support ring to carry out pre-determined bit to described cavity;
Place an annulus skewback along described mandrel, utilize the conical surface of described annulus skewback outwards to be extruded by described movable bracer and the madial wall of described cavity is blocked location, then described annulus skewback is fixed on described mandrel by nut; Afterwards described movable bracer is fixedly connected with described base plate;
Arrange an installing plate along described mandrel, described installing plate has a U-shaped draw-in groove, by described draw-in groove install side inwall have 60 degree of inclination angles first on modular ring, utilize modular ring on described first to carry out first time 60 degree of punch formings to described cavity;
Modular ring on described first is taken off, described installing plate is installed side inwall have 30 degree of inclination angles second on modular ring, utilize modular ring on described second to carry out second time 30 degree of punch formings to described cavity;
Modular ring upset on modular ring or first on described second is installed by described installing plate, utilizes the flat bottom surface of modular ring on modular ring or described first on described second to carry out third time 0 degree of punch forming to described cavity;
Pull down annulus skewback, unclamp the connection of described movable bracer and described base plate, take out after being drawn in by described movable bracer afterwards to centre, finally stamping forming described part can be taken out, whole punching course terminates.
2., for a fixture for method according to claim 1, for positioning with shaping in the back-up ring part punching process of described aeroengine combustor buring room, described part comprises a tubaeform cavity; The upper opening portion of described cavity has the crimp that angle that is inside and vertical direction is 90 degree, and described fixture comprises a base plate; A mandrel be fixedly connected with described base plate; A fixed support ring be fixedly connected with described base plate, multiple movable bracer can placed around described mandrel; An annulus skewback can placed along described mandrel, described movable bracer outwards can extrude and the madial wall of described cavity is blocked location by the conical surface of described annulus skewback; An installing plate with U-shaped draw-in groove; side inwall be fixedly connected with described installing plate by described draw-in groove have 60 degree of inclination angles first on modular ring, side inwall be fixedly connected with described installing plate by described draw-in groove have 30 degree of inclination angles second on modular ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410361562.9A CN104259285B (en) | 2014-07-28 | 2014-07-28 | The forming method of a kind of aeroengine combustor buring room back-up ring and fixture thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410361562.9A CN104259285B (en) | 2014-07-28 | 2014-07-28 | The forming method of a kind of aeroengine combustor buring room back-up ring and fixture thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104259285A true CN104259285A (en) | 2015-01-07 |
| CN104259285B CN104259285B (en) | 2016-02-24 |
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| CN201410361562.9A Active CN104259285B (en) | 2014-07-28 | 2014-07-28 | The forming method of a kind of aeroengine combustor buring room back-up ring and fixture thereof |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1207968A (en) * | 1997-08-08 | 1999-02-17 | 周兴平 | Two-step rings billet punching formation and composite die used therein |
| CN101633021A (en) * | 2009-08-11 | 2010-01-27 | 河南省电力公司新乡供电公司 | Hooping cold bending punch forming module |
| CN102430642A (en) * | 2011-09-19 | 2012-05-02 | 天津市津兆机电开发有限公司 | Molding process of progressive die of high temperature alloy sheet metal component with high flanging hole |
| CN102658327A (en) * | 2010-12-23 | 2012-09-12 | 福特环球技术公司 | Method of reducing cycle time in a hydro-mechanical forming process and a tool for hydro-mechanically forming a part |
| CN103611805A (en) * | 2013-11-20 | 2014-03-05 | 江苏荣腾精密组件科技股份有限公司 | Punching stretching tool |
-
2014
- 2014-07-28 CN CN201410361562.9A patent/CN104259285B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1207968A (en) * | 1997-08-08 | 1999-02-17 | 周兴平 | Two-step rings billet punching formation and composite die used therein |
| CN101633021A (en) * | 2009-08-11 | 2010-01-27 | 河南省电力公司新乡供电公司 | Hooping cold bending punch forming module |
| CN102658327A (en) * | 2010-12-23 | 2012-09-12 | 福特环球技术公司 | Method of reducing cycle time in a hydro-mechanical forming process and a tool for hydro-mechanically forming a part |
| CN102430642A (en) * | 2011-09-19 | 2012-05-02 | 天津市津兆机电开发有限公司 | Molding process of progressive die of high temperature alloy sheet metal component with high flanging hole |
| CN103611805A (en) * | 2013-11-20 | 2014-03-05 | 江苏荣腾精密组件科技股份有限公司 | Punching stretching tool |
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| Publication number | Publication date |
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| CN104259285B (en) | 2016-02-24 |
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Address after: 412000 No. 2 Airway Road, Lusong District, Zhuzhou City, Hunan Province Patentee after: Hunan Nanfang General Aviation Engine Co., Ltd. Address before: 412002 No. 2 Aviation Road, Lusong District, Zhuzhou City, Hunan Province Patentee before: AVIC HUNAN GENERAL AVIATION ENGINE CO., LTD. |