CN203864035U - Airplane blade forming tooling - Google Patents
Airplane blade forming tooling Download PDFInfo
- Publication number
- CN203864035U CN203864035U CN201420287320.5U CN201420287320U CN203864035U CN 203864035 U CN203864035 U CN 203864035U CN 201420287320 U CN201420287320 U CN 201420287320U CN 203864035 U CN203864035 U CN 203864035U
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- CN
- China
- Prior art keywords
- fan blade
- lower bolster
- blade forming
- aircraft fan
- forming frock
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Abstract
The utility model provides an airplane blade forming tooling, belongs to the field of airplane manufacturing, and solves the problem that no available equipment or toolings can be provided for the production of a composite airplane blade. The airplane blade forming tooling comprises an upper die plate with an upper forming cavity and a lower die plate with a lower forming cavity; the upper die plate and the lower die plate are subjected to mold closing to form a forming cavity; heating holes are formed in the upper die plate and the lower die plate respectively; a shaft sleeve positioning column is fixed onto the lower die plate; a demoulding device capable of ejecting an airplane blade in the forming cavity out is arranged on the lower die plate. The airplane blade forming tooling is suitable for producing the composite airplane blade, can ensure the consistency of blades, and has the advantages of being simple in structure and convenient to demould.
Description
Technical field
The utility model belongs to aircraft manufacturing technical field, particularly relates to a kind of aircraft fan blade forming frock.
Background technology
Aircraft fan blade is one of core component of gas-turbine unit.Higher revolution, tall and big mechanical strength, longer blade and lighter weight are the problems that aircraft fan blade will solve all the time.
Before, Boeing has designed and has produced the fan blade of the engine of a kind of crying " wide string is without convex shoulder hollow interlayer structure blade ", and blade has adopted the shape of wide string to strengthen mechanical strength and hollow-core construction to reduce weight; Blade also adopts titanium-alloy thin-plate to make, and also reduces thus weight.
Along with scientific and technological development, General Corporation has designed again and has produced the fan blade that adopts composite to make.Composite is as carbon fibre composite, fiberglass.Especially the made blade structure weight of carbon fibre composite is extremely light, and intensity is very big.Above-mentioned blade structure as shown in Figure 1, comprises the leaf dish and the blade that adopt metal axle sleeve and adopt composite to make; Blade is connected with the lateral surface of leaf dish, and blade is obliquely installed with respect to leaf disk axis.At present, the domestic process equipment of not manufacturing above-mentioned composite fan blade.
Summary of the invention
The purpose of this utility model is to have the problems referred to above for existing technology, has proposed a kind of forming frock of applicable production technique for aircraft composite fan blade.
The purpose of this utility model can realize by following technical proposal: this aircraft fan blade forming frock, it is characterized in that, this forming frock comprises the cope match-plate pattern with upper forming cavity and the lower bolster with compacted under chamber, cope match-plate pattern and lower bolster matched moulds are formed into die cavity, all offer bottoming hole on cope match-plate pattern and lower bolster; Described lower bolster is fixed with axle sleeve locating dowel; Described lower bolster is provided with the stripper apparatus that the aircraft fan blade in forming cavity can be ejected.
Utilize this forming frock to produce aircraft fan blade, insert heating rod in bottoming hole, axle sleeve is first set in axle sleeve locating dowel, then lays composite in compacted under chamber, then matched moulds and heating cope match-plate pattern and lower bolster; After last aircraft fan blade moulding, parting and employing stripper apparatus eject aircraft fan blade in compacted under chamber.
In above-mentioned aircraft fan blade forming frock, described upper forming cavity and compacted under chamber all have leaf disc molding chamber, have and contain clout groove on the bottom surface in described leaf disc molding chamber.The component of laying composite may the actual required component of slightly unnecessary product, and so much remaining composite is just squeezed into be contained in clout groove.
In above-mentioned aircraft fan blade forming frock, described Sheng clout groove is annular groove, annular groove axis and the dead in line of axle sleeve locating dowel.
In above-mentioned aircraft fan blade forming frock, described compacted under chamber has blade forming chamber, and the length in blade forming chamber is slightly larger than the length of aircraft leaf blade; The space of laying unnecessary composite is held in formation, and above-mentioned space is positioned at the outer end in blade forming chamber, and this structure is easily removed overlap, also avoids overlap to affect the fineness of blade side simultaneously.
In above-mentioned aircraft fan blade forming frock, described stripper apparatus comprises stripper plate, on the bottom surface, leaf disc molding chamber of lower bolster, has several guide through hole, is all equipped with a thimble in each guide through hole, and all thimbles are all fixedly connected with stripper plate.
In above-mentioned aircraft fan blade forming frock, on described stripper plate, be equipped with some guide pillars, a side of stripper plate is provided with base plate, and base plate is fixedly connected with lower bolster, and guide pillar is fixedly connected with base plate; Between stripper plate and lower bolster, be provided with back-moving spring, back-moving spring is set on guide pillar.
In above-mentioned aircraft fan blade forming frock, described guide pillar end face and lower bolster bottom surface lean, and this structure can improve the fixing stability of guide pillar.
In above-mentioned aircraft fan blade forming frock, described stripper apparatus also comprises some parting push rods, and parting push rod is located in lower bolster, and parting push rod is fixedly connected with stripper plate.When parting, cope match-plate pattern can be backed down with respect to lower bolster, aircraft fan blade be ejected in compacted under chamber simultaneously, impeller of blower is attached on cope match-plate pattern, and then conveniently takes off impeller of blower.
Compared with prior art, this forming frock is applicable to producing technique for aircraft composite fan blade, utilizes this forming frock to produce the uniformity that aircraft fan blade can guarantee product.This forming frock has simple in structure, the advantage being convenient in demoulding.
Accompanying drawing explanation
Fig. 1 is the perspective view of aircraft fan blade.
Fig. 2 is the perspective view of this aircraft fan blade forming frock.
Fig. 3 is the main TV structure schematic diagram of this aircraft fan blade forming frock.
Fig. 4 is the sectional structure schematic diagram of A-A in Fig. 3.
Fig. 5 is the sectional structure schematic diagram of B-B in Fig. 3.
Fig. 6 is the sectional structure schematic diagram of C-C in Fig. 3.
Fig. 7 is the sectional structure schematic diagram of D-D in Fig. 3.
Fig. 8 is A place structure enlarged drawing in Fig. 7.
Fig. 9 is B place structure enlarged drawing in Fig. 7.
Figure 10 is the perspective view of this aircraft fan blade forming frock cope match-plate pattern.
Figure 11 is the perspective view of this aircraft fan blade forming frock lower bolster.
In figure, 1, aircraft fan blade; 1a, axle sleeve; 1b, leaf dish; 1c, blade; 2, cope match-plate pattern; 3, lower bolster; 4, base plate; 5, axle sleeve locating dowel; 6, contain clout groove; 7, bottoming hole; 8, stripper plate; 9, thimble; 10, guide pillar; 11, back-moving spring; 12, parting push rod; 13, leaf disc molding chamber; 14, blade forming face; 15, blade forming chamber.
The specific embodiment
Be below specific embodiment of the utility model by reference to the accompanying drawings, the technical solution of the utility model is further described, but the utility model be not limited to these embodiment.
As shown in Fig. 2, Fig. 3 and Fig. 7, this aircraft fan blade forming frock comprises cope match-plate pattern 2, lower bolster 3, base plate 4 and stripper apparatus.
In cope match-plate pattern 2, there is upper forming cavity, in lower bolster 3, there is compacted under chamber; Cope match-plate pattern 2 is formed into die cavity with lower bolster 3 matched moulds; Lower bolster 3 is fixed with axle sleeve locating dowel 5, and axle sleeve locating dowel 5 is positioned at compacted under chamber.Specifically, as shown in figure 10, upper forming cavity comprises leaf disc molding chamber 13 and blade forming face 14.As shown in figure 11, compacted under chamber comprises leaf disc molding chamber 13 and blade forming chamber 15; Hence one can see that, and the die joint of this forming frock is with respect to the position of aircraft fan blade 1, and this structure has the demoulding and is easy to advantage.As shown in Figure 8 and Figure 9, on leaf disc molding chamber 13 in cope match-plate pattern 2 and 13 bottom surfaces, leaf disc molding chamber in lower bolster 3, all have and contain clout groove 6, contain clout groove 6 and be positioned at 13 places, base angle, leaf disc molding chamber, containing clout groove 6 is annular groove, annular groove axis and 5 deads in line of axle sleeve locating dowel.As shown in Figure 7, the length in blade forming chamber 15 is slightly larger than the length of aircraft fan blade 1 blade 1c; The space of laying unnecessary composite is held in formation, and above-mentioned space is positioned at the outer end in blade forming chamber 15.
As shown in Figures 4 to 7, on cope match-plate pattern 2 and lower bolster 3, all offer four bottoming holes 7.
As shown in Figures 2 to 7, stripper apparatus is arranged on lower bolster 3, and stripper apparatus can eject the aircraft fan blade 1 in forming cavity.Specifically, stripper apparatus comprises stripper plate 8, thimble 9, guide pillar 10, back-moving spring 11 and parting push rod 12.Base plate 4 is positioned at the downside of lower bolster 3, and base plate 4 is fixedly connected with lower bolster 3.Stripper plate 8 is between base plate 4 and lower bolster 3.On 13 bottom surfaces, leaf disc molding chamber of lower bolster 3, have several guide through hole, be all equipped with a thimble 9 in each guide through hole, all thimbles 9 are all fixedly connected with stripper plate 8.Promote stripper plate 8, thimble 9 ejects aircraft fan blade 1, and several guide through hole are circumferentially uniformly distributed and can improve aircraft fan blade 1 stress balance around axle sleeve locating dowel 5 axis.
As shown in Figure 5, the quantity of guide pillar 10 is the six roots of sensation, and guide pillar 10 is located on stripper plate 8; Guide pillar 10 bottoms are fixedly connected with base plate 4, and guide pillar 10 end faces and lower bolster 3 bottom surfaces lean; Promote in stripper plate 8 processes, stripper plate 8 moves along guide pillar 10, and then effectively improves the stability of stripper plate 8 motions, and then guarantees aircraft fan blade 1 stress balance.
Back-moving spring 11 is set on guide pillar 10, and one end of back-moving spring 11 and stripper plate 8 lean, and the other end and lower bolster 3 lean, and stripper plate 8 can automatically reset until stripper plate 8 leans with base plate 4 under the elastic force effect of back-moving spring 11.
As shown in Figure 6, the quantity of parting push rod 12 is four, is located in respectively the place, four angles of lower bolster 3, and parting push rod 12 is fixedly connected with stripper plate 8.
Claims (9)
1. an aircraft fan blade forming frock, it is characterized in that, this forming frock comprises the cope match-plate pattern (2) with upper forming cavity and the lower bolster (3) with compacted under chamber, cope match-plate pattern (2) is formed into die cavity with lower bolster (3) matched moulds, on cope match-plate pattern (2) and lower bolster (3), all offers bottoming hole (7); Described lower bolster (3) is fixed with axle sleeve locating dowel (5); Described lower bolster (3) is provided with the stripper apparatus that the aircraft fan blade (1) in forming cavity can be ejected.
2. aircraft fan blade forming frock according to claim 1, is characterized in that, described upper forming cavity and compacted under chamber all have leaf disc molding chamber (13), has and contain clout groove (6) on the bottom surface in described leaf disc molding chamber (13).
3. aircraft fan blade forming frock according to claim 2, is characterized in that, described Sheng clout groove (6) is positioned at place, base angle, leaf disc molding chamber (13).
4. aircraft fan blade forming frock according to claim 2, is characterized in that, described Sheng clout groove (6) is annular groove, annular groove axis and axle sleeve locating dowel (5) dead in line.
5. aircraft fan blade forming frock according to claim 1, is characterized in that, described compacted under chamber has blade forming chamber (15), and the outer end of blade forming chamber (15) has the space that holds unnecessary composite.
6. according to the aircraft fan blade forming frock described in any one in claim 1 to 5, it is characterized in that, described stripper apparatus comprises stripper plate (8), on the bottom surface, leaf disc molding chamber (13) of lower bolster (3), have several guide through hole, in each guide through hole, be all equipped with a thimble (9), all thimbles (9) are all fixedly connected with stripper plate (8).
7. aircraft fan blade forming frock according to claim 6, it is characterized in that, on described stripper plate (8), be equipped with some guide pillars (10), one side of stripper plate (8) is provided with base plate (4), base plate (4) is fixedly connected with lower bolster (3), and guide pillar (10) is fixedly connected with base plate (4); Between stripper plate (8) and lower bolster (3), be provided with back-moving spring (11), back-moving spring (11) is set on guide pillar (10).
8. aircraft fan blade forming frock according to claim 7, is characterized in that, described guide pillar (10) end face and lower bolster (3) bottom surface lean.
9. aircraft fan blade forming frock according to claim 6, it is characterized in that, described stripper apparatus also comprises some parting push rods (12), and parting push rod (12) is located in lower bolster (3), and parting push rod (12) is fixedly connected with stripper plate (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420287320.5U CN203864035U (en) | 2014-05-29 | 2014-05-29 | Airplane blade forming tooling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420287320.5U CN203864035U (en) | 2014-05-29 | 2014-05-29 | Airplane blade forming tooling |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203864035U true CN203864035U (en) | 2014-10-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420287320.5U Expired - Fee Related CN203864035U (en) | 2014-05-29 | 2014-05-29 | Airplane blade forming tooling |
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| CN (1) | CN203864035U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106273551A (en) * | 2016-10-13 | 2017-01-04 | 西北工业大学 | Shape-memory alloy fibers strengthens the one-body molded equipment of composite RTM |
| CN106938549A (en) * | 2017-05-05 | 2017-07-11 | 湖南大学 | A kind of adjustable RTM mold of sheet thickness self adaptation and plate preparation method |
| CN107225737A (en) * | 2016-03-24 | 2017-10-03 | 浙江正泰电器股份有限公司 | The ejecting mechanism of injection mold |
-
2014
- 2014-05-29 CN CN201420287320.5U patent/CN203864035U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107225737A (en) * | 2016-03-24 | 2017-10-03 | 浙江正泰电器股份有限公司 | The ejecting mechanism of injection mold |
| CN107225737B (en) * | 2016-03-24 | 2024-04-12 | 浙江正泰电器股份有限公司 | Ejection mechanism of injection mold |
| CN106273551A (en) * | 2016-10-13 | 2017-01-04 | 西北工业大学 | Shape-memory alloy fibers strengthens the one-body molded equipment of composite RTM |
| CN106273551B (en) * | 2016-10-13 | 2018-08-14 | 西北工业大学 | Shape Memory Alloy Fibers enhance composite material RTM and are integrally formed equipment |
| CN106938549A (en) * | 2017-05-05 | 2017-07-11 | 湖南大学 | A kind of adjustable RTM mold of sheet thickness self adaptation and plate preparation method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Airplane blade forming tooling Effective date of registration: 20180806 Granted publication date: 20141008 Pledgee: Zhejiang Tailong commercial bank Taizhou branch of Limited by Share Ltd Pledgor: ZHEJIANG HUARONG AVIATION EQUIPMENT CO., LTD. Registration number: 2018330000220 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141008 Termination date: 20200529 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |