CN109228397B - Composite material propeller mould pressing die and product thereof - Google Patents
Composite material propeller mould pressing die and product thereof Download PDFInfo
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- CN109228397B CN109228397B CN201810880242.2A CN201810880242A CN109228397B CN 109228397 B CN109228397 B CN 109228397B CN 201810880242 A CN201810880242 A CN 201810880242A CN 109228397 B CN109228397 B CN 109228397B
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- 239000002131 composite material Substances 0.000 title claims abstract description 62
- 238000003825 pressing Methods 0.000 title abstract description 22
- 238000004519 manufacturing process Methods 0.000 claims abstract description 11
- 238000007723 die pressing method Methods 0.000 claims abstract description 5
- 238000000465 moulding Methods 0.000 claims description 17
- 238000000748 compression moulding Methods 0.000 claims description 9
- 125000006850 spacer group Chemical group 0.000 claims 2
- 230000006835 compression Effects 0.000 claims 1
- 238000007906 compression Methods 0.000 claims 1
- 239000000463 material Substances 0.000 abstract description 6
- 239000003292 glue Substances 0.000 description 9
- 229920000049 Carbon (fiber) Polymers 0.000 description 8
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- 238000000034 method Methods 0.000 description 8
- 238000010586 diagram Methods 0.000 description 7
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 7
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- 238000001228 spectrum Methods 0.000 description 2
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- 238000004804 winding Methods 0.000 description 2
- 229910000776 Common brass Inorganic materials 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
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- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
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- 239000002184 metal Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3067—Ships
Abstract
The invention discloses a composite material propeller die pressing die which comprises a cover plate and an outer die arranged on the cover plate, wherein the die further comprises a large end cover, a small end cover, a framework die and a unit die, the structures of the large end cover and the small end cover are matched, the large end cover and the small end cover respectively comprise a multi-layer cylinder structure, the framework die comprises a front framework core die, a framework oblique block and a rear framework core die, and the unit die comprises a front core die, a core die oblique block and a rear core die. The invention also discloses a composite propeller. The mould pressing mould of the composite material propeller is used for carrying out presoaking mould pressing forming on the presoaked material through the mould cavities formed by combining the plurality of groups of framework moulds to obtain the blank mould of the propeller, continuously paving presoaked material on the surface of the blank mould through the mould cavities formed by combining the plurality of groups of unit moulds, and carrying out mould pressing forming again to manufacture the composite material propeller, so that the structural strength of the composite material propeller can be ensured, the profile precision of the composite material propeller can be ensured, and the problems of low manufacturing precision, insufficient structural strength and the like of the composite material propeller are solved.
Description
Technical Field
The invention belongs to the technical field of mold structures, and particularly relates to a mold pressing mold of a composite material propeller and a product thereof.
Background
Mechanical (structural) noise, propeller noise and flow noise constitute the ship's underwater radiation sound field. As the speed of the ship increases, the boat propeller noise becomes a major part of the radiated noise. The noise of the propeller is self radiation noise, noise caused by wake field and tail vibration noise caused by the propeller. Studies have shown that propeller noise is a wideband continuum of subsonic frequencies from a few hertz up to hundreds of kilohertz supersonic frequencies superimposed with a few low frequency characteristic line spectra, the line spectra having frequencies that are the propeller's blade frequency and its various orders of blade frequencies. The propeller noise in the middle-low frequency range is mainly caused by the pulsating pressure born by the blades and the vortex in the wake of the propeller, the main noise in the middle-high frequency range is cavitation noise, and the propeller can also generate singing sound caused by karman vortex street in the high frequency range.
Compared with the traditional metal propeller, the composite propeller has the characteristics of low vibration, low noise, light weight, high efficiency, seawater corrosion resistance, easiness in maintenance and the like.
Patent number CN101704302A discloses an integral molding die of a composite propeller and a manufacturing method thereof, and mainly aims to solve the problems that a hub and a blade shafting of the existing propeller vibrate and the root of the blade is easy to damage. The die consists of an upper die block, a lower die and a cover plate, is manufactured by adopting an RTM process, and is suitable for composite material propellers with less blades and small blade curvature. Patent number CN104149361a discloses a method for manufacturing a secondarily molded carbon fiber composite propeller, which comprises the steps of selecting and processing a die and a material, then performing primary molding on a propeller hub, and performing secondary molding on the propeller, so that the process is simple and mature, and autonomous production of the carbon fiber composite propeller is realized. Patent number CN103253367a discloses a preparation mould of composite material air propeller, through designing composite material air propeller into split type structure, including last wallboard appearance face mould, last wallboard interior shape face mould, lower wallboard appearance face mould and lower wallboard interior shape face mould, last wallboard appearance face mould and go up wallboard interior shape face mould and dock the cooperation each other inside and form last wallboard die cavity. At present, the complex composite material propeller forming process is mainly split forming, the blades are formed by RTM (resin transfer molding), and then are positioned in a column shape with the hub, and the adopted dies are mainly propeller blade RTM dies; the composite material propeller with fewer blades and simple structure mostly adopts RTM, mould pressing technology and the like.
Disclosure of Invention
Aiming at the defects or improvement demands in the prior art, the invention provides a mould pressing mould of a composite material propeller and a product thereof, and aims to provide the mould pressing mould of the composite material propeller and the product thereof.
In order to achieve the above object, according to one aspect of the present invention, there is provided a composite material pusher molding die comprising a cover plate and an outer die provided on the cover plate, the die further comprising a large end cap, a small end cap, a skeleton die and a unit die; wherein,
the large end cover and the small end cover are matched in structure and comprise a multi-layer cylinder structure so as to form a boss structure at the opposite ends of the large end cover and the small end cover;
the framework mold comprises a front framework core mold, a framework oblique block and a rear framework core mold, wherein the front framework core mold, the framework oblique block and the rear framework core mold are six-sided special-shaped pieces, shoulders matched with the boss structures are arranged at two ends of the six-sided special-shaped pieces, and a plurality of groups of mold cavities formed by combining the framework molds are subjected to prepreg compression molding to obtain a blank mold of the propeller;
the unit die comprises a front core die, a core die oblique block and a rear core die, the front core die, the core die oblique block and the rear core die are six-sided special-shaped pieces, shoulders matched with the boss structures are arranged at two ends of the front core die, a plurality of groups of die cavities formed after the unit die are combined are convenient for continuously paving prepreg on the surface of the blank die and performing compression molding to manufacture the composite material propeller.
Further, the front core mold is a six-sided special-shaped piece, wherein the upper end and the lower end of the front core mold are planes, the front end surface and the left end surface of the front core mold are three-dimensional value surfaces of the blank mold, the conical surface of the outer end of the front core mold is a non-working surface and is in contact with the outer mold, and the right end plane is in contact with the core mold inclined block.
Further, the oblique block of the core mold is a six-sided special-shaped piece, wherein the upper end and the lower end of the oblique block are planes, the front end face of the oblique block is the three-dimensional model value face of the blank mold, the conical surface at the outer end is a non-working face and is provided with an oblique block demoulding hole, and the left plane and the right plane are respectively contacted with the front core mold and the rear core mold.
Further, the back core mould is a six-sided special-shaped piece, wherein the upper end and the lower end are planes, the back end and the right end face are three-dimensional value faces of the blank mould, the conical surface of the outer end is a non-working face and is contacted with the outer mould, and the plane of the left end is contacted with the core mould inclined block.
Further, the big end cover comprises a big end cover top plate, a big end cover boss and a mandrel, a countersunk cylindrical through hole is formed in the center of the mandrel, a plurality of cylindrical bolt through holes are uniformly formed in the periphery of the big end cover top plate, and the outer diameter of a cylinder of the big end cover boss is matched with a cylindrical hole of a product to ensure concentricity of the big end cover boss and the product.
Further, the small end cover comprises a small end cover boss and a small end cover bottom plate, a countersunk inner hexagonal cylindrical through hole is formed in the center of the small end cover boss, and the outer diameter of a cylinder of the small end cover bottom plate is matched with a product cylindrical hole to ensure concentricity with a product.
Further, the outer die is of a conical boss structure with a hollow inside and comprises an outer die body and an outer die end cover, and the outer die body is of a structure with an inclined angle.
Further, the cover plate is of a cylindrical structure, a cylindrical through hole is formed in the center of the cover plate, a plurality of cylindrical holes are uniformly distributed around the cover plate, and the bottom end of each cylindrical hole is an inner hexagonal countersink.
The die also comprises an auxiliary tool, wherein the auxiliary tool comprises an inner hexagon screw, a nut, a square nut, a large cushion block, a small cushion block, a bracket and a die puller.
According to another aspect of the invention, a product is provided, which is manufactured using the composite pusher molding die.
In general, the above technical solutions conceived by the present invention, compared with the prior art, enable the following beneficial effects to be obtained:
(1) The invention relates to a mould pressing mould of a composite material propeller, which comprises a cover plate, an outer mould, a large end cover, a small end cover, a framework mould, a unit mould and auxiliary tools, wherein a mould cavity formed by combining a plurality of groups of framework moulds is used for carrying out prepreg mould pressing to obtain a blank mould of the propeller, the prepreg is continuously paved on the surface of the blank mould by using the mould cavity formed by combining a plurality of groups of unit moulds, and the composite material propeller is manufactured by mould pressing again, so that the structural strength of the composite material propeller can be ensured, the profile precision of the composite material propeller can be ensured, and the problems of low manufacturing precision, insufficient structural strength and the like of the composite material propeller in the prior art can be simultaneously solved.
(2) The mould pressing mould of the composite material propeller has similar structure, the difference is that the structure size of the skeleton mould is smaller than that of the unit mould, the skeleton mould is convenient for the first prepreg mould pressing process to form a propeller blank mould, the unit mould is used for continuously paving prepreg on the surface of the blank mould for the second time, and the composite material propeller is manufactured by mould pressing again, so that the two mould pressing forming of the composite material propeller is realized, and the manufacturing precision of the composite material propeller is improved.
(3) The invention relates to a mould pressing mould of a composite material propeller, which comprises a front core mould, a core mould oblique block and a rear core mould, wherein the three groups of the unit moulds are combined along a hub gear to form a mould core, a mould cavity formed after the combination is in the shape of a blade of the propeller, a certain amount of carbon fiber prepreg is put into the mould cavity, and after the mould is combined, the carbon fiber prepreg is heated and softened in the mould cavity under the action of certain temperature and pressure, flows under pressure, is filled in the mould cavity to be molded and solidified into a composite material product, namely the composite material propeller.
(4) The mould pressing mould of the composite material propeller disclosed by the invention has the advantages that the skeleton mould and the unit mould are six-sided special-shaped pieces, the upper end surface and the lower end surface of the skeleton mould are plane surfaces and are provided with the shoulders which are respectively matched with the large end cover boss and the small end cover boss, so that the tight mould closing of the skeleton mould and the unit mould and the large end cover and the small end cover is ensured, and the mould precision is further improved.
(5) The outer die of the die-pressing die of the composite material propeller is of an inner hollow conical boss structure and comprises an outer die body and an outer die end cover, the outer die body is inclined to ensure smooth demoulding and effective force transmission, threaded holes are uniformly distributed in the center of the top end of the outer die body and are used for demoulding products, two cylindrical boss holes are symmetrically formed in the circumferential direction of the outer die body, and when the turnover shaft is inserted, the whole die can be turned over and can be used for demoulding of the outer die.
(6) The large end cover of the mould pressing mould of the composite material propeller consists of a multi-layer cylindrical structure, a countersunk cylindrical through hole is arranged in the center of a mandrel and used for locking the upper end cover and the lower end cover, a plurality of cylindrical bolt through holes are uniformly arranged on the periphery of a top plate of the large end cover, small cushion blocks are placed at the bottom ends of the through holes, the holes and the cushion blocks are used for demoulding the large end cover and preventing glue overflow, the cylinder outer diameter of the top plate of the large end cover is matched with the cylindrical hole of the through hole of the cover plate to ensure the mould heart, and the cylinder outer diameter of the boss of the large end cover is matched with the cylindrical hole of the product to ensure concentricity of the product and the glue overflow.
(7) The invention relates to a mould pressing mould of a composite material propeller, a small end cover consists of a multi-layer cylindrical structure, a countersunk inner hexagonal cylindrical through hole is arranged in the center of a boss of the small end cover and used for locking an upper end cover and a lower end cover, a plurality of cylindrical bolt through holes are uniformly arranged on the periphery of the boss of the small end cover, a large cushion block is placed at the bottom end of the through hole, the holes and the cushion block are used for demoulding the small end cover, meanwhile, glue overflow is prevented, the outer diameter of a cylinder of a bottom plate of the small end cover is matched with a cylindrical hole of a through hole of a cover plate, the outer diameter of the cylinder of the boss of the small end cover is matched with an inner diameter hole of the lower end of the cylinder of the large end cover to jointly ensure concentricity of a product, and the concentricity of the small bottom plate cylinder of the small end cover and the cylindrical hole of the product are matched with the cylindrical hole of the product.
(8) The product prepared by the mould pressing mould of the composite material propeller disclosed by the invention has the advantages that the structural weight is reduced by 17% compared with that of a common brass alloy propeller, the propelling efficiency is higher, the production efficiency of the whole mould pressing technology is high, and compared with the traditional manual molding and RTM technology, the product has the advantages of good integrity, smaller deviation of a model value, stable technology and higher strength.
Drawings
FIG. 1 is a schematic structural view of a composite propeller according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a molding die of a composite pusher according to an embodiment of the present invention;
FIG. 3 is a schematic view of the assembly of a large end cap, hub gear and small end cap according to an embodiment of the present invention;
FIG. 4 is a schematic view of a rotor hub gear ply winding structure in accordance with an embodiment of the present invention;
FIG. 5 is a schematic diagram of a skeleton mold and a unit mold according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of a skeleton or unit die structure according to an embodiment of the invention;
FIG. 7 is a schematic view of a front skeleton mold or a front core mold according to an embodiment of the present invention;
FIG. 8 is a schematic diagram of a framework or core module according to an embodiment of the present invention;
FIG. 9 is a schematic view of a rear matrix or rear core mold according to an embodiment of the present invention;
FIG. 10 is a schematic diagram of a cover plate according to an embodiment of the invention;
FIG. 11 is a schematic diagram of an outer mold structure according to an embodiment of the present invention;
FIG. 12 is a schematic view of a large end cap according to an embodiment of the present invention;
FIG. 13 is a schematic view of a small end cap according to an embodiment of the present invention;
fig. 14 is a schematic structural diagram of a mold drawer according to an embodiment of the invention.
Like reference numerals denote like technical features throughout the drawings, in particular: 1-cover plate, 2-outer mold, 201-outer mold body, 202-outer mold end cap, 3-large end cap, 301-large end cap top plate, large end cap boss, 303-mandrel, 4-small end cap, 401-small end cap boss, 402-small end cap bottom plate, 601-front core mold, 6011-front core mold curved surface, 6012-front core mold bottom shoulder, 6013-front core mold top shoulder, 602-core mold oblique block, 6022-oblique block bottom shoulder, 6023-oblique block top shoulder, 603-rear core mold, 6031-rear core mold curved surface, 6032-rear core mold bottom shoulder, 6033-rear core mold top shoulder, 604-oblique block demolding hole, 7-auxiliary tool, 8-hub gear, 801-first ply, 802-second ply, 803-third ply, 804-fourth ply, 9-blade.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
Fig. 1 is a schematic structural view of a composite propeller according to an embodiment of the present invention. As shown in fig. 1, the composite propeller comprises a hub and blades, wherein the blades are three-way curved surfaces, the structure is complex, the molding precision is required to be high, and the materials of the blades are composite materials, so that the structural strength requirement must be met, the molding process is complex, and the mold design faces great difficulties. In order to solve the problems, the invention divides the compression molding of the composite material propeller into two molding, adopts the skeleton mold to carry out the prepreg compression molding process for molding the propeller blank mold for the first time, adopts the unit mold for the second time, continuously spreads and sticks the prepreg on the surface of the blank mold, and carries out compression molding again to manufacture the composite material propeller, and the first molding and the second molding are carried out according to a certain proportion, thereby ensuring the product strength and the product precision.
As shown in fig. 2 to 14, an embodiment of the present invention provides a composite material pusher molding die including a cover plate 1, an outer die 2, a large end cap 3, a small end cap 4, a skeleton die, a unit die 6, and an auxiliary tool 7. As shown in fig. 2, the large end cover 3 is sleeved with the hub gear 8 and then is matched and fixed with the small end cover 4, and the large end cover 3 is matched and fixed and then is used for winding on the outer circle Zhou Fenceng of the hub gear according to the model value of the propeller product, so that the hub is manufactured. As shown in fig. 3, the structural profile of the hub gear is preferably divided into four different curved surface structures, namely a first pavement 801, a second pavement 802 and a third pavement 803, namely a fourth pavement 804, wherein the first pavement 801 is of a trapezoid structure, the cross section of the second pavement 802 is approximately of a trapezoid structure, the short side of the second pavement 802 is tightly attached to the long side of the first pavement 801, the third pavement 803 is arranged between the small end cover 4 and the second pavement 802, the cross section of the third pavement 803 is of a triangle structure, the cross section of the fourth pavement 804 is of a quadrilateral structure, one side of the fourth pavement is tightly attached to the long side of the third pavement 803, fibers between the various pavements are preferably continuous, and the packaging hub has required structural strength.
As shown in fig. 5-9, the skeleton mold is similar to the unit mold 6 in structure, and the only difference is that the structural size of the skeleton mold is smaller than that of the unit mold 6, so that the skeleton mold is used for molding the prepreg mold by the prepreg compression molding process for the first time, the unit mold 6 is used for continuously paving the prepreg on the surface of the prepreg mold for the second time, and the composite material propeller is manufactured by compression molding again. The framework mold comprises a front framework core mold, a framework oblique block and a rear framework core mold. The cavity parts of the combined multiple groups of framework molds 5 form a propeller blank mold structure, the outer wall is a conical boss, and the outer wall is adhered to the inner wall of the outer mold and transmits force to the propeller structure of the inner wall.
For clarity of description of the structural form of the skeleton mold and the unit mold 6, taking the unit mold 6 as an example, the unit mold 6 includes a front core mold 601, a core mold inclined block 602 and a rear core mold 603, and the three are in a group, and the total multiple groups of unit molds 6 are assembled along the hub gear 8 to form a mold core. Preferably, the unit die 6 is 11 groups, the die cavity formed after the unit die 6 is assembled is in the shape of a blade of a propeller, a certain amount of carbon fiber prepreg is placed into the die cavity, and after the unit die is assembled, the carbon fiber prepreg is heated and softened in the die cavity, flows under pressure and under the action of certain temperature and pressure, and is fully filled in the die cavity to be molded and solidified into a composite material product.
As shown in fig. 7, the front core mold 601 is a six-sided shaped piece in which both upper and lower ends are flat surfaces, and a front core mold bottom shoulder 6012 and a front core mold top shoulder 6013 are provided, similar to a jig. The front core mold curved surface 6011 is a three-dimensional curved surface, namely an embryo model value surface; the conical surface of the outer end is a non-working surface and is contacted with the outer die 2, so that the stress is high; the right end plane is in contact with the core die bevel 602.
As shown in fig. 8, the core mold inclined block 602 is a six-sided special-shaped piece, wherein the upper end and the lower end are planes, and an inclined block bottom shoulder 6022 and an inclined block top shoulder 6023 are arranged, which are similar to a jig; the front three-dimensional curved surface is an embryo model value surface; the rear conical surface is a non-working surface and is provided with an inclined block demoulding hole 604, and the left plane and the right plane are respectively contacted with the front mandrel and the rear mandrel.
The rear core die 603 is a six-sided shaped piece, in which the upper and lower ends are flat surfaces, provided with a rear core die bottom shoulder 6032 and a rear core die top shoulder 6033, similar to a jig; the curved surfaces of the rear core mould at the rear end and the right end are three-dimensional curved surfaces, namely embryo model value surfaces; the conical surface of the outer end is a non-working surface and is contacted with the outer die, so that the stress is high; the left end plane is in contact with the core die bevel 602.
The auxiliary tool 7 comprises various types of hexagon socket screws and nuts, square nuts, large cushion blocks, small cushion blocks, a bracket and a die puller.
As shown in fig. 10, the cover plate 1 has a cylindrical structure, a cylindrical through hole is arranged in the center, a plurality of cylindrical holes are uniformly distributed around the cylindrical through hole, and the bottom end of the cylindrical hole is an inner hexagonal countersink.
As shown in fig. 11, the outer mold 2 is a conical boss structure with hollow inside, and comprises an outer mold body 201 and an outer mold end cover 202, wherein the inclined angle of the outer mold body 201 can ensure smooth demolding and can effectively transfer force, threaded holes are uniformly distributed in the center of the top end of the outer mold body for demolding of products, two cylindrical boss holes are symmetrically formed in the circumferential direction of the outer mold body 201, and after the turnover shaft is inserted, the whole mold can be turned over and can be used for demolding of the outer mold. A plurality of cylindrical holes are uniformly distributed around the outer die end cover 202 and are used for being matched with corresponding cylindrical holes of the cover plate 1, and the cover plate and the outer die are locked by inner hexagonal cylindrical screw bolts to apply pressure; an annular glue overflow groove is formed in the inner ring of the outer mold end cover 202.
As shown in fig. 12 and 13, after the large end cover 3 and the small end cover 4 are assembled and matched, the large end cover 3 and the small end cover 4 can be locked by the inner hexagon screw and the nut, the end parts of the large end cover 3 and the small end cover 4 are respectively provided with counter bore interference fit, and the screw heads and the nut are respectively arranged in the counter bores, so that the assembly of other parts is not affected.
As shown in fig. 12, the large end cover 3 is composed of a multi-layer cylindrical structure, which is respectively a large end cover top plate 301, a large end cover boss 302 and a mandrel 303, wherein a countersunk cylindrical through hole is arranged in the center of the mandrel 303 and used for locking the upper end cover and the lower end cover; a plurality of cylindrical bolt through holes are uniformly formed in the periphery of the top plate 301 of the large end cover, small cushion blocks are placed at the bottom ends of the through holes, and the holes and the cushion blocks are used for demoulding the large end cover and preventing glue overflow; the outer diameter of the cylinder of the large end cover top plate 301 is matched with the cylinder hole of the through hole of the cover plate 1 to ensure the mold concentricity; the outer diameter of the large end cover boss 302 cylinder is matched with the cylindrical hole of the product to ensure concentricity with the product and solve the problem of glue overflow.
As shown in fig. 13, the small end cover 4 is composed of a multi-layer cylindrical structure, namely a small end cover boss 401 and a small end cover bottom plate 402, wherein a countersunk inner hexagonal cylindrical through hole is formed in the center of the small end cover boss 401 and used for locking the upper end cover and the lower end cover, a plurality of cylindrical bolt through holes are uniformly formed in the periphery of the small end cover boss 401, a large cushion block is placed at the bottom end of each through hole, and the holes and the cushion blocks are used for demolding of the small end cover and preventing glue overflow; the outer diameter of the cylinder of the bottom plate 402 of the small end cover is matched with the cylinder hole of the through hole of the cover plate, and the outer diameter of the cylinder of the boss 401 of the small end cover is matched with the inner diameter hole of the lower end of the cylinder of the large end cover to jointly ensure concentricity with a product; the outer diameter of the cylinder of the bottom plate 402 of the small end cover is matched with the cylindrical hole of the product to ensure concentricity with the product and solve the problem of glue overflow.
The large cushion block and the small cushion block are of cylindrical structures, the surfaces of the structures are smooth, chamfers are arranged on the upper end faces, the circumferential dimension is in interference fit with the counter bore at the corresponding position of the large end cover and the small end cover, and the lower end faces are kept complete to prevent glue overflow.
As shown in fig. 14, the mold drawing device is composed of a top screw, a rotating sleeve, a smooth stud and a movable sleeve, wherein the top screw is replaceable and rotatable, the rotating sleeve can lock the top screw, the movable sleeve can freely slide on the smooth stud, and the movable sleeve can slide away from a mold stripping hole during film stripping.
Preferably, the large end cover 3, the small end cover 4, the framework die and the unit die 6 are made of P20 materials, the thermal expansion coefficients of the materials and the carbon fibers are closest to each other, and the precision of the products after the products are subjected to film stripping is better ensured;
the method of combining laser scanning and three coordinates is adopted to detect the product wax pattern and the carbon fiber prepreg pattern line, and the result shows that the precision of the composite material molding die value reaches 0.05mm, and the precision of the molded composite material product reaches 0.25mm.
It will be readily appreciated by those skilled in the art that the foregoing description is merely a preferred embodiment of the invention and is not intended to limit the invention, but any modifications, equivalents, improvements or alternatives falling within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (7)
1. The composite material propeller die pressing die comprises a cover plate and an outer die arranged on the cover plate, and is characterized by further comprising a large end cover, a small end cover, a framework die and a unit die; wherein,
the large end cover and the small end cover are matched in structure and comprise a multi-layer cylinder structure so as to form a boss structure at the opposite ends of the large end cover and the small end cover;
the framework mold comprises a front framework core mold, a framework oblique block and a rear framework core mold, wherein the front framework core mold, the framework oblique block and the rear framework core mold are six-sided special-shaped pieces, shoulders matched with the boss structures are arranged at two ends of the six-sided special-shaped pieces, and a plurality of groups of mold cavities formed by combining the framework molds are subjected to prepreg compression molding to obtain a blank mold of the propeller;
the unit die comprises a front core die, a core die oblique block and a rear core die, wherein the front core die, the core die oblique block and the rear core die are six-sided special-shaped pieces, shoulders matched with the boss structures are arranged at two ends of the front core die, the core die oblique block and the rear core die, a plurality of groups of die cavities formed by combining the unit die are convenient for continuously paving prepreg on the surface of the blank die and performing compression molding to manufacture the composite material propeller;
the front core mold is a six-sided special-shaped piece, wherein the upper end and the lower end of the front core mold are planes, the front end surface and the left end surface of the front core mold are three-dimensional value surfaces of the blank mold, the conical surface of the outer end of the front core mold is a non-working surface and is contacted with the outer mold, and the right end plane is contacted with the core mold inclined block;
the core mould inclined block is a six-sided special-shaped piece, wherein the upper end and the lower end of the core mould inclined block are planes, the front end face of the core mould inclined block is a three-dimensional value face of the blank mould, the conical surface of the outer end of the core mould inclined block is a non-working face and is provided with an inclined block demoulding hole, and the left plane and the right plane are respectively contacted with the front core mould and the rear core mould;
the rear core mold is a six-sided special-shaped piece, wherein the upper end and the lower end are planes, the rear end and the right end face are three-dimensional model value faces of the blank mold, the conical surface of the outer end is a non-working face and is contacted with the outer mold, and the plane of the left end is contacted with the core mold inclined block.
2. The composite material propeller die pressing die of claim 1, wherein the large end cover comprises a large end cover top plate, a large end cover boss and a mandrel, a countersunk cylindrical through hole is formed in the center of the mandrel, a plurality of cylindrical bolt through holes are uniformly formed in the periphery of the large end cover top plate, and the outer diameter of a cylinder of the large end cover boss is matched with the cylindrical hole of a product to ensure concentricity with the product.
3. The composite pusher molding die of claim 1, wherein the small end cap comprises a small end cap boss and a small end cap bottom plate, a countersunk inner hexagonal cylindrical through hole is arranged in the center of the small end cap boss, and the cylindrical outer diameter of the small end cap bottom plate is matched with the cylindrical hole of the product to ensure concentricity with the product.
4. The composite pusher die of claim 1 wherein the outer die is an internally hollow conical boss structure comprising an outer die body and an outer die end cap, the outer die body being of an angled configuration.
5. The composite material propeller die pressing die of claim 1, wherein the cover plate is of a cylindrical structure, a cylindrical through hole is formed in the center of the cover plate, a plurality of cylindrical holes are uniformly distributed on the periphery of the cover plate, and an inner hexagonal countersink is formed in the bottom end of each cylindrical hole.
6. The composite pusher die of claim 1, further comprising an auxiliary tool comprising socket head cap screws and nuts, square nuts, large spacers, small spacers, brackets, and a extractor.
7. A composite pusher prepared using a composite pusher compression mold according to any one of claims 1-6.
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| CN114248473A (en) * | 2021-12-20 | 2022-03-29 | 中国电子科技集团公司第十四研究所 | Carbon fiber machine case shaping mold core structure |
| CN114559680A (en) * | 2022-01-27 | 2022-05-31 | 武汉海威船舶与海洋工程科技有限公司 | Autoclave forming die and forming method for ship propeller composite material blade |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004018186A1 (en) * | 2002-08-20 | 2004-03-04 | Mitsubishi Rayon Co.,Ltd. | Method of producing formed product of fiber-reinforced composite material and the formed product |
| CN201249523Y (en) * | 2008-07-29 | 2009-06-03 | 王维东 | Mold for wholly molding glass fibre reinforced plastic centrifugal fan vanes |
| CN101486256A (en) * | 2008-01-18 | 2009-07-22 | 明安国际企业股份有限公司 | Method for manufacturing armrest of transportation means seat and product produced thereby |
| KR20110132648A (en) * | 2010-06-03 | 2011-12-09 | 김병하 | A flexible propeller and a method for manufacturing thereof |
| CN103128981A (en) * | 2011-11-30 | 2013-06-05 | 波音公司 | Stabilized dry preform and method |
| CN204054418U (en) * | 2014-01-17 | 2014-12-31 | 佛山市建准电子有限公司 | Impeller |
| CN105269833A (en) * | 2014-11-04 | 2016-01-27 | 北京盛华瑞科技有限公司 | Two-time compression molding technology for thermoplastic composite material |
| DE102014222841A1 (en) * | 2014-11-10 | 2016-05-12 | Zf Friedrichshafen Ag | Method for producing an at least approximately rotationally symmetrical fiber-plastic composite component with at least one axial undercut section |
| CN106553357A (en) * | 2016-11-09 | 2017-04-05 | 江苏恒神股份有限公司 | Hollow multi-cavity abnormal shape surface composite material complex structural member integral forming technique |
| CN208993139U (en) * | 2018-08-03 | 2019-06-18 | 中国人民解放军92578部队 | A kind of Composite propulsor molding die and products thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010141984A1 (en) * | 2009-06-12 | 2010-12-16 | Quickstep Technologies Pty Ltd | Method of producing advanced composite components |
-
2018
- 2018-08-03 CN CN201810880242.2A patent/CN109228397B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004018186A1 (en) * | 2002-08-20 | 2004-03-04 | Mitsubishi Rayon Co.,Ltd. | Method of producing formed product of fiber-reinforced composite material and the formed product |
| CN101486256A (en) * | 2008-01-18 | 2009-07-22 | 明安国际企业股份有限公司 | Method for manufacturing armrest of transportation means seat and product produced thereby |
| CN201249523Y (en) * | 2008-07-29 | 2009-06-03 | 王维东 | Mold for wholly molding glass fibre reinforced plastic centrifugal fan vanes |
| KR20110132648A (en) * | 2010-06-03 | 2011-12-09 | 김병하 | A flexible propeller and a method for manufacturing thereof |
| CN103128981A (en) * | 2011-11-30 | 2013-06-05 | 波音公司 | Stabilized dry preform and method |
| CN204054418U (en) * | 2014-01-17 | 2014-12-31 | 佛山市建准电子有限公司 | Impeller |
| CN105269833A (en) * | 2014-11-04 | 2016-01-27 | 北京盛华瑞科技有限公司 | Two-time compression molding technology for thermoplastic composite material |
| DE102014222841A1 (en) * | 2014-11-10 | 2016-05-12 | Zf Friedrichshafen Ag | Method for producing an at least approximately rotationally symmetrical fiber-plastic composite component with at least one axial undercut section |
| CN106553357A (en) * | 2016-11-09 | 2017-04-05 | 江苏恒神股份有限公司 | Hollow multi-cavity abnormal shape surface composite material complex structural member integral forming technique |
| CN208993139U (en) * | 2018-08-03 | 2019-06-18 | 中国人民解放军92578部队 | A kind of Composite propulsor molding die and products thereof |
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