CN114211781A - Carbon fiber helicopter engine blade forming device and forming method - Google Patents

Carbon fiber helicopter engine blade forming device and forming method Download PDF

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Publication number
CN114211781A
CN114211781A CN202111436170.0A CN202111436170A CN114211781A CN 114211781 A CN114211781 A CN 114211781A CN 202111436170 A CN202111436170 A CN 202111436170A CN 114211781 A CN114211781 A CN 114211781A
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China
Prior art keywords
glue
layer
blade
aluminum sheet
sucking
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Granted
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CN202111436170.0A
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CN114211781B (en
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武书明
胡建国
陈仲刚
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Chengdu China Glass Composite Material Co ltd
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Chengdu China Glass Composite Material Co ltd
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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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/681—Component parts, details or accessories; Auxiliary operations
    • 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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/681—Component parts, details or accessories; Auxiliary operations
    • B29C70/682—Preformed parts characterised by their structure, e.g. form
    • 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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/70—Completely encapsulating inserts
    • 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
    • B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
    • 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
    • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
    • B29L2031/082—Blades, e.g. for helicopters
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50—Manufacturing or production processes characterised by the final manufactured product

Abstract

The invention discloses a carbon fiber helicopter engine blade forming device and a forming method, wherein the forming device comprises a glue sucking device, the glue sucking device comprises a glue sucking structure and a vacuum pumping device connected with the glue sucking structure, and the glue sucking structure comprises a glue sucking base plate, a glue sucking layer, a flow guide layer, a supporting layer and a gas barrier layer arranged outside the supporting layer; the glue sucking backing plate is provided with a groove body, a protrusion and a glue containing cavity, step surfaces are arranged on the periphery of the glue sucking backing plate, and a glue inlet communicated with the glue containing cavity is formed in each step surface; the glue absorbing layer comprises a first glue absorbing layer arranged on the upper surface of the glue absorbing base plate and a second glue absorbing layer arranged between the flow guide layer and a product to be glued; the flow guide layer and the supporting layer are sequentially arranged outside the second glue suction layer, the periphery of the supporting layer is respectively contacted with the glue inlet along the side wall of the glue suction base plate, and the gas barrier layer is coated outside the whole glue suction base plate and the supporting layer. Which can improve the forming quality of the blade.

Description

Carbon fiber helicopter engine blade forming device and forming method
Technical Field
The invention belongs to the technical field of carbon fiber blade forming, and particularly relates to a carbon fiber helicopter engine blade forming device and a carbon fiber helicopter engine blade forming method.
Background
For engine blades, rigidity is an important index, and related researches starting at the end of the last century show that carbon fiber composite materials have superior anti-fatigue characteristics, and when the carbon fiber composite materials are mixed with resin materials, the carbon fiber composite materials become one of the best materials for the engine blades and the like to adapt to severe conditions, and the rigidity of the carbon fiber composite materials is 3 to 5 times that of glass composite blades.
In order to enhance the strength of the carbon fiber helicopter engine blade, a foam sandwich layer is arranged in the blade cambered surface of the carbon fiber composite layer, but the problem of low strength and poor high temperature resistance exists by adopting the foam sandwich layer. The inventor develops an aluminum sheet-based sandwich layer, and when the blade with the structure is prepared and molded, a plurality of processes are required, and a glue absorbing process is a quite important process and is directly related to the molding quality of the blade. Therefore, how to improve the forming quality of the blade is a worthy of study.
Disclosure of Invention
In order to solve the problem of the existing blade prepared by adopting a foam sandwich, the invention provides a carbon fiber helicopter engine blade forming device and a forming method, which can improve the forming quality of the blade.
The invention is realized by the following technical scheme:
the invention provides a carbon fiber helicopter engine blade forming device which comprises a glue sucking device, wherein the glue sucking device comprises a glue sucking structure and a vacuumizing device connected with the glue sucking structure,
the glue absorbing structure comprises a glue absorbing base plate, a glue absorbing layer, a flow guide layer, a supporting layer and a gas barrier layer arranged outside the supporting layer;
the glue sucking backing plate is provided with a groove body, a protrusion and a glue containing cavity, step surfaces are arranged on the periphery of the glue sucking backing plate, and a glue inlet communicated with the glue containing cavity is formed in each step surface;
the glue absorbing layer comprises a first glue absorbing layer arranged on the upper surface of the glue absorbing base plate and a second glue absorbing layer arranged between the flow guide layer and a product to be glued; the flow guide layer and the supporting layer are sequentially arranged outside the second glue suction layer, the periphery of the supporting layer is respectively contacted with the glue inlet along the side wall of the glue suction base plate, and the gas barrier layer is coated outside the whole glue suction base plate and the supporting layer.
The blade forming device of this scheme holds gluey chamber through setting up on inhaling the plastic backing plate, inhales the glue water conservancy diversion on the plastic layer with the second through the water conservancy diversion layer and to holding to glue the intracavity and have storing up, both can make and inhale the plastic layer and keep lasting inhaling gluey ability, also can avoid the vacuum to inhale gluey back, and the backward flow of unnecessary volume of gluing leads to gluing too much, influences blade shaping quality.
In one possible design, the support is arranged in the groove body and comprises an upper support surface, a lower support surface and a support rod connected between the upper support surface and the lower support surface.
When the core material adopts aluminum sheet support piece, its aluminum sheet is thinner, when the vacuum is inhaled and is glued, can cause certain destruction to aluminum sheet structural stability, adopts support piece realization to aluminum sheet support piece's protection, improves blade shaping quality.
In one possible design, the flow guiding layer is a film, and flow guiding holes are formed in the film.
The scheme adopts the film to realize diversion, the film has small adsorption effect on liquid substances such as glue and the like, and the diversion effect is good.
In a second aspect, the invention provides a method for forming a carbon fiber helicopter engine blade, comprising the following steps,
preparing a core material, wherein the core material comprises a first aluminum sheet, a second aluminum sheet and a third aluminum sheet, the first aluminum sheet is square, the first aluminum sheet, the second aluminum sheet and the third aluminum sheet are all provided with a plurality of clamping seams, and the first aluminum sheet, the second aluminum sheet and the third aluminum sheet are clamped through the clamping seams to form a plurality of triangular cavities surrounded by the first aluminum sheet, the second aluminum sheet and the third aluminum sheet;
preparing prepreg by compounding carbon fiber and epoxy resin, and cutting according to the shapes of the cambered surface of the first blade and the cambered surface of the second blade of the blade;
by adopting the carbon fiber helicopter engine blade forming device in the first aspect and any one possibility, after a first adhesive absorption layer is laid on the upper surface of an adhesive absorption backing plate, the prepared core material is placed in the groove body, and prepregs of the first blade cambered surface and the second blade cambered surface are respectively placed at the corresponding outlets of the groove body and the protrusion;
sequentially laying a second glue absorbing layer, a flow guide layer and a supporting layer on the prepreg of the first blade cambered surface and the second blade cambered surface, and placing the whole glue absorbing base plate in an air isolating layer to obtain a product to be subjected to vacuum glue absorbing after the supporting layer is contacted with a glue inlet along the side wall of the glue absorbing base plate;
putting the product to be subjected to vacuum glue suction into a hot pressing tank, and vacuumizing and sucking glue;
the cambered surface of the first blade and the core material after glue suction are reversely buckled into a glass fiber reinforced plastic female die which is attached to the blade profile, then the cambered surface of the second blade after glue suction is reversely buckled into another glass fiber reinforced plastic female die which is attached to the blade profile, and mounting columns are inserted into mounting holes of the cambered surface of the first blade and the cambered surface of the second blade;
and (5) closing the mold, curing and molding.
The core material is formed by clamping and connecting a first aluminum sheet, a second aluminum sheet and a third aluminum sheet through clamping and connecting seams, and the aluminum sheet with the clamping seams is unstable in connectivity at the clamping and connecting positions. This scheme has improved on the basis of current blade forming method, through set up the cell body in order to hold the core on inhaling the adhesive backing plate, the core top is the preimpregnation material of first paddle cambered surface or second paddle cambered surface, when inhaling the glue in the vacuum, epoxy on the preimpregnation material can follow the aluminum sheet and flow to the first adhesive layer in the cell body on, at this moment, epoxy can carry out the glue-filling to aluminum sheet joint seam department and handle, when the solidification, can improve aluminum sheet joint seam department and with first paddle cambered surface, the stability of being connected is connected to second paddle cambered surface connection face. In the glue sucking process, a part of the epoxy resin glue on the cambered surface of the first blade or the cambered surface of the second blade flows onto the first glue sucking layer in the groove body along the aluminum sheet, and a part of the epoxy resin glue is adsorbed by the second glue sucking layer. When the adsorption capacity of the second glue absorbing layer is too large, the second glue absorbing layer is guided to the glue accommodating cavity through the guide layer to be stored, and the problem that the glue flows back to influence the forming quality of the blade after vacuum is finished is avoided.
In a possible design, the prepreg with the first blade arc surface and the second blade arc surface is respectively placed at the corresponding outlet of the groove body and the protrusion, and before the step, the method further includes:
and placing the support piece in a triangular cavity defined by the first aluminum sheet, the second aluminum sheet and the third aluminum sheet to attach the lower support surface to the first adhesive absorbing layer.
According to the scheme, the supporting piece is arranged in the triangular cavity, so that the core material can be protected; because the core material is the multi-chamber structure that the aluminum sheet constitutes, at the vacuum glue absorption in-process, the cavity can influence and inhale gluey quality, adopts support piece, and its cavity supporting role of its terminal surface can improve and inhale gluey quality greatly.
In one possible design, the vacuum suction glue comprises:
and vacuumizing the gas barrier, wherein the glue absorption temperature in the hot pressing tank is 70-75 ℃, the pressure is 0.1-0.2 Mpa, and the glue absorption time is 90-100 min.
This scheme is optimized through inhaling glue time, temperature, pressure, avoids glue too much piling up on the aluminum sheet, improves and inhales gluey quality, and then improves the shaping quality of blade.
In one possible design, the vacuum suction glue comprises:
and vacuumizing the gas barrier, wherein the glue suction temperature in the hot pressing tank is 75 ℃, the pressure is 0.17Mpa, and the glue suction time is 90 min.
Compared with the prior art, the invention at least has the following advantages and beneficial effects:
1. according to the invention, the glue containing cavity is arranged on the glue absorbing base plate, and the glue on the second glue absorbing layer is guided to the glue containing cavity through the flow guide layer to be stored, so that the glue absorbing layer can keep continuous glue absorbing capacity, and excessive glue caused by backflow of redundant glue after vacuum glue absorption can be avoided, and the forming quality of the blade is influenced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural view of a glue-sucking backing plate of the glue-sucking structure of the present invention;
FIG. 2 is a sectional view of a glue-sucking backing plate of the glue-sucking structure of the present invention;
FIG. 3 is a schematic structural view of a core material of the present invention;
FIG. 4 is a schematic structural view of the support member of the present invention;
FIG. 5 is a schematic view of a first aluminum sheet of the present invention;
FIG. 6 is a schematic structural view of a second aluminum sheet of the present invention;
FIG. 7 is a schematic structural view of a third aluminum sheet of the present invention;
FIG. 8 is a schematic view of the configuration of the first blade camber and core of the present invention;
FIG. 9 is a schematic structural view of a blade made by the method of the present invention.
Detailed Description
The invention is further described with reference to the following figures and specific embodiments. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. Specific structural and functional details disclosed herein are merely illustrative of example embodiments of the invention. This invention may, however, be embodied in many alternate forms and should not be construed as limited to the embodiments set forth herein.
It should be understood that, for the term "and/or" as may appear herein, it is merely an associative relationship that describes an associated object, meaning that three relationships may exist, e.g., a and/or B may mean: a exists alone, B exists alone, and A and B exist at the same time; for the term "/and" as may appear herein, which describes another associative object relationship, it means that two relationships may exist, e.g., a/and B, may mean: a exists independently, and A and B exist independently; in addition, for the character "/" that may appear herein, it generally means that the former and latter associated objects are in an "or" relationship.
It should be understood that specific details are provided in the following description to facilitate a thorough understanding of example embodiments. However, it will be understood by those of ordinary skill in the art that the example embodiments may be practiced without these specific details. For example, systems may be shown in block diagrams in order not to obscure the examples in unnecessary detail. In other instances, well-known processes, structures and techniques may not be shown in unnecessary detail to avoid obscuring the examples.
The invention discloses a carbon fiber helicopter engine blade forming device which comprises a glue sucking device, wherein the glue sucking device comprises a glue sucking structure and a vacuumizing device connected with the glue sucking structure. The vacuum pumping device is prior art and is not shown in the figure of this embodiment.
The glue absorbing structure comprises a glue absorbing base plate 21, a glue absorbing layer, a flow guide layer, a supporting layer and a gas barrier layer arranged outside the supporting layer. Specifically, as shown in fig. 1 and 2, a groove 22, a protrusion 24 and a glue containing cavity 25 are arranged on the glue absorbing pad 21, step surfaces 26 are arranged around the glue absorbing pad 21, and a glue inlet 23 communicated with the glue containing cavity 25 is arranged on the step surfaces 26.
The glue absorbing layer comprises a first glue absorbing layer 31 arranged on the upper surface of the glue absorbing backing plate 21 and a second glue absorbing layer arranged between the flow guide layer and a product to be glue absorbed; the upper surface of the glue absorbing backing plate 21 not only includes the upper end surfaces except the groove body 22 and the protrusion 24, but also includes the bottom surface of the groove body 22 and the protrusion surface of the protrusion 24, namely, an arc surface. The bottom surface of the groove body 22 and the rear surface of the bulge 24 are respectively matched with the blade core material.
The flow guide layer and the supporting layer are sequentially arranged outside the second glue suction layer, the periphery of the supporting layer is respectively contacted with the glue inlet 23 along the side wall of the glue suction base plate 21, and the air barrier layer is coated outside the whole glue suction base plate 21 and the supporting layer. The air-isolating layer is provided with an air exhaust hole to realize connection with a vacuum-pumping device.
Preferably, a support member, as shown in fig. 3, including an upper support surface 221, a lower support surface 222, and a support rod 223 connected between the upper support surface 221 and the lower support surface 222, may be further provided in the housing 22. The lower support surface 222 is in contact with the first blotter layer and the upper support surface 221 is in contact with the second blotter layer. The shapes of the upper support surface 221 and the lower support surface 222 are matched with the cavity structure formed by the core material.
The flow guide layer is a film, and flow guide holes are formed in the film. The film should have a certain toughness. The water conservancy diversion effect is realized to the guiding layer, and the supporting layer plays the supporting role, avoids the long water conservancy diversion hole of guiding layer to be blockked up, makes to have the clearance between guiding layer and the gas barrier layer, guarantees the reliable water conservancy diversion of glue. The supporting layer can be made of materials with certain hardness and gaps such as felts and wire loops with large gaps. The wire loops are made of materials with certain hardness and are stacked after being made into threads, such as PCV wire loops of a ground mat.
The invention discloses a forming method of a carbon fiber helicopter engine blade in a second aspect, which comprises the following steps,
preparing a core material, wherein the core material comprises a first aluminum sheet 11, a second aluminum sheet 12 and a third aluminum sheet 13, the first aluminum sheet 11 is square, the first aluminum sheet 11, the second aluminum sheet 12 and the third aluminum sheet 13 are all provided with a plurality of clamping seams 14, and the first aluminum sheet 11, the second aluminum sheet 12 and the third aluminum sheet 13 are clamped and connected through the clamping seams to form a plurality of triangular cavities surrounded by the first aluminum sheet 11, the second aluminum sheet 12 and the third aluminum sheet 13. The cavity of this scheme is triangle-shaped, by the most stable principle of triangle-shaped, can improve the supporting role of core greatly. First aluminum sheet 11 is square, and it transversely sets up along the blade cavity, and is unanimous with blade length direction promptly, because the cavity of blade be the dysmorphism, only need with second aluminum sheet 12 and third aluminum sheet set up to the opposite sex can, can simplify the complexity of aluminum sheet preparation greatly, specifically, the setting of joint can refer to 5-7 on first aluminum sheet 11, second aluminum sheet 12 and the third aluminum sheet 13, of course, also can adopt other joint to set up the structure, as long as the reliable joint of three can. The weight of the whole blade is not easy to be too heavy, and the weight is generally controlled to be 0.06kg/m in the blade of the helicopter engine3About, the volume weight is controlled to be 0.055kg/m3To 0.066kg/m3. In order to improve the strength of the bladeThe thickness of the first aluminum sheet 11, the second aluminum sheet 12 and the third aluminum sheet 13 was controlled to be 0.05mm to 0.2 mm.
The prepreg is prepared by compounding carbon fibers and epoxy resin, and is cut according to the shapes of the cambered surfaces of the first blade and the second blade of the blade. Specifically, a hot melting method is adopted to prepare prepreg, a layer of a three-dimensional model is spread and converted into a two-dimensional image, and a proper graph is cut according to the two-dimensional image.
By adopting the carbon fiber helicopter engine blade forming device in the first aspect and any one of the possibilities, after the first adhesive absorption layer 31 is laid on the upper surface of the adhesive absorption backing plate 21, the prepared core material is placed in the groove body 22, and the prepreg of the first blade cambered surface and the prepreg of the second blade cambered surface are respectively placed at the corresponding outlet of the groove body 22 and the protrusion 24. The groove body 22 and the protrusions 24 are arranged, so that the first paddle cambered surface and the second paddle cambered surface are contacted with each other after the first paddle cambered surface and the second paddle cambered surface are placed, and the glue absorption quality is improved.
Under the condition that the carbon fiber helicopter engine blade forming device has the supporting piece, at this time, the method further comprises the step of placing the supporting piece in a triangular cavity defined by the first aluminum sheet 11, the second aluminum sheet 12 and the third aluminum sheet 13 so that the lower supporting surface 222 is attached to the first adhesive absorption layer. The number of the supporting pieces can be determined according to the number of the triangular cavities, and the length of each side of the upper supporting surface 221 and the lower supporting surface 222 of each supporting piece is slightly smaller than that of each side of the triangular cavity at the position of each supporting piece, so that the supporting pieces can be conveniently separated from the core material after the glue suction is finished.
And laying a second glue absorbing layer, a flow guide layer and a supporting layer on the prepreg of the first blade cambered surface and the second blade cambered surface in sequence, and placing the whole glue absorbing backing plate 21 in the air isolating layer after the supporting layer is contacted with the glue inlet 23 along the side wall of the glue absorbing backing plate 21 to obtain a product to be vacuum-absorbed. The arrangement of the supporting layer enables a gap to exist between the flow guide layer and the air isolation layer, and reliable flow guide of the glue is achieved.
And putting the product to be vacuumized and glue-absorbed into a hot-pressing tank, and vacuumizing and absorbing glue. Specifically, the air barrier layer is vacuumized, the glue absorption temperature in the hot pressing tank is 70-75 ℃, the pressure is 0.1-0.2 Mpa, and the glue absorption time is 90-100 min. In the step, the control of the temperature, the pressure and the glue sucking time is particularly important, and the glue sucking time and the proper glue sucking temperature are ensured to be long enough, so that a little glue is adhered to the aluminum sheet. Preferably, the parameters can be controlled at the following values: the glue suction temperature in the hot pressing tank is 75 ℃, the pressure is 0.17Mpa, and the glue suction time is 90 min.
And the first blade cambered surface and the core material after the glue suction are reversely buckled into a glass fiber reinforced plastic female die which is attached to the blade profile, the structures of the first blade cambered surface and the core material are shown in figure 8, then the second blade cambered surface after the glue suction is reversely buckled into another glass fiber reinforced plastic female die which is attached to the blade profile, and mounting columns are inserted into mounting holes of the first blade cambered surface and the second blade cambered surface. In the step, a cavity formed by the two glass fiber reinforced plastic female die molds is matched with the blade. The erection column is blade and rotor oar presss from both sides connecting portion.
The mold is closed and cured to obtain the blade shown in FIG. 9. Specifically, the die is closed and then placed into a hot pressing tank, the curing temperature is kept at 160-170 ℃ under the vacuum condition, the curing time is kept at 3-6 h, and the pressure in the hot pressing tank is 0.2-0.3 MPa.
The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: modifications may be made to the embodiments described above, or equivalents may be substituted for some of the features described. And such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.

Claims (7)

1. A carbon fiber helicopter engine blade forming device comprises a glue sucking device and is characterized in that the glue sucking device comprises a glue sucking structure and a vacuum pumping device connected with the glue sucking structure,
the glue absorbing structure comprises a glue absorbing base plate (21), a glue absorbing layer, a flow guide layer, a supporting layer and a gas barrier layer arranged outside the supporting layer;
the glue sucking backing plate (21) is provided with a groove body (22), a protrusion (24) and a glue containing cavity, the periphery of the glue sucking backing plate (21) is provided with a step surface, and the step surface is provided with a glue inlet (23) communicated with the glue containing cavity;
the glue absorbing layer comprises a first glue absorbing layer (31) arranged on the upper surface of the glue absorbing base plate (21) and a second glue absorbing layer arranged between the flow guide layer and a product to be glued; the flow guide layer and the supporting layer are sequentially arranged outside the second glue suction layer, the periphery of the supporting layer is respectively contacted with the glue inlet (23) along the side wall of the glue suction base plate (21), and the air barrier layer is coated outside the whole glue suction base plate (21) and the supporting layer.
2. The carbon fiber helicopter engine blade forming device of claim 1, further comprising a support member disposed within the slot (22), the support member comprising an upper support surface (221), a lower support surface (222), and a support rod (223) connected between the upper support surface (221) and the lower support surface (222).
3. The carbon fiber helicopter engine blade forming device of claim 1, wherein the flow guiding layer is a film, and flow guiding holes are formed in the film.
4. A carbon fiber helicopter engine blade forming method is characterized by comprising the following steps,
preparing a core material, wherein the core material comprises a first aluminum sheet (11), a second aluminum sheet (12) and a third aluminum sheet (13), the first aluminum sheet (11) is square, the first aluminum sheet (11), the second aluminum sheet (12) and the third aluminum sheet (13) are all provided with a plurality of clamping seams (14), and the first aluminum sheet (11), the second aluminum sheet (12) and the third aluminum sheet (13) are clamped by the clamping seams (14) to form a plurality of triangular cavities surrounded by the first aluminum sheet (11), the second aluminum sheet (12) and the third aluminum sheet (13);
preparing prepreg by compounding carbon fiber and epoxy resin, and cutting according to the shapes of the cambered surface of the first blade and the cambered surface of the second blade of the blade;
by adopting the carbon fiber helicopter engine blade forming device as claimed in any one of claims 1 to 3, after the first adhesive absorption layer (31) is laid on the upper surface of the adhesive absorption backing plate (21), the prepared core material is placed in the tank body (22), and the prepregs of the first blade cambered surface and the second blade cambered surface are respectively placed at the corresponding outlets of the tank body (22) and the protrusion (24);
sequentially laying a second glue absorbing layer, a flow guide layer and a supporting layer on the prepreg of the first blade cambered surface and the second blade cambered surface, and placing the whole glue absorbing backing plate (21) in an air isolating layer to obtain a product to be vacuum-absorbed glue after the supporting layer is contacted with a glue inlet (23) along the side wall of the glue absorbing backing plate (21);
putting the product to be subjected to vacuum glue suction into a hot pressing tank, and vacuumizing and sucking glue;
the cambered surface of the first blade and the core material after glue suction are reversely buckled into a glass fiber reinforced plastic female die which is attached to the blade profile, then the cambered surface of the second blade after glue suction is reversely buckled into another glass fiber reinforced plastic female die which is attached to the blade profile, and mounting columns are inserted into mounting holes of the cambered surface of the first blade and the cambered surface of the second blade;
and (5) closing the mold, curing and molding.
5. The carbon fiber helicopter engine blade forming method according to claim 4, wherein the prepreg of the first blade cambered surface and the prepreg of the second blade cambered surface are respectively placed at the corresponding outlets of the groove body (22) and the protrusion (24), and the method further comprises the following steps:
and placing the supporting piece in a triangular cavity defined by the first aluminum sheet (11), the second aluminum sheet (12) and the third aluminum sheet (13) to attach the lower supporting surface (222) to the first absorbent layer.
6. The method of claim 4, wherein the vacuum suction of glue comprises:
and vacuumizing the gas barrier, wherein the glue absorption temperature in the hot pressing tank is 70-75 ℃, the pressure is 0.1-0.2 Mpa, and the glue absorption time is 90-100 min.
7. The method of claim 4, wherein the vacuum suction of glue comprises:
and vacuumizing the gas barrier, wherein the glue suction temperature in the hot pressing tank is 75 ℃, the pressure is 0.17Mpa, and the glue suction time is 90 min.
CN202111436170.0A 2021-11-29 2021-11-29 Carbon fiber helicopter engine blade forming device and forming method Active CN114211781B (en)

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Application Number Priority Date Filing Date Title
CN202111436170.0A CN114211781B (en) 2021-11-29 2021-11-29 Carbon fiber helicopter engine blade forming device and forming method

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Application Number Priority Date Filing Date Title
CN202111436170.0A CN114211781B (en) 2021-11-29 2021-11-29 Carbon fiber helicopter engine blade forming device and forming method

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Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101725464A (en) * 2008-10-17 2010-06-09 中国科学院宁波材料技术与工程研究所 Method for making vane of wind-driven generator by adopting ultra-high strength polyethylene fiber composites
CN101830095A (en) * 2010-03-10 2010-09-15 中国人民解放军国防科学技术大学 Composite material member with surface function layer and VIMP preparation method thereof
CN102001184A (en) * 2010-09-28 2011-04-06 天津南车风电叶片工程有限公司 Vacuumizing method for producing large-sized composite material member and composite air extracting layer
CN202370763U (en) * 2011-12-27 2012-08-08 天津鑫茂鑫风能源科技有限公司 Large-diameter wind power blade of aluminum honeycomb sandwich material
CN103921457A (en) * 2014-04-28 2014-07-16 连云港中复连众复合材料集团有限公司 Method for manufacturing main beam or auxiliary beam of fan blade by unidirectional sheets manufactured by use of pultrusion process
CN104358708A (en) * 2014-08-19 2015-02-18 航天材料及工艺研究所 Carbon fiber composite foam core sandwich structure wind tunnel fan blade and molding method
CN104401092A (en) * 2014-11-18 2015-03-11 江苏恒神纤维材料有限公司 Method for enabling carbon fiber composite thick laminated structure to uniformly absorb resin and laminated structure
CN104690987A (en) * 2015-04-03 2015-06-10 郑伟 Draught fan blade manufacturing process based on RTM
CN105690790A (en) * 2014-11-26 2016-06-22 上海越科复合材料有限公司 Integral molding method of composite material blade for wind power generation, and apparatus thereof
CN207647684U (en) * 2017-12-25 2018-07-24 江苏金风科技有限公司 Wind generator set blade building block, blade and wind power generating set
CN109826761A (en) * 2019-03-05 2019-05-31 戴铂新材料(张家港)有限公司 The structure of fluting perforation processing is cut for core surfaces
US20190195073A1 (en) * 2017-12-21 2019-06-27 General Electric Company Composite hollow blade and a method of forming the composite hollow blade
CN110549654A (en) * 2018-05-31 2019-12-10 中国船舶重工集团公司第七一一研究所 Integrated manufacturing method of fan blade and fan blade
CN210082456U (en) * 2019-06-20 2020-02-18 四川东树新材料有限公司 Fiber laying composite material forming die and wind power blade main beam cap forming die
WO2021224070A1 (en) * 2020-05-07 2021-11-11 Siemens Gamesa Renewable Energy A/S Method for manufacturing a wind turbine blade and fixture for manufacturing a wind turbine blade

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101725464A (en) * 2008-10-17 2010-06-09 中国科学院宁波材料技术与工程研究所 Method for making vane of wind-driven generator by adopting ultra-high strength polyethylene fiber composites
CN101830095A (en) * 2010-03-10 2010-09-15 中国人民解放军国防科学技术大学 Composite material member with surface function layer and VIMP preparation method thereof
CN102001184A (en) * 2010-09-28 2011-04-06 天津南车风电叶片工程有限公司 Vacuumizing method for producing large-sized composite material member and composite air extracting layer
CN202370763U (en) * 2011-12-27 2012-08-08 天津鑫茂鑫风能源科技有限公司 Large-diameter wind power blade of aluminum honeycomb sandwich material
CN103921457A (en) * 2014-04-28 2014-07-16 连云港中复连众复合材料集团有限公司 Method for manufacturing main beam or auxiliary beam of fan blade by unidirectional sheets manufactured by use of pultrusion process
CN104358708A (en) * 2014-08-19 2015-02-18 航天材料及工艺研究所 Carbon fiber composite foam core sandwich structure wind tunnel fan blade and molding method
CN104401092A (en) * 2014-11-18 2015-03-11 江苏恒神纤维材料有限公司 Method for enabling carbon fiber composite thick laminated structure to uniformly absorb resin and laminated structure
CN105690790A (en) * 2014-11-26 2016-06-22 上海越科复合材料有限公司 Integral molding method of composite material blade for wind power generation, and apparatus thereof
CN104690987A (en) * 2015-04-03 2015-06-10 郑伟 Draught fan blade manufacturing process based on RTM
US20190195073A1 (en) * 2017-12-21 2019-06-27 General Electric Company Composite hollow blade and a method of forming the composite hollow blade
CN207647684U (en) * 2017-12-25 2018-07-24 江苏金风科技有限公司 Wind generator set blade building block, blade and wind power generating set
CN110549654A (en) * 2018-05-31 2019-12-10 中国船舶重工集团公司第七一一研究所 Integrated manufacturing method of fan blade and fan blade
CN109826761A (en) * 2019-03-05 2019-05-31 戴铂新材料(张家港)有限公司 The structure of fluting perforation processing is cut for core surfaces
CN210082456U (en) * 2019-06-20 2020-02-18 四川东树新材料有限公司 Fiber laying composite material forming die and wind power blade main beam cap forming die
WO2021224070A1 (en) * 2020-05-07 2021-11-11 Siemens Gamesa Renewable Energy A/S Method for manufacturing a wind turbine blade and fixture for manufacturing a wind turbine blade

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