WO2018207702A1 - 複合材翼及び複合材翼の製造方法 - Google Patents

複合材翼及び複合材翼の製造方法 Download PDF

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Publication number
WO2018207702A1
WO2018207702A1 PCT/JP2018/017534 JP2018017534W WO2018207702A1 WO 2018207702 A1 WO2018207702 A1 WO 2018207702A1 JP 2018017534 W JP2018017534 W JP 2018017534W WO 2018207702 A1 WO2018207702 A1 WO 2018207702A1
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WIPO (PCT)
Prior art keywords
composite material
ventral
region
layer
blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2018/017534
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
良次 岡部
新藤　健太郎
昌美 神谷
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to US16/611,404 priority Critical patent/US11371365B2/en
Priority to CN201880030399.4A priority patent/CN110612398B/zh
Priority to DE112018002364.8T priority patent/DE112018002364T5/de
Publication of WO2018207702A1 publication Critical patent/WO2018207702A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
    • 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
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
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    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/04—Layered products comprising a layer of synthetic resin as impregnant, bonding, or embedding substance
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    • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B27/065—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of foam
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    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J5/00—Manufacture of articles or shaped materials containing macromolecular substances
    • C08J5/04—Reinforcing macromolecular compounds with loose or coherent fibrous material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
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    • F01D5/14—Form or construction
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    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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Definitions

  • the present invention relates to a composite wing and a method for manufacturing the composite wing.
  • a composite blade formed by laminating a composite material layer in which a reinforcing fiber is impregnated with a resin is used.
  • a composite blade used in an industrial gas turbine compressor has a high-dimensional torsion, and the change in thickness in the blade thickness direction is large.
  • the composite wing needs to ensure the accuracy of the contour and thickness of the back surface, the ventral surface, the front edge side surface and the rear edge side surface.
  • Such a composite blade has been proposed to have a laminated structure in which long and short composite material layers are combined in order to avoid shear peeling in a portion having a large shape change (see Patent Document 1).
  • the composite blade described in Patent Document 1 ensures the accuracy of the contour and thickness by superposing a large amount of thin composite material layers. Moreover, the composite material wing
  • the process of preparing a thin composite material layer with high precision, the process of stacking a large amount of thin composite material layers with high precision, and the process of changing the number of stacked composite material layers with high precision depending on the location Since this is a difficult process, the method described in Patent Document 1 has a problem in that it cannot sufficiently ensure the accuracy of the profile and thickness of the composite blade. In addition, since these processes are difficult processes, the method described in Patent Document 1 decreases the yield of manufacturing the composite blade, and as a result, increases the cost of manufacturing the composite blade. There was a problem that.
  • the present invention has been made in view of the above, and provides a composite blade and a method for manufacturing the composite blade that can sufficiently ensure the accuracy of the contour and thickness, and can reduce the manufacturing cost.
  • the purpose is to provide.
  • the composite wing is a composite wing formed by laminating a composite material layer in which a reinforcing fiber is impregnated with a resin
  • the composite material layer includes: Laminated in the blade thickness direction, which is the direction connecting the back side and the ventral side of the composite blade, and a surface layer region from the surface to the predetermined depth in the blade thickness direction, and the predetermined depth from the surface in the blade thickness direction.
  • a thick layer portion including a deeper layer region, and the median thickness of the composite material layer in the surface layer region is a median thickness of the composite material layer in the deep layer region. It is characterized by being thinner than the value.
  • the composite material blade is a composite material blade formed by laminating a composite material layer in which a reinforcing fiber is impregnated with a resin, and the composite material layer includes the composite material layer Are laminated in the blade thickness direction, which is a direction connecting the back side and the ventral side of the composite blade, and a surface layer region from the surface to a predetermined depth in the blade thickness direction, and the predetermined thickness in the blade thickness direction from the surface.
  • an average value of the thickness per layer of the composite material layer in the surface layer region is the thickness per layer of the composite material layer in the deep layer region. It is characterized by being thinner than the average value of.
  • a relatively thin composite material layer is used in the surface layer region and a relatively thick composite material layer is used in the deep layer region, it is possible to sufficiently ensure the accuracy of the contour by the relatively thin composite material layer.
  • a relatively thick composite material layer can reduce manufacturing costs, and as a whole, sufficient thickness accuracy can be ensured.
  • a blade width direction that is a direction connecting the leading edge side and the trailing edge side of the composite blade
  • a blade length direction that is a direction connecting the blade top side and the blade root side of the composite blade.
  • the composite material layer in the surface region has a larger area than the composite material layer in the deep region. According to this configuration, in a surface layer region using a relatively thin composite material layer, it is possible to ensure a wider range of contour accuracy in the plane direction including the blade width direction and the blade length direction.
  • the wing portion on the back side includes a dorsal surface layer region from the dorsal surface to the predetermined depth in the wing thickness direction, and a dorsal side deeper than the predetermined depth in the wing thickness direction from the dorsal surface.
  • a ventral deep layer region deeper than the predetermined depth it is possible to sufficiently ensure the accuracy of the contour degree by the relatively thin composite material layer on each of the back side and the ventral side, and reduce the manufacturing cost by the relatively thick composite material layer. As a whole, sufficient thickness accuracy can be ensured.
  • the end portion in the wing width direction which is the direction connecting the front edge side and the rear edge side of the composite wing, is the back surface layer region and the ventral surface layer.
  • the end portion in the wing width direction of the composite material layer in the dorsal surface layer region and the end portion in the wing width direction of the composite material layer in the ventral surface layer region are alternately arranged on the other surface layer. It is preferable to be provided in contact with the neutral surface side surface of the composite material layer in the region.
  • the ply drop which is a gap generated in the vicinity of the neutral surface as the composite material layers are stacked, can be divided by the end portion in the blade width direction of the composite material layer, and can be reduced.
  • strength and reliability in the edge part in a wing span direction can be improved.
  • the composite material blade is a composite material blade formed by laminating a composite material layer in which a reinforcing fiber is impregnated with a resin
  • the composite material layer includes the composite material layer Is laminated in the blade thickness direction, which is a direction connecting the back side and the ventral side of the composite material wing, and a back surface layer region from the back surface to a predetermined depth in the wing thickness direction, and the back side A dorsal deep layer region deeper than the predetermined depth in the blade thickness direction from the surface, a ventral surface layer region from the ventral surface to the predetermined depth in the blade thickness direction, and the blade thickness from the ventral surface.
  • a ventral deep layer region deeper than the predetermined depth in the direction, and the dorsal surface layer region and the dorsal deep layer region are joined to the ventral surface layer region and the ventral deep layer region at a neutral plane.
  • the blade width direction which is the direction connecting the leading edge side and the trailing edge side of the composite blade.
  • the portion is configured by the back surface layer region and the ventral surface layer region, the end portion in the blade width direction of the composite material layer in the back surface layer region, and the wing of the composite material layer in the ventral surface layer region Ends in the width direction are provided alternately in contact with the neutral surface side surface of the composite material layer of the other surface layer region.
  • the ply drop which is a gap generated in the vicinity of the neutral surface as the composite material layers are stacked, can be divided by the end portion of the composite material layer and reduced.
  • strength and reliability in the edge part in a wing span direction can be improved.
  • the shape is stabilized, it is possible to sufficiently ensure the accuracy of the contour and the thickness.
  • the manufacturing cost can be reduced.
  • a method for manufacturing a composite wing is a method of manufacturing a composite wing by laminating a composite material layer impregnated with resin in a reinforcing fiber, In a blade thickness direction that is a direction connecting the back side and the abdomen side of the composite material wing from the back side surface to a back side molding die having a back side molding surface that molds the back side surface of the material wing.
  • a method for manufacturing a composite wing is a method for manufacturing a composite wing by laminating a composite material layer impregnated with resin in a reinforcing fiber,
  • the blade thickness direction which is the direction connecting the back side and the ventral side of the composite material wing from the back surface to the back side molding die having a back side molding surface for molding the back side surface of the composite material wing
  • a backside surface layer layer stacking step for stacking a composite material layer constituting a backside surface layer region up to a predetermined depth; and a backside surface layer region laminated on the backside mold on the backside surface layer region.
  • a relatively thin composite material layer is used in the surface layer region and a relatively thick composite material layer is used in the deep layer region.
  • the accuracy of the contour can be ensured, the manufacturing cost can be reduced by the relatively thick composite material layer, and the accuracy of the thickness can be sufficiently secured as a whole.
  • FIG. 1 is a schematic plan view of a composite blade according to the first embodiment.
  • FIG. 2 is a schematic cross-sectional view of a cross section including a thin portion of the composite wing according to the first embodiment.
  • FIG. 3 is a schematic cross-sectional view in a cross section including a thick portion of the composite material blade according to the first embodiment.
  • FIG. 4 is an enlarged cross-sectional view of the end portion of the composite blade according to the first embodiment.
  • FIG. 5 is an explanatory view for explaining the thickness range of the composite material layer constituting the composite blade according to the first embodiment.
  • FIG. 6 is a flowchart showing a method for manufacturing the composite blade according to the first embodiment.
  • FIG. 7 is an explanatory diagram for explaining a state in the middle of the flow in the method for manufacturing the composite blade according to the first embodiment.
  • FIG. 1 is a schematic plan view of a composite blade 10 according to the first embodiment.
  • the composite wing 10 includes a composite material.
  • the composite material blade 10 is formed by laminating composite material layers in the blade thickness direction, which is a direction connecting the back side and the abdomen side of the composite material blade 10.
  • the composite blade 10 has an internal region 19 inside.
  • the inner region 19 is a region where, for example, a material different from the composite material, specifically, a foam material is used to reduce the weight of the composite blade 10.
  • the composite blade 10 is not limited to the configuration with the internal region 19, and may have a configuration without the internal region 19.
  • the L direction shown in FIG. 1 is a blade length direction that is a direction connecting the blade top side and the blade root side of the composite blade 10.
  • the W direction shown in FIG. 1 is a blade width direction that is a direction connecting the leading edge side and the trailing edge side of the composite blade 10.
  • the composite material included in the composite wing 10 has reinforcing fibers and a resin impregnated with the reinforcing fibers.
  • the composite material include materials used for aircraft, automobiles, ships, and the like.
  • the reinforcing fiber include those obtained by bundling several hundred to several thousand basic fibers of 5 ⁇ m or more and 7 ⁇ m or less.
  • As the basic fibers constituting the reinforcing fibers glass fibers, carbon fibers, and aramid fibers are exemplified as preferable examples.
  • the basic fiber constituting the reinforcing fiber is not limited to this, and may be other plastic fiber or metal fiber. Although not shown in FIGS. 1 to 4 and 7, the reinforcing fibers are actually arranged in a thin and lined state inside the composite blade 10.
  • the resin impregnated in the reinforcing fibers is preferably a thermosetting resin, but may be a thermoplastic resin.
  • the thermosetting resin include an epoxy resin, a polyester resin, and a vinyl ester resin.
  • the thermoplastic resin include polyamide resin, polypropylene resin, ABS (Acrylonitrile Butadiene Styrene) resin, polyether ether ketone (PEEK), polyether ketone ketone (PEKK), and polyphenylene sulfide (PPS).
  • the resin impregnated in the reinforcing fibers is not limited to this, and other resins may be used.
  • the thermosetting resin can be in a softened state, a cured state, and a semi-cured state.
  • the softened state is a state before thermosetting the thermosetting resin.
  • the softened state is a state that does not have self-supporting property, and is a state where the shape cannot be maintained when it is not supported by the support.
  • the softened state is a state in which the thermosetting resin can be thermoset by being heated.
  • the cured state is a state after thermosetting the thermosetting resin.
  • the cured state is a state having self-supporting property, and is a state in which the shape can be maintained even when not supported by the support.
  • the cured state is a state where the thermosetting resin cannot perform a thermosetting reaction even when heated.
  • the semi-cured state is a state between a softened state and a cured state.
  • the semi-cured state is a state in which thermosetting resin having a degree weaker than the cured state is made into a thermosetting resin.
  • the semi-cured state is a state having self-supporting property, and is a state in which the shape can be maintained even when not supported by the support.
  • the semi-cured state is a state in which the thermosetting resin can be thermoset by being heated.
  • the composite material layer forming the composite blade 10 is preferably a prepreg in which the thermosetting resin is in a semi-cured state.
  • the composite material layers forming the composite blade 10 are laminated with different orientation angles of reinforcing fibers, that is, different angles with respect to the blade length direction in the direction in which the reinforcing fibers are arranged.
  • the orientation angle of the reinforcing fiber is defined to be a positive direction clockwise with the blade length direction being 0 degree.
  • the composite material layers forming the composite blade 10 are laminated with the reinforcing fibers having orientation angles of 0 degrees, 90 degrees, +45 degrees, and ⁇ 45 degrees, respectively, at appropriate ratios.
  • the composite material layer forming the composite blade 10 has different elastic modulus in each direction depending on the orientation angle of the reinforcing fiber, and the one having the orientation angle of the reinforcing fiber of 0 degrees has the highest elasticity.
  • the composite blade 10 can improve resistance to high centrifugal force by preferentially strengthening the blade length direction, that is, increasing the orientation ratio in the 0 degree direction. Moreover, the composite wing
  • FIG. 2 is a schematic cross-sectional view in a cross section including the thin portion 10a of the composite blade 10 according to the first embodiment.
  • 2 is a cross-sectional view taken along the line AA in FIG.
  • FIG. 3 is a schematic cross-sectional view in a cross section including the thick portion 10b of the composite blade 10 according to the first embodiment.
  • 3 is a cross-sectional view taken along the line BB in FIG. 2 and 3 is the blade thickness direction of the composite blade 10.
  • the thin portion 10a is thinner in the blade thickness direction than the thick portion 10b.
  • the composite wing 10 includes a thin portion 10a as shown in FIG.
  • the thin portion 10 a has a back surface region 12 and a ventral surface region 14.
  • the back surface layer region 12 is a region from the back surface to a predetermined depth in the blade thickness direction.
  • the ventral surface region 14 is a region from the ventral surface to a predetermined depth in the blade thickness direction. Both the back surface region 12 and the ventral surface region 14 are included in the surface layer region from the surface to a predetermined depth in the blade thickness direction.
  • the thin portion 10a does not include a deep layer region described later, that is, the back side deep layer region 16 and the ventral side deep layer region 18.
  • the composite blade 10 includes a thick portion 10b as shown in FIG.
  • the thick portion 10 b includes a back surface layer region 12, a ventral surface layer region 14, a back deep layer region 16, a ventral deep layer region 18, and an internal region 19.
  • the dorsal deep layer region 16 is a region deeper than a predetermined depth in the blade thickness direction from the dorsal surface.
  • the ventral deep layer region 18 is a region deeper than a predetermined depth in the blade thickness direction from the ventral surface. Both the back-side deep layer region 16 and the ventral-side deep layer region 18 are included in a surface layer region deeper than a predetermined depth in the blade thickness direction from the surface.
  • the composite wing 10 includes a dorsal surface layer region 12, a ventral surface layer region 14, a dorsal deep layer region 16, a ventral deep layer region 18, and an internal region 19.
  • the back side surface layer region 12 and the back side deep layer region 16 are both regions on the back side with respect to the middle in the blade thickness direction, and are included in the back side wing portion.
  • the ventral surface layer region 14 and the ventral deep layer region 18 are both regions on the ventral side with respect to the middle in the blade thickness direction, and are included in the ventral wing portion. That is, the composite wing 10 has a back wing portion and a ventral wing portion.
  • the back wing portion and the ventral wing portion are joined at a neutral plane.
  • the back side deep layer region 16 in the back side wing portion and the ventral side deep layer region 18 in the ventral side wing portion are joined at the neutral plane.
  • the dorsal surface layer region 12 and the ventral surface layer region 14, which are the surface layer regions, are the dorsal deep layer region 16 and the ventral deep layer that are the deep layer regions.
  • the area is larger than that of the region 18. That is, the composite material wing 10 has a dorsal deep layer in which the composite material layer in the dorsal surface layer region 12 and the ventral surface layer region 14 as the surface layer region is a deep layer region in the plane direction including the blade width direction and the blade length direction. The area is larger than the composite material layer in the region 16 and the ventral deep region 18.
  • FIG. 4 is an enlarged cross-sectional view of the end portion of the composite blade 10 according to the first embodiment.
  • FIG. 4 is an enlarged view of a region C in FIG.
  • the composite blade 10 has an end in the blade width direction, that is, an end on the front edge side and an end on the rear edge side of the composite blade 10 in a cross section cut by a plane orthogonal to the blade length direction. Is constituted by a back side surface layer region 12 and a ventral side surface region 14 which are surface layer regions.
  • the end portions of the plurality of composite material layers 12 s in the back surface region 12 and the end portions of the plurality of composite material layers 14 s in the ventral surface layer region 14 are alternately arranged at the end portions in the blade width direction.
  • the composite blade 10 includes a contact portion 21 in which the end of the composite material layer 12s is in contact with the surface of the composite material layer 14s and an end of the composite material layer 14s at the end in the blade width direction. Are alternately arranged with contact portions 22 in contact with the surface of the composite material layer 12s.
  • the composite blade 10 since the contact portions 21 and the contact portions 22 are alternately arranged at the end in the blade width direction, the end of the composite material layer 12 s and the end of the composite material layer 14 s are in contact with each other. In comparison with the composite material layer, the ply drop, which is a gap generated in the vicinity of the neutral surface with the lamination of the composite material layer, can be divided by the end portion of the composite material layer to be small. Thereby, the composite material blade
  • FIG. 5 is an explanatory diagram for explaining the thickness range of the composite material layer constituting the composite blade 10 according to the first embodiment.
  • the composite wing 10 has a back surface region 12 that is a surface region and an abdomen as shown in the column (1) of FIG. 5.
  • the thickness range S1 of the composite material layer in the side surface layer region 14 and the thickness range D1 of the composite material layer in the back layer deep layer region 16 and the ventral deep layer region 18 that are deep layers Have.
  • the median value of the range S1, that is, the median thickness of the composite material layer in the surface region is the median value of the range D1, that is, the median thickness of the composite material layer in the deep region. Thinner than.
  • the average value of the range S1, that is, the average value of the thickness per layer of the composite material layer in the surface layer region is the average value of the range D1, that is, the thickness per layer of the composite material layer in the deep region. Thinner than average. For this reason, in the pattern 1, the thickness per layer of the composite material layer in the surface layer region tends to be thinner than the thickness per layer of the composite material layer in the deep layer region. In the pattern 1, the range S1 and the range D1 have an overlap. For this reason, in the pattern 1, there is a place where the tendency is switched between the thickness per layer of the composite material layer in the surface layer region and the thickness per layer of the composite material layer in the deep layer region. For example, in the pattern 1, the thickest layer among the composite material layers in the surface layer region is thicker than the thinnest layer among the composite material layers in the deep layer region.
  • the composite wing 10 has a back surface region 12 and an abdomen as the surface layer region as shown in the column (2) of FIG. 5.
  • the median value of the range S2, that is, the median thickness of each composite material layer in the surface region is the median value of the range D2, that is, the median thickness of the composite material layer in the deep region. Thinner than.
  • the average value of the range S2, that is, the average value of the thickness per layer of the composite material layer in the surface layer region is the average value of the range D2, that is, the thickness per layer of the composite material layer in the deep layer region. Thinner than average. For this reason, in the pattern 2, the thickness per layer of the composite material layer in the surface layer region tends to be thinner than the thickness per layer of the composite material layer in the deep layer region. In the pattern 2, the range S2 and the range D2 overlap with only a specific thickness. For this reason, in the pattern 2, the thickest layer among the composite material layers in the surface layer region has the same thickness as the thinnest layer among the composite material layers in the deep layer region.
  • the composite wing 10 has a back surface region 12 that is a surface region and an abdomen as shown in the column (3) of FIG. 5.
  • the median value of the range S3, that is, the median thickness of each composite material layer in the surface region is the median value of the range D3, that is, the median thickness of the composite material layer in the deep region. Thinner than.
  • the average value of the range S3, that is, the average thickness per layer of the composite material layer in the surface layer region is the average value of the range D3, that is, the thickness per layer of the composite material layer in the deep region. Thinner than average. For this reason, in the pattern 3, the thickness per layer of the composite material layer in the surface layer region tends to be thinner than the thickness per layer of the composite material layer in the deep layer region. Note that the pattern 3 has a gap having a certain thickness between the range S3 and the range D3. For this reason, in the pattern 3, even the thickest layer among the composite material layers in the surface layer region is thinner than the thinnest layer among the composite material layers in the deep layer region.
  • the tendency of the thickness per layer of the composite material layer in the surface layer region is not monotonous in any of the above patterns. That is, the composite material blade 10 has a portion where the composite material layer becomes thicker in the surface layer region and a portion where the composite material layer becomes thinner in the blade thickness direction. Moreover, the composite blade 10 has a monotonous tendency for the thickness per layer of the composite material layer in the deep layer region in any of the above patterns. That is, the composite blade 10 has a portion where the composite material layer becomes thicker in the deep region and a portion where the composite material layer becomes thinner in the blade thickness direction.
  • the composite material layer in the surface layer region has a tendency to be thinner than the thickness of the composite material layer in the deep layer region.
  • the material wing 10 can achieve both a sufficient degree of contouring and a reduction in manufacturing cost without substantially reducing the degree of freedom in design. Moreover, the composite material wing
  • the composite material layer in the dorsal surface layer region 12 and the ventral surface layer region 14 which are the surface layer regions is preferably a spread-type woven fabric in which the reinforcing fibers are widened by opening fiber bundles constituting the reinforcing fibers.
  • the composite material layers in the back surface region 12 and the ventral surface region 14 which are the surface regions can thin the fiber bundles constituting the reinforcing fibers, it is possible to ensure the degree of contour with higher accuracy. it can.
  • the composite material wing 10 divides the back wing portion into two regions, a back surface region 12 and a back deep region 16, and the composite material has a relatively thin thickness per layer in the back surface region 12.
  • the layers are stacked, and a composite material layer having a relatively large thickness per layer is stacked in the back-side deep region 16.
  • the total thickness of the back surface layer region 12 is thinner than the total thickness of the back deep layer region 16 in the central portion on the blade root side in the blade width direction, that is, the entire back surface layer region 12. It is preferable that the thickness ratio of the back side of the total thickness of the back side deep layer region 16 is 1 or less.
  • the composite blade 10 is more preferably 0.5 or less, and more preferably 0.33 or less in the central portion on the blade root side in the blade width direction. In this case, the composite blade 10 can sufficiently ensure the accuracy of the contour and thickness of the back blade portion, and can further reduce the manufacturing cost.
  • the composite wing 10 divides the ventral wing portion into two regions, a ventral surface region 14 and a ventral deep layer region 18, and a composite material layer having a relatively thin thickness per layer in the ventral surface layer region 14. And a composite material layer having a relatively large thickness per layer is laminated in the ventral deep layer region 18.
  • the entire thickness of the ventral surface layer region 14 is thinner than the total thickness of the ventral deep layer region 18 in the central portion on the blade root side in the blade width direction, that is, the entire ventral surface layer region 14. It is preferable that the ratio of the ventral side thickness between the thickness of the ventral side and the total thickness of the ventral deep layer region 18 is 1 or less.
  • the composite blade 10 is more preferably 0.5 or less, and more preferably 0.33 or less, in the central portion on the blade root side in the blade width direction.
  • the composite wing 10 can sufficiently ensure the accuracy of the contour and thickness of the ventral wing portion, and can further reduce the manufacturing cost.
  • the composite wing 10 divides the back wing portion into two regions, a back surface region 12 and a back deep region 16, but is not limited to this, and is divided into three or more regions. Also good.
  • a composite material layer having a relatively thin thickness per layer is formed on the layer shallower in the blade thickness direction from the back surface. Laminate, and a composite material layer having a relatively thicker thickness per layer is laminated from the back surface to the deeper layer in the blade thickness direction.
  • the composite material wing 10 can adjust the accuracy of the degree of contour and thickness and the reduction of the manufacturing cost at a fine level for the back wing portion.
  • the composite wing 10 divides the ventral wing portion into two regions, the ventral surface layer region 14 and the ventral deep region 18, but is not limited thereto, and may be divided into three or more regions. Good.
  • the composite wing 10 has a composite material layer having a relatively thin thickness per layer on the layer shallower in the wing thickness direction from the ventral surface. Laminate and laminate a composite material layer having a relatively thicker thickness as it goes from the ventral surface to the deeper layer in the blade thickness direction. In this case, the composite material wing 10 can adjust the accuracy of the degree of contour and thickness and the reduction of the manufacturing cost at a fine level for the wing portion on the ventral side.
  • FIG. 6 is a flowchart showing a method for manufacturing the composite blade 10 according to the first embodiment.
  • FIG. 7 is an explanatory diagram for explaining a state in the middle of the flow in the method for manufacturing the composite blade 10 according to the first embodiment.
  • FIG. 7 is a cross-sectional view similar to FIGS. 2 and 3.
  • a method for manufacturing the composite blade 10 according to the first embodiment will be described with reference to FIGS. 6 and 7.
  • the method for manufacturing the composite blade 10 according to the first embodiment is an example of a method for obtaining the composite blade 10 according to the first embodiment. As shown in FIG.
  • the manufacturing method of the composite wing 10 includes a back surface region lamination step (step S12), a back deep layer region lamination step (step S14), and a ventral surface layer region lamination step (step S16). And a ventral deep layer region stacking step (step S18) and a joining step (step S20).
  • a dorsal molding die 32 having a dorsal molding surface 32a for molding the dorsal surface of the composite blade 10 and a flat dorsal mold mating surface 32b provided around the dorsal molding surface 32a.
  • the back mold 32 is placed so that the back molding surface 32a faces upward in the vertical direction.
  • region 12 is laminated
  • a composite material layer constituting the back-side deep region 16 is laminated on the composite material layer constituting the back-side surface region 12 laminated on the back-side mold 32 (step S14). Thereafter, a foam material constituting the back side portion of the internal region 19 is laminated on the composite material layer constituting the back side deep region 16 laminated on the back side mold 32 to form a neutral surface.
  • a ventral mold 34 having a ventral mold surface 34a for molding the ventral surface of the composite blade 10 and a flat ventral mold mating surface 34b provided around the ventral mold surface 34a is provided.
  • the ventral mold 34 is placed so that the ventral molding surface 34a faces upward in the vertical direction.
  • a composite material layer constituting the ventral surface region 14 is laminated on the ventral molding surface 34a of the ventral mold 34 (step S16).
  • a composite material layer constituting the ventral deep layer region 18 is laminated on the composite material layer constituting the ventral surface region 14 laminated on the ventral mold 34 (step S18). Thereafter, a foam material constituting the ventral portion of the internal region 19 is laminated on the composite material layer constituting the ventral deep layer region 18 laminated on the ventral mold 34 to form a neutral surface.
  • step S12 to step S18 can be changed as appropriate if step S14 is performed after step S12 and step S18 is performed after step S16.
  • it may be performed in the order of step S12, step S16, step S14, and step S18, or may be performed in the order of step S16, step S18, step S12, and step S14.
  • thermosetting resin is in a softened state or a semi-cured state.
  • Each of these composite material layers is preferably a prepreg in which the thermosetting resin is in a semi-cured state.
  • Steps S12 and S16 in the method for manufacturing the composite blade 10 according to the first embodiment include the end portions of the composite material layers 12s in the dorsal surface layer region 12 and the ventral surface layer at the end portions in the blade width direction.
  • the plurality of composite material layers 12s and the plurality of composites are arranged so that the end portions of the plurality of composite material layers 14s in the region 14 are alternately provided in contact with the neutral surface side surface of the composite material layer in the other surface layer region.
  • Each of the material layers 14s is preferably laminated.
  • the end of the composite material layer 12s is on the surface of the composite material layer 14s at the end in the blade width direction.
  • the plurality of composite material layers 12s and the plurality of composite material layers 12s and the plurality of composite material layers 12s and the contact portions 22 in which the end portions of the composite material layer 14s are in contact with the surface of the composite material layer 12s are alternately arranged.
  • the composite material layers 14s are preferably laminated.
  • the foam material constituting the ventral portion of the inner region 19 laminated on the side mold 34 is overlapped on the neutral plane.
  • the composite material layers respectively constituting the back surface layer region 12 and the back deep layer region 16 become the pre back surface layer region 12P and the pre back deep layer region 16P, respectively.
  • the composite material layers constituting the ventral surface layer region 14 and the ventral deep layer region 18 respectively become a pre ventral surface layer region 14P and a pre ventral deep layer region 18P. Further, the foam material constituting the inner region 19 becomes the pre-inner region 19P.
  • the contour of the composite blade 10 is obtained by overlapping the back-side mold mating surface 32b of the back-side mold 32 and the ventral-type mating surface 34b of the ventral mold 34.
  • the accuracy of the degree and the thickness can be reliably ensured.
  • the superimposed composite material layer is heated to cure the thermosetting resin contained in the composite material layer from the softened state or the semi-cured state to the semi-cured state or the cured state.
  • the composite material layers are joined (step S20).
  • the pre-dorsal surface layer region 12P, the pre-ventral side surface layer region 14P, the pre-dorsal side deep layer region 16P, and the pre-abdominal side deep layer region 18P are respectively composed of the dorsal surface layer region 12 and the ventral surface layer to which the composite material is bonded.
  • the region 14, the back side deep layer region 16, and the ventral side deep layer region 18 are formed.
  • the pre-inner area 19P becomes the inner area 19. In this way, the composite blade 10 is obtained.
  • the composite blade 10 and the method for manufacturing the composite blade 10 have the above-described configuration, a relatively thin composite material layer is used in the surface layer region, and a relatively thick composite material layer is used in the deep layer region. For this reason, the composite blade 10 and the method for manufacturing the composite blade 10 can sufficiently ensure the accuracy of the contour by the relatively thin composite material layer, and reduce the manufacturing cost by the relatively thick composite material layer. As a whole, sufficient thickness accuracy can be ensured.
  • the composite material layer in the surface region has a larger area than the composite material layer in the deep region in the plane direction including the blade width direction and the blade length direction. For this reason, the composite blade 10 and the method for manufacturing the composite blade 10 are a surface layer region using a relatively thin composite material layer, and the accuracy of a wider range of contours in the plane direction including the blade width direction and the blade length direction. Can be secured.
  • the composite blade 10 and the method of manufacturing the composite blade 10 further include a thin portion 10a that is thinner than the thick portion 10b and does not include a deep layer region. For this reason, the composite blade 10 and the method of manufacturing the composite blade 10 can ensure the thickness accuracy in the thin portion in the blade thickness direction in the surface layer region using the relatively thin composite material layer.
  • the composite wing 10 and the method of manufacturing the composite wing 10 have a back wing portion and a ventral wing portion, and the back wing portion and the ventral wing portion are joined at a neutral plane,
  • the dorsal wing portion includes the dorsal surface layer region 12 and the dorsal deep layer region 16, and the ventral wing portion includes the ventral surface layer region 14 and the ventral deep layer region 18.
  • the composite material blade 10 and the method for manufacturing the composite material blade 10 can sufficiently ensure the accuracy of the contour degree by the relatively thin composite material layer on each of the back side and the abdomen side.
  • the manufacturing cost can be reduced by the material layer, and the thickness accuracy can be sufficiently secured as a whole.
  • the end portion in the blade width direction is further constituted by the back surface region 12 and the ventral surface region 14, and the composite material layer in the back surface region 12
  • the end portions of 12s and the end portions of the composite material layer 14s in the ventral surface layer region 14 are alternately provided in contact with the neutral surface side surface of the composite material layer of the other surface layer region.
  • the composite wing 10 and the method for manufacturing the composite wing 10 are associated with the stacking of the composite material layer as compared with the case where the end of the composite material layer 12s is in contact with the end of the composite material layer 14s.
  • the ply drop which is a gap generated in the vicinity of the neutral surface, can be divided by the end portion of the composite material layer to be reduced.
  • wing 10 can improve the intensity
  • the composite blade 10 and the method for manufacturing the composite blade 10 can stabilize the shape of the composite blade 10, it is possible to sufficiently ensure the accuracy of the contour and the thickness.
  • the composite material blade 10 and the method for manufacturing the composite material blade 10 do not need to overlap the composite material layer symmetrically in the blade thickness direction with respect to the neutral plane, and thus can reduce the manufacturing cost.
  • the composite blade described in Patent Document 1 has a large amount of thin composite material layers stacked symmetrically with respect to the neutral plane in the blade thickness direction. For this reason, the composite blade described in Patent Document 1 has a problem in that a ply drop, which is a gap generated in the vicinity of the neutral surface with the lamination of the composite material layer, is greatly formed on the neutral surface. It was.
  • the composite material blade described in Patent Document 1 has a problem in that strength and reliability at the end in the blade width direction are reduced due to a ply drop that is formed to be large.
  • the composite blade according to the second embodiment has been made in view of these problems, and the composite blade and the method for manufacturing the composite blade improved in strength and reliability at the end in the blade width direction. Is intended to provide.
  • the composite blade according to the second embodiment has a tendency of the thickness per layer of the composite material layer constituting the composite blade as shown in FIG. There is no. That is, in the composite blade according to the second embodiment, the composite blade according to the first embodiment is such that the median value or average value of the thickness per layer of the composite material layer in the surface layer region is the deep layer region. There is no tendency to be thinner than the median or average value of the thickness of each composite material layer.
  • the composite blade according to the second embodiment is the same as the composite blade 10 in other configurations. In the description of the second embodiment, the same code group as that of the first embodiment is used in the same configuration as that of the first embodiment, and the detailed description thereof is omitted.
  • the composite blade according to the second embodiment is formed by laminating a composite material layer in which a reinforcing fiber is impregnated with resin in the blade thickness direction, similarly to the composite blade 10.
  • the reinforcing fibers and resin constituting the composite material layer included in the composite blade according to the second embodiment are the same as the reinforcing fibers and resin constituting the composite material layer included in the composite blade 10.
  • the composite wing according to the second embodiment has a dorsal surface layer region 12, a ventral surface layer region 14, and a dorsal deep layer region 16, as shown in FIGS. 2 and 3. And a ventral deep region 18 and an internal region 19.
  • the dorsal surface layer region 12 is a region from the dorsal surface to a predetermined depth in the blade thickness direction.
  • the dorsal deep layer region 16 is a region deeper than a predetermined depth in the blade thickness direction from the dorsal surface.
  • the ventral surface layer region 14 is a region from the ventral surface to a predetermined depth in the blade thickness direction.
  • the ventral deep layer region 18 is a region deeper than a predetermined depth in the blade thickness direction from the ventral surface.
  • the back surface layer region 12 and the ventral surface layer region 14 in the composite wing according to the second embodiment are both included in the surface layer region from the surface to a predetermined depth in the blade thickness direction, like the composite wing 10. It is. Both the back-side deep layer region 16 and the ventral-side deep layer region 18 in the composite blade according to the second embodiment are included in a deep layer region deeper than a predetermined depth from the surface in the blade thickness direction, like the composite blade 10. It is.
  • the composite blade according to the second embodiment has a thin portion 10 a and a thick portion 10 b, as in the composite blade 10.
  • the thin portion 10a has a surface layer region, that is, a dorsal surface layer region 12 and a ventral surface layer region 14.
  • the thin portion 10a does not include a deep layer region, that is, the dorsal deep layer region 16 and the ventral deep layer region 18.
  • the thick portion 10 b includes a back surface layer region 12, a ventral surface layer region 14, a back deep layer region 16, a ventral deep layer region 18, and an internal region 19.
  • the composite material wing according to the second embodiment has a back wing portion and a ventral wing portion.
  • the wing portion on the back side is a region on the dorsal side with respect to the middle in the blade thickness direction, and includes a dorsal surface layer region 12 and a dorsal deep layer region 16.
  • the ventral wing portion is a region on the ventral side with respect to the middle in the blade thickness direction, and includes a ventral surface layer region 14 and a ventral deep layer region 18.
  • the back wing portion and the ventral wing portion are joined at the neutral plane.
  • the back side deep layer region 16 in the back side wing portion and the ventral side deep layer region 18 in the ventral side wing portion are provided. Are joined at the neutral plane.
  • the dorsal surface layer region 12 and the ventral surface layer region 14, which are surface layer regions, in the surface direction including the blade width direction and the blade length direction are The area is larger than the back side deep layer region 16 and the ventral side deep layer region 18 which are deep layer regions. That is, the composite wing according to the second embodiment is similar to the composite wing 10 in the surface direction including the wing width direction and the wing length direction, and the dorsal surface layer region 12 and the ventral surface layer region which are the surface layer regions.
  • the composite material layer in 14 has a larger area than the composite material layer in the back side deep layer region 16 and the ventral side deep layer region 18 which are deep layer regions.
  • the composite blade according to the second embodiment has a back surface region 12 and a ventral surface region 14 whose end portions in the blade width direction are surface regions, as shown in FIG. 4. It is constituted by.
  • the end portions of the plurality of composite material layers 12 s in the back surface region 12 and the end portions of the plurality of composite material layers 14 s in the ventral surface layer region 14 are alternately arranged at the end portions in the blade width direction.
  • the end of the composite material layer 12s contacts the surface of the composite material layer 14s at the end in the blade width direction.
  • the contact portions 21 and the contact portions 22 in which the end portions of the composite material layer 14s are in contact with the surface of the composite material layer 12s are alternately arranged.
  • the contact portions 21 and the contact portions 22 are alternately arranged at the end in the blade width direction.
  • the ply drop which is a gap caused by the lamination of the composite material layer, can be divided by the end portion of the composite material layer to be reduced.
  • wing which concerns on 2nd Embodiment improves intensity
  • the shape of the composite blade according to the second embodiment is stabilized similarly to the composite blade 10, it is possible to sufficiently ensure the accuracy of the contour and the thickness. Further, the composite blade 10 does not need to overlap the composite material layer symmetrically in the blade thickness direction with respect to the neutral plane, and thus the manufacturing cost can be reduced.
  • the method for producing a composite wing according to the second embodiment is an example of a method for obtaining the composite wing according to the second embodiment. Similar to the method for manufacturing the composite blade 10 according to the first embodiment, the method for manufacturing the composite blade according to the second embodiment, as shown in FIG. And a back deep layer region stacking step (step S14), a ventral surface layer region stacking step (step S16), a ventral deep layer region stacking step (step S18), and a joining step (step S20).
  • Steps S12 and S16 in the method for manufacturing a composite wing according to the second embodiment are similar to the first embodiment in that a plurality of composite material layers 12s in the dorsal surface layer region 12 at the end in the wing width direction are used. And the end portions of the plurality of composite material layers 14s in the ventral surface layer region 14 are alternately provided in contact with the neutral surface side surface of the composite material layer in the other surface layer region. A composite material layer 12s and a plurality of composite material layers 14s are respectively stacked.
  • step S12 and step S16 in the method for manufacturing a composite blade according to the second embodiment are similar to the first embodiment in that the end portion of the composite material layer 12s is the end portion in the blade width direction.
  • the contact portions 21 in contact with the surface of the composite material layer 14s and the contact portions 22 in which the ends of the composite material layer 14s are in contact with the surface of the composite material layer 12s are arranged.
  • a plurality of composite material layers 12s and a plurality of composite material layers 14s are stacked. Thereby, the manufacturing method of the composite material wing
  • the composite blade according to the second embodiment and the method for manufacturing the composite blade according to the second embodiment have the above-described configuration, a ply drop that is a gap generated with the lamination of the composite material layers is removed. It can be divided by the end portion of the composite material layer to reduce the size.
  • blade which concerns on 2nd Embodiment improve intensity
  • the shape of the composite blade according to the second embodiment and the method for manufacturing the composite blade according to the second embodiment is stabilized, it is possible to sufficiently ensure the accuracy of the contour and thickness. it can. Further, the composite blade according to the second embodiment and the method for manufacturing the composite blade according to the second embodiment do not need to overlap the composite material layers symmetrically in the blade thickness direction with respect to the neutral plane. The manufacturing cost can be reduced.
  • the composite blade according to the second embodiment and the method for manufacturing the composite blade according to the second embodiment are similar to the composite blade 10 and the method for manufacturing the composite blade 10 in the blade width direction and the blade length direction.
  • the surface area of the composite material layer in the surface region is larger than the composite material layer in the deep layer region.
  • the composite blade according to the second embodiment and the method for manufacturing the composite blade according to the second embodiment are configured so that the end portions in the blade width direction of the composite material layer are provided in contact with each other alternately. Strength and reliability are further improved.
  • the composite blade according to the second embodiment and the method for manufacturing the composite blade according to the second embodiment stabilize the shape in a wider range in the plane direction including the blade width direction and the blade length direction. Therefore, it is possible to ensure the accuracy of the contour in a wider range in the plane direction including the blade width direction and the blade length direction.
  • the composite blade according to the second embodiment and the method for manufacturing the composite blade according to the second embodiment are thinner than the thick portion 10b, as in the method for manufacturing the composite blade 10 and the composite blade 10. It further has a thin portion 10a that does not include a deep region.
  • the composite blade according to the second embodiment and the method for manufacturing the composite blade according to the second embodiment are configured so that the end portions in the blade width direction of the composite material layer are provided in contact with each other alternately. Further, the strength and reliability are further improved in the thin portion in the blade thickness direction. For this reason, the shape of the composite blade according to the second embodiment and the method for manufacturing the composite blade according to the second embodiment is stabilized in the thin portion in the blade thickness direction. It is possible to ensure the accuracy of the thickness in the thin portion.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • General Engineering & Computer Science (AREA)
  • Medicinal Chemistry (AREA)
  • Textile Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Architecture (AREA)
  • Polymers & Plastics (AREA)
  • Organic Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Reinforced Plastic Materials (AREA)
  • Laminated Bodies (AREA)
  • Moulding By Coating Moulds (AREA)
PCT/JP2018/017534 2017-05-08 2018-05-02 複合材翼及び複合材翼の製造方法 Ceased WO2018207702A1 (ja)

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US16/611,404 US11371365B2 (en) 2017-05-08 2018-05-02 Composite blade and method for manufacturing composite blade
CN201880030399.4A CN110612398B (zh) 2017-05-08 2018-05-02 复合材料叶片及复合材料叶片的制造方法
DE112018002364.8T DE112018002364T5 (de) 2017-05-08 2018-05-02 Verbundschaufel und verfahren zum herstellen einer verbundschaufel

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CN112937819B (zh) * 2021-03-30 2024-05-14 大连海事大学 一种耐蚀耐冲击的船用混杂纤维复合材料螺旋桨叶及其制备方法
US12241386B2 (en) * 2023-02-21 2025-03-04 General Electric Company Turbine engine airfoil with a woven core and woven layer
CN119801961B (zh) * 2025-01-26 2025-11-11 宁波方太厨具有限公司 轴流风机及包括其的油烟机

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JP2018189028A (ja) 2018-11-29
US20200173292A1 (en) 2020-06-04
DE112018002364T5 (de) 2020-01-16
US11371365B2 (en) 2022-06-28
JP6800805B2 (ja) 2020-12-16
CN110612398B (zh) 2021-09-17

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