CN109989938B - Fan blade of aeroengine and manufacturing method thereof - Google Patents
Fan blade of aeroengine and manufacturing method thereof Download PDFInfo
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- CN109989938B CN109989938B CN201910226426.1A CN201910226426A CN109989938B CN 109989938 B CN109989938 B CN 109989938B CN 201910226426 A CN201910226426 A CN 201910226426A CN 109989938 B CN109989938 B CN 109989938B
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- 238000004519 manufacturing process Methods 0.000 title claims description 13
- 229910052751 metal Inorganic materials 0.000 claims abstract description 76
- 239000002184 metal Substances 0.000 claims abstract description 75
- 239000011347 resin Substances 0.000 claims abstract description 9
- 229920005989 resin Polymers 0.000 claims abstract description 9
- 230000003014 reinforcing effect Effects 0.000 claims description 16
- 239000000463 material Substances 0.000 claims description 14
- 239000000835 fiber Substances 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 12
- 238000005516 engineering process Methods 0.000 claims description 5
- 238000010146 3D printing Methods 0.000 claims description 4
- 238000003754 machining Methods 0.000 claims description 4
- 239000002131 composite material Substances 0.000 abstract description 18
- 239000011159 matrix material Substances 0.000 abstract description 4
- 239000010410 layer Substances 0.000 description 54
- 238000010586 diagram Methods 0.000 description 3
- 239000011229 interlayer Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 208000010392 Bone Fractures Diseases 0.000 description 2
- 206010017076 Fracture Diseases 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 238000009954 braiding Methods 0.000 description 2
- 239000000805 composite resin Substances 0.000 description 2
- 208000037265 diseases, disorders, signs and symptoms Diseases 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000002657 fibrous material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000035515 penetration Effects 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 238000004220 aggregation Methods 0.000 description 1
- 230000002776 aggregation Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 239000011247 coating layer Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000007688 edging Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000007788 roughening Methods 0.000 description 1
- 238000005488 sandblasting Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
- F04D29/386—Skewed blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A fan blade for an aircraft engine, comprising: the hollow metal framework (1) comprises a blade body (11), wherein the cross section of the blade body (11) is an arc double arrow, the concave surface of the blade body (11) is a blade basin (112) of the blade body (11), the convex surface of the blade body (11) is a blade back (113) of the blade body (11), a plurality of rectangular holes (111) are formed in the blade body (11), and the rectangular holes (111) penetrate through the blade basin (112) and the blade back (113); an inner cured layer (2) which covers the outer surfaces of the leaf basin (112) and the leaf back (113) and penetrates through the rectangular hole (111); the outer curing layer (3) is covered on the outer surfaces of the inner curing layer (2) and the hollowed-out metal framework (1); and the metal wrapping edge (4) is arranged at the windward end of the outer curing layer (3). The impact strength of the composite material blade is improved by utilizing the structural strength of the metal framework, the weight of the blade is reduced by utilizing the resin matrix composite material, and the composite material blade has important significance for improving the thrust-weight ratio and the comprehensive tactical index of the aeroengine.
Description
Technical Field
The invention relates to the technical field of aeroengines, in particular to a fan blade of an aeroengine and a manufacturing method thereof.
Background
The large duct is longer than the fan blade of the engine, the weight is larger, the requirements of people on the performance of the aeroengine are higher and higher along with the progress of technology, in order to reduce the weight of the engine and increase the thrust of the engine, a plurality of new structural designs are continuously proposed, and new processes are continuously applied, wherein resin-based composite materials are widely applied to the structural designs, the existing large duct is made of integral composite materials, however, if the fan blade designed based on the traditional method and the structural design cannot meet the impact, the root strength of the integrally woven blade is insufficient, and the root fracture is easy to occur. The prior art composite material blade with the mixed structure comprises a titanium alloy matrix from the bottom of a tenon to the tip of the blade, a frame structure in the shape of a Chinese character 'tian' is arranged on the titanium alloy matrix, a blade body is formed by covering composite material fillers on two sides of a blade basin and a blade back of the matrix, and a blade profile is formed by covering a skin on the outer surface of the blade. The other type of the composite material fan blade is coated and reinforced by using the net-shaped coating layer, and the additional centrifugal load brought by the metal net during high-speed rotation finally acts on the composite material blade root through the composite material layer, so that the load of the composite material blade is additionally increased; in the other patents, hollow blades and aeroengines are adopted, all the blades are manufactured by additive manufacturing and printed, and compared with a composite material, the structure is heavier, and the lightweight design and manufacturing concept of the existing engine cannot be better met.
Disclosure of Invention
First, the technical problem to be solved
Based on the technical problems, the invention provides a fan blade of an aero-engine, which aims to improve the impact strength of a composite material blade by utilizing the structural strength of a metal framework, and fully utilizes a resin-based composite material to reduce the weight of the whole blade.
(II) technical scheme
In a first aspect, the present invention provides a fan blade for an aircraft engine, comprising: the hollow metal framework 1 comprises a blade body 11, wherein the cross section of the blade body 11 is in the shape of an arc double arrow or a fishbone, the concave surface of the blade body 11 is a blade basin 112, the convex surface of the blade body 11 is a blade back 113, a plurality of rectangular holes 111 are formed in the blade body 11, and the rectangular holes 111 penetrate through the blade basin 112 and the blade back 113; an inner cured layer 2 which covers the outer surfaces of the leaf basin 112 and the leaf back 113 and penetrates the rectangular hole 111; the outer curing layer 3 is covered on the outer surfaces of the inner curing layer 2 and the hollowed-out metal framework 1; and the metal wrapping edge 4 is arranged at the windward end of the outer solidified layer 3.
Optionally, a plurality of reinforcing plates 5 are further included, and the plurality of reinforcing plates 5 are interposed between the outer cured layer 3 and/or the inner cured layer 2.
Alternatively, the material of the reinforcing plate 5 is Z-pin.
Optionally, a round chamfer is arranged on the rectangular hole.
Optionally, the inner cured layer 2 is cured from fibers and resin.
Optionally, the hollowed-out metal skeleton 1 and the metal wrapping 4 are spatially overlapped.
Alternatively, the material of the outer cured layer 3 is a prepreg.
Optionally, the hollow metal skeleton 1 further comprises a tenon root 12, and the blade body 11 is vertically arranged on the surface of the tenon root 12.
Optionally, the surface of the blade body 11 furthest from the tenon root 12 is a tip 114 of the blade body 11, and at least one protrusion 115 is provided on the surface of the blade body 11, and each protrusion 115 extends from the tenon root 12 to the tip 114.
On the other hand, the invention provides a manufacturing method of the fan blade of the aeroengine, which comprises the following steps: s1, generating a hollowed-out metal framework 1 by adopting a machining or 3D printing technology; s2, curing fibers and resin on a leaf basin 112 and a leaf back 113 of the hollow metal framework 1 by adopting a seam laying method to generate an inner curing layer 2; s3, covering the outer surfaces of the solidified layer 2 and the hollowed-out metal framework 1 by using prepreg to generate an outer solidified layer 3, and embedding a reinforcing plate 5 while covering the outer surfaces of the solidified layer 2 and the hollowed-out metal framework 1; s4, covering the windward end of the outer solidified layer 3 by adopting a metal plate to generate a metal wrapping edge 4.
(III) beneficial effects
The invention provides a fan blade of an aeroengine, which has at least the following technical effects:
(1) The inside of the blade adopts a metal framework which is double-arrow-head-shaped, and the structure strength is high, so that the blade is not easy to damage after being impacted;
(2) The metal wrapping edges 4 and the hollow metal framework 1 are in an overlapped design, so that the front edge of the blade is prevented from being damaged after being impacted;
(3) Besides the metal wrapping edges 4 and the hollow metal framework 1, other structures adopt composite materials, so that the weight of the blade is reduced;
(4) The braiding of the inner solidified layer 2 and the hollow metal framework 1 is completed by adopting a seam laying method, the combination between metal and composite materials is reinforced, layering of different material structures of the blade at high rotating speed is avoided, and the service life of the blade is prolonged.
Drawings
FIG. 1A schematically illustrates a front view of a fan blade of an embodiment of the present disclosure;
FIG. 1B schematically illustrates a cross-sectional view corresponding to section line A-A in FIG. 1 of an embodiment of the present disclosure;
FIG. 2 schematically illustrates a cross-sectional view of an embodiment of the present disclosure corresponding to a section line perpendicular to the section line A-A in FIG. 1
Fig. 3A schematically illustrates a top view of the hollowed out metal skeleton 1 of a fan blade according to an embodiment of the present disclosure;
fig. 3B schematically illustrates a three-dimensional perspective view of the hollowed out metal skeleton 1 of a fan blade according to an embodiment of the present disclosure;
fig. 4A schematically illustrates a top view of the hollow metal skeleton 1 of a fan blade according to an embodiment of the present disclosure, when the blade body 11 does not have the protrusions 115;
fig. 4B schematically illustrates a top view of the blade body 11 of the hollow metal skeleton 1 of the fan blade according to the embodiment of the present disclosure, with one protrusion 115;
fig. 4C schematically illustrates a top view of a blade body 11 of a hollowed out metal skeleton 1 of a fan blade according to an embodiment of the present disclosure, with three protrusions 115;
FIG. 4D schematically illustrates a perspective view corresponding to FIG. 4C of an embodiment of the present disclosure;
FIG. 5A schematically illustrates a three-dimensional block diagram of an inner cured layer 2 of a fan blade according to an embodiment of the present disclosure;
FIG. 5B schematically illustrates a three-dimensional cross-sectional view corresponding to section line E-E in FIG. 5A in accordance with an embodiment of the present disclosure;
FIG. 6A schematically illustrates a three-dimensional block diagram of the outer cured layer 3 of a fan blade in accordance with an embodiment of the present disclosure;
FIG. 6B schematically illustrates a front view of the outer cured layer 3 of a fan blade in accordance with an embodiment of the present disclosure;
FIG. 6C schematically illustrates a cross-sectional view corresponding to section line D-D in FIG. 6B in accordance with an embodiment of the present disclosure;
fig. 7 schematically illustrates a structural schematic of the outer cured layer 3 and the reinforcing plate 5 of the embodiment of the present disclosure;
FIG. 8 schematically illustrates a partial cross-sectional view of a fan blade including a metallic shroud 4 in accordance with an embodiment of the present disclosure;
FIG. 9 schematically illustrates a constraint schematic of a fan blade of an embodiment of the present disclosure;
fig. 10 schematically illustrates a method step diagram for fabricating a fan blade for an aircraft engine in accordance with an embodiment of the present disclosure.
Detailed Description
The present invention will be further described in detail below with reference to specific embodiments and with reference to the accompanying drawings, in order to make the objects, technical solutions and advantages of the present invention more apparent.
The invention provides a fan blade of an aeroengine, referring to fig. 1A, 1B and 2, wherein A-A in fig. 1A is a section line, fig. 1B is a section corresponding to the section line A-A, and fig. 2 is a section corresponding to the section line perpendicular to the section line A-A, it can be seen that the fan blade comprises a hollowed-out metal skeleton 1, an inner solidified layer 2, an outer solidified layer 3, a metal wrapping edge 4 and a reinforcing plate 5, wherein: the hollow metal framework 1 comprises a blade body 11, wherein the section of the blade body 11 is in an arc double-arrow or fishbone shape, the concave surface of the blade body 11 is a blade basin 112 of the blade body 11, the convex surface of the blade body 11 is a blade back 113 of the blade body 11, a plurality of rectangular holes 111 are formed in the blade body 11, and the rectangular holes 111 penetrate through the blade basin 112 and the blade back 113; an inner cured layer 2 which covers the outer surfaces of the leaf basin 112 and the leaf back 113 and penetrates the rectangular hole 111; the outer curing layer 3 is covered on the outer surfaces of the inner curing layer 2 and the hollowed-out metal framework 1; and the metal wrapping edge 4 is arranged at the windward end of the outer solidified layer 3. Which will be described in detail below.
The hollow metal framework 1, see fig. 3A and 3B, comprises a blade body 11, wherein the section of the blade body 11 is arc double-arrow or fishbone, the concave surface of the blade body 11 is a blade basin 112 of the blade body 11, the convex surface of the blade body 11 is a blade back 113 of the blade body 11, a plurality of rectangular holes 111 are formed in the blade body 11, and the rectangular holes 111 penetrate through the blade basin 112 and the blade back 113;
specifically, the hollowed-out metal skeleton 1 comprises a blade body 11, the concave surface of the blade body 11 is a blade basin 112 of the blade body 11, the convex surface of the blade body 11 is a blade back 113 of the blade body 11, a plurality of rectangular holes 111 are formed in the blade body 11, the rectangular holes 111 penetrate through the blade basin 112 and the blade back 113, the rectangular holes 111 are lightening holes, the specific number of the rectangular holes is determined after strength design calculation is carried out according to actual needs, and the rectangular structure can avoid disorder of a fiber layering structure in the blade caused by aggregation of fibers to round holes or elliptical holes in the stress process of the blade possibly existing in other round or elliptical structural designs, so that the service performance of the blade is reduced and the strength is reduced due to disorder of fiber distribution; the periphery of the rectangular hole 111 is provided with a larger round chamfer, so that the condition that the strength of the hollowed-out metal skeleton 1 is reduced due to stress concentration at the edge of the sharp corner is effectively avoided, and the service life of the whole blade is prolonged; meanwhile, the rectangular holes 111 are used for fiber penetration during braiding of the hollow metal framework 1 and the fiber material and fiber penetration during fiber seam laying, and the surface of the rectangular holes is subjected to sand blasting or roughening treatment, so that the roughness of the surface is increased, and the rectangular holes are convenient to combine with the interface of the fiber material. Referring to fig. 3A, the hollowed-out metal skeleton 1 further includes a tenon 12, the blade body 11 is vertically disposed on the surface of the tenon 12, the surface of the blade body 11 farthest from the tenon 12 is a blade top 114 of the blade body 11, at least one protrusion 115 is disposed on the surface of the blade body 11, referring to fig. 4A to 4D, and each protrusion 115 extends from the tenon 12 to the blade top 114. The protrusion 115 plays a role of a reinforcing rib, and is distributed with a plurality of rows of installation blades, so that the strength analysis is lack under the actual running condition, when the rotating speed of the small blades is low, a simplified design method of double-headed arrows can be directly adopted, when the size and the length of the blades are large, and when the rotating speed is high, the protrusion 115 of the reinforcing rib can be designed according to the strength requirement, the strength of the hollowed-out metal skeleton 1 is further enhanced, and the requirement of the impact resistance is met.
The hollow metal skeleton 1 can be produced by adopting the technologies such as machining or 3D printing.
An inner cured layer 2, as shown in fig. 5A and 5B, which covers the outer surfaces of the leaf basin 112 and the leaf back 113 and fills the rectangular hole 111;
specifically, the material of the inner cured layer 2 is fiber and resin, the fiber is firstly used to penetrate the outer surfaces of the leaf basin 112 and the leaf back 113, the rectangular hole 111 is penetrated, then resin curing is adopted to firmly wrap the hollow metal framework 1, the inner cured layer 2 after resin curing can be inlaid in the groove between the two bulges 115, a smooth profile curved surface is finally formed, and the outer cured layer 3 is conveniently wrapped, paved and cured to form the inner core structure of the whole fan blade.
Fig. 6A to 6C show an external cured layer 3, wherein fig. 6A is a three-dimensional oblique view of the external cured layer 3, fig. 6B is a front view of the external cured layer 3, and fig. 6C is a cross-sectional view corresponding to a section line D-D in fig. 6B, which covers the external surfaces of the internal cured layer 2 and the hollow metal skeleton 1;
specifically, the material of the outer solidified layer 3 is prepreg, the prepreg is adopted to be paved along the tenon root 12 to the blade top 114, the prepreg is adopted to wrap and wind, the wrapping and winding are required to ensure the continuity of the material, the deformation of the fan blade can be reduced to the greatest extent, the deformation of the hollow metal skeleton 1 and the inner composite material of the blade is close, the interlayer stress is reduced, and finally the outer surface of the fan blade is formed.
The fan blade further comprises a plurality of reinforcing plates 5, as shown in fig. 7, wherein the plurality of reinforcing plates 5 are inserted into the outer curing layer 3 and/or the inner curing layer 2;
specifically, the material of the reinforcing plate 5 is Z-pin, which is inserted into the outer curing layer 3 to strengthen the interlayer strength of the outer curing layer 3, and part of the reinforcing plate 5 can be simultaneously inserted into the outer curing layer 3 and the inner curing layer 2 to strengthen the bonding strength between the outer curing layer 3 and the inner curing layer 2, so that the interlayer separation of the composite material caused by the internal deformation of the blade in the axial direction in the impact process is avoided, the service performance of the composite material is improved, and the blade is ensured to meet the strength requirement.
The metal edging 4, see fig. 8, is provided at the windward end of the outer solidified layer 3.
Specifically, the metal wrapping 4 is coated on the windward end of the outer cured layer 3, and is mainly used for resisting the impact of flying birds, etc., and as shown in fig. 8, the arrow direction is a possible stress direction, and an overlap exists between the metal wrapping 4 and the hollow metal skeleton 1. Under the action of impact force, the outer solidified layer 3 between the metal covered edge 4 and the front edge of the hollow metal framework 1 is subjected to compression deformation, and nesting overlapping exists, so that the front edges of the metal covered edge 4 and the hollow metal framework 1 can be prevented from dislocation, the phenomenon that the outer solidified layer 3 is torn due to dislocation of the metal covered edge 4 and the hollow metal framework 1 is avoided, the occurrence of front edge cracking and layering caused by bird strike is avoided, and the integral front edge impact resistance effect of the blade is ensured.
As shown schematically in fig. 9, which is a schematic view illustrating constraint of a blade in an embodiment of the present disclosure, black arrows in the drawing indicate constraint of a tongue-and-groove to the blade during assembly and operation of the blade, the blade root of the hollowed metal skeleton 1 and the lower part of the outer solidified layer 3 together form the blade root of the fan blade, in this structure, the blade root of the hollowed metal skeleton 1 bears most of centrifugal force during high-speed operation and is transferred to the tongue-and-groove through the lower part of the outer solidified layer 3 together, so that the centrifugal force of the blade itself is avoided depending on the composite material, and the material of the outer solidified layer 3 is only pressed by the extrusion force between the blade root of the hollowed metal skeleton 1 and the tongue-and-groove, and the sliding friction load acting on the material is relatively small, so that the mechanical property of the material can be fully exerted, and the fracture risk of the blade root of the fan blade of the aeroengine is avoided.
On the other hand, referring to fig. 10, the invention provides a method for manufacturing a fan blade of an aeroengine, which comprises the following steps: s1, generating a hollowed-out metal framework 1 by adopting a machining or 3D printing technology; s2, curing fibers and resin on a leaf basin 112 and a leaf back 113 of the hollow metal framework 1 by adopting a seam laying method to generate an inner curing layer 2; s3, covering the outer surfaces of the solidified layer 2 and the hollowed-out metal framework 1 by using prepreg to generate an outer solidified layer 3, and embedding a reinforcing plate 5 while covering the outer surfaces of the solidified layer 2 and the hollowed-out metal framework 1; s4, covering the windward end of the outer solidified layer 3 by adopting a metal plate to generate a metal wrapping edge 4.
While the foregoing is directed to embodiments of the present invention, other and further details of the invention may be had by the present invention, it should be understood that the foregoing description is merely illustrative of the present invention and that no limitations are intended to the scope of the invention, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the invention.
Claims (5)
1. A method of making a fan blade for an aircraft engine, the fan blade comprising:
the hollow metal framework (1) comprises a blade body (11), wherein the cross section of the blade body (11) is in the shape of an arc double arrow or a fishbone, the concave surface of the blade body (11) is a blade basin (112), the convex surface of the blade body (11) is a blade back (113), a plurality of rectangular holes (111) are formed in the blade body (11), the rectangular holes (111) penetrate through the blade basin (112) and the blade back (113), and round chamfer angles are formed in the rectangular holes (111); the hollow metal framework (1) further comprises a tenon root (12), the blade body (11) is vertically arranged on the surface of the tenon root (12), the surface, farthest from the tenon root (12), of the blade body (11) is a blade top (114) of the blade body (11), at least one protrusion (115) is arranged on the surface of the blade body (11), and each protrusion (115) extends from the tenon root (12) to the blade top (114);
an inner cured layer (2) which covers the outer surfaces of the leaf basin (112) and the leaf back (113) and penetrates through the rectangular hole (111);
the outer curing layer (3) is covered on the outer surfaces of the inner curing layer (2) and the hollowed-out metal framework (1);
the metal wrapping edge (4) is arranged at the windward end of the outer curing layer (3);
a plurality of reinforcing plates (5), wherein the plurality of reinforcing plates (5) are inserted into the outer curing layer (3);
the manufacturing method of the fan blade comprises the following steps:
s1, generating the hollowed-out metal framework (1) by adopting a machining or 3D printing technology;
s2, curing fibers and resin on the leaf basin (112) and the leaf back (113) of the hollowed-out metal skeleton (1) by adopting a seam laying method to generate the inner curing layer (2);
s3, covering the outer surfaces of the inner curing layer (2) and the hollowed-out metal framework (1) by prepreg to generate an outer curing layer (3), and embedding the reinforcing plate (5) while covering the outer surfaces of the inner curing layer (2) and the hollowed-out metal framework (1);
s4, covering the windward end of the outer curing layer (3) by adopting a metal plate to generate the metal wrapping edge (4).
2. A method of manufacturing a fan blade according to claim 1, characterized in that the material of the stiffening plate (5) is Z-pin.
3. A method of manufacturing a fan blade according to claim 1, characterized in that the inner cured layer (2) is formed by curing fibres and resin.
4. The method for manufacturing the fan blade according to claim 1, wherein the hollowed-out metal skeleton (1) and the metal wrapping (4) are spatially overlapped.
5. A method of manufacturing a fan blade according to claim 1, characterized in that the material of the outer cured layer (3) is prepreg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910226426.1A CN109989938B (en) | 2019-03-22 | 2019-03-22 | Fan blade of aeroengine and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910226426.1A CN109989938B (en) | 2019-03-22 | 2019-03-22 | Fan blade of aeroengine and manufacturing method thereof |
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| Publication Number | Publication Date |
|---|---|
| CN109989938A CN109989938A (en) | 2019-07-09 |
| CN109989938B true CN109989938B (en) | 2024-02-06 |
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| CN201910226426.1A Active CN109989938B (en) | 2019-03-22 | 2019-03-22 | Fan blade of aeroengine and manufacturing method thereof |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110795803B (en) * | 2019-11-10 | 2023-09-29 | 中国航发南方工业有限公司 | Extrusion molding blade |
| CN111499338B (en) * | 2020-04-27 | 2021-11-26 | 江苏优格曼航空科技有限公司 | Preparation method of composite material blade for high-specific-strength ventilator |
| CN112112835B (en) * | 2020-09-04 | 2022-03-25 | 杜涛 | Composite material fan blade of aero-engine and manufacturing method thereof |
| CN112277343A (en) * | 2020-09-30 | 2021-01-29 | 株洲时代新材料科技股份有限公司 | Composite material blade edge covering method and structure |
| CN114876862B (en) * | 2022-05-10 | 2024-06-04 | 中国科学院工程热物理研究所 | Impact-resistant composite material fan blade and processing method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101418811A (en) * | 2008-09-03 | 2009-04-29 | 中国航空工业第一集团公司北京航空材料研究院 | Hollow fan blade for aircraft engine |
| CN102808657A (en) * | 2012-09-11 | 2012-12-05 | 上海交通大学 | Fan blade in metal/composite material mixed structure and manufacturing method thereof |
| CN106762813A (en) * | 2017-03-31 | 2017-05-31 | 中航商用航空发动机有限责任公司 | A kind of fan blade |
| JP2018066289A (en) * | 2016-10-18 | 2018-04-26 | 株式会社Ihi | Fan rotor blade and method for manufacturing the same |
| CN210152973U (en) * | 2019-03-22 | 2020-03-17 | 中国科学院工程热物理研究所 | Fan blade of aircraft engine |
Family Cites Families (1)
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101418811A (en) * | 2008-09-03 | 2009-04-29 | 中国航空工业第一集团公司北京航空材料研究院 | Hollow fan blade for aircraft engine |
| CN102808657A (en) * | 2012-09-11 | 2012-12-05 | 上海交通大学 | Fan blade in metal/composite material mixed structure and manufacturing method thereof |
| JP2018066289A (en) * | 2016-10-18 | 2018-04-26 | 株式会社Ihi | Fan rotor blade and method for manufacturing the same |
| CN106762813A (en) * | 2017-03-31 | 2017-05-31 | 中航商用航空发动机有限责任公司 | A kind of fan blade |
| CN210152973U (en) * | 2019-03-22 | 2020-03-17 | 中国科学院工程热物理研究所 | Fan blade of aircraft engine |
Non-Patent Citations (1)
| Title |
|---|
| 涡轮叶片冷却新方法;顾维藻, 张玉明, 许鸿坤;工程热物理学报(第01期);第73-75页 * |
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