Blade test assembly and manufacturing method and testing method thereof

Abstract

The present invention discloses a blade test assembly and a manufacturing method and a testing method thereof. The manufacturing method of the blade test assembly includes: providing a blade sampling piece, cutting the covering portion, and splitting the covering portion into an edge portion connected to the nose cone portion, and a residual portion separated from the edge portion; avoiding the blade portion, and opening a first through hole in the nose cone portion; avoiding the edge portion, and opening a second through hole in the blade portion. By cutting the reinforcement, only the bonding strength of a part of the covering portion can be tested, reducing the requirements for applying load, and the bonding performance can be evaluated more simply and accurately. The blade test assembly obtained by the above-mentioned manufacturing method can more conveniently perform a bonding performance tensile test and obtain a more accurate evaluation result.

Description

Technical Field

[0001] The present application relates to the field of aero-engine testing, and in particular to a blade test assembly and a manufacturing method and a testing method thereof. Background Art

[0002] Composite materials have the characteristics of light weight and high specific strength. However, due to their weak impact resistance, composite fan blades need to withstand very severe bird strike impact loads. Therefore, a common practice is to cover the leading edge of the composite blade 2' with a metal reinforcement 1' (such as Figure 1 As shown in the figure, the composite part is protected from breaking when subjected to the severe load of bird strike impact. The metal reinforcement 1′ and the composite blade 2′ are connected by glue, so the bonding strength determines the ability of the composite blade to withstand impact loads. If the bonding strength is too low, the metal reinforcement 1′ and the composite blade 2′ will be debonded during bird strike impact, causing the metal reinforcement 1′ to fly off, resulting in direct contact between the bird body and the composite blade 2′, and the purpose of the metal reinforcement protecting the composite part cannot be achieved. Therefore, it is necessary to ensure that the bonding strength meets the load requirements, which requires the bonding strength test.

[0003] The fan blades have a relatively high span-wise height, generally at least 0.5 m, and have irregular shapes such as bends, sweeps, and surface twists, which bring certain difficulties to the bonding process. As a result, when bonding metal reinforcements and composite blades, it is impossible to ensure that the bonding strength between the composite material and the reinforcement is consistent with the bonding strength measured using a standard equal-thickness plate. Therefore, it is necessary to evaluate the bonding strength between the metal reinforcement and the composite blade, but the existing technology cannot evaluate the bonding strength at every point on the blade. Summary of the invention

[0004] The technical problem to be solved by the present invention is to overcome the defect in the prior art that the bonding strength between the blade and the leading edge metal reinforcement cannot be evaluated, and to provide a blade test assembly and a manufacturing method and a testing method thereof.

[0005] The present invention solves the above technical problems through the following technical solutions:

[0006] A method for manufacturing a blade test assembly, the method comprising:

[0007] A blade sampling piece is provided, wherein the blade sampling piece comprises a blade portion and a reinforcement piece, the blade portion corresponds to a portion of a leading edge of the blade, the reinforcement piece is glued to the blade portion, and the reinforcement piece is coated on the leading edge of the blade portion, the reinforcement piece comprises a nose cone portion glued to the front of the leading edge of the blade portion, and a coating portion glued to the pressure surface or the suction surface of the blade portion, and the coating portion is connected to the nose cone portion;

[0008] Cutting the covering portion to separate the covering portion into an edge portion connected to the nose cone portion and a residual portion spaced apart from the edge portion;

[0009] A first through hole is formed in the nose cone portion, avoiding the blade portion;

[0010] A second through hole is formed in the blade portion, avoiding the edge portion.

[0011] Due to the large size of the blade and its complex structural features such as bending and sweeping, it is difficult to evaluate the bonding strength between the blade and the reinforcement. In this scheme, by sampling a small part of the leading edge of the blade, the blade sampling piece is close to a flat plate structure, so that the local bonding shear strength of the blade can be evaluated. By sampling different parts of the blade, the leading edge bonding strength of the entire blade can be evaluated.

[0012] Since the covering portion of the reinforcement is relatively long, if the bonding shear strength of the reinforcement as a whole is measured, a relatively large load needs to be applied. It is even possible that during the load application process, the blade portion or the reinforcement fails due to reaching the tensile yield strength before the bonding fails, and the bonding failure strength cannot be obtained. Therefore, by cutting the covering portion, only the bonding strength of a portion of the covering portion (the edge portion) can be tested, and the bonding strength of the entire covering portion can be evaluated based on the test result and the dimensional relationship.

[0013] The stretching device can use the first through hole and the second through hole to perform a tensile test on the blade test assembly. Since the first through hole does not pass through the blade portion and the second through hole does not pass through the edging portion, when the edging portion and the blade portion are separated, it indicates that the adhesive layer between the edging portion and the blade portion has shear failure, thereby ensuring the accuracy of the test results.

[0014] Preferably, the providing of a leaf sampling member comprises:

[0015] Providing a complete blade having a complete reinforcement bonded to the leading edge of the blade;

[0016] The complete leaf is cut to obtain the leaf sampling piece.

[0017] In this solution, blade samples are obtained by cutting complete blades and complete reinforcements, that is, cutting real blades. Such blade samples are closer to the actual performance, so the results of subsequent tensile tests are closer to the actual performance.

[0018] Preferably, the providing of a leaf sampling member comprises:

[0019] A blade portion having a partial leading edge of the blade is obtained by machining, and a corresponding reinforcement member is glued to the leading edge of the blade portion to obtain the blade sampling member.

[0020] In this solution, the blade sampling piece is directly obtained by manufacturing a part of the real blade, which can reduce the cost of the blade sampling piece and shorten the test cycle.

[0021] A blade test assembly, the blade test assembly comprising a blade portion and a reinforcement, the blade portion corresponding to a portion of the leading edge of the blade, the reinforcement being glued to the blade portion and covering the leading edge of the blade portion, the reinforcement comprising a nose cone portion glued to the front of the leading edge of the blade portion, and a covering portion glued to the pressure surface or suction surface of the blade portion, the covering portion comprising an edging portion connected to the nose cone portion, and a residual portion spaced apart from the edging portion, the nose cone portion being provided with a first through hole, and the blade portion being provided with a second through hole, wherein the first through hole does not pass through the blade portion, and the edging portion does not overlap with the opening of the second through hole.

[0022] In this solution, the blade test assembly obtained by the above-mentioned manufacturing method can more accurately measure the bonding performance of the blade leading edge reinforcement ribs, and can be used to evaluate the strength performance of the bonding on the actual blade structure, and can also be used to evaluate the stability of the blade bonding performance.

[0023] Preferably, the curvature changes of the suction surface and the pressure surface of the blade portion do not exceed 20%.

[0024] In this solution, the structure of the blade test assembly is close to a flat plate by making the adhesive failure basically occur under pure shear load at the location where the curvature of the blade leading edge changes less. Preferably, the curvature change of the suction surface and the pressure surface of the blade part does not exceed 10%.

[0025] Preferably, the chord length of the hemming portion is 5 to 15 mm.

[0026] In the present scheme, if the chord-wise length of the edging portion is too long, the adhesive layer between the edging portion and the blade portion is not easy to fail, and it is even possible that during the process of applying the load, before the adhesive fails, the blade portion or the reinforcement fails due to reaching the tensile yield strength, resulting in the inability to obtain the adhesive failure strength; if the chord-wise length of the edging portion is too short, it is difficult to accurately evaluate the adhesive strength, and the adhesive layer may be unevenly distributed, resulting in adhesive failure under a smaller load.

[0027] Preferably, two sides of the nose cone are respectively fixedly connected with a first clamping member, and the first clamping member is provided with a third through hole corresponding to the position of the first through hole.

[0028] In this solution, if the tensile device acts directly on the first through hole, due to the thin thickness and low strength of the nose cone, in the process of increasing the tensile load, plastic deformation may occur at the first through hole before the adhesive failure, resulting in no adhesive failure and the inability to measure the adhesive strength. By setting the first clamp, the tensile load can be shared by the third through hole, thereby improving the bearing capacity of the blade test assembly, wherein the first clamp can be fixed to the nose cone by bolts or adhesive. Preferably, the diameters of the first through hole and the third through hole are equal.

[0029] Preferably, two sides of the blade portion are respectively fixedly connected with a second clamping member, and the second clamping member is provided with a fourth through hole corresponding to the position of the second through hole.

[0030] In this solution, if the stretching device acts directly on the second through hole, due to the thin thickness and low strength of the blade part, in the process of increasing the tensile load, plastic deformation may occur at the second through hole before the adhesive failure, resulting in no adhesive failure and the inability to measure the adhesive strength. By setting a second clamp, the fourth through hole can be used to share the tensile load, thereby improving the bearing capacity of the blade test assembly, wherein the second clamp can be fixed to the blade part by bolts or adhesive bonding. Preferably, the second through hole and the fourth through hole have the same diameter. Specifically, a plurality of second through holes can be provided to share the tensile load and improve the bearing capacity of the blade part.

[0031] Preferably, the two axial end faces of the blade test assembly are symmetrical about the symmetry plane, the line between the intersection points of the two ends of the edging portions away from the nose cone portion and the symmetry plane is the first neutral line, the intersection line of the symmetry plane and the leading edge of the blade portion is the second neutral line, the line between the midpoint of the first neutral line and the midpoint of the second neutral line constitutes a neutral axis, the axial line of the first through hole intersects with the neutral axis, and the axial line of the first through hole is perpendicular to the neutral line.

[0032] In this scheme, the pressure surface and suction surface of the blade part are approximate planes, and the neutral axis is basically parallel to the pressure surface and the suction surface. During the tensile test, the pin is inserted into the first through hole and stretched with the help of the pin. Since the first through hole is perpendicular to the neutral axis, during the tensile test, the stretching direction is basically along the direction of the neutral axis, and no eccentric loading occurs, that is, the direction of the tensile load should coincide with the neutral axis. The performance obtained by measurement in this way is closest to the pure shear performance of the bond.

[0033] A method for testing the bonding performance of a blade leading edge, the method comprising:

[0034] Providing a blade test assembly as described above;

[0035] The blade test assembly is stretched by using the first through hole and the second through hole until the bonding between the hemming portion and the blade portion fails, thereby obtaining the strength performance of the bonding.

[0036] Preferably, the providing of the blade test assembly as described above comprises:

[0037] A first pin is cooperatively inserted into the first through hole, and a second pin is cooperatively inserted into the second through hole, and the first pin and the second pin are installed on the stretching device.

[0038] In this solution, the diameters of the first pin and the first through hole, and the second pin and the second through hole are matched, so that the pin and the through hole are in surface contact as much as possible, thereby dispersing the load during the tensile test and avoiding failure at the pin or the through hole.

[0039] The positive and progressive effects of the present invention are: the manufacturing method of the blade test assembly of the present invention can test the bonding strength of only a part of the covering part by cutting the sample piece in the part with less curvature change in the blade and cutting the reinforcement, thereby reducing the requirement for applying load and being able to evaluate the bonding performance more simply and accurately. The blade test assembly obtained by the above manufacturing method can more conveniently perform a tensile test on the bonding performance and obtain a more accurate evaluation result. The above test method can more accurately evaluate the bonding performance of the leading edge of the blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 It is a schematic diagram of the structure of composite blades and metal reinforcements in the prior art.

[0041] Figure 2 The present invention is a flowchart of a method for manufacturing a blade test assembly according to an embodiment of the present invention.

[0042] Figure 3 The diagram is a schematic diagram showing the position of a blade sampling piece corresponding to a blade used in a method for manufacturing a blade test assembly according to an embodiment of the present invention.

[0043] Figure 4 It is a schematic structural diagram of a blade sampling piece used in a method for manufacturing a blade test assembly according to an embodiment of the present invention.

[0044] Figure 5 The figure is a cross-sectional schematic diagram of a blade test assembly according to an embodiment of the present invention.

[0045] Figure 6 It is a schematic structural diagram of a blade test assembly according to an embodiment of the present invention.

[0046] Figure 7 It is a schematic structural diagram of a blade test assembly during a tensile test according to an embodiment of the present invention.

[0047] Figure 8 The figure is a flow chart of a method for testing the bonding performance of a blade leading edge according to an embodiment of the present invention.

[0048] Description of Reference Numerals in the Background Art

[0049] Metal reinforcement 1′

[0050] Blade 2′

[0051] Description of Reference Numerals

[0052] Reinforcement 1

[0053] Nose cone 11

[0054] Covering part 12

[0055] Edge 13

[0056] Remaining part 14

[0057] Blade 2

[0058] Leaf sampling piece 3

[0059] First clamping member 4

[0060] Second clamping member 5

[0061] First neutral line 6

[0062] Second neutral line 7

[0063] Neutral axis 8

[0064] The first through hole 10

[0065] The second through hole 20

[0066] First pin 30

[0067] Second pin 40

[0068] First end surface 50

[0069] Second end surface 60 DETAILED DESCRIPTION

[0070] The present invention is further described below by way of examples, but the present invention is not limited to the scope of the examples.

[0071] This embodiment provides a blade test assembly and a manufacturing method thereof, such as Figure 2 As shown, the manufacturing method comprises:

[0072] Provide a blade sampling member 3, the blade sampling member 3 can be Figure 3The area defined by the box A, i.e., the leaf sampling member 3 corresponds to the area in the box A on the leaf, wherein Figure 4 As shown, the blade sampling member 3 includes a blade portion 2 and a reinforcement member 1, the blade portion 2 corresponds to a portion of the leading edge of the blade, the reinforcement member 1 is glued to the blade portion 2, and the reinforcement member 1 is coated on the leading edge of the blade portion 2, the reinforcement member 1 includes a nose cone portion 11 glued to the front of the leading edge of the blade portion 2, and a covering portion 12 glued to the pressure surface or suction surface of the blade portion 2, and the covering portion 12 is connected to the nose cone portion 11;

[0073] Cutting the covering portion 12 to separate the covering portion 12 into an edge portion 13 connected to the nose cone portion 11 and a residual portion 14 spaced apart from the edge portion 13;

[0074] A first through hole 10 is formed in the nose cone 11, avoiding the blade portion 2;

[0075] A second through hole 20 is formed in the blade portion 2 , avoiding the edge portion 13 . The present application does not limit the order in which the first through hole 10 and the second through hole 20 are formed.

[0076] The blade sample 3 obtained by this method is as follows Figure 5 and Figure 6 shown.

[0077] Since the blade is large in size and has complex structural features such as bends and sweeps, it is difficult to evaluate the bonding strength between the blade and the reinforcement 1. In this embodiment, by sampling a small part of the leading edge of the blade, the blade sampling piece 3 is close to a flat plate structure, so that the local bonding shear strength of the blade can be evaluated. By sampling different parts of the blade, the bonding strength of the leading edge of the entire blade can be evaluated.

[0078] Since the covering portion 12 of the reinforcement 1 is relatively long, if the bonding shear strength of the reinforcement 1 as a whole is measured, a relatively large load needs to be applied. It is even possible that during the load application, the blade portion 2 or the reinforcement 1 fails due to reaching the tensile yield strength before the bonding fails, and the bonding failure strength cannot be obtained. Therefore, by cutting the covering portion 12, only the bonding strength of a portion of the covering portion 12 (the edging portion 13) can be tested, and the bonding strength of the entire covering portion 12 can be evaluated based on the test result and the dimensional relationship.

[0079] The stretching device can use the first through hole 10 and the second through hole 20 to perform a stretching test on the blade test assembly, that is, the blade test assembly can be installed on the stretching device through the first through hole 10 and the second through hole 20. Since the first through hole 10 does not pass through the blade portion 2 and the second through hole 20 does not pass through the edge portion 13, when the edge portion 13 is separated from the blade portion 2, it means that the adhesive layer between the edge portion 13 and the blade portion 2 has shear failure, thereby ensuring the accuracy of the test results.

[0080] Specifically, the reinforcement member 1 may be made of a metal material, and the blade portion 2 may be made of a composite material.

[0081] In this embodiment, the first pin 30 can be inserted into the first through hole 10, and the second pin 40 can be inserted into the second through hole 20. The first pin 30 and the second pin 40 are fixed on the stretching device, and the blade part 2 is stretched by the first pin 30 and the second pin 40.

[0082] When providing the blade sampling member 3, the blade sampling member 3 should be as close to a flat plate structure as possible, that is, the sample should be taken at a position on the blade where the curvature change is small. Preferably, the curvature change of the suction surface and the pressure surface of the blade portion 2 does not exceed 20%. The requirement of curvature change can be met by selecting a smaller blade sampling member 3.

[0083] By making the structure of the blade test assembly close to a flat plate at the position where the curvature of the blade leading edge changes less, the adhesive failure is basically a failure under pure shear load. Preferably, the curvature change of the suction surface and the pressure surface of the blade part 2 does not exceed 10%.

[0084] When cutting the covering portion 12, the selected cutting position should make the chord length of the edge portion 13 5 to 15 mm. If the chord length of the edge portion 13 is too long, the adhesive layer between the edge portion 13 and the blade portion 2 is not easy to fail, and it is even possible that during the process of applying the load, before the adhesive fails, the blade portion 2 or the reinforcement 1 fails due to reaching the tensile yield strength, resulting in the inability to obtain the adhesive failure strength; if the chord length of the edge portion 13 is too short, it is difficult to accurately evaluate the adhesive strength, and it is possible that the adhesive layer is unevenly distributed, resulting in adhesive failure under a smaller load.

[0085] Avoiding the blade portion 2, after the first through hole 10 is opened in the nose cone portion 11, the following steps are included:

[0086] A first clamping member 4 is fixedly connected to both sides of the nose cone 11, and the first clamping member 4 is provided with a third through hole ( Figure 7 not shown).

[0087] If the stretching device acts directly on the first through hole 10, due to the thin thickness and low strength of the nose cone 11, in the process of increasing the tensile load, plastic deformation may occur at the first through hole 10 before the adhesive failure, resulting in no adhesive failure and no ability to measure the adhesive strength. Figure 7As shown, the third through hole can be used to share the tensile load, thereby improving the bearing capacity of the blade test assembly, wherein the first clamping member 4 can be fixed to the nose cone 11 by bolts or adhesive bonding. Preferably, the first through hole 10 and the third through hole have the same diameter, so when the first pin 30 is inserted into the first through hole 10 and the third through hole, the inner walls of the first through hole 10 and the third through hole are in contact with the outer wall of the first pin 30, thereby dispersing the pressure and improving the bearing capacity of the first pin 30.

[0088] Similarly, avoiding the edge portion 13, after the second through hole 20 is formed in the blade portion 2, the following steps are included:

[0089] A second clamping member 5 is fixedly connected to both sides of the blade portion 2. The second clamping member 5 is provided with a fourth through hole ( Figure 7 not shown).

[0090] If the tensile device acts directly on the second through hole 20 through the second pin 40, due to the thin thickness and low strength of the blade part 2, in the process of increasing the tensile load, it is possible that plastic deformation occurs at the second through hole 20 before the adhesive failure, resulting in no adhesive failure and no ability to measure the adhesive strength. By providing the second clamp 5, the tensile load can be shared by the fourth through hole, thereby improving the bearing capacity of the blade test assembly, wherein the second clamp 5 can be fixed to the blade part 2 by bolts or adhesive. Preferably, the second through hole 20 and the fourth through hole have the same diameter, so when the second pin 40 is inserted into the second through hole 20 and the fourth through hole, the inner walls of the second through hole 20 and the fourth through hole are in contact with the outer wall of the first pin 30, thereby dispersing the pressure and improving the bearing capacity of the second pin 40. Specifically, a plurality of second through holes 20 can be provided to share the tensile load and improve the bearing capacity of the blade part 2. In this embodiment, two second through holes 20 are provided.

[0091] like Figure 6 As shown, the two end faces of the blade test assembly in the blade axial direction are respectively a first end face 50 and a second end face 60, and the two end faces are symmetrical about a symmetry plane (wherein the symmetry plane is not shown in the figure), as shown in FIG. Figure 7 As shown, the line between the ends of the two edging portions 13 away from the nose cone portion 11 and the intersection of the symmetry plane is the first neutral line 6, the intersection of the symmetry plane and the leading edge of the blade portion 2 is the second neutral line 7, the line between the midpoint of the first neutral line 6 and the midpoint of the second neutral line 7 constitutes the neutral axis 8, the axial line of the first through hole 10 intersects with the neutral axis 8, and the axial line of the first through hole is perpendicular to the neutral line.

[0092] The pressure surface and the suction surface of the blade portion 2 are approximately planes, and the neutral axis 8 is substantially parallel to the pressure surface and the suction surface. During the tensile test, the pin is inserted into the first through hole 10 and stretched with the help of the pin. Since the first through hole 10 is perpendicular to the neutral axis 8, during the tensile test, the loading direction ( Figure 7 The direction of the tensile load (the direction of the arrow in the middle) is basically along the direction of the neutral axis 8, and no eccentric loading occurs, that is, the direction of the tensile load should coincide with the neutral axis 8. In this way, the performance obtained by measurement is closest to the pure shear performance of the bond.

[0093] In addition, the stress state of the bonding area in the blade test assembly can be adjusted by performing eccentric loading (i.e., changing the position of the first through hole 10) or oblique loading (i.e., changing the angle between the loading direction and the neutral axis 8), and the strength characteristics of the bonding area under different peel stress to shear stress ratios can be measured.

[0094] The blade sampling part 3 provided in the foregoing text includes:

[0095] Providing a complete blade, with a complete reinforcement 1 glued to the leading edge of the blade;

[0096] The complete leaf is cut to obtain leaf sample 3.

[0097] The blade sample 3 is obtained by cutting a complete blade and a complete reinforcement member 1, that is, cutting a real blade. Such a blade sample 3 is closer to the real performance, so the result of the subsequent tensile test is closer to the real performance.

[0098] In some preferred embodiments, providing the leaf sampling member 3 comprises:

[0099] A blade portion 2 having a partial leading edge of the blade is obtained by processing, and a corresponding reinforcement member 1 is glued to the leading edge of the blade portion 2 to obtain a blade sampling member 3.

[0100] In this way, the blade sampling part 3 is directly obtained by manufacturing a part of the real blade, which can reduce the cost of the blade sampling part 3 and shorten the test cycle.

[0101] As mentioned above, the blade test assembly of this embodiment includes a blade portion 2 and a reinforcement 1, wherein the blade portion 2 corresponds to a portion of the leading edge of the blade, the reinforcement 1 is glued to the blade portion 2, and the reinforcement 1 is wrapped around the leading edge of the blade portion 2, the reinforcement 1 includes a nose cone portion 11 glued to the front of the leading edge of the blade portion 2, and a wrapping portion 12 glued to the pressure surface or suction surface of the blade portion 2, the wrapping portion 12 includes a rim portion 13 connected to the nose cone portion 11, and a residual portion 14 spaced from the rim portion 13, the nose cone portion 11 is provided with a first through hole 10, and the blade portion 2 is provided with a second through hole 20. Among them, the first through hole 10 does not pass through the blade portion 2, and the rim portion 13 does not overlap with the opening of the second through hole 20.

[0102] The blade test assembly obtained by the above manufacturing method can relatively accurately measure the bonding performance of the blade leading edge reinforcement ribs, can be used to evaluate the strength performance of the bonding on the actual blade structure, and can also be used to evaluate the stability of the blade bonding performance.

[0103] like Figure 8 As shown, this embodiment also provides a method for testing the bonding performance of the leading edge of a blade, the testing method comprising:

[0104] Providing a blade test assembly as before;

[0105] The blade test assembly is stretched by using the first through hole 10 and the second through hole 20 until the bonding between the edge portion 13 and the blade portion 2 fails, thereby obtaining the strength performance of the bonding.

[0106] The blade test kit as above is then provided to include:

[0107] The first pin 30 is inserted into the first through hole 10 in a matching manner, and the second pin 40 is inserted into the second through hole 20 in a matching manner, and the first pin 30 and the second pin 40 are installed on the stretching device.

[0108] The diameters of the first pin 30 and the first through hole 10, and the second pin 40 and the second through hole 20 are adapted to each other, so that the pin and the through hole are in surface contact as much as possible, thereby dispersing the load during the tensile test and avoiding failure at the pin or the through hole.

[0109] Although the specific embodiments of the present invention are described above, it should be understood by those skilled in the art that this is only for illustration and the protection scope of the present invention is defined by the appended claims. Those skilled in the art may make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. A method for manufacturing a blade test assembly, It is characterized in that The method comprises: A blade sampling piece is provided, wherein the blade sampling piece comprises a blade portion and a reinforcement piece, the blade portion corresponds to a portion of a leading edge of the blade, the reinforcement piece is glued to the blade portion, and the reinforcement piece is coated on the leading edge of the blade portion, the reinforcement piece comprises a nose cone portion glued to the front of the leading edge of the blade portion, and a coating portion glued to the pressure surface or the suction surface of the blade portion, and the coating portion is connected to the nose cone portion; Cutting the covering portion to separate the covering portion into an edge portion connected to the nose cone portion and a residual portion spaced apart from the edge portion; A first through hole is formed in the nose cone portion, avoiding the blade portion; A second through hole is formed in the blade portion, avoiding the edge portion.

2. A method for manufacturing a blade test assembly according to claim 1, It is characterized in that The blade sampling member provided comprises: Providing a complete blade having a complete reinforcement bonded to the leading edge of the blade; The complete leaf is cut to obtain the leaf sampling piece.

3. The method for manufacturing the blade test assembly according to claim 1, It is characterized in that The blade sampling member provided comprises: A blade portion having a partial leading edge of the blade is obtained by machining, and a corresponding reinforcement member is glued to the leading edge of the blade portion to obtain the blade sampling member.

4. A blade test assembly, It is characterized in that The blade test assembly includes a blade portion and a reinforcement, the blade portion corresponds to a portion of the leading edge of the blade, the reinforcement is glued to the blade portion, and the reinforcement is wrapped around the leading edge of the blade portion, the reinforcement includes a nose cone portion glued to the front of the leading edge of the blade portion, and a wrapping portion glued to the pressure surface or the suction surface of the blade portion, the wrapping portion includes an edging portion connected to the nose cone portion, and a residual portion spaced apart from the edging portion, the nose cone portion is provided with a first through hole, and the blade portion is provided with a second through hole, wherein the first through hole does not pass through the blade portion, and the edging portion does not overlap with the opening of the second through hole.

5. The blade test assembly according to claim 4, It is characterized in that The curvature changes of the suction surface and the pressure surface of the blade portion do not exceed 20%.

6. The blade test assembly according to claim 4, It is characterized in that The chord length of the hemming portion is 5 to 15 mm.

7. The blade test assembly according to claim 4, It is characterized in that A first clamping member is fixedly connected to both sides of the nose cone, and the first clamping member is provided with a third through hole corresponding to the position of the first through hole.

8. The blade test assembly according to claim 4, It is characterized in that A second clamping member is fixedly connected to both sides of the blade portion, and the second clamping member is provided with a fourth through hole corresponding to the position of the second through hole.

9. The blade test assembly according to claim 4, It is characterized in that The two end faces of the blade test assembly located in the axial direction of the blade are symmetrical about a symmetry plane, the line between the intersection points of the two ends of the edging parts away from the nose cone part and the symmetry plane is the first neutral line, the intersection line of the symmetry plane and the leading edge of the blade part is the second neutral line, the line between the midpoint of the first neutral line and the midpoint of the second neutral line constitutes a neutral axis, the axial line of the first through hole intersects with the neutral axis, and the axial line of the first through hole is perpendicular to the neutral line.

10. A method for testing the bonding performance of the leading edge of a blade. It is characterized in that The method comprises: Providing a blade test assembly as described in any one of claims 4 to 9; The blade test assembly is stretched by using the first through hole and the second through hole until the bonding between the hemming portion and the blade portion fails, thereby obtaining the strength performance of the bonding.

11. The method for testing the bonding performance of the leading edge of a blade according to claim 10, It is characterized in that The method of stretching the blade test assembly by using the first through hole and the second through hole comprises: A first pin is cooperatively inserted into the first through hole, and a second pin is cooperatively inserted into the second through hole, and the first pin and the second pin are installed on the stretching device.

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