Target missile and impact test device for simulating fan blades

Abstract

The present invention relates to a target missile for simulating a fan blade, which comprises: a first plate member made of a composite material, the first plate member being configured in a curved shape and configured to simulate a fan blade made of a composite material; and a second plate member made of a metal material, a first end of the second plate member being connected to a first end of the first plate member, a second end of the second plate member extending to a second end of the first plate member, the second plate member being configured to simulate a metal reinforcing edge of the fan blade. The present invention can be used to simulate a composite material fan blade with a metal reinforcing edge, and to simulate the impact load characteristics of a composite material fan blade with a metal reinforcing edge, alleviating the problem that the design and test of traditional metal target missiles cannot truly characterize the working condition characteristics of a composite material fan blade when subjected to an impact load.

Description

Technical Field

[0001] The present invention relates to the field of aerospace equipment, and particularly to a target missile for simulating a fan blade and an impact test device. Background Art

[0002] During long-term service, the fan blades in an aero turbofan engine may experience fatigue failure or break due to foreign object impact, which will impose a sudden impact load on the surrounding containment casing. To ensure the safety of the airframe, the containment casing needs to be free from penetrative damage during the impact of the blades. At the same time, the damage and fracture of individual blades will cause a dynamically dangerous unbalanced load on the high-speed rotating fan system. The design of the engine bearings and fusing mechanisms needs to have a sufficient understanding of the characteristics of such impact loads and dynamic unbalanced loads for effective design.

[0003] In the related art, a titanium alloy target missile is used for impact tests in the containment casing. Since the damage failure mode of the titanium alloy target missile is very different from that of the fan blade, the impact load spectrum it causes does not represent the characteristics of the fan blade. Summary of the Invention

[0004] Some embodiments of the present invention provide a target missile for simulating a fan blade and an impact test device to alleviate the problem of inaccurate simulation results.

[0005] Some embodiments of the present invention provide a target missile for simulating a fan blade, which includes:

[0006] A first plate member made of a composite material, the first plate member is configured to be curved, and the first plate member is configured to simulate a fan blade made of a composite material; and

[0007] A second plate member made of a metal material, a first end of the second plate member is connected to a first end of the first plate member, a second end of the second plate member extends to a second end of the first plate member, and the second plate member is configured to simulate a metal reinforcing edge of the fan blade.

[0008] In some embodiments, the cross-section of the component formed by the combination of the first plate member and the second plate member is annular.

[0009] In some embodiments, the annular shape includes a square annular shape or a semi-circular annular shape.

[0010] In some embodiments, the first end of the second plate member is configured as a flange, and the first end of the first plate member is inserted between the upper flange and the lower flange of the first end of the second plate member.

[0011] In some embodiments, a third plate member is further included. The third plate member is made of a composite material and is configured to be bent. The first plate member and the third plate member are stacked vertically. The first end of the first plate member is in contact with the first end of the third plate member, and the second end of the first plate member is aligned with the second end of the third plate member. The first end of the second plate member connects the first end of the first plate member and the first end of the third plate member, and the second end of the second plate member extends between the second end of the first plate member and the second end of the third plate member.

[0012] In some embodiments, the first plate member and the third plate member are symmetrically arranged.

[0013] In some embodiments, the cross-section of the component formed by combining the first plate member and the second plate member is annular, and / or the cross-section of the component formed by combining the third plate member and the second plate member is annular.

[0014] In some embodiments, the annulus includes a square annulus or a semi-circular annulus.

[0015] In some embodiments, the first end of the second plate member is configured as a flange, and the first end of the first plate member and the first end of the third plate member are inserted side by side between the upper flange and the lower flange of the first end of the second plate member.

[0016] Some embodiments of the present invention provide an impact test device, which includes a target plate for simulating a containment casing and the above-mentioned target projectile for simulating a fan blade. The target plate is made of a composite material.

[0017] Based on the above technical solutions, the present invention has at least the following beneficial effects:

[0018] In some embodiments, the target projectile for simulating a fan blade includes a first plate member and a second plate member. The first plate member is made of a composite material, and the second plate member is made of a metal material. It can be used to simulate a composite fan blade with a metal reinforcement edge and the impact load characteristics of a composite fan blade with a metal reinforcement edge, alleviating the problem that the design and test of traditional metal target projectiles cannot truly characterize the working condition characteristics of composite fan blades when subjected to impact loads. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0020] Figure 1 Schematic diagram of a target projectile for simulating a fan blade according to the first embodiment of the present invention;

[0021] Figure 2 Schematic diagram of a target missile for simulating a fan blade according to the second embodiment of the present invention;

[0022] Figure 3 Schematic diagram of a target missile for simulating a fan blade according to the third embodiment of the present invention;

[0023] Figure 4 Schematic diagram of a target missile for simulating a fan blade according to the fourth embodiment of the present invention. Detailed implementation manners

[0024] Next, the technical solutions in the embodiments will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0025] In the description of the present invention, it should be understood that the orientation or positional relationships indicated by the terms "center", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are based on the orientation or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the protection scope of the present invention.

[0026] When the fan blade in an aero turbofan engine fails due to fatigue during long-term service or breaks after being impacted by foreign objects, it will generate a sudden impact load on the surrounding containment casing. To ensure the safety of the airframe, the containment casing needs to be free from penetrative damage during the impact of the blade.

[0027] In the related art, a titanium alloy target missile is used to conduct impact tests on a target plate to simulate the impact of a fan blade on the containment casing. Since the damage failure mode of the titanium alloy target missile is very different from that of the fan blade, the impact load spectrum it generates does not represent the characteristics of the fan blade.

[0028] Based on this, the present disclosure provides a target missile for simulating a fan blade to alleviate the problem of inaccurate simulation test results.

[0029] As Figures 1 to 4 shown, some embodiments provide a target missile for simulating a fan blade, which includes a first plate member 1 and a second plate member 2.

[0030] The first plate member 1 is made of a composite material and is configured to be curved. The first plate member 1 is configured to simulate a fan blade made of a composite material.

[0031] The second plate member 2 is made of a metallic material. The first end of the second plate member 2 is connected to the first end of the first plate member 1, and the second end of the second plate member 2 extends to the second end of the first plate member 1. The second plate member 2 is configured to simulate the metallic reinforcing edge of a fan blade.

[0032] Optionally, the connection between the first end of the second plate member 2 and the first end of the first plate member 1 is a glued connection.

[0033] Since the damage failure mode of a composite fan blade with a metallic reinforcing edge impacting the casing is a complex combined effect, first, the leading-edge titanium alloy hollow blade produces "plowing" damage on the composite casing, then the connection interface between the titanium alloy edging and the composite blade body is damaged and separated, and finally, the composite blade body produces an impact load of end crushing on the casing with "plowing" damage.

[0034] The target projectile for simulating a fan blade provided by an embodiment of the present disclosure includes a first plate member 1 and a second plate member 2. The first plate member 1 is made of a composite material, and the second plate member 2 is made of a metallic material. It can be used to simulate a composite fan blade with a metallic reinforcing edge and the impact load characteristics of a composite fan blade with a metallic reinforcing edge, alleviating the problem that the design and test of traditional metallic target projectiles cannot truly characterize the working condition characteristics of a composite fan blade when subjected to an impact load. At the same time, the target projectile provided by the embodiment of the present disclosure can be launched by a conventional-caliber air gun, can accurately control the attitude and speed, and can more cost-effectively and efficiently study the impact load spectrum and damage failure process of the containment casing under the impact load characteristics of a composite fan blade, or screen different casing design schemes.

[0035] The first plate member 1 provided by the embodiment of the present disclosure is used to simulate a fan blade made of a composite material, and the second plate member 2 is used to simulate the metallic reinforcing edge of the fan blade. The first plate member 1 is configured to be curved, that is, the target projectile simulates the structural and material characteristics of the composite fan blade body through a curved composite material plate, and simulates the mass and material characteristics of the metallic reinforcing edge of the composite fan blade by gluing a metallic reinforcing edge to the edge of the composite material plate, economically and effectively realizing the load characteristics equivalent to those of a composite fan blade for the impact containment casing.

[0036] In some embodiments, the first plate member 1 is curved into an annular shape with an opening. The opening is formed between the first end and the second end of the first plate member 1. The cross-section of the component formed by the combination of the first plate member 1 and the second plate member 2 is annular, and there is still a preset gap between the second end of the first plate member 1 and the second end of the second plate member 2.

[0037] The first plate member 1 is configured to be bent, and the first end and the second end of the first plate member 1 are not fully butted. The first end of the second plate member 2 is connected to the first end of the first plate member 1, and the second end of the second plate member 2 extends to the second end of the first plate member 1, forming an annular structure with an opening. It can achieve geometric scales and mass characteristics equivalent to those of wide-chord blades with a smaller diameter and can be launched by an air cannon with a conventional aperture. This not only greatly reduces the test cost of the casing containing the impact of composite fan blades but also can more accurately control the attitude and speed of the impact body. Conducting impact tests in a stationary state on the ground can more accurately monitor the impact load spectrum and the impact damage and failure process of the casing, providing rich information feedback for simulation analysis.

[0038] In some embodiments, as Figure 1 shown, the cross-section of the component formed by combining the first plate member 1 and the second plate member 2 is annular, and the annulus includes a square annulus. That is to say, the first plate member 1 is configured to be bent, and the first end and the second end of the first plate member 1 are not fully butted in a square frame structure. The second plate member 2 is connected to the first end of the first plate member 1 and extends towards the second end of the first plate member 1, and there is still a small gap opening in the square frame structure.

[0039] In some embodiments, as Figure 2 shown, the cross-section of the component formed by combining the first plate member 1 and the second plate member 2 is annular, and the annulus includes a semi-circular annulus. That is to say, the first plate member 1 is configured to be bent, and the first end and the second end of the first plate member 1 are not fully butted in a semi-circular frame structure. The second plate member 2 is connected to the first end of the first plate member 1 and extends towards the second end of the first plate member 1, and there is still a small gap opening in the semi-circular frame structure.

[0040] In some embodiments, the first end of the second plate member 2 is configured as a flange, and the flange includes an upper flange and a lower flange. The first end of the first plate member 1 is inserted between the upper flange and the lower flange of the first end of the second plate member 2.

[0041] In some embodiments, as Figure 3 and Figure 4 shown, the target missile for simulating a fan blade further includes a third plate member 3. The third plate member 3 is made of a composite material and is configured to be bent. The first plate member 1 and the third plate member 3 are stacked up and down. The first end of the first plate member 1 is in contact with the first end of the third plate member 3, and the second end of the first plate member 1 is aligned with the second end of the third plate member 3. There is a gap between the second end of the first plate member 1 and the second end of the third plate member 3. The first end of the second plate member 2 is connected to the first end of the first plate member 1 and the first end of the third plate member 3, and the second end of the second plate member 2 extends to a position close to between the second end of the first plate member 1 and the second end of the third plate member 3.

[0042] In some embodiments, the first plate member 1 and the third plate member 3 are symmetrically arranged.

[0043] In some embodiments, the cross-section of the component formed by combining the first plate member 1 and the second plate member 2 is annular.

[0044] In some embodiments, the cross-section of the component formed by combining the third plate member 3 and the second plate member 2 is annular.

[0045] In some embodiments, the cross-section of the component formed by combining the first plate member 1 and the second plate member 2 is annular; and the cross-section of the component formed by combining the third plate member 3 and the second plate member 2 is annular.

[0046] In some embodiments, the above-mentioned annulus includes a square annulus or a semi-circular annulus.

[0047] The cross-section of the component formed by combining the first plate member 1 and the second plate member 2 is semi-circular; and the cross-section of the component formed by combining the third plate member 3 and the second plate member 2 is semi-circular, and the cross-section of the component formed by stacking the first plate member 1 and the third plate member 3 up and down is circular.

[0048] In some embodiments, the first end of the second plate member 2 is configured as a flange, the flange includes an upper flange and a lower flange, and the first ends of the first plate member 1 and the third plate member 3 are inserted side by side between the upper flange and the lower flange of the first end of the second plate member 2.

[0049] In some embodiments, the composite material includes a laminated composite material or a woven composite material.

[0050] The target missile provided by the embodiments of the present disclosure includes a composite material target missile with an external metal reinforcing edge and an internal composite material target missile.

[0051] As Figure 1 and Figure 2 shown, it is a composite material target missile with an external metal reinforcing edge.

[0052] As Figure 1 shown, the first plate member 1 is made of a composite material and manufactured into a bent plate to form a square frame structure with an opening.

[0053] The second plate member 1 is made of a metal material. The first end of the second plate member 1 is configured as a flange. The first end of the first plate member 1 is inserted between the upper flange and the lower flange of the first end of the second plate member 2 as a metal reinforcing edge with a flange. The second end of the second plate member 1 is machined into a 1 / 4 arc-shaped cut angle whose outer contour is tangent to the lower surface of the second plate member 1 and perpendicularly intersects the upper surface of the second plate member 1 to simulate the pressure surface and suction surface transition region of the metal reinforcing edge of the composite material fan blade.

[0054] The corners of the first plate member 1 are provided with a preset radius to avoid wrinkles. After the upper flange and the lower flange of the second plate member 1 are inserted into the first end of the first plate member 1, there is a gap with a thickness of two layers of adhesive film for the adhesive bonding process.

[0055] After the inner side of the flange of the second plate member 1 is surface anodized, it is adhesively bonded to the first end of the first plate member 1 with an adhesive film. The adhesive film and the adhesive bonding process parameters are the same as those used for the adhesive bonding of the metal reinforcement edge of the composite fan blade, so as to ensure that the failure and shedding load characteristics of the adhesive film at the reinforcement edge during the impact of the target missile made of the composite material disclosed in this application are similar to those of the composite fan blade.

[0056] As Figure 2 shown, the first plate member 1 is manufactured into a curved plate to form a semi-circular structure with an opening. The second plate member 1 serves as a metal reinforcement edge, and the manufacturing and adhesive bonding processes are the same as those of the embodiment shown in Figure 1 shown.

[0057] As Figure 3 and Figure 4 shown, it is a composite material target missile with the metal reinforcement edge centered.

[0058] As Figure 3 shown, the first plate member 1 and the third plate member 3 are made of composite materials and are manufactured into curved plates to form a square structure with an opening. The width of the square structure is twice the height. Due to the effect of the opening, for the square structure with an opening, the width of one side is greater than the width of the opposite side of this side. The first plate member 1 and the third plate member 3 are stacked up and down, and the shorter sides in the width direction of the first plate member 1 and the third plate member 3 are mutually attached. The formed thickness is twice the thickness of the wider side. After the shorter sides in the width direction of the first plate member 1 and the third plate member 3 are attached, they are inserted between the upper flange and the lower flange of the second plate member 2, and there is still a gap with a thickness of three layers of adhesive film between the upper flange and the lower flange for the adhesive bonding of the first plate member 1, the third plate member 3 and the second plate member 2.

[0059] The open square structures made of the first plate member 1 and the third plate member 3 are stacked and symmetrically arranged, and the shorter sides in the width direction of the first plate member 1 and the third plate member 3 are mutually attached and symmetrically adhesively bonded. Before adhesive bonding, the adhesive bonding surfaces are roughened by grinding with a diamond sand gun.

[0060] After the inner side of the flange of the second plate member 2 is surface anodized, it is adhesively bonded to the first ends of the first plate member 1 and the third plate member 3 with an adhesive film. The adhesive film and the adhesive bonding process parameters are the same as those used for the adhesive bonding of the metal reinforcement edge of the composite fan blade, so as to ensure that the failure and shedding load characteristics of the adhesive film at the reinforcement edge during the impact of the composite material target missile provided in the embodiment of this disclosure are similar to those of the composite fan blade.

[0061] AsFigure 4 As shown, the first plate member 1 and the third plate member 3 can also be made into a semi-circular outer shape structure with an open side having a chordal flat plate. The manufacturing and bonding process of the second plate member 2 is the same as that in Step 2. The composite target projectile after bonding and forming has an approximate cylindrical outer shape with an opening, and can have a better aerodynamic outer shape for attitude control.

[0062] In some embodiments, the first plate member 1 and / or the third plate member 3 adopt a variable thickness structure with a thicker center and thinner sides similar to that of an actual composite material blade. The second plate member 2 adopts a design that gradually thickens from the arc cutting edge to the flange.

[0063] Some embodiments provide an impact test device, which includes a target plate for simulating a containment casing and the above-mentioned target projectile for simulating a fan blade, wherein the target plate is made of a composite material.

[0064] The composite material fan blade adopts a design scheme of laying and weaving composite materials with a metal reinforcing edge on the outside. Due to the fragmentation characteristics of the composite material blade breaking and impacting the casing, the containment casing can also adopt a lighter composite material structure.

[0065] The impact test device is used to simulate the load characteristics of a composite material fan blade with a metal reinforcing edge flying off and impacting the containment casing in an aeroengine, and is used for the inclusive impact test research, performance screening and assessment of the containment casing or its typical characteristic components.

[0066] The impact test device can economically and effectively simulate the load characteristics of a composite material fan blade with a metal reinforcing edge impacting the containment casing. The target projectile for simulating the fan blade can be launched by a conventional caliber air gun, and the manufacturing and test costs are less than 1 / 50 of the rotary impact test method used in the composite material fan blade fly-off containment test. The attitude and speed of the target projectile impacting the containment casing can be controlled with higher precision than the rotary impact test, and can achieve a more accurate damage failure process and deformation detection during the casing impact test, providing richer calibration information for simulation analysis.

[0067] Based on the above embodiments of the present invention, without explicit negation, the technical features of one embodiment can be beneficially combined with one or more other embodiments.

[0068] In the description of the present invention, it should be understood that using words such as "first", "second", "third", etc. to limit the components is only for the convenience of differentiating the above components. Without additional declaration, the above words have no special meaning, so it cannot be understood as a limitation on the protection scope of the present invention.

[0069] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit them; although the present invention has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that it is still possible to modify the specific implementation manners of the present invention or perform equivalent replacements for some technical features; without departing from the spirit of the technical solutions of the present invention, they should all be covered within the scope of the technical solutions claimed by the present invention.

Claims

1. A target missile for simulating a fan blade, characterized in that, Comprising: A first plate member (1), made of a composite material, the first plate member (1) being configured to be curved, and the first plate member (1) being configured to simulate a fan blade made of a composite material; And A second plate member (2), made of a metallic material, a first end of the second plate member (2) being connected to a first end of the first plate member (1), a second end of the second plate member (2) extending to a second end of the first plate member (1), and the second plate member (2) being configured to simulate a metallic reinforcing edge of the fan blade.

2. The target missile for simulating a fan blade according to claim 1, characterized in that, A cross-section of the component formed by combining the first plate member (1) and the second plate member (2) is annular.

3. The target missile for simulating a fan blade according to claim 2, wherein The annulus includes a square annulus or a semi-circular annulus.

4. The target missile for simulating a fan blade according to claim 1, wherein The first end of the second plate member (2) is configured as a flange, and the first end of the first plate member (1) is inserted between an upper flange and a lower flange of the first end of the second plate member (2).

5. The target missile for simulating a fan blade according to claim 1, characterized in that, It further includes a third plate member (3), the third plate member (3) being made of a composite material, the third plate member (3) being configured to be curved, the first plate member (1) and the third plate member (3) being stacked up and down, a first end of the first plate member (1) being in contact with a first end of the third plate member (3), a second end of the first plate member (1) being aligned with a second end of the third plate member (3), a first end of the second plate member (2) being connected to the first end of the first plate member (1) and the first end of the third plate member (3), and a second end of the second plate member (2) extending between the second end of the first plate member (1) and the second end of the third plate member (3).

6. The target missile for simulating a fan blade according to claim 5, characterized in that, The first plate member (1) and the third plate member (3) are symmetrically arranged.

7. The target missile for simulating a fan blade according to claim 5, wherein A cross-section of the component formed by combining the first plate member (1) and the second plate member (2) is annular, and / or a cross-section of the component formed by combining the third plate member (3) and the second plate member (2) is annular.

8. The target missile for simulating a fan blade according to claim 7, wherein The annulus includes a square annulus or a semi-circular annulus.

9. The target missile for simulating a fan blade according to claim 5, characterized in that, The first end of the second plate member (2) is configured as a flange, and the first ends of the first plate member (1) and the third plate member (3) are inserted side by side between an upper flange and a lower flange of the first end of the second plate member (2).

10. An impact test device, characterized in that, It includes a target plate for simulating a containment casing and a target projectile for simulating a fan blade according to any one of claims 1 to 9, the target plate being made of a composite material.

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