An aeroengine guide vane and its manufacturing method

Abstract

The present invention discloses an airfoil for an aeroengine and a manufacturing method thereof, including an airfoil main body; the airfoil main body includes a first curved surface, a second curved surface and a bending portion; one side of the first curved surface and the second curved surface is connected through the bending portion, and the other side of the first curved surface and the second curved surface is directly connected, and a through-flow channel is formed among the first curved surface, the second curved surface and the bending portion. In order to reduce the processing cost and processing difficulty of the airfoil, the present invention designs an effective structure.

Description

Technical Field

[0001] The present invention belongs to the field of aviation industry manufacturing, and relates to an aviation engine guide vane and a manufacturing method thereof. Background Art

[0002] The structural forms of aviation engine fan guide vanes are diverse. Due to the characteristics of the fluid such as easy fluidity, curved guide vanes are generally selected to efficiently regulate the air flow. However, curved guide vanes have problems such as difficult machining and difficult shape assurance. Summary of the Invention

[0003] The main purpose of the present invention is to provide an aviation engine guide vane and a manufacturing method thereof. In order to reduce the processing cost and difficulty of the guide vane, the present invention designs an effective integral structure.

[0004] To achieve the above object, the technical solution adopted by the present invention is as follows:

[0005] An aviation engine guide vane includes a guide vane body; the guide vane body includes a first curved surface, a second curved surface and a bending part;

[0006] One side of the first curved surface and the second curved surface is connected by the bending part, and the other side of the first curved surface and the second curved surface is directly connected. A through-flow guide channel is formed among the first curved surface, the second curved surface and the bending part.

[0007] As a further improvement of the present invention, one end surface of the first curved surface is bent outward to form a first flanging, and one end surface of the second curved surface is bent outward to form a second flanging. The first flanging and the second flanging are arranged at the same end.

[0008] As a further improvement of the present invention, waveform ribs are formed at the direct connection parts of the first curved surface and the second curved surface.

[0009] As a further improvement of the present invention, the waveform ribs of the first curved surface and the second curved surface are fixed by spot welding.

[0010] As a further improvement of the present invention, the bending part is a plane.

[0011] As a further improvement of the present invention, the radius of curvature of the first curved surface is smaller than that of the second curved surface.

[0012] As a further improvement of the present invention, the end section length of the first curved surface = the end section length of the second curved surface + the section length of the bending part.

[0013] As a further improvement of the present invention, the guide vane body is formed by bending and welding a whole metal plate.

[0014] As a further improvement of the present invention, the cross-sectional area of the diversion channel tapers from one end to the other end.

[0015] A manufacturing method of an aero-engine guide vane includes the following steps:

[0016] Select a whole metal plate and cut it into a blank;

[0017] Pre-press and form a curved surface shape along the symmetry line by relying on a mold, and process the flanging;

[0018] Stamping and forming a complete curved surface according to the tooling to form a diversion channel;

[0019] Stamping into a corrugated edge on the edge with a corrugated edge forming mold;

[0020] Welding and forming the corrugated edge on the edge by spot welding to obtain the aero-engine guide vane.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] The present invention realizes the manufacturing of the guide vane by using sheet metal and welding processes instead of traditional machining processes, thereby designing a corresponding integrated structure. Specifically, the guide vane body is composed of a first curved surface, a second curved surface and a bending part, and a diversion channel is formed in the middle; it is formed by integral sheet metal bending and welding, and this structure significantly reduces the processing cost of the guide vane. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained according to these drawings.

[0024] Figure 1 Schematic diagram of an aero-engine guide vane;

[0025] Figure 2 Top view sectional view of the guide vane;

[0026] Figure 3 Blank cutting and unfolding diagram;

[0027] Figure 4 Pre-press forming diagram;

[0028] Figure 5 For Figure 4 Schematic diagram of being disconnected along the A-A direction in

[0029] Figure 6 Stamping forming diagram;

[0030] Figure 7 Forming diagram of the outer corrugation

[0031] Figure 8 Side view of the outer corrugation;

[0032] Figure 9 Forming diagram of spot welding.

[0033] Among them, 100 is a metal plate, 1 is the first flanging, 2 is the first curved surface, 3 is the second flanging, 4 is the second curved surface, 5 is the corrugated edge, 6 is the bending part, and 7 is the diversion channel. Specific implementation manners

[0034] In order to make the objectives and technical solutions of the present invention clearer and easier to understand, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. The specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0035] In the description of the present invention, it should be understood that the orientation or positional relationships indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "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 therefore should not be construed as limiting the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, the meaning of "plurality" is two or more. In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "mounted", "connected" and "connected" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected, or indirectly connected through an intermediate medium, and it may be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0036] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings and specific embodiments. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the scope of the present invention.

[0037] In order to make the technical means, creative features, achieved purposes and effects of the present invention easily understood, the present invention will be further described below in conjunction with specific embodiments.

[0038] As Figures 1 to 2 shown, an airfoil for an aeroengine, characterized in that it includes an airfoil body; the airfoil body includes a first curved surface 2, a second curved surface 4 and a bending portion 6;

[0039] One side of the first curved surface 2 and the second curved surface 4 is connected by the bending portion 6, and the other side of the first curved surface 2 and the second curved surface 4 is directly connected. A through-flow channel 7 is formed among the first curved surface 2, the second curved surface 4 and the bending portion 6. The airfoil body is formed by bending and welding a whole metal plate 100.

[0040] Furthermore, one end surface of the first curved surface 2 is bent outward to form a first flange 1, and one end surface of the second curved surface 4 is bent outward to form a second flange 3. The first flange 1 and the second flange 3 are arranged at the same end.

[0041] The cross-sectional area of the flow channel 7 gradually decreases from one end to the other end. And it gradually decreases from the end with flanges to the end without flanges.

[0042] For the requirements of firm fixation and strength at the connection, corrugated ribs 5 are formed at the direct connection of the first curved surface 2 and the second curved surface 4. The corrugated ribs of the first curved surface 2 and the second curved surface 4 are fixed by spot welding.

[0043] Among them, the bending portion 6 is a plane. The radius of curvature of the first curved surface 2 is smaller than the radius of curvature of the second curved surface 4. The end cross-sectional length of the first curved surface 2 = the end cross-sectional length of the second curved surface 4 + the cross-sectional length of the bending portion 6.

[0044] As Figures 3 to 9 shown, the manufacturing method of the above-mentioned airfoil for an aeroengine includes the following steps:

[0045] Select a whole metal plate 100 and cut it into a blank;

[0046] Pre-press along the symmetry line against the mold to form a curved surface shape and process the flanges;

[0047] According to the tooling, press and form a complete curved surface and form the flow channel 7;

[0048] At the edge, press and form corrugated ribs with a corrugated rib forming mold;

[0049] Spot-weld the edges to form the corrugated ribs, and obtain the airfoil for an aeroengine.

[0050] The present invention will be further described in detail below with reference to the accompanying drawings and examples:

[0051] Embodiment

[0052] The product of the present invention, the guide vane of an aero-engine, is composed of multiple curved surfaces. As Figure 1 shown, the external shape of the product is as Figure 1 , Figure 2 shown. Figure 1 is the front view of the product, Figure 2 is the top view sectional drawing of the product.

[0053] The following further describes the present invention in detail with reference to the drawings and examples:

[0054] As Figures 3 to 5 shown, this structural design is a kind of integral sheet metal bending and forming structure, and the structure is formed by the sheet metal being formed multiple times in the mold.

[0055] As Figure 4 shown, the upper flanging structure of this structure is also sheet metal formed and is part of the product structure requirements.

[0056] As Figures 7 to 9 shown, after the integral bending and forming, the joint is designed into a corrugated shape, which is beneficial to spot welding forming and increases its strength.

[0057] ① Select a metal sheet and cut it into the Figure 2 outer shape, and punch several small holes.

[0058] ② Along the symmetry line, pre-press and form it against the mold as Figure 3 , slightly in a curved surface shape with flanging.

[0059] ③ Put it into the formal tooling and stamp to form a complete curved surface.

[0060] ④ Use a corrugated forming mold to stamp the edge into a corrugated shape.

[0061] ⑤ Weld the edge by spot welding to form.

[0062] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. What is described in the above embodiments and the specification only illustrates the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements all fall within the scope of the present invention claimed. The scope of protection claimed by the present invention is defined by the appended claims and their equivalents.

[0063] The above is only a preferred embodiment of the present invention, and does not impose any limitation on the present invention. Any simple modification, change and equivalent structural change made to the above embodiments according to the technical essence of the present invention still fall within the scope of protection of the technical solution of the present invention.

[0064] The above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those of ordinary skill in the art can still modify the specific implementation manners of the present invention or make equivalent replacements, and any modifications or equivalent replacements that do not depart from the spirit and scope of the present invention are all within the scope of protection of the claims of the present invention.

Claims

1. A manufacturing method of an aeroengine guide vane, characterized in that, The airfoil of an aeroengine includes an airfoil main body; the airfoil main body includes a first curved surface (2), a second curved surface (4) and a bending part (6); One side of the first curved surface (2) and the second curved surface (4) is connected by the bending part (6), and the other side of the first curved surface (2) and the second curved surface (4) is directly connected. A through-flow channel (7) is formed among the first curved surface (2), the second curved surface (4) and the bending part (6); Wave-shaped ribs (5) are formed at the direct connection positions of the first curved surface (2) and the second curved surface (4); the wave-shaped ribs of the first curved surface (2) and the second curved surface (4) are fixed by spot welding; The bending part (6) is a plane; The end cross-sectional length of the first curved surface (2) = the end cross-sectional length of the second curved surface (4) + the cross-sectional length of the bending part (6); The cross-sectional area of the through-flow channel (7) tapers from one end to the other end; One end face of the first curved surface (2) is bent outward to form a first flange (1), and one end face of the second curved surface (4) is bent outward to form a second flange (3). The first flange (1) and the second flange (3) are arranged at the same end; The manufacturing method of the airfoil of an aeroengine includes the following steps: Select a whole metal plate (100) and cut it into a blank; Pre-press along the symmetry line against a mold to form a curved surface shape and process the flanges; Press and form a complete curved surface according to the tooling and form the through-flow channel (7); Press into wave-shaped ribs at the edge with a wave-shaped rib forming mold; Weld the wave-shaped ribs at the edge by spot welding to obtain the airfoil of an aeroengine.

2. The manufacturing method of an aeroengine guide vane according to claim 1, characterized in that, The radius of curvature of the first curved surface (2) is smaller than the radius of curvature of the second curved surface (4).

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