CN112814948A - Aeroengine flow deflector and manufacturing method thereof - Google Patents
Aeroengine flow deflector and manufacturing method thereof Download PDFInfo
- Publication number
- CN112814948A CN112814948A CN202011643925.XA CN202011643925A CN112814948A CN 112814948 A CN112814948 A CN 112814948A CN 202011643925 A CN202011643925 A CN 202011643925A CN 112814948 A CN112814948 A CN 112814948A
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- Prior art keywords
- curved surface
- guide vane
- aircraft engine
- edges
- forming
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 10
- 238000005452 bending Methods 0.000 claims abstract description 20
- 238000012545 processing Methods 0.000 claims abstract description 9
- 238000003466 welding Methods 0.000 claims description 16
- 239000002184 metal Substances 0.000 claims description 11
- 238000004080 punching Methods 0.000 claims description 6
- 238000000465 moulding Methods 0.000 claims description 5
- 238000005520 cutting process Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000010009 beating Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The invention discloses an aeroengine guide vane and a manufacturing method thereof, comprising a guide vane main body; the flow deflector main body comprises a first curved surface, a second curved surface and a bending part; one side of the first curved surface is connected with one side of the second curved surface through a bending part, the other side of the first curved surface is directly connected with the other side of the second curved surface, and a through flow guide channel is formed by the first curved surface, the second curved surface and the bending part in a surrounding mode. The invention designs an effective structure in order to reduce the processing cost and the processing difficulty of the flow deflector.
Description
Technical Field
The invention belongs to the field of manufacturing of the aviation industry, and relates to an aeroengine flow deflector and a manufacturing method thereof.
Background
The aeroengine fan guide vane has various structural forms, and the guide vane is generally a curve guide vane for efficiently regulating air flow due to the characteristic of easy flowability of fluid and the like. The curved guide vane has the problems of difficult processing, difficult shape guarantee and the like.
Disclosure of Invention
The invention mainly aims to provide an aircraft engine guide vane and a manufacturing method thereof, and an effective integrated structure is designed to reduce the processing cost and the processing difficulty of the guide vane.
In order to achieve the purpose, the invention adopts the technical scheme that:
an aircraft engine guide vane comprises a guide vane main body; the flow deflector main body comprises a first curved surface, a second curved surface and a bending part;
one side of the first curved surface is connected with one side of the second curved surface through a bending part, the other side of the first curved surface is directly connected with the other side of the second curved surface, and a through flow guide channel is formed by the first curved surface, the second curved surface and the bending part in a surrounding mode.
As a further improvement of the invention, one end face of the first curved surface is bent outwards to form a first flanging, one end face of the second curved surface is bent outwards to form a second flanging, and the first flanging and the second flanging are arranged at the same end.
As a further improvement of the invention, the direct connection part of the first curved surface and the second curved surface forms a wave-shaped edge.
As a further improvement of the present invention, the wavy edges of the first curved surface and the second curved surface are spot-welded.
As a further improvement of the invention, the bending part is a plane.
As a further improvement of the present invention, the radius of curvature of the first curved surface is smaller than the radius of curvature of the second curved surface.
In a further improvement of the present invention, the end section length of the first curved surface is equal to the end section length of the second curved surface plus the section length of the bent portion.
As a further improvement of the invention, the flow deflector main body is formed by bending and welding a whole metal plate.
As a further development of the invention, the cross-sectional area of the flow-guiding channel tapers from one end to the other end.
A manufacturing method of an aircraft engine guide vane comprises the following steps:
selecting a whole metal plate and cutting into blank;
prepressing and molding a curved surface shape along a symmetrical line profile mold, and processing a flanging;
forming a complete curved surface by punching according to the tool, and forming a flow guide channel;
punching the edges into corrugated edges by using a corrugated edge forming die;
and welding the edges with spot welding wave-shaped edges for forming to obtain the aeroengine flow deflector.
Compared with the prior art, the invention has the following beneficial effects:
the invention realizes the manufacture of the flow deflector by replacing the traditional machining process with the metal plate and welding process, thereby designing a corresponding integrated structure. The flow deflector main body comprises a first curved surface, a second curved surface and a bent part, and a flow guide channel is formed in the middle; adopt the panel beating of integral type to bend welding forming, this structure obviously reduces the processing cost of water conservancy diversion piece.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic view of an aircraft engine vane;
fig. 2 is a top cut-away view of the guide vane;
FIG. 3 is a development of the blanking process;
FIG. 4 is a diagram of pre-compression forming;
FIG. 5 is a schematic view broken away along line A-A of FIG. 4;
FIG. 6 is a press forming view;
FIG. 7 is a drawing showing the formation of outer edge wave
FIG. 8 is a side view of an outer corrugation;
FIG. 9 is a spot-welded drawing.
Wherein 100 is a metal plate, 1 is a first flanging, 2 is a first curved surface, 3 is a second flanging, 4 is a second curved surface, 5 is a wave-shaped edge, 6 is a bending part, and 7 is a flow guide channel.
Detailed Description
In order to make the objects and technical solutions of the present invention clearer and easier to understand. The present invention will be described in further detail with reference to the following drawings and examples, wherein the specific examples are provided for illustrative purposes only and are not intended to limit the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified. In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings and specific embodiments, and it is to be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the invention without making creative efforts, fall within the scope of the invention.
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
As shown in fig. 1 to 2, an aircraft engine vane is characterized by comprising a vane body; the flow deflector main body comprises a first curved surface 2, a second curved surface 4 and a bending part 6;
one side of the first curved surface 2 is connected with one side of the second curved surface 4 through a bending part 6, the other side of the first curved surface 2 is directly connected with the other side of the second curved surface 4, and a through flow guide channel 7 is formed by the first curved surface 2, the second curved surface 4 and the bending part 6 in a surrounding mode. The guide vane main body is formed by bending and welding a whole metal plate 100.
Furthermore, 2 terminal surfaces of first curved surface outwards bend and form first turn- ups 1, and 4 terminal surfaces of second curved surface outwards bend and form second turn-ups 3, and first turn-ups 1 and second turn-ups 3 set up at same one end.
The cross-sectional area of the flow guide channel 7 tapers from one end to the other. And tapers from the cuff end to the cuff-less end.
In order to meet the requirements of fixing and fastening the joint and strength, the corrugated edge 5 is formed at the direct joint of the first curved surface 2 and the second curved surface 4. The wave-shaped edges of the first curved surface 2 and the second curved surface 4 are fixed by spot welding.
Wherein, the bending part 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 section length of the first curved surface 2 is equal to the end section length of the second curved surface 4 plus the section length of the bent portion 6.
As shown in fig. 3 to 9, the method for manufacturing an aircraft engine guide vane includes the following steps:
selecting a whole metal plate 100 to be cut into blank;
prepressing and molding a curved surface shape along a symmetrical line profile mold, and processing a flanging;
forming a complete curved surface according to the tool in a stamping mode, and forming a flow guide channel 7;
punching the edges into corrugated edges by using a corrugated edge forming die;
and welding the edges with spot welding wave-shaped edges for forming to obtain the aeroengine flow deflector.
The invention is described in further detail below with reference to the following figures and examples:
examples
The product aeroengine guide vane is composed of a plurality of curved surfaces, as shown in figure 1, the product appearance is as shown in figures 1 and 2, figure 1 is a product front view, and figure 2 is a product top cut-away view.
The invention is described in further detail below with reference to the following figures and examples:
as shown in figures 3-5, the structure designs an integral metal plate bending and forming structure, and the structure is formed by multiple times of forming of plates in a die.
As shown in FIG. 4, the flanging structure at the upper part of the structure is also formed by sheet metal, and is a part of the structural requirements of the product.
As shown in FIGS. 7 to 9, the seam is designed to be corrugated after the integral bending molding, which is beneficial to spot welding molding and increases the strength.
Firstly, a metal plate is selected and cut into the shape of figure 2, and a plurality of small holes are punched.
Secondly, prepressing and forming by a profiling die along a symmetrical line as shown in figure 3, and slightly forming a curved surface shape with a flanging.
Putting the formal tool, and punching and forming the complete curved surface.
And fourthly, stamping the edges into the wave edge shape by using a wave edge forming die.
And fifthly, welding and forming the edge by spot welding.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
The above embodiments are only preferred embodiments of the present invention, and are not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiments according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.
Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art can make modifications and equivalents to the specific embodiments of the present invention without departing from the spirit and scope of the present invention, which is set forth in the following claims.
Claims (10)
1. An aircraft engine guide vane is characterized by comprising a guide vane main body; the flow deflector main body comprises a first curved surface (2), a second curved surface (4) and a bending part (6);
one side of the first curved surface (2) is connected with one side of the second curved surface (4) through a bending part (6), the other side of the first curved surface (2) is directly connected with the other side of the second curved surface (4), and a through flow guide channel (7) is formed by the first curved surface (2), the second curved surface (4) and the bending part (6) in a surrounding mode.
2. The aircraft engine guide vane according to claim 1, wherein one end surface of the first curved surface (2) is bent outwards to form a first flange (1), one end surface of the second curved surface (4) is bent outwards to form a second flange (3), and the first flange (1) and the second flange (3) are arranged at the same end.
3. The aircraft engine guide vane according to claim 1, wherein the direct connection of the first curved surface (2) and the second curved surface (4) forms a wave-shaped edge (5).
4. The aircraft engine guide vane according to claim 1, wherein the wave-shaped edges of the first curved surface (2) and the second curved surface (4) are fixed by spot welding.
5. The aircraft engine guide vane as claimed in claim 1, characterised in that the bend (6) is planar.
6. An aircraft engine guide vane according to claim 1, characterised 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).
7. The aircraft engine guide vane according to claim 1, wherein the end section length of the first curved surface (2) is equal to the end section length of the second curved surface (4) plus the section length of the bent portion (6).
8. The aircraft engine guide vane of claim 1, wherein the guide vane body is formed by bending and welding a single metal plate (100).
9. An aircraft engine guide vane according to claim 1, characterised in that the cross-sectional area of the guide channel (7) tapers from one end to the other.
10. The manufacturing method of the aeroengine guide vane is characterized by comprising the following steps:
selecting a whole metal plate (100) and cutting into blank;
prepressing and molding a curved surface shape along a symmetrical line profile mold, and processing a flanging;
forming a complete curved surface by punching according to the tool, and forming a flow guide channel (7);
punching the edges into corrugated edges by using a corrugated edge forming die;
and welding the edges with spot welding wave-shaped edges for forming to obtain the aeroengine flow deflector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011643925.XA CN112814948A (en) | 2020-12-31 | 2020-12-31 | Aeroengine flow deflector and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011643925.XA CN112814948A (en) | 2020-12-31 | 2020-12-31 | Aeroengine flow deflector and manufacturing method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112814948A true CN112814948A (en) | 2021-05-18 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011643925.XA Pending CN112814948A (en) | 2020-12-31 | 2020-12-31 | Aeroengine flow deflector and manufacturing method thereof |
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| Country | Link |
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| CN (1) | CN112814948A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113339078A (en) * | 2021-05-27 | 2021-09-03 | 中国航发南方工业有限公司 | Flow deflector and processing method thereof |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05305376A (en) * | 1992-04-30 | 1993-11-19 | Asahi M & Ii:Kk | Method for forming blade for oblique flow fan |
| US20050042083A1 (en) * | 2003-07-09 | 2005-02-24 | Milburn Richard G. | Guide vane |
| DE102005016557A1 (en) * | 2004-04-14 | 2005-11-03 | C.R.E.A.S. Snc Di Sgarlazzetta A. & C. | Method for producing cooling insert for stator blades in gas turbines involves shaping outwardly curved and inwardly curved walls from single plate which is then bent about rear edge and welded along leading edge |
| KR20060087872A (en) * | 2005-01-31 | 2006-08-03 | 한국동서발전(주) | Gas turbine equipped with cooler for air in compressor |
| US20070107426A1 (en) * | 2003-12-31 | 2007-05-17 | Honeywell International | Cambered vane for use in turbochargers |
| US20070297898A1 (en) * | 2006-06-22 | 2007-12-27 | Rolls-Royce Plc | Aerofoil |
| US20090044592A1 (en) * | 2007-07-24 | 2009-02-19 | Honda Motor Co., Ltd. | Method for manufacturing an edge protector and die assemblies therefor |
| US20140255178A1 (en) * | 2011-11-24 | 2014-09-11 | Aircelle | Aircraft engine air flow straightening vane and associated flow straightening structure |
| US20160271674A1 (en) * | 2014-01-22 | 2016-09-22 | Taiyuan University Of Science And Technology | Method for preparing metal composite plate strip by rolling |
| CN214533723U (en) * | 2020-12-31 | 2021-10-29 | 西安汇腾航空科技有限公司 | Aeroengine flow deflector |
-
2020
- 2020-12-31 CN CN202011643925.XA patent/CN112814948A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05305376A (en) * | 1992-04-30 | 1993-11-19 | Asahi M & Ii:Kk | Method for forming blade for oblique flow fan |
| US20050042083A1 (en) * | 2003-07-09 | 2005-02-24 | Milburn Richard G. | Guide vane |
| US20070107426A1 (en) * | 2003-12-31 | 2007-05-17 | Honeywell International | Cambered vane for use in turbochargers |
| DE102005016557A1 (en) * | 2004-04-14 | 2005-11-03 | C.R.E.A.S. Snc Di Sgarlazzetta A. & C. | Method for producing cooling insert for stator blades in gas turbines involves shaping outwardly curved and inwardly curved walls from single plate which is then bent about rear edge and welded along leading edge |
| KR20060087872A (en) * | 2005-01-31 | 2006-08-03 | 한국동서발전(주) | Gas turbine equipped with cooler for air in compressor |
| US20070297898A1 (en) * | 2006-06-22 | 2007-12-27 | Rolls-Royce Plc | Aerofoil |
| US20090044592A1 (en) * | 2007-07-24 | 2009-02-19 | Honda Motor Co., Ltd. | Method for manufacturing an edge protector and die assemblies therefor |
| US20140255178A1 (en) * | 2011-11-24 | 2014-09-11 | Aircelle | Aircraft engine air flow straightening vane and associated flow straightening structure |
| US20160271674A1 (en) * | 2014-01-22 | 2016-09-22 | Taiyuan University Of Science And Technology | Method for preparing metal composite plate strip by rolling |
| CN214533723U (en) * | 2020-12-31 | 2021-10-29 | 西安汇腾航空科技有限公司 | Aeroengine flow deflector |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113339078A (en) * | 2021-05-27 | 2021-09-03 | 中国航发南方工业有限公司 | Flow deflector and processing method thereof |
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