CN210714788U - Metal edge covering and machining tool for fan blade of aircraft engine - Google Patents
Metal edge covering and machining tool for fan blade of aircraft engine Download PDFInfo
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- CN210714788U CN210714788U CN201921310395.XU CN201921310395U CN210714788U CN 210714788 U CN210714788 U CN 210714788U CN 201921310395 U CN201921310395 U CN 201921310395U CN 210714788 U CN210714788 U CN 210714788U
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Abstract
The utility model discloses a metal edge covering for fan blades of an aircraft engine, a processing tool and a processing method, belonging to the manufacturing technology of aircraft parts, wherein the metal edge covering comprises a side plate and a nose wing; the processing tool comprises a jacking part, an inner supporting part, a side pressing plate, an end clamping plate, an embedded fixing part and an external pulling fixing seat, wherein the jacking part and the side pressing plate are connected by adopting a four-connecting-rod pressing and positioning assembly in a pivoted mode; the method comprises the steps of preparing a tool, clamping a metal wrapping edge, welding the metal wrapping edge, performing stress relief heat treatment and removing the tool to finish machining. The method is used for welding the metal wrapping edges clamped and positioned by the tool, can adapt to the metal wrapping edges with multi-curvature complex three-dimensional appearance, pre-levels the clamped metal, implements welding modes including but not limited to electron beams, CMT or laser and the like, can carry out heat treatment operation along with the processing tool after welding, ensures the shape-correcting effect, can obviously reduce the processing cost of the part, and improves the efficiency.
Description
Technical Field
The utility model relates to an aircraft engine fan blade makes the field, especially relates to aircraft engine fan blade is with metal borduring and processing frock.
Background
In the manufacture of aircraft engine fan blades, metal shrouds have been commonly employed to enhance the performance of composite fan blade bodies. Aircraft engine design and manufacturing companies, represented by general electric and snelmar, have now generally adopted metal-clad reinforced composites to manufacture their fan blades in engine models such as GENX, GE9X, LEAP, and the like. China commercial aircraft engines (Inc.) is also working on the design and manufacture of fan blades based on composite and metal claddings (CN 109723671A; CN 103628923B). The novel composite material fan blade can help the engine to obviously reduce weight, improve fuel efficiency and thrust-weight ratio and has obvious economic benefit. The design of metal bordures is in order to improve blade intensity for the engine can resist the striking of foreign object in service, keeps the integrality of blade, ensures flight safety.
The composite fan blade has complex blade shape, the metal wrapping needs to be matched with the composite material body, the composite fan blade is a typical V-shaped structure with large length-width ratio, thin wall, deep groove and narrow opening, the precision requirement is high, the machining difficulty is large, and the cost is high. In addition to the traditional milling method, companies and colleges at home and abroad are also continuously exploring and improving to improve the processing efficiency and reduce the cost. Barnes (US 2012/0114494A1) and the trade company (CN 109723671A) adopt different methods, but both propose a method of forming a nose wing by 3D printing after manufacturing a side plate. The institute of aerospace manufacturing technology (CN 109202373a) proposed a method of directly performing 3D printing. But 3D printing molding processes currently lack process standards and certification methods in such parts. Northwest university of industry (CN 106181237B) proposed processing by superplastic forming. Sneakerma (CN104364031B) and shanghai university of transportation (CN 109483183a) also proposed diffusion welding.
Therefore, a new manufacturing method is needed for the metal wrapping of the fan blade to avoid the problems that the integral metal wrapping is difficult to process and the matching of the fan blade with a complex shape is poor.
SUMMERY OF THE UTILITY MODEL
In order to overcome the defects of the prior art, the utility model aims to provide an aircraft engine is metal borduring and processing frock for fan blade.
The purpose of the utility model is realized by adopting the following technical scheme:
the metal edge covering comprises side plates and a nose wing, wherein the outer side surface of the nose wing is formed into a large-curvature bulge from bottom to top, the bottom of the nose wing is concave to form an inner concave surface, at least one of the two side plates is arranged in a split manner with the nose wing, and the split side plates are connected with the nose wing in a welding manner.
Preferably, the inner concave surface includes, but is not limited to, a semicircular inner concave surface, a V-shaped inner concave surface, a rectangular inner concave surface, a notched inner concave surface, etc., and the inner concave surface is matched with the outer edge of the fan blade.
The utility model provides a weld according to above-mentioned metal and use processing frock, processing frock includes roof pressure piece, interior support piece, side guide, end splint, embedded mounting and draws the fixing base outward, roof pressure piece and side guide all adopt four connecting rods to compress tightly locating component pivot connection, the top of embedded mounting is connected to interior support piece's bottom, embedded mounting lower part joint advances in the taut spout that the middle part of drawing the fixing base was seted up outward, draw outward and set up the mounting hole on the fixing base, pass through the bolt the mounting hole will draw the fixing base outward and fix to welding station bench.
Preferably, the jacking piece is a V-shaped pressing piece matched with the outer surface of the metal-covered nose wing, and the inner pressing angle of the jacking piece is smaller than the included angle of the outer wall surface of the nose wing.
Preferably, the outer wall supporting included angle of the inner supporting piece is equal to the included angle of the two metal-clad side plates, a top cooling groove is formed in the top of the inner supporting piece, a welding process groove is formed in the side face of the top of the inner supporting piece, and the welding process groove corresponds to a welding seam at the butt joint between the side plates and the nose wing which are arranged in a split mode.
Preferably, a through hole is formed between two end faces of the inner support member, and at least one end clamping plate is arranged on each end face to longitudinally position and fasten the inner support member.
Preferably, the top end of the embedded fixing piece and the bottom end of the inner supporting piece are integrally arranged, welded and connected or fastened through bolts.
Preferably, the lower part of the embedded fixing part is a T-shaped head, the tensioning chute formed in the middle of the outer pulling fixing seat is an inverted T-shaped groove, and the T-shaped head is matched with the inverted T-shaped groove.
The utility model provides an adopt above-mentioned processing frock to bordure to the metal and carry out welded method, the method includes:
preparing a tool, preparing a processing tool for welding assistance according to metal edge wrapping, pre-installing an outward-pulling fixing seat on a welding station table by using bolts, sliding an embedded fixing part with an inner supporting piece at the upper part into a tensioning sliding groove from one end of the outward-pulling fixing seat, pre-installing a four-connecting-rod pressing and positioning assembly with a top pressing piece and a side pressing plate at a linkage end on the welding station table at two sides of the outward-pulling fixing seat, fastening the outward-pulling fixing seat and a base of the four-connecting-rod pressing and positioning assembly according to ridge lines of a nose wing of the metal edge wrapping, and preparing an end clamping plate.
The metal wrapping is clamped, a side plate and a nose wing of the metal wrapping to be welded are sleeved on an inner supporting piece, a jacking piece is pressed against the top of the nose wing through adjusting a four-connecting-rod pressing and positioning assembly, at least two groups of side pressing plates are pressed against the outer sides of the side plate, and end clamping plates are pressed against two ends of the inner supporting piece through bolts so as to position the side ends of the side plate.
And welding the metal wrapping edges, leveling the welding seams of the clamped metal wrapping edges by using a positioner, and performing electron beam, CMT or laser welding on the butt joint of the side plates and the nose wings on the welding station platform after leveling the workpiece.
And (4) stress relief heat treatment, namely performing stress relief and shape correction heat treatment on the welded metal edge covering by using a machining tool.
And removing the tool to complete processing, and after the heat treatment is completed, sequentially detaching the jacking piece, the end clamping plate and the side pressing plate from top to bottom, so that the processed metal edge covering can be taken down.
Preferably, when a laser welding mode is adopted, the laser power of the laser welding equipment is 700-1600W, the diameter of a laser spot is 0.3-0.8 mm, and the moving speed of the laser spot is 0.3-0.8 mm/min.
Compared with the prior art, the beneficial effects of the utility model reside in that: the utility model discloses a metal is bordured and is adopted curb plate and the split type structure of nose wing, and split type structure and the processing frock that corresponds are particularly adapted to the metal of the complicated three-dimensional appearance of fan blade bordure, and the metal good to the clamping is made level in advance, can carry out the heat treatment operation together with the processing frock after the welding, has guaranteed orthopedic effect, and this method can obviously reduce the processing cost of this part, raises the efficiency.
Drawings
Fig. 1 is a schematic view of a metal edge covering arranged in a fully-split manner according to an embodiment of the present invention;
fig. 2 is a schematic view of a metal edge covering with a single side plate separately arranged according to another embodiment of the present invention;
FIG. 3 is a side view of the metal wrapping for positioning the machining tool;
FIG. 4 is an axial side view of the metal wrapping for positioning the tooling;
FIG. 5 is a schematic side view of a metal wrapping shaft for positioning and compressing a tool by using a four-bar compressing and positioning assembly;
FIG. 6 is a side view of a metal wrapping that uses a four-bar linkage compression positioning assembly to position and compress a tool.
In the figure: 1/2, side panels; 2. a side plate; 3. a nasal ala; 31/32, weld seam;
100. processing a tool; 101. a jacking member; 102. an inner support; 103. side pressing plates; 104/105, end clamp plate; 106. a fixing part is embedded; 107. a fixed seat is pulled outwards;
200. the four-bar linkage compresses tightly locating component.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Referring to fig. 1 and 2, the metal covered edge for the fan blade of the aircraft engine comprises side plates (1 and 2) and a nose wing 3, wherein the outer side surface of the nose wing 3 is formed into a large-curvature bulge from bottom to top, the bottom of the nose wing 3 is concave upwards to form an inner concave surface, at least one of the two side plates (1 and 2) and the nose wing 3 are arranged in a split mode, and the side plates arranged in the split mode are welded and connected with the nose wing 3 through welding.
As shown in fig. 1, two side plates (1, 2) are arranged separately from the nose wing 3 to form welding seams (31, 32); as shown in fig. 2, one side plate 1 is integrally formed with the nose piece 3, and the other side plate 2 is provided separately from the nose piece 3 to form a weld 32. The positions of the welding seams (31, 32) of the actual metal wrapping can avoid the weak strength area according to the strength requirement, and the position with the proper plate thickness is selected, so that the deformation problem caused by welding heat input is reduced as much as possible.
The side plates (1 and 2) which are arranged in a split mode need to be fixedly connected with the bottom end of the nose wing 3, and a welding connection mode is generally adopted, so that welding seams (31 and 32) need to have higher precision, and if the welding seams are smaller than 0.1mm, the technological requirements are met.
Referring to fig. 3 to 6, the utility model provides a weld according to above-mentioned metal bordures with processing frock 100, processing frock 100 includes roof pressure piece 101, interior support 102, side pressure plate 103, end splint 104, 105, embedded mounting 106 and draws fixing base 107 outward.
Referring to fig. 5 and 6, the top pressing member 101 and the side pressing plate 103 are pivotally connected by a four-bar compressing and positioning assembly 200, and specifically, the four-bar compressing and positioning assembly 200 sequentially comprises a base connecting bar, a pivot connecting bar, a compressing connecting bar and a pressure-bearing connecting bar, the base connecting bar is fixedly connected with the welding station table, one end of the pivot connecting bar extends to form a pivot connecting end, and one end of the compressing connecting bar extends outwards to form a compressing handle.
The top end of the embedded fixing part 106 is connected to the bottom of the inner supporting part 102, the lower part of the embedded fixing part 106 is clamped into a tensioning sliding groove formed in the middle of the outer pulling fixing seat 107, a mounting hole is formed in the outer pulling fixing seat 107, and the outer pulling fixing seat 107 is fixed to a welding station table through a bolt penetrating through the mounting hole.
The jacking piece 101 is a V-shaped pressing piece matched with the outer surface of the metal-covered nose wing 3, and the internal pressure angle of the jacking piece is smaller than the included angle of the outer wall surface of the nose wing 3. The outer wall supporting included angle of the inner supporting piece 102 is equal to the included angle of the two metal-clad side plates 1 and 2, a top cooling groove is formed in the top of the inner supporting piece 102, a welding process groove is formed in the side face of the top of the inner supporting piece 102, and the welding process groove corresponds to a butt joint welding seam between the side plate 2 and the nose wing 3 which are arranged in a split mode, so that exhaust or slag discharge in the welding process is guaranteed, and the welding with a tool is prevented from being welded together.
Furthermore, a through hole is arranged between two end faces of the inner support member 102, and at least one end clamping plate (104, 105) is arranged on each end face to longitudinally position and fasten the inner support member.
The top end of the embedded fixing member 106 and the bottom end of the inner support member 102 are integrally disposed, welded, or fastened by bolts. The lower part of the embedded fixing part 106 is a T-shaped head, the tensioning chute formed in the middle of the outer pulling fixing seat 107 is an inverted T-shaped groove, and the T-shaped head is matched with the inverted T-shaped groove.
The method for welding the metal covered edge by adopting the processing tool comprises the following steps:
preparing a tool, preparing a processing tool 100 for welding assistance according to metal edge wrapping, pre-installing an external pulling fixing seat 107 on a welding station table by using bolts, sliding an embedded fixing part 106 with an internal supporting part 102 at the upper part into a tensioning sliding chute from one end of the external pulling fixing seat 107, pre-installing a four-bar compression positioning assembly 200 with a top pressing part 101 and a side pressing plate 103 at a linkage end on the welding station table at two sides of the external pulling fixing seat 107, fastening bases of the external pulling fixing seat 107 and the four-bar compression positioning assembly 200 according to ridge lines of a nose wing 3 of the metal edge wrapping, and preparing end clamping plates (104, 105).
Clamping metal wrapping edges, sleeving side plates (1 and 2) and a nose wing 3 of the metal wrapping edges to be welded on an inner supporting piece 102, pressing a top pressing piece 101 to the top of the nose wing 3 through adjusting a four-bar pressing and positioning assembly 200, pressing at least two groups of side pressing plates 103 to the outer sides of the side plates (1 and 2), and pressing end clamping plates (104 and 105) to two ends of the inner supporting piece 102 through bolts to position the side ends of the side plates (1 and 2).
And welding the metal wrapping edges, leveling the welding seams of the clamped metal wrapping edges by using a positioner, and performing laser welding on the butt joint parts of the side plates (1 and 2) and the nose wings 3 on the welding station platform after leveling the workpiece.
The robot drives the laser welding head to move horizontally, and the materials are melted and then solidified to form a welding seam, so that the materials are welded. The laser power of the laser welding equipment is 700-1600W, the diameter of a laser spot is 0.3-0.8 mm, and the moving speed of the laser spot is 0.3-0.8 mm/min. When the materials of the metal binding edges are different, continuous laser or pulse laser welding can be selected.
And (4) stress relief heat treatment, namely performing stress relief and shape correction heat treatment on the welded metal edge covering by using a machining tool.
And (3) removing the tool to complete processing, and after the heat treatment is completed, sequentially detaching the jacking piece 101, the end clamping plates (104 and 105) and the side pressing plate 103 from top to bottom, so that the processed metal edge covering can be taken down.
For convenience of explanation, the drawings of the present invention all use ruled surfaces as examples, but the actual metal edge of the fan blade of the aircraft engine or the metal reinforcing edge is a complex three-dimensional curved surface, and the ridge line of the nose wing is a complex three-dimensional complex curve. In addition, the material thickness of the metal wrapping edge with the actual 3D design is changed along the length direction at the positions of the welding seams (31, 32), so that in the implementation process, the welding process needs to be planned, the metal wrapping edge needs to be prepared in a machining or hot pressing mode, and the variable-parameter welding processing is carried out.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.
Claims (7)
1. Aircraft engine fan blade is with metal bordure, the metal bordure is including curb plate (1, 2) and nosewing (3), its characterized in that: the outer side face of the nose wing (3) is formed into a large-curvature bulge from bottom to top, the bottom of the nose wing (3) is concave upwards to form an inner concave face, at least one of the two side plates (1 and 2) is arranged in a split mode with the nose wing (3), and the side plates arranged in the split mode are connected with the nose wing (3) in a welding mode.
2. A metal bordure welding machining tool according to claim 1, wherein the machining tool (100) comprises a top pressing piece (101), an inner supporting piece (102), side pressing plates (103), end clamping plates (104, 105), an embedded fixing piece (106) and an outer pulling fixing seat (107), and is characterized in that: roof pressure spare (101) and side pressure board (103) all adopt four-bar linkage to compress tightly locating component (200) pivot connection, the top of embedded mounting (106) is connected to the bottom of interior support piece (102), embedded mounting (106) lower part joint advances in draw the taut spout that the middle part of fixing base (107) was seted up outward, draw outward and set up the mounting hole on fixing base (107), pass through the bolt the mounting hole will draw fixing base (107) outward and fix to welding station bench.
3. The processing tool according to claim 2, characterized in that: the jacking piece (101) is a V-shaped pressing piece matched with the outer surface of the metal edge-covered nose wing (3), and the inner pressing angle of the jacking piece is smaller than the included angle of the outer wall surface of the nose wing (3).
4. The processing tool according to claim 2, characterized in that: the outer wall supporting included angle of the inner supporting piece (102) is equal to the included angle of the two metal-coated side plates (1 and 2), a top cooling groove is formed in the top of the inner supporting piece (102), a welding process groove is formed in the side face of the top of the inner supporting piece (102), and the welding process groove corresponds to a butt joint welding seam between the side plate (2) and the nose wing (3) which are arranged in a split mode.
5. The processing tool according to claim 4, wherein: a through hole is arranged between two end faces of the inner support piece (102), and at least one end clamping plate (104, 105) is arranged on each end face to longitudinally position and fasten the inner support piece.
6. The processing tool according to claim 4, wherein: the top end of the embedded fixing piece (106) and the bottom end of the inner supporting piece (102) are integrally arranged, welded and connected or fastened through bolts.
7. The processing tool according to claim 2, characterized in that: the lower part of the embedded fixing piece (106) is a T-shaped head, the tensioning sliding groove formed in the middle of the outer pulling fixing seat (107) is an inverted T-shaped groove, and the T-shaped head is matched with the inverted T-shaped groove.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921310395.XU CN210714788U (en) | 2019-08-14 | 2019-08-14 | Metal edge covering and machining tool for fan blade of aircraft engine |
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| CN201921310395.XU CN210714788U (en) | 2019-08-14 | 2019-08-14 | Metal edge covering and machining tool for fan blade of aircraft engine |
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| CN210714788U true CN210714788U (en) | 2020-06-09 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110439623A (en) * | 2019-08-14 | 2019-11-12 | 上海两擎机电科技合伙企业(有限合伙) | Aircraft engine fan blade metal hemming edge, processing tool and processing method |
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2019
- 2019-08-14 CN CN201921310395.XU patent/CN210714788U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110439623A (en) * | 2019-08-14 | 2019-11-12 | 上海两擎机电科技合伙企业(有限合伙) | Aircraft engine fan blade metal hemming edge, processing tool and processing method |
| CN110439623B (en) * | 2019-08-14 | 2024-05-14 | 上海两擎机电科技合伙企业(有限合伙) | Metal edging for aircraft engine fan blade, machining tool and machining method |
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Effective date of registration: 20221208 Address after: 201611 1st Floor, Building 23, No. 3255, Shengang Road, Songjiang District, Shanghai Patentee after: Shanghai United Engine Power Technology Co.,Ltd. Address before: 201611 1st floor, Building 23, No. 3255, Shengang Road, Songjiang District, Shanghai Patentee before: Shanghai Liangqing Electromechanical Technology Partnership (L.P.) |