CN111594273B - Lapping and combining integrated compensation body for damage of engine disc - Google Patents
Lapping and combining integrated compensation body for damage of engine disc Download PDFInfo
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- CN111594273B CN111594273B CN202010481293.5A CN202010481293A CN111594273B CN 111594273 B CN111594273 B CN 111594273B CN 202010481293 A CN202010481293 A CN 202010481293A CN 111594273 B CN111594273 B CN 111594273B
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- lap
- joint body
- joint
- blade
- butt
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/005—Repairing methods or devices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
- B23K20/122—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding using a non-consumable tool, e.g. friction stir welding
- B23K20/127—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding using a non-consumable tool, e.g. friction stir welding friction stir welding involving a mechanical connection
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Laser Beam Processing (AREA)
Abstract
The invention discloses a lap-pair composite integrated compensation body for damage of an engine disc, which comprises a first lap-joint body, a second lap-joint body and a butt-joint body, wherein the second lap-joint body is positioned below the first lap-joint body, the butt-joint body is connected with the same side of the first lap-joint body and the second lap-joint body, the first lap-joint body, the second lap-joint body and the butt-joint body are encircled to form a clamping groove, the clamping groove is used for inserting a retained blade, a cutting surface of the retained blade is attached to the side surface of the clamping groove, and a welding seam is arranged between the first lap-joint body and the butt-joint body. And by adopting a lap joint/butt joint composite mode, welding defects such as air holes, undercut and the like can be effectively avoided.
Description
Technical Field
The invention relates to a lap/butt composite integrated compensation body for damage of an engine disc, in particular to a compensation body with allowance for processing.
Background
With the development of the design technology of the aero-engine, the requirement on the dimensional accuracy of the aero-engine blade is higher and higher. The turboshaft engine completely depends on gas flow to generate thrust, and as the requirements of thrust-weight ratio/power-weight ratio, structural reliability and precision consistency of the aero-engine are continuously improved, a severe service environment easily causes disc failure.
The large-area failure of the blade can be caused by the damage of foreign objects and the extreme severe service environment of the aeroengine, the cost of the whole replacement is high, and the inevitable selection of repairing the blade disc blade and prolonging the service life of the blade disc blade of the engine is realized by adopting the repair and replacement technology; however, the requirement for the reliability and the precision of the structure of the engine disk is high, and the blades are of a thin-wall structure, and the difference of the overall performance of the repaired blades can be caused by the difference of compensation structures used in the repair and replacement process.
Under the condition that the size and the shape of the repair blade meet the requirements in the repair and replacement of the large-area damaged blade, the connector which is retained after the repair and replacement and the allowance removal needs to be set to have the best performance, and the size and the structure of the compensation body, the matching relation of the compensation body and the cutting retained blade, the position of the stirring needle and the distance between the stirring needle and the upper boundary and the lower boundary of the compensation body need to be considered in the design.
Disclosure of Invention
The invention aims to provide a compensation body for friction stir welding repair of an engine disk aiming at large-area damage repair of an aeroengine disk, and the compensation body can ensure the repair quality of blades.
In order to achieve the purpose, the lap-pair composite integrated compensation body for damage of the engine disc comprises a first lap-joint body, a second lap-joint body and a butt-joint body, wherein the second lap-joint body is positioned below the first lap-joint body, the butt-joint body is connected to the same side of the first lap-joint body and the second lap-joint body, the first lap-joint body, the second lap-joint body and the butt-joint body are enclosed to form a clamping groove, the clamping groove is used for inserting a retained blade, a cutting surface of the retained blade is attached to the side surface of the clamping groove, and a welding seam is arranged between the first lap-joint body and the butt-joint body.
Further, when the leave-on blade is inserted into the clamping groove, the vertical distance between the upper surface of the leave-on blade and the upper surface of the first lap joint body is 0.5 mm-3 mm.
Further, when the leave-on blade is inserted into the clamping groove, the vertical distance between the lower surface of the leave-on blade and the lower surface of the second lap joint body is 1 mm-2 mm.
Furthermore, the width of the welding seam is 0.5 mm-3 mm.
Further, the width of the welding seam is 1 mm-2 mm.
Further, when the surface of the remaining blade is of a spatial curved surface structure, the first lapping body and the butt joint body are completely isolated by the welding seam.
Further, when the blade inserts the draw-in groove, bottom surface and the upper surface laminating of surviving the blade on the draw-in groove, the bottom surface is laminated with the lower surface of surviving the blade under the draw-in groove.
Furthermore, the composite integrated compensation body is provided with machining allowance, and the machining allowance of the composite integrated compensation body in each direction is 0.5 mm-3 mm.
Compared with the prior art, the invention has at least the following beneficial technical effects:
the invention adopts a lap joint/butt joint composite mode, and can effectively avoid welding defects such as air holes, undercut and the like. During welding, gas introduced into the interface and the molten pool can be gathered on the surface of the compensating body, and a perfect tissue structure is kept in a welding seam body phase; under the structural design of the compensation body lap joint/butt joint, toe undercut on the surface of a welding joint can be avoided, a full joint shape is formed, a compensation effect is formed on a welding line area, and subsequent surface profile precision recovery is facilitated.
Furthermore, the vertical distance between the upper surface of the reserved blade and the upper surface of the multi-body structure compensation body is 0.5 mm-3 mm, and the vertical distance between the lower surface of the reserved blade and the lower surface of the compensation body is 1 mm-2 mm. By adopting the distance, the butt joint can be formed under the condition that the laser is ensured to fully melt the retained blade and the compensation body, and the good combination of the retained blade and the compensation body is realized.
Furthermore, the width of the welding line is 0.5-3mm, the optimal width is 1-2mm, the forming quality can be ensured by the proper width of the welding line, and the excessive width of the welding line can greatly influence the plasticity and toughness of the joint.
Furthermore, the compensation body is provided with machining allowance, so that the compensation body is machined into the same shape of the blade in the later stage.
The compensation body can be applied to friction stir welding repair, the stability of a repair replacement process is realized, machining allowance is reserved on the compensation body to ensure that the blade with the shape and the size meeting the requirements can be obtained, meanwhile, the best performance of a joint of the repaired blade can be ensured after the machining allowance is removed, and the improvement of the overall performance of the repaired blade is ensured. The compensating body can be directly used for repairing and replacing large-area damage of blades of blade discs of aero-engines, and can also be used for other engine blades and other related specialties.
Drawings
FIG. 1 is a schematic view of the single compensation body and the retaining blade;
FIG. 2 is a schematic view of a monomer compensator;
FIG. 3 is a schematic view of the mating of a multi-body compensator and retention vanes;
fig. 4 is a schematic diagram of a multi-body compensation structure.
In the drawings: 1. the clamping groove, 2, a first lap joint body, 3, a second lap joint body, 4, a butt joint body, 5, a welding line, 6, a clamping groove side face, 7, a clamping groove upper bottom face, 8, a clamping groove lower bottom face, 9, a first lap joint body side face, 10, a butt joint body side face, 11 and a retaining blade.
Detailed Description
The technical solutions in the embodiments of the present invention are described below with reference to the drawings in the embodiments of the present invention, and the described embodiments are only a single part of the embodiments of the present invention, and do not represent all the embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of 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 invention provides a compensating body for friction stir welding repair of an engine disc, wherein the compensating body 1 is of a single structure with a clamping groove 1 or a multi-body structure with a plurality of parts capable of being assembled, the single structure and the multi-body structure are provided with a lapping surface and a butt joint surface, the single structure or the multi-body structure can be assembled with a damaged and cut blade to keep the compensating body completely attached to a contact part of a retained blade, the contact surfaces of all parts of the compensating body are completely attached, and the assembled compensating body is provided with a processing allowance to ensure that a repaired blade meeting the shape and size requirements of the blade is obtained by processing.
Example 1
As shown in fig. 1, in this embodiment, the compensation body for saving the blade surface as the replacement repair of the spatial planar structure is selected to be a single-body structure compensation body.
Referring to fig. 2, draw-in groove 1 has been seted up in the monomer compensation structure, and draw-in groove 1 is used for the blade cutting back to be preserved blade 11 and inserts, and the cutting plane of preserving blade 11 is laminated with draw-in groove 1 side, stretches into draw-in groove 1's 11 upper surface of preserving blade and draw-in groove 1 upper surface laminating, stretches into draw-in groove 1's the laminating of bottom surface 8 under the lower surface of preserving blade and the draw-in groove.
Wherein, the cutting plane of reserving blade 11 is a pair of butt joint face with draw-in groove side 6, reserves blade 11 upper surface and draw-in groove 1 upper bottom surface 7 and is a pair of faying face, reserves blade lower surface and draw-in groove 1 lower bottom surface 8 and is another pair of faying face, forms overlap joint and butt joint complex mode.
The single body compensation structure comprises a first lap joint body 2, a second lap joint body 3 and a butt joint body 4. The upside of the upper bottom surface of the clamping groove 1 is marked as a first overlapping body 2, the downside of the lower bottom surface of the clamping groove 1 is marked as a second overlapping body 3, a welding line 5 is arranged right above the butt joint surface, one side of the welding line is a clamping groove 1, and the other side of the welding line is a butt joint body 4. The width of the welding seam 5 is 0.5-3mm, the optimal width is 1-2mm, the proper welding seam width can ensure the forming quality, and the excessive welding seam width can greatly influence the plasticity and toughness of the joint.
The vertical distance between the upper surface of the reserved blade 11 and the upper surface of the multi-body structure compensation body is 0.5 mm-3 mm, and the vertical distance between the lower surface of the reserved blade and the lower surface of the compensation body is 1 mm-2 mm. By adopting the distance, the butt joint can be formed under the condition that the laser is ensured to fully melt the retained blade and the compensation body, and the good combination of the retained blade and the compensation body is realized.
The compensation body of the single body structure is provided with machining allowance, wherein the thickness of the machining allowance which can be machined in each direction is 0.5-3 mm.
Laser is focused on the position of the welding seam 5, so that the lap joint surface and the butt joint surface of the compensation body and the retention blade 11 are fully melted, and finally, a welding seam joint with the strength meeting the requirement and good toughness is formed.
Example 2
As shown in fig. 3 and 4, in this embodiment, the compensating body 1 for saving the blade surface as a spatial curved surface structure replacement repair is selected as a multi-body structure compensating body.
The multi-body structure compensation body comprises a first lapping body 2, a second lapping body 3 and a butt-joint body 4, wherein the second lapping body 3 and the butt-joint body 4 are a whole, and a welding seam 5 is arranged between the first lapping body 2 and the butt-joint body 4. One side of the welding seam 5 is a first lap joint body side surface 9, and the other side is a butt joint body side surface. The multi-body structure compensation body is provided with a clamping groove 1, the upper side wall of the clamping groove 1 is a first lapping body 2, the lower side wall of the clamping groove 1 is a second lapping body 3, and the rest part of the multi-body structure compensation body is a butt joint body 4.
The upper bottom surface 7 of the clamping groove (namely the lower surface of the first lapping body 2) is jointed with the upper surface of the retaining blade 11; the lower bottom surface 8 of the clamping groove (namely the upper surface of the second lapping body) is attached to the lower surface of the reserved blade 11, the side surface 6 of the clamping groove is attached to the cutting surface of the reserved blade 11, and the side surface 9 of the first lapping body is attached to the upper portion of the side surface 10 of the butting body.
The vertical distance between the upper surface of the reserved blade 11 and the upper surface of the multi-body structure compensation body 2 is 0.5 mm-3 mm, and the vertical distance between the lower surface of the reserved blade and the lower surface of the compensation body is 1 mm-2 mm. By adopting the distance, the butt joint can be formed under the condition that the laser is ensured to fully melt the retained blade and the compensation body, and the good combination of the retained blade and the compensation body is realized.
The multi-body structure compensation body which can be assembled by a plurality of parts is provided with machining allowance, wherein the thickness of the machining allowance which can be machined in each direction is 0.6-5 mm.
The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (6)
1. The lap-joint composite integrated compensation body for damage of the engine disc is characterized by comprising a first lap-joint body (2), a second lap-joint body (3) and a butt-joint body (4), wherein the second lap-joint body (3) is positioned below the first lap-joint body (2), the butt-joint body (4) is connected to the same side of the first lap-joint body (2) and the second lap-joint body (3), the first lap-joint body (2), the second lap-joint body (3) and the butt-joint body (4) are enclosed to form a clamping groove (1), the clamping groove (1) is used for inserting a retained blade (11), a cutting surface of the retained blade (11) is attached to the side surface of the clamping groove (1), and a welding seam (5) is arranged between the first lap-joint body (2) and the butt-joint body (4); the first lap joint body (2) and the butt joint body (4) are completely isolated by a welding seam (5); when the reserved blade (11) is inserted into the clamping groove (1), the upper bottom surface (7) of the clamping groove is attached to the upper surface of the reserved blade (11), and the lower bottom surface (8) of the clamping groove is attached to the lower surface of the reserved blade (11).
2. The lap-joint composite integrated compensation body for the damage of the engine disc according to claim 1, characterized in that when the retaining blade (11) is inserted into the clamping groove (1), the vertical distance between the upper surface of the retaining blade (11) and the upper surface of the first lap-joint body (2) is 0.5 mm-3 mm.
3. The lap-joint composite integrated compensation body for the damage of the engine disc according to claim 1, characterized in that when the retaining blade (11) is inserted into the slot (1), the vertical distance between the lower surface of the retaining blade (11) and the lower surface of the second lap-joint body (3) is 1 mm-2 mm.
4. Lap-on composite integral compensation body for engine disc damage according to claim 1, characterized in that said weld seam (5) has a width comprised between 0.5 mm and 3 mm.
5. The lap-joint composite integrated compensation body for engine disc damage according to claim 1 or 4, characterized in that the width of the weld seam (5) is 1 mm-2 mm.
6. The lap-joint composite integrated compensation body for the damage of the engine disc as claimed in claim 1, wherein the composite integrated compensation body is provided with machining allowance, and the machining allowance in each direction is 0.5 mm-3 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010481293.5A CN111594273B (en) | 2020-05-31 | 2020-05-31 | Lapping and combining integrated compensation body for damage of engine disc |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010481293.5A CN111594273B (en) | 2020-05-31 | 2020-05-31 | Lapping and combining integrated compensation body for damage of engine disc |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111594273A CN111594273A (en) | 2020-08-28 |
| CN111594273B true CN111594273B (en) | 2022-01-25 |
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| CN202010481293.5A Active CN111594273B (en) | 2020-05-31 | 2020-05-31 | Lapping and combining integrated compensation body for damage of engine disc |
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Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2889091B1 (en) * | 2005-07-29 | 2007-10-19 | Snecma | PROCESS FOR REPAIRING A VANE OF A MONOBLOC TURBOMACHINE AIRBORNE DISC AND TEST FOR CARRYING OUT THE PROCESS |
| US9797253B2 (en) * | 2014-09-17 | 2017-10-24 | General Electric Company | System and method for repairing blades |
| US10400628B2 (en) * | 2016-04-08 | 2019-09-03 | Hamilton Sundstrand Corporation | Method for weld repairing a turbine housing of an air cycle machine |
| CN108372386B (en) * | 2016-12-21 | 2020-03-17 | 中国航空制造技术研究院 | Blisk linear friction welding repair method |
| CN108372387A (en) * | 2017-01-04 | 2018-08-07 | 中国航空制造技术研究院 | A kind of engine blade patching type restorative procedure |
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