CN108437497B - Typical damage repair process for reverse thrust grid of engine - Google Patents
Typical damage repair process for reverse thrust grid of engine Download PDFInfo
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- CN108437497B CN108437497B CN201810226334.9A CN201810226334A CN108437497B CN 108437497 B CN108437497 B CN 108437497B CN 201810226334 A CN201810226334 A CN 201810226334A CN 108437497 B CN108437497 B CN 108437497B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/02—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using liquid or paste-like material
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- 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
- B23P6/00—Restoring or reconditioning objects
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- 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
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
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- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Reinforced Plastic Materials (AREA)
Abstract
The invention discloses a typical damage repair process for a reverse thrust grid of an engine, which comprises the following steps: 1) determining the typical damage type of an engine reverse thrust grid; 2) for hyperboloid edge aperture damage, its maintenance mode includes: 2.1 grid shape maintenance; 2.2 repairing the outer surface of the grating; 2.3 repairing the inner surface of the grating; 3) for the damage of the metal guide vane, the maintenance mode comprises 3.1, selecting the metal guide vane with partial damage, and removing the damaged part; 3.2, drawing the outline of the grating by utilizing three-dimensional scanning, and designing the outline of the metal joint according to the outline of the grating; 3.3, manufacturing a metal joint by adopting numerical control machining, and reinforcing the damaged metal guide vane by the metal joint. The repair process can repair the damage typical of the reverse thrust grid of the engine.
Description
Technical Field
The invention belongs to the technical field of airplane maintenance, and particularly relates to a typical damage repairing process for a reverse thrust grid of an engine.
Background
Because the thrust reverser airflow driven by the fan when the airplane is on the ground is very large in force borne by the thrust reverser of the engine, foreign objects are easily eroded and damaged on the thrust reverser grille, the thrust reverser grille (shown in figure 1) of the engine is easily damaged after long-time use, the repair cost of the thrust reverser grille is high, and the repair period can seriously influence the operation condition of the whole fleet. The research on the repair technology of the reverse thrust grid of the V2500 engine can not only reduce the maintenance cost, but also ensure the maintenance quality.
The grille is an important component of the engine thrust reversal component and plays a role in making the airflow of the engine jet reversely at a certain included angle, unloading thrust and providing reverse thrust. Each grid is provided with a series of guide vanes with the same shape, and the guide vanes fold the bypass airflow to the front to generate reverse thrust. The airflow guide on each grille is different, and the direction of the reverse thrust airflow at different positions in the circumferential direction can be controlled, so that the required stable braking effect can be generated, and the safe operation of the airplane and the engine is not influenced.
When a V2500 engine is repaired and refurbished in a reverse thrust mode, damage such as cracks or grooves of the reverse thrust grid of the engine is often found. The grid is a winding type complex carbon fiber laminated plate structure, and the grid repair difficulty is very large due to the characteristics of multiple curved surfaces and small area.
No relevant grid REPAIR methods are given in the CMM manual, and the SRM manual also has only 5 grid-related REPAIR solutions (reparar 027, reparar 028, reparar 050, reparar 052, reparar 064). But in practice there are only two REPAIR options available, REPAIR options available in respect of grids, REPAIR options available in REPAIR 027 and REPAIR 028, and they have strong limitations. REPAIR 027 requires that the crack or groove depth not exceed 12.7mm and also has high requirements at the REPAIR site: the front and rear edges of the grating can not be repaired within 76.2mm, and the transverse and longitudinal joints of the grating can not be repaired within 3.175mm, so the reparable range of REPAIR 027 is very small. REPAIR 028 requires that the depth of the crack or groove exceed 12.7mm and the guide vane is cut off, but two continuous guide vanes cannot be cut off, and at most 3 guide vanes can be cut off on each grid.
Therefore, the typical damage of the grating (damage of the hyperboloid edge aperture and damage of the continuous metal guide vane) needs to be researched urgently.
Disclosure of Invention
The invention aims to provide a repairing process for typical damage of a reverse thrust grid of an engine, which can repair the typical damage of the grid.
The above object of the present invention is achieved by the following technical solutions: a typical damage repair process for an engine thrust reverser grille comprises the following steps:
1) determining typical damage types of a reverse thrust grid of an engine, including hyperboloid edge aperture damage and metal guide vane damage;
2) for hyperboloid edge aperture damage, its maintenance mode includes:
2.1, keeping the shape of the grid in the grid close to the damaged area of the aperture at the edge of the hyperboloid, arranging a separation adhesive film or a separation adhesive tape in the grid, and arranging filling adhesive in the separation adhesive film or the separation adhesive tape;
2.2, repairing the outer surface of the grid, namely repairing the aperture damaged area of the hyperboloid edge from the outer surface, firstly polishing the slope, after polishing is finished, spreading carbon fiber prepreg to the slope layer by layer from the outer surface of the aperture damaged area to form a filling layer, arranging a carbon fiber reinforced layer and a glass fiber polishing layer outside the filling layer, curing, polishing and finishing after curing, and completing the repairing of the outer surface of the grid;
2.3 repairing the inner surface of the grid to remove the filling adhesive and the separation membrane in the grid, repairing the damaged area of the edge aperture of the hyperboloid from the inner surface, respectively arranging the carbon fiber impregnated with the epoxy resin as a repairing layer and the glass fiber impregnated with the epoxy resin as a polishing layer on the inner surface of the repairing area of the grid, curing, polishing and finishing after curing, and finishing the repairing of the inner surface of the grid;
3) for the damage of the metal guide vane, the maintenance method comprises the following steps:
3.1, selecting a metal guide vane with partial damage, and removing the damaged part;
3.2, drawing the outline of the grating by utilizing three-dimensional scanning, and designing the outline of the metal joint according to the outline of the grating;
3.3, manufacturing a metal joint by adopting numerical control machining, and reinforcing the damaged metal guide vane by the metal joint.
In the typical damage repair process for the thrust reversal grid of the engine:
the piece number of the separation adhesive film in the step (2.1) is QZ 5111.
The part number of the filled glue in the step (2.1) is EC 3524B/A.
The carbon fiber prepreg in the step (2.2) is 14 layers of carbon fiber prepregs (prepreg part number: F155-76), and the lap joint size of each layer is 0.90 +/-0.10 mm.
In the step (2.2), the curing temperature is 115.5-126.6 ℃, and the curing time is 60-90 min.
The epoxy resin in the step (2.3) is the epoxy resin with the model number of EA 9396.
In the step (2.3), the curing temperature is 65.6-76.7 ℃, and the curing time is 60-90 min.
And (3) arranging a pressure equalizing plate which plays a role of balancing pressure application above the repair area of the grating during curing in the step (2.2) and the step (2.3).
Compared with the prior art, the invention has the following advantages:
(1) the repair process can ensure the reliability of the reversed grating after repair, expand the repair range of the grating and greatly reduce the maintenance cost of the grating;
(2) the repair process can ensure the appearance of the grating, and does not generate secondary damage to the original structure in the repair engineering;
(3) the repairing process can complete the repairing of the damage of the continuous metal guide vane and eliminate technical blind spots.
Drawings
FIG. 1 is a schematic representation of an engine thrust reverser grille in accordance with the present invention;
FIG. 2 is a schematic view of the invention for structural filling of a grid (separation glue film or separation tape and structural filling glue);
FIG. 3 is a schematic diagram of a grating of the present invention after slope grinding of the damaged area of the hyperboloid edge aperture;
FIG. 4 is a schematic view of the repair of the outer surface of the grid of the present invention;
FIG. 5 is a schematic view of the repair of the inner surface of the grid in accordance with the present invention;
FIG. 6 is a schematic view of two damages of the metal guide vane of the present invention;
FIG. 7 is a schematic view of the structure of the joint in example 1;
FIG. 8 is a schematic view of the joint repair metal guide vane of example 1 showing damage to one of the guide vanes;
FIG. 9 is a schematic view of the structure of a joint in example 2;
FIG. 10 is a schematic view showing repair of another damage to a metal guide vane by the joint in example 2;
FIG. 11 is a schematic view showing a damaged metallic guide vane repaired in example 1-2.
Detailed Description
Example 1
A typical damage repair process for an engine thrust reverser grille comprises the following steps:
1) determining typical damage types of a reverse thrust grid of an engine, including hyperboloid edge aperture damage and metal guide vane damage;
2) for hyperboloid edge aperture damage, its maintenance mode includes:
2.1 the grid profile is maintained in the grid close to the double-curved-surface edge aperture damage area, a separation glue film (not shown in the figure) is arranged in the grid, and filling glue 1 (filling glue part number EC 3524B/A) is arranged in the separation glue film (separation glue part number QZ5111), as shown in FIG. 2;
2.2 repairing the outer surface of the grid, namely repairing the damaged area 2 of the aperture of the hyperboloid edge from the outer surface, firstly polishing the slope, after polishing, paving carbon fiber prepregs 3 on the outer surface of the damaged area of the aperture layer by layer to the slope to form a filling layer, arranging a carbon fiber reinforced layer 4 and a glass fiber polishing layer 5 outside the filling layer, as shown in fig. 4, curing, polishing and finishing after curing, and completing the repairing of the outer surface of the grid;
the curing temperature is 115.5-126.6 ℃, and the curing time is 60-90 min.
Wherein the carbon fiber is 14 layers of carbon fiber prepreg (prepreg part number: F155-76), and the lap joint size of each layer is 0.90 +/-0.10 mm.
2.3 repairing the inner surface of the grid, removing the filling adhesive and the separation adhesive film in the grid, repairing the damaged area of the edge aperture of the hyperboloid from the inner surface, using the carbon fiber impregnated with the epoxy resin as a repairing layer 6, using the glass fiber impregnated with the epoxy resin as a polishing layer 7, respectively arranging the carbon fiber and the glass fiber on the inner surface of the repairing area of the grid as shown in FIG. 5, then curing, polishing and finishing after curing, and finishing the repairing of the inner surface of the grid;
the epoxy resin is an epoxy resin with the model number EA 9396.
The curing temperature is 65.6-76.7 ℃, and the curing time is 60-90 min.
3) For the damage of the metal guide vane, the maintenance method comprises the following steps:
3.1, selecting a metal guide vane 8 with partial damage, and removing the damaged part, as shown in figure 6;
3.2, drawing the outline of the grating by utilizing three-dimensional scanning, and designing the outline of the metal joint according to the outline of the grating;
3.3, manufacturing a metal joint 9 by adopting numerical control machining, as shown in fig. 7, and reinforcing the damaged metal guide vane by the metal joint, as shown in fig. 8 and 11.
Example 2
A typical damage repair process for an engine thrust reverser grille comprises the following steps:
1) determining typical damage types of a reverse thrust grid of an engine, including hyperboloid edge aperture damage and metal guide vane damage;
2) for hyperboloid edge aperture damage, its maintenance mode includes:
2.1 the shape of the grid is kept in the grid close to the damaged area of the aperture at the edge of the hyperboloid, a blue high-temperature separation adhesive tape is arranged in the grid, and filling glue is arranged in the adhesive tape, as shown in FIG. 2;
wherein the blue adhesive tape is AIRIECH Flashbreaker 1R, and the filling adhesive is EC 3524B/A.
The method for filling the adhesive by using the blue adhesive tape and the structure can ensure the strength of the filling structure and effectively prevent the secondary damage to the original structure.
2.2 repairing the outer surface of the grid, namely repairing the damaged area of the aperture of the hyperboloid edge from the outer surface, firstly polishing the slope, after polishing, spreading carbon fiber prepreg to the slope layer by layer from the outer surface of the damaged area of the aperture to form a filling layer, arranging a carbon fiber reinforced layer and a glass fiber polishing layer outside the filling layer, as shown in fig. 4, curing, polishing and finishing after curing, and completing the repairing of the outer surface of the grid;
the curing temperature is 115.5-126.6 ℃, and the curing time is 60-90 min.
The carbon fibers are 14 layers of carbon fiber prepregs, and the lap joint size of each layer is 0.90 +/-0.10 mm.
2.3 repairing the inner surface of the grid, removing the filling adhesive and the blue adhesive tape in the grid, repairing the damaged area of the edge aperture of the hyperboloid from the inner surface, using the carbon fiber impregnated with the epoxy resin as a repairing layer and the glass fiber impregnated with the epoxy resin as a polishing layer, respectively arranging the repairing layers on the inner surface of the repairing area of the grid as shown in figure 5, then curing, polishing and finishing after curing, and finishing the repairing of the inner surface of the grid;
the carbon fibers are 14 layers of carbon fiber prepregs, and the lap joint size of each layer is 0.90 +/-0.10 mm.
The epoxy resin is an epoxy resin with the model number EA 9396.
The curing temperature is 65.6-76.7 ℃, and the curing time is 60-90 min.
And (3) a pressure equalizing plate for balancing and pressing is arranged above the repair area of the grating during curing in the step (2.2) and the step (2.3).
The pressure equalizing plate can be an aluminum plate with the thickness of 1.6-2.5 mm, and can be a forming template for manufacturing a corresponding area on the outer surface of the grating.
3) For the damage of the metal guide vane, the maintenance method comprises the following steps:
3.1, selecting a metal guide vane 8 with partial damage, and removing the damaged part, as shown in figure 6;
3.2, drawing the outline of the grating by utilizing three-dimensional scanning, and designing the outline of the metal joint according to the outline of the grating;
3.3, manufacturing a metal joint 9 by adopting numerical control machining, as shown in fig. 9, and reinforcing the damaged metal guide vane by the metal joint as shown in fig. 10 and 11.
Example 3
A typical damage repair process for an engine thrust reverser grille comprises the following steps:
1) determining the typical damage type of the reverse thrust grid of the engine as the damage of the hyperboloid edge aperture;
2) for hyperboloid edge aperture damage, its maintenance mode includes:
2.1 the shape of the grid is kept in the grid close to the damaged area of the aperture at the edge of the hyperboloid, a blue high-temperature separation adhesive tape is arranged in the grid, and filling glue is arranged in the adhesive tape, as shown in FIG. 2;
wherein the blue adhesive tape is AIRIECH Flashbreaker 1R, and the filling adhesive is EC 3524B/A.
The method for filling the adhesive by using the blue adhesive tape and the structure can ensure the strength of the filling structure and effectively prevent the secondary damage to the original structure.
2.2 repairing the outer surface of the grid, namely repairing the damaged area of the aperture of the hyperboloid edge from the outer surface, firstly polishing the slope, after polishing, spreading carbon fiber prepreg to the slope layer by layer from the outer surface of the damaged area of the aperture to form a filling layer, arranging a carbon fiber reinforced layer and a glass fiber polishing layer outside the filling layer, as shown in fig. 4, curing, polishing and finishing after curing, and completing the repairing of the outer surface of the grid;
the curing temperature is 115.5-126.6 ℃, and the curing time is 60-90 min.
2.3 repairing the inner surface of the grid, removing the filling adhesive and the blue adhesive tape in the grid, repairing the damaged area of the edge aperture of the hyperboloid from the inner surface, using the carbon fiber impregnated with the epoxy resin as a repairing layer and the glass fiber impregnated with the epoxy resin as a polishing layer, respectively arranging the repairing layers on the inner surface of the repairing area of the grid as shown in figure 5, then curing, polishing and finishing after curing, and finishing the repairing of the inner surface of the grid;
the epoxy resin is an epoxy resin with the model number EA 9396.
The curing temperature is 65.6-76.7 ℃, and the curing time is 60-90 min.
3) For the damage of the metal guide vane, the maintenance method comprises the following steps:
3.1, selecting a metal guide vane with partial damage, and removing the damaged part;
3.2, drawing the outline of the grating by utilizing three-dimensional scanning, and designing the outline of the metal joint according to the outline of the grating;
3.3, manufacturing a metal joint by adopting numerical control machining, and reinforcing the damaged metal guide vane by the metal joint.
The present invention is illustrated by the following examples, which are not intended to limit the scope of the invention. Other insubstantial modifications and adaptations of the present invention can be made without departing from the scope of the present invention.
Claims (8)
1. A typical damage repairing process for a thrust reversal grille of an engine is characterized by comprising the following steps:
1) determining typical damage types of a reverse thrust grid of an engine, including hyperboloid edge aperture damage and metal guide vane damage;
2) for hyperboloid edge aperture damage, its maintenance mode includes:
2.1, keeping the shape of the grid in the grid close to the damaged area of the aperture at the edge of the hyperboloid, arranging a separation adhesive film or a separation adhesive tape in the grid, and arranging filling adhesive in the separation adhesive film or the separation adhesive tape;
2.2, repairing the outer surface of the grid, namely repairing the aperture damaged area of the hyperboloid edge from the outer surface, firstly polishing the slope, after polishing is finished, spreading carbon fiber prepreg to the slope layer by layer from the outer surface of the aperture damaged area to form a filling layer, arranging a carbon fiber reinforced layer and a glass fiber polishing layer outside the filling layer, curing, polishing and finishing after curing, and completing the repairing of the outer surface of the grid;
2.3 repairing the inner surface of the grid to remove the filling adhesive and the separation membrane in the grid, repairing the damaged area of the edge aperture of the hyperboloid from the inner surface, respectively arranging the carbon fiber impregnated with the epoxy resin as a repairing layer and the glass fiber impregnated with the epoxy resin as a polishing layer on the inner surface of the repairing area of the grid, curing, polishing and finishing after curing, and finishing the repairing of the inner surface of the grid;
3) for the damage of the metal guide vane, the maintenance method comprises the following steps:
3.1, selecting a metal guide vane with partial damage, and removing the damaged part;
3.2, drawing the outline of the grating by utilizing three-dimensional scanning, and designing the outline of the metal joint according to the outline of the grating;
3.3, manufacturing a metal joint by adopting numerical control machining, and reinforcing the damaged metal guide vane by the metal joint.
2. The process for repairing typical damage to an engine thrust reverser grate as claimed in claim 1, wherein: the type of the separation adhesive film in the step (2.1) is QZ 5111.
3. The process for repairing typical damage to an engine thrust reverser grate as claimed in claim 1, wherein: the type of the filling adhesive in the step (2.1) is EC 3524B/A.
4. The process for repairing typical damage to an engine thrust reverser grate as claimed in claim 1, wherein: the carbon fiber prepreg in the step (2.2) is 14 layers of carbon fiber prepregs, and the lap joint size of each layer is 0.90 +/-0.10 mm.
5. The process for repairing typical damage to an engine thrust reverser grate as claimed in claim 1, wherein: in the step (2.2), the curing temperature is 115.5-126.6 ℃, and the curing time is 60-90 min.
6. The process for repairing typical damage to an engine thrust reverser grate as claimed in claim 1, wherein: the epoxy resin in the step (2.3) is the epoxy resin with the model number of EA 9396.
7. The process for repairing typical damage to an engine thrust reverser grate as claimed in claim 1, wherein: in the step (2.3), the curing temperature is 65.6-76.7 ℃, and the curing time is 60-90 min.
8. The process for repairing typical damage to an engine thrust reverser grate as claimed in claim 1, wherein: and (3) arranging a pressure equalizing plate which plays a role of balancing pressure application above the repair area of the grating during curing in the step (2.2) and the step (2.3).
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| CN113085229B (en) * | 2021-04-22 | 2022-02-15 | 同济大学 | Device and method for repairing layered damage of carbon fiber reinforced thermosetting resin-based composite material |
| CN113978754B (en) * | 2021-10-27 | 2023-11-21 | 大新华飞机维修服务有限公司 | Repairing process for return air grille of passenger cabin of Boeing 737 passenger plane |
| CN114227138B (en) * | 2021-11-24 | 2022-12-06 | 中国南方航空股份有限公司 | Typical damage repair process for reverse-thrust sliding rail beam of engine |
| CN114368174B (en) * | 2021-11-24 | 2023-12-26 | 中国南方航空股份有限公司 | Hyperboloid shape recovery method for repairing tip of translation door of V2500 engine |
| CN114211784B (en) * | 2021-12-13 | 2024-05-28 | 中国人民解放军陆军航空兵学院 | Helicopter skin bullet hole repairing process |
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| US20080233346A1 (en) * | 2007-03-23 | 2008-09-25 | United Technologies Corporation | Repair of a composite sandwich structure having a perforated skin |
| CN102649342A (en) * | 2011-02-24 | 2012-08-29 | 成都飞机工业（集团）有限责任公司 | Patching and repairing method for local damage of carbon-fiber reinforced resin base laminating plate |
| JP2014188996A (en) * | 2013-03-28 | 2014-10-06 | Mitsubishi Aircraft Corp | Honeycomb core sandwich structure repair method, and repair result |
| CN105153950A (en) * | 2015-09-26 | 2015-12-16 | 刘龙权 | Repairing structure with composite repairing piece and method for forming repairing structure |
| CN206736396U (en) * | 2017-04-14 | 2017-12-12 | 安徽淮海奥可装备再制造有限公司 | A kind of device for being used to repair workpiece surface damage |
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