CN110561796B - Reinforcing and repairing method for damaged composite material blade skin - Google Patents

Reinforcing and repairing method for damaged composite material blade skin Download PDF

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Publication number
CN110561796B
CN110561796B CN201910890113.6A CN201910890113A CN110561796B CN 110561796 B CN110561796 B CN 110561796B CN 201910890113 A CN201910890113 A CN 201910890113A CN 110561796 B CN110561796 B CN 110561796B
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China
Prior art keywords
area
blade
skin
filling
core material
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CN201910890113.6A
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CN110561796A (en
Inventor
刘启迪
任淼
康健
李丽丽
颜佳瑶
吕楠
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Harbin Hafei Aviation Industry Co Ltd
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Harbin Hafei Aviation Industry Co Ltd
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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
    • B29C73/04—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 preformed elements
    • 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
    • B29C73/24—Apparatus or accessories not otherwise provided for
    • 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
    • B29C73/24—Apparatus or accessories not otherwise provided for
    • B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
    • 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
    • B29C73/24—Apparatus or accessories not otherwise provided for
    • B29C73/30—Apparatus or accessories not otherwise provided for for local pressing or local heating
    • 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
    • B29C73/24—Apparatus or accessories not otherwise provided for
    • B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
    • B29C2073/262—Apparatus or accessories not otherwise provided for for mechanical pretreatment for polishing, roughening, buffing or sanding the area to be repaired
    • 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
    • B29C73/24—Apparatus or accessories not otherwise provided for
    • B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
    • B29C2073/264—Apparatus or accessories not otherwise provided for for mechanical pretreatment for cutting out or grooving the area to be repaired

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)

Abstract

The invention belongs to a repair technology of a composite material blade of a rotor system, and relates to a composite material blade skin and an enhancement method after damage of the composite material blade skin is filled in the composite material blade. The method comprises the following steps: after the damaged area is cleaned, a filling area is formed; laying adhesive films in the filling area, wherein the adhesive films cover the bottom surface and the side surface of the core material filling area; filling a core material in a core material filling area, and laying an adhesive film material in the whole repairing area above the filled core material, wherein the adhesive film material covers all skin damage areas; covering the filling core material and the blade structure body in the butt joint area with the skin prepreg. The filling core material is used for smoothing small step difference between the filling core material and the blade structure.

Description

Reinforcing and repairing method for damaged composite material blade skin
Technical Field
The invention belongs to a repair technology of a composite material blade of a rotor system, and relates to a composite material blade skin and an enhancement method after damage of the composite material blade skin is filled in the composite material blade.
Background
The composite material paddle is mainly formed by die pressing structural components such as a skin, a crossbeam, a foam core, a front edge wrapping sheet and the like. The covering skin covers the outer surface of the whole blade, is an important component of the composite material blade, ensures the integral aerodynamic appearance of the blade, and greatly contributes to the torsional rigidity and the shimmy rigidity of the blade.
In the use process of the composite material paddle, the damage condition of the skin and the internal foam core structure is easy to occur, and the structural rigidity, the strength, the fatigue life and the flight safety of the paddle are greatly influenced.
In the traditional method, repair glue is generally injected into the local part of the skin of the damaged area for repair, the repair method has simple process, but has the problems of limited repair area, concentrated local stress, easy secondary debonding, large blade weight increment and the like; for the condition that the damaged area is slightly large, the skin and the foam are generally repaired by adopting a method of locally patching the skin and the foam, the repairing method can deal with the damaged condition of the skin and the foam core with slightly large area, but the post-patched foam is easy to have the defects of edge collapse, serious step difference and the like, and the repairing method has great influence on the strength, the pneumatic performance and the like of a blade repairing area.
Disclosure of Invention
The technical problems solved by the invention are as follows: avoid repairing regional stress concentration, prevent that the benefit foam edge after sinks to the influence to repairing intensity, furthest reduces the covering jump, avoids the influence to aerodynamic shape. The repair requirements on various skin damage conditions are met, and the stability of composite material blade skin damage repair is improved.
The technical scheme of the invention is as follows: a method for reinforcing and repairing a composite blade skin after damage, said method comprising the steps of:
after the damaged area is cleaned, a filling area is formed;
laying adhesive films in the filling area, wherein the adhesive films cover the bottom surface and the side surface of the core material filling area;
filling a core material in a core material filling area, and laying an adhesive film material in the whole repairing area above the filled core material, wherein the adhesive film material covers all skin damage areas;
covering the filling core material and the blade structure body in the butt joint area with the skin prepreg. The filling core material is used for smoothing small step difference between the filling core material and the blade structure.
Preferably, the skin prepreg covered above the butt joint area of the filler core material and the blade structure is a pre-cured material. The method has the advantages that the pre-cured skin prepreg has a certain supporting effect, wrinkles in the process of repairing the skin prepreg are avoided, and the strength of the lap joint position is reduced.
Preferably, the skin prepregs covered over the butt-joint region of the infill core and blade structure are symmetrically distributed on both sides of the butt-joint region. The method has the effects of ensuring uniform pressure transmission and avoiding instability of the filling core material.
Preferably, the side surface of the filling area is in a step shape, so that the repair of the skin prepreg is ensured to be overlapped layer by layer, and the bonding strength is increased.
Preferably the skin prepreg is located at 2/3 where the width of the step face is less than the width of the step face. The repair skin prepreg of the inner layer is ensured to completely cover the repair skin prepreg, and the adhesive force of the skin of the layer is not influenced.
Preferably, the method further comprises the steps of:
and paving an adhesive film on the skin prepreg covered above the butt joint area of the filling core material and the blade structure body, and paving the skin prepreg in the filling area. For restoring the full airfoil profile and providing sufficient adhesive.
Preferably, the method further comprises the steps of: and putting the filled blade into a prefabricated mould with the same theoretical shape as the blade for pressurization. The skin shape of the repair area is guaranteed to be repaired to be in a theoretical state, the step difference of the outer layer overlapping area is reduced, and the aerodynamic shape is guaranteed.
Preferably, the mould covers a localised region of the paddle. The heat affected zone is reduced, and meanwhile, unnecessary resource waste caused by integral heating of the blades is avoided.
Preferably, the mould covers a full section of the blade. Avoiding over-pressurization or over-burning of other unrepaired areas.
Preferably, the method further comprises the steps of: the blades are weighed before and after repair. And recording the weight change of the blade in the repair process, and accumulating data for the adjustment of the blade state later.
Drawings
FIG. 1 is a cross-sectional view of a damaged reinforcement repair ply for a composite blade skin;
wherein: 1-outer layer repair skin prepreg
2-intermediate layer repair skin prepreg
3-inner layer repair skin prepreg
4-surface adhesive film
5-precuring joint-covering prepreg
6-glue film for enhancing glue force
7-filling core material
8-covering and filling core material damage area
9-glue-joint glue film filled with core material
10-original skin
11-original skin peeled off in steps
12-filling core material butt-joint region
FIG. 2 is a cross-sectional view of a composite blade mold repair forming die.
Wherein: a-repairing blade
B-local mould pressing forming die
Detailed Description
The first step is as follows: the blade is weighed before repair. The purpose is to determine the total weight before repair, facilitating calculation of the weight gain during repair.
The second step is that: the damaged areas of the blade skins and the filling core materials are cleaned, the damaged areas are used as cleaning centers, all layers of skins outside the areas are cleaned layer by layer in a step mode, the cleaning range is gradually enlarged from the inner skins to the outer skins, and the cleaning areas are generally circular or rectangular and are as regular as possible. The step aims to remove all materials in the damaged area, ensure the overlapping requirement of the back-up skin structure and improve the bonding strength.
The third step: and laying a layer of adhesive film material on the inner surface of the filling core material gluing area. Aims to improve the adhesive force of the filling core material and control the adhesive amount.
The fourth step: and (4) laying the filling core material again in the glue area of the filling core material, wherein the shape of the filling core material is the same as that of the damaged area of the filling core material, and the mould pressing amount which is the same as that of the original filling core material is reserved in the height direction. The purpose is to ensure that the repair area is uniformly pressed and the pneumatic appearance of the blade is kept.
The fifth step: and measuring the outline dimension of the butt joint area of the filling core material, cutting a cover seam prepreg with the same shape and dimension and the width of 4/3 of a single step surface, and performing pre-curing treatment. The cover seam prepreg aims at protecting and filling a butt joint area of a core material and avoiding the wrinkle collapse of an inner layer repairing skin prepreg.
And a sixth step: and laying a layer of adhesive film material on the original skin 11 which is filled with the core material and stripped according to the steps. The adhesive is used for providing an adhesive between the repair area and the repair skin prepreg.
The seventh step: and laying a layer of pre-cured joint-covering prepreg symmetrically along the gap above the butt joint area of the filling core material, and laying a surface adhesive film on the upper surface of the pre-cured joint-covering prepreg. And the wrinkle collapse of the inner layer repair skin prepreg is avoided.
Eighth step: and (3) overlapping and laying a repair skin prepreg on the filling core material and the original skin 11 stripped according to the steps, wherein the material and the laying angle of each layer of the skin are the same as those of the original skin 10. The purpose is to change the raw material system to the minimum degree and ensure the bonding strength and the original rigidity of the blade.
The ninth step: and putting the laminated blade into a prefabricated local section mould with the same theoretical shape as the blade for pressurization. The aim is to restore the theoretical profile of the blade repair site.
The tenth step: and locally curing the blade repair area. The aim is to reduce the heat affected zone.
The eleventh step: and polishing and cleaning the flashes overflowing from the blade repairing area. The purpose is for guaranteeing paddle overall dimension, avoids the glue film too thick to lead to in the use droing.
The twelfth step: the cleaned blade was reweighed. The purpose is to record the weight change of the paddle in the repair process and to accumulate data for the adjustment of the state of the paddle in the future.
Example (b):
the implementation process of the invention is more fully explained with reference to the attached drawings, and specifically comprises the following steps:
the first step is as follows: and weighing the repaired blade A before repair, and recording the weight before repair.
The second step is that: and excavating and cleaning the damaged area 8 of the skin and the filled core material in the repaired blade A, taking the damaged area as a cleaning center, stripping the skin in the area, cleaning the original skin 11 stripped according to the steps outside the area layer by layer according to a step form, and gradually increasing the cleaning range from the inner skin to the outer skin, wherein the step width can be 15mm to 25 mm. The cleaning area is generally round or rectangular, and is as regular as possible.
The third step: integrally polishing and cleaning the damaged area 8 of the skin and the filling core material and the area of the original skin 11 stripped according to the steps; and a glue film 9 for gluing and filling the core material is integrally paved on the area 8 for removing the damage of the skin and the foam core.
The fourth step: and refilling the damaged area 8 of the skin and the filling core material with the filling core material 7, wherein the shape is the same as that of the cleaning area, and the mould pressing amount which is the same as that of the original filling core material is reserved.
The fifth step: and measuring the overall dimension of the butt joint area 12 of the filling core materials, cutting a piece of skin prepreg with the same shape and dimension and the width of 20mm, and pre-curing at a curing temperature slightly lower than the formal curing temperature to manufacture the pre-cured crack-covered prepreg 5.
And a sixth step: and a layer of adhesive film 6 for enhancing adhesive force is laid on the filling core material and the original skin stripped according to the steps and is overlapped with the original skin 11 stripped according to the steps on the outermost layer, and the overlapping width can be 15mm to 25 mm.
The seventh step: a layer of pre-cured joint-covering prepreg 5 is symmetrically laid above the filling core material butt joint area 12, and the surface of the prepreg is covered with a layer of surface adhesive film 4.
Eighth step: and sequentially laying an inner layer repair skin prepreg 3, an intermediate layer repair skin prepreg 2 and an outer layer repair skin prepreg 1 above the adhesive film 6 for enhancing the adhesive force, wherein the outer layer repair skin prepreg 1 and the adhesive film 6 for enhancing the adhesive force have the same size, and the material and the laying angle for each layer of repair skin prepreg are the same as those of the original skin.
The ninth step: and (3) putting the repaired blade A into a prefabricated local die pressing forming die B with the same theoretical appearance as the blade, and pressing.
The tenth step: and carrying out local formal curing on the repaired blade A.
The eleventh step: and polishing and cleaning the flash overflowing from the repair area of the repair blade A.
The twelfth step: the repaired blade a is reweighed and the repaired weight is recorded.
Example two:
when the upper and lower wing surfaces of the composite material blade to be repaired are damaged, debonded or formed through scars, the repair is carried out according to the following examples:
the first step is as follows: and (4) performing paint removal treatment on the blade skin damage area, and weighing before repairing.
The second step is that: and cleaning the damaged area of the blade skin, taking the damaged area as a cleaning center, stripping the upper and lower airfoil skin of the area, cleaning the skins outside the area layer by layer according to a step form, and gradually increasing the cleaning range from the inner skin to the outer skin.
The third step: and laying a layer of adhesive film material on the whole area for removing the filling core material.
The fourth step: preferentially processing the side with larger damage area; if the areas are the same, the lower airfoil surface is preferentially treated. And returning the blade to the forming die, wherein the surface to be repaired faces upwards.
The fifth step: and refilling the core material in the core material cleaning area, wherein the shape of the core material cleaning area is the same as that of the core material cleaning area, and the mold pressing amount of the core material cleaning area is kept the same as that of the core material filling area.
And a sixth step: measuring the outline dimension of the butt joint area of the filling core materials, cutting out a piece of skin prepreg with the same shape and dimension and a slightly wider width, and pre-curing at a curing temperature slightly lower than the formal curing temperature for later use.
The seventh step: and laying a layer of adhesive film material on all the skin removing areas, and overlapping with the outermost skin. And laying a pre-cured skin prepreg layer on the area to be covered with the seam, and covering a glue film layer on the surface of the skin prepreg layer.
Eighth step: and overlapping and laying skin prepreg materials on the whole repair area, wherein the size of the outermost layer of prepreg is the same as that of the glue film laid in the sixth step, and the material and laying angle of each layer of skin are the same as those of the original skin.
The ninth step: and (5) overturning the blade, and repairing the other surface of the blade according to the sixth step, the seventh step and the eighth step.
The tenth step: and putting the laid blade into a prefabricated local section mould with the same theoretical shape as the blade for pressurization.
The eleventh step: and locally curing the blade repair area.
The twelfth step: and polishing and cleaning the flashes overflowing from the blade repairing area.
The thirteenth step: and re-weighing and spraying paint on the cleaned blade.

Claims (6)

1. A method for reinforcing and repairing damaged composite material blade skin is characterized by comprising the following steps:
after the damaged area is cleaned, a filling area is formed;
laying adhesive films in the filling area, wherein the adhesive films cover the bottom surface and the side surface of the core material filling area;
filling a core material in a core material filling area, and laying an adhesive film material in the whole repairing area above the filled core material, wherein the adhesive film material covers all skin damage areas;
covering a gap-covered prepreg above a butt joint area of the filling core material and the blade structure body, wherein the gap-covered prepreg is a material subjected to pre-curing treatment; the cover seam prepreg is symmetrically distributed on two sides of the seam of the butt joint area;
and paving an adhesive film on the joint-covering prepreg, and paving a skin prepreg in the filling area.
2. The method for reinforcing and repairing the composite material blade skin after being damaged according to claim 1, wherein the side face of the filling area is stepped, and the width of the cover seam prepreg on the step face is smaller than 2/3 of the width of the step face.
3. The method of claim 2, further comprising the steps of: and putting the filled blade into a prefabricated mould with the same theoretical shape as the blade for pressurization.
4. The method as claimed in claim 3, wherein the form covers a localized area of the blade.
5. The method as claimed in claim 4, wherein the form covers a full area of the blade.
6. The method of claim 1, further comprising the steps of: the blades are weighed before and after repair.
CN201910890113.6A 2019-09-19 2019-09-19 Reinforcing and repairing method for damaged composite material blade skin Active CN110561796B (en)

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Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113734462B (en) * 2021-06-10 2023-08-15 江苏航空职业技术学院 Skin maintenance method for sports aircraft
CN113942657B (en) * 2021-10-09 2023-09-08 中国直升机设计研究所 Repair method for rear edge and tip rear edge of composite blade
CN114368173B (en) * 2021-11-24 2023-07-07 中国南方航空股份有限公司 Typical gradual change step type hyperbolic laminate structure penetrating damage repair process
CN113977993A (en) * 2021-11-26 2022-01-28 哈尔滨飞机工业集团有限责任公司 Method for repairing damage of single-closed-cavity foam sandwich structure

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CN105173109A (en) * 2014-06-06 2015-12-23 哈尔滨飞机工业集团有限责任公司 Repairing method for honeycomb sandwich structure
CN109514891A (en) * 2018-09-29 2019-03-26 中国人民解放军第五七九工厂 Contain casing inner surface high-temp glue restorative procedure outside a kind of composite material

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Publication number Priority date Publication date Assignee Title
US10265915B2 (en) * 2014-01-17 2019-04-23 Sikorsky Aircraft Corporation Composite bonded repair method

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Publication number Priority date Publication date Assignee Title
CN105173109A (en) * 2014-06-06 2015-12-23 哈尔滨飞机工业集团有限责任公司 Repairing method for honeycomb sandwich structure
CN109514891A (en) * 2018-09-29 2019-03-26 中国人民解放军第五七九工厂 Contain casing inner surface high-temp glue restorative procedure outside a kind of composite material

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