CN109628857A - A kind of pottery aluminium composite material aeroengine fan blades and preparation method thereof - Google Patents
A kind of pottery aluminium composite material aeroengine fan blades and preparation method thereof Download PDFInfo
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- CN109628857A CN109628857A CN201910039285.2A CN201910039285A CN109628857A CN 109628857 A CN109628857 A CN 109628857A CN 201910039285 A CN201910039285 A CN 201910039285A CN 109628857 A CN109628857 A CN 109628857A
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- Prior art keywords
- fan blades
- silicon carbide
- aeroengine
- aeroengine fan
- carbon fiber
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
- C22C47/02—Pretreatment of the fibres or filaments
- C22C47/04—Pretreatment of the fibres or filaments by coating, e.g. with a protective or activated covering
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D23/00—Casting processes not provided for in groups B22D1/00 - B22D21/00
- B22D23/04—Casting by dipping
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
- C04B35/56—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides
- C04B35/565—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide
- C04B35/571—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide obtained from Si-containing polymer precursors or organosilicon monomers
-
- C04B35/806—
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
- C22C47/02—Pretreatment of the fibres or filaments
- C22C47/06—Pretreatment of the fibres or filaments by forming the fibres or filaments into a preformed structure, e.g. using a temporary binder to form a mat-like element
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
- C22C47/08—Making alloys containing metallic or non-metallic fibres or filaments by contacting the fibres or filaments with molten metal, e.g. by infiltrating the fibres or filaments placed in a mould
- C22C47/12—Infiltration or casting under mechanical pressure
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5248—Carbon, e.g. graphite
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Organic Chemistry (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Ceramic Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Structural Engineering (AREA)
- Crystallography & Structural Chemistry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of pottery aluminium composite material aeroengine fan blades, it is made of carbon fiber, boundary layer, silicon carbide substrate and alloy matrix aluminum, it is characterized in that carbon fiber is woven into aeroengine fan blades precast body, boundary layer is wrapped in carbon fiber surface, silicon carbide substrate filling in situ is in aeroengine fan blades precast body, carbon fibre reinforced silicon carbide aeroengine fan blades porous body is formed, last alloy matrix aluminum is filled in carbon fibre reinforced silicon carbide aeroengine fan blades porous body.Carbon fiber is woven into aeroengine fan blades precast body by the present invention can significantly improve the impact flexibility, structural stability and performance reliability of blade, by silicon carbide substrate filling in situ into aeroengine fan blades precast body, it can effectively improve intensity, rigidity, hardness, temperature resistant capability and the impact resistant capability of blade, finally fill aluminium alloy, the porosity defects of blade interior are significantly reduced, the comprehensive performance of blade is effectively improved.
Description
Technical field
The present invention relates to a kind of aeroengine fan blades and preparation method thereof, in particular to a kind of pottery aluminium composite material
Aeroengine fan blades and preparation method thereof.
Background technique
Big Bypass Ratio Turbofan Engine is the core of large aircraft, is to determine that large aircraft develops the pass of success
Key.Low-density, high specific strength and the high specific stiffness that composite material has metal material incomparable, in order to reach the height of engine
Thrust ratio, low consumption oil cut rate, low noise, low maintenance cost needs, each major engine manufacturer, the world all widely popularize it is compound
Use of the material in big Bypass Ratio Turbofan Engine.Fan blade be the most important component of Modern Commercial Aircraft Engine ' it
One, according to statistics, fan section quality accounts for about the 30% ~ 35% of engine gross mass, and reducing fan section quality is to reduce engine quality
With the key means for improving engine efficiency, use is bigger, lighter fan blade has become the development trend of engine.Fan
The every loss of weight 1kg of blade, fancase and transmission system also accordingly reduce 1kg, while wing/fuselage of engine structure and aircraft
Structure also distinguishes loss of weight 0.5kg, this since to iterate effect extremely important to the loss of weight of aircraft for fan structure loss of weight bring.This
Outside, the main thrust of big Bypass Ratio Turbofan Engine will meet biggish bypass ratio from the cold air for flowing through by-pass air duct, it is necessary to
Using the fan of larger size.It therefore, is to realize the higher bypass ratio of engine and loss of weight only using composite material fan blade
One approach.
Currently, composite material fan blade mainly uses polymer matrix composites, or added using polymer matrix composites
Titanium alloy binding structure.Although it is excellent that this has given full play to that polymer matrix composites tensile strength is high, light-weight, damage tolerance is high etc.
Point, but polymer matrix composites rigidity is lower, hardness is low, lead to fan blade when rotated and may occur slight deformation with
And crash-protective characteristics decline.The impact resistance of polymer matrix composites blade although can be improved using titanium alloy bound edge, but
It is to increase the difficulty of fan blade preparation process, while the easily presence of the connection reliability of titanium alloy and polymer matrix composites is asked
Topic.
Pottery aluminium composite material is mainly made of carbon fiber, silicon carbide and aluminium alloy, has density low, and intensity is high, and modulus is high,
Good rigidity, the excellent characteristics such as fracture toughness is good, impact resistance is excellent, thermal expansion coefficient is low can be advantageously applied to aviation
Engine blower blade industry.
Authorization Notice No. is that the Chinese invention patent of CN104385619B discloses a kind of aero-engine composite material wind
The manufacturing method of fan leaf uniformly coats one layer of release agent and bloom gel coat in moulding press die cavity upper and lower surfaces first；Secondly will
Fan blade die is placed in lower mode cavity, and in its 29 fiber preform body of surface laying Kevlar, being acted on by pressure will
Epoxy resin injects in die cavity；Then moulding press is integrally placed in curing oven and is solidified, demoulding of coming out of the stove later；It is finally right
Fan blade after demoulding carries out simple Milling Process.
Application publication number is that the Chinese invention patent of CN108930664A discloses a kind of mixed structure aero-engine wind
Fan leaf comprising metal leading edge panel and composite portions, the metal leading edge panel and the composite portions with
The mode of interface connection is combined into one.
Application publication number is that the Chinese invention patent of CN108661945A discloses a kind of fan blade, the fan blade
Leading edge portion be made of metal material, blade face part along the fan blade thickness direction, by the composite material of front and back
The intermediate metallic core of clamping is made, and wherein the metal material of leading edge portion is made into integration with the metallic core.
Summary of the invention
To solve the above problems, the present invention proposes a kind of pottery aluminium composite material aeroengine fan blades and its preparation side
Method had not only given full play to the advantage that composite material is applied in aeroengine fan blades field, but also has improved aero-engine
The integrally-built stability of fan blade and anti-collision performance.
A kind of pottery aluminium composite material aeroengine fan blades, by carbon fiber, boundary layer, silicon carbide substrate and aluminium alloy
Matrix composition, it is characterised in that carbon fiber is woven into aeroengine fan blades precast body, and boundary layer is wrapped in carbon fiber surface
Face, silicon carbide substrate filling in situ form carbon fibre reinforced silicon carbide aviation hair in aeroengine fan blades precast body
Motivation fan blade porous body, it is porous that last alloy matrix aluminum is filled in carbon fibre reinforced silicon carbide aeroengine fan blades
In body；The aeroengine fan blades precast body carbon fibrous body fraction is 35 ~ 55%, and carbon fiber weaving manner is
2.5D, 3D, needled sewing close one of structure；The boundary layer is one of pyrolytic carbon, BN；The silicon carbide substrate
Volume fraction is 20 ~ 45%；The alloy matrix aluminum volume fraction is 15 ~ 40%.
A kind of preparation method for aluminium composite material aeroengine fan blades of making pottery, it is characterised in that including following sequences
Step:
(1) aeroengine fan blades graphite jig is prepared, carbon fiber is woven into aero-engine wind on graphite jig
Fan leaf precast body；
(2) interfacial layer, depositing temperature are prepared in aeroengine fan blades precast body using chemical vapor infiltration
It is 600 ~ 1000 DEG C；
(3) precursor infiltration and pyrolysis method is used, using Polycarbosilane as precursor, in the aerial engine fan for preparing boundary layer
Filling in situ silicon carbide substrate in blade precast body, cracking temperature is 900 ~ 1200 DEG C, or uses chemical vapor infiltration, with
Trichloromethyl silane is source gas, and filling in situ is silicon carbide-based in the aeroengine fan blades precast body for preparing boundary layer
Body, depositing temperature are 800 ~ 1200 DEG C, obtain carbon fibre reinforced silicon carbide aeroengine fan blades porous body；
(4) the carbon fibre reinforced silicon carbide aeroengine fan blades porous body prepared is subjected to surface numerical control finishing,
And be cleaned by ultrasonic with dehydrated alcohol, then dried in vacuum drying oven；
(5) the carbon fibre reinforced silicon carbide aeroengine fan blades porous body dried in step (4) is packed into moulds of industrial equipment
In, it is then placed in vacuum gas pressure infiltration furnace, is evacuated to 0.01 ~ 10Pa, be preheated to 400 ~ 700 DEG C and keep the temperature 0.5 ~ 2h, it will
Molten aluminium alloy is poured into moulds of industrial equipment, filling air pressure to 0.5 ~ 3.0MPa, and 0.5 ~ 2h of pressure maintaining, and tooling mould is removed after cooling
Tool obtains pottery aluminium composite material aeroengine fan blades.
Carbon fiber, which is woven into aeroengine fan blades precast body, the invention has the advantages that: (1) to significantly improve
Impact flexibility, structural stability and the performance reliability of blade；(2) by silicon carbide substrate filling in situ to aerial engine fan
In blade precast body, intensity, rigidity, hardness, temperature resistant capability and the impact resistant capability of blade can effectively improve；(3) using true
Empty gas pressure infiltration aluminium alloy can effectively exclude the porous intracorporal gas of carbon fibre reinforced silicon carbide aeroengine fan blades
Body avoids forming porosity defects in blade interior, effectively improves the comprehensive performance of blade.
Specific embodiment
A kind of pottery aluminium composite material aeroengine fan blades, by carbon fiber, boundary layer, silicon carbide substrate and aluminium alloy
Matrix composition, it is characterised in that carbon fiber is woven into aeroengine fan blades precast body, and boundary layer is wrapped in carbon fiber surface
Face, silicon carbide substrate filling in situ form carbon fibre reinforced silicon carbide aviation hair in aeroengine fan blades precast body
Motivation fan blade porous body, it is porous that last alloy matrix aluminum is filled in carbon fibre reinforced silicon carbide aeroengine fan blades
In body；The aeroengine fan blades precast body carbon fibrous body fraction is 40%, and carbon fiber weaving manner is 3D knot
Structure；The boundary layer is pyrolytic carbon；The silicon carbide substrate volume fraction is 35%；The alloy matrix aluminum volume point
Number is 22%.
A kind of preparation method for aluminium composite material aeroengine fan blades of making pottery, it is characterised in that including following sequences
Step:
(1) aeroengine fan blades graphite jig is prepared, carbon fiber is woven into aero-engine wind on graphite jig
Fan leaf precast body；
(2) interfacial layer, depositing temperature are prepared in aeroengine fan blades precast body using chemical vapor infiltration
It is 900 DEG C；
(3) precursor infiltration and pyrolysis method is used, using Polycarbosilane as precursor, in the aerial engine fan for preparing boundary layer
Filling in situ silicon carbide substrate in blade precast body, cracking temperature are 1100 DEG C, obtain carbon fibre reinforced silicon carbide aeroplane engine
Machine fan blade porous body；
(4) the carbon fibre reinforced silicon carbide aeroengine fan blades porous body prepared is subjected to surface numerical control finishing,
And be cleaned by ultrasonic with dehydrated alcohol, then dried in vacuum drying oven；
(5) the carbon fibre reinforced silicon carbide aeroengine fan blades porous body dried in step (4) is packed into moulds of industrial equipment
In, it is then placed in vacuum gas pressure infiltration furnace, is evacuated to 1.0Pa, be preheated to 600 DEG C and keep the temperature 1h, molten aluminium alloy is poured
It infuses in moulds of industrial equipment, filling air pressure to 1.5MPa, and pressure maintaining 1h, moulds of industrial equipment is removed after cooling and obtain pottery aluminium composite material boat
Empty engine blower blade.
The above is only a specific embodiment of the present invention, but the design concept of the present invention is not limited to this, all to utilize this
Design makes a non-material change to the present invention, and should belong to the behavior for invading the scope of protection of the invention.But it is all not take off
Content from technical solution of the present invention, it is to the above embodiments according to the technical essence of the invention any type of simply to repair
Change, equivalent variations and remodeling, still falls within the protection scope of technical solution of the present invention.
Claims (2)
1. a kind of pottery aluminium composite material aeroengine fan blades, by carbon fiber, boundary layer, silicon carbide substrate and aluminium alloy base
Body composition, it is characterised in that carbon fiber is woven into aeroengine fan blades precast body, and boundary layer is wrapped in carbon fiber surface,
Silicon carbide substrate filling in situ forms carbon fibre reinforced silicon carbide aero-engine in aeroengine fan blades precast body
Fan blade porous body, last alloy matrix aluminum are filled in carbon fibre reinforced silicon carbide aeroengine fan blades porous body
In；The aeroengine fan blades precast body carbon fibrous body fraction be 35 ~ 55%, carbon fiber weaving manner be 2.5D,
3D, needled sewing close one of structure；The boundary layer is one of pyrolytic carbon, BN；The silicon carbide substrate volume
Score is 20 ~ 45%；The alloy matrix aluminum volume fraction is 15 ~ 40%.
2. a kind of preparation method for aluminium composite material aeroengine fan blades of making pottery, it is characterised in that the step including following sequences
It is rapid:
(1) aeroengine fan blades graphite jig is prepared, carbon fiber is woven into aero-engine wind on graphite jig
Fan leaf precast body；
(2) interfacial layer, depositing temperature are prepared in aeroengine fan blades precast body using chemical vapor infiltration
It is 600 ~ 1000 DEG C；
(3) precursor infiltration and pyrolysis method is used, using Polycarbosilane as precursor, in the aerial engine fan for preparing boundary layer
Filling in situ silicon carbide substrate in blade precast body, cracking temperature is 900 ~ 1200 DEG C, or uses chemical vapor infiltration, with
Trichloromethyl silane is source gas, and filling in situ is silicon carbide-based in the aeroengine fan blades precast body for preparing boundary layer
Body, depositing temperature are 800 ~ 1200 DEG C, obtain carbon fibre reinforced silicon carbide aeroengine fan blades porous body；
(4) the carbon fibre reinforced silicon carbide aeroengine fan blades porous body prepared is subjected to surface numerical control finishing,
And be cleaned by ultrasonic with dehydrated alcohol, then dried in vacuum drying oven；
(5) the carbon fibre reinforced silicon carbide aeroengine fan blades porous body dried in step (4) is packed into moulds of industrial equipment
In, it is then placed in vacuum gas pressure infiltration furnace, is evacuated to 0.01 ~ 10Pa, be preheated to 400 ~ 700 DEG C and keep the temperature 0.5 ~ 2h, it will
Molten aluminium alloy is poured into moulds of industrial equipment, filling air pressure to 0.5 ~ 3.0MPa, and 0.5 ~ 2h of pressure maintaining, and tooling mould is removed after cooling
Tool obtains pottery aluminium composite material aeroengine fan blades.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910039285.2A CN109628857A (en) | 2019-01-16 | 2019-01-16 | A kind of pottery aluminium composite material aeroengine fan blades and preparation method thereof |
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| CN201910039285.2A CN109628857A (en) | 2019-01-16 | 2019-01-16 | A kind of pottery aluminium composite material aeroengine fan blades and preparation method thereof |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110468358A (en) * | 2019-08-28 | 2019-11-19 | 苏州宏久航空防热材料科技有限公司 | A kind of metal ceramic-based composite material barrel support of fibre reinforced and preparation method thereof |
| CN114645226A (en) * | 2020-12-21 | 2022-06-21 | 南京航空航天大学 | Unidirectional laminated structure carbon fiber reinforced silicon carbide/aluminum-based composite material and preparation method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007239050A (en) * | 2006-03-09 | 2007-09-20 | Nissei Plastics Ind Co | Method for manufacturing composite metal alloy, and method for manufacturing composite metal molded article |
| CN108441791A (en) * | 2018-03-21 | 2018-08-24 | 苏州宏久航空防热材料科技有限公司 | A kind of metal ceramic-based composite material of fibre reinforced |
-
2019
- 2019-01-16 CN CN201910039285.2A patent/CN109628857A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007239050A (en) * | 2006-03-09 | 2007-09-20 | Nissei Plastics Ind Co | Method for manufacturing composite metal alloy, and method for manufacturing composite metal molded article |
| CN108441791A (en) * | 2018-03-21 | 2018-08-24 | 苏州宏久航空防热材料科技有限公司 | A kind of metal ceramic-based composite material of fibre reinforced |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110468358A (en) * | 2019-08-28 | 2019-11-19 | 苏州宏久航空防热材料科技有限公司 | A kind of metal ceramic-based composite material barrel support of fibre reinforced and preparation method thereof |
| CN114645226A (en) * | 2020-12-21 | 2022-06-21 | 南京航空航天大学 | Unidirectional laminated structure carbon fiber reinforced silicon carbide/aluminum-based composite material and preparation method thereof |
| CN114645226B (en) * | 2020-12-21 | 2023-04-14 | 南京航空航天大学 | Unidirectional laminated structure carbon fiber reinforced silicon carbide/aluminum-based composite material and preparation method thereof |
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Application publication date: 20190416 |