CN110439630A - A kind of Varying-thickness composite material stator blade and its forming method - Google Patents
A kind of Varying-thickness composite material stator blade and its forming method Download PDFInfo
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- CN110439630A CN110439630A CN201910741549.9A CN201910741549A CN110439630A CN 110439630 A CN110439630 A CN 110439630A CN 201910741549 A CN201910741549 A CN 201910741549A CN 110439630 A CN110439630 A CN 110439630A
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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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/005—Selecting particular materials
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
- B29L2031/082—Blades, e.g. for helicopters
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Materials Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The present invention relates to a kind of Varying-thickness composite material stator blade and its forming methods to belong to advanced composite material technical field more particularly to Varying-thickness stator blade integral shaping method.The blade includes leading-edge panel, Varying-thickness blade, posterior marginal shield, and three is same composite material and integrated molding, and the windward side of the blade uses wear-resistant nonmetallic edge protection.Molding die is designed as the composable mold of 4 valve composite module of closed mould cavity, and taper guide and limit mating surface is designed as between module.In conjunction with the blade neutral surface and net volume fill method of extraction, board design goes out the sideline profile for each paving prepreg block layer being consistent with blade different zones overall thickness.Blade realizes that precast body makes using continuous-filament woven fabric prepreg on 4 valve molding dies, then is embedded in corresponding position for metal is pre-buried, and heat pressing process is utilized to realize the co-curing preparation of built-in fitting and blade body.The forming method guarantees that stator blade had both been able to satisfy structural strength rigidity requirement, while meeting the type face required precision of its aerodynamic configuration.
Description
Technical field
The present invention relates to a kind of Varying-thickness composite material stator blade and its forming methods, more particularly to Varying-thickness stator
Blade integral shaping method belongs to advanced composite material technical field.
Background technique
Polymer matrix composites are due to becoming aero-engine cold end zero with the performances such as good specific strength and specific modulus
The research hot topic material of component.By the development of many decades, polymer matrix composites in big bypass ratio turbofan and
Outer culvert casing, rotor and the stator blade of small bypass ratio augmented turbofan engine contain casing, engine nacelle and anti-
There is important application in thrust device.
The stator part of aero-engine also more and more uses fiber-reinforced resin matrix compound material.For example P&W is public
The PW4056/4168/4084 engine blower export orientation blade of department uses the asphalt mixtures modified by epoxy resin of the fibre reinforced of compression moulding
Resin-based composite；The compressor stator blade of PW4084 and PW4168 engine just uses the PR500 asphalt mixtures modified by epoxy resin of 3M company
Resin-based composite, stator blade weight saving 39% of the stator blade made of the material compared with titanium alloy material, cost drop
Low 38%.The PW8000 engine of German MTU company can in the inlet guide vane of high velocity, low pressure compressor and the 1st grade, the 2nd grade
Stator blade is adjusted to use PMC composite material.And China is built also in exploration in polymer matrix composites stator blade field,
The country such as America and Europe is not overripened relatively.Domestic composite material stator blade and its forming technique develop later, carbon fiber composite
Expect that the research of stator blade is less.
Country's stator blade uses metal, glass reinforced plastic or low performance carbon fibre composite material at present, but comprehensive
The needs of aero-engine stator blade requirements at the higher level are unable to satisfy in performance, it would be highly desirable to develop a kind of lightweight, high rigidity, high-strength
The stator blade of degree and high-profile precision.Although reported above apply composite material on stator blade, it is not met by
Higher performance requires (performance requirements such as big Varying-thickness, high rigidity, high intensity).
Summary of the invention
Technical problem solved by the present invention is high-performance aeroengine Varying-thickness stator blade manufacturing issue is solved,
It proposes a kind of Varying-thickness composite material stator blade and its forming method, is designed by composable mold, net prepreg thickness tablet side
Line profile, heat pressing process design realize the control of good internal soundness and pneumatic outer mold surface, complete high-performance variable thickness composite wood
Expect stator blade molding.
The scheme that the present invention solves technology is: a kind of Varying-thickness composite material stator blade of the invention, the blade include
Leading-edge panel, Varying-thickness blade, posterior marginal shield, Varying-thickness blade between leading-edge panel and posterior marginal shield, leading-edge panel, Varying-thickness blade,
Posterior marginal shield is same composite material and is integrally formed that the windward side of blade uses wear-resistant nonmetallic edge protection.
In an alternative embodiment, the leading-edge panel, blade, posterior marginal shield manufacture material all carbon fibre fabric is used to increase
Strong epoxy resin toughened composite material.
In an alternative embodiment, the carbon fiber includes T700, T800, T100, M40J grade carbon fiber, the carbon fiber
Form of fabric includes that plain weave, twill, five pieces of satin or eight piece three are winged, and the resin content of the composite material is in 38%-48%
Between.
In an alternative embodiment, leading-edge panel assembly connection region partial thickening is reinforced, setting in the join domain
The pre-buried set of metal, the pre-buried set of metal and leading-edge panel are integrally formed.
In an alternative embodiment, the pre-buried set material is aluminium alloy or titanium alloy.
In an alternative embodiment, the nonmetallic bound edge material is polyurethane or polyimides.
A kind of Varying-thickness composite material stator blade forming method of the invention, which comprises the following steps:
1) the blade external surface of stator blade is the non-processing face of dead size, and molding die is designed as the combination of 4 valve of closed mould cavity
The composable mold of module, wherein mold two sides in blade upper and lower end face are reserved front and back listrium paving region and are designed as 4 corners
Taper guide and limit, it is ensured that after upper and lower end module molding without departing from；Front and back listrium side mold is designed as taper fit face simultaneously, in advance
Stay compacting step in place, it is ensured that compression conforms to design position；
2) it is required according to blade construction feature and air-driven type face, using net volume fill method, according in the blade extracted
Property face, board design goes out the 3D solid face and its side of each paving prepreg block layer being consistent with blade different zones overall thickness
Line profile；
3) convert X-Y scheme for the sideline profile for each layered material block that step 2) obtains, and by figure sideline from greatly to
Minispread；In conjunction with listrium feature and laying symmetry principle, the continuous fiber prepreg block of integral blade is designed and cut out；
4) the prepreg block for cutting step 3) is laid in blade using blade two sides parting line as position baseline according to this
On the die-face of upper and lower end face, is molded after completing precast body paving, obtain blade precast body；
5) the blade precast body that step 4) obtains is taken out from mold, the bound edge cut according to size is fitted in prefabricated
The windward side of blade places into the blade interior molding compacting of terminal mould up and down；
6) after pressing ply stacking-sequence paving at least two layers of prepreg block on leading-edge panel side mold, according still further to join domain thickness
After requiring corresponding prepreg block is laminated, suction glue laminated reality with size, paving completes remaining prepreg on leading-edge panel side mold
The paving of block；It will be in the pre-buried join domain being embedded in after paving of metal；It is completed in advance on posterior marginal shield side mold by ply stacking-sequence
Leaching material block paving；
7) leading-edge panel for obtaining step 6) is fitted in the leading edge Board position after step 5) molding, positions and is compacted；Again will
The posterior marginal shield side mold for completing laying is fitted in the rear Board position after step 5) molding, completes integral blade laying；
8) to auxiliary material is coated on the outside of composable mold in step 7), the co-curing of integral blade is realized using heat pressing process
Preparation；
9) the forward and backward listrium surplus rim charge of stator blade after solidification is processed, to meet blade dimensions design requirement.
Inhaling glue in an alternative embodiment, in step 6) is carried out in autoclave or hot press, suction glue temperature 60 C~
80 DEG C, inhale glue time 20min~40min, hot pressing pressure inside the tank 0.3MPa~0.6Mpa；It inhales glue and treats the preimpregnation for inhaling glue in the process
Material block is vacuumized.
In an alternative embodiment, solidification process is carried out in autoclave or hot press in step 8), solidification temperature
It is 120 DEG C~130 DEG C or 165 DEG C~180 DEG C, curing time 3h~6h, hot pressing pressure inside the tank 0.6MPa~1.0Mpa.
Varying-thickness composite material stator blade made of above-mentioned forming method is suitable for aero-engine.
Compared with the prior art, the invention has the advantages that:
One kind provided by the invention novel Varying-thickness composite material stator blade and forming method.The stator blade includes
Leading-edge panel, Varying-thickness blade, posterior marginal shield, three are same composite material and integrated molding, and the windward side of the blade is using resistance to
Wear nonmetallic edge protection.Molding die is designed as the composable mold of 4 valve composite module of closed mould cavity.It is filled using net volume
Method board design obtains the separation tablet sideline profile for meeting blade overall thickness.Stator blade is integrally solid altogether using heat pressing process
Change manufacture to obtain, blade air-driven type face is processed without secondary mechanical；The technique guarantees that stator blade is both able to satisfy structural strength
Rigidity requirement, while meeting the surface figure accuracy requirement of its aerodynamic configuration.
The present invention technical advantage is obvious, can promote the use of the High-performance static blades of military/civil aircraft engine
On and the lightweight load-carrying construction that all has higher requirements of some pairs of aerodynamic configurations and rigidity, intensity on.The present invention energy
Enough meet the development needs of the aero-engine High-performance static blades to grow to even greater heights in China, economic benefit and perspective protrusion.
Detailed description of the invention
Fig. 1 is stator blade overall structure figure；
Fig. 2 a, 2b, 2c, 2d are respectively stator blade molding die composite entity figure, blade lower end die drawing, blade upper end
Die drawing, leading edge side board die figure；
Fig. 3 a is the laminated figure of tablet on the left of stator blade neutral surface；
Fig. 3 b is the laminated figure of tablet on the right side of stator blade neutral surface.
Specific embodiment
A kind of Varying-thickness composite material stator blade of the invention, the blade include leading-edge panel, Varying-thickness blade, rear
Plate, Varying-thickness blade between leading-edge panel and posterior marginal shield, leading-edge panel, Varying-thickness blade, posterior marginal shield be same composite material and
It is integrally formed, the windward side of blade uses wear-resistant nonmetallic edge protection, and blade construction schematic diagram is shown in attached drawing 1.
Specifically, in the embodiment of the present invention, the leading-edge panel, blade, posterior marginal shield manufacture material all use carbon fiber
Fabric activeness and quietness epoxy resin composite material.The carbon fiber includes T700, T800, T100, M40J grade carbon fiber, the carbon
Fabric form includes that plain weave, twill, five pieces of satin or eight piece three are winged, and the resin content of the composite material is in 38%-
Between 48%.Leading-edge panel assembly connection region partial thickening is reinforced, and the pre-buried set of metal is arranged in the join domain, and metal is pre-
It buries set and leading-edge panel is integrally formed.The pre-buried set material is aluminium alloy or titanium alloy.The nonmetallic bound edge material is poly- ammonia
Ester or polyimides.
A kind of Varying-thickness composite material stator blade forming method of the invention, which comprises the following steps:
1) the blade external surface of stator blade is the non-processing face of dead size, and molding die is designed as the combination of 4 valve of closed mould cavity
The composable mold of module, wherein mold two sides in blade upper and lower end face are reserved front and back listrium paving region and are designed as 4 corners
Taper guide and limit, it is ensured that after upper and lower end module molding without departing from；Front and back listrium side mold is designed as taper fit face simultaneously, in advance
Stay compacting step in place, it is ensured that compression conforms to design position；Mold design figure is shown in attached drawing 2a-2d.
Specifically, in the embodiment of the present invention, the preferred Q235 steel of the material of the mold, 45# steel, P20 steel.
2) it is required according to blade construction feature and air-driven type face, using net volume fill method, according in the blade extracted
Property face, board design goes out the 3D solid face and its side of each paving prepreg block layer being consistent with blade different zones overall thickness
Line profile；The two groups of material block boundaries obtained by two Side Volume of blade neutral surface；
Specifically, in embodiments of the present invention, according to the target blade each position thickness and the single layer of prepreg used
Thickness designs each layer of prepreg block of blade different zones thickness, obtains the pre- of the different sizes of all pavings and position
Tablet is soaked, sees attached drawing 3a, 3b.
3) convert X-Y scheme for the sideline profile for each layered material block that step 2) obtains, and by figure sideline from greatly to
Minispread；In conjunction with listrium feature and laying symmetry principle, the continuous fiber prepreg block of integral blade is designed and cut out；
Specifically, in embodiments of the present invention, it according to the X-Y scheme, obtains each in two Side Volume of blade neutral surface
Expect the ply stacking-sequence of block layer.
4) the prepreg block for cutting step 3) is laid in blade using blade two sides parting line as position baseline according to this
On the die-face of upper and lower end face, is molded after completing precast body paving, obtain blade precast body；
Specifically, in embodiments of the present invention, during the prepreg block laying, every paving 3-5 layered material block take out true
Pneumatics is real.
5) the blade precast body that step 4) obtains is taken out from mold, the bound edge cut according to size is fitted in prefabricated
The windward side of blade places into the blade interior molding compacting of terminal mould up and down.
6) after pressing ply stacking-sequence paving at least two layers of prepreg block on leading-edge panel side mold, according still further to join domain thickness
After requiring corresponding prepreg block is laminated, suction glue laminated reality with size, paving completes remaining prepreg on leading-edge panel side mold
The paving of block；It will be in the pre-buried join domain being embedded in after paving of metal；It is completed in advance on posterior marginal shield side mold by ply stacking-sequence
Leaching material block paving；
Specifically, in the embodiment of the present invention, inhaling glue is carried out in autoclave or hot press, inhales glue temperature 60 C~80
DEG C, inhale glue time 20min~40min, hot pressing pressure inside the tank 0.3MPa~0.6Mpa；It inhales glue and treats the prepreg for inhaling glue in the process
Block is vacuumized.
7) leading-edge panel for obtaining step 6) is fitted in the leading edge Board position after step 5) molding, positions and is compacted；Again will
The posterior marginal shield side mold for completing laying is fitted in the rear Board position after step 5) molding, completes integral blade laying.
8) to auxiliary material is coated on the outside of composable mold in step 7), the co-curing of integral blade is realized using heat pressing process
Preparation；
Specifically, in the embodiment of the present invention, solidification process is carried out in autoclave or hot press, and solidification temperature is
120 DEG C~130 DEG C or 165 DEG C~180 DEG C, curing time 3h~6h, hot pressing pressure inside the tank 0.6MPa~1.0Mpa.
9) the forward and backward listrium surplus rim charge of stator blade after solidification is processed, to meet blade dimensions design requirement；
In an alternative embodiment, solidification process is carried out in autoclave or hot press in step 8), solidification temperature
It is 120 DEG C~130 DEG C or 165 DEG C~180 DEG C, curing time 3h~6h, hot pressing pressure inside the tank 0.6MPa~1.0Mpa.
The following are several specific embodiments of the invention:
Embodiment 1
Varying-thickness composite material stator blade described in the embodiment of the present invention, the blade include leading-edge panel, Varying-thickness leaf
Body, posterior marginal shield, for Varying-thickness blade between leading-edge panel and posterior marginal shield, leading-edge panel, Varying-thickness blade, posterior marginal shield are same compound
It material and is integrally formed, the windward side of blade uses wear-resistant nonmetallic edge protection.Leading-edge panel, blade, posterior marginal shield
The reinforcement that manufacture material uses is T800 carbon fiber fiber twills, and resin matrix is 603 ring epoxy resin of toughening, preparation
The prepreg trade mark be T800-6k-XW/603, after solidification thickness in monolayer be 0.2mm.
Blade fades to 1.0mm by 5.5mm to posterior marginal shield root thickness for leading-edge panel root；Blade left side edge
0.8mm maximum increases to 5.0mm, after fade to 0.9mm again.Leading-edge panel, posterior marginal shield are with a thickness of 3mm.Leading-edge panel assembly connection region
Partial thickening is reinforced, and buildup area is with a thickness of 20mm；The pre-buried set of metal, the pre-buried set of metal and leading-edge panel one are set in the join domain
It is body formed.Wear-resistant bound edge material is polyurethane, and the pre-buried set material of metal is titanium alloy.
The Varying-thickness composite material stator blade forming method, comprising the following steps:
1) the blade external surface of stator blade is the non-processing face of dead size, and molding die is designed as the combination of 4 valve of closed mould cavity
The composable mold of module, wherein mold two sides in blade upper and lower end face are reserved front and back listrium paving region and are designed as 4 corners
Taper guide and limit, it is ensured that after upper and lower end module molding without departing from；Front and back listrium side mold is designed as taper fit face simultaneously, in advance
Stay compacting step in place, it is ensured that compression conforms to design position；The preferred 45# steel of the material of mold；
2) it is required according to blade construction feature and air-driven type face, using net volume fill method, according in the blade extracted
Property face, according to the target blade each position thickness and the thickness in monolayer of prepreg used, board design goes out and blade not same district
The 3D solid face for each paving prepreg block layer that domain overall thickness is consistent and its sideline profile；Press two Side Volume of blade neutral surface
Two groups obtained totally 29 layered material block boundary；
3) X-Y scheme is converted by the sideline profile of obtained each layered material block, and is arranged from big to small by figure sideline
Column；In conjunction with listrium feature and quasi-isotropic ply stacking-sequence design principle, each material in two Side Volume of blade neutral surface is obtained
The ply stacking-sequence of block layer designs and cuts out the continuous fiber prepreg block of integral blade；
4) the prepreg block that will be cut is laid in blade upper and lower side using blade two sides parting line as position baseline according to this
On the die-face of face, every paving 3-5 layered material block carries out vacuumizing compacting, molds after completing precast body paving, it is prefabricated to obtain blade
Body；
5) obtained blade precast body is taken out from mold, the bound edge cut according to size is fitted in prefabricated blade
Windward side places into the blade interior molding compacting of terminal mould up and down；
6) after pressing two layers of prepreg block of ply stacking-sequence paving on leading-edge panel side mold, according still further to join domain thickness and ruler
Very little requirement is laminated by corresponding prepreg block, and suction glue is carried out in autoclave or hot press, inhales glue temperature 70 C, inhales the glue time
30min, hot pressing pressure inside the tank 0.6Mpa；After inhaling glue laminated reality, paving completes remaining prepreg block on leading-edge panel side mold
Paving；It will be in the pre-buried join domain being embedded in after paving of metal；Prepreg is completed by ply stacking-sequence on posterior marginal shield side mold
Block paving；
7) leading-edge panel for obtaining step 6) is fitted in the leading edge Board position after step 5) molding, positions and is compacted；Again will
The posterior marginal shield side mold for completing laying is fitted in the rear Board position after step 5) molding, completes integral blade laying.
8) the coating product auxiliary material to be solidified for obtaining step 7), solidifies in autoclave or hot press, solidification temperature
Degree is 180 DEG C, curing time 4h, solidifying pressure 0.7Mpa；Built-in fitting is realized using heat pressing process and the total of blade body is consolidated
Change preparation, the composite material stator blade prepared.
9) the forward and backward listrium surplus rim charge of stator blade after solidification is processed, to meet blade dimensions design requirement.
Embodiment 2
Varying-thickness composite material stator blade described in the embodiment of the present invention, the blade include leading-edge panel, Varying-thickness leaf
Body, posterior marginal shield, for Varying-thickness blade between leading-edge panel and posterior marginal shield, leading-edge panel, Varying-thickness blade, posterior marginal shield are same compound
It material and is integrally formed, the windward side of blade uses wear-resistant nonmetallic edge protection.Leading-edge panel, blade, posterior marginal shield
The reinforcement that manufacture material uses is T800 carbon fiber fiber twills, and resin matrix is 602 ring epoxy resin of toughening, preparation
The prepreg trade mark be T800-6k-XW/602, after solidification thickness in monolayer be 0.2mm.
Blade fades to 1.2mm by 6.0mm to posterior marginal shield root thickness for leading-edge panel root；Blade left side edge
1.0mm maximum increases to 5.0mm, after fade to 1.0mm again.Leading-edge panel, posterior marginal shield are with a thickness of 3.6mm.Leading-edge panel assembly connection area
Domain partial thickening is reinforced, and buildup area is with a thickness of 24mm；The pre-buried set of metal, the pre-buried set of metal and leading-edge panel are set in the join domain
It is integrally formed.Wear-resistant bound edge material is polyimides, and the pre-buried set material of metal is aluminium alloy.
The Varying-thickness composite material stator blade forming method, comprising the following steps:
1) the blade external surface of stator blade is the non-processing face of dead size, and molding die is designed as the combination of 4 valve of closed mould cavity
The composable mold of module, wherein mold two sides in blade upper and lower end face are reserved front and back listrium paving region and are designed as 4 corners
Taper guide and limit, it is ensured that after upper and lower end module molding without departing from；Front and back listrium side mold is designed as taper fit face simultaneously, in advance
Stay compacting step in place, it is ensured that compression conforms to design position；The preferred Q235 steel of the material of mold；
2) it is required according to blade construction feature and air-driven type face, using net volume fill method, according in the blade extracted
Property face, according to the target blade each position thickness and the thickness in monolayer of prepreg used, board design goes out and blade not same district
The 3D solid face for each paving prepreg block layer that domain overall thickness is consistent and its sideline profile；Press two Side Volume of blade neutral surface
Two groups obtained totally 36 layered material block boundary；
3) X-Y scheme is converted by the sideline profile of obtained each layered material block, and is arranged from big to small by figure sideline
Column；In conjunction with listrium feature and quasi-isotropic ply stacking-sequence design principle, each material in two Side Volume of blade neutral surface is obtained
The ply stacking-sequence of block layer designs and cuts out the continuous fiber prepreg block of integral blade；
4) the prepreg block that will be cut is laid in blade upper and lower side using blade two sides parting line as position baseline according to this
On the die-face of face, every paving 3-5 layered material block carries out vacuumizing compacting, molds after completing precast body paving, it is prefabricated to obtain blade
Body；
5) obtained blade precast body is taken out from mold, the bound edge cut according to size is fitted in prefabricated blade
Windward side places into the blade interior molding compacting of terminal mould up and down；
6) after pressing two layers of prepreg block of ply stacking-sequence paving on leading-edge panel side mold, according still further to join domain thickness and ruler
Very little requirement is laminated by corresponding prepreg block, and suction glue is carried out in autoclave or hot press, inhales glue temperature 70 C, inhales the glue time
30min, hot pressing pressure inside the tank 0.6Mpa；After inhaling glue laminated reality, paving completes remaining prepreg block on leading-edge panel side mold
Paving；It will be in the pre-buried join domain being embedded in after paving of metal；Prepreg is completed by ply stacking-sequence on posterior marginal shield side mold
Block paving；
7) leading-edge panel for obtaining step 6) is fitted in the leading edge Board position after step 5) molding, positions and is compacted；Again will
The posterior marginal shield side mold for completing laying is fitted in the rear Board position after step 5) molding, completes integral blade laying.
8) the coating product auxiliary material to be solidified for obtaining step 7), solidifies in autoclave or hot press, solidification temperature
Degree is 125 DEG C, curing time 5h, solidifying pressure 0.8Mpa；Built-in fitting is realized using heat pressing process and the total of blade body is consolidated
Change preparation, the composite material stator blade prepared.
9) the forward and backward listrium surplus rim charge of stator blade after solidification is processed, to meet blade dimensions design requirement.
Although the invention has been described by way of example and in terms of the preferred embodiments, but it is not for limiting the present invention, any this field
Technical staff without departing from the spirit and scope of the present invention, may be by the methods and technical content of the disclosure above to this hair
Bright technical solution makes possible variation and modification, therefore, anything that does not depart from the technical scheme of the invention, and according to the present invention
Technical spirit any simple modifications, equivalents, and modifications to the above embodiments, belong to technical solution of the present invention
Protection scope.
Claims (10)
1. a kind of Varying-thickness composite material stator blade, including leading-edge panel, Varying-thickness blade, posterior marginal shield；It is characterized by: described
Varying-thickness blade between leading-edge panel and posterior marginal shield, leading-edge panel, Varying-thickness blade, posterior marginal shield be same composite material and three
Person is integrally formed, and the windward side of the blade uses wear-resistant nonmetallic edge protection.
2. blade according to claim 1, it is characterised in that: the leading-edge panel, blade, the manufacture material of posterior marginal shield are complete
Portion uses carbon fibre fabric activeness and quietness epoxy resin composite material.
3. blade according to claim 2, it is characterised in that: the carbon fiber includes T700, T800, T100, M40J grades
Carbon fiber, the carbon fibre fabric form include that plain weave, twill, five pieces of satin or eight piece three are winged, the resinite of the composite material
Content is measured between 38%-48%.
4. blade according to claim 1, it is characterised in that: the leading-edge panel assembly connection region partial thickening adds
By force, metal pre-buried set is set in the join domain, and the pre-buried set of metal and leading-edge panel are integrally formed.
5. blade according to claim 4, it is characterised in that: the pre-buried set material is aluminium alloy or titanium alloy.
6. blade according to claim 1, it is characterised in that: the nonmetallic bound edge material is that polyurethane or polyamides are sub-
Amine.
7. a kind of Varying-thickness composite material stator blade forming method, it is characterised in that include the following steps:
1) the blade external surface of stator blade is the non-processing face of dead size, and molding die is designed as 4 valve composite module of closed mould cavity
Composable mold, wherein the reserved front and back listrium paving region in blade upper and lower end face mold two sides and be designed as taper 4 corners
Guide and limit, it is ensured that after upper and lower end module molding without departing from；Front and back listrium side mold is designed as taper fit face simultaneously, reserves pressure
Actual arrival position step, it is ensured that compression conforms to design position；
2) it is required according to blade construction feature and air-driven type face, the blade neutral surface extracted using net volume fill method, foundation,
Board design goes out 3D solid face and its sideline wheel for each paving prepreg block layer being consistent with blade different zones overall thickness
It is wide；
3) X-Y scheme is converted by the sideline profile for each layered material block that step 2) obtains, and is arranged from big to small by figure sideline
Column；In conjunction with listrium feature and laying symmetry principle, the continuous fiber prepreg block of integral blade is designed and cut out；
4) the prepreg block for cutting step 3) is laid in blade or more using blade two sides parting line as position baseline according to this
On the die-face of end face, is molded after completing precast body paving, obtain blade precast body；
5) the blade precast body that step 4) obtains is taken out from mold, the bound edge cut according to size is fitted in prefabricated blade
Windward side, place into blade molding compacting in terminal mould up and down；
6) after pressing ply stacking-sequence paving at least two layers of prepreg block on leading-edge panel side mold, according still further to join domain thickness and ruler
Very little requirement is laminated by corresponding prepreg block, inhale glue laminated reality after, paving completes remaining prepreg block on leading-edge panel side mold
Paving；It will be in the pre-buried join domain being embedded in after paving of metal；Prepreg is completed by ply stacking-sequence on posterior marginal shield side mold
Block paving；
7) leading-edge panel for obtaining step 6) is fitted in the leading edge Board position after step 5) molding, positions and is compacted；It will complete again
The posterior marginal shield side mold of laying is fitted in the rear Board position after step 5) molding, completes integral blade laying；
8) to auxiliary material is coated on the outside of composable mold in step 7), the co-curing system of integral blade is realized using heat pressing process
It is standby；
9) the forward and backward listrium surplus rim charge of stator blade after solidification is processed, to meet blade dimensions design requirement.
8. according to the method described in claim 7, it is characterized by: step 6) in inhale glue be in autoclave or hot press into
Row inhales glue temperature 60 C~80 DEG C, inhales glue time 20min~40min, hot pressing pressure inside the tank 0.3MPa~0.6Mpa；Inhale glue mistake
The prepreg block that suction glue is treated in journey is vacuumized.
9. according to the method described in claim 7, it is characterized by: solidification process is in autoclave or hot press in step 8)
It carries out, solidification temperature is 120 DEG C~130 DEG C or 165 DEG C~180 DEG C, curing time 3h~6h, hot pressing pressure inside the tank 0.6MPa
~1.0Mpa.
10. being suitable for according to Varying-thickness composite material stator blade made of the described in any item forming methods of claim 7-9
Aero-engine.
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| CN111664124A (en) * | 2020-06-05 | 2020-09-15 | 中国航发沈阳发动机研究所 | Stator structure, rotor and stator assembly structure with same and assembly method of rotor and stator assembly structure |
| CN112453513A (en) * | 2020-10-14 | 2021-03-09 | 沈阳透平机械股份有限公司 | Method for machining impeller blade of centrifugal compressor and impeller blade |
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| CN114800797A (en) * | 2022-05-19 | 2022-07-29 | 西北工业大学 | Multipurpose mold and application thereof |
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| CN114800797A (en) * | 2022-05-19 | 2022-07-29 | 西北工业大学 | Multipurpose mold and application thereof |
| CN115302815A (en) * | 2022-10-11 | 2022-11-08 | 江苏新扬新材料股份有限公司 | Manufacturing method of special-shaped airplane frame upright post |
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