CN104690982A - Composite stator blade of engine and preparation method of composite stator blade - Google Patents
Composite stator blade of engine and preparation method of composite stator blade Download PDFInfo
- Publication number
- CN104690982A CN104690982A CN201310663400.6A CN201310663400A CN104690982A CN 104690982 A CN104690982 A CN 104690982A CN 201310663400 A CN201310663400 A CN 201310663400A CN 104690982 A CN104690982 A CN 104690982A
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- Prior art keywords
- module
- stator blade
- cut
- parts
- blade
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Classifications
-
- 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
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Manufacture Of Motors, Generators (AREA)
Abstract
The invention discloses a composite stator blade of an engine and a preparation method of the composite stator blade. The stator blade comprises a blade body prepared from a piece of presoaked carbon cloth, an upper margin plate, a lower margin plate, a skin, a front edge nickel coverage edge and a metal lining, wherein a mounting hole connected with a case of the engine is formed in the upper margin plate; the skin prepared from a piece of presoaked glass cloth wraps the blade body, the upper flange plate, the lower flange plate and the mounting hole; the front edge nickel coverage edge is glued and fixed at the front edge part of the blade body; the metal lining is embedded into the mounting hole of the upper margin plate. The composite stator blade is high in specific intensity, high in rigidity, high in high temperature capacity, light in weight, high in impact resistance and high in pressure resistance, so that the efficiency of the engine is greatly improved, and the oil consumption of the engine is reduced. According to the method, by adoption of a mode of parting module laying, integrated die pressing and stage-by-stage solidification, a die closing clearance can be well controlled, the structural completeness of the product is guaranteed, the requirement on the design size is met, and the problems of interlayer sliding of laid layers and zigzag wrinkling of the cloth layers are solved.
Description
Technical field
Composite stator blade that the present invention relates to a kind of engine and preparation method thereof.
Background technology
The stator blade of existing engine is all be made up of metal material, adopts stainless steel 1Cr11Ni2W2MoV, nickel alloy and titanium alloy, adopts milling, die-cut, roughing, heat treatment, throwing are repaiied, finish rolling, the again technique such as heat treatment and cut-out complete.Although stainless steel 1Cr11Ni2W2MoV, nickel alloy and titanium alloy still have the leeway of improving its intensity, rigidity and resistant to elevated temperatures performance further, its development potentiality is limited, is difficult to meet the harsher temperature of following aero-engine and weight demands.Along with improving constantly of aero-engine performance, particularly weight constantly alleviates, to more and more depend on the strong advanced material of high specific strength, low-density, high rigidity and heat-resisting ability: as the composite of preimpregnation carbon cloth and preimpregnate glass cloth, because preimpregnation carbon cloth is completely different with the structure of tangible traditional metal materials with the composite of preimpregnate glass cloth, so the stator blade also not adopting the composite such as preimpregnation carbon cloth and preimpregnate glass cloth to make at present.And due to little relative to nickel alloy and titanium alloy material of impact resistance and the crushing resistance of preimpregnation carbon cloth and the composite of preimpregnate glass cloth, so, as the stator blade adopting the composite of preimpregnation carbon cloth and preimpregnate glass cloth to make, it easily causes blade damaged under airflow scouring, especially blade inlet edge part, easily wear and tear in blades installation hole place, position, hole becomes large, and installation stationarity is poor.
Summary of the invention
Object of the present invention solves the above-mentioned problems in the prior art exactly, and provide a kind of specific strength high, specific stiffness is high, heat-resisting ability is strong, lightweight, and impact resistance and crushing resistance are also very strong, all-composite engine stator blade of long service life and preparation method thereof.
For achieving the above object, technical solution of the present invention is: a kind of composite stator blade of engine, and it comprises the blade be made up of preimpregnation carbon cloth, upper and lower listrium, covering, nickel leading edge bound edge and metal lining; Supramarginal plate has the installing hole be connected with engine crankcase, the covering be made up of preimpregnate glass cloth is wrapped in outside blade, upper and lower listrium and installing hole; Nickel leading edge bound edge glueds joint the leading edge portion being fixed on blade, and metal lining is embedded in the installing hole of supramarginal plate.
The preparation method of the composite stator blade of engine described above, it comprises the following steps:
The design and manufaction of A, mould, product size requirement is met for ease of matched moulds and die sinking, stator blade mould adopts multimode separate assembling, according to the complex appearance of composite stator blade, whole blade forming mould is divided into 4 modules: upper module, lower module, supramarginal plate module and inframarginal module; The profile of the inner chamber after upper module, lower module, supramarginal plate module and inframarginal module matched moulds and the stator blade of design code matches;
The preparation of the cut-parts of B, preimpregnation carbon cloth and preimpregnate glass cloth, the cut-parts of preimpregnation carbon cloth and the cut-parts of preimpregnate glass cloth that use blanking machine or model to cut out to match with the appearance and size of the blade of the stator blade of design code and upper and lower listrium;
Before C, paving mould, the preparation of modules, sprays releasing agent, and is preheated to 35 DEG C ± 5 DEG C in the die cavity of the upper module cleaned out, lower module, supramarginal plate module and inframarginal module;
D, sub-module laying, according to the laying quantity of design code and order preheated in advance and spray first lay glass cloth cut-parts respectively in the upper module of remover, lower module, supramarginal plate module and inframarginal module, lay preimpregnation carbon cloth cut-parts in glass cloth cut-parts again, until all cut-parts of the complete design code of lay; Fit tightly between cut-parts, protective layer and foreign matter must not be left between laying;
E, mould overall package, be first that benchmark matched moulds is on lower module by the upper module completing the cut-parts of preimpregnate glass cloth and the cut-parts of preimpregnation carbon cloth with alignment pin, move on to be preheated to 50 DEG C ± 10 DEG C hot press on, hot press is forced into 8MPa ~ 10MPa, to ensure that the gap between upper and lower module is not more than 0.5mm; Metal lining is installed on the alignment pin installing listrium module side of the upper and lower module after matched moulds, then supramarginal plate module and inframarginal module are assembled into the both sides of the upper and lower module after matched moulds respectively, evenly tighten screw, avoid damaging mould;
F, molded curing are shaping, are warming up to 140 DEG C with the heating rate of 1 DEG C ~ 3 DEG C/min; At 140 DEG C ~ 145 DEG C insulation 30min ~ 60min; 180 DEG C ± 5 DEG C are warming up to again with the heating rate of 1 DEG C ~ 3 DEG C/min; At 180 DEG C ± 5 DEG C insulation 2h ~ 2.5h;
G, pattern drawing are repaiied, and after the condition of cure in completing steps F, turn off hot press, when mold temperature is cooled to below 60 DEG C, is taken off by mould, open mould, trip out stator blade, and clear up stator blade from hot press, carry out type repair the overlap of stator blade;
H, blast is carried out to the leading edge position of the stator blade that type is fixed and nickel leading edge bound edge and after cleaning up, uses adhesive to be bonded in stator blade leading edge by nickel leading edge bound edge.
Product employing specific strength of the present invention and the composite that specific stiffness is high, high temperature resistant, density is low and structural stability is high are made, it has high strength, high rigidity, lightweight and resistant to elevated temperatures feature, so, it meets the performance requirement of stator blade, be applicable in the comparatively severe air dielectric of the working environment of long-term work in-55 DEG C ~ 120 DEG C temperature ranges, its dimensional stability is high, long service life.Its covering adopts preimpregnate glass cloth to make, and its appearance surfaces quality is good, and its leading edge portion glueds joint the nickel leading edge bound edge having resistance to erosion, and make its anti-airflow scouring ability strong, namely impact resistance is strong; The metal lining installed in the installing hole of supramarginal plate makes the anti-pressure ability at its position, hole place greatly improve.These all substantially prolongs the service life of stator blade.The present invention improves the efficiency of engine greatly, meets the low oil consumption designing requirement of engine, improves the market competitiveness of engine.Method of the present invention adopts the mode of sub-module laying, integral die, cured in stages, good control matched moulds gap, ensure that the structural intergrity of product, meet design size requirement, solve laying and produce the wrinkling problem of interlayer slip, layer of cloth setback.
Accompanying drawing explanation
Fig. 1 is the structural representation of stator blade of the present invention;
Fig. 2 is mould decomposition texture schematic diagram of the present invention.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention will be further described.
As shown in Figure 1, the stator blade of the present embodiment comprises the blade 1 be made up of preimpregnation carbon cloth, upper and lower listrium 2,5, covering 6, nickel leading edge bound edge 4 and metal lining 3.Supramarginal plate 2 has the installing hole be connected with engine crankcase, the covering 6 be made up of preimpregnate glass cloth is wrapped in blade 1, upper and lower listrium 2,5, and outside installing hole.Nickel leading edge bound edge 4 glueds joint the leading edge portion being fixed on blade 1, and metal lining 3 is embedded in the installing hole of supramarginal plate 2.The preimpregnation carbon cloth 5224C/F3052 that preimpregnation carbon cloth in the present embodiment and preimpregnate glass cloth adopt Beijing Research Inst. of Aeronautic Material to develop respectively and preimpregnate glass cloth 5224/EW110C.Wherein, 5224 resin systems are that intensity is high, good toughness, impact-resistant hot setting epoxy.
The preparation method of stator blade described above, it comprises the following steps:
The design and manufaction of A, mould, product size requirement is met for ease of matched moulds and die sinking, stator blade mould adopts multimode separate assembling, according to the complex appearance of composite stator blade, whole blade forming mould is divided into 4 modules: upper module 8, lower module 10, supramarginal plate module 7 and inframarginal module 9; The profile of the inner chamber after upper module 8, lower module 10, supramarginal plate module 7 and inframarginal module 9 matched moulds and the stator blade of design code matches.
The preparation of the cut-parts of B, preimpregnation carbon cloth and preimpregnate glass cloth, the cut-parts of preimpregnation carbon cloth and the cut-parts of preimpregnate glass cloth that use blanking machine or model to cut out to match with the appearance and size of the blade of the stator blade of design code and upper and lower listrium;
Before C, paving mould, the preparation of modules, sprays releasing agent, and is preheated to 35 DEG C ± 5 DEG C in the die cavity of the upper module cleaned out, lower module, supramarginal plate module and inframarginal module;
D, sub-module laying, according to the laying quantity of design code and order preheated in advance and spray first lay glass cloth cut-parts respectively in the upper module of remover, lower module, supramarginal plate module and inframarginal module, lay preimpregnation carbon cloth cut-parts in glass cloth cut-parts again, until all cut-parts of the complete design code of lay; Fit tightly between cut-parts, protective layer and foreign matter must not be left between laying;
E, mould overall package, be first that benchmark matched moulds is on lower module by the upper module completing the cut-parts of preimpregnate glass cloth and the cut-parts of preimpregnation carbon cloth with alignment pin, move on to be preheated to 50 DEG C ± 10 DEG C hot press on, hot press is forced into 8MPa ~ 10MPa, to ensure that the gap between upper and lower module is not more than 0.5mm; Metal lining is installed on the alignment pin installing listrium module side of the upper and lower module after matched moulds, then supramarginal plate module and inframarginal module are assembled into the both sides of the upper and lower module after matched moulds respectively, evenly tighten screw, avoid damaging mould;
F, molded curing are shaping, are warming up to 140 DEG C with the heating rate of 1 DEG C ~ 3 DEG C/min; At 140 DEG C ~ 145 DEG C insulation 30min ~ 60min; 180 DEG C ± 5 DEG C are warming up to again with the heating rate of 1 DEG C ~ 3 DEG C/min; At 180 DEG C ± 5 DEG C insulation 2h ~ 2.5h;
G, pattern drawing are repaiied, and after the condition of cure in completing steps F, turn off hot press, when mold temperature is cooled to below 60 DEG C, is taken off by mould, open mould, trip out stator blade, and clear up stator blade from hot press, carry out type repair the overlap of stator blade;
H, blast is carried out to the leading edge position of the stator blade that type is fixed and nickel leading edge bound edge and after cleaning up, uses adhesive to be bonded in stator blade leading edge by nickel leading edge bound edge.
Above-described embodiment is only preferred and exemplary, and those skilled in the art can do equivalent technologies according to the spirit of this patent and improve, and these all covered by the protection domain of this patent.
Claims (2)
1. a composite stator blade for engine, is characterized in that: it comprises the blade be made up of preimpregnation carbon cloth, upper and lower listrium, covering, nickel leading edge bound edge and metal lining; Supramarginal plate has the installing hole be connected with engine crankcase, the covering be made up of preimpregnate glass cloth is wrapped in outside blade, upper and lower listrium and installing hole; Nickel leading edge bound edge glueds joint the leading edge portion being fixed on blade, and metal lining is embedded in the installing hole of supramarginal plate.
2. a preparation method for the composite stator blade of engine, it comprises the following steps:
The design and manufaction of A, mould, stator blade mould adopts multimode separate assembling, according to the profile of composite stator blade, stator blade mould is divided into 4 modules: upper module, lower module, supramarginal plate module and inframarginal module; The profile of the inner chamber after upper module, lower module, supramarginal plate module and inframarginal module matched moulds and the stator blade of design code matches;
The preparation of the cut-parts of B, preimpregnation carbon cloth and preimpregnate glass cloth, the cut-parts of preimpregnation carbon cloth and the cut-parts of preimpregnate glass cloth that use blanking machine or model to cut out to match with the appearance and size of the blade of the stator blade of design code and upper and lower listrium;
Before C, paving mould, the preparation of modules, sprays releasing agent, and is preheated to 35 DEG C ± 5 DEG C in the die cavity of the upper module cleaned out, lower module, supramarginal plate module and inframarginal module;
D, sub-module laying, according to the laying quantity of design code and order preheated in advance and spray first lay glass cloth cut-parts respectively in the upper module of remover, lower module, supramarginal plate module and inframarginal module, lay preimpregnation carbon cloth cut-parts in glass cloth cut-parts again, until all cut-parts of the complete design code of lay; Fit tightly between cut-parts, protective layer and foreign matter must not be left between laying;
E, mould overall package, be first that benchmark matched moulds is on lower module by the upper module completing the cut-parts of preimpregnate glass cloth and the cut-parts of preimpregnation carbon cloth with alignment pin, move on to be preheated to 50 DEG C ± 10 DEG C hot press on, hot press is forced into 8MPa ~ 10MPa, to ensure that the gap between upper and lower module is not more than 0.5mm; Metal lining is installed on the alignment pin installing listrium module side of the upper and lower module after matched moulds, then supramarginal plate module and inframarginal module are assembled into the both sides of the upper and lower module after matched moulds respectively, evenly tighten screw, avoid damaging mould;
F, molded curing are shaping, are warming up to 140 DEG C with the heating rate of 1 DEG C ~ 3 DEG C/min; At 140 DEG C ~ 145 DEG C insulation 30min ~ 60min; 180 DEG C ± 5 DEG C are warming up to again with the heating rate of 1 DEG C ~ 3 DEG C/min; At 180 DEG C ± 5 DEG C insulation 2h ~ 2.5h;
G, pattern drawing are repaiied, and after the condition of cure in completing steps F, turn off hot press, when mold temperature is cooled to below 60 DEG C, is taken off by mould, open mould, trip out stator blade, and clear up stator blade from hot press, carry out type repair the overlap of stator blade;
H, blast is carried out to the leading edge position of the stator blade that type is fixed and nickel leading edge bound edge and after cleaning up, uses adhesive to be bonded in stator blade leading edge by nickel leading edge bound edge.
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| CN201310663400.6A CN104690982B (en) | 2013-12-10 | 2013-12-10 | A kind of composite stator blade of engine and preparation method thereof |
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| CN201310663400.6A CN104690982B (en) | 2013-12-10 | 2013-12-10 | A kind of composite stator blade of engine and preparation method thereof |
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| CN104690982B CN104690982B (en) | 2018-02-02 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105128353A (en) * | 2015-07-09 | 2015-12-09 | 中国航空工业集团公司沈阳发动机设计研究所 | Forming die of integrally solidified composite material stator blade, and tail rim coating method thereof |
| CN109016560A (en) * | 2018-07-11 | 2018-12-18 | 江苏新扬新材料股份有限公司 | A kind of preparation method of grinding wheel sheet matrix |
| CN110439630A (en) * | 2019-08-12 | 2019-11-12 | 航天材料及工艺研究所 | A kind of Varying-thickness composite material stator blade and its forming method |
| CN111169036A (en) * | 2019-12-26 | 2020-05-19 | 中航复合材料有限责任公司 | Be used for fashioned flange frock of combined material fan blade tenon |
| CN115256996A (en) * | 2022-07-29 | 2022-11-01 | 中国航发沈阳发动机研究所 | Layering method for cavity area of composite material blade |
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| CN203702263U (en) * | 2013-12-10 | 2014-07-09 | 惠阳航空螺旋桨有限责任公司 | Composite stator blade of engine |
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| JP2013537595A (en) * | 2010-06-28 | 2013-10-03 | ヘラクレス | Turbomachine blades with complementary asymmetric geometry |
| CN103133268A (en) * | 2011-11-24 | 2013-06-05 | 德国恩德能源有限公司 | Wind turbine rotor blade having a heating element and a method of making the same |
| CN202520649U (en) * | 2011-12-29 | 2012-11-07 | 惠阳航空螺旋桨有限责任公司 | Large diameter cooling tower fan blade |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105128353A (en) * | 2015-07-09 | 2015-12-09 | 中国航空工业集团公司沈阳发动机设计研究所 | Forming die of integrally solidified composite material stator blade, and tail rim coating method thereof |
| CN105128353B (en) * | 2015-07-09 | 2017-04-19 | 中国航空工业集团公司沈阳发动机设计研究所 | Forming die of integrally solidified composite material stator blade, and tail rim coating method thereof |
| CN109016560A (en) * | 2018-07-11 | 2018-12-18 | 江苏新扬新材料股份有限公司 | A kind of preparation method of grinding wheel sheet matrix |
| CN110439630A (en) * | 2019-08-12 | 2019-11-12 | 航天材料及工艺研究所 | A kind of Varying-thickness composite material stator blade and its forming method |
| CN111169036A (en) * | 2019-12-26 | 2020-05-19 | 中航复合材料有限责任公司 | Be used for fashioned flange frock of combined material fan blade tenon |
| CN115256996A (en) * | 2022-07-29 | 2022-11-01 | 中国航发沈阳发动机研究所 | Layering method for cavity area of composite material blade |
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| CN104690982B (en) | 2018-02-02 |
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