CN108316977A - Multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud - Google Patents

Multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud Download PDF

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CN108316977A
CN108316977A CN201810059256.8A CN201810059256A CN108316977A CN 108316977 A CN108316977 A CN 108316977A CN 201810059256 A CN201810059256 A CN 201810059256A CN 108316977 A CN108316977 A CN 108316977A
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layer
self
healing
turbine outer
matric composite
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CN108316977B (en
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罗瑞盈
邓楚燕
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Beihang University
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Beihang University
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    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/08—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer the fibres or filaments of a layer being of different substances, e.g. conjugate fibres, mixture of different fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B9/041—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material of metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B9/047—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material made of fibres or filaments
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B9/048—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material made of particles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/14—Mixture of at least two fibres made of different materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2264/00—Composition or properties of particles which form a particulate layer or are present as additives
    • B32B2264/10—Inorganic particles
    • B32B2264/102—Oxide or hydroxide
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2264/00—Composition or properties of particles which form a particulate layer or are present as additives
    • B32B2264/10—Inorganic particles
    • B32B2264/107—Ceramic
    • B32B2264/108—Carbon, e.g. graphite particles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2264/00—Composition or properties of particles which form a particulate layer or are present as additives
    • B32B2264/12—Mixture of at least two particles made of different materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/70—Other properties
    • B32B2307/762—Self-repairing, self-healing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft

Abstract

The present invention relates to a kind of multi-component multi-layer self-healing ceramic matric composite engine turbine outer shrouds, and turbine outer ring is prepared using fiber reinforced ceramic matrix composites；Fiber reinforced ceramic matrix composites is made of fibrous layer, the first base layer and the second base layer successively；Wherein, the first base layer is aln layer；Fiber is carbon fiber and/or silicon carbide fibre.Multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud provided by the invention, by increasing AlN ceramic boundary layer between the fiber and silicon carbide substrate of multi-component multi-layer self-healing ceramic matric composite, the maximum stress inside turbine outer ring can be reduced, to effectively realize the energy release of material internal in cooling procedure, the formation for controlling crackle, can better meet the demand of engine especially High Performance Aeroengine.

Description

Multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud
Technical field
The present invention relates to technology field of ceramic matrix composite material, and in particular to a kind of multi-component multi-layer self-healing ceramic base is compound Material engine turbine outer shroud.
Background technology
With the development of civil and military aero-engine, the requirement for aero-engine is higher and higher, such as thrust-weight ratio It is higher and higher.And the main path that turbojet engine improves thrust-weight ratio is to reduce weight, improve turbine inlet temperature, to starting Machine internal component elevated temperature strength, corrosion resistance and antioxygenic property requirement are also higher and higher, and wherein engine turbine outer shroud is whirlpool Take turns main stator part, bear high temperature, high pressure, it is desirable that can free wxpansion, wear-resisting, touched with adapting to the expansion of casing and the appropriate of rotor Mill.Turbine outer ring generally use is Ni-based at present and cobalt base superalloy material and logical cold air cooling, it is difficult to meet engine health High temperature creep strength necessary to reliably working and high-temperature oxidation resistant corrosive power, and reduce engine structure weight and improve work( Again than demand, therefore, home and overseas is carrying out material, technique and the application study of ceramic base turbine outer ring.Due to pottery Porcelain based composites compared to high temperature alloy have higher tolerable temperature, lower density, it is insensitive to crackle, disaster does not occur The excellent properties such as the damage of property, it has also become the preferred material of engine turbine outer shroud.But due to aero-engine internal component work Make under high temperature water oxygen coupling ring border, it, need to be by being carried out to matrix in order to improve ceramic matric composite oxidation-resistance property Self-healing modification improves the long-time high-temperature oxidation resistance of ceramic matric composite.
For traditional multi-component multi-layer self-healing ceramic matric composite, due to the coefficient of thermal expansion phase such as fiber, SiC, BC4 It is poor big, the quick diffusion admittance to form oxygen is easily cracked between them because of thermal expansion mismatch, fiber/SiC parts is caused to lose Effect.Therefore, control crackle is formed, and is the difficult point for needing to overcome.
Invention content
For the defects in the prior art, present invention aims at provide a kind of multi-component multi-layer self-healing ceramic base composite wood Engine turbine outer shroud is expected, to reduce the maximum stress inside turbine outer ring, to effectively realize material internal in cooling procedure In energy release, control the formation of crackle.
To achieve the above object, technical solution provided by the invention is：
The present invention provides a kind of multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud, turbine outer ring is It is prepared using fiber reinforced ceramic matrix composites；Fiber reinforced ceramic matrix composites is successively by fibrous layer, the first base Body layer and the second base layer composition；Wherein, the first base layer is aln layer；Fiber is carbon fiber and/or silicon carbide fibre.It needs It is introduced it is noted that the present invention leads to nitrogen reduction synthesis process between carbon fiber and silicon carbide substrate by the oxide of aluminium and graphite A kind of new interface phase：AlN can since the coefficient of thermal expansion of boron nitride is between silicon carbide fibre and silicon carbide substrate The stress concentration at fibrous matrix interface is effectively relieved, effectively controls crackle and formed.It should be noted that in carbon fiber and carbonization The interfaces nitrogen reduction synthesis process introducing AlN are led to graphite by the oxide of aluminium between silicon substrate and mutually specifically include step：Using quality Than being 1:3 alumina powder and graphite is raw material, by ball milling mixing, obtains the powder that grain size is 5~15 μm, then will carbonization Silicon precast body embeds in the powder, is placed in graphite crucible, in N2AlN synthesis is carried out under atmosphere, synthesis temperature is 1600 DEG C, is protected Warm 4h；10h is kept the temperature in 600 DEG C, you can AlN boundary layers are made in air later.
Preferably, the second base layer is made of the silicon carbide layer and self-healing layer of alternating deposit.
Preferably, self-healing layer is BC4Layer.
Preferably, in the second base layer, the number of alternating deposit is multiple, multiple preferred finger 2~5 times, more preferably 2 It is secondary, it obtains being increased by the fiber that fibrous layer, aln layer, silicon carbide layer, self-healing layer, silicon carbide layer and self-healing layer form successively Strong ceramic matric composite.
Preferably, the thickness of the first base layer is 2 μm, and the thickness of each silicon carbide layer and each self-healing layer is 2 μm.
Preferably, the thickness of fibrous layer and the first base layer ratio is 2:1.
Preferably, the maximum stress of the inside of multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud is not high In 1.86GPa.
The present invention also protects multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud in preparing engine Application；Application especially in preparing aero-engine.
Technical solution provided by the invention has following advantageous effect：Multi-component multi-layer self-healing pottery provided by the invention Porcelain based composites engine turbine outer shroud, by the fiber of multi-component multi-layer self-healing ceramic matric composite and silicon carbide-based Increase AlN ceramic boundary layer between body, the maximum stress of material internal can be reduced, to effectively realize material internal cooled Energy release in journey, controls the formation of crackle；So as to better meet engine especially High Performance Aeroengine Demand.
The additional aspect and advantage of the present invention will be set forth in part in the description, and will partly become from the following description Obviously, or practice through the invention is recognized.
Description of the drawings
Fig. 1 is the structural model figure of 1/18 turbine outer ring in the embodiment of the present invention one；
Fig. 2 is the structural model mesh generation schematic diagram of 1/18 turbine outer ring in the embodiment of the present invention one；
Fig. 3 is that the structural model load of 1/18 turbine outer ring in the embodiment of the present invention one applies schematic diagram；
Fig. 4 is the displacement diagram after the structural model of 1/18 turbine outer ring in the embodiment of the present invention one solves；
Fig. 5 is the structural model stress envelope of 1/18 turbine outer ring in the embodiment of the present invention one；
Fig. 6 is the structural model inboard wall stress distribution map of 1/18 turbine outer ring in the embodiment of the present invention one；
Fig. 7 is the illustraton of model of the multi-component multi-layer ceramic matric composite in the embodiment of the present invention two；
Fig. 8 is that the model meshes of the multi-component multi-layer ceramic matric composite in the embodiment of the present invention two divide schematic diagram；
Fig. 9 is that the Model load of the multi-component multi-layer ceramic matric composite in the embodiment of the present invention two applies schematic diagram；
Figure 10 is the model stress distribution knot of traditional multi-component multi-layer ceramic matric composite in the embodiment of the present invention two Fruit is schemed；
Figure 11 is the model stress distribution of the improved multi-component multi-layer ceramic matric composite in the embodiment of the present invention two Result figure.
Specific implementation mode
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete Site preparation describes.The following examples are only intended to illustrate the technical solution of the present invention more clearly, therefore is intended only as example, without It can be limited the scope of the invention with this.Experimental method in following embodiments is unless otherwise specified conventional side Method.
The structure composition of multi-component multi-layer ceramic matric composite is carbon fiber or silicon carbide fibre as reinforcement, is passed through Matrix is replaced with self-healing constituent element and is added in composite material by CVI PIP preparation processes, by after being heat-treated, process etc. Continuous technique, is finally prepared.When being cooled to room temperature by preparation temperature due to composite material, the difference of inside and outside cooling velocity and The mismatch of coefficient of thermal expansion between matrix and reinforcement, can form residual stress in the composite.The thermal stress can be in base Interface between body and reinforcement is formed about stress concentration, is produced bigger effect to the mechanical property of composite material.
For traditional multi-component multi-layer self-healing ceramic matric composite, one of the most common is C/SiC-BC4 ceramic bases Composite material, structure are：Carbon fiber/(silicon carbide/carbon boron layer) n, n are 2~5 times, and table 1 gives multi-component multi-layer ceramic base The correlated performance of composite material composition.
The correlated performance of 1 multi-component multi-layer ceramic matric composite constituent of table
Material Elasticity modulus/GPa Poisson's ratio Density g/cm3
Carbon fiber 220 0.12 1.75
SiC 350 0.2 3.06
BC4 360 0.2 2.5
AlN 310 0.2 3.26
From table 1 it follows that since there are the differences of larger coefficient of thermal expansion between silicon carbide fibre and silicon carbide substrate It is different, so causing crackle to generate to forming larger stress concentration easily between fiber and matrix during material preparation, it is unfavorable for Material at high temperature is anti-oxidant, is closed so the present invention leads to nitrogen reduction between carbon fiber and silicon carbide substrate by the oxide of aluminium and graphite A kind of new interface phase is introduced at method：AlN, since the coefficient of thermal expansion of boron nitride is between silicon carbide fibre and silicon carbide substrate Between, the stress concentration at fibrous matrix interface can be effectively relieved, effectively control crackle and formed.
Below by specific embodiment to multi-component multi-layer self-healing ceramic matric composite engine provided by the invention whirlpool Wheel outer shroud is described further.
Embodiment one
The present embodiment provides a kind of multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud, turbine outer ring is It is prepared using fiber reinforced ceramic matrix composites；Fiber reinforced ceramic matrix composites successively by silicon carbide fibre layer, First base layer and the second base layer composition；Wherein, the first base layer is aln layer；Second base layer by alternating deposit carbon SiClx layer and self-healing layer BC4The number of layer composition, alternating deposit is 2 times.That is, the fiber reinforcement pottery in the present embodiment Porcelain based composites include successively：Silicon carbide fibre layer, aln layer, silicon carbide layer, BC4Layer, silicon carbide layer and BC4Layer, carbonization The thickness of silica fibre layer is 4 μm, and the thickness of aln layer is 2 μm, and the thickness of each silicon carbide layer and each self-healing layer is 2 μm.
For the embodiment, inventor is compound to multi-component multi-layer self-healing ceramic base by finite element analysis software ANSYS Stress behavior in the cooling procedure of material engine turbine outer shroud is analyzed.
Specifically, ceramic matric composite parameter is set as：Elasticity modulus is：103GPa, coefficient of thermal expansion are equal 4.0MK-1, Poisson's ratio equal 0.149, the equal 2.14g/cm of density3.The thermal conductivity of fiber and matrix be respectively 40.98W/ (mK) and 36.55W/(m·K)。
It is 1/18 structure of turbine outer ring as shown in Figure 1, since turbine outer ring is cyclic symmetric structure, it is possible to select Take 1/18 wherein representative structure as research object, the result of study one of result of study and integral turbine outer shroud It causes.
The group of turbine outer ring Local map becomes：Inner wall be radian be 20 ° of internal diameter be 100, outer diameter 102, a height of 10 Cylinder, middle layer be radian be 20 ° of internal diameter be 102, outer diameter 104, a height of 8 cylinder, outer layer is the cylinder group in L-type section At, wherein " 1 " is partly radian be 20 ° of internal diameter be 104, outer diameter 104.5, a height of 10 cylinder (the cylinder bottom of front three Portion is coplanar), "-" part be radian be 20 ° of internal diameter be 104.5, outer diameter 107, a height of 1 cylinder is finally 2 ° in radian To between 9 °, internal diameter 102, outer diameter 107, a height of cylinder region from the part of Z axis 1 to 1 hollows out, and is equally in radian Between 11 ° to 18 °, internal diameter 102, outer diameter 107 is a height of to be hollowed out from the part cylinder region of Z axis 1 to 1, and final combination obtains The partial structurtes of turbine outer ring.
Mesh generation is carried out to model using Structural Solid Brick 8node Unit 45.The unit is 3D Entity member：For 3D solid elements for simulating 3D solid structure, such each node of unit all has three degree of freedom, i.e. Ux, Tri- translational degree of freedom of Uy, Uz.Unit size control selections when being partitioned from by grid are SmartSizing, use free net Lattice divide, free mesh, to physical model without particular/special requirement.
In finite element modelling, cooling procedure is realized by applying temperature loading.Inner wall temperature is set as 1300 DEG C, outside Side temperature setting is 20 DEG C, since turbine outer ring to be gone can be in axial and circumferential free wxpansion, so entire model is only arranged Z-direction displacement be 0.
As can be seen from Figure 6 maximum stress value is located at internal face.
Embodiment two
By traditional multi-component multi-layer self-healing ceramic matric composite and the improved composite material (embodiment of the present invention one The multi-component multi-layer self-healing ceramic matric composite of offer) ANSYS finite element modellings are carried out, both analyses are in High-temperature cooling process The distribution of middle residual stress.Concrete analysis process is as follows.
1, the micromodel of multi-component multi-layer self-healing ceramic matric composite is established
For traditional multi-component multi-layer self-healing ceramic matric composite, structure is：Silicon carbide fibre/silicon carbide/from Heal layer/silicon carbide/self-healing layer/silicon carbide, and wherein self-healing layer is BC4 layers, for improved multi-component multi-layer self-healing Ceramic matric composite, as a result silicon carbide fibre/aluminium nitride/silicon carbide/self-healing layer/silicon carbide/self-healing layer, i.e., with Traditional structure difference is that AlN layers are increased between silicon carbide fibre and silicon carbide substrate, internal alternate matrix thickness Degree is 2 μm, and the thickness ratio of the first base layer (silicon carbide layer) and carbon fiber is 1:2.By selecting representative knot Structure unit (internal face maximum stress value structural unit) is used as research object, to the structure of multi-component multi-layer ceramic matric composite into Row analysis.The model schematic of multi-component multi-layer ceramic matric composite is as shown in Figure 7.
2, mesh generation
For multi-component multi-layer self-healing ceramic matric composite, definition unit type is octahedral unit, and is arranged each Partial material property parameter.It is as shown in Figure 8 that the model meshes of multi-component multi-layer ceramic matric composite divide schematic diagram.
3, apply load and boundary condition
In order to keep the consistency of microstructure and macrostructure stress, the displacement constraint in the faces setting X=0 is the faces 0, Y=0 Displacement constraint be 0；The temperature loading that the faces X=0 are arranged simultaneously is 1300 DEG C.The model of multi-component multi-layer ceramic matric composite carries It is as shown in Figure 9 that lotus applies schematic diagram.
4, analysis result compares
Figure 10 and Figure 11 is respectively stress envelope and the improvement of traditional multi-component multi-layer self-healing ceramic matric composite The stress envelope of multi-component multi-layer self-healing ceramic matric composite afterwards.
As can be seen that applying AlN influences less the overall trend of stress distribution from Figure 10 and Figure 11, but two kinds of moulds The maximum stress of type is respectively 1.9444GPa and 1.8554GPa, that is, after increasing AlN layers, the maximum stress of material internal declines 4.58%.
To sum up, by increasing AlN potteries between the fiber and silicon carbide substrate of multi-component multi-layer self-healing ceramic matric composite Porcelain boundary layer can effectively realize the energy release of material internal in cooling procedure, control the formation of crackle.
It should be noted that unless otherwise indicated, technical term or scientific terminology used in this application should be this hair The ordinary meaning that bright one of ordinary skill in the art are understood.Unless specifically stated otherwise, it otherwise illustrates in these embodiments Component and opposite step, numerical expression and the numerical value of step are not limit the scope of the invention.It is illustrated and described herein In all examples, unless otherwise prescribed, any occurrence should be construed as merely illustrative, not as limitation, because This, other examples of exemplary embodiment can have different values.
In the description of the present invention, it is to be understood that, term " first ", " second " are used for description purposes only, and cannot It is interpreted as indicating or implies relative importance or implicitly indicate the quantity of indicated technical characteristic.Define as a result, " the One ", the feature of " second " can explicitly or implicitly include one or more this feature.In the description of the present invention, The meaning of " plurality " is two or more, unless otherwise specifically defined.
Finally it should be noted that：The above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations；To the greatest extent Present invention has been described in detail with reference to the aforementioned embodiments for pipe, it will be understood by those of ordinary skill in the art that：Its according to So can with technical scheme described in the above embodiments is modified, either to which part or all technical features into Row equivalent replacement；And these modifications or replacements, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution The range of scheme should all cover in protection scope of the present invention.

Claims (9)

1. a kind of multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud, it is characterised in that：
The turbine outer ring is prepared using fiber reinforced ceramic matrix composites；The fiber reinforced ceramic-base composite wood Material is made of fibrous layer, the first base layer and the second base layer successively；
Wherein, first base layer is aln layer；The fiber is carbon fiber and/or silicon carbide fibre.
2. multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud according to claim 1, feature exist In：
Second base layer is made of the silicon carbide layer and self-healing layer of alternating deposit.
3. multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud according to claim 2, feature exist In：
The self-healing layer is BC4Layer.
4. multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud according to claim 2, feature exist In：
In second base layer, the number of alternating deposit is multiple, preferably 2 times, is obtained successively by fibrous layer, aluminium nitride The fiber reinforced ceramic matrix composites of layer, silicon carbide layer, self-healing layer, silicon carbide layer and self-healing layer composition.
5. multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud according to claim 2, feature exist In：
The thickness of first base layer is 2 μm, and the thickness of each silicon carbide layer and each self-healing layer is 2 μm.
6. multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud according to claim 2, feature exist In：
The thickness ratio of the fibrous layer and first base layer is 2:1.
7. multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud according to claim 1, feature exist In：
The maximum stress of the inside of the multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud is not higher than 1.86GPa。
8. the multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud described in any one of claim 1-7 is being made Application in preparation motivation.
9. the multi-component multi-layer self-healing ceramic matric composite engine turbine outer shroud described in any one of claim 1-7 is being made Application in standby aero-engine.
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