JPH0867574A - Part prepared from fiber-reinforced ceramic-based composite material and its production - Google Patents

Abstract

PURPOSE: To obtain a part prepared from fiber-reinforced ceramic-based composite material improved in initial fracture strength, fracture energy and oxidation resistance, and having high reliability. CONSTITUTION: This part is so designed as to laminatedly put plural fiber layers 3 in a ceramic matrix 2 and has such a characteristic that the fiber content within the region from at least one surface thereof to T/3 in depth is lower than that within the region from T/3 to 2T/3 in depth (where, T is the thickness of the part in the direction rectangular to the fiber layers 3). Besides, it is recommended that a specified thickness of a matrix layer be provided on the whole surface of the part.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ceramic-based fiber composite material component and a method for producing the same, and more particularly to a ceramic-based fiber composite material component having improved initial fracture strength, fracture energy and oxidation resistance and having high reliability. The manufacturing method is related.

[0002]

2. Description of the Related Art Generally, a ceramic sintered body has little strength decrease up to a high temperature, and has various characteristics such as hardness, electric insulation, wear resistance, heat resistance, corrosion resistance, and lightness as compared with conventional metal materials. Since it is excellent, it is used in a wide range of fields as electronic materials and structural materials such as heavy electric equipment parts, aircraft parts, automobile parts, electronic devices, precision machine parts, and semiconductor device materials.

However, the ceramics sintered body is weaker in tensile stress than in compressive stress, and has a defect of so-called brittleness in which fracture progresses at a stretch under this tensile stress. For this reason, in order to enable the application of the ceramic component to the site where high reliability is required, it is strongly required to increase the toughness and increase the fracture energy of the ceramic sintered body.

That is, gas turbine parts, aircraft parts,
High reliability is required in addition to heat resistance and high temperature strength such as ceramic structural parts used for automobile parts.
For this reason, research on the practical application of ceramics composite material parts in which reinforcing materials made of inorganic substances and metals, whiskers, plates, particles, and other reinforcing materials are dispersed and compounded in a matrix sintered body to increase the toughness value and fracture energy value, etc. Are being promoted by research institutes.

[0005]

However, among the ceramic composite material parts as described above, the simple and small shape using long fibers as a reinforcing material is excellent in the effect of increasing fracture toughness and fracture energy and is reliable. However, when it is actually applied to a large-sized component having a complicated shape, especially a thick component, there is a problem that the strength and the breaking energy value are significantly reduced.

Up to now, various prototypes of ceramic-based fiber composite material parts have been manufactured at a relatively small test piece level, but for large-sized thick parts, a firm manufacturing method thereof has not yet been established. The point that is not left as an issue. Therefore, control of the microstructure corresponding to the shape of the ceramic composite material is also insufficient, and sufficient and stable properties such as high temperature strength and toughness value have not yet been obtained.

That is, a ceramic-based fiber composite material component having a structure in which a plurality of fiber layers or woven fabrics formed by arranging long fibers in one direction or two directions are laminated in a ceramic matrix has been put into practical use. But,
The effect of the arrangement of the above-mentioned woven fabric in the matrix on the strength properties etc. has not been sufficiently studied. In some cases, the strength of the composite material component is significantly smaller than that of the monolithic ceramic material, which has been a factor that hinders the widespread practical use of the composite material as a mechanical component.

Further, in the conventional composite material parts, the fiber as the reinforcing material is exposed on the surface of the parts, and there is a problem that surface defects due to oxidation are likely to occur particularly in the case of parts used in high temperature conditions. . That is, a gap is likely to be formed at the interface between the fiber exposed on the surface of the component and the matrix due to oxidation, and stress concentrates in the gap and cracks develop even at low stress, so the initial fracture strength of the component is small,
Once a crack has once occurred, there is a problem that the material deterioration further progresses rapidly and the fracture energy value sharply decreases.

The present invention has been made to solve the above problems, and provides a ceramic-based fiber composite material component having improved initial fracture strength, fracture energy and oxidation resistance and high reliability, and a method for producing the same. The purpose is to provide.

[0010]

In order to achieve the above object, the inventors of the present application have clarified the mechanism of crack generation when the above composite material part is used as a mechanical part, and obtained the following findings. That is, when an external force acts on a composite material component that is a combination of a ceramic fiber and a ceramic matrix material that are currently technically available, in many cases, the amount of strain leading to fracture is greater in the fiber portion than in the matrix portion. The initial crack of the composite material component is likely to occur in the matrix portion because the thermal stress and the mechanical stress tend to concentrate near the surface of the component. The occurrence of this initial crack causes the strength of the component to decrease.

Therefore, by relatively increasing the matrix fraction in the vicinity of the surface of the component where thermal stress or mechanical stress is likely to be concentrated, the initial fracture strength is increased and the fracture energy of the entire component is significantly increased. We have found that it will be possible.

Further, by forming a matrix simple substance layer having a predetermined thickness integrally on the surface of the component so that the fibers are not exposed on the surface of the component, the fibers themselves and the interface layer between the fibers and the matrix are deteriorated by the influence of heat and oxidation. It has been found that the above can be effectively prevented, and that temporal changes in mechanical properties such as breaking energy can be prevented.

The present invention has been completed based on the above findings. That is, the ceramic-based fiber composite material component according to the present invention is a ceramic-based fiber composite material component in which a plurality of fiber layers are laminated and arranged in a matrix made of ceramics, and the component thickness in the direction perpendicular to the fiber layer is T. Where T / from at least one surface of the component
The fiber content in the region within 3 is from T / 3 to 2T /
It is characterized by being smaller than the fiber content in the region up to 3. Further, the thickness of the matrix located between the fiber layers may be equal to or larger than the thickness of the fiber layers. Furthermore, it is preferable to integrally form a single matrix layer having a thickness of 500 μm or less on the entire surface of the component.

As another aspect, the ceramic-based fiber composite material component according to the present invention has a matrix layer having a thickness of 500 μm or less integrally formed on the entire surface of a composite body in which fibers are dispersed in a matrix made of ceramics. It is characterized by being formed. Further, the content ratio of fibers in the composite is preferably set to 5 to 60% by volume.

Here, various ceramics can be used as the ceramics forming the matrix of the ceramic-based fiber composite material component, and for example, silicon carbide (SiC), aluminum nitride (AlN), silicon nitride (Si _3). N ₄ ), boron nitride (BN), sialon (Si-Al-O-N) and other non-oxide general-purpose ceramics sintered bodies, alumina, zirconia, titania, mullite, beryllia, cordierite, zircon, etc. One or a mixture of oxide-based ceramics and silicide-based ceramics such as molybdenum silicide is used. If necessary, a sintering aid or additive such as yttrium oxide, aluminum oxide, cerium oxide, magnesium carbonate, calcium carbonate, or silicic acid is added to the ceramic raw material powder for forming the sintered body. . It is also possible to form the matrix during the reactive sintering process.

The fibers dispersed or laminated in the matrix are compounded in a predetermined amount in order to enhance the toughness of the composite material component. The material of the above fiber is
It is not particularly limited, and ceramic fibers or metal fibers similar to the constituent material of the matrix can be used. Specific examples of such ceramic fibers include silicon carbide-based fibers (SiC, Si-C-O, Si-
Ti—C—O, etc.), SiC coated fiber (core wire is C, for example), alumina fiber, zirconia fiber, carbon fiber, boron fiber, silicon nitride fiber, Si ₃ N ₄ coated fiber (core wire is C) and mullite. (3Al ₂ O ₃ · 2SiO
_{2 ~2Al 2 O 3 · SiO 2} ) has fibers, it may use at least one selected from these.

These fibers are added at a fiber volume ratio (Vf) of 5% or more with respect to the entire composite material component.
However, if the added amount exceeds 60%, it becomes difficult to uniformly arrange the matrix around each fiber, and the strength characteristics of the composite material component are rapidly deteriorated due to the occurrence of defects such as voids. Therefore, the preferred amount of addition that produces a combined effect is in the range of 20 to 40% by volume.

The diameter and the length of the fiber have a great influence on the shape-imparting property, the dispersion and orientation of the fiber, and the material properties such as strength and fracture energy of the composite material part. In the present invention, the diameter is 3 ~ 150μm, length 0.1mm
The above short fibers or continuous fibers are used. Diameter is 3 μm
If it is less than the above, the reinforcing effect of the matrix is small, and in the case of a thick fiber having a diameter of more than 150 μm, the effect of preventing crack propagation in the target microscopic range cannot be expected, and the fiber has a high rigidity to impart a shape. It becomes difficult to remove. Also, when the length of the fiber is less than 0.1 mm, the effect of preventing crack growth is small and the effect of improving toughness is small.

That is, by using fibers having a diameter of 3 to 150 μm and a length of 0.1 mm or more, it is possible to significantly improve the composite effect of the fibers while maintaining good shape imparting performance. Become. However, if the content of such fibers is less than 5%, the composite effect of the fibers is reduced, so the content of fibers is preferably 5% or more.

The interface between the fibers and the matrix is
An interface layer having a thickness of 5 μm or less may be formed on the surface of the ceramic fiber in order to effectively develop the pull-out of the fiber after the initial fracture and to prevent the reaction between the two and to make the slip resistance at the interface a proper value. This interface layer is formed by coating the surface of the fiber with carbon (C) or boron nitride (BN).

The above-mentioned interface layer relaxes the strong bonding strength between the ceramic fiber and the matrix, peels off at the interface when stress is applied, and pulls out the fiber which is indispensable for improving the toughness, resulting in a high toughness value. A composite material part is obtained.

Further, a matrix layer having a thickness of 500 μm or more and composed only of a matrix is integrally formed on the entire surface of the composite material part so that the fibers themselves and the interface between the fibers and the matrix are not exposed on the surface of the composite material part. As a result, it is possible to effectively suppress deterioration of characteristics due to heat and oxidation. The matrix layer has a thickness of 500 μm
By the following formation, the above-mentioned characteristic deterioration preventing function can be sufficiently exhibited without significantly impairing the composite effect of the fibers.

A plate-shaped ceramic-based fiber composite material component in which a plurality of fiber layers are laminated and arranged in the matrix is
For example, it is manufactured as follows. That is, ceramic raw material powders containing sintering aids and additives are laminated and arranged at a predetermined ratio above and below each fiber woven fabric layer formed by weaving a bundle of ceramic fibers (yarn) It is manufactured by sintering the molded body in a non-oxidizing atmosphere by a hot pressing method, an atmospheric pressure sintering method or a reaction sintering method.

The fiber content in the region within T / 3 from at least one surface of the composite material component (total thickness T) obtained here is smaller than in the region between T / 3 and 2T / 3. Is adjusted. If the region where the fiber content is low exceeds T / 3, the initial fracture stress of the component increases and the strength improves, but the toughness or fracture energy decreases.

On the other hand, a ceramic-based fiber composite material component having a complicated shape, such as a turbine rotor blade, instead of a flat plate shape, is manufactured, for example, by the following method. That is, by knitting fibers, a preformed body (preform) having a shape similar to a predetermined part is formed, and a ceramic slurry serving as a matrix is impregnated into the preformed body to form a primary molded body. The compact is pre-sintered to form a calcined body, and the calcined body obtained is ground and polished to form a secondary compact having a predetermined shape, and a ceramic slurry is formed on the entire surface of the secondary compact. Is applied and then main-sintered.

Further, instead of coating the ceramic slurry on the entire surface of the secondary compact and then sintering the slurry to form a matrix single layer, the secondary compact is main-sintered to form a composite. CVD method (Chemical Vapor Deposition method) on all surfaces of the body
Etc. may be used to form a matrix layer having a predetermined thickness. Furthermore, a matrix layer having a predetermined thickness may be formed by combining a method of applying a ceramics slurry on the entire surface of the secondary molded body and sintering it, and a CVD method.

The thickness of the matrix layer is set to 500 μm or less. If the thickness exceeds 500 μm, a portion having a small fiber content (fiber volume ratio Vf) is formed in the vicinity of the surface of the component, so that the breaking energy of the component is reduced. On the other hand, when the thickness of the matrix layer is less than 5 μm, it becomes difficult to completely cover the fibers exposed on the surface of the component, defects are likely to occur in the fiber exposed portion, and the initial breaking strength and oxidation resistance of the component are reduced. Resulting in. Therefore,
The thickness of the matrix layer may be set to 5 to 500 μm.

According to the above-mentioned manufacturing method, it becomes possible to uniformly form a matrix layer having a constant thickness on the entire surface of the component in units of micron, and the matrix layer lowers the initial breaking strength and oxidation resistance of the matrix. Can be effectively prevented.

[0029]

According to the above ceramic-based fiber composite material component and its manufacturing method, the fiber content in the region within T / 3 from at least one surface of the component is higher than that in the region between T / 3 and 2T / 3. Since the size is made smaller and the matrix fraction in the surface portion is increased, the initial fracture strength at the surface portion of the component is increased, and a composite material component having large fracture energy and high reliability as a whole component can be obtained.

Particularly, by forming a matrix layer having a predetermined thickness integrally on the entire surface of the component so that the fibers are not exposed, deterioration of the fibers themselves and the bonding interface between the fibers and the matrix due to heat and oxidation may occur. It can be effectively prevented.

Therefore, by using the composite material component of the present invention as a mechanical component which is used in a severe corrosive atmosphere at high temperature and where stress concentration is likely to occur, deterioration due to oxidation and breakage due to stress concentration are suppressed, and reliability is improved. It is possible to provide a device having excellent properties.

[0032]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described below with reference to the accompanying drawings.

Examples 1 to 6 500 continuous SiC fibers having a diameter of 15 μm are bundled, the surface of the fiber bundle (yarn) is coated with carbon (C) having a thickness of 0.5 μm, and the carbon-coated yarn is woven. A plain weave cloth woven fabric was produced. On the other hand, 5% by weight of Y was added to each of Si ₃ N ₄ powder having an average particle size of 1.0 μm.
₂ O ₃ powder and 3% by weight of Al ₂ O ₃ powder were added as sintering aids and uniformly mixed with a mixer to prepare a matrix raw material powder.

Next, the matrix raw material powder and the fiber woven fabric were sequentially stacked and packed in a molding die at different filling ratios, and then compression-molded at a pressing pressure of 20 MPa to obtain a molded body for each example. Next, each of the obtained compacts was set in a hot press machine and sintered in a nitrogen gas atmosphere under a pressure of 40 MPa at a temperature of 1600 ° C. for 1 hour to obtain Examples 1 to 6 as shown in FIG. Composite material part 1 was manufactured.

In the composite material component 1 according to each example, as shown in FIG. 1, a plurality of fiber layers 3 made of SiC fibers and having a thickness F are laminated in a matrix 2 made of a sintered Si ₃ N ₄ body. It has a structure. Then, the total thickness of the component 1 is T
In such a case, in the region (first region and third region) within T / 3 from both surfaces of the component, the arrangement pitch (P ₁ , P ₃ ) of the fiber layer 3 is made sparse to thereby make The fiber content (fiber volume ratio) is reduced. On the other hand, in the intermediate area (second area) other than the above area,
By making the arrangement pitch (P ₂ ) of the fiber layers 3 dense, the fiber content in the intermediate region is relatively increased. A surface matrix layer 2a (thicknesses t ₁ , t ₂ , t ₃ ) containing no fiber is integrally formed on the surface portion, the side surface portion, and the back surface portion of the component 1, if necessary.

With respect to the composite material parts 1 according to the respective examples prepared as described above, the thickness t of the surface matrix layer 2a
Tables 1 and 1 show t ₁ , t ₂ and t ₃ , and the arrangement pitches P ₁ , P ₂ and P ₃ of the fiber layer 3 in the respective regions. The thickness of the fiber layer 3 is 200 μm, and the total thickness T of the component 1 is T.
Was 12 mm.

In order to evaluate the properties such as strength and toughness of the composite material component 1 according to each example, a test piece was cut out from each component 1 and its initial fracture stress, maximum stress and fracture energy were measured. The test piece has a thickness T of 1
The rectangular parallelepiped has a width of 2 mm, a width W of 16 mm, and a length L of 150 mm. For this test piece, a 3-point bending test was performed with a span of 120 mm, a stress-strain curve was recorded, and the stress that indicated the initial failure in this stress-strain curve was converted into a 3-point bending strength formula to determine the initial failure stress. On the other hand, the maximum stress was similarly converted to the maximum load on the curve. Further, the area surrounded by the same curve was integrated to calculate the fracture energy. Each breaking energy was shown as a relative value with the breaking energy value of the test piece of Comparative Example 1 below as the reference value 1.

Comparative Examples 1 to 2 except that t ₁ = t ₂ = t ₃ = 0, the surface matrix layer 2a was not formed, and the fiber layers were arranged at a predetermined pitch over the entire region in the thickness direction. The composite material parts according to Comparative Examples 1 and 2 having the same thickness (T = 12 mm) as in Examples 1 and 2 were prepared by treating in the same manner as in Examples 1 and 2, and respective characteristic values were measured in the same manner.

Comparative Examples 3 to 4 The same processing is performed as in Examples 3 to 4 except that the thickness of the matrix located in the first and third regions is set smaller than that in the second region. The composite material parts according to Comparative Examples 3 to 4 were prepared, and the respective characteristic values were measured in the same manner.

The measured values are summarized in Table 1 below.

[0041]

[Table 1]

As is clear from the results shown in Table 1, the ceramic bases according to Examples 1 to 6 in which the fiber content in the region within T / 3 from both surfaces of the component was set smaller than the content in the intermediate region In the fiber composite material part, since the matrix fraction in the surface portion is higher than in any of Comparative Examples 1 to 4, the initial fracture strength is increased, the fracture progress resistance is increased, and the fracture energy is large, It was confirmed to have excellent durability and reliability as parts.

In particular, in the composite material parts according to Examples 3 to 6 in which the matrix layer is formed relatively thick on the surface portion, the initial fracture strength is further improved and the fiber layer is not exposed on the surface of the part. Therefore, deterioration of the fiber itself and the bonding interface between the fiber and the matrix due to heat and oxidation can be prevented, and a composite material component having excellent durability was obtained.

On the other hand, in the composite material parts according to Comparative Examples 1 to 4, since the fibers are arranged uniformly over the entire area or more in the area near the surface than in the interior, the toughness as a whole is good, but The initial fracture stress at the surface is small, and as a result the effective fracture energy is small,
It has been found that there are drawbacks that cracks easily occur and cracks easily propagate. It was found that the components according to Comparative Examples 3 to 4 were excellent in oxidation resistance because they had a matrix layer formed on the surface, but had the same drawbacks as described above.

According to this embodiment, a laminated ceramic-based fiber composite material part having a high initial fracture strength of the matrix and a high fracture propagation resistance can be obtained.

In the above-mentioned embodiment, a flat plate-shaped ceramic-based fiber composite material component in which a plurality of fiber layers are laminated and arranged in a matrix is exemplified. Next, the composite material component of the present invention is formed into a complicated shape. An example will be described in which the invention is applied to a turbine rotor blade that the present invention has.

Example 7 Phenol was prepared by weaving an SiC continuous fiber having a diameter of 15 μm (trade name: Hynicalon, manufactured by Nippon Carbon Co., Ltd.), winding a tape-shaped woven fabric around a core having a desired component shape, and diluting it. Using resin as a shape-retaining agent,
A preform (fiber laminated preform) 4 having a three-dimensional shape as shown in (a) was prepared.

On the other hand, SiC powder (particle size 32
(μm or less) and carbon black as a carbon source were dispersed in a solvent to prepare a low-viscosity matrix slurry. Next, the preform 4 was pressure-impregnated and filled with the matrix slurry by using the pressure casting method. The molding pressure was 5 MPa and the molding time was 10 minutes. The amount of the matrix slurry impregnated was set so that the fiber content rate (fiber volume ratio: Vf) in the composite material was 30%. Further, the preformed body impregnated with the matrix slurry was dried to prepare a primary formed body 5 as shown in FIG. 2 (b).

Next, the primary compact shown in FIG. 2 (b) was calcined (pre-sintered) at a temperature of 1000 ° C. for 1 hour in an argon atmosphere to form a calcined body. By this calcination treatment, the primary molded body 5 was provided with a strength sufficient to withstand the raw processing in the next step. Next, the obtained calcined body is subjected to raw processing to be finished into a dimension close to the shape of the component, and
A secondary molded body 6 as shown in (c) is obtained. In this green processing, the size of the secondary molded body 6 is set to a value obtained by subtracting the thickness of the surface matrix layer described later from the size of the target part. As shown in FIG. 2C, the fibers 7 are partially exposed on the surface of the secondary molded body 6.

Next, on the entire surface of the green-formed secondary molded body 6,
Using the spraying method, the matrix slurry was uniformly applied, naturally dried, and then degreased at 600 ° C. for 2 hours in a N ₂ gas atmosphere in order to remove the organic component added to the slurry as a molding aid. After that, main body sintering (reaction sintering) is performed by heating at a temperature of 1420 ° C. for 2 hours while impregnating the molded body with molten Si in a vacuum, and the reaction sintered SiC made of SiC is formed inside the secondary molded body 6. At the same time as forming the matrix, a thickness of 200 to 10 is formed on the surface of the secondary molded body 6.
A matrix layer 2a of 00 μm was integrally formed, and surface finishing for final finishing was performed to manufacture a turbine rotor blade 8a as a SiC-based fiber composite material component 8 as shown in FIG. 2 (d).

Comparative Example 5 On the other hand, except that the matrix layer 2a was not formed, the same treatment as in Example 7 was carried out to prepare a turbine rotor blade according to Comparative Example 5 having the same dimensions.

The initial breaking strengths of the turbine rotor blades of Example 7 thus prepared were higher than those of Comparative Example 5 and about 300 MPa, and the resistance to crack propagation was sufficiently high. It is difficult to generate and develop, and it has excellent durability and excellent characteristics. However, it was confirmed that when the thickness of the surface matrix layer was set to a value exceeding 500 μm, the initial fracture strength increased, but the fracture energy tended to decrease. Therefore, the thickness of the surface matrix layer is 500 μm or less, preferably 30 μm.
It is necessary to set it to 0 μm or less.

On the other hand, in the turbine rotor blade according to Comparative Example 5, the composite fiber was exposed on the surface, so that the initial fracture strength and oxidation resistance of the matrix were significantly reduced as compared with Example 7, and the durability was improved. The sex is inferior.

Conventionally, it was very difficult to uniformly form a matrix layer having a constant thickness on the entire surface of a component having a complicated shape. However, according to the method for manufacturing a composite material component according to this embodiment. For example, even in the case of a component having a complicated shape in a turbine blade, it becomes easy to uniformly form a matrix layer having a constant thickness on the entire surface thereof. Further, by integrally forming a matrix layer having a predetermined thickness on the entire surface of the component, the initial fracture strength and the oxidation resistance can be greatly improved, and the composite material component excellent in durability was easily obtained.

In the above-mentioned embodiment, an example is shown in which the slurry is applied to the entire surface of the secondary molded body and then main-baked to form a matrix single layer. However, in place of the above forming method, when the secondary compact is main-sintered to form a composite and a matrix simple substance layer having a predetermined thickness is formed on the surface of the composite by the CVD method, almost the same characteristics are obtained. Was obtained.

[0056]

As described above, according to the ceramic-based fiber composite material component and the manufacturing method thereof according to the present invention,
Since the fiber content in the region within T / 3 from at least one surface of the component is smaller than that in the region from T / 3 to 2T / 3, and the matrix fraction in the surface is increased, the component surface The initial breaking strength increases,
Highly reliable composite material parts with high breaking energy as a whole can be obtained.

Particularly, by forming a matrix layer having a predetermined thickness integrally on the entire surface of the component so that the fibers are not exposed, deterioration of the fibers themselves and the bonding interface between the fibers and the matrix due to heat and oxidation is caused. It can be effectively prevented.

Therefore, by using the composite material part of the present invention as a mechanical part which is used in a severe corrosive atmosphere at high temperature and where stress concentration is likely to occur, deterioration due to oxidation and breakage due to stress concentration are suppressed, and reliability is improved. It is possible to provide a device having excellent properties.

[Brief description of drawings]

FIG. 1 is a cross-sectional view showing the structure of a ceramic-based fiber composite material component according to the present invention.

FIG. 2 is a perspective view showing a manufacturing process of a turbine blade as a ceramic-based fiber composite material component according to the present invention,
(A) is a perspective view showing the shape of a preform, (b) is a perspective view showing a state where the preform is impregnated with a matrix,
(C) is a perspective view showing a state after raw processing of a preformed body impregnated with a matrix, and (d) is a perspective view showing a state where a matrix simple substance layer is formed on the surface of the raw processed calcined body.

[Explanation of symbols]

1,1a Ceramics-based fiber composite material component 2 Matrix (Si ₃ N ₄ ) 2a Matrix layer 3 Fiber layer (SiC) 4 Preform (fiber laminated preform) 5 Primary compact 6 Secondary compact 7 Fiber 8 SiC base Fiber composite material parts 8a Turbine rotor blade

Claims (6)

[Claims] 1. A ceramic-based fiber composite material component in which a plurality of fiber layers are laminated and arranged in a matrix made of ceramics, where T is the thickness of the component in the direction perpendicular to the fiber layer. T / from the surface
The fiber content in the region within 3 is from T / 3 to 2T /
A ceramic-based fiber composite material part having a fiber content smaller than that in the region up to 3. 2. The ceramic-based fiber composite material component according to claim 1, wherein a matrix layer having a thickness of 500 μm or less is integrally formed on the entire surface of the component. 3. A composite having a matrix made of ceramics and fibers dispersed therein has a thickness of 500 μm.
A ceramic-based fiber composite material part, characterized in that a matrix layer of m or less is integrally formed. 4. The content ratio of fibers in the composite is 5 to 5.
The ceramic-based fiber composite material component according to claim 3, wherein the content is 60% by volume. 5. A preformed body (preform) having a shape close to that of a component is formed by using a fiber woven fabric, and a ceramic slurry serving as a matrix is impregnated into the preformed body to form a primary molded body. The obtained primary compact is pre-sintered to form a calcined body, and the calcined body obtained is ground and polished to form a secondary compact having a predetermined shape, and the entire surface of the secondary compact is formed. A method for manufacturing a ceramics-based fiber composite material part, which comprises applying a ceramics slurry to and then performing main sintering. 6. A fibrous woven fabric is used to form a preformed body (preform) having a shape similar to that of a component, and the preformed body is impregnated with a ceramics slurry serving as a matrix to form a primary molded body. The obtained primary compact is pre-sintered to form a calcined body, and the calcined body obtained is ground and polished to form a secondary compact having a predetermined shape. A characteristic is that a ceramic slurry is applied to the entire surface and then main sintering is performed to form a composite, and a matrix single layer having a thickness of 200 μm or less is integrally formed on the entire surface of the composite by using a CVD method. And a method for producing a ceramic-based fiber composite material part.