CN114810820A - Integrated-structure special-shaped bearing based on ceramic matrix composite material and preparation method thereof - Google Patents
Integrated-structure special-shaped bearing based on ceramic matrix composite material and preparation method thereof Download PDFInfo
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- CN114810820A CN114810820A CN202210500514.8A CN202210500514A CN114810820A CN 114810820 A CN114810820 A CN 114810820A CN 202210500514 A CN202210500514 A CN 202210500514A CN 114810820 A CN114810820 A CN 114810820A
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Abstract
The invention relates to a composite material bearing, in particular to an integrated structure special-shaped bearing based on a ceramic matrix composite material and a preparation method thereof. The high-temperature alloy bearing solves the technical problems of short service life, poor lubricating property, complex and heavy structure, large size precision change during high-temperature and low-temperature circulation, poor environmental adaptability, complex installation, complex operation process and the like of the existing widely-used high-temperature alloy bearing. The special-shaped bearing comprises an inner ring and an outer ring component; the inner ring and the outer ring assembly are made of ceramic matrix composite materials, the outer ring assembly comprises an outer ring, flanges arranged at two ends of the outer ring and two mounting grooves arranged on the outer ring, the inner wall of the outer ring is of a spherical structure protruding outwards, the inner diameters of two ends of the inner wall of the outer ring are the same, and the molded surface of the outer wall of the inner ring is matched with the molded surface of the inner wall of the outer ring; the outer ring and the flange are of an integrated structure; the radial depth of the mounting groove, which is half of the height of the outer ring along the axial direction, can meet the requirement that the inner ring is mounted into the outer ring.
Description
Technical Field
The invention relates to a composite material bearing, in particular to an integrated structure special-shaped bearing based on a ceramic matrix composite material and a preparation method thereof.
Background
With the rapid development of aerospace technology, the performances of light weight, high temperature resistance, high strength and the like become core technical indexes of advanced aircrafts. The ceramic matrix composite material gradually becomes a main alternative material of the next generation of advanced aircraft structural member due to the excellent performances of low density, high specific strength, high temperature resistance, corrosion resistance and the like.
At present, although the ceramic matrix composite material is successfully applied to the field of aircraft thermal protection structural members, the integrated design of structural functions is still difficult to realize. In order to realize the structure and physical functions of an aircraft or a satellite optical machine product in a microgravity environment or a space environment, gradually reduce the proportion of metal materials in the field of the satellite optical machine, better adapt to and meet the requirements of the field of next generation aircraft and satellite optical machines on structure weight reduction, and solve the technical problems that a high-temperature alloy bearing widely used in the field of aerospace has short service life, poor high-temperature lubricity, complex and heavy structure, large size precision change during high-temperature and low-temperature circulation, poor environmental adaptability, the requirement of coordination and matching with a bearing seat in the installation process, complex operation process and the like, the research and exploration of a ceramic matrix composite bearing capable of realizing the function and structure integrated design are urgently needed.
Disclosure of Invention
The invention aims to solve the technical problems of short service life, poor lubricating property, complex and heavy structure, large size precision change in high and low temperature circulation, poor environmental adaptability, complex installation, complex operation process and the like of the existing widely used high-temperature alloy bearing, and provides an integrated structure special-shaped bearing based on a ceramic matrix composite material and a forming method thereof.
The technical solution of the invention is as follows:
an integrated structure special-shaped bearing based on ceramic matrix composite, which is characterized in that: comprises an inner ring and an outer ring component sleeved on the inner ring;
the inner ring and the outer ring are both made of ceramic matrix composite materials;
the outer ring component comprises an outer ring with a cylindrical structure, flanges which are arranged at two ends of the outer ring and extend outwards, and two mounting grooves which are symmetrically arranged at the inner side of the mounting end of the outer ring along the axial direction; the inner wall of the outer ring is of a spherical structure protruding outwards, and the inner diameters of two ends of the inner wall of the outer ring are the same;
the molded surface of the outer wall of the inner ring is matched with the molded surface of the inner wall of the outer ring;
the outer ring and the flange are of an integrated structure;
the depth of the mounting groove along the axial direction is half of the height of the outer ring;
the radial depth of the mounting groove can meet the requirement that the inner ring is mounted in the outer ring;
the width dimension of the installation groove is matched with the axial height dimension of the inner ring.
Further, the thickness of the flange is half of the minimum wall thickness of the outer ring.
Further, the flange is of a quadrilateral structure.
The preparation method of the ceramic matrix composite-based integrated-structure special-shaped bearing is characterized by comprising the following steps of:
step 1) preparing an inner ring fiber preform and an outer ring assembly fiber preform;
step 1.1) adopting high-purity graphite, respectively preparing an inner mold and an outer mold of the outer ring and the inner ring according to the inner and outer molded surfaces of the outer ring and the inner ring, wherein a plurality of vent holes are formed in the inner mold and the outer mold;
step 1.2) adopting plain cloth made of carbon fiber or silicon carbide fiber, pre-cutting the plain cloth into corresponding sizes according to the sizes of the inner ring, winding the plain cloth with the required thickness on the inner film of the inner ring, and carrying out die assembly and fixed molding on the inner die and the outer die of the inner ring to obtain an inner ring fiber preform;
step 1.3) adopting plain cloth made of carbon fiber or silicon carbide fiber, pre-cutting the plain cloth into corresponding sizes according to the sizes of an outer ring and a flange, winding the plain cloth with the required thickness on the outer wall surface of an inner film of an outer ring component, obtaining the flange through extension, sewing through a vent hole on a graphite mold, and correspondingly performing die assembly fixing molding on an inner die and an outer die of the outer ring component to obtain an outer ring component fiber prefabricated body;
step 2) forming a pyrolytic carbon interface layer or a boron nitride interface layer on the surfaces of the inner ring fiber preform and the outer ring component fiber preform by using a chemical vapor infiltration method;
the thickness of the pyrolytic carbon interface layer is 80-300 nm;
the thickness of the boron nitride interface layer is 350-800 nm;
step 3) preparing an inner ring ceramic matrix and an outer ring ceramic matrix;
respectively carrying out 4-6 times of chemical vapor infiltration processes of silicon carbide deposition on the inner ring fiber preform and the outer ring component fiber preform treated in the step 2), and controlling the gas flow to obtain an inner ring ceramic substrate and an outer ring component ceramic substrate with required densities;
after each round of chemical vapor infiltration process is finished, turning the inner ring fiber preform or the outer ring assembly fiber preform up and down;
the density of the inner ring ceramic matrix and the outer ring component ceramic matrix made of carbon fiber after silicon carbide deposition is 1.7-2.0 g/cm 3 ；
The density of the inner ring ceramic matrix and the outer ring component ceramic matrix made of the silicon carbide fiber material after silicon carbide deposition is 2.3-2.5 g/cm 3 ；
Step 4), machining;
machining the inner and outer molded surfaces of the inner ring ceramic base body and the outer and inner molded surfaces of the outer ring ceramic base body by using machining equipment to ensure that the fiber cloth layer is continuous, machining two opposite mounting grooves on the outer ring to ensure that the inner ring can be mounted in the outer ring and rotates relative to the outer ring;
step 5), densification treatment of the inner ring ceramic base body and the outer ring component ceramic base body;
respectively depositing a layer of silicon carbide ceramic phase on the inner ring ceramic matrix and the outer ring component ceramic matrix by adopting a chemical vapor infiltration process, and controlling the gas flow to reach the required density after densification;
the inner ring ceramic matrix and the outer ring component ceramic matrix which are made of carbon fiber materials are adopted, and the density after densification is 2.0-2.2 g/cm 3 ；
The inner ring ceramic matrix and the outer ring ceramic matrix are made of silicon carbide fiber materials, and the density after densification is 2.5-2.7 g/cm 3 ；
Step 6) respectively processing the inner ring ceramic matrix and the outer ring component ceramic matrix after the densification treatment by adopting a silicon infiltration process to obtain crude products of the inner ring and the outer ring with the flange;
step 7) respectively carrying out abrasive flow fine polishing treatment on the crude products of the inner ring component and the outer ring component to obtain the inner ring component and the outer ring component;
and 8) assembling the outer ring assembly and the inner ring to obtain the integrated structure special-shaped bearing based on the ceramic matrix composite material.
Further, in step 3), the chemical vapor infiltration process for depositing silicon carbide specifically includes: heating to 800-1400 ℃ under the pressure of 200-2000 Pa, keeping the temperature for 2-3 h, introducing mixed gas of trichloromethylsilane, hydrogen and argon in a flow ratio of 1: 5-15: 10-20, depositing for 25-70 h, keeping the temperature for 2h, and cooling to room temperature;
in the step 5), the process for depositing a layer of silicon carbide ceramic phase by adopting the chemical vapor infiltration process specifically comprises the following steps: heating to 1000-1400 ℃ under the condition that the pressure is 200-2000 Pa, preserving heat for 2-3 h, introducing mixed gas of trichloromethylsilane, hydrogen and argon in the flow ratio of 1: 5-15: 10-20, depositing for 30-70 h, continuing preserving heat for 2h, and cooling to room temperature.
Further, in the step 3), the density of the inner ring ceramic matrix and the outer ring component ceramic matrix made of the carbon fiber material is 1.8g/cm 3 ；
The density of the inner ring ceramic matrix and the outer ring component ceramic matrix made of the silicon carbide fiber material is 2.3g/cm 3 。
Further, in the step 3), the inner ring fiber preform and the outer ring assembly fiber preform are respectively subjected to 5 rounds of chemical vapor infiltration processes of silicon carbide deposition.
Further, in the step 4), the depth precision of the installation groove (11) along the axial direction is as follows: + 0.15- +0.2 mm; mounting groove (11) width and inner ring (2) axial height looks adaptation, mounting groove (11) width size precision is: + 0.2- +0.3 mm; the external surface precision of the inner ring (2) is-0.15 to-0.10 mm.
Further, in step 6), the infiltration silicon process specifically includes: setting the vacuum degree in the infiltration furnace to be 10 -3 Pa, firstly, the temperature in the furnace is increased to 1250Keeping the temperature for 2 hours at +/-30 ℃; continuously heating to 1650 +/-30 ℃, and preserving heat for 3 hours; after heat preservation is finished, cooling to 300 ℃, introducing argon until the product is cooled to normal temperature, and taking out crude products of the inner ring and the outer ring components;
in the step 7), the technological parameters of the abrasive flow fine polishing treatment are as follows: the processing feeding speed is 50-100 mm/s, and the polishing and grinding times are 15-20 times; the specification of the abrasive is 600-1000 meshes of diamond abrasive, and the application magnitude of the abrasive is 5-8 grids; the distance between the polishing head and the surface of the workpiece is 300-500 mm, the included angle between the spray head and the surface of the workpiece is 30-60 degrees, and the working pressure is 6-10 Mpa.
Further, in step 1.3, the method for obtaining the flange by extending specifically includes: the flanges are formed by flanging and extending the two ends of the plain cloth along the flanges at the two ends of the inner die of the outer ring component through the interlayer, or the flanges are obtained by laying a 2.5D woven layer and a 2D woven layer in a mixed mode.
The invention has the beneficial effects that:
1. the integrated structure special-shaped bearing based on the ceramic matrix composite creatively integrates the special-shaped outer ring and the flange, and the flange can be in any shape, such as quadrangle, pentagon and polygon.
2. In the preparation method of the integrated structure special-shaped bearing based on the ceramic matrix composite material, the silicon-based coating is arranged between the inner ring and the outer ring, so that the special-shaped bearing has a self-lubricating function, and the densification uniformity is further improved. Lubricating grease is not needed, and the problems that the conventional bearing is carbonized and loses efficacy under a high-temperature environment, the rotating function of the bearing is lost and the like are fundamentally solved.
3. According to the forming method of the integrated structure special-shaped bearing based on the ceramic matrix composite, the outer ring and the flange edge fiber are kept continuous, and noise interference and resonance caused by assembly gaps in a high-frequency vibration environment are avoided.
4. The forming method of the integrated structure special-shaped bearing based on the ceramic matrix composite solves the problems that when the traditional metal bearing is assembled with a composite material, a fiber cloth layer is broken at the installation part of the composite material, and the like.
5. The ceramic matrix composite material is used for the integrated structure special-shaped bearing based on the ceramic matrix composite material, so that the problem of thermal adaptation of the metal bearing and the composite material is solved, the usage amount of heat insulation materials between the traditional metal bearing and the composite material is reduced, the load is further increased, and the product weight is reduced.
6. Compared with the traditional metal bearing, the integrated-structure special-shaped bearing based on the ceramic matrix composite material has the advantages of simple structure (only an inner ring and an outer ring), high reliability, light weight, high temperature resistance, small thermal expansion amount and the like.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of the integrated structure special-shaped bearing based on the ceramic matrix composite material according to the present invention;
FIG. 2 is a schematic structural diagram of an outer ring assembly according to an embodiment of the present invention;
FIG. 3 is a cross-sectional view A-A of FIG. 2;
FIG. 4 is a schematic structural diagram of an inner ring in an embodiment of the present invention;
FIG. 5 is a cross-sectional view B-B of FIG. 4;
FIG. 6 is a diagram illustrating a process of installing an inner ring into an outer ring according to an embodiment of the present invention;
FIG. 7 is a structural display view of an embodiment of the present invention with the inner ring and outer ring axes at a 90 ° angle;
FIG. 8 is a schematic structural diagram of an outer ring assembly according to another embodiment of the present invention.
Reference numerals: 1-outer ring, 10-outer ring inner wall, 11-inner ring mounting groove, 12-flange, 2-inner ring, and 20-inner ring outer wall.
Detailed Description
In order to make the objects, features and advantages of the present invention comprehensible, the present invention is described in detail with reference to the accompanying drawings and examples, but it should be understood that the scope of the present invention is not limited to the specific embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
As shown in fig. 1-5, the integrated structure special-shaped bearing based on the ceramic matrix composite material of the present invention comprises an inner ring 2 and an outer ring assembly sleeved on the inner ring 2; the inner ring 2 and the outer ring component are both made of ceramic matrix composite materials; the outer ring component comprises an outer ring 1 with a cylindrical structure, flanges 12 which are arranged at two ends of the outer ring 1 and extend outwards, and two mounting grooves 11 which are symmetrically arranged at the inner side of the mounting end of the outer ring 1 along the axial direction; the inner wall 10 of the outer ring 1 is of a spherical structure protruding outwards, and the inner diameters of two ends of the inner wall 10 of the outer ring are the same; the profile of the inner ring outer wall 20 of the inner ring 2 is matched with the profile of the outer ring inner wall 10 of the outer ring 1; the outer ring 1 and the flange 12 are of an integrated structure; the depth of the mounting groove 11 along the axial direction is half of the height of the outer ring 1; the depth of the mounting groove 11 in the radial direction can meet the requirement that the inner ring 2 is mounted in the outer ring 1; the width dimension of the mounting groove 11 is matched with the axial height dimension of the inner ring 2. The thickness of the flange 12 is half of the minimum wall thickness of the outer ring 1, the outer shape of the flange 12 is a quadrilateral structure, and the outer shape of the flange 12 can be designed according to needs in other embodiments, as shown in fig. 8, which is another shape of the flange 12 in another embodiment. The structure of the inner ring 2 at an angle of 90 ° to the axis of the outer ring 1 is shown in fig. 7. The distance between the two mounting grooves is equal to the maximum diameter of the inner ring.
The invention also provides a preparation method of the integrated structure special-shaped bearing based on the ceramic matrix composite material, and the preparation method of the integrated structure special-shaped bearing based on the ceramic matrix composite material is described in detail through the embodiment.
Examples 1, 2 and 3 are methods of manufacturing a special-shaped bearing using carbon fiber plain cloth, and examples 4, 5 and 6 are methods of manufacturing a special-shaped bearing using silicon carbide fiber plain cloth.
Example 1
Step 1) preparing an inner ring fiber preform and an outer ring assembly fiber preform;
step 1.1) adopting high-purity graphite, respectively preparing an inner mold and an outer mold of the outer ring 1 and the inner ring 2 according to the inner and outer molded surfaces of the outer ring 1 and the inner ring 2, wherein the inner mold and the outer mold are respectively provided with a plurality of phi 4mm vent holes, the axial distribution distance of the vent holes is 5mm, and the circumferential hole distance is 6 mm;
step 1.2) adopting carbon fiber plain cloth, pre-cutting the carbon fiber plain cloth into a proper size according to the size of the inner ring 2, winding the plain cloth with a required thickness on an inner film of the inner ring 2, and carrying out die assembly and fixed molding on an inner die and an outer die of the inner ring 1 to obtain an inner ring fiber preform;
step 1.3) adopting carbon fiber plain cloth, pre-cutting the carbon fiber plain cloth into proper sizes according to the sizes of the outer ring 1 and the flange 12, winding the plain cloth with required thickness on the outer wall surface of the inner film of the outer ring component, flanging and extending two ends of the plain cloth along flanges at two ends of the inner mold of the outer ring component by using an interlayer, sewing through vent holes, and correspondingly performing die assembly and fixed molding on the inner mold and the outer mold of the outer ring component to obtain an outer ring component fiber prefabricated body;
the flange 12 can further lay a whole circle of fiber cloth layer on the flange surface according to the use condition scene, and further extend the flange edge, that is, the flange edge provides design redundancy for further integrated design with the periphery of the bearing, and is not limited to a polygon or any profile shape. In order to improve the bearing capacity of the special-shaped bearing, when the outer ring 1 and the fiber cloth layer at the flange edge part are laid, the fibers of the fiber cloth layer can also be laid along the radial direction of the outer ring 1 along the non-orthogonal direction. In order to improve the bonding strength of the outer ring 1 and the flange 12, when the fiber cloth layer of the flange 12 is laid, a 2.5D weaving layer and a 2D weaving layer can be mixed and laid at the flange, the laid 2.5D weaving layer and the laid 2D weaving layer are sewn with plain cloth wound on the outer wall surface of the inner die of the outer ring 1, the thickness of the laid 2.5D weaving layer and the laid 2D weaving layer on the flange is one half of the thickness of the plain cloth on the inner die of the outer ring, and the 2.5D weaving layer and the laid 2D weaving layer are sewn.
Step 2) forming a pyrolytic carbon interface layer or a boron nitride interface layer on the surfaces of the inner ring fiber preform and the outer ring component fiber preform by using a chemical vapor infiltration method; when a pyrolytic carbon interface layer is adopted, the thickness of pyrolytic carbon on the surface of the fiber is 200 +/-10 nm, and when a boron nitride interface layer is adopted, the thickness of boron nitride on the surface of the fiber is 500 +/-10 nm;
step 3) preparing an inner ring ceramic matrix and an outer ring ceramic matrix;
respectively carrying out 5 rounds of chemical vapor infiltration processes of silicon carbide deposition on the inner ring fiber preform and the outer ring component fiber preform treated in the step 2), and controlling gas flow to obtain an inner ring ceramic matrix and an outer ring component silicon carbide ceramic matrix;
after each round of chemical vapor infiltration process is finished, turning the inner ring fiber preform or the outer ring assembly fiber preform up and down; the chemical vapor infiltration process for silicon carbide deposition comprises the following specific steps: heating to 1000 ℃ under the pressure of 200Pa, keeping the temperature for 3h, introducing mixed gas of trichloromethylsilane, hydrogen and argon with the flow ratio of 1:15:20, depositing for 50h, keeping the temperature for 2h, and cooling to room temperature to obtain an inner ring ceramic matrix and an outer ring component ceramic matrix with the density of 1.8g/cm 3 ；
Step 4), machining;
machining the inner and outer molded surfaces of the inner ring ceramic base body and the outer ring component ceramic base body by using machining equipment to ensure that the fiber cloth layer is continuous, machining two opposite mounting grooves 11 on the outer ring 1 and ensuring that the inner ring 2 can be mounted in the outer ring 1 and rotates relative to the outer ring; the depth of the mounting groove 11 along the axial direction is half of the height of the outer ring 1; the depth precision of the mounting groove along the axial direction is +0.2 mm; the width of the mounting groove 11 is consistent with the axial height of the inner ring 2, and the width dimension precision of the mounting groove 11 is +0.2 mm; the outer profile accuracy of the inner ring 2 is-0.10 mm.
Step 5), densification treatment of the inner ring ceramic base body and the outer ring component ceramic base body;
respectively depositing a layer of silicon carbide ceramic phase on the product by adopting a chemical vapor infiltration process on the inner ring ceramic matrix and the outer ring component ceramic matrix; the inner ring ceramic matrix and the outer ring component ceramic matrix which are made of carbon fiber materials are adopted, and the density after densification is 2.1g/cm 3 ；
The process for depositing a layer of silicon carbide ceramic phase by adopting the chemical vapor infiltration process comprises the following specific steps: heating to 1000 ℃ under the condition that the pressure is 1000Pa, keeping the temperature for 2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon with the flow ratio of 1:5:10, depositing for 30h, keeping the temperature for 2h, and cooling to the room temperature.
And 6) respectively treating the inner ring ceramic matrix and the outer ring component ceramic matrix after the densification treatment by adopting a silicon infiltration process to obtain crude products of the inner ring 2 and the outer ring 1 with the flange 12.
The infiltration silicon process comprises the following steps: setting the vacuum degree in the infiltration furnace to be 10 -3 Pa, firstly, raising the temperature in the furnace to 1250 +/-30 ℃, and preserving the temperature for 2 hours; continuously heating to 1650 +/-30 ℃, and preserving heat for 3 hours; after heat preservation is finished, cooling to 300 ℃, introducing argon until the product is cooled to normal temperature, and taking out crude products of the inner ring and the outer ring components;
and 7) respectively carrying out abrasive flow fine polishing treatment on the crude products of the inner ring 2 and the outer ring component to obtain the inner ring 2 and the outer ring component.
The technological parameters of the abrasive flow fine polishing treatment are as follows: the processing feeding speed is 80mm/s, and the polishing and grinding times are 20 times; the specification of the abrasive is 800 meshes of diamond abrasive, and the application magnitude of the abrasive is 6 grids; the distance between the polishing head and the surface of the workpiece is 350mm, the included angle between the spray head and the surface of the workpiece is 45 degrees, and the working pressure is 8 Mpa.
And 8) assembling the outer ring component and the inner ring 2 to obtain the special-shaped bearing.
As shown in figure 6, the inner ring 2 is inserted through the mounting groove 11, during the insertion process, the axis of the inner ring 1 is always vertical to the axis of the outer ring 1, after the inner ring 2 reaches the design position, the inner ring 2 is rotated by 90 degrees to enable the axis of the inner ring 2 to be overlapped with the axis of the outer ring 1, as shown in figure 1, the installation is finished.
Example 2
Step 1) preparing an inner ring fiber preform and an outer ring assembly fiber preform;
step 1.1) adopting high-purity graphite, respectively preparing an inner mold and an outer mold according to inner and outer molded surfaces of an outer ring 1 and an inner ring 2, wherein the inner mold and the outer mold are respectively provided with a plurality of phi 4mm vent holes, the axial distribution distance of the vent holes is 5mm, and the circumferential hole distance is 6 mm;
step 1.2) adopting carbon fiber plain cloth, pre-cutting the carbon fiber plain cloth into a proper size according to the size of the inner ring 2, winding the plain cloth with a required thickness on an inner film of the inner ring 2, and carrying out die assembly and fixed molding on an inner die and an outer die of the inner ring 1 to obtain an inner ring fiber preform;
step 1.3) adopting carbon fiber plain cloth, pre-cutting the carbon fiber plain cloth into proper sizes according to the sizes of the outer ring 1 and the flange 12, winding the plain cloth with required thickness on the outer wall surface of the inner film of the outer ring component, flanging and extending two ends of the plain cloth along flanges at two ends of the inner mold of the outer ring component by using an interlayer, sewing through vent holes, and correspondingly performing die assembly and fixed molding on the inner mold and the outer mold of the outer ring component to obtain an outer ring component fiber prefabricated body;
step 2) forming a pyrolytic carbon interface layer or a boron nitride interface layer on the surfaces of the inner ring fiber preform and the outer ring component fiber preform by using a chemical vapor infiltration method; when a pyrolytic carbon interface layer is adopted, the thickness of pyrolytic carbon on the surface of the fiber is 90 +/-10 nm, and when a boron nitride interface layer is adopted, the thickness of boron nitride on the surface of the fiber is 340 +/-10 nm;
step 3) preparing an inner ring ceramic matrix and an outer ring ceramic matrix;
respectively carrying out 4 rounds of silicon carbide deposition chemical vapor infiltration processes on the inner ring fiber preform and the outer ring component fiber preform treated in the step 2), and controlling gas flow to obtain an inner ring ceramic matrix and an outer ring component silicon carbide ceramic matrix;
after each round of chemical vapor infiltration process is finished, turning the inner ring fiber preform or the outer ring assembly fiber preform up and down; the chemical vapor infiltration process for silicon carbide deposition comprises the following specific steps: heating to 800 ℃ under the pressure of 2000Pa, keeping the temperature for 2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon with the flow ratio of 1:5:10, depositing for 25h, keeping the temperature for 2h, and cooling to room temperature to obtain an inner ring ceramic matrix and an outer ring component ceramic matrix with the density of 1.7g/cm 3 ；
Step 4), machining;
machining the inner and outer molded surfaces of the inner ring ceramic base body and the outer ring component ceramic base body by using machining equipment to ensure that the fiber cloth layer is continuous, machining two opposite mounting grooves 11 on the outer ring 1 and ensuring that the inner ring 2 can be mounted in the outer ring 1 and rotates relative to the outer ring; the depth of the mounting groove 11 along the axial direction is half of the height of the outer ring; the depth precision of the mounting groove along the axial direction is +0.15 mm; the width of the mounting groove 11 is consistent with the axial height of the inner ring 2, and the width dimension precision of the mounting groove 11 is +0.26 mm; the outer profile accuracy of the inner ring 2 is-0.15 mm.
Step 5), densification treatment of the inner ring ceramic base body and the outer ring component ceramic base body;
depositing a layer of silicon carbide ceramic phase on the product by respectively adopting a chemical vapor infiltration process for the inner ring ceramic matrix and the outer ring component ceramic matrix; the inner ring ceramic matrix and the outer ring component ceramic matrix which are made of carbon fiber materials are adopted, and the density after densification is 2.0g/cm 3 ；
The process for depositing a layer of silicon carbide ceramic phase by adopting the chemical vapor infiltration process comprises the following specific steps: heating to 1400 ℃ under the pressure of 200Pa, keeping the temperature for 3h, introducing mixed gas of trichloromethylsilane, hydrogen and argon in the flow ratio of 1:10:15, depositing for 70h, keeping the temperature for 2h, and cooling to room temperature.
And 6) respectively treating the inner ring ceramic matrix and the outer ring component ceramic matrix after the densification treatment by adopting a silicon infiltration process to obtain crude products of the inner ring 2 and the outer ring 1 with the flange 12.
The infiltration silicon process comprises the following steps: setting the vacuum degree in the infiltration furnace to be 10 -3 Pa, firstly, raising the temperature in the furnace to 1250 +/-30 ℃, and preserving the temperature for 2 hours; continuously heating to 1650 +/-30 ℃, and preserving heat for 3 hours; after heat preservation is finished, cooling to 300 ℃, introducing argon until the product is cooled to normal temperature, and taking out crude products of the inner ring 2 and the outer ring component;
and 7) respectively carrying out abrasive flow fine polishing treatment on the crude products of the inner ring 2 and the outer ring component to obtain the inner ring 2 and the outer ring component.
The technological parameters of the abrasive flow fine polishing treatment are as follows: the processing feeding speed is 50mm/s, and the polishing and grinding times are 15 times; the specification of the abrasive is 600 meshes of diamond abrasive, and the application magnitude of the abrasive is 5 grids; the distance between the polishing head and the surface of the workpiece is 300mm, the included angle between the spray head and the surface of the workpiece is 60 degrees, and the working pressure is 10 Mpa.
And 8) assembling the outer ring component and the inner ring 2 to obtain the special-shaped bearing.
As shown in fig. 6, the inner ring 2 is inserted through the mounting groove 11, during the insertion process, the axis of the inner ring 1 is always perpendicular to the axis of the outer ring 1, and after reaching the design position, the inner ring 2 is rotated by 90 degrees to make the axes of the inner ring 2 and the outer ring 1 coincide, and the installation is finished.
Example 3
Step 1) preparing an inner ring fiber preform and an outer ring assembly fiber preform;
step 1.1) adopting high-purity graphite, respectively preparing an inner mold and an outer mold of the outer ring 1 and the inner ring 2 according to the inner and outer molded surfaces of the outer ring 1 and the inner ring 2, wherein the inner mold and the outer mold are respectively provided with a plurality of phi 4mm vent holes, the axial distribution distance of the vent holes is 5mm, and the circumferential hole distance is 6 mm;
step 1.2) adopting carbon fiber plain cloth, pre-cutting the carbon fiber plain cloth into a proper size according to the size of the inner ring 2, winding the plain cloth with a required thickness on an inner film of the inner ring 2, and carrying out die assembly and fixed molding on an inner die and an outer die of the inner ring 1 to obtain an inner ring fiber preform;
step 1.3) adopting plain cloth of carbon fiber, pre-cutting the plain cloth into proper size according to the size of an outer ring 1 and a flange 12, winding the plain cloth with required thickness on the outer wall surface of an inner film of an outer ring component, flanging and extending two ends of the plain cloth along flanges at two ends of an inner mold of the outer ring component by an interlayer, sewing through vent holes, and correspondingly performing die assembly and fixed molding on an inner mold and an outer mold of the outer ring component to obtain a fiber prefabricated body of the outer ring component;
step 2) forming a pyrolytic carbon interface layer or a boron nitride interface layer on the surfaces of the inner ring fiber preform and the outer ring component fiber preform by using a chemical vapor infiltration method; when a pyrolytic carbon interface layer is adopted, the thickness of pyrolytic carbon on the surface of the fiber is 290 +/-10 nm, and when a boron nitride interface layer is adopted, the thickness of boron nitride on the surface of the fiber is 790 +/-10 nm;
step 3) preparing an inner ring ceramic matrix and an outer ring ceramic matrix;
respectively carrying out 6 rounds of silicon carbide deposition chemical vapor infiltration processes on the inner ring fiber preform and the outer ring component fiber preform treated in the step 2), and controlling gas flow to obtain an inner ring ceramic matrix and an outer ring component silicon carbide ceramic matrix;
after each round of chemical vapor infiltration process is finished, turning the inner ring fiber preform or the outer ring assembly fiber preform up and down; the chemical vapor infiltration process for silicon carbide deposition comprises the following specific steps: heating to 1400 ℃ under the condition of 1000Pa, preserving heat for 2.5h, introducing mixed gas of trichloromethylsilane, hydrogen and argon with the flow ratio of 1:11:13, and precipitatingKeeping the temperature for 2h after 70h accumulation, and cooling to room temperature to obtain inner ring ceramic matrix and outer ring component ceramic matrix with density of 2.0g/cm 3 ；
Step 4), machining;
machining the inner and outer molded surfaces of the inner ring ceramic base body and the outer and inner molded surfaces of the outer ring component ceramic base body by using machining equipment to ensure that the fiber cloth layers are continuous, machining two opposite mounting grooves 11 on the outer ring 1 to ensure that the inner ring 2 can be mounted in the outer ring 1 and rotates relative to the outer ring; the depth of the mounting groove 11 is half of the height of the outer ring; the depth precision of the mounting groove is +0.17 mm; the width of the mounting groove 11 is consistent with the axial height of the inner ring 2, and the width precision of the mounting groove 11 is +0.3 mm; the outer profile accuracy of the inner ring 2 is-0.17 mm.
Step 5), densification treatment of the inner ring ceramic base body and the outer ring component ceramic base body;
respectively depositing a layer of silicon carbide ceramic phase on the product by adopting a chemical vapor infiltration process on the inner ring ceramic matrix and the outer ring component ceramic matrix; the density of the inner ring ceramic matrix and the outer ring component ceramic matrix which adopt carbon fibers after being compacted is 2.2g/cm 3 ；
The process for depositing a layer of silicon carbide ceramic phase by adopting the chemical vapor infiltration process comprises the following specific steps: heating to 1400 ℃ under the pressure of 2000Pa, keeping the temperature for 2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon in the flow ratio of 1:10:15, depositing for 50h, keeping the temperature for 2h, and cooling to room temperature.
And 6) respectively treating the inner ring ceramic matrix and the outer ring component ceramic matrix after the densification treatment by adopting a silicon infiltration process to obtain crude products of the inner ring and the outer ring with the flange 12.
The infiltration silicon process comprises the following steps: setting the vacuum degree in the infiltration furnace to be 10 -3 Pa, firstly, raising the temperature in the furnace to 1250 +/-30 ℃, and preserving the temperature for 2 hours; continuously heating to 1650 +/-30 ℃, and preserving heat for 3 hours; after heat preservation is finished, cooling to 300 ℃, introducing argon until the product is cooled to normal temperature, and taking out crude products of the inner ring and the outer ring components;
and 7) respectively carrying out abrasive flow fine polishing treatment on the crude products of the inner ring component and the outer ring component to obtain an inner ring 2 and an outer ring component.
The technological parameters of the abrasive flow fine polishing treatment are as follows: the processing feed speed is 100mm/s, and the polishing and grinding times are 18 times; the specification of the abrasive is 1000 meshes of diamond abrasive, and the application magnitude of the abrasive is 8 grids; the distance between the polishing head and the surface of the workpiece is 500mm, the included angle between the spray head and the surface of the workpiece is 30 degrees, and the working pressure is 6 Mpa.
And 8) assembling the outer ring component and the inner ring 2 to obtain the special-shaped bearing.
Insert inner ring 2 through mounting groove 11, in the insertion process, 1 axis of inner ring is perpendicular 1 axis of outer ring all the time, reaches behind the design position and rotates inner ring 290 and makes inner ring 2 and 1 axis coincidence of outer ring, and the installation finishes, and during the use, rotates inner ring 2 to required angle, and the pivoted direction is for guaranteeing that the relative outer ring 1 pivoted route of inner ring 2 passes through mounting groove 11.
Example 4
Step 1) preparing an inner ring fiber preform and an outer ring assembly fiber preform;
step 1.1) adopting high-purity graphite, respectively preparing an inner mold and an outer mold according to inner and outer molded surfaces of an outer ring 1 and an inner ring 2, wherein the inner mold and the outer mold are respectively provided with a plurality of phi 5mm vent holes, the axial distribution distance of the vent holes is 6mm, and the circumferential hole distance is 7 mm;
step 1.2) adopting plain cloth made of silicon carbide fiber materials, pre-cutting the plain cloth into proper sizes according to the size of the inner ring 2, winding the plain cloth with required thickness on an inner film of the inner ring 2, and carrying out die assembly and fixed molding on an inner die and an outer die of the inner ring 1 to obtain an inner ring fiber prefabricated body;
step 1.3) adopting plain cloth made of silicon carbide fiber materials, pre-cutting the plain cloth into proper sizes according to the sizes of an outer ring 1 and a flange 12, winding the plain cloth with required thickness on the outer wall surface of an inner film of an outer ring component, flanging and extending two ends of the plain cloth along flanges at two ends of an inner mold of the outer ring component by using an interlayer, sewing through vent holes, and correspondingly performing die assembly and fixed molding on an inner mold and an outer mold of the outer ring component to obtain an outer ring component fiber prefabricated body;
step 2) forming a pyrolytic carbon interface layer or a boron nitride interface layer on the surfaces of the inner ring fiber preform and the outer ring component fiber preform by using a chemical vapor infiltration method; when a pyrolytic carbon interface layer is adopted, the thickness of pyrolytic carbon on the surface of the fiber is 150 +/-10 nm, and when a boron nitride interface layer is adopted, the thickness of boron nitride on the surface of the fiber is 500 +/-10 nm;
step 3) preparing an inner ring ceramic matrix and an outer ring ceramic matrix;
respectively carrying out 5 rounds of silicon carbide deposition chemical vapor infiltration processes on the inner ring fiber preform and the outer ring component fiber preform treated in the step 2), and controlling gas flow to obtain an inner ring ceramic matrix and an outer ring component silicon carbide ceramic matrix;
after each round of chemical vapor infiltration process is finished, turning the inner ring fiber preform or the outer ring assembly fiber preform up and down; the chemical vapor infiltration process for silicon carbide deposition comprises the following specific steps: heating to 1400 ℃ under the pressure of 2000Pa, keeping the temperature for 3h, introducing mixed gas of trichloromethylsilane, hydrogen and argon with the flow ratio of 1:5:20, depositing for 60h, keeping the temperature for 2h, and cooling to room temperature to obtain an inner ring ceramic matrix and an outer ring component ceramic matrix with the density of 2.3g/cm 3 ；
Step 4), machining;
machining the inner and outer molded surfaces of the inner ring ceramic base body and the outer ring component ceramic base body by using machining equipment to ensure that the fiber cloth layer is continuous, machining two opposite mounting grooves 11 on the outer ring 1 and ensuring that the inner ring 2 can be mounted in the outer ring 1 and rotates relative to the outer ring; the depth of the mounting groove 11 along the axial direction is half of the height of the outer ring; the depth precision of the mounting groove along the axial direction is +0.15 mm; the width of the mounting groove 11 is consistent with the axial height of the inner ring 2, and the width precision of the mounting groove 11 is +0.3 mm; the outer profile accuracy of the inner ring 2 is-0.15 mm.
Step 5), densification treatment of the inner ring ceramic matrix and the outer ring component ceramic matrix;
respectively depositing a layer of silicon carbide ceramic phase on the product by adopting a chemical vapor infiltration process on the inner ring ceramic matrix and the outer ring component ceramic matrix; the density of the inner ring ceramic matrix and the outer ring component ceramic matrix after being densified is 2.6g/cm 3 ；
The process for depositing a layer of silicon carbide ceramic phase by adopting the chemical vapor infiltration process comprises the following specific steps: heating to 1000 ℃ under the pressure of 1500Pa, keeping the temperature for 3h, introducing mixed gas of trichloromethylsilane, hydrogen and argon in the flow ratio of 1:5:15, depositing for 70h, keeping the temperature for 2h, and cooling to room temperature.
And 6) respectively treating the inner ring ceramic matrix and the outer ring component ceramic matrix after the densification treatment by adopting a silicon infiltration process to obtain crude products of the inner ring 2 and the outer ring 1 with the flange 12.
The infiltration silicon process comprises the following steps: setting the vacuum degree in the infiltration furnace to be 10 -3 Pa, firstly, raising the temperature in the furnace to 1250 +/-30 ℃, and preserving the temperature for 2 hours; continuously heating to 1650 +/-30 ℃, and preserving heat for 3 hours; after heat preservation is finished, cooling to 300 ℃, introducing argon until the product is cooled to normal temperature, and taking out crude products of the inner ring 2 and the outer ring component;
and 7) respectively carrying out abrasive flow fine polishing treatment on the crude products of the inner ring 2 and the outer ring component to obtain the inner ring 2 and the outer ring component.
The technological parameters of the abrasive flow fine polishing treatment are as follows: the processing feeding speed is 60mm/s, and the polishing and grinding times are 16 times; the specification of the abrasive is 900-mesh diamond abrasive, and the application magnitude of the abrasive is 6 grids; the distance between the polishing head and the surface of the workpiece is 400mm, the included angle between the spray head and the surface of the workpiece is 30 degrees, and the working pressure is 10 Mpa.
And 8) assembling the outer ring component and the inner ring 2 to obtain the special-shaped bearing.
The inner ring 2 is inserted through the mounting groove 11, in the inserting process, the axis of the inner ring 1 is always vertical to the axis of the outer ring 1, the inner ring 2 is rotated by 90 degrees after reaching the design position, so that the axes of the inner ring 2 and the outer ring 1 are overlapped, and the installation is finished.
Example 5
Step 1) preparing an inner ring fiber preform and an outer ring assembly fiber preform;
step 1.1) adopting high-purity graphite, respectively preparing an inner mold and an outer mold of the outer ring 1 and the inner ring 2 according to the inner and outer molded surfaces of the outer ring 1 and the inner ring 2, wherein the inner mold and the outer mold are respectively provided with a plurality of phi 4mm vent holes, the axial distribution distance of the vent holes is 5mm, and the circumferential hole distance is 6 mm;
step 1.2) adopting plain cloth made of silicon carbide fiber materials, pre-cutting the plain cloth into proper sizes according to the size of the inner ring 2, winding the plain cloth with required thickness on an inner film of the inner ring 2, and carrying out die assembly and fixed molding on an inner die and an outer die of the inner ring 1 to obtain an inner ring fiber prefabricated body;
step 1.3) adopting plain cloth made of silicon carbide fiber materials, pre-cutting the plain cloth into proper sizes according to the sizes of an outer ring 1 and a flange 12, winding the plain cloth with required thickness on the outer wall surface of an inner film of an outer ring component, flanging and extending two ends of the plain cloth along flanges at two ends of an inner mold of the outer ring component by using an interlayer, sewing through vent holes, and correspondingly performing die assembly and fixed molding on an inner mold and an outer mold of the outer ring component to obtain an outer ring component fiber prefabricated body;
step 2) forming a pyrolytic carbon interface layer or a boron nitride interface layer on the surfaces of the inner ring fiber preform and the outer ring component fiber preform by using a chemical vapor infiltration method; when a pyrolytic carbon interface layer is adopted, the thickness of pyrolytic carbon on the surface of the fiber is 200 +/-10 nm, and when a boron nitride interface layer is adopted, the thickness of boron nitride on the surface of the fiber is 600 +/-10 nm;
step 3) preparing an inner ring ceramic matrix and an outer ring ceramic matrix;
respectively carrying out 6 rounds of chemical vapor infiltration processes of silicon carbide deposition on the inner ring fiber preform and the outer ring component fiber preform treated in the step 2), and controlling gas flow to obtain an inner ring ceramic matrix and an outer ring component silicon carbide ceramic matrix;
after each round of chemical vapor infiltration process is finished, turning the inner ring fiber preform or the outer ring assembly fiber preform up and down; the chemical vapor infiltration process for silicon carbide deposition comprises the following specific steps: heating to 1000 ℃ under the pressure of 1400Pa, keeping the temperature for 2.5h, introducing mixed gas of trichloromethylsilane, hydrogen and argon with the flow ratio of 1:8:14, depositing for 55h, keeping the temperature for 2h, and cooling to room temperature to obtain an inner ring ceramic matrix and an outer ring component ceramic matrix with the density of 2.5g/cm 3 ；
Step 4), machining;
machining the inner and outer molded surfaces of the inner ring ceramic base body and the outer ring component ceramic base body by using machining equipment to ensure that the fiber cloth layer is continuous, machining two opposite mounting grooves 11 on the outer ring 1 and ensuring that the inner ring 2 can be mounted in the outer ring 1 and rotates relative to the outer ring; the depth of the mounting groove 11 along the axial direction is half of the height of the outer ring; the depth precision of the mounting groove along the axial direction is +0.2 mm; the width of the mounting groove 11 is consistent with the axial height of the inner ring 2, and the width precision of the mounting groove 11 is +0.2 mm; the outer profile accuracy of the inner ring 2 is-0.10 mm.
Step 5), densification treatment of the inner ring ceramic base body and the outer ring component ceramic base body;
respectively depositing a layer of silicon carbide ceramic phase on the product by adopting a chemical vapor infiltration process on the inner ring ceramic matrix and the outer ring component ceramic matrix; the density of the inner ring ceramic matrix and the outer ring component ceramic matrix after being densified is 2.5g/cm 3 ；
The process for depositing a layer of silicon carbide ceramic phase by adopting the chemical vapor infiltration process comprises the following specific steps: heating to 1000 ℃ under the pressure of 2000Pa, keeping the temperature for 2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon in the flow ratio of 1:15:20, depositing for 70h, keeping the temperature for 2h, and cooling to room temperature.
And 6) respectively treating the inner ring ceramic matrix and the outer ring component ceramic matrix after the densification treatment by adopting a silicon infiltration process to obtain crude products of the inner ring 2 and the outer ring 1 with the flange 12.
The infiltration silicon process comprises the following steps: setting the vacuum degree in the infiltration furnace to be 10 -3 Pa, firstly, raising the temperature in the furnace to 1250 +/-30 ℃, and preserving the temperature for 2 hours; continuously heating to 1650 +/-30 ℃, and preserving heat for 3 hours; after heat preservation is finished, cooling to 300 ℃, introducing argon until the product is cooled to normal temperature, and taking out crude products of the inner ring 2 and the outer ring component;
and 7) respectively carrying out abrasive flow fine polishing treatment on the crude products of the inner ring 2 and the outer ring component to obtain the inner ring 2 and the outer ring component.
The technological parameters of the abrasive flow fine polishing treatment are as follows: the processing feeding speed is 90mm/s, and the polishing and grinding times are 16 times; the specification of the abrasive is 900-mesh diamond abrasive, and the application magnitude of the abrasive is 6 grids; the distance between the polishing head and the surface of the workpiece is 400mm, the included angle between the spray head and the surface of the workpiece is 55 degrees, and the working pressure is 9 Mpa.
And 8) assembling the outer ring component and the inner ring 2 to obtain the special-shaped bearing.
The inner ring 2 is inserted through the mounting groove 11, in the inserting process, the axis of the inner ring 1 is always vertical to the axis of the outer ring 1, the inner ring 2 is rotated by 90 degrees after reaching the design position, so that the axes of the inner ring 2 and the outer ring 1 are overlapped, and the installation is finished.
Example 6
Step 1) preparing an inner ring fiber preform and an outer ring assembly fiber preform;
step 1.1) adopting high-purity graphite, respectively preparing an inner mold and an outer mold of the outer ring 1 and the inner ring 2 according to the inner and outer molded surfaces of the outer ring 1 and the inner ring 2, wherein the inner mold and the outer mold are respectively provided with a plurality of phi 5mm vent holes, the axial distribution distance of the vent holes is 5mm, and the circumferential hole distance is 6 mm;
step 1.2) adopting plain cloth made of silicon carbide fiber materials, pre-cutting the plain cloth into proper sizes according to the size of the inner ring 2, winding the plain cloth with required thickness on an inner film of the inner ring 2, and carrying out die assembly and fixed molding on an inner die and an outer die of the inner ring 1 to obtain an inner ring fiber prefabricated body;
step 1.3) adopting plain cloth made of silicon carbide fiber materials, pre-cutting the plain cloth into proper sizes according to the sizes of an outer ring 1 and a flange 12, winding the plain cloth with required thickness on the outer wall surface of an inner film of an outer ring component, flanging and extending two ends of the plain cloth along flanges at two ends of an inner mold of the outer ring component by using an interlayer, sewing through vent holes, and correspondingly performing die assembly and fixed molding on an inner mold and an outer mold of the outer ring component to obtain an outer ring component fiber prefabricated body;
step 2) forming a pyrolytic carbon interface layer or a boron nitride interface layer on the surfaces of the inner ring fiber preform and the outer ring component fiber preform by using a chemical vapor infiltration method; when a pyrolytic carbon interface layer is adopted, the thickness of pyrolytic carbon on the surface of the fiber is 250 +/-10 nm, and when a boron nitride interface layer is adopted, the thickness of boron nitride on the surface of the fiber is 700 +/-10 nm;
step 3) preparing an inner ring ceramic matrix and an outer ring ceramic matrix;
respectively carrying out 5 times of chemical vapor infiltration processes on the inner ring fiber preform and the outer ring component fiber preform treated in the step 2), and controlling the gas flow to obtain an inner ring ceramic matrix and an outer ring component silicon carbide ceramic matrix;
after each round of chemical vapor infiltration process is finished, turning the inner ring fiber preform or the outer ring assembly fiber preform up and down; the chemical vapor infiltration process for silicon carbide deposition comprises the following specific steps: heating to 800 ℃ under the condition of 1000Pa, keeping the temperature for 3h, introducing mixed gas of trichloromethylsilane, hydrogen and argon with the flow ratio of 1:7:15, depositing for 60h, keeping the temperature for 2h, and cooling to room temperature to obtain an inner ring ceramic matrix and an outer ring component ceramic matrix with the density of 2.4g/cm 3 ；
Step 4), machining;
machining the inner and outer molded surfaces of the inner ring ceramic base body and the outer ring component ceramic base body by using machining equipment to ensure that the fiber cloth layer is continuous, machining two opposite mounting grooves 11 on the outer ring 1 and ensuring that the inner ring 2 can be mounted in the outer ring 1 and rotates relative to the outer ring; the depth of the mounting groove 11 along the axial direction is half of the height of the outer ring; the depth precision of the mounting groove along the axial direction is +0.2 mm; the width of the mounting groove 11 is consistent with the axial height of the inner ring 2, and the width precision of the mounting groove 11 is +0.2 mm; the outer profile accuracy of the inner ring 2 is-0.10 mm.
Step 5), densification treatment of the inner ring ceramic base body and the outer ring component ceramic base body;
respectively depositing a layer of silicon carbide ceramic phase on the product by adopting a chemical vapor infiltration process on the inner ring ceramic matrix and the outer ring component ceramic matrix; the density of the inner ring ceramic matrix and the outer ring component ceramic matrix after being densified is 2.5g/cm 3 ；
The process for depositing a layer of silicon carbide ceramic phase by adopting the chemical vapor infiltration process comprises the following specific steps: heating to 1400 ℃ under the condition of 1000Pa, keeping the temperature for 2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon in a flow ratio of 1:5:10, depositing for 45h, keeping the temperature for 2h, and cooling to room temperature.
And 6) respectively treating the inner ring ceramic matrix and the outer ring component ceramic matrix after the densification treatment by adopting a silicon infiltration process to obtain crude products of the inner ring 2 and the outer ring with the flange 12.
The infiltration silicon process comprises the following steps: setting the vacuum degree in the infiltration furnace to be 10 -3 Pa, firstly, the temperature in the furnace is raised to 1250 +/-30 ℃,preserving the heat for 2 hours; continuously heating to 1650 +/-30 ℃, and preserving heat for 3 hours; after heat preservation is finished, cooling to 300 ℃, introducing argon until the product is cooled to normal temperature, and taking out crude products of the inner ring 2 and the outer ring component;
and 7) respectively carrying out abrasive flow fine polishing treatment on the crude products of the inner ring 2 and the outer ring component to obtain the inner ring 2 and the outer ring component.
The technological parameters of the abrasive flow fine polishing treatment are as follows: the processing feeding speed is 90mm/s, and the polishing and grinding times are 16 times; the specification of the abrasive is 900-mesh diamond abrasive, and the application magnitude of the abrasive is 6 grids; the distance between the polishing head and the surface of the workpiece is 400mm, the included angle between the spray head and the surface of the workpiece is 55 degrees, and the working pressure is 9 Mpa.
And 8) assembling the outer ring component and the inner ring 2 to obtain the special-shaped bearing.
The inner ring 2 is inserted through the mounting groove 11, in the inserting process, the axis of the inner ring 1 is always vertical to the axis of the outer ring 1, the inner ring 2 is rotated by 90 degrees after reaching the design position, so that the axes of the inner ring 2 and the outer ring 1 are overlapped, and the installation is finished.
Claims (10)
1. The utility model provides an integrated structure dysmorphism bearing based on ceramic matrix composite which characterized in that: comprises an inner ring (2) and an outer ring component sleeved on the inner ring (2);
the inner ring (2) and the outer ring component are both made of ceramic matrix composite materials;
the outer ring component comprises an outer ring (1) with a cylindrical structure, flanges (12) which are arranged at two ends of the outer ring (1) and extend outwards, and two mounting grooves (11) which are axially and symmetrically arranged at the inner side of the mounting end of the outer ring (1); the inner wall (10) of the outer ring (1) is of a spherical structure protruding outwards, and the inner diameters of two ends of the inner wall (10) of the outer ring are the same;
the profile of the outer wall (20) of the inner ring (2) is matched with the profile of the inner wall (10) of the outer ring (1);
the outer ring (1) and the flange (12) are of an integrated structure;
the depth of the mounting groove (11) along the axial direction is one half of the height of the outer ring (1);
the radial depth of the mounting groove (11) can meet the requirement that the inner ring (2) is mounted in the outer ring (1);
the width dimension of the mounting groove (11) is matched with the axial height dimension of the inner ring (2).
2. The ceramic matrix composite based integrated structural special-shaped bearing according to claim 1, characterized in that: the thickness of the flange (12) is half of the minimum wall thickness of the outer ring (1).
3. The ceramic matrix composite based integrated structural special-shaped bearing according to claim 2, characterized in that: the flange (12) is of a quadrilateral structure.
4. A method for manufacturing a ceramic matrix composite based integrally structured profiled bearing according to any of the claims 1 to 3, characterized in that it comprises the following steps:
step 1) preparing an inner ring fiber preform and an outer ring assembly fiber preform;
step 1.1), preparing an inner mold and an outer mold of the outer ring (1) and the inner ring (2) respectively according to the inner and outer molded surfaces of the outer ring (1) and the inner ring (2) by adopting high-purity graphite, wherein a plurality of vent holes are formed in the inner mold and the outer mold;
step 1.2) adopting plain cloth made of carbon fiber or silicon carbide fiber, pre-cutting the plain cloth into corresponding sizes according to the size of the inner ring (2), winding the plain cloth with required thickness on the inner film of the inner ring (2), and carrying out die assembly and fixed molding on the inner die and the outer die of the inner ring (1) to obtain an inner ring fiber preform;
step 1.3) adopting plain cloth made of carbon fiber or silicon carbide fiber, pre-cutting the plain cloth into corresponding sizes according to the sizes of the outer ring (1) and the flange (12), winding the plain cloth with the required thickness on the outer wall surface of the inner film of the outer ring component, obtaining the flange (12) through extension, sewing through a vent hole on a graphite mold, and correspondingly performing die assembly fixing molding on an inner die and an outer die of the outer ring component to obtain an outer ring component fiber prefabricated body;
step 2) forming a pyrolytic carbon interface layer or a boron nitride interface layer on the surfaces of the inner ring fiber preform and the outer ring component fiber preform by using a chemical vapor infiltration method;
the thickness of the pyrolytic carbon interface layer is 80-300 nm;
the thickness of the boron nitride interface layer is 350-800 nm;
step 3) preparing an inner ring ceramic matrix and an outer ring ceramic matrix;
respectively carrying out 4-6 times of chemical vapor infiltration processes of silicon carbide deposition on the inner ring fiber preform and the outer ring component fiber preform treated in the step 2), and controlling the gas flow to obtain an inner ring ceramic substrate and an outer ring component ceramic substrate with required densities;
after each round of chemical vapor infiltration process is finished, turning the inner ring fiber preform or the outer ring assembly fiber preform up and down;
the density of the inner ring ceramic matrix and the outer ring component ceramic matrix made of carbon fiber after silicon carbide deposition is 1.7-2.0 g/cm 3 ；
The density of the inner ring ceramic matrix and the outer ring component ceramic matrix made of the silicon carbide fiber material after silicon carbide deposition is 2.3-2.5 g/cm 3 ；
Step 4), machining;
machining the inner and outer molded surfaces of the inner ring ceramic base body and the outer ring ceramic base body by using machining equipment to ensure that the fiber cloth layer is continuous, machining two opposite mounting grooves (11) on the outer ring (1) to ensure that the inner ring (2) can be mounted in the outer ring (1) and rotates relative to the outer ring (1);
step 5), densification treatment of the inner ring ceramic base body and the outer ring component ceramic base body;
respectively depositing a layer of silicon carbide ceramic phase on the inner ring ceramic matrix and the outer ring component ceramic matrix by adopting a chemical vapor infiltration process, and controlling the gas flow to reach the required density after densification;
the inner ring ceramic matrix and the outer ring component ceramic matrix which are made of carbon fiber materials are adopted, and the density after densification is 2.0-2.2 g/cm 3 ；
The inner ring ceramic matrix and the outer ring ceramic matrix are made of silicon carbide fiber materials, and the density after densification is 2.5-2.7 g/cm 3 ；
Step 6) respectively treating the inner ring ceramic matrix and the outer ring component ceramic matrix after the densification treatment by adopting a silicon infiltration process to obtain crude products of the inner ring (2) and the outer ring (1) with the flange (12);
step 7) respectively carrying out abrasive flow fine polishing treatment on the crude products of the inner ring (2) and the outer ring component to obtain the inner ring (2) and the outer ring component;
and 8) assembling the outer ring assembly and the inner ring (2) to obtain the integrated structure special-shaped bearing based on the ceramic matrix composite material.
5. The method for preparing the ceramic matrix composite based integrally-structured special-shaped bearing according to claim 4, wherein in the step 3), the chemical vapor infiltration process for silicon carbide deposition specifically comprises the following steps: heating to 800-1400 ℃ under the pressure of 200-2000 Pa, keeping the temperature for 2-3 h, introducing mixed gas of trichloromethylsilane, hydrogen and argon in a flow ratio of 1: 5-15: 10-20, depositing for 25-70 h, keeping the temperature for 2h, and cooling to room temperature;
in the step 5), the process for depositing a layer of silicon carbide ceramic phase by adopting the chemical vapor infiltration process specifically comprises the following steps: heating to 1000-1400 ℃ under the condition that the pressure is 200-2000 Pa, preserving heat for 2-3 h, introducing mixed gas of trichloromethylsilane, hydrogen and argon in the flow ratio of 1: 5-15: 10-20, depositing for 30-70 h, continuing preserving heat for 2h, and cooling to room temperature.
6. The method for preparing the ceramic matrix composite-based integrally-structured special-shaped bearing according to claim 5, wherein in the step 3), the density of the ceramic substrates of the inner ring and the outer ring of the carbon fiber material is 1.8g/cm 3 ；
The density of the inner ring ceramic matrix and the outer ring component ceramic matrix made of the silicon carbide fiber material is 2.3g/cm 3 。
7. The method for preparing the ceramic matrix composite based integrally-structured special-shaped bearing according to claim 5, wherein the method comprises the following steps:
and 3), respectively carrying out 5 rounds of chemical vapor infiltration processes of silicon carbide deposition on the inner ring fiber preform and the outer ring assembly fiber preform.
8. The method for preparing a ceramic matrix composite based integrally structured special-shaped bearing according to any one of claims 4 to 7, wherein in the step 4), the depth precision of the installation groove (11) along the axial direction is as follows: + 0.15- +0.2 mm; mounting groove (11) width and inner ring (2) axial height looks adaptation, mounting groove (11) width size precision is: + 0.2- +0.3 mm;
the external surface precision of the inner ring (2) is-0.15 to-0.10 mm.
9. The method for preparing the ceramic matrix composite-based integrally-structured special-shaped bearing according to claim 8, wherein in the step 6), the siliconizing melting process specifically comprises the following steps: setting the vacuum degree in the infiltration furnace to be 10 -3 Pa, firstly, raising the temperature in the furnace to 1250 +/-30 ℃, and preserving the temperature for 2 hours; continuously heating to 1650 +/-30 ℃, and preserving heat for 3 hours; after heat preservation is finished, cooling to 300 ℃, introducing argon until the product is cooled to normal temperature, and taking out crude products of the inner ring and the outer ring components;
in the step 7), the technological parameters of the abrasive flow fine polishing treatment are as follows: the processing feeding speed is 50-100 mm/s, and the polishing and grinding times are 15-20 times; the specification of the abrasive is 600-1000 meshes of diamond abrasive, and the application magnitude of the abrasive is 5-8 grids; the distance between the polishing head and the surface of the workpiece is 300-500 mm, the included angle between the spray head and the surface of the workpiece is 30-60 degrees, and the working pressure is 6-10 Mpa.
10. The method for preparing a ceramic matrix composite based integrally structured special-shaped bearing according to claim 9, wherein in step 1.3, the method for obtaining the flange (12) by extension is specifically as follows: flanges (12) are obtained by flanging and extending the two ends of the plain cloth along flanges at the two ends of the inner die of the outer ring component through the interlayer or by adopting a mixed laying of a 2.5D woven layer and a 2D woven layer.
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| US20210147302A1 (en) * | 2019-11-15 | 2021-05-20 | Rolls-Royce High Temperature Composites Inc. | Method to achieve a smooth surface with precise tolerance control for a complex (non-flat) geometry |
| CN113685436A (en) * | 2021-08-23 | 2021-11-23 | 航天精工股份有限公司 | High unitized joint bearing for aerospace and aviation |
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| US20180149193A1 (en) * | 2015-05-28 | 2018-05-31 | Schaeffler Technologies AG & Co. KG | Method for producing a spherical bearing and associated spherical bearing |
| CN112789419A (en) * | 2018-12-05 | 2021-05-11 | 舍弗勒技术股份两合公司 | Sliding bearing and method for producing a bearing element of a sliding bearing |
| CN111706606A (en) * | 2019-03-18 | 2020-09-25 | 斯凯孚航空法国公司 | Spherical ball joint |
| CN110173506A (en) * | 2019-05-30 | 2019-08-27 | 沈阳建筑大学 | For high temperature, perishable, under oxidizable working environment full ceramic articulation bearing |
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