Parameter adjusting method of ceramic matrix composite plain woven preform framework applied to aero-engine

Abstract

The invention discloses a parameter adjusting method of a ceramic matrix composite plain woven preform framework applied to an aero-engine, and relates to the technical field of engineering thermophysics. The ceramic matrix composite plain woven preform framework comprises multiple layers of fiber cloth, a first fiber bundle and a second fiber bundle are both woven with a plurality of third fiber bundles and a plurality of fourth fiber bundles, and the parameter adjusting method comprises the steps of adjusting the size of pores between the bundles, adjusting the gap between the pores between the adjacent bundles and adjusting the size of the pores between the layers in the first direction. The method comprises the following steps: weaving multiple layers of fiber cloth to form inter-beam pores, overlapping the multiple layers of fiber cloth to form inter-layer pores, and adjusting the inter-beam pores and the inter-layer pores to adjust the flow of cooling gas in a seepage channel, so that the cooling gas can cover the surface of a hot-end component to form a gas film, and the temperature rise influence of high-temperature gas flow on a ceramic-based composite material is further reduced; therefore, the temperature of a hot end component is reduced, and high-temperature corrosion of high-temperature water-oxygen fuel gas to the hot end component is prevented.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of engineering thermophysics, and particularly to a parameter adjustment method of a ceramic matrix composite plain weave preform framework applied to an aero-engine. BACKGROUND

[0002] The future aero-engine combustion chamber combustion temperature can reach 2200K or above, and the existing flame tube material dominated by high-temperature alloy is difficult to withstand such high temperature, so the material needs to be actively cooled. In the existing cooling scheme, high-pressure air at the outlet of the compressor is generally used as secondary flow cooling air to cool the flame tube wall surface. In the high-temperature rise engine combustion chamber, a high-temperature alloy and a dense gas film hole gas film cooling method are generally used for cooling. However, the maximum temperature resistance of the high-temperature alloy is generally 1400K, and the temperature of the future aero-engine combustion chamber will reach 2200K or above. The existing cooling method of the high-temperature alloy is difficult to meet the development needs of the future. In some other existing schemes, holes are generally punched on the ceramic matrix composite material to actively cool through sweating cooling. However, this technical solution reduces the structural strength of the ceramic matrix composite material, resulting in a decrease in the mechanical properties of the ceramic matrix composite material. SUMMARY

[0003] The present application aims to at least solve one of the technical problems existing in the prior art. To this end, one object of the present application is to propose a parameter adjustment method of a ceramic matrix composite plain weave preform framework applied to an aero-engine, which can adjust the inter-beam porosity and the inter-layer porosity to adjust the performance of the ceramic matrix composite material, so that the ceramic matrix composite material can be reliably applied to the cooling of the hot end parts (such as the combustion chamber flame tube) of the aero-engine.

[0004] The parameter adjustment method of the ceramic matrix composite plain weave preform framework applied to the aero-engine according to the embodiment of the present application, the ceramic matrix composite material comprises: a plurality of layers of fiber cloths arranged in sequence along a first direction, any two adjacent layers of the fiber cloths jointly define interlayer pores, the fiber cloth comprises: a plurality of first fiber bundles and a plurality of second fiber bundles arranged alternately along a second direction, and a plurality of third fiber bundles and a plurality of fourth fiber bundles arranged alternately along a third direction, any two of the first direction, the second direction and the third direction are orthogonal; the first fiber bundle and any adjacent second fiber bundle are constructed as a first fiber bundle group, the third fiber bundle and any adjacent fourth fiber bundle are constructed as a second fiber bundle group, the first fiber bundle group and the second fiber bundle group jointly define bundle interstices, along the first direction, a plurality of opposite bundle interstices and a plurality of interlayer pores jointly construct a flow channel; the parameter adjustment method comprises: adjusting the size of the bundle interstices; adjusting the interstitial distance of adjacent bundle interstices; adjusting the size of the interlayer pores along the first direction.

[0005] The parameter adjustment method of the ceramic matrix composite plain weave preform framework applied to the aero-engine according to the embodiment of the present application, by weaving a plurality of layers of fiber cloths to form bundle interstices, a plurality of layers of fiber cloths are stacked to form interlayer pores, and the bundle interstices and the interlayer pores are adjusted to adjust the flow of cooling gas in the flow channel, so that the cooling gas can cover the surface of the hot end component to form a gas film, thereby reducing the temperature of the hot end component and preventing high-temperature water-oxygen-gas from corroding the hot end component.

[0006] According to some embodiments of the present application, the adjusting the size of the bundle interstices comprises: adjusting the size of the bundle interstices by adjusting the distance between the first fiber bundle and the second fiber bundle in the corresponding first fiber bundle group; and / or, adjusting the size of the bundle interstices by adjusting the distance between the third fiber bundle and the fourth fiber bundle in the corresponding second fiber bundle group.

[0007] According to some embodiments of the present application, the adjusting the interstitial distance of adjacent bundle interstices comprises: adjusting the size of the bundle interstices by adjusting the width of the first fiber bundle and / or the second fiber bundle in the corresponding first fiber bundle group; and / or, adjusting the size of the bundle interstices by adjusting the width of the third fiber bundle and / or the fourth fiber bundle in the corresponding second fiber bundle group.

[0008] According to some embodiments of the present invention, the cross-sections of the first fiber bundle, the second fiber bundle, the third fiber bundle, and the fourth fiber bundle are all constructed as ellipses, and adjusting the pore spacing between adjacent inter-bundle pores includes: adjusting the size of the inter-bundle pores by adjusting the major axis of the first fiber bundle and / or the second fiber bundle in the corresponding first fiber bundle group; and / or, adjusting the size of the inter-bundle pores by adjusting the major axis of the third fiber bundle and / or the fourth fiber bundle in the corresponding second fiber bundle group.

[0009] According to some embodiments of the present invention, the cross-sections of the first fiber bundle, the second fiber bundle, the third fiber bundle, and the fourth fiber bundle are all constructed as ellipses, and adjusting the size of the interlayer porosity along the first direction includes: adjusting the minor axis of the first fiber bundle and / or the second fiber bundle in the corresponding first fiber bundle group to adjust the size of the interlayer porosity along the first direction; and / or, adjusting the minor axis of the third fiber bundle and / or the fourth fiber bundle in the corresponding second fiber bundle group to adjust the size of the interlayer porosity along the first direction.

[0010] According to some embodiments of the present invention, the longitudinal sections of the first fiber bundle, the second fiber bundle, the third fiber bundle, and the fourth fiber bundle are all constructed as sinusoidal curves, and adjusting the size of the interlayer porosity along the first direction includes: adjusting the amplitude of the first fiber bundle and / or the second fiber bundle in the corresponding first fiber bundle group to adjust the size of the interlayer porosity along the first direction; and / or, adjusting the amplitude of the third fiber bundle and / or the fourth fiber bundle in the corresponding second fiber bundle group to adjust the size of the interlayer porosity along the first direction.

[0011] According to some embodiments of the present invention, the parameter adjustment method further includes: adjusting the path of the seepage channel.

[0012] According to some embodiments of the present invention, adjusting the path of the permeation channel includes rotating at least one of the fiber cloths about the first direction as an axis to adjust the path of the permeation channel.

[0013] According to some embodiments of the present invention, the parameter adjustment method further includes: adjusting the angle between the seepage channel and the first direction to change the orientation of the seepage channel.

[0014] According to some embodiments of the present invention, adjusting the angle between the seepage channel and the first direction includes: defining a plurality of fiber cloths arranged sequentially along the first direction as a first fiber cloth, a second fiber cloth, a third fiber cloth, ..., an Nth fiber cloth; displacing the Nth fiber cloth relative to the (N-1)th fiber cloth by a preset size in a direction parallel to a first plane, wherein the first plane is orthogonal to the first direction, so as to adjust the angle between the seepage channel and the first direction, wherein the sum of the displacements of all the fiber cloths is less than the size of the inter-bundle pores along the corresponding direction.

[0015] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0016] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which: Figure 1 This is a schematic diagram of a ceramic matrix composite material according to an embodiment of the present invention; Figure 2 This is a schematic diagram of two layers of fiber cloth twisting relative to each other according to an embodiment of the present invention; Figure 3 This is a schematic diagram showing the displacement of a multilayer fiber cloth by a predetermined dimension along a direction parallel to the first plane according to an embodiment of the present invention; Figure 4 This is a schematic diagram of a single-layer fiber cloth according to an embodiment of the present invention; Figure 5 This is a schematic diagram of plain weave according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the interlayer pores between two layers of fiber cloth according to an embodiment of the present invention; Figure 7 This is a schematic diagram of the first fiber bundle according to an embodiment of the present invention; Figure 8 This is a schematic diagram of the weaving of the first fiber bundle, the third fiber bundle, and the fourth fiber bundle according to an embodiment of the present invention; Figure 9 This is a flowchart of a parameter adjustment method for a plain weave preform skeleton of ceramic matrix composite material applied to an aero-engine according to an embodiment of the present invention; Figure 10 This is a schematic diagram of a fiber cloth with widened fiber bundles according to an embodiment of the present invention; Figure 11 This is a schematic diagram of an elliptical cross-section of a fiber bundle according to an embodiment of the present invention.

[0017] Figure label: Fiber cloth 1; First fiber bundle group 11; First fiber bundle 111; Second fiber bundle 112; Second fiber bundle group 12; Third fiber bundle 121; Fourth fiber bundle 122; Permeation channel 13; Inter-bundle pore 131; Interlayer pore 132; Major axis 14; Minor axis 15; Ceramic matrix composite material 10. Detailed Implementation

[0018] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0019] The following is for reference. Figures 1-11 This invention describes a method for adjusting parameters of a plain weave prefabricated ceramic matrix composite skeleton for use in an aero-engine, according to an embodiment of the present invention.

[0020] like Figure 1 As shown, according to an embodiment of the present invention, a parameter adjustment method for a plain weave prefabricated skeleton of a ceramic matrix composite material 10 applied to an aero-engine is provided. The ceramic matrix composite material includes: multiple layers of fiber cloth 1 arranged sequentially along a first direction, wherein any two adjacent layers of fiber cloth 1 together define interlayer pores 132.

[0021] Among them, the ceramic matrix composite material 10 is a composite material that combines fiber bundles and a matrix. The fiber bundles can be carbon fibers or silicon carbide fibers, for example, the fiber bundles can be woven from silicon carbide filaments. The fiber bundles are woven into fiber cloth 1, and multiple layers of fiber cloth 1 are stacked to form a preform. The structure of the preform can be a plain weave structure. The silicon carbide matrix needs to be deposited by chemical vapor deposition or other methods to achieve ceramicization.

[0022] Ceramic matrix composite material 10 possesses advantages such as high temperature resistance, light weight, and high specific strength. It can be applied to hot-end components of aero-engines (e.g., turbine blades, combustion chamber flame tube walls). By utilizing its high-temperature resistance, the adverse effects of high-temperature airflow on the performance of hot-end components can be reduced. The in-situ self-generated pores within the ceramic matrix composite material serve as cooling air permeation channels for evaporative cooling, effectively lowering the material temperature. This, in turn, can increase the combustion temperature of the aero-engine, thereby improving important performance parameters such as thrust-to-weight ratio. Furthermore, by leveraging the light weight of the ceramic matrix composite material 10, its weight percentage can be reduced. Compared to related technologies that use metal materials as hot-end components (the density of the ceramic matrix composite material 10 is approximately 1 / 4 to 1 / 3 of the density of the aforementioned metal materials), the ceramic matrix composite material 10 can reduce the overall weight, thus improving the thrust-to-weight ratio of the aero-engine.

[0023] like Figures 1-3 As shown, the ceramic matrix composite material 10 includes multiple layers of fiber cloth 1 stacked sequentially along a first direction. Any two adjacent layers of fiber cloth 1 jointly define interlayer pores 132. The interlayer pores 132 enable the ceramic matrix composite material 10 to have the prerequisite for sweating and cooling. Cooling gas can permeate through the interlayer pores 132 to the side of the ceramic matrix composite material 10 facing the high-temperature airflow. Permeation can be understood as the cooling gas flowing in the inter-beam pores 131 and interlayer pores 132. Low-temperature gas can reduce the high-temperature corrosion of the ceramic matrix composite material 10 by the high-temperature airflow, so that the ceramic matrix composite material 10 can cope with the high-temperature airflow, thereby meeting the high-temperature environment requirements of hot-end components, so that the aero-engine can have a higher operating temperature, which is beneficial to improving the thrust-to-weight ratio of the aero-engine.

[0024] like Figure 4 and Figure 5 As shown, the fiber fabric includes a plurality of first fiber bundles 111 and a plurality of second fiber bundles 112 arranged alternately along a second direction, and a plurality of third fiber bundles 121 and a plurality of fourth fiber bundles 122 arranged alternately along a third direction. Any two of the first, second, and third directions are orthogonal. The first fiber bundles 111 and second fiber bundles 112 are woven with the plurality of third fiber bundles 121 and the plurality of fourth fiber bundles 122. Along the first direction, the contact point between the first fiber bundle 111 and the third fiber bundle 121 is located above the corresponding third fiber bundle 121, the contact point between the first fiber bundle 111 and the fourth fiber bundle 122 is located below the corresponding fourth fiber bundle 122, the contact point between the second fiber bundle 112 and the third fiber bundle 121 is located below the corresponding third fiber bundle 121, and the contact point between the first fiber bundle 111 and the fourth fiber bundle 122 is located above the corresponding fourth fiber bundle 122.

[0025] Specifically, multiple first fiber bundles 111 and multiple second fiber bundles 112 can extend along a third direction, and the multiple first fiber bundles 111 and multiple second fiber bundles 112 are arranged alternately along a second direction. That is, along the second direction, each first fiber bundle 111 (excluding the first fiber bundle 111 located on the side) has a second fiber bundle 112 arranged on both sides, and each second fiber bundle 112 (excluding the second fiber bundle 112 located on the side) has a first fiber bundle 111 arranged on both sides. It should be noted that the longitudinal sections of the first fiber bundles 111 and the second fiber bundles 112 can both be constructed as sine curves. In fact, the first fiber bundles 111 and the second fiber bundles 112 can have the same structure, that is, the sine functions satisfied by the longitudinal sections of the first fiber bundles 111 and the second fiber bundles 112 have the same shape. The sine function satisfied by the first fiber bundle 111 is defined as the first sine function, and the sine function satisfied by the second fiber bundle 112 is defined as the second sine function. The amplitude, period, and angular frequency of the first sine function and the second sine function are the same. Along the third direction, the initial phases of the first sine function and the second sine function differ by half a cycle, so that the waveforms of the first sine function and the second sine function are opposite along the second direction.

[0026] Similarly, multiple third fiber bundles 121 and multiple fourth fiber bundles 122 can extend along the second direction, and the multiple third fiber bundles 121 and multiple fourth fiber bundles 122 are arranged alternately along the third direction. That is, along the third direction, each third fiber bundle 121 (excluding the third fiber bundle 121 located on the side) has a fourth fiber bundle 122 arranged on both sides, and each fourth fiber bundle 122 (excluding the fourth fiber bundle 122 located on the side) has a third fiber bundle 121 arranged on both sides. It should be noted that the longitudinal section of both the third fiber bundle 121 and the fourth fiber bundle 122 can be constructed as a sine curve. In fact, the third fiber bundle 121 and the fourth fiber bundle 122 can have the same structure. In other words, the sine functions satisfied by the longitudinal sections of the third fiber bundle 121 and the fourth fiber bundle 122 have the same shape. The sine function satisfied by the third fiber bundle 121 is defined as the third sine function, and the sine function satisfied by the fourth fiber bundle 122 is defined as the fourth sine function. The amplitude, period, and angular frequency of the third sine function and the fourth sine function are the same.

[0027] Furthermore, such as Figure 4 and Figure 5As shown, the first fiber bundle 111 and the second fiber bundle 112 are both woven with a plurality of third fiber bundles 121 and a plurality of fourth fiber bundles 122. Along the first direction, among adjacent first fiber bundles 111 and second fiber bundles 112, if the position where the third fiber bundle 121 contacts the first fiber bundle 111 is located above the corresponding first fiber bundle 111, then the position where the third fiber bundle 121 contacts the second fiber bundle 112 is located below the corresponding second fiber bundle 112. If the position where the fourth fiber bundle 122 contacts the first fiber bundle 111 is located below the corresponding first fiber bundle 111, then the position where the fourth fiber bundle 122 contacts the second fiber bundle 112 is located above the corresponding second fiber bundle 112.

[0028] Similarly, such as Figure 4 and Figure 5 As shown, the third fiber bundle 121 and the fourth fiber bundle 122 are both woven with a plurality of first fiber bundles 111 and a plurality of second fiber bundles 112. Along the first direction, in adjacent third fiber bundles 121 and fourth fiber bundles 122, if the contact position between the first fiber bundle 111 and the third fiber bundle 121 is located on the upper side of the corresponding third fiber bundle 121, then the contact position between the first fiber bundle 111 and the fourth fiber bundle 122 is located on the lower side of the corresponding fourth fiber bundle 122. If the contact position between the second fiber bundle 112 and the third fiber bundle 121 is located on the lower side of the corresponding third fiber bundle 121, then the contact position between the first fiber bundle 111 and the fourth fiber bundle 122 is located on the upper side of the corresponding fourth fiber bundle 122.

[0029] like Figure 1 As shown, the first fiber bundle 111 and any adjacent second fiber bundle 112 constitute a first fiber bundle group 11, and the third fiber bundle 121 and any adjacent fourth fiber bundle 122 constitute a second fiber bundle group 12. The first fiber bundle group 11 and the second fiber bundle group 12 together define the inter-bundle pores 131. Along the first direction, the multiple opposing inter-bundle pores 131 and the multiple interlayer pores 132 together constitute a seepage channel 13.

[0030] Furthermore, such as Figure 1As shown, the first fiber bundle 111 and any adjacent second fiber bundle 112 constitute a first fiber bundle group 11, and the third fiber bundle 121 and any adjacent fourth fiber bundle 122 constitute a second fiber bundle group 12. The extension direction of the first fiber bundle group 11 is orthogonal to the extension direction of the second fiber bundle group 12. The first fiber bundle group 11 and the second fiber bundle group 12 together define the inter-bundle pores 131. Along the first direction, multiple opposing inter-bundle pores 131 and multiple interlayer pores 132 together constitute a permeation channel 13. Through the permeation channel 13, the ceramic matrix composite material 10 can reduce its own temperature by sweating and cooling. When the ceramic matrix composite material 10 is applied to a hot-end component (e.g., attached to the combustion chamber wall), along the thickness direction of the ceramic matrix composite material 10, cooling gas can permeate from the side near the hot-end component through the permeation channel 13 to the side near the high-temperature gas flow, so that the cooling gas can cover the surface of the hot-end component to form a gas film, thereby reducing the temperature rise effect of the high-temperature gas flow on the ceramic matrix composite material 10, so as to reduce the temperature of the hot-end component and prevent high-temperature corrosion of the hot-end component by high-temperature water, oxygen and gas.

[0031] The following is based on Figure 9 The flowchart shown describes the parameter adjustment method of this application for a ceramic matrix composite 10 plain weave preform skeleton applied to aero-engines. The parameter adjustment method includes the following steps: S1, Adjust the size of the inter-fiber pore 131. As some embodiments of this application, by adjusting the distance between the first fiber bundle 111 and the second fiber bundle 112 in the first fiber bundle group 11 along the second direction, and by adjusting the distance between the third fiber bundle 121 and the fourth fiber bundle 122 in the second fiber bundle group 12 along the third direction, the flow area size of the inter-fiber pore 131 jointly defined by the first fiber bundle group 11 and the second fiber bundle group 12 can be adjusted. The side length of the inter-fiber pore 131 can be between 0.4 mm and 0.6 mm, and the side length of the inter-fiber pore 131 can be 0.4 mm, 0.5 mm, 0.6 mm, etc. This setting allows the fiber bundle to have both structural strength and cooling capacity, thereby improving the reliability of the ceramic matrix composite material 10.

[0032] Therefore, by adjusting the size of the inter-beam pore 131, the flow rate of the cooling gas passing through the inter-beam pore 131 can be adjusted to regulate the cooling effect on the ceramic matrix composite material 10. Furthermore, in the ceramic matrix composite material 10, in areas where high-intensity cooling is required, the cooling gas flow rate can be increased by enlarging the corresponding inter-beam pore 131 to enhance the cooling effect.

[0033] S2, as Figure 10As shown, the pore spacing between adjacent inter-bundle pores 131 is adjusted. Two adjacent inter-bundle pores 131 can be separated by a first fiber bundle 111, a second fiber bundle 112, a third fiber bundle 121, or a fourth fiber bundle 122. The pore spacing between adjacent inter-bundle pores 131 can be adjusted by adjusting the width of the corresponding first fiber bundle 111, second fiber bundle 112, third fiber bundle 121, or fourth fiber bundle 122. The width of the corresponding first fiber bundle 111, second fiber bundle 112, third fiber bundle 121, or fourth fiber bundle 122 is the pore spacing between adjacent inter-bundle pores 131.

[0034] Therefore, by adjusting the pore spacing between adjacent inter-beam pores 131, the overall cooling gas flow rate through all inter-beam pores 131 is adjusted, thereby macroscopically controlling the cooling effect on the ceramic matrix composite material 10.

[0035] S3, Adjust the size of the interlayer pores 132 along the first direction. The size of the interlayer pores 132 along the first direction can be adjusted by changing the thickness of the corresponding fiber bundle (the size along the first direction). The larger the thickness of the fiber bundle, the larger the size of the interlayer pores 132 along the first direction.

[0036] Therefore, by adjusting the size of the interlayer pores 132 along the first direction, the flow rate of cooling gas through the interlayer pores 132 can be adjusted. The larger the interlayer pores 132, the greater the flow rate of cooling gas, and the better the cooling effect on the ceramic matrix composite material 10.

[0037] In the above embodiments, multiple fiber bundles are woven to form inter-bundle pores 131, and multiple layers of fiber cloth 1 are stacked to form inter-layer pores 132. The inter-bundle pores 131 and inter-layer pores 132 are adjusted to regulate the flow rate of cooling gas in the permeation channel 13, so that the cooling gas can cover the surface of the hot end component to form a gas film, thereby reducing the temperature rise effect of high-temperature airflow on the ceramic matrix composite material 10, so as to reduce the temperature of the hot end component and prevent high-temperature corrosion of the hot end component by high-temperature water, oxygen and gas.

[0038] It should be added that, such as Figures 5-8As shown, the fiber cloth 1 is made by plain weave. During the weaving process, the flow rate of the cooling gas can be adjusted by adjusting parameters, including: the long axis 14 of the fiber bundle, the short axis 15 of the fiber bundle, and the arrangement of adjacent layers of fiber cloth 1. For example, increasing the size of the long axis 14 of the fiber bundle can increase the width of the fiber bundle, and thus the spacing between the pores 131 between adjacent bundles can be adjusted by adjusting the width of the fiber bundle; increasing the size of the short axis 15 of the fiber bundle can increase the distance between adjacent layers of fiber cloth 1, and thus the size of the interlayer pores 132 along the first direction can be adjusted by adjusting the thickness of the fiber bundle; by rotating at least one fiber cloth 1 about the first direction as an axis, the fiber cloth 1 adjacent to the rotated fiber cloth 1 is misaligned with the rotated fiber cloth 1, so that the interlayer pores 131 of the fiber cloth 1 adjacent to the rotated fiber cloth 1 are aligned with the rotated fiber cloth 1. The inter-beam pores 131 are misaligned to extend the path of the permeation channel 13, increase the flow resistance to the cooling gas, reduce the flow rate of the cooling gas, and thus achieve the effect of controlling the cooling capacity of the cooling gas on the ceramic matrix composite material 10. The angle between the permeation channel 13 and the first direction is adjusted by changing the interlayer phase displacement. That is, the two adjacent fiber cloths 1 are misaligned to change the orientation of the permeation channel 13, so that the orientation of the permeation channel 13 has an angle with the first direction, thereby extending the length of the permeation channel 13 and reducing the outlet angle of the cooling gas, so as to generate a certain resistance to the flow of the cooling gas and appropriately reduce the cooling capacity of the cooling gas on the ceramic matrix composite material 10.

[0039] In some embodiments of the present invention, adjusting the size of the inter-bundle aperture 131 includes: adjusting the spacing between the first fiber bundle 111 and the second fiber bundle 112 in the corresponding first fiber bundle group 11 to adjust the size of the inter-bundle aperture 131; and / or, adjusting the spacing between the third fiber bundle 121 and the fourth fiber bundle 122 in the corresponding second fiber bundle group 12 to adjust the size of the inter-bundle aperture 131.

[0040] Each inter-beam pore 131 can be defined by a corresponding first fiber bundle group 11 and a second fiber bundle group 12. To adjust the size of the inter-beam pore 131, the spacing between the first fiber bundle 111 and the second fiber bundle 112 in the corresponding first fiber bundle group 11 can be adjusted. A larger spacing between the first fiber bundle 111 and the second fiber bundle 112 in the corresponding first fiber bundle group 11 results in a larger inter-beam pore 131. Alternatively, the spacing between the third fiber bundle 121 and the fourth fiber bundle 122 in the corresponding second fiber bundle group 12 can be adjusted. A larger spacing between the third fiber bundle 121 and the fourth fiber bundle 122 in the corresponding second fiber bundle group 12 results in a larger inter-beam pore 131. By adjusting the size of the inter-beam pore 131, the flow rate of the cooling gas passing through the inter-beam pore 131 can be adjusted to regulate the cooling effect on the ceramic matrix composite material 10. Furthermore, in areas of the ceramic matrix composite material 10 requiring high-intensity cooling, increasing the size of the corresponding inter-beam pore 131 can increase the flow rate of the cooling gas and improve the cooling effect. The adjustment method is simple, efficient, and easy to implement.

[0041] In some embodiments of the present invention, adjusting the pore spacing of adjacent inter-bundle pores 131 includes: adjusting the width of the first fiber bundle 111 and / or the second fiber bundle 112 in the corresponding first fiber bundle group 11 to adjust the size of the inter-bundle pore 131; and / or, adjusting the width of the third fiber bundle 121 and / or the fourth fiber bundle 122 in the corresponding second fiber bundle group 12 to adjust the size of the inter-bundle pore 131.

[0042] The adjacent inter-bundle pores 131 can be separated by the first fiber bundle 111 and / or the second fiber bundle 112 in the first fiber bundle group 11. That is, adjacent inter-bundle pores 131 can be separated by the first fiber bundle 111 in the first fiber bundle group 11, or by the second fiber bundle 112 in the first fiber bundle group 11, or by both the first fiber bundle 111 and the second fiber bundle 112 in the first fiber bundle group 11. To adjust the pore spacing of adjacent inter-bundle pores 131, the width of the corresponding first fiber bundle 111 and / or the second fiber bundle 112 in the first fiber bundle group 11 can be adjusted. The larger the width of the corresponding first fiber bundle 111 and / or the second fiber bundle 112 in the first fiber bundle group 11, the larger the pore spacing of adjacent inter-bundle pores 131.

[0043] Similarly, adjacent inter-bundle pores 131 can also be separated by the third fiber bundle 121 and / or the fourth fiber bundle 122 in the second fiber bundle group 12. That is, adjacent inter-bundle pores 131 can be separated by the third fiber bundle 121 in the second fiber bundle group 12, or by the fourth fiber bundle 122 in the second fiber bundle group 12, or by both the third fiber bundle 121 and the fourth fiber bundle 122 in the second fiber bundle group 12. To adjust the pore spacing of adjacent inter-bundle pores 131, the width of the corresponding third fiber bundle 121 and / or the fourth fiber bundle 122 in the second fiber bundle group 12 can be adjusted. The larger the width of the corresponding third fiber bundle 121 and / or the fourth fiber bundle 122 in the second fiber bundle group 12, the larger the pore spacing of adjacent inter-bundle pores 131.

[0044] Therefore, by adjusting the pore spacing of adjacent inter-beam pores 131, the density of the inter-beam pores 131 can be adjusted, thereby regulating the overall flow rate through all inter-beam pores 131, and thus macroscopically controlling the cooling effect on the ceramic matrix composite material 10. The adjustment method is simple, efficient, and easy to implement.

[0045] In some embodiments of the present invention, such as Figures 5-8 , Figure 11 As shown, the cross-sections of the first fiber bundle 111, the second fiber bundle 112, the third fiber bundle 121, and the fourth fiber bundle 122 are all constructed as ellipses. Adjusting the pore spacing of the adjacent inter-bundle pores 131 includes: adjusting the size of the inter-bundle pores 131 by adjusting the major axis 14 of the first fiber bundle 111 and / or the second fiber bundle 112 in the corresponding first fiber bundle group 11; and / or, adjusting the size of the inter-bundle pores 131 by adjusting the major axis 14 of the third fiber bundle 121 and / or the fourth fiber bundle 122 in the corresponding second fiber bundle group 12.

[0046] The cross-sections of the first fiber bundle 111, the second fiber bundle 112, the third fiber bundle 121, and the fourth fiber bundle 122 can all be constructed as ellipses. The width of each fiber bundle is the major axis 14 of the ellipse, and the thickness is the minor axis 15 of the ellipse. The length of the major axis 14 can range from 1.8 mm to 2.2 mm, and can be 1.8 mm, 2.0 mm, 2.2 mm, etc. The length of the minor axis 15 can range from 0.2 mm to 0.4 mm, and can be 0.2 mm, 0.3 mm, 0.4 mm, etc. This configuration ensures that the cross-sectional dimensions of the first fiber bundle 111, the second fiber bundle 112, the third fiber bundle 121, and the fourth fiber bundle 122 are reasonable.

[0047] To adjust the pore spacing between adjacent fiber bundles 131, the major axis 14 of the first fiber bundle 111 and / or the second fiber bundle 112 in the corresponding first fiber bundle group 11 can be adjusted. That is, the size of the inter-bundle pore 131 can be adjusted by adjusting the major axis 14 of the first fiber bundle 111 in the corresponding first fiber bundle group 11, or vice versa. A larger major axis 14 of the first fiber bundle 111 and / or the second fiber bundle 112 in the corresponding first fiber bundle group 11 results in a larger pore spacing between adjacent fiber bundles 131. To adjust the pore spacing between adjacent fiber bundles 131, the major axis 14 of the third fiber bundle 121 and / or the fourth fiber bundle 122 in the corresponding second fiber bundle group 12 can be adjusted. The larger the major axis 14 of the third fiber bundle 121 and / or the fourth fiber bundle 122 in the corresponding second fiber bundle group 12, the larger the pore spacing between adjacent fiber bundles 131.

[0048] Therefore, by adjusting the pore spacing of adjacent inter-beam pores 131, the density of the inter-beam pores 131 is adjusted, thereby regulating the overall cooling gas flow rate through all inter-beam pores 131, thus macroscopically controlling the cooling effect on the ceramic matrix composite material 10. The adjustment method is simple, efficient, and easy to implement.

[0049] In some embodiments of the present invention, such as Figures 5-8 , Figure 11 As shown, the cross-sections of the first fiber bundle 111, the second fiber bundle 112, the third fiber bundle 121, and the fourth fiber bundle 122 are all constructed as ellipses. Adjusting the size of the interlayer pore 132 along the first direction includes: adjusting the minor axis 15 of the first fiber bundle 111 and / or the second fiber bundle 112 in the corresponding first fiber bundle group 11 to adjust the size of the interlayer pore 132 along the first direction; and / or, adjusting the minor axis 15 of the third fiber bundle 121 and / or the fourth fiber bundle 122 in the corresponding second fiber bundle group 12 to adjust the size of the interlayer pore 132 along the first direction.

[0050] To adjust the size of the interlayer pores 132 along the first direction, the minor axis 15 of the first fiber bundle 111 and / or the second fiber bundle 112 in the corresponding first fiber bundle group 11 can be adjusted. Specifically, the size of the interlayer pores 132 along the first direction can be adjusted by adjusting the minor axis 15 of the first fiber bundle 111, or vice versa. A larger minor axis 15 of the first fiber bundle 111 and / or the second fiber bundle 112 in the corresponding first fiber bundle group 11 results in a larger pore spacing between adjacent interlayer pores 132.

[0051] Similarly, to adjust the size of the interlayer pores 132 along the first direction, the minor axis 15 of the third fiber bundle 121 and / or the fourth fiber bundle 122 in the corresponding second fiber bundle group 12 can be adjusted. That is, the size of the interlayer pores 132 along the first direction can be adjusted by adjusting the minor axis 15 of the third fiber bundle 121 in the corresponding second fiber bundle group 12, or by adjusting the minor axis 15 of the fourth fiber bundle 122 in the corresponding second fiber bundle group 12, or by adjusting the minor axes 15 of both the third and fourth fiber bundles 121 and 122 in the corresponding second fiber bundle group 12. The larger the minor axis 15 of the third fiber bundle 121 and / or the fourth fiber bundle 122 in the corresponding second fiber bundle group 12, the larger the pore spacing between adjacent interlayer pores 132.

[0052] As some embodiments of this application, the size of the interlayer pore 132 along the first direction can be in the range of 0.01mm to 0.1mm, and the size of the interlayer pore 132 along the first direction can be 0.01mm, 0.05mm, 0.1mm, etc. This setting can make the size of the interlayer pore 132 along the first direction reasonable, so as to reasonably adjust the flow rate of cooling gas.

[0053] Therefore, by adjusting the pore spacing of adjacent inter-beam pores 131, the density of the inter-beam pores 131 can be adjusted, thereby regulating the overall flow rate through all inter-beam pores 131, and thus macroscopically controlling the cooling effect on the ceramic matrix composite material 10. The adjustment method is simple, efficient, and easy to implement.

[0054] In some embodiments of the present invention, the longitudinal sections of the first fiber bundle 111, the second fiber bundle 112, the third fiber bundle 121, and the fourth fiber bundle 122 are all constructed as sinusoidal curves. Adjusting the size of the interlayer pore 132 along the first direction includes: adjusting the amplitude of the first fiber bundle 111 and / or the second fiber bundle 112 in the corresponding first fiber bundle group 11 to adjust the size of the interlayer pore 132 along the first direction; and / or, adjusting the amplitude of the third fiber bundle 121 and / or the fourth fiber bundle 122 in the corresponding second fiber bundle group 12 to adjust the size of the interlayer pore 132 along the first direction.

[0055] The longitudinal sections of the first fiber bundle 111, the second fiber bundle 112, the third fiber bundle 121, and the fourth fiber bundle 122 can all be constructed as sine curves. The amplitude, period, and angular frequency of the sine function satisfied by the longitudinal sections of the first fiber bundle 111, the second fiber bundle 112, the third fiber bundle 121, and the fourth fiber bundle 122 are all the same. The larger the absolute value of the amplitude of the sine function satisfied by the longitudinal sections of the first fiber bundle 111, the second fiber bundle 112, the third fiber bundle 121, and the fourth fiber bundle 122, the larger the dimension of the first fiber bundle 111, the second fiber bundle 112, the third fiber bundle 121, and the fourth fiber bundle 122 along the first direction.

[0056] The size of the interlayer pore 132 along the first direction can be adjusted by adjusting the amplitude of the first fiber bundle 111 and / or the second fiber bundle 112 in the corresponding first fiber bundle group 11. That is, the size of the interlayer pore 132 along the first direction can be adjusted by adjusting the amplitude of the first fiber bundle 111 in the corresponding first fiber bundle group 11, or the size of the interlayer pore 132 along the first direction can be adjusted by adjusting the amplitude of the second fiber bundle 112 in the corresponding first fiber bundle group 11, or the size of the interlayer pore 132 along the first direction can be adjusted by simultaneously adjusting the amplitudes of the first fiber bundle 111 and the second fiber bundle 112 in the corresponding first fiber bundle group 11.

[0057] Similarly, the size of the interlayer pore 132 along the first direction can be adjusted by adjusting the amplitude of the third fiber bundle 121 and / or the fourth fiber bundle 122 in the corresponding second fiber bundle group 12. That is, the size of the interlayer pore 132 along the first direction can be adjusted by adjusting the amplitude of the third fiber bundle 121 in the corresponding second fiber bundle group 12, or the size of the interlayer pore 132 along the first direction can be adjusted by adjusting the amplitude of the fourth fiber bundle 122 in the corresponding second fiber bundle group 12, or the size of the interlayer pore 132 along the first direction can be adjusted by simultaneously adjusting the amplitudes of the third fiber bundle 121 and the fourth fiber bundle 122 in the corresponding second fiber bundle group 12.

[0058] Therefore, by adjusting the size of the interlayer pores 132 along the first direction, the flow rate of the cooling gas through the interlayer pores 132 can be adjusted. The larger the interlayer pores 132, the greater the flow rate of the cooling gas, and the better the cooling effect on the ceramic matrix composite material 10.

[0059] In some embodiments of the present invention, such as Figure 9 As shown, the parameter adjustment method also includes adjusting the path of the seepage channel 13.

[0060] It should be noted that the shortest path of the percolation channel 13 is approximately equal to the thickness of the ceramic matrix composite material 10. When the percolation channel 13 has a shortest path, the extension direction of the multiple inter-beam pores 131 forming the percolation channel 13 is parallel to the first direction. The cooling gas flows through the shortest path of the percolation channel 13, resulting in a shorter path. In this case, the resistance of the ceramic matrix composite material 10 to the flow of cooling gas is smaller, allowing for smoother flow and improving the cooling capacity of the cooling gas on the ceramic matrix composite material 10. At certain locations on the ceramic matrix composite material 10, where a strong cooling capacity is not required, the path of the percolation channel 13 can be appropriately lengthened to create some resistance to the flow of cooling gas, thereby appropriately reducing the cooling capacity of the cooling gas on the ceramic matrix composite material 10. This ensures that the cooling capacity of the cooling gas on the ceramic matrix composite material 10 matches the required cooling effect, saves cooling gas, and improves the reliability of the ceramic matrix composite material 10.

[0061] In some embodiments of the present invention, such as Figure 2 As shown, adjusting the path of the seepage channel 13 includes rotating at least one fiber cloth 1 about a first direction as an axis to adjust the path of the seepage channel 13.

[0062] In this embodiment, at least one fiber cloth 1 is rotated about a first direction as an axis to adjust the path of the permeation channel 13, thereby controlling the cooling capacity of the cooling gas on the ceramic matrix composite material 10. In some embodiments of this application, by rotating at least one fiber cloth 1 about a first direction as an axis, the fiber cloth 1 adjacent to the rotated fiber cloth 1 is misaligned with the rotated fiber cloth 1, causing the inter-bundle pores 131 of the fiber cloth 1 adjacent to the rotated fiber cloth 1 to be misaligned with the inter-bundle pores 131 of the rotated fiber cloth 1. This extends the path of the permeation channel 13, increases the flow resistance to the cooling gas, reduces the cooling gas flow rate, and thus controls the cooling capacity of the cooling gas on the ceramic matrix composite material 10.

[0063] In some embodiments of the present invention, such as Figure 3 As shown, the parameter adjustment method also includes: adjusting the angle between the seepage channel 13 and the first direction to change the orientation of the seepage channel 13.

[0064] The angle between the permeation channel 13 and the first direction can be adjusted by changing the interlayer phase displacement. That is, the two adjacent fiber cloths 1 are staggered to change the orientation of the permeation channel 13, so that the orientation of the permeation channel 13 has an angle with the first direction, thereby extending the length of the permeation channel 13 and reducing the outlet angle of the cooling gas, so as to generate a certain resistance to the flow of the cooling gas and appropriately reduce the cooling capacity of the cooling gas on the ceramic matrix composite material 10. This makes the cooling capacity of the cooling gas on the ceramic matrix composite material 10 match the required cooling effect, and can save cooling gas, which is beneficial to improving the reliability of the ceramic matrix composite material 10.

[0065] In some embodiments of the present invention, adjusting the angle between the seepage channel 13 and the first direction includes: defining the multilayer fiber cloth 1 arranged sequentially along the first direction as the first fiber cloth, the second fiber cloth, the third fiber cloth, ... the Nth fiber cloth, and placing the Nth fiber cloth relative to the (N-1)th fiber cloth, with the first plane orthogonal to the first direction, so as to adjust the angle between the seepage channel 13 and the first direction, wherein the total displacement of all fiber cloths 1 is less than the size of the inter-bundle pores 131 along the corresponding direction.

[0066] Specifically, multiple fiber cloths 1 stacked along the first direction are defined as first fiber cloth, second fiber cloth, third fiber cloth, ... Nth fiber cloth. A plane orthogonal to the first direction is defined as the first plane. The Nth fiber cloth is displaced by a preset size relative to the (N-1)th fiber cloth in a direction parallel to the first plane, so that the Nth fiber cloth and the (N-1)th fiber cloth are staggered in a direction parallel to the first plane. This allows the permeation channel 13 to have an angle with the first direction, thereby extending the length of the permeation channel 13 and generating a certain resistance to the flow of cooling gas, so as to appropriately reduce the cooling capacity of the cooling gas on the ceramic matrix composite material 10. It should be noted that the total displacement of all fiber cloths 1 (the sum of all preset sizes) is less than the size of the inter-bundle pores 131 in the corresponding direction, so that the permeation channel 13 can allow the cooling gas to flow through, so that the permeation channel 13 can function properly.

[0067] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0068] In the description of this invention, "first feature" and "second feature" may include one or more of the features.

[0069] In the description of this invention, "a plurality of" means two or more.

[0070] In the description of this invention, the first feature being "above" or "below" the second feature may include the first and second features being in direct contact, or it may include the first and second features not being in direct contact but being in contact through another feature between them.

[0071] In the description of this invention, the terms "above," "over," and "on top" for the first feature and the second feature include the first feature being directly above or diagonally above the second feature, or simply indicating that the first feature is at a higher horizontal level than the second feature.

[0072] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0073] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A method for adjusting parameters of a ceramic matrix composite plain weave preform skeleton applied to an aeroengine, characterized in that, The ceramic matrix composite comprises: a plurality of fiber cloths arranged in sequence along a first direction, any two adjacent fiber cloths defining an interlayer pore, the fiber cloth comprising: a plurality of first fiber bundles and a plurality of second fiber bundles arranged alternately along a second direction, and a plurality of third fiber bundles and a plurality of fourth fiber bundles arranged alternately along a third direction, any two of the first direction, the second direction, and the third direction being orthogonal; The first fiber bundle and any adjacent second fiber bundle form a first fiber bundle group, and the third fiber bundle and any adjacent fourth fiber bundle form a second fiber bundle group, the first fiber bundle group and the second fiber bundle group defining a bundle inter-pore, along the first direction, a plurality of opposite bundle inter-pores and a plurality of interlayer pores form a flow channel. The parameter adjustment method comprises: Adjusting the size of the bundle inter-pore; Adjusting the inter-pore spacing of adjacent bundle inter-pores; Adjusting the size of the interlayer pore along the first direction.

2. The method of adjusting parameters of a ceramic matrix composite plain weave preform skeleton for an aeroengine according to claim 1, characterized in that, The adjustment of the size of the bundle inter-pore comprises: Adjusting the size of the bundle inter-pore by adjusting the spacing between the first fiber bundle and the second fiber bundle in the corresponding first fiber bundle group; and / or, adjusting the size of the bundle inter-pore by adjusting the spacing between the third fiber bundle and the fourth fiber bundle in the corresponding second fiber bundle group.

3. The method of adjusting parameters of a ceramic matrix composite plain weave preform skeleton for an aeroengine according to claim 1, characterized in that, The adjustment of the inter-pore spacing of adjacent bundle inter-pores comprises: Adjusting the size of the bundle inter-pore by adjusting the width of the first fiber bundle and / or the second fiber bundle in the corresponding first fiber bundle group; and / or, adjusting the size of the bundle inter-pore by adjusting the width of the third fiber bundle and / or the fourth fiber bundle in the corresponding second fiber bundle group.

4. The method for adjusting parameters of a ceramic matrix composite plain weave preform skeleton applied to an aero-engine according to claim 1 or 3, characterized in that, The cross section of the first fiber bundle, the second fiber bundle, the third fiber bundle, and the fourth fiber bundle is configured as an ellipse, and the adjustment of the inter-pore spacing of adjacent bundle inter-pores comprises: Adjusting the size of the bundle inter-pore by adjusting the major axis of the first fiber bundle and / or the second fiber bundle in the corresponding first fiber bundle group; and / or, adjusting the size of the bundle inter-pore by adjusting the major axis of the third fiber bundle and / or the fourth fiber bundle in the corresponding second fiber bundle group.

5. The method of adjusting parameters of a ceramic matrix composite plain weave preform skeleton for an aeroengine according to claim 1, characterized in that, The cross section of the first fiber bundle, the second fiber bundle, the third fiber bundle, and the fourth fiber bundle is configured as an ellipse, and the adjustment of the size of the interlayer pore along the first direction comprises: Adjusting the size of the interlayer pore along the first direction by adjusting the minor axis of the first fiber bundle and / or the second fiber bundle in the corresponding first fiber bundle group; and / or, adjusting the size of the interlayer pore along the first direction by adjusting the minor axis of the third fiber bundle and / or the fourth fiber bundle in the corresponding second fiber bundle group.

6. The method for adjusting parameters of a ceramic matrix composite plain weave preform skeleton applied to an aero-engine according to claim 1 or 5, characterized in that, The longitudinal section of the first fiber bundle, the second fiber bundle, the third fiber bundle, and the fourth fiber bundle is configured as a sinusoidal curve, and the adjustment of the size of the interlayer pore along the first direction comprises: adjusting amplitudes of the first fiber bundles and / or the second fiber bundles in the corresponding first fiber bundle group to adjust sizes of the interlayer pores along the first direction; and / or, adjusting amplitudes of the third fiber bundles and / or the fourth fiber bundles in the corresponding second fiber bundle group to adjust sizes of the interlayer pores along the first direction.

7. The method of adjusting parameters of a ceramic matrix composite plain weave preform skeleton for an aeroengine according to claim 1, characterized in that, The parameter adjusting method further comprises: adjusting a path of the percolation channel.

8. The method of adjusting parameters of a ceramic matrix composite plain weave preform skeleton for an aeroengine according to claim 7, characterized in that, The adjusting the path of the percolation channel comprises: rotating at least one of the fiber cloths around the first direction as an axis to adjust the path of the percolation channel.

9. The method of adjusting parameters of a ceramic matrix composite plain weave preform skeleton for an aeroengine according to claim 1, characterized in that, The parameter adjusting method further comprises: adjusting an included angle between the percolation channel and the first direction to change an orientation of the percolation channel.

10. The method of adjusting parameters of a ceramic matrix composite plain weave preform skeleton for an aeroengine according to claim 9, characterized in that, The adjusting the included angle between the percolation channel and the first direction comprises: defining a plurality of the fiber cloths arranged in sequence along the first direction as a first fiber cloth, a second fiber cloth, a third fiber cloth, …, an Nth fiber cloth, displacing the Nth fiber cloth relative to the (N-1)th fiber cloth along a direction parallel to a first plane by a preset size, the first plane being orthogonal to the first direction, to adjust the included angle between the percolation channel and the first direction, wherein a total sum of displacements of all the fiber cloths is less than a size of the interbundle pores along the corresponding direction.

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