Connection assembly for metal-ceramic matrix composites, metal-ceramic matrix composite component

Abstract

This invention relates to a connecting assembly and a metal-ceramic matrix composite component for use in metal-ceramic matrix composites, addressing the technical problem that existing assembly methods for ceramic-ceramic matrix composite components and metal components lead to reduced performance of the ceramic-ceramic matrix composite. The connecting assembly includes a ceramic-ceramic matrix composite connecting section and a metal connecting section connected to the ceramic-ceramic matrix composite connecting section; the ceramic-ceramic matrix composite connecting section is used to connect to a ceramic-ceramic matrix composite component, and the metal connecting section is used to connect to a metal component; the ceramic-ceramic matrix composite connecting section has two opposing first surfaces and two opposing second surfaces; the first surfaces are provided with inorganic fiber cloth for connecting to the bearing surface of the ceramic-ceramic matrix composite component; the ceramic-ceramic matrix composite connecting section has mounting pin holes and deformation compensation grooves penetrating the two second surfaces; the fastening portion of the ceramic-ceramic matrix composite component can be attached to the second surfaces and connected by pins penetrating the mounting pin holes.

Description

Technical Field

[0001] This invention relates to a connection device for ceramic-based composite components and metal components, specifically to a connection component for metal-ceramic composites and a metal-ceramic composite component. Background Technology

[0002] Hypersonic vehicles fly at high speeds under harsh conditions, with temperatures reaching 1000°C or even higher in most areas. Under such conditions, the performance of conventional metallic materials deteriorates drastically, making safe flight impossible. Ceramic matrix composites, due to their superior properties such as high temperature resistance, low density, resistance to oxidation and ablation, high specific strength, and high specific modulus, are increasingly widely used in the aerospace field as suitable materials for aircraft components.

[0003] The use of ceramic matrix composite (CMC) components creates certain process separation surfaces, requiring appropriate connection devices for assembly between CMC and metal components. Traditional assembly methods often employ mechanical connections such as screws and riveting. However, CMC has relatively low fracture strain and weak impact resistance, making screwing or riveting unsuitable for the use of CMC components. Summary of the Invention

[0004] The purpose of this invention is to solve the technical problem that the existing assembly methods of ceramic-based composite components and metal components lead to a reduction in the performance of ceramic-based composites. This invention proposes a connecting component and a metal-ceramic-based composite component for metal-ceramic composites to achieve effective connection between metal components and ceramic-based composite components, ensure the overall assembly reliability of the metal-ceramic-based components, and improve the overall product stability.

[0005] The technical solution provided by this invention is as follows:

[0006] A connection assembly for metal-ceramic matrix composites is characterized in that it includes a ceramic matrix composite connection segment and a metal connection segment connected to the ceramic matrix composite connection segment; both the ceramic matrix composite connection segment and the metal connection segment are made of titanium alloy.

[0007] The ceramic-based composite connecting section is used to connect with the ceramic-based composite component, and the metal connecting section is used to connect with the metal component;

[0008] The ceramic matrix composite connecting section has two first surfaces and two second surfaces arranged opposite to each other; the first surface is provided with inorganic fiber cloth for connecting with the bearing surface of the ceramic matrix composite component;

[0009] The ceramic matrix composite connecting section has mounting pin holes and deformation compensation grooves penetrating the two second surfaces; the two second surfaces are used to attach to the fastening part of the ceramic matrix composite assembly and are connected by pins penetrating the mounting pin holes.

[0010] Furthermore, the coefficient of thermal expansion of the inorganic fiber cloth material is less than that of the ceramic matrix composite component material;

[0011] The service temperature range of inorganic fiber cloth is from room temperature to 1600℃, and the modulus range is from 0 to 80 GPa.

[0012] Furthermore, the inorganic fiber cloth is quartz glass fiber cloth or basalt fiber fabric.

[0013] Furthermore, there are multiple mounting pin holes and deformation compensation grooves, which are arranged sequentially at intervals along the extension direction of the ceramic matrix composite connecting section;

[0014] The center line of the arrangement of the mounting pin holes and deformation compensation grooves is the center line of the second surface.

[0015] Furthermore, the deformation compensation groove is a dumbbell-shaped through groove; the extension direction of the deformation compensation groove is consistent with the arrangement direction of the deformation compensation groove.

[0016] Furthermore, the groove width X of the deformation compensation groove is:

[0017] X = a * L * ΔT

[0018] Where a is the coefficient of linear expansion of the ceramic-based composite connecting section and the metal connecting section, L is the sum of the lengths of the ceramic-based composite connecting section and the metal connecting section, and ΔT is the temperature difference of the operating environment.

[0019] Furthermore, the ceramic-based composite connecting section and the metal connecting section are provided with through holes along the axial direction for weight reduction.

[0020] The two ends of the pin are fixed by cotter pins, and a washer is provided between the cotter pin and the fastening part of the ceramic matrix composite component.

[0021] The cotter pin is made of GH3030, and the pin and washer are both made of GH4169.

[0022] Furthermore, the shape of the metal connecting segment matches the shape of the metal component to be connected;

[0023] A bushing and a flange are fitted on the outside of the metal connecting section to enable the connection between the metal connecting section and the metal component;

[0024] Both the bushing and the flange are made of titanium alloy.

[0025] The present invention also provides a metal-ceramic matrix composite component, which is characterized in that it includes a ceramic matrix composite component, a connecting component and a metal component connected in sequence;

[0026] The connecting component is the connecting component described above for metal-ceramic matrix composites.

[0027] The beneficial effects of this invention are:

[0028] 1. The present invention provides an inorganic fiber cloth between the ceramic matrix composite connecting section and the ceramic matrix composite assembly in the metal-ceramic matrix composite connecting component. When the aircraft is in a high-temperature environment, the inorganic fiber cloth can effectively solve the thermal compatibility problem between the composite component and the metal ceramic matrix composite connecting section.

[0029] 2. The present invention provides a deformation compensation groove on the second surface of the ceramic composite connecting section of the metal-ceramic composite connecting assembly, which can effectively solve the problem of different thermal deformation caused by the mismatch of thermal expansion coefficients between the ceramic composite connecting section and the ceramic composite assembly in high-temperature environments, thereby improving the reliability of the connection.

[0030] 3. The present invention designs pin connection holes between deformation compensation grooves on the second surface of the composite connecting shaft section. The composite connecting shaft section is connected to the ceramic matrix composite component through pins, washers and cotter pins. This can ensure the mechanical connection between the ceramic matrix composite component and the connecting component for metal-ceramic matrix composite, reduce assembly difficulty, improve operability and enhance overall reliability.

[0031] 4. The present invention designs the end face of the metal connection section of the connection component for metal-ceramic composite material that is connected to the metal component to match the actual shape and size of the metal component, and connects it to the metal component of the aircraft through bushings and flanges to ensure the overall connection strength.

[0032] 5. The connecting component for metal-ceramic matrix composites described in this invention is designed with a hollow structure, which can effectively reduce the overall weight of the aircraft. Simultaneously, the connecting component has openings at both ends and is manufactured using a dip-casting process, facilitating demolding during the manufacturing process.

[0033] 6. The connection component structure for metal-ceramic matrix composites described in this invention can provide sufficient bending moment for ceramic matrix composite components, ensuring the strength of the overall structure of the aircraft. Attached Figure Description

[0034] Figure 1 This is a three-dimensional schematic diagram of the ceramic-based composite connecting segment and the metal connecting segment in an embodiment of the connecting component for metal-ceramic composites of the present invention;

[0035] Figure 2 This is a perspective view of an embodiment of the connection component of the present invention for metal-ceramic matrix composites (the bushing and flange are not shown);

[0036] Figure 3 This is a schematic diagram of the ceramic matrix composite connecting section and the ceramic matrix composite component assembly.

[0037] The attached figures are labeled as follows:

[0038] 1-Ceramic matrix composite connecting section, 2-Metal connecting section, 11-Deformation compensation groove, 12-Mounting pin hole, 13-Cotter pin, 14-Gasket, 15-Pin, 3-Ceramic matrix composite assembly, 31-Bearing surface, 32-Fastening part, 4-Flange. Detailed Implementation

[0039] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0040] The term "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the invention. "Other embodiments" appearing in different places in this specification do not all refer to the same embodiment, nor are they isolated embodiments or selective embodiments that are mutually exclusive with other embodiments.

[0041] The schematic diagrams described in this invention are merely examples and should not be construed as limiting the scope of protection of this invention. Furthermore, in actual manufacturing, the three-dimensional spatial dimensions of length, width, and depth should be included.

[0042] Furthermore, it should be noted in the description of this invention that the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0043] See Figures 1-3 This embodiment provides a connecting component for metal-ceramic matrix composites. The connecting component includes a ceramic matrix composite connecting section 1 and a metal connecting section 2 connected to the ceramic matrix composite connecting section 1. The ceramic matrix composite connecting section 1 is used to connect to a ceramic matrix composite component 3, and the metal connecting section 2 is used to connect to a metal component. The ceramic matrix composite connecting section 1 and the metal connecting section 2 are provided with through holes along the axial direction for weight reduction, which can effectively reduce the weight of the overall metal-ceramic matrix composite component. At the same time, it facilitates the production of the connecting component for metal-ceramic matrix composites by dip casting process and facilitates demolding during the preparation process of the connecting component.

[0044] The shape of the metal connecting section 2 matches the shape of the metal component to be connected. A bushing and a flange 4 are fitted on the outside of the metal connecting section 2 to connect the metal connecting section 2 to the metal component.

[0045] The ceramic matrix composite connecting section 1 has two first surfaces and two second surfaces arranged opposite to each other. In this embodiment, the two first surfaces are two non-adjacent parallel surfaces. In other embodiments, the two first surfaces may also be two non-parallel surfaces. The first surfaces may be regularly shaped planes, irregularly shaped planes, or curved surfaces that match the ceramic matrix composite component 3. For example, the ceramic matrix composite component 3 consists of an upper plate, a lower plate, and a reinforcing rib connecting the upper plate and the lower plate. Figure 3 The diagram shows a partial structure of the ceramic matrix composite assembly, thus forming an installation space for the ceramic matrix composite connecting section 1 between the upper plate, the lower plate, and the reinforcing rib. The lower surface of the upper plate and the upper surface of the lower plate are the bearing surfaces 31, and the reinforcing rib is the fastening part 32.

[0046] The first surface is provided with inorganic fiber cloth for connection to the bearing surface 31 of the ceramic matrix composite component 3. The coefficient of thermal expansion of the inorganic fiber cloth is less than that of the ceramic matrix composite component 3, and the inorganic fiber cloth is a high-temperature resistant (operating environment temperature range of room temperature to 1600℃), low-modulus (modulus range of 0 to 80 GPa), strong thermal insulation, good thermal insulation, and high chemical stability fiber fabric. Since the coefficient of thermal expansion of the ceramic matrix composite connecting section 1 is much greater than that of the ceramic matrix composite component 3, when the aircraft is in a high-temperature environment, deformation can easily occur at the assembly joint due to thermal compatibility issues. The inorganic fiber cloth can act as a buffer between the ceramic matrix composite connecting section 1 and the ceramic matrix composite component 3, solving the thermal compatibility problem between the two. Quartz glass fiber cloth or basalt fiber fabric is preferably used for the inorganic fiber cloth.

[0047] The ceramic-based composite connecting section 1 has mounting pin holes 12 and deformation compensation grooves 11 penetrating the two second surfaces. The deformation compensation grooves 11 are used to buffer deformation stress when the ceramic-based composite connecting section 1 and the metal connecting section 2 deform under high temperature conditions. There are multiple mounting pin holes 12 and deformation compensation grooves 11, which are arranged sequentially at intervals along the extension direction of the ceramic-based composite connecting section 1. The center line of the arrangement of the mounting pin holes 12 and deformation compensation grooves 11 is the center line of the second surface.

[0048] The deformation compensation groove 11 is a dumbbell-shaped, slender through groove; the extending direction of the deformation compensation groove 11 is consistent with the arrangement direction of the deformation compensation groove 11; the groove width X of the deformation compensation groove 11 is:

[0049] X = a * L * ΔT

[0050] Where a is the coefficient of linear expansion of the ceramic-based composite connecting section 1 and the metal connecting section 2, L is the sum of the lengths of the ceramic-based composite connecting section 1 and the metal connecting section 2, and ΔT is the temperature difference of the operating environment.

[0051] Based on the calculated width of the deformation compensation groove 11, the length of each deformation compensation groove 11 that satisfies the buffering deformation stress is obtained through finite element simulation analysis; the lengths of each deformation compensation groove 11 can be the same or different; similarly, the radius of the arc at both ends of the dumbbell-shaped slender through groove is obtained by finite element simulation analysis.

[0052] The fastening part 32 of the ceramic matrix composite component 3 can be attached to the second surface and connected by a pin 15 that passes through the mounting pin hole 12; both ends of the pin 15 are fixed by cotter pins 13, and a washer 14 is provided between the cotter pin 13 and the fastening part 32 of the ceramic matrix composite component 3. The connection and fixation between the cotter pin 13, the washer 14 and the fastening part 32 of the ceramic matrix composite component 3 can be achieved by adjusting the thickness of the washer 14.

[0053] This embodiment provides a metal-ceramic matrix composite component, which includes a ceramic matrix composite component 3, a connecting component, and a metal component connected in sequence; the connecting component adopts the above-mentioned connecting component for metal-ceramic matrix composites.

Claims

1. A connection component for metal-ceramic matrix composites, characterized in that: It includes a ceramic matrix composite connecting section (1) and a metal connecting section (2) connected to the ceramic matrix composite connecting section (1); both the ceramic matrix composite connecting section (1) and the metal connecting section (2) are made of titanium alloy. The ceramic-based composite connecting section (1) is used to connect with the ceramic-based composite component (3), and the metal connecting section (2) is used to connect with the metal component; The ceramic-based composite connecting section (1) has two first surfaces and two second surfaces arranged opposite to each other; the first surface is provided with inorganic fiber cloth for connecting with the bearing surface (31) of the ceramic-based composite component (3); The ceramic matrix composite connecting section (1) has mounting pin holes (12) and deformation compensation grooves (11) penetrating the two second surfaces; the two second surfaces are used to attach to the fastening part (32) of the ceramic matrix composite assembly (3) and are connected by pins (15) penetrating the mounting pin holes (12).

2. The connection assembly for metal-ceramic matrix composites according to claim 1, characterized in that: The coefficient of thermal expansion of the inorganic fiber cloth material is less than that of the ceramic matrix composite component (3); The service temperature range of inorganic fiber cloth is from room temperature to 1600℃, and the modulus range is from 0 to 80 GPa.

3. The connection assembly for metal-ceramic matrix composites according to claim 2, characterized in that: The inorganic fiber cloth is quartz glass fiber cloth or basalt fiber fabric.

4. The connection assembly for metal-ceramic matrix composites according to claim 3, characterized in that: The number of mounting pin holes (12) and deformation compensation grooves (11) are both multiple, and they are arranged sequentially at intervals along the extension direction of the ceramic matrix composite connecting section (1); The center line of the arrangement of the mounting pin hole (12) and the deformation compensation groove (11) is the center line of the second surface.

5. The connection assembly for metal-ceramic matrix composites according to claim 4, characterized in that: The deformation compensation groove (11) is a dumbbell-shaped through groove; the extension direction of the deformation compensation groove (11) is consistent with the arrangement direction of the deformation compensation groove (11).

6. The connection assembly for metal-ceramic matrix composites according to any one of claims 1-5, characterized in that: The groove width X of the deformation compensation groove (11) is: X = a * L * ΔT Where a is the linear expansion coefficient of the ceramic-based composite connecting section (1) and the metal connecting section (2), L is the sum of the lengths of the ceramic-based composite connecting section (1) and the metal connecting section (2), and ΔT is the temperature difference of the operating environment.

7. The connection assembly for metal-ceramic matrix composites according to claim 6, characterized in that: The ceramic-based composite connecting section (1) and the metal connecting section (2) are provided with through holes along the axial direction for weight reduction. The two ends of the pin (15) are fixed by cotter pins (13), and a gasket (14) is provided between the cotter pin (13) and the fastening part (32) of the ceramic matrix composite component (3); The cotter pin (13) is made of GH3030, and the pin (15) and washer (14) are both made of GH4169.

8. The connection assembly for metal-ceramic matrix composites according to claim 7, characterized in that: The shape of the metal connecting segment (2) matches the shape of the metal component to be connected; A bushing and a flange (4) are fitted on the outside of the metal connecting section (2) to enable the metal connecting section (2) to connect with the metal components; The bushing and flange (4) are both made of titanium alloy.

9. A metal-ceramic matrix composite component, characterized in that: It includes a ceramic-based composite material component (3), a connecting component, and a metal component connected in sequence; The connecting component is the connecting component for metal-ceramic matrix composites as described in any one of claims 1-8.

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