High-bearing-capacity double-cavity ceramic matrix composite blade assembly

Abstract

The invention provides a high-bearing-capacity double-cavity ceramic matrix composite material blade assembly, and belongs to the technical field of aero-engines, the ceramic matrix composite material blade assembly comprises a ceramic matrix composite material blade, the ceramic matrix composite material blade comprises a blade body with a cavity, a blade upper edge plate and a blade lower edge plate, and the blade upper edge plate and the blade lower edge plate are located on the two sides of the blade body; a partition rib is arranged in the cavity of the blade body and divides the cavity into a front cavity and a rear cavity; the front cavity metal framework is integrally connected with a metal lower edge plate, the rear cavity metal framework is integrally connected with a metal upper edge plate, the metal lower edge plate and the metal upper edge plate are connected with an engine bearing structure, the front cavity metal framework is arranged in a front cavity of the blade body, and the rear cavity metal framework is arranged in a rear cavity of the blade body. The rear cavity metal framework is arranged in a rear cavity of the blade body, the front cavity metal framework is connected with the upper metal edge plate through a connecting piece, and the rear cavity metal framework is connected with the lower metal edge plate through a connecting piece.

Description

Technical Field

[0001] The present application belongs to the technical field of aero-engines or gas turbines, and in particular relates to a high-load-bearing double-cavity ceramic-based composite blade assembly. Background Art

[0002] As the "heart" of an aircraft, the service performance of an aircraft engine directly determines the flight performance of the aircraft and is an important indicator of national defense strength and high-end manufacturing capabilities. In recent years, with the development of the aviation industry, the inlet temperature of aircraft engines has been continuously increased to achieve the goals of high efficiency, high thrust and low emissions. In order to achieve higher inlet temperatures, it is necessary to systematically improve the cooling structure, materials and coating technology. At present, the temperature bearing capacity of nickel-based high-temperature alloys has reached its inherent limit and it is difficult to improve it further. SiC ceramic-based composites, with their excellent properties of light weight, high strength and high temperature resistance, perfectly meet the needs of aircraft engines. At present, SiC-CMC has been used in hot end components such as combustion chamber liners, tail nozzle sealing adjustment plates, etc.

[0003] The guide vanes serve in complex and changeable temperature and airflow field environments, covering high heat, high load and other working conditions, and the requirements for material performance are extremely stringent. As a ceramic-based composite material, although CMC materials have an operating temperature far exceeding that of high-temperature alloys, their mechanical properties are obviously insufficient compared to metal materials. Foreign research reports point out that for guide vane materials, they must meet the requirements of a cumulative service of 1000 hours under 100-170Mpa. The mechanical properties of CMC materials decrease rapidly with the increase of service temperature. The creep life of three-dimensional woven CMC in an atmospheric environment of 1482℃ / 100MPa is only 600h, which is far from meeting the use requirements; however, when the temperature remains unchanged and the stress level is reduced to 70MPa, the creep life of CMC can reach 1000h, meeting the use requirements.

[0004] In order to give full play to the advantages of CMC materials' high temperature resistance, and overcome the disadvantage of CMC's poor mechanical properties when pure ceramic-based composites (CMC) are used as blade materials in the existing technology, CMC can bear both temperature and force. In order to meet the development needs of the new generation of turbines, a blade that combines CMC's external heat-insulating blade body with a metal internal load-bearing skeleton is needed to effectively reduce the stress level of the CMC blade body, and realize the reasonable distribution of cold air based on the characteristics of high-conductivity blades. Summary of the invention

[0005] The purpose of the present application is to provide a high-load-bearing dual-cavity ceramic-based composite blade component to solve or alleviate at least one problem in the background technology.

[0006] The technical solution of the present application is: a high-load-bearing dual-cavity ceramic-based composite blade assembly, comprising:

[0007] A ceramic-based composite blade, the ceramic-based composite blade comprising a blade body having a cavity and a blade upper edge plate and a blade lower edge plate located on both sides of the blade body, the cavity of the blade body having partition ribs, the partition ribs dividing the cavity into a front cavity and a rear cavity;

[0008] A metal frame, the front cavity metal frame and the rear cavity metal frame, the front cavity metal frame is integrally connected with a metal lower edge plate, the rear cavity metal frame is integrally connected with a metal upper edge plate, the metal lower edge plate and the metal upper edge plate are connected to the engine bearing structure, the front cavity metal frame is arranged in the front cavity of the blade body, the rear cavity metal frame is arranged in the rear cavity of the blade body, and the front cavity metal frame is connected to the metal upper edge plate by a connecting piece, and the rear cavity metal frame is connected to the metal lower edge plate by a connecting piece.

[0009] In an optional embodiment of the present application, the blade body, blade upper edge plate, blade lower edge plate and partition ribs are integrally formed as a whole structure.

[0010] In an optional embodiment of the present application, the front cavity metal frame and the metal lower edge plate are formed into an integrated structure by welding or integral casting, and the rear cavity metal frame and the metal upper edge plate are formed into an integrated structure by welding or integral casting.

[0011] In an optional embodiment of the present application, metal gaskets are provided on the basin side and the leading edge of the metal skeleton near the metal upper edge plate and the metal lower edge plate to transfer the blade load of the ceramic-based composite blade to the metal skeleton.

[0012] In an optional embodiment of the present application, a front cavity connecting ear is provided at one end of the non-edge plate of the front cavity metal skeleton, a rear cavity connecting ear is provided at one end of the non-edge plate of the rear cavity metal skeleton, a positioning hole adapted to the outer shape of the rear cavity metal skeleton is provided on the metal lower edge plate, and a lower edge plate mounting seat is provided at the position of the positioning hole, a positioning hole adapted to the outer shape of the front cavity metal skeleton is provided on the metal upper edge plate, and an upper edge plate mounting seat is provided at the position of the positioning hole, the front cavity connecting ear is inserted into the positioning hole of the metal upper edge plate and fixedly connected to the upper edge plate mounting seat by a connecting piece, and the rear cavity connecting ear is inserted into the positioning hole of the metal lower edge plate and fixedly connected to the lower edge plate mounting seat by a connecting piece.

[0013] In an optional embodiment of the present application, the blade upper edge plate and the blade lower edge plate of the ceramic-based composite material blade are provided with axial and circumferential edge plate grooves, and the metal upper edge plate and the metal lower edge plate in the metal skeleton are provided with edge plate protrusions adapted to the edge plate grooves, for achieving the limiting of the ceramic-based composite material blade and the metal skeleton.

[0014] In an optional embodiment of the present application, the metal skeleton is provided with impact holes for cooling the ceramic-based composite material blades.

[0015] The dual-cavity ceramic-based composite material blade assembly provided in the present application is supported by a metal skeleton, while the ceramic-based composite material blade is used to bear the temperature, thereby effectively distinguishing the temperature-bearing and load-bearing functions of the blade, and the temperature-bearing and load-bearing are undertaken by components of different materials, giving full play to the advantages of each material, improving the strength reserve of the ceramic-based composite material blade, improving the safety of blade use, and ultimately increasing the service life of the ceramic-based composite material blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0017] Figure 1 This is a schematic diagram of the dual-cavity ceramic-based composite blade assembly of the present application.

[0018] Figure 2 This is a schematic cross-sectional view of the ceramic-based composite blade of the present application.

[0019] Figure 3 This is a schematic diagram of the metal skeleton of this application.

[0020] Figure 4 This is a schematic diagram of the decomposed state of the metal skeleton of the present application.

[0021] Figure 5 This is a schematic diagram of the assembly of the metal frame and ceramic-based composite blade of the present application.

[0022] Reference numerals:

[0023] 10-Ceramic matrix composite blades

[0024] 11-Leaf

[0025] 12- Blade upper edge plate

[0026] 13-Blade lower edge plate

[0027] 14- Rib

[0028] 15-Edge plate groove

[0029] 20-Metal frame

[0030] 21-Front cavity metal frame

[0031] 22-Metal lower edge plate

[0032] 23-Back cavity metal frame

[0033] 24-Metal upper edge plate

[0034] 25-Metal gasket DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0036] In order to solve the problem of poor mechanical properties of ceramic-based composite blades, the present application proposes a structure that supports and bears weight through a metal skeleton inside the ceramic-based composite blade. The supporting and weight-bearing structure has a two-cavity configuration. On the basis of improving the weight-bearing level, it can achieve effective distribution of cold air and effectively support the ceramic-based blades.

[0037] like Figure 1 As shown, the high-load-bearing dual-cavity ceramic-based composite material blade assembly provided by the present application includes: a ceramic-based composite material high-guide vane 10 and a metal skeleton 20.

[0038] The ceramic-based composite high-conductivity blade 10 includes a blade body 11 having a cavity and a blade upper edge plate 12 and a blade lower edge plate 13 located at the upper and lower ends of the blade body 11. The blade body 11 and the blade upper edge plate 12 and the blade lower edge plate 13 form a ceramic-based composite blade body-edge plate integral structure. Figure 2 As shown, a partition rib 14 is provided in the cavity of the blade body 11, and the partition rib 14 divides the cavity into two front and rear cavities. The partition rib 14 can be integrally formed with the ceramic-based composite blade body-edge plate integral structure.

[0039] The metal frame 20 includes a front cavity metal frame 21 and a rear cavity metal frame 23. The lower side of the front cavity metal frame 21 is integrally connected with a metal lower edge plate 22, and the upper side of the rear cavity metal frame 23 is integrally connected with a metal upper edge plate 24. The metal lower edge plate 22 and the metal upper edge plate 24 are connected to a bearing structure such as an engine casing. It can be understood that the lower side of the front cavity metal frame 21 can also be integrally connected with the metal upper edge plate 24, and the upper side of the rear cavity metal frame 23 can be integrally connected with the metal lower edge plate 22. The front cavity metal frame 21 is arranged in the front cavity of the blade 11, and the rear cavity metal frame 23 is arranged in the rear cavity of the blade 11, and the front cavity metal frame 21 is connected to the metal upper edge plate 24 through a connector, and the rear cavity metal frame 23 is connected to the metal lower edge plate 22 through a connector. The ceramic-based composite blade 10 completely covers the metal upper and lower edge plates and the metal frame to form a heat insulation sleeve, which greatly increases the temperature bearing capacity of the ceramic-based composite blade.

[0040] In some embodiments of the present application, the front cavity metal frame 21 and the metal lower edge plate 22 can be formed into an integrated structure by welding or integral casting, and the rear cavity metal frame 23 and the metal upper edge plate 24 can be formed into an integrated structure by welding or integral casting.

[0041] like Figure 3 As shown, in the present application, metal gaskets 25 are provided on the basin side and the leading edge of the metal skeleton 20 near the upper and lower edge plates, which can effectively transfer the blade load of the ceramic-based composite blade 10 to the metal component, thereby achieving the purpose of the metal skeleton 20 bearing the load.

[0042] like Figure 4 As shown, a front cavity connecting ear piece 211 is provided at the upper end of the front cavity metal skeleton 21, and a rear cavity connecting ear piece 231 is provided at the lower end of the rear cavity metal skeleton 23. Correspondingly, a positioning hole adapted to the lower end shape of the rear cavity metal skeleton 23 is provided on the metal lower edge plate 22, and a lower edge plate mounting seat 221 is provided at the position of the positioning hole. A positioning hole adapted to the upper end shape of the front cavity metal skeleton 21 is provided on the metal upper edge plate 24, and an upper edge plate mounting seat 241 is provided at the position of the positioning hole. The upper end front cavity connecting ear piece 211 of the front cavity metal skeleton 21 is inserted into the positioning hole of the metal upper edge plate 24 and is fixedly connected to the upper edge plate mounting seat 241 through a connecting piece. The lower end rear cavity connecting ear piece 231 of the rear cavity metal skeleton 23 is inserted into the positioning hole of the metal lower edge plate 22 and is fixedly connected to the lower edge plate mounting seat 221 through a connecting piece. The ceramic-based composite material blade relies on the metal skeleton and its upper and lower edge plates to achieve limited fixation, thereby effectively limiting the radial movement of the blade body of the ceramic-based composite material blade.

[0043] In the preferred embodiment of the present application, the upper and lower edge plates of the ceramic matrix composite blade 10 are provided with axial and circumferential edge plate grooves 15, and the metal upper edge plate 24 and the metal lower edge plate 22 are provided with matching edge plate protrusions, so as to achieve the limitation of the ceramic matrix composite blade 10 and the metal frame 20. Figure 5 In the illustrated embodiment of the matching structure of the blade upper edge plate 12 and the metal upper edge plate 24, an edge plate groove 15 is provided on the blade upper edge plate 12, and correspondingly, an edge plate protrusion 242 is provided on the lower side of the metal upper edge plate 24, and the two cooperate to achieve the limiting of the blade upper edge plate 12 and the metal upper edge plate 24.

[0044] It can be understood that the embodiment in the present application in which the front cavity metal frame 21 and the metal lower edge plate 22 are fixed into a whole by welding, and the rear cavity metal frame 23 and the metal upper edge plate 24 are fixed into a whole are only used for example. In some other embodiments of the present application, the front cavity metal frame 21 can also be fixed into a whole with the metal upper edge plate 24 by welding, and the rear cavity metal frame 23 and the metal lower edge plate 22 are fixed into a whole by welding, and other corresponding structures are adaptively adjusted.

[0045] The double-cavity ceramic-based composite blade assembly provided in the present application is supported by a metal skeleton, while the ceramic-based composite blade is used to bear temperature, thereby effectively distinguishing the heat-bearing and force-bearing functions of the blade, and the heat-bearing and load-bearing are undertaken by components of different materials, giving full play to the advantages of each material, improving the strength reserve of the ceramic-based composite blade, improving the safety of blade use, and ultimately improving the service life of the ceramic-based composite blade. The ceramic-based composite blade of the present application adopts a double-cavity structure to match the metal skeleton, which can effectively enhance the CMC blade body and achieve axial and circumferential fixation. By setting impact holes and spoiler ribs on the metal skeleton, the cooling gas distribution can be optimized to a certain extent. Finally, the metal upper and lower edge plate assembly in the present application still adopts the existing metal material structure, which can be effectively assembled with the casing and other structures, and can basically achieve in-situ replacement, with greater designability and guarantee of accurate assembly and positioning of high-guide vanes.

[0046] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A high-load-bearing dual-cavity ceramic-based composite blade assembly, characterized in that: include: A ceramic-based composite blade, the ceramic-based composite blade comprising a blade body having a cavity and a blade upper edge plate and a blade lower edge plate located on both sides of the blade body, the cavity of the blade body having partition ribs, the partition ribs dividing the cavity into a front cavity and a rear cavity; A metal frame, the front cavity metal frame and the rear cavity metal frame, the front cavity metal frame is integrally connected with a metal lower edge plate, the rear cavity metal frame is integrally connected with a metal upper edge plate, the metal lower edge plate and the metal upper edge plate are connected to the engine bearing structure, the front cavity metal frame is arranged in the front cavity of the blade body, the rear cavity metal frame is arranged in the rear cavity of the blade body, and the front cavity metal frame is connected to the metal upper edge plate by a connecting piece, and the rear cavity metal frame is connected to the metal lower edge plate by a connecting piece.

2. The high-load-bearing dual-cavity ceramic-based composite blade assembly according to claim 1, characterized in that: The blade body, the blade upper edge plate, the blade lower edge plate and the partition ribs are an integral structure.

3. The high-load-bearing dual-cavity ceramic-based composite blade assembly according to claim 1, characterized in that: The front cavity metal frame and the metal lower edge plate are welded or integrally cast to form an integrated overall structure, and the rear cavity metal frame and the metal upper edge plate are welded or integrally cast to form an integrated overall structure.

4. The high-load-bearing dual-cavity ceramic-based composite blade assembly according to claim 1, characterized in that: Metal gaskets are provided on the basin side and the leading edge of the metal frame near the metal upper edge plate and the metal lower edge plate to transfer the blade body load of the ceramic-based composite material blade to the metal frame.

5. The high-load-bearing dual-cavity ceramic-based composite blade assembly according to claim 1, characterized in that: A front cavity connecting ear is provided at one end of the non-edge plate of the front cavity metal skeleton, and a rear cavity connecting ear is provided at one end of the non-edge plate of the rear cavity metal skeleton. A positioning hole adapted to the outer shape of the rear cavity metal skeleton is provided on the metal lower edge plate, and a lower edge plate mounting seat is provided at the position of the positioning hole. A positioning hole adapted to the outer shape of the front cavity metal skeleton is provided on the metal upper edge plate, and an upper edge plate mounting seat is provided at the position of the positioning hole. The front cavity connecting ear is inserted into the positioning hole of the metal upper edge plate and fixedly connected to the upper edge plate mounting seat by a connecting piece. The rear cavity connecting ear is inserted into the positioning hole of the metal lower edge plate and fixedly connected to the lower edge plate mounting seat by a connecting piece.

6. The high-load-bearing dual-cavity ceramic-based composite blade assembly according to claim 1, characterized in that: The blade upper edge plate and blade lower edge plate of the ceramic-based composite material blade are provided with axial and circumferential edge plate grooves, and the metal upper edge plate and metal lower edge plate in the metal frame are provided with edge plate protrusions adapted to the edge plate grooves, so as to realize the limiting of the ceramic-based composite material blade and the metal frame.

7. The high-load-bearing dual-cavity ceramic-based composite blade assembly according to claim 1, characterized in that: The metal skeleton is provided with impact holes for cooling the ceramic-based composite material blades.

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