Ceramic matrix composite high-conductivity blade cooling structure based on metal framework

Abstract

The invention provides a ceramic-based composite material high-conductivity blade cooling structure based on a metal framework, and belongs to the technical field of aero-engines, the ceramic-based composite material high-conductivity blade cooling structure comprises a ceramic-based composite material high-conductivity blade, the ceramic-based composite material high-conductivity blade comprises a blade body internally provided with a cavity, and the cavity is formed in the blade body; the blade body is provided with a surface air film hole and a trailing edge crack; the metal framework is arranged in a blade body cavity of the ceramic matrix composite blade and follows the shape of the blade body cavity, a partition rib is arranged in the metal framework and divides the interior of the metal framework into a front cavity and a rear cavity, impact holes are formed in the front cavity and the rear cavity, and the front cavity and the rear cavity are communicated with the partition rib. Impact cooling is carried out on a blade body of the ceramic matrix composite high-conductivity blade through the impact holes, and turbulent flow ribs are arranged on the outer side of the metal framework.

Description

Technical Field

[0001] The present application belongs to the field of aero engines or gas turbines, and in particular relates to a ceramic-based composite material high-guide vane cooling structure based on a metal skeleton. 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 temperature before the turbine of an aircraft engine has been continuously increased to achieve the goals of high efficiency, high thrust and low emissions. In order to achieve a higher temperature before the turbine, it is necessary to systematically improve the cooling structure, materials and coating technology.

[0003] At present, the temperature before the turbine of high thrust-to-weight ratio aircraft engines has reached 2200K, which has reached the temperature bearing limit of nickel-based high-temperature alloys and is difficult to improve. SiC ceramic-based composite materials (CMC for short) perfectly meet the needs of the next generation of aircraft engines with their excellent characteristics of light weight, high strength and high temperature resistance. However, the temperature bearing limit of CMC materials is around 1600K at this stage, and the 600K temperature difference with high-temperature combustion gas (i.e., the temperature before the turbine) needs to be controlled by a corresponding cooling solution. Limited by the intrinsic characteristics of CMC materials, there are still many limitations in its processing and manufacturing. It cannot be cooled in a complex way such as double-layer wall like traditional metal materials, and the number of air film holes on the surface of the blade should not be too many, which greatly reduces its air cooling effect. The cooling of existing CMC high-pressure turbine guide blades (referred to as high-guide blades) is mainly achieved through dense air film holes on the blade body. Small hole spacing will lead to a decrease in the mechanical properties of CMC materials, and the cooling effect is poor when only air film holes are used for cooling. Summary of the invention

[0004] The purpose of the present application is to provide a ceramic matrix composite high guide vane cooling structure based on a metal skeleton to solve or alleviate at least one problem in the background technology.

[0005] The technical solution of the present application is: a ceramic matrix composite material high guide vane cooling structure based on a metal skeleton, comprising:

[0006] A ceramic matrix composite material high guide vane, the ceramic matrix composite material high guide vane comprising a blade body with a cavity inside, the blade body being provided with surface air film holes and a trailing edge slit; and

[0007] A metal skeleton, wherein the metal skeleton is arranged inside the blade body cavity of the ceramic-based composite material blade and follows the shape of the blade body cavity, wherein the metal skeleton has partition ribs inside, and the partition ribs divide the interior of the metal skeleton into a front cavity and a rear cavity, and the front cavity and the rear cavity are provided with impact holes, and the blade body of the ceramic-based composite material high-conductivity blade is impact-cooled through the impact holes, and spoiler ribs are provided on the outside of the metal skeleton.

[0008] In an optional embodiment of the present application, radial ribs are provided on the outer side of the metal skeleton along the blade height direction.

[0009] In an optional embodiment of the present application, the skeleton radial ribs and the partition ribs are arranged in the same line.

[0010] In an optional embodiment of the present application, the blade body of the ceramic matrix composite material high guide vane is provided with blade body radial ribs extending along the blade height direction.

[0011] In an optional embodiment of the present application, spoiler ribs are designed on the blade body.

[0012] In an optional implementation manner of the present application, the spoiler ribs extend laterally and are convergently arranged.

[0013] In an optional embodiment of the present application, the ceramic-based composite material high-conductivity blade includes a blade upper edge plate and a blade lower edge plate, and the metal frame includes a skeleton upper edge plate and a skeleton lower edge plate, and the skeleton upper edge plate and the skeleton lower edge plate are adhered to the blade upper edge plate and the blade lower edge plate, and the skeleton upper edge plate and the skeleton lower edge plate are welded and fixed to the metal frame.

[0014] The CMC high guide blade cooling structure provided in the present application is based on the metal load-bearing ceramic-based composite guide blade. By matching the surface impact and turbulence structure of the metal skeleton with the structural form of the film cooling of the CMC blade body, the cooling efficiency is effectively improved and the amount of cold air is saved. By adopting a metal skeleton with divided cavities, the radial ribs between the metal skeleton and the CMC blade body cavity are combined to achieve reasonable distribution of cold air. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] 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.

[0016] Figure 1 This is a schematic diagram of the cooling structure of the ceramic-based composite material high-guide vane based on a metal skeleton in the present application.

[0017] Figure 2 This is a cross-sectional view of the cooling structure of the ceramic matrix composite high guide vane of the present application.

[0018] Figure 3Schematic diagram of the metal skeleton in this application.

[0019] Figure 4 Schematic diagram of the ceramic matrix composite high guide vane in this application.

[0020] Figure 5 This is a complete schematic diagram of the metal skeleton in this application.

[0021] Reference numerals:

[0022] 10-Ceramic matrix composite blades

[0023] 11-Leaf

[0024] 12- Blade upper edge plate

[0025] 13-Blade lower edge plate

[0026] 14-Surface air film holes

[0027] 15-Tail edge split

[0028] 16-Radial ribs on blade

[0029] 20-Metal frame

[0030] 21-Frame upper edge plate

[0031] 22-frame lower edge plate

[0032] 23- Rib

[0033] 24-Impact hole

[0034] 25-Spoiler Ribs

[0035] 26-Frame radial ribs DETAILED DESCRIPTION

[0036] 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.

[0037] Based on the configuration of ceramic-based composite guide vanes, the present application improves the existing cooling scheme in view of the high-temperature service conditions faced by high-guide vanes, thereby overcoming the problem that the temperature bearing capacity of existing ceramic-based composite high-guide vanes is far lower than the high-pressure turbine gas inlet temperature and cannot meet the use requirements.

[0038] like Figure 1 and Figure 2 As shown, the ceramic-based composite material high guide vane cooling structure based on a metal skeleton provided in the present application comprises: a ceramic-based composite material high guide vane 10 and a metal skeleton 20 .

[0039] The ceramic-based composite material high-conductivity blade 10 includes a blade body 11 and a blade upper edge plate 12 and a blade lower edge plate 13 located at both ends of the blade body 11. Similar to the traditional metal material high-conductivity blade, the ceramic-based composite material high-conductivity blade 10 of the present application is provided with air-cooling structures such as surface air film holes 14 and trailing edge slits 15. These air-cooling structures are still effective means to reduce the surface temperature of the ceramic-based composite material high-conductivity blade. In view of the high temperature-bearing characteristics of CMC, its cooling air volume requirement is smaller than that of metal blades. In order to improve the cooling efficiency, in the present application, "point-to-point" directional cooling is realized for different areas of the ceramic-based composite material high-conductivity blade. According to the surface temperature field distribution of the ceramic-based composite material high-conductivity blade, the distribution of the cooling gas is optimized in the form of a divided cavity.

[0040] To this end, in the present application, a conformal metal skeleton 20 is provided inside the blade body 11 of the ceramic matrix composite blade 10, that is, the metal skeleton 20 has the same shape as the cavity inside the blade body but is smaller in size than the cavity. The high designability of the metal skeleton 20 inside the blade body 11 is utilized to effectively cool the ceramic matrix composite blade, thereby improving the strength and cooling effect of the basin side or back side of the ceramic matrix composite blade.

[0041] like Figure 3 to Figure 4 As shown, the metal frame 20 of the present application has partition ribs 23 inside, and the partition ribs 23 divide the inner cavity of the metal frame 20 into two front and rear cavities, namely the front cavity and the rear cavity. Considering that the mutual penetration between the metal frame 20 and the blade body 11 is not conducive to the distribution of cold air, in the present application, the frame radial ribs 26 are arranged on the outer side of the metal frame 20 along the blade height direction, or the blade body radial ribs 16 are arranged in the inner cavity of the blade body 11 along the blade height direction, which cooperate with the partition ribs 23 in the inner cavity of the metal frame 20 to improve the structural strength and cooling effect.

[0042] In the preferred embodiment of the present application, when the skeleton radial ribs 26 are provided on the metal skeleton 20, the skeleton radial ribs 26 are provided in line with the partition ribs 23. The blade radial ribs 16 provided in the inner cavity of the blade 11 along the blade height direction can be provided on both the basin side and the back side of the inner cavity of the blade 11.

[0043] In the present application, the metal skeleton 20 may be designed with structures such as spoiler ribs 25 and impact holes 24, which cooperate with the air film holes on the ceramic-based composite material high guide vane 10 to form composite cooling to reduce the temperature of the blade surface and increase its service life.

[0044] like Figure 5 As shown, impact holes 24 are provided on the front cavity and the rear cavity of the metal skeleton 20. The impact holes 24 are distributed on the front and rear edges of the metal skeleton 20 and the back side of the basin. The impact holes 24 on the front and rear edges of the metal skeleton 20 are used to supply air to the high-temperature areas of the front and rear edges of the CMC blade body. The impact holes on the back side of the basin can be arranged according to the temperature field distribution of the blade body.

[0045] Furthermore, in the present application, transversely converging spoiler ribs 25 are designed on the metal frame 20 and / or the blade body 11, and the spoiler ribs 25 can be adjusted according to the cavity form to improve the structural strength and cooling effect.

[0046] In addition, the metal skeleton 20 in the present application also includes a skeleton upper edge plate 21 and a skeleton lower edge plate 22. The skeleton upper edge plate 21 and the skeleton lower edge plate 22 can form a whole with the metal skeleton 20 by welding. The skeleton upper edge plate 21 and the skeleton lower edge plate 22 are respectively attached to the blade upper edge plate 12 and the blade lower edge plate 13, thereby achieving the fixation of the metal skeleton 20.

[0047] The CMC high guide blade cooling structure provided in the present application is based on the metal load-bearing ceramic-based composite guide blade. By matching the surface impact and turbulence structure of the metal skeleton with the structural form of the film cooling of the CMC blade body, the cooling efficiency is effectively improved and the amount of cold air is saved. By adopting a metal skeleton with divided cavities, the radial ribs between the metal skeleton and the CMC blade body cavity are combined to achieve reasonable distribution of cold air.

[0048] 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 ceramic matrix composite high guide vane cooling structure based on a metal skeleton, characterized in that: include: A ceramic-based composite material high-conductivity blade, the ceramic-based composite material high-conductivity blade comprising a blade body with a cavity inside, the blade body being provided with surface air film holes and a trailing edge slit; and A metal skeleton, wherein the metal skeleton is arranged inside the blade body cavity of the ceramic-based composite material blade and follows the shape of the blade body cavity, wherein the metal skeleton has partition ribs inside, and the partition ribs divide the interior of the metal skeleton into a front cavity and a rear cavity, and the front cavity and the rear cavity are provided with impact holes, and the blade body of the ceramic-based composite material high-conductivity blade is impact-cooled through the impact holes, and spoiler ribs are provided on the outside of the metal skeleton.

2. The metal skeleton-based ceramic matrix composite high guide vane cooling structure according to claim 1, characterized in that: The outer side of the metal frame is provided with frame radial ribs along the blade height direction.

3. The metal skeleton-based ceramic matrix composite high guide vane cooling structure according to claim 2, characterized in that: The skeleton radial ribs and the partition ribs are arranged in the same line.

4. The metal skeleton-based ceramic matrix composite high guide vane cooling structure according to claim 1, characterized in that: The blade body of the ceramic-based composite material high guide vane is provided with blade body radial ribs extending along the blade height direction.

5. The metal skeleton-based ceramic matrix composite high guide vane cooling structure according to claim 1, characterized in that: The blade body is designed with spoiler ribs.

6. The ceramic matrix composite material high guide vane cooling structure based on a metal skeleton as claimed in claim 1 or 5, characterized in that: The spoiler ribs extend transversely and are arranged to converge.

7. The ceramic matrix composite material high guide vane cooling structure based on a metal skeleton as claimed in claim 1, characterized in that: The ceramic-based composite material high-conductivity blade includes a blade upper edge plate and a blade lower edge plate, and the metal frame includes a frame upper edge plate and a frame lower edge plate, the frame upper edge plate and the frame lower edge plate are attached to the blade upper edge plate and the blade lower edge plate, and the frame upper edge plate and the frame lower edge plate are welded and fixed to the metal frame.

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