Aviation turbine blade with micro-structure reinforced surface

Abstract

The utility model provides an aviation turbine blade with a micro-structure reinforced surface, and relates to the technical field of turbine blades. Fixing grooves are evenly formed in the side wall of an inner cavity of the fixing shell. Threaded grooves are evenly formed in the edge of the left side wall of the fixed shell. The surface of the turbine blade is subjected to laser cladding, spraying and other methods, a metal coating with excellent performance is formed on the surface of the blade, the metal coating can be ceramic or metal or a composite material, the abrasion resistance and the oxidation resistance of the turbine blade can be effectively improved, the microstructure of the turbine blade is changed, and a nanocrystalline structure is formed. The structure can obviously improve the strength and toughness of the material, and solves the problem that the turbine blade is often contacted with high-temperature airflow during operation, so that the surface of the blade needs to be subjected to microstructure strengthening, otherwise, the blade cannot bear the high-temperature airflow and is easy to damage.

Description

TECHNICAL FIELD

[0001] The utility model relates to turbine blade technical field especially microstructure reinforced surface aviation turbine blade. BACKGROUND

[0002] Traditional turbine blade materials are mostly nickel-based alloys and cobalt-based alloys. These materials have excellent high-temperature performance and oxidation resistance, but still face problems such as thermal fatigue, oxidation corrosion, and thermal stress under extreme working conditions. In recent years, microstructure reinforcement technology has gradually become a hot spot in the research of aviation materials. Microstructure reinforcement is achieved by introducing micron or nanometer structures on the surface of the material to improve the strength, hardness, and wear resistance of the material. This technology not only effectively improves the service life of the turbine blade, but also improves its performance in high-temperature and high-pressure environments. Through microstructure reinforcement, the fatigue resistance and oxidation resistance of the turbine blade can be significantly improved without increasing the weight of the material, thereby meeting the high-performance requirements of modern aviation engines for turbine blades.

[0003] During use, the turbine blade is often in contact with high-temperature gas flow, so it needs to be microstructure reinforced on the blade surface. Otherwise, the blade may be damaged under load. In addition, the turbine blade needs to be fixed and installed separately. If it cannot be disassembled and replaced together, it will cause greater economic loss. SUMMARY

[0004] The disclosed microstructure reinforced surface aviation turbine blade has an outer end of the anti-falling disc rotationally installed in the anti-falling groove, and a stabilizing ring rotationally installed in the rotating groove. During turbine rotation, both ends are limited, so that the turbine does not deviate when it rotates quickly. The turbine blade surface is treated by laser cladding, spraying, or other methods to form a layer of metal coating with excellent performance on the blade surface. These metal coatings can be ceramic, metal, or composite materials, which can effectively improve the wear resistance and oxidation resistance of the turbine blade, change the microstructure of the turbine blade, and form a nanocrystalline structure. This structure can significantly improve the strength and toughness of the material.

[0005] In a first aspect, the disclosed microstructure reinforced surface aviation turbine blade includes a fixed housing, a fixed groove uniformly formed on the side wall of the inner cavity of the fixed housing, a threaded groove uniformly formed on the edge of the left side wall of the fixed housing, a bearing frame fixedly installed at the fixed groove of the fixed housing, a fixed hole penetrating the middle of the bearing frame, a gas compressor fixedly installed in the fixed hole of the bearing frame, and a blade fixedly installed on the rotating shaft of the gas compressor.

[0006] The left end side wall of the blade is sprayed with a metal coating, a close-limiting disc is installed at the left end of the metal coating, an air inlet cone is fixedly installed at the left end of the limiting disc, limiting notches are uniformly arranged at the outer end of the right end side wall of the blade, a guide groove is arranged at the inner side wall of each of the six limiting notches, and a positioning block is slidably installed in the guide groove, and a guide strip is fixedly installed at the side wall of each of the six positioning blocks;

[0007] The inner cavity of the fixed shell is fixedly installed with an anti-falling disc, an annular stable groove is arranged at the side wall of the anti-falling disc, a circle of bolts are rotatably installed in the stable groove, a turbine is installed at the stable groove, a stabilizing ring is fixedly installed at the left side wall of the turbine, and a positioning groove is uniformly arranged at the inner side wall of the right end of the turbine.

[0008] In at least some embodiments, a connecting disc is fixedly installed at the right end of the fixed shell, a circle of threaded holes are arranged in the connecting disc, an anti-falling groove is arranged at the side wall of the inner cavity of the fixed shell, and a fixed disc is installed at the port portion of the left end of the fixed shell.

[0009] In at least some embodiments, a protective net is fixedly installed at the middle portion of the fixed disc, and an annular rotating groove is arranged at the side wall of the right end of the fixed disc.

[0010] The microstructure reinforced surface aviation turbine blade has the following beneficial effects:

[0011] In the utility model, when the turbine blade is used, the blade surface is treated by melting by using laser technology, and a special microstructure is formed on the turbine blade surface by using advanced microprocessing technology, so that the blade surface hardness, wear resistance, fatigue strength and thermal stability are improved.

[0012] The outer end of the anti-falling disc is rotatably installed in the anti-falling groove, and the stabilizing ring is rotatably installed in the rotating groove, so that both ends are limited during the rotation of the turbine, and the turbine does not deviate when rotating quickly, and the turbine blade surface is treated by laser cladding, spraying and other methods to form a layer of metal coating with excellent performance on the blade surface, which can be ceramic, metal or composite material, so that the wear resistance and oxidation resistance of the turbine blade are effectively improved, the microstructure of the turbine blade is changed, and a nanocrystalline structure is formed. This structure can significantly improve the strength and toughness of the material. BRIEF DESCRIPTION OF DRAWINGS

[0013] In order to more clearly illustrate the technical scheme of the embodiments of the utility model, the drawings of the embodiments will be briefly introduced below.

[0014] The drawings described below only relate to some embodiments of the utility model, and are not limited to the utility model.

[0015] In the drawings:

[0016] Figure 1 The left front upper axial structure schematic diagram of the present application is shown;

[0017] Figure 2 The bearing frame part structure schematic diagram of the present application is shown;

[0018] Figure 3 The blade part disassembled structure schematic diagram of the present application is shown;

[0019] Figure 4 The explosion structure schematic diagram of the present application is shown.

[0020] List of reference signs

[0021] 1, fixed shell; 101, connecting disc; 102, anti-off groove; 103, fixed disc; 104, protective net; 105, rotating groove; 2, bearing frame; 201, compressor; 202, inlet cone; 203, blade; 204, metal coating; 205, limiting disc; 206, limiting notch; 207, guide groove; 208, positioning block; 209, guide bar; 3, anti-off disc; 301, stable groove; 302, turbine; 303, stabilizing ring; 304, positioning groove. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical scheme and advantages of the embodiments of the present application more clear, the technical scheme of the embodiments of the present application will be described clearly and completely below in combination with the drawings of the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the described embodiments of the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0023] Embodiment one: please refer to Figures 1 to 4 :

[0024] The utility model provides a microstructure reinforced surface aviation turbine blade, include: fixed housing 1, the even opening of fixed groove of the side wall of fixed housing 1 inner chamber, the even opening of threaded groove of the edge of fixed housing 1 left side wall, the fixed groove of fixed housing 1 is fixedly installed with bearing frame 2, and the middle part of bearing frame 2 is equipped with the fixed hole of penetration, the inner chamber fixed installation of fixed housing 1 is equipped with anti -drop disc 3, and the side wall of anti -drop disc 3 is equipped with annular steady groove 301, a circle of bolt is rotatably installed on steady groove 301, and turbine 302 is installed at steady groove 301, the bolt on steady groove 301 is rotatably inserted on turbine 302, and turbine 302 is fixedly installed at steady groove 301, so turbine 302 will not fall when rotating, and turbine 302 is fixedly installed on the left side wall of steady ring 303, and steady ring 303 is rotatably installed in rotary groove 105, when turbine 302 rotates, will not deviate, turbine 302 can stably and rapidly rotate, and the inner side wall of the right end of turbine 302 is evenly equipped with positioning groove 304.

[0025] Among them, the right end of fixed housing 1 is fixedly installed with connecting disc 101, and a circle of threaded hole is formed in connecting disc 101, and connecting disc 101 and fixed housing 1 are fixedly installed on the aeroengine by the threaded hole on connecting disc 101, the anti -drop groove 102 is formed in the side wall of the inner chamber of fixed housing 1, the outer end of anti -drop disc 3 is rotatably installed in anti -drop groove 102, when turbine 302 rotates, will not deviate, turbine 302 can stably rotate, fixed disc 103 is installed on the left end port of fixed housing 1, the edge of fixed disc 103 is rotatably inserted with the bolt of penetration, the bolt on fixed disc 103 is rotatably inserted in the threaded groove of the left side wall of fixed housing 1, and fixed disc 103 is fixedly installed on fixed housing 1, so fixed disc 103 will not fall from fixed housing 1, the middle part of fixed disc 103 is fixedly installed with protective net 104, and annular rotary groove 105 is formed in the right end side wall of fixed disc 103.

[0026] The fixed hole of the bearing frame 2 is fixedly installed with a compressor 201, and the rotating shaft of the compressor 201 is fixedly installed with a blade 203. The left end side wall of the blade 203 is sprayed with a metal coating 204. Starting the blade 203 and the metal coating 204 on the rotating shaft of the compressor 201 will rotate, and the connected turbine 302 will also rotate. The left end of the metal coating 204 is installed with a close limiting disc 205. The left end of the limiting disc 205 is fixedly installed with an air inlet cone 202. The design of the air inlet cone 202 aims to optimize the entering mode of the airflow, reduce the vortex and turbulence of the airflow when entering the engine or other equipment, and thus improve the stability and efficiency of the airflow. The outer end of the right end side wall of the blade 203 is uniformly provided with a limiting slot 206. The inner side wall of the six limiting slots 206 is respectively provided with a guide groove 207, and the guide groove 207 is slidably installed with a positioning block 208. The positioning block 208 is rotatably inserted with two penetrating bolts. The positioning block 208 is slidably inserted into the positioning groove 304, and then the bolts on the positioning block 208 are rotatably inserted into the limiting slot 206 to fix and limit the positioning block 208. In this way, the positioning block 208 cannot move on the limiting slot 206, so as to temporarily fix and install the blade 203 on the turbine 302. In this way, when the blade 203 and the turbine 302 and other parts are damaged, they can be conveniently disassembled and replaced. The side wall of the six positioning blocks 208 is respectively fixedly installed with a guide strip 209, which is slidably installed in the guide groove 207. When the positioning block 208 slides, the guide strip 209 is limited by the guide groove 207, and the positioning block 208 cannot deviate when it slides, preventing the positioning block 208 from deviating during the sliding process and being stably inserted into the positioning groove 304.

[0027] In example two, on the basis of example one, as shown in Figure 1 and Figure 4 A circle of bolts is rotatably installed on the stable groove 301. The turbine 302 is installed at the stable groove 301. The stable groove 301 and the bolts are deleted, and then the turbine 302 is fixedly welded on the side wall of the anti-off disc 3. In this way, when the turbine 302 rotates or is touched, it will not move, avoiding the loosening of the bolts during long-term use, and also saving the cost of parts.

[0028] The working principle of the embodiment is as follows: when in use, the positioning block 208 is slidably inserted into the positioning groove 304, and then the bolt on the positioning block 208 is rotatably inserted into the limiting slot 206 to fix and limit the positioning block 208, so that the positioning block 208 cannot move on the limiting slot 206, thereby temporarily fixing and installing the blade 203 on the turbine 302, so that the blade 203 and the turbine 302 and other parts can be conveniently disassembled and replaced when damaged, the blade 203 and the metal coating 204 on the rotating shaft of the compressor 201 are rotated, and the connected turbine 302 also rotates, the outer end of the anti-falling disc 3 is rotatably installed in the anti-falling groove 102, and the turbine 302 cannot deviate when rotating, and the stabilizing ring 303 is rotatably installed in the rotating groove 105, and the turbine 302 cannot deviate when rotating, so that the turbine 302 can stably and quickly rotate.

[0029] In this document, the following points need to be noted:

[0030] 1. The drawings of the embodiments of the present disclosure only relate to the structures involved in the embodiments of the present disclosure, and other structures can refer to the general design.

[0031] 2. In the case of no conflict, the embodiments of the present disclosure and the features in the embodiments can be combined with each other to obtain new embodiments.

[0032] The above is only a specific implementation of the present disclosure, but the protection scope of the present disclosure is not limited to this, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present disclosure, which should be covered within the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be subject to the protection scope of the claims.

Claims

1. A microstructure- strengthened surface aero turbine blade comprising: The utility model provides a fixed shell (1), the even fixed groove of the side wall of the inner chamber of fixed shell (1), the even screw groove of the edge of left side wall of fixed shell (1) is set up, the fixed groove of fixed shell (1) is fixedly installed with the bearing frame (2) of fixed shell (1), and the fixed hole of bearing frame (2) middle part is set up and penetrates, its characterized in that, the fixed hole of bearing frame (2) is fixedly installed with compressor (201), and the rotating shaft of compressor (201) is fixedly installed with blade (203), the left end side wall of blade (203) is sprayed with metal coating (204), the left end of metal coating (204) is installed with the abutting limiting disc (205), the left end of limiting disc (205) is fixedly installed with the air intake cone (202), the outer end of the right end side wall of blade (203) is evenly set up with the restriction slot mouth (206), the inner side wall of six restriction slot mouth (206) is set up with guide groove (207) respectively, and guide groove (207) is slidably installed with the locating block (208), and the side wall of six locating block (208) is fixedly installed with guide strip (209) respectively, the inner chamber of fixed shell (1) is fixedly installed with the anti -drop disc (3), and the side wall of anti -drop disc (3) is set up with annular firm groove (301), the firm groove (301) is rotatably installed with a circle bolt, the firm groove (301) is installed with turbine (302), the left side wall of turbine (302) is fixedly installed with stabilizing ring (303), the inner side wall of the right end of turbine (302) is evenly set up with positioning groove (304).

2. The microstructure- strengthened surface aero turbine vane of claim 1, wherein: The right end of fixed shell (1) is fixedly installed with connecting disc (101), and a circle threaded hole is set up on connecting disc (101), the inner chamber side wall of fixed shell (1) is set up with anti -drop groove (102), and the left end port part of fixed shell (1) is installed with fixed disc (103).

3. The micro-textured surface air turbine blade of claim 2, wherein: The middle part of fixed disc (103) is fixedly installed with protective net (104), and the right end side wall of fixed disc (103) is set up with annular rotary groove (105). The middle part of fixed disc (103) is fixedly installed with protective net (104), and the right end side wall of fixed disc (103) is set up with annular rotary groove (105).

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