Working blade of turbine and turbine

Abstract

The invention relates to the technical field of engines, and discloses a turbine working blade and a turbine. The turbine working blade is characterized in that a tenon and a blade body are integrally formed and manufactured by adopting a ceramic matrix composite material; the blade basin side edge plate is composed of a first runner plate and a first attaching plate. The first runner plate is attached to the blade body; the first attaching plate is attached to the tenon; the blade back side edge plate is composed of a second runner plate and a second attaching plate. The second runner plate is attached to the blade body; the second attaching plate is attached to the tenon; the blade basin side edge plate and the blade back side edge plate are made of high-temperature alloy. By arranging the blade body and the tenon which are made of the ceramic matrix composite material and the blade basin side edge plate and the blade back side edge plate which are made of the high-temperature alloy material, the problem that the strength is reduced due to the fact that the edge plates are machined in a fiber bending mode is avoided. The continuity of fibers in the turbine working blade is remarkably improved, the machining workload is reduced, and the bearing capacity and reliability of the turbine working blade are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of engines, and in particular to a turbine working blade and a turbine. Background Art

[0002] Ceramic-based composites (CMCs), due to their high-temperature resistance and low density, hold great promise for the manufacture of high-temperature components in aircraft engines. CMCs are particularly useful in the manufacture of high-temperature rotating components in aircraft engines, such as turbine blades. Because the fiber arrangement of CMC components decisively influences the performance of the final component, when using continuous fiber-reinforced and toughened CMCs to manufacture turbine blades subject to high loads, it is crucial to minimize bending of the ceramic fibers to ensure the mechanical properties of the CMCs.

[0003] Existing turbine blades made of ceramic-based composite materials are usually an integrated structure of a blade body, a lip plate, and a tenon. Since the lip plate is a horizontally protruding cantilever structure relative to the blade body and the tenon, the ceramic fiber must be bent nearly 90 degrees from the blade body or the tenon to extend out of the lip plate. However, the use of the above-mentioned ceramic fiber bending method to make the lip plate not only makes the quality dispersion of the lip plate structure large, causes damage to the ceramic fiber itself, and has poor mechanical properties, significantly reduces the strength of the connection between the lip plate and the blade body and the tenon, and significantly increases the difficulty of making the turbine blade, but also requires a large amount of mechanical processing and shaping operations on the lip plate, which significantly increases the production cost; at the same time, it causes the load-bearing capacity of the turbine blade to be low, making it difficult to use in aircraft engines. Summary of the Invention

[0004] In view of this, the present invention provides an improved turbine working blade to solve the problem that when the existing turbine working blades made of ceramic-based composite materials adopt the ceramic fiber bending method to make the edge plate, not only the quality dispersion of the edge plate structure molding is large, the ceramic fiber itself is damaged, the mechanical properties are poor, the strength of the edge plate at the connection position with the blade body and the tenon is significantly reduced, and the difficulty of manufacturing the turbine working blade is significantly increased, but also a large number of mechanical processing and shaping operations are required on the edge plate, which significantly increases the manufacturing cost; at the same time, it causes the problem that the load-bearing capacity of the turbine working blade is low and it is difficult to use in aircraft engines.

[0005] In a first aspect, the present invention provides a turbine blade, comprising:

[0006] leaf body;

[0007] The tenon and the blade body are integrally formed using ceramic-based composite materials;

[0008] The blade basin side edge plate is located on the blade basin side of the blade body, and the blade basin side edge plate is composed of a first flow channel plate and a first bonding plate that are connected and arranged; the inner side of the first flow channel plate is bonded to the root of the blade body; and the first bonding plate is bonded to the outer contour of the tenon;

[0009] The blade back side edge plate is located on the back side of the blade body, and is composed of a second flow channel plate and a second bonding plate connected to each other; the inner side of the second flow channel plate is bonded to the root of the blade body; the second bonding plate is bonded to the outer contour of the tenon; the blade basin side edge plate and the blade back side edge plate are respectively made of high-temperature alloy material in one piece;

[0010] The turbine blade is suitable for being fitted with the blade basin side edge plate, blade back side edge plate, blade body, and tenon in a bonded state, with the first bonding plate and the second bonding plate both embedded and installed in the tenon groove of the turbine disk. Beneficial Effects: This application adopts the above-mentioned technical solution, and by providing a blade body and tenon made of ceramic-based composite materials and a blade basin side edge plate and blade back side edge plate made of high-temperature alloy materials, it avoids the strength reduction problem caused by traditional ceramic-based composite turbine blades that are processed using fiber-bent edge plates or edge plates connected by bonding and pinning. The integrally formed blade body and tenon allow the blade body fibers to extend more continuously to the tenon, thereby reducing the difficulty of manufacturing the blade body and tenon. At the same time, the continuous fibers can improve the tenon's ability to bear the centrifugal load of the blade body. In other words, the technical solution of this application can significantly improve the continuity of the fibers within the turbine blade, reduce machining workload, increase the load-bearing capacity and reliability of the turbine blade, and facilitate its application in aircraft engines.

[0011] Optionally, the cross section of the tenon is dovetail-shaped. Beneficial effect: The present application adopts the above technical solution to reduce the difficulty of manufacturing the tenon.

[0012] Optionally, a smooth transition is adopted between the blade body and the tenon.

[0013] Optionally, the first bonding plate is composed of a first extended root, a first tenon and a first tooth bottom connected in sequence; the first extended root is connected to the first flow channel plate;

[0014] The second bonding plate is composed of a second extended root, a second tenon tooth and a second tooth bottom that are connected in sequence; the second extended root is connected to the second flow channel plate.

[0015] Optionally, the first flow channel plate and the second flow channel plate are connected to each other at their extended portions beyond the blade; and the first bonding plate and the second bonding plate are connected to each other at their outer end surfaces. Beneficial Effect: This application adopts the above technical solution to reduce gaps on the flow channel surface and reduce gas leakage.

[0016] Advantageous Effects: The above technical solution adopted in this application can reduce the workload of installing and removing turbine blades on the turbine disc in the later stage, reduce the gaps on the flow path surface, and reduce gas leakage.

[0017] Optionally, the first and second flow channel plates may have a gas flow channel profile along the axial direction on the surface facing the blade tip; the axial direction being the direction of the rotation axis of the turbine blades in the rotating working state. Beneficial Effect: This application utilizes the above technical solution to ensure the dimensional requirements of the flow channel during subsequent turbine assembly.

[0018] Optionally, the sum of the circumferential dimensions of the blade basin side edge plate and the blade back side edge plate is L, where L is the dimension of a circumferential pitch between adjacent turbine blades mounted on the turbine disk; the circumferential direction is the rotational direction of the turbine blades in a rotating operating state. Advantageous Effects: This application utilizes the above-described technical solution, and during subsequent turbine assembly, the blade back side edge plates and blade basin side edge plates of adjacent turbine blades fit tightly together to form a continuous flow path surface.

[0019] Optionally, the thickness of the first flow channel plate and the second flow channel plate ranges from 1 mm to 2 mm; the thickness of the first laminating plate and the second laminating plate ranges from 0.6 mm to 1.0 mm.

[0020] In a second aspect, the present invention further provides a turbine, comprising:

[0021] a turbine disk, wherein a plurality of tongues and grooves are provided at intervals on the outer circumference of the turbine disk;

[0022] The plurality of turbine blades are respectively embedded and installed in the plurality of tongues and grooves; the first flow channel plates and the second flow channel plates of adjacent turbine blades are in abutment with each other on the side away from their respective blade bodies to form a continuous annular gas flow channel surface. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0024] Figure 1 A schematic diagram of a partial three-dimensional structure of a turbine blade provided in an embodiment of the present invention;

[0025] Figure 2 A schematic diagram of the three-dimensional structure of the blade basin side edge plate provided in an embodiment of the present invention;

[0026] Figure 3 This is a schematic diagram of the three-dimensional structure of the blade back side edge plate provided in an embodiment of the present invention;

[0027] Figure 4 Schematic diagram of the three-dimensional structure of the turbine blade provided in an embodiment of the present invention Figure 1 ;

[0028] Figure 5 Schematic diagram of the three-dimensional structure of the turbine blade provided in an embodiment of the present invention Figure 2 ;

[0029] Figure 6 A schematic diagram of a partial three-dimensional structure of a turbine provided in an embodiment of the present invention;

[0030] Figure 7 This is a schematic diagram of the main structure of a turbine provided in an embodiment of the present invention;

[0031] Figure 8 Schematic diagram of the three-dimensional structure of the turbine blade provided in an embodiment of the present invention Figure 3 .

[0032] Description of reference numerals:

[0033] 1. Blade body; 2. Tenon; 3. Blade basin side edge plate; 4. Blade back side edge plate; 5. First flow channel plate; 6. Second flow channel plate; 7. Turbine disk; 8. Tenon groove; 9. First extended root; 10. First tenon tooth; 11. First tooth bottom; 12. Second extended root; 13. Second tenon tooth; 14. Second tooth bottom; 15. Flow channel surface seam; 16. Tooth bottom seam. DETAILED DESCRIPTION

[0034] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0035] Existing turbine blades made of ceramic-based composite materials can also be formed by bonding the blade blade to the blade body and tenon using ceramic powder or pinning, followed by a secondary high-temperature firing process. This method of manufacturing turbine blades results in poor molding quality and mechanical properties at the connection points between the blade blade, the blade body, and the tenon. This makes the turbine blades susceptible to failures such as cracking and separation when subjected to high temperature gradients and high loads. For these reasons, the present application proposes an improved turbine blade.

[0036] like Figures 1 to 8 A specific embodiment of the turbine blade shown includes: a blade body 1, a tenon 2, a blade basin side edge plate 3 and a blade back side edge plate 4. The turbine blade described in this application is a combined turbine blade.

[0037] like Figures 1 to 4 As shown, the tenon 2 and the blade body 1 are made of ceramic-based composite materials in one piece. The blade basin side edge plate 3 is located on the blade basin side of the blade body 1. The blade basin side edge plate 3 is composed of a first flow channel plate 5 and a first bonding plate that are connected. The inner side of the first flow channel plate 5 is bonded to the root of the blade body 1. The first bonding plate is bonded to the outer contour of the tenon 2. The blade back side edge plate 4 is located on the back side of the blade body 1. The blade back side edge plate 4 is composed of a second flow channel plate 6 and a second bonding plate that are connected. The inner side of the second flow channel plate 6 is bonded to the root of the blade body 1. The second bonding plate is bonded to the outer contour of the tenon 2. That is, the blade basin side edge plate 3 and the blade back side edge plate 4 are bonded to the blade body 1 and the tenon 2 from the blade basin and back directions, respectively. The inner side configuration of the first bonding plate is consistent with the outer contour of the tenon 2 on the blade basin side, and the inner side configuration of the second bonding plate is consistent with the outer contour of the tenon 2 on the back side.

[0038] The blade basin side edge plate 3 and the blade back side edge plate 4 are respectively made of a high temperature alloy material in one piece; specifically, the blade basin side edge plate 3 and the blade back side edge plate 4 can be made by high temperature alloy casting. The grade of the high temperature alloy material can be GH3536 or GH625.

[0039] like Figure 6 As shown, the turbine blade is suitable for being fitted with the blade basin side edge plate 3, blade back side edge plate 4, blade body 1, and tenon 2, with the first and second fitting plates both being embedded in the tenon groove 8 of the turbine disk 7. That is, the turbine blade is integrally assembled into the tenon groove 8 of the turbine disk 7.

[0040] Further, such as Figure 1 As shown, the cross section of the tenon 2 is dovetail-shaped.

[0041] Further, such as Figure 1 As shown, a smooth transition is adopted between the blade body 1 and the tenon 2.

[0042] Specifically, such as Figure 2 As shown, the first laminating plate is composed of a first extended root 9 , a first tenon 10 and a first tooth bottom 11 connected in sequence; the first extended root 9 is connected to the first flow channel plate 5 .

[0043] Specifically, such as Figure 3As shown, the second bonding plate is composed of a second extended root 12 , a second tenon 13 and a second tooth bottom 14 connected in sequence; the second extended root 12 is connected to the second flow channel plate 6 .

[0044] like Figure 6 As shown, when the turbine working blade is in the rotating working state, the blade body 1, the tenon 2, the blade basin side edge plate 3 and the blade back side edge plate 4 are under the action of centrifugal force. The tenon 2 will press the first tenon 10 of the blade basin side edge plate 3 and the second tenon 13 of the blade back side edge plate 4. The first tenon 10 of the blade basin side edge plate 3 will then press the tenon groove 8. The second tenon 13 of the blade back side edge plate 4 will then press the tenon groove 8, thereby realizing the connection between the turbine working blade and the turbine disk 7 in this application.

[0045] Further, such as Figure 8 As shown, considering that the blade basin side edge plate 3, the blade back side edge plate 4, the blade body 1 and the tenon 2 need to be assembled and combined each time during installation, the process is relatively complicated, and the location where the flow path surfaces of the blade basin side edge plate 3 and the blade back side edge plate 4 meet can easily form a flow path surface joint 15 and a tooth bottom joint 16, which poses a risk of gas leakage. Therefore, the first flow path plate 5 and the second flow path plate 6 are abutted and connected at the extension portion beyond the blade body 1; the outer end surfaces of the first bonding plate and the second bonding plate are abutted and connected. Specifically, the abutting connection is a welding connection. That is, the blade basin side edge plate 3 and the blade back side edge plate 4 form a welded metal edge plate. Generally, the blade basin side edge plate 3 and the blade back side edge plate 4 are first assembled to the blade body 1 and the tenon 2, and then welded.

[0046] Furthermore, the first flow channel plate 5 and the second flow channel plate 6 have a gas flow channel profile along the axial direction on one side facing the top of the blade 1; the axial direction is the direction of the rotation axis of the turbine blade in the rotating working state.

[0047] Further, such as Figure 5 As shown, the sum of the circumferential dimensions of the blade basin side edge plate 3 and the blade back side edge plate 4 is L, and L is the dimension of a circumferential pitch between adjacent turbine working blades installed on the turbine disk 7; the circumferential direction is the rotation direction of the turbine working blades in the rotating working state.

[0048] Specifically, the thickness of the first flow channel plate 5 and the second flow channel plate 6 ranges from 1 mm to 2 mm; the thickness of the first laminating plate and the second laminating plate both ranges from 0.6 mm to 1.0 mm.

[0049] The turbine blades provided in this application use high-temperature alloy blade basin side edge plates 3 and blade back side edge plates 4 to replace the complex ceramic-based composite edge plates in traditional solutions, avoiding the difficulties in preparation and reduced strength caused by fiber bending or the use of bonding and pinning methods in traditional solutions to prepare ceramic edge plates. The blade body 1 and tenon 2 in this application are integrally formed using ceramic-based composite materials. The smooth transition between the blade body 1 and the tenon 2 can reduce the difficulty of preparing the ceramic-based composite tenon 2, while allowing the fibers of the blade body 1 to extend more continuously to the tenon 2, thereby improving the tenon 2's ability to bear the centrifugal load of the blade body 1.

[0050] like Figure 6 and Figure 7 As shown, the present application also proposes a turbine, comprising: a turbine disk 7 and a plurality of turbine blades as described above. A plurality of grooves 8 are spaced apart on the outer circumference of the turbine disk 7. The turbine blades are respectively embedded in the grooves 8. The first flow plate 5 and the second flow plate 6 of adjacent turbine blades abut against each other on the side facing away from the respective blade airfoil 1 to form a continuous annular gas flow surface. The turbine described in the present application is particularly useful in gas turbine engines.

[0051] The turbine blades provided in this application have been simulated to effectively reduce the difficulty of preparing existing ceramic-based composite turbine blades and improve the load-bearing capacity of the turbine blades.

[0052] Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention. Such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A turbine blade, characterized in that: include: Leaf body (1); The tenon (2) and the blade (1) are integrally formed using a ceramic-based composite material; A blade basin side edge plate (3) is located on the blade basin side of the blade body (1), and the blade basin side edge plate (3) is composed of a first flow channel plate (5) and a first bonding plate that are connected and arranged; the inner side of the first flow channel plate (5) is bonded to the root of the blade body (1); and the first bonding plate is bonded to the outer contour of the tenon (2); The blade back side edge plate (4) is located on the blade back side of the blade body (1), and the blade back side edge plate (4) is composed of a second flow channel plate (6) and a second bonding plate that are connected and arranged; the inner side of the second flow channel plate (6) is bonded to the root of the blade body (1); the second bonding plate is bonded to the outer contour of the tenon (2); the blade basin side edge plate (3) and the blade back side edge plate (4) are respectively made of high-temperature alloy material and integrally formed; The turbine working blade is suitable for being in a state where the blade basin side edge plate (3), the blade back side edge plate (4), the blade body (1), and the tenon (2) are in a fitted state, and the first fitting plate and the second fitting plate are both embedded in the tenon groove (8) of the turbine disk (7).

2. The turbine blade according to claim 1, characterized in that: The cross section of the tenon (2) is dovetail-shaped.

3. The turbine blade according to claim 1, characterized in that: A smooth transition is provided between the blade body (1) and the tenon (2).

4. The turbine blade according to claim 1, wherein: The first bonding plate is composed of a first extended root (9), a first tenon (10) and a first tooth bottom (11) connected in sequence; the first extended root (9) is connected to the first flow channel plate (5); The second bonding plate is composed of a second extended root (12), a second tenon (13) and a second tooth bottom (14) connected in sequence; the second extended root (12) is connected to the second flow channel plate (6).

5. The turbine blade according to any one of claims 1 to 4, characterized in that: The first flow channel plate (5) and the second flow channel plate (6) are abutted and connected at the extended portion beyond the blade (1); and the outer end surfaces of the first bonding plate and the second bonding plate are abutted and connected.

6. The turbine blade according to claim 5, characterized in that: The abutting connection is a welding connection.

7. The turbine blade according to any one of claims 1 to 4, characterized in that: The first flow channel plate (5) and the second flow channel plate (6) have a combustion gas flow channel profile along the axial direction on one side facing the top of the blade (1); the axial direction is the direction of the rotation axis of the turbine working blade in a rotating working state.

8. The turbine blade according to any one of claims 1 to 4, characterized in that: The sum of the circumferential dimensions of the blade basin side edge plate (3) and the blade back side edge plate (4) is L, wherein L is the dimension of a grating distance between adjacent turbine working blades mounted on a turbine disk (7) along the circumferential direction; and the circumferential direction is the rotation direction of the turbine working blades in a rotating working state.

9. The turbine blade according to any one of claims 1 to 4, characterized in that: The thickness of the first flow channel plate (5) and the second flow channel plate (6) ranges from 1 mm to 2 mm; the thickness of the first laminating plate and the second laminating plate both ranges from 0.6 mm to 1.0 mm.

10. A turbine, characterized in that: include: A turbine disk (7), wherein a plurality of tongues and grooves (8) are provided at intervals on the outer periphery of the turbine disk (7); A plurality of turbine blades according to any one of claims 1 to 9, wherein the plurality of turbine blades are respectively embedded and installed in the plurality of tongues and grooves (8); the first flow channel plates (5) and the second flow channel plates (6) of adjacent turbine blades are in abutment with each other on a side away from the respective blade bodies (1) to form a continuous annular gas flow channel surface.

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