A turbine blade for an aeroengine

Abstract

The utility model discloses an aero-engine turbine blade belongs to aero-engine technical field, including tenon seat, the top fixedly connected with arc plate of tenon seat, the outside fixedly connected with arc blade of arc plate, the rear end of arc blade is provided with the heat dissipation groove, the middle part fixedly connected with reinforcing pad of heat dissipation groove inner chamber, one side fixedly connected with convex block of arc plate, the other side of arc plate is provided with convex slot. In the utility model, when installing, tenon seat is sleeved in the mortise of turbine disc side part, and simultaneously arc plate is sleeved in the outside of turbine disc, when two adjacent blades are inserted, make the convex block of one arc plate side part insert into the convex slot of the other arc plate side part, make two arc plates connect, utilize multiple connected arc plates to guarantee the connecting strength between multiple blades, and simultaneously the connecting strength between auxiliary tenon seat and turbine disc is guaranteed.

Description

Technical Field

[0001] This utility model relates to the field of aero-engine technology, and more specifically, to an aero-engine turbine blade. Background Technology

[0002] An aero-engine is a highly complex and precise thermodynamic machine that provides the power required for aircraft flight. As the heart of an aircraft, it directly affects its performance, reliability, and economy. Among them, gas turbine engines are the most widely used, including turbojet engines, turbofan engines, turboprop engines, and turboshaft engines. Previously, the turbine disk and blades were integrated; if any one or more blades failed, the entire turbine disk needed to be replaced, increasing maintenance costs. Therefore, an assembly of the turbine disk and blades was developed to reduce maintenance costs. Existing blades are installed by mating tenons on the blade with inverted wedge grooves on the rim. However, multiple blades are relatively independent, affecting the stability of the blade installation. Furthermore, the blades generate heat during operation, and heat dissipation needs improvement. Therefore, we propose an aero-engine turbine blade. Utility Model Content

[0003] In view of the problems mentioned in the background art above, the purpose of this utility model is to provide an aero-engine turbine blade.

[0004] To solve the above problems, the present invention adopts the following technical solution: an aero-engine turbine blade, including a tenon seat, an arc-shaped plate fixedly connected to the top of the tenon seat, an arc-shaped blade fixedly connected to the outer side of the arc-shaped plate, a heat dissipation groove provided at the rear end of the arc-shaped blade, a reinforcing block fixedly connected to the middle of the inner cavity of the heat dissipation groove, a convex block fixedly connected to one side of the arc-shaped plate, a convex groove provided on the other side of the arc-shaped plate, and two ventilation holes provided on the arc-shaped plate.

[0005] As a preferred embodiment of this utility model, an arc-shaped reinforcing angle is provided between the bottom end of the arc-shaped blade and the top surface of the tenon seat.

[0006] As a preferred embodiment of this utility model, the front end and top end of the arc-shaped blade are provided with an air-guiding arc angle.

[0007] As a preferred embodiment of this utility model, multiple card slots are provided on both sides of the tenon seat.

[0008] In a preferred embodiment of this invention, the size of the inner cavity of the convex groove is equal to the size of the outer shape of the convex block.

[0009] As a preferred embodiment of this utility model, the tenon seat, the arc plate, the arc blade, the convex block, and the card seat are integrally formed.

[0010] The advantages of this utility model are: (1) In this utility model, when installing, the tenon seat is fitted into the tenon groove on the side of the turbine disk, and the arc plate is fitted onto the outside of the turbine disk. When two adjacent blades are inserted, the convex block on the side of one arc plate is inserted into the convex groove on the side of another arc plate, so that the two arc plates are connected. The connection strength between multiple blades is guaranteed by multiple connected arc plates, and the connection strength between the tenon seat and the turbine disk is also assisted.

[0011] (2) In this utility model, when the turbine disk drives the arc plate and the arc blade to rotate, the arc blade converts the kinetic energy of the gas into mechanical energy. The heat on the arc blade can be released from the heat dissipation groove. At the same time, the air flowing in the ventilation hole can carry away the heat on the tenon seat and the arc plate, thus ensuring the heat dissipation effect of the turbine blade. Attached Figure Description

[0012] Figure 1 is a schematic diagram of the overall structure of this utility model.

[0013] Figure 2 is a schematic diagram of the structure of the arc-shaped plate of this utility model.

[0014] Figure 3 is a structural schematic diagram of the tenon seat of this utility model.

[0015] Figure 4 is a schematic diagram of the structure of the arc-shaped blade of this utility model.

[0016] The following are the labels in the diagram: 1. Tenon seat; 2. Curved plate; 3. Curved blade; 4. Heat dissipation groove; 5. Reinforcing block; 6. Convex groove; 7. Convex block; 8. Ventilation hole; 9. Card seat; 10. Curved reinforcing angle; 11. Air intake curved angle. Detailed Implementation

[0017] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0018] In the description of this utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "top / bottom," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0019] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "sleeved / connected," "connected," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances. Example 1

[0020] As shown in Figures 1 to 4, an aero-engine turbine blade includes a tenon seat 1. An arc-shaped plate 2 is fixedly connected to the top of the tenon seat 1. Multiple arc-shaped plates 2 can form a complete circle. An arc-shaped blade 3 is fixedly connected to the outer side of the arc-shaped plate 2. A heat dissipation groove 4 is provided at the rear end of the arc-shaped blade 3 to facilitate the dissipation of heat generated by the arc-shaped blade 3. A reinforcing block 5 is fixedly connected to the middle of the inner cavity of the heat dissipation groove 4 to support the inner cavity of the heat dissipation groove 4 and ensure the strength of the arc-shaped blade 3. A convex block 7 is fixedly connected to one side of the arc-shaped plate 2, and a convex groove 6 is provided on the other side of the arc-shaped plate 2. Two ventilation holes 8 are provided on the arc-shaped plate 2 to dissipate the internal temperature of the arc-shaped plate 2. Multiple retainers 9 are provided on both sides of the tenon seat 1. The size of the inner cavity of the convex groove 6 is equal to the size of the outer shape of the convex block 7 to ensure the stability of the convex block 7 when it is inserted into the inner cavity of the convex groove 6, thereby connecting two adjacent arc-shaped plates 2. Example 2

[0021] Based on Embodiment 1, as shown in Figure 3, an arc-shaped reinforcing angle 10 is provided between the bottom end of the arc-shaped blade 3 and the top surface of the tenon seat 1. The arc-shaped reinforcing angle 10 is used to enhance the connection strength between the arc-shaped plate 2 and the arc-shaped blade 3. The front end and top end of the arc-shaped blade 3 are provided with air-guiding arc-shaped angles 11. The air-guiding arc-shaped angles 11 are used to guide the airflow and reduce the resistance between the air and the arc-shaped blade 3. Example 3

[0022] Based on Embodiment 1 and Embodiment 2, as shown in Figures 1 to 4, the tenon seat 1, the arc plate 2, the arc blade 3, the convex block 7, and the card seat 9 are integrally formed structures to ensure the overall strength of the blade, which can be manufactured by casting.

[0023] It should be noted that this utility model is an aero-engine turbine blade. During assembly, the tenon seats 1 below multiple turbine blades are snapped into the mortises on the side of the turbine disk. At the same time, the convex blocks 7 on one side of the arc-shaped plates 2 at the top of multiple tenon seats 1 are snapped into the convex grooves 6 on the side of another arc-shaped plate 2, thereby connecting two adjacent arc-shaped plates 2 so that the multiple arc-shaped plates 2 at the top of the tenon seats 1 form a complete circle. At this time, the inner side of the arc-shaped plates 2 is in contact with the outer side of the turbine disk. When the turbine disk drives multiple blades to rotate, the kinetic energy of the gas is converted into mechanical energy by the arc-shaped blades 3. The heat dissipation grooves 4 on the arc-shaped blades 3 accelerate the heat dissipation on the arc-shaped blades 3, and the air flow in the ventilation holes 8 carries away the heat from the tenon seats 1 and the arc-shaped plates 2, ensuring the heat dissipation effect.

[0024] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model based on the technical solution and its improved concept should be covered within the protection scope of the present utility model.

Claims

1. An aero-engine turbine blade, comprising a tenon seat (1), characterized in that: The top of the tenon seat (1) is fixedly connected to an arc plate (2), and the outer side of the arc plate (2) is fixedly connected to an arc blade (3). The rear end of the arc blade (3) is provided with a heat dissipation groove (4). The middle of the inner cavity of the heat dissipation groove (4) is fixedly connected to a reinforcing block (5). A convex block (7) is fixedly connected to one side of the arc plate (2), and a convex groove (6) is provided on the other side of the arc plate (2). Two ventilation holes (8) are provided on the arc plate (2).

2. The aero-engine turbine blade according to claim 1, characterized in that: An arc-shaped reinforcing angle (10) is provided between the bottom end of the arc blade (3) and the top surface of the tenon seat (1).

3. The aero-engine turbine blade according to claim 2, characterized in that: The front end and top end of the arc blade (3) are provided with an air-guiding arc angle (11).

4. The aero-engine turbine blade according to claim 3, characterized in that: Multiple card slots (9) are provided on both sides of the tenon seat (1).

5. The aero-engine turbine blade according to claim 1, characterized in that: The size of the inner cavity of the convex groove (6) is equal to the size of the outer shape of the convex block (7).

6. The aero-engine turbine blade according to claim 3, characterized in that: The tenon seat (1), arc plate (2), arc blade (3), convex block (7), and card seat (9) are integrally formed structures.

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