Turbine rotor blade, turbine rotor and engine turbine

Abstract

The utility model discloses a turbine rotor blade, a turbine rotor and an engine turbine, belongs to the technical field of aero-engines, and is used for solving the technical problems that a damper of the turbine rotor blade is complex to process and assemble and limited in vibration reduction effect. The utility model relates to a turbine rotor blade which comprises a cavity and a damper located in the cavity. The dampers comprise a first damper and a second damper; the first damper is used for weakening first-order bending vibration and second-order bending vibration of the blade; and the second damper is used for weakening the first-order torsional vibration of the blade. The turbine rotor blade is convenient to machine and does not need to be assembled and machined subsequently, meanwhile, the vibration reduction performance of the blade and the turbine rotor is improved, and the risk that an engine loses efficacy due to vibration is reduced.

Description

Technical Field

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

[0002] Turbine rotor blades are one of the core components of aero-engines. Their operating environment is harsh; in addition to withstanding centrifugal loads from high-speed rotation, they must also withstand temperature and aerodynamic loads from high-temperature, high-pressure combustion gases, as well as forced vibrations and loads caused by the turbine blades themselves, such as resonance, surge, and flutter. In recent years, vibration failures have accounted for over 60% of major engine failures, and blade vibration failures account for over 70% of all vibration failures. Therefore, various blade vibration problems directly affect engine reliability.

[0003] Currently, vibration reduction of turbine blades is mainly achieved by adjusting the shape of certain parts of the blade, changing the blade material, and setting additional extension roots or dampers on the blade flanges. However, these methods have limited vibration reduction effects, and sometimes the vibration reduction effect of turbine rotor blades can be reduced due to manufacturing errors, assembly and other factors. Therefore, the risk of vibration cannot be completely avoided. Utility Model Content

[0004] Based on the above analysis, this utility model aims to provide a turbine rotor blade, a turbine rotor, and an engine turbine to solve the technical problem that the vibration reduction effect of turbine rotor blades is limited due to manufacturing errors, assembly, and other factors.

[0005] The purpose of this utility model is mainly achieved through the following technical solutions.

[0006] The first aspect of this utility model provides a turbine rotor blade, including a cavity, a damper, and a blade body; the cavity is located within the blade body and extends through the blade body in the radial direction; the damper is located within the cavity, and the damper includes a first damper and a second damper; the first damper is used to reduce the first-order bending vibration and the second-order bending vibration of the blade body, and the second damper is used to reduce the first-order torsional vibration of the blade body.

[0007] Furthermore, the first damper includes a first rib and a second rib, both of which are transverse ribs and are arranged opposite each other along the thickness direction of the blade body; a first friction damping structure is formed between the first rib and the second rib through a first gap.

[0008] Furthermore, the second damper includes a first protrusion and a second protrusion, which are arranged opposite to each other along the thickness direction of the blade body. The second damper is far from the first-order torsional vibration nodal line of the blade, and a second friction damping structure is formed between the first protrusion and the second protrusion through a second gap.

[0009] Furthermore, multiple first dampers are provided, and these multiple first dampers are distributed at intervals along the radial direction of the blade body between the two second-order vibration bending nodal lines.

[0010] Furthermore, the radial thickness W1 of the first convex strip is less than the radial thickness W2 of the second convex strip, and the length L1 of the first convex strip is greater than the length L2 of the second convex strip.

[0011] Furthermore, compared to the position of the first damper, the second damper is positioned closer to the blade tip of the blade body.

[0012] Furthermore, multiple second dampers are provided, and these multiple second dampers are distributed at intervals along the radial direction of the blade body.

[0013] Furthermore, both the first and second protrusions are cylinders, with the diameter of the first protrusion being larger than that of the second protrusion.

[0014] The second aspect of this utility model provides a turbine rotor, including a turbine disk, a turbine neck, and turbine rotor blades as described in any of the first aspects; a vibration damping device is provided between the rootstocks of two adjacent turbine rotor blades.

[0015] The third aspect of this utility model provides an engine turbine, including the turbine rotor described in the second aspect.

[0016] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0017] 1. The turbine rotor blade of this utility model, by setting a cavity and setting a damper in the cavity, can greatly reduce the risk of blade failure due to vibration on the basis of the original vibration reduction measures of the blade; and the position, shape and size of the damper can be changed according to the design of the turbine blade, and can be integrally formed during the manufacturing of the turbine blade, without the need for subsequent assembly and processing, thereby improving the vibration reduction performance and reliability of the blade.

[0018] 2. The turbine rotor blade of this utility model, by setting the first damper as a convex strip and arranging it between two second-order bending vibration nodal lines, can ensure that the first damper plays a role in vibration reduction without bringing high centrifugal load to the blade, and can also increase strength.

[0019] 3. The turbine rotor blade of this utility model has a better damping effect by setting the second damper as a protrusion and arranging it on the leading edge of the blade, and the centrifugal load on the blade is also relatively low.

[0020] 4. The turbine rotor blade of this utility model can maintain a constant contact area of ​​the damper by setting different values ​​for the length and thickness of the first and second convex strips and the diameter of the first and second convex blocks, so as to maintain a stable damping effect.

[0021] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objectives and other advantages of this invention can be realized and obtained through the embodiments described and the accompanying drawings, which are particularly pointed out. Attached Figure Description

[0022] Figure 1 This is a cross-sectional view of the turbine rotor blades of Embodiment 1 of the present invention.

[0023] Figure 2 for Figure 1 Schematic diagram of section B in the middle;

[0024] Figure 3 for Figure 2 A structural diagram of section D;

[0025] Figure 4 for Figure 2 A structural diagram of section C;

[0026] Figure 5 This is a schematic diagram of the nodal line position of the second-order bending vibration in Embodiment 1 of this utility model;

[0027] Figure 6 This is a schematic diagram of the position of the nodal line of the first-order torsional vibration in Embodiment 1 of this utility model;

[0028] Figure 7 This is a schematic diagram of the overall structure of the turbine rotor in Embodiment 2 of this utility model;

[0029] Figure 8 This is a partial cross-sectional view of the turbine rotor of Embodiment 2 of this utility model.

[0030] Figure label:

[0031] 1-Cavity; 2-Damper; 21-First damper; 211-First convex strip; 212-Second convex strip; 213-First gap; 22-Second damper; 221-First protrusion; 222-Second protrusion; 223-Second gap; 3-Blade body;

[0032] 100 - Nodal line of second-order bending vibration; 200 - Nodal line of first-order torsional vibration;

[0033] W1 - Radial thickness of the first convex strip; W2 - Radial thickness of the second convex strip; L1 - Length of the first convex strip; L2 - Length of the second convex strip; - Diameter of the first bump; - Diameter of the second protrusion; б1 - Width of the first gap; б2 - Width of the second gap;

[0034] 10 - Turbine rotor blade; 20 - Turbine disc; 30 - Turbine neck; 40 - Vibration damping device. Detailed Implementation

[0035] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0036] Example 1

[0037] This embodiment provides a turbine rotor blade, such as Figure 1 and Figure 2 As shown, it includes a cavity 1, a damper 2, and a blade body 3.

[0038] The cavity 1 is located inside the blade body 3 and extends through the radial direction of the blade body 3. This not only reduces the mass of the high-pressure turbine blade and improves the turbine performance, but also provides space for the damper 2 to be installed inside the blade body 3.

[0039] like Figure 1 As shown, the damper 2 is disposed in the cavity 1, including a first damper 21 and a second damper 22;

[0040] like Figure 1 , Figure 2 and Figure 3 As shown, the first damper 21 includes a first rib 211 and a second rib 212 arranged opposite to each other along the thickness direction of the blade body 3. A friction damping structure is formed between the first rib 211 and the second rib 212 through a first gap 213. The first rib 211 and the second rib 212 are both transverse ribs, so that the first damper 21 can reduce the first-order bending vibration and the second-order bending vibration of the blade body 3.

[0041] like Figure 1 , Figure 2 and Figure 4 As shown, the second damper 22 includes a first protrusion 221 and a second protrusion 222 arranged opposite to each other along the thickness direction of the blade body 3. The first protrusion 221 and the second protrusion 222 form a friction damping structure through a second gap 223. The second damper 22 is far away from the first torsional vibration nodal line 200 of the blade body 3, so that the second damper 22 can weaken the first torsional vibration of the blade body 3.

[0042] In this embodiment, a damper 2 with a gap is installed in the cavity 1 of the turbine rotor blade. When vibration occurs, the deformation of the blade body 3 reduces the values ​​of the first gap width б1 and the second gap width б2, thereby generating a friction damping effect and reducing the vibration of the blade body 3. The damper 2 in this embodiment can greatly reduce the risk of turbine rotor failure due to vibration, based on the original vibration reduction measures of the turbine rotor. At the same time, the position, shape, and size of the damper 2 in this embodiment can be changed according to the design of the turbine rotor blade, and it is integrally formed during the manufacturing of the turbine rotor blade, eliminating the need for subsequent assembly and processing, thus improving the vibration reduction performance and reliability of the turbine rotor blade.

[0043] like Figure 1 and Figure 5 As shown, in a preferred embodiment of this invention, two first dampers 21 are provided, and the two first dampers 21 are distributed at intervals along the radial direction of the blade body 3 between the two second-order bending vibration nodal lines 100. When the blade body 3 generates first-order and second-order bending vibrations, frictional damping is generated between the two pairs of first convex strips 211 and second convex strips 212, thereby weakening the first-order and second-order bending vibrations. Since the first dampers 21 are located at positions with a small radius of rotation of the blade body 3, they can reduce vibration and increase strength without causing high centrifugal loads on the blade body 3. Multiple first dampers 21 can also be provided.

[0044] like Figure 3 As shown, in order to keep the contact area of ​​the first protrusion 211 and the second protrusion 212 constant when the first damper 21 is working, the radial thickness W1 of the first protrusion 211 is less than the radial thickness W2 of the second protrusion 212, and the length L1 of the first protrusion 211 is greater than the length L2 of the second protrusion 212, so that the contact area of ​​the first protrusion 211 and the second protrusion 212 remains unchanged, so as to maintain a stable damping effect.

[0045] Preferably, the first gap 213 has the same curvature as the blade body 3 at the first gap 213, so that the force is uniform at each part between the first protrusion 211 and the second protrusion 212. Preferably, the width of the first gap 213 is between 0.1mm and 0.2mm.

[0046] like Figure 1 and Figure 6As shown, in a preferred embodiment of this invention, three second dampers 22 are provided and spaced apart along the radial direction of the blade body 3, with the three second dampers 22 close to the leading edge of the blade body 3. When the blade body 3 generates first-order torsional vibration, frictional damping is generated between the three pairs of first protrusions 221 and second protrusions 222, thereby weakening the first-order torsional vibration. Since the second dampers 22 have a better damping effect as they are closer to the high amplitude of the blade, and although the second dampers 22 are located at a position with a large radius of rotation of the blade body 3, the centrifugal load brought by the second dampers 22 to the blade body 3 is relatively low because the mass of the protrusion-shaped second dampers 22 is much smaller than that of the convex strip-shaped first dampers 21. Multiple second dampers 22 can also be provided, and multiple second dampers 22 can also be arranged on both sides of the nodal line of the first-order torsional vibration.

[0047] Preferred, such as Figure 4 As shown, both the first protrusion 221 and the second protrusion 222 are cylindrical. To ensure that the contact area between the first protrusion 221 and the second protrusion 222 remains constant during the operation of the second damper 22, the diameter of the first protrusion 221 is... The diameter of the second protrusion is greater than that of the second protrusion 222. The contact area between the first protrusion 221 and the second protrusion 222 remains constant to maintain a stable damping effect. Preferably, the width of the second gap 223 is between 0.1 mm and 0.2 mm.

[0048] Furthermore, the two contact surfaces of the damper 2 can also be coated with a wear-resistant coating, thereby extending the service life of the damper 2.

[0049] Example 2

[0050] This embodiment provides a turbine rotor, including the turbine rotor blades 10 of Embodiment 1.

[0051] like Figure 7 As shown, the turbine rotor in this embodiment also includes a turbine disc 20 and a turbine neck 30; as Figure 8 As shown, a vibration damping device 40 is provided between the roots of two adjacent turbine rotor blades. In this embodiment, the turbine rotor can significantly improve its vibration damping performance by providing the vibration damping device 40 and the damper 2 built into the turbine rotor blade 10.

[0052] Example 3

[0053] This embodiment provides an engine turbine, including the turbine rotor of Embodiment 2. By using the turbine rotor of Embodiment 2, the risk of engine failure due to vibration can be significantly reduced.

[0054] 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 changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. A turbine rotor blade characterized by, The turbine rotor blade (10) comprises a cavity (1), a damper (2) and a blade body (3); The cavity (1) is located in the blade body (3) and penetrates through the blade body (3) in the radial direction of the blade body (3); The damper (2) is located in the cavity (1), and the damper (2) comprises a first damper (21) and a second damper (22); The first damper (21) is used for weakening the first-order bending vibration and the second-order bending vibration of the blade body (3), and the second damper (22) is used for weakening the first-order torsional vibration of the blade body (3).

2. The turbine rotor blade of claim 1, wherein, The first damper (21) comprises a first protrusion (211) and a second protrusion (212), and the first protrusion (211) and the second protrusion (212) are both transverse ribs and oppositely arranged in the thickness direction of the blade body (3); a first friction damping structure is formed between the first protrusion (211) and the second protrusion (212) through a first gap (213).

3. The turbine rotor blade of claim 1, wherein, The second damper (22) comprises a first protrusion (221) and a second protrusion (222), and the first protrusion (221) and the second protrusion (222) are oppositely arranged in the thickness direction of the blade body (3); the second damper (22) is away from the first-order torsional vibration nodal line (200) of the blade, and a second friction damping structure is formed between the first protrusion (221) and the second protrusion (222) through a second gap (223).

4. The turbine rotor blade of claim 2, wherein, A plurality of first dampers (21) are arranged, and the plurality of first dampers (21) are arranged in the radial direction of the blade body (3) and are distributed between two second-order bending vibration nodal lines (100).

5. The turbine rotor blade of claim 4, wherein, The first protrusion radial thickness W1 of the first protrusion (211) is less than the second protrusion radial thickness W2 of the second protrusion (212), and the first protrusion length L1 of the first protrusion (211) is greater than the second protrusion length L2 of the second protrusion (212).

6. The turbine rotor blade of claim 3, wherein, Compared with the position of the first damper (21), the second damper (22) is arranged closer to the blade tip of the blade body (3).

7. The turbine rotor blade of claim 6, wherein, A plurality of second dampers (22) are arranged, and the plurality of second dampers (22) are arranged in the radial direction of the blade body (3) and are distributed.

8. The turbine rotor blade of claim 7, wherein, The first protrusion (221) and the second protrusion (222) are both cylindrical, and the diameter of the first protrusion (221) is greater than the diameter of the second protrusion (222).

9. A turborotor characterized by The turbine rotor comprises a turbine rotor disc (20), a turbine rotor hub (30) and the turbine rotor blade (10) according to any one of claims 1 to 8; a damping device (40) is arranged between the blade roots of two adjacent turbine rotor blades (10).

10. An engine turbine characterized by, The turbine rotor comprises the turbine rotor according to claim 9.

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