Turbine wheel disc and turbine blade damping device thereof

Abstract

The utility model provides a turbine blade damping device which comprises a damping element, the damping element comprises an element body and a plurality of cold air channels arranged on the element body at intervals in the length direction of the element body, and the element body is arranged below the splicing position of two adjacent edge plates and abuts against the two edge plates. The cold air channel comprises an inlet close to the wheel disc and an outlet located under the splicing position. The utility model further provides a turbine wheel disc which comprises the turbine blade damping device. In conclusion, the turbine blade damping device can cool the blade margin plate adjacent to the turbine blade damping device while achieving the damping effect, the problems that the blade vibrates and the margin plate is overheated and ablated are solved, the service life of the blade is greatly prolonged, and the rejection rate of the blade is reduced; and meanwhile, the damage of vibration and overheating to the turbine blade in the actual service process can be reduced, and the maintenance cost is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of gas turbines, in particular to a turbine wheel disc and a turbine blade damping device thereof. Background Art

[0002] As we all know, during the operation of gas turbines, turbine blades are in a harsh environment of high temperature and high speed, and are washed by high-temperature combustion gas, and are subjected to huge mechanical and thermal stresses. On the one hand, the non-uniform flow generated by the upstream blades will cause the downstream blades to be subjected to periodic airflow excitation, thereby inducing forced vibration and high-cycle fatigue damage of the blades. On the other hand, when the excitation frequency is equal to the natural frequency of the blades, the blades will resonate. Once a strong resonance occurs, it is easy to cause high-cycle fatigue damage to the blades. In order to avoid high-cycle fatigue failure caused by turbine blade vibration and affect the life of the blades, it is necessary to carry out vibration reduction design on the turbine blades.

[0003] Common blade vibration reduction methods usually include setting a blade crown on the blade, setting a vibration-damping boss on the blade body, or setting a damper on the edge plate. Blades with crowns will introduce larger centrifugal loads and cause strength problems; setting a vibration-damping boss on the blade body will not only cause strength problems, but also affect the airflow in the flow channel and affect the working efficiency of the turbine. Therefore, for gas turbine blades, the current method of setting a damper on the edge plate is mostly used to reduce vibration. Typically, the vibration damper is usually set below the edge plate or between the edge plates of adjacent blades, and uses dry friction damping to consume and diffuse the vibration energy, so that the transient vibration response is rapidly attenuated, reducing the vibration amplitude of the blade, thereby increasing the high-cycle fatigue life of the blade.

[0004] At present, many different forms of vibration damper devices (or damper pins) have been created in order to achieve better vibration reduction effects and reduce high-cycle fatigue damage to blades. However, in fact, combined with the actual service conditions of gas turbine moving blades, there is often severe overheating and ablation on both sides of the edge plate of gas turbine blades after service, which greatly reduces the service life of the blades and increases the repair cost and cycle of gas turbine blades. Utility Model Content

[0005] In view of the above-mentioned defects, the purpose of the utility model is to provide a turbine blade damping device, which can not only have a vibration reduction effect but also cool the adjacent blade edge plate to solve the problem of overheating and ablation of the blade edge plate.

[0006] The utility model provides a turbine blade damping device, wherein the turbine wheel disc comprises a wheel disc and a plurality of blades mounted on the wheel disc, each blade comprises an edge plate, a blade body and a blade root arranged on opposite sides of the edge plate, the blade root is mounted on the wheel disc, a plurality of the edge plates are spliced ​​together to form a complete ring, comprising a damping element, the damping element comprises an element body and a plurality of cold air channels arranged on the element body at intervals along the length direction of the element body, the element body is arranged below the joint of two adjacent edge plates and abuts against the two edge plates, the cold air channel comprises an inlet close to the wheel disc and an outlet located directly below the joint.

[0007] Preferably, the element body extends along the axial direction of the wheel disc.

[0008] Preferably, the plurality of cold air channels are a plurality of cold air grooves arranged at intervals on the outer wall of the element body.

[0009] Preferably, the plurality of cold air passages are a plurality of through holes arranged at intervals in the element body.

[0010] Preferably, an angle is formed between an extending direction of the through hole and a length direction of the component body.

[0011] Preferably, the invention further comprises a baffle plate arranged between the end of the element body and the wheel disc.

[0012] Preferably, a fitting groove is provided at the end of the element body, a wheel disc groove is provided on the wheel disc, the fitting groove and the wheel disc groove are arranged opposite to each other, and the baffle is arranged between the fitting groove and the wheel disc groove.

[0013] The utility model also provides a turbine wheel disc, comprising the above-mentioned turbine blade damping device.

[0014] To sum up, the turbine blade damping device provided by the utility model can achieve the vibration reduction effect while cooling the adjacent blade edge plate, thereby solving the problems of blade vibration and edge plate overheating and ablation, greatly improving the service life of the blade and reducing the blade scrap rate; at the same time, it can also reduce the damage to the turbine blades caused by vibration and overheating during actual service, thereby reducing maintenance costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic diagram of the position of the turbine blade damping device of the utility model in the turbine wheel;

[0016] Figure 2 for Figure 1 Sectional view at AA in the middle;

[0017] Figure 3It is a schematic diagram of the position of the turbine blade damping device of the utility model on the wheel disc;

[0018] Figure 4 for Figure 2 Sectional view at the middle BB;

[0019] Figure 5 for Figure 4 The enlarged view of the part in the middle circle shows the flow direction of the cooling gas;

[0020] Figure 6 This is a front view of the first embodiment of the turbine blade damping device of the utility model;

[0021] Figure 7 It is a top view of the first embodiment of the turbine blade damping device of the utility model;

[0022] Figure 8 This is a schematic structural diagram of a second embodiment of the turbine blade damping device of the utility model.

[0023] Component number description:

[0024] 1 Damping element

[0025] 11 Component body

[0026] 111 Mounting groove

[0027] 12 Air conditioning duct

[0028] 121 Air conditioning recess

[0029] 122 Through Hole

[0030] 2 Baffle

[0031] 3 blades

[0032] 31 Edge board

[0033] 32 blades

[0034] 33 Yegen

[0035] 4 Roulette

[0036] 41 Roulette groove

[0037] 51 Cold side

[0038] 511 Cooling air

[0039] 52 Hot side DETAILED DESCRIPTION

[0040] The following is a further detailed description of the specific implementations of the present invention in conjunction with the accompanying drawings. These implementations are only used to illustrate the present invention, but not to limit the present invention.

[0041] In the description of the present invention, it should be noted that the terms "top", "bottom", "inside", "outside", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0042] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0043] In addition, in the description of the present invention, unless otherwise specified, “plurality” means two or more.

[0044] The utility model provides a turbine blade damping device and a turbine wheel including the turbine blade damping device. Figure 1 As shown, the turbine wheel includes a wheel disc 4 and a plurality of blades 3 mounted on the wheel disc 4. Each blade 3 includes an edge plate 31, a blade body 32 and a blade root 33 arranged on opposite sides of the edge plate 31. The blade root 33 is mounted on the wheel disc 4 through a tenon. A plurality of edge plates 31 are spliced ​​together to form a full circle. A cold air chamber (hereinafter referred to as the cold side 51) is formed between the edge plate 31, the blade root 33 and the wheel disc 4, in which there is cooling air 511 with a lower temperature than the high-temperature combustion gas. The side of the edge plate 31 close to the blade body 32 is a high-temperature combustion gas channel (hereinafter referred to as the hot side 52), in which the high-temperature combustion gas flows.

[0045] like Figure 1-5 As shown, the turbine blade damping device includes a damping element 1, and the damping element 1 includes an element body 11 and a plurality of cold air channels 12 arranged on the element body 11 at intervals along the length direction of the element body 11. The element body 11 is arranged below the joint of two adjacent edge plates 31 and abuts against the two edge plates 31, that is, the element body 11 is located on the cold side 51. The cold air channel 12 includes an inlet close to the wheel disc 4 and an outlet located directly below the joint, which can connect the cooling air 511 on the cold side 51 to the joint, so that the cooling air 511 flows to the hot side 52 through the gap at the joint. Specifically, the element body 11 extends along the axial direction of the wheel disc 4, and its structure includes but is not limited to a cuboid or a straight rod. Its cross-sectional shape is not limited, and it can also be an irregular shape in addition to a rectangle and a circle.

[0046] The utility model is beneficial in that, on the one hand, through the contact between the damping element 1 and the edge plate 31, a part of the vibration of the blade 3 is absorbed, and a part of the vibration is transmitted back to the wheel disc 4, and the dry friction damping is used to consume and diffuse the vibration energy, so that the transient vibration response is rapidly attenuated, the vibration amplitude of the blade 3 is reduced, and the high-cycle fatigue life of the blade 3 is improved; on the other hand, the cooling air 511 from the cold side 51 enters the hot side 52 through the cold air channel 12 and the gap at the joint of two adjacent edge plates 31, so that the cooling air 511 covers the edge area adjacent to the edge plate 31 and the damping element 1, forming a layer of air film, so as to avoid the high-temperature combustion gas directly scouring the edge of the edge plate 31 and causing ablation of the blade 3, thereby playing a cooling and protective role for the blade 3.

[0047] like Figure 3-7 As shown, in the first embodiment of the present invention, the plurality of cold air channels 12 are a plurality of through holes 122 arranged in the component body 11 at intervals along the length direction of the component body 11. The cooling air 511 from the cold side 51 can enter the hot side 52 through the through holes 122 and the gap between the two edge plates 31, covering the edge area adjacent to the edge plate 31 and the component body 11. Preferably, there is a certain angle between the extension direction of the through hole 122 and the length direction of the component body 11, that is, the extension direction of the through hole 122 and the length direction of the component body 11 are not perpendicular to each other. Such an arrangement helps to change the flow direction of the cooling air 511, so that the cooling air 511 can better fit the outer wall of the edge plate 31 after flowing out of the component body 11, thereby protecting the edge plate 31 from overheating.

[0048] like Figure 8 As shown, in the second embodiment of the utility model, the plurality of cold air channels 12 are a plurality of cold air grooves 121 arranged on the outer wall of the component body 11 at intervals along the length direction of the component body 11. The cold air grooves 121 are curved. In addition to being able to introduce the cooling air 511 from the cold side 51 to the hot side 52, the cooling air 511 can also flow to the two edge plates 31 respectively.

[0049] like Figure 1-3As shown, the turbine blade damping device provided by the utility model also includes a baffle 2 arranged between the end of the element body 11 and the wheel disc 4, and the baffle 2 is used to prevent the cold air 511 from leaking outward through the gap between the two adjacent blade roots 33 and the wheel disc 4. Its shape matches the shape of the gap between the two adjacent blade roots 33 and the wheel disc 4. Specifically, an assembly groove 111 is respectively provided at both ends of the element body 11, and a wheel disc groove 41 is respectively provided on both sides of the wheel disc 4. The assembly groove 111 and the wheel disc groove 41 are arranged oppositely, and the baffle 2 is arranged between the assembly groove 111 and the wheel disc groove 41 on the same side. The spacing d1 between the two assembly grooves 111 is equal to the spacing d2 between the two wheel disc grooves 41, and the groove width of the assembly groove 111 and the wheel disc groove 41 is greater than or equal to the thickness of the baffle 2. During installation, the baffle 2 is first placed in the wheel groove 41, and then the assembly groove 111 of the element body 11 is matched with the baffle 2. At this time, the element body 11 is in contact with the two edge plates 31, and the element body 11 is thus fixed. This arrangement can prevent the element body 11 and the baffle 2 from slipping during installation or operation, and ensure the stability of the structure.

[0050] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and substitutions can be made without departing from the technical principles of the present invention. These improvements and substitutions should also be regarded as the protection scope of the present invention.

Claims

1. A turbine blade damping device, wherein the turbine wheel comprises a wheel disc and a plurality of blades mounted on the wheel disc, each blade comprises an edge plate, a blade body and a blade root arranged on opposite sides of the edge plate, the blade root is mounted on the wheel disc, and a plurality of the edge plates are spliced ​​together to form a complete ring, characterized in that: It includes a damping element, which includes an element body and a plurality of cold air channels arranged on the element body at intervals along the length direction of the element body. The element body is arranged below the joint of two adjacent edge plates and abuts against the two edge plates. The cold air channel includes an inlet close to the wheel disc and an outlet directly below the joint.

2. The turbine blade damping device according to claim 1, characterized in that: The element body extends along the axial direction of the wheel disc.

3. The turbine blade damping device according to claim 1, characterized in that: The plurality of cold air channels are a plurality of cold air grooves arranged at intervals on the outer wall of the element body.

4. The turbine blade damping device according to claim 1, characterized in that: The plurality of cold air passages are a plurality of through holes arranged at intervals in the element body.

5. The turbine blade damping device according to claim 4, characterized in that: An angle is formed between the extending direction of the through hole and the length direction of the component body.

6. The turbine blade damping device according to claim 1, characterized in that: Also included is a baffle disposed between the end of the element body and the wheel disc.

7. The turbine blade damping device according to claim 6, characterized in that: An assembly groove is provided at the end of the element body, a wheel disc groove is provided on the wheel disc, the assembly groove and the wheel disc groove are arranged opposite to each other, and the baffle is arranged between the assembly groove and the wheel disc groove.

8. A turbine wheel, characterized in that: Comprising a turbine blade damping device as claimed in any one of claims 1 to 7.

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