Blade structure with aerodynamic damping function in a turbomachine

Abstract

This utility model discloses a blade structure with aerodynamic damping function in turbomachinery, belonging to the technical field of blade structure technology. It includes a blade, a swing groove, a damping block, a connecting hole, and damping air holes. The swing groove is located at the root of the blade, and the blade has a matching connector for the turbomachinery. The connecting hole is located within the connector. The damping block includes a connecting part, a swing part, and a damping part, all made of elastic material. The connecting part is inserted into the connecting hole, and the damping part is located within the swing groove. The connecting part and the damping part are connected by the swinging part, and the top of the damping part is fixed to the top of the swing groove. Multiple damping air holes are provided through the blade at positions corresponding to the swing groove. This utility model dissipates energy through the elastic swing of the damping block and the damping air holes, without affecting the structural integrity of the overall impeller in the turbomachinery, and suppresses high-order modal vibrations.

Description

Technical Field

[0001] This utility model relates to a blade structure with aerodynamic damping function in turbomachinery, belonging to the field of blade structure technology. Background Technology

[0002] In the operating system of turbomachinery, the moving blades are the core components, and their operating status directly affects the performance and reliability of the entire machine. During operation, the moving blades are subjected to a combination of high centrifugal loads, aerodynamic loads, and alternating loads. Taking turbine blades in aero-engines as an example, when the engine is running at high speed, the blades not only endure enormous centrifugal forces but also face the scouring of high-temperature, high-pressure gas flow and alternating stresses caused by unstable airflow. This makes the moving blades one of the most vulnerable components in the entire turbomachinery system.

[0003] Among various blade failures, blade vibration failure accounts for a significant proportion. When the blade vibration amplitude is too large, it accelerates blade fatigue damage and can even lead to blade breakage, causing catastrophic consequences. To effectively reduce blade vibration failures, increasing blade damping and reducing aerodynamic excitation of the blade body have become two main countermeasures. Traditionally, increasing blade damping is mostly achieved by designing structural dampers on the blade or impeller. By increasing the damping of the blade unit, the blade amplitude is reduced, thereby enhancing the blade's vibration resistance.

[0004] Structural dampers are typically designed for the primary low-order modes. However, in actual blade flow fields, fluid excitation often induces higher-order mode vibrations, making structural dampers less effective at suppressing these vibrations. For example, in some transonic compressors, complex airflow can easily trigger higher-order mode vibrations in the blades, which traditional structural dampers struggle to address effectively. Secondly, for the integral bladed disk structure widely used in modern advanced turbomachinery, adding structural dampers significantly increases the complexity and cost of the manufacturing process. Integral bladed disks integrate the blades and disk to improve mechanical performance and reliability, but this also makes adding additional structural dampers extremely difficult, not only in terms of manufacturing complexity but also potentially affecting the structural integrity of the integral bladed disk. Utility Model Content

[0005] The purpose of this invention is to provide a blade structure with aerodynamic damping function in turbomachinery, which can suppress high-order modal vibrations without affecting the structural integrity of the overall impeller in turbomachinery.

[0006] To achieve the above objectives, this utility model employs the following technical solution:

[0007] This utility model provides a blade structure with aerodynamic damping function in turbomachinery, including: blade, swing groove, damping block, connecting hole and damping air hole;

[0008] The swing groove is located at the root of the blade, and the blade is provided with a connector for matching the impeller mechanism, with the connection hole located inside the connector.

[0009] The damping block includes a connecting part, a swinging part, and a damping part, all made of elastic material. The connecting part is inserted into a connecting hole, and the damping part is disposed in a swinging groove. The connecting part and the damping part are oscillatingly connected through the swinging part, and the top of the damping part is fixed to the top of the swinging groove.

[0010] Damping air holes are installed through the blade at positions corresponding to the swing grooves, and there are multiple damping air holes.

[0011] Furthermore, it also includes a support cable, with the head of the support cable fixed to the top of the swing groove and the tail of the support cable fixed to the bottom of the plug socket.

[0012] Furthermore, it also includes a counterweight, which is fitted onto the head of the supporting steel cable.

[0013] Furthermore, it also includes an adjusting sleeve, which is threadedly connected to the bottom of the plug-in base, and the tail of the support steel cable is fixed on the adjusting sleeve.

[0014] Furthermore, it also includes a limiting hole and a limiting block. The limiting hole is disposed in the adjusting sleeve, one end of the limiting block is embedded in the limiting hole, and the other end of the limiting block is fixed to the tail of the supporting steel cable.

[0015] Furthermore, the adjusting sleeve is also connected to the connecting hole.

[0016] Furthermore, a stepped hole is provided at the bottom of the connector, and the stepped hole communicates with the connection hole.

[0017] Furthermore, it also includes a limiting part, which is connected to the connecting part and makes limiting contact with the end face of the stepped hole.

[0018] Furthermore, it also includes an adapter sleeve, which is disposed on the inner wall of the stepped hole. The end of the adapter sleeve is provided with a limiting ring that contacts the end face of the stepped hole, and the limiting part is inserted into the adapter sleeve.

[0019] Furthermore, it also includes interference flaps, with the interference flap array positioned on the damping block at a location corresponding to the damping air holes.

[0020] Compared with the prior art, the beneficial effects achieved by this utility model are:

[0021] This invention provides a blade structure with aerodynamic damping function in turbomachinery. By setting an elastic damping block inside the blade, the airflow energy brought by the damping vent can be dynamically consumed through the elastic swing of the damping block, thereby reducing the vibration of the blade caused by the direct action of the airflow on the blade. At the same time, the damping block can eliminate the vibration brought by the blade through its own vibration. When the blade vibrates due to airflow excitation, the main airflow that causes the vibration at the bottom of the blade will pass through the damping vent and consume energy. The above-mentioned aerodynamic damping function is not based on a traditional structural damper, but on a combination of aerodynamic damper and structural damper. It does not affect the structural integrity of the overall blade disk in the turbomachinery and can suppress high-order modal vibrations. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of a blade structure with aerodynamic damping function in a turbomachinery provided by this utility model;

[0023] Figure 2 This is a schematic diagram of the impeller provided by this utility model.

[0024] In the diagram: 1. Impeller disk; 2. Impeller ring; 3. Blade; 4. Connector; 5. Connecting plate; 6. Connecting part; 7. Swinging part; 8. Damping part; 9. Bolt; 10. Support cable; 11. Counterweight; 12. Turbine; 13. Adapter sleeve; 14. Limiting part; 15. Connecting hole; 16. Adjusting sleeve; 17. Limiting block; 18. Damping air hole. Detailed Implementation

[0025] The present invention will be further described below with reference to the accompanying drawings. The following embodiments are only used to illustrate the technical solution of the present invention more clearly, and should not be used to limit the protection scope of the present invention.

[0026] In the description of the utility model, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the 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. Therefore, they should not be construed as limitations on the utility model. In addition, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, features defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of the utility model, unless otherwise stated, "a plurality of" means two or more.

[0027] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation", "connection", and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood through the specific circumstances.

[0028] Example 1

[0029] like Figure 1 As shown, the present invention provides a blade structure with aerodynamic damping function in a turbomachinery, comprising: blade 3, swing groove, damping block, connecting hole 15 and damping air hole 18.

[0030] The swing groove is set at the root of the blade 3, and the blade 3 is provided with a plug-in seat 4 that matches the impeller mechanism. The connection hole 15 is set in the plug-in seat 4.

[0031] The damping block includes a connecting part 6, a swinging part 7, and a damping part 8, all made of elastic material. The connecting part 6 is inserted into the connecting hole 15, and the damping part 8 is disposed in the swinging groove. The connecting part 6 and the damping part 8 are oscillatingly connected through the swinging part 7, and the top of the damping part 8 is fixed to the top of the swinging groove.

[0032] Damping air holes 18 are provided through the blade 3 at positions corresponding to the swing groove, and multiple damping air holes 18 are provided.

[0033] This invention, by setting an elastic damping block inside the blade 3, can dynamically consume the airflow energy brought by the damping vent 18 through the elastic swing of the damping block, thereby reducing the vibration of the blade 3 caused by the direct action of the airflow on the blade 3. At the same time, the damping block can eliminate the vibration brought by the blade 3 through its own vibration. When the blade 3 vibrates due to airflow excitation, the main airflow that brings vibration at the bottom of the blade 3 will pass through the damping vent 18 and consume energy. The realization of the above-mentioned aerodynamic damping function does not rely on the traditional structural damper, but on the combination of aerodynamic damper and structural damper. It will not affect the structural integrity of the overall blade disk in the turbomachinery, and can suppress high-order modal vibration.

[0034] Example 2

[0035] like Figure 1 As shown, the present invention provides a blade structure with aerodynamic damping function in turbomachinery, comprising:

[0036] A swing groove is provided at the root of the blade 3, and a connection hole 15 is provided in the plug-in seat 4 of the blade 3.

[0037] A damping block is provided in the root of the blade 3 through the connecting hole 15. The damping block includes a connecting part 6 inserted into the connecting hole 15 and a damping part 8 provided in the swing groove. The damping part 8 and the connecting part 6 are oscillatingly connected through the swing part 7. The top of the damping part 8 is fixed to the top of the swing groove. A counterweight 11 is provided in the damping part 8.

[0038] Several damping holes 18 are provided through the blade 3 at the position corresponding to the swing groove.

[0039] By setting an elastic damping block inside the blade 3, the airflow energy brought by the damping hole 18 can be dynamically consumed through the elastic swing of the damping block, thereby reducing the vibration of the blade 3 caused by the airflow directly acting on the blade 3. At the same time, the damping block can eliminate the vibration brought by the blade 3 through its own vibration.

[0040] A support steel cable 10 is installed inside the damping block. The head of the support steel cable 10 is fixed to the top of the swing groove, and the tail of the support steel cable 10 is fixed to the bottom of the plug-in seat 4. The support steel cable 10 can improve the strength of the damping block.

[0041] It also includes a counterweight 11 and an adjusting sleeve 16. The counterweight 11 is sleeved on the head of the support cable 10, and the adjusting sleeve 16 is threadedly connected to the bottom of the plug-in seat 4. The tail of the support cable 10 is fixed on the adjusting sleeve 16. The flange fixation has high stability.

[0042] A limiting hole is provided inside the adjusting sleeve 16, and a limiting block 17 is provided at the tail of the supporting steel cable 10, which is embedded in the limiting hole. The limiting block 17 has a simple structure and is more durable than welding fixation and one-piece manufacturing. It can rotate the adjusting sleeve 16 at will without falling off.

[0043] like Figure 2 As shown, the blades 3 are fixed to the impeller disk 1 in a ring array via the plug-in base 4. The impeller disk 1 has a connecting hole 15, and the adjusting sleeve 16 is threaded into the connecting hole 15. The threaded connection of the adjusting sleeve 16 into the recessed connecting hole 15 can reduce the thickness of the plug-in base 4 and optimize the structure.

[0044] The bottom of the connector 4 has a stepped hole that communicates with the connecting hole 15. A limiting part 14 is connected to the connecting part 6, and the limiting part 14 makes limiting contact with the end face of the stepped hole. The limiting structure can ensure that the damping block is stably connected to the connecting hole 15 and is not easy to come out of the connecting hole 15.

[0045] An adapter sleeve 13 is provided on the inner wall of the stepped hole. A limiting ring is provided at the end of the adapter sleeve 13, which contacts the end face of the stepped hole. The limiting part 14 is inserted into the adapter sleeve 13. The adapter sleeve 13 can reduce the friction between the damping block and the impeller and improve the service life of the damping hole.

[0046] Several disturbance vanes 12 are arrayed at the positions corresponding to the damping air holes 18 on the damping block. The disturbance vanes 12 can increase the disturbance of the high-speed airflow blown from the damping air holes 18 at the position of the damping block, stabilize the pressure drop, and reduce the vibration of the damping block.

[0047] During processing, a swing groove for embedding the damping hole is milled at the root of the blade 3, and a corresponding connecting hole 15 is machined in the insertion seat 4 of the blade 3. One end of the damping block is inserted into the connecting hole 15. The damping block is made of elastic material, and the limiting structure can also pass smoothly through the connecting hole 15. Then, the other end of the damping block is fixed to the top of the swing groove with bolts 9. Then, the blade 3 is installed between the impeller disk 1 and the impeller ring 2, and the top of the blade 3 is fixed to the impeller ring 2 with the connecting plate 5. At the same time, the counterweight 11 is welded to the head of the support steel cable 10 by lead welding, and the support steel cable 10 is fixed by adjusting the counterweight 11. The assembly of the entire blade structure can then be completed.

[0048] When the steam turbine (a type of turbomachinery) starts working, the blades 3 rotate at high speed. When the blades 3 vibrate due to airflow excitation, the main airflow that causes the vibration at the bottom of the blades 3 passes through the damping air hole 18, consuming energy, while the damping block plays its role. Since the damping part 8 and the connecting part 6 are oscillatingly connected by the swinging part 7, and the damping part 8 contains a counterweight 11, the damping block will swing with the vibration of the blades 3, further consuming the airflow energy, and consuming the vibration transmitted by the blades 3 themselves through its own elastic vibration.

[0049] High-speed airflow enters the swing groove through damping vent 18 and interacts with the damping block. The turbulence plate 12 increases the disturbance of the airflow at the position of the damping block, smooths the airflow pressure drop, and reduces the vibration of the damping block.

[0050] The supporting steel cable 10 enhances the strength of the damping block, ensuring its stability under high-speed rotation and vibration conditions. The adjusting sleeve 16 can be adjusted in position via a threaded connection to adapt to different working conditions. The structural design of the limiting block 17 and the limiting part 14 ensures a stable connection between the damping block and the blade 3 and impeller disk 1, preventing the damping block from coming off.

[0051] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.

Claims

1. A blade structure with aerodynamic damping function in turbomachinery, characterized in that, include: Blades, swing grooves, damping blocks, connecting holes, and damping air vents; The swing groove is located at the root of the blade, and the blade is provided with a connector for matching the impeller mechanism, with the connection hole located inside the connector. The damping block includes a connecting part, a swinging part, and a damping part, all made of elastic material. The connecting part is inserted into a connecting hole, and the damping part is disposed in a swinging groove. The connecting part and the damping part are oscillatingly connected through the swinging part, and the top of the damping part is fixed to the top of the swinging groove. Damping air holes are installed through the blade at positions corresponding to the swing grooves, and there are multiple damping air holes.

2. The blade structure with aerodynamic damping function in turbomachinery according to claim 1, characterized in that, It also includes a support cable, with the head of the support cable fixed to the top of the swing groove and the tail of the support cable fixed to the bottom of the plug socket.

3. The blade structure with aerodynamic damping function in turbomachinery according to claim 2, characterized in that, It also includes a counterweight, which is fitted onto the head of the supporting steel cable.

4. The blade structure with aerodynamic damping function in turbomachinery according to claim 2, characterized in that, It also includes an adjustment sleeve, which is threadedly connected to the bottom of the plug-in base, and the tail of the support steel cable is fixed on the adjustment sleeve.

5. The blade structure with aerodynamic damping function in turbomachinery according to claim 4, characterized in that, It also includes a limiting hole and a limiting block. The limiting hole is disposed in the adjusting sleeve, one end of the limiting block is embedded in the limiting hole, and the other end of the limiting block is fixed to the tail of the supporting steel cable.

6. The blade structure with aerodynamic damping function in turbomachinery according to claim 4, characterized in that, The adjusting sleeve is also connected to the connecting hole.

7. The blade structure with aerodynamic damping function in turbomachinery according to claim 1, characterized in that, The bottom of the connector has a stepped hole, which is connected to the connection hole.

8. The blade structure with aerodynamic damping function in turbomachinery according to claim 7, characterized in that, It also includes a limiting part, which is connected to the connecting part, and the limiting part and the end face of the stepped hole make limiting contact.

9. The blade structure with aerodynamic damping function in turbomachinery according to claim 7, characterized in that, It also includes an adapter sleeve, which is disposed on the inner wall of the stepped hole. The end of the adapter sleeve is provided with a limiting part that contacts the end face of the stepped hole, and the limiting part is inserted into the adapter sleeve.

10. The blade structure with aerodynamic damping function in turbomachinery according to claim 1, characterized in that, It also includes interference flaps, and the interference flap array is set on the damping block at the position corresponding to the damping air hole.

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