Deflector anti-shake stabilizing structure for turbine blade

Abstract

The flow deflector anti-shake stabilizing structure for the turbine blade comprises a base, a connecting shaft is arranged at the top of the base, the top of the base is connected with a main flow deflector through a connecting shaft bearing, and the outer wall of the main flow deflector is connected with a spring compression rod through a bearing. The other end of the spring compression rod is in bearing connection with a pressure dividing piece, a clamping groove is formed in the top of the base, and an anti-deviation assembly is connected into the clamping groove in a clamped mode. According to the flow deflector anti-shake stabilizing structure for the turbine blade, the flow deflector is designed to be in a specific shape and angle, the main flow deflector and the pressure dividing plate are independently installed for flow dividing design so as to optimize the flowing path of airflow, the impact force of the airflow on the blade can be effectively reduced, and therefore vibration is reduced, and the service life of the blade is prolonged. And meanwhile, the distance between the main flow guide piece and the pressure dividing piece is adjusted according to the flow through the spring compression rod, and therefore the flow guide pressure of the turbine blade is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of turbine blades, in particular to an anti-vibration and stable structure of a guide vane for a turbine blade. Background Technique

[0002] In the utility model patent application with the application publication number CN112459852B, the application publication date of September 24, 2021, and the name of "A Double-Deflector Rib Deflection Structure Applied to the Trailing Edge Half-Slit of a Turbine Blade", the present invention relates to a double-deflector rib deflection structure and a deflection method applied to the trailing edge half-slit of a turbine blade. The structure includes a blade trailing edge pressure surface, a blade trailing edge suction surface, a trailing edge half-slit wall surface, a downstream wall surface of the slit, a dividing rib, and double deflector ribs. After cutting off a part of the wall surface near the trailing edge of the turbine blade pressure surface, multiple trailing edge half-slit structures are formed with the dividing rib. After the cooling gas flows out from the outlet, a cooling gas film is formed on the half-slit wall surface and the downstream wall surface to isolate the high-temperature mainstream gas and reduce the wall temperature. By arranging the double deflector ribs on the downstream wall surface of the half-slit to generate a turbulent flow effect on the cooling gas film, the uneven distribution of the gas film downstream of the half-slit is significantly weakened, the spanwise coverage effect and cooling efficiency of the cooling gas film are improved, and the reduction of the highest temperature and temperature gradient at the trailing edge is realized. The present invention arranges a double-deflector rib structure on the downstream wall surface of the half-slit, which has the characteristics of simple structure, convenient processing, and good cooling effect, and can be applied to various trailing edge half-slit structures of turbine blades.

[0003] In the prior art including the above patents, turbine blades play a crucial role in turbine engines. In order to improve efficiency and performance, the blades need to have excellent aerodynamic characteristics. However, in actual operation, they are often affected by various vibrations, such as air flow disturbances, centrifugal forces, and thermal stresses. These vibrations can cause fatigue and wear of the blades, and even failure. Therefore, it is very necessary to design an effective anti-vibration and stable structure. Content of the Utility Model

[0004] The purpose of the present utility model is to provide an anti-vibration and stable structure of a guide vane for a turbine blade to solve the problems of pressure division and correction of the jitter position mentioned in the above background technique.

[0005] To achieve the above purpose, the present utility model provides the following technical solution: An anti-vibration and stable structure of a guide vane for a turbine blade, including a base. A connecting shaft is arranged at the top of the base. The top of the base is connected to a main guide vane through a connecting shaft bearing. The outer wall of the main guide vane is connected to a spring compression rod through a bearing. The other end of the spring compression rod is connected to a pressure dividing piece through a bearing. A clamping groove is arranged at the top of the base, and an anti-offset component is clamped and connected inside the clamping groove.

[0006] Inside the anti-offset component, there are a clamping block, a spiral correction rod, a movable cylinder, and a correction traction rope. The clamping block is fitted and connected inside the clamping groove. The top of the clamping block is connected by a bearing to the spiral correction rod. The outer wall of the spiral correction rod is threadedly connected to the movable cylinder. The outer wall of the movable cylinder is fixedly connected to the correction traction rope.

[0007] Further, the anti-offset components are symmetric with each other along the central axis of the base, and the correction traction ropes cross and penetrate through the main flow guide vane. There are several groups of anti-offset components.

[0008] Further, the main flow guide vane is an arc-shaped flow guide vane, and the pressure dividing vane is an S-shaped pressure dividing vane. The tangent line of the arc point of the main flow guide vane is parallel to the tangent line of the arc point of the pressure dividing vane.

[0009] Further, the clamping groove and the clamping block are directly fitted with each other, and the number of clamping grooves is the same as the number of clamping blocks.

[0010] Further, both ends of the spring compression rod are provided with rotating shafts. The spring compression rod is connected to the main flow guide vane and the pressure dividing vane at both ends through the rotating shafts. There are several spring compression rods between the main flow guide vane and the pressure dividing vane.

[0011] Further, the connecting shaft is located at the center of the base, and the main flow guide vane is located above the central line of the base.

[0012] Compared with the prior art, the beneficial effects of the present utility model are as follows: The anti-vibration and stability structure of the flow guide vane for a turbine blade is reasonable and has the following advantages:

[0013] (1) By designing the flow guide vane into a specific shape and angle, and separately installing the main flow guide vane and the pressure dividing vane for a flow splitting design to optimize the flow path of the air flow. While expanding the contact area for cooling, they can also effectively reduce the impact force of the air flow on the blade, thereby reducing vibration. At the same time, the spring compression rod is used to adjust the distance between the main flow guide vane and the pressure dividing vane according to the flow rate, thereby reducing the pressure of the flow guiding of the turbine blade itself;

[0014] (2) By using the anti-offset component to guide and stabilize the main flow guide vane, the aerodynamic load fluctuation affecting the blade is reduced, thereby effectively reducing the vibration amplitude of the blade. At the same time, when the main flow guide vane is displaced, the movable spiral correction rod can be used to adjust the position of the main flow guide vane. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 is a schematic diagram of the overall structure of the present utility model;

[0016] Figure 2 is a side sectional view of the present utility model;

[0017] Figure 3Schematic diagram of the connection structure between the spring telescopic rod and the main deflector of the present utility model;

[0018] Figure 4 Schematic diagram of the anti-offset component structure of the present utility model;

[0019] Figure 5 Schematic diagram of the connection structure between the spiral correction rod and the movable cylinder of the present utility model.

[0020] In the figure: 1, base; 2, connecting shaft; 3, main deflector; 4, spring compression rod; 5, pressure dividing plate; 6, card slot; 7, anti-offset component; 701, clamping block; 702, spiral correction rod; 703, movable cylinder; 704, correction traction rope. Specific implementation mode

[0021] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all of the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0022] Please refer to Figures 1-5 , a technical solution provided by the present utility model:

[0023] Embodiment 1:

[0024] An anti-vibration and stability structure for a deflector of a turbine blade, including a base 1. A connecting shaft 2 is arranged at the top of the base 1. The main deflector 3 is connected to the top of the base 1 through the connecting shaft 2 by bearings. The outer wall of the main deflector 3 is connected to a spring compression rod 4 by bearings. The other end of the spring compression rod 4 is connected to a pressure dividing plate 5 by bearings. A card slot 6 is arranged at the top of the base 1. An anti-offset component 7 is snap-fitted inside the card slot 6.

[0025] The above structure adjusts the distance between the main deflector 3 and the pressure dividing plate 5 according to the flow rate by using the spring compression rod 4, thereby reducing the pressure of the deflector of the turbine blade itself.

[0026] The inside of the anti-offset component 7 includes a clamping block 701, a spiral correction rod 702, a movable cylinder 703 and a correction traction rope 704. The clamping block 701 is fitted inside the card slot 6. The top of the clamping block 701 is connected to the spiral correction rod 702 by bearings. The outer wall of the spiral correction rod 702 is threadedly connected to the movable cylinder 703. The outer wall of the movable cylinder 703 is fixedly connected to the correction traction rope 704.

[0027] The above structure reduces the aerodynamic load fluctuations affecting the blades by utilizing the anti-deviation component 7 to guide and stabilize the main flow blade 3, thereby effectively reducing the vibration amplitude of the blades. At the same time, when the main flow blade 3 is shifted, the movable spiral correction rod 702 is used to adjust the position of the main flow blade 3.

[0028] Furthermore, a plurality of anti-deviation components 7 are aligned with each other along the central axis of the base 1 , and the correction traction rope 704 crosses and penetrates the main flow sheet 3 .

[0029] The above structure pulls both sides through the correction traction rope 704, so as to pull and correct the main flow blade 3.

[0030] Furthermore, the main guide plate 3 is an arc-shaped guide plate, and the pressure divider plate 5 is an S-shaped pressure divider plate, and the arc point tangent of the main guide plate 3 is parallel to the arc point tangent of the pressure divider plate 5, the card slot 6 and the card block 701 are directly engaged with each other, and the number of the card slots 6 is consistent with the number of the card blocks 701.

[0031] The above structure controls the flow rate through the distance between the main flow plate 3 and the pressure divider plate 5, and at the same time improves the coverage of the cooling air film in the extension direction. The S-type has a wider coverage area at the same plane position and a better cooling effect.

[0032] Furthermore, both ends of the spring compression rod 4 are provided with a rotating shaft, and a plurality of spring compression rods 4 are connected to the main flow plate 3 and the pressure dividing plate 5 at both ends through the rotating shaft. The connecting shaft 2 is located at the center position of the base 1, and the main flow plate 3 is located above the midline of the base 1.

[0033] The above structure is designed with a central axis to facilitate subsequent correction.

[0034] Working principle: When in use, firstly, by utilizing the guide vane designed into a specific shape and angle, and separately installing the main guide vane 3 and the pressure divider 5 for diversion design, the flow path of the airflow is optimized, which can effectively reduce the impact force of the airflow on the blades, thereby reducing vibration;

[0035] Secondly, the distance between the main flow plate 3 and the pressure dividing plate 5 is adjusted according to the flow rate by using the spring compression rod 4. When the flow rate is large, the spring compression rod 4 will be stretched open by the flow pressure, thereby increasing the flow rate. When the flow rate is small, the pressure dividing plate 5 is close to the main flow plate 3 to reduce the flow rate, thereby reducing the pressure of the turbine blade itself.

[0036] Finally, by using the anti-offset component 7 to guide and stabilize the main flow guide vane 3, the aerodynamic load fluctuation affecting the blade is reduced, thereby effectively reducing the vibration amplitude of the blade. At the same time, when the main flow guide vane 3 is offset and displaced, the movable spiral correction rod 702 is used to adjust the position of the main flow guide vane 3, that is, by rotating the spiral correction rod 702, the movable cylinder 703 is made to move. Due to the direction limitation of the correction traction rope 704, the movable cylinder 703 moves along the spiral correction rod 702, so that the correction traction rope 704 can be straightened. In the straightened state, the main flow guide vane 3 is at the central axis position of the base 1.

[0037] For those skilled in the art, it is obvious that the present utility model is not limited to the details of the above exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or basic characteristics of the present utility model. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present utility model is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present utility model. Any reference signs in the claims should not be construed as limiting the claimed rights.

Claims

1. A flow deflector anti-vibration and stabilization structure for a turbine blade, comprising a base (1), characterized in that: A connecting shaft (2) is provided at the top of the base (1). The top of the base (1) is connected to a main flow deflector (3) by a bearing through the connecting shaft (2). The outer wall of the main flow deflector (3) is connected to a spring compression rod (4) by a bearing. The other end of the spring compression rod (4) is connected to a pressure dividing plate (5) by a bearing. A card slot (6) is provided at the top of the base (1), and an anti-offset component (7) is snap-fitted inside the card slot (6).

2. The anti-vibration and stability structure of the guide vane for a turbine blade according to claim 1, characterized in that: The inside of the anti-offset component (7) includes a clamping block (701), a spiral correction rod (702), a movable cylinder (703), and a correction traction rope (704). The clamping block (701) is fitted inside the card slot (6). The top of the clamping block (701) is connected to the spiral correction rod (702) by a bearing. The movable cylinder (703) is threadedly connected to the outer wall of the spiral correction rod (702). The correction traction rope (704) is fixedly connected to the outer wall of the movable cylinder (703).

3. A flow guiding vane anti-vibration and stabilization structure for a turbine blade according to claim 2, characterized in that: The anti-offset components (7) are symmetric with each other along the central axis of the base (1), and the correction traction ropes (704) cross through the main flow deflector (3).

4. A flow guiding vane anti-vibration and stability structure for a turbine blade according to claim 1, characterized in that: The main flow deflector (3) is an arc-shaped flow deflector, and the pressure dividing plate (5) is an S-shaped pressure dividing plate. The tangent line of the arc point of the main flow deflector (3) is parallel to the tangent line of the arc point of the pressure dividing plate (5).

5. A flow guiding vane anti-vibration and stabilization structure for a turbine blade according to claim 2, characterized in that: The card slot (6) and the clamping block (701) are directly fitted with each other, and the number of card slots (6) is the same as the number of clamping blocks (701).

6. The anti-vibration and stabilization structure of a deflector for a turbine blade according to claim 1, characterized in that: Rotating shafts are provided at both ends of the spring compression rod (4), and the spring compression rod (4) is connected to the main flow deflector (3) and the pressure dividing plate (5) at both ends through the rotating shafts.

7. The anti-vibration and stability structure of the guide vane for a turbine blade according to claim 1, characterized in that: The connecting shaft (2) is located at the center of the base (1), and the main flow deflector (3) is located above the center line of the base (1).

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