A turbine blade vibration reduction and interstage sealing device for an aero turboshaft engine

Abstract

The utility model provides a kind of turbine blade vibration reduction and stage-to-stage sealing device for aviation turboshaft engine, including turbine disc and turbine blade main body, the turbine disc side detachably connected with multiple turbine blade main body of annular array distribution;Damping sealing sheet, damping sealing sheet is arranged between the turbine disc and turbine blade main body, and damping sealing sheet is used for the damping and stage-to-stage sealing of aviation turboshaft engine turbine blade.The utility model whole simple structure, high integration, low in cost, by damping sealing sheet is endowed with two big functions of damping and sealing with a single part simultaneously, save the complex damper and additional sealing structure, compact structure, extremely light, almost not increase the additional burden of rotor system;Its damping force is directly derived from rotational speed (centrifugal force), and it is adaptively matched with working condition, and the higher the rotational speed, the greater the centrifugal force, and the better the damping positive pressure and sealing effect.

Description

Technical Field

[0001] This utility model relates to the field of engines, and in particular to a turbine blade vibration reduction and interstage sealing device for aero-turbo shaft engines. Background Technology

[0002] A turboshaft engine, also known simply as a turboshaft engine, is a type of turbojet engine that outputs shaft power and is specifically designed for helicopters and special-purpose aircraft. Its core principle involves converting the chemical energy of fuel into high-temperature, high-pressure gas through a gas generator, which drives a turbine to rotate, ultimately powering the helicopter's rotor and tail rotor via the output shaft.

[0003] Turboshaft engines are the core power unit of modern helicopters, operating in extreme environments and requiring extremely high reliability and lifespan. Turbine rotor components, especially the high-temperature turbine section, are subjected to harsh conditions of high speed, high temperature, and high stress for extended periods.

[0004] During engine operation, the high-speed rotation of the rotor generates enormous centrifugal force, while airflow excitation induces complex vibrations in the blades. Among these, inter-blade vibration (i.e., the vibration mode of relative misalignment between adjacent blades) is a common and highly detrimental form of vibration. This vibration leads to high-cycle fatigue at the blade root, which is one of the main causes of turbine blade failure and seriously threatens the safe operation of the engine.

[0005] Furthermore, a gap inevitably exists between the rims of adjacent blades. High-temperature combustion gases can leak into the turbine disk chamber through this gap. This not only causes energy loss and reduces engine efficiency but also leads to localized overheating of the turbine disk, affecting its structural integrity and service life. Currently, separate sealing structures (such as grate seals) are typically used to seal the disk chamber, but this increases the complexity and weight of the system. Utility Model Content

[0006] The technical problem to be solved by this utility model is to overcome the defects of existing technology, such as the difficulty in suppressing inter-stage vibration and poor interstage sealing performance, and to provide a turbine blade vibration reduction and interstage sealing device for aero-turbo shaft engines.

[0007] The present invention solves the above-mentioned technical problems through the following technical solution:

[0008] This utility model provides a turbine blade vibration reduction and interstage sealing device for aero-turbo shaft engines, including a turbine disk and a turbine blade body, wherein multiple turbine blade bodies arranged in a ring array are detachably connected to the side of the turbine disk.

[0009] Vibration damping sealing plates are provided between the turbine disk and the turbine blade body. The vibration damping sealing plates are used for vibration damping and interstage sealing of turbine blades in aero-turbo shaft engines.

[0010] In this technical solution, the vibration damping sealing plate uses the centrifugal force of the rotor itself as the source of positive pressure. When inter-blade vibration occurs, it generates micro-slippage and friction with the bottom surface of the blade edge plate, converting harmful vibration energy into heat energy and dissipating it, thereby significantly reducing the vibration stress level of the blade and improving its resistance to high-cycle fatigue.

[0011] Meanwhile, the shoe-shaped design of the vibration damping sealing plate allows it to cover and block the gaps between adjacent blade rims to the maximum extent under centrifugal force, greatly reducing the leakage of high-temperature gas, improving turbine efficiency, and effectively reducing the operating temperature of the turbine disk.

[0012] Preferably, the turbine blade body includes a blade root tenon and a blade plate, the blade root tenon and the blade plate are connected to each other, and the side of the blade root tenon away from the blade plate is detachably connected to the side of the turbine disk.

[0013] Preferably, the turbine disk has multiple mounting tenons arranged in a ring array on its side, and the tenon at the root of the blade engages with the mounting tenons to mount the turbine blade body to the side of the turbine disk.

[0014] In this technical solution, the fit between the blade root tenon and the mounting mortise facilitates the installation of the turbine blade body onto the turbine disk.

[0015] Preferably, the turbine blade body further includes a blade rim plate, and blade rim plates are connected to both sides of the connection between the blade root tenon and the blade rim plate, with the blade rim plates of two adjacent turbine blade bodies close to each other.

[0016] In this technical solution, blade rim plates are used to increase the stability of the turbine blade body during installation.

[0017] Preferably, the vibration damping sealing plate is positioned between the blade rim and the turbine disk.

[0018] In this technical solution, the turbine blades can be damped and sealed by the vibration damping sealing plate. The structure is simple, highly integrated, and low in cost.

[0019] Preferably, the vibration damping sealing sheet includes a base plate and an inclined wall plate, the base plate and the inclined wall plate being connected to each other.

[0020] Preferably, the overall outline of the vibration damping sealing sheet is in the shape of a "shoe", the substrate is the "shoe sole", and the inclined wall panel is the "shoe upper".

[0021] Preferably, the substrate conforms to the profile of the bottom of the blade edge plate, and the substrate is used to cover most of the gap between adjacent blade edge plates.

[0022] In this technical solution, the substrate can conform to the shape of the bottom of the blade edge plate and form a large-area contact with it under the action of centrifugal force, ensuring that it can effectively block most of the gaps between adjacent blade edge plates.

[0023] Preferably, the inclined wall panel is a plate-like structure that bends upward from both sides of the substrate.

[0024] In this technical solution, the design of the sloping wall panel ensures that its position in the workspace does not shift significantly.

[0025] Preferably, a damping component is provided in the gap between the turbine disk and the turbine blade body. The damping component includes a damping block, and the damping block has a plurality of first heat dissipation holes and second heat dissipation holes.

[0026] In this technical solution, the gap between the turbine disk and the turbine blade body can be filled by the sealing component, so as to achieve the purpose of vibration reduction and sealing, without affecting the heat dissipation between the turbine disk and the turbine blade body.

[0027] Based on common knowledge in the field, the above-mentioned preferred conditions can be combined arbitrarily to obtain various preferred embodiments of this utility model.

[0028] The positive and progressive effects of this utility model are as follows:

[0029] This utility model of vibration damping sealing plate utilizes the centrifugal force of the rotor itself as the source of positive pressure. When inter-blade vibration occurs, it generates micro-slippage and friction with the bottom surface of the blade edge plate, converting harmful vibration energy into heat energy and dissipating it, thereby significantly reducing the vibration stress level of the blade and improving its resistance to high-cycle fatigue.

[0030] Meanwhile, the shoe-shaped design of the vibration damping sealing plate allows it to cover and block the gaps between adjacent blade rims to the maximum extent under centrifugal force, greatly reducing the leakage of high-temperature combustion gas, improving turbine efficiency, and effectively reducing the operating temperature of the turbine disk.

[0031] The overall structure is simple, highly integrated, and low in cost. By using a vibration damping and sealing plate, a single part is given both vibration damping and sealing functions, eliminating the need for complex dampers and additional sealing structures. The structure is compact, extremely lightweight, and adds almost no extra burden to the rotor system.

[0032] Furthermore, its damping force comes directly from the rotational speed (centrifugal force), which is adaptively matched with the operating conditions. The higher the rotational speed, the greater the centrifugal force, and the better the damping positive pressure and sealing effect. This perfectly matches the actual working requirements of the engine. As a passive device, it does not require external operation or control, and has strong adaptability and high reliability. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of the structure of a turbine blade vibration reduction and interstage sealing device for an aero-turbo engine according to an embodiment of the present invention.

[0034] Figure 2 for Figure 1 The diagram shows a three-dimensional structure of a vibration damping sealing plate used in turbine blade vibration reduction and interstage sealing devices for aircraft turboshaft engines.

[0035] Figure 3 for Figure 1 The diagram shows a cross-sectional view of the vibration damping sealing plate used in a turbine blade vibration reduction and interstage sealing device for an aero-turboshaft engine.

[0036] Figure 4 for Figure 1 The diagram shown is a side view of the turbine blade assembly in the turbine blade vibration reduction and interstage sealing device for aero-turbo engines.

[0037] Figure 5 for Figure 4 The diagram shows a cross-sectional view of section AA of a turbine blade vibration reduction and interstage sealing device used in aero-turbo shaft engines.

[0038] Figure 6 for Figure 1 The diagram shows a cross-sectional view of the connection between the turbine disk, turbine blade body, vibration damping sealing plate, and mounting tenon in a turbine blade vibration damping and interstage sealing device for an aero-turbo shaft engine.

[0039] Figure 7 for Figure 1 The diagram shows a cross-sectional view of the connection between the turbine disk, turbine blade body, damping assembly, and mounting tenon in a turbine blade vibration reduction and interstage sealing device for an aero-turbo engine.

[0040] Figure 8 for Figure 7 The diagram shows a three-dimensional structural schematic of a damping and sealing component for a turbine blade vibration reduction and interstage sealing device used in aero-turboshaft engines.

[0041] Explanation of reference numerals in the attached figures

[0042] 1. Turbine disk;

[0043] 2. Turbine blade body; 21. Blade root tenon; 22. Blade plate; 23. Blade rim plate;

[0044] 3. Vibration damping sealing sheet; 31. Substrate; 32. Sloping wall panel;

[0045] 4. Install the tenon and mortise;

[0046] 5. Sealing reduction component; 51. Damping sealing reduction block; 52. First heat dissipation hole; 53. Second heat dissipation hole. Detailed Implementation

[0047] The present invention will be further described below by way of embodiments, but the present invention is not limited to the scope of the embodiments described herein.

[0048] Figures 1 to 8 The diagram shown is a structural schematic of an embodiment of the present invention for a turbine blade vibration reduction and interstage sealing device for an aero-turbo engine.

[0049] Example 1

[0050] like Figures 1 to 6 As shown, the turbine blade vibration reduction and interstage sealing device for aero-turbo shaft engines includes a turbine disk 1 and a turbine blade body 2. Multiple turbine blade bodies 2 arranged in a ring array are detachably connected to the side of the turbine disk 1.

[0051] Vibration damping sealing plate 3 is provided between the turbine disk 1 and the turbine blade body 2. The vibration damping sealing plate 3 is used for vibration damping and interstage sealing of the turbine blades of the aero-turbo shaft engine.

[0052] In this technical solution, the vibration damping sealing plate 3 uses the centrifugal force of the rotor itself as the source of positive pressure. When inter-blade vibration occurs, it generates micro-slippage and friction with the bottom surface of the blade edge plate 23, converting harmful vibration energy into heat energy and dissipating it, thereby significantly reducing the vibration stress level of the blade and improving its resistance to high-cycle fatigue.

[0053] Meanwhile, the shoe-shaped design of the vibration damping sealing plate 3 allows it to cover and block the gaps between adjacent blade edge plates 23 to the maximum extent under centrifugal force, greatly reducing the leakage of high-temperature gas, improving turbine efficiency, and effectively reducing the operating temperature of turbine disk 1.

[0054] The overall structure is simple, highly integrated, and low in cost. By using the vibration damping and sealing plate 3, a single part is given both vibration damping and sealing functions, eliminating the need for complex dampers and additional sealing structures. The structure is compact, extremely lightweight, and adds almost no extra burden to the rotor system.

[0055] Furthermore, its damping force originates directly from the centrifugal force of the engine speed, adaptively matching the operating conditions. The higher the engine speed, the greater the centrifugal force, resulting in better damping normal pressure and sealing effect. This perfectly matches the actual working requirements of the engine. As a passive device, it requires no external actuation or control, exhibiting strong adaptability and high reliability.

[0056] The turbine blade body 2 includes a blade root tenon 21 and a blade plate 22. The blade root tenon 21 and the blade plate 22 are connected to each other. The side of the blade root tenon 21 away from the blade plate 22 is detachably connected to the side of the turbine disk 1.

[0057] The turbine disk 1 has multiple mounting tenons 4 arranged in a ring array on its side. The blade root tenon 21 cooperates with the mounting tenon 4 to install the turbine blade body 2 onto the side of the turbine disk 1.

[0058] In this technical solution, the fit between the blade root tenon 21 and the mounting tenon 4 facilitates the installation of the turbine blade body 2 onto the turbine disk 1.

[0059] The turbine blade body 2 also includes blade edge plates 23. Blade edge plates 23 are connected to both sides of the connection between the blade root tenon 21 and the blade plate 22. The blade edge plates 23 of two adjacent turbine blade bodies 2 are close to each other.

[0060] In this technical solution, the blade edge plate 23 is used to increase the stability of the turbine blade body 2 during installation.

[0061] The vibration damping sealing plate 3 is positioned between the blade edge plate 23 and the turbine disk 1.

[0062] In this technical solution, the turbine blades can be damped and sealed by the vibration damping and sealing plate 3. The structure is simple, highly integrated, and low in cost.

[0063] The vibration damping sealing plate 3 includes a base plate 31 and an inclined wall plate 32, which are connected to each other.

[0064] The overall outline of the vibration damping sealing plate 3 is shaped like a "shoe", the base plate 31 is the "shoe sole", and the inclined wall plate 32 is the "shoe upper".

[0065] The substrate 31 conforms to the profile of the bottom of the blade edge plate 23, and the substrate 31 is used to cover most of the gap between adjacent blade edge plates 23.

[0066] In this technical solution, the substrate 31 can conform to the shape of the bottom of the blade edge plate 23 and form a large-area contact with it under the action of centrifugal force, ensuring that it can effectively block most of the gaps between adjacent blade edge plates 23.

[0067] The inclined wall panel 32 is a plate-like structure that extends upward from both sides of the substrate 31.

[0068] In this technical solution, the design of the inclined wall panel 32 ensures that its position in the workspace does not shift significantly.

[0069] The presence of the vibration damping sealing plate 3 provides a "shoe-shaped" thin plate structure that integrates vibration damping and sealing functions, and it is cleverly arranged in the narrow space formed by the bottom of the blade edge plate and the surface of the turbine disk.

[0070] This application breaks with the traditional approach of separating vibration reduction and sealing, creatively placing a single component in the underutilized space below the blade rim and above the turbine disk.

[0071] Its vibration reduction principle is that when the rotor rotates, the vibration damping sealing plate 3 is "thrown" towards the outer diameter of the turbine disk by centrifugal force, and its base plate 31 is pressed tightly against the bottom of the edge plate of two adjacent blades; when the blades vibrate between blades and move closer or further away from each other, they will have relative micro-slippage with the pressed vibration damping sealing plate 3, generating dry friction and forming friction damping, thereby consuming vibration energy.

[0072] Its sealing principle is that, under the action of centrifugal force, part of the substrate 31 acts like a "curtain" or "baffle", moving upward and covering the gap under the blade edge plate, forming a physical barrier that blocks the main leakage path of the gas.

[0073] In this application, the inherent centrifugal force is used as the sole driving force to achieve the two major functions of compression and vibration reduction and upward sealing. There is no need for external pre-tightening devices such as springs and hydraulic systems. This achieves a completely passive adaptive adjustment that is positively correlated with the engine speed. As the engine speed increases, the centrifugal force increases, and the vibration reduction and sealing effects are enhanced simultaneously. This is highly compatible with the working characteristics of the engine.

[0074] Furthermore, wear-resistant materials such as MCrAlY alloy or ceramic materials can be sprayed or inlaid on the contact surface between the vibration damping sealing plate 3 and the blade edge plate 23. This not only protects the expensive blades but also maintains a stable coefficient of friction during long-term operation, ensuring the durability of the damping effect.

[0075] The vibration damping sealing plate 3 is preferably made of GH3536 high-temperature alloy. GH3536 is a solid solution strengthened nickel-based high-temperature alloy with a long-term service temperature of up to 1100℃ and a short-term withstand temperature of up to 1150℃. This alloy exhibits excellent oxidation resistance, corrosion resistance (including resistance to sulfur, chlorine, nitrogen, and oxygen media corrosion), and good hot working properties at high temperatures. Its typical chemical composition by mass percentage is as follows: Ni 47.5–53%, Cr 20–23%, Fe 17–20%, Mo 8–10%, Co ≤1.0%, C ≤0.05%, with the remainder being trace elements. This material is not prone to embrittlement or cracking under high-temperature and high-pressure alternating conditions, and its density is approximately 8.3 g / cm³. 3 These characteristics make it ideal for the working environment of hot-end components in engines.

[0076] The vibration damping sealing plate 3 is mainly manufactured by stamping, and the steps are as follows:

[0077] Step 1: Raw material preparation. GH3536 high-temperature alloy cold-rolled sheet with a thickness of 0.3mm is selected as the raw material. This thickness can ensure that the sealing sheet has sufficient structural strength and wear resistance while maintaining its flexibility to adapt to small vibration displacements.

[0078] Step 2: Mold Design and Stamping. Based on the designed "shoe-shaped" two-dimensional unfolded contour, a precision stamping mold is made. The stamping process is carried out on a special stamping machine. To prevent cracks from occurring during the stamping process, especially in areas with large side areas due to uneven material flow, stress relief grooves are pre-designed and processed in these critical areas. These grooves can be U-shaped or V-shaped, and their depth and width are precisely calculated to effectively disperse concentrated stress during stamping and prevent material cracking.

[0079] Step 3: Post-processing. The stamped vibration damping sealing sheet is subjected to solution treatment to obtain a uniform solution structure and optimize its high-temperature performance and fatigue resistance.

[0080] The assembly process of vibration damping sealing plate 3 is as follows:

[0081] S1. Initially install the blades by inserting the tenons 21 at the root of all turbine blade bodies 2 into the corresponding mounting grooves 4 of the turbine disk, but do not immediately install or rivet them in place. This step is intended to initially position the blades.

[0082] S2. Place the vibration damping sealing sheet. Between every two adjacent turbine blades, place one of the prepared vibration damping sealing sheets 3 into the space enclosed by the bottom of the blade edge plate 23 and the surface of the turbine disk 1. When placing it, make sure that the base plate 31 faces the blade edge plate 23.

[0083] S3. Final positioning and riveting of the blades: After all the vibration damping sealing plates 3 have been placed, all turbine blade bodies 2 are fully pushed and installed into the designed positions. This step ensures that the blade edge plate 23 constrains the vibration damping sealing plates 3 in their designed positions. Subsequently, the turbine blade body 2 and the turbine disk 1 are finally fixed with rivets according to the standard process specifications. After assembly, it is necessary to ensure that the turbine blade body 2 meets the specified technical requirements.

[0084] S4. Dynamic balancing verification: The assembled rotor assembly must undergo rigorous dynamic balancing tests and adjustments to ensure the smooth operation of the engine.

[0085] Example 2

[0086] As one embodiment of this application, such as Figure 7 and Figure 8 As shown, the difference between it and Embodiment 1 is that a damping component 5 is provided in the gap between the turbine disk 1 and the turbine blade body 2. The damping component 5 includes a damping block 51, and the damping block 51 has a plurality of first heat dissipation holes 52 and second heat dissipation holes 53.

[0087] In this technical solution, the gap between the turbine disk 1 and the turbine blade body 2 can be filled by the sealing component 5 to achieve the purpose of vibration reduction and sealing, without affecting the heat dissipation between the turbine disk 1 and the turbine blade body 2.

[0088] In use, the damping sealing component 5 is placed in the gap between the turbine disk 1 and the turbine blade body 2. The tip of the damping sealing block 51 is set upward. The damping sealing block 51 is used to achieve vibration reduction and sealing. The first heat dissipation hole 52 and the second heat dissipation hole 53 can be used for heat dissipation treatment to prevent heat dissipation from affecting the operation of the turbine.

[0089] While specific embodiments of this utility model have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of this utility model is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of this utility model, but all such changes and modifications fall within the scope of protection of this utility model.

Claims

1. A device for vibration reduction and interstage sealing of turbine blades in an aero-turboshaft engine, characterized in that: It includes a turbine disk (1) and a turbine blade body (2), wherein a plurality of turbine blade bodies (2) are detachably connected to the side of the turbine disk (1) in a ring array; Vibration damping sealing plate (3): Vibration damping sealing plate (3) is provided between the turbine disk (1) and the turbine blade body (2). The vibration damping sealing plate (3) is used for vibration damping and interstage sealing of the turbine blades of the aircraft turboshaft engine.

2. The turbine blade vibration reduction and interstage sealing device for aero-turboshaft engines as described in claim 1, characterized in that: The turbine blade body (2) includes a blade root tenon (21) and a blade plate (22). The blade root tenon (21) and the blade plate (22) are connected to each other. The side of the blade root tenon (21) away from the blade plate (22) is detachably connected to the side of the turbine disk (1).

3. The turbine blade vibration reduction and interstage sealing device for aero-turboshaft engines as described in claim 2, characterized in that: The turbine disk (1) has multiple mounting tenons (4) arranged in a ring array on its side. The blade root tenon (21) cooperates with the mounting tenon (4) to install the turbine blade body (2) onto the side of the turbine disk (1).

4. The turbine blade vibration reduction and interstage sealing device for aero-turboshaft engines as described in claim 2, characterized in that: The turbine blade body (2) also includes blade edge plates (23). Blade edge plates (23) are connected to both sides of the connection between the blade root tenon (21) and the blade plate (22). The blade edge plates (23) of two adjacent turbine blade bodies (2) are close to each other.

5. The turbine blade vibration reduction and interstage sealing device for aero-turboshaft engines as described in claim 4, characterized in that: The vibration damping sealing plate (3) is positioned between the blade edge plate (23) and the turbine disk (1).

6. The turbine blade vibration reduction and interstage sealing device for aero-turboshaft engines as described in claim 1, characterized in that: The vibration damping sealing plate (3) includes a base plate (31) and a sloped wall plate (32), which are connected to each other.

7. The turbine blade vibration reduction and interstage sealing device for aero-turboshaft engines as described in claim 6, characterized in that: The overall outline of the vibration damping sealing plate (3) is "shoe" shaped, the base plate (31) is "shoe sole", and the inclined wall plate (32) is "shoe upper".

8. The turbine blade vibration reduction and interstage sealing device for aero-turboshaft engines as described in claim 7, characterized in that: The substrate (31) conforms to the profile of the bottom of the blade edge plate (23) and is used to cover most of the gap between adjacent blade edge plates (23).

9. The turbine blade vibration reduction and interstage sealing device for aero-turboshaft engines as described in claim 7, characterized in that: The inclined wall panel (32) is a plate-like structure that extends upward from both sides of the substrate (31).

10. The turbine blade vibration reduction and interstage sealing device for aero-turboshaft engines as described in claim 1, characterized in that: A damping assembly (5) is provided in the gap between the turbine disk (1) and the turbine blade body (2). The damping assembly (5) includes a damping block (51), which has a plurality of first heat dissipation holes (52) and second heat dissipation holes (53).

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