Multi-layer hollow air cooling channel structure of turbine blade

Abstract

The utility model discloses a turbine blade multilayer hollow air cooling channel structure which comprises a connecting shaft, and the inner wall of the connecting shaft is connected with a blade structure in a sliding mode. The blade structure comprises a connecting plate, and a sliding block is fixedly connected to the outer wall of the bottom of the connecting plate. According to the blade structure, heat exchange with the blade is conducted in a staged mode through multiple layers of air cooling channels of the front blade plate, the middle blade plate and the tail blade plate, heat generated when the blade works is gradually taken away, the temperature of the blade is effectively reduced, and material performance reduction and structural damage caused by high temperature are avoided; no matter in a forward rotation working condition or a reverse rotation working condition, impurities in cooling gas can be effectively filtered, air cooling channel blockage or internal structure abrasion is prevented, and the maintenance frequency and the maintenance cost are reduced.

Description

Technical Field

[0001] This utility model relates to the field of turbine blade technology, specifically to a multi-layer hollow air-cooling channel structure for turbine blades. Background Technology

[0002] As a key component of turbine engines, turbine blades are subjected to extreme conditions of high temperature, high pressure and high speed rotation for a long time. They are subjected to the scouring of gas exceeding the melting point of the material and are prone to material creep, fatigue failure or even structural damage due to overheating. Therefore, efficient cooling technology has become the core element to ensure the stable operation of turbine blades.

[0003] Currently, most common turbine blade cooling structures employ single-layer or double-layer hollow air-cooling channels, which introduce cooling gas to exchange heat with the blades to achieve cooling. However, such structures have some shortcomings. Traditional cooling structures lack a two-way protection mechanism. Under special operating conditions such as turbine reversal, impurities in the cooling gas can easily enter the channel, causing blockage of the air film pores or wear of the inner wall of the channel, which significantly reduces cooling efficiency and increases maintenance costs. Utility Model Content

[0004] (a) Technical problems to be solved

[0005] To address the shortcomings of existing technologies, this invention provides a multi-layer hollow air-cooling channel structure for turbine blades, which solves the problem that traditional cooling structures lack a two-way protection mechanism, and that impurities in the cooling gas can easily enter the channel, causing blockage of the air film pores or wear of the channel inner wall.

[0006] (II) Technical Solution

[0007] To achieve the above objectives, this utility model provides the following technical solution:

[0008] A multi-layer hollow air-cooling channel structure for turbine blades includes: a connecting shaft, on the inner wall of which a blade structure is slidably connected; the blade structure includes a connecting plate, a slider is fixedly connected to the outer wall of the bottom of the connecting plate, and a front blade plate, a middle blade plate, and a tail blade plate are fixedly connected to the outer wall of the top of the connecting plate; the outer wall of the middle blade plate is fixedly connected to the outer wall of the front blade plate, and the outer wall of the middle blade plate on the side away from the front blade plate is fixedly connected to the outer wall of the tail blade plate.

[0009] Preferably, the outer wall of the front blade away from the middle blade has a first flow guide opening, and a first filter screen is fixedly connected to the outer wall of the front blade. The first filter screen is located outside the first flow guide opening. The first filter screen can effectively filter out impurities in the gas and prevent them from entering the air-cooling channel and causing blockage or wear on the internal structure of the blade.

[0010] Preferably, a first partition is fixedly connected to the inner wall of the middle blade plate near the front blade plate, and a first through hole is opened on the outer wall of the first partition plate. Gas enters the interior of the middle blade plate through the first through hole on the first partition plate on the inner wall of the middle blade plate.

[0011] Preferably, a second partition is fixedly connected to the inner wall of the tail blade plate near the middle blade plate, and a second through hole is opened on the outer wall of the second partition. Gas can enter the space inside the tail blade plate by passing through the second through hole on the second partition plate on the inner wall of the tail blade plate.

[0012] Preferably, a second flow guide is provided on the outer wall of the tail blade on the side away from the middle blade. A second filter is fixedly connected to the outer wall of the tail blade, and the second filter is located outside the second flow guide. Gas carrying heat is discharged from the second flow guide on the side of the tail blade away from the middle blade. When the turbine blade reverses, the gas flows in the opposite direction, and the second filter also plays the role of preventing impurities.

[0013] Preferably, the outer wall of the slider is slidably connected to the inner wall of the connecting shaft, and the sliders are arranged in a ring along the central point of the connecting shaft. The connecting shaft is connected to an external drive shaft and drives the blade structure to operate.

[0014] (III) Beneficial Effects

[0015] This invention provides a multi-layer hollow air-cooling channel structure for turbine blades. It has the following advantages:

[0016] (I) The blade structure exchanges heat with the blade in stages through the multi-layer air-cooling channels of the front blade, middle blade and tail blade, gradually removing the heat generated by the blade during operation, effectively reducing the blade temperature, avoiding material performance degradation and structural damage caused by high temperature, ensuring the stable operation of the turbine blade under extreme conditions, and extending the blade service life.

[0017] (ii) The front blade, through the first filter and the second filter on the tail blade, can effectively filter impurities in the cooling gas in both forward and reverse operation, prevent blockage of the air cooling passage or wear of the internal structure, reduce maintenance frequency and maintenance costs, ensure long-term stable operation of the cooling system, and improve the overall reliability of the turbine operation. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0019] Figure 2 This is a schematic diagram of the blade structure of this utility model;

[0020] Figure 3 This is a schematic diagram of the structure of the leaf plate in this utility model.

[0021] In the diagram: 1. Connecting shaft; 2. Blade structure; 21. Connecting plate; 22. Slider; 23. Front blade plate; 24. First guide port; 25. First filter screen; 26. Middle blade plate; 261. First partition plate; 262. First through hole; 27. Tail blade plate; 271. Second partition plate; 272. Second through hole; 28. Second guide port; 29. ​​Second filter screen. Detailed Implementation

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] Please see Figure 1-3 This utility model provides a technical solution: a multi-layer hollow air-cooling channel structure for turbine blades, comprising: a connecting shaft 1, with a blade structure 2 slidably connected to the inner wall of the connecting shaft 1; the blade structure 2 includes a connecting plate 21, with a slider 22 fixedly connected to the outer wall of the bottom of the connecting plate 21, and a front blade plate 23, a middle blade plate 26, and a tail blade plate 27 fixedly connected to the outer wall of the top of the connecting plate 21, the outer wall of the middle blade plate 26 being fixedly connected to the outer wall of the front blade plate 23, and the outer wall of the middle blade plate 26 on the side away from the front blade plate 23 being fixedly connected to the outer wall of the tail blade plate 27.

[0024] The outer wall of the front blade 23 away from the middle blade 26 has a first flow guide port 24. The outer wall of the front blade 23 is fixedly connected to a first filter screen 25, and the first filter screen 25 is located outside the first flow guide port 24. The first filter screen 25 can effectively filter out impurities in the gas and prevent them from entering the air cooling channel and causing blockage or wear on the internal structure of the blade.

[0025] A first partition 261 is fixedly connected to the inner wall of the middle blade plate 26 near the front blade plate 23. A first through hole 262 is opened on the outer wall of the first partition 261. Gas enters the interior of the middle blade plate 26 through the first through hole 262 on the first partition 261 on the inner wall of the middle blade plate 26.

[0026] A second partition 271 is fixedly connected to the inner wall of the tail blade plate 27 on the side near the middle blade plate 26. A second through hole 272 is opened on the outer wall of the second partition 271. Gas can enter the space inside the tail blade plate 27 by passing through the second through hole 272 on the second partition 271 on the inner wall of the tail blade plate 27.

[0027] A second flow guide 28 is provided on the outer wall of the tail blade 27 on the side away from the middle blade 26. A second filter 29 is fixedly connected to the outer wall of the tail blade 27 and is located outside the second flow guide 28. Gas carrying heat is discharged from the second flow guide 28 on the side of the tail blade 27 away from the middle blade 26. When the turbine blade reverses, the gas flows in the opposite direction, and the second filter 29 also plays the role of preventing impurities.

[0028] The outer wall of the slider 22 is slidably connected to the inner wall of the connecting shaft 1, and the slider 22 is arranged in a ring along the central point of the connecting shaft 1. The connecting shaft 1 is connected to the external drive shaft and drives the blade structure 2 to operate.

[0029] In use, the blade structure 2 is slidably connected to the inner wall of the connecting shaft 1 via the slider 22 at the bottom of the connecting plate 21, and the connecting shaft 1 is connected to the external drive shaft to operate;

[0030] During operation, the cooling gas first enters from the first guide port 24 on the side of the front blade 23 away from the middle blade 26. The first filter screen 25 can effectively filter out impurities in the gas, preventing them from entering the air-cooling channel and causing blockage or wear on the internal structure of the blade.

[0031] The filtered gas enters the space between the front blade 23 and the middle blade 26. Then, the gas enters the interior of the middle blade 26 through the first through hole 262 on the first partition 261 on the inner wall of the middle blade 26. Inside the middle blade 26, the gas continues to flow and exchange heat with the blades, absorbing the heat generated when the blades are working. Then, the gas passes through the second through hole 272 on the second partition 271 on the inner wall of the tail blade 27 and enters the space inside the tail blade 27, further carrying away heat.

[0032] Finally, the gas carrying heat is discharged from the second guide port 28 on the side of the tail vane 27 away from the middle vane 26. When the turbine blades reverse, the gas flows in the opposite direction. The second filter 29 also serves to prevent impurities from entering the air-cooling channel and causing reverse contamination.

[0033] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0034] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A multi-layer hollow air-cooling channel structure for turbine blades, characterized in that, include: A connecting shaft (1) is provided, and a blade structure (2) is slidably connected to the inner wall of the connecting shaft (1); The blade structure (2) includes a connecting plate (21). A slider (22) is fixedly connected to the outer wall of the bottom of the connecting plate (21). A front blade plate (23), a middle blade plate (26), and a tail blade plate (27) are fixedly connected to the outer wall of the top of the connecting plate (21). The outer wall of the middle blade plate (26) is fixedly connected to the outer wall of the front blade plate (23), and the outer wall of the middle blade plate (26) on the side away from the front blade plate (23) is fixedly connected to the outer wall of the tail blade plate (27).

2. The multi-layer hollow air-cooling channel structure for turbine blades according to claim 1, characterized in that: The front blade (23) has a first flow guide (24) on the outer wall away from the middle blade (26). A first filter (25) is fixedly connected to the outer wall of the front blade (23), and the first filter (25) is located outside the first flow guide (24).

3. The multi-layer hollow air-cooling channel structure for turbine blades according to claim 1, characterized in that: The inner wall of the middle blade (26) near the front blade (23) is fixedly connected to a first partition (261), and the outer wall of the first partition (261) is provided with a first through hole (262).

4. The multi-layer hollow air-cooling channel structure for turbine blades according to claim 1, characterized in that: The tail blade plate (27) has a second partition plate (271) fixedly connected to the inner wall of the side near the middle blade plate (26), and the outer wall of the second partition plate (271) has a second through hole (272).

5. The multi-layer hollow air-cooling channel structure for turbine blades according to claim 1, characterized in that: The tail blade (27) has a second flow guide (28) on the outer wall away from the middle blade (26). A second filter (29) is fixedly connected to the outer wall of the tail blade (27), and the second filter (29) is located outside the second flow guide (28).

6. The multi-layer hollow air-cooling channel structure for turbine blades according to claim 1, characterized in that: The outer wall of the slider (22) is slidably connected to the inner wall of the connecting shaft (1), and the slider (22) is arranged in a ring along the central point of the connecting shaft (1).

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