Turbine rotor blade platform cooling structure

Abstract

The utility model relates to the technical field of turbine rotor blades, in particular to a turbine rotor blade platform cooling structure which comprises a cooling platform, a first cold air pipe, a second cold air pipe, an adjusting plate, a nozzle, an air guide plate, an isolating ring, a blade mounting plate and a mounting seat. The first cold air pipe is arranged in the first air guide groove, and the second cold air pipe is arranged in the cooling platform. A first cold air pipe can be installed through a first air guide groove in the cooling platform, when the first cold air pipe communicates with a second cold air pipe, wind energy conveying at the bottom of the cooling platform can be achieved, cold air plates are obliquely arranged in the first cold air pipe and the second cold air pipe, and when the flow effect of air can be achieved through the cold air plates, the air flow effect is improved. When the internal energy of the gas is converted into kinetic energy due to the release of the pressure energy, the internal energy is reduced, the temperature of the gas is reduced, and the cyclic utilization of the wind energy can be realized.

Description

Technical Field

[0001] The utility model relates to the technical field of turbine rotor blades, in particular to a turbine rotor blade platform cooling structure. Background Art

[0002] Turbine blades are a crucial component of the turbine section of a gas turbine engine. These high-speed rotating blades draw high-temperature, high-pressure air into the combustor to maintain engine operation. To ensure stable and long-term operation in these extreme environments, turbine blades are often forged from high-temperature alloys and cooled using various methods, such as internal airflow cooling, boundary layer cooling, or thermal barrier coatings to ensure operational reliability. In steam and gas turbine engines, blade metal fatigue is the leading cause of engine failure. Intense vibrations and resonance can lead to metal fatigue. Engineers often use friction dampers to mitigate the damage these factors can cause to the blades.

[0003] Chinese Patent Publication No. CN213574236U discloses a turbine rotor blade platform cooling structure, comprising: a turbine rotor blade airfoil; a platform connected thereto; the airfoil being provided with an internal cooling channel, with cooling gas flowing from a cooling gas inlet at the lower portion of the blade root; and an internal cooling structure comprising a platform cavity formed within the platform's pressure and suction sides, not within the airfoil profile envelope. A plurality of grid-like, vertically staggered ribs are disposed within the platform cavity, forming a platform cooling channel formed by the vertically staggered ribs and the platform cavity. Cooling gas is supplied to the platform cooling channel by the airfoil's internal cooling channel. After cooling the platform, the cooling gas flows out through outlets disposed on the platform's inlet, outlet, pressure, and suction sides, and into the main flow of the blade channel. This platform cooling structure, with its grid-like, staggered rib channel cooling structure and corresponding cold air inlet channels and outlets, can reduce platform temperature gradients and minimize mixing losses of the cold air outflow with the main flow.

[0004] The turbine rotor blade platform cooling structure in the above-mentioned patent is similar to the common similar devices on the market. During use, it is generally through the cold air inlet channel and the outlet hole to cooperate to reduce the platform temperature gradient, thereby reducing the mixing loss of the cold air outflow to the mainstream. However, the cold air cannot be effectively recycled during use, resulting in a waste of resources. Utility Model Content

[0005] In response to the above problems, a turbine rotor blade platform cooling structure is provided. The first air guide groove inside the cooling platform can be used to install the first cold air pipe. When the first cold air pipe is connected to the second cold air pipe, wind energy can be transported to the bottom of the cooling platform. In addition, cold air plates are arranged obliquely inside the first cold air pipe and the second cold air pipe. When the flow effect of the gas is achieved through the cold air plates, when the internal energy of the gas is converted into kinetic energy due to the release of pressure energy, the internal energy is reduced, the gas temperature is lowered, and the recycling of wind energy can be achieved.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a turbine rotor blade platform cooling structure, comprising a cooling platform, a first cooling air pipe, a second cooling air pipe, an adjustment plate, a nozzle, an air guide plate, an isolation ring, a blade mounting plate and a mounting seat, a first air guide groove is provided in a ring shape at the bottom of the inner wall of the cooling platform, the first cooling air pipe is arranged inside the first air guide groove, the second cooling air pipe is arranged inside the cooling platform, the adjustment plate is arranged above the cooling platform, the nozzle is arranged on one side of the adjustment plate, the air guide plate is arranged at the air outlet of the nozzle, the cross-sectional shape of the air guide plate is set to be U-shaped, the isolation ring is arranged inside the cooling platform, the blade mounting plate is arranged at the bottom of the inner wall of the cooling platform, and the mounting seat is arranged on the top of the blade mounting plate.

[0007] Furthermore, a second guide groove matching the first cooling air pipe and the second cooling air pipe is provided in an inner ring of the cooling platform, the cross-sectional shape of the second guide groove is set to be L-shaped, and a positioning spiral tube is provided on the output end of the second cooling air pipe.

[0008] Furthermore, cold air plates are symmetrically arranged inside the first cold air pipe and the second cold air pipe, and the angle between the cold air plates and the first cold air pipe and the second cold air pipe is 30°.

[0009] Furthermore, a load-bearing plate is distributed in an annular pattern on the inner wall of the cooling platform, a gantry is provided on the top of the load-bearing plate, a guide hole connected to the adjustment plate is penetrated on one side of the gantry, and a screw rod is penetrated through the internal thread of the adjustment plate.

[0010] Furthermore, a fixing plate is provided at the bottom of the adjusting plate, a wire groove matching the nozzle is opened inside the fixing plate, and the nozzle and the positioning spiral tube are connected through a telescopic tube.

[0011] Furthermore, a cold air discharge port is opened inside the isolation ring, and a first connecting plate is distributed in an annular shape on the outer wall of the isolation ring. A second connecting plate connected to the cooling platform is provided on one side of the first connecting plate, and the first connecting plate and the second connecting plate are connected by auxiliary bolts.

[0012] Furthermore, there are four blade mounting plates, each of which is connected to a mounting seat, and a positioning groove for mounting rotor blades is provided inside the mounting seat.

[0013] Compared with the prior art, the present invention has the following beneficial effects: the turbine rotor blade platform cooling structure is reasonable and has the following advantages:

[0014] The first air guide groove inside the cooling platform can be used to install the first cooling pipe. When the first cooling pipe is connected to the second cooling pipe, wind energy can be transported to the bottom of the cooling platform. In addition, cooling plates are provided at an angle inside the first cooling pipe and the second cooling pipe. When the cooling plates achieve a gas flow effect, when the internal energy of the gas is converted into kinetic energy due to the release of pressure energy, the internal energy decreases, which lowers the gas temperature and enables the recycling of wind energy.

[0015] The height of the nozzle and the air guide plate are adjusted under the action of the adjustment plate, and the wind energy is transported through the nozzle. The wind energy is transported to the bottom of the turbine rotor blades under the action of the air guide plate, which can avoid the problem of cold air only cooling the upper part of the turbine rotor blades, thereby achieving overall cooling of the turbine rotor blades. Moreover, the recycled wind energy is isolated under the action of the isolation ring, so that it can be accurately transported to the designated position, thereby improving the cooling effect of the cooling platform and allowing the turbine rotor blades to be cooled efficiently. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0017] Figure 2 This is a schematic diagram of the installation structure of the isolation ring of the utility model;

[0018] Figure 3 This is a schematic cross-sectional structural diagram of the cooling platform of the present invention;

[0019] Figure 4 This is a schematic diagram of the installation structure of the telescopic tube of the utility model;

[0020] Figure 5 This is a schematic diagram of the cold air plate installation structure of the present utility model.

[0021] In the figure: 1. Cooling platform; 2. First cold air pipe; 3. Second cold air pipe; 4. Adjustment plate; 5. Nozzle; 6. Air guide plate; 7. Isolation ring; 8. Blade mounting plate; 9. Mounting seat; 10. Second guide groove; 11. Positioning screw; 12. Cold air plate; 13. Gantry; 14. Screw; 15. Fixing plate; 16. Telescopic tube; 17. First connecting plate; 18. Second connecting plate; 19. Positioning groove. DETAILED DESCRIPTION

[0022] Clearly, the described embodiments are merely a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0023] Please refer to Figures 1 to 5 A turbine rotor blade platform cooling structure, comprising a cooling platform 1, a first cold gas pipe 2, a second cold gas pipe 3, an adjusting plate 4, a nozzle 5, a gas guide plate 6, an isolation ring 7, a blade mounting plate 8 and a mounting seat 9, the inner wall bottom of the cooling platform 1 is annularly provided with a first gas guide groove, the first cold gas pipe 2 is arranged inside the first gas guide groove, the second cold gas pipe 3 is arranged inside the cooling platform 1, the adjusting plate 4 is arranged above the cooling platform 1, the nozzle 5 is arranged on one side of the adjusting plate 4, the gas guide plate 6 is arranged at the air outlet of the nozzle 5, the cross-sectional shape of the gas guide plate 6 is arranged as a U-shaped, the isolation ring 7 is arranged inside the cooling platform 1, the blade mounting plate 8 is arranged at the inner wall bottom of the cooling platform 1, and the mounting seat 9 is arranged at the top of the blade mounting plate 8.

[0024] In use, the mounting seat 9 is positioned by the blade mounting plate 8, the turbine rotor blade is installed under the action of the mounting seat 9, then the first cold gas pipe 2 can be installed through the first gas guide groove inside the cooling platform 1, the first cold gas pipe 2 is communicated with the second cold gas pipe 3, the circulation of cold air can be realized, then the height of the nozzle 5 and the gas guide plate 6 is adjusted under the action of the adjusting plate 4, the wind energy is transported through the nozzle 5, and the circulating wind energy is transported to the bottom of the turbine rotor blade under the action of the gas guide plate 6, which can avoid that the cold air only cools the upper part of the turbine rotor blade, so as to realize the overall cooling of the turbine rotor blade, and the circulating wind energy can be isolated under the action of the isolation ring 7, so that it can be accurately transported to the specified position, the refrigeration effect of the cooling platform 1 is improved, and the turbine rotor blade is cooled efficiently.

[0025] As Figure 1 and Figure 3 shown, the inside of the cooling platform 1 is annularly provided with a second guide groove 10 matched with the first cold gas pipe 2 and the second cold gas pipe 3, the cross-sectional shape of the second guide groove 10 is arranged as an L-shaped, and the output end of the second cold gas pipe 3 is threadedly provided with a positioning pipe 11.

[0026] The first cold air pipe 2 and the second cold air pipe 3 are installed through the second guide groove 10 to allow the gas inside the first cold air pipe 2 and the second cold air pipe 3 to circulate, and the positioning screw 11 is installed under the action of the second cold air pipe 3. When the positioning screw 11 is moved, the second cold air pipe 3 can be disassembled and assembled, making it easy to replace it.

[0027] like Figure 3 and Figure 5 As shown, cold air plates 12 are symmetrically arranged inside the first cold air pipe 2 and the second cold air pipe 3 , and the angle between the cold air plates 12 and the first cold air pipe 2 and the second cold air pipe 3 is 30°.

[0028] When the cold air plate 12 is installed inside the first cold air pipe 2 and the second cold air pipe 3, the flow effect of the gas can be achieved through the inclined cold air plate 12. The internal energy of the gas may be converted into kinetic energy due to the release of pressure energy, resulting in a decrease in internal energy, which in turn will reduce the gas temperature.

[0029] like Figure 3 and Figure 4 As shown, the inner wall of the cooling platform 1 is annularly distributed with load-bearing plates, and a gantry 13 is provided on the top of the load-bearing plate. A guide hole connected to the adjustment plate 4 is penetrated on one side of the gantry 13, and a screw rod 14 is penetrated by the internal thread of the adjustment plate 4. A fixing plate 15 is provided at the bottom of the adjustment plate 4, and a wire groove matching the nozzle 5 is provided inside the fixing plate 15. The nozzle 5 and the positioning screw tube 11 are connected by a telescopic tube 16.

[0030] The load-bearing plate and the gantry 13 are installed under the action of the cooling platform 1. When the screw 14 is rotated, the height of the adjustment plate 4 can be adjusted under the action of the guide hole. When the adjustment plate 4 moves, the height of the fixed plate 15, the nozzle 5 and the air guide plate 6 can be adjusted. The cooled gas is blown into the interior of the air guide plate 6 through the nozzle 5. The gas is discharged under the action of the air guide plate 6, so that the gas can be transported to the bottom of the turbine rotor blades, thereby improving the cooling effect of the turbine rotor blades.

[0031] like Figure 1 As shown, a cold air discharge port is provided inside the isolation ring 7, and a first connecting plate 17 is distributed in an annular shape on the outer wall of the isolation ring 7. A second connecting plate 18 connected to the cooling platform 1 is provided on one side of the first connecting plate 17, and the first connecting plate 17 and the second connecting plate 18 are connected by auxiliary bolts.

[0032] The isolation ring 7 is placed inside the cooling platform 1 , and the first connecting plate 17 is driven by the cooling platform 1 . The first connecting plate 17 and the second connecting plate 18 are installed under the action of auxiliary bolts, which makes it easy to disassemble and assemble the isolation ring 7 .

[0033] like Figure 3 As shown, the number of the blade mounting plates 8 is set to four, the blade mounting plates 8 are connected with the mounting bases 9, and the mounting bases 9 are internally provided with positioning grooves 19 for mounting the rotor blades.

[0034] The blade mounting plates 8 are arranged inside the cooling platform 1, the mounting bases 9 are fixed through the blade mounting plates 8, and the rotor blades can be disassembled through the positioning grooves 19 inside the mounting bases 9.

[0035] The above embodiment only expresses one or several embodiments of the present application, the description is more specific and detailed, but it cannot be understood as the limitation of the scope of the present application. It should be pointed out that for ordinary skilled in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which belong to the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the appended claims.

Claims

1. A turbine rotor blade platform cooling structure, characterized in that , comprising a cooling platform (1), a first cold air pipe (2), a second cold air pipe (3), an adjustment plate (4), a nozzle (5), an air guide plate (6), an isolation ring (7), a blade mounting plate (8) and a mounting seat (9), wherein a first air guide groove is provided in an annular manner at the bottom of the inner wall of the cooling platform (1), the first cold air pipe (2) is arranged inside the first air guide groove, the second cold air pipe (3) is arranged inside the cooling platform (1), the adjustment plate (4) is arranged above the cooling platform (1), the nozzle (5) is arranged on one side of the adjustment plate (4), the air guide plate (6) is arranged at the air outlet of the nozzle (5), the cross-sectional shape of the air guide plate (6) is set to be U-shaped, the isolation ring (7) is arranged inside the cooling platform (1), the blade mounting plate (8) is arranged at the bottom of the inner wall of the cooling platform (1), and the mounting seat (9) is arranged on the top of the blade mounting plate (8).

2. The turbine rotor blade platform cooling structure according to claim 1, characterized in that: The cooling platform (1) is provided with a second guide groove (10) in an annular shape inside the cooling platform (1) and matching the first cold air pipe (2) and the second cold air pipe (3). The cross-sectional shape of the second guide groove (10) is set to be L-shaped, and the output end of the second cold air pipe (3) is threadedly provided with a positioning screw (11).

3. The turbine rotor blade platform cooling structure according to claim 1, characterized in that: Cold air plates (12) are symmetrically arranged inside the first cold air pipe (2) and the second cold air pipe (3), and the angle between the cold air plates (12) and the first cold air pipe (2) and the second cold air pipe (3) is 30°.

4. The turbine rotor blade platform cooling structure according to claim 3, characterized in that: The inner wall of the cooling platform (1) is provided with a load-bearing plate in an annular shape, and a gantry (13) is provided on the top of the load-bearing plate. A guide hole connected to the adjustment plate (4) is provided through one side of the gantry (13), and a screw rod (14) is passed through the internal thread of the adjustment plate (4).

5. The turbine rotor blade platform cooling structure according to claim 1, characterized in that: A fixing plate (15) is provided at the bottom of the regulating plate (4), a wire groove matching the nozzle (5) is provided inside the fixing plate (15), and the nozzle (5) is connected to the positioning spiral tube (11) via a telescopic tube (16).

6. The turbine rotor blade platform cooling structure according to claim 1, characterized in that: A cold air discharge port is provided inside the isolation ring (7), and a first connecting plate (17) is distributed in an annular shape on the outer wall of the isolation ring (7). A second connecting plate (18) connected to the cooling platform (1) is provided on one side of the first connecting plate (17), and the first connecting plate (17) and the second connecting plate (18) are connected by auxiliary bolts.

7. The turbine rotor blade platform cooling structure according to claim 1, characterized in that: The number of the blade mounting plates (8) is four, and the blade mounting plates (8) are connected to the mounting seat (9). A positioning groove (19) for mounting the rotor blade is provided inside the mounting seat (9).

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