Variable area side-dump cooling gas turbine transition piece

Abstract

The application discloses a variable cross-section side reinforced cooling gas turbine transition section, which comprises a transition section body, an impact bushing and a cooling member, the transition section body is used for conveying high-temperature gas generated by a combustion chamber into a turbine, the impact bushing is sleeved on the outer circumferential surface of the transition section body, the inner circumferential surface of the impact bushing and the outer circumferential surface of the transition section body are spaced to form an airflow channel, the impact bushing is provided with a mounting hole penetrating through the impact bushing in the direction from inside to outside, the cooling member is installed on the inner circumferential surface of the transition section body through the mounting hole, and the cooling member is provided with a plurality of turbulence holes penetrating through the cooling member, the plurality of turbulence holes are spaced into multiple rows in the height direction of the cooling member, and each row comprises a plurality of turbulence holes which are spaced in the length direction of the cooling member. The transition section for the gas turbine has the advantages of simple structure and good cooling effect.

Description

Technical Field

[0001] This invention relates to the field of gas turbines, and more specifically, to a gas turbine transition section with variable cross-section side-enhanced cooling. Background Technology

[0002] A gas turbine mainly consists of three major components: a compressor, a combustion chamber, and a turbine. The compressor compresses air, and the high-pressure air enters the combustion chamber to mix and burn with fuel. The resulting high-temperature gas does work through the turbine. Part of the power generated by the turbine drives the compressor to compress air, and the other part of the power drives the generator to generate electricity.

[0003] The combustion chamber mainly consists of a fuel nozzle, a flow guide bushing, a flame tube, and a transition section. Compressed air flows in the opposite direction into the annular channel between the flow guide bushing and the flame tube, where it is premixed with the fuel in the nozzle. The combustible mixture enters the flame tube, and the high-temperature gas produced after combustion enters the turbine through the transition section. The transition section body is in direct contact with the high-temperature combustion gas and needs to be properly cooled to meet the service life requirements.

[0004] In related technologies, the cooling effect of the transition section is poor and its service life is short. Summary of the Invention

[0005] This utility model is based on the inventor's discovery and understanding of the following facts and problems: When impact cooling is used in the transition section, the pressure difference between the inside and outside of the impact bushing forms an impact jet, enhancing surface cooling of the transition section. However, the space between adjacent transition sections is narrow. When compressed air enters the combustion cylinder and passes through the area between adjacent transition sections, the air velocity increases. This decreases the static pressure, leading to a reduction in the pressure difference between the inside and outside of the impact bushing, a decrease in jet velocity, and insufficient cooling capacity to lower the transition section temperature, resulting in adverse effects such as overheating. While arranging a spoon-shaped flow guide structure on the side can achieve some effect, it results in significant flow losses, affecting efficiency. This invention aims to at least partially solve one of the technical problems in related technologies.

[0006] The present invention aims to at least partially solve one of the technical problems in the related art.

[0007] Therefore, embodiments of the present invention propose a gas turbine transition section with variable cross-section side-enhanced cooling that has a simple structure and good cooling effect.

[0008] According to an embodiment of the present invention, a gas turbine transition section with variable cross-section side-cooled enhancement includes: a transition section body for conveying high-temperature gas generated in the combustion chamber to the turbine; an impact bushing fitted on the outer peripheral surface of the transition section body, the inner peripheral surface of the impact bushing and the outer peripheral surface of the transition section body being spaced apart to form an airflow channel, the impact bushing having mounting holes penetrating the impact bushing in an inward and outward direction; and a cooling member installed on the inner peripheral surface of the transition section body through the mounting holes, the cooling member having a plurality of turbulence holes penetrating the cooling member, the plurality of turbulence holes being spaced apart in multiple rows along the height direction of the cooling member, each row including a plurality of turbulence holes spaced apart along the length direction of the cooling member, the surface area to volume ratio of the cooling member being higher than the area to volume ratio of the inner peripheral surface of the airflow channel, so as to improve the heat transfer coefficient between the transition section body and the impact bushing.

[0009] The variable cross-section side-cooled gas turbine transition section of the present invention is equipped with cooling components, which improves the cooling effect of the transition section, extends the service life of the transition section, reduces the pressure loss in the combustion chamber, and thus improves the gas turbine efficiency.

[0010] In some embodiments, the cooling member has a first part and a second part connected in sequence. The first part is disposed in the mounting hole, and the second part is disposed in the airflow channel and connected to the outer peripheral surface of the transition section body. A portion of the plurality of turbulence holes is located on the first part, and another portion of the plurality of turbulence holes is located on the second part.

[0011] In some embodiments, the impact bushing has a first side and a second side in its width direction, and the mounting hole includes a first mounting hole and a second mounting hole, the first mounting hole and the second mounting hole being formed on the first side and the second side respectively, and both the first mounting hole and the second mounting hole are provided with the cooling member.

[0012] In some embodiments, the cooling component includes a base plate and a plurality of connecting units. Each connecting unit includes a first rod, a second rod, and a third rod. The second rod and the third rod are both located at one end of the first rod. The extension directions of the second rod and the third rod intersect the extension direction of the first rod at an angle. The plurality of connecting units are arranged in multiple rows along the height direction of the base plate. Each row of connecting units includes several sequentially arranged connecting units. The free end of the second rod of a connecting unit intersects the free end of the third rod of its adjacent connecting unit at a point A. The free end of the first rod of a connecting unit is located at point A of the connecting unit in its adjacent row.

[0013] In some embodiments, the diameter of the multiple rows of turbulence holes gradually decreases along the direction adjacent to the transition section body.

[0014] In some embodiments, the mounting hole is located adjacent to the turbine of the impact bushing, and the mounting hole extends along the length of the impact bushing.

[0015] In some embodiments, there are multiple mounting holes, which are spaced apart circumferentially along the impact bushing, and there are multiple cooling components, with at least one cooling component provided in each mounting hole.

[0016] In some embodiments, the cooling components are respectively connected to the outer peripheral surface of the transition section body by welding.

[0017] In some embodiments, the gas turbine transition section with variable cross-section side-cooled enhancement further includes a plurality of baffles. The plurality of baffles are disposed in the airflow channel and connected to the inner circumferential surface of the transition section body. The ratio of the surface area to the volume of the baffles is A1, and the ratio of the area to the volume of the inner circumferential surface of the airflow channel is A2. A1 is greater than A2 in order to improve the heat transfer coefficient of the transition section body.

[0018] In some embodiments, the shape of the disturbance element is any one of an X-shaped lattice shape, a Kagome lattice shape, a face-centered cubic lattice shape, etc.

[0019] In some embodiments, the cooling member has a first part and a second part connected in sequence. The first part is disposed in the mounting hole, and the second part is disposed in the airflow channel and connected to the outer peripheral surface of the transition section body. A portion of the plurality of turbulence holes is located on the first part, and another portion of the plurality of turbulence holes is located on the second part.

[0020] In some embodiments, there are multiple cooling components, which are spaced apart within the mounting holes along the length of the transition section body.

[0021] In some embodiments, in a projection plane orthogonal to the length direction of the impact bushing, the turbulence holes of two adjacent cooling components are offset in the length direction of the transition section body.

[0022] In some embodiments, the gas turbine transition section with variable cross-section side-enhanced cooling further includes a connecting rod disposed between two adjacent cooling components, with both ends of the connecting rod connected to the two adjacent cooling components respectively.

[0023] In some embodiments, the diameter of the multiple rows of turbulence holes gradually decreases along the direction adjacent to the transition section body.

[0024] In some embodiments, the mounting hole is located adjacent to the turbine of the impact bushing, and the mounting hole extends along the length of the impact bushing.

[0025] In some embodiments, there are multiple mounting holes, which are spaced apart circumferentially along the impact bushing, and there are multiple cooling components, with at least one cooling component provided in each mounting hole.

[0026] In some embodiments, the cooling components are respectively connected to the outer peripheral surface of the transition section body by welding.

[0027] In some embodiments, the gas turbine transition section with variable cross-section side-cooled enhancement further includes a plurality of baffles. The plurality of baffles are disposed in the airflow channel and connected to the inner circumferential surface of the transition section body. The ratio of the surface area to the volume of the baffles is A1, and the ratio of the area to the volume of the inner circumferential surface of the airflow channel is A2. A1 is greater than A2 in order to improve the heat transfer coefficient of the transition section body. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the structure of the gas turbine transition section with variable cross-section side-cooled enhancement according to an embodiment of the present invention.

[0029] Figure 2 This is a cross-sectional view of the transition section of a gas turbine with variable cross-section side-cooled reinforcement, according to an embodiment of the present invention.

[0030] Figure 3 This is a cross-sectional view of the gas turbine transition section with variable cross-section side-cooled enhanced cooling according to an embodiment of the present invention, showing the removal of cooling components.

[0031] Figure 4 This is a schematic diagram of the impact bushing of the gas turbine transition section with variable cross-section side-cooled reinforcement according to an embodiment of the present invention.

[0032] Figure 5 This is a schematic diagram of the cooling component of the gas turbine transition section with variable cross-section side-enhanced cooling according to an embodiment of the present invention.

[0033] Figure 6 This is a schematic diagram of the structure of the turbulence component of the gas turbine transition section with variable cross-section side-cooled enhancement according to an embodiment of the present invention.

[0034] Gas turbine transition section 100 with variable cross-section side-cooled reinforcement; Transition section body 1; Impact bushing 2; airflow channel 21; air inlet 22; mounting hole 23 Cooling component 3; turbulence hole 31; base plate 32; connecting unit 33; first rod 331; second rod 332; third rod 333; first connecting unit 334, second connecting unit 335, third connecting unit 336, fourth connecting unit 337, fifth connecting unit 338; 4. Aerodynamic component. Detailed Implementation

[0035] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0036] The following description, with reference to the accompanying drawings, describes a gas turbine transition section with variable cross-section side-enhanced cooling according to an embodiment of the present invention.

[0037] like Figure 1-6 As shown, the gas turbine transition section 100 with variable cross-section side-cooled reinforcement according to an embodiment of the present invention includes a transition section body 1, an impact bushing 2, and a cooling component 3.

[0038] The transition section body 1 is used to transport the high-temperature gas generated in the combustion chamber to the turbine. The impact bushing 2 is fitted on the outer peripheral surface of the transition section body 1. The inner peripheral surface of the impact bushing and the outer peripheral surface of the transition section body 1 are spaced apart to form an airflow channel 21. The impact bushing is provided with mounting holes 23 that penetrate the impact bushing in the inward and outward directions.

[0039] Specifically, such as Figure 1-3 As shown, the left end of the transition section body 1 is the inlet and can communicate with the combustion chamber, and the right end of the transition section body 1 is the outlet and is connected to the turbine. The high-temperature gas generated in the combustion chamber flows into the turbine through the transition section body 1, thereby driving the turbine to rotate and converting the internal energy of the fuel into mechanical energy. The transition section body 1 is installed inside the impact bushing 2 and is spaced apart from the impact bushing 2 in the inner and outer directions. The outer circumferential surface of the impact bushing 2 is provided with air inlet holes 22 spaced apart in the thickness direction. Cooling gas can flow into the airflow channel 21 through the impact hole 31. The cooling gas cools the transition section body 1, prevents the transition section body 1 from being damaged by the high-temperature gas, and extends the service life of the transition section body 1.

[0040] The cooling component 3 is mounted on the inner circumferential surface of the transition section body 1 through the mounting hole 23. The cooling component 3 has multiple turbulence holes 31 penetrating the cooling component 3, and the multiple turbulence holes 31 are along the height direction of the cooling component (e.g., Figure 4 The cooling components (shown in the vertical direction) are arranged in multiple rows, each row including several turbulence holes 31 spaced apart along the length of the cooling component. The surface area to volume ratio of the cooling component 3 is higher than the area to volume ratio of the inner circumferential surface of the airflow channel, in order to improve the heat transfer coefficient between the transition section body 1 and the impact bushing 2. Specifically, as shown... Figure 4 As shown, the cooling component 3 has turbulence holes 31 that penetrate the cooling component 3 in the front-to-back direction. Multiple turbulence holes 31 are arranged in multiple rows at intervals in the up-down direction. Each row of turbulence holes 31 is arranged sequentially in the front-to-back direction. When the cooling gas flows into the mounting hole 23, due to the large specific surface area of ​​the cooling component 3, the surface area of ​​the cooling gas blowing over the cooling component 3 is relatively large under the same volume. This makes the setting of the cooling component 3 improve the heat transfer coefficient between the impact bushing 2 and the transition section body 1, and improve the cooling effect of the transition section body 1. Moreover, the setting of the turbulence holes 31 can ensure that it not only has a turbulence effect on the cooling gas, but also allows the cooling gas to flow into the airflow channel 21 through the turbulence holes 31.

[0041] The variable cross-section side-cooled gas turbine transition section 100 of this embodiment of the invention is provided with a cooling component 3. The cooling component 3 improves the heat transfer coefficient between the impact bushing 2 and the transition section body 1, thereby improving the cooling effect of the variable cross-section side-cooled gas turbine transition section 100 and extending its service life. In addition, the spoon-shaped flow guide structure in related technologies is eliminated, reducing the flow loss of cooling gas. Furthermore, the installation hole 23 and the turbulence hole 31 can increase the flow rate of cooling gas flowing into the airflow channel 21, increase the flow rate of cooling gas flowing into the combustion chamber from the airflow channel 21, reduce the pressure loss in the combustion chamber, and thus improve the gas turbine efficiency.

[0042] In some embodiments, the cooling member 3 has a first part and a second part connected in sequence. The first part is disposed within the mounting hole 23, and the second part is disposed within the airflow channel 21 and connected to the outer peripheral surface of the transition section body 1. A portion of a plurality of turbulence holes 31 is located on the first part, and another portion of the plurality of turbulence holes 31 is located on the second part. Specifically, as shown... Figure 4 As shown, the second part passes through the mounting hole 23 and is located in the airflow channel 21, and the lower end face of the second part is fixedly mounted on the outer peripheral surface of the transition section body 1. The first part is mounted above the second part and is located in the mounting hole 23. Thus, the effective space of the mounting hole 23 is reasonably utilized, making the arrangement of the cooling component 3 more reasonable and improving the heat exchange efficiency of the cooling component 3.

[0043] In some embodiments, since the cooling air flows from the outside of the impact bushing 2 through the inlet 22 to the inside to form an impact, the intensity of the impact depends on the pressure difference between the inside and outside of the impact bushing 2. The pressure difference between the inside and outside of the impact bushing 2 is approximately the same throughout the entire transition section 100. However, because the flow velocity on the front and rear sides of the impact bushing 2 is relatively fast, the external static pressure in these two areas is relatively small (the faster the velocity, the smaller the static pressure, Bernoulli's principle), which in turn leads to poor cooling effect on the front and rear sides of the impact bushing 2. Therefore, in some embodiments, the impact bushing 2 in its width direction (e.g., Figure 2 (As shown in the front-to-back direction) It has a first side and a second side, and the mounting holes include a first mounting hole 131 and a second mounting hole 132. The first mounting hole and the second mounting hole are respectively formed on the first side and the second side. Both the first mounting hole 131 and the second mounting hole are provided with multiple cooling components 3. In some embodiments, the cooling component 3 includes a base plate 32 and a plurality of connecting units 33. The connecting unit 33 includes a first rod 331, a second rod 332, and a third rod 333. The second rod 332 and the third rod 333 are both located at one end of the first rod 331. The extension directions of the second rod 332 and the third rod 333 intersect the extension direction of the first rod 331 at an angle. The plurality of connecting units 33 are arranged in multiple rows along the height direction of the base plate 32. Each row of connecting units 33 includes several sequentially arranged connecting units 33. The free end of the second rod 332 of the connecting unit 33 intersects the free end of the third rod 333 of the adjacent connecting unit 33 at a point A. The free end of the first rod 331 of the connecting unit 33 is located at point A of the connecting unit 33 in the adjacent row.

[0044] Specifically, such as Figure 5 As shown, the connecting unit 33 is generally Y-shaped, consisting of the first rod 331, the second rod 332, and the third rod 333. Multiple connecting units 33 are arranged in multiple layers on the base plate 32 along the left and right directions. Each layer of connecting units 33 includes multiple rows arranged sequentially along the up and down directions. Each row includes several connecting units 33 spaced apart along the front and back directions. The following uses the first connecting unit 334, the second connecting unit 335, the third connecting unit 336, and the fourth connecting unit 337 as examples to specifically illustrate the composition of the cooling component 3.

[0045] The first rod 331 of the first connecting unit 334, the first rod 331 of the second connecting unit 335, and the first rod 331 of the third connecting unit 336 are arranged in a first row along the left and right direction and are on the base. The third rod 333 of the first connecting unit 334 is connected to the first rod 331 of the second connecting unit 335 to form point A. The second rod 332 of the second connecting unit 335 is connected to the first rod 331 of the third connecting unit 336 to form point B. The fourth connecting unit 337 and the fifth connecting unit 338 are arranged in a second row along the left and right direction and are located above the first row. The lower end of the first rod 331 of the fourth connecting unit 337 is fixed at point A, and the lower end of the first rod 331 of the fifth connecting unit 338 is fixed at point B. The third rod 333 of the fourth connecting unit 337 and the second rod 332 of the fifth connecting unit 338 are connected. Thus, the cooling component 3 is set as a whole.

[0046] In some embodiments, the gas turbine transition section 100 with variable cross-section side-enhanced cooling further includes multiple cooling components 3, which are spaced apart within mounting holes 23 along the length of the transition section body 1. Specifically, as Figure 1 As shown, multiple cooling components 3 are spaced apart in the mounting holes 23 along the left and right directions. Thus, the cooling effect of the transition section body 1 is further improved by the multiple cooling components 3, and the service life of the transition section body 1 is extended.

[0047] In some embodiments, a connecting rod (not shown in the figure) is disposed between two adjacent cooling components 3, with both ends of the connecting rod connected to the two adjacent cooling components 3 respectively. Specifically, the transition section is a horizontal rod extending left and right, disposed between two adjacent cooling components 3, with the left and right ends of the horizontal rod welded to the two cooling components 3 respectively. This allows multiple cooling components 3 to form a whole through the connecting rod, preventing the cooling components 3 from shaking under the action of cooling gas and improving the stability of the multiple cooling components 3.

[0048] In some embodiments, the aperture of the multiple rows of turbulence holes 31 gradually decreases along the direction adjacent to the transition section body 1. Specifically, as Figure 4 As shown, on the same cooling component 3, the diameter of the lower row of turbulence holes 31 is smaller than that of the upper row of turbulence holes 31. In other words, the diameter of the first rod 331, the second rod 332 and the third rod 333 of the lower row of cooling components 3 is larger than that of the first rod 331, the second rod 332 and the third rod 333 of the upper row of cooling components 3. This ensures the strength of the lower end of the cooling component 3 and extends the service life of the cooling component 3.

[0049] In some embodiments, the mounting hole 23 is located near the turbine of the impact bushing 2, and the mounting hole 23 extends along the length of the impact bushing 2. Specifically, as Figure 1-2 As shown, the mounting hole 23 extends from the right end of the impact bushing 2 to the left. In other words, the mounting hole 23 is located on the right half of the impact bushing 2. Since the airflow at the left end of the airflow channel 21 needs to flow into the combustion chamber, the mounting hole 23 is located on the side adjacent to the outlet of the inner shell. This ensures that the airflow of the cooling gas in the combustion chamber is not affected, thus ensuring the working efficiency of the gas turbine.

[0050] In some embodiments, there are multiple mounting holes 23, which are spaced apart circumferentially along the impact bushing 2. There are also multiple cooling members 3, with at least one cooling member 3 disposed within each mounting hole 23. Specifically, as shown... Figure 1-2As shown, the number of mounting holes 23 can be set to multiple according to actual conditions. Multiple mounting holes 23 are equally spaced along the circumference of the impact bushing 2, and each mounting hole 23 is provided with multiple cooling components 3 spaced apart in the left and right directions. Thus, the cooling effect of the transition section body 1 is achieved through multiple mounting holes 23.

[0051] In some embodiments, the cooling components 3 are respectively connected to the outer peripheral surface of the transition section body 1 by welding. Specifically, the cooling components 3 can be integrally formed by additive manufacturing process, thereby reducing the processing and manufacturing process of the cooling components 3, and the cooling components 3 can be fixed to the outer peripheral surface of the transition section body 1 by welding, thereby making the cooling components 3 firmly fixed to the transition section body 1, and making the arrangement of the cooling components 3 and the transition section body 1 more reasonable.

[0052] In some embodiments, the gas turbine transition section 100 with variable cross-section side-cooled enhancement further includes a plurality of baffles 4. The plurality of baffles 4 are disposed in the airflow channel 21 and connected to the inner peripheral surface of the transition section body 1. The ratio of the surface area to the volume of the baffles 4 is A1, and the ratio of the area to the volume of the inner peripheral surface of the airflow channel 21 is A2. A1 is greater than A2 in order to improve the heat transfer coefficient of the transition section body 1. Specifically, multiple baffles 4 are connected in sequence and disposed within the airflow channel 21. All baffles 4 are connected to the inner circumferential surface of the transition section body 1. The ratio of the surface area of ​​the baffles 4 to the volume of the baffles 4 is A1, and the ratio of the surface area of ​​the inner circumferential surface of the airflow channel 21 to the volume of the airflow channel 21 is A2, and A1 is greater than A2 (in other words, the baffles 4 have a higher specific surface area, and under the same volume, the surface area of ​​the cooling air blowing over the baffles 4 is relatively large). The baffles 4 have a turbulent effect on the cooling air within the airflow channel 21. Therefore, the arrangement of the baffles 4 improves the heat transfer coefficient between the transition section body 1 and the impact bushing 2, and improves the cooling effect of the transition section body 1.

[0053] In some embodiments, such as Figure 5 As shown, the shape of the baffle 4 can be any one of the following: X-shaped lattice, Kagome lattice, or face-centered cubic lattice. Since lattice shapes have a larger specific surface area, for the same volume, the surface area of ​​the baffle 4 over which the airflow passes is larger. Therefore, the baffle 4 with a lattice shape has a better cooling effect, and also has higher strength and hardness, thereby improving its service life.

[0054] Because additive manufacturing offers advantages such as freeform manufacturing and rapid production, in some embodiments, the spoiler 4 is formed using additive manufacturing. Specifically, a single spoiler 4 can be integrally formed using additive manufacturing, and multiple spoilers 4 installed in the mounting cavity can also be integrally formed using additive manufacturing. This reduces the processing and manufacturing time of the spoiler 4 and ensures its manufacturing quality.

[0055] It is worth noting that the present invention does not limit the arrangement of multiple aerodynamic components 4, and multiple aerodynamic components 4 can be fixed together in sequence according to the actual situation.

[0056] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to 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 this invention.

[0057] Furthermore, the terms "first" and "second" 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, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0058] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0059] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0060] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0061] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A gas turbine transition section with variable cross-section side-enhanced cooling, characterized in that, include: The transition section body is used to transport the high-temperature gas generated in the combustion chamber to the turbine. An impact bushing is fitted onto the outer peripheral surface of the transition section body. The inner peripheral surface of the impact bushing and the outer peripheral surface of the transition section body are spaced apart to form an airflow channel. The impact bushing is provided with mounting holes that penetrate the impact bushing in the inward and outward directions. A cooling component is mounted on the inner circumferential surface of the transition section body through the mounting hole. The cooling component has multiple perforated flow-dispersing holes arranged in multiple rows along the height direction of the cooling component. Each row includes several flow-dispersing holes arranged in multiple rows along the length direction of the cooling component. The surface area to volume ratio of the cooling component is higher than the area to volume ratio of the inner circumferential surface of the airflow channel, in order to improve the heat transfer coefficient between the transition section body and the impact bushing. The cooling component includes a base plate and multiple connecting units. Each connecting unit includes a first rod, a second rod, and a third rod. The second rod and the third rod are both located at one end of the first rod. The extension directions of the second rod and the third rod intersect the extension direction of the first rod at an angle. The multiple connecting units are arranged in multiple rows along the height direction of the base plate, and each row of connecting units includes several sequentially arranged connecting units. The free end of the second rod of the connecting unit intersects at point A with the free end of the third rod of the adjacent connecting unit, and the free end of the first rod of the connecting unit is located at point A of the connecting unit in the adjacent row.

2. The gas turbine transition section with variable cross-section side-cooled reinforcement according to claim 1, characterized in that, The cooling component has a first part and a second part connected in sequence. The first part is disposed in the mounting hole, and the second part is disposed in the airflow channel and connected to the outer peripheral surface of the transition section body. A portion of the plurality of turbulence holes is located on the first part, and another portion of the plurality of turbulence holes is located on the second part.

3. The gas turbine transition section with variable cross-section side-cooled reinforcement according to claim 1, characterized in that, The impact bushing has a first side and a second side in its width direction. The mounting hole includes a first mounting hole and a second mounting hole, which are respectively formed on the first side and the second side. Both the first mounting hole and the second mounting hole are provided with the cooling component.

4. The gas turbine transition section with variable cross-section side-cooled reinforcement according to claim 1, characterized in that, The diameter of the multiple rows of turbulence holes gradually decreases along the direction adjacent to the transition section body.

5. The gas turbine transition section with variable cross-section side-cooled reinforcement according to claim 1, characterized in that, The mounting hole is located near the turbine of the impact bushing, and the mounting hole extends along the length of the impact bushing.

6. The gas turbine transition section with variable cross-section side-cooled reinforcement according to claim 1, characterized in that, There are multiple mounting holes, which are spaced apart circumferentially along the impact bushing. There are multiple cooling components, and at least one cooling component is provided in each mounting hole.

7. The gas turbine transition section with variable cross-section side-cooled reinforcement according to claim 1, characterized in that, The cooling components are respectively connected to the outer peripheral surface of the transition section body by welding.

8. The gas turbine transition section with variable cross-section side-cooled reinforcement according to any one of claims 1-7, characterized in that, It also includes multiple flow-disrupting elements, which are disposed in the airflow channel and connected to the inner circumferential surface of the transition section body. The ratio of the surface area to the volume of the flow-disrupting element is A1, and the ratio of the area to the volume of the inner circumferential surface of the airflow channel is A2. A1 is greater than A2 in order to improve the heat transfer coefficient of the transition section body.

9. The gas turbine transition section with variable cross-section side-cooled reinforcement according to claim 8, characterized in that, The shape of the disturbance element can be any one of the following: X-shaped lattice, Kagome lattice, or face-centered cubic lattice.

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