Side-cooled gas turbine transition section and gas turbine

Abstract

This invention discloses a side-cooled gas turbine transition section and a gas turbine. The side-cooled gas turbine transition section includes an outer shell, an inner shell, and a baffle member. The inner shell is fitted inside the outer shell and spaced apart along the inner and outer directions to form airflow channels. The outer shell has an air inlet communicating with the airflow channels, so that cooling air flows into the airflow channels through the air inlet to reduce the temperature of the inner shell. The outer shell has a mounting hole penetrating the outer shell along its thickness direction, communicating with the airflow channels. The baffle member is disposed in the mounting hole to agitate the airflow flowing into the mounting hole. The ratio of the surface area to the volume of the baffle member is A1, and the ratio of the area to the volume of the sidewall of the mounting hole is A2, where A1 is greater than A2. At least a portion of the baffle member is located within the airflow channels and connected to the outer peripheral surface of the inner shell to improve the heat transfer coefficient of the inner shell. The side-cooled gas turbine transition section of this invention has the advantages of simple structure and good cooling effect.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, specifically to a gas turbine transition section with enhanced side cooling and a gas turbine. 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 invention is based on the inventor's discoveries and understanding of the following facts and problems:

[0006] 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.

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

[0008] The embodiments of the present invention propose a gas turbine with low pressure loss and high gas turbine efficiency.

[0009] The gas turbine transition section with enhanced side cooling according to an embodiment of the present invention includes: an outer shell and an inner shell, the inner shell being sleeved inside the outer shell and spaced apart along the inner and outer directions to form an airflow channel, the outer shell having an air inlet communicating with the airflow channel so that cooling gas flows into the airflow channel through the air inlet to reduce the temperature of the inner shell, the outer shell having a mounting hole penetrating the outer shell along its thickness direction, the mounting hole communicating with the airflow channel; and a turbulence member disposed in the mounting hole so that the turbulence member disturbs the airflow flowing into the mounting hole, the ratio of the surface area to the volume of the turbulence member being A1, the ratio of the area to the volume of the inner circumferential surface of the airflow channel being A2, A1 being greater than A2, and at least a portion of the turbulence member being located within the airflow channel and connected to the outer circumferential surface of the inner shell to improve the heat transfer coefficient of the inner shell.

[0010] The gas turbine transition section with enhanced side cooling of the present invention is equipped with a turbulence-inducing component, 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 efficiency of the gas turbine.

[0011] In some embodiments, there are multiple mounting holes, which are spaced apart circumferentially along the housing. Each mounting hole is provided with multiple flow-disrupting components, which are arranged in multiple rows along the inward and outward directions. Each row includes several flow-disrupting components arranged sequentially along the length direction of the mounting holes.

[0012] In some embodiments, the inner shell has a chamber, an inlet, and an outlet, both of which are in communication with the chamber. The inlet is adapted to communicate with a combustion chamber so that high-temperature gas in the combustion chamber flows into the chamber. The outlet is adapted to connect with a turbine so that high-temperature gas flowing out of the inner shell flows into the turbine to drive the turbine to do work. The cross-sectional area of ​​the inner circumferential surface of the chamber gradually decreases along the length of the inner shell on the side adjacent to the outlet.

[0013] In some embodiments, the mounting hole is located on the side adjacent to the outlet of the inner shell, and the mounting hole extends along the length of the outer shell.

[0014] In some embodiments, there are multiple baffles, which can be divided into multiple parts. At least one baffle is disposed in the mounting cavity, and the remaining multiple baffles are disposed in the airflow channel and spaced apart circumferentially along the inner shell.

[0015] In some embodiments, the housing has a first side and a second side in its width direction, and the mounting holes include 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 a plurality of baffles.

[0016] In some embodiments, the shape of the turbulence-disrupting component is any one of an X-shaped lattice shape, a Kagome lattice shape, or a face-centered cubic lattice shape.

[0017] In some embodiments, there are multiple air inlets, which are arranged in multiple rows along the length of the housing, with each row including a plurality of air inlets arranged circumferentially along the housing.

[0018] In some embodiments, the turbulence-causing component is formed by an additive manufacturing process.

[0019] A gas turbine according to an embodiment of the present invention includes: a combustion chamber for generating high-temperature gas; a turbine for using the high-temperature gas to perform work, so as to convert the internal energy of the high-temperature gas into mechanical energy; and a transition section, which is any of the transition sections described in the above embodiments, with both ends of the transition section connected to the combustion chamber and the turbine respectively, so that the high-temperature gas generated by the combustion chamber is transported to the turbine through the transition section. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure of the gas turbine transition section with enhanced side cooling according to an embodiment of the present invention.

[0021] Figure 2 yes Figure 1 Sectional view of AA.

[0022] Figure 3 This is the outer shell of the gas turbine transition section with enhanced side cooling according to an embodiment of the present invention.

[0023] Figure 4 This is a turbulence-inducing component for the transition section of a gas turbine with enhanced side cooling, as described in this embodiment of the invention.

[0024] Transition section 100;

[0025] 1. Outer casing; 11. Airflow channel; 12. Air inlet; 13. Mounting hole; 131. First mounting hole; 132. Second mounting hole; 14. First side; 15. Second side;

[0026] Inner shell 2;

[0027] 3. Fluid deflector; 4. Cooling gas. Detailed Implementation

[0028] 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.

[0029] A gas turbine according to an embodiment of the present invention will now be described with reference to the accompanying drawings.

[0030] like Figure 1-4 As shown, the gas turbine according to an embodiment of the present invention includes a combustion chamber (not shown in the figure), a turbine (not shown in the figure), and a transition section 100.

[0031] The combustion chamber is used to generate high-temperature gas. The turbine uses the high-temperature gas to do work, thereby converting the internal energy of the high-temperature gas into mechanical energy. Specifically, the combustion chamber is located on the left side of the transition section 100, and the turbine is located on the right side of the transition section 100, with the combustion chamber and turbine spaced apart in the left-right direction. Fuel can be burned in the combustion chamber to generate high-temperature gas, and the turbine can use the thermal energy of the high-temperature gas to rotate, thus converting the thermal energy of the high-temperature gas into mechanical energy.

[0032] The two ends of the transition section 100 are connected to the combustion chamber and the turbine, respectively, so that the high-temperature gas generated in the combustion chamber can be transported to the turbine through the transition section 100. Specifically, the transition section 100 extends in the left-right direction, with the left end of the transition section 100 connected to the combustion chamber and the right end of the transition section 100 connected to the turbine, so that the high-temperature gas generated in the combustion chamber can flow into the turbine shown through the transition section 100.

[0033] The transition section 100 includes an outer shell 1, an inner shell 2, and a flow-deflecting component 3.

[0034] The inner shell 2 is fitted inside the outer shell 1 and spaced apart along the inner and outer directions to form an airflow channel 11. The outer shell 1 is provided with an air inlet 12 communicating with the airflow channel 11, so that cooling air 4 flows into the airflow channel 11 through the air inlet 12 to reduce the temperature of the inner shell 2. The outer shell 1 is provided with a mounting hole 13 penetrating the outer shell 1 along its thickness direction, and the mounting hole 13 communicating with the airflow channel 11. Specifically, as shown... Figure 1-3 As shown, the left end of the inner shell 2 is connected to the combustion chamber, and the right end of the inner shell 2 is connected to the turbine, so that the high-temperature gas generated in the combustion chamber flows into the combustion chamber through the inner shell 2. The inner circumferential surface of the outer shell 1 and the outer circumferential surface of the inner shell 2 are spaced apart in the inward and outward directions to form an airflow channel 11. The outer circumferential surface of the outer shell 1 is provided with an air inlet 12 that penetrates the outer shell 1 in the inward and outward directions. The cooling gas 4 can flow into the airflow channel 11 through the air inlet 12, so as to cool the inner shell 2, prevent the inner shell 2 from being damaged by the high-temperature gas, and extend the service life of the inner shell 2.

[0035] A flow-deflecting member 3 is disposed within the mounting hole 13 to agitate the airflow flowing into the mounting hole 13. The ratio of the surface area to the volume of the flow-deflecting member 3 is A1, and the ratio of the area to the volume of the inner circumferential surface of the airflow channel 11 is A2, where A1 is greater than A2. At least a portion of the flow-deflecting member 3 is located within the airflow channel 11 and connected to the outer circumferential surface of the inner shell 2 to improve the heat transfer coefficient of the inner shell 2. Specifically, as shown... Figure 1-3 As shown, a portion of the turbulence-disrupting component 3 is disposed within and connected to the mounting hole 13, while another portion of the turbulence-disrupting component 3 is located within the airflow channel 11 and connected to the inner circumferential surface of the outer shell 1. The ratio of the surface area to the volume of the turbulence-disrupting component 3 is A1, and the ratio of the surface area to the volume of the inner circumferential surface of the airflow channel 11 is A2, with A1 being greater than A2. (In other words, the turbulence-disrupting component 3 has a higher specific surface area, and under the same volume, the surface area of ​​the cooling gas 4 blowing over the turbulence-disrupting component 3 is relatively large.) Furthermore, the turbulence-disrupting component 3 has a turbulent effect on the cooling gas 4 within the airflow channel 11. Therefore, the arrangement of the turbulence-disrupting component 3 improves the heat transfer coefficient between the inner shell 2 and the outer shell 1, thereby improving the cooling effect of the inner shell 2.

[0036] The gas turbine transition section 100 with enhanced side cooling in this embodiment of the invention is provided with a turbulence member 3. The turbulence member 3 improves the heat transfer coefficient between the inner shell 2 and the outer shell 1, thereby improving the cooling effect of the transition section 100 and extending its service life. In addition, the spoon-shaped guide structure in related technologies is eliminated, reducing the flow loss of cooling gas. Furthermore, the installation hole 13 can improve the airflow of cooling gas 4 into the airflow channel 11, thereby improving the airflow of cooling gas 4 into the combustion chamber from the airflow channel 11, reducing the pressure loss in the combustion chamber, and thus improving the gas turbine efficiency.

[0037] The gas turbine of this invention has advantages such as simple structure and long service life.

[0038] In some embodiments, there are multiple mounting holes 13, which are spaced apart circumferentially along the outer casing 1. Each mounting hole 13 is provided with multiple flow-dispersing members 3, which are arranged in multiple rows along the inward and outward directions. Each row includes a number of flow-dispersing members 3 arranged sequentially along the length direction of the mounting holes 13. Specifically, as shown... Figure 1-3 As shown, the number of mounting holes 13 can be set to multiple according to actual conditions. In this embodiment of the invention, the outer shell 1 of the gas turbine transition section 100 with side-enhanced cooling is provided with two (e.g., Figure 3 As shown, two mounting holes 13 are equally spaced along the circumference of the outer shell 1. Multiple flow-dispersing components 3 are arranged in multiple rows along the inner and outer directions. Each row includes several flow-dispersing components 3 arranged sequentially in the left and right directions. Thus, the cooling effect of the transition section 100 is improved by multiple mounting holes 13 and multiple flow-dispersing components 3.

[0039] In some embodiments, the inner shell 2 has a chamber, an inlet, and an outlet, both of which communicate with the chamber. The inlet is adapted to communicate with a combustion chamber so that high-temperature gas from the combustion chamber flows into the chamber. The outlet is adapted to connect with a turbine so that high-temperature gas flowing out of the inner shell 2 flows into the turbine to drive the turbine to perform work. The cross-sectional area of ​​the inner circumferential surface of the chamber gradually decreases along the length of the inner shell 2 on the side adjacent to the outlet. Specifically, as shown... Figure 2 As shown, the inlet is located at the left end of the inner shell 2 and is connected to the outlet of the combustion chamber, while the outlet is located at the right end of the inner shell 2 and is connected to the inlet of the turbine. This allows the high-temperature gas generated in the combustion chamber to flow into the turbine through the inner shell 2. The cross-sectional area of ​​the inner circumferential surface of the chamber gradually decreases from left to right, which facilitates the flow of high-pressure gas generated in the combustion chamber into the chamber. After being pressurized by the chamber, the gas flows into the turbine, improving the working efficiency of the gas turbine.

[0040] In some embodiments, the mounting hole 13 is provided on one side adjacent to the outlet of the inner shell 2, and the mounting hole 13 extends along the length direction of the outer shell 1. Specifically, as shown in the figure... Figure 1 and Figure 3 As shown, the mounting hole 13 extends from the right end of the outer casing 1 to the left. In other words, the mounting hole 13 is located in the right half of the outer casing 1. Since the airflow at the left end of the airflow channel 11 needs to flow into the combustion chamber, the mounting hole 13 is located on the side adjacent to the outlet of the inner casing 2. This ensures that the airflow of the cooling gas 4 in the combustion chamber is not affected, thus ensuring the working efficiency of the gas turbine.

[0041] In some embodiments, there are multiple baffle members 3, which can be divided into multiple parts. At least one baffle member 3 is disposed in the mounting cavity, and the remaining multiple baffle members 3 are disposed in the airflow channel 11 and are spaced apart along the circumference of the inner shell 2. Specifically, the baffle members 3 can be configured into multiple parts according to actual conditions. One baffle member 3 is disposed in the mounting cavity and connected to the outer circumferential surface of the inner shell 2, and the remaining baffle members 3 are disposed in the airflow channel 11 and connected to the inner shell 2. This further improves the cooling effect of the transition section 100.

[0042] In some embodiments, the turbulence-disrupting member 3 is welded to the inner shell 2 and the outer shell 1, respectively. Specifically, the outer peripheral surface of the turbulence-disrupting member 3 is welded to the inner peripheral surface of the mounting hole 13 and the outer peripheral surface of the inner shell 2, thereby making the connection between the turbulence-disrupting member 3, the inner shell 2 and the outer shell 1 more robust and reducing the processing and manufacturing cost of the gas turbine transition section 100 with enhanced side cooling.

[0043] In some embodiments, such as Figure 4As shown, the shape of the flow-deflecting component 3 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 flow-deflecting component 3 over which the airflow passes is larger. Therefore, the flow-deflecting component 3 has a better cooling effect, and it also has higher strength and hardness, thus improving its service life.

[0044] Since the cooling air 4 flows from the outside of the outer casing 1 into the interior through the air inlet 12 to create an impact, the intensity of the impact depends on the pressure difference between the inside and outside of the outer casing 1. The pressure difference between the inside and outside of the outer casing 1 is approximately the same throughout the entire transition section 100. However, because the flow velocity on the front and rear sides of the outer casing 1 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). Consequently, the cooling effect on the front and rear sides of the outer casing 1 is poor. Therefore, in some embodiments, the outer casing 1 in its width direction (e.g., Figure 2 The front and rear directions shown have a first side 14 and a second side 15. The mounting holes include a first mounting hole 131 and a second mounting hole 132. The first mounting hole 131 and the second mounting hole 132 are respectively formed on the first side 14 and the second side 15. Both the first mounting hole 131 and the second mounting hole 132 are provided with multiple turbulence-disrupting components 3.

[0045] Specifically, such as Figure 2-3 As shown, a first side 14 is formed on the front side of the housing, and a second side 15 is formed on the rear side of the housing. A first mounting hole 131 is provided on the first side 14, and a second mounting hole 132 is provided on the second side 15. (In other words, the first mounting hole 131 is formed on the front side of the right end of the housing, and the second mounting hole 132 is formed on the rear side of the right end of the housing.) Thus, by setting the first mounting hole 131 and the second mounting hole 132, the heat transfer coefficient of the front and rear sides of the housing 1 is improved, the cooling effect of the transition section 100 is improved, and the service life of the transition section 100 is extended.

[0046] In some embodiments, such as Figure 1 and Figure 3 As shown, there are multiple air inlets 12, which are arranged in multiple rows along the length of the outer shell 1. Each row includes several air inlets 12 spaced apart along the circumference of the outer shell 1. Thus, the air intake of the airflow channel 11 is increased through multiple air inlets 12, ensuring the cooling effect of the inner shell 2.

[0047] Because additive manufacturing offers advantages such as freeform manufacturing and rapid production, in some embodiments, the aerodynamic component 3 is formed using additive manufacturing. Specifically, a single aerodynamic component 3 can be integrally formed using additive manufacturing, and multiple aerodynamic components 3 installed in the mounting cavity can also be integrally formed using additive manufacturing. This reduces the processing and manufacturing time of the aerodynamic component 3 and ensures its manufacturing quality.

[0048] It is worth noting that the present invention does not limit the arrangement of multiple flow-disrupting components 3, and multiple flow-disrupting components 3 can be fixed together in sequence according to the actual situation.

[0049] 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.

[0050] 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.

[0051] 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.

[0052] 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.

[0053] 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.

[0054] 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 side- cooled gas turbine transition piece characterized by, include: The outer shell and the inner shell are fitted inside the outer shell and spaced apart in the inward and outward directions to form an airflow channel. The outer shell is provided with an air inlet communicating with the airflow channel so that cooling air flows into the airflow channel through the air inlet to reduce the temperature of the inner shell. The outer shell is provided with a mounting hole that penetrates the outer shell along its thickness direction and communicates with the airflow channel. A flow-disrupting component is provided within the mounting hole to agitate the airflow flowing into the mounting hole. The ratio of the surface area to the volume of the flow-disrupting component is A1, and the ratio of the area to the volume of the inner circumferential surface of the airflow channel is A2, where A1 is greater than A2. At least a portion of the flow-disrupting component is located within the airflow channel and connected to the outer circumferential surface of the inner shell to improve the heat transfer coefficient of the inner shell. Multiple mounting holes are provided, spaced apart circumferentially along the outer shell. Each mounting hole is provided with multiple flow-disrupting components, arranged in multiple rows along the inner and outer directions. Each row includes several flow-disrupting components arranged sequentially along the length of the mounting holes. The inner shell has a chamber, an inlet, and an outlet. The mounting hole is located on the side adjacent to the outlet of the inner shell and extends along the length of the outer shell.

2. The side-plenum-cooled gas turbine transition piece of claim 1, wherein, Both the inlet and the outlet are connected to the chamber. The inlet is adapted to be connected to the combustion chamber so that high-temperature gas in the combustion chamber flows into the chamber. The outlet is adapted to be connected to the turbine so that high-temperature gas flowing out of the inner shell flows into the turbine to drive the turbine to do work. The cross-sectional area of ​​the inner circumferential surface of the chamber gradually decreases along the side adjacent to the outlet in the length direction of the inner shell.

3. The side-plenum-cooled gas turbine transition piece of claim 1, wherein, There are multiple turbulence-disrupting components, which can be divided into multiple parts. At least one part of the turbulence-disrupting component is disposed in the mounting hole, and the remaining multiple parts of the turbulence-disrupting component are disposed in the airflow channel and are spaced apart along the circumference of the inner shell.

4. The gas turbine transition section with enhanced side cooling according to claim 1, characterized in that, The housing has a first side and a second side in its width direction. The mounting holes include a first mounting hole and a second mounting hole. 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 and the second mounting hole are provided with a plurality of the aforementioned baffles.

5. The gas turbine transition section with enhanced side cooling according to any one of claims 1-4, characterized in that, The shape of the turbulence-disrupting component can be any one of the following: X-shaped lattice, Kagome lattice, or face-centered cubic lattice.

6. The gas turbine transition section with enhanced side cooling according to any one of claims 1-4, characterized in that, There are multiple air inlets, which are arranged in multiple rows along the length of the outer shell. Each row includes several air inlets arranged circumferentially along the outer shell.

7. The gas turbine transition section with enhanced side cooling according to any one of claims 1-4, characterized in that, The aerodynamic component is formed by additive manufacturing.

8. A gas turbine, characterized in that, include: Combustion chamber, the combustion chamber being used to generate high-temperature gas; A turbine that uses the high-temperature gas to do work in order to convert the internal energy of the high-temperature gas into mechanical energy; The transition section is the transition section described in any one of claims 1-7, and the two ends of the transition section are respectively connected to the combustion chamber and the turbine, so that the high-temperature gas generated in the combustion chamber is transported to the turbine through the transition section.

Images