Annular meander combustion chamber

Abstract

This invention belongs to the field of aero-engines, specifically relating to an annular meandering combustor. A first flow channel is provided between the combustor casing and the flame tube; a second flow channel is provided between the flame tube and the central tie rod cavity; a third flow channel is provided between the combustor casing and the turbine guide vane; and a fourth flow channel is provided between the flame tube and the turbine guide vane. The first and third flow channels are connected, as are the second and fourth flow channels. A first exhaust flow channel of the flame tube is connected to a second exhaust flow channel of the turbine guide vane. A first and second intake structure are provided on the flame tube via the second flow channel, and a third intake structure is provided on the flame tube via the fourth flow channel. This invention can intervene in the flow direction of the airflow entering the flame tube, effectively constraining the area of ​​the large annular vortex, stabilizing the flame while improving combustor performance.

Description

Technical Field

[0001] This invention belongs to the field of aero-engines, and specifically relates to an annular meandering combustion chamber. Background Technology

[0002] The combustion chamber is a crucial component of an aero-engine, primarily consisting of the flame tube, combustion chamber casing, and fuel nozzles. During engine operation, the combustion chamber receives high-pressure air from the compressor and mixes it with aviation kerosene from the fuel system for combustion, producing high-temperature, high-pressure combustion gases that are then supplied to the turbine for power conversion. The aerodynamic and structural design of the combustion chamber directly affects reliable ignition and stable combustion, thus influencing the performance of both the combustion chamber and the overall engine.

[0003] Aero engines commonly use annular recirculation combustors and annular deflector combustors. In annular recirculation combustors, the flame tube has an exhaust section; air inside the flame tube rotates 180° before entering a radial or axial turbine, typically supplied with fuel via fuel injectors. In annular deflector combustors, the flame tube's internal passages are shaped like the letter "U". The combustion gases initially flow radially, forming a recirculation zone at the flame tube head, before flowing axially into the axial turbine, where fuel is supplied via an oil slinger.

[0004] Traditional annular recirculation combustion chambers are often located outside the turbine, resulting in a large combustion chamber diameter. Consequently, the matching compressor diameter is also large, which affects the increase of engine speed and is not conducive to optimizing the overall thrust-to-weight ratio.

[0005] Traditional annular deflector combustors are equipped with axial flow turbines at the tail end. Therefore, the diameter of the annular deflector combustor is much smaller than that of the annular recirculation combustor. However, the annular deflector combustor is often equipped with an oil slinger for fuel supply. Therefore, the combustor casing and flame tube need to be designed outside the oil slinger assembly and sealing ring assembly. If the fuel supply structure is optimized, the diameter of the combustor can be further reduced.

[0006] In traditional annular baffle combustors, the oil slinger is located between the inner and outer rings of the flame tube. Since the inner and outer rings cannot be welded together to form a single flame tube assembly, the flame tube of the baffle combustor generally needs to be formed during the overall machine assembly. Furthermore, relative positional constraints must be imposed, and the thickness of adjusting shims is used to ensure the positional accuracy meets requirements. Selecting the appropriate shim thickness requires repeated disassembly and reassembly of the combustor and the fabrication of a set of shims of varying thicknesses.

[0007] Traditionally, annular baffle walls are used to set main combustion holes and mixing holes for the air intake of the flame tube. The main combustion holes and mixing holes are often opened using laser drilling. When high-pressure air passes through the main combustion holes and mixing holes, it is often perpendicular to the wall surface, and the airflow penetration depth is relatively small. In addition, the high-pressure air entering the flame tube does not have a circumferential velocity component, resulting in poor performance in ignition and flame continuity and poor outlet non-uniformity.

[0008] Flame tube wall cooling often utilizes divergent orifices, which are angled relative to the wall surface for cooling. A smaller angle results in better divergent cooling; the angle is typically between 18° and 40°. However, when the high-pressure airflow is large, the pressure loss through the flame tube increases. Simply increasing the orifice diameter, for example, when the wall thickness and orifice diameter are the same, diminishes the effectiveness of the divergent cooling angle design, thus impacting wall cooling performance.

[0009] Film cooling structures utilize air-film cooling tanks, allowing air to flow through them and achieve cooling by adhering to the tank walls. Traditional film cooling tanks consist of an outer and an inner wall. The outer wall contacts a two-channel annular cavity, while the inner wall contacts the high-temperature combustion gas inside the flame tube. Air inlets are often machined into the outer wall using laser drilling; however, the size of the inlets and the distance between them are limited. Inlets that are too large or too small will affect the strength of the structure.

[0010] In view of this, the present invention is hereby proposed. Summary of the Invention

[0011] To address the technical problems existing in the prior art, the present invention provides an annular meandering combustion chamber. The present invention can intervene in the flow direction of the airflow entering the flame tube, effectively constrain the area of ​​the large annular vortex, stabilize the flame, and improve the performance of the combustion chamber.

[0012] This invention includes the following technical solutions:

[0013] This invention provides an annular meandering combustor, comprising a combustor casing, a turbine guide vane, a flame tube, and a central tie rod cavity. The flame tube and the central tie rod cavity are disposed within the combustor casing. A first flow channel is provided between the combustor casing and the flame tube, a second flow channel is provided between the flame tube and the central tie rod cavity, a third flow channel is provided between the combustor casing and the turbine guide vane, and a fourth flow channel is provided between the flame tube and the turbine guide vane. The first flow channel communicates with the third flow channel, and the second flow channel communicates with the fourth flow channel.

[0014] The first air outlet duct of the flame tube is connected to the second air outlet duct of the turbine guide;

[0015] The second flow channel is provided with a first air intake structure and a second air intake structure on the flame tube, and the fourth flow channel is provided with a third air intake structure on the flame tube.

[0016] Furthermore, the second air intake structure is disposed on the inner annular wall of the flame tube; preferably, the second air intake structure is cylindrical and is circumferentially inclined.

[0017] Furthermore, a mixing hole is provided on the flame tube located in the first outlet airflow channel; preferably, the mixing hole includes a first mixing hole and a second mixing hole, the first mixing hole connecting the first flow channel and the first outlet airflow channel, and the second mixing hole connecting the fourth flow channel and the first outlet airflow channel.

[0018] Furthermore, the fuel nozzle extends through the turbine guide and the flame tube assembly.

[0019] Furthermore, the third flow channel and the fourth flow channel are connected through a blade channel provided on the turbine guide; the fuel nozzle is disposed through the blade channel.

[0020] Furthermore, cooling channels are provided on the wall of the flame tube.

[0021] Furthermore, the cooling channel is connected to the combustion chamber of the flame tube.

[0022] Furthermore, the flame tube includes a large curved ring assembly and a small curved ring assembly. The cross-section of the large curved ring assembly is C-shaped, and the cross-section of the small curved ring assembly is S-shaped. The large curved ring assembly and the small curved ring assembly are connected by heat dissipation ring teeth to form a cooling channel. The first air intake structure and the second air intake structure are disposed on the large curved ring assembly, and the third air intake structure is disposed on the small curved ring assembly.

[0023] Furthermore, the large bend ring assembly includes a first ring wall, a second ring wall, and a third ring wall. The first ring wall and the second ring wall are connected by heat dissipation ring teeth to form a cooling channel. The second ring wall and the third ring wall are connected by heat dissipation ring teeth to form a cooling channel. The third ring wall is connected to the large bend ring assembly by heat dissipation ring teeth to form a cooling channel.

[0024] Wherein, the first annular wall is the outer annular wall of the flame tube, and the third annular wall is the inner annular wall of the flame tube;

[0025] Preferably, the first air intake structure is disposed on the second annular wall, and the second air intake structure is disposed on the third annular wall.

[0026] Furthermore, a partition plate connects the combustion chamber casing to the central tie rod cavity, forming an intake channel between the partition plate and the combustion chamber casing. A diffuser is installed at the intake position of the combustion chamber casing. By adopting the above technical solution, the present invention has the following advantages:

[0027] 1. This invention can intervene in the flow direction of the airflow entering the flame tube, effectively constrain the area of ​​the large annular vortex, stabilize the flame, and improve the performance of the combustion chamber.

[0028] 2. This invention strengthens the circumferential movement of the gas through a bottom-mounted sleeve structure with a circumferential tilt angle, effectively improving the ignition and flame continuity performance of the flame tube.

[0029] 3. By designing a cooling channel, this invention provides circumferential velocity to the high-temperature gas in the combustion chamber of the flame tube while ensuring the cooling performance of the flame tube wall, thereby improving the mixing performance.

[0030] 4. The first, second, and third air intake structures of the present invention constitute a flame stabilizing structure, which effectively controls the size of the main combustion zone of the combustion chamber and can form a large annular vortex at the bottom of the combustion chamber of the flame tube, which is beneficial to the stability of the flame; at the same time, the second air intake structure with a circumferential tilt angle can strengthen the circumferential movement of the gas and effectively improve the ignition and flame continuity performance in the flame tube.

[0031] 5. The fuel nozzle of the present invention passes through the combustion chamber casing, turbine guide and flame tube in sequence in the rear injection fuel supply structure, which replaces the traditional annular deflector combustion chamber oil slinger structure. This effectively reduces the diameter of the combustion chamber. At the same time, compared with the oil slinger structure, the rear injection fuel supply structure does not require adjusting the thickness of the adjusting shim. It also avoids the repeated disassembly and assembly of the combustion chamber caused by the wall surface adjusting the thickness of the adjusting shim, and has better installability.

[0032] 6. The heat dissipation ring teeth of the present invention control the circumferential velocity by adjusting the included angle between the ring wall and the ring teeth, and adjust the spacing between each ring tooth along the circumference to control the flow rate of cooling air at different positions in the circumference, which is beneficial to the control of wall temperature uniformity.

[0033] 7. This invention can be used in the combustion chamber of aircraft engines and auxiliary power units, as well as in low-emission and energy-saving combustion fields such as gas turbines that require premixing of fuel or gas with air.

[0034] 8. The present invention places the nozzle seat of the turbine guide within the blade channel, which can heat the fuel and improve the atomization performance of combustion.

[0035] Other features and advantages of the invention will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention can be realized and obtained by means of the structures pointed out in the description and the drawings. Attached Figure Description

[0036] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0037] Figure 1 This is a schematic cross-sectional view of the annular meandering combustion chamber at position 0 (0 o'clock position) in an embodiment of the present invention. Figure 1 ;

[0038] Figure 2 This is a schematic cross-sectional view of the annular meandering combustion chamber at position 0 (0 o'clock position) in an embodiment of the present invention. Figure 2 ;

[0039] Figure 3 This is a cross-sectional view of the flame tube in an embodiment of the present invention;

[0040] Figure 4 This is a partial structural diagram of the flame tube in an embodiment of the present invention. Figure 1 ;

[0041] Figure 5 This is a partial structural diagram of the flame tube in an embodiment of the present invention. Figure 2 ;

[0042] Figure 6 This is a schematic diagram of the structure of the large bend ring assembly in an embodiment of the present invention;

[0043] Figure 7 This is a schematic diagram of the small bend ring assembly in an embodiment of the present invention;

[0044] Figure 8 This is a schematic diagram of the connection structure of the heat dissipation ring teeth in an embodiment of the present invention;

[0045] Figure 9 This is a schematic diagram of the heat dissipation ring tooth structure in an embodiment of the present invention;

[0046] Figure 10 This is a schematic diagram of the combustion chamber casing in an embodiment of the present invention. Figure 1 ;

[0047] Figure 11 This is a schematic diagram of the combustion chamber casing in an embodiment of the present invention. Figure 2 ;

[0048] Figure 12 This is a schematic diagram of the turbine guide vane in an embodiment of the present invention. Figure 1 ;

[0049] Figure 13 This is a schematic diagram of the turbine guide vane in an embodiment of the present invention. Figure 2 ;

[0050] Figure 14 This is a schematic cross-sectional view of the annular meandering combustion chamber at position 0 (0 o'clock position) in an embodiment of the present invention. Figure 3 ;

[0051] In the diagram: 10-Combustion chamber casing, 101-Nozzle seat, 102-Electrical nozzle seat, 20-Turbine guide vane, 201-Blade passage, 202-Electrical nozzle seat for turbine guide vane, 30-Flame tube, 31-Large curved ring assembly, 311-First annular wall, 312-Second annular wall, 313-Third annular wall, 32-Small curved ring assembly, 301-First intake structure, 302-Second intake structure, 303-Third intake structure, 3041-First mixing orifice 3042-Second mixing hole, 305-Cooling channel, 306-Combustion chamber, 40-Center tie rod chamber, 50-First channel, 60-Second channel, 70-Third channel, 80-Fourth channel, 90-First outlet channel, 100-Second outlet channel, 110-Fuel nozzle, 120-Heat dissipation ring teeth, 121-Ring wall, 122-Ring teeth, 130-Baffle, 140-Intake channel, 150-Diffuser, 160-Ignition nozzle. Detailed Implementation

[0052] The following description provides many different embodiments or examples for implementing various features of the invention. The elements and arrangements described in the specific examples below are only for concise expression of the invention and are merely examples, not intended to limit the invention.

[0053] In the description of this invention, 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 indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0054] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection, an electrical connection, or a connection that allows for communication; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of multiple components or the interaction between multiple components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0055] In the description of this invention, it should be understood that all terms used to indicate orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are 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, and should not be construed as a limitation of this invention.

[0056] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0057] This embodiment provides an annular meandering combustion chamber, such as Figure 1 As shown, the system includes a combustion chamber casing 10, a turbine guide vane 20, a flame tube 30, and a central tie rod cavity 40. The combustion chamber casing 10 houses the flame tube 30 and the central tie rod cavity 40. A first flow channel 50 is provided between the combustion chamber casing 10 and the flame tube 30. A second flow channel 60 is provided between the flame tube 30 and the central tie rod cavity 40. A third flow channel 70 is provided between the combustion chamber casing 10 and the turbine guide vane 20. A fourth flow channel 80 is provided between the flame tube 30 and the turbine guide vane 20. The first flow channel 50 communicates with the third flow channel 70, and the second flow channel 60 communicates with the fourth flow channel 80.

[0058] The first air outlet duct 90 of the flame tube 30 is connected to the second air outlet duct 100 of the turbine guide 20;

[0059] The second flow channel 60 is provided with a first air intake structure 301 and a second air intake structure 302 on the flame tube 30, and the fourth flow channel 80 is provided with a third air intake structure 303 on the flame tube 30.

[0060] like Figure 2 As shown, based on this structure, it is possible to form [something] in the combustion chamber. Figure 2 The airflow direction shown effectively controls the size of the main combustion zone of the combustion chamber 306 of the flame tube 30, and can form a large annular vortex at the bottom of the combustion chamber 306, which is beneficial to the stability of the flame.

[0061] In some embodiments, the second air intake structure 302 is disposed on the inner annular wall of the flame tube 30; being disposed on the inner annular wall enables the air intake of the second air intake structure 302 to form an annular airflow, thereby achieving a better flame continuity effect.

[0062] Preferably, the second air intake structure 302 is cylindrical, such as... Figure 3 As shown, Figure 3The figure shows a cross-sectional view of the flame tube 30 at the second air intake structure 302. The second air intake structure 302 is circumferentially inclined. The cylindrical structure facilitates the circumferentially inclined setting of the second air intake structure 302, and makes it easier to control the tilt direction of the second air intake structure 302. The circumferentially inclined setting can achieve a better flame continuity effect.

[0063] In some embodiments, cooling channels 305 are provided on the wall of the flame tube 30. This has the advantage of reducing the temperature of the flame tube 30.

[0064] In some embodiments, the cooling channel 305 is connected to the combustion chamber 306 of the flame tube 30. This not only dissipates heat from the flame tube 30, but also allows the high-temperature combustion gas passing through the cooling channel 305 to enter the flame tube 30 for combustion, thus improving heat utilization.

[0065] It should be noted that there are no restrictions on the specific structure of the flame tube 30 described above. Any flame tube 30 structure that can achieve the above-mentioned airflow should be within the protection scope of this invention.

[0066] In some embodiments, such as Figure 4 , Figure 5 As shown, Figure 4 and Figure 5 The diagram shows the partial structure of the flame tube 30 from different perspectives. The flame tube 30 includes a large curved ring assembly 31 and a small curved ring assembly 32. The cross-section of the large curved ring assembly 31 is C-shaped, and the cross-section of the small curved ring assembly 32 is S-shaped. The large curved ring assembly 31 and the small curved ring assembly 32 are connected by heat dissipation ring teeth 120. This connection of heat dissipation ring teeth 120 forms a cooling channel 305 between the large curved ring assembly 31 and the small curved ring assembly 32, which has a cooling effect on the wall of the flame tube 30. At the same time, the heat dissipation airflow through the cooling channel 305 enters the combustion chamber 306 of the flame tube 30, providing circumferential velocity to the high-temperature gas in the combustion chamber 306 of the flame tube 30, improving the mixing performance. At the same time, the high-temperature gas can also be used for turbine power, which is beneficial to improving the thrust-to-weight ratio of the engine. The first air intake structure 301 and the second air intake structure 302 are disposed on the large curved ring assembly 31, and the third air intake structure 303 is disposed on the small curved ring assembly 32. In this way, the first air intake structure 301, the second air intake structure 302 and the third air intake structure 303 constitute a flame stabilizing structure, which effectively controls the size of the main combustion zone of the combustion chamber 306 and can form a large annular vortex at the bottom of the combustion chamber 306 of the flame tube 30, which is beneficial to the stability of the flame. At the same time, the second air intake structure 302 with a circumferential tilt angle can strengthen the circumferential movement of the gas, effectively improving the ignition and flame continuity performance in the flame tube 30.

[0067] It should be noted that the connection method via the heat dissipation ring teeth 120 is only a preferred method. Other connection methods should also be within the protection scope of this invention, such as welding, integral molding, etc.

[0068] like Figure 4 , Figure 5 As shown, the first air intake structure 301 can be a front sleeve, the second air intake structure 302 is a bottom sleeve, and the third air intake structure 303 is a rear sleeve.

[0069] In some embodiments, such as Figure 6 As shown, the large curved ring assembly 31 includes a first ring wall 311, a second ring wall 312, and a third ring wall 313. The first ring wall 311 and the second ring wall 312 are connected by heat dissipation ring teeth 120, the second ring wall 312 and the third ring wall 313 are connected by heat dissipation ring teeth 120, and the third ring wall 313 is connected to the large curved ring assembly 31 by heat dissipation ring teeth 120. The first ring wall 311 is the outer ring wall of the flame tube 30, and the third ring wall 313 is the inner ring wall of the flame tube 30. This structure is more conducive to heat dissipation of the flame tube 30.

[0070] Preferred, such as Figure 7 As shown, the first air intake structure 301 is provided on the second annular wall 312, and the second air intake structure 302 is provided on the third annular wall 313.

[0071] like Figure 8 As shown in the figure, the heat dissipation ring teeth 120 and cooling flow channels 305 are illustrated; the connection structures of the large curved ring assembly 31 (including the first ring wall 311, the second ring wall 312 and the third ring wall 313), the small curved ring assembly 32, etc., can all be as follows: Figure 8 The structure shown not only serves as a connector, but the structure and specific connection positions of the heat dissipation ring 120 also need to ensure that a cooling flow channel 305 can be formed after the connection; for example... Figure 9 The diagram shows a schematic of the structure of the heat dissipation ring tooth 120. The heat dissipation ring tooth 120 includes a ring wall 121 and ring teeth 122. The ring teeth 122 are arranged circumferentially inclined. Preferably, the inclined direction of the ring teeth 122 is consistent with the inclined direction of the second air intake structure 302 (bottom sleeve), which is more conducive to the mixing of gas entering the combustion chamber 306.

[0072] In some embodiments, such as Figures 4-7 As shown, a mixing hole is provided on the flame tube 30 located in the first outlet airflow channel 90; preferably, the mixing hole includes a first mixing hole 3041 and a second mixing hole 3042, the first mixing hole 3041 connecting the first flow channel 50 and the first outlet airflow channel 90, and the second mixing hole 3042 connecting the fourth flow channel 80 and the first outlet airflow channel 90. This has the effect of making the flame tube 30 dissipate heat evenly.

[0073] In some embodiments, such as Figure 14 As shown, the fuel nozzle 110 is disposed through the turbine guide 20 and the flame tube 30; preferably, as Figure 14 As shown, the fuel injector 110 is positioned rearward, which has the advantage of reducing the combustion chamber radius. Figure 10 , Figure 11 The diagram shows a schematic of the combustion chamber housing 10. The combustion chamber housing 10 is provided with a nozzle seat 101 for mounting fuel nozzles 110. There are six nozzle seats 101 arranged around the combustion chamber housing 100. It should be noted that the six nozzle seats 101 are only one specific implementation method. The combustion chamber housing 10 is also provided with an electric nozzle seat 102. Similarly, nozzle seats 101 are provided on the flame tube 30 and the turbine guide 20.

[0074] In some embodiments, the third flow channel 70 and the fourth flow channel 80 are connected through a blade passage 201 disposed on the turbine guide 20, and the fuel nozzle 110 is disposed through the blade passage 201. The fuel nozzle 110 can also be connected to the turbine guide 20 by providing a nozzle seat 101 on the turbine guide 20; since airflow passes through the blade passage 201, therefore... Figure 12 As shown, the nozzle seat 101 of the turbine guide 20 is placed inside the blade passage 201, which can heat the fuel and improve the combustion atomization performance.

[0075] In some embodiments, such as Figure 1 As shown, the combustion chamber casing 10 is connected to the central tie rod cavity 40 by a partition 130, and an air intake channel 140 is formed between the partition 130 and the combustion chamber casing 10. A diffuser 150 is provided at the air intake position of the combustion chamber casing 10.

[0076] It should be noted that the first air intake structure 301, the second air intake structure 302, the third air intake structure 303, the first mixing hole 3041, the second mixing hole 3042, the blade channel 201, etc., can all be arranged evenly around each other; the present invention does not limit the number of them arranged around each other.

[0077] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An annular meandering combustion chamber, comprising a combustion chamber casing (10), a turbine guide vane (20), a flame tube (30), and a central tie rod cavity (40), wherein the flame tube (30) and the central tie rod cavity (40) are disposed within the combustion chamber casing (10), characterized in that, A first flow channel (50) is provided between the combustion chamber casing (10) and the flame tube (30), a second flow channel (60) is provided between the flame tube (30) and the central tie rod cavity (40), a third flow channel (70) is provided between the combustion chamber casing (10) and the turbine guide (20), and a fourth flow channel (80) is provided between the flame tube (30) and the turbine guide (20); the first flow channel (50) is connected to the third flow channel (70), and the second flow channel (60) is connected to the fourth flow channel (80); The first outlet air passage (90) of the flame tube (30) is connected to the second outlet air passage (100) of the turbine guide (20); The second flow channel (60) has a first air intake structure (301) and a second air intake structure (302) on the flame tube (30), and the fourth flow channel (80) has a third air intake structure (303) on the flame tube (30). The second air intake structure (302) is disposed on the inner annular wall of the flame tube (30); the second air intake structure (302) is cylindrical and is circumferentially inclined. A fuel injector (110) is disposed through the turbine guide (20) and the flame tube (30); The third flow channel (70) and the fourth flow channel (80) are connected through a blade passage (201) provided on the turbine guide (20); the fuel nozzle (110) is provided through the blade passage (201); The flame tube (30) includes a large bend ring assembly (31) and a small bend ring assembly (32). The cross-section of the large bend ring assembly (31) is C-shaped, and the cross-section of the small bend ring assembly (32) is S-shaped. The large bend ring assembly (31) and the small bend ring assembly (32) are connected by heat dissipation ring teeth (120) to form a cooling channel (305). The first air intake structure (301) and the second air intake structure (302) are disposed on the large bend ring assembly (31), and the third air intake structure (303) is disposed on the small bend ring assembly (32). The heat dissipation ring tooth (120) includes a ring wall (121) and ring teeth (122), wherein the ring teeth (122) are circumferentially inclined; the heat dissipation ring tooth (120) controls the circumferential velocity by adjusting the included angle between the ring wall (121) and the ring teeth (122), and adjusts the spacing between each ring tooth (122) along the circumference to control the flow rate of cooling air at different circumferential positions.

2. The annular meandering combustion chamber according to claim 1, characterized in that, A mixing hole is provided on the flame tube (30) located in the first outlet airflow channel (90).

3. The annular meandering combustion chamber according to claim 2, characterized in that, The mixing hole includes a first mixing hole (3041) and a second mixing hole (3042). The first mixing hole (3041) is connected to the first flow channel (50) and the first outlet flow channel (90). The second mixing hole (3042) is connected to the fourth flow channel (80) and the first outlet flow channel (90).

4. The annular meandering combustion chamber according to claim 1, characterized in that, The flame tube (30) is provided with cooling channels (305) on its wall.

5. The annular meandering combustion chamber according to claim 4, characterized in that, The cooling channel (305) is connected to the combustion chamber (306) of the flame tube (30).

6. The annular meandering combustion chamber according to claim 1, characterized in that, The large bend ring assembly (31) includes a first ring wall (311), a second ring wall (312), and a third ring wall (313). The first ring wall (311) and the second ring wall (312) are connected by heat dissipation ring teeth (120) to form a cooling channel (305). The second ring wall (312) and the third ring wall (313) are connected by heat dissipation ring teeth (120) to form a cooling channel (305). The third ring wall (313) is connected to the large bend ring assembly (31) by heat dissipation ring teeth (120) to form a cooling channel (305). The first annular wall (311) is the outer annular wall of the flame tube (30), and the third annular wall (313) is the inner annular wall of the flame tube (30).

7. The annular meandering combustion chamber according to claim 6, characterized in that, The first air intake structure (301) is provided on the second annular wall (312), and the second air intake structure (302) is provided on the third annular wall (313).

8. An annular meandering combustion chamber according to any one of claims 6-7, characterized in that, The combustion chamber casing (10) is connected to the central tie rod cavity (40) by a partition (130), and an air intake channel (140) is formed between the partition (130) and the combustion chamber casing (10). A diffuser (150) is provided at the air intake position of the combustion chamber casing (10).

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