Combustion chamber head structure and combustion chamber

Abstract

The application belongs to the technical field of engines, and proposes a combustion chamber head structure and a combustion chamber. The combustion chamber head structure comprises a head ring and a guide plate. The inner wall of the guide plate is sleeved with a vortex generator. A fuel nozzle cap cover is inserted into the vortex generator to form a swirl cup structure. A plurality of blowout holes for blowing off carbon are arranged on the side wall of the fuel nozzle cap cover to realize the fuel flushing of the nozzle shell blowout port, effectively inhibit the fuel adhesion on the nozzle shell blowout port and the nozzle end face, and ensure the long-time work of the nozzle shell. Meanwhile, in combination with the vortex generator, the extinguishing margin of the ground slow speed and the air slow speed is expanded while meeting the long-life work of the nozzle.

Description

Technical Field

[0001] This invention belongs to the field of engine technology, and specifically relates to a combustion chamber head structure and a combustion chamber. Background Technology

[0002] For the design of aero-engine combustors, not only is good design point performance required, but also excellent lean-fuel shutdown characteristics are needed to prevent lean-fuel shutdown when the engine is shifted from high-power to low-power operation. To address lean-fuel shutdown, aero-engines require the combustor to operate stably at a fuel-air ratio of 0.005. In addition, when the engine is shifted from high power to low power, the nozzle housing atomization deteriorates, and the nozzle surface temperature drops suddenly, creating a temperature difference that makes the nozzle prone to carbon buildup, which is detrimental to the long-term operation of the combustor.

[0003] To meet the aforementioned comprehensive performance requirements and long nozzle lifespan, the main methods for improving lean combustion and preventing flameout are as follows: For the flow field, this is primarily achieved by enhancing the recirculation zone to improve combustion stability. In the main combustion zone, a larger low static pressure area is created in the swirl cup, causing the gas to flow back towards the swirl cup under the influence of the reverse pressure gradient. With the assistance of the upper and lower rows of main combustion orifices, a relatively large axisymmetric recirculation zone is formed in the main combustion zone, which is beneficial for fuel-air mixing and increasing mixing time. For the oil mist field, this mainly involves increasing the local fuel concentration or, while ensuring atomization fineness, making the oil mist particle size as relatively dispersed as possible, which is beneficial for stable combustion under low operating conditions. For nozzle carbon buildup prevention, this is often achieved by suppressing the recirculation of high-temperature combustion gases. However, this requires designing the Venturi throat of the swirl converter to be sufficiently small to increase the axial velocity of the swirl converter, while simultaneously reducing its outlet size. This also reduces the recirculation zone area of ​​the combustion chamber, which is detrimental to stable lean combustion.

[0004] Therefore, overcoming the shortcomings of the existing technology is an urgent problem to be solved in this technical field. Summary of the Invention

[0005] To address the aforementioned problems, this invention proposes a combustion chamber head structure, comprising: a head ring, with a through hole and an air inlet at the end of the head ring, a guide plate coaxially sleeved on the inner wall of the through hole, a vortex generator sleeved on the inner wall of the guide plate, a through cavity coaxially formed in the vortex generator, and a through groove formed on the side wall of the vortex generator connecting the through cavity and the inner cavity of the combustion chamber, one end of the through cavity connecting to the inner cavity of the head ring, and the other end of the through cavity coaxially sleeved on the outer wall of the fuel nozzle cap, the inner wall of the fuel nozzle cap coaxially sleeved on the outer wall of the nozzle housing; The nozzle housing has an outlet facing the through cavity. The fuel nozzle cap has a working port corresponding to the outlet facing the through cavity. Several carbon-blowing holes are opened on the side wall of the fuel nozzle cap. An annular groove is opened on the inner wall of the fuel nozzle cap. One end of the annular groove is connected to the carbon-blowing hole, and the other end of the annular groove faces the outlet direction of the nozzle housing.

[0006] Furthermore, the annular groove includes connected axial groove sections and radial groove sections. One end of the radial groove section is connected to the input end of several nozzle carbon-depositing holes, and one end of the axial groove section faces the nozzle direction of the nozzle housing.

[0007] Furthermore, the centerlines of several nozzle carbon-depositing holes form an acute angle with the centerline of the fuel nozzle cap, and the axial groove section forms an obtuse angle with the radial groove section.

[0008] Furthermore, the diameter of some nozzle carbon-depositing holes is 1.37 mm to 1.43 mm.

[0009] Furthermore, the vortex generator includes a first-stage vortex generator, a venturi tube, and a second-stage vortex generator connected coaxially in sequence. The through-slot includes a first-stage vortex slot and a second-stage vortex slot. The first-stage vortex generator has several first-stage vortex slots arranged in a circumferential array on the side wall of the venturi tube, and the second-stage vortex generator has several second-stage vortex slots arranged in a circumferential array on the side wall of the venturi tube. Both the first-stage and second-stage vortex slots are connected to the through-cavity and the combustion chamber cavity.

[0010] Furthermore, the radial axis of several primary swirl channels maintains a first angle with the axis of the vortex generator, and the radial axis of several secondary swirl channels maintains a second angle with the axis of the vortex generator, with the first angle and the second angle having opposite directions.

[0011] Furthermore, both the primary and secondary vortex tanks adopt square through slots. The width of the primary vortex tank is 1.58mm to 1.62mm, and the radial height is 5.47mm to 5.53mm. The width of the secondary cyclone trough is 1.58mm to 1.62mm, and the radial height is 9.47mm to 9.53mm.

[0012] Furthermore, the number of secondary swirl cells is an even number more than the number of primary swirl cells.

[0013] Furthermore, the ratio of the effective area of ​​the first-stage eddy current generator to the throat area of ​​the venturi tube is 0.30 to 0.35.

[0014] The present invention also proposes a combustion chamber including a combustion chamber head structure as described above, and further including: a diffuser, inner and outer ring casings, an inner wall of the flame tube, an outer casing of the combustion chamber, and an outer wall of the flame tube; The inner and outer ring casings and the outer casing of the combustion chamber form the inner cavity of the combustion chamber. One end of the inner cavity of the combustion chamber is connected to the output end of the diffuser. The inner wall of the flame tube, the outer wall of the flame tube, and the head structure of the combustion chamber are all housed in the inner cavity of the combustion chamber. The inner wall of the flame tube, the outer wall of the flame tube, and the head structure of the combustion chamber form the inner cavity of the flame tube.

[0015] Compared with the prior art, the embodiments of the present invention have at least the following advantages: The combustion chamber head structure proposed in this application, in actual use, delivers pressurized fuel from the nozzle housing nozzle orifice to the through cavity and the inner cavity of the head annulus, thereby satisfying the subsequent fuel combustion operation in the inner cavity of the head annulus. At the same time, the gas in the combustion chamber cavity from the outside enters the annular groove through several nozzle carbon-depositing holes. The gas output from the annular groove flushes the fuel at the nozzle housing nozzle orifice and reduces the temperature of the nozzle housing nozzle orifice, expanding the lean fuel shut-off margin of the combustion chamber and ensuring stable combustion. In addition, it effectively suppresses fuel adhesion at the nozzle housing nozzle orifice and nozzle end face, improving the long-term reliability of the combustion chamber. Furthermore, combined with the vortex generator, it expands the shut-off margin of the engine at ground idle and air idle, ensuring stable lean fuel combustion and overall comprehensive performance.

[0016] 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 may be realized and obtained by means of the structures pointed out in the description and the drawings. Attached Figure Description

[0017] 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.

[0018] Figure 1 A schematic diagram of the combustion chamber head structure in an embodiment of the present invention is shown; Figure 2 A partial schematic diagram of the combustion chamber head structure in an embodiment of the present invention is shown; Figure 3 A cross-sectional schematic diagram of the vortex generator in an embodiment of the present invention is shown; Figure 4 A side view of the vortex generator in an embodiment of the present invention is shown; Figure 5 A cross-sectional schematic diagram of a first-stage eddy current generator in an embodiment of the present invention is shown; Figure 6 A cross-sectional schematic diagram of a two-stage eddy current generator in an embodiment of the present invention is shown; Figure 7 A schematic diagram of the lean flameout margin of the combustion chamber head structure in an embodiment of the present invention is shown; Figure 8 A schematic diagram of the combustion chamber in an embodiment of the present invention is shown.

[0019] In the diagram, 1. Head ring; 2. Air intake port; 3. Baffle plate; 4. Swirl generator; 401. First-stage swirl generator; 402. Venturi tube; 403. Second-stage swirl generator; 404. First-stage swirl groove; 405. Second-stage swirl groove; 5. Fuel nozzle cap; 6. Nozzle housing; 7. Nozzle carbon removal hole; 8. Annular groove; 100. Diffuser; 200. Inner and outer ring casings; 300. Combustion chamber head structure; 400. Inner wall of the flame tube; 500. Outer casing of the combustion chamber; 600. Outer wall of the flame tube. Detailed Implementation

[0020] 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.

[0021] 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.

[0022] This invention provides a combustion chamber head structure. Figure 1 A schematic diagram of the combustion chamber head structure in an embodiment of the present invention is shown. Figure 1 In the combustion chamber head structure, there are: a head ring 1, with a through hole and an air inlet 2 at the end of the head ring 1. One end of a guide plate 3 is coaxially sleeved on the inner wall of the through hole, and the other end of the guide plate 3 extends into the inner cavity of the head ring 1. The airflow from the air inlet 2 impacts the guide plate 3, and the other part enters the flame tube through the gap between the guide plate and the inner ring 4 and the outer ring 6 of the flame tube. The inner wall of the guide plate 3 is fitted with a vortex generator 4. The vortex generator 4 is coaxially opened with a through cavity, and the side wall of the vortex generator 4 is provided with a through groove connecting the through cavity and the combustion chamber cavity. One end of the through cavity is connected to the inner cavity of the head ring 1, and the inner wall of the other end of the through cavity is coaxially fitted with the outer wall of the fuel nozzle cap 5. The inner wall of the fuel nozzle cap 5 is coaxially fitted with the outer wall of the nozzle housing 6, and the nozzle housing 6 is connected to the fuel pipeline. The nozzle housing 6 has a nozzle at one end facing the through cavity, and the fuel nozzle cap 5 has a working port corresponding to the nozzle at one end facing the through cavity. The fuel nozzle cap 5 has a plurality of nozzle carbon-depositing holes 7 arranged in a circumferential array on the side wall. The fuel nozzle cap 5 has an annular groove 8 on the inner wall, one end of which is connected to the plurality of nozzle carbon-depositing holes 7, and the other end of which faces the nozzle direction of the nozzle housing 6.

[0023] The combustion chamber head structure proposed in this application, in actual use, delivers pressurized fuel from the nozzle housing 6 nozzle orifice to the through cavity and the inner cavity of the head annular ring 1, thereby satisfying the subsequent fuel combustion operation in the inner cavity of the head annular ring 1. At the same time, the gas in the combustion chamber cavity from the outside enters the annular groove 8 through several nozzle carbon blowing holes 7 and is output from the annular groove 8 toward one end of the nozzle housing 6 nozzle orifice. Since the gas is pressurized by the diffuser before entering the combustion chamber cavity, the gas output from the annular groove 8 can achieve airflow flushing of the fuel at the nozzle housing 6 nozzle orifice, thereby achieving temperature drop of the nozzle housing 6 nozzle orifice and effectively suppressing fuel adhesion at the nozzle housing 6 nozzle orifice and nozzle end face, so as to ensure long-term operation of the nozzle housing. In addition, combined with the vortex generator 4 and the through groove on the vortex generator 4 connecting the through cavity and the combustion chamber cavity, while ensuring long-term operation of the nozzle, the flameout margin is expanded.

[0024] In this embodiment, Figure 2 In the example shown, the outer wall of the nozzle housing 6 is threadedly connected to the inner wall of the fuel nozzle cap 5. Correspondingly, the annular groove 8 includes a connected axial groove section and a radial groove section. One end of the radial groove section is connected to the input end of several nozzle carbon deposit blowing holes 7, and one end of the axial groove section faces the nozzle nozzle direction. Through the connection of the axial groove section and the radial groove section, the high-pressure air input from the nozzle carbon deposit blowing holes 7 is guided to flow. Based on the increase in the inner cavity of the annular groove 8 relative to the inner cavity of the nozzle carbon deposit blowing holes 7, the gas is buffered, so that the gas is sprayed at high speed from the radial groove section to the nozzle nozzle of the nozzle housing 6, forming a nozzle carbon deposit blowing airflow, which is used to cool the nozzle nozzle of the nozzle housing 6, reduce the temperature at the nozzle nozzle of the nozzle housing 6, blow away the fuel adhering to the nozzle nozzle end face, and inhibit the carbon deposits of fuel on the nozzle end face.

[0025] Correspondingly, the axial groove and the radial groove form an obtuse angle to guide the airflow output from the radial groove to have a velocity component in the direction of penetrating the cavity, ensuring that the airflow washes the fuel at the nozzle orifice of the nozzle housing 6.

[0026] In addition, the axis of several of the nozzle carbon deposit blowing holes 7 forms an acute angle with the axis of the fuel nozzle cap 5, so that the gas entering the annular groove 8 from the nozzle carbon deposit blowing holes 7 also has a component velocity in the direction of penetrating the cavity, which corresponds to the airflow output of the radial groove section and ensures the smoothness of airflow.

[0027] In this embodiment, the fuel nozzle cap 5 has 12 nozzle carbon-depositing holes 7 arranged in a circumferential array on its side wall. The angle between the axis of the nozzle carbon-depositing holes 7 and the axis of the fuel nozzle cap 5 is 39°, and the diameter of the nozzle carbon-depositing holes 7 is 1.37mm to 1.43mm.

[0028] refer to Figure 3 and Figure 4 The vortex generator 4 includes a primary vortex generator 401, a venturi tube 402, and a secondary vortex generator 403. The primary vortex generator 401, venturi tube 402, and secondary vortex generator 403 are arranged coaxially, with one side wall of the venturi tube 402 connected to the side wall of the primary vortex generator 401, and the other side wall of the venturi tube 402 connected to the side wall of the secondary vortex generator 403. Figure 3 In the example shown, the end of the first-stage vortex generator 401 facing the fuel nozzle cap 5 has a flared structure to accommodate the installation of the fuel nozzle cap 5 and the nozzle housing 6.

[0029] The through channel includes a primary swirl channel 404 and a secondary swirl channel 405. The primary vortex generator 401 is used to connect with the side wall of the venturi tube 402 and has several primary swirl channels 404 to form a rotating airflow. The several primary swirl channels 404 are arranged in a circular array about the axis of the primary vortex generator 401. The slot openings of the several primary swirl channels 404 are connected to one side wall of the venturi tube 402. The primary swirl channels 404 all connect the combustion chamber cavity and the through channel. The secondary vortex generator 403 is used to connect with the side wall of the venturi tube 402 and has several secondary swirl grooves 405 to form a rotating airflow. The several secondary swirl grooves 405 are arranged in a circular array about the axis of the secondary vortex generator 403. The groove openings of the several secondary swirl grooves 405 are connected to the other side wall of the venturi tube 402. The secondary swirl grooves 405 are all connected to the combustion chamber cavity and the through cavity. In operation, the oil mist ejected from the nozzle housing 6 impacts the inner wall of the venturi tube 402, forming an oil film along the wall of the venturi tube 402. Meanwhile, high-pressure air from the compressor flows in through the first-stage swirl channel 404 and the second-stage swirl channel 405. Under the action of the through-cavity of the vortex generator 4, the flow changes from along the axis to rotating around the axis. The input airflow from the first-stage swirl channel 404 and the second-stage swirl channel 405 flows downstream from the vortex generator 4 through the channels on both sides of the venturi tube 402. At the same time, the oil film on the wall of the venturi tube 402 moves to the outlet of the venturi tube 402. Under the combined action of the rotating airflow from the first-stage vortex generator 401 and the rotating airflow from the second-stage vortex generator 403, the oil film on the wall of the venturi tube 402 and the oil mist ejected from the nozzle housing 6 are rapidly atomized into fine droplets that enter the flame tube for combustion reaction.

[0030] refer to Figure 4The radial axis of each of the first-stage swirl channels 404 maintains a first angle with the axis of the vortex generator 4, and the radial axis of each of the second-stage swirl channels 405 maintains a second angle with the axis of the vortex generator 4. The first angle and the second angle are in opposite directions, thereby causing the input airflow of the first-stage swirl channels 404 and the second-stage swirl channels 405 to flow in opposite directions. This achieves disturbance of the airflow in the cavity of the vortex generator 4, ensuring the atomization process of the fuel sprayed from the nozzle housing 6, so as to improve the efficiency of fuel use in subsequent combustion operations.

[0031] In this embodiment, both the primary vortex channel 404 and the secondary vortex channel 405 are square through channels to reduce production costs. The number of secondary vortex channels 405 is an even number more than the number of primary vortex channels 404. Figure 5 In the example shown, there are 12 primary swirl channels 404, the channel width h1 of the primary swirl channels 404 is 1.58mm to 1.62mm, and the radial height L1 of the primary swirl channels 404 is 5.47mm to 5.53mm. exist Figure 6 In the example shown, there are 16 secondary swirl channels 405, the channel width h2 of the secondary swirl channels 405 is 1.58mm to 1.62mm, and the radial height L2 of the secondary swirl channels 405 is 9.47mm to 9.53mm.

[0032] It should be noted that the effective area of ​​a vortex generator refers to the minimum cross-sectional area that the vortex generator actually allows air to pass through, and it is calculated as the product of the geometric area and the flow coefficient. The area ratio is a key design parameter that directly affects flow characteristics, mixing efficiency, and combustion stability.

[0033] The interaction between the throat acceleration effect of the venturi tube 402 and the rotating flow of the vortex tube affects the size of the recirculation zone, fuel atomization, and flame dwell time. In this embodiment, the ratio of the effective area (including the area of ​​the carbon deposit holes) of the first-stage vortex tube 401 to the throat area of ​​the venturi tube 402 is set to 0.30 to 0.35. For example, the ratio of the effective area (including the area of ​​the carbon deposit holes) of the first-stage vortex tube 401 to the throat area of ​​the venturi tube 402 is set to 0.35, thereby ensuring that the flow distribution between the first-stage vortex tube 401 and the venturi tube 402 meets the requirements for a large margin of flameout. At the same time, the outlet angle of the second-stage vortex tube 403 facing the through cavity is set to 40°.

[0034] Based on the design of this application, and referring to Figure 7 , Figure 7 It shows the lean fuel shutdown margin. Figure 7 The vertical axis represents the air-fuel ratio and the flameout margin, while the horizontal axis represents the equivalent velocity. Based on... Figure 7It can be seen that the lean fuel-air ratio of the combustor in ground idle state is 0.00265, and the lean fuel-air ratio in air idle state is 0.00221. Compared with the requirement that the combustor of an aero-engine should be able to operate stably in idle state with a fuel-air ratio of 0.005, the flameout margin of this application can reach 47% and 55.8% in ground idle and air idle state, respectively, which realizes the optimization and improvement of lean fuel flameout performance.

[0035] The combustion chamber head structure proposed in this invention involves inserting the nozzle housing 6 into the vortex generator 4 to form a swirling cup structure. Several carbon-depositing nozzle holes 7 are formed on the side wall of the fuel nozzle cap 5 to flush the fuel at the nozzle nozzle 6, effectively suppressing fuel adhesion at the nozzle nozzle 6 nozzle orifice and nozzle end face, thus ensuring long-term operation of the nozzle housing. Simultaneously, the vortex generator 4, composed of a two-stage radial vortex generator, expands the engine's shutdown margin during ground and air idle, ensuring stable lean combustion and overall performance.

[0036] In addition, refer to Figure 8 The present invention also discloses a combustion chamber, including a combustion chamber head structure 300 as described above, and further including: a diffuser 100, inner and outer ring casings 200, an inner wall of the flame tube 400, an outer casing of the combustion chamber 500, and an outer wall of the flame tube 600. The inner and outer ring casings 200 and the outer casing 500 of the combustion chamber form an inner cavity of the combustion chamber. One end of the inner cavity of the combustion chamber is connected to the output end of the diffuser 100. The inner wall 400 of the flame tube, the outer wall 600 of the flame tube, and the head structure 300 of the combustion chamber are all housed in the inner cavity of the combustion chamber. The inner wall 400 of the flame tube, the outer wall 600 of the flame tube, and the head structure 300 of the combustion chamber form the inner cavity of the flame tube.

[0037] 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. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly; for example, they may refer to a fixed connection, a detachable connection, or an integral connection; they may refer to a mechanical connection, an electrical connection, or a connection that allows for communication; they may refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention according to the specific circumstances.

[0038] 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 accompanying drawings and are only for the convenience of describing the present 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 the present invention.

[0039] 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. A combustion chamber head structure, comprising: A head ring (1) is provided with a through hole and an air inlet (2) at the end of the head ring (1). A guide plate (3) is coaxially sleeved on the inner wall of the through hole. The guide plate (3) is characterized in that a vortex (4) is sleeved on the inner wall of the guide plate (3). The vortex (4) is coaxially provided with a through cavity, and the side wall of the vortex (4) is provided with a through groove connecting the through cavity and the combustion chamber. One end of the through cavity is connected to the inner cavity of the head ring (1). The inner wall of the other end of the through cavity is coaxially sleeved on the outer wall of the fuel nozzle cap (5). The inner wall of the fuel nozzle cap (5) is coaxially sleeved on the outer wall of the nozzle housing (6). The nozzle housing (6) has a nozzle at one end facing the through cavity, and the fuel nozzle cap (5) has a working port corresponding to the nozzle at one end facing the through cavity. The fuel nozzle cap (5) has several nozzle carbon blowing holes (7) on its side wall, and an annular groove (8) is formed on the inner wall of the fuel nozzle cap (5). One end of the annular groove (8) is connected to the nozzle carbon blowing hole (7), and the other end of the annular groove (8) faces the nozzle direction of the nozzle housing (6).

2. The combustion chamber head structure according to claim 1, characterized in that, The annular groove (8) includes an axial groove section and a radial groove section connected together. One end of the radial groove section is connected to the input end of a plurality of nozzle carbon-depositing holes (7), and one end of the axial groove section is oriented toward the nozzle direction of the nozzle housing (6).

3. The combustion chamber head structure according to claim 2, characterized in that, The axis of several of the nozzle carbon deposit holes (7) forms an acute angle with the axis of the fuel nozzle cap (5), and the axial groove section forms an obtuse angle with the radial groove section.

4. The combustion chamber head structure according to claim 3, characterized in that, The diameter of some of the nozzle carbon-depositing holes (7) is 1.37 mm to 1.43 mm.

5. The combustion chamber head structure according to claim 1, characterized in that, The vortex generator (4) includes a first-stage vortex generator (401), a venturi tube (402), and a second-stage vortex generator (403) connected coaxially in sequence. The through slot includes a first-stage swirl slot (404) and a second-stage swirl slot (405). The first-stage vortex generator (401) is connected to the circumferential array of the side wall of the venturi tube (402) and has several first-stage swirl slots (404). The second-stage vortex generator (403) is connected to the circumferential array of the side wall of the venturi tube (402) and has several second-stage swirl slots (405). The first-stage swirl slots (404) and the second-stage swirl slots (405) are connected to the through cavity and the combustion chamber cavity.

6. The combustion chamber head structure according to claim 5, characterized in that, The radial axis of several primary swirl channels (404) is at a first angle to the axis of the vortex generator (4), and the radial axis of several secondary swirl channels (405) is at a second angle to the axis of the vortex generator (4). The first angle and the second angle are opposite in direction.

7. The combustion chamber head structure according to claim 6, characterized in that, Both the primary vortex channel (404) and the secondary vortex channel (405) are square through channels. The width of the primary vortex channel (404) is 1.58mm to 1.62mm, and the radial height is 5.47mm to 5.53mm. The width of the secondary vortex trough (405) is 1.58mm to 1.62mm, and the radial height is 9.47mm to 9.53mm.

8. The combustion chamber head structure according to claim 7, characterized in that, The number of secondary swirl channels (405) is an even number more than the number of primary swirl channels (404).

9. The combustion chamber head structure according to claim 8, characterized in that, The effective area of ​​the first-stage vortex generator (401) is 0.30 to 0.35 of the throat area of ​​the venturi tube (402).

10. A combustion chamber, characterized in that, The combustion chamber head structure (300) as described in any one of claims 1-9 further includes: a diffuser (100), inner and outer ring casings (200), an inner wall of the flame tube (400), an outer casing of the combustion chamber (500), and an outer wall of the flame tube (600). The inner and outer ring casings (200) and the outer casing of the combustion chamber (500) form an inner cavity of the combustion chamber. One end of the inner cavity of the combustion chamber is connected to the output end of the diffuser (100). The inner wall (400) of the flame tube, the outer wall (600) of the flame tube, and the head structure (300) of the combustion chamber are all housed in the inner cavity of the combustion chamber. The inner wall (400) of the flame tube, the outer wall (600) of the flame tube, and the head structure (300) of the combustion chamber form the inner cavity of the flame tube.

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