Complete-mixing, efficient, stable-combustion, anti-backfire and low-emission combustion chamber head structure

Abstract

According to the full-mixing efficient stable-combustion anti-backfire low-emission combustion chamber head structure, a main combustion stage adopts a pre-mixing design of high-rotational-flow-intensity fuel and air, so that the combustion efficiency is improved; the pre-combustion stage adopts a pre-mixing design of fuel with low rotational flow intensity and air, so that the flame is kept stable; the on-duty level adopts a direct fuel supply diffusion combustion design, so that the flame stability is improved; by additionally arranging the on-duty air channel, a high-temperature area is prevented from being generated on the wall surface of the on-duty case, and tempering of the on-duty case is prevented; a main combustion stage jet hole and a jet regulation and control mechanism are additionally arranged, the main flow of a main combustion stage is controlled to form a vortex, the airflow speed of fluid in a boundary layer is increased through the vortex, the probability of boundary layer tempering of the main combustion stage of the combustion chamber is reduced, and even if boundary layer tempering occurs, reverse propagation of flames along the boundary layer can be blocked by adjusting the jet flow; through cooperation of the on-duty stage and the pre-combustion stage, low-working-condition stable combustion is achieved; through cooperation of the main combustion stage and the pre-combustion stage, nitrogen oxide emission is reduced under the high working condition.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of lean premixed combustion, and particularly relates to a full-mixing high-efficiency stable-combustion anti-backfire low-emission combustion chamber head structure. BACKGROUND

[0002] At present, gas turbines, aeroengines and the like are continuously facing the major challenge of reducing pollutant emissions, so the lean premixed combustion technology is becoming a development trend of low-emission combustion chambers.

[0003] When the lean premixed combustion system is working, excess air is supplied to the main combustion zone so as to significantly reduce the local flame temperature and in turn reduce the generation amount of nitrogen oxides, and the mixing uniformity of the fuel and air mixture is also a key factor to achieve a lower flame temperature.

[0004] The main feature of the combustion chamber adopting the lean premixed combustion technology is that the fuel and air are fully mixed before combustion, and through lean fuel combustion in the main combustion zone, the emission amount of nitrogen oxides can be sharply reduced, and through controlling the mixing degree of the fuel and air, the combustion temperature can be controlled, so as to achieve excellent low-emission performance.

[0005] However, while obtaining the low-emission performance through the lean fuel combustion, the combustion chamber is prone to combustion instability, and even may appear backfire.

[0006] Taking a center-staged swirled combustion chamber as an example, it is concerned in the fields of aviation and energy due to its good combustion efficiency, lower pollutant generation and better stability, and through optimizing the mixing process of the fuel and air and the layout of the combustion zone, the center-staged swirled combustion chamber can effectively inhibit the local high-temperature zone, so as to reduce the generation of thermal nitrogen oxides.

[0007] However, the main combustion stage of the traditional center-staged swirled combustion chamber adopts a long premixing distance design, which is the main reason for the significant backfire risk, and will seriously affect the reliability and service life of the combustion chamber.

[0008] Therefore, in order to achieve stable and clean combustion under all working conditions, it is imperative to develop a low-emission combustion chamber head structure with high efficiency and anti-backfire function. SUMMARY

[0009] To address the problems existing in the prior art, this invention provides a fully mixed, highly efficient, stable, backfire-preventing, and low-emission combustion chamber head structure. The main combustion stage employs a high-swirl intensity fuel-air premixing design to improve combustion efficiency; the pre-combustion stage employs a low-swirl intensity fuel-air premixing design to maintain flame stability; the control stage employs a direct fuel supply diffusion combustion design to improve flame stability; an additional control stage air channel is added to prevent high-temperature zones from forming on the control stage casing wall, while also preventing backfire; additional main combustion stage jet orifices and jet control mechanisms are added to control the formation of vortices in the main combustion stage's mainstream, using these vortices to increase the airflow velocity within the boundary layer, reducing the probability of boundary layer backfire in the main combustion stage; even if boundary layer backfire occurs, the reverse propagation of the flame along the boundary layer can be blocked by adjusting the jet flow rate; the cooperation between the control stage and the pre-combustion stage achieves stable combustion under low operating conditions; and the cooperation between the main combustion stage and the pre-combustion stage achieves the goal of reducing nitrogen oxide emissions under high operating conditions.

[0010] To achieve the above objectives, the present invention adopts the following technical solution: a fully mixed, highly efficient, stable, backfire-preventing, and low-emission combustion chamber head structure, comprising a main combustion stage, a pre-combustion stage, and a duty stage; the duty stage is located at the center of the combustion chamber, the pre-combustion stage is concentrically arranged on the outer periphery of the duty stage, and the main combustion stage is concentrically arranged on the outer periphery of the pre-combustion stage; a duty stage air passage is provided between the duty stage and the pre-combustion stage; and a main combustion stage jet orifice and a jet control mechanism are provided on the main combustion stage.

[0011] The main combustion stage includes a main combustion stage casing, a main combustion stage fuel inlet pipe, and main combustion stage swirl vanes. A circumferentially distributed main combustion stage fuel chamber is provided inside the wall of the main combustion stage casing. One end of the main combustion stage fuel inlet pipe is connected to the main combustion stage fuel chamber, and the other end of the main combustion stage fuel inlet pipe is sealed and extends out of the combustion chamber outside the main combustion stage casing. The main combustion stage swirl vanes are arranged circumferentially on the inner surface of the wall of the main combustion stage casing, and main combustion stage fuel flow channel nozzles are provided inside the main combustion stage swirl vanes, which are connected to the main combustion stage fuel chambers.

[0012] The pre-combustion stage includes a pre-combustion stage casing, a pre-combustion stage fuel inlet pipe, and pre-combustion stage swirl blades. A premixing chamber casing is concentrically arranged between the pre-combustion stage casing and the main combustion stage casing. The circumferential space between the premixing chamber casing and the main combustion stage casing constitutes the main combustion stage premixing chamber. The main combustion stage swirl blades are located upstream of the airflow in the main combustion stage premixing chamber and are fixedly connected to the outer surface of the premixing chamber casing wall. Inside the wall of the pre-combustion stage casing, there are... A pre-combustion stage fuel chamber is distributed circumferentially; one end of the pre-combustion stage fuel inlet pipe is connected to the pre-combustion stage fuel chamber, and the other end of the pre-combustion stage fuel inlet pipe is sealed and extends out of the combustion chamber casing; the pre-combustion stage swirl blades are arranged circumferentially on the outer surface of the pre-combustion stage casing wall, and pre-combustion stage fuel flow channel nozzles are provided inside the pre-combustion stage swirl blades, which are connected to the pre-combustion stage fuel chamber; the pre-combustion stage swirl blades are located in the downstream region of the airflow in the pre-combustion stage premixing chamber, and the pre-combustion stage swirl blades are fixedly connected to the inner surface of the premixing chamber casing wall.

[0013] The duty unit includes a duty unit housing and a duty unit fuel inlet pipe; the duty unit includes a duty unit housing concentrically fitted inside the pre-combustion stage housing, and the circumferential gap between the duty unit housing and the pre-combustion stage housing forms a duty unit air passage; the inner cavity of the duty unit housing serves as the duty unit fuel chamber, one end of the duty unit housing is sealed and extends out of the outer housing of the combustion chamber, and the other end of the duty unit housing is provided with a duty unit fuel flow channel nozzle, the outlet side of the duty unit fuel flow channel nozzle facing the combustion zone; the duty unit fuel inlet pipe is located outside the outer housing of the combustion chamber, and the duty unit fuel inlet pipe is connected to the duty unit fuel chamber.

[0014] The swirl intensity of the main combustion stage swirl blades is higher than that of the pre-combustion stage swirl blades.

[0015] In the combustion zone adjacent to the downstream region of the airflow from the main combustion stage premixing chamber, main combustion stage jet holes are arranged circumferentially on the wall of the main combustion stage casing.

[0016] The jet control mechanism includes a circumferential baffle, a baffle rotation attitude adjustment driver, a temperature sensor, and a dynamic pressure sensor. Jet control holes are arranged circumferentially on the circumferential baffle, and the number of jet control holes is equal to that of the main combustion stage jet holes, the same size, and the positions correspond one-to-one. The baffle rotation attitude adjustment driver is located between the circumferential baffle and the main combustion stage casing. The temperature sensor and the dynamic pressure sensor are both located in the main combustion stage premixing chamber.

[0017] The baffle rotation attitude adjustment actuator includes, but is not limited to, pneumatic actuators, hydraulic actuators, and electric actuators.

[0018] The overlap between the jet control orifice and the main combustion stage jet orifice is adjusted based on feedback data from the temperature sensor and the dynamic pressure sensor.

[0019] The beneficial effects of this invention are: This invention relates to a fully mixed, highly efficient, stable, backfire-preventing, and low-emission combustion chamber head structure. The main combustion stage employs a high-swirl intensity fuel-air premixing design to improve combustion efficiency; the pre-combustion stage employs a low-swirl intensity fuel-air premixing design to maintain flame stability; and the control stage employs a direct fuel supply diffusion combustion design to enhance flame stability. An additional control stage air passage prevents the formation of high-temperature zones on the control stage casing wall and also prevents backfire. The addition of main combustion stage jet orifices and a jet control mechanism controls the formation of vortices in the main combustion stage's mainstream flow, increasing the airflow velocity within the boundary layer and reducing the probability of boundary layer backfire in the main combustion stage. Even if boundary layer backfire occurs, adjusting the jet flow rate can block the flame's reverse propagation along the boundary layer. The coordination between the control stage and the pre-combustion stage achieves stable combustion under low operating conditions and reduces nitrogen oxide emissions under high operating conditions. Attached Figure Description

[0020] Fig. 1 This is a schematic diagram of a fully mixed, highly efficient, stable, backfire-preventing, and low-emission combustion chamber head structure according to the present invention; Fig. 2 This is a three-dimensional partial cross-sectional view of a fully mixed, high-efficiency, stable, backfire-preventing, and low-emission combustion chamber head structure (after assembly with the outer casing of the combustion chamber) according to the present invention (the overlap between the jet control hole and the main combustion stage jet hole is 0%). Fig. 3 This is a cross-sectional schematic diagram of a fully mixed, highly efficient, stable, backfire-preventing, and low-emission combustion chamber head structure (after assembly with the outer casing of the combustion chamber) according to the present invention (the orifice overlap between the jet control hole and the main combustion stage jet hole is 100%). Fig. 4 This is a cross-sectional schematic diagram of a fully mixed, high-efficiency, stable, backfire-preventing, and low-emission combustion chamber head structure (after assembly with the outer casing of the combustion chamber) according to the present invention (the overlap between the jet control hole and the main combustion stage jet hole is 0). Fig. 5 This is a longitudinal section schematic diagram of a fully mixed, highly efficient, stable, backfire-preventing, and low-emission combustion chamber head structure (after assembly with the outer casing of the combustion chamber) according to the present invention (the overlap between the jet control hole and the main combustion stage jet hole is 0). In the diagram, 1—Air passage for duty personnel, 2—Main combustion stage jet orifice, 3—Main combustion stage casing, 4—Main combustion stage fuel inlet pipe, 5—Main combustion stage swirl vane, 6—Main combustion stage fuel chamber, 7—Main combustion stage fuel flow channel nozzle, 8—Outer casing of combustion chamber, 9—Main combustion stage premixing chamber, 10—Pre-combustion stage casing, 11—Pre-combustion stage fuel inlet pipe, 12—Pre-combustion stage swirl vane, 13—Pre-combustion stage fuel chamber, 14—Pre-combustion stage fuel flow channel nozzle, 15—Pre-combustion stage premixing chamber, 16—Duty personnel casing, 17—Duty personnel fuel inlet pipe, 18—Duty personnel fuel chamber, 19—Duty personnel fuel flow channel nozzle, 20—Premixing chamber casing, 21—Circular baffle, 22—Jet control hole. Detailed Implementation

[0021] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0022] like Figs. 1-5 As shown, a fully mixed, efficient, stable, backfire-preventing, and low-emission combustion chamber head structure includes a main combustion stage, a pre-combustion stage, and a duty stage; the duty stage is located at the center of the combustion chamber, the pre-combustion stage is concentrically arranged on the outer periphery of the duty stage, and the main combustion stage is concentrically arranged on the outer periphery of the pre-combustion stage; a duty stage air passage 1 is provided between the duty stage and the pre-combustion stage; a main combustion stage jet orifice 2 and a jet control mechanism are provided on the main combustion stage.

[0023] The main combustion stage includes a main combustion stage casing 3, a main combustion stage fuel inlet pipe 4, and main combustion stage swirl blades 5; a circumferentially distributed main combustion stage fuel chamber 6 is provided inside the wall of the main combustion stage casing 3; one end of the main combustion stage fuel inlet pipe 4 is connected to the main combustion stage fuel chamber 6, and the other end of the main combustion stage fuel inlet pipe 4 is sealed and extends out of the combustion chamber 8 outside the casing; the main combustion stage swirl blades 5 are arranged circumferentially on the inner surface of the wall of the main combustion stage casing 3, and a main combustion stage fuel flow channel nozzle 7 is provided inside the main combustion stage swirl blades 5, which is connected to the main combustion stage fuel chamber 6.

[0024] The pre-combustion stage includes a pre-combustion stage casing 10, a pre-combustion stage fuel inlet pipe 11, and pre-combustion stage swirl blades 12. A premixing chamber casing 20 is concentrically arranged between the pre-combustion stage casing 10 and the main combustion stage casing 3. The circumferential space between the premixing chamber casing 20 and the main combustion stage casing 3 constitutes the main combustion stage premixing chamber 9, and the circumferential space between the premixing chamber casing 20 and the pre-combustion stage casing 10 constitutes the pre-combustion stage premixing chamber 15. The main combustion stage swirl blades 5 are located upstream of the airflow in the main combustion stage premixing chamber 9, and the main combustion stage swirl blades 5 are fixedly connected to the outer surface of the wall of the premixing chamber casing 20. Inside the wall of the pre-combustion stage casing 10, there are... A pre-combustion stage fuel chamber 13 is distributed circumferentially; one end of the pre-combustion stage fuel inlet pipe 11 is connected to the pre-combustion stage fuel chamber 13, and the other end of the pre-combustion stage fuel inlet pipe 11 is sealed and extends out of the combustion chamber outer casing 8; the pre-combustion stage swirl blades 12 are arranged circumferentially on the outer surface of the wall of the pre-combustion stage casing 10, and a pre-combustion stage fuel flow channel nozzle 14 is provided inside the pre-combustion stage swirl blades 12, which is connected to the pre-combustion stage fuel chamber 13; the pre-combustion stage swirl blades 12 are located in the downstream region of the airflow in the pre-combustion stage premixing chamber 15, and the pre-combustion stage swirl blades 12 are fixedly connected to the inner surface of the wall of the premixing chamber casing 20.

[0025] The duty unit includes a duty unit housing 16 and a duty unit fuel inlet pipe 17. The duty unit housing 16 is concentrically fitted inside the pre-combustion stage housing 10, and the circumferential gap between the duty unit housing 16 and the pre-combustion stage housing 10 forms the duty unit air passage 1. The inner cavity of the duty unit housing 16 serves as the duty unit fuel chamber 18. One end of the duty unit housing 16 is sealed and extends out of the outer housing 8 of the combustion chamber, and the other end of the duty unit housing 16 is provided with a duty unit fuel flow channel nozzle 19, with the outlet side of the duty unit fuel flow channel nozzle 19 facing the combustion zone. The duty unit fuel inlet pipe 17 is located outside the outer housing 8 of the combustion chamber and is connected to the duty unit fuel chamber 18.

[0026] The swirl intensity of the main combustion stage swirl blade 5 is higher than that of the pre-combustion stage swirl blade 12.

[0027] In the combustion zone adjacent to the downstream region of the airflow from the main combustion stage premixing chamber 9, main combustion stage jet holes 2 are arranged circumferentially on the wall of the main combustion stage casing 3.

[0028] The jet control mechanism includes a circumferential baffle 21, a baffle rotation attitude adjustment driver, a temperature sensor, and a dynamic pressure sensor. Jet control holes 22 are arranged circumferentially on the circumferential baffle 21. The number of jet control holes 22 is equal to the number of main combustion stage jet holes 2, the same size, and the positions correspond one-to-one. The baffle rotation attitude adjustment driver is located between the circumferential baffle 21 and the main combustion stage casing 3. The temperature sensor and the dynamic pressure sensor are both located in the main combustion stage premixing chamber 9.

[0029] The baffle rotation attitude adjustment actuator includes, but is not limited to, pneumatic actuators, hydraulic actuators, and electric actuators.

[0030] The overlap between the jet control orifice 22 and the main combustion stage jet orifice 2 is adjusted based on feedback data from the temperature sensor and the dynamic pressure sensor.

[0031] The following description, in conjunction with the accompanying drawings, illustrates the usage of this invention: During the operation of the combustion chamber, for the main combustion stage, the fuel first enters the main combustion stage fuel chamber 6 through the main combustion stage fuel inlet pipe 4, and then is evenly distributed by the main combustion stage fuel chamber 6 to the main combustion stage fuel flow channel nozzles 7 in each main combustion stage swirl blade 5. Then, it is concentratedly injected into the main combustion stage premixing chamber 9 by the main combustion stage fuel flow channel nozzles 7, and is fully mixed with the incoming air flow in the main combustion stage premixing chamber 9. Under the action of the high swirl intensity generated by the main combustion stage swirl blade 5, the premixing uniformity of fuel and air is ensured, and the combustion efficiency of the fuel and air mixture in the combustion zone is effectively improved.

[0032] During the operation of the combustion chamber, for the pre-combustion stage, the fuel first enters the pre-combustion stage fuel chamber 13 through the pre-combustion stage fuel inlet pipe 11, and is then evenly distributed by the pre-combustion stage fuel chamber 13 to the pre-combustion stage fuel flow channel nozzles 14 in each pre-combustion stage swirl blade 12. Then, it is concentratedly injected into the pre-combustion stage premixing chamber 15 by the pre-combustion stage fuel flow channel nozzles 14, and is fully mixed with the incoming air flow in the pre-combustion stage premixing chamber 15. Under the action of the low swirl intensity generated by the pre-combustion stage swirl blades 12, the premixing uniformity of fuel and air is ensured, while the flame stability of the fuel-air mixture in the combustion zone is maintained.

[0033] During the operation of the combustion chamber, for the shift, the fuel directly enters the shift fuel chamber 18 inside the shift housing 16 through the shift fuel inlet pipe 17, and then is directly injected into the combustion zone through the shift fuel flow channel nozzle 19, thereby improving the flame stability of the combustion zone.

[0034] During combustion chamber operation, air can flow directly through the duty air passage 1. As the air flows through the duty air passage 1, it continuously carries away heat from the walls of the duty chamber casing 16 through heat conduction, preventing the formation of high-temperature zones on the walls of the duty chamber casing 16. Simultaneously, the air ejected from the duty air passage 1 not only prevents backfire but also allows for more thorough mixing of the air with the fuel ejected from the duty fuel flow channel nozzle 19, reducing the high-temperature zone and effectively decreasing the formation of thermal nitrogen oxides.

[0035] During combustion chamber operation, the temperature inside the main combustion stage premixing chamber 9 is monitored in real time by a temperature sensor, and the airflow velocity inside the main combustion stage premixing chamber 9 is monitored in real time by a dynamic pressure sensor. When the detected data is within a set threshold range, the overlap between the jet control orifice 22 and the main combustion stage jet orifice 2 is at a preset value. By adjusting the overlap between the jet control orifice 22 and the main combustion stage jet orifice 2, air can be injected into the combustion zone at a set angle. Under the action of the jet, the mainstream of the main combustion stage can form a vortex, thereby increasing the airflow velocity of the fluid in the boundary layer and reducing the probability of boundary layer backfire in the main combustion stage of the combustion chamber. If boundary layer flashback occurs in the main combustion stage of the combustion chamber, the abnormal feedback information of the main combustion stage premixing chamber 9 can be detected immediately by temperature sensor and dynamic pressure sensor. According to the preset program, the baffle rotation attitude adjustment driver is activated, which drives the circumferential baffle 21 to rotate at a set angle, thereby changing the overlap between the jet control hole 22 and the main combustion stage jet hole 2, so as to increase the jet flow rate. By increasing the jet flow rate, the flame is effectively blocked from propagating backward along the boundary layer, thereby eliminating flashback.

[0036] During combustion chamber operation, if low-operational-condition operation is required, only the ignition stage and pre-combustion stage need to be activated simultaneously; the main combustion stage can be deactivated. Stable combustion and low emission performance can be achieved through the coordination of the ignition stage and pre-combustion stage. If high-operational-condition operation is required, the ignition stage, pre-combustion stage, and main combustion stage are activated simultaneously. The ignition stage acts as a ignition source to stabilize the flame, while combustion efficiency is ensured primarily through the coordination of the pre-combustion stage and main combustion stage, thereby reducing nitrogen oxide emissions.

[0037] The solutions in the embodiments are not intended to limit the scope of protection of the present invention. All equivalent implementations or modifications that do not depart from the present invention are included in the scope of protection of the present invention.

Claims

1. A combustion chamber head structure for thorough mixing, high efficiency, stable combustion, backfire prevention, and low emissions, characterized in that: It includes the main combustion stage, the pre-combustion stage, and the duty station; the duty station is located at the center of the combustion chamber, the pre-combustion stage is concentrically arranged on the outer periphery of the duty station, and the main combustion stage is concentrically arranged on the outer periphery of the pre-combustion stage; An air passage for the duty officer is provided between the duty officer station and the pre-combustion stage. The main combustion stage is provided with a main combustion stage jet orifice and a jet control mechanism.

2. The combustion chamber head structure for thorough mixing, high efficiency, stable combustion, backfire prevention, and low emissions according to claim 1, characterized in that: The main combustion stage includes a main combustion stage casing, a main combustion stage fuel inlet pipe, and main combustion stage swirl blades; The main combustion stage fuel chambers are arranged in a ring direction inside the wall of the main combustion stage casing; One end of the main combustion stage fuel inlet pipe is connected to the main combustion stage fuel chamber, and the other end of the main combustion stage fuel inlet pipe is sealed and extends out of the combustion chamber. The main combustion stage swirl blades are arranged circumferentially on the inner surface of the main combustion stage casing. The main combustion stage fuel flow channel nozzles are provided inside the main combustion stage swirl blades and are connected to the main combustion stage fuel chamber.

3. The combustion chamber head structure for thorough mixing, high efficiency, stable combustion, backfire prevention, and low emissions according to claim 2, characterized in that: The pre-combustion stage includes a pre-combustion stage casing, a pre-combustion stage fuel inlet pipe, and pre-combustion stage swirl blades; a premixing chamber casing is concentrically arranged between the pre-combustion stage casing and the main combustion stage casing, the circumferential space between the premixing chamber casing and the main combustion stage casing constitutes the main combustion stage premixing chamber, and the circumferential space between the premixing chamber casing and the pre-combustion stage casing constitutes the pre-combustion stage premixing chamber. The main combustion stage swirl blades are located upstream of the airflow in the main combustion stage premixing chamber, and are fixedly connected to the outer surface of the premixing chamber casing wall. A circumferentially distributed precombustion stage fuel chamber is provided inside the precombustion stage casing wall. One end of the precombustion stage fuel inlet pipe is connected to the precombustion stage fuel chamber, and the other end of the precombustion stage fuel inlet pipe is sealed and extends out of the combustion chamber casing. The precombustion stage swirl blades are circumferentially arranged on the outer surface of the precombustion stage casing wall, and precombustion stage fuel flow channel nozzles are provided inside the precombustion stage swirl blades, which are connected to the precombustion stage fuel chamber. The precombustion stage swirl blades are located downstream of the airflow in the precombustion stage premixing chamber, and are fixedly connected to the inner surface of the premixing chamber casing wall.

4. The combustion chamber head structure for thorough mixing, high efficiency, stable combustion, backfire prevention, and low emissions according to claim 3, characterized in that: The duty unit includes a duty unit housing and a duty unit fuel inlet pipe; the duty unit includes a duty unit housing concentrically fitted inside the pre-combustion stage housing, and the circumferential gap between the duty unit housing and the pre-combustion stage housing forms a duty unit air passage; the inner cavity of the duty unit housing serves as the duty unit fuel chamber, one end of the duty unit housing is sealed and extends out of the outer housing of the combustion chamber, and the other end of the duty unit housing is provided with a duty unit fuel flow channel nozzle, the outlet side of the duty unit fuel flow channel nozzle facing the combustion zone; the duty unit fuel inlet pipe is located outside the outer housing of the combustion chamber, and the duty unit fuel inlet pipe is connected to the duty unit fuel chamber.

5. The combustion chamber head structure for thorough mixing, high efficiency, stable combustion, backfire prevention, and low emissions according to claim 4, characterized in that: The swirl intensity of the main combustion stage swirl blades is higher than that of the pre-combustion stage swirl blades.

6. The combustion chamber head structure for thorough mixing, high efficiency, stable combustion, backfire prevention, and low emissions according to claim 3, characterized in that: In the combustion zone adjacent to the downstream region of the airflow from the main combustion stage premixing chamber, main combustion stage jet holes are arranged circumferentially on the wall of the main combustion stage casing.

7. The combustion chamber head structure for thorough mixing, high efficiency, stable combustion, backfire prevention, and low emissions according to claim 3, characterized in that: The jet control mechanism includes a circumferential baffle, a baffle rotation attitude adjustment driver, a temperature sensor, and a dynamic pressure sensor. Jet control holes are arranged circumferentially on the circumferential baffle, and the number of jet control holes is equal to that of the main combustion stage jet holes, the same size, and the positions correspond one-to-one. The baffle rotation attitude adjustment driver is located between the circumferential baffle and the main combustion stage casing. The temperature sensor and the dynamic pressure sensor are both located in the main combustion stage premixing chamber.

8. The combustion chamber head structure for thorough mixing, high efficiency, stable combustion, backfire prevention, and low emissions according to claim 7, characterized in that: The baffle rotation attitude adjustment actuator includes, but is not limited to, pneumatic actuators, hydraulic actuators, and electric actuators.

9. The combustion chamber head structure for thorough mixing, high efficiency, stable combustion, backfire prevention, and low emissions according to claim 7, characterized in that: The overlap between the jet control orifice and the main combustion stage jet orifice is adjusted based on feedback data from the temperature sensor and the dynamic pressure sensor.

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