CN104406196A - Two-stage prefilming delamination part premixing high-temperature-rise combustion chamber structure - Google Patents

Abstract

The invention discloses a double-stage pre-film layered partly premixed high-temperature rise combustion chamber structure. The flame in the main combustion zone in the combustion chamber is divided into a pre-combustion stage and a main combustion stage, which respectively adopt diffusion combustion and direct fuel injection combustion. Diffusion combustion Coupling with direct fuel injection combustion to achieve stratified partially premixed combustion. Both the main combustion stage and the pre-combustion stage fuel oil adopt the pre-film air atomization technology in the channel. The stage pre-film layered partly premixed high-temperature rising combustor provides a stable ignition source, and the main combustion stage flame uses the high-temperature gas provided by the swirling flow and the pre-combustion stage flame to stabilize the flame. The pre-combustion nozzle improves the atomization quality through double-stage swirl pre-film air atomization, and the main combustion nozzle separates the fuel atomization and blending process to achieve rapid and uniform blending of oil and gas.

Description

A two-stage pre-film layered partly premixed high-temperature rise combustor structure

technical field

The invention relates to the field of aero-engines, in particular to a layered partly premixed high-temperature rise combustor structure utilizing atomization and step-by-step pre-film air atomization and rapid oil-gas mixing technology to realize uniform combustion in the main combustion zone.

Background technique

High temperature rise combustors are required for military aero engines. In order to meet the aerodynamic and thermal properties of the next-generation military aeroengine with a thrust-to-weight ratio of 12-15, the turbine inlet temperature of the military aeroengine should be significantly higher than that of the military aeroengine currently in service. Therefore, the design of combustion chamber components will develop in the direction of high temperature and high heat capacity combustion. The temperature rise of the combustion chamber of an active military aero-engine is about 900°C, and the next-generation military aviation turbofan engine requires a combustion room temperature rise of approximately 1400°C. With the rise of the combustion chamber, the air intake at the head of the combustion chamber increases significantly compared with the traditional combustion chamber, from about 20% to more than 60%, which will lead to combustion organization, oil and gas matching and mixing, wall cooling and outlet A series of problems such as temperature field quality control must seek breakthroughs in aerothermodynamics, fuel atomization, new structures, and high-temperature-resistant lightweight materials.

Compared with conventional temperature-rise combustors, the requirements for lean combustion stability and outlet temperature distribution quality of high-temperature-rise combustors cannot be lowered, and the high-temperature-rise combustor has a higher oil-gas ratio in a large state. Therefore, high-temperature combustors The first technical challenge is to expand the stable working range of the combustion chamber; at the same time, the high-temperature rise combustion chamber requires more air to participate in combustion as the oil-gas ratio increases. After the temperature of the main combustion zone increases, the amount of cooling air is less, which is harmful to the combustion chamber. Wall cooling and regulation of outlet temperature distribution present new difficulties and challenges.

Aiming at the technical research and development of the high-temperature rising combustion chamber, some research programs have been published at home and abroad. The combustion structure of the combustion chamber head is the key to ensure the full satisfaction of the combustion performance. At present, the partition staged combustion technology is expected to broaden the stable working range of the high-temperature rise combustor through the local combustion of the pre-combustion stage under low operating conditions and the simultaneous combustion of the pre-combustion stage and the main combustion stage in the main combustion zone under high operating conditions; Due to the reasons of technical secrecy, few related technologies of high-temperature rise combustion chambers have been publicly published. The existing zoning and staging technology disclosed uses staged combustion to widen the stable working range of the combustion chamber, and at the same time utilizes the lean premixed combustion of the main combustion stage to reduce NOX pollutant emissions. However, lean premixed combustion has combustion instability problems such as thermoacoustic oscillations. With the increase of the inlet temperature of the combustion chamber, the combustion instability is strengthened, and it is not suitable for high-temperature rise combustion chambers with higher pressure ratios.

Contents of the invention

The technical problem to be solved in the present invention is: in order to overcome the shortcoming and deficiency of above-mentioned prior art, the two-stage pre-film layered partly premixed high-temperature rising combustor structure of the present invention adopts the double-stage pre-film layered part combustion technology, fully Combined with the characteristics of high thrust-to-weight ratio and large air intake at the head of the combustion chamber of the engine, the pre-combustion stage adopts pre-film air atomization to improve the quality of fuel atomization, so as to improve the combustion stability under low-load conditions, and the main combustion stage uses pre-film air atomization Atomization and fuel atomization/oil-gas mixing are carried out step by step to achieve rapid and uniform mixing of oil and gas, avoiding combustion instability problems such as spontaneous combustion or flashback, and uniform combustion in the main combustion area to avoid local high temperature, which is conducive to the quality of outlet temperature distribution Regulation, adjust the flame length through the swirl intensity of the main combustion stage, which is used to shorten the length of the combustion chamber.

The technical solution adopted by the present invention to solve its technical problems:

According to one aspect of the present invention, a double-stage pre-film layered partly premixed high-temperature rising combustor structure is provided, including a combustor casing, a diffuser and a flame tube, and the diffuser is arranged on the combustor casing The inlet end of the flame tube is arranged in the inner cavity of the combustion chamber casing and coincides with the central axis of the combustion chamber casing, and the end wall of the flame tube near the side of the diffuser is provided with double Layer pre-film air atomizing nozzle, characterized in that,

The circumferential outer side of the double-layer pre-film air atomizing nozzle is provided with a head baffle connected to the end wall of the flame tube, and the side of the double-layer pre-film air atomizing nozzle extending into the inside of the flame tube is connected to the An annular deflector is connected, and the double-layer pre-film air atomization nozzle includes a main combustion stage assembly and a pre-combustion stage assembly, wherein,

The pre-combustion stage assembly includes a central diversion cone, a primary air cyclone, an outer shell of the primary air cyclone channel, an inner shell of the secondary air cyclone channel, and a secondary air cyclone that are sequentially arranged from the inside to the outside. Flow device, second-stage cyclone channel outer shell, third-stage air cyclone and third-stage air cyclone outer shell, wherein,

A pre-combustion level fuel channel is set in the annular cylinder composed of the primary air swirler channel outer shell and the secondary air swirler channel inner shell, and a pre-combustion level fuel oil channel is set in the pre-combustion level fuel channel A swirler, the inlet end of the pre-combustion level fuel channel is connected to the pre-combustion level fuel pipe, and the outlet end is provided with an annular fuel injection port, and the fuel flowing out through the annular fuel injection port is in the first-stage air swirler An oil film is formed on the inner wall surface of the outer casing of the channel, and then the pre-film air atomization is carried out under the action of the first-stage swirl air and the second-stage swirl air;

The main combustion stage assembly is located on the outer ring of the pre-combustion stage assembly and is coaxial with the pre-combustion stage assembly, including four-stage air swirlers and four-stage air swirler flow channel casings arranged in sequence from the inside to the outside body, five-stage air cyclone channel inner shell, five-stage air cyclone, five-stage cyclone outer shell and six-stage air cyclone, wherein,

The main combustion stage fuel channel is set in the annular cylinder composed of the fourth-stage air cyclone flow channel outer casing and the fifth-stage air cyclone flow channel inner casing, and the main combustion stage fuel channel is arranged in the main combustion stage fuel channel. The fuel oil swirler, the inlet end of the main combustion stage fuel channel is connected with the main combustion stage fuel pipe, and the outlet end is provided with a main combustion stage fuel injection port. After flowing out through the main combustion stage fuel injection port, an annular uniform thin oil film is formed, which is quickly atomized under the joint action of the fourth-stage and fifth-stage swirl air, and then mixed with the sixth-stage swirl air to form a uniform oil gas The mixture enters the main combustion zone for combustion.

Preferably, the combustor casing includes a combustor outer casing and a combustor inner casing.

Preferably, the flame cylinder includes an outer cylinder of the flame cylinder and an inner cylinder of the flame cylinder.

Preferably, the outer shell of the channel of the primary air cyclone and the inner shell of the channel of the secondary air cyclone are basically consistent in shape, both include an inlet section and an outlet section, and the diameter of the outlet section is smaller than that of the inlet section.

Preferably, the primary air cyclone is arranged between the central diversion cone and the inlet section of the outer casing of the channel of the primary air cyclone.

Preferably, the secondary air cyclone is arranged between the outlet section of the inner casing of the channel of the secondary air cyclone and the inlet section of the outer casing of the flow path of the secondary air cyclone, and the secondary cyclone The outlet section of the outer casing of the flow channel of the device is in the shape of a cone with a gradually decreasing diameter.

Preferably, the tertiary air cyclone is arranged between the inlet section of the outer casing of the flow passage of the second-stage air cyclone and the inlet section of the outer casing of the flow passage of the third-stage air cyclone, and the third-stage air cyclone The outlet section of the outer shell of the flow path of the flow device is in the shape of a trumpet with a sudden expansion in diameter. The three-stage air cyclone is used to cool the outer shell of the flow path of the three-stage cyclone. In the low-speed zone formed by sudden expansion.

Preferably, the six-stage air cyclone is a radial air intake, the lower bottom surface of the left side wall is flush with the inner wall surface of the five-stage cyclone outer shell, and the axis of the right side wall is in line with the combustion chamber machine. The central axis of the box coincides.

Preferably, the installation positions of the fourth-stage air cyclone and the fifth-stage air cyclone are closer to the diffuser than the installation positions of the second-stage air cyclone and the third-stage air cyclone in the axial position. device.

Preferably, the first-stage air cyclone and the second-stage air cyclone rotate in opposite directions, and the third-stage air cyclone and the second-stage air cyclone rotate in the same direction.

Preferably, the fourth-stage air swirler and the fifth-stage air swirler rotate in the opposite direction, and the sixth-stage air swirler and the fifth-stage air swirler rotate in the opposite direction, so as to facilitate the atomization of the main combustion stage fuel oil and oil gas Blend quickly.

Preferably, the fuel oils of the pre-combustion grade and the main combustion grade are controlled separately.

Preferably, the three-stage cyclone adopts a strong swirling flow, so that the three-stage cyclone air is close to the inner wall surface of the flared section of the outer shell of the three-stage cyclone, so as to ensure the cooling effect, and the inclination angle of the blade relative to the central axis is 50-75°, and the angle of the flared section on the outer wall of the third-stage cyclone is between 10-30°.

Preferably, the fuel distribution ratio of the main combustion stage of the two-stage pre-film air atomization nozzle is 60-90%.

Preferably, the intake air volume at the head of the combustion chamber accounts for 60-90% of the total air volume.

In the structure of the double-stage pre-film layered partial premixed high-temperature rise combustor of the present invention, both the main combustion stage and the pre-combustion stage fuel assembly make full use of the increase in combustion air intake at the head of the high thrust-to-weight ratio engine combustion chamber compared to the traditional combustion chamber Features, using pre-film air atomization nozzles in the channel, coupling diffusion combustion and direct fuel injection combustion to form stratified partial premixed combustion, widening the stable working range of the combustion chamber, and improving the quality of temperature distribution at the outlet of the high-temperature rise combustion chamber; pre-combustion level The flame uses a three-stage swirler and a flame stabilizer to stabilize the flame. The first-stage air swirler and the second-stage air swirler, which rotate in opposite directions, use shear force to atomize the pre-filmed fuel oil. The three-stage swirler Cool the flame stabilizer outside the pre-combustion stage flame; the main combustion stage flame is burned by direct fuel injection, the fuel atomization process is separated from the oil-gas mixing process, and the fuel passes through the main combustion stage fuel channel, the main combustion stage fuel swirler and The fuel injection port of the main combustion stage forms an annular thin oil film, and the fuel is pre-filmed by air atomization under the action of the fourth-stage swirl air and the fifth-stage swirl air, and then, at the outlet of the main combustion stage swirler, the atomized The oil-air mixture and the swirling air in the sixth-stage cyclone are quickly mixed. The main combustion stage adopts this atomization method to avoid combustion instability and improve the quality of oil-gas mixing, which is beneficial to the outlet of the high-temperature rise combustion chamber Control of temperature distribution.

The principle of the present invention: the two-stage pre-film layered partly premixed high-temperature rise combustion chamber realizes partitioned and staged combustion based on the layered partly premixed combustion organization principle, and the pre-combustion stage adopts pre-film air atomization to improve the fuel atomization quality to improve the small Combustion stability in the state, the main combustion stage adopts the pre-film air atomization technology of fuel atomization and oil-gas mixing step by step to achieve rapid and uniform mixing of oil and gas, avoiding combustion instability such as spontaneous combustion or tempering, and at the same time mixing evenly The main combustion stage oil-gas mixture burns evenly in the main combustion zone, which is beneficial to the regulation of the temperature distribution of the combustion chamber outlet, and the central pre-combustion stage is used to stabilize the main combustion stage flame, and the flame length and flame shape are adjusted through the main combustion stage swirl intensity. To shorten the length of the combustion chamber.

Compared with the prior art, the present invention has the following advantages:

(1) The present invention adopts the layered partial premixed combustion organization technology, fully combines the characteristics of high thrust-to-weight ratio engine combustion chamber head with more air intake, and couples the two-stage pre-film fuel staged atomization to realize partitioned staged combustion.

(2) The pre-combustion grade fuel adopts pre-film air atomization to improve the atomization quality, combined with the swirl and flame stabilization device to expand the stable working range of lean fuel combustion under the low thrust state of the engine, and at the same time, under the high thrust state of the engine, pre-combustion The primary stage provides a stable ignition source for the main combustion stage.

(3) The fuel atomization of the main combustion stage adopts the step-by-step method of fuel atomization and blending process to realize pre-film air atomization and rapid oil/gas blending, avoiding the combustion instability problem of lean premixed combustion.

(4) In the present invention, the rapid and uniform mixing of main combustion stage oil and gas can avoid the generation of local high temperature areas in the main combustion zone, which is beneficial to the quality control of the outlet temperature of the combustion chamber. length.

Description of drawings

Fig. 1 is the cross-sectional view of the structure of the double-stage pre-film layered part premixed high-temperature rising combustor of the present invention;

Fig. 2 is the cross-sectional view of the flame tube structure of the double-stage pre-film layered part premixed high-temperature rise combustor of the present invention;

Fig. 3 is a cross-sectional view of the head structure of the double-stage pre-film layered part premixed high-temperature rising combustor of the present invention;

Fig. 4 is a cross-sectional view of the structure of the main combustion stage fuel nozzle of the dual-stage pre-film layered partial premixed high-temperature rise combustor of the present invention.

Detailed ways

In order to make the object, technical solution and advantages of the present invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and examples.

Fig. 1 is the cross-sectional view of the structure of the double-stage pre-film layered partly premixed high-temperature rising combustor of the present invention, which adopts the layered partly premixed combustion organization scheme and the short ring structure plan of the double-stage pre-film, including the combustion chamber 1 outside the combustion chamber, the combustion chamber Indoor casing 2, diffuser 3, igniter 4, flame cylinder outer cylinder 5, flame cylinder inner cylinder 6, head baffle 7, deflector 8 and double-layer pre-film air atomizing nozzle 9.

Fig. 2 is the cross-sectional view of the flame cylinder structure of the double-stage pre-film layered part premixed high-temperature rising combustor of the present invention. The stage nozzle enters the combustion chamber, the pre-combustion stage adopts diffusion combustion, which is used to expand the stable working range of the combustion chamber lean fuel combustion, and the main combustion stage adopts lean fuel direct injection combustion, which is used to improve the uniformity of the temperature distribution in the main combustion zone, thereby improving Combustion chamber outlet temperature mass.

The axial and radial spatial distribution of the pre-combustion flame and the main combustion flame are different in the flame tube. The pre-combustion flame is closer to the head and center of the combustion chamber, and the main combustion flame is on the periphery of the pre-combustion flame and along the flow direction. Near the downstream, the pre-combustion stage and the main combustion stage in the combustion chamber are partitioned for combustion. When the working condition is low, the pre-combustion stage works alone, and when the working condition is high, the pre-combustion stage and the main combustion stage work simultaneously. The amount of fuel injected at the main combustion stage accounts for 60-90% of the total fuel, and the air intake at the head of the combustion chamber accounts for 60-90% of the total gas volume. The added feature adopts air atomization, and the main combustion level fuel nozzle separates the process of fuel atomization and blending, and combines aerodynamic and structural features to achieve rapid and uniform blending of oil and gas.

Fig. 3 is a cross-sectional view of the head structure of the double-stage pre-film layered part premixed high-temperature rise combustor of the present invention, the fuel nozzle includes a main combustion stage assembly and a pre-combustion stage assembly, and the pre-combustion stage includes a pre-combustion stage central diversion cone 14, The first-stage air swirler 15, the second-stage air swirler 28, the third-stage air swirler 29, the pre-combustion fuel channel, the pre-combustion fuel swirler 33 and the pre-combustion fuel injection port 20, wherein,

The center deflector cone 14 is located at the center of the device, and the primary air swirler 15 is arranged on the outside of the central deflector cone 14, and the pre-combustion level fuel passage, the pre-combustion level combustion swirler 33 and the pre-combustion level fuel injection port 20 is located in the middle of the primary air swirler and the secondary air swirler, the fuel oil flowing out through the annular fuel injection port 20 forms an oil film on the inner wall surface of the primary air swirler 15 channel, and then flows in the primary swirl air The pre-film air atomization is carried out under the action of the secondary cyclone air, the three-stage air cyclone is located on the outside of the secondary air cyclone, and is used to cool the outer wall surface 23 of the three-stage cyclone, and the pre-combustion stage flame is stable at In the low-velocity zone formed by the sudden expansion of the outer wall surface 23 of the three-stage cyclone. The main combustion stage is located on the outer ring of the pre-combustion stage and coaxial with the pre-combustion stage, including the main combustion stage fuel pipe 19, the fourth stage air swirler 30, the fifth stage air swirler 31, the sixth stage stage air swirler 32, and main combustion stage fuel oil swirler 34, the main combustion stage fuel oil forms an annular uniform thin oil film through the swirler 34, under the action of the fourth and fifth stage swirlers in the opposite direction of rotation The pre-film is quickly atomized, and then the atomized oil-air mixture is mixed with the sixth-stage cyclone air at the outlet of the main combustion-stage cyclone to form a uniform oil-air mixture.

Fig. 4 is the sectional view of the fuel nozzle structure of the main combustion stage of the double-stage pre-film layered partial premixed high-temperature rise combustor of the present invention, including the fourth-stage air swirler 30, the fifth-stage air swirler 31, the sixth-stage air swirler Swirler 32, main combustion grade fuel swirler 34 main combustion grade fuel channel and main combustion grade fuel injection port 35, etc., main combustion grade fuel forms a ring-shaped uniform thin oil film through swirler 34, and in the opposite direction of rotation Under the action of the fourth-stage and fifth-stage cyclones, the pre-film is rapidly atomized, and then the atomized oil-air mixture is mixed with the sixth-stage cyclone air at the outlet of the main combustion-stage cyclone to form a uniform oil-air mixture, which enters the main combustion stage. combustion zone.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included in the present invention. within the range.

Claims (10)

1. A double-stage pre-film layered part premixed high-temperature rising combustor structure, comprising a combustor casing, a diffuser and a flame tube, and the diffuser is arranged at the intake end of the combustor casing, and the The flame cylinder is arranged in the inner cavity of the combustion chamber casing and coincides with the central axis of the combustion chamber casing, and a double-layer pre-film air atomizing nozzle is arranged on the end wall of the flame cylinder near the diffuser , characterized in that, The circumferential outer side of the double-layer pre-film air atomizing nozzle is provided with a head baffle connected to the end wall of the flame tube, and the side of the double-layer pre-film air atomizing nozzle extending into the inside of the flame tube is connected to the An annular deflector is connected, and the double-layer pre-film air atomization nozzle includes a main combustion stage assembly and a pre-combustion stage assembly, wherein, The pre-combustion stage assembly includes a central diversion cone, a primary air cyclone, an outer shell of the primary air cyclone channel, an inner shell of the secondary air cyclone channel, and a secondary air cyclone that are sequentially arranged from the inside to the outside. Flow device, second-stage cyclone channel outer shell, third-stage air cyclone and third-stage air cyclone outer shell, wherein, A pre-combustion level fuel channel is set in the annular cylinder composed of the primary air swirler channel outer shell and the secondary air swirler channel inner shell, and a pre-combustion level fuel oil channel is set in the pre-combustion level fuel channel A swirler, the inlet end of the pre-combustion level fuel channel is connected to the pre-combustion level fuel pipe, and the outlet end is provided with an annular fuel injection port, and the fuel flowing out through the annular fuel injection port is in the first-stage air swirler An oil film is formed on the inner wall surface of the outer casing of the channel, and then the pre-film air atomization is carried out under the action of the first-stage swirl air and the second-stage swirl air; The main combustion stage assembly is located on the outer ring of the pre-combustion stage assembly and is coaxial with the pre-combustion stage assembly, including four-stage air swirlers and four-stage air swirler flow channel casings arranged in sequence from the inside to the outside body, five-stage air cyclone channel inner shell, five-stage air cyclone, five-stage cyclone outer shell and six-stage air cyclone, wherein, The main combustion stage fuel channel is set in the annular cylinder composed of the fourth-stage air cyclone flow channel outer casing and the fifth-stage air cyclone flow channel inner casing, and the main combustion stage fuel channel is arranged in the main combustion stage fuel channel. The fuel oil swirler, the inlet end of the main combustion stage fuel channel is connected with the main combustion stage fuel pipe, and the outlet end is provided with a main combustion stage fuel injection port. After flowing out through the main combustion stage fuel injection port, an annular uniform thin oil film is formed, which is quickly atomized under the joint action of the fourth-stage and fifth-stage swirl air, and then mixed with the sixth-stage swirl air to form a uniform oil gas The mixture enters the main combustion zone for combustion. 2. The double-stage pre-film layered partial premixed high-temperature rise combustor structure according to claim 1, characterized in that, the outer shell of the primary air swirler channel and the inner shell of the secondary air swirler channel The shapes of the valves are basically consistent, including an inlet section and an outlet section, and the diameter of the outlet section is smaller than that of the inlet section. Preferably, the primary air cyclone is arranged between the central guide cone and the inlet section of the channel outer shell of the primary air cyclone. 3. The double-stage pre-film layered partial premixed high-temperature rise combustor structure according to claim 1 or 2, wherein the secondary air swirler is arranged in the passage of the secondary air swirler Between the outlet section of the shell and the inlet section of the outer casing of the flow path of the secondary cyclone, the outlet section of the outer casing of the flow path of the secondary cyclone is in the shape of a cone with a gradually reduced diameter. 4. The double-stage pre-film layered partial premixed high-temperature rise combustor structure according to the preceding claim, characterized in that the three-stage air swirler is arranged at the outer shell of the secondary swirler flow path Between the inlet section and the inlet section of the outer casing of the flow path of the three-stage air cyclone, the outlet section of the outer casing of the flow path of the three-stage air cyclone is in the shape of a horn with a sudden expansion in diameter, and the third-stage air cyclone is used for To cool the outer casing of the three-stage cyclone flow channel, the pre-combustion stage flame is stable in the low-velocity zone formed by the sudden expansion of the outer casing of the three-stage cyclone. 5. The structure of the two-stage pre-film layered partial premixed high-temperature rising combustion chamber according to the preceding claim, wherein the six-stage air swirler is a radial air intake, and the lower bottom surface of the left side wall is in contact with the The inner wall of the outer casing of the five-stage swirler is flush, and the axis of the right side wall coincides with the central axis of the combustion chamber casing. 6. The double-stage pre-film layered partial premixed high-temperature rise combustor structure according to the preceding claim, characterized in that the installation positions of the four-stage air swirler and the five-stage air swirler are in the axial position The installation position of the secondary air cyclone and the tertiary air cyclone is closer to the diffuser. 7. The double-stage pre-film layered partial premixed high-temperature rise combustor structure according to the preceding claim, wherein the first-stage air swirler and the second-stage air swirler rotate in opposite directions, and the third-stage air swirler The swirl direction of the cyclone is the same as that of the second-stage air cyclone. 8. The double-stage pre-film layered partial premixed high-temperature rise combustor structure according to the preceding claim, characterized in that the four-stage air swirler and the fifth-stage air swirler rotate in opposite directions, and the six-stage air swirler The cyclone and the five-stage air cyclone rotate in opposite directions to facilitate the atomization of the main combustion fuel and the rapid mixing of oil and gas. 9. The structure of the two-stage pre-film layered partly premixed high-temperature rising combustion chamber according to the above claim, characterized in that the three-stage swirler adopts strong swirl, so that the three-stage swirl air is close to the third-stage The inner wall of the flared section of the outer shell of the cyclone is to ensure the cooling effect. The inclination angle of the blades relative to the central axis is 50-75°, and the angle of the flared section of the outer wall of the three-stage cyclone is between 10-30°. 10. The double-stage pre-film layered partial premixed high-temperature rise combustor structure according to the preceding claim, characterized in that the fuel distribution ratio of the main combustion stage of the two-stage pre-film air atomization nozzle is 60-90%. Preferably, the intake air volume at the head of the combustion chamber accounts for 60-90% of the total air volume.