Dual-mode low-emission combustion chamber matched with standing vortex evaporation pipe and method

Abstract

The invention discloses a dual-mode low-emission combustion chamber matched with a standing vortex evaporation tube and a method. The combustion chamber comprises a multi-channel diffuser, an inner casing, an outer casing, a flame tube and a high-energy ignition electric nozzle. The flame tube comprises an outer ring wall plate, an inner ring wall plate, a single-concave-cavity structure, a cap cover, a cross flame supporting plate and M * N evaporation pipes. The trapped vortex combustion chamber is combined with two low-emission advanced combustion organization technologies of RQL and LPP, different combustion modes are adopted in different states or different areas in the whole flight cycle so as to adapt to the oil-gas ratios in different states, and the pollutant emission in the whole working condition range is reduced. And meanwhile, the M * N evaporation pipes can also be used for solving the problem that multiphase fuel oil is difficult to supply normally under the aviation kerosene phase state change caused by fuel oil regenerative cooling.

Description

Technical Field

[0001] This invention relates to the field of novel gas turbine combustion technology, and in particular to a dual-mode low-emission combustion chamber and method with matched vortex evaporator tubes. Background Technology

[0002] With increasingly frequent aviation activities worldwide and the growing demand for wider ranges of aircraft (wider Mach numbers, wider fuel-air ratios, and wider flight altitudes), the emissions per aircraft and total emissions will increase dramatically if left unchecked. Currently, subsonic commercial airliners operate at speeds of Mach 0.7-0.8 and altitudes of 9000-12000m. In contrast, next-generation supersonic commercial airliners have maximum cruise speeds exceeding Mach 2 and altitudes increased to 12000-18000m. This results in significant changes to the inlet parameters of combustion chamber components, further increasing thrust performance requirements. Supersonic airliners face multiple operational phases throughout their flight cycle, including idle, takeoff, subsonic flight, breaking the sound barrier, and supersonic cruise. While maintaining performance at the flameout boundary, they must increase the design point fuel-air ratio to improve temperature rise and increase engine thrust. To reduce drag, supersonic airliners operate at higher altitudes, making emissions more likely to directly damage the ozone layer, leading to stricter emission limits in the LTO cycle.

[0003] This places demands on both combustion performance and emission performance in aero-engine combustors, necessitating the development of wide-range, multi-modal, multi-fuel, high-efficiency, low-emission combustion technologies. Currently, four generations of low-emission combustors have been developed internationally, with RQL (Rich-Quenched Lean Combustion) and LPP (Lean Premixed Prevaporization) technologies showing outstanding emission performance in fourth-generation low-emission combustors. Even with the commercial success of advanced combustors like TAPS and TALON, achieving near-term emission standards, LPP and RQL combustion technologies still have their limitations. For example, LPP combustion technology faces issues such as combustion instability and auto-ignition / backfire, while RQL combustion technology has CO and UHC emission levels that are an order of magnitude higher than lean combustion. The naturally occurring geometric zoning of the TVC combustor is well-suited for low-emission combustor design, allowing for the integration of LPP and RQL combustion technologies through different mainstream design approaches. Therefore, under the requirements of a wider range, in order to seek a more effective low-emission combustor design scheme, this paper, based on the structure of the vortex concave cavity and combined with various advanced combustion technologies, uses literature review, theoretical analysis, and simulation and experimental research methods to analyze combustion performance and emission performance, and explore suitable low-emission vortex combustor schemes. In addition, with the increase of combustor inlet air temperature and fuel-air ratio, the quality of cooling gas deteriorates and the cooling air flow rate decreases. Fuel regeneration cooling has gradually become an important cooling method; however, this may lead to changes in the temperature and phase state of aviation kerosene, making it difficult for conventional fuel supply methods to match multiphase fuel for normal supply. Therefore, to solve the technical problems brought about by the wider range of combustor operating conditions, more stringent performance requirements, stricter emission requirements, and fuel phase state, a dual-mode low-emission combustor with vortex evaporator matching radial stages has been developed. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to address the deficiencies mentioned in the background art by providing a dual-mode low-emission combustor and method with matching vortex evaporator tubes. By combining the combustor with two advanced low-emission combustion organization technologies, RQL and LPP, different combustion modes (rich combustion, lean combustion, or a combination of both) are adopted in different states or regions throughout the flight cycle to adapt to different fuel-air ratios and reduce pollutant emissions across the entire operating range.

[0005] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0006] A dual-mode low-emission combustion chamber matched with a vortex evaporator tube includes a multi-channel diffuser, an inner casing, an outer casing, a flame tube, and a high-energy ignition nozzle;

[0007] The multi-channel diffuser is located at the combustion chamber inlet to decelerate and pressurize the gas, and to divert it into the combustion chamber. In the multi-channel diffuser, the inlets of the outer wall plate and the inner wall plate are coplanar, and the distance of the outer wall plate in the axial direction of the combustion chamber is less than the distance of the inner wall plate in the axial direction of the combustion chamber.

[0008] The flame tube includes an outer ring wall plate, an inner ring wall plate, a single concave cavity structure, a cap, a flame support plate, and M*N evaporation tubes, where M and N are both natural numbers greater than or equal to 3.

[0009] The outer ring wall plate and the inner ring wall plate are coaxially arranged, wherein the downstream end of the outer ring wall plate is coaxially fixed to the outer casing to form the outer ring channel of the combustion chamber; the downstream end of the inner ring wall plate is coaxially fixed to the inner casing to form the inner ring channel of the combustion chamber.

[0010] The single concave cavity structure is located upstream of the outer ring wall plate. The single concave cavity structure includes a front wall, a side wall, and a rear wall. The side wall is a hollow cylinder with openings at both ends. The side wall is coaxially arranged inside the outer ring wall plate, with its upstream end coaxially fixed to the outer side of the front wall and its downstream end coaxially fixed to the outer side of the rear wall, forming a U-shaped concave cavity with the opening facing inward. The inner side of the rear wall is coaxially fixed to the upstream end of the outer ring wall plate. The inner side of the front wall is coaxially fixed to the outer side of the flame-connecting support plate. The front wall has an annular inlet slit, and the rear wall has P rear inlet slits evenly arranged circumferentially, where P is a natural number greater than or equal to 3.

[0011] The front wall of the concave cavity is uniformly provided with Q duty oil supply nozzles on the inner side of the inlet air gap for supplying oil into the single concave cavity structure, where Q is a natural number greater than or equal to 3.

[0012] The radius of the cap gradually increases from upstream to downstream. The downstream end of the cap is coaxially fixed to the upstream end of the concave cavity sidewall, and the upstream end of the cap is located inside the Q inlet air slits.

[0013] The flame support plate is provided with M sets of mounting holes at equal intervals from the outside to the inside. Each set contains N mounting holes evenly arranged in the circumference. The axis of the i-th mounting hole in the M sets is coplanar with the axis of the combustion chamber. i is a natural number greater than or equal to 1 and less than or equal to N.

[0014] The evaporator tube includes a tube body, a reflective sputtering plate, a connecting rod, and a flow guide stabilizer. The tube body is a hollow cylinder with openings at both ends. The flow guide stabilizer is disposed inside the tube body and located at the outlet of the tube body. The reflective sputtering plate is coaxially disposed inside the tube body via the connecting rod. The tube body has several air inlets evenly distributed circumferentially between the reflective sputtering plate and the flow guide stabilizer.

[0015] The M*N evaporator tubes are respectively installed in the M*N mounting holes on the flame support plate; the downstream end of the evaporator tube is coaxially fixed in its corresponding mounting hole, and the air inlet on the evaporator tube is located upstream of the flame support plate; the upstream ends of the M*N evaporator tubes are coplanar.

[0016] Each of the evaporator tubes is equipped with a main combustion stage fuel supply nozzle at its inlet, and the main combustion stage fuel supply nozzle is a direct injection nozzle.

[0017] The high-energy ignition nozzle extends from the front wall of the concave cavity into the single concave cavity structure for ignition;

[0018] The flame tube is also provided with several mixing holes evenly distributed around the tail end of its outer shell and inner shell to introduce inner and outer ring cold air to regulate the temperature field at the outlet of the combustion chamber.

[0019] The inner shell, outer shell, and flame-connecting support plate are all uniformly provided with a number of cooling holes for forming an air film to cool their inner wall surfaces.

[0020] As a further optimization of the dual-mode low-emission combustion chamber matched with the vortex evaporator tube of the present invention, the shift fuel supply nozzle adopts a centrifugal nozzle.

[0021] This invention also discloses a method for operating a dual-mode low-emission combustor matched with the vortex evaporator tube, comprising the following steps:

[0022] The flame tube forms a duty zone and a main combustion zone. Fuel is supplied to the duty zone through Q duty zone fuel supply nozzles, and fuel is supplied to the main combustion zone through M*N main combustion zone fuel supply nozzles in the evaporator tubes.

[0023] If it is necessary to operate in RQL mode, the control duty zone equivalence ratio range is 1.2-1.6, and the main combustion zone equivalence ratio range is 0.5-0.6;

[0024] If it is necessary to operate in LPP mode, the equivalence ratio range of the control zone is 0.6-0.9, and the equivalence ratio range of the main combustion zone is 0.6-0.8.

[0025] Compared with the prior art, the present invention, employing the above technical solution, has the following technical effects:

[0026] 1. The dual-mode low-emission combustor with radially graded vortex evaporator tubes matched in this invention is an advanced ultra-low emission combustor. It overcomes design shortcomings in existing low-emission combustor designs by utilizing the flameout capability of the vortex concave cavity and the compact structure of the single concave cavity. It fully leverages the inherent zoned combustion advantages of the vortex concave cavity, combining it with two advanced low-emission combustion organization technologies, RQL and LPP. Different combustion modes (rich combustion, lean combustion, or a combination of both) are employed in different states or regions throughout the flight cycle to adapt to varying air-fuel ratios and reduce pollutant emissions across the entire operating range.

[0027] 2. In RQL mode, the mainstream does not supply fuel, the concave cavity is fuel-rich for combustion and quenched by the low-temperature incoming mainstream flow, ensuring ignition and flame stability while reducing pollutant emissions. In LPP mode, the concave cavity switches to lean combustion, the mainstream is premixed for fuel supply, and the mainstream mixture is ignited through the concave cavity, achieving rapid and efficient combustion under high-pressure conditions and reducing pollutant emissions.

[0028] 3. The single concave cavity structure design ensures that the airflow and flame stability in the combustion chamber are almost unaffected by the flow of the main combustion stage, thereby improving ignition performance and widening the flame stability range; the main combustion stage uses M*N independently working evaporator tubes to achieve efficient combustion of premixed pre-evaporation, and adopts different fuel supply strategies for different operating conditions to achieve low emission benefits.

[0029] 4. The evaporator tube can independently supply fuel of different phases, which can solve the problem of difficulty in supplying multiphase fuel under the phase change of aviation kerosene caused by fuel regeneration cooling. Attached Figure Description

[0030] Figure 1 This is a cross-sectional schematic diagram of the present invention;

[0031] Figure 2 This is a partial cross-sectional view of the evaporator tube and the main combustion stage fuel supply nozzle in this invention.

[0032] In the diagram, 1-outer wall plate of the multi-channel diffuser, 2-inner wall plate of the multi-channel diffuser, 3-outer casing, 4-inner casing, 5-front wall of the cavity, 6-side wall of the cavity, 7-rear wall of the cavity, 8-cap, 9-high-energy ignition nozzle, 10-flame support plate, 11-outer ring wall plate, 12-inner ring wall plate, 13-evaporator tube, 14-on-duty fuel supply nozzle, 15-main combustion stage fuel supply nozzle, 16-fuel supply line of the main combustion stage fuel supply nozzle, 17-pipe body, 18-reflector plate, 19-connecting rod, 20-flow guide stabilizer, 21-air inlet on the pipe body. Detailed Implementation

[0033] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings:

[0034] This invention can be implemented in many different forms and should not be considered limited to the embodiments described herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully express the scope of the invention to those skilled in the art. In the drawings, components are enlarged for clarity.

[0035] It should be understood that although the terms first, second, third, etc., may be used herein to describe various elements, components, and / or parts, these elements, components, and / or parts are not limited by these terms. These terms are merely used to distinguish elements, components, and / or parts from one another. Therefore, the first element, component, and / or part discussed below may be a second element, component, or part without departing from the teachings of this invention.

[0036] In the description of this invention, it should be understood that the terms "horizontal," "vertical," "left," "right," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and should not be construed as limiting this invention; the terms "installation," "connection," "fixing," etc., should be interpreted broadly, for example, they can refer to a fixed connection, a detachable connection, or an integral connection, they can refer to a direct connection, an indirect connection through an intermediate medium, or a connection within two components; for those skilled in the art, the specific meaning of the above terms in this invention can be understood according to the specific circumstances.

[0037] like Figure 1 As shown, the present invention discloses a dual-mode low-emission combustion chamber matched with a vortex evaporator tube, including a multi-channel diffuser, an inner casing, an outer casing, a flame tube, and a high-energy ignition nozzle;

[0038] The multi-channel diffuser is located at the combustion chamber inlet to decelerate and pressurize the gas, and to divert it into the combustion chamber. In the multi-channel diffuser, the inlets of the outer wall plate and the inner wall plate are coplanar, and the distance of the outer wall plate in the axial direction of the combustion chamber is less than the distance of the inner wall plate in the axial direction of the combustion chamber.

[0039] The flame tube includes an outer ring wall plate, an inner ring wall plate, a single concave cavity structure, a cap, a flame support plate, and M*N evaporation tubes, where M and N are both natural numbers greater than or equal to 3.

[0040] The outer ring wall plate and the inner ring wall plate are coaxially arranged, wherein the downstream end of the outer ring wall plate is coaxially fixed to the outer casing to form the outer ring channel of the combustion chamber; the downstream end of the inner ring wall plate is coaxially fixed to the inner casing to form the inner ring channel of the combustion chamber.

[0041] The single concave cavity structure is located upstream of the outer ring wall plate. The single concave cavity structure includes a front wall, a side wall, and a rear wall. The side wall is a hollow cylinder with openings at both ends. The side wall is coaxially arranged inside the outer ring wall plate, with its upstream end coaxially fixed to the outer side of the front wall and its downstream end coaxially fixed to the outer side of the rear wall, forming a U-shaped concave cavity with the opening facing inward. The inner side of the rear wall is coaxially fixed to the upstream end of the outer ring wall plate. The inner side of the front wall is coaxially fixed to the outer side of the flame-connecting support plate. The front wall has an annular inlet slit, and the rear wall has P rear inlet slits evenly arranged circumferentially, where P is a natural number greater than or equal to 3.

[0042] The front wall of the concave cavity is uniformly provided with Q duty oil supply nozzles on the inner side of the inlet air gap for supplying oil into the single concave cavity structure, where Q is a natural number greater than or equal to 3.

[0043] The radius of the cap gradually increases from upstream to downstream. The downstream end of the cap is coaxially fixed to the upstream end of the concave cavity sidewall, and the upstream end of the cap is located inside the Q inlet air slits.

[0044] The flame support plate is provided with M sets of mounting holes at equal intervals from the outside to the inside. Each set contains N mounting holes evenly arranged in the circumference. The axis of the i-th mounting hole in the M sets is coplanar with the axis of the combustion chamber. i is a natural number greater than or equal to 1 and less than or equal to N.

[0045] like Figure 2 As shown, the evaporator tube includes a tube body, a reflective sputtering plate, a connecting rod, and a flow guide stabilizer. The tube body is a hollow cylinder with openings at both ends. The flow guide stabilizer is disposed inside the tube body and located at the outlet of the tube body. The reflective sputtering plate is coaxially disposed inside the tube body via the connecting rod. The tube body has several air inlets evenly distributed circumferentially between the reflective sputtering plate and the flow guide stabilizer.

[0046] The M*N evaporator tubes are respectively installed in the M*N mounting holes on the flame support plate; the downstream end of the evaporator tube is coaxially fixed in its corresponding mounting hole, and the air inlet on the evaporator tube is located upstream of the flame support plate; the upstream ends of the M*N evaporator tubes are coplanar.

[0047] Each of the evaporator tubes is equipped with a main combustion stage fuel supply nozzle at its inlet, and the main combustion stage fuel supply nozzle is a direct injection nozzle.

[0048] The high-energy ignition nozzle extends from the front wall of the concave cavity into the single concave cavity structure for ignition;

[0049] The flame tube is also provided with several mixing holes evenly distributed around the tail end of its outer shell and inner shell to introduce inner and outer ring cold air to regulate the temperature field at the outlet of the combustion chamber.

[0050] The inner shell, outer shell, and flame-connecting support plate are all uniformly provided with a number of cooling holes for forming an air film to cool their inner wall surfaces.

[0051] The on-duty oil supply nozzles should preferably be centrifugal nozzles.

[0052] This invention also discloses a method for operating a dual-mode low-emission combustor matched with the vortex evaporator tube, comprising the following steps:

[0053] The flame tube forms a duty zone and a main combustion zone. Fuel is supplied to the duty zone through Q duty zone fuel supply nozzles, and fuel is supplied to the main combustion zone through M*N main combustion zone fuel supply nozzles in the evaporator tubes.

[0054] If it is necessary to operate in RQL mode, the control duty zone equivalence ratio range is 1.2-1.6, and the main combustion zone equivalence ratio range is 0.5-0.6;

[0055] If it is necessary to operate in LPP mode, the equivalence ratio range of the control zone is 0.6-0.9, and the equivalence ratio range of the main combustion zone is 0.6-0.8.

[0056] The duty unit consists of a single concave cavity structure with front and rear dual air intakes and a duty unit fuel supply nozzle. It is responsible for ignition, flame stabilization, and efficient combustion under low conditions. A low-speed backflow vortex structure is formed in the single concave cavity structure, which is not easily affected by the main flow, so that the concave cavity area has the ability to ignite and stabilize the flame.

[0057] The flame support plate mainly serves to propagate the concave flame to the mainstream, ensuring successful ignition of the premixed oil and gas downstream of each evaporator pipe in the mainstream.

[0058] The main combustion stage consists of M*N evaporator tubes and their internal fuel supply nozzles, achieving clean and efficient combustion under high operating conditions. Fuel is ejected through the direct-injection nozzles within the evaporator tubes, impacting the splash plate wall for secondary abrasion and shearing with the high-speed airflow. It mixes thoroughly in the low-speed zone downstream of the reflective splash plate, then is diverted by the flow guide stabilizer and evenly enters the low-speed zone behind the stabilizer for complete combustion. The evaporator tubes can operate independently; the M*N tubes can be adjusted according to demand to achieve local equivalence ratio control in the main combustion zone, better controlling the generation of thermal pollutants. Simultaneously, the M*N evaporator tubes can independently supply fuel of different phases, addressing issues such as the difficulty in supplying multiphase fuel due to phase changes in aviation kerosene caused by fuel regeneration cooling.

[0059] The working principle of this invention is as follows: Air from the compressor outlet is decelerated and pressurized by a multi-channel diffuser before entering the combustion chamber, where it is divided into four streams. One stream enters the outer annular channel of the combustion chamber, one stream enters the inner annular channel, one stream enters the combustion chamber through the inlet slit of a single-cavity structure, and one stream enters the combustion chamber through M*N evaporator tubes. The airflow in the outer annular channel is divided into three parts: one part enters the cavity through the rear inlet slit of the single-cavity structure, forming a cavity recirculation zone with part of the inlet air from the single-cavity structure; one part enters the flame tube through the outer annular mixing holes; and one part enters the flame tube through the outer annular cooling holes. The airflow in the inner annular channel is divided into two parts: one part enters the flame tube through the inner annular mixing holes; and one part enters the flame tube through the inner annular cooling holes.

[0060] When the engine starts, the high-energy ignition electrode releases an electric spark, supplying fuel to the main combustion chamber. This fuel mixes with the incoming air in the combustion chamber, igniting the combustible mixture and forming a stable flame in the main combustion chamber region. At idle, in RQL mode, only the combustion chamber supplies fuel, while the main flow does not. The combustion chamber is fuel-rich and quenched by the low-temperature incoming flow in the main flow. The equivalence ratio in the main combustion chamber is 1.2-1.6, ensuring ignition and flame stability while reducing pollutant emissions. As operating conditions increase, some unit evaporators can supply fuel, ensuring lean combustion in the main combustion zone, with an equivalence ratio between 0.5-0.6. During the design phase, the system switches to LPP mode, supplying more fuel to the main combustion zone. The combustion chamber transitions to lean combustion, with an equivalence ratio of 0.6-0.9 in the duty zone. Fuel from the main combustion stage is pre-mixed and pre-evaporated within the evaporator tubes, forming an unburned mixture. The high-temperature, already-burned mixture in the combustion chamber flows through the flame support plate to ignite the unburned mixture in the main combustion zone, maintaining an equivalence ratio of 0.6-0.8. Based on different fuel supply strategies, the fuel supply to different evaporator tube units is adjusted to achieve rapid and efficient combustion under high-pressure conditions, while maintaining the combustion zone temperature between 1600K and 1900K throughout the process, effectively reducing nitrogen oxide (NOx) emissions. Simultaneously, the multi-unit evaporator tubes can independently supply fuel of different phases, addressing issues such as the difficulty in supplying multiphase fuel due to phase changes in aviation kerosene caused by fuel regeneration cooling.

[0061] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein.

[0062] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A dual mode low emission combustor with trapped vortex evaporator tube matching characterized in that, The multi-channel diffuser, the inner casing, the outer casing, the flame tube and the high-energy ignition electrode; The multi-channel diffuser is arranged at the inlet of the combustion chamber to slow down and pressurize the gas and to divide the gas into the combustion chamber; in the multi-channel diffuser, the inlets of the outer wall plate and the inner wall plate are coplanar, and the distance of the outer wall plate in the axial direction of the combustion chamber is smaller than the distance of the inner wall plate in the axial direction of the combustion chamber; The flame tube comprises an outer ring wall plate, an inner ring wall plate, a single concave cavity structure, a cap, a flame-branching plate and M*N evaporation tubes, where M and N are natural numbers greater than or equal to 3; The outer ring wall plate and the inner ring wall plate are coaxially arranged, wherein the downstream end of the outer ring wall plate is coaxially fixed to the outer casing to form an outer ring channel of the combustion chamber, and the downstream end of the inner ring wall plate is coaxially fixed to the inner casing to form an inner ring channel of the combustion chamber; The single concave cavity structure is arranged upstream of the outer ring wall plate; the single concave cavity structure comprises a concave cavity front wall, a concave cavity side wall and a concave cavity rear wall, wherein the concave cavity side wall is a hollow cylinder with both ends open; the concave cavity side wall is coaxially arranged in the outer ring wall plate, the upstream end of the concave cavity side wall is coaxially fixed to the outer side of the concave cavity front wall, and the downstream end of the concave cavity side wall is coaxially fixed to the outer side of the concave cavity rear wall to form a U-shaped concave cavity with an opening facing inward; the inner side of the concave cavity rear wall is coaxially fixed to the upstream end of the outer ring wall plate; the inner side of the concave cavity front wall is coaxially fixed to the outer side of the flame-branching plate; the concave cavity front wall is provided with a ring-shaped front air inlet slot, and the concave cavity rear wall is circumferentially and uniformly provided with P rear air inlet slots, where P is a natural number greater than or equal to 3; The concave cavity front wall is circumferentially and uniformly provided with Q duty oil supply nozzles for supplying oil into the single concave cavity structure inside the front air inlet slot, where Q is a natural number greater than or equal to 3; The radius of the cap gradually increases from upstream to downstream, the downstream end of the cap is coaxially fixed to the upstream end of the concave cavity side wall, and the upstream end of the cap is located inside the Q front air inlet slots; The flame-branching plate is equidistantly provided with M groups of mounting holes from outside to inside, each group of mounting holes comprises N mounting holes arranged circumferentially, and the axis of the i th mounting hole of the M groups is coplanar with the axis of the combustion chamber, where i is a natural number greater than or equal to 1 and less than or equal to N; The evaporation tube comprises a tube body, a reflection splash plate, a connecting rod and a flow guide stabilizer, wherein the tube body is a hollow cylinder with both ends open; the flow guide stabilizer is arranged in the tube body and located at the outlet of the tube body; the reflection splash plate is coaxially arranged in the tube body through the connecting rod; the tube body is circumferentially and uniformly provided with a plurality of air inlet holes between the reflection splash plate and the flow guide stabilizer; The M*N evaporation tubes are arranged in the M*N mounting holes on the flame-branching plate one by one; the downstream end of the evaporation tube is coaxially fixed in the corresponding mounting hole, and the air inlet hole on the evaporation tube is located upstream of the flame-branching plate; the upstream ends of the M*N evaporation tubes are coplanar; The inlet of the evaporation tube is provided with a main combustion stage oil supply nozzle, and the main combustion stage oil supply nozzle adopts a direct jet nozzle; The high-energy ignition electrode extends into the single concave cavity structure from the concave cavity front wall to ignite; The flame tube is further circumferentially and uniformly provided with a plurality of mixing holes at the tail end of the outer shell and the inner shell to introduce inner and outer ring cold air to adjust the temperature field at the outlet of the combustion chamber. The inner shell, the outer shell and the flame plate are uniformly provided with a plurality of cooling holes for forming air film cooling inner wall surface.

2. The trapped vortex evaporation tube matched dual mode low emissions combustor of claim 1, wherein, The on-duty class fuel supply nozzle adopts a centrifugal nozzle.

3. The method of operating a dual mode low emission combustion chamber matched with a vortex-shedding evaporation tube according to claim 1, characterized in that, The method comprises the following steps: The flame tube is formed with an on-duty area and a main combustion area, the on-duty area is supplied with fuel through Q on-duty class fuel supply nozzles, and the main combustion area is supplied with fuel through main combustion class fuel supply nozzles in M*N evaporation tubes; If working in the RQL mode, the equivalence ratio of the on-duty area is controlled to be in the range of 1.2-1.6, and the equivalence ratio of the main combustion area is controlled to be in the range of 0.5-0.6; If working in the LPP mode, the equivalence ratio of the on-duty area is controlled to be in the range of 0.6-0.9, and the equivalence ratio of the main combustion area is controlled to be in the range of 0.6-0.8.

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