CN115899766A

CN115899766A - Combustion chamber

Info

Publication number: CN115899766A
Application number: CN202211354281.1A
Authority: CN
Inventors: 高雅; 丁国玉; 陈丕敏; 郭政言
Original assignee: Hunan Aviation Powerplant Research Institute AECC
Current assignee: Hunan Aviation Powerplant Research Institute AECC
Priority date: 2022-10-31
Filing date: 2022-10-31
Publication date: 2023-04-04

Abstract

The invention discloses a combustion chamber which comprises a casing assembly, a flame tube, an oil supply assembly and a premixing pre-evaporation tube. The casing assembly is formed with an inner cavity, an air inlet and a fuel gas outlet. The flame tube is arranged in the inner cavity, and the inner part of the flame tube is divided into a main combustion area, an annular vortex area and a mixing area. The oil supply assembly comprises a main combustion stage nozzle and an on-duty stage nozzle, the main combustion stage nozzle is mounted on the flame tube and communicated with the main combustion area, and the on-duty stage nozzle is mounted at the head of the flame tube and communicated with the annular vortex area. The premixing pre-evaporation pipe is arranged between the main combustion stage nozzle and the flame tube and is used for premixing and pre-evaporating the mixture of air and oil mist. The invention provides a wide-range oil-gas adaptive premixing pre-evaporation low-pollution combustion chamber, which effectively reduces NO _X The discharge and the flow loss are small, and a more ideal outlet temperature field can be obtained; realizes the ignition flame linkage of the full-ring combustion chamber, has high altitude ignition height,the combustion chamber can be ignited and flame-linked in a wide oil-gas ratio range; the flame stability of the whole combustion chamber is better.

Description

Combustion chamber

Technical Field

The invention relates to the technical field of aero-engines, in particular to a combustion chamber.

Background

Along with the rapid development of the aviation industry, the operating environment of an aero-engine faces is increasingly complex, the problems of reliable ignition, stable wide oil-gas range and efficient combustion in multiple working conditions of a combustion chamber are more prominent, and novel combustion schemes and technical researches are urgently needed to be developed.

At present, the combustion chambers can be divided into two categories according to the characteristics of the head: one is the ring vortex type combustion chamber with a flow field organized by swirl plates and impact holes, which is excellent in high-altitude ignition, but has the problems of weak head flow, weak oil-gas mixing and poor outlet temperature field quality; and secondly, the swirl type combustion chamber of the flow field is organized by the swirler, the flame is stabilized by the rotating airflow at the head part, the oil-gas mixing can be enhanced, the oil-gas mixing in the space is uniform, and the quality of the outlet temperature field can be obviously improved. Based on the zoning combustion concept, the combustion chamber combining the ring vortex type combustion chamber and the cyclone type combustion chamber also appears in recent years, and the combustion chamber is called as a WFA (Wide-range Fuel-air attached) combustion chamber due to the characteristics of stable Wide oil-gas range and high-efficiency combustion.

The existing WFA combustion chamber comprises an inner casing, an outer casing, a flame tube inner ring, a flame tube outer ring, a diffuser, a nozzle and other parts, a main combustion stage nozzle is directly communicated with a main combustion area for oil inlet, fuel oil is not pre-evaporated and is not uniformly premixed with air, the lean oil combustion performance in the main combustion area is low, the combustion temperature is high, and NO is enabled to be generated _X The discharge amount is high.

Disclosure of Invention

The invention mainly aims to provide a combustion chamber, aiming at realizing premixing and pre-evaporation combustion of main combustion grade fuel oil in a lean oil atmosphere so as to reduce the temperature of a main combustion zone and inhibit NO _X Thereby reducing pollution.

In order to achieve the above object, the present invention provides a combustion chamber, applied to an aircraft engine, comprising:

the casing component is formed with an inner cavity, an air inlet and a fuel gas outlet which are communicated with the inner cavity;

the flame tube is arranged in the inner cavity, the inner part of the flame tube is divided into a main combustion area, an annular vortex area and a mixing area, the flame tube is provided with an airflow inlet, and the mixing area of the flame tube is communicated with the fuel gas outlet; and

the oil supply assembly comprises a main combustion stage nozzle and an on-duty stage nozzle, the main combustion stage nozzle is mounted on the flame tube and communicated with the main combustion zone, and the on-duty stage nozzle is mounted at the head of the flame tube and communicated with the annular vortex zone; and

the premixing pre-evaporation pipe is arranged between the main combustion stage nozzle and the flame tube, and is provided with a mixing evaporation channel for premixing and pre-evaporating the mixture of air and oil mist.

Optionally, the outlet end of the pre-mixing pre-evaporator tube is provided with a convergent nozzle for flashback prevention.

Optionally, the outlet end of the premixing pre-evaporation tube is mounted on the flame tube through a swirl assembly, the swirl assembly comprises an inner-head swirler and an outer-head swirler surrounding the outer side of the inner-head swirler, and the inner-head swirler is communicated with the outlet end of the premixing pre-evaporation tube.

Optionally, the swirl assembly further comprises an inlet swirler disposed at the main combustion stage nozzle and the inlet end of the pre-mixing pre-evaporation tube.

Optionally, the fuel distribution ratio of the main fuel stage nozzles to the main fuel stage nozzles is 4:1.

Optionally, the head of the flame tube is radially divided into a ring vortex flow head and a rotational flow head, the ring vortex flow head forms the ring vortex region, the rotational flow head forms the main combustion region, the ring vortex flow head is connected with the rotational flow head through a support plate, and the support plate is provided with a support plate air inlet.

Optionally, an eddy flow plate is installed in the top end of the eddy flow head, an eddy air inlet hole is formed in the top end of the eddy flow head, an eddy front wall jet hole is formed in the front wall of the eddy flow head, and an eddy rear wall jet hole is formed in the rear wall of the eddy flow head.

Optionally, the on-duty nozzle is a single-oil-path centrifugal nozzle or a double-oil-path centrifugal nozzle, and the on-duty nozzle is mounted on the front wall of the cavity of the ring vortex flow head and is used for spraying in the direction close to the ring vortex swirling sheet;

the main combustion stage nozzle is a single-oil-way centrifugal nozzle or a double-oil-way centrifugal nozzle, and is inserted into the mixed evaporation channel along the center line of the inlet swirler.

Optionally, the combustion chamber further includes an igniter, the casing assembly is provided with a nozzle hole, the igniter is mounted in the nozzle hole and extends into the ring vortex zone, and an ignition nozzle of the igniter is flush with an inner wall surface of the ring vortex flow head.

Optionally, an inner ring main combustion hole, an inner ring mixing hole and a cooling hole are formed in the wall surface of the inner ring of the flame tube, and an outer ring mixing hole is formed in the wall surface of the outer ring of the flame tube; the inner ring main combustion hole is used for intercepting a main flow backflow area, afterburning and strengthening main flow oil-gas mixing, and the inner ring mixing hole and the outer ring mixing hole are used for adjusting an outlet temperature field; the cooling holes are full-divergence multi-inclined holes;

the airflow inlet comprises the support plate air inlet, the ring vortex air inlet, the inner ring main combustion hole, the inner ring mixing hole, the outer ring mixing hole and the cooling hole.

In the technical scheme of the invention, the combustion chamber comprises a casing assembly, a flame tube, an oil supply assembly and a premixing pre-evaporation pipe; the casing component is formed with an inner cavity, an air inlet and a fuel gas outlet which are communicated with the inner cavity; the flame tube is arranged in the inner cavity, the inner part of the flame tube is divided into a main combustion area, an annular vortex area and a mixing area, the flame tube is provided with an airflow inlet, and the mixing area of the flame tube is communicated with a fuel gas outlet; the oil supply assembly comprises a main combustion grade nozzle and an on-duty grade nozzle, the main combustion grade nozzle is mounted on the flame tube and communicated with the main combustion zone, and the on-duty grade nozzle is mounted at the head of the flame tube and communicated with the annular vortex zone; the premixing pre-evaporation pipe is arranged between the main combustion stage nozzle and the flame tube, and is provided with a mixing evaporation channel for premixing and pre-evaporating the mixture of air and oil mist.

According to the invention, the premixing pre-evaporation pipe is additionally arranged between the main combustion stage nozzle and the main combustion zone, premixing and pre-evaporation combustion of the main combustion stage fuel oil in a lean oil atmosphere are realized, the main combustion zone fuel oil is combusted in a deviation of equivalence ratio as much as possible, the flame temperature can be effectively reduced, and NO is inhibited _X Ultimately reducing the NO in the entire combustion chamber _X And (5) discharging.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.

FIG. 1 is a schematic structural view of a combustion chamber according to an embodiment of the present invention;

FIG. 2 is a schematic structural view of a premixing pre-evaporator tube, a main stage nozzle and a swirler assembly in an embodiment of a combustor of the present invention;

FIG. 3 is a schematic structural diagram of a head of a combustor basket according to an embodiment of the present invention.

The reference numbers indicate:

10. a case assembly; 20. a flame tube; 40. pre-mixing a pre-evaporation pipe; 60. a diffuser; 201. a primary combustion zone; 202. a ring vortex region; 203. a blending region; 31. a primary combustion stage nozzle; 32. a duty-grade nozzle; 401. a hybrid evaporation channel; 402. a nozzle is contracted; 51. a head inner swirler; 52. an outer head swirler; 53. an inlet cyclone; 23. a support plate; 23a, a support plate air inlet hole; 24. a vortex sheet; 24a, a ring vortex inlet; 24b, a jet hole on the front wall of the ring vortex; 24c, a jet hole on the back wall of the ring vortex; 10d, electric nozzle holes; 25a, an inner ring main burning hole; 25b, inner ring mixing holes; 25c, outer ring mixing holes; 25d, cooling holes.

The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that, if directional indications (such as up, down, left, right, front, and back … …) are involved in the embodiment of the present invention, the directional indications are only used to explain the relative position relationship between the components, the motion situation, and the like in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indications are changed accordingly.

In addition, if there is a description relating to "first", "second", etc. in the embodiments of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, if appearing throughout the text, "and/or" is meant to include three juxtaposed aspects, taking "a and/or B" as an example, including either the a aspect, or the B aspect, or both the a and B aspects. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.

In recent years, the aviation protection Committee (CAEP) under the International Civil Aviation Organization (ICAO) has enacted a series of regulations on emission standards for pollution in relation to aeronautical power plants, in which NO is regulated _X The emission limits of (a) are becoming more stringent,european Association of aviation research counseling (ACARE) was also proposed to 2050, NO _X Emission needs to be reduced by 90% compared with 2000. Therefore, low NO _X Emissions are an important evaluation index for low pollution combustors. Various studies on low-pollution combustion technology have shown that improving lean combustion performance and lowering combustion temperature in the main combustion zone are effective in suppressing NO _X And Lean Premixed Pre-evaporation (LPP) combustion is among the most promising combustion modes. The basic mode for realizing the lean oil premixing and pre-evaporation is to pre-evaporate fuel oil, uniformly mix the fuel oil with air, enter a main combustion area, and combust the fuel oil in a lean oil atmosphere.

The invention proposes a combustion chamber for use in aircraft engines, in particular gas turbines. The invention relates to a ring vortex type and spiral flow type combined combustion chamber based on a zoned combustion concept, which belongs to a WFA combustion chamber due to the characteristics of wide oil-gas range, stability and high-efficiency combustion.

Referring to fig. 1 and 2, in an embodiment of the present invention, the combustor includes a casing assembly 10, a liner 20, an oil supply assembly, and a pre-mixing pre-evaporation tube 40. The casing assembly 10 is formed with an inner cavity, and an air inlet and a gas outlet which are communicated with the inner cavity. The flame tube 20 is arranged in the inner cavity, the inner part of the flame tube 20 is divided into a main combustion area 201, an annular vortex area 202 and a blending area 203, the flame tube 20 is provided with an airflow inlet, and the blending area 203 of the flame tube 20 is communicated with a fuel gas outlet. The oil supply assembly comprises a main combustion stage nozzle 31 and an on-duty stage nozzle 32, wherein the main combustion stage nozzle 31 is mounted on the flame tube 20 and communicated with the main combustion area 201, and the on-duty stage nozzle 32 is mounted at the head of the flame tube 20 and communicated with the annular vortex area 202. The premixing pre-evaporation tube 40 is arranged between the main combustion stage nozzle 31 and the flame tube 20, and the premixing pre-evaporation tube 40 is provided with a mixing evaporation channel 401 for performing premixing and pre-evaporation treatment on the air and oil mist mixture.

In this embodiment, the casing assembly 10 may include an inner casing and an outer casing, one end of the casing assembly 10 is provided with an air inlet, a diffuser 60 is installed at the air inlet to perform a pressure increasing and speed reducing process on the entering air, the other end of the casing assembly 10 is provided with a gas outlet, and the gas outlet end of the liner 20 is installed at the gas outlet.

The combustor basket 20 may include an inner ring, an outer ring and a head, the inner ring and the outer ring of the combustor basket 20 are surrounded to form a blending region 203, the head of the combustor basket 20 is radially divided into a vortex-surrounding flow head and a swirl flow head, the vortex-surrounding flow head forms a vortex region 202, and the swirl flow head forms a main combustion region 201.

The oil supply assembly further comprises a main combustion level fuel main pipe and an on-duty level fuel main pipe, the main combustion level fuel main pipe is used for conveying fuel oil and communicated with the main combustion level nozzle 31, and the on-duty level fuel main pipe is communicated with the on-duty level nozzle 32. The number of the main burner stage nozzles 31 and the number of the shift stage nozzles 32 are at least one, and is not limited herein.

The shape of the mixing evaporation passage 401 of the pre-mixing pre-evaporation tube 40 is not limited, and is preferably a circular passage. The outlet end of the pre-mixing pre-evaporation tube 40 is provided with a contraction nozzle 402 which can play a certain anti-backfire role. By arranging the premixing pre-evaporation pipe 40 with the contraction nozzle 402 on the main combustion stage, on one hand, the complete atomization of the fuel oil of the main combustion stage can be realized, on the other hand, the fuel oil can be fully mixed with air, the problems of backfire and spontaneous combustion are considered during the design, and the normal operation of the LPP working mode is ensured.

The invention combines the main combustion level of the WFA combustion chamber and the LPP combustion technology to realize the premixing and the pre-evaporation combustion of the main combustion level fuel oil under the lean atmosphere so as to reduce the temperature of the main combustion area 201 and inhibit NO _X Thereby reducing pollution.

Referring primarily to FIG. 2, in one embodiment, the outlet ends of the premixing pre-evaporation tubes 40 may be mounted to the flame tube 20 by a swirler assembly including an inner header swirler 51 and an outer header swirler 52 surrounding the outer side of the inner header swirler 51, the inner header swirler 51 communicating with the outlet ends of the premixing pre-evaporation tubes 40.

In this embodiment, the swirl assembly may further include an inlet swirler 53, the inlet swirler 53 being disposed at the inlet end of the main stage nozzle 31 and the pre-mixing pre-evaporation tube 40.

The design of the head inner swirler 51 and the head outer swirler 52 adopted by the invention can strengthen the oil-gas mixing of the main combustion zone 201, does not bring large flow loss, and can obtain a more ideal outlet temperature field.

The class nozzles 32 may be mounted on the front wall of the bowl and may be single or double channel nozzles, with the spray direction being three dimensional including a tangential angle to spray near the top spinning disk. The main combustion stage nozzle 31 can also adopt a single-oil-way centrifugal nozzle or a double-oil-way centrifugal nozzle, is inserted into the mixed evaporation channel 401 along the central line of the inlet swirler 53, most of the fuel oil is completely evaporated after passing through the premixing and pre-evaporation section, and a small amount of liquid drops possibly exist and hit on the wall of the premixing and pre-evaporation pipe 40, and secondary atomization is carried out at the outlet.

Because the main combustion stage nozzle 31 adopts a centrifugal nozzle to atomize fuel oil, in an LPP (low pressure fuel process) working mode, the main combustion zone 201 can work in a lean oil state by adjusting an oil-gas ratio, oil mist sprayed by the centrifugal nozzle is atomized under the action of swirling air, and an air-oil mist mixture enters the mixing evaporation channel 401 to be fully mixed and evaporated. The fuel oil distribution ratio of the main combustion level nozzle 31 and the on-duty level nozzle 32 is about 4:1, the equivalence ratio of the pre-mixing pre-evaporation section is designed to be beyond the combustible limit, so that the backfire of the section can be prevented, meanwhile, the residence time of the oil vapor in the section is designed to be beyond the spontaneous combustion time, so that the spontaneous combustion is prevented, and the outlet end of the pre-mixing pre-evaporation pipe 40 is designed to be provided with a contraction nozzle 402, so that a certain backfire preventing effect can be achieved.

In addition, the outer side of the contraction nozzle 402 is provided with a head inner swirler 51, a strong swirl opaque design is adopted, a backflow region with a certain size can be formed at the downstream after a small part of main combustion level air passes through the inner swirler, the backflow region can strengthen flame stability on one hand, and simultaneously can be used as an ignition source to independently stabilize main combustion level oil gas, so that mutual support between the main combustion level and an on-duty level is facilitated, and on the other hand, the flow field structure is relatively regular in spatial distribution, so that the flow field structure is easy to control, and organization of combustion is facilitated. The outer head swirler 52 may be of a weak swirl flow light transmission designThe optical cyclone integrates the advantages of rotational flow and direct flow, and the larger total pressure loss is avoided while the oil-gas mixing is enhanced. The pre-mixing pre-evaporation tube 40 is added in the LPP design of the main combustion stage, the structural replacement and installation are convenient, and meanwhile, the fuel oil in the main combustion zone 201 is combusted in a way of deviating from the equivalence ratio as much as possible, so that the flame temperature can be effectively reduced, and NO is inhibited _X Ultimately reducing the NO of the entire combustion chamber _X And (5) discharging.

Referring to fig. 3, in one embodiment, the swirling flow head and the swirling flow head can be connected by a support plate 23, and the support plate 23 is provided with a support plate air inlet 23a.

The class is connected with the main combustion stage by a support plate 23, and a small amount of straight-through airflow can enter the flame tube 20 through support plate air inlet holes 23a on the front wall and the rear wall of the support plate 23. The design of the support plate 23 can protect the flow in the duty class from being influenced by the main flow, so that the duty class can keep better ignition and extinction performance and wide-range flame stability performance, and the existence of the support plate 23 can strengthen the radial flow between adjacent areas between the duty class and the main combustion class, so that the flame in the concave cavity can be smoothly propagated to the main combustion class, the flame propagation between the duty class and the main combustion class is facilitated, and in addition, an axial backflow area can be formed at the downstream of the support plate 23, so the support plate 23 also has certain flame stability capability. The class, the main combustion stage and the support plate 23 have certain flame stabilizing capability and are mutually independent and have radial flow in space, so that the three can support each other and greatly enhance the flame stability.

That is to say, the support plate 23 structure on the one hand protects the independence of the duty stage and the LPP main combustion stage, on the other hand, the flame stability of the combustion chamber can also be provided with 'triple insurance', and the 'triple insurance' can support each other, so the flame stability of the whole combustion chamber is better.

In addition, the invention adopts radial grading, the structure is compact, the cooling area is smaller, the LPP main combustion stage adopts the design scheme of an inner strong swirler and an outer weak swirler, and simultaneously the pre-mixing pre-evaporation tube 40 is matched, the oil-gas mixing of the main combustion area 201 is enhanced by using smaller total pressure loss, the outlet temperature distribution of the flame tube 20 is more ideal, and the wall surface temperature of the flame tube 20 is effectively reduced.

Referring to fig. 1 to 3, in an embodiment, a vortex sheet 24 is installed in a top end of a vortex-surrounding flow head of the combustion chamber, a vortex inlet 24a is formed in the top end of the vortex-surrounding flow head, a vortex front wall jet hole 24b is formed in a front wall of the vortex-surrounding flow head, and a vortex rear wall jet hole 24c is formed in a rear wall of the vortex-surrounding flow head.

The on-duty nozzle 32 of the combustion chamber can adopt a centrifugal nozzle to supply oil tangentially, the ring vortex region 202 forms tangential flow with larger scale in space through static pressure air inlet of the ring vortex air inlet hole 24a and a circumferential swirl plate combination mode, and a plurality of backflow regions with different scales are formed in the ring vortex region 202 under the cutting action of the ring vortex front wall jet hole 24b and the ring vortex rear wall jet hole 24c. The duty-stage ring vortex head can not only realize reliable ignition flame coupling with the high-altitude ignition height of more than 8km by using a small number of fuel nozzles, but also realize high-efficiency stable combustion under low working conditions, and can better bear the function of flame stabilization so as to adapt to variable and complex working environments.

Referring to fig. 1 and 3, in an embodiment, the casing assembly 10 may be provided with a nozzle hole 10d, the igniter is mounted in the nozzle hole 10d and extends into the vortex ring zone 202, and an ignition nozzle of the igniter is flush with an inner wall surface of the vortex ring flow head.

In this embodiment, the combustion chamber is ignited by a high-energy ignition torch, and the torch hole 10d may be opened in the outer casing.

Referring mainly to fig. 1, in an embodiment, according to the requirements of flowing, mixing and cooling, an inner ring main combustion hole 25a, an inner ring mixing hole 25b and a cooling hole 25d are formed in the inner ring wall surface of the flame tube 20, and an outer ring mixing hole 25c is formed in the outer ring wall surface of the flame tube 20; the inner ring main combustion hole 25a is used for cutting off a main flow backflow area, afterburning and strengthening main flow oil-gas mixing, and the inner ring mixing hole 25b and the outer ring mixing hole 25c are used for adjusting an outlet temperature field; the cooling holes 25d are fully divergent multi-angled holes, the angle of which is a compound angle having a spatial three-dimensional angle.

Referring to fig. 1 and 3, in the present embodiment, the airflow inlet of the combustor basket 20 includes a support plate air inlet hole 23a, a ring vortex air inlet hole 24a, an inner ring main combustion hole 25a, an inner ring dilution hole 25b, an outer ring dilution hole 25c, and a cooling hole 25d.

In this embodiment, the combustor has six air inlets, so the liner 20 can be divided into a main combustion zone 201, a ring vortex zone 202 and a blending zone 203. The ring vortex region 202 mainly takes over the function of ignition and flame connection, and the main combustion region 201 can realize low NO through LPP technology _X Generation, and thus, reduction of NO is emphasized _X The effect of the venting, blending region 203, is to help achieve a more uniform outlet temperature field of the liner 20.

The invention provides a wide-range oil-gas adaptive LPP low-pollution combustor, which combines the characteristics of a ring vortex type combustor and a cyclone type combustor, has the common point with a conventional combustor in terms of aerodynamics, and air enters the combustor after being pressurized and decelerated through a diffuser 60 and then respectively enters the interior of a flame tube 20 from an inner ring, an outer ring and a head of the flame tube 20 after being divided into three paths. Fuel enters the interior of the liner 20 radially through the class nozzles 32, which are located outside the interior cavity of the barrel assembly 10, and the main stage nozzles 31, which are located inside the interior cavity of the barrel assembly 10.

The above description is only an alternative embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, which are within the spirit of the present invention, are included in the scope of the present invention.

Claims

1. A combustion chamber for an aircraft engine, comprising:

the casing assembly is provided with an inner cavity, an air inlet and a fuel gas outlet which are communicated with the inner cavity;

2. The combustor of claim 1, wherein the outlet end of said pre-mix pre-evaporator tube is provided with a converging nozzle for flashback prevention.

3. The combustor of claim 2, wherein the outlet ends of the pre-mix pre-evaporator tubes are mounted to the liner by a swirler assembly, the swirler assembly including an inner-header swirler in communication with the outlet ends of the pre-mix pre-evaporator tubes and an outer-header swirler surrounding the outer side of the inner-header swirler.

4. The combustor of claim 3, wherein the swirl assembly further comprises an inlet swirler disposed at an inlet end of the main combustion stage nozzle and the pre-mix pre-evaporator tube.

5. The combustor of claim 1, wherein the fuel distribution ratio of the main burner stage nozzles to the class stage nozzles is 4:1.

6. The combustor of claim 4, wherein the head of the liner is radially divided into a vortex-surrounding flow head and a swirl flow head, the vortex-surrounding flow head forms the vortex-surrounding region, the swirl flow head forms the main combustion region, the vortex-surrounding flow head and the swirl flow head are connected by a support plate, and the support plate is provided with a support plate air inlet hole.

7. The combustor according to claim 6, wherein a vortex sheet is installed in a top end of the vortex-surrounding flow head, a vortex inlet hole is formed in the top end of the vortex-surrounding flow head, a vortex front wall jet hole is formed in a front wall of the vortex-surrounding flow head, and a vortex rear wall jet hole is formed in a rear wall of the vortex-surrounding flow head.

8. The combustor of claim 7, wherein the class spray nozzle is a single oil path centrifugal spray nozzle or a double oil path centrifugal spray nozzle, and is mounted on a front wall of a cavity of the ring vortex flow head and has a spray direction of spraying near the ring vortex flow sheet;

9. The combustor of claim 7, further comprising an igniter, wherein the casing assembly is provided with a nozzle hole, wherein the igniter is mounted in the nozzle hole and extends into the ring vortex zone, and wherein an ignition nozzle of the igniter is flush with an inner wall surface of the ring vortex flow head.

10. The combustion chamber as claimed in claim 7, wherein the inner ring wall of the flame tube is provided with an inner ring main combustion hole, an inner ring mixing hole and a cooling hole, and the outer ring wall of the flame tube is provided with an outer ring mixing hole; the inner ring main combustion hole is used for cutting off a main flow backflow area, afterburning and strengthening main flow oil-gas mixing, and the inner ring mixing hole and the outer ring mixing hole are used for adjusting an outlet temperature field; the cooling holes are full-divergence multi-inclined holes;