1. A swirl standing vortex partition combustion chamber is characterized by comprising a diffuser, an inner casing, an outer casing, an oil supply module, a high-energy ignition electric nozzle and a flame tube;

the diffuser is arranged at the inlet of the combustion chamber and is used for decelerating and pressurizing gas to enter the combustion chamber;

the flame tube comprises an outer shell, an inner shell, a bluff body, a crossfire plate, a fixed plate, first to third connecting plates and a plurality of axial cyclones;

the outer casing and the inner casing are hollow cylinders with openings at two ends and are coaxially arranged, wherein the outer casing and the outer casing form an outer ring channel of the combustion chamber, and the inner casing form an inner ring channel of the combustion chamber;

the front end of the inner shell is provided with an annular single-cavity structure protruding inwards; the single-cavity structure comprises a cavity front wall, a guide plate, a cavity lower wall and a cavity rear wall, wherein the guide plate is an inwards concave annular plate, and the diameter of the guide plate is gradually reduced from front to back; the front wall and the rear wall of the concave cavity are both annular plates, and the lower wall of the concave cavity is a hollow cylinder with two open ends; the lower wall of the concave cavity is coaxial with the shell, the front end of the lower wall of the concave cavity is connected with the rear end of the guide plate, and the rear end of the lower wall of the concave cavity is connected with the inner side of the rear wall of the concave cavity;

the concave cavity front wall is arranged between the concave cavity front wall and the front end of the guide plate and is parallel to the concave cavity rear wall; a plurality of oil guide pipes are uniformly arranged between the inner side of the front wall of the concave cavity and the guide plate in the circumferential direction; one end of each oil guide pipe is fixedly connected with the guide plate, and the other end of each oil guide pipe is fixedly connected with the inner side of the front wall of the cavity and used for enabling the nozzle to extend into the single cavity structure from the outside of the single cavity structure to spray fuel oil into the single cavity structure; the guide plate is used for enabling a part of gas entering the combustion chamber from the diffuser to enter the single concave cavity structure along the guide plate from a gap between the guide plate and the front wall of the concave cavity to form a backflow area;

the first connecting plate, the second connecting plate, the third connecting plate and the fourth connecting plate are hollow cylinders with openings at two ends, are coaxial with the shell and sequentially reduce in radius;

the flame-coupling plate and the fixed plate are both annular plates, wherein the flame-coupling plate and the front wall of the concave cavity are on the same plane, the inner side of the flame-coupling plate is fixedly connected with the outer side of the front wall of the concave cavity, and the outer side of the flame-coupling plate is fixedly connected with the front end of the shell through the inner wall of the blunt body; the fixed plate and the crossfire plate are arranged in parallel, the outer side of the fixed plate is fixedly connected with the lower end of the outer wall of the bluff body, and the inner side of the fixed plate is fixedly connected with the lower end of the crossfire plate through the third connecting plate, so that a closed cavity is formed among the lower wall of the bluff body, the fixed plate, the crossfire plate and the third connecting plate;

the first connecting plate and the second connecting plate are both arranged in a closed cavity between the fixed plate and the crossfire plate and are divided into a first cavity, a second cavity and a third cavity from outside to inside;

the axial swirler comprises an inner fixed cylinder, an outer fixed cylinder and a plurality of blades, wherein the inner fixed cylinder and the outer fixed cylinder are hollow cylinders with openings at two ends; the outer fixing cylinder is sleeved outside the inner fixing cylinder and is coaxial with the inner fixing cylinder; the blades are uniformly arranged between the inner fixed cylinder and the outer fixed cylinder in the circumferential direction, the roots of the blades are fixedly connected with the outer wall of the inner fixed cylinder, and the tails of the blades are fixedly connected with the inner wall of the outer fixed cylinder;

a plurality of mounting holes which correspond to the axial cyclones one by one are circumferentially formed in the first cavity of the fixing plate and the flame connecting plate; the front end of the outer fixed cylinder of the axial swirler is hermetically and fixedly connected with the corresponding mounting hole on the fixed plate, and the rear end of the outer fixed cylinder is hermetically and fixedly connected with the corresponding mounting hole on the crossfire plate, so that part of the gas entering the combustion chamber from the diffuser forms axial swirling flow and enters the crossfire cylinder;

the fixing plate and the flame connecting plate are circumferentially provided with a plurality of vent holes which are in one-to-one correspondence at the second cavity, so that a plurality of main flow channels are formed in the second cavity by the fixing plate and the flame connecting plate, and part of gas entering the combustion chamber from the diffuser passes through the second cavity and enters the flame tube;

a plurality of first rear air inlet holes for enabling fresh air to enter the single cavity structure and enable the fresh air to burn are formed in the circumferential direction of the rear wall of the cavity;

the rear wall of the concave cavity is also circumferentially provided with a plurality of second rear air inlet holes used for enabling fresh gas to enter the single concave cavity structure to supplement tissue combustion below the first rear air inlet holes;

the oil supply module comprises an on-duty oil supply unit, a main combustion stage rotational flow oil supply unit and a main flow channel oil supply unit;

the on-duty oil supply unit comprises an on-duty oil supply main pipe and a plurality of on-duty fuel nozzles which are uniformly arranged on the on-duty oil supply main pipe in the circumferential direction and correspond to the oil guide pipes one by one, wherein the on-duty oil supply main pipe is arranged at the upstream of the flow guide plate and is provided with an on-duty oil supply inlet pipe for introducing fuel oil from the outside; the class fuel nozzles extend into the corresponding oil guide pipes and are used for injecting fuel into the single cavity structure and mixing with fresh air in the single cavity structure;

the main combustion stage rotational flow oil supply unit comprises a main combustion stage rotational flow oil supply main pipe and a plurality of main combustion stage rotational flow fuel oil nozzles which are uniformly arranged on the main combustion stage rotational flow oil supply main pipe in the circumferential direction and correspond to the axial swirlers one by one, wherein the main combustion stage rotational flow oil supply main pipe is arranged at the upstream of the fixed plate and is provided with a main combustion stage rotational flow oil supply inlet pipe for introducing fuel oil from the outside; the main combustion stage rotational flow fuel nozzles correspondingly extend into the inner fixed cylinders of the corresponding axial swirlers and are used for injecting fuel into the flame tube and mixing the fuel with the rotational flow of the inner axes of the flame tube;

the main flow channel oil supply unit comprises a main flow channel oil supply header and a plurality of main flow channel fuel oil spray holes which are uniformly arranged on the main flow channel oil supply header in the circumferential direction and correspond to the main flow channels in the second cavity in a one-to-one mode, wherein the main flow channel oil supply header is arranged in the third cavity, and a plurality of through holes which correspond to the main flow channel fuel oil spray holes in the one-to-one mode are uniformly arranged on the second connecting plate in the circumferential direction, so that the main flow channel oil supply header can spray oil into the main flow channels in the second cavity through the main flow channel fuel oil spray holes on the main flow channel oil supply header and mix the oil with air flow in the main flow channel fuel oil spray holes;

the high-energy ignition electric nozzle extends into the single cavity structure from the front wall of the cavity and is used for ignition;

the tail ends of the outer shell and the inner shell of the flame tube are also uniformly provided with a plurality of mixing holes in the circumferential direction so as to introduce inner and outer ring cold air to adjust the outlet temperature field of the combustion chamber and protect the turbine guide blades from being ablated;

a plurality of cooling holes for forming air films to cool the inner wall surface of the inner shell, the outer shell and the crossfire plate are uniformly arranged on the inner shell, the outer shell and the crossfire plate; the fixing plate is provided with a plurality of vent holes, so that air can enter the first cavity and then enter the flame tube from the cooling holes in the crossfire plate.

2. The swirl trapped vortex zoned combustor of claim 1, wherein the class fuel nozzle is a centrifugal nozzle.

3. The swirl trapped vortex zoned combustor of claim 1, wherein the primary stage swirl fuel nozzle is a centrifugal nozzle.

4. The cyclone standing vortex partition combustor of claim 1, wherein the installation angle of the vanes in the axial swirler is 45 ° and the number of vanes ranges from 8 to 12.

Background

With the further development of the aircraft engine technology, the thrust-weight ratio is continuously increased, the inlet temperature of the combustion chamber is increased, the oil-gas ratio and the temperature rise of the combustion chamber are increased, the requirements on the performance of the combustion chamber are gradually increased, but the weight of the combustion chamber is further limited, so that the development of the high-oil-ratio combustion chamber faces a plurality of technical challenges: 1. the device can stably work in a wider range, and mainly solves the problems of combustion stability in a low-power state and invisible exhaust smoke combustion in a high-power state; 2. under the conditions of reduced cooling gas distribution and reduced cooling gas quality, the durability of the flame tube is further maintained or even improved; 3. the exhaust pollution is reduced under a large state; 4. the turbine works normally in a severe environment with extremely high temperature, and the outlet temperature distribution coefficient must be greatly reduced. Approaches for solving the above problems can be divided into two categories, one is to adopt reasonable measures to optimize a conventional swirl stabilized combustion chamber, and feasible measures comprise fuel classification, air classification, lean oil premixing, pre-evaporation, multi-stage swirl and the like; the other type is to explore a brand new combustion organization mode and develop a new concept combustor on the basis of mastering basic principles, such as a Trapped Vortex Combustor (TVC), an Ultra Compact Combustor (UCC) and the like.

On the other hand, with the rapid development of the aircraft engine technology, the increasingly severe market competition and the continuous stricter environmental protection requirements, large aircraft engines are developed towards lower cost, higher performance and better environmental protection characteristics. Therefore, while engines such as GE90, PW4084 and TRENT800 are improved and developed and engines such as GP7200, TRENT900, GEnx and TRENT1000 are newly developed, a series of pre-research plans are independently or jointly implemented in the United states and European Union countries, future conventional large-circulation aircraft engine technologies with high performance, light weight, high reliability and low emission and noise are developed and verified, more economic and environment-friendly advanced large-circulation aircraft engine technologies are explored and researched, and a good technical basis is laid for development of future large aircraft engines.

The conventional combustion chamber generates a backflow area after passing through the swirler, so that high-temperature fuel gas is transferred upstream to ignite oil-gas mixed gas under the effect of the backflow area formed behind the swirler, and the backflow area also plays a role in stabilizing flame. The Trapped Vortex Combustor (TVC) is a novel combustion organization mode developed from the 90 s of the 20 th century, and adopts a concept of staged and zoned combustion, wherein a trapped vortex area is in class, a pneumatic structure of a vortex is formed inside through a geometric structure, and the stable vortex trapped structure can realize stable combustion in a wide range after fuel is supplied and ignited; the air of the main combustion stage enters the combustion chamber through different main flow head structures, and high-temperature fuel gas is transferred by the cross-flame structure to enter the main combustion stage from the on-duty stage and ignite the oil-gas mixture of the main combustion stage. In a small state, only the duty level supplies oil, and the main combustion level does not supply oil; in a large state, the class and the main combustion class (main flow) are supplied with oil simultaneously. Foreign research finds that the trapped vortex combustor can obtain very good performance under real conditions: compared with the conventional technology, the ignition performance, the lean blowout performance and the high-altitude ignition performance are improved by 50 percent; the emission of nitrogen oxides is reduced by 40-60% compared with the 1996 ICAO standard CAEP 2; the working range of combustion efficiency up to or exceeding 99% is widened by more than 40%. The united states air force, navy, department of energy, NASA, etc. are all seeking to migrate the technology to possible military small bypass ratio turbofan engines, commercial large bypass ratio turbofan engines, industrial and marine gas turbines. But the swirler structure that conventional combustion chamber set up compares and to stay whirlpool combustion chamber head structure and have better oil-gas mixture ability, can also reduce the flow direction speed of air current simultaneously, becomes rotatory air current with the air current bundle of flow direction, increases the dwell time of air current in the flame tube. Therefore, compared with a conventional combustion chamber, the oil-gas matching of the trapped vortex combustion chamber is more difficult, and the outlet temperature distribution is more difficult to adjust.

Therefore, there is a need for optimization of the trapped vortex combustor and the advantages of the conventional combustor.

Disclosure of Invention

The invention aims to solve the technical problem of providing a swirl standing vortex partition combustion chamber, which adopts a partition mode to set an on-duty class and a main combustion class, and the arrangement mode of the swirl standing vortex partition combustion chamber ensures that the on-duty class combustion is basically not influenced by the main combustion class, thereby realizing high-efficiency combustion during single combustion and realizing the joint work of the on-duty class and the main combustion class. When the flame-retardant combustion chamber works together, high-temperature fuel gas in the trapped vortex area can be transmitted to the main combustion stage through the crossfire plate structure, and fresh mixed gas of the main combustion stage enters the flame tube to be combusted under the wrapping of the duty-level high-temperature fuel gas. The cyclone and the head structure of the traditional trapped vortex combustor are integrally designed, the advantages of the cyclone and the structure of the crossfire plate are combined, and the main combustion stage head which has the advantages of good oil-gas mixing effect, long air flow residence time, stable two-stage operation, compact structure and high space utilization rate is obtained.

The invention adopts the following technical scheme for solving the technical problems:

a swirl standing vortex partition combustion chamber comprises a diffuser, an inner casing, an outer casing, an oil supply module, a high-energy ignition electric nozzle and a flame tube;

the diffuser is arranged at the inlet of the combustion chamber and is used for decelerating and pressurizing gas to enter the combustion chamber;

the flame tube comprises an outer shell, an inner shell, a bluff body, a crossfire plate, a fixed plate, first to third connecting plates and a plurality of axial cyclones;

the outer casing and the inner casing are hollow cylinders with openings at two ends and are coaxially arranged, wherein the outer casing and the outer casing form an outer ring channel of the combustion chamber, and the inner casing form an inner ring channel of the combustion chamber;

the front end of the inner shell is provided with an annular single-cavity structure protruding inwards; the single-cavity structure comprises a cavity front wall, a guide plate, a cavity lower wall and a cavity rear wall, wherein the guide plate is an inwards concave annular plate, and the diameter of the guide plate is gradually reduced from front to back; the front wall and the rear wall of the concave cavity are both annular plates, and the lower wall of the concave cavity is a hollow cylinder with two open ends; the lower wall of the concave cavity is coaxial with the shell, the front end of the lower wall of the concave cavity is connected with the rear end of the guide plate, and the rear end of the lower wall of the concave cavity is connected with the inner side of the rear wall of the concave cavity;

the concave cavity front wall is arranged between the concave cavity front wall and the front end of the guide plate and is parallel to the concave cavity rear wall; a plurality of oil guide pipes are uniformly arranged between the inner side of the front wall of the concave cavity and the guide plate in the circumferential direction; one end of each oil guide pipe is fixedly connected with the guide plate, and the other end of each oil guide pipe is fixedly connected with the inner side of the front wall of the cavity and used for enabling the nozzle to extend into the single cavity structure from the outside of the single cavity structure to spray oil into the single cavity structure; the guide plate is used for enabling a part of gas entering the combustion chamber from the diffuser to enter the single concave cavity structure along the guide plate from a gap between the guide plate and the front wall of the concave cavity to form a backflow area;

the first connecting plate, the second connecting plate, the third connecting plate and the fourth connecting plate are hollow cylinders with openings at two ends, are coaxial with the shell and sequentially reduce in radius;

the flame-coupling plate and the fixed plate are both annular plates, wherein the flame-coupling plate and the front wall of the concave cavity are on the same plane, the inner side of the flame-coupling plate is fixedly connected with the outer side of the front wall of the concave cavity, and the outer side of the flame-coupling plate is fixedly connected with the front end of the shell through the inner wall of the blunt body; the fixed plate and the crossfire plate are arranged in parallel, the outer side of the fixed plate is fixedly connected with the lower end of the outer wall of the bluff body, and the inner side of the fixed plate is fixedly connected with the lower end of the crossfire plate through the third connecting plate, so that a closed cavity is formed among the lower wall of the bluff body, the fixed plate, the crossfire plate and the third connecting plate;

the first connecting plate and the second connecting plate are both arranged in a closed cavity between the fixed plate and the crossfire plate and are divided into a first cavity, a second cavity and a third cavity from outside to inside;

the axial swirler comprises an inner fixed cylinder, an outer fixed cylinder and a plurality of blades, wherein the inner fixed cylinder and the outer fixed cylinder are hollow cylinders with openings at two ends; the outer fixing cylinder is sleeved outside the inner fixing cylinder and is coaxial with the inner fixing cylinder; the blades are uniformly arranged between the inner fixed cylinder and the outer fixed cylinder in the circumferential direction, the roots of the blades are fixedly connected with the outer wall of the inner fixed cylinder, and the tails of the blades are fixedly connected with the inner wall of the outer fixed cylinder;

a plurality of mounting holes which correspond to the axial cyclones one by one are circumferentially formed in the first cavity of the fixing plate and the flame connecting plate; the front end of the outer fixed cylinder of the axial swirler is hermetically and fixedly connected with the corresponding mounting hole on the fixed plate, and the rear end of the outer fixed cylinder is hermetically and fixedly connected with the corresponding mounting hole on the crossfire plate, so that part of the gas entering the combustion chamber from the diffuser forms axial swirling flow and enters the crossfire cylinder;

the fixing plate and the flame connecting plate are circumferentially provided with a plurality of vent holes which are in one-to-one correspondence at the second cavity, so that a plurality of main flow channels are formed in the second cavity by the fixing plate and the flame connecting plate, and part of gas entering the combustion chamber from the diffuser passes through the second cavity and enters the flame tube;

a plurality of first rear air inlet holes for enabling fresh air to enter the single cavity structure and enable the fresh air to burn are formed in the circumferential direction of the rear wall of the cavity;

the rear wall of the concave cavity is also circumferentially provided with a plurality of second rear air inlet holes used for enabling fresh gas to enter the single concave cavity structure to supplement tissue combustion below the first rear air inlet holes;

the oil supply module comprises an on-duty oil supply unit, a main combustion stage rotational flow oil supply unit and a main flow channel oil supply unit;

the on-duty oil supply unit comprises an on-duty oil supply main pipe and a plurality of on-duty fuel nozzles which are uniformly arranged on the on-duty oil supply main pipe in the circumferential direction and correspond to the oil guide pipes one by one, wherein the on-duty oil supply main pipe is arranged at the upstream of the flow guide plate and is provided with an on-duty oil supply inlet pipe for introducing oil from the outside; the class fuel nozzles extend into the corresponding oil guide pipes and are used for injecting oil into the single concave cavity structure and mixing with fresh air in the single concave cavity structure;

the main combustion stage rotational flow oil supply unit comprises a main combustion stage rotational flow oil supply main pipe and a plurality of main combustion stage rotational flow fuel oil nozzles which are uniformly arranged on the main combustion stage rotational flow oil supply main pipe in the circumferential direction and correspond to the axial swirlers one by one, wherein the main combustion stage rotational flow oil supply main pipe is arranged at the upstream of the fixed plate and is provided with a main combustion stage rotational flow oil supply inlet pipe for introducing oil from the outside; the main combustion stage swirl fuel nozzles correspondingly extend into the inner fixed cylinders of the corresponding axial swirlers and are used for injecting oil into the flame tube and mixing the oil with the inner axial line of the flame tube in a swirl manner;

the main flow channel oil supply unit comprises a main flow channel oil supply header and a plurality of main flow channel fuel oil spray holes which are uniformly arranged on the main flow channel oil supply header in the circumferential direction and correspond to the main flow channels in the second cavity in a one-to-one mode, wherein the main flow channel oil supply header is arranged in the third cavity, and a plurality of through holes which correspond to the main flow channel fuel oil spray holes in the one-to-one mode are uniformly arranged on the second connecting plate in the circumferential direction, so that the main flow channel oil supply header can spray oil into the main flow channels in the second cavity through the main flow channel fuel oil spray holes on the main flow channel oil supply header and mix the oil with air flow in the main flow channel fuel oil spray holes;

the high-energy ignition electric nozzle extends into the single cavity structure from the front wall of the cavity and is used for ignition;

the tail ends of the outer shell and the inner shell of the flame tube are also uniformly provided with a plurality of mixing holes in the circumferential direction so as to introduce an outlet temperature field of the inner and outer ring cold air conditioning combustion chamber and protect the turbine guide blades from being ablated;

a plurality of cooling holes for forming air films to cool the inner wall surface of the inner shell, the outer shell and the crossfire plate are uniformly arranged on the inner shell, the outer shell and the crossfire plate; the fixing plate is provided with a plurality of vent holes, so that air can enter the first cavity and then enter the flame tube from the cooling holes in the crossfire plate.

As a further optimization scheme of the swirling flow trapped vortex partition combustion chamber, the on-duty fuel nozzle is a centrifugal nozzle.

As a further optimization scheme of the swirl standing vortex partition combustion chamber, the main combustion stage swirl fuel nozzle adopts a centrifugal nozzle.

As a further optimization scheme of the swirling trapped vortex partition combustion chamber, the installation angle of the blades in the axial swirler is 45 degrees, and the number of the blades ranges from 8 to 12.

Compared with the prior art, the invention adopting the technical scheme has the following technical effects:

1. the swirling flow standing vortex partition combustion chamber is a partition combustion chamber, and efficient combustion in a wider oil-gas range can be realized due to the special arrangement of an overtime stage and a main combustion stage; the class adopts a simple and compact single-cavity form, the airflow forms vortex stationary in the single cavity, the vortex stationary can be used as a stable ignition source to widen the flameout boundary of the combustion chamber, and the stable combustion can be realized under any working condition. The main combustion stage is used for integrally designing the conventional standing vortex combustion chamber and the head of the rotational flow combustion chamber, and the center of the head adopts a structure of a cyclone and a crossfire plate, so that the defect of poor oil-gas mixing effect of a main flow structure of the standing vortex combustion chamber is optimized; the joint of the lower part and the front wall surface of the concave cavity adopts a channel and crossfire plate form, so that the value class and the main combustion class are mutually independent and jointly act to efficiently combust; the high-temperature gas on duty can be transmitted to the main combustion stage from the on duty stage along with the crossfire plate structure, and the fresh mixed gas is wrapped, so that the high-efficiency combustion is realized. In a small state, only the duty level works; in a large state, the duty class and the main combustion class supply oil simultaneously.

2. The swirling trapped vortex partition combustion chamber disclosed by the invention is based on a classification partition concept, realizes the function that each area can work independently and work together efficiently, and widens the flameout point boundary.

3. In the aero-engine with a high oil-gas ratio and a high temperature rise combustion chamber, the integrated head design is utilized to organize high-efficiency stable combustion, the temperature distribution of the outlet of the combustion chamber is effectively adjusted, and smoke and the emission of gaseous pollutants are effectively reduced.

4. The swirl standing vortex partition combustion chamber has the advantages that the head part of the combustion chamber is more compact, the structure is simpler, and the weight and the total pressure loss of the combustion chamber are greatly reduced.

Drawings

FIG. 1 is a schematic view of a full ring configuration of a cyclonic trapped vortex zone combustor in accordance with the present invention;

FIG. 2 is a partial cross-sectional view of the cyclonic trapped vortex zone combustor shown in FIG. 1;

FIG. 3 is an exploded view, partially in section, of the flame tube of the present invention;

FIG. 4 is a schematic partial cross-sectional view of a flame tube of the present invention;

FIG. 5 is a schematic structural diagram of an oil supply unit according to the present invention;

FIG. 6 is a schematic view of the cross-sectional flow and combustion process of the main flow central axis of the swirling trapped vortex zone combustor according to the present invention;

FIG. 7 is a schematic view of the axial cross-section flow and combustion process of the swirling trapped vortex zone combustor crossfire plate of the present invention.

In the figure, 1-cyclone standing vortex partition combustion chamber, 2-diffuser, 3-outer casing, 4-inner casing, 5-ignition electric nozzle, 6-single concave cavity structure, 7-fixed plate, 8-second rear air inlet on the back wall of the concave cavity, 9-first rear air inlet on the back wall of the concave cavity, 10-gap between the front wall of the concave cavity and the guide plate, 11-axial swirler, 12-outer casing, 13-inner casing, 14-bluff body, 15-crossfire plate, 16-cooling hole, 17-duty level oil inlet pipe, 18-duty level oil inlet header pipe, 19-duty level oil nozzle, 20-main fuel level cyclone oil inlet pipe, 21-main fuel level cyclone oil inlet header pipe, 22-main fuel level cyclone oil nozzle, 23-main flow channel oil inlet header pipe, 24-a main flow channel oil supply inlet pipe, 25-a main flow channel fuel spray hole, 26-a mixing hole, 27-a cavity lower wall, 28-a cavity rear wall, 29-a cavity front wall, 30-a guide plate, 31-a main flow channel, 32-a first connecting plate, 33-a second connecting plate, 34-a third connecting plate and 35-an oil guide pipe.

Detailed Description

The technical scheme of the invention is further explained in detail by combining the attached drawings:

the present invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, components are exaggerated for clarity.

Referring to fig. 1 to 5, the present invention discloses a swirl trapped vortex zone combustion chamber, which comprises a diffuser, an inner casing, an outer casing, an oil supply module, a high-energy ignition electric nozzle and a flame tube;

as shown in fig. 1, the diffuser is arranged at the inlet of the combustion chamber and is used for decelerating and pressurizing gas to enter the combustion chamber;

as shown in fig. 3 and 4, the flame tube includes an outer casing, an inner casing, a bluff body, a cross-fire plate, a fixing plate, first to third connecting plates, and a plurality of axial swirlers;

the outer casing and the inner casing are hollow cylinders with openings at two ends and are coaxially arranged, wherein the outer casing and the outer casing form an outer ring channel of the combustion chamber, and the inner casing form an inner ring channel of the combustion chamber;

the front end of the inner shell is provided with an annular single-cavity structure protruding inwards; the single-cavity structure comprises a cavity front wall, a guide plate, a cavity lower wall and a cavity rear wall, wherein the guide plate is an inwards concave annular plate, and the diameter of the guide plate is gradually reduced from front to back; the front wall and the rear wall of the concave cavity are both annular plates, and the lower wall of the concave cavity is a hollow cylinder with two open ends; the lower wall of the concave cavity is coaxial with the shell, the front end of the lower wall of the concave cavity is connected with the rear end of the guide plate, and the rear end of the lower wall of the concave cavity is connected with the inner side of the rear wall of the concave cavity;

the concave cavity front wall is arranged between the concave cavity front wall and the front end of the guide plate and is parallel to the concave cavity rear wall; a plurality of oil guide pipes are uniformly arranged between the inner side of the front wall of the concave cavity and the guide plate in the circumferential direction; one end of each oil guide pipe is fixedly connected with the guide plate, and the other end of each oil guide pipe is fixedly connected with the inner side of the front wall of the cavity and used for enabling the nozzle to extend into the single cavity structure from the outside of the single cavity structure to spray oil into the single cavity structure; the guide plate is used for enabling a part of gas entering the combustion chamber from the diffuser to enter the single concave cavity structure along the guide plate from a gap between the guide plate and the front wall of the concave cavity to form a backflow area;

the first connecting plate, the second connecting plate, the third connecting plate and the fourth connecting plate are hollow cylinders with openings at two ends, are coaxial with the shell and sequentially reduce in radius;

the flame-coupling plate and the fixed plate are both annular plates, wherein the flame-coupling plate and the front wall of the concave cavity are on the same plane, the inner side of the flame-coupling plate is fixedly connected with the outer side of the front wall of the concave cavity, and the outer side of the flame-coupling plate is fixedly connected with the front end of the shell through the inner wall of the blunt body; the fixed plate and the crossfire plate are arranged in parallel, the outer side of the fixed plate is fixedly connected with the lower end of the outer wall of the bluff body, and the inner side of the fixed plate is fixedly connected with the lower end of the crossfire plate through the third connecting plate, so that a closed cavity is formed among the lower wall of the bluff body, the fixed plate, the crossfire plate and the third connecting plate;

the first connecting plate and the second connecting plate are both arranged in a closed cavity between the fixed plate and the crossfire plate and are divided into a first cavity, a second cavity and a third cavity from outside to inside;

the axial swirler comprises an inner fixed cylinder, an outer fixed cylinder and a plurality of blades, wherein the inner fixed cylinder and the outer fixed cylinder are hollow cylinders with openings at two ends; the outer fixing cylinder is sleeved outside the inner fixing cylinder and is coaxial with the inner fixing cylinder; the blades are uniformly arranged between the inner fixed cylinder and the outer fixed cylinder in the circumferential direction, the roots of the blades are fixedly connected with the outer wall of the inner fixed cylinder, and the tails of the blades are fixedly connected with the inner wall of the outer fixed cylinder;

as shown in fig. 2, the fixing plate and the crossfire plate are respectively provided with a plurality of mounting holes corresponding to the axial cyclones one to one in the circumferential direction at the first cavity; the front end of the outer fixed cylinder of the axial swirler is hermetically and fixedly connected with the corresponding mounting hole on the fixed plate, and the rear end of the outer fixed cylinder is hermetically and fixedly connected with the corresponding mounting hole on the crossfire plate, so that part of the gas entering the combustion chamber from the diffuser forms axial swirling flow and enters the crossfire cylinder;

the fixing plate and the flame connecting plate are circumferentially provided with a plurality of vent holes which are in one-to-one correspondence at the second cavity, so that a plurality of main flow channels are formed in the second cavity by the fixing plate and the flame connecting plate, and part of gas entering the combustion chamber from the diffuser passes through the second cavity and enters the flame tube;

a plurality of first rear air inlet holes for enabling fresh air to enter the single cavity structure and enable the fresh air to burn are formed in the circumferential direction of the rear wall of the cavity;

the rear wall of the concave cavity is also circumferentially provided with a plurality of second rear air inlet holes used for enabling fresh gas to enter the single concave cavity structure to supplement tissue combustion below the first rear air inlet holes;

as shown in fig. 5, the oil supply module includes an on-duty oil supply unit, a main combustion stage swirl oil supply unit, and a main flow channel oil supply unit;

the on-duty oil supply unit comprises an on-duty oil supply main pipe and a plurality of on-duty fuel nozzles which are uniformly arranged on the on-duty oil supply main pipe in the circumferential direction and correspond to the oil guide pipes one by one, wherein the on-duty oil supply main pipe is arranged at the upstream of the flow guide plate and is provided with an on-duty oil supply inlet pipe for introducing oil from the outside; the class fuel nozzles extend into the corresponding oil guide pipes and are used for injecting oil into the single concave cavity structure and mixing with fresh air in the single concave cavity structure;

the main combustion stage rotational flow oil supply unit comprises a main combustion stage rotational flow oil supply main pipe and a plurality of main combustion stage rotational flow fuel oil nozzles which are uniformly arranged on the main combustion stage rotational flow oil supply main pipe in the circumferential direction and correspond to the axial swirlers one by one, wherein the main combustion stage rotational flow oil supply main pipe is arranged at the upstream of the fixed plate and is provided with a main combustion stage rotational flow oil supply inlet pipe for introducing oil from the outside; the main combustion stage swirl fuel nozzles correspondingly extend into the inner fixed cylinders of the corresponding axial swirlers and are used for injecting oil into the flame tube and mixing the oil with the inner axial line of the flame tube in a swirl manner;

the main flow channel oil supply unit comprises a main flow channel oil supply header and a plurality of main flow channel fuel oil spray holes which are uniformly arranged on the main flow channel oil supply header in the circumferential direction and correspond to the main flow channels in the second cavity in a one-to-one mode, wherein the main flow channel oil supply header is arranged in the third cavity, and a plurality of through holes which correspond to the main flow channel fuel oil spray holes in the one-to-one mode are uniformly arranged on the second connecting plate in the circumferential direction, so that the main flow channel oil supply header can spray oil into the main flow channels in the second cavity through the main flow channel fuel oil spray holes on the main flow channel oil supply header and mix the oil with air flow in the main flow channel fuel oil spray holes;

the high-energy ignition electric nozzle extends into the single cavity structure from the front wall of the cavity and is used for ignition;

the tail ends of the outer shell and the inner shell of the flame tube are also uniformly provided with a plurality of mixing holes in the circumferential direction so as to introduce an outlet temperature field of the inner and outer ring cold air conditioning combustion chamber and protect the turbine guide blades from being ablated;

a plurality of cooling holes for forming air films to cool the inner wall surface of the inner shell, the outer shell and the crossfire plate are uniformly arranged on the inner shell, the outer shell and the crossfire plate; the fixing plate is provided with a plurality of vent holes, so that air can enter the first cavity and then enter the flame tube from the cooling holes in the crossfire plate.

Centrifugal nozzles are preferentially adopted by the on-duty fuel nozzle and the main combustion level swirl fuel nozzle.

The installation angle of the blades in the axial swirler is preferably 45 degrees, and the number of the blades ranges from 8 to 12.

As shown in fig. 6 and 7, the air from the outlet of the compressor is subjected to speed reduction and pressure boost by the curved-wall diffuser, enters the combustion chamber and is divided into three parts, wherein one part of the air enters the outer ring channel of the combustion chamber, one part of the air enters the inner ring channel of the combustion chamber, and the other part of the air enters the combustion chamber through the head part of the combustion chamber;

the outer loop airflow is divided into two parts: one part enters the flame tube through the cooling hole to cool the wall surface of the flame tube; the other part enters the flame tube through the upper mixing hole and is mixed with high-temperature fuel gas to adjust the temperature field of the outlet.

The inner ring air flow is divided into five parts: (1) the flame tube enters the flame tube through the wall surface seam after passing through the single concave cavity; (2) the flame tube enters the flame tube through the single concave cavity rear wall hole; (3) the mixture enters the flame tube through the cooling holes to cool the wall surface of the flame tube; (4) the mixture enters the flame tube through the lower mixing hole and is mixed with high-temperature fuel gas to adjust the temperature field of the outlet; (5) enters the flame tube through the front wall seam of the single concave cavity.

The head airflow is divided into three parts: (1) entering the flame tube through the swirler; (2) enters the flame tube through the main flow channel; (3) enters the flame tube through the cooling holes to cool the wall surface of the flame tube.

Referring to fig. 6 and 7, at the main flow center interface, the gas entering the single cavity structure from the gap between the cavity front wall and the guide plate, the first rear air inlet hole on the cavity rear wall, the second rear air inlet hole on the cavity rear wall and the cooling hole forms a stable double vortex structure in the single cavity structure. At the moment, the cyclone coupling class fuel nozzle of the front air inlet of the single concave cavity structure sprays fuel to be mixed with the air flow in the single concave cavity structure to form combustible mixed gas with proper equivalence ratio. And when the engine is started, the high-energy ignition electric nozzle releases electric sparks to ignite the mixed gas and perform stationary combustion in the single concave cavity structure. Referring to the illustration, at the center interface of the crossfire plate, the high temperature combustion gases in the single bowl configuration flow along the crossfire plate to the head and upper portion of the flame tube. The outlet of the main flow channel and the outlet of the axial swirler are wrapped by high-temperature fuel gas, mixed gas flowing out of the main flow channel and the axial swirler is ignited under the action of the high-temperature fuel gas, then fresh mixed gas continuously enters the flame tube from the head part and is continuously combusted, and combustion is stabilized under the combined action of the class and the main combustion class. And the mixed air before the outlet jointly acts to flow out of the flame tube to impact the turbine.

It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.

The above-mentioned embodiments, objects, technical solutions and advantages of the present invention are further described in detail, it should be understood that the above-mentioned embodiments are only illustrative of the present invention and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.