CN116293808A - Full-cyclone grading combustion chamber - Google Patents

Abstract

The invention discloses a full-swirl staged combustion chamber, which adopts the idea of staged fuel supply and partitioned combustion, and combines the advantages of physical partitions of conventional afterburners and aerodynamic partitions of swirlers. The present invention uses peripheral strong swirling secondary swirlers to form a duty class, where both ignition and duty combustion take place; at the same time, the central weak swirling main swirler is used to increase the residence time of the main combustion stage and perform main combustion stage combustion , by rationally arranging the rotation direction of each swirler to promote the high-speed flame propagation. The invention achieves a balance between widening the ignition boundary, improving combustion efficiency and controlling flow resistance loss, and ensures that the flow resistance loss of the combustion chamber is small, and is especially suitable for high-flow inlets and small and medium-sized aeroengines that need to increase the total pressure recovery coefficient.

Description

A full swirl staged combustor

technical field

The invention relates to the technical field of new-concept aviation gas turbine combustion, in particular to a fully swirling staged combustor.

Background technique

National defense and military requirements make the flight altitude and flight Mach number of various military aircrafts more and more large. At present, for various advanced afterburners and sub-combustion ram combustors, the Mach number of the inlet before the diffuser has exceeded 0.4, which is much higher than the turbulent flame propagation velocity of aviation kerosene; at the same time, when working near the left boundary of the flight envelope, The inlet of the combustion chamber is often under negative pressure conditions, the air density is low, the chemical reaction rate is slow, and the fuel atomization and mixing performance is poor. These harsh inlet conditions challenge the combustor for wide boundary ignition, flame stabilization and efficient combustion. A common solution is to apply the idea of partitioned fuel supply and staged combustion in the design of the combustion chamber, that is, to use various partition methods to form a relatively independent duty class in the combustion chamber, and to manufacture fires suitable for flame stability inside the duty class. The low-speed return flow field, and set up independent oil supply nozzles for oil supply, ignition and combustion. The area outside the duty class is used as the main combustion stage, and its stable ignition depends entirely on the spread of the duty class flame.

In the current afterburner and sub-combustion ram combustor, the physical structure is mostly used for classification, that is, the independent duty class space is divided by physical walls. Based on this classification idea, a variety of on-duty flame stabilizers such as blunt body type and concave cavity type have been produced; in decades of research and application, the ignition performance, working boundary and combustion efficiency of these flame stabilizers have been obtained. proof. In order to prevent the flame from being blown out by the high-speed incoming flow, the air intake velocity and air flow of the duty stage are not high, and the corresponding oil supply flow is also very low, which means that most of the temperature rise of the combustion chamber still needs to be controlled by the main combustion stage. supply. However, physical classification needs to divide a large duty class area to ensure the stability of the flame, which wastes the limited combustion chamber space and reduces the mixed gas residence time and combustion efficiency of the main combustion stage. In addition, with the continuous increase of the incoming flow velocity at the inlet of the afterburner/ram combustion chamber, the larger frontal area brought by the physical wall will also lead to a sharp increase in the total pressure loss and reduce the engine thrust. The above two shortcomings are particularly prominent in small and medium-sized aero-engines with limited internal space.

Contents of the invention

The technical problem to be solved by the present invention is to provide a fully swirl staged combustion chamber for the defects involved in the background technology.

The present invention adopts the following technical solutions for solving the problems of the technologies described above:

A full-swirl staged combustion chamber, including an intake pipe, casing, flame tube, mounting plate, main swirler, N auxiliary swirlers, corrugated heat shield and high-energy electric nozzle, N is a natural number greater than or equal to 3 ;

The casing is a hollow cylinder with openings at both ends;

The downstream end of the air intake pipe is airtightly connected with the upstream end of the casing for introducing air into the combustion chamber;

The flame tube is coaxially arranged in the casing, and M connecting blocks are arranged on the outer wall of the casing, and M is a natural number greater than or equal to 3; one end of the connecting block is fixedly connected to the outer wall of the flame tube, and the other end is connected to the outer wall of the flame tube. The inner wall of the casing is fixedly connected;

The mounting plate is in the shape of a ring, and its outer wall is airtightly connected with the upstream end of the flame tube;

The main cyclone adopts a secondary cyclone, which is arranged in the center of the mounting plate, and its secondary outer ring is coaxially fixed with the inner wall of the mounting plate;

N mounting holes are evenly arranged on the mounting plate around the circumference of the main cyclone, and the N secondary cyclones are arranged in the N mounting holes correspondingly;

The corrugated heat shield is arranged in the casing, and its upstream end is coaxially fixed to the downstream end of the flame tube;

The inlet pipe is evenly provided with P fuel injection rods extending into it from the outside in the circumferential direction, which are used to input the fuel supply of the main combustion stage, and P is a natural number greater than or equal to 3;

The secondary swirler adopts a single-stage swirl, and its central body is provided with a through hole along its axis, and the through hole of the central body is provided with a nozzle for injecting duty-grade fuel toward the combustion chamber; the N secondary swirls The nozzle in the center of the device communicates with the outside world through the casing through the oil delivery pipe, and is used to input the oil supply of the duty level;

The main swirler is used to separate the homogeneous oil-air mixture formed by the atomization and evaporation of the main combustion grade fuel sprayed through the fuel injection rod and the air to be fully mixed into two inner and outer swirls with opposite rotation directions, so as to enhance the flow of the inner and outer stages. Mixing ability, improve the atomization ability of main combustion grade fuel and the uniformity of oil and gas mixing;

The secondary swirler is used to form a closed return flow, thereby providing a duty-level flow field for stable ignition and high-efficiency combustion;

The high-energy electric nozzle extends into the combustion chamber behind the secondary swirler through the casing and the flame tube in turn for ignition.

As a further optimization scheme of a fully swirling staged combustion chamber in the present invention, the outer ring of the secondary swirler is elliptical, and the straight line where the center of the ellipse and the center of the mounting plate are located is L1, and the line where the major axis of the ellipse is located is L2. Then L1 is perpendicular to L2.

As a further optimization scheme of the full swirl staged combustion chamber of the present invention, the cross section of the intake pipe gradually expands from upstream to downstream, so that the air velocity decreases and the static pressure increases when the air is introduced into the combustion chamber.

As a further optimization scheme of the full swirl staged combustion chamber of the present invention, the nozzle in the through hole of the center body of the secondary swirler adopts a small centrifugal nozzle.

Compared with the prior art, the present invention adopts the above technical scheme and has the following technical effects:

1. The full-swirl staged combustion chamber of the present invention adopts the design idea of oil supply in different areas and staged combustion. In the two classifications, the on-duty class adopts multiple strong swirl secondary swirlers, which can form a stationary symmetrical recirculation zone with the physical wall of the peripheral flame tube and the intake jet of the flame tube diversion hole. The recirculation zone is relatively independent in structure and is not affected by the high-speed mainstream. At the same time, it is equipped with a centrifugal nozzle with good atomization performance and matching oil mist cone and flow field. Therefore, the duty class can successfully ignite and form a stable ignition source under harsh inlet conditions, and then continuously ignite the main combustion stage mixture.

2. In the two classifications, the main combustion stage adopts a two-stage weak swirling main cyclone, the primary and secondary swirls of the main cyclone are opposite in direction, and the turbulent shear layer formed between the primary and secondary swirls can promote the main cyclone Fuel-grade fuel-gas mixture and rapid spread of flame in radial and circumferential directions. The weak swirl can also increase the fuel residence time to a certain extent, thereby improving the combustion efficiency.

3. From the perspective of flow resistance control, the duty-level secondary cyclone has high swirl intensity but a small windward area, and the main combustion-level main cyclone has a large windward area but low swirl intensity, so that neither the inner nor outer stages will generate excessive High flow resistance loss reduces thrust loss under high-speed flow.

4. The straight wall flame tube and transverse corrugated heat shield are used in the design; according to the structural characteristics of the wall and the flow field near the wall, multi-slant hole air film cooling and straight hole evaporative cooling are adopted to prevent the wall from being ablated and improve the Combustion chamber structural strength and service life.

5. The outer ring of the secondary cyclone adopts an oval shape, so that the duty-level recirculation zone formed behind the secondary cyclone can be greatly expanded in the direction of the long axis of the ellipse, effectively improving the joint flame between the secondary cyclones in the circumferential direction The purpose of circumferential cross-flaming can be achieved by using fewer elliptical secondary swirlers, which reduces the weight and complexity of the overall structure of the combustion chamber.

Description of drawings

Fig. 1 is a structural schematic diagram of the present invention.

Fig. 2 is a half-cut schematic diagram of the intake pipe and the outer casing of the present invention.

Fig. 3 is a schematic diagram of the structure of the main cyclone in the present invention.

Fig. 4 is a partial cutaway schematic diagram of the auxiliary swirler and the nozzle on duty in the present invention.

Fig. 5 is a partially cutaway schematic view of the flame tube in the present invention.

Fig. 6 is a schematic diagram of the longitudinal section, flow and combustion process of the central section of the secondary swirler in the present invention.

In the figure, 1-intake pipe, 2-casing, 3-main cyclone, 4-secondary cyclone, 5-flame tube, 6-corrugated heat shield, 7-high-energy electric nozzle, 8-fuel injection rod , 9-The curved pipe part of the duty-level oil pipeline, 10-The duty-level nozzle, 11-The straight pipe part of the duty-level oil pipeline, 12-The central cone of the main cyclone, 13-The primary blade of the main cyclone, 14-The main cyclone Secondary vanes of the deflector, 15-cooling holes of the flame tube, 16-front diversion holes of the flame tube, 17-rear diversion holes of the flame tube, 18-connection block, 19-high-energy electric nozzle installation hole, 20-inner channel , 21-outer duct, 22-duty level strong swirl backflow, 23-intake jet of diversion hole, 24-duty level oil mist cone, 25-duty level combustion zone, 26-main fuel level oil-gas mixture, 27- The primary weak swirl of the main combustion stage, 28-the secondary weak swirl of the main combustion stage, 29-the combustion zone of the main combustion stage, 30-the cooling air intake of the flame tube, and 31-the cooling intake air of the corrugated heat shield.

Implementation

Below in conjunction with accompanying drawing, technical scheme of the present invention is described in further detail:

This 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.

It should be understood that although the terms first, second, third etc. may be used herein to describe various elements, components and/or sections, these elements, components and/or sections should not be limited by these terms. These terms are only used to distinguish one element, component and/or section from another. Thus, a first element, component and/or section discussed below could be termed a second element, component or section without departing from the teachings of the present invention.

As shown in Fig. 1 and Fig. 2, the present invention discloses a full-swirl staged combustion chamber, including an intake pipe, casing, flame tube, mounting plate, main swirler, N auxiliary swirlers, corrugated heat insulation Screen and high-energy nozzle, N is a natural number greater than or equal to 3;

The casing is a hollow cylinder with openings at both ends;

The downstream end of the air intake pipe is airtightly connected with the upstream end of the casing for introducing air into the combustion chamber;

The flame tube is coaxially arranged in the casing, and M connecting blocks are arranged on the outer wall of the casing, and M is a natural number greater than or equal to 3; one end of the connecting block is fixedly connected to the outer wall of the flame tube, and the other end is connected to the outer wall of the flame tube. The inner wall of the casing is fixedly connected;

As shown in Figure 3, the mounting plate is in the shape of a ring, and its outer wall is airtightly connected to the upstream end of the flame tube;

The main cyclone adopts a secondary cyclone, which is arranged in the center of the mounting plate, and its secondary outer ring is coaxially fixed with the inner wall of the mounting plate;

N mounting holes are evenly arranged on the mounting plate around the circumference of the main cyclone, and the N secondary cyclones are arranged in the N mounting holes correspondingly;

The corrugated heat shield is arranged in the casing, and its upstream end is coaxially fixed to the downstream end of the flame tube;

The inlet pipe is evenly provided with P fuel injection rods extending into it from the outside in the circumferential direction, which are used to input the fuel supply of the main combustion stage, and P is a natural number greater than or equal to 3;

The secondary swirler adopts a single-stage swirl, and its central body is provided with a through hole along its axis, and the through hole of the central body is provided with a nozzle for injecting duty-grade fuel toward the combustion chamber; the N secondary swirls The nozzle in the center of the device passes through the casing and communicates with the outside world through the oil delivery pipe, and is used to input the oil supply of the duty level, as shown in Figure 4;

The main swirler is used to separate the homogeneous oil-air mixture formed by the atomization and evaporation of the main combustion grade fuel sprayed through the fuel injection rod and the air to be fully mixed into two inner and outer swirls with opposite rotation directions, so as to enhance the flow of the inner and outer stages. Mixing ability, improve the atomization ability of main combustion grade fuel and the uniformity of oil and gas mixing;

The secondary swirler is used to form a closed return flow, thereby providing a duty-level flow field for stable ignition and high-efficiency combustion;

The high-energy electric nozzle extends into the combustion chamber behind the secondary swirler through the casing and the flame tube in turn for ignition.

As a further optimization scheme of a fully swirling staged combustion chamber in the present invention, the outer ring of the secondary swirler is elliptical, and the straight line where the center of the ellipse and the center of the mounting plate are located is L1, and the line where the major axis of the ellipse is located is L2. Then L1 is perpendicular to L2.

As a further optimization scheme of the full swirl staged combustion chamber of the present invention, the cross section of the intake pipe gradually expands from upstream to downstream, so that the air velocity decreases and the static pressure increases when the air is introduced into the combustion chamber.

As a further optimization scheme of the full swirl staged combustion chamber of the present invention, the nozzle in the through hole of the center body of the secondary swirler adopts a small centrifugal nozzle.

Each secondary swirler corresponds to an oil supply circuit. The fuel is supplied to the rear of the secondary swirler through the duty-level nozzle installed in the center of the secondary swirler to form a duty-grade oil mist cone. Two high-energy electric nozzles are installed symmetrically on the circumference of the combustion chamber, and the high-energy electric nozzles extend into the flame tube. , its front end discharges in the duty-grade strong swirl backflow and ignites the duty-grade oil-gas mixture.

The main cyclone in the center of the flame tube is a two-stage swirl, which can be divided into the central cone of the main cyclone, the primary blade of the main cyclone and the secondary blade of the main cyclone from the inside to the outside. The front of the main cyclone must be The fuel injection rod of the main fuel level is installed at the distance, and multiple radial fuel injection rods penetrate the intake pipe and extend into the interior of the intake passage. Multiple fuel injection holes are radially arranged on each fuel injection rod, and the fuel is injected automatically. The oil hole is ejected sideways, broken up by aerodynamic force and mixed with air. The formed oil-gas mixture flows through the main swirler, and is separated into the primary weak swirl flow of the main combustion stage and the secondary weak swirl flow of the main combustion stage by the first-stage blade of the main swirler and the second-stage blade of the main swirler. The oil-gas mixture in the main combustion stage will be ignited by the flame on duty and undergo combustion in the main combustion stage.

As shown in Figure 5, multiple rows of cooling holes are provided on the walls of the flame tube and the corrugated heat shield. Among them, the cooling holes on the wall of the flame tube adopt the form of multi-slope holes, and the cooling holes on the wall of the corrugated heat shield adopt the form of straight holes. The cold air flowing through the outer duct flows into the inner duct from the cooling hole, forming an air film near the wall of the flame tube and the corrugated heat shield and protecting the wall structure.

Please refer to shown in accompanying drawing 6, the working principle of the full-swirl staged combustor of the present invention is:

1. The incoming air flows into the casing through the air inlet. During this process, the air circulation area increases, the flow velocity decreases, and the static pressure increases, which helps to improve the total pressure recovery coefficient and combustion efficiency. Part of the incoming air flowing into the casing enters the outer duct, and the other part enters the inner duct.

2. In the air entering the inner channel, a small part of the air enters the rear duty class through the auxiliary cyclone, and forms a swirl under the guidance of the auxiliary cyclone. The front of the swirl is limited by the secondary swirler, the upper part is limited by the physical wall of the flame tube, and the rear is blocked by the air inlet jet of the diversion hole formed by the front row of flame tube diversion holes and the flame tube rear row of diversion holes. This combination of aerodynamic restriction and physical restriction restricts the excessive extension of the airflow, thus forming a closed streamline, symmetrical and stable strong swirling backflow of the duty class in the duty class. The return flow is relatively independent, and is less affected by the time-varying or distortion of the incoming flow of the main combustion stage, so it can maintain stable duty-stage combustion under extreme inlet conditions such as low pressure and high speed. At the same time, due to the large return flow of the strong swirling flow, the duty stage does not need an excessively large volume to achieve good flame stability, and the size of the auxiliary swirler can be designed to be smaller, so that the frontal area of the duty stage can be reduced, thereby reducing Small flow resistance loss.

3. A small part of the fuel flows through the duty-level fuel delivery pipe and the duty-level fuel supply nozzle successively, and enters behind the secondary swirler to form an oil mist cone. Rapid atomization evaporates and mixes with air, ignites under the discharge of the high-energy electric nozzle, and forms a stable duty-grade flame in the return flow. At the same time, due to the gradual expansion of the duty-grade strong swirl backflow in the circumferential direction behind the different secondary cyclones, the duty-grade flame can naturally spread in the circumferential direction and ignite the oil-gas mixture behind all the secondary cyclones.

4. Most of the air entering the inner channel flows through the main cyclone; since the fuel injection rod is installed at a certain distance in front of the main cyclone, the main fuel grade fuel is sprayed into the air, and the fuel droplets are atomized, Evaporate and fully mix with air, and the formed uniform oil-gas mixture is separated into the first-level weak swirl flow of the main combustion stage and the second-level weak swirl flow of the main combustion stage by the first-stage blade of the main swirler and the second-stage blade of the main swirler. The combusted high-temperature gas mixture of the above-mentioned duty class diffuses radially, first ignites the secondary weak swirl of the main combustion stage on the outside, and continues to ignite the first-level weak swirl of the main combustion stage inward, forming a combustion zone of the main combustion stage. Because the strength of the two swirls is weak, the flow resistance loss of the main combustion stage can be reduced; the weak swirl itself also increases the residence time of fuel to a certain extent. In addition, the primary weak swirl of the main combustion stage and the secondary weak swirl of the main combustion stage have the opposite direction of rotation, and a strong turbulent shear layer will be formed at the junction of the two, and the high vorticity and high turbulence in the shear layer will Promote oil-gas mixing and flame radial and circumferential diffusion, and improve the combustion efficiency of the main combustion stage.

5. During the combustion process of the combustion chamber, the cold air flowing through the outer channel flows into the inner channel from the cooling holes opened on the flame tube and the corrugated heat shield, forming an air film and protecting the wall structure.

Different from the traditional afterburner/ram combustion chamber, the present invention applies the idea of aerodynamic classification, that is, the duty area and the main combustion area are divided by swirling airflows with different swirl directions. In this classification idea, the swirl intensity can be controlled by adjusting the swirl number of the swirler to achieve a balance between flame stability and total pressure loss; even a variable structure can be designed for different inlet speeds and residual gas Coefficients and other working conditions should be reasonably adapted.

In order to solve the inherent problems of physical staging, the present invention designs a staging combustor in the form of a full swirl, and introduces the aerodynamic staging function of the swirler into the afterburner/ramming combustor design. Considering that the reference cross-section velocity of the afterburner/ram combustion chamber is much higher than that of the main combustion chamber, and serious inlet distortion and inlet time variation often occur, it will be difficult to stabilize the flame if it relies solely on aerodynamic classification, so the physical structure is also partially applied in the design. Strengthen the independence and stability of combustion at the duty level. In the combustion chamber scheme, the peripheral strong swirl secondary swirler is used to form a duty stage, where ignition and duty combustion all take place; at the same time, the central weak swirl main swirler is used to increase the residence time of the main combustion stage and carry out the main combustion Stage combustion, by rationally arranging the swirl direction of each swirler to promote high-speed flame propagation. This combustion organization idea combines the respective advantages of aerodynamic classification and physical classification, and achieves a balance between broadening the ignition boundary, improving combustion efficiency and controlling flow resistance loss.

The full swirl staged combustor of the present invention is a new type of combustor structure design and combustion organization scheme, which is suitable for inlet conditions with high incoming flow velocity and low inlet total pressure, such as afterburner and sub-combustion ram combustor. The combustor adopts the idea of staged fuel supply and zoned combustion, which combines the advantages of conventional afterburner physical zone and swirler aerodynamic zone. Both the main combustion stage and the duty stage use the swirler structure. The duty class uses a cyclone with strong swirling flow, and cooperates with the physical wall surface and the inlet jet of the external duct to form a stable duty class backflow. The duty class flow field is not affected by the mainstream, which can effectively improve the ignition and combustion stability under extreme inlet conditions. sex. The multiple swirls in the duty stage and the main combustion stage can exchange energy and matter through the shear layer between the swirls, so as to promote the mixing of oil and gas, and achieve the purpose of rapid flame transfer and efficient combustion. At the same time, because the duty stage under the strong swirl design combines the characteristics of the aerodynamic classification of the swirler, it can achieve flame stability with a small physical frontal area; while the main combustion stage under the weak swirl design can reduce the high-speed mainstream. The above two points ensure that the flow resistance loss of the combustion chamber is small, so this design is especially suitable for high-flow inlets and small and medium-sized aero-engines that need to increase the total pressure recovery coefficient.

Those skilled in the art can understand that, unless otherwise defined, all terms (including technical terms and scientific terms) used herein have the same meaning as commonly understood by those of ordinary skill in the art to which this invention belongs. It should also be understood that terms such as those defined in commonly used dictionaries should be understood to have a meaning consistent with the meaning in the context of the prior art, and unless defined as herein, are not to be interpreted in an idealized or overly formal sense explain.

The specific embodiments described above have further described the purpose, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above descriptions are only specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims (4)

1. A full-swirl staged combustor, characterized in that it comprises an intake pipe, casing, flame tube, mounting plate, main swirler, N auxiliary swirlers, corrugated heat shield and high-energy electric nozzle, N is a natural number greater than or equal to 3; The casing is a hollow cylinder with openings at both ends; The downstream end of the air intake pipe is airtightly connected with the upstream end of the casing for introducing air into the combustion chamber; The flame tube is coaxially arranged in the casing, and M connecting blocks are arranged on the outer wall of the casing, and M is a natural number greater than or equal to 3; one end of the connecting block is fixedly connected to the outer wall of the flame tube, and the other end is connected to the outer wall of the flame tube. The inner wall of the casing is fixedly connected; The mounting plate is in the shape of a ring, and its outer wall is airtightly connected with the upstream end of the flame tube; The main cyclone adopts a secondary cyclone, which is arranged in the center of the mounting plate, and its secondary outer ring is coaxially fixed with the inner wall of the mounting plate; N mounting holes are evenly arranged on the mounting plate around the circumference of the main cyclone, and the N secondary cyclones are arranged in the N mounting holes correspondingly; The corrugated heat shield is arranged in the casing, and its upstream end is coaxially fixed to the downstream end of the flame tube; The inlet pipe is evenly provided with P fuel injection rods extending into it from the outside in the circumferential direction, which are used to input the fuel supply of the main combustion stage, and P is a natural number greater than or equal to 3; The secondary swirler adopts a single-stage swirl, and its central body is provided with a through hole along its axis, and the through hole of the central body is provided with a nozzle for injecting duty-grade fuel toward the combustion chamber; the N secondary swirls The nozzle in the center of the device communicates with the outside world through the casing through the oil delivery pipe, and is used to input the oil supply of the duty level; The main swirler is used to separate the homogeneous oil-air mixture formed by the atomization and evaporation of the main combustion grade fuel sprayed through the fuel injection rod and the air to be fully mixed into two inner and outer swirls with opposite rotation directions, so as to enhance the flow of the inner and outer stages. Mixing ability, improve the atomization ability of main combustion grade fuel and the uniformity of oil and gas mixing; The secondary swirler is used to form a closed return flow, thereby providing a duty-level flow field for stable ignition and high-efficiency combustion; The high-energy electric nozzle extends into the combustion chamber behind the secondary swirler through the casing and the flame tube in turn for ignition. 2. The full-swirl staged combustion chamber according to claim 1, characterized in that the outer ring of the secondary swirler is elliptical, the straight line where the center of the ellipse and the center of the mounting plate are located is L1, and the major axis of the ellipse is located The line is L2, then L1 is perpendicular to L2. 3. The full-swirl staged combustion chamber according to claim 1, characterized in that, the cross-section of the intake pipe gradually expands from upstream to downstream, so that when the air is introduced into the combustion chamber, the velocity decreases and the static pressure increases. 4. The full swirl staged combustor according to claim 1, characterized in that the nozzle in the through hole of the center body of the secondary swirler adopts a small centrifugal nozzle.

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