CN117267750A

CN117267750A - Bidirectional swirler with double-layer blades and turbine engine combustion chamber

Info

Publication number: CN117267750A
Application number: CN202311480361.6A
Authority: CN
Inventors: 魏光华; 蒋欣儒; 魏峥
Original assignee: Shanghai Jiaotong University
Current assignee: Shanghai Jiaotong University
Priority date: 2023-11-08
Filing date: 2023-11-08
Publication date: 2023-12-22

Abstract

The invention relates to a bi-directional swirler with double-layer blades and a turbine engine combustion chamber, wherein the bi-directional swirler with double-layer blades comprises an inner-layer blade and an outer-layer blade; the inclination directions of the inner layer blades and the outer layer blades are opposite; the inclined direction of the outer layer blade forms an inclined angle with the bottom surface direction of the bidirectional cyclone; the deflection direction of the inner layer blade forms an inclination angle with the bottom surface direction of the bidirectional cyclone; the inner layer blades and the outer layer blades are concentric and have opposite deflection directions; an interlayer is arranged between the inner layer blade and the outer layer blade. Compared with the prior art, the bidirectional cyclone consists of the inner layer of blades, the outer layer of blades and the fuel nozzle at the head, wherein the inclination angles of the inner layer of blades and the outer layer of blades are opposite in direction, so that ignition and combustion maintenance are facilitated, the structure is simple, the manufacture is easy, the practicability and the wide applicability are very strong, and the bidirectional cyclone is helpful for improving the combustion efficiency and the combustion stability of a combustion chamber.

Description

Bidirectional swirler with double-layer blades and turbine engine combustion chamber

Technical Field

The invention relates to the technical field of turbine engines, in particular to a bidirectional cyclone with double-layer blades and a turbine engine combustion chamber.

Background

With the popularity of industrial unmanned aerial vehicles and the trend of unmanned aerial vehicle upsizing, small turbine engines (including scroll shafts, turbine paddles, and turbine jet and turbofan engines of the same power class) are gaining more attention. The combustion chamber is an important component of a small turbine engine, providing kinetic energy to the engine through the mixed combustion of fuel and high pressure air.

In small engines, combustion stability and fuel economy are important indicators of performance. The existing swirler often adopts a single-layer vane design, and the design is simpler in manufacturing process, but the ignition area in the flame tube cannot completely meet the requirements of various combustion chambers, so that the combustion stability of the swirler still has room for improvement, and on the other hand, the temperature distribution of the outlet gas of the combustion chamber provided with the single-layer vane swirler is not very uniform, so that the fuel economy of an engine is reduced. In summary, the swirler provided with the double-layer vanes plays a vital role in improving combustion stability and fuel economy.

For the above reasons, it is necessary to develop a swirler disposed in a combustion chamber of an engine, which can effectively achieve high energy efficiency and stability of fuel combustion under normal operation of the engine, and reduce damage of combustion to an inner wall of a flame tube under long-term operation of the engine.

Disclosure of Invention

The invention aims to solve the defects of the prior art and provide a bidirectional cyclone with double-layer blades and a turbine engine combustion chamber.

The aim of the invention can be achieved by the following technical scheme:

a first object of the present invention is to provide a bi-directional swirler with double-layer vanes, comprising an inner layer vane and an outer layer vane; the inclination directions of the inner layer blades and the outer layer blades are opposite; the outer layer blades and the bottom surface direction of the bidirectional cyclone form an inclination angle; the inner layer blades and the bottom surface direction of the bidirectional cyclone form an inclination angle; the inner layer blades and the outer layer blades are concentric and have opposite deflection directions; an interlayer is arranged between the inner layer blade and the outer layer blade.

Further, the bi-directional swirler with double-layer vanes is in an annular configuration.

Further, a through hole is arranged in the center of the bidirectional swirler with the double-layer blades, so that the fuel nozzle passes through.

Further, the bi-directional swirler with double-layer vanes further comprises a fuel nozzle; the fuel nozzle is arranged at the top end of the bidirectional cyclone and is communicated with the bottom end of the bidirectional cyclone; the fuel nozzle passes through the through hole.

Further, the bidirectional swirler with double-layer blades is arranged on the flame tube of the combustion chamber of the turbine engine in an embedded mode, and the outer ring of the bidirectional swirler with double-layer blades is lower than the surface of the flame tube wall.

Further, the inclination angle formed between the outer layer blades and the bottom surface direction of the bidirectional cyclone is 30-60 degrees; the inner layer blades and the bottom surface direction of the bidirectional cyclone form an inclined angle of 120-150 degrees.

Further preferably, the inclination angle formed by the outer layer blades and the bottom surface direction of the bidirectional cyclone is 45 degrees; the inner layer blades and the bottom surface direction of the bidirectional cyclone form an inclination angle of 135 degrees.

Further, the outer layer blades and the inner layer blades have the same number of blades.

Further, the outer layer blades and the inner layer blades are different in blade length.

Further, the bidirectional cyclone further comprises a cyclone body; the inner layer blades and the outer layer blades are fixedly connected with the cyclone body.

The opposite inclined direction means that the direction of the inner layer blades and the bottom surface direction of the bidirectional cyclone and the direction of the outer layer blades and the opposite inclined direction of the bottom surface direction of the bidirectional cyclone are opposite, and the deflection direction means that the deflection directions of the inner layer blades and the outer layer blades are opposite (clockwise deflection and anticlockwise deflection).

The cyclone consists of the blades which are obliquely arranged on the inner layer and the outer layer, and the lengths, the deflection angles and the inclination angles of the blades on the inner layer and the outer layer of the cyclone are different, so that the vortex speeds and the angles generated by the two groups of blades are different. The vortex flows respectively generated by the two layers of blades and having different flow speeds and directions are converged at the downstream position of the cyclone, and turbulent flow is formed in the converged region. The axial flow velocity of the intersection area formed by the cyclone with the double-layer blades is lower under the influence of turbulence, and the area of the low flow velocity area formed by the cyclone with the double-layer blades is larger, so that the fuel combustion is facilitated.

It is a second object of the present invention to provide a turbine engine combustor including a bi-directional swirler with double-layer vanes.

Further, the turbine engine combustion chamber further comprises a flame tube, the bidirectional swirler with double-layer blades is arranged on the flame tube of the turbine engine combustion chamber in an embedded mode, and the outer ring of the bidirectional swirler with double-layer blades is lower than the surface of the flame tube wall.

Further, the flame tube refers to a formed space surrounded by the wall surface of the inner layer of the combustion chamber of the turbine engine.

Further, the turbine engine combustion chamber further comprises a fuel pipeline, wherein the fuel pipeline is arranged at the bottom end of the bidirectional cyclone and penetrates through the bidirectional cyclone with the double-layer blades.

Further, the turbine engine combustion chamber further comprises a gas film hole, and the gas film hole is arranged on the wall surface of the flame tube.

Further, the turbine engine combustor also includes a housing that engages the wall of the flame tube.

Further, the turbine engine combustion chamber is a can-annular combustion chamber, and the can-annular combustion chamber is provided with a plurality of swirlers for generating vortex flow which is beneficial to combustion at the downstream of the mounting position.

Further, the fuel pipeline comprises a fuel main pipe and fuel branch pipes, each fuel nozzle is connected with one fuel branch pipe, and all the fuel branch pipes are arranged on the fuel main pipe in a welding or bolting mode.

Further, the flame tube wall surface comprises a first flame tube wall surface and a second flame tube wall surface, and the vertical section of the first flame tube wall surface and the vertical section of the second flame tube wall surface are arc sections.

Further, the vertical section of the first flame tube wall surface and the vertical section of the second flame tube wall surface are concentric, and the length of the vertical section of the first flame tube wall surface is smaller than that of the vertical section of the second flame tube wall surface.

Further, the annular pipe combustion chamber is formed by splicing a plurality of annular pipe combustion chamber monomers in an annular way, and each annular pipe combustion chamber monomer comprises the bidirectional cyclone with the double-layer blades.

In the technical scheme, the small turbine engine combustion chamber consists of a cyclone, a flame tube, an inner casing, an outer casing, a fuel pipeline and the like. The vortex device consists of a plurality of deflection blades, when the airflow passes through, the airflow generates rotation to form vortex at the upstream part inside the flame tube, the center of the vortex is a low-pressure area, so that a part of burnt high-temperature fuel gas flows back to form a backflow area, and fresh mixed gas formed by evaporation of fuel droplets is continuously ignited. The highest temperature in the combustion chamber reaches over 2000 degrees and exceeds the heat resistance limit of the flame tube material. In order to ensure combustion safety, secondary air flow is introduced through the air film holes, a cold air film with low temperature is formed to isolate the high-temperature fuel gas on the wall surface, and part of radiant heat of the high-temperature fuel gas is carried away from the wall surface of the part, so that a good cooling protection effect is achieved on the wall surface. Compared with the prior art, the invention has the following beneficial effects:

1) The bidirectional cyclone with double-layer blades provided by the invention consists of an inner layer blade, an outer layer blade and a fuel nozzle at the head. The inner and outer blades have opposite inclination angles for simultaneously flowing air in two directions and colliding to form vortex in the combustion chamber to facilitate ignition and maintain combustion.

2) The bidirectional cyclone with double-layer blades provided by the invention can be arranged on a flame tube of a turbine engine combustion chamber to communicate an air inlet with the inside of the combustion chamber, is simple in structure and easy to manufacture, is a type of cyclone which can be applied to various types of turbine engine combustion chambers, has strong practicability and wide applicability, and provides assistance for improving the combustion efficiency and combustion stability of the combustion chamber.

Drawings

FIG. 1 is a schematic cross-sectional view of a turbine engine combustor of example 1 of the present invention.

Fig. 2 is a schematic structural view (a, front view, b, G-G cross-sectional view in a) of the bidirectional cyclone in embodiment 1 of the present invention.

FIG. 3 is a schematic longitudinal sectional view of a turbine engine combustor of example 1 of the present invention.

Fig. 4 is a perspective view of a bidirectional swirler mounting portion of a turbine engine combustor in accordance with example 1 of the present invention.

FIG. 5 is a schematic cross-sectional view of a turbine engine combustor of example 2 of the present invention.

Fig. 6 is a schematic structural view (a, perspective view, b, front view, C-C cross-sectional view) of the bidirectional cyclone in embodiment 2 of the present invention.

Fig. 7 is a schematic structural view (a, perspective view, b, front view, c, F-F cross-sectional view) of the unidirectional cyclone in the comparative example.

Fig. 8 is a schematic view (bidirectional cyclone) of the gas flowing in the combustion chamber in example 2 of the present invention.

Fig. 9 is a schematic view of the state of gas flowing in the combustion chamber (single-vane cyclone) in the comparative example.

Fig. 10 is a cloud of gas outlet temperature distribution (bidirectional cyclone) in example 2 of the present invention.

Fig. 11 is a cloud of gas outlet temperature distribution (single vane cyclone) in the comparative example.

FIG. 12 is a left side view of a turbine engine combustor of embodiment 2 of the present invention.

FIG. 13 is a front view of a turbine engine combustor of embodiment 2 of the present invention.

FIG. 14 is a right side view of a turbine engine combustor of embodiment 2 of the present invention.

Fig. 15 is a transverse cross-sectional view of H-H of fig. 13.

Fig. 16 is a longitudinal cross-sectional view of the I-I of fig. 13.

The meaning of the symbols in the drawings is as follows:

1. a fuel nozzle, 2, an inner layer blade, 3, an outer layer blade, 4, a hollow structure, 4', a solid structure, 5, a fuel pipeline, 6, an air inlet, 7, a fuel gas outlet, 8, a flame tube, 9, gas film holes 9, 10 and a shell; 11. a fairing; 12. turbine engine combustors.

Detailed Description

The invention will now be described in detail with reference to the drawings and specific examples. Features such as a part model, a material name, a connection structure, a control method and the like which are not explicitly described in the technical scheme are all regarded as common technical features disclosed in the prior art.

In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.

It is noted that in the present invention, relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises an element.

Example 1

As shown in fig. 1 to 4, the present embodiment provides a bi-directional swirler with double-layer blades, which includes an inner-layer blade 2 and an outer-layer blade 3; the inclination directions of the inner layer blades 2 and the outer layer blades 3 are opposite; the outer layer blades 3 form an inclination angle with the bottom surface direction of the bidirectional cyclone; the inner layer blades 2 form an inclination angle with the bottom surface direction of the bidirectional cyclone; the inner layer blades 2 and the outer layer blades 3 are concentric and have opposite deflection directions; an interlayer is arranged between the inner layer blade 2 and the outer layer blade 3.

The bidirectional cyclone with the double-layer blades is in an annular structure.

The center of the bidirectional swirler with double-layer blades is provided with a through hole for enabling the fuel nozzle 1 to pass through.

The bi-directional swirler with double-layer vanes further comprises a fuel nozzle 1; the fuel nozzle 1 is arranged at the top end of the bidirectional cyclone and is communicated with the bottom end of the bidirectional cyclone; the fuel nozzle 1 passes through the through hole.

In this embodiment, the fuel nozzle 1 comprises a hollow structure 4.

As shown in fig. 4, the bidirectional swirler with double-layer blades is mounted on a flame tube 8 of a combustion chamber of a turbine engine in an embedded mode, and the outer ring of the bidirectional swirler with double-layer blades is lower than the wall surface of the flame tube 8.

The inclination angle formed between the outer layer blades 3 and the bottom surface direction of the bidirectional cyclone is 30-60 degrees; the inner layer blades 2 and the bottom surface direction of the bidirectional cyclone form an inclined angle of 120-150 degrees.

The number of the outer layer blades 3 is the same as that of the inner layer blades 2.

The outer layer blades 3 and the inner layer blades 2 have different blade lengths.

The bidirectional cyclone also comprises a cyclone body; the inner layer blades 2 and the outer layer blades 3 are fixedly connected with the cyclone body.

The cyclone consists of an inner layer of blades and an outer layer of blades which are obliquely arranged, as shown in figure 1. The length, deflection angle and inclination angle of the inner layer blades 3 and the outer layer blades of the cyclone are different, so that the vortex speed and the angle generated by the two groups of blades are different. The vortex flows respectively generated by the two layers of blades and having different flow speeds and directions are converged at the downstream position of the cyclone, and turbulent flow is formed in the converged region. The axial flow velocity of the intersection area formed by the cyclone with the double-layer blades is lower under the influence of turbulence, and the area of the low flow velocity area formed by the cyclone with the double-layer blades is larger, so that the fuel combustion is facilitated.

The present embodiment further provides a turbine engine combustor including a bi-directional swirler with double-layer vanes.

The turbine engine combustion chamber further comprises a flame tube 8, the bidirectional swirler with double-layer blades is arranged on the flame tube 8 of the turbine engine combustion chamber in an embedded mode, and the outer ring of the bidirectional swirler with double-layer blades is lower than the wall surface of the flame tube 8.

The flame tube 8 is a space formed by the whole wall surface of the inner layer of the combustion chamber of the turbine engine.

The turbine engine combustion chamber further comprises a fuel pipeline 5, wherein the fuel pipeline 5 is arranged at the bottom end of the bidirectional cyclone and penetrates through the bidirectional cyclone with double-layer blades.

The turbine engine combustion chamber further comprises a gas film hole 9, and the gas film hole 9 is arranged on the wall surface of the flame tube 8.

The turbine engine combustor also includes a housing 10, the housing 10 engaging the wall of the liner 8.

The turbine engine combustion chamber is a can-annular combustion chamber, and the can-annular combustion chamber is provided with a plurality of swirlers and is used for generating vortex which is beneficial to combustion at the downstream of the installation position.

The fuel line 5 comprises a fuel manifold and fuel branches, one for each fuel nozzle 1, all of which are mounted on the fuel manifold by welding or bolting.

The wall surface of the flame tube 8 comprises a first flame tube 8 wall surface and a second flame tube 8 wall surface, and the vertical section of the first flame tube 8 wall surface and the vertical section of the second flame tube 8 wall surface are arc sections.

The vertical section of the wall surface of the first flame tube 8 and the vertical section of the wall surface of the second flame tube 8 are concentric, and the length of the vertical section of the wall surface of the first flame tube 8 is smaller than that of the vertical section of the wall surface of the second flame tube 8.

The annular pipe combustion chamber is formed by splicing a plurality of annular pipe combustion chamber monomers in an annular way, and each annular pipe combustion chamber monomer comprises the bidirectional cyclone with the double-layer blades.

The turbine engine combustion chamber further comprises an air inlet 6, a gas outlet 7. The air inlet 6 is provided at one end of the flame tube 8, and the gas outlet 7 is provided at one end of the housing 10.

Example 2

As shown in fig. 5 to 6, the turbine engine combustor 12 of the present embodiment includes a combustor basket 8, a swirler body, a fuel nozzle 1, a cowling 11, and an inner and outer two-layer casing.

The cyclone body and the fuel nozzle 1 form a bidirectional cyclone with double-layer blades.

The front part of the annular tube flame tube 8 is connected with a cyclone through a riveting mode, and a cavity structure is designed in the cyclone and used as a fuel main pipe and a fuel branch pipe. As shown in fig. 12 to 16, 9 fuel nozzles 1 are connected to the fuel manifold inside the cowling 11 by bolting, and 9 swirlers are connected to the cowling 11 by bolting, respectively, and the fuel nozzles 1 are ensured to be coaxial with the swirler body. The structure of the bidirectional swirler with double-layer blades is shown in fig. 6, the swirler comprises a swirler body and a fuel nozzle 1, the swirler body comprises inner and outer layers of blades with opposite deflection directions, the thickness of the two layers of blades is 0.7mm, and the number of the blades is 12; as shown in FIG. 6, the inner diameter of the outer layer blade 3 is 11.5mm, the outer diameter is 14.2mm, the chord length of the blade is 10.6mm, the aspect ratio is 0.26, and the inclination angle formed by the outer layer blade 3 and the bottom surface of the cyclone is 45 degrees; the inner diameter of the inner layer blade 2 is 7.4mm, the outer diameter is 10.5mm, the chord length of the blade is 9.9mm, the aspect ratio is 0.31, and an inclination angle is 135 degrees with the bottom surface of the cyclone; a partition plate with the thickness of 1mm is arranged between the inner layer of blades and the outer layer of blades, and a through hole structure is designed in the center of the cyclone body so that the fuel nozzle 1 penetrates through the cyclone body.

The turbine engine combustor 12 further comprises an air inlet 6, a gas outlet 7. The air inlet 6 is provided at one end of the flame tube 8, and the gas outlet 7 is provided at one end of the housing 10.

In this embodiment, the fuel nozzle 1 includes a solid structure 4' for performing relevant performance tests.

Comparative example

As shown in fig. 7, the comparative example is the same as example 2 except for the cyclone vane structure. The cyclone structure of the comparative example adopts single-layer blades, the thickness is 0.7mm, and the number of the blades is 12; as shown in fig. 7, the inner diameter of the outer layer blade 3 is 7.4mm, the outer diameter is 13.2mm, the chord length of the blade is 10.6mm, the aspect ratio is 0.26, an inclination angle of 45 degrees is formed with the bottom surface of the cyclone, under the engine running state, the gas flowing through the cyclone is divided into two parts, the gas flowing through the outer layer blade 3 of the cyclone forms a clockwise vortex, the gas flowing through the inner layer blade 2 of the cyclone forms a anticlockwise vortex, and after being mixed at the downstream position of the cyclone, the two parts of gas generate vortex, so that the axial speed of the gas at the downstream of the cyclone is reduced and is diffused towards the radial direction of the cyclone.

As shown in fig. 8 and 9, in the range of emphasis, the gas in example 2 forms a lower velocity, more regular shape velocity swirl region at the downstream position of the swirler, in which the gas is uniformly diffused in the combustion chamber, improving combustion efficiency, as compared with the comparative example, and on the other hand, the velocity distribution at the outlet position of the swirler in example 2 is also more uniform than that in the comparative example.

The fuel passes through a fuel line disposed within the spinner to the fuel nozzle 1 and enters the downstream region of the swirler within the barrel 8 via the fuel nozzle 1 in an atomized state and is mixed with air downstream of the swirler. In an embodiment, diffusion occurs in the high temperature region of the flame due to the reduced flow velocity of air along the axial direction of the swirler and the increased flow velocity along the radial direction of the swirler. The flame high temperature region in example 2 was more dispersed and distributed than the flame high temperature region concentrated at a position axially downstream of the cyclone in the comparative example. This improvement can be such that: 1) The area of the ignition area in the flame tube 8 is enlarged, the probability of successful ignition of the engine can be effectively improved, and meanwhile, the combustion chamber is not easy to flameout, so that the reliability of the engine under extreme working conditions is improved. The method comprises the steps of carrying out a first treatment on the surface of the 2) The post-combustion and cooling gas and the high-temperature gas are mixed more fully at the downstream position of the flame tube 8, so that the temperature distribution at the outlet position of the combustion chamber is more uniform while the combustion efficiency is improved.

The outlet temperature distribution coefficient OTDF is defined as the ratio of the difference between the outlet maximum temperature and the average temperature to the difference between the inlet and the outlet average temperature, and this parameter is used to indicate the uniformity of the outlet temperature distribution, and a lower parameter indicates a more uniform temperature distribution. As shown in fig. 10 and 11, according to the results of the numerical simulation, in the case of changing only the cyclone structure in the comparative example and example 2, the average flame temperature in the comparative example is 1106.25K, the highest temperature is 1796.26K, the lowest temperature is 729.13K, and the otdf is 1.05 under the same conditions; in example 2, the average flame temperature was 1128.71K, the highest temperature was 1568.33K, the lowest temperature was 912.91K, and the OTDF was 0.64. The higher average temperature of the outlet in example 2 means higher combustion efficiency and lower OTDF means more uniform temperature distribution.

The previous description of the embodiments is provided to facilitate a person of ordinary skill in the art in order to make and use the present invention. It will be apparent to those skilled in the art that various modifications can be readily made to these embodiments and the generic principles described herein may be applied to other embodiments without the use of the inventive faculty. Therefore, the present invention is not limited to the above-described embodiments, and those skilled in the art, based on the present disclosure, should make improvements and modifications without departing from the scope of the present invention.

Claims

1. A bi-directional swirler with double-layer blades, characterized in that the bi-directional swirler with double-layer blades comprises an inner-layer blade (2) and an outer-layer blade (3);

the inclination angles of the inner layer blades (2) and the outer layer blades (3) are opposite;

the inclined direction of the outer layer blades (3) forms an inclined angle with the bottom surface direction of the bidirectional cyclone;

the inclined direction of the inner layer blades (2) forms an inclined angle with the bottom surface direction of the bidirectional cyclone;

the inner layer blades (2) and the outer layer blades (3) are concentric and have opposite deflection directions;

an interlayer is arranged between the inner layer blade (2) and the outer layer blade (3).

2. The bi-layer bladed bi-directional cyclone of claim 1 wherein the bi-layer bladed bi-directional cyclone is of annular configuration.

3. The bi-directional swirler with double-layer vanes according to claim 1, wherein a through hole is provided in the center of the bi-directional swirler with double-layer vanes.

4. A bi-layer bladed bi-directional swirler as in claim 3, further comprising a fuel nozzle (1);

the fuel nozzle (1) is arranged at the top end of the bidirectional cyclone and is communicated with the bottom end of the bidirectional cyclone;

the fuel nozzle (1) passes through the through hole.

5. The bi-directional swirler with double-layer blades as claimed in claim 1, wherein the bi-directional swirler with double-layer blades is mounted on a flame tube (8) of a combustion chamber of a turbine engine in an embedded manner, and an outer ring of the bi-directional swirler with double-layer blades is lower than a wall surface of the flame tube (8).

6. The bi-directional swirler with double-layer vanes according to claim 1, characterized in that the inclination angle formed by the outer layer vanes (3) and the bottom surface direction of the bi-directional swirler is 30-60 degrees;

the inner layer blades (2) and the bottom surface direction of the bidirectional cyclone form an inclination angle of 120-150 degrees.

7. A bi-directional swirler with double-deck vanes according to claim 1, characterized in that the number of vanes of the outer-deck vanes (3) and the inner-deck vanes (2) is the same.

8. A bi-directional swirler with double-deck vanes according to claim 1, characterized in that the vane lengths of the outer-deck vanes (3) and the inner-deck vanes (2) are different.

9. The bi-directional swirler with double-layer vanes of claim 1, further comprising a swirler body;

the inner layer blades (2) and the outer layer blades (3) are fixedly connected with the cyclone body.

10. A turbine engine combustion chamber comprising the bi-directional swirler with double-layer vanes of any one of claims 1-9.