radial-radial-axial cyclone assembly

Abstract

A swirler assembly for a combustor includes a first air swirler having a first swirler vane assembly, a second air swirler adjacent the first air swirler and having a second swirler vane assembly, and a collar coupled to the first air swirler and the second air swirler. The collar includes a collar swirler having a plurality of vanes. The first swirler vane assembly is configured to produce a first radially rotating airflow, and the second swirler vane assembly is configured to produce a second radially rotating airflow. The plurality of vanes of the collar swirler are configured to produce a collar axial airflow to interact with and mix the first radially rotating airflow and the second radially rotating airflow.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to fuel-air mixer assemblies, and in particular to swirler assemblies for fuel-air mixer assemblies and fuel-air mixer assemblies. BACKGROUND

[0002] Engines, and in particular gas or combustion turbine engines, are rotary engines that extract energy from a flow of combustion gases passing over a plurality of turbine blades. Turbine engines have been used for land and marine locomotion as well as for power generation. Turbine engines are commonly used for aviation applications, such as aircraft, including helicopters and airplanes. In aircraft, turbine engines are used to propel the aircraft. In ground-based applications, turbine engines are commonly used for power generation.

[0003] Turbine engines include fuel-air mixer assemblies for mixing fuel and air in a combustion chamber of the turbine engine. The fuel-air mixer assemblies include an air swirler. The performance of the combustor in the combustion chamber plays an important role in the overall performance of the gas turbine engine.

[0004] Combustion performance is controlled to a large extent by the performance of the fuel-air mixer assembly, including the swirler, and involves many competing design objectives. For example, it is desirable to combust properly and completely, i.e., rich combustion, to reduce exhaust emissions while reducing the effects of flameout. Typically, the swirler itself is carefully designed to operate in a manner that mixes compressed air with injected fuel in a manner consistent with the desired combustor performance. BRIEF DESCRIPTION OF DRAWINGS

[0005] The foregoing and other features and advantages will be apparent from the following more particular description of various exemplary embodiments, as illustrated in the accompanying drawings in which like reference characters refer to the same, similar or analogous elements.

[0006] Figure 1 is a schematic illustration of a turbine engine in accordance with an embodiment of the present disclosure.

[0007] Figure 2 is a cross-sectional view of a portion of a combustor of a combustor assembly of a turbine engine in accordance with an embodiment of the present disclosure.

[0008] Figure 3 is a cross-sectional view of a fuel-air mixer assembly that can be used in a combustor (shown in Figure 2 ) in accordance with an embodiment of the present disclosure.

[0009] Figure 4 is a perspective cross-sectional view of a fuel-air mixer assembly (shown in Figure 3 ) in accordance with an embodiment of the present disclosure. DETAILED DESCRIPTION

[0010] Additional features, advantages, and embodiments of the present disclosure are set forth in or are apparent from the following detailed description, figures and claims. Moreover, it should be understood that the foregoing summary of the present disclosure, as well as the following detailed description, are exemplary only and are intended to provide further explanation of the disclosure as claimed.

[0011] Various embodiments of the present disclosure are discussed in detail below. While specific embodiments are discussed, this is simply for illustration. Those skilled in the relevant art will recognize that other components and configurations can be used without departing from the spirit and scope of this disclosure.

[0012] In the following description and claims, reference to the word "optional" or "optionally" means that the subsequently described event or circumstance can or can not occur, and that the description includes instances where the event occurs and instances where it does not.

[0013] Approximating language can be used herein to convey the approximate but not exact nature of one or more parameters embodying an aspect. Thus, a parameter specified in terms such as "about," "approximately,” or "substantially” is not limited to an exact value but can mean an approximate value that is within a reasonable range given the nature of the parameter. In at least some instances, the approximate language can correspond to the precision of an instrument used to measure the parameter. Ranges can be combined and / or interchanged. Such ranges are identified and include all the sub-ranges included therein unless context or language indicates otherwise. This disclosure also contemplates that where any parameter is implied to take only a single value, this is intended to encompass at least a range that includes that single value.

[0014] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to a centerline of the turbine engine or combustor. Further, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the turbine engine or fuel-air mixer assembly. Further, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends arcuately about the centerline of the turbine engine or fuel-air mixer assembly.

[0015] Embodiments of the present disclosure seek to provide a radial-radial-axial swirler by placing an additional swirler through a collar to improve flame stability in a rich burn combustor. The swirler within the collar, referred to herein as a "collar swirler," can be axial (or at a zero degree angle) or at a radially inward angle relative to the overall flow direction. In embodiments, the vanes of the collar swirler can be twisted and shaped to a desired vane exit air velocity profile.

[0016] The collar swirler can be implemented with minimal modification to a rich burn combustor (e.g., straight / counterflow) using conventional manufacturing techniques and / or additive techniques. The collar swirler airflow can be used as a handle to optimize the interaction of the airflow through the collar swirler with the primary swirler airflow. This allows control that can improve combustion stability and / or improve fuel-air mixing swirler flow aerodynamics.

[0017] Figure 1 is a schematic illustration of a turbine engine 10 according to embodiments of the present disclosure. The turbine engine 10 includes a fan assembly 12, a low pressure or booster compressor assembly 14, a high pressure compressor assembly 16, and a combustor assembly 18. The fan assembly 12, the booster compressor assembly 14, the high pressure compressor assembly 16, and the combustor assembly 18 are coupled in flow communication. The turbine engine 10 also includes a high pressure turbine assembly 20 coupled in flow communication with the combustor assembly 18 and a low pressure turbine assembly 22. The fan assembly 12 includes an array of fan blades 24 extending radially outward from a rotor disk 26. The low pressure turbine assembly 22 is coupled to the fan assembly 12 and the booster compressor assembly 14 by a first drive shaft 28, and the high pressure turbine assembly 20 is coupled to the high pressure compressor assembly 16 by a second drive shaft 30. The turbine engine 10 has an air intake 32 and an exhaust 34. The turbine engine 10 also includes a centerline (axis) 36 about which the fan assembly 12, the booster compressor assembly 14, the high pressure compressor assembly 16, the high pressure turbine assembly 20, and the low pressure turbine engine assembly 22 rotate.

[0018] In operation, air entering the turbine engine 10 through the air intake 32 is directed through the fan assembly 12 toward the booster compressor assembly 14. Compressed air is discharged from the booster compressor assembly 14 toward the high pressure compressor assembly 16. Highly compressed air is directed from the high pressure compressor assembly 16 toward the combustor assembly 18, mixed with fuel, and the mixture of air and fuel is combusted within the combustor assembly 18. The high temperature combustion gases produced by the combustor assembly 18 are directed toward the high pressure turbine assembly 20 and the low pressure turbine assembly 22. The combustion gases are subsequently exhausted from the turbine engine 10 via the exhaust 34.

[0019] Figure 2is a cross-sectional view of a portion of a combustor 38 of a combustor assembly 18 of a turbine engine 10 according to embodiments of the present disclosure. The combustor 38 defines a combustion chamber 40 in which highly compressed air is mixed with fuel and combusted. The combustor 38 includes an outer liner 42 and an inner liner 44. The outer liner 42 defines an outer boundary of the combustion chamber 40 and the inner liner 44 defines an inner boundary of the combustion chamber 40. An annular dome 46 is mounted upstream of the outer liner 42 and the inner liner 44 and defines an upstream end of the combustion chamber 40. One or more fuel injection systems 48 are positioned on the annular dome 46. In embodiments, each fuel injection system 48 includes a fuel nozzle assembly 50 and a fuel-air mixer assembly 52 coupled to the fuel nozzle assembly 50. The fuel-air mixer assembly 52 includes an air swirler 53 that will be described in further detail in the following paragraphs. The fuel-air mixer assembly 52 receives fuel from the fuel nozzle assembly 50, receives air from a high pressure compressor assembly 16 (as shown, for example, in FIG. 1) via a diffuser 54, and discharges a fuel-air mixture 56 into the combustion chamber 40 where the mixture is ignited using a fuel ignition assembly 60 and combusted. Figure 1

[0020] Currently, there are three basic types of air swirler. In one design, a row of primary orifice discharges a primary swirled air jet followed by a row of secondary radial swirler vanes in sequence, a jet-rad design. Fuel is injected in the center of the primary air jet, which first rotates the compressed air around the fuel, and the secondary radial vanes rotate additional air, typically counter-rotating to the primary swirled air. The primary jet of swirled air promotes a stable recirculation zone of combustion gases within the combustor dome and requires a minimal amount of purge air usage through the fuel injector.

[0021] In a known second design, a row of primary radial swirler vanes replaces the primary jet and operates with secondary radial swirler vanes, a rad-rad design, typically counter-rotating the air around the injected fuel. However, the rad-rad design requires a large amount of purge air from the fuel injector to create axial momentum in the fuel and air mixture to establish the desired flow structure in the combustor.

[0022] A third type of air swirler design exists in a dual annular combustor. The air swirler includes a primary axial swirler vane that cooperates with a secondary radial swirler vane, an ax-rad design. In this design, the primary vane directly receives pressurized air at dynamic pressure with axial momentum through the swirler. However, variations in the dynamic pressure of the compressed air around the circumference of each swirler and around the circumference of the dual annular combustor result in variations in the performance of the individual swirler and the resulting combustor performance.

[0023] ​Accordingly, to address the above-referenced shortcomings and other shortcomings of existing air swirler configurations, a different air swirler configuration is provided herein for enhancing combustor performance while reducing purge air requirements and also reducing manufacturing complexity and swirler cost.

[0024] Figure 3 is a cross-sectional view of a fuel-air mixer assembly that can be used in a combustor (shown in Figure 2 ) in accordance with embodiments of the present disclosure. Figure 4 is a perspective cross-sectional view of a fuel-air mixer assembly shown in Figure 3 FIG. 4. The fuel-air mixer assembly 52 includes an air swirler 102 and a torch cup portion 104 coupled to the air swirler 102. In embodiments, the air swirler 102 includes a first air swirler 106 (i.e., a primary air swirler) and a second air swirler 108 (i.e., a secondary air swirler) adjacent to the first air swirler 106. The first air swirler 106 includes a first swirler vane assembly 106A positioned therein. The second air swirler 108 includes a second swirler vane assembly 108A positioned therein. In embodiments, the first swirler vane assembly 106A is configured to generate a first radially rotating air flow 107 and the second swirler vane assembly 108A is configured to generate a second radially rotating air flow 109. In embodiments, the first swirler vane assembly 106A is configured to turn the first radially rotating air flow 107 in a counterclockwise direction and the second swirler vane assembly 108A is configured to turn the second radially rotating air flow 109 in a clockwise direction. In another embodiment, the first swirler vane assembly 106A is configured to turn the first radially rotating air flow 107 in a clockwise direction and the second swirler vane assembly 108A is configured to turn the second radially rotating air flow 109 in a counterclockwise direction. In embodiments, the first swirler vane assembly 106A of the first air swirler 106 and the second swirler vane assembly 108A of the second air swirler are configured to turn the respective first radially rotating air flow 107 and second radially rotating air flow 109 in a counter-rotating manner.

[0025] The fuel-air mixer assembly 52 also includes a ferrule 200 coupled to the air swirler 102. In embodiments, the ferrule 200 is coupled to the first air swirler 106 and the second air swirler 108. The ferrule 200 includes a fuel nozzle 202. The ferrule 200 includes a ferrule swirler 210. The ferrule swirler 210 has a body 204 with a plurality of vanes 206, as shown in Figure 3 and 4The annular swirler 210 is configured to provide a controlled annular axial air flow 201 that is mixed with the first radial rotational air flow 107 and the second radial rotational air flow 109 to produce an air flow vortex. In an embodiment, the plurality of vanes 206 can be formed by three sides. That is, the radially innermost surface of the swirler vane can remain open and the open side will be closed after the fuel nozzle is assembled. The outer surface of the fuel nozzle will be used to close the open side of the swirler vane. In an embodiment, the plurality of vanes 206 can be configured such that the annular axial air flow 201 is rotated in the same direction as the first radial rotational air flow 107. In another embodiment, the plurality of vanes 206 can be configured such that the annular axial air flow 201 is rotated in the same direction as the second radial rotational air flow 109. The first air swirler 106 and the second air swirler 108 form a swirler assembly 99 with the annular swirler 210.

[0026] The fuel nozzle 202 in the annulus 200 is configured to provide a fuel jet 203 for mixing with the annular axial air flow 201, the first radial rotational air flow 107, and the second radial rotational air flow 109. The fuel jet 203 is directed to interact with the air flow vortex produced by the annular axial air flow 201 and the first radial rotational air flow 107 and the second radial rotational air flow 109 to produce a controlled fuel-air mixture. In an embodiment, the fuel nozzle 202 in the annulus 200 is configured to provide a fuel jet 203 to mix with the air flow vortex produced by the interaction of the annular axial air flow 201 and the first radial rotational air flow 107 and the second radial rotational air flow 109. In an embodiment, the combination of the series of splits and swirl arrays between the annular swirler 210 and the primary swirler, the first air swirler 106, and the second air swirler 108, provides stable swirler flow dynamics through the interaction between the annular axial air flow and the first radial rotational air flow 107 and the second radial rotational air flow 109. In an embodiment, the plurality of vanes 206 can be twisted and shaped for the desired level of interaction of the annular axial air flow 201 and the first radial rotational air flow 107 and the second radial rotational air flow 109.

[0027] In an embodiment, the annular swirler 210 can be axial with respect to the overall flow direction, or angled radially inward with respect to the longitudinal axis AA, for example Figure 3embodiments, the angle of the collar axial airflow 201 relative to the longitudinal axis A-A can be in a range between zero degrees and sixty degrees. The angle can be selected by selecting an orientation of the plurality of vanes 206 of the collar swirler 210. In embodiments, the plurality of vanes 206 of the collar swirler 210 can be twisted and shaped to a desired exit velocity profile of the collar axial airflow 201. In this regard, the present embodiments have a“radial-radial-axial swirler” configuration, as there are two radial air swirlers corresponding to the first air swirler 106 and the second air swirler 108, and an axial swirler corresponding to the collar swirler 210. As used herein, the term“axial” includes any angle between zero degrees and sixty degrees relative to the longitudinal axis A-A. The term“axial” can also include a“tangential” component. That is, the axial airflow can or can not have a tangential component.

[0028] The collar swirler can be implemented with minimal modification on a rich burn combustor (straight flow / reverse flow). The collar swirler axial airflow can be used as a handle to optimize the interaction of the collar axial airflow 201 through the collar swirler 210 with the primary swirler airflow (i.e., the first radial rotational airflow 107 and the second radial rotational airflow 109). This allows for control of swirler flow aerodynamics, which can improve combustion stability and / or improve fuel-air mixing.

[0029] Further, the collar 200 is configured to“float” relative to the fuel nozzle 202. The term“float” is used herein to mean that the collar 200 can move radially up and down relative to the longitudinal axis AA in a BB direction that is generally perpendicular to the longitudinal axis AA, as shown in Figure 3

[0030] As a result, the above-described embodiments of the present disclosure provide stable swirler flow dynamics. The above-described configurations are applicable to additive build in any manufacturing method. With additive manufacturing, these configurations can be easily implemented, allowing for greater flexibility in combustor design. The above-described configurations also allow for meeting emissions requirements while improving durability of the combustor system and engine as a whole.

[0031] From the above discussion, it can be appreciated that a swirler assembly is provided in a combustor. The swirler assembly includes a first air swirler having a first swirler vane assembly, a second air swirler adjacent to the first air swirler and having a second swirler vane assembly, and a collar coupled to the first air swirler and the second air swirler. The collar includes a collar swirler having a plurality of vanes. The first swirler vane assembly is configured to produce a first radial rotational airflow. The second swirler vane assembly is configured to produce a second radial rotational airflow. The plurality of vanes of the collar swirler are configured to produce a collar axial rotational airflow to interact with and mix with the first radial rotational airflow and the second radial rotational airflow. ​

[0032] According to the scroll assembly of the above clause, the first scroll vane assembly is configured to turn the first radially rotating air flow in a counterclockwise direction, and the second scroll vane assembly is configured to turn the second radially rotating air flow in a clockwise direction or a counterclockwise direction.

[0033] According to the scroll assembly of any of the above clauses, the first scroll vane assembly is configured to turn the first radially rotating air flow in a clockwise direction, and the second scroll vane assembly is configured to turn the second radially rotating air flow in a counterclockwise direction or a clockwise direction.

[0034] According to the scroll assembly of any of the above clauses, wherein the plurality of vanes of the collar scroll are configured to cause the collar axial air flow to rotate in the same direction as the first radially rotating air flow or in the same direction as the second radially rotating air flow.

[0035] According to the scroll assembly of any of the above clauses, wherein the collar axial air flow forms an angle between zero degrees and sixty degrees relative to a longitudinal axis of the scroll assembly.

[0036] According to the scroll assembly of any of the above clauses, wherein the collar is radially movable in a direction that is substantially perpendicular to a longitudinal axis of the scroll assembly.

[0037] According to the scroll assembly of any of the above clauses, wherein the collar axial air flow interacting with the first radially rotating air flow and the second radially rotating air flow is capable of controlling scroll flow aerodynamics.

[0038] According to another aspect of the disclosure, a fuel-air mixer assembly for use in a combustor, the fuel-air mixer assembly comprising (A) a first air scroll having a first scroll vane assembly configured to produce a first radially rotating air flow, (B) a second air scroll adjacent to the first air scroll and having a second scroll vane assembly configured to produce a second radially rotating air flow, and (C) a collar coupled to the first air scroll and the second air scroll. The collar comprises (a) a fuel nozzle configured to produce a fuel jet, and (b) a collar scroll having a plurality of vanes, the plurality of vanes of the collar scroll configured to produce a collar axial air flow to interact with and mix the first radially rotating air flow and the second radially rotating air flow to produce an air flow vortex. The fuel jet is directed to interact with the air flow vortex to produce a controlled fuel-air mixture.

[0039] The fuel-air mixer assembly of any of the above clauses, wherein the first swirler vane assembly is configured to turn the first radially rotating air flow in a counterclockwise direction and the second swirler vane assembly is configured to turn the second radially rotating air flow in a clockwise direction or a counterclockwise direction.

[0040] The fuel-air mixer assembly of any of the above clauses, wherein the first swirler vane assembly is configured to turn the first radially rotating air flow in a clockwise direction and the second swirler vane assembly is configured to turn the second radially rotating air flow in a counterclockwise direction or a clockwise direction.

[0041] The fuel-air mixer assembly of any of the above clauses, wherein the plurality of vanes of the collar swirler are configured such that the collar axial air flow is rotated in the same direction as the first radially rotating air flow or the same direction as the second radially rotating air flow.

[0042] The fuel-air mixer assembly of any of the above clauses, wherein the collar axial air flow forms an angle between zero degrees and sixty degrees relative to a longitudinal axis of the fuel-air mixer assembly.

[0043] The fuel-air mixer assembly of any of the above clauses, wherein the collar is radially movable in a direction that is substantially perpendicular to a longitudinal axis of the fuel-air mixer assembly.

[0044] The fuel-air mixer assembly of any of the above clauses, wherein the collar axial air flow interacting with the first radially rotating air flow and the second radially rotating air flow is capable of controlling swirler flow aerodynamics.

[0045] According to another aspect of the disclosure, a turbine engine includes a combustor including a fuel-air mixer assembly and a fuel ignition assembly. The fuel-air mixer assembly includes (A) a first air swirler having a first swirler vane assembly configured to produce a first radially rotating air flow, (B) a second air swirler adjacent to the first air swirler and having a second swirler vane assembly configured to produce a second radially rotating air flow, and (C) a collar coupled to the first air swirler and the second air swirler. The collar includes (a) a fuel nozzle configured to produce a fuel jet, and (b) a collar swirler having a plurality of vanes configured to produce a collar axial air flow to interact with the first radially rotating air flow and the second radially rotating air flow and mix to produce an air flow vortex. The fuel jet is directed to interact with the air flow vortex to produce a controlled fuel-air mixture for ignition by the fuel ignition assembly.

[0046] The turbine engine of any of the above paragraphs, wherein the first swirler vane assembly is configured to turn the first radially rotating airflow in a counterclockwise direction, and wherein the second swirler vane assembly is configured to turn the second radially rotating airflow in a clockwise direction or a counterclockwise direction.

[0047] The turbine engine of any of the above paragraphs, wherein the first swirler vane assembly is configured to turn the first radially rotating airflow in a clockwise direction, and wherein the second swirler vane assembly is configured to turn the second radially rotating airflow in a counterclockwise direction or a clockwise direction.

[0048] The turbine engine of any of the above paragraphs, wherein the plurality of vanes of the collar swirler are configured such that the collar axial airflow is rotated in the same direction as the first radially rotating airflow or in the same direction as the second radially rotating airflow.

[0049] The turbine engine of any of the above paragraphs, wherein the collar axial airflow forms an angle between zero degrees and sixty degrees relative to a longitudinal axis of the fuel-air mixer assembly.

[0050] The turbine engine of any of the above paragraphs, wherein the collar is radially movable in a direction that is substantially perpendicular to the longitudinal axis of the fuel-air mixer assembly.

[0051] While the forgoing has been set forth in particular embodiments, it is not intended that the application be limited to the embodiments described. On the contrary, it is intended to cover all modifications and alternative methods and materials coming within the spirit and scope of the application. Further, the features of one embodiment can be used with other embodiments, even if not explicitly stated above.

Claims

1. A cyclone assembly for a burner, characterized in that, The cyclone assembly includes: A first air cyclone, the first air cyclone having a first cyclone impeller assembly, wherein the first cyclone impeller assembly is configured to generate a first radially rotating airflow; A second air cyclone, adjacent to the first air cyclone and having a second cyclone impeller assembly, wherein the second cyclone impeller assembly is configured to generate a second radially rotating airflow; and A ring, connected to a first air vortex and a second air vortex, the ring including a fuel nozzle and a ring vortex having a plurality of blades, wherein the plurality of blades of the ring vortex are configured to generate a ring axial airflow to interact with and mix with the first radially rotating airflow and the second radially rotating airflow, the plurality of blades being formed by three sides such that the radially innermost side of the plurality of blades is closed by the outer surface of the fuel nozzle, the fuel nozzle being configured to generate a fuel jet to mix with the ring axial airflow, the first radially rotating airflow and the second radially rotating airflow.

2. The hydrocyclone assembly according to claim 1, characterized in that, The first cyclone impeller assembly is configured to rotate the first radial rotating airflow in a counterclockwise direction, and the second cyclone impeller assembly is configured to rotate the second radial rotating airflow in a clockwise or counterclockwise direction.

3. The hydrocyclone assembly according to claim 1, characterized in that, The first cyclone impeller assembly is configured to rotate the first radial rotating airflow in a clockwise direction, and the second cyclone impeller assembly is configured to rotate the second radial rotating airflow in a counterclockwise or clockwise direction.

4. The hydrocyclone assembly according to claim 1, characterized in that, The plurality of blades of the swirling vortex are configured such that the axial airflow of the swirling vortex rotates in the same direction as the first radial rotating airflow or in the same direction as the second radial rotating airflow.

5. The hydrocyclone assembly according to claim 1, characterized in that, The axial airflow of the swirling ring forms an angle between zero and sixty degrees relative to the longitudinal axis of the swirling assembly.

6. The hydrocyclone assembly according to claim 1, characterized in that, The collar is capable of radial movement in a direction substantially perpendicular to the longitudinal axis of the hydrocyclone assembly.

7. The hydrocyclone assembly according to claim 1, characterized in that, The axial airflow of the vortex ring, which interacts with the first radial rotating airflow and the second radial rotating airflow, can control the aerodynamics of the cyclone flow.

8. A fuel-air mixer assembly for a burner, characterized in that, The fuel-air mixer assembly includes: (A) A first air cyclone, the first air cyclone having a first cyclone impeller assembly, the first cyclone impeller assembly being configured to generate a first radially rotating airflow; (B) A second air cyclone, the second air cyclone being adjacent to the first air cyclone and having a second cyclone impeller assembly, the second cyclone impeller assembly being configured to generate a second radially rotating airflow; and (C) a collar, the collar being connected to the first air cyclone separator and the second air cyclone separator, the collar comprising: (a) Fuel nozzle, and (b) A ring-shaped vortex having a plurality of blades configured to generate a ring-shaped axial airflow to interact with and mix with a first radially rotating airflow and a second radially rotating airflow to generate an airflow vortex, the plurality of blades being formed by three sides such that the innermost radial side of the plurality of blades is closed by the outer surface of the fuel nozzle, the fuel nozzle being configured to generate a fuel jet to mix with the ring-shaped axial airflow, the first radially rotating airflow, and the second radially rotating airflow. The fuel jet is guided to interact with the airflow vortex, thereby producing a controlled fuel-air mixture.

9. The fuel-air mixer assembly according to claim 8, characterized in that, The first cyclone impeller assembly is configured to rotate the first radial rotating airflow in a counterclockwise direction, and the second cyclone impeller assembly is configured to rotate the second radial rotating airflow in a clockwise or counterclockwise direction.

10. The fuel-air mixer assembly according to claim 8, characterized in that, The first cyclone impeller assembly is configured to rotate the first radial rotating airflow in a clockwise direction, and the second cyclone impeller assembly is configured to rotate the second radial rotating airflow in a counterclockwise or clockwise direction.

11. The fuel-air mixer assembly according to claim 8, characterized in that, The plurality of blades of the swirling vortex are configured such that the axial airflow of the swirling vortex rotates in the same direction as the first radial rotating airflow or in the same direction as the second radial rotating airflow.

12. The fuel-air mixer assembly according to claim 8, characterized in that, The axial airflow of the ring is formed at an angle between zero and sixty degrees relative to the longitudinal axis of the fuel-air mixer assembly.

13. The fuel-air mixer assembly according to claim 8, characterized in that, The collar is capable of radial movement in a direction substantially perpendicular to the longitudinal axis of the fuel-air mixer assembly.

14. The fuel-air mixer assembly according to claim 8, characterized in that, The axial airflow of the vortex ring, which interacts with the first radial rotating airflow and the second radial rotating airflow, can control the aerodynamics of the cyclone flow.

15. A turbine engine, characterized in that, include: A burner, comprising a fuel-air mixer assembly and a fuel ignition assembly, the fuel-air mixer assembly comprising: (A) A first air cyclone, the first air cyclone having a first cyclone impeller assembly, the first cyclone impeller assembly being configured to generate a first radially rotating airflow; (B) A second air cyclone, the second air cyclone being adjacent to the first air cyclone and having a second cyclone impeller assembly, the second cyclone impeller assembly being configured to generate a second radially rotating airflow; and (C) a collar, the collar being connected to the first air cyclone separator and the second air cyclone separator, the collar comprising: (a) Fuel nozzle, and (b) A ring-shaped vortex having a plurality of blades configured to generate a ring-shaped axial airflow to interact with and mix with a first radially rotating airflow and a second radially rotating airflow to generate an airflow vortex, the plurality of blades being formed by three sides such that the innermost radial side of the plurality of blades is closed by the outer surface of the fuel nozzle, the fuel nozzle being configured to generate a fuel jet to mix with the ring-shaped axial airflow, the first radially rotating airflow, and the second radially rotating airflow. The fuel jet is guided to interact with the airflow vortex to generate a controlled fuel-air mixture for ignition by the fuel ignition assembly.

16. The turbine engine according to claim 15, characterized in that, The first cyclone impeller assembly is configured to rotate the first radial rotating airflow in a counterclockwise direction, and the second cyclone impeller assembly is configured to rotate the second radial rotating airflow in a clockwise or counterclockwise direction.

17. The turbine engine according to claim 15, characterized in that, The first cyclone impeller assembly is configured to rotate the first radial rotating airflow in a clockwise direction, and the second cyclone impeller assembly is configured to rotate the second radial rotating airflow in a counterclockwise or clockwise direction.

18. The turbine engine according to claim 15, characterized in that, The plurality of blades of the swirling vortex are configured such that the axial airflow of the swirling vortex rotates in the same direction as the first radial rotating airflow or in the same direction as the second radial rotating airflow.

19. The turbine engine according to claim 15, characterized in that, The axial airflow of the ring is formed at an angle between zero and sixty degrees relative to the longitudinal axis of the fuel-air mixer assembly.

20. The turbine engine according to claim 15, characterized in that, The collar is capable of radial movement in a direction substantially perpendicular to the longitudinal axis of the fuel-air mixer assembly.

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