Dome with integrated trumpet swirler

Abstract

A swirler assembly includes a swirler having a primary swirler and a secondary swirler, a bell mouth connecting the secondary swirler, and a dome disposed radially outward of the bell mouth. A trumpet-shaped oxidant flow passage is defined by a trumpet-shaped outer surface and an inner surface of the dome. The trumpet-shaped oxidant flow passage includes a swirl-inducing member therein that induces a swirl flow of the oxidant passing through the trumpet-shaped oxidant flow passage into a combustion chamber.

Description

Technical Field

[0001] The present disclosure relates to a swirler assembly for a combustor of a gas turbine engine having a dome with an integrated trumpet-shaped swirler. Background Art

[0002] Some conventional gas turbine engines are known to include rich-burn combustors, which typically use a swirler integrated with a fuel nozzle to deliver a swirling fuel-air mixture to the combustor. A radial-radial swirler is an example of such a swirler and includes a primary radial swirler, a secondary radial swirler, a bellmouth connected to the secondary swirler, and a dome connected radially outward of the bellmouth. The primary swirler includes a primary swirler venturi, wherein a primary swirling airflow from the primary swirler mixes with fuel injected into the primary swirler venturi through the fuel nozzle to generate a swirling primary fuel-air mixture. The secondary swirler provides a secondary swirling airflow downstream of the primary swirler, wherein the secondary swirling airflow mixes with the swirling primary fuel-air mixture to generate a swirling fuel-air mixture. The swirling fuel-air mixture then flows downstream to a bellmouth connected to the downstream end of the secondary swirler. The bell mouth typically has a tapered outlet that disperses the swirling secondary fuel-air mixture into the combustion chamber where it is ignited and combusted to produce combustion product gases. Some rich-burn combustors also include a bell purge, where cooling air is supplied through axial holes or radially inward holes between the bell mouth and the dome to provide impingement cooling to the back of the bell mouth. BRIEF DESCRIPTION OF THE DRAWINGS

[0003] Features and advantages of the present disclosure will become apparent from the following description of various exemplary embodiments, as illustrated in the accompanying drawings, in which like reference numbers generally indicate identical, functionally similar, and / or structurally similar elements.

[0004] Figure 1 is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine according to aspects of the present disclosure.

[0005] Figure 2 is a partial cross-sectional side view of an exemplary combustion section according to aspects of the present disclosure.

[0006] Figure 3 is a partial cross-sectional side view of an exemplary swirler assembly according to aspects of the present disclosure.

[0007] Figure 4 Depicted in accordance with aspects of the present disclosure Figure 3 Detail view 100 of an exemplary trumpet-shaped oxidant flow channel and cyclone arrangement.

[0008] Figure 5 Another aspect of the present disclosure is described in Figure 3 Another exemplary trumpet-shaped oxidant flow channel and cyclone arrangement is shown in detail view 100 of FIG.

[0009] Figure 6 According to another aspect of the present disclosure, Figure 3 Detail view 100 of FIG. 1 shows another exemplary trumpet-shaped oxidant flow channel and cyclone arrangement.

[0010] Figure 7 is Figure 4 FIG. 1 is a partial cross-sectional view through the trumpet-shaped oxidant flow passage 108 including the swirl inducing member 106 , taken at plane 7 - 7 of FIG.

[0011] Figure 8 is a rear perspective view of an exemplary swirler assembly with the dome removed according to aspects of the present disclosure.

[0012] Figure 9 is Figure 5 A partial cross-sectional view through the trumpet-shaped oxidant flow passage 108 including the swirl inducing member 106, taken at plane 9-9 of FIG.

[0013] Figure 10 is Figure 6 A partial cross-sectional view through the trumpet-shaped oxidant flow passage 108 including the swirl inducing member 106 is shown at cut line 10 - 10 .

[0014] Figure 11 According to another aspect of the present disclosure, Figure 3 Detail view 100 of FIG. 1 shows another exemplary trumpet-shaped oxidant flow channel and cyclone arrangement.

[0015] Figure 12 is Figure 11 FIG. 1 is a partial cross-sectional view through the trumpet-shaped oxidant flow passage 108 including the swirl inducing member 106 , taken at plane 12 - 12 of FIG.

[0016] Figure 13 Another aspect of the present disclosure is described in Figure 3 Detail view 100 of FIG. 1 shows another exemplary trumpet-shaped oxidant flow channel and cyclone arrangement.

[0017] Figure 14 is Figure 2 Partial cross-sectional rear and front views taken at plane 14-14 shown in FIG.

[0018] Figure 15 is a flow chart of an exemplary method of operating a combustor according to aspects of the present disclosure. DETAILED DESCRIPTION

[0019] Features, advantages and embodiments of the present disclosure are set forth or apparent by considering the following detailed description, drawings and claims. In addition, it should be understood that the following detailed description is exemplary and is intended to provide further explanation without limiting the scope of the present disclosure as claimed.

[0020] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

[0021] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of each component.

[0022] The terms "upstream" and "downstream" refer to relative directions of fluid flow in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing.

[0023] In a rich-burn combustor including a radial-radial swirler, air is supplied from the combustor's pressure chamber to a swirler assembly, where swirl vanes in both the primary and secondary swirlers induce swirl in the air. Fuel is injected into the swirling air in the primary swirler, and the swirling primary fuel-air mixture then flows to the secondary swirler, where it further mixes with swirling air from the secondary swirler. The secondary swirling fuel-air mixture then flows downstream to a flared cone, where it expands and disperses into the combustion chamber before being ignited and burned to produce combustion product gases. The flared mouth may be surrounded by a dome or deflector wall, and a flared purge cavity may be formed between the dome and the flared mouth. The flared purge cavity may include axial holes or radially inward holes to allow impingement cooling air to pass between the flared outer surface and the dome, thereby providing impingement cooling for the flared outer tip. However, the trumpet-shaped purge impingement cooling flow cannot provide sufficient turbulence, mixing or flame strain at the flame front near the trumpet outlet and the inner surface of the dome, resulting in a localized higher hot spot area and increased NOx emissions.

[0024] The present disclosure solves the above-mentioned problems by inducing a swirl flow of the oxidant between the bell mouth and the dome. More specifically, the oxidant flow channel provided between the bell-shaped outer surface and the dome inner surface includes a swirl inducing member, such as a plurality of swirl vanes arranged around the circumference of the bell mouth. The swirl vanes induce swirl in the oxidant flow passing through the oxidant flow channel, so that a swirling trumpet-shaped oxidant flow exits the channel. The swirling trumpet-shaped oxidant flow provides higher turbulence and better mixing at the flame front near the trumpet outlet, thereby reducing NOx emissions. The swirling trumpet-shaped oxidant flow is also closer to the dome plane to better cool the dome surface.

[0025] Referring now to the accompanying drawings, Figure 1 is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine 10 (referred to herein as "engine 10") in which various embodiments of the present disclosure may be incorporated. Although further described below with reference to a ducted turbofan engine, the present disclosure is also generally applicable to turbomachinery, including turbojets, turboprops, and turboshaft gas turbine engines, including marine and industrial turbine engines and auxiliary power units. Furthermore, the present disclosure is not limited to, for example, Figure 1 The ducted fan type turbine engine shown in FIG. 1 may be implemented in a unducted fan (UDF) type turbine engine. Figure 1 As shown, for reference, engine 10 has a longitudinal or axial centerline axis 12 extending therethrough from an upstream end 98 to a downstream end 99. Generally, engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of fan assembly 14.

[0026] The core engine 16 may generally include a casing 18 defining an annular inlet 20. The casing 18 surrounds or at least partially forms, in serial flow relationship: a compressor section having a supercharger or low pressure (LP) compressor 22, a high pressure (HP) compressor 24; a combustion section 26; a turbine section including a high pressure (HP) turbine 28, a low pressure (LP) turbine 30; and an ejection exhaust nozzle section 32. A high pressure (HP) rotor shaft 34 drivingly connects the HP turbine 28 to the HP compressor 24. A low pressure (LP) rotor shaft 36 drivingly connects the LP turbine 30 to the LP compressor 22. The LP rotor shaft 36 may also be connected to a fan shaft 38 of the fan assembly 14. In certain embodiments, as Figure 1 As shown, LP rotor shaft 36 may be connected to fan shaft 38 via reduction gear 40, such as in an indirect drive or gear drive configuration. In other embodiments, although not shown, engine 10 may also include an intermediate pressure (IP) compressor and a turbine rotatable with the IP shaft.

[0027] like Figure 1As shown, the fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from the fan shaft 38. An annular fan casing or nacelle 44 circumferentially surrounds the fan assembly 14 and / or at least a portion of the core engine 16. In one embodiment, the nacelle 44 may be supported relative to the core engine 16 by a plurality of circumferentially spaced outlet guide vanes or struts 46. In addition, at least a portion of the nacelle 44 may extend over an outer portion of the core engine 16 to define a bypass airflow passage 48 therebetween.

[0028] Figure 2 An exemplary combustion section 26 according to the present disclosure is depicted. Figure 2 In FIG, the combustion section 26 includes a swirler assembly 50, a fuel nozzle assembly 52, a dome assembly 54, and an annular combustion liner 56 within an outer casing 64. The annular combustion liner 56 includes an outer liner 58 and an inner liner 60 forming a combustion chamber 62 therebetween. A pressure chamber 66 is formed within the dome assembly 54. Return to Reference Figure 1 In operation, air 73 enters the nacelle 44, and a portion of the air 73 enters the compressor section as compressor inlet air flow 80, where it is compressed. Another portion of the air 73 enters the bypass air flow passage 48, thereby providing a bypass air flow 78. Figure 2 , compressed air 82 from the compressor section (22 / 24) enters the combustion section 26 via a diffuser (not shown). A portion of the compressed air 82(a) enters the dome assembly 54 into the plenum 66, while another portion of the compressed air 82(b) enters the outer flow passage 68 between the annular combustion liner 56 and the outer casing 64. As will be described below, the portion of the compressed air 82(a) in the plenum 66 passes through the swirler assembly 50, thereby mixing with the fuel injected by the fuel nozzle assembly 52 and igniting to generate combustion product gases 86.

[0029] Figure 3 A partial cross-sectional view of the front portion of the cyclone assembly 50 is depicted. The cyclone assembly 50 is generally symmetrical about a cyclone assembly centerline 69 extending in the longitudinal direction L and generally perpendicular to the radial direction R. The cyclone assembly 50 includes a plurality of cyclone assemblies 50 connected to the cyclone assembly 50 via a support wall 94 (see FIG. Figure 2) and dome 92 are appropriately connected to the dome assembly 54. The swirler assembly 50 includes a swirler 51 and a fuel nozzle 76 disposed within the swirler 51. The swirler 51 includes a primary swirler 70 having a primary swirler venturi 96, a secondary swirler 72, and a swirler collar plate 74. The primary swirler 70 includes a plurality of primary swirler swirl vanes 88 circumferentially arranged in a row such that each primary swirler swirl vane 88 extends radially inward. The primary swirler 70 also includes a primary swirler venturi 96 that extends concentrically about the swirler assembly centerline 69 in the longitudinal direction L. The primary swirler 70 is configured to swirl a corresponding portion of the compressed air 82(a) from the pressure chamber 66 radially inward (i.e., clockwise about the swirler assembly centerline 69 or counterclockwise about the swirler assembly centerline 69) within the primary swirler 70 in a primary swirl direction.

[0030] The secondary swirler 72 similarly includes a row of secondary swirler swirl vanes 90 arranged circumferentially, such that each secondary swirler swirl vane 90 extends radially inward. The secondary swirler 72 is configured to swirl another corresponding portion of the compressed air 82(a) from the pressure chamber 66 radially inward. The swirler 51 also includes a bellmouth 75 connected to a downstream end 77 of the secondary swirler 72.

[0031] Fuel nozzle 76 ( Figure 2 ) is disposed within the swirler collar plate 74 of the swirler 51. The fuel nozzle 76 injects fuel 84 into the primary swirler venturi 96, where the fuel 84 mixes with the portion of compressed air 82(a) from the primary swirler 70 in the primary swirler venturi mixing region 102. The fuel and air mixture in the primary swirler venturi 96 is further mixed with the portion of compressed air 82(a) from the secondary swirler 72 downstream of the tapered opening 110 of the bellmouth 75. The fuel and air mixture from the bellmouth 75 is then dispersed at a diverging angle from the bellmouth 75 into the combustion chamber 62, where the fuel and air mixture is ignited and combusted to generate combustion product gases 86 within the primary combustion zone 87 of the combustion chamber 62.

[0032] As described above, the swirler assembly 50 includes the dome 92. As will be described in more detail below, a trumpet-shaped oxidant flow passage 108 is defined between the bellmouth and the dome 92, and a swirl inducing member 106 is disposed within the trumpet-shaped oxidant flow passage 108. In operation, the portion of the compressed air 82(a) within the pressure chamber 66 flows through the trumpet-shaped oxidant flow passage 108 as a cooling airflow, wherein the swirl inducing member 106 induces swirl in the cooling airflow. The swirling cooling airflow exiting the trumpet-shaped oxidant flow passage 108 and entering the combustion chamber 62 remains closer to the plane of the dome and creates high turbulence in the primary combustion zone 87 of the combustion chamber 62, thereby providing better mixing of the cooling air with the fuel-air mixture exiting the bellmouth 75. This swirling air creates high flame strain in the primary zone of the combustor, reducing the area of ​​peak temperature closer to the flame, thereby reducing NOx emissions. Reference will now be made to Figure 3 Detailed view 100 in FIG. 1 details various arrangements of swirl inducing members 106 within the trumpet-shaped oxidant flow passage 108 .

[0033] Figure 4 Depicted in accordance with aspects of the present disclosure Figure 3 An exemplary trumpet-shaped oxidant flow channel and cyclone arrangement is shown in detail view 100 of FIG. Figure 4 9, the flared oxidant flow passage and swirler arrangement can be seen, including the flared mouth 75, the dome 92, the flared oxidant flow passage 108, and the swirl inducing member 106. The flared mouth 75 includes a flared axial wall 112 and a flared conical wall 114. The flared axial wall 112 is an annular wall that extends in a longitudinal direction relative to the swirler assembly centerline 69 and extends in a circumferential direction 104 around the swirler assembly centerline 69. The flared conical wall 114 is also an annular wall that connects to the flared axial wall 112 at a downstream end 120 of the flared axial wall 112. The flared conical wall 114 extends circumferentially around the swirler assembly centerline 69 and extends radially outward and longitudinally downstream from the downstream end 120 of the flared axial wall 112. The flared conical wall 114 may have an angle 122 relative to the swirler assembly centerline 69, for example, of 45 degrees, or may be in the range of 30 to 60 degrees. Of course, the opening angle 122 is not limited to the above range, and other opening angles may be implemented instead. The flared axial wall 112 includes a flared axial wall outer surface 116, and the flared conical wall 114 includes a flared conical wall outer surface 118. The flared axial wall outer surface 116 and the flared conical wall outer surface 118 may be collectively referred to as a flared outer surface 124.

[0034] Dome 92 can be seen to include a dome axial wall 126, a dome conical wall 128, and a dome radial wall 130. Dome axial wall 126 is an annular wall that extends longitudinally relative to swirler assembly centerline 69 and in a circumferential direction 104 about swirler assembly centerline 69. Dome conical wall 128 is also an annular wall that extends circumferentially about swirler assembly centerline 69. Dome conical wall 128 is connected to dome axial wall 126 at a downstream end 132 of dome axial wall 126 and extends radially outward and longitudinally downstream from the downstream end 132 of dome axial wall 126. Dome radial wall 130 is connected to dome conical wall 128 at a downstream end 134 of dome conical wall 128. Dome radial wall 130 generally extends radially outward from the downstream end 134 and generally extends circumferentially about swirler assembly centerline 69. Although not depicted, the dome radial wall 130 may also extend radially outward and downstream at an angle from the dome conical wall downstream end 134 .

[0035] Dome axial wall 126 includes dome axial wall inner surface 136, and dome conical wall 128 includes dome conical wall inner surface 138. Dome axial wall inner surface 136 and dome conical wall inner surface 138 together form dome inner surface 140. Dome inner surface 140 and flared outer surface 124 are spaced apart from each other via swirl inducing member 106 to form flared oxidant flow passage 108 therebetween.

[0036] exist Figure 4 , the swirl inducing member 106 is shown as being disposed between the dome-shaped conical wall inner surface 138 and the flared conical wall outer surface 118. However, as Figure 5 As seen in FIG. 1 , the swirl inducing member 106 may be disposed between the dome axial wall inner surface 136 and the flared axial wall outer surface 116. Figure 5 In the illustrated arrangement, the flared conical wall 114 may optionally include flared conical wall corrugations 182. The flared conical wall corrugations 182 may help improve the turbulence of the oxidant flow through the flared oxidant flow channel 108. Furthermore, similar to the flared conical wall 114, the domed conical wall 128 may optionally include domed conical wall corrugations 184. The domed conical wall corrugations 184 may also help improve the turbulence of the oxidant flow through the flared oxidant flow channel 108. Of course, although not shown in the figures, corrugations similar to the flared conical wall corrugations 182 may be provided to extend radially outward from the flared axial wall 112 into the flared oxidant flow channel 108, and the corrugations may be included as part of the swirl inducing member 106. Similarly, corrugations similar to the domed conical wall corrugations 184 may be provided to extend radially inward from the domed axial wall 126 into the flared oxidant flow passage 108 and included as part of the swirl inducing member 106 .

[0037] Or, as Figure 6 As shown, the swirl inducing member 106 may be disposed between the domed axial wall inner surface 136 and the flared axial wall outer surface 116 and extend downstream within the flared oxidant flow passage 108 so as to also be disposed between the domed conical wall inner surface 138 and the flared conical wall outer surface 118. This arrangement may also include flared conical wall corrugations 182 and 184, as well as corrugations (not shown) on the flared axial wall 112 and / or the domed axial wall 126.

[0038] Now about Figures 7 to 10 Various arrangements of swirl inducing members 106 are described. Figure 7 is Figure 4 A partial cross-sectional view of the flared oxidant flow passage 108 including the swirl inducing member 106 taken at plane 7-7 of FIG. Figure 7 In the arrangement of , the swirl inducing member 106 is implemented as a plurality of swirl vanes 142 that are circumferentially spaced apart from one another around the circumference of the flared conical wall 114 such that the flared oxidant flow passage 108 is defined between consecutive pairs of the plurality of swirl vanes 142. As is well known in the art, a swirl vane may generally be a relatively thin wall extending between two surfaces and arranged at an angle or having a specific shape to impart a change in direction to the air flow passing over the surface of the swirl vane. Thus, in Figure 4 In another aspect, the swirl vanes 142 may be such thin walls that extend between the flared cone wall outer surface 118 and the domed cone wall inner surface 138 .

[0039] It can be seen that the swirl vanes 142 extend from the upstream end 119 of the trumpet-shaped conical wall 118 (see also Figure 4 ) extends to the downstream end 121 of the flared conical wall 118 (see also Figure 4 ). It is also seen that the swirl vanes 142 are along the swirler assembly centerline 69 ( Figure 4 ) is arranged at a swirl vane angle 144 relative to the longitudinal direction. The swirl vane angle 144 can be set to exit the trumpet-shaped oxidant flow channel 108 and enter the combustion chamber 62 ( Figure 3 ) provides the desired swirl number for the airflow. As will be described in more detail below, the swirl vane angle 144 does not have to be the same for all swirl vanes 142, but can be different around the circumference of the bell mouth 75. Figure 7 In this aspect, the swirl vanes 142 are also generally shown as axial vanes (i.e., straight along their lengths), but as seen in alternative aspects, may alternatively be configured as curved swirl vanes 146. The curved swirl vanes 146 may have a continuous curvature along their lengths, or they may have a sharper curvature toward the outlet end 150 of the curved swirl vane 146 than at the inlet end 148 of the curved swirl vane 146.

[0040] Figure 8 is a rear perspective view of an exemplary cyclone 51, wherein the dome 92 ( Figure 4 ) is removed to illustrate an example of a plurality of curved swirl vanes 146 arranged around the circumference of the flared conical wall 114. As yet another example, in Figure 7 , the swirl vane 142 may alternatively be a curved swirl vane 146 having a curved swirl vane outlet end 150 and may include an axial portion at the inlet end 148, wherein the curved swirl vane outlet end begins mid-length of the curved swirl vane 146 such that the outlet end 150 is curved to impart a higher swirl number in the air flow exiting the flared oxidant flow passage 108.

[0041] Figure 9 Depicted in Figure 5 A partial cross-sectional view of the swirl inducing member 106 and the trumpet-shaped oxidant flow passage 108 taken at plane 9-9 in FIG. Figure 5 , the swirl inducing member 106 is shown disposed between the flared axial wall outer surface 116 and the domed axial wall inner surface 136. Figure 9 In, similar to Figure 7 , a plurality of swirl vanes 152 can be seen to implement the swirl inducing member 106. The swirl vanes 152 can be similar to the swirl vanes 142 ( Figure 7 ), as they may be axial and arranged at a swirl angle 154, or may be implemented as curved swirl vanes 156 that induce a higher swirl number at the outlet end 160 of the swirl vane 152 than at the inlet end 158 of the swirl vane 152.

[0042] Figure 10 Depicted in Figure 6 A partial cross-sectional view of the swirl inducing member 106 taken at the cutting line 10-10 in FIG. Figure 6 , the swirl inducing member 106 is shown disposed between the flared outer surface 124 and the domed inner surface 140. Figure 10 In, similar to Figure 7 and 9 , a plurality of swirl vanes 162 can be seen to implement the swirl inducing member 106. The swirl vanes 162 can be similar to the swirl vanes 142 ( Figure 7 ) and swirl vane 152 ( Figure 9 ), as they may be axial and arranged at a swirl angle 164, or may be implemented as curved swirl vanes 166 that induce a higher swirl number at the outlet end 170 of the swirl vane 162 than at the inlet end 168 of the swirl vane 162. Figure 10As another alternative shown in , the swirl vanes 162 or curved swirl vanes 166 may include an axial inlet portion 172 that may be generally axially aligned with the swirler assembly centerline 69 rather than disposed at the swirl angle 164 .

[0043] exist Figures 7 to 10 In the embodiment, the swirl inducing member 106 is described as being implemented by a plurality of swirl vanes. However, the swirl inducing member 106 is not limited to swirl vanes, and Figure 11 and 12 Another embodiment of a swirl inducing member 106 is depicted. Figure 11 and 12 In FIG. 1 , the swirl inducing member 106 is implemented as an annular ring 174 having a plurality of apertures 176 therethrough. Each of the plurality of apertures 176 may be arranged at an angle 180 relative to the circumferential direction such that an outlet end 178 of each of the apertures 176 provides a tangential flow of the oxidant therethrough into the combustion chamber 62. Figure 7 ) of the swirl vane angle 144, the angle 180 can be set to enter the combustion chamber 62 ( Figure 2 ) to provide a desired swirl number in the oxidant flow entering the combustion chamber 62. In addition, the number of orifices 176, the size of the orifices 176, and the circumferential spacing of the orifices 176 can be set to provide a desired amount of oxidant flow therethrough and a desired swirl number for the oxidant flow entering the combustion chamber 62.

[0044] Figure 13 Another aspect of the present disclosure is described in Figure 3 Another exemplary trumpet-shaped oxidant flow channel and cyclone arrangement is shown in detail view 100 of FIG. Figure 13 , an intermediate wall 186 is included within the trumpet-shaped oxidant flow channel 108 to divide the trumpet-shaped oxidant flow channel 108 into a trumpet-side oxidant flow channel 192 and a dome-side oxidant flow channel 194. The intermediate wall 186 is defined by an intermediate axial wall 188 and an intermediate conical wall 190. The intermediate axial wall 188 can be approximately evenly spaced between the dome axial wall 126 and the trumpet axial wall 112, and the intermediate conical wall 190 can also be approximately evenly spaced between the dome conical wall 128 and the trumpet conical wall 114. When this arrangement is implemented, the trumpet-side oxidant flow channel 192 and the dome-side oxidant flow channel 194 can generally have approximately the same height throughout the length of the channel. However, the intermediate wall 186 can be closer to the dome 92 ( Figure 2 ) is offset so that the height of the bell-mouth side oxidant flow channel 192 is greater than the height of the dome side oxidant flow channel 194. Alternatively, the intermediate wall 186 may be closer to the bell mouth 75 ( Figure 2) such that the flared-side oxidant flow channel 192 has a smaller height than the dome-side oxidant flow channel 194. Furthermore, the intermediate tapered walls 190 may not be evenly spaced between the flared-tapered wall 114 and the dome-side tapered wall 128, but may be unevenly arranged to form the intermediate tapered wall 248. When this arrangement is implemented, the dome-side oxidant flow channel outlet end 250 of the dome-side oxidant flow channel 194 may form a converging outlet, while the flared-side oxidant flow channel outlet end 252 of the flared-side oxidant flow channel 192 may form a diverging outlet.

[0045] exist Figure 13 In the embodiment, for the two oxidant flow passages, a bell-mouth side swirl inducing member 198 is provided in the bell-mouth side oxidant flow passage 192, and a dome side swirl inducing member 200 is provided in the dome side oxidant flow passage 194. Both the bell-mouth side swirl inducing member 198 and the dome side swirl inducing member 200 can be implemented as described above. Figures 4 to 12 That is, as an example, both the bell-side swirl inducing member 198 and the dome-side swirl inducing member 200 may be configured with Figure 4 The swirl inducing member 106 is the same as that of the embodiment of the present invention and includes Figure 7 However, the dome-side swirl inducing member 200 may extend between the dome axial wall downstream end 132 and the intermediate axial wall downstream end 196 at the curved swirl vane inlet end 148. Therefore, the foregoing description of those embodiments will not be repeated herein.

[0046] However, in Figure 13 In terms of the bell-side swirl inducing member 198 and the dome-side swirl inducing member 200, the bell-side swirl inducing member 198 may also be different from each other. As an example, the bell-side swirl inducing member 198 may implement the swirl inducing member 106. Figure 4 aspects, and includes Figure 7 The swirl vane 142 of the dome side swirl inducing member 200 can implement the swirl inducing member 106 Figure 5 aspects, and includes Figure 9 swirl vanes 152. In addition, the bell-side swirl inducing member 198 and the dome-side swirl inducing member 200 can be arranged to swirl the oxidant flow therethrough in opposite swirl directions. For example, the bell-side swirl inducing member 198 can be arranged to provide a clockwise swirl of the oxidant about the swirler assembly centerline 69, while the dome-side swirl inducing member 200 can be arranged to provide a clockwise swirl of the oxidant therethrough about the swirler assembly centerline 69 ( Figure 2The bell-side swirl inducing member 198 may also be arranged to provide a bell-side swirl 244 of the oxidant in the same direction as the swirling secondary fuel-oxidant mixture 232, or in an opposite direction to the swirling secondary fuel-oxidant mixture 232.

[0047] Figure 14 is Figure 2 A partial cross-sectional rear and front view taken at plane 14-14 is shown in FIG. Figure 14 , a description will be given of an embodiment in which a combination of the swirl vanes 142 and the curved swirl vanes 146 is alternately arranged around the circumference of the bell mouth 75. Figure 14 , radial reference line 210 is seen extending in radial direction R through cyclone assembly centerline 69. A first sector start reference line 214 is seen angularly offset from radial reference line 210 in a clockwise direction by an angle 212 (e.g., forty-five degrees). A first sector 202 is defined about the circumference of bellmouth 75 in a counterclockwise direction about cyclone assembly centerline 69 between first sector start reference line 214 and first sector end reference line 216. First sector 202 is seen on the outer liner side of bellmouth 75 (i.e., closest to outer liner 58). A first sector angle 222 of first sector 202 may be, for example, ninety degrees. A second sector 204 is defined in a counterclockwise direction from first sector end reference line 216 to second sector end reference line 218, and a second sector angle 224 of second sector 204 may be, for example, ninety degrees. The third sector 206 is defined as extending counterclockwise from the second sector end reference line 218 to the third sector end reference line 220, and the third sector angle 226 may also be, for example, ninety degrees. It can be seen that the third sector 206 is disposed on the liner side of the flare 75 (i.e., closest to the liner 60). The fourth sector 208 is defined as extending counterclockwise from the third sector end reference line 220 to the first sector start reference line 214, and the fourth sector angle 228 of the fourth sector 208 may be, for example, ninety degrees.

[0048] Regarding the circumference of the bellmouth 75, when swirl vanes (such as swirl vanes 142 and curved swirl vanes 146) are implemented as the swirl-inducing member 106, the swirl vanes may be circumferentially arranged to include different groups of swirl vanes within each of the first sector 202, the second sector 204, the third sector 206, and the fourth sector 208. For example, a first group 236 of swirl vanes 142 may be circumferentially implemented within the first sector 202, while a second group 238 of swirl vanes 142 may be implemented within the third sector 206, opposite the first group 236 of swirl vanes 142 within the first sector 202. On the other hand, a third group 240 of curved swirl vanes 146 may be circumferentially implemented within the second sector 204, while a fourth group 242 of curved swirl vanes 146 may be implemented within the fourth sector 208, opposite the third group 240 of curved swirl vanes 146 within the second sector 204. The embodiment of the swirl vanes 142 in the first sector 202 and the third sector 206 provides swirl vanes with a lower swirl number that are disposed closest to the outer liner 58 and the inner liner 60. On the other hand, the embodiment of the curved swirl vanes 146 in the second sector 204 and the fourth sector 208 provides a higher swirl number than the swirl vanes 142 in the first sector 202 and the third sector 206. Therefore, the higher swirl number induced by the curved swirl vanes 146 in the second sector 204 and the fourth sector 208 helps maintain the swirling trumpet-shaped oxidant flow 234 ( Figure 3 ) circumferentially closer to the swirler assembly centerline 69. As a result, for example, when a higher swirl number oxidant flows counterclockwise from the fourth sector 208 through the first sector 202, the higher swirl oxidant flow does not severely impinge on the outer liner 58, thereby reducing flame scrubbing on the outer liner 58 and improving the durability of the outer liner 58. The same applies to the higher swirl numbers of the curved swirl vanes 146 implemented in the second sector 204, as the higher swirl oxidant flows through the third sector 206 and may impinge on the inner liner 60.

[0049] Figure 15 is a flow chart depicting the process steps of a method of operating a combustor of a gas turbine according to aspects of the present disclosure. Figure 15The method includes operating the combustion section 26 (also referred to as a combustor) of the gas turbine engine 10. Therefore, for this method, the combustion section 26 includes a swirler assembly 50 having: a swirler 51 having a primary swirler 70, a secondary swirler 72, and a bell mouth 75 connected to the secondary swirler 72; a dome 92 disposed radially outside the bell mouth 75; and a trumpet-shaped oxidant flow channel 108 circumferentially arranged between the bell mouth 75 and the dome 92. In addition, a swirl inducing member 106 is disposed within the trumpet-shaped oxidant flow channel 108. The combustion section 26 also includes an outer liner 58 and an inner liner 60, wherein the outer liner 58 and the inner liner 60 define a combustion chamber 62 therebetween. The fuel nozzle 76 is also disposed in the swirler 51.

[0050] exist Figure 15 In the method, a first step 1500 provides for flowing an oxidant (e.g., a portion of the compressed air 82(a)) through the primary swirler 70 and injecting the fuel 84 from the fuel nozzle 76 into the primary swirler 70 to generate a swirling primary fuel-oxidant mixture 230 ( Figure 3 The second step 1501 of the method provides for flowing an oxidant (e.g., a portion of the compressed air 82(a)) through the secondary cyclone 72 and mixing the swirling oxidant from the secondary cyclone 72 with the swirling primary fuel-oxidant mixture 230 to produce a swirling secondary fuel-oxidant mixture 232 ( Figure 3 The third step 1502 includes flowing the swirling secondary fuel-oxidant mixture 232 from the bell mouth 75 into the combustion chamber 62,

[0051] Step 1503 of the method includes flowing oxidant (e.g., portion of compressed air 82(a)) through the trumpet-shaped oxidant flow passage 108 between the bell mouth 75 and the dome 92, and step 1504 includes inducing swirl into the oxidant flow flowing through the trumpet-shaped oxidant flow passage 108 via the swirl inducing member 106 to generate a swirling trumpet-shaped oxidant flow 234 ( Figure 3 )(Step 1505). Step 1506 then includes igniting the secondary fuel-oxidant mixture in the combustion chamber 62 to generate combustion product gases.

[0052] In the inducing step 1504, the method may also be implemented via a plurality of swirl vanes 142 and a plurality of curved swirl vanes 146 circumferentially arranged within the trumpet-shaped oxidant flow passage 108. In this arrangement, inducing swirl of the oxidant through the oxidant flow passage includes inducing a first swirl of the oxidant having a first swirl number via a first group 236 of swirl vanes 142 and a second group 238 of swirl vanes 142 circumferentially opposite the first group 236 of swirl vanes 142, and inducing a second swirl of the oxidant having a second swirl number higher than the first swirl number via a third group 240 of curved swirl vanes 146 and a fourth group 242 of curved swirl vanes 146 circumferentially opposite the third group 249 of curved swirl vanes 146. The third group 240 of curved swirl vanes 146 is circumferentially disposed between the first group 236 of swirl vanes 142 and the second group 238 of swirl vanes 142. The fourth group 242 of curved swirl vanes 146 is circumferentially disposed opposite the third group 240 of curved swirl vanes 146 and between the first group 236 of swirl vanes 142 and the second group 238 of swirl vanes 142. The first group 236 of swirl vanes 142 is disposed in a first sector 202 adjacent to the outer liner 58 and in a third sector 206 opposite the first sector 202 and adjacent to the inner liner 60. The third group 240 of curved swirl vanes 146 is disposed in a second sector 204 between the first sector 202 and the third sector 206 and in a fourth sector 208 opposite the second sector 204 and between the first sector 202 and the third sector 206.

[0053] In another aspect, inducing step 1504 can be implemented by dividing trumpet-shaped oxidant flow channel 108 into a plurality of flow channels. Trumpet-shaped oxidant flow channel 108 includes intermediate wall 186 disposed between bellmouth 75 and dome 92. Intermediate wall 186 defines a bellmouth-side oxidant flow channel 192 between bellmouth 75 and intermediate wall 186, and a dome-side oxidant flow channel 194 disposed between dome 92 and intermediate wall 186. Bellmouth-side oxidant flow channel 192 includes bellmouth-side swirl inducing member 198, while dome-side oxidant flow channel 194 includes dome-side swirl inducing member 200. In this arrangement, inducing step 1504 includes inducing bellmouth-side swirl 244 of the oxidant via bellmouth-side swirl inducing member 198 and inducing dome-side swirl 246 of the oxidant via dome-side swirl inducing member 200. The swirl direction of the bell-side swirl 244 of the oxidant can be in the same swirl direction as the swirl direction of the dome-side swirl 246 of the oxidant (i.e., both are in a clockwise direction or both are in a counterclockwise direction), or the swirl direction of the bell-side swirl 244 of the oxidant can be in the opposite swirl direction as the swirl direction of the dome-side swirl 246 of the oxidant (i.e., one is in a clockwise direction and the other is in a counterclockwise direction).

[0054] While the above description generally relates to gas turbine engines, it will be readily understood that gas turbine engines can be implemented in a variety of environments. For example, the engine can be implemented in an aircraft, but can also be implemented in non-aircraft applications, such as power plants, marine applications, or oil and gas production applications. Therefore, the present disclosure is not limited to use in aircraft.

[0055] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0056] A swirler assembly for a gas turbine engine, the swirler assembly defining a swirler assembly centerline passing therethrough, a longitudinal direction along the swirler assembly centerline, a radial direction extending outward from the swirler assembly centerline, and a circumferential direction about the swirler assembly centerline, the swirler assembly comprising: a swirler having a primary swirler and a secondary swirler, the secondary swirler being longitudinally disposed downstream of the primary swirler along the swirler assembly centerline; and a bellmouth connected to a downstream end of the secondary swirler. The bell mouth includes: (i) a bell-shaped axial wall, the bell-shaped axial wall extending circumferentially around the center line of the swirler assembly and extending in the longitudinal direction, the bell-shaped axial wall having a bell-shaped axial wall outer surface; and (ii) a bell-shaped conical wall connected to the downstream end of the bell-shaped axial wall and extending circumferentially around the center line of the swirler assembly and extending radially outward and longitudinally downstream from the downstream end of the bell-shaped axial wall, the bell-shaped conical wall having a bell-shaped conical wall outer surface, wherein the bell-shaped axial wall outer surface The flared outer surface is defined by a surface and an outer surface of the flared conical wall; and a dome, the dome being arranged radially outward of the flared mouth, the dome comprising: (i) a dome axial wall, the dome axial wall extending circumferentially around the centerline of the swirler assembly and extending in the longitudinal direction, the dome axial wall having a dome axial wall inner surface; and (ii) a dome conical wall connected to the downstream end of the dome axial wall and extending circumferentially around the centerline of the swirler assembly, and extending radially outward and longitudinally downstream from the downstream end of the dome axial wall. and (iii) a dome radial wall extending radially outward from a downstream end of the dome conical wall, the dome conical wall having a dome conical wall inner surface, wherein the dome axial wall inner surface and the dome conical wall inner surface define a dome inner surface, wherein a trumpet-shaped oxidant flow channel is defined by the trumpet-shaped outer surface and the dome inner surface, and wherein the trumpet-shaped oxidant flow channel includes a swirl inducing member therein, the swirl inducing member inducing a swirl of the oxidant passing through the trumpet-shaped oxidant flow channel into the combustion chamber.

[0057] A swirler assembly as claimed in any preceding clause, wherein the swirl inducing member is arranged to induce the swirl flow in a co-directional swirl direction with the swirl direction of the secondary swirler.

[0058] A swirler assembly as claimed in any preceding clause, wherein the swirl inducing member is arranged to induce the swirl flow in a counter swirl direction to that of the secondary swirler.

[0059] A swirler assembly according to any preceding clause, wherein the swirl inducing member comprises an annular ring having a plurality of apertures therethrough, wherein an outlet end of each of the plurality of apertures extends at least partially in the circumferential direction so as to provide tangential flow of the oxidant therethrough into the combustion chamber.

[0060] A swirler assembly as claimed in any preceding clause, wherein at least a portion of the flared outer surface comprises corrugations, and wherein at least a portion of the dome inner surface comprises corrugations.

[0061] A swirler assembly as described in any preceding clause, wherein the swirl inducing member comprises a plurality of swirl vanes.

[0062] A swirler assembly as in any preceding clause, wherein the plurality of swirl vanes are arranged between the flared conical wall outer surface and the domed conical wall inner surface.

[0063] The swirler assembly of any preceding clause, wherein the plurality of swirl vanes are curved swirl vanes extending from an upstream end of the flared conical wall outer surface to a downstream end of the flared conical wall outer surface and extending at least partially in the circumferential direction about the swirler assembly centerline.

[0064] A swirler assembly as in any preceding clause, wherein the plurality of swirl vanes are arranged between the flared axial wall outer surface and the domed axial wall inner surface.

[0065] The swirler assembly of any preceding clause, wherein the plurality of swirl vanes are arranged in a plurality of groups around the circumference of the bell mouth, wherein a first group of swirl vanes and a second group of swirl vanes are configured to induce a first swirl number into the flow of the oxidant, the second group of swirl vanes are circumferentially opposed to the first group of swirl vanes about a centerline of the swirler assembly, and a third group of swirl vanes arranged between the first and second groups of swirl vanes and a fourth group of swirl vanes circumferentially opposed to the third group of swirl vanes about the centerline of the swirler assembly are configured to induce a second swirl number into the flow of the oxidant, the first swirl number being less than the second swirl number.

[0066] A swirler assembly as claimed in any preceding clause, wherein the first set of swirl vanes are arranged on an outer liner side of the bell mouth and the second set of swirl vanes are arranged on an inner liner side of the bell mouth.

[0067] The swirler assembly according to any preceding clause further comprises an intermediate wall in the trumpet-shaped oxidant flow channel, the intermediate wall comprising an intermediate axial wall and an intermediate conical wall, the intermediate axial wall extending circumferentially around the centerline of the swirler assembly and extending in the longitudinal direction, the intermediate conical wall being connected to the downstream end of the intermediate axial wall and extending circumferentially around the centerline of the swirler assembly and extending radially outward and longitudinally downstream from the downstream end of the intermediate axial wall, wherein the trumpet-shaped oxidant flow channel comprises a bell-mouth-side oxidant flow channel and a dome-side oxidant flow channel, the bell-mouth-side oxidant flow channel being defined by the trumpet outer surface and the intermediate wall, and the dome-side oxidant flow channel being defined by the dome inner surface and the intermediate wall, and wherein the swirl inducing member comprises a first swirl inducing member in the trumpet-side oxidant flow channel and a second swirl inducing member in the dome-side oxidant flow channel.

[0068] The swirler assembly of any preceding clause, wherein the first swirl inducing member induces a bell-side swirl of the oxidant and the second swirl inducing member induces a dome-side swirl of the oxidant, the bell-side swirl of the oxidant and the dome-side swirl of the oxidant being in a co-swirl direction relative to each other.

[0069] The swirler assembly of any preceding clause, wherein the first swirl inducing member induces a bell-side swirl of the oxidant and the second swirl inducing member induces a dome-side swirl of the oxidant, the bell-side swirl of the oxidant and the dome-side swirl of the oxidant being in a co-swirl direction relative to each other or in a counter-swirl direction relative to each other, and wherein the bell-side swirl of the oxidant is in a co-swirl direction relative to the swirl direction of the secondary swirler or in a counter-swirl direction relative to the swirl direction of the secondary swirler.

[0070] 1. A method of operating a combustor of a gas turbine, the combustor comprising: (i) a swirler assembly, the swirler assembly comprising: (a) a primary swirler, (b) a secondary swirler, (c) a bell mouth connected to the secondary swirler, (d) a dome disposed radially outwardly of the bell mouth, and (e) an oxidant flow channel circumferentially arranged between the bell mouth and the dome, wherein a swirl inducing member is disposed in the oxidant flow channel; (ii) a combustor liner, the combustor liner comprising an outer liner and an inner liner, the outer liner and the inner liner defining a combustion chamber therebetween; and (iii) a fuel nozzle disposed in the swirler assembly, the method comprising: flowing an oxidant through the primary swirler and injecting a fuel into the swirler; The fuel is injected into the primary swirler from the fuel nozzle to generate a swirling primary fuel-oxidizer mixture; the oxidizer is caused to flow through the secondary swirler, and the oxidizer from the secondary swirler is mixed with the swirling primary fuel-oxidizer mixture to generate a swirling secondary fuel-oxidizer mixture; the swirling secondary fuel-oxidizer mixture is caused to flow from the bell mouth into the combustion chamber; the oxidizer is caused to flow through the oxidizer flow channel between the bell mouth and the dome; the swirl inducing member induces a swirl of the oxidizer flowing through the oxidizer flow channel to generate a swirling oxidizer flow entering the combustion chamber; and the swirling secondary fuel-oxidizer mixture in the combustion chamber is ignited to generate combustion product gas.

[0071] A method as in any preceding clause, wherein said inducing induces oxidant flow in a co-swirl direction with a swirl direction of said swirling secondary fuel-oxidant mixture.

[0072] A method as in any preceding clause, wherein the swirl inducing member comprises a plurality of swirl vanes disposed circumferentially within the oxidant flow passage.

[0073] The method of any preceding clause, wherein the swirl inducing member includes a plurality of swirl vanes circumferentially arranged within the oxidant flow passage, and wherein inducing the swirl of the oxidant through the oxidant flow passage includes: inducing a first swirl of the oxidant having a first swirl number by a first group of swirl vanes among the plurality of swirl vanes and a second group of swirl vanes circumferentially opposite the first group of swirl vanes; and inducing a second swirl of the oxidant having a second swirl number higher than the first swirl number by a third group of swirl vanes among the plurality of swirl vanes and a fourth group of swirl vanes circumferentially opposite the third group of swirl vanes, wherein the third group of swirl vanes is arranged between the first group of swirl vanes and the second group of swirl vanes, and wherein the fourth group of swirl vanes is arranged circumferentially opposite the third group of swirl vanes and between the first group of swirl vanes and the second group of swirl vanes.

[0074] The method of any preceding clause, wherein the first set of swirl vanes are circumferentially arranged in a first sector adjacent to the outer liner and circumferentially arranged in a second sector opposite the first sector and adjacent to the inner liner, the second set of swirl vanes are arranged in a third sector between the first and second sectors, and in a fourth sector opposite the third sector and between the first and second sectors.

[0075] A method according to any preceding clause, wherein the oxidant flow channel includes an intermediate wall between the bell mouth and the dome, the intermediate wall defining a bell mouth-side oxidant flow channel between the bell mouth and the intermediate wall, and a dome-side oxidant flow channel between the dome and the intermediate wall, and wherein a bell mouth-side swirl inducing member is disposed in the bell mouth-side oxidant flow channel, a dome-side swirl inducing member is disposed in the dome-side oxidant flow channel, wherein the inducing includes (a) inducing a bell mouth-side swirl of the oxidant by the bell mouth-side swirl inducing member, and (b) inducing a dome-side swirl of the oxidant by the dome-side swirl inducing member.

[0076] A method as in any preceding clause, wherein the swirl direction of the bell-side swirl of the oxidant is opposite to the swirl direction of the dome-side swirl of the oxidant.

[0077] Although the foregoing description is directed to some exemplary embodiments of the present disclosure, other variations and modifications will be apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, features described in conjunction with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A swirler assembly for a gas turbine engine, the swirler assembly defining a swirler assembly centerline therethrough, a longitudinal direction along the swirler assembly centerline, a radial direction extending outward from the swirler assembly centerline, and a circumferential direction about the swirler assembly centerline, wherein: The cyclone assembly comprises: a cyclone, the cyclone comprising a primary cyclone and a secondary cyclone, the secondary cyclone being longitudinally arranged downstream of the primary cyclone along a centerline of the cyclone assembly; a bell mouth connected to a downstream end of the secondary swirler, the bell mouth comprising: (i) a trumpet-shaped axial wall extending circumferentially about a centerline of the swirler assembly and in the longitudinal direction, the trumpet-shaped axial wall having a trumpet-shaped axial wall outer surface; and (ii) a trumpet-shaped conical wall connected to a downstream end of the trumpet-shaped axial wall and extending circumferentially about the centerline of the swirler assembly and extending radially outward and longitudinally downstream from the downstream end of the trumpet-shaped axial wall, the trumpet-shaped conical wall having a trumpet-shaped conical wall outer surface, wherein the trumpet-shaped axial wall outer surface and the trumpet-shaped conical wall outer surface define a trumpet-shaped outer surface; and A dome is provided radially outside the bell mouth, the dome comprising: (i) a dome axial wall, the dome axial wall extending circumferentially around the centerline of the swirler assembly and in the longitudinal direction, the dome axial wall having a dome axial wall inner surface; (ii) a dome conical wall connected to a downstream end of the dome axial wall and extending circumferentially around the centerline of the swirler assembly, and extending radially outward and longitudinally downstream from the downstream end of the dome axial wall; and (iii) a dome radial wall extending radially outward from the downstream end of the dome conical wall, the dome conical wall having a dome conical wall inner surface, wherein the dome axial wall inner surface and the dome conical wall inner surface define a dome inner surface. wherein the trumpet-shaped oxidant flow channel is defined by the trumpet-shaped outer surface and the dome inner surface, and The trumpet-shaped oxidant flow passage includes a swirl inducing member therein, and the swirl inducing member induces a swirl flow of the oxidant passing through the trumpet-shaped oxidant flow passage into the combustion chamber.

2. The cyclone assembly according to claim 1, characterized in that The swirl inducing member is arranged to induce the swirl flow in a swirl direction that is the same as the swirl direction of the secondary swirler.

3. The cyclone assembly according to claim 1, characterized in that The swirl inducing member is arranged to induce the swirl flow in a direction opposite to the swirl direction of the secondary swirler.

4. The cyclone assembly according to claim 1, characterized in that wherein the swirl inducing member comprises an annular ring having a plurality of apertures therethrough, wherein an outlet end of each of the plurality of apertures extends at least partially in the circumferential direction to provide tangential flow of the oxidant therethrough into the combustion chamber.

5. The cyclone assembly according to claim 1, characterized in that Wherein at least a portion of the flared outer surface comprises corrugations, and wherein at least a portion of the dome inner surface comprises corrugations.

6. The cyclone assembly according to claim 1, characterized in that The swirl inducing component includes a plurality of swirl vanes.

7. The cyclone assembly according to claim 6, characterized in that The plurality of swirl vanes are arranged between the outer surface of the trumpet-shaped conical wall and the inner surface of the dome-shaped conical wall.

8. The cyclone assembly according to claim 7, characterized in that The plurality of swirl vanes are curved swirl vanes extending from an upstream end of the flared conical wall outer surface to a downstream end of the flared conical wall outer surface and extending at least partially in the circumferential direction around a centerline of the swirler assembly.

9. The cyclone assembly according to claim 6, characterized in that The plurality of swirl vanes are arranged between the outer surface of the trumpet-shaped axial wall and the inner surface of the dome-shaped axial wall.

10. The cyclone assembly according to claim 6, characterized in that wherein the plurality of swirl vanes are arranged into a plurality of groups around the circumference of the bell mouth, wherein a first set of swirl vanes and a second set of swirl vanes are configured to induce a first swirl number into the flow of the oxidant, the second set of swirl vanes being circumferentially opposed to the first set of swirl vanes about a centerline of the swirler assembly, and A third set of swirl vanes disposed between the first set of swirl vanes and the second set of swirl vanes and a fourth set of swirl vanes circumferentially opposite the third set of swirl vanes about a centerline of the swirler assembly are configured to induce a second swirl number into the flow of the oxidant, the first swirl number being less than the second swirl number.

11. The cyclone assembly according to claim 10, characterized in that The first group of swirl vanes is arranged on the outer lining side of the bell mouth, and the second group of swirl vanes is arranged on the inner lining side of the bell mouth.

12. The cyclone assembly according to claim 1, characterized in that The oxidizer further comprises an intermediate wall in the trumpet-shaped oxidant flow channel, the intermediate wall comprising an intermediate axial wall and an intermediate conical wall, the intermediate axial wall extending circumferentially around the centerline of the cyclone assembly and extending in the longitudinal direction, the intermediate conical wall being connected to the downstream end of the intermediate axial wall and extending circumferentially around the centerline of the cyclone assembly, and extending radially outward and longitudinally downstream from the downstream end of the intermediate axial wall. wherein the trumpet-shaped oxidant flow channel includes a trumpet-side oxidant flow channel and a dome-side oxidant flow channel, the trumpet-side oxidant flow channel is defined by the trumpet-shaped outer surface and the intermediate wall, and the dome-side oxidant flow channel is defined by the dome inner surface and the intermediate wall, and The swirl flow inducing member includes a first swirl flow inducing member in the bell-mouth-side oxidant flow channel and a second swirl flow inducing member in the dome-side oxidant flow channel.

13. The cyclone assembly according to claim 12, characterized in that The first swirl inducing member induces a bell-side swirl of the oxidant, and the second swirl inducing member induces a dome-side swirl of the oxidant, the bell-side swirl of the oxidant and the dome-side swirl of the oxidant being in the same swirl direction relative to each other.

14. The cyclone assembly according to claim 12, wherein: wherein the first swirl inducing member induces a bell-mouth-side swirl of the oxidant, and the second swirl inducing member induces a dome-side swirl of the oxidant, the bell-mouth-side swirl of the oxidant and the dome-side swirl of the oxidant being in the same swirl direction or in opposite swirl directions relative to each other, and The bell-mouth side swirl of the oxidant is in the same swirl direction as the swirl direction of the secondary swirler, or in the opposite swirl direction as the swirl direction of the secondary swirler.

15. A method of operating a combustor of a gas turbine, characterized in that The combustor comprises: (i) a swirler assembly, the swirler assembly comprising (a) a primary swirler, (b) a secondary swirler, (c) a bellmouth connected to the secondary swirler, the bellmouth comprising a bell-shaped conical wall extending in radial and downstream directions and having a bell-shaped conical wall outer surface, (d) a dome disposed radially outward of the bellmouth, the dome comprising a dome wall having a dome wall inner surface, and (e) an oxidant flow passage circumferentially arranged between the bellmouth and the dome, wherein a swirl inducing member is disposed in the oxidant flow passage, the oxidant flow passage being between the bell-shaped conical wall outer surface and the dome wall inner surface; (ii) a combustor liner comprising an outer liner and an inner liner, the outer liner and the inner liner defining a combustion chamber therebetween; and (iii) a fuel nozzle disposed in the swirler assembly, the method comprising: flowing an oxidant through the primary swirler and injecting fuel from the fuel nozzle into the primary swirler to generate a swirling primary fuel-oxidant mixture; flowing an oxidant through the secondary cyclone and mixing the oxidant from the secondary cyclone with the swirling primary fuel-oxidant mixture to produce a swirling secondary fuel-oxidant mixture; allowing the swirling secondary fuel-oxidant mixture to flow from the bell mouth into the combustion chamber; allowing an oxidant to flow through the oxidant flow passage between the bell mouth and the dome; inducing a swirl flow of the oxidant flowing through the oxidant flow passage by the swirl inducing member to generate a swirling oxidant flow entering the combustion chamber; and The swirling secondary fuel-oxidant mixture in the combustion chamber is ignited to generate combustion product gases.

16. The method according to claim 15, characterized in that wherein said inducing induces oxidant flow in a co-directional swirl direction of said swirling secondary fuel-oxidant mixture.

17. The method according to claim 15, characterized in that The swirl inducing member includes a plurality of swirl vanes circumferentially arranged in the oxidant flow channel.

18. The method according to claim 15, characterized in that wherein the swirl inducing member comprises a plurality of swirl vanes circumferentially arranged in the oxidant flow channel, and Wherein, inducing the swirl flow of the oxidant through the oxidant flow channel comprises: inducing a first swirl flow of the oxidant having a first swirl number by a first set of swirl vanes among the plurality of swirl vanes and a second set of swirl vanes circumferentially opposite the first set of swirl vanes; and A second swirl flow of the oxidant having a second swirl number is induced by a third group of swirl vanes among the plurality of swirl vanes and a fourth group of swirl vanes circumferentially opposite to the third group of swirl vanes, wherein the second swirl number is higher than the first swirl number, The third group of swirl vanes is arranged between the first group of swirl vanes and the second group of swirl vanes, and the fourth group of swirl vanes is arranged circumferentially opposite to the third group of swirl vanes and between the first group of swirl vanes and the second group of swirl vanes.

19. The method according to claim 18, characterized in that The first group of swirl vanes is circumferentially arranged in a first sector adjacent to the outer liner, and circumferentially arranged in a second sector opposite to the first sector and adjacent to the inner liner; the second group of swirl vanes is arranged in a third sector between the first sector and the second sector, and in a fourth sector opposite to the third sector and between the first sector and the second sector.

20. The method according to claim 15, wherein wherein the oxidant flow passage includes an intermediate wall between the bell mouth and the dome, the intermediate wall defining a bell mouth-side oxidant flow passage between the bell mouth and the intermediate wall, and a dome-side oxidant flow passage between the dome and the intermediate wall, and wherein a bell mouth-side swirl inducing member is disposed in the bell mouth-side oxidant flow passage, and a dome-side swirl inducing member is disposed in the dome-side oxidant flow passage, The inducing includes (a) inducing a bell-side swirl flow of the oxidant by the bell-side swirl flow inducing member, and (b) inducing a dome-side swirl flow of the oxidant by the dome-side swirl flow inducing member.

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