Multi-pressure-drop cyclone liner plate

Abstract

A cyclone assembly includes a cyclone having a primary cyclone with a primary cyclone venturi, a cyclone liner plate connected to the primary cyclone, and a fuel nozzle disposed in the cyclone liner plate. The cyclone liner plate has a back wall, an annular conical wall, and an annular cavity wall that together form an annular cavity. The annular cavity includes a plurality of inlet orifices and at least one outlet orifice. A flow of oxidant into the annular cavity through the plurality of inlet orifices causes a first pressure drop from a first pressure of a plenum to a second pressure that is lower than the first pressure, and a flow of oxidant from the annular cavity into the primary cyclone venturi through the at least one outlet orifice causes a second pressure drop from the second pressure to a third pressure that is lower than the second pressure.

Description

Technical Field

[0001] This disclosure relates to a swirler ring plate for a swirler assembly in a combustor of a gas turbine engine. Background Technology

[0002] Some conventional gas turbine engines are known to include rich-fuel combustors, which typically use swirlers integrated with fuel nozzles 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, and a swirler collar plate surrounding the fuel nozzle. The primary swirler includes a primary swirler venturi tube, where a primary swirling airflow from the primary swirler mixes with fuel injected into the primary swirler venturi tube through the fuel nozzle. The swirler collar plate may include purge orifices that provide a purge airflow from the pressure chamber to the primary swirler venturi tube. The purge flow through the swirler collar plate is at a relatively high velocity as it exits the swirler collar plate and enters the primary swirler venturi tube. Summary of the Invention

[0003] According to one aspect, this disclosure relates to a swirler assembly of a burner, the swirler assembly defining a centerline therethrough. The swirler assembly of this aspect includes (i) a swirler including a primary swirler having a primary swirler venturi tube, (ii) a swirler collar plate connected to an upstream side of the primary swirler and including a fuel nozzle opening extending through it along the centerline of the swirler assembly, and (iii) a fuel nozzle disposed in the fuel nozzle opening of the swirler collar plate. The swirler collar plate includes (a) a rear wall extending radially outward from the fuel nozzle opening, (b) an annular conical wall extending radially inward from a portion of the rear wall at the fuel nozzle opening and extending radially outward upstream from the rear wall, and (c) an annular cavity wall connecting the radially outward portion of the rear wall and the upstream end of the annular conical wall, an annular cavity formed between the rear wall, the annular conical wall, and the annular cavity wall including a plurality of inlet orifices therethrough. The hydrocyclone collar plate includes at least one outlet orifice providing fluid communication between the annular cavity and the primary hydrocyclone venturi tube, and the flow of oxidant into the annular cavity through multiple inlet orifices causes a first pressure drop from a first pressure in the pressure chamber to a second pressure below the first pressure, and the flow of oxidant into the primary hydrocyclone venturi tube from the annular cavity through at least one outlet orifice causes a second pressure drop from the second pressure to a third pressure below the second pressure.

[0004] According to another aspect, this disclosure relates to a method of operating a combustor for a gas turbine. In this aspect, the combustor includes (i) a pressure chamber, (ii) a swirler assembly including (a) a swirler having a primary swirler with a primary swirler venturi tube, and (b) a swirler collar plate connected to the primary swirler and including a fuel nozzle opening extending therethrough and an annular pressure drop chamber having a plurality of inlet orifices in fluid communication with the pressure chamber and at least one outlet orifice in fluid communication with a region of the primary swirler venturi tube, and (iii) a fuel nozzle disposed in the fuel nozzle opening of the swirler collar plate. A method of operating a combustor of a gas turbine engine includes (1) providing a first stream of oxidant to a pressure chamber having a first pressure, (2) providing a second stream of oxidant from the pressure chamber to an annular pressure drop chamber of a cyclone ring plate via a plurality of inlet orifices of an annular pressure drop chamber, the second stream of oxidant causing a first pressure drop in the flow of oxidant in the annular pressure drop chamber from the first pressure to a second pressure below the first pressure, and (3) providing a third stream of oxidant from the annular pressure drop chamber to a venturi tube region of a primary cyclone via at least one outlet orifice of the cyclone ring plate, the third stream of oxidant causing a second pressure drop in the flow of oxidant from the second pressure to a third pressure below the second pressure.

[0005] Additional features, advantages, and embodiments of this disclosure will become apparent from consideration of the following detailed description, accompanying drawings, and claims. Furthermore, it should be understood that the foregoing overview and the following detailed description are exemplary and intended to provide further explanation without limiting the scope of the claimed disclosure. Attached Figure Description

[0006] The above and other features and advantages will become apparent from the more specific description of the various exemplary embodiments below, as shown in the accompanying drawings, wherein similar reference numerals generally indicate the same, functionally similar and / or structurally similar elements.

[0007] Figure 1 This is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine according to aspects of this disclosure.

[0008] Figure 2 This is a partial cross-sectional side view of an exemplary combustion section according to aspects of this disclosure.

[0009] Figure 3 yes Figure 2 A partial cross-sectional side view of the front portion of an exemplary combustion section.

[0010] Figure 4 This is a partial cross-sectional side view detail of an exemplary fuel nozzle assembly according to aspects of this disclosure.

[0011] Figure 5 This is a rear perspective view of an exemplary cyclone assembly according to aspects of this disclosure.

[0012] Figure 6 This is a front perspective view of an exemplary hydrocyclone ring plate according to aspects of this disclosure.

[0013] Figure 7 Based on aspects of this disclosure Figure 4 A partial cross-sectional side view of the exemplary hydrocyclone collar plate, taken at point 7-7.

[0014] Figure 8 This is a rear-view front view of an exemplary cyclone collar plate according to aspects of this disclosure.

[0015] Figure 9 It is based on another aspect of this disclosure. Figure 4 A partial cross-sectional side view detailing the exemplary hydrocyclone collar plate outlet orifice arrangement, taken at detail 9-9.

[0016] Figure 10 This is a partial cross-sectional side view detailing the arrangement of the outlet orifice of an exemplary hydrocyclone ring plate according to another aspect of this disclosure.

[0017] Figure 11 It is in accordance with another aspect of this disclosure in response to Figure 4 plane AA Figure 9 A partial cross-sectional rear-view front view of the arrangement of the hydrocyclone collar plate and fuel nozzle outlet orifice, taken at plane 11-11.

[0018] Figure 12 It is in accordance with another aspect of this disclosure in response to Figure 4 plane AA Figure 9 A partial cross-sectional rear-view front view of the arrangement of the hydrocyclone collar plate and fuel nozzle outlet orifice, taken at plane 12-12.

[0019] Figure 13 It is in accordance with another aspect of this disclosure in response to Figure 4 plane AA Figure 10 A partial cross-sectional rear-view front view of the arrangement of the hydrocyclone collar plate and fuel nozzle outlet orifice, taken at plane 13-13.

[0020] Figure 14 This is a flowchart of the processing steps of a method for operating a burner according to aspects of this disclosure. Detailed Implementation

[0021] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the art will recognize that other components and constructions can be used without departing from the spirit and scope of this disclosure.

[0022] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0023] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0024] In a fuel-rich combustor including a radial-radial cyclone, air is supplied from the pressure chamber of the combustor to the primary radial cyclone, where swirling blades in the primary cyclone induce swirl in the air as it flows through. The primary cyclone also includes a venturi tube and a fuel nozzle that injects fuel into the venturi tube, where the fuel mixes with the swirling airflow from the primary cyclone. A cyclone ring plate surrounds the fuel nozzle and may include purge orifices that provide purge airflow from the pressure chamber to the venturi tube. The purge flow through the cyclone ring plate is at relatively high pressure and high exit velocity as it exits the cyclone ring plate and enters the venturi tube of the primary cyclone. The high-speed airflow from the ring plate interacts directly with the swirling air from the primary cyclone, leading to hydrodynamic instabilities and introducing greater turbulence in the flow within the primary cyclone, particularly before the fuel nozzle tip. These hydrodynamic instabilities force instabilities in fuel distribution and heat release within the burner, resulting in pressure fluctuations within the venturi tube that are greater than expected.

[0025] This disclosure addresses the aforementioned problems by reducing hydrodynamic instabilities and maintaining the amplitude of venturi pressure fluctuations at or below a desired level. According to this disclosure, a hydrocyclone ring plate includes an annular cavity having an inlet orifice and an outlet orifice. Pressurized air contained in a pressure chamber flows through the inlet orifice into the annular cavity of the hydrocyclone ring plate. A second flow of this air causes a first pressure drop, such that the air pressure within the annular cavity is lower than the air pressure in the pressure chamber. The air in the annular cavity of the hydrocyclone ring plate then flows through the outlet orifice into the primary hydrocyclone venturi tube. A third flow of this air causes a second pressure drop, such that the pressure of the airflow within the venturi tube is lower than the pressure of the air in the annular cavity. As a result, the velocity of the flow exiting the ring plate can be maintained at a low velocity, thus reducing disturbances in the primary hydrocyclone airflow. Therefore, this disclosure reduces the hydrodynamic instabilities present in conventional ring plates.

[0026] Now refer to the attached diagram, Figure 1 This is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine 10 (referred to herein as "engine 10") that can be incorporated into various embodiments of the present disclosure. Although further described below with reference to turbofan engines, this disclosure is also applicable to general turbomachinery, including turbojet engines, turboprop engines, and turboshaft gas turbine engines, including marine and industrial turbine engines and auxiliary power units. Figure 1 As shown, engine 10 has a longitudinal or axial centerline axis 12 extending from upstream end 98 to downstream end 99, for reference. Typically, engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0027] The core engine 16 typically includes a housing 18 defining an annular inlet 20. The housing 18 surrounds or at least partially forms, in a series flow relationship, a compressor section having a boost or low-pressure (LP) compressor 22, a high-pressure (HP) compressor 24; a combustor 26; a turbine section including a high-pressure (HP) turbine 28, a low-pressure (LP) turbine 30; and an injection exhaust nozzle section 32. A high-pressure (HP) rotor shaft 34 drivesly connects the HP turbine 28 to the HP compressor 24. A low-pressure (LP) rotor shaft 36 drivesly 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, such as Figure 1 As shown, the LP rotor shaft 36 can be connected to the fan shaft 38 via a reduction gear 40, for example in an indirect drive configuration or a gear transmission configuration. In other embodiments, although not shown, the engine 10 may also include an intermediate pressure (IP) compressor and a turbine that rotates with the intermediate pressure shaft.

[0028] like Figure 1 As 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 housing or nacelle 44 circumferentially surrounds at least a portion of the fan assembly 14 and / or 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. Furthermore, at least a portion of the nacelle 44 may extend over the outer portion of the core engine 16 to define a bypass airflow passage 48 therebetween.

[0029] Figure 2 An exemplary burner 26 according to this disclosure is depicted. Figure 2In this design, the burner 26 includes a swirler assembly 50, a fuel nozzle assembly 52, a dome assembly 54, and an annular combustion bushing 56 within a housing 64. The annular combustion bushing 56 includes an annular outer liner 58 and an annular inner liner 60, forming a combustion chamber 62 between them. A pressure chamber 66 is formed within the dome assembly 54. (Return to Reference) Figure 1 During operation, air 73 enters the engine compartment 44, and a portion of the air 73 enters the compressor section as the compressor inlet airflow 80, where this portion of air is compressed. Another portion of the air 73 enters the bypass airflow passage 48 as bypass airflow 78. Figure 2 In the combustion chamber 26, air 82 from the compressor section (22 / 24) enters via a diffuser (not shown). A portion of the air 82(a) enters the dome assembly 54 into the pressure chamber 66, while another portion of the air 82(b) flows into the external flow passage 68 between the annular combustion bushing 56 and the outer casing 64. As will be described below, the air 82(a) in the pressure chamber 66 passes through the swirler assembly 50 to mix with the fuel injected by the fuel nozzle assembly 52 and is ignited to generate combustion product gases 86.

[0030] refer to Figure 3 and Figure 4 , Figure 3 A partial cross-sectional view of the front portion of the burner in the burner 26, including the swirler assembly 50, is depicted. Figure 4 A partial cross-sectional view of the hydrocyclone assembly 50 is depicted. Figure 3In this configuration, the burner 26 defines itself in a longitudinal direction L relative to the engine centerline axis 12, and in a radial direction R relative to the engine centerline axis 12. The swirler assembly 50 is symmetrical about a swirler assembly centerline 69, which extends in the longitudinal direction L and is perpendicular to the radial direction R. The swirler assembly 50 is suitably connected to the dome assembly 54. The swirler assembly 50 includes a swirler 51 and a fuel nozzle 90 disposed within the swirler 51. As will be described in more detail below, the swirler 51 includes: a primary swirler 70, which includes a primary swirler venturi tube 100; a secondary swirler 72; and a swirler collar plate 91. The primary swirler 70 includes a plurality of primary swirler blades 74. The primary swirler blades 74 are arranged circumferentially in a row such that each primary swirler blade 74 extends radially inward to a primary swirler blade lip 76. The primary cyclone separator 70 also includes a primary cyclone venturi tube 100, which extends concentrically about the centerline 69 of the cyclone assembly in the longitudinal direction L. Thus, the primary cyclone separator 70 is configured to cause corresponding portions of pressurized air 82(a) from the pressure chamber 66 to swirl radially inward from a plurality of primary cyclone impeller blades 74, and then swirl within the primary cyclone separator 70 in the primary swirl direction 104 (i.e., clockwise or counterclockwise about the centerline 69 of the cyclone assembly).

[0031] The secondary cyclone 72 similarly includes secondary cyclone impellers 84 arranged circumferentially in a row, such that each secondary cyclone impeller 84 extends radially inward to a secondary cyclone impeller lip 88. Thus, the secondary cyclone 72 is configured to cause another corresponding portion of the pressurized air 82(a) from the pressure chamber 66 to swirl radially inward from the plurality of secondary cyclone impellers 84 of the secondary cyclone 72.

[0032] As can be seen, the fuel nozzle assembly 52 includes a fuel nozzle 90 disposed within the cyclone ring plate 91 of the cyclone 51. The fuel nozzle 90 injects fuel 92 into the primary cyclone venturi region 102 of the primary cyclone venturi 100. Figure 4 Here, fuel 92 is mixed with air 82(a) from the primary cyclone separator 70. The fuel and air mixture in the venturi tube is further mixed downstream with air 82(a) from the secondary cyclone separator 72 downstream of the primary cyclone separator venturi tube 100. The primary cyclone separator venturi tube 100 radially separates the air swirling from the primary cyclone separator impeller 74 and the secondary cyclone separator impeller 84.

[0033] exist Figure 4In this configuration, the hydrocyclone collar plate 91 interfaces with the primary hydrocyclone 70 on its upstream side 112. Various structural embodiments of the hydrocyclone collar plate 91 will be discussed in more detail below. In short, the hydrocyclone collar plate 91 includes an annular cavity 110 (which may also be referred to herein as an "annular pressure drop cavity"), a plurality of inlet orifices 106, and at least one outlet orifice 108. The plurality of inlet orifices 106 provide fluid communication between the pressure chamber 66 and the annular cavity 110, while the at least one outlet orifice provides fluid communication between the annular cavity 110 and the primary hydrocyclone venturi region 102 of the primary hydrocyclone.

[0034] During operation, due to the compression of air by the compressor section, the air 82(a) (also referred to herein as the oxidant) in the pressure chamber 66 is pressurized to a first pressure P1, and a second flow 114 of a portion of the air 82(a) (oxidant) flows from the pressure chamber 66 through multiple inlet orifices 106 into the annular cavity 110 of the hydrocyclone collar plate 91. The second flow 114 through the inlet orifices 106 into the annular cavity 110 causes a first pressure drop ΔP1 from the first pressure P1 to a second pressure P2 lower than the first pressure P1. Therefore, the oxidant within the annular cavity 110 is at the second pressure P2. A third flow 116 of the oxidant contained within the annular cavity 110 then flows through at least one outlet orifice 108 into the venturi region 102 of the primary hydrocyclone. The third flow 116 of the oxidant through at least one outlet orifice 108 causes a second pressure drop ΔP2 from the second pressure P2 to a third pressure P3 lower than the second pressure P2. Therefore, the total pressure drop ΔPT through the hydrocyclone ring plate 91 can be defined as ΔPT = ΔP1 + ΔP2.

[0035] The size, shape, and / or number of the plurality of inlet orifices 106, the size / shape of the annular cavity 110, and the size, shape, and number of at least one outlet orifice 108 can all be configured to obtain desired ΔP1, ΔP2, and ΔPT. In some exemplary embodiments, the arrangement of the plurality of inlet orifices 106 (e.g., size, shape, and number) and the arrangement of the annular cavity 110 (e.g., size and shape) can enable the provision of ΔP1 between 10% and 90% of ΔPT. The arrangement of the annular cavity 110 (e.g., size and shape) and the arrangement of at least one outlet orifice 108 (e.g., size, shape, and number) can enable the provision of ΔP2, which constitutes the remaining percentage of ΔPT.

[0036] Figure 5 A rear perspective view of an exemplary swirler 51 according to aspects of this disclosure is depicted. It is visible that the swirler 51 includes a primary swirler 70, a secondary swirler 72, and a swirler bead plate 91. A fuel nozzle 90, forming part of the swirler assembly 50, is not... Figure 5 As described above. Figure 4The hydrocyclone collar plate 91 is connected to the primary hydrocyclone 70 at the upstream side 112 of the primary hydrocyclone 70. Figure 5 An exemplary inlet orifice 106 in the hydrocyclone ring plate 91 is also depicted. (See image) Figure 5 The exemplary inlet opening 106 shown constitutes a circular opening (i.e., a circular hole), but as will be described in more detail below, the inlet opening 106 may be constructed to have other shapes.

[0037] Figure 6 This is a front perspective view of an exemplary cyclone ring plate 91 according to aspects of this disclosure. Figure 7 Is it like this? Figure 4 The diagram shows a cross-sectional view of an exemplary cyclone separator ring plate 91, taken at detail 7-7. The cyclone separator ring plate 91 includes a rear wall 118 that extends radially outward from the cyclone assembly centerline 69 in the radial direction R and also extends circumferentially around the cyclone assembly centerline 69. A fuel nozzle opening 124 is defined through the rear wall 118. Figure 4 As shown, as part of the cyclone assembly 50, the fuel nozzle 90 is disposed in the fuel nozzle opening 124 of the cyclone ring plate 91. Although the rear wall 118 is described as a generally cylindrical wall, the rear wall 118 is not limited to a cylindrical shape and may instead be other shapes, such as square, rectangular, hexagonal, etc.

[0038] The cyclone ring plate 91 also includes an annular conical wall 120 and an annular cavity wall 122. The annular conical wall 120 extends radially outward from a radially inward portion 128 of the rear wall 118 of the fuel nozzle opening 124, and extends upstream of the radially inward portion 128 at the fuel nozzle opening 124. The annular conical wall also extends circumferentially about the cyclone assembly centerline 69, thereby forming a radially inward conical opening at the upstream end of the fuel nozzle opening 124. The annular cavity wall 122 connects to the radially outward portion 130 of the rear wall 118 and the upstream end 132 of the annular conical wall 120. The annular cavity wall 122 extends circumferentially about the cyclone assembly centerline 69. Therefore, the rear wall 118, the annular conical wall 120, and the annular cavity wall 122 form an annular cavity 110.

[0039] Multiple inlet orifices 106 are formed through the annular cavity wall 122. As discussed above, the inlet orifices 106 provide a second flow of oxidant from the pressure chamber 66 into the annular cavity 110. As mentioned above, the multiple inlet orifices may have different shapes and / or sizes. Figure 6 and 7The inlet orifice 106 shown is generally circular. Alternatively, the inlet orifice 106 may include orifices of other shapes, such as triangular, trapezoidal, elliptical, rectangular, etc. Furthermore, the inlet orifice 106 may be a through-hole, or alternatively, it may be tapered. For example, the inlet orifice 106 may have a smaller size at its outer end (i.e., on the outer side adjacent to the annular wall 122 of the pressure chamber 66) and a larger size at its inner end (i.e., on the inner side adjacent to the annular wall 122 of the annular cavity 110). Alternatively, the inlet orifice 106 may have a larger size at its outer end (i.e., on the outer side adjacent to the annular wall 122 of the pressure chamber 66) and a smaller size at its inner end (i.e., on the inner side adjacent to the annular wall 122 of the annular cavity 110).

[0040] As described above, the number of inlet orifices 106 through the annular cavity wall 122 can vary based on the desired pressure drop ΔP1. Furthermore, the circumferential spacing of the inlet orifices 106 around the annular cavity wall can vary, allowing the inlet orifices 106 to have either a small or large circumferential spacing. The circumferential spacing can also be unequal around the circumference, wherein, for example, the first and second inlet orifices can be circumferentially spaced apart by a first distance, and then the third inlet orifice can be spaced apart from the second inlet orifice by a second distance greater than the first distance.

[0041] exist Figure 7 In the diagram, the inlet orifice 106 is shown as a single row circumferentially around the annular cavity wall 122, wherein this single row is arranged at an axial distance 134 from the rear surface 136 on the downstream side of the rear wall 118. However, the inlet orifice 106 may be arranged in multiple rows circumferentially around the annular cavity wall 122. For example, the inlet orifice 106 may be arranged in two rows circumferentially around the annular cavity wall 122, wherein the first row may be arranged at an axial distance 134, and the second row may be arranged at a second axial distance (not shown), which may be greater than or less than the axial distance 134. Furthermore, the inlet orifices 106 of the first row may be circumferentially staggered with the inlet orifices 106 of the second row.

[0042] You can also see that Figure 7 The hydrocyclone collar plate 91 includes at least one outlet orifice 108. The at least one outlet orifice 108 provides fluid communication between the annular cavity 110 and the primary hydrocyclone venturi region 102. Figure 7 In the middle, multiple outlet orifices 108 are included in the hydrocyclone collar plate 91. Figure 7The outlet orifice 108 is shown as a generally cylindrical hole through the rear wall 118. However, the outlet orifice 108 does not have to be cylindrical; it can instead be other shapes, such as triangular, rectangular, trapezoidal, elliptical, etc. Furthermore, similar to the inlet orifice 106, the outlet orifice 108 can be tapered. For example, the outlet orifice 108 can have a smaller size at the inlet end (i.e., the inlet side of the outlet orifice at the front surface 146 of the rear wall 118) and a larger size at the outlet end (i.e., the outlet side of the outlet orifice at the rear surface 136 of the rear wall 118). Alternatively, the outlet orifice 108 can have a larger size at the inlet end and a smaller size at the outlet end.

[0043] Figure 7 The outlet orifice 108 is shown set at an outlet orifice radial angle 126. The outlet orifice radial angle 126 is shown extending radially inward from the front surface 146 of the rear wall 118 to the rear surface 136 of the rear wall 118. The outlet orifice radial angle 126 is used to provide a third flow of oxidant from the annular cavity 110 into the venturi region 102 of the primary cyclone separator in a radially inward direction toward the tip 94 of the fuel nozzle 90. The outlet orifice radial angle 126 is shown relative to the centerline 69 of the cyclone assembly and can range from 0 degrees (i.e., an outlet orifice aligned axially parallel to the centerline 69 of the cyclone assembly) to 70 degrees.

[0044] Figure 8 This is a rear-view front view of an exemplary cyclone collar plate 91 according to this disclosure. Figure 8 The arrangement of the outlet orifice 108 through the rear surface 136 of the rear wall 118 is depicted. (Brief review) Figure 7 The outlet orifice 108 is shown at an outlet orifice radial angle of 126 relative to the centerline 69 of the hydrocyclone assembly. Figure 7 The outlet orifice 108 shown is in Figure 8 The outlet orifice is indicated by outlet orifice 108(a). However, outlet orifice 108 can also be arranged with an outlet orifice circumferential angle of 138. That is, outlet orifice 108 can be aligned with an outlet orifice radial angle of 126 and an outlet orifice circumferential angle of 138 (see, for example, outlet orifice 108(b)) to provide a third flow of oxidant from the annular cavity 110 to the primary hydrocyclone venturi region 102, radially inside and circumferentially around the hydrocyclone assembly centerline 69. Figure 8 In this configuration, the swirling direction of the outlet orifice 108(b) will be counterclockwise around the centerline 69 of the cyclone assembly. However, the circumferential angle 138 of the outlet orifice can be... Figure 8Conversely, as shown, a third flow of oxidant is provided in a clockwise direction around the centerline 69 of the hydrocyclone assembly. Whether the outlet orifice circumferential angle 138 provides a clockwise or counterclockwise oxidant flow, this direction can be arranged to co-swirl with or with the primary swirling direction 104 of the oxidant provided by the primary hydrocyclone 70 in the primary hydrocyclone venturi region 102 (see...). Figure 4 It is in the direction of the reverse vortex.

[0045] Figure 8 The arrangement of multiple rows of outlet orifices 108 that may be included in the hydrocyclone collar plate 91 is also depicted. For example, a first row 140 and a second row 144 of outlet orifices 108 may be included in the hydrocyclone collar plate 91. The first row 140 of outlet orifices 108 may be arranged circumferentially at a radial distance 142 from the centerline 69 of the hydrocyclone assembly, while the second row 144 of outlet orifices 108 may be arranged at a second radial distance 145 from the centerline 69 of the hydrocyclone assembly. The outlet orifices 108 of the first row 140 may be circumferentially equidistant from each other at an angular distance 152. The outlet orifices 108 of the second row 144 may similarly be circumferentially equidistant from each other at an angular distance 154. Of course, the outlet orifices 108 of the first row 140 or the second row 144 do not need to be circumferentially equidistant and may have different angular distances 152, and the individual outlet orifices 108 within each row may have different angular distances 154. Furthermore, the outlet orifices 108 of the first row 140 can be staggered (i.e., offset) relative to the outlet orifices 108 of the second row 144. For example, using a reference line 148 connecting the center line 69 of the hydrocyclone assembly and the center of one of the outlet orifices 108 of the second row 144 (e.g., the center of outlet orifice 108(a)), the outlet orifices 108 of the first row 140 can be circumferentially offset by an offset angle 150 relative to the outlet orifices 108 of the second row 144.

[0046] Figures 9 to 13 Another arrangement of the outlet orifice 108 according to aspects of this disclosure is depicted. Figure 9 and 10 Is Figure 4 A partial cross-sectional view of an alternative embodiment, taken at detail 9-9. Figure 9 In the middle, the outlet orifice 108 is through an angled hole in the rear wall 118. Figure 4 In contrast, the outlet orifice 108 is shown positioned at the fuel nozzle opening 124 via the rear wall 118. That is, the outlet orifice 108 is formed at the fuel nozzle opening 124 between the fuel nozzle outer surface 156 of the fuel nozzle 90 and the cyclone collar plate 91. Figure 11 In the corresponding Figure 4 plane AA Figure 9A partial cross-sectional view taken at plane 11-11. Figure 11 As can be seen, the outlet orifice 108 of this arrangement is formed as a rectangular outlet orifice, or a groove formed by the fuel nozzle opening 124 of the cyclone ring plate 91. Therefore, the outer surface 156 of the fuel nozzle 90 defines the radially inward portion of the outlet orifice 108. Of course, similar to the previous aspects of this disclosure, the outlet orifice 108 is not limited to a rectangular shape, but can be implemented in other shapes instead. Furthermore, the number, size, and spacing of the rectangular outlet orifices 108 can vary similarly to those described above. Furthermore, although... Figure 11 A plurality of rectangular outlet orifices 108 spaced circumferentially around the fuel nozzle opening 124 are depicted, but a single annular outlet orifice may alternatively be implemented. For example, in Figure 12 middle, Figure 12 Also in response to Figure 4 plane AA Figure 9 A partial cross-sectional view taken at plane 12-12 can be used to replace a single circumferential or annular outlet orifice 168. Figure 11 Multiple outlet ports 108.

[0047] Return to reference Figure 9 To provide fluid communication between the annular cavity 110 and the outlet orifice 108, a channel 158 extending radially inward through a portion of the annular conical wall 120 is included. The radially inward portion of the channel 158 defines a portion of the outlet orifice 108. In this aspect, to provide support for the annular conical wall 120 and seal the front side of the annular cavity 110 in which the channel 158 is formed, a support rib 160 may be included as part of a hydrocyclone ring plate 91. The inner surface 162 of the support rib 160 forms a fuel nozzle opening 124 in which the hydrocyclone ring plate in which the outlet orifice 108 is formed. The support rib 160 may be formed as part of a circumferential annular wall around the centerline 69 of the hydrocyclone assembly in which the outlet orifice 108 is formed. Thus, for this aspect, the flow path for the third flow of oxidant from the annular cavity 110 to the primary hydrocyclone venturi region 102 passes through the channel 158 and then through the outlet orifice 108. Similarly, the size, quantity, and arrangement of the aforementioned flow path elements can be configured to achieve the desired second pressure drop ΔP2. Furthermore, annular outlet orifices can be implemented... Figure 12 In this respect, the channel 158 can form an annular channel around the entire circumference of the fuel nozzle opening 124.

[0048] Figure 10 Another arrangement of the outlet orifice according to aspects of this disclosure is depicted. Figure 10 In some ways, it is similar to Figure 9In this respect, it includes a channel 158 and a support rib 160, but the outlet orifice 108 is not formed through the rear wall 118. Instead, the fuel nozzle 90 includes a fuel nozzle cavity 164 and a fuel nozzle outlet orifice 166 formed in the radially outer portion of the fuel nozzle. The fuel nozzle outlet orifice 166 provides fluid communication between the fuel nozzle cavity 164 and the primary cyclone venturi region 102. As in Figure 13 As seen in the text, Figure 13 In the corresponding Figure 4 plane AA Figure 10 A partial cross-sectional view taken at plane 13-13 shows that multiple fuel nozzle chambers 164 and corresponding fuel nozzle outlet orifices 166 can be provided circumferentially around the fuel nozzle 90. Alternatively, although not depicted in the figure, the fuel nozzle chambers 164 and / or fuel nozzle outlet orifices 166 can be formed as annular fuel nozzle chambers and annular outlet orifices around the entire circumference of the fuel nozzle 90, similar to... Figure 12 As shown in the diagram. In this case, the channel 158 can also be formed around the entire circumference of the fuel nozzle opening 124. Thus, in this aspect, the third flow of oxidant enters the fuel nozzle chamber 164 from the annular cavity 110 through the channel 158, and exits through the fuel nozzle outlet orifice 166 into the primary cyclone venturi tube region 102.

[0049] Another aspect of this disclosure relates to a method of operating the combustor of a gas turbine engine. Figure 14 A flowchart depicting the processing steps of the method of this aspect of the present disclosure is provided. In step 1400, a burner 26 is provided. The burner includes various components, such as (i) a pressure chamber 66 and (ii) a swirler assembly 50, which includes: (a) a swirler 51 having a primary swirler 70 with a primary swirler venturi tube 100; and (b) a swirler collar plate 91 connected to the primary swirler 70 and including a fuel nozzle opening 124 extending therethrough and an annular pressure drop chamber (annular cavity 110). The annular cavity 110 has a plurality of inlet orifices 106 in fluid communication with the pressure chamber 66 and at least one outlet orifice 108 in fluid communication with the primary swirler venturi tube region 102. The swirler assembly 50 also includes a fuel nozzle 90 disposed in the fuel nozzle opening 124 of the swirler collar plate 91. The structure and arrangement of any of the aforementioned burner components may be as described above. Figures 1 to 13 Any structure and arrangement described.

[0050] Once the burner according to this disclosure is provided, the remaining operational processes for operating the burner are performed. It will be readily understood that the following processes of this method are performed via the operation of engine 10. In step 1401, the first stream 113 of oxidant ( Figure 2The oxidant is supplied to the pressure chamber 66, where the first stream 113 of oxidant has a first pressure P1. The process described above involves the engine 10 drawing in air 73, and a portion of the compressor inlet air stream 80 entering the compressor section (22 / 24), where it is compressed. The compressed air 82 is then supplied to the combustor 26 via the diffuser, with a portion of the air 82(a) entering the pressure chamber 66.

[0051] Next, in step 1402, a second stream 114 of oxidant is supplied from the pressure chamber 66 to the annular cavity 110 of the cyclone ring plate 91 via a plurality of inlet orifices 106. Coincidentally, although not in Figure 14 As depicted in the flowchart, however, a portion of the oxidant (pressurized air 82(a)) in the pressure chamber 66 is also supplied to the cyclone 51, wherein the oxidant enters the primary cyclone 70, and the primary cyclone 70 induces swirl in the oxidant flow therethrough to provide a swirling flow 115 of oxidant entering the venturi tube 100 of the primary cyclone in the primary swirling direction 104. Figure 4 Returning to step 1403, the second flow 114 of the oxidant through the inlet orifice 106 to the annular cavity 110 causes a first pressure drop ΔP1 in the second flow 114 of the oxidant in the annular cavity 110 from the first pressure P1 to a second pressure P2 lower than the first pressure (step 1403).

[0052] In step 1404, a third stream 116 of oxidant is supplied from the annular cavity 110 to the primary hydrocyclone venturi region 102 (third stream 116) via at least one outlet orifice 108 of the hydrocyclone collar plate 91. The third stream 116 of oxidant through at least one outlet orifice 108 of the hydrocyclone collar plate 91 causes a second pressure drop ΔP2 in the third stream 116, from the second pressure P2 to a third pressure P3 below the second pressure (step 1405). The first pressure drop ΔP1 and the second pressure drop ΔP2 form a total pressure drop ΔPT through the hydrocyclone collar plate 91. The first pressure drop ΔP1 can provide between 10% and 90% of the total pressure drop ΔPT, while the second pressure drop ΔP2 can provide the remainder of the total pressure drop.

[0053] Next, in step 1406, the third stream 116 of oxidant entering the primary cyclone venturi region 102 is mixed with the swirling stream 115 of oxidant from the primary cyclone 70. The swirling stream 115 of oxidant from the primary cyclone 70, described above, and the oxidant stream (pressurized air 82(a)) swirled by the primary cyclone 70 to generate the swirling stream 115 of oxidant, from the pressure chamber 66 to the primary cyclone 70, can be referred to as the fourth stream 117 providing oxidant from the pressure chamber 66 to the primary cyclone 70. Fuel 92 is also injected into the primary cyclone venturi region 102 of the primary cyclone venturi 100 through the fuel nozzle 90. Fuel 92 is mixed with the third stream 116 of oxidant and the swirling stream 115 of oxidant from the primary cyclone 70 to generate a primary cyclone fuel-air mixture 119. The primary cyclone fuel-air mixture 119 travels through the primary cyclone venturi tube 100 toward the downstream end 99 of the cyclone assembly 50. Then, the primary cyclone fuel-air mixture 119 mixes with the secondary cyclone oxidant 121 from the secondary cyclone 72 in the flare cone 123 downstream of the primary cyclone venturi tube 100. Figure 4 ) are mixed to generate a cyclone assembly fuel-air mixture 85 ( Figure 2 (Step 1407). Then, the fuel-air mixture 85 of the cyclone assembly is ignited in the combustion chamber 62 to form combustion product gas 86 (Step 1408).

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

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

[0056] A swirler assembly for a burner, the swirler assembly defining a centerline therethrough, the swirler assembly comprising: a swirler including a primary swirler having a primary swirler venturi tube; a swirler collar plate connected to an upstream side of the primary swirler and including a fuel nozzle opening extending through it along the centerline of the swirler assembly; and a fuel nozzle disposed in the fuel nozzle opening of the swirler collar plate, the swirler collar plate including: (a) a rear wall extending radially outward from the fuel nozzle opening; and (b) an annular conical wall extending radially inward from the rear wall at the fuel nozzle opening and extending radially outward upstream from the rear wall; and (c) an annular cavity wall connecting the radially outward portion of the rear wall and the upstream end of the annular conical wall, the annular cavity being formed between the rear wall, the annular conical wall and the annular cavity wall, the annular cavity wall including a plurality of inlet orifices therethrough, wherein the hydrocyclone collar plate includes at least one outlet orifice providing fluid communication between the annular cavity and the primary hydrocyclone venturi tube, and wherein the flow of oxidant into the annular cavity through the plurality of inlet orifices causes a first pressure drop from a first pressure in the pressure chamber to a second pressure below the first pressure, and the flow of oxidant into the primary hydrocyclone venturi tube from the annular cavity through the at least one outlet orifice causes a second pressure drop from the second pressure to a third pressure below the second pressure.

[0057] According to any of the preceding clauses, the at least one outlet orifice comprises a plurality of outlet orifices arranged axially through the rear wall relative to the centerline of the hydrocyclone assembly.

[0058] According to any of the foregoing clauses, the at least one outlet orifice comprises a plurality of outlet orifices arranged at a radially inward angle relative to the centerline of the hydrocyclone assembly from an upstream side to a downstream side of the rear wall, so as to guide the flow of the oxidant through therein toward the tip of the fuel nozzle.

[0059] According to any of the foregoing clauses, the primary hydrocyclone has a swirling direction, and the plurality of outlet orifices are further arranged circumferentially at an angle in a co-swirling or anti-swirling direction with respect to the swirling direction of the primary hydrocyclone.

[0060] According to any of the foregoing clauses, the first pressure drop comprises between 10% and 90% of the total pressure drop through the hydrocyclone ferrule plate, and the second pressure drop comprises the remainder of the total pressure drop through the hydrocyclone ferrule plate.

[0061] According to any of the preceding clauses of the cyclone assembly, wherein the at least one outlet orifice comprises a plurality of outlet orifices, each outlet orifice being defined adjacent to the fuel nozzle, wherein the outer surface of the fuel nozzle defines a portion of each outlet orifice.

[0062] According to any of the preceding clauses of the cyclone assembly, wherein the at least one outlet orifice comprises a plurality of outlet orifices, wherein the fuel nozzle comprises a plurality of fuel nozzle chambers on the radially outer portion of the fuel nozzle, each of the plurality of fuel nozzle chambers being in fluid communication with the annular cavity via a corresponding outlet orifice of the plurality of outlet orifices, and wherein each fuel nozzle chamber includes a fuel nozzle outlet orifice providing fluid communication between the fuel nozzle chamber and the primary cyclone venturi tube.

[0063] According to any of the preceding clauses of the cyclone assembly, wherein the at least one outlet orifice includes an annular channel defining the fuel nozzle opening through the cyclone collar plate, and wherein the fuel nozzle includes (i) an annular fuel nozzle cavity in the radially outer portion of the fuel nozzle, the annular fuel nozzle cavity being in fluid communication with the annular cavity via the annular channel, and (ii) at least one fuel nozzle outlet orifice providing fluid communication between the annular fuel nozzle cavity and the primary cyclone venturi tube.

[0064] According to any of the foregoing clauses, the at least one fuel nozzle outlet orifice includes an annular outlet orifice.

[0065] According to any of the foregoing clauses, the at least one outlet orifice comprises multiple rows of outlet orifices arranged circumferentially through the rear wall, each of the multiple rows of outlet orifices being arranged at a different radial distance from the centerline of the hydrocyclone assembly.

[0066] According to any of the preceding clauses, the at least one outlet orifice comprises any one of a circular orifice, a rectangular orifice, a triangular orifice, and a trapezoidal orifice.

[0067] According to any of the preceding clauses of the hydrocyclone assembly, wherein the at least one outlet orifice is tapered from a first dimension at the front surface of the rear wall to a second dimension at the rear surface of the rear wall, the first dimension being different from the second dimension.

[0068] A method of operating a combustor for a gas turbine engine, the combustor comprising (i) a pressure chamber, (ii) a swirler assembly, the swirler assembly comprising (a) a swirler having a primary swirler with a primary swirler venturi tube, and (b) a swirler collar plate connected to the primary swirler and including a fuel nozzle opening extending therethrough and an annular pressure drop chamber having a plurality of inlet orifices in fluid communication with the pressure chamber and at least one outlet orifice in fluid communication with a region of the primary swirler venturi tube, and (iii) a fuel nozzle disposed in the fuel nozzle opening of the swirler collar plate, the method comprising: oxidizing... A first stream of oxidant is provided to the pressure chamber, the first stream of oxidant having a first pressure; a second stream of oxidant is provided from the pressure chamber to the annular pressure drop chamber of the hydrocyclone ring plate via the plurality of inlet orifices of the annular pressure drop chamber, the second stream of oxidant in the annular pressure drop chamber causing a first pressure drop from the first pressure to a second pressure below the first pressure in the stream of oxidant; and a third stream of oxidant is provided from the annular pressure drop chamber to the venturi region of the primary hydrocyclone via at least one outlet orifice of the hydrocyclone ring plate, the third stream of oxidant causing a second pressure drop from the second pressure to a third pressure below the second pressure in the stream of oxidant.

[0069] According to any of the foregoing descriptions, the at least one outlet orifice comprises a plurality of outlet orifices arranged through the rear wall of the hydrocyclone ring plate, and the third flow of the oxidant is directed radially inward from the plurality of outlet orifices toward the tip of the fuel nozzle.

[0070] The method according to any of the foregoing clauses further includes providing a fourth stream of the oxidant from the pressure chamber to the primary cyclone separator, the primary cyclone separator causing a vortex in the primary cyclone direction of the oxidant into the venturi tube of the primary cyclone separator, wherein the plurality of outlet orifices are further arranged to provide a third stream of the oxidant to the venturi tube of the primary cyclone separator in a co-swirling or anti-swirling direction with respect to the primary cyclone direction.

[0071] According to any of the preceding clauses of the method, wherein the first pressure drop comprises between 10% and 90% of the total pressure drop through the hydrocyclone ring plate, and the second pressure drop comprises the remainder of the total pressure drop through the hydrocyclone ring plate.

[0072] According to any of the foregoing clauses of the method, the at least one outlet orifice comprises a plurality of outlet orifices, each outlet orifice being defined at the fuel nozzle opening of the hydrocyclone ferrule plate, and wherein the outer surface of the fuel nozzle forms a radially inward portion of each outlet orifice.

[0073] According to the method of any of the foregoing clauses, wherein the at least one outlet orifice comprises a plurality of outlet orifices, wherein the fuel nozzle comprises a plurality of fuel nozzle chambers, each of the plurality of fuel nozzle chambers being in fluid communication with the annular pressure drop chamber via a corresponding outlet orifice of the plurality of outlet orifices, wherein each fuel nozzle chamber includes a fuel nozzle outlet orifice providing fluid communication between the fuel nozzle chamber and the primary hydrocyclone venturi tube, and wherein a third flow of oxidant is provided from the annular pressure drop chamber to the primary hydrocyclone venturi tube via the fuel nozzle chambers and their respective fuel nozzle outlet orifices.

[0074] According to any of the foregoing clauses of the method, wherein the at least one outlet orifice includes an annular channel defined to open through the fuel nozzle, wherein the fuel nozzle includes (i) an annular fuel nozzle cavity in a radially outer portion of the fuel nozzle, the annular fuel nozzle cavity being in fluid communication with the annular channel, and (ii) at least one fuel nozzle outlet orifice providing fluid communication between the annular fuel nozzle cavity and the primary hydrocyclone venturi tube, and wherein a third flow of oxidant is provided from the annular pressure drop cavity to the primary hydrocyclone venturi tube via the annular channel, the annular fuel nozzle cavity, and the at least one fuel nozzle outlet orifice.

[0075] According to any of the preceding clauses of the method, wherein the at least one fuel nozzle outlet orifice comprises an annular outlet orifice surrounding the radially outer portion of the fuel nozzle.

[0076] While the foregoing description is directed to some exemplary embodiments of this disclosure, it should be noted that other changes and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of this disclosure. Furthermore, features described in connection with one embodiment of this disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A cyclone assembly for a burner, characterized in that, The hydrocyclone assembly defines a centerline passing through it, the hydrocyclone assembly comprising: A hydrocyclone, the hydrocyclone comprising a primary hydrocyclone having a primary hydrocyclone venturi tube; A hydrocyclone collar plate, the hydrocyclone collar plate being connected to the upstream side of the primary hydrocyclone, and including a fuel nozzle opening extending therethrough along the centerline of the hydrocyclone assembly; and A fuel nozzle, wherein the fuel nozzle is disposed in the fuel nozzle opening of the hydrocyclone collar plate. The hydrocyclone collar plate includes: (a) A rear wall that extends radially outward from the fuel nozzle opening; (b) An annular conical wall extending radially inward from the rear wall at the fuel nozzle opening and radially outward upstream from the rear wall; and (c) An annular cavity wall connecting the radially outward portion of the rear wall and the upstream end of the annular conical wall, the annular cavity being formed between the rear wall, the annular conical wall, and the annular cavity wall, the annular cavity wall including a plurality of inlet orifices therethrough. The hydrocyclone collar plate includes at least one outlet orifice providing fluid communication between the annular cavity and the primary hydrocyclone venturi tube, and The flow of oxidant into the annular cavity through the plurality of inlet orifices causes a first pressure drop from a first pressure in the pressure chamber to a second pressure lower than the first pressure, and the flow of oxidant into the venturi tube of the primary hydrocyclone through the at least one outlet orifice from the annular cavity causes a second pressure drop from the second pressure to a third pressure lower than the second pressure. The at least one outlet orifice includes a plurality of outlet orifices, each outlet orifice being defined adjacent to the fuel nozzle, wherein the outer surface of the fuel nozzle defines a portion of each outlet orifice.

2. The hydrocyclone assembly according to claim 1, characterized in that, The at least one outlet orifice further comprises multiple rows of outlet orifices arranged circumferentially through the rear wall, each of the multiple rows of outlet orifices being arranged at a different radial distance from the centerline of the hydrocyclone assembly.

3. The hydrocyclone assembly according to claim 1, characterized in that, The at least one outlet orifice includes any one of a circular orifice, a rectangular orifice, a triangular orifice, and a trapezoidal orifice.

4. The hydrocyclone assembly according to claim 1, characterized in that, The at least one outlet orifice is tapered from a first dimension at the front surface of the rear wall to a second dimension at the rear surface of the rear wall, wherein the first dimension is different from the second dimension.

5. A method for operating the combustor of a gas turbine engine, characterized in that, The burner includes (i) a pressure chamber, (ii) a swirler assembly, the swirler assembly including (a) a swirler having a primary swirler with a primary swirler venturi tube, and (b) a swirler collar plate connected to the primary swirler and including a fuel nozzle opening extending therethrough and an annular pressure drop chamber having a plurality of inlet orifices in fluid communication with the pressure chamber and at least one outlet orifice in fluid communication with a region of the primary swirler venturi tube, and (iii) a fuel nozzle disposed in the fuel nozzle opening of the swirler collar plate, the method comprising: A first stream of oxidant is provided to the pressurized gas chamber, the first stream of oxidant having a first pressure; A second flow of the oxidant is provided from the pressure chamber to the annular pressure drop chamber of the hydrocyclone ring plate via the plurality of inlet orifices of the annular pressure drop chamber. This second flow of the oxidant in the annular pressure drop chamber causes a first pressure drop from the first pressure to a second pressure lower than the first pressure. A third flow of the oxidant is provided from the annular pressure drop chamber to the venturi region of the primary hydrocyclone via at least one outlet orifice of the hydrocyclone ring plate. This third flow of the oxidant causes a second pressure drop in the oxidant flow, from the second pressure to a third pressure lower than the second pressure. The at least one outlet orifice comprises a plurality of outlet orifices, each outlet orifice being defined at the fuel nozzle opening of the hydrocyclone ring plate, and The outer surface of the fuel nozzle forms a radially inward portion of each of the outlet orifices.

6. A cyclone assembly for a burner, characterized in that, The hydrocyclone assembly defines a centerline passing through it, the hydrocyclone assembly comprising: A hydrocyclone, the hydrocyclone comprising a primary hydrocyclone having a primary hydrocyclone venturi tube; A hydrocyclone collar plate, the hydrocyclone collar plate being connected to the upstream side of the primary hydrocyclone, and including a fuel nozzle opening extending therethrough along the centerline of the hydrocyclone assembly; and A fuel nozzle, wherein the fuel nozzle is disposed in the fuel nozzle opening of the hydrocyclone collar plate. The hydrocyclone collar plate includes: (a) A rear wall that extends radially outward from the fuel nozzle opening; (b) An annular conical wall extending radially inward from the rear wall at the fuel nozzle opening and radially outward upstream from the rear wall; and (c) An annular cavity wall connecting the radially outward portion of the rear wall and the upstream end of the annular conical wall, the annular cavity being formed between the rear wall, the annular conical wall, and the annular cavity wall, the annular cavity wall including a plurality of inlet orifices therethrough. The hydrocyclone collar plate includes at least one outlet orifice providing fluid communication between the annular cavity and the primary hydrocyclone venturi tube. The flow of oxidant into the annular cavity through the plurality of inlet orifices causes a first pressure drop from a first pressure in the pressure chamber to a second pressure lower than the first pressure, and the flow of oxidant into the venturi tube of the primary hydrocyclone through the at least one outlet orifice from the annular cavity causes a second pressure drop from the second pressure to a third pressure lower than the second pressure. The at least one outlet orifice includes multiple outlet orifices. The fuel nozzle includes a plurality of fuel nozzle chambers on its radially outer portion, each of the plurality of fuel nozzle chambers being in fluid communication with the annular cavity via a corresponding outlet orifice among the plurality of outlet orifices. Each fuel nozzle chamber includes a fuel nozzle outlet orifice that provides fluid communication between the fuel nozzle chamber and the primary cyclone venturi tube.

7. A cyclone assembly for a burner, characterized in that, The hydrocyclone assembly defines a centerline passing through it, the hydrocyclone assembly comprising: A hydrocyclone, the hydrocyclone comprising a primary hydrocyclone having a primary hydrocyclone venturi tube; A hydrocyclone collar plate, the hydrocyclone collar plate being connected to the upstream side of the primary hydrocyclone, and including a fuel nozzle opening extending therethrough along the centerline of the hydrocyclone assembly; and A fuel nozzle, wherein the fuel nozzle is disposed in the fuel nozzle opening of the hydrocyclone collar plate. The hydrocyclone collar plate includes: (a) A rear wall that extends radially outward from the fuel nozzle opening; (b) An annular conical wall extending radially inward from the rear wall at the fuel nozzle opening and radially outward upstream from the rear wall; and (c) An annular cavity wall connecting the radially outward portion of the rear wall and the upstream end of the annular conical wall, the annular cavity being formed between the rear wall, the annular conical wall, and the annular cavity wall, the annular cavity wall including a plurality of inlet orifices therethrough. The hydrocyclone collar plate includes at least one outlet orifice providing fluid communication between the annular cavity and the primary hydrocyclone venturi tube. The flow of oxidant into the annular cavity through the plurality of inlet orifices causes a first pressure drop from a first pressure in the pressure chamber to a second pressure lower than the first pressure, and the flow of oxidant into the venturi tube of the primary hydrocyclone through the at least one outlet orifice from the annular cavity causes a second pressure drop from the second pressure to a third pressure lower than the second pressure. The at least one outlet orifice includes an annular channel defining the fuel nozzle opening through the cyclone ring plate, and The fuel nozzle includes (i) an annular fuel nozzle cavity in the radially outer portion of the fuel nozzle, the annular fuel nozzle cavity being in fluid communication with the annular cavity via the annular channel, and (ii) at least one fuel nozzle outlet orifice, the at least one fuel nozzle outlet orifice providing fluid communication between the annular fuel nozzle cavity and the primary cyclone venturi tube.

8. The hydrocyclone assembly according to claim 7, characterized in that, The at least one fuel nozzle outlet orifice includes an annular outlet orifice.

9. A method for operating a combustor of a gas turbine engine, characterized in that, The burner includes (i) a pressure chamber, (ii) a swirler assembly, the swirler assembly including (a) a swirler having a primary swirler with a primary swirler venturi tube, and (b) a swirler collar plate connected to the primary swirler and including a fuel nozzle opening extending therethrough and an annular pressure drop chamber having a plurality of inlet orifices in fluid communication with the pressure chamber and at least one outlet orifice in fluid communication with a region of the primary swirler venturi tube, and (iii) a fuel nozzle disposed in the fuel nozzle opening of the swirler collar plate, the method comprising: A first stream of oxidant is provided to the pressurized gas chamber, the first stream of oxidant having a first pressure; A second flow of the oxidant is provided from the pressure chamber to the annular pressure drop chamber of the hydrocyclone ring plate via the plurality of inlet orifices of the annular pressure drop chamber. This second flow of the oxidant in the annular pressure drop chamber causes a first pressure drop from the first pressure to a second pressure lower than the first pressure. A third flow of the oxidant is provided from the annular pressure drop chamber to the venturi region of the primary hydrocyclone via at least one outlet orifice of the hydrocyclone ring plate. This third flow of the oxidant causes a second pressure drop in the oxidant flow, from the second pressure to a third pressure lower than the second pressure. The at least one outlet orifice includes multiple outlet orifices. The fuel nozzle includes multiple fuel nozzle chambers, each of which is in fluid communication with the annular pressure drop chamber via a corresponding outlet orifice among the multiple outlet orifices. Each fuel nozzle chamber includes a fuel nozzle outlet orifice that provides fluid communication between the fuel nozzle chamber and the primary cyclone venturi tube. The third stream of oxidant is provided from the annular pressure drop chamber to the primary cyclone venturi tube via the fuel nozzle chamber and their respective fuel nozzle outlet orifices.

10. A method for operating a combustor of a gas turbine engine, characterized in that, The burner includes (i) a pressure chamber, (ii) a swirler assembly, the swirler assembly including (a) a swirler having a primary swirler with a primary swirler venturi tube, and (b) a swirler collar plate connected to the primary swirler and including a fuel nozzle opening extending therethrough and an annular pressure drop chamber having a plurality of inlet orifices in fluid communication with the pressure chamber and at least one outlet orifice in fluid communication with a region of the primary swirler venturi tube, and (iii) a fuel nozzle disposed in the fuel nozzle opening of the swirler collar plate, the method comprising: A first stream of oxidant is provided to the pressurized gas chamber, the first stream of oxidant having a first pressure; A second flow of the oxidant is provided from the pressure chamber to the annular pressure drop chamber of the hydrocyclone ring plate via the plurality of inlet orifices of the annular pressure drop chamber. This second flow of the oxidant in the annular pressure drop chamber causes a first pressure drop from the first pressure to a second pressure lower than the first pressure. A third flow of the oxidant is provided from the annular pressure drop chamber to the venturi region of the primary hydrocyclone via at least one outlet orifice of the hydrocyclone ring plate. This third flow of the oxidant causes a second pressure drop in the oxidant flow, from the second pressure to a third pressure lower than the second pressure. The at least one outlet orifice includes an annular channel defined as an opening through the fuel nozzle. The fuel nozzle includes (i) an annular fuel nozzle cavity in the radially outer portion of the fuel nozzle, the annular fuel nozzle cavity being in fluid communication with the annular channel, and (ii) at least one fuel nozzle outlet orifice providing fluid communication between the annular fuel nozzle cavity and the primary cyclone venturi tube. The third flow of the oxidant is provided from the annular pressure drop chamber to the primary cyclone venturi tube via the annular channel, the annular fuel nozzle chamber, and the at least one fuel nozzle outlet orifice.

11. The method according to claim 10, characterized in that, The at least one fuel nozzle outlet orifice includes an annular outlet orifice surrounding the radially outer portion of the fuel nozzle.

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