Floating primary impeller hydrocyclone

Abstract

A cyclone assembly includes a primary cyclone having a primary cyclone connection portion, a fuel nozzle connection portion for connecting a fuel nozzle to the primary cyclone, and a primary oxidant flow channel extending at least partially in a longitudinal direction, and a secondary cyclone having a secondary cyclone connection member, wherein the primary cyclone connection portion and the secondary cyclone connection member engage to connect the primary cyclone and the secondary cyclone in a longitudinal direction and allow radial movement of the primary cyclone relative to the secondary cyclone.

Description

Technical Field

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

[0002] Some conventional gas turbine engines are known to include a fuel-rich combustor, which typically uses a swirler integrated with the 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 and a secondary radial swirler, which are interconnected such that the primary and secondary swirlers are substantially connected together in both the axial and radial directions. The fuel nozzle is positioned within the primary swirler and mixes the fuel injected by the fuel nozzle with air swirling radially inward from the tip of the fuel nozzle within the primary swirler. The fuel nozzle positioned within the primary swirler is typically capable of radial movement relative to the primary swirler, resulting in a deflection of the primary swirling air relative to the fuel injected by the fuel nozzle. This deflection leads to uneven fuel distribution within the venturi tube of the secondary swirler. Attached Figure Description

[0003] Features and advantages of this disclosure will become apparent from the following description of various exemplary embodiments, as illustrated in the accompanying drawings, wherein the same reference numerals generally denote the same, functionally similar and / or structurally similar elements.

[0004] Figure 1 This is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine according to one aspect of this disclosure.

[0005] Figure 2 This is a partial cross-sectional side view of an exemplary combustion section according to one aspect of this disclosure.

[0006] Figure 3 This is a partial cross-sectional side view of an exemplary cyclone assembly according to one aspect of this disclosure.

[0007] Figure 4 An exemplary cyclone assembly according to one aspect of this disclosure is in Figure 3 A detailed cross-sectional view taken from point 150.

[0008] Figure 5 This is a partial cross-sectional top view of an exemplary cyclone assembly according to one aspect of this disclosure.

[0009] Figure 6 This is a perspective view of an exemplary primary cyclone assembly according to another aspect of this disclosure.

[0010] Figure 7This is a perspective view of an exemplary secondary cyclone assembly according to one aspect of this disclosure.

[0011] Figure 8 An exemplary cyclone assembly according to another aspect of this disclosure is in Figure 3 A detailed cross-sectional view taken from point 150.

[0012] Figure 9 An exemplary cyclone assembly according to another aspect of this disclosure is in Figure 3 A detailed cross-sectional view taken from point 150.

[0013] Figure 10 An exemplary cyclone assembly according to another aspect of this disclosure is in Figure 3 A detailed cross-sectional view taken from point 150.

[0014] Figure 11 An exemplary cyclone assembly according to another aspect of this disclosure is in Figure 3 A detailed cross-sectional view taken from point 150. Detailed Implementation

[0015] The features, advantages, and embodiments of this disclosure will be apparent or obvious upon consideration of the following detailed description, accompanying drawings, and claims. Furthermore, it should be understood that the following detailed description is exemplary and intended to provide further explanation without limiting the scope of the claimed disclosure.

[0016] Various embodiments are discussed in detail below. Although specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and configurations can be used without departing from the spirit and scope of this disclosure.

[0017] 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.

[0018] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid channel. For example, "upstream" refers to the direction from which fluid flows out, and "downstream" refers to the direction from which fluid flows into.

[0019] In a fuel-rich combustor including radial-radial swirlers, the swirler assembly has a primary swirler and a secondary swirler connected together. The fuel nozzle is connected to a shroud, which in turn is connected to the primary swirler. The primary swirler typically introduces swirling energy radially inward into the primary mixing zone upstream of the venturi tube at the tip of the fuel nozzle. Fuel from the fuel nozzle is injected into the swirling primary airflow in the primary mixing zone. In this conventional system, radial misalignment can occur between the fuel nozzles relative to the primary impeller of the swirler, and the venturi tube introduces non-uniformity in velocity distribution, which can lead to non-uniformity in fuel distribution. This non-uniformity in fuel distribution results in high temperatures in the primary combustion zone, leading to higher NOx emissions. Furthermore, in gas turbines using water injected from the fuel nozzles to reduce NOx emissions, misalignment can cause non-uniform water distribution, resulting in flame extinguishing on one side, leading to higher CO emissions and reduced combustion efficiency.

[0020] This disclosure aims to address the aforementioned problems by limiting the radial movement of the fuel nozzle relative to the primary cyclone, while also allowing radial movement between the components of the cyclone / fuel nozzle assembly. Therefore, this disclosure provides a cyclone assembly in which a floating primary cyclone engages with a secondary cyclone to allow radial movement between the primary and secondary cyclones while maintaining their axial connection. Furthermore, the primary cyclone and fuel nozzle are positioned such that when the fuel nozzle moves radially, the primary cyclone also moves radially with the fuel nozzle. Thus, the primary cyclone, floating with the fuel nozzle, maintains a radial relationship between the fuel injected by the fuel nozzle and the primary airflow from the primary cyclone. Additionally, the radial cyclone is arranged with a flow channel that guides the primary cyclone airflow radially inward not only at the tip of the fuel nozzle but also radially inward at an angle in the downstream direction toward a venturi tube contained within the secondary cyclone. Therefore, the cyclone assembly of this disclosure can provide a more uniform fuel distribution within the venturi tube, thereby reducing NOx and CO emissions.

[0021] 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," which may be incorporated into various embodiments of this disclosure. Although further described below with reference to a ducted turbofan engine, 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. Furthermore, this disclosure is not limited to, for example, Figure 1 The ducted fan type turbine engine shown can be implemented in a ductless fan (UDF) type turbine engine. For example... Figure 1As shown, the engine 10 has an axial central shaft 12 extending through it from an upstream end 98 to a downstream end 99, for reference. Typically, the engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0022] The core engine 16 typically includes a housing 18 defining an annular inlet 20. The housing 18 surrounds or at least partially forms a compressor section having a supercharger or low-pressure (LP) compressor 22, a high-pressure (HP) compressor 24, a combustion section 26 including a high-pressure (HP) turbine 28, a low-pressure (LP) turbine 30, and an injection exhaust nozzle section 32 in a series flow relationship. 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 or gear drive configuration. In other embodiments, although not shown, the engine 10 may also include an intermediate pressure (IP) compressor and a turbine capable of rotating with the intermediate pressure shaft.

[0023] like Figure 1 As shown, the fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from a 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 externally to the core engine 16 to define a bypass airflow passage 48 therebetween.

[0024] Figure 2 An exemplary combustion section 26 according to this disclosure is depicted. Figure 2 In the combustion section 26, therein, a swirler assembly 50, a fuel nozzle assembly 52, a dome assembly 54, a combustion bushing 56, and a fairing 57. The combustion bushing 56 includes an annular outer bushing 58 and an inner bushing 60, forming a combustion chamber 62 therebetween. A pressure chamber 66 is formed within the fairing 57. An outer flow channel 68 is formed between the outer shell 64 and the annular outer bushing 58, and an inner flow channel 69 is formed between the inner shell 65 and the annular inner bushing 60. (Back to Reference) Figure 1During operation, air 73 enters the nacelle 44 at nacelle inlet 76, and a portion of the air 73 enters the compressor section (22 / 24) as compressor inlet airflow 80, where it is compressed. Another portion of the air 73 enters the bypass airflow passage 48, thus providing bypass airflow 78. Figure 2 In the combustion section 26, compressed air 82 from the compressor section (22 / 24) enters via a diffuser (not shown). A portion of the compressed air 82(a) enters the shroud 57 and reaches the pressure chamber 66, while another portion of the compressed air 82(b) passes through the outer flow passage 68 and the inner flow passage 69. As will be described below, the compressed air 82(a) in the pressure chamber 66 passes through the swirler assembly 50, mixes with the fuel injected by the fuel nozzle assembly 52, and is ignited to produce combustion product gases 86.

[0025] Figure 3 A partial cross-sectional view of the cyclone assembly 50 is depicted. The cyclone assembly 50 generally defines a longitudinal direction (L) along the centerline 100 of the cyclone assembly, a radial direction (R) extending outward from the centerline 100 of the cyclone assembly, and a circumferential direction (C) around the centerline 100 of the cyclone assembly. The cyclone assembly 50 includes a primary cyclone 102 and a secondary cyclone 104. A fuel nozzle 106 is disposed within the primary cyclone 102, and a bell 108 is connected to the secondary cyclone 104. The secondary cyclone 104 is suitably connected to the dome assembly 54 and the primary cyclone 102 is connected to the secondary cyclone 104 in a manner that allows the primary cyclone 102 and the fuel nozzle 106 disposed therein to be offset in the radial direction while maintaining a close fit between the primary cyclone 102 and the secondary cyclone 104 in the longitudinal direction.

[0026] The primary cyclone separator 102 is considered to include a primary cyclone section 110, which defines a primary cyclone passage 112 having a plurality of primary cyclone impellers 114 therein. The primary cyclone impellers 114 introduce radial swirl into the air passing through the primary cyclone passage 112. A fuel nozzle connection portion 116 is arranged radially inside the primary cyclone section 110 and configured to connect to a fuel nozzle 106. A primary cyclone separator connection portion 118 is arranged downstream of the primary cyclone section 110 120 and has a primary cyclone separator flow opening 122 passing through it. The primary cyclone connector 118 is configured to allow radial movement (e.g., displacement or movement in the radial direction) between the primary cyclone 102 and the fuel nozzle 106 connected thereto, but maintains a tight longitudinal fit between the primary cyclone 102 and the secondary cyclone 104. The construction of the primary cyclone connector 118 will be discussed in more detail below. The primary cyclone flow opening 122 allows the fuel-air mixture to pass through the primary cyclone 102 to the venturi tube 124 of the secondary cyclone 104. The fuel nozzle connector 116 and the primary cyclone connector 118 define a primary oxidant flow passage 126 between them, which is in fluid communication with the primary cyclone passage 112. The primary oxidant flow passage 126 may extend at least partially in the longitudinal direction (L). For example, as will be described below, the primary oxidant flow channel 126 may have an outlet that guides the airflow longitudinally in the downstream direction, or it may have an outlet that guides the airflow radially inward at an angle to guide the air downstream and inward. Swirling primary air 130 from the primary swirl channel 112 flows through the primary oxidant flow channel 126, such that the swirling primary air 130 mixes with the fuel 128 injected by the fuel nozzle 106. Various configurations of the primary oxidant flow channel 126 will be described below.

[0027] Still refer to Figure 3The secondary cyclone separator 104 includes a secondary cyclone section 132, within which a secondary cyclone channel 134 having a plurality of secondary cyclone impellers 136 is defined. The secondary cyclone separator 104 also includes a secondary annular axial wall 138 extending longitudinally downstream of the secondary cyclone section 132, and a Venturi tube 124 disposed radially inward of the secondary cyclone section 132 and the secondary annular axial wall 138. A secondary oxidant flow channel 140 is defined between the Venturi tube 124 and the secondary cyclone section 132 and the secondary annular axial wall 138. The secondary oxidant flow channel 140 provides an airflow 146 swirled by the secondary cyclone impellers 136 of the secondary cyclone section 132, causing it to flow to the outside of the Venturi tube 124 and into a bell mouth 108, where it mixes with the fuel-air mixture flowing from the Venturi tube 124 into the bell mouth 108. The secondary cyclone 104 also includes a secondary cyclone connecting member 142 disposed on the upstream side 144 of the secondary cyclone 104. The connection between the primary cyclone 102 and the secondary cyclone 104 will be described in more detail below.

[0028] Figure 4 Is Figure 3 A detailed cross-sectional view taken at point 150. Figure 4 In this configuration, the primary swirling section 110 is considered to include a first primary swirling section radial wall 152, a second primary swirling section radial wall 154 downstream of the first primary swirling section radial wall 152, and a plurality of primary swirling impellers 114 connecting the first and second primary swirling section radial walls 152 and 154. The first and second primary swirling section radial walls 152 and 154 extend circumferentially around the centerline 100 of the swirler assembly. The plurality of primary swirling impellers 114 extend circumferentially around the centerline 100 of the swirler assembly. Figure 3 The circumferentially spaced and arranged to introduce swirls into the air flowing through the primary swirl channel 112.

[0029] The fuel nozzle connection portion 116 includes an annular fuel nozzle wall 156 extending radially between the fuel nozzle opening 158 and the radial wall 152 of the first primary swirl portion, and includes a radially inner portion 160 of the fuel nozzle wall extending downstream relative to the radial wall 152 of the first primary swirl portion. The upstream surface 162 of the primary oxidant flow passage 126 is defined by the radially outer surface 164 of the radially inner portion 160 of the fuel nozzle wall.

[0030] The primary cyclone connector 118 has a primary cyclone connector radial wall 166, which has a primary cyclone connector radial wall opening 177 passing through it, which at least partially defines the primary cyclone flow opening 122. For example... Figure 4As shown, the opening 177 of the primary cyclone connection radial wall 166, passing through the primary cyclone connection radial wall, may have a tapered surface 178 having a tapered profile extending radially outward in the downstream direction relative to the cyclone assembly centerline 100. The angle 180 of the tapered surface 178 relative to the cyclone assembly centerline 100 may be in the range of, for example, thirty to seventy degrees. The primary cyclone connection radial wall 166 also includes a primary cyclone connection connecting wall 168 that connects the radially inner portion 170 of the primary cyclone connection radial wall 166 and the second primary cyclone connection radial wall 154 to define a primary cyclone connection gap 172 between the downstream surface 173 of the second primary cyclone connection radial wall 154 and the upstream surface 175 of the primary cyclone connection radial wall 166. The radial inner surface 174 of the connecting wall 168 of the primary cyclone separator defines the downstream surface 176 of the primary oxidant flow channel 126.

[0031] The secondary swirl section 132 includes a first-stage swirl section radial wall 182 on its upstream side and a second-stage swirl section radial wall 184 on its downstream side. A plurality of secondary swirler blades 136 extend and connect between the first-stage and second-stage swirl section radial walls 182 and 184. Similar to the primary swirl blades 114, the secondary swirl blades 136 are circumferentially spaced around the swirl assembly centerline 100 and arranged to introduce swirls into the air flowing through the secondary swirl channel 134.

[0032] Now refer to Figures 5 to 7 An exemplary connection between the primary cyclone separator 102 and the secondary cyclone separator 104 is described. Figure 5 It is similar to Figure 3 A partial cross-sectional view of the hydrocyclone assembly 50, but the hydrocyclone assembly 50 is rotated 90 degrees around the hydrocyclone assembly centerline 100. Figure 6 This is a perspective view of the downstream side of the primary hydrocyclone 102. Figure 7 This is a perspective view of the upstream side of the secondary cyclone separator 104. Figure 5 and Figure 6In the diagram, the primary cyclone connector 118 is shown as having a primary cyclone connector radial wall 166, which is essentially an annular wall extending circumferentially around the centerline 100 of the cyclone assembly. A primary cyclone connector gap 172 is disposed between the primary cyclone connector radial wall 166 and the second primary cyclone connector radial wall 154. Of course, the primary cyclone connector radial wall 166 does not need to extend a full 360 degrees around the centerline 100 of the cyclone assembly; other arrangements can be implemented, provided that at least a portion of the primary cyclone connector radial wall 166 engages with the secondary cyclone connector 142.

[0033] refer to Figure 5 and Figure 7 As described above, the secondary cyclone connecting member 142 is disposed on the upstream side 144 of the secondary cyclone 104. Figure 7 In one aspect shown, the secondary cyclone connector 142 is illustrated as comprising a plurality of supports 192 and a retaining member 194 connected to the plurality of supports 192. The retaining member 194 is configured to be mounted within a primary cyclone connector gap 172 within a primary cyclone connector portion 118. The height 196 of the supports 192 may be slightly greater than the thickness 198 of the radial wall 166 of the primary cyclone connector portion in order to engage the downstream surface 188 of the radial wall 166 of the primary cyclone connector portion with the upstream surface 190 of the radial wall 182 of the primary cyclone connector portion, providing a tight fit between the downstream surface 188 and the upstream surface 190, but still loose enough to allow the primary cyclone 102 to be radially offset relative to the secondary cyclone 104. Furthermore, the distance 206 from the centerline 100 of the hydrocyclone assembly to the radially outer surface 202 of the radial wall 166 of the primary hydrocyclone connection portion, and the distance 208 from the centerline 100 of the hydrocyclone assembly to the inner surface 200 of the support 192, can be configured to form a gap 204 between the inner surface 200 and the radially outer surface 202 to allow radial movement of the primary hydrocyclone 102 relative to the secondary hydrocyclone 104. The gap 204 can be sized such that the inner surface 200 of the support 192 acts as a radial stop, thereby limiting the radial offset of the primary hydrocyclone 102 relative to the secondary hydrocyclone 104.

[0034] refer to Figure 4 and Figure 8 Describe the various arrangements of the primary oxidant flow channel 126. (See also...) Figure 4As can be seen, the primary oxidant flow channel 126 includes an inlet end 210 and an outlet end 212. The inlet end 210 of the primary oxidant flow channel 126 extends radially inward toward the hydrocyclone assembly centerline 100, and the outlet end 212 of the primary oxidant flow channel 126 extends downstream in the longitudinal direction, forming an angle 216 with respect to the radial direction (R) and radially inward toward the hydrocyclone assembly centerline 100. In some aspects, the angle 216 can range from fifty degrees to one hundred and fifty degrees. When the angle 216 is ninety degrees, the outlet end 212 of the primary oxidant flow channel 126 extends downstream in the longitudinal direction (e.g., parallel to the hydrocyclone assembly centerline 100). Figure 4 As shown, the fuel nozzle tip 240 of the fuel nozzle 106 is aligned downstream in the longitudinal direction of the primary swirl channel 112, and the outlet end 212 of the primary oxidant flow channel 126 is substantially aligned with the fuel nozzle tip 240. This arrangement sets the primary swirl airflow from the primary swirl channel 112 closer to the fuel nozzle tip 240, where fuel 128 is injected. Furthermore, since the fuel nozzle 106 moves together with the primary swirler 102, a more uniform swirl fuel-air mixture can be obtained within the primary swirler 102. Therefore, the non-uniformity of velocity distribution within the venturi tube, which leads to uneven fuel distribution, can be reduced. Additionally, the high-temperature zone in the primary combustion zone that may result in higher NOx emissions can be reduced or eliminated. Furthermore, if water is injected from the fuel nozzle to reduce NOx, the non-uniformity of water distribution, which causes high flame extinguishing on one side, resulting in higher CO emissions and lower combustion efficiency, will be reduced.

[0035] exist Figure 4 As shown, the upstream surface 162 of the primary oxidant flow channel may be formed with a concave curved profile, while the downstream surface 176 of the primary oxidant flow channel may be formed with a convex curved profile. Alternatively, the conical surface 218 of the downstream surface 176 of the primary oxidant flow channel may be formed as a conical surface, and the conical surface 220 of the upstream surface 162 of the primary oxidant flow channel may be formed as a conical surface. In one aspect, the height 214 of the primary oxidant flow channel 126 may have a constant height over its entire length. In another aspect, the upstream surface 162 and the downstream surface 176 of the primary oxidant flow channel may have constant regions relative to each other. Alternatively, the upstream surface 162 and the downstream surface 176 of the primary oxidant flow channel may have divergent regions relative to each other, or they may have convergent regions relative to each other.

[0036] Figure 8 The arrangement of the primary oxidant flow channels according to another aspect of this disclosure is depicted. Figure 8In this arrangement, the downstream end 222 of the radially inner portion 160 of the fuel nozzle wall is truncated in the upstream direction to define a position relative to the centerline 100 of the cyclone assembly. Figure 5 The truncated downstream end surface 224 extends radially outward. Furthermore, although... Figure 4 The arrangement can be described as conical surfaces 178 and 218 forming vertex 226, as shown. Figure 8 As shown, however, vertex 226 can be truncated such that the radially inner surface 228 of the primary cyclone connection portion 118 forms a horizontal surface that extends in the longitudinal direction relative to the centerline 100 of the cyclone assembly.

[0037] Additional features of the primary cyclone separator 102 will now be referenced. Figure 9 and Figure 10 Describe it. In Figure 9 As can be seen, the primary cyclone connector 118 includes a plurality of primary purge orifices 230. The primary purge orifices 230 extend from the primary cyclone connector gap 172 through the conical surface 178 and can extend tangentially to the conical surface 178. That is, the primary purge orifices 230 can be arranged to provide an airflow from the primary cyclone connector gap 172 that flows circumferentially around the conical surface 178 and is tangential to the conical surface 178. Figure 10 The arrangement of the primary purge orifice 238 according to another aspect of this disclosure is depicted. Figure 10 In the primary cyclone connector radial wall 166, an annular recess 232 is included in a conical surface 178, extending partially between the conical surface 178 and the radially outer end 236 of the primary cyclone connector radial wall 166. A primary purge orifice 238 extends through the primary cyclone connector radial wall 166 to the annular recess 232 to provide purge airflow from the primary cyclone connector gap 172 to the annular recess 232. Similar to... Figure 9 The primary purge orifice 230 and primary purge orifice 238 can be tangentially arranged to provide a tangential flow of purge air around the circumference of the annular recess 232. The depth 234 of the annular recess 232 can be set based on the size of the primary purge orifice 238, and the required amount of airflow can be provided from the annular recess 232.

[0038] Figure 11 Another aspect of the cyclone assembly 50 according to this disclosure is depicted. Figure 11 In this context, the primary cyclone separator 102 can correspond to any of the above aspects, and the main difference lies in the arrangement of the secondary cyclone separator 104. Figure 11As can be seen, the secondary cyclone 104 includes an intermediate cyclone 242 connected to the upstream surface 190 of the secondary cyclone 104. The intermediate cyclone 242 may include an intermediate cyclone radial wall 244, which is located around the centerline 100 of the cyclone assembly. Figure 5 A circumferentially extending annular wall includes an intermediate cyclone radial wall opening 250 passing through it, such that the intermediate cyclone 242 is in fluid communication with the venturi tube 124. A plurality of intermediate cyclone blades 246, similar to the primary cyclone blades 114, are disposed between the intermediate cyclone radial wall 244 and the first-stage cyclone radial wall 182, forming an intermediate cyclone flow channel 252 passing through it. The intermediate cyclone blades 246 introduce swirl into the airflow passing through the intermediate cyclone flow channel 252, thereby providing a circumferentially swirling airflow within the intermediate cyclone radial wall opening 250 at the upstream end of the venturi tube 124. The swirl direction of the intermediate cyclone blades 246 may be the same as that of the primary cyclone blades 114. Although Figure 11 Not shown, but the secondary cyclone connecting member 142 is provided at the upstream surface 248 of the intermediate cyclone radial wall 244. Figure 11 The secondary cyclone connector 142 can be connected to the above-mentioned secondary cyclone connector. Figure 3 and Figure 4 The aspects described are the same.

[0039] exist Figure 11 The aspect includes an intermediate swirler 242, which, in order to better mix the fuel with the primary swirling airflow 254 from the primary oxidant flow channel 126 and the intermediate swirling airflow 256 from the intermediate swirler 242, allows the fuel nozzle 106 to be further offset downstream when it is mounted in the primary swirler 102. For example, the fuel nozzle 106 can be further offset downstream such that the fuel nozzle tip 240 is substantially aligned with the upstream surface 248 of the radial wall of the intermediate swirler.

[0040] 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.

[0041] Further aspects of the invention are provided by way of the subject matter of the following clauses:

[0042] A swirler assembly for a gas turbine engine, the swirler assembly comprising: a primary swirler, the primary swirler including: (a) a primary swirling portion defining a primary swirling passage having a plurality of primary swirling blades therein; (b) a fuel nozzle connection portion disposed radially inward of the primary swirling portion and having a fuel nozzle opening therethrough, the fuel nozzle opening being configured to engage with a fuel nozzle; and (c) a primary swirler connection portion disposed downstream of the primary swirling portion and having a primary swirler flow opening therethrough, wherein the fuel... A nozzle connection portion and the primary cyclone connection portion define a primary oxidant flow channel therebetween, the primary oxidant flow channel being in fluid communication with the primary cyclone channel, the primary oxidant flow channel extending at least partially in the longitudinal direction; and a secondary cyclone, the secondary cyclone including (a) a venturi tube, and (b) a secondary cyclone connection member disposed on the upstream side of the secondary cyclone, wherein the primary cyclone connection portion and the secondary cyclone connection member engage to engage the primary cyclone and the secondary cyclone in the longitudinal direction and allow radial movement of the primary cyclone relative to the secondary cyclone.

[0043] According to any hydrocyclone assembly in the preceding paragraph, wherein the hydrocyclone assembly defines a hydrocyclone assembly centerline passing through it, a longitudinal direction along the hydrocyclone assembly centerline, a radial direction extending outward from the hydrocyclone assembly centerline, and a circumferential direction around the hydrocyclone assembly centerline, and the secondary hydrocyclone further includes (c) a secondary swirling portion defining a secondary swirling channel having a plurality of secondary swirling blades therein, and (d) a secondary annular axial wall extending downstream of the secondary swirling portion in the longitudinal direction, the venturi tube being arranged radially inside the secondary swirling portion and the secondary annular axial wall, and a secondary oxidant flow channel being defined between the venturi tube, the secondary swirling portion, and the secondary annular axial wall.

[0044] According to any hydrocyclone assembly in the preceding paragraph, the primary oxidant flow channel extends radially inward at the inlet end of the primary oxidant flow channel and extends downstream in the longitudinal direction at the outlet end of the primary oxidant flow channel.

[0045] According to any hydrocyclone assembly in the preceding paragraph, wherein the primary oxidant flow channel extends radially inward at the inlet end of the primary oxidant flow channel and extends radially inward at an angle relative to the radial direction in the longitudinal direction at the outlet end of the primary oxidant flow channel.

[0046] According to any cyclone assembly in the preceding paragraph, the angle has a range from fifty degrees to one hundred and fifty degrees between the radial direction and the longitudinal direction.

[0047] According to any hydrocyclone assembly in the preceding paragraph, the primary hydrocyclone flow opening of the primary hydrocyclone connection portion is in fluid communication with the venturi tube of the secondary hydrocyclone.

[0048] According to any cyclone assembly in the preceding paragraph, the fuel nozzle connection portion is configured to connect to the fuel nozzle such that the tip of the fuel nozzle is positioned downstream of the primary cyclone passage in the primary cyclone portion.

[0049] According to any cyclone assembly under the preceding clause, wherein the primary cyclone portion comprises: (i) a first primary cyclone portion radial wall, (ii) a second primary cyclone portion radial wall downstream of the first primary cyclone portion radial wall, and (iii) a primary cyclone impeller connecting the first and second primary cyclone portion radial walls, the fuel nozzle connection portion comprising an annular fuel nozzle wall extending radially between the fuel nozzle opening and the first primary cyclone portion radial wall, and including a radially inner portion of the fuel nozzle wall downward relative to the first primary cyclone portion radial wall. The primary oxidant flow channel is further defined by the radially outer surface of the radially inner portion of the fuel nozzle wall, and the primary cyclone connection includes a primary cyclone connection radial wall having a primary cyclone flow opening therethrough, and includes a connecting wall connecting the radially inner portion of the primary cyclone connection radial wall and the second primary cyclone radial wall to define a primary cyclone connection gap between the second primary cyclone radial wall and the primary cyclone connection radial wall, the radially inner surface of the connecting wall defining the downstream surface of the primary oxidant flow channel.

[0050] According to any hydrocyclone assembly in the preceding paragraph, wherein the secondary hydrocyclone portion includes a primary hydrocyclone portion radial wall on the upstream side of the secondary hydrocyclone, and the secondary hydrocyclone connecting member is disposed on the upstream surface of the primary hydrocyclone portion radial wall and configured to engage the primary hydrocyclone connecting portion radial wall to engage the downstream surface of the primary hydrocyclone connecting portion radial wall with the upstream surface of the primary hydrocyclone portion radial wall.

[0051] According to any hydrocyclone assembly in the preceding paragraph, the primary oxidant flow channel has a constant height between the upstream surface of the primary oxidant flow channel and the downstream surface of the primary oxidant flow channel.

[0052] According to any hydrocyclone assembly in the preceding paragraph, the upstream surface of the primary oxidant flow channel and the downstream surface of the primary oxidant flow channel have constant regions relative to each other.

[0053] According to any cyclone assembly in the preceding paragraph, the upstream surface of the primary oxidant flow channel and the downstream surface of the primary oxidant flow channel have divergent regions relative to each other, or convergent regions relative to each other.

[0054] According to any cyclone assembly in the preceding paragraph, the downstream end of the radially inner portion of the fuel nozzle wall includes a truncated downstream end surface extending radially outward relative to the centerline of the cyclone assembly, and the connecting wall of the primary cyclone connecting portion has an inner surface extending in the longitudinal direction relative to the centerline of the cyclone assembly.

[0055] According to any cyclone assembly in the preceding paragraph, wherein the primary cyclone connection gap is defined between an upstream surface of the radial wall of the primary cyclone connection and a downstream surface of the radial wall of the second primary cyclone connection, and the secondary cyclone connection member includes a plurality of retaining members disposed in the primary cyclone connection gap.

[0056] According to any of the hydrocyclone components in the preceding paragraph, the upstream surface of the primary oxidant flow channel has a concave curved profile, and the downstream surface of the primary oxidant flow channel has a convex curved profile.

[0057] According to any hydrocyclone assembly in the preceding paragraph, the upstream surface of the primary oxidant flow channel has a tapered profile at the outlet end of the primary oxidant flow channel, and the downstream surface of the primary oxidant flow channel has a tapered profile at the outlet end of the primary oxidant flow channel.

[0058] According to any cyclone assembly in the preceding paragraph, wherein the primary cyclone connection radial wall includes a primary cyclone connection radial wall opening therethrough, the primary cyclone connection radial wall opening partially defining the primary cyclone flow opening, the primary cyclone connection radial wall opening defining a tapered surface extending radially outward in a downstream direction relative to the centerline of the cyclone assembly.

[0059] According to any cyclone assembly in the preceding paragraph, wherein the radial wall of the primary cyclone connection portion includes an annular recess extending partially between the conical surface and the radially outer end of the radial wall of the primary cyclone connection portion, and the primary cyclone connection portion includes a plurality of primary purge orifices extending through the radial wall of the primary cyclone connection portion to the annular recess.

[0060] According to any cyclone assembly in the preceding paragraph, wherein the primary cyclone connection portion includes a plurality of primary purge orifices extending from the primary cyclone connection portion gap through the conical surface of the radial wall opening of the primary cyclone connection portion, and the plurality of primary purge orifices are arranged to provide a tangential flow of oxidant around the circumference of the conical surface of the radial wall of the primary cyclone connection portion.

[0061] The secondary cyclone further includes an intermediate cyclone disposed on the upstream surface of the secondary cyclone section, the intermediate cyclone being in fluid communication with the venturi tube, and the secondary cyclone connecting member being disposed on the upstream surface of the intermediate cyclone, and the primary cyclone providing at least partially a primary flow of oxidant from the primary oxidant flow channel in the longitudinal direction, and the intermediate cyclone providing a radially inward flow of oxidant in the radial direction.

[0062] While 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 can be made without departing from the spirit or scope of the present disclosure. Furthermore, features described in connection with one embodiment of the present disclosure can be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A cyclone assembly for a gas turbine engine, characterized in that, The cyclone assembly includes: A primary cyclone separator, comprising: (a) a primary cyclone portion defining a primary cyclone channel having a plurality of primary cyclone impellers therein; (b) a fuel nozzle connection portion disposed radially inward of the primary cyclone portion and having a fuel nozzle opening therethrough, the fuel nozzle opening being configured to engage a fuel nozzle; and (c) a primary cyclone separator connection portion disposed downstream of the primary cyclone portion and having a primary cyclone separator flow opening therethrough, the fuel nozzle connection portion and the primary cyclone separator connection portion defining a primary oxidant flow channel therebetween, the primary oxidant flow channel being in fluid communication with the primary cyclone channel, the primary oxidant flow channel extending at least partially in a longitudinal direction; and A secondary hydrocyclone, comprising (a) a venturi tube and (b) a secondary hydrocyclone connecting member disposed on the upstream side of the secondary hydrocyclone. The primary cyclone connector and the secondary cyclone connector engage to join the primary and secondary cyclones in the longitudinal direction, and to allow radial movement of the primary cyclone relative to the secondary cyclone. The cyclone assembly defines a centerline passing through it, a longitudinal direction along the centerline, a radial direction extending outward from the centerline, and a circumferential direction around the centerline. The secondary cyclone further includes (c) a secondary cyclone section defining a secondary cyclone channel having a plurality of secondary cyclone impellers, and (d) a secondary annular axial wall extending downstream of the secondary cyclone section in the longitudinal direction. The venturi tube is arranged radially inside the secondary cyclone section and the secondary annular axial wall. A secondary oxidant flow channel is defined between the venturi tube, the secondary cyclone section, and the secondary annular axial wall. The primary swirling section includes: (i) a first primary swirling section radial wall, (ii) a second primary swirling section radial wall downstream of the first primary swirling section radial wall, and (iii) a primary swirling impeller connecting the first primary swirling section radial wall and the second primary swirling section radial wall. The fuel nozzle connection portion includes an annular fuel nozzle wall extending radially between the fuel nozzle opening and the radial wall of the first primary swirl portion, and includes a radially inner portion extending downstream relative to the radial wall of the first primary swirl portion. The upstream surface of the primary oxidant flow channel is defined by the radially outer surface of the radially inner portion of the fuel nozzle wall. The primary cyclone connection portion includes a primary cyclone connection portion radial wall having a primary cyclone flow opening therethrough and including a connecting wall connecting a radially inner portion of the primary cyclone connection portion radial wall and a second primary cyclone portion radial wall to define a primary cyclone connection portion gap between the second primary cyclone portion radial wall and the primary cyclone connection portion radial wall, the radially inner surface of the connecting wall defining a downstream surface of the primary oxidant flow channel.

2. The hydrocyclone assembly according to claim 1, characterized in that, The primary oxidant flow channel extends radially inward at its inlet end and extends downstream in the longitudinal direction at its outlet end.

3. The hydrocyclone assembly according to claim 1, characterized in that, The primary oxidant flow channel extends radially inward at its inlet end and extends radially inward at an angle relative to the radial direction in the longitudinal direction at its outlet end.

4. The hydrocyclone assembly according to claim 3, characterized in that, The angle therein has a range of 50 to 150 degrees between the radial direction and the longitudinal direction.

5. The hydrocyclone assembly according to claim 1, characterized in that, The primary hydrocyclone connection portion of the primary hydrocyclone has a flow opening that is in fluid communication with the venturi tube of the secondary hydrocyclone.

6. The hydrocyclone assembly according to claim 1, characterized in that, The fuel nozzle connection portion is configured to connect to the fuel nozzle such that the tip of the fuel nozzle is positioned downstream of the primary swirl channel in the primary swirl portion.

7. The hydrocyclone assembly according to claim 1, characterized in that, The secondary swirling portion includes a first-stage swirling portion radial wall on the upstream side of the secondary swirling device. The secondary swirling device connecting member is disposed on the upstream surface of the first-stage swirling portion radial wall and configured to engage the primary swirling device connecting portion radial wall to engage the downstream surface of the primary swirling device connecting portion radial wall with the upstream surface of the first-stage swirling portion radial wall.

8. The hydrocyclone assembly according to claim 1, characterized in that, The primary oxidant flow channel has a constant height between its upstream surface and its downstream surface.

9. The hydrocyclone assembly according to claim 1, characterized in that, The upstream surface of the primary oxidant flow channel and the downstream surface of the primary oxidant flow channel have a constant region relative to each other.

10. The hydrocyclone assembly according to claim 1, characterized in that, The upstream surface of the primary oxidant flow channel and the downstream surface of the primary oxidant flow channel have divergent regions relative to each other, or convergent regions relative to each other.

11. The cyclone assembly according to claim 1, characterized in that, The downstream end of the radially inner portion of the fuel nozzle wall includes a truncated downstream end surface that extends radially outward relative to the centerline of the cyclone assembly, and the connecting wall of the primary cyclone connection portion has an inner surface that extends in the longitudinal direction relative to the centerline of the cyclone assembly.

12. The cyclone assembly according to claim 1, characterized in that, The primary cyclone connection gap is defined between the upstream surface of the radial wall of the primary cyclone connection and the downstream surface of the radial wall of the second primary cyclone, and the secondary cyclone connection member includes a plurality of retaining members disposed in the primary cyclone connection gap.

13. The hydrocyclone assembly according to claim 1, characterized in that, The upstream surface of the primary oxidant flow channel has a concave curved profile, and the downstream surface of the primary oxidant flow channel has a convex curved profile.

14. The hydrocyclone assembly according to claim 1, characterized in that, The upstream surface of the primary oxidant flow channel has a tapered profile at the outlet end of the primary oxidant flow channel, and the downstream surface of the primary oxidant flow channel has a tapered profile at the outlet end of the primary oxidant flow channel.

15. The hydrocyclone assembly according to claim 1, characterized in that, The primary cyclone connector radial wall includes a primary cyclone connector radial wall opening therethrough, the primary cyclone connector radial wall opening partially defining the primary cyclone flow opening, the primary cyclone connector radial wall opening being a tapered opening extending radially outward in the downstream direction relative to the centerline of the cyclone assembly.

16. The hydrocyclone assembly according to claim 15, characterized in that, The primary cyclone connector radial wall includes an annular recess extending partially between the conical opening and the radially outer end of the primary cyclone connector radial wall. The primary cyclone connector includes a plurality of primary purge orifices extending through the radial wall of the primary cyclone connector to the annular recess.

17. The hydrocyclone assembly according to claim 15, characterized in that, The primary cyclone connection portion includes a plurality of primary purge orifices extending from the gap of the primary cyclone connection portion through the conical opening of the radial wall opening of the primary cyclone connection portion, and the plurality of primary purge orifices are arranged to provide a tangential flow of oxidant around the circumference of the conical opening of the radial wall of the primary cyclone connection portion.

18. The hydrocyclone assembly according to claim 1, characterized in that, The secondary cyclone further includes an intermediate cyclone disposed on the upstream surface of the secondary cyclone section, the intermediate cyclone being in fluid communication with the venturi tube, and the secondary cyclone connecting member being disposed on the upstream surface of the intermediate cyclone. The primary cyclone separator provides at least a partial primary flow of oxidant from the primary oxidant flow channel in the longitudinal direction, and the intermediate cyclone separator provides a radially inward flow of oxidant in the radial direction.

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