Cyclone separator for gas turbine engine

Abstract

A cyclonic separator for a gas turbine engine includes a housing, a fluid inlet, a first fluid outlet, a second fluid outlet, and a particulate separator. The housing includes a first end, a second end, and an outer wall extending between the first end and the second end. A fluid inlet is disposed at a first end of the housing. A first fluid outlet is disposed at the second end of the housing. The second fluid outlet is disposed in an outer wall downstream of the first end of the housing and extends at least partially outward in the radial direction. A particle separator is disposed in the housing between the first end and the second end, inside the outer wall in the radial direction, and extending in the circumferential direction. The particle separator defines a plurality of openings extending in a radial direction.

Description

Technical Field

[0001] The present disclosure relates to a gas turbine engine, and more particularly to a cyclone separator for a gas turbine engine. Background Art

[0002] A turbine engine, particularly a gas or combustion turbine engine, is a rotary engine that extracts energy from the combustion gases flowing through the engine onto a plurality of turbine blades. Gas turbine engines have been used for land and marine sports and power generation, but are most commonly used in aviation applications, such as aircraft. In aircraft, gas turbine engines are used to propel the aircraft. In land-based applications, turbine engines are typically used to generate electricity.

[0003] Aircraft gas turbine engines are designed to operate at high temperatures to maximize engine efficiency, necessitating cooling of certain engine components, such as the high-pressure and low-pressure turbines. Typically, this cooling is achieved by delivering cooler air from the high-pressure and / or low-pressure compressors to the engine components requiring cooling. Although compressor air is supplied at a higher temperature, it is relatively cooler than turbine air and can therefore be used to cool the turbine. When cooling the turbine, the cooling air is supplied to various turbine components, including the interior of the turbine blades and the turbine shroud. BRIEF DESCRIPTION OF THE DRAWINGS

[0004] A full and enabling disclosure of the present disclosure, including the best mode thereof, is set forth to those skilled in the art in the specification with reference to the accompanying drawings, in which:

[0005] Figure 1 is a cross-sectional view of an exemplary gas turbine engine.

[0006] Figure 2 yes Figure 1 Cross-sectional view of the cooling circuit of a gas turbine engine.

[0007] Figures 3A-3B yes Figure 2 Side and axial views of the cyclone separator of the cooling circuit.

[0008] Figure 4 yes Figures 3A-3B Side view of the particle separator of a cyclone separator.

[0009] Figures 5A-5F yes Figure 4 Enlarged view of an exemplary arrangement of openings of a particle separator.

[0010] Figures 6A-6E is a cross-sectional view of a particle separator with protrusions.

[0011] Figures 7A-7Cis a cross-sectional view of another exemplary particle separator of a cyclone separator.

[0012] Figure 8 is another exemplary cyclone separator for use in a cooling circuit. DETAILED DESCRIPTION

[0013] Reference will now be made in detail to the present embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. The same or similar designations in the drawings and the description have been used to refer to the same or similar parts of the present disclosure.

[0014] As used herein, the word "exemplary" means "serving as an example, instance, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Furthermore, unless expressly stated otherwise, all embodiments described herein should be considered exemplary.

[0015] The singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise.

[0016] For example, the term "at least one" in the context of "at least one of A, B, and C" refers to A alone, B alone, C alone, or any combination of A, B, and C.

[0017] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of each component.

[0018] The terms "upstream" and "downstream" refer to relative directions relative to the flow of a fluid. For example, "upstream" refers to the direction from which the fluid is flowing, while "downstream" refers to the direction toward which the fluid is flowing.

[0019] The present disclosure generally relates to removing particulate matter from the airflow of a gas turbine engine. Air flowing through the engine to cool various components of the gas turbine engine can accumulate particulate matter. Particulate matter (e.g., dirt, dust, sand, ash, and other environmental contaminants) in the cooling air can cause cooling loss and reduce operating time in an aircraft environment. Particulate matter supplied to turbine components can clog, obstruct, or coat component flow passages and surfaces, thereby shortening component service life.

[0020] To reduce the amount of particulate matter in the cooling air stream, a cyclone separator rotates the air in a circular motion, exerting centrifugal forces on the particles. These centrifugal forces propel the particles toward the radial edges of the cyclone, which then prevents them from returning to the rotating air stream. The exit flow removes the particles from the cyclone, and the rotating air stream exits the cyclone to cool gas turbine engine components.

[0021] Now refer to Figure 1 , according to an example embodiment of the present disclosure, a schematic cross-sectional view of a gas turbine engine 100 is provided. Specifically, Figure 1 A turbofan engine having a rotor assembly with a single stage of unducted rotor blades is provided. In this manner, the rotor assembly may be referred to herein as a "unducted fan," or the entire gas turbine engine 100 may be referred to as a "unducted turbofan engine." Additionally, Figure 1 Gas turbine engine 100 includes a third flow path extending from the compressor section to a rotor assembly above the turbine, as will be explained in greater detail below.

[0022] For reference, the gas turbine engine 100 defines an axial direction A, a radial direction R, and a circumferential direction C. Furthermore, the gas turbine engine 100 defines an axial centerline or longitudinal axis 112 extending along the axial direction A. Generally, the axial direction A extends parallel to the longitudinal axis 112, the radial direction R extends outwardly from and inwardly to the longitudinal axis 112 in a direction orthogonal to the axial direction A, and the circumferential direction extends three hundred and sixty degrees (360°) about the longitudinal axis 112. The gas turbine engine 100 extends between a forward end 114 and an aft end 116, e.g., along the axial direction A.

[0023] The gas turbine engine 100 includes a turbine 120 and a rotor assembly (also referred to as a fan section 150) located upstream thereof. Generally, the turbine 120 includes a compressor section, a combustion section, a turbine section, and an exhaust section in a series flow order. Specifically, as shown in FIG. Figure 1 As shown, the turbine 120 includes a core shroud 122 that defines an annular core inlet 124. The core shroud 122 also at least partially surrounds a low-pressure system and a high-pressure system. For example, the core shroud 122 shown at least partially surrounds and supports a supercharger or low-pressure ("LP") compressor (referred to herein as LP compressor 126) for pressurizing air entering the turbine 120 through the core inlet 124. A high-pressure ("HP"), multi-stage, axial-flow compressor (referred to herein as HP compressor 128) receives the pressurized air from the LP compressor 126 and further increases the pressure of the air. The pressurized air flows downstream to the combustor 130 of the combustion section, where fuel is injected into the pressurized air flow and ignited to increase the temperature and energy level of the pressurized air.

[0024] It should be understood that, as used herein, the terms "high / low speed" and "high / low pressure" are interchangeable for high-pressure / high-speed systems and low-pressure / low-speed systems. Furthermore, it should be understood that the terms "high" and "low" are used in the same context to distinguish between the two systems and are not meant to imply any absolute speed and / or pressure values.

[0025] The high-energy combustion products flow downstream from the combustor 130 to an HP turbine 132. The HP turbine 132 drives the HP compressor 128 via an HP shaft 136. In this respect, the HP turbine 132 is drivingly coupled to the HP compressor 128. The high-energy combustion products then flow to an LP turbine 134. The LP turbine 134 drives the LP compressor 126 and components of the fan section 150 via an LP shaft 138. In this respect, the LP turbine 134 is drivingly coupled to components of the LP compressor 126 and the fan section 150. In this exemplary embodiment, the LP shaft 138 is coaxial with the HP shaft 136. After driving each turbine 132, 134, the combustion products exit the turbine 120 through a turbine exhaust nozzle 140.

[0026] Thus, the turbine 120 defines a working gas flow path or core duct 142 that extends between the core inlet 124 and the turbine exhaust nozzle 140. The core duct 142 is an annular duct located generally inwardly of the core shroud 122 in the radial direction R. The core duct 142 (e.g., the working gas flow path through the turbine 120) may be referred to as a secondary flow.

[0027] Fan section 150 includes fan 152, which is the primary fan in this example embodiment. Figure 1 In the illustrated embodiment, the fan 152 is an open rotor or unducted fan. In this manner, the gas turbine engine 100 may be referred to as an open rotor engine.

[0028] As shown, fan 152 includes an array of fan blades 154 ( Figure 1 Only one is shown). The fan blades 154 are capable of rotating, for example, about the longitudinal axis 112. As described above, the fan 152 is drivingly coupled to the LP turbine 134 via the LP shaft 138. Figure 1 In the embodiment shown in FIG, the fan 152 is coupled to the LP shaft 138 via a reduction gearbox 155, for example, in an indirect drive or gear drive configuration.

[0029] Furthermore, the array of fan blades 154 can be arranged equally spaced about the longitudinal axis 112. Each fan blade 154 has a root and a tip, and a span defined therebetween. Each fan blade 154 defines a central blade axis 156. For this embodiment, each fan blade 154 of the fan 152 is capable of rotating about its central blade axis 156, e.g., rotating in unison with one another. One or more actuators 158 are provided to facilitate such rotation and can therefore be used to change the pitch of the fan blades 154 about their respective central blade axes 156.

[0030] The fan section 150 also includes a fan guide vane array 160 including fan guide vanes 162 ( Figure 1 For this embodiment, the fan guide vanes 162 are not rotatable about the longitudinal axis 112. Each fan guide vane 162 has a root and a tip and a span defined therebetween. The fan guide vanes 162 may be configured as follows: Figure 1 It is shown without a shroud, or it may be shrouded, for example, by way of an annular shroud spaced outwardly from the tips of the fan guide vanes 162 in the radial direction R or attached to the fan guide vanes 162 .

[0031] Each fan guide vane 162 defines a central blade axis 164. For this embodiment, each fan guide vane 162 of the fan guide vane array 160 is capable of rotating about its respective central blade axis 164, e.g., rotating in unison with one another. One or more actuators 166 are provided to facilitate such rotation and thus can be used to change the pitch of the fan guide vanes 162 about their respective central blade axis 164. However, in other embodiments, each fan guide vane 162 may be fixed or unable to pitch about its central blade axis 164. The fan guide vanes 162 are mounted to a fan housing 170.

[0032] like Figure 1 As shown, in addition to the unducted fan 152, a ducted fan 184 is also included at the rear of the fan 152, so that the gas turbine engine 100 includes both ducted and unducted fans, both of which are used to generate thrust by moving air without passing through at least a portion of the turbine 120 (e.g., without passing through the HP compressor 128 and the combustion section in the illustrated embodiment). The ducted fan 184 is capable of rotating about the same axis as the fan blades 154 (e.g., the longitudinal axis 112). In the illustrated embodiment, the ducted fan 184 is driven by the LP turbine 134 (e.g., coupled to the LP shaft 138). In the illustrated embodiment, as described above, the fan 152 may be referred to as the primary fan, while the ducted fan 184 may be referred to as the secondary fan. It should be understood that the terms "primary" and "secondary" are used for convenience only and do not imply any special importance, authority, etc.

[0033] The duct fan 184 includes a plurality of fan blades ( Figure 1 (not separately labeled), these fan blades are arranged in a single stage, and thus ducted fan 184 may be referred to as a single-stage fan. The fan blades of ducted fan 184 may be equally spaced about longitudinal axis 112. Each blade of ducted fan 184 has a root and a tip, and a span defined therebetween.

[0034] Fan shroud 170 annularly surrounds at least a portion of core shroud 122 and is generally located outside of at least a portion of core shroud 122 in radial direction R. Specifically, a downstream section of fan shroud 170 extends above a front portion of core shroud 122 to define a fan duct flow path, or simply, fan duct 172. According to this embodiment, fan flow path or fan duct 172 may be understood as forming at least a portion of the tertiary flow of gas turbine engine 100.

[0035] Incoming air may enter the fan duct 172 through the fan duct inlet 176 and may be discharged through the fan exhaust nozzle 178 to generate propulsive thrust. The fan duct 172 is an annular duct that is generally located outside the core duct 142 in the radial direction R. The fan shroud 170 and the core shroud 122 are connected together and are supported by a plurality of substantially radially extending, circumferentially spaced fixed struts 174 ( Figure 1 The fan duct 172 and the core duct 142 may be supported by the fan duct 170 and the core duct 142 (only one is shown). Each fixed strut 174 may have an aerodynamic profile to guide the air flowing therethrough. In addition to the fixed struts 174, other struts may also be used to connect and support the fan shroud 170 and / or the core shroud 122. In many embodiments, the fan duct 172 and the core duct 142 may at least partially extend together (typically axially) on opposite sides (e.g., opposite radial sides) of the core shroud 122. For example, the fan duct 172 and the core duct 142 may each extend directly from the leading edge 144 of the core shroud 122 and may partially extend together generally axially on opposite radial sides of the core shroud 122.

[0036] Gas turbine engine 100 further defines or includes an inlet duct 180. Inlet duct 180 extends between an engine inlet 182 and core inlet 124 / fan duct inlet 176. Engine inlet 182 is generally defined at the forward end of fan casing 170 and is located between fan 152 and fan guide vane array 160 in axial direction A. Inlet duct 180 is an annular duct located inwardly of fan casing 170 in radial direction R. Air flowing downstream along inlet duct 180 is divided, not necessarily evenly, into core duct 142 and fan duct 172 by fan duct splitter or leading edge 144 of core casing 122. In the illustrated embodiment, inlet duct 180 is wider in radial direction R than core duct 142. Inlet duct 180 is also wider in radial direction R than fan duct 172.

[0037] Notably, for the illustrated embodiment, gas turbine engine 100 includes one or more features to increase the efficiency of third-stream thrust (e.g., thrust generated by the airflow exiting fan exhaust nozzle 178 through fan duct 172, at least in part by ducted fan 184). Specifically, gas turbine engine 100 also includes an array of inlet guide vanes 186 located in inlet duct 180, upstream of ducted fan 184 and downstream of engine inlet 182. The array of inlet guide vanes 186 is arranged about longitudinal axis 112. For this embodiment, inlet guide vanes 186 are non-rotatable about longitudinal axis 112. Each inlet guide vane 186 defines a central blade axis (not labeled for clarity) and is capable of rotating about its respective central blade axis, e.g., in unison with one another. In this manner, inlet guide vanes 186 can be considered variable geometry components. One or more actuators 188 are provided to facilitate this rotation, thereby enabling the pitch of inlet guide vanes 186 to be varied about their respective central blade axes. However, in other embodiments, each inlet guide vane 186 may be fixed or non-pitched about its central vane axis.

[0038] In addition, gas turbine engine 100 includes an array of outlet guide vanes 190 located downstream of ducted fan 184 and upstream of fan duct inlet 176. Like array of inlet guide vanes 186, array of outlet guide vanes 190 is non-rotatable about longitudinal axis 112. However, for the illustrated embodiment, unlike array of inlet guide vanes 186, array of outlet guide vanes 190 is configured as fixed-pitch outlet guide vanes.

[0039] Furthermore, it should be understood that for the illustrated embodiment, the fan exhaust nozzle 178 of the fan duct 172 is also configured as a variable geometry exhaust nozzle. In this manner, the gas turbine engine 100 includes one or more actuators 192 for adjusting the variable geometry exhaust nozzle. For example, the variable geometry exhaust nozzle can be configured to vary the total cross-sectional area (e.g., the area of the nozzle in a plane perpendicular to the longitudinal axis 112) to adjust the amount of thrust generated based on one or more engine operating conditions (e.g., the temperature, pressure, mass flow rate, etc. of the airflow through the fan duct 172). A fixed geometry exhaust nozzle may also be employed.

[0040] The combination of the array of inlet guide vanes 186 located upstream of the ducted fan 184, the array of outlet guide vanes 190 located downstream of the ducted fan 184, and the fan exhaust nozzle 178 can more efficiently generate third stream thrust under one or more engine operating conditions. Furthermore, by incorporating variability in the geometry of the inlet guide vanes 186 and the fan exhaust nozzle 178, the gas turbine engine 100 is able to generate more efficient third stream thrust under a relatively wide range of engine operating conditions, including takeoff and climb (where maximum total engine thrust is typically required) and cruise (where a smaller amount of total engine thrust is typically required).

[0041] In addition, still refer to Figure 1 In an exemplary embodiment, the air passing through fan duct 172 may be relatively cooler (e.g., at a lower temperature) than one or more fluids used in turbine 120. As such, one or more heat exchangers 194 may be positioned in thermal communication with fan duct 172. For example, one or more heat exchangers 194 may be disposed within fan duct 172 and used to cool one or more fluids from the core engine, where air passing through fan duct 172 serves as a source for removing heat from the fluids (e.g., compressor exhaust, oil, or fuel).

[0042] Although not shown, heat exchanger 194 may be an annular heat exchanger extending approximately 360 degrees (e.g., at least 300 degrees, such as at least 330 degrees) within fan duct 172. In this manner, heat exchanger 194 may effectively utilize the air passing through fan duct 172 to cool one or more systems of gas turbine engine 100 (e.g., lubricating oil system, compressor exhaust, electrical components, etc.). Heat exchanger 194 uses the air passing through fan duct 172 as a heat sink and accordingly increases the temperature of the air downstream of heat exchanger 194 and exiting fan exhaust nozzle 178.

[0043] However, it should be understood that the exemplary gas turbine engine 100 is provided by way of example only. In other exemplary embodiments, the gas turbine engine 100 may have any other configuration. For example, in other exemplary embodiments, the turbine 120 may have any other number and arrangement of shafts, spools, compressors, turbines, etc. Furthermore, in other exemplary embodiments, the gas turbine engine 100 may alternatively be configured as a ducted turbofan engine (including an outer nacelle surrounding the fan 152 and a portion of the turbine 120); a direct drive gas turbine engine (which may not include a reduction gearbox, such as the gearbox 155); a fixed pitch gas turbine engine (which may not include a variable pitch fan, such as the fan 152); a dual flow gas turbine engine (which may not include the fan duct 172); etc.

[0044] Now refer to Figure 2The gas turbine engine 100 includes a cooling circuit 200. The cooling circuit 200 is disposed between the compressor section and the turbine section to provide cooling air 201 from the compressor section to the turbine section. More specifically, the cooling air 201 flows from the HP compressor 128, bypasses the combustor 130, and passes through the cooling circuit 200. The cooling air 201 then flows to the HP turbine 132.

[0045] Cooling circuit 200 includes a cyclone separator 202 for removing impurities, such as dust or debris, from the air. Cyclone separator 202 defines a radial direction R1, an axial direction A1, and a circumferential direction C1. It will be appreciated that the directions R1, A1, and C1 of cyclone separator 202 are defined locally relative to cyclone separator 202. However, in the illustrated embodiment, axial direction A1 is arranged parallel to axial direction A of gas turbine engine 100.

[0046] The cyclone separator 202 includes a housing 204 extending from a first end 206 to a second end 208, a fluid inlet 210 disposed at the first end 206 of the housing 204, a first fluid outlet 212 disposed at the second end 208 of the housing 204, and a second fluid outlet 214 extending outward from the housing 204 at least partially in a radial direction R1. The fluid inlet 210 receives air from the compressor section, and the first fluid outlet 212 delivers the air to the turbine section. The fluid inlet 210 can be angled relative to the circumferential direction C1 to create a swirling flow in the incoming air. As an example, the fluid inlet 210 can be angled between 30 and 70 degrees relative to the circumferential direction C1, and the fluid inlet 210 can be angled clockwise or counterclockwise. The second fluid outlet 214 delivers the impurity-laden air to an outlet stream 216, which is directed away from the combustion section and the turbine section. The cooling circuit 200 provides air suitable for cooling one or more components of the gas turbine engine 100 , such as the HP turbine 132 and the LP turbine 134 .

[0047] More specifically, the HP turbine 132 defines a cooling passage 218 and includes an inducer 220 configured to introduce a circumferential swirl into the cooling air provided by the cooling circuit 200 to the cooling passage 218 of the HP turbine 132. Specifically, the cooling circuit 200 may receive cooling air 201 from the compressor section (e.g., from the outlet of the compressor section). The gas turbine engine 100 includes, in the combustion section, an internal airflow passage 222 and an annular chamber 224 located inside the combustor 130 in a radial direction R of the gas turbine engine 100. In the illustrated embodiment, the cooling air 201 is provided to the annular chamber 224 via the internal airflow passage 222. The cooling air 201 in the annular chamber 224 is provided to the cooling circuit 200 of the present disclosure, where particles in the cooling air 201 are separated as described herein. The clean cooling air 201 is provided through the inducer 220 and into the cooling passage 218 of the HP turbine 132 to cool the HP turbine 132 .

[0048] refer to Figures 3A-3B , shows the cyclone separator 202 in a cross-sectional view. Specifically, Figure 3A A side cross-sectional view of the cyclone separator 202 is shown. Figure 3B A front cross-sectional view of the cyclone separator along line BB is shown.

[0049] The housing 204 of the cyclone separator 202 includes an outer wall 228 extending between a first end 206 and a second end 208. A fluid inlet 210 is provided at the first end 206 and introduces air into the housing 204. A first fluid outlet 212 is provided at the second end 208 of the housing 204, and a second fluid outlet 214 is provided in the outer wall 228 downstream of the first end 206.

[0050] The cyclone separator 202 includes a particle separator 230. The particle separator 230 is disposed in the housing 204 between the first end 206 and the second end 208, inwardly of the outer wall 228 in the radial direction R1. The particle separator 230 extends in the circumferential direction C1 around the center of the housing 204, allowing particles to flow toward the outer wall 228 while inhibiting particles from returning to the center of the housing 204. As described in more detail below, the particle separator 230 includes one or more openings that allow air and particles to pass through.

[0051] like Figure 3A As shown, the particle separator 230 extends from the first end 206 of the housing to the second end 208 of the housing. In this form, the housing 204 can support the particle separator 230 at the first end 206, the second end 208, or both. As an example, the particle separator 230 can be welded, fastened, or adhered to the first end 206 or the second end 208.

[0052] Alternatively, the particle separator 230 may partially extend between the first end 206 and the second end 208. In this form, the particle separator 230 is spaced apart from one of the first end 206 or the second end 208.

[0053] Additionally or alternatively, the cyclone separator 202 can include one or more pins 232 extending radially from the outer wall 228 to the particle separator 230. The pins 232, if included, secure the particle separator 230 to the outer wall 228, thereby securing the particle separator 230 within the housing 204.

[0054] For clarity, Figure 3B The arrows in FIG. 2 indicate the air flow in the cyclone separator 202, showing the movement of air from the fluid inlet 210 to the first fluid outlet 212 and the second fluid outlet 214. The fluid inlet 210 is arranged on the inner side of the particle separator 230 along the radial direction R1, and the particles in the air are introduced into the interior of the housing 204 through the fluid inlet 210. Figures 3A-3B In the exemplary embodiment, the cyclone separator 202 includes two fluid inlets 210. It will be appreciated that the cyclone separator 202 may include a different number of fluid inlets 210. The cyclone separator 202 rotates the air from the fluid inlets 210, causing particulate matter to accumulate radially outside the particle separator 230 and causing the remaining air to flow toward the first fluid outlet 212. More specifically, the fluid inlets 210 are positioned radially outside the center of the housing 204, which induces a vortex along the center of the housing toward the first fluid outlet 212. This vortex causes the air to rotate in a circumferential direction C1.

[0055] The second fluid outlet 214 is disposed radially outwardly of the particle separator 230. The second fluid outlet 214 defines an outlet passage 234 therethrough, and the outlet passage 234 is in fluid communication with the outlet stream 216 that removes air from the cyclone separator 202. As the air rotates within the housing 204, at least some of the particulate matter is pushed by centrifugal force through the opening of the particle separator 230 to the outer wall 228. Because the opening of the particle separator 230 is in fluid communication with the outlet passage 234 and the outlet stream, the particulate matter flows circumferentially around the outer wall 228 and through the outlet passage 234 of the second fluid outlet 214 to the outlet stream, thereby removing the particulate matter from the cyclone separator 202. Simultaneously, the remaining rotating air flows through the housing 204 toward the first fluid outlet 212, having lost at least some of the particulate matter, and reaches the turbine section, as described above with reference to FIG. Figure 2 As stated.

[0056] Now refer to Figure 4 , a schematic diagram of a particle separator 230 is shown according to an exemplary embodiment of the present disclosure. Figure 4 The exemplary particle separator 230 may be incorporated into the above referenced Figure 2-3B In the cyclone separator described.

[0057] The particle separator 230 defines a plurality of openings 236. When disposed in the cyclone separator 202, the openings 236 extend in the radial direction R1 toward the outer wall 228 (see FIG. Figure 3A 、 3B ). The openings 236 are evenly distributed around the particle separator 230 in the circumferential direction C1 and the axial direction A1, for example Figure 4 Checkered pattern shown.

[0058] However, alternatively, in other exemplary embodiments, the openings 236 may be arranged in a different pattern, such as a staggered configuration. Figure 4 As will be discussed in more detail below, the plurality of openings 236 may include circular openings, oval openings, polygonal openings, or combinations thereof.

[0059] Now refer to Figures 5A to 5F , provides a schematic plan view of a particle separator 230 according to various exemplary embodiments of the present disclosure. Figures 5A to 5F The exemplary particle separator 230 may be incorporated into the above referenced Figure 2-3B The cyclone separator 202 is described.

[0060] like Figures 5A-5F As shown, the plurality of openings 236 can be one of a variety of shapes and can be distributed along the particle separator 230 in one of a variety of patterns. For clarity, the term "openings 236" will generally refer to the openings of the particle separator 230, and Figures 5A-5B Each of the may use an additional number to refer to the specific shape and pattern of openings 236 in a particular figure.

[0061] Figure 5A The circular openings 238 are shown arranged in a grid pattern, ie, each circular opening 238 is arranged in a rectangular grid, and each circular opening 238 is substantially the same size. A grid arrangement may be easier to manufacture than other arrangements because the spacing between each opening 236 is substantially uniform.

[0062] Figure 5B Circular openings 240 are shown arranged in a grid pattern, the size of which decreases along the axial direction A1. In this arrangement, the size of a first opening 240A among the plurality of openings 240 defined in the particle separator 230 at a first position in the axial direction A1 is greater than the size of a second opening 240B among the plurality of openings 240 defined in the particle separator 230 at a second position in the axial direction A1. Figure 5BIn the example of FIG. 1 , the size of the openings 240 is reduced eightfold, showing openings 240A, 240B, 240C, 240D, 240E, 240F, 240G, and 240H.

[0063] However, it should be understood that in other exemplary embodiments, the particle separator 230 can have a different number of sizes, such as two, four, six, or other numbers, and the sizes can increase or decrease at different positions in the axial direction A1, including decreasing and increasing in an uneven or alternating pattern.

[0064] Particles moving through the larger openings (e.g., openings 240A and 240B) may be too large to pass through the smaller openings (e.g., 240G and 240H). Therefore, the smaller openings inhibit the movement of particles back into the airflow at the center of the cyclone separator 202, forcing the air to flow through the second fluid outlet 214 along with the particles.

[0065] Figure 5C The circular openings 242 are shown arranged in a staggered configuration such that the openings 242 are not aligned in the axial direction A1 with the preceding and following adjacent openings 242. The staggered configuration allows particles that may not be able to pass through an opening 242 at one axial position to pass through other openings 242 at a different axial position, thereby increasing the likelihood that the particle will pass through at least one opening 242 and, therefore, the second fluid outlet 214.

[0066] Figure 5D Polygonal openings 244 are shown, specifically rectangular openings, arranged in a grid. Figure 5E An irregularly shaped opening 246 is shown, such as a barbell shape. The polygonal and irregular shapes of the openings 244, 246 may provide advantageous physical properties, such as specific gravity or stress distribution, while removing particles from the air flowing in the cyclone separator 202.

[0067] Figure 5F The particle separator 230 is shown as a mesh with openings 248 formed between the intersections of the lines forming the mesh. The particle separator 230 can be formed from a prefabricated mesh having a specified opening size, thereby reducing the overall manufacturing volume performed on the particle separator 230. Figures 5A-5E The mesh may also reduce the overall weight of the particle separator 230 as compared to a cylindrical tube having openings 236, 238, 240, 242, 244, and 246 as shown.

[0068] It should be understood that the various patterns described herein may be modified, combined, or otherwise adjusted to provide suitable particle removal from an air stream.

[0069] refer to Figures 6A-6E, a cross-sectional view of the particle separator 230 is shown. Figure 6A A view of a particle separator 230 is provided, having protrusions extending radially outward. Figure 6B A view of a particle separator 230 is provided, having protrusions extending radially inward. Figure 6C is an enlarged view of one of the protrusions of the particle separator 230 . Figure 6D is an enlarged view of another one of the protrusions of the particle separator 230 . Figure 6E is an enlarged view of another one of the protrusions of the particle separator 230 . Figure 6A and Figure 6B The exemplary particle separator 230 may be configured with Figure 2-5F The exemplary particle separator 230 is configured in substantially the same manner.

[0070] Each particle separator 230 shown comprises one or more protrusions 250 extending in a radial direction R1 of the cooling circuit 200 comprising the corresponding particle separator 230 (see, for example, FIG. Figure 3A 、 3B ) such that one of the openings 236 is defined by each protrusion 250. The protrusions 250 are tubes or passages through which particles move from the center of the housing 204 to the outer wall 228. To assist in particle movement from the center and inhibit particle movement back to the center, the protrusions 250 define an angle 252 with a centerline 254 of the housing 204. The protrusions 250 alter the trajectory of particles moving outward in the radial direction R1, thereby reducing or eliminating particle movement back to the center. More specifically, particles moving along the protrusions 250 may be propelled outward in the radial direction R1 of the cooling circuit 200 and forward in the axial direction A1 of the cooling circuit 200 (see, e.g., FIG. 2 ). Figure 3A 、 3B ), rebounding from the outer wall 228 of the cooling circuit 200 back inward in the radial direction R1. Because the protrusion 250 is angled forward in the axial direction A1, particles that rebound from the outer wall 228 are less likely to travel downward back into the opening 236, resulting in a trajectory that includes backward motion in the axial direction A1. By providing momentum to particles traveling forward in the axial direction A1, fewer particles return to the center of the housing 204, and more particles are removed from the cyclone separator 202. Angle 252 can be acute, i.e., less than 90 degrees, to achieve this trajectory-changing feature.

[0071] Figure 6A The protrusion 250 is shown extending outwardly in the radial direction R1 toward the outer wall 228 of the cooling circuit 200. The protrusion 250 extending outwardly from the particle separator extends partially toward the outer wall 228 to guide particles to the outer wall 228.

[0072] In contrast, Figure 6BThe protrusions 250 are shown extending in radial direction R1 inwardly away from the outer wall 228 of the cooling circuit 200. The protrusions 250 receive particles from the center of the housing 204 and direct the particles toward the outer wall 228.

[0073] Now refer to Figures 6C-6E , the protrusion 250 may have Figures 6A-6B The straight protrusions 250 shown in FIG. Figure 6C As shown, the protrusion 250 may extend along a convexly curved path 256. The convexly curved path 256 directs particles away from the particle separator 230 in a downstream direction.

[0074] like Figure 6D As shown, the protrusion 250 can extend along a concave curved path 257. The concave curved path 257 directs particles radially away from the particle separator 230.

[0075] like Figure 6E As shown, the protrusion 250 may extend along a serpentine path 258. The serpentine path 258 directs particles radially away and away from the particle separator 230 in a downstream direction.

[0076] It should be understood that the particle separator 230 may include protrusions 250 extending at different angles 252 and extending toward the outer wall 228, extending away from the outer wall 228, having different curved paths 256, 257, 258 or a combination thereof, and some or all of the openings 236 of the particle separator 230 may extend through one of the protrusions 250.

[0077] Now refer to Figure 7A , a cross-sectional view of another cyclone separator 260 is shown. Figure 7A The cyclone separator 260 includes a particle separator 230 and a second particle separator 262. The second particle separator 262 is arranged on the radial inner side of the particle separator 230. The second particle separator 262 includes a plurality of openings (not shown) that allow particles to pass through. The openings of the second particle separator 262 can be different from the openings of the particle separator 230 to filter particles of different sizes. For example, the particle separator 230 may include an opening having a first size, while the second particle separator 262 may include an opening having a second size, the second size being larger than the first size. In this form, larger particles pass through the openings of the second particle separator 262, but are blocked by the smaller openings of the particle separator 230 and cannot return to the center of the cyclone separator 260.

[0078] Now refer to Figure 7B, shows a cross-sectional view of another cyclone separator 270. The cyclone separator 270 includes a particle separator 272 having an octagonal shape. The octagonal shape of the particle separator 272 allows for different air flow patterns in the cyclone separator 270. It should be understood that the particle separator 272 can have different polygonal shapes, such as square, triangular, hexagonal, or shapes with different numbers of sides.

[0079] refer to Figure 7C , shows a cross-sectional view of another cyclone separator 280. The cyclone separator 280 includes a particle separator 282. The particle separator 282 is arranged in the cyclone separator 280 so that the center of the particle separator 282 is spaced apart from the center of the outer wall 228 of the cyclone separator 280. In other words, the particle separator 282 and the outer wall 228 are not concentric. By eccentrically arranging the particle separator 282 relative to the outer wall 228, the particle separator 282 can filter particles accumulated in a specific section of the cyclone separator 280. More specifically, based on the flow direction of the cooling air 201 in the cyclone separator 280, particles may preferentially accumulate in a specific area. In order to more easily filter particles, the particle separator 282 can be eccentrically arranged in a specific area.

[0080] Now refer to Figure 8 , shows another exemplary embodiment of the cyclone separator 300. Specifically, Figure 8 A schematic cross-sectional view of a cyclone separator 300 is provided.

[0081] exist Figure 8 In the embodiment of the present invention, the cyclone separator 300 defines a radial direction R2, an axial direction A2, and a circumferential direction C2. The cyclone separator 300 includes a housing 302, which includes a fluid inlet 304, a first fluid outlet 306, a second fluid outlet 308, a center body 310 along a centerline 312 of the cyclone separator 300, and an outer wall 314. It should be understood that similarly named components in the cyclone separator 300 perform similar functions as in the cyclone separator 202, and that the numbering used in the cyclone separator 300 is different from that used in the cyclone separator 202 only for the sake of clarity.

[0082] The cyclone separator 300 includes a particle separator 316 positioned between the center body 310 and the outer wall 314. The center body 310 causes the cooling air 201 from the fluid inlet 304 to rotate about the centerline 312 through the housing 302 to the first fluid outlet 306. The rotation of the airflow causes particles to move through the particle separator 316 toward the outer wall 314 to the second fluid outlet 308 and then out of the cyclone separator 300. Specifically, the particle separator 316 can be fixed to the first fluid outlet 306 so that the rotating cooling air 201 flowing around the center body 310 passes through or through the particle separator 316 before reaching the first fluid outlet 306. The particle separator 316 is positioned to increase the movement of particles toward the second fluid outlet 308, thereby removing particles from the rotating cooling air exiting the cyclone separator 300 through the first fluid outlet 306.

[0083] It is worth noting that the cyclone separator 300 may be located in the gas turbine engine and Figure 2 The cyclone separator 300 is similarly positioned as the cyclone separator 202 of the cooling circuit 200. In this manner, the cyclone separator 300 can receive cooling air from the compressor section of the gas turbine engine via the fluid inlet 304 and can provide the cooling air 201 to the turbine of the turbine section of the gas turbine engine 100 via the first fluid outlet 306. The second fluid outlet 308 can discharge the particle-laden air to an ambient location via the outlet stream 216.

[0084] The particle separator 316 may be of similar construction and may include Figures 5A-7C One or more of the features described above for the particle separator 230 may include the size and shape of the openings 236 and protrusions 250 suitable for removing particulate matter from the air flow. By including the center body 310 in the cyclone separator 300, the air flow is separated from the cyclone 300 by a different Figures 3A-3B The cyclone separator 202 rotates in a manner that may be suitable for a particular cooling application.

[0085] As shown in the accompanying figures and described above, a cyclone separator rotates air in a circular motion, exerting centrifugal forces on particulate matter in the air flowing through it. Centrifugal forces propel particulate matter toward the radial edges of the cyclone, where they reduce or inhibit the flow of particulate matter back into the center of the cyclone. As it moves through the cyclone, the outlet air removes particulate matter from the cyclone, leaving clean air to flow toward the fluid outlet. The clean air exits the cyclone to cool gas turbine engine components.

[0086] Further aspects are provided by the subject matter of the following clauses:

[0087] A cyclone separator for a turbine cooling airflow of a gas turbine engine, the cyclone separator defining a centerline, an axial direction, a radial direction, and a circumferential direction. The cyclone separator includes a housing, the housing including a first end, a second end, and an outer wall extending between the first and second ends; a fluid inlet disposed at the first end of the housing; a first fluid outlet disposed at the second end of the housing, the second end being opposite the first end in the axial direction; a second fluid outlet disposed in the outer wall downstream of the first end of the housing, the second fluid outlet extending at least partially outward in the radial direction relative to the outer wall; and a particle separator disposed in the housing between the first and second ends, inward of the outer wall in the radial direction, the particle separator extending in the circumferential direction. The particle separator defines a plurality of openings extending in the radial direction toward the outer wall.

[0088] A cyclone separator according to the preceding clause, wherein the housing further comprises a central body, wherein the particle separator is disposed between the central body and the outer wall.

[0089] A cyclonic separator according to any preceding clause, wherein the second fluid outlet defines an outlet passage in fluid communication with an outlet stream, and wherein the plurality of openings of the particle separator are in fluid communication with the outlet passage.

[0090] A cyclonic separator as claimed in any preceding clause, wherein the particle separator extends from the first end of the housing to the second end of the housing.

[0091] A cyclonic separator according to any one of the preceding clauses, wherein the plurality of openings comprises circular openings, elliptical openings, polygonal openings or a combination thereof.

[0092] A cyclone separator as claimed in any preceding clause, wherein the particle separator is a mesh.

[0093] A cyclone separator according to any of the preceding clauses, wherein a size of a first opening of the plurality of openings defined in the particle separator at a first position in the axial direction is greater than a size of a second opening of the plurality of openings defined in the particle separator at a second position in the axial direction.

[0094] A cyclone separator according to any one of the preceding clauses, wherein the particle separator further comprises a protrusion extending in the radial direction, wherein at least one opening of the plurality of openings is defined through the protrusion.

[0095] A cyclonic separator as claimed in any preceding clause, wherein the protrusion defines an angle of less than 90 degrees with the centre line.

[0096] A cyclonic separator according to any of the preceding clauses, wherein the gas turbine engine comprises a turbine section including a turbine having a cooling passage, and wherein the first fluid outlet provided at the second end of the casing is configured to be fluidly connected to the cooling passage of the turbine.

[0097] A cyclone separator according to any of the preceding clauses, wherein the plurality of openings are evenly distributed around the particle separator in the circumferential direction.

[0098] A cyclone separator according to any of the preceding clauses, wherein the plurality of openings are evenly distributed along the particle separator in the axial direction.

[0099] A cyclone separator according to any one of the preceding clauses, wherein the fluid inlet is arranged inside the particle separator in the radial direction.

[0100] A gas turbine engine comprises a compressor section; a turbine section located downstream of the compressor section; and a cyclone separator located between the compressor section and the turbine section. The cyclone separator defines an axial direction, a radial direction, and a circumferential direction. The cyclone separator comprises: a casing comprising a first end, a second end, and an outer wall extending between the first and second ends; a fluid inlet disposed at the first end of the casing and fluidically connected to the compressor section; a first fluid outlet disposed at the second end of the casing and fluidically connected to the turbine section, the second end being opposite the first end in the axial direction; a second fluid outlet disposed in the outer wall downstream of the first end, the second fluid outlet extending at least partially outward in the radial direction relative to the outer wall and fluidically connected to an outlet flow directed away from the turbine section; and a particle separator disposed in the casing between the first and second ends, inward of the outer wall in the radial direction, the particle separator extending in the circumferential direction. The particle separator defines a plurality of openings extending in the radial direction toward the outer wall.

[0101] The gas turbine engine according to any of the preceding clauses, wherein the casing further comprises a center body, wherein the particle separator is disposed between the center body and the outer wall.

[0102] The gas turbine engine of any of the preceding clauses, wherein the plurality of openings comprises circular openings, elliptical openings, polygonal openings, or a combination thereof.

[0103] A gas turbine engine as claimed in any one of the preceding clauses, wherein the particle separator is a mesh.

[0104] The gas turbine engine according to any one of the preceding clauses, wherein the particle separator further comprises a protrusion extending in the radial direction, wherein at least one opening of the plurality of openings is defined through the protrusion.

[0105] A gas turbine engine as claimed in any one of the preceding clauses, wherein the protrusion defines an angle of less than 90 degrees with a centre line of the cyclonic separator.

[0106] The gas turbine engine according to any of the preceding clauses, wherein the turbine section comprises a turbine having a cooling passage, and wherein the first fluid outlet provided at the second end of the casing is in fluid connection with the cooling passage of the turbine.

[0107] This written description uses examples to disclose the present disclosure, including the best mode, and also to enable any person skilled in the art to practice the present disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the present disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.

Claims

1. A cyclone separator for a turbine cooling airflow of a gas turbine engine, the cyclone separator defining a centerline, an axial direction, a radial direction, and a circumferential direction, wherein: The cyclone separator comprises: a housing including a first end, a second end opposite to the first end in the axial direction, and an outer wall extending between the first end and the second end; a fluid inlet disposed at the first end of the housing; a first fluid outlet disposed at the second end of the housing; a second fluid outlet disposed in the outer wall downstream of the first end of the housing, the second fluid outlet extending at least partially outward in the radial direction relative to the outer wall; and a particle separator disposed in the housing between the first end and the second end and on the inner side of the outer wall in the radial direction, the particle separator extending in the circumferential direction; Wherein, the particle separator defines a plurality of openings extending in the radial direction toward the outer wall.

2. The cyclone separator according to claim 1, characterized in that in, The housing further includes a center body, wherein the particle separator is disposed between the center body and the outer wall.

3. The cyclone separator according to claim 1, characterized in that in, The second fluid outlet defines an outlet passage in fluid communication with an outlet stream, and wherein the plurality of openings of the particle separator are in fluid communication with the outlet passage.

4. The cyclone separator according to claim 1, characterized in that in, The particle separator extends from the first end of the housing to the second end of the housing.

5. The cyclone separator according to claim 1, characterized in that in, The plurality of openings include circular openings, elliptical openings, polygonal openings or a combination thereof.

6. The cyclone separator according to claim 1, characterized in that in, The particle separator is a mesh.

7. The cyclone separator according to claim 1, characterized in that in, A size of a first opening of the plurality of openings defined in the particle separator at a first position in the axial direction is larger than a size of a second opening of the plurality of openings defined in the particle separator at a second position in the axial direction.

8. The cyclone separator according to claim 1, characterized in that in, The particle separator further includes a protrusion extending in the radial direction, wherein at least one opening of the plurality of openings is defined through the protrusion.

9. The cyclone separator according to claim 8, characterized in that in, The protrusion defines an angle with the centerline that is less than 90 degrees.

10. The cyclone separator according to claim 1, wherein in, The gas turbine engine includes a turbine section including a turbine having a cooling passage, and wherein the first fluid outlet provided at the second end of the casing is configured to be fluidly connected to the cooling passage of the turbine.

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