Heat exchanger assembly configurations for gas turbine engines

Abstract

A gas turbine engine defines a radial direction and an axial direction. The gas turbine engine includes an inlet duct including a splitter, a fan duct downstream of the inlet duct and the splitter, and a core duct downstream of the inlet duct and the splitter. The core duct can be located radially inward of the fan duct. A heat exchanger assembly can extend annularly about at least one of the inlet duct, the fan duct, or the core duct. The heat exchanger assembly can include a sheet that extends circumferentially about at least one of the inlet duct, the fan duct, and the core duct. One or more aerodynamic features extend from the sheet, the one or more aerodynamic features being located within at least one of the inlet duct, the fan duct, and the core duct.

Description

Technical Field

[0001] This disclosure relates to a gas turbine engine. Background Technology

[0002] Gas turbine engines typically include a turbine and a rotor assembly. For at least some gas turbine engines, the turbine may include a heat exchanger assembly. Attached Figure Description

[0003] The complete and practical disclosure of this disclosure is set forth in the specification with reference to the accompanying drawings, wherein:

[0004] Figure 1 This is a cross-sectional view of a gas turbine engine according to various aspects of this disclosure.

[0005] Figure 2 This is a perspective view of a heat exchanger assembly according to various aspects of this disclosure.

[0006] Figure 3 This is a front view of a heat exchanger assembly according to various aspects of this disclosure.

[0007] Figure 4 This is a side view of a heat exchanger assembly according to various aspects of this disclosure.

[0008] Figure 5 This is a close-up perspective view of a heat exchanger assembly according to various aspects of this disclosure.

[0009] Figure 6 This is a perspective view of a heat exchanger assembly including a fluid circulation system according to various aspects of this disclosure.

[0010] Figure 7 This is a perspective view of a single core segment of a heat exchanger assembly according to various aspects of this disclosure, showing a portion of a fluid circulation system.

[0011] Figure 8 It is along Figure 7 The cross-sectional view along lines VIII-VIII shows a portion of the manifold assembly of the heat exchanger assembly according to various aspects of this disclosure.

[0012] Figure 9 A schematic diagram of a method for transferring thermal energy between a first fluid flow and a second fluid flow according to various aspects of this disclosure is shown. Detailed Implementation

[0013] Reference will now be made in detail to embodiments of the present disclosure, one or more of which are illustrated in the accompanying drawings. Detailed descriptions use numbers and letters to denote features in the figures. The same or similar reference numerals used in the drawings and description are used to denote the same or similar portions of the present disclosure.

[0014] As used herein, the term "exemplary" means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as being more preferred or advantageous than other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0015] The singular forms “one,” “a,” and “the” include plural references unless the context clearly indicates otherwise.

[0016] 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 individual components. The singular forms “a,” “an,” and “the” include plural references unless the context clearly specifies otherwise. Furthermore, as used herein, the term “group” or “set” of elements can refer to any number of elements, including only one.

[0017] Connection references (e.g., attachments, joins, connections, and engagements) should be interpreted broadly and may include intermediate structural elements between sets of elements and relative movement between elements, unless otherwise stated. Therefore, a connection reference does not necessarily mean that two elements are directly connected and fixed to each other. The accompanying drawings are for illustrative purposes only, and the dimensions, positions, orders, and relative sizes reflected in the drawings may vary.

[0018] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are used for identification purposes only to help the reader understand this disclosure and do not constitute a limitation, in particular a limitation on the location, orientation, or use of the aspects described in this disclosure.

[0019] As used herein, the terms "monolithic," "monolithic," or "monolithic" to describe a structure mean that the structure is formed integrally from a continuous material or group of materials without seams, joints, or other connections. The monolithic or monolithic structures described herein can be formed by additive manufacturing to have the structure, or alternatively by casting processes, etc.

[0020] As used herein, the term "monolithic" indicates that the final component has a structure in which the integrated parts are inseparable, and is distinct from a component comprising multiple independent component parts that are joined together but remain independent, and where the individual component is not inseparable (e.g., the part can be reseparated). Therefore, a monolithic component may comprise a substantially continuous piece of material, or it may comprise multiple parts permanently bonded together. In any case, the various parts forming a monolithic component are integrated with each other, such that the monolithic component is a single piece with inseparable parts.

[0021] As used herein, the term "composite material" refers to a material made of two or more constituent materials. "Composite material" also means that at least one constituent material is a non-metallic material. Exemplary composite materials include polymer-based composites (PMCs), ceramic-based composites (CMCs), chopped fiber composites, etc.

[0022] The term “adjacent” as used in this document with respect to two walls and / or surfaces means that the two walls and / or surfaces are in contact with each other, or that the two walls and / or surfaces are separated only by one or more unstructured layers, and that the two walls and / or surfaces and the one or more unstructured layers are in a series contact relationship (e.g., the first wall / surface contacts the one or more unstructured layers, and the one or more unstructured layers contact the second wall / surface).

[0023] The phrases “from X to Y” and “between X and Y” both refer to a range of values ​​that includes the endpoints (e.g., a range of values ​​that includes both X and Y).

[0024] The term "turbine" refers to a machine that includes one or more compressors, a heat generation section (e.g., a combustion section), and one or more turbines, which together produce torque output.

[0025] The term "gas turbine engine" refers to an engine that has a turbine as its power source, either entirely or partially. Examples of gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, and hybrid electric versions of one or more of these engines.

[0026] The terms “low” and “high” or their respective comparatives (e.g., lower, higher, as applicable), when used with compressors, turbines, shafts, or spool components, refer to relative speeds within an engine, unless otherwise specified. For example, “low turbine” or “low-speed turbine” defines a component configured to operate at a rotational speed (e.g., maximum permissible rotational speed) lower than that of the engine’s “high turbine” or “high-speed turbine”.

[0027] The terms "forward" and "backward" refer to the relative positions within the gas turbine engine or vehicle, and are based on the normal operating attitude of the gas turbine engine or vehicle. More specifically, in this document, forward and backward refer to the direction of travel of the vehicle and the direction of propulsion thrust of the gas turbine engine.

[0028] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to the centerline of the gas turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the gas turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends in an arc around the centerline of the gas turbine engine.

[0029] The terms "upstream" and "downstream" refer to the relative directions of flow within a pathway. For example, in fluid flow, "upstream" refers to the direction from which the fluid flows out, and "downstream" refers to the direction from which the fluid flows in. For instance, when used for fluid flow, forward / forward can indicate upstream, while backward / backward can indicate downstream.

[0030] Furthermore, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to the direction along a ray extending between the engine's central longitudinal axis and the engine's outer circumference.

[0031] Furthermore, any arrangement of components that perform the same function is effectively “associated” to achieve that function. Therefore, any two components combined in this document to achieve a specific function can be considered “associated” with each other, enabling the defined function regardless of the architecture or intermediate components. Similarly, any two such associated components can also be considered “operably connected” or “operably linked” with each other to achieve the defined function, and any two components that can be suchly associated can also be considered “operably linkable” with each other to achieve the defined function. Some examples of being operablely linkable include, but are not limited to, physically matchable, physically interacting components, wirelessly interactive components, logically interactive and / or logically interactive components.

[0032] As used herein, the term "fluid" can refer to a gas or a liquid. The term "fluid connectivity" means that fluids can establish connections between specified areas.

[0033] As used herein, the term "around" describes a circular path around a center point and / or axis. For example, when an object rotates clockwise and / or counterclockwise around its center, it can be described as "rotating around its center".

[0034] In this paper, "third flow" refers to a non-primary airflow that can increase fluid energy to generate a small portion of the total thrust of the propulsion system. The third flow typically receives inlet air (air from a duct downstream of the main fan) rather than free-flowing air (as with the main fan). The pressure ratio of the third flow can be higher than that of the primary propulsion flow (e.g., bypass or propeller-driven propulsion flow). Thrust can be generated through dedicated nozzles or through a mixture of the third flow and the primary or core propulsion flow, such as through a common nozzle.

[0035] In some embodiments, the operating temperature of the airflow through the third flow can be below the engine's maximum compressor exhaust temperature, more specifically below 350 degrees Fahrenheit (e.g., below 300 degrees Fahrenheit, below 250 degrees Fahrenheit, below 200 degrees Fahrenheit, and at least as high as ambient temperature). In some embodiments, these operating temperatures can facilitate heat transfer to or from the airflow through the third flow and the individual fluid flows. Furthermore, in some embodiments, under takeoff conditions, or more specifically, under operating conditions at rated takeoff power at sea level, static flight speed, and an ambient temperature of 86 degrees Fahrenheit, the airflow through the third flow can contribute less than 50% (and at least, for example, 2%) of the total engine thrust. Furthermore, in some embodiments, the various aspects of the third flow (e.g., airflow, mixing, or exhaust characteristics) and the resulting percentage of total thrust contribution described above can be passively adjusted during engine operation or purposefully modified by using engine control features (e.g., fuel flow rate, motor power, variable stator, variable inlet guide vanes, valves, variable exhaust geometry, or fluid characteristics) to adjust or optimize overall system performance under a wide range of potential operating conditions.

[0036] Approximate language, as used throughout this specification and claims, is used to modify any quantitative expression that can be permissibly varied without altering the essential function it relates to. Therefore, values ​​modified by terms or phrases such as “about,” “approximately,” and “substantially” are not limited to the specified precise values. At least in some cases, approximate language may correspond to the precision of the instrument measuring the value, or the precision of the method or apparatus for constructing or manufacturing the component and / or system. For example, approximate language may refer to a margin of ten percent.

[0037] This disclosure generally relates to gas turbine engines and heat exchanger assemblies. Typically, a gas turbine engine may include despinning features (e.g., an outlet guide vane arrangement) at a mid-fan location and / or a low-pressure turbine location upstream of the heat exchanger assembly. The heat exchanger assembly is used to exchange heat energy between various fluids within the gas turbine engine for the operation of various components. This despinning feature typically despins the flow upstream of the heat exchanger assembly. That is, the despinning feature removes the circumferential component of the flow velocity vector upstream of the heat exchanger assembly. However, this arrangement may introduce undesirable pressure drops across the heat exchanger assembly, thus affecting engine performance. Therefore, the heat exchanger assembly and / or structural frame struts may include despinning mechanisms arranged to produce a more axially aligned flow through the heat exchanger and around engine ducts without including despinning features for the function of the heat exchanger assembly. For example, the heat exchanger assembly may include one or more aerodynamic features extending into at least one of the inlet ducts, fan ducts, and / or core ducts to improve the efficiency of the heat exchanger assembly while modulating and / or eliminating the circumferential component of the flow velocity vector of the fluid flow. This reduces the pressure drop across the heat exchanger assembly, thus contributing to improved engine performance. Furthermore, the reduced pressure drop allows for a shorter axial length of the heat exchanger assembly, which benefits the encapsulation process.

[0038] Now for reference Figure 1 A schematic cross-sectional view of a gas turbine engine 100 is provided. Specifically, Figure 1 A turbofan engine with a rotor assembly having single-stage ductless rotor blades is provided. Thus, the rotor assembly may be referred to herein as a "ductless fan," or the entire engine 100 may be referred to as a "ductless turbofan engine." Furthermore, Figure 1 The engine 100 includes a third flow that extends from the compressor section to the rotor assembly flow path above the turbine, as will be explained in more detail below.

[0039] For reference, engine 100 defines an axial direction A, a radial direction R, and a circumferential direction C. Furthermore, engine 100 defines an axial centerline or longitudinal axis 112 extending along the axial direction A. Typically, the axial direction A extends parallel to the longitudinal axis 112, the radial direction R extends outward and inward from the longitudinal axis 112 in a direction perpendicular to the axial direction A, and the circumferential direction extends 360° around the longitudinal axis 112. Engine 100 extends along the axial direction A between a front end 114 and a rear end 116.

[0040] Engine 100 includes a turbine 120 and a rotor assembly located upstream therefrom, also referred to as a fan section 150. Typically, turbine 120 includes, in sequence, a compressor section, a combustion section, a turbine section, and an exhaust section. Specifically, as... Figure 1 As shown, turbine 120 includes a core shroud 122 that defines an annular core inlet 124. The core shroud 122 also at least partially surrounds the low-pressure system and the high-pressure system. For example, the illustrated core shroud 122 at least partially surrounds and supports a turbocharger or low-pressure (“LP”) compressor 126 for pressurizing air entering turbine 120 through core inlet 124. A high-pressure (“HP”) multi-stage axial compressor 128 receives the pressurized air from the LP compressor 126 and further increases the air pressure. The pressurized air flows downstream to a combustor 130 in 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.

[0041] It should be understood that, as used herein, the terms “high / low speed” and “high / low pressure” are used interchangeably for high-pressure / high-speed systems and low-pressure / low-speed systems, respectively. Furthermore, it should be understood that the terms “high” and “low” are used in this same context to distinguish between the two systems and do not imply any absolute speed and / or pressure values.

[0042] High-energy combustion products flow downstream from combustor 130 to high-pressure turbine 132. High-pressure turbine 132 drives high-pressure compressor 128 via high-pressure shaft 136. In this respect, high-pressure turbine 132 is drivably connected to high-pressure compressor 128. The high-energy combustion products then flow to low-pressure turbine 134. Low-pressure turbine 134 drives components of low-pressure compressor 126 and fan section 150 via low-pressure shaft 138. In this respect, low-pressure turbine 134 is drivably connected to components of low-pressure compressor 126 and fan section 150. The LP shaft 138 may be coaxial with the HP shaft 136. After driving the respective turbines 132 and 134, the combustion products exit turbine 120 through turbine exhaust nozzle 140.

[0043] Therefore, turbine 120 defines a working gas flow path, or core duct 142, which extends between core inlet 124 and turbine exhaust nozzle 140. Core duct 142 is an annular duct, typically located inside core shroud 122 in the radial direction R. Core duct 142 (e.g., through the working gas flow path of turbine 120) may be referred to as a second flow.

[0044] Fan section 150 includes fan 152, which in the example shown is the main fan. For Figure 1 In the example shown, fan 152 is an open rotor or ductless fan 152. Thus, engine 100 can be referred to as an open rotor engine.

[0045] As shown in the figure, fan 152 includes an array of fan blades 154 ( Figure 1 (Only one is shown). Fan blade 154 is capable, for example, of rotating about longitudinal axis 112. As described above, fan 152 is drivenly connected to low-pressure turbine 134 via LP shaft 138. For Figure 1 In the example shown, fan 152 is connected to LP shaft 138 via reduction gearbox 155, for example, in an indirect drive or gear drive configuration.

[0046] Furthermore, the array of fan blades 154 can be arranged at equal intervals around 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. In the illustrated example, each fan blade 154 of the fan 152 is capable of rotating about its respective central blade axis 156, for example, rotating synchronously with each other. One or more actuators 158 are provided to facilitate this rotation, and thus can be used to change the pitch of the fan blades 154 about their respective central blade axes 156.

[0047] Fan section 150 further includes a fan guide vane array 160, which includes fan guide vanes 162 arranged around a longitudinal axis 112. Figure 1 (Only one is shown). In the example shown, the fan guide vane 162 cannot rotate about the longitudinal axis 112. Each fan guide vane 162 has a root and a tip. The span is defined between the root and the tip. The fan guide vane 162 can be unshielded, such as... Figure 1 As shown, it can also be a shielded one, for example, an annular shield spaced apart from or attached to the tip of the fan guide vane 162 in the radial direction R.

[0048] Each fan guide vane 162 defines a central blade axis 164. In the illustrated example, each fan guide vane 162 of the fan guide vane array 160 is rotatable about its respective central blade axis 164, for example, rotatable synchronously with each other. One or more actuators 166 are provided to facilitate this rotation, and thus can be used to change the pitch of the fan guide vane 162 about its respective central blade axis 164. However, 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 on a fan shroud 170.

[0049] like Figure 1As shown, in addition to the ductless fan 152, a ducted fan 184 is further included at the rear of fan 152, so engine 100 includes both a ducted fan and a ductless fan, both used to generate thrust by the movement of air without passing through at least a portion of the passage of turbine 120 (e.g., in the illustrated example, without passing through the passage of HP compressor 128 and the combustion section). The ducted fan 184 is rotatable about the same axis as the fan blades 154 (e.g., longitudinal axis 112). The ducted fan 184 may be driven by a low-pressure turbine 134 (e.g., coupled to LP shaft 138). As mentioned above, fan 152 may be referred to as the primary fan, while ducted fan 184 may be referred to as the secondary fan. It should be understood that these terms "primary" and "secondary" are convenient designations and do not imply any particular importance, power, etc.

[0050] The duct fan 184 includes multiple fan blades arranged in a single stage. Figure 1 (Not separately marked), therefore the duct fan 184 can be referred to as a single-stage fan. The fan blades of the duct fan 184 can be arranged at equal intervals around the longitudinal axis 112. Each blade of the duct fan 184 has a root and a tip. The span is defined between the root and the tip.

[0051] The fan shroud 170 annularly surrounds at least a portion of the core shroud 122 and is generally located outside at least a portion of the core shroud 122 in the radial direction R. Specifically, a downstream section of the fan shroud 170 extends over the front portion of the core shroud 122 to define a fan duct flow path, or simply fan duct 172. In the illustrated example, the fan flow path or fan duct 172 can be understood as forming at least a portion of the third flow of the engine 100.

[0052] Incoming air enters fan duct 172 through fan duct inlet 176 and exits through fan exhaust nozzle 178 to generate propulsive thrust. Fan duct 172 is an annular duct, typically located radially R outside core duct 142. Fan shroud 170 and core shroud 122 are connected by a plurality of generally radially extending, circumferentially spaced fixed struts 174 ( Figure 1 (Only one is shown in the diagram) Connections and supports. Each fixed strut 174 may have an aerodynamic profile to guide the flow of air. In addition to the fixed struts 174, other struts may 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 extend at least partially (generally 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 extend directly from the leading edge 144 of the core shroud 122 and may extend substantially axially and partially together on opposite radial sides of the core shroud 122.

[0053] Engine 100 also defines or includes an inlet duct 180. Inlet duct 180 extends between engine inlet 182 and core inlet 124 / fan duct inlet 176. Engine inlet 182 is generally defined at the front end of fan shroud 170 and is located axially A between fan 152 and fan guide vane array 160. Inlet duct 180 is an annular duct located radially R inside fan shroud 170. Air flowing downstream along inlet duct 180 is diverted (not necessarily uniformly) into core duct 142 and fan duct 172 by a fan duct splitter or the leading edge 144 of core shroud 122. In the example shown, inlet duct 180 is wider radially R than core duct 142. Inlet duct 180 is also wider radially R than fan duct 172.

[0054] It is worth noting that engine 100 includes one or more features to enhance third-flow thrust Fn 3S (For example, the thrust generated by the airflow through fan duct 172 and discharged from fan exhaust nozzle 178, at least partially generated by duct fan 184) efficiency. Specifically, engine 100 further includes an array of inlet guide vanes 186 located in inlet duct 180, upstream of duct fan 184 and downstream of engine inlet 182. The array of inlet guide vanes 186 is arranged about a longitudinal axis 112. As shown, the inlet guide vanes 186 cannot rotate about the 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, for example, rotating synchronously with each other. Thus, the inlet guide vanes 186 can be considered variable geometry components. One or more actuators 188 are provided to facilitate this rotation and can therefore be used to change the pitch of the inlet guide vanes 186 about their respective central blade axes. However, each inlet guide vane 186 may be fixed or unable to pitch about its central blade axis.

[0055] Furthermore, the fan exhaust nozzle 178 of the fan duct 172 can be further configured as a variable geometry exhaust nozzle. Thus, the 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 change its total cross-sectional area (e.g., the area of ​​the nozzle in a plane perpendicular to the longitudinal axis 112) to adjust the generated thrust 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 can also be used.

[0056] The combination of the inlet guide vane array 186 located upstream of the duct fan 184 and the fan exhaust nozzle 178 can achieve a more efficient third-flow thrust Fn under one or more engine operating conditions. 3S The generation of the engine. Furthermore, by introducing geometric variability into the inlet guide vane 186 and the fan exhaust nozzle 178, the engine 100 can operate under a relatively wide range of engine operating conditions (including takeoff and climb, which typically require maximum total engine thrust Fn). Total And cruise (which typically requires a smaller amount of total engine thrust Fn) Total This generates a more efficient third-flow thrust Fn 3S .

[0057] In addition, still refer to Figure 1 In some cases, the air passing through fan duct 172 may be relatively colder (e.g., lower in temperature) than one or more fluids utilized in turbine 120. Thus, one or more heat exchanger assemblies 200 may be positioned in thermal communication with fan duct 172. For example, one or more heat exchanger assemblies 200 may be arranged within fan duct 172 and utilize the air passing through fan duct 172 to cool one or more fluids of engine 100 as a resource for removing heat from fluids (e.g., compressor bleed air, oil, fuel, and / or any other fluid).

[0058] The heat exchanger assembly 200 may be an annular heat exchanger assembly extending substantially 360 degrees (e.g., at least 300 degrees, such as at least 330 degrees) within the fan duct 172. In this way, the heat exchanger assembly 200 can effectively utilize the air passing through the fan duct 172 to cool one or more systems of the engine 100 (e.g., lubrication system, compressor bleed air, electrical components, etc.). The heat exchanger assembly 200 can use the air passing through the fan duct 172 as a heat sink, and accordingly increase the temperature of the air downstream of the heat exchanger assembly 200 and discharged from the fan exhaust nozzle 178.

[0059] The heat exchanger assembly 200 may be an air-cooled oil cooler (ACOC), a waste heat recovery heat exchanger, or any other heat exchanger assembly suitable for the configuration of the gas turbine engine 100. Furthermore, the heat exchanger assembly 200 may be arranged within the gas turbine engine 100, for example, within (e.g., around) any suitable piping, to perform any suitable heat transfer.

[0060] Now for reference Figure 2-5Several views of a heat exchanger assembly 200 according to various aspects of this disclosure are depicted. As described above, the heat exchanger assembly 200 may extend annularly around an engine conduit 202. For example, the heat exchanger assembly 200 may extend annularly around the centerline of any suitable engine conduit 202, which may be arranged as an inlet conduit 180 ( Figure 1 ), Fan duct 172 ( Figure 1 ), core pipeline 142 ( Figure 1 (or any other conduit). The heat exchanger assembly 200 may extend circumferentially around the centerline 210 of the engine conduit 202 along the inner surface of the engine conduit 202.

[0061] As mentioned above, in the gas turbine engine 100 ( Figure 1 During operation, fluid flow through engine conduit 202 can provide a means of heat transfer with another fluid flow through heat exchanger assembly 200. For example, a first fluid flow 204 can be guided through engine conduit 202 and exchange heat with a second fluid flow 206 within heat exchanger assembly 200. That is, the first fluid flow 204 can be guided through engine conduit 202 to interact with components of heat exchanger assembly 200, while the second fluid flow 206 can flow through components of heat exchanger assembly 200 to achieve heat transfer with the first fluid flow 204.

[0062] Still referencing Figure 2-5 The heat exchanger assembly 200 may include a sheet assembly 208 that extends circumferentially about the engine duct centerline axis 210 and is located on the inner surface 201 of the engine duct 202. Figure 3 The radial inner side of the sheet assembly 208. For example, the sheet assembly 208 may be composed of sheet 209. More specifically, the sheet assembly 208 may be composed of at least one sheet and up to five sheets, each sheet being concentrically spaced apart from each other. Additionally, or alternatively, in some cases, the inner and outer walls defining the engine conduit 202 may serve as sheet 209.

[0063] The heat exchanger assembly 200 may also include one or more aerodynamic features 212 extending from the sheet assembly 208. For example, one or more aerodynamic features 212 may extend radially from the sheet 209. The one or more aerodynamic features 212 may extend any suitable length in either direction to engage with the respective sheets 209 of the sheet assembly 208. For example, the aerodynamic features 212 may contact multiple sheets 209 within the sheet assembly 208, which may mitigate the deflection of the respective sheets 209 during operation of the gas turbine engine 100. For example, one or more aerodynamic features 212 extend from the inner surface 201 of the engine duct 202 (… Figure 3The aerodynamic features 212 extend radially inward toward the engine duct centerline axis 210. Furthermore, one or more aerodynamic features 212 may extend from the sheet assembly 208 at a first angle 213. For example, the first angle 213 between one or more aerodynamic features 212 and the sheet assembly 208 may be at least 20 degrees and up to 90 degrees. In various examples, one or more aerodynamic features 212 may consist of a set of fins 214, a manifold assembly 216, and / or any suitable feature configuration to achieve the function of the heat exchanger assembly 200.

[0064] In an example where one or more aerodynamic features 212 may consist of a set of fins 214, the set of fins 214 may be spaced apart from each other in the circumferential direction at least by a portion of the sheet assembly 208. For example, the set of fins 214 may be spaced apart from each other in a uniform, non-uniform, or any suitable manner. Furthermore, one or more aerodynamic features 212 may consist of at least one set of fins 214 to any practically feasible number of sets of fins 214. In addition, a set of fins 214 may consist of at least one fin, up to fifty fins, and / or any other practically feasible number of fins.

[0065] Each of the set of fins 214 can define a fin thickness 218. As shown, the fin thickness 218 can be defined as the length of the fin in the circumferential direction. In some examples, the fin thickness 218 can be uniform along the entire length of the fin in the axial direction. In other cases, the fin thickness 218 can increase or decrease along the axial length of the fin. Furthermore, each of the set of fins 214 can have the same fin thickness 218 as the remaining fins 214 in the set. In other cases, at least one of the fins 214 in the set can have a thickness different from that of at least one of the fins 214 in the set.

[0066] Furthermore, each of the set of fins 214 may include a fin chord length 220. As shown, the fin chord length 220 may be the length of the fin in the axial direction. For example, each of the set of fins 214 may have the same fin chord length 220. In other cases, at least one of the set of fins 214 may have a different fin chord length 220 than the other in the set of fins 214. Moreover, the fin chord length 220 may be any suitable length to exchange heat energy with the first fluid 204 flowing through the engine conduit 202.

[0067] In various embodiments, the set of fins 214 may also include axially straight fin sections 222 and curved fin sections 224 in the axial direction. As shown, the axially straight fin section 222 may be downstream of the curved fin section 224. Specifically, the curved fin section 224 may be twenty percent or more of the fin chord length 220. In some cases, the curved fin section 224 may be half of the fin chord length 220. In other cases, the fin may include only the curved fin section 224, which extends from the leading edge to the trailing edge of the fin. In some examples, the set of fins 214 may be arranged such that each individual fin has the same shape, that is, the curved fin section 224 and the axially straight fin section 222 are equal in each individual fin. Thus, the set of fins 214 can be arranged such that they can nest with each other. As used herein, “nested” and “nested” can mean that each of the manifold assembly 216 and / or fin 214 maintains the same shape and allows the same circumferential spacing between each fin 214 and the plurality of manifolds 215 to be maintained over the entire length of each of the manifolds 215 and / or fins 214.

[0068] During operation, the first fluid flow 204 through engine duct 202 can interact with the curved fin section 224. For example, the curved fin section 224 can help create a more axially aligned first fluid flow 204 by deswirling the first fluid flow 204. As used herein, "deswirling" can refer to removing the circumferential component of the flow velocity vector. In particular, the swirling flow may follow a helical or plug-drill pattern. However, the circumferential motion of the airflow does not contribute to the thrust of the gas turbine engine 100. Thus, deswirling the fluid flow from a helical pattern to an axial flow is beneficial to improving the thrust generation efficiency of the gas turbine engine 100. Therefore, the curved fin section 224 can interact with the fluid flow, particularly with the circumferential component of the flow velocity vector. The curved fin section 224 can remove the circumferential component to achieve a more axially aligned first fluid flow 204.

[0069] Each of the set of fins 214 may define a fin height 226. As shown, the fin height 226 is the length from the radially inner end section to the radially outer end section. The fin height 226 can be any suitable length to facilitate heat transfer between the first fluid flow 204 through the engine conduit 202 and the second fluid flow 206 through the heat exchanger assembly 200. Each of the set of fins 214 may have a uniform fin height 226, a non-uniform fin height 226, or any combination of fin heights 226 among themselves.

[0070] Still referencing Figure 2-5In various configurations, one or more aerodynamic features 212 are arranged as a manifold assembly 216. The manifold assembly 216 may include one or more manifolds 215. Each manifold 215 of the manifold assembly 216 may be spaced apart from each other in the circumferential direction by at least a portion of the sheet assembly 208. For example, each manifold 215 of the manifold assembly 216 may be spaced apart from each other in a uniform, non-uniform, or any suitable manner. Furthermore, each manifold 215 of the manifold assembly 216 may include a front fairing 228 and a rear fairing 230. For example, the front fairing 228 may include the foremost portion of the manifold 215, and the rear fairing 230 may include the downstreammost portion of the manifold 215.

[0071] In various cases, manifold assembly 216 can supply or recover working fluid, such as second fluid 206, to or from the heat exchanger assembly. Additionally or alternatively, manifold assembly 216 can engage sections and / or portions of heat exchanger assembly 200, such as sheet assembly 208, at least a portion of a set of fins 214, or any other component of heat exchanger assembly 200 to encompass the entire assembly. In this way, manifold assembly 216 can alleviate manufacturing limitations associated with incorporating one or more aerodynamic features 212 into heat exchanger assembly 200. Furthermore, the arrangement of manifold assembly 216 can alleviate mechanical limitations in terms of the overall size of heat exchanger assembly 200 by serving a variety of purposes.

[0072] In various cases, manifold assembly 216 may include a first manifold 217 and a second manifold 219. The first manifold 217 may be separated from the second manifold 219 by at least a portion of a sheet 209. For example, the first manifold 217 may be spaced apart from the second manifold 219 in a circumferential direction, wherein the sheet 209 spans at least a portion of the space between the first manifold 217 and the second manifold 219. In other cases, manifold assembly 216 may include any suitable number of manifolds 215.

[0073] Each manifold 215 of manifold assembly 216 may define a manifold thickness 232. As shown, the manifold thickness 232 may be the length spanned in the circumferential direction by opposite endpoints on the surface of manifold 215. For example, each manifold 215 in manifold assembly 216 may include a uniform manifold thickness 232, a non-uniform manifold thickness 232, or any combination thereof. In various examples, a first manifold 217 may define a first manifold thickness, and a second manifold 219 may define a second manifold thickness. The first manifold thickness may be the same as the second manifold thickness. In other cases, the first manifold thickness may be different from the second manifold thickness.

[0074] Each manifold 215 in manifold assembly 216 may also define a manifold chord length 234. As shown, the manifold chord length 234 can be the length spanned in the axial direction by the manifold 215 from opposite endpoints on the surface of the manifold 215, for example, from the front fairing 228 to the rear fairing 230. For example, each manifold 215 in manifold assembly 216 may define a uniform manifold chord length 234, a non-uniform manifold chord length 234, or any combination of manifold chord lengths 234. For example, a first manifold 217 may define a first manifold chord length, and a second manifold 219 may define a second manifold chord length. The first manifold chord length may be the same as the second manifold chord length. In other cases, the first manifold chord length may be different from the second manifold chord length.

[0075] In various cases, the manifold chord length 234 may also include an axially straight manifold section 236 and a curved manifold section 238. As shown, the axially straight manifold section 236 may be downstream of the curved manifold section 238. Specifically, the curved manifold section 238 may be twenty percent or more of the manifold chord length 234. In some cases, the curved manifold section 238 may be half the manifold chord length 234. In other cases, the manifold chord length 234 may consist only of the curved manifold section 238, which extends from the front fairing 228 and the rear fairing 230. For example, the manifold assembly 216 may be arranged such that each individual manifold 215 is identical in shape, meaning that the curved manifold section 238 and the axially straight manifold section 236 are equal throughout the manifold assembly 216. Thus, the manifold assembly 216 can be arranged such that they can nest with each other.

[0076] During operation, the first fluid flow 204 through engine conduit 202 can interact with the curved manifold section 238. For example, the curved manifold section 238 can help create a more axially aligned first fluid flow 204 by despinning the first fluid flow 204. Similar to the function of the curved fin section 224 mentioned above, the curved manifold section 238 can function in a similar manner. More specifically, the thrust efficiency of the gas turbine engine can be improved by a more axially aligned flow generated through the interaction of the circumferential component of the fluid flow (specifically the flow velocity vector) with the curved manifold section 238.

[0077] In various cases, each manifold 215 of manifold assembly 216 may also define a manifold height 240. As shown, the manifold height 240 can be the length spanned in the radial direction by the manifold 215 from opposite endpoints (e.g., radial inner and radial outer ends) on the surface of the manifold 215. For example, each manifold 215 of manifold assembly 216 may define a uniform manifold height 240, a non-uniform manifold height 240, or any combination of manifold heights 240. For example, a first manifold 217 may define a first manifold height, and a second manifold 219 may define a second manifold height. The first manifold height may be the same as the second manifold height. In other cases, the first manifold height may be different from the second manifold height.

[0078] Still referencing Figure 2-5 One or more aerodynamic features 212 may include a combination of a set of fins 214 and a manifold assembly 216 as shown. For example, a heat exchanger assembly 200 may have a first manifold 217 and a second manifold 219 separated from each other in the circumferential direction. Furthermore, the heat exchanger assembly 200 may include at least a portion of a set of fins 214 between the first manifold 217 and the second manifold 219. In other cases, the heat exchanger assembly 200 may include any number of manifolds 215 separated from each other in the circumferential direction. At least a portion of a set of fins 214 may be located between each manifold 215. The space between each manifold 215 may have at least one fin, up to thirty fins, and / or any other practically feasible number of fins. Additionally, a sheet assembly 208 may extend in the circumferential direction between each aerodynamic feature 212.

[0079] Furthermore, one or more aerodynamic features 212, such as a combination of fins 214 and manifold assemblies 216, can be arranged in a nested manner. As described in more detail above, the manifold chord 234 may include an axial straight manifold section 236 and a curved manifold section 238. Additionally, the fin chord 220 may include an axial straight fin section 222 and a curved fin section 224. As shown, the axial straight manifold section 236 and the axial straight fin section 222 may have the same length throughout the heat exchanger assembly 200, such that each of the one or more aerodynamic features 212 can be nested with each other. For example, each curved manifold section 238 may have the same curvature as each curved fin section 224. Thus, the manifold 215 and fins 214 are arranged such that the same circumferential spacing is maintained between each fin and each manifold 215 along the entire length of each of the manifold 215 and / or fins 214. In other cases, the manifold chord 234 may consist only of the curved manifold section 238, and the fin chord 220 may consist only of the curved fin section 224. In this case, the manifold assembly 216 and a set of fins 214 may be arranged such that the curvature of each manifold 215 and fin 214 is parallel to each other, allowing the same circumferential spacing between each fin and manifold 215 to be maintained over the entire length of each of the manifolds 215 and / or fins 214.

[0080] In various cases, the set of fins 214 can also define a fin thickness chord ratio. As used herein, the fin thickness chord ratio is the ratio of fin thickness 218 to fin chord length 220. Furthermore, the manifold assembly 216 can also define a manifold thickness chord ratio. As used herein, the manifold thickness chord ratio is the ratio of manifold thickness 232 to manifold chord length 234. In various cases, the manifold thickness chord ratio can be greater than the fin thickness chord ratio. Furthermore, the manifold chord length 234 of each manifold 215 of the manifold assembly 216 can be longer than the fin chord length 220 of each fin of the set of fins 214.

[0081] Still referencing Figure 2-5 The manifold chord length 234 can be greater than the manifold height 240. For example, the manifold chord length 234 can be twice the length of the manifold height 240. In other cases, the manifold chord length 234 can be three times the length of the manifold height 240. Furthermore, the manifold chord length 234 can be any multiple greater than one times the length of the manifold height 240. Similarly, the fin chord length 220 can be greater than the fin height 226. For example, the fin chord length 220 can be twice the length of the fin height 226. In other cases, the fin chord length 220 can be three times the length of the fin height 226. Furthermore, the fin chord length 220 can be any multiple greater than one times the length of the fin height 226.

[0082] In various cases, the manifold chord length 234 can be greater than the manifold thickness 232. For example, the manifold chord length 234 can be eight times the manifold thickness 232. In other cases, the manifold chord length 234 can be twenty times the manifold thickness 232. Furthermore, the manifold chord length 234 can be any multiple greater than five times the manifold thickness 232. Similarly, the fin chord length 220 can be greater than the fin thickness 218. For example, the fin chord length 220 can be eight times the fin thickness 218. In other cases, the fin chord length 220 can be twenty times the fin thickness 218. Furthermore, the fin chord length 220 can be any multiple greater than five times the fin thickness 218.

[0083] Still referencing Figure 2-5 The heat exchanger assembly 200 can be arranged such that each manifold 215 of the manifold assembly 216 and each fin of the set of fins 214 are connected to each circumferentially extending sheet 209 of the sheet assembly 208. This allows the manifold assembly 216 and / or the set of fins 214 to mitigate flexure of the sheet assembly 208 during operation of the heat exchanger assembly 200. In other cases, the sheet assembly 208 may include two or more sheets 209. These sheets 209 can be arranged concentrically. As shown, the manifold assembly 216 and / or the set of fins 214 are connected to two or more sheets 209 of the sheet assembly 208 such that the sheet assemblies 208 can be interconnected with each other via the manifold assembly 216 and / or the set of fins 214.

[0084] The heat exchanger assembly 200 may also define a plurality of conduits 242 formed by the junction of the manifold assembly 216 and / or a set of fins 214 and the sheet assembly 208. As shown, the combined arrangement of the manifold assembly 216, the set of fins 214 and the sheet assembly 208 forms a plurality of conduits 242 through which a first fluid 204 passing through the engine conduit 202 flows and interacts with the heat exchanger assembly 200, as described in more detail below.

[0085] During operation, the first fluid 204 flow can interact with multiple conduits 242. For example, the first fluid 204 can be de-rotated through the curved manifold section 238 of the manifold assembly 216 and / or the curved fin section 224 of the set of fins 214. More specifically, the first fluid 204 flow can be guided through multiple conduits 242 to interact with the curved manifold section 238 of the manifold assembly 216 and / or the curved fin section 224 of the set of fins 214. In this way, the thrust efficiency of the gas turbine engine can be improved by a more axially aligned flow generated by the interaction of the circumferential component of the fluid flow (particularly the flow velocity vector) and the curved manifold section 238 of the manifold assembly 216 and / or the curved fin section 224 of the set of fins 214.

[0086] Now for reference Figure 6-8 The heat exchanger assembly 200 may also include a channel assembly 244 within the sheet assembly 208. The channel assembly 244 may be positioned within each sheet 209 and configured to circumferentially guide the flow of the second fluid 206 about the engine duct centerline axis 210, which may be along each sheet 209 of the sheet assembly 208. As shown, the channel assembly 244 may extend from a front end portion and meander axially toward a downstream end portion of the sheet assembly 208. For example, the channel assembly 244 may initially extend circumferentially in a clockwise direction and then turn counterclockwise to form channel windings 246, and vice versa. This pattern may be repeated any number of times in the axial direction. For example, the channel assembly 244 may consist of at least one channel winding 246 extending in the axial direction and up to fifty channel windings 246. In other cases, the channel assembly 244 may consist of any suitable number of channel windings 246 to transfer heat between the first fluid 204 flow and the second fluid 206 flow.

[0087] The heat exchanger assembly 200 may further include a channel assembly 248 within the manifold assembly 216. The channel assembly 248 may be positioned within each manifold 215 of the manifold assembly 216 and arranged to guide fluid flow radially along the surface of the manifold assembly 216, thereby transferring heat energy from or to the first fluid 204. For example, the channel assembly 248 may be positioned in fluid connection with a channel assembly 244 to transfer a second fluid 206 flow between the manifold assembly 216 and the sheet assembly 208. Specifically, as shown... Figure 8 As shown, the channel assembly 248 can flow radially inward along the surface of the manifold 215, then turn and flow radially outward along the surface of the manifold 215, and vice versa, forming the channel winding 250. This pattern can be repeated any number of times along the surface of the manifold 215.

[0088] Manifold assembly 216 may further include an inlet manifold portion 252 and an outlet manifold portion 254. As shown, the inlet manifold portion 252 and the outlet manifold portion 254 may form two halves of a single manifold 215. For example, the inlet manifold portion 252 may be adjacent to and connected to the outlet manifold portion 254 in the circumferential direction. Specifically, adjacent manifold portions 252, 254 may be connected together by welding, brazing, bolting, or any other suitable mechanical connection. In various cases, the inlet manifold portion 252 and the outlet manifold portion 254 may remain separate to allow independent movement during operation of the heat exchanger assembly 200. In various cases, the inlet manifold portion 252 and the outlet manifold portion 254 may form a separate structure. In other cases, the inlet manifold portion 252 and the outlet manifold portion 254 may be a single structure separated by an internal partition wall. Furthermore, the inlet manifold portion 252 may be fluidly connected to the outlet manifold portion 254 through at least a portion of a channel assembly. For example, the channel assembly may define a channel inlet 256 on the inlet manifold portion 252 and a channel outlet 258 on the outlet manifold portion 254.

[0089] In various cases, manifold assembly 216 may also include an intermediate manifold 266. As shown, intermediate manifold 266 may consist of an inlet manifold portion 252 and an outlet manifold portion 254, but may not include the channel inlet 256 and channel outlet 258 of channel assembly 248. For example, the inlet manifold portion 252 and the outlet manifold portion 254 of intermediate manifold 266 may be welded together, and may not include an internal partition wall between two adjacent portions of intermediate manifold 266. In some examples, one or more aerodynamic features 212 may include a manifold assembly comprising a first manifold 217, a second manifold 219, and an intermediate manifold, or third manifold 266, located between the first manifold 217 and the second manifold 219. A first set of fins 214 may extend circumferentially from sheet assembly 208 between the first manifold 217 and the third manifold 266. Additionally or alternatively, the second set of fins 214 may extend circumferentially from the sheet assembly 208 between the third manifold 266 and the second manifold 219.

[0090] Furthermore, in various cases, the heat exchanger assembly 200 may define a plurality of segments 268. Each segment 268 may be circumferentially separated by adjacent individual manifolds 215 of the manifold assembly 216. As shown, the heat exchanger assembly 200 may include at least a first heat exchanger segment comprising at least a portion of the manifold assembly 216, a set of fins 214, and at least a portion of the sheet assembly 208. In various cases, the first heat exchanger segment 257 may be defined as a circumferentially separated segment between the first manifold 217 and the second manifold 219. The first heat exchanger segment 257 may also include a set of fins 214 between the first manifold 217 and the second manifold 219. The set of fins 214 may be circumferentially spaced apart from each other in the space between them. For example, both the first manifold 217 and the second manifold 219 may include an inlet manifold portion 252 and an outlet manifold portion 254. Furthermore, the first manifold 217, the second manifold 219, and the set of fins 214 are connected to the sheet assembly 208. In other cases, the first heat exchanger section 257 may be defined as having the first manifold 217 and the second manifold 219 circumferentially separated, with a third manifold 221 between them. The first heat exchanger section 257 may also include a set of fins 214 circumferentially spaced apart from each other in the space between the first manifold 217 and the third manifold 221, and in the space between the second manifold 219 and the third manifold 221. For example, the third manifold 221 may be an intermediate manifold 266, while the first manifold 217 and the second manifold 219 each include a channel inlet 256 and a channel outlet 258. Furthermore, the first manifold 217, the second manifold 219, the third manifold 221, and the set of fins 214 are connected to the sheet assembly 208.

[0091] Typically, heat exchanger assembly 200 is used to exchange heat between various fluids within gas turbine engine 100 for the operation of various components. In some cases, heat exchanger assembly 200 may include a despinning mechanism to generate a more axially aligned flow through heat exchanger 200 and around engine duct 202 without including despinning features (e.g., outlet guide vane arrangement) for the function of heat exchanger assembly 200. That is, the despinning mechanism can remove the circumferential component of the flow velocity vector of the flow through heat exchanger assembly 200. For example, heat exchanger assembly 200 may include one or more aerodynamic features 212 extending to at least one of inlet duct 180, fan duct 172, and / or core duct 142 to improve the efficiency of heat exchanger assembly 200 while adjusting and / or eliminating the circumferential component of the flow velocity vector of the fluid flow. This reduces the pressure drop across heat exchanger assembly 200, thereby contributing to improved engine performance. Furthermore, due to the reduction in pressure drop, the axial length of heat exchanger assembly 200 can be reduced, providing benefits for encapsulation.

[0092] During operation, a first fluid flow 204 from engine conduit 202 is guided through a plurality of conduits 242 defined by components of heat exchanger assembly 200. The first fluid flow 204 may be de-rotated through a curved manifold section 238 of manifold assembly 216 and / or a curved fin section 224 of a set of fins 214. While the first fluid flow 204 contacts manifold assembly 216, sheet assembly 208, and set of fins 214, a second fluid flow 206 may be guided through a channel inlet 256 of inlet manifold portion 252. The second fluid flow 206 is then guided through at least a portion of a channel assembly 248 along the surface of manifold assembly 216. The first fluid flow 204 may come into thermal contact with the surface of manifold 215, thereby exchanging heat with the second fluid flow 206 in this manner. Furthermore, the second fluid flow 206 is then guided from channel assembly 248 into channel assembly 244 of sheet assembly 208. The first fluid 204 can make thermal contact with the surface of the sheet assembly 208, thereby exchanging heat energy with the second fluid 206 within the channel assembly 244. The second fluid 206 then returns from the channel assembly 244 to the channel assembly 248 located within the manifold assembly 216. The second fluid 206 is then directed into the outlet manifold portion 254 within the channel assembly 248 and returns to the gas turbine engine 100 via the channel outlet 258.

[0093] In other cases, the channel assembly 248 guides a third fluid flow 260 along the surface of the manifold 215. For example, the channel assembly 248 and the channel assembly 244 may not be fluidly connected; instead, the second fluid flow 206 and the third fluid flow 260 interact with the first fluid flow 204, respectively. Thus, the channel assembly 248 meanders along the surface of the manifold 215 to transfer heat with the first fluid flow 204. During operation, the first fluid flow 204 can be guided through a plurality of conduits 242 defined by components of the heat exchanger assembly 200. The first fluid flow 204 can contact the sheet assembly 208 and the manifold assembly 216. Thus, the first fluid flow 204 can exchange heat with the second fluid flow 206 within the sheet assembly 208 and the third fluid flow 260 within the manifold assembly 216. The third fluid flow 260 can flow along the surface of manifold 215, entering manifold 215 through channel inlet 256, flowing along the surface of manifold 215 in a serpentine manner, and then exiting manifold 215 through channel outlet 258. The second fluid flow 206 can enter channel assembly 244 through channel inlet 262 located on the surface of sheet 209, and flow along the surface of sheet 209 in the manner described in more detail above. Furthermore, the second fluid flow 206 can then exit channel assembly through channel outlet 264 located on the surface of sheet 209.

[0094] The heat exchanger assembly 200 may include any suitable arrangement to provide a deswirl effect on the first fluid 204 flow and to transfer heat energy with the second and / or third fluid flow located within the heat exchanger assembly 200, without departing from the scope of this disclosure.

[0095] Now for reference Figure 9 This provides a schematic diagram of a method for transferring heat energy between a first fluid flow 204 and a second fluid flow 206 according to various aspects of this disclosure. Typically, this method will refer to the above-described combination... Figure 2-8 The gas turbine engine 100 and heat exchanger assembly 200 are described. However, those skilled in the art will understand that the disclosed methods can generally be used in any suitable cooling system configuration. Furthermore, although... Figure 9 For illustrative and discussion purposes, the steps have been described in a specific order, but the methods discussed herein are not limited to any particular order or arrangement. Those skilled in the art, using the disclosure provided herein, will understand that the various steps of the methods disclosed herein can be omitted, rearranged, combined, and / or modified in various ways without departing from the scope of this disclosure.

[0096] In step 902, method 900 may include directing a first fluid flow through engine conduits. As described above, directing the first fluid flow through engine conduits may involve flow through inlet conduits, core conduits, or fan conduits. Furthermore, the first fluid flow may be any suitable flow for propelling a gas turbine engine. For example, the first fluid flow may be a core fluid flow or an additional fluid flow arranged via a third flow.

[0097] In step 904, method 900 may include using a manifold assembly and a set of fins to deswirl a first fluid flow through the engine conduit. As described above, the first fluid flow may contact a heat exchanger assembly assembled around the engine conduit. Here, the heat exchanger assembly may include deswirl elements (i.e., curved manifold sections and / or curved fin sections) that allow the first fluid flow through the engine conduit to be deswirled using the manifold assembly and / or the set of fins. Thus, the first fluid flow is directed through a plurality of conduits defined by components of the heat exchanger assembly, including the manifold assembly and the set of fins. The curved manifold sections of the manifold assembly and / or the curved fin sections of the set of fins can produce a deswirl effect on the first fluid flow through the engine conduit. For example, when the first fluid flow is directed through the plurality of conduits, it may interact with the curved manifold sections of the manifold assembly and / or the curved fin sections of the set of fins, thus deswirling the fluid flow due to the aerodynamic interaction between the first fluid flow and the curved manifold sections and / or the curved fin sections.

[0098] In step 906, method 900 may include guiding a second fluid flow through the sheet. As described above, the second fluid flow may flow through the sheet using a channel assembly disposed within each sheet of the sheet assembly. For example, the second fluid flow may enter the channel assembly via a channel inlet in the inlet manifold portion of the manifold assembly, first entering the heat exchanger assembly. The second fluid flow then flows through a channel assembly disposed within the sheet, the channel assembly consisting of a plurality of windings extending axially downstream along the sheet.

[0099] In step 908, method 900 may include transferring thermal energy between the first fluid flow and the second fluid flow. As described above, the first fluid flow contacts the sheet as the second fluid flow is guided through it. In this way, the second and first fluid flows can exchange thermal energy. For example, the second fluid flow may be guided in a serpentine arrangement close to the sheet surface through the sheet. The first fluid flow is guided through multiple conduits, interacting with the surfaces of the manifold assembly, the set of fins, and the sheet assembly. Thus, the first and second fluid flows can exchange thermal energy. After the thermal energy transfer, the second fluid flow is then guided to the outlet manifold portion to return to the gas turbine engine through the channel outlet.

[0100] In other cases, method 900 may further include guiding a first fluid flow through a plurality of conduits defined by a manifold assembly, the set of fins, and sheets. As described above, the first fluid flow may be guided through the plurality of conduits defined by the manifold assembly, the plurality of curved fins, and sheets to deswirl the first fluid flow. During the guidance through the plurality of conduits, the first fluid flow increases its contact with the heat exchanger assembly, allowing for improved efficiency of heat transfer between the first fluid flow and a second fluid flow guided along the inner surface of the heat exchanger assembly.

[0101] In other cases, method 900 may further include guiding a second fluid flow through a channel assembly within the sheet, guiding the second fluid flow from the channel assembly to a channel assembly within a manifold assembly, and guiding the second fluid flow through the channel assembly within the manifold assembly. As described above, the second fluid flow may be guided into the channel assembly, which comprises at least one channel. For example, the channel assembly may include a serpentine arrangement along the interior of the sheet. The channel assembly may guide the fluid in a winding arrangement extending axially downstream. After the second fluid flow reaches the axially downstream end of the sheet, the second fluid flow is then guided into a channel assembly within a manifold of the manifold assembly. For example, the second fluid flow may be guided through a joint between the channel assembly and the channel assembly to fluidly connect the two components.

[0102] In other cases, method 900 may further include guiding a second fluid flow along the surfaces of the manifold assembly and the sheet, and bringing the first fluid flow into thermal contact with the surfaces of the manifold assembly and the sheet. As described in more detail above, the second fluid flow may be guided through a channel assembly located within the sheet. For example, the channel assembly may be close to the surface of the sheet to allow the second fluid flow to exchange heat with the first fluid flow when the first fluid flow contacts the outer surface of the sheet. Furthermore, the second fluid flow may be guided from the channel assembly within the sheet to a channel assembly of the manifold assembly. The second fluid flow may be guided through a channel assembly housed within the manifold assembly. For example, the channel assembly may be close to the surface of the manifold assembly to allow the second fluid flow to exchange heat with the first fluid flow when the first fluid flow contacts the outer surface of the manifold assembly.

[0103] This disclosure generally relates to a gas turbine engine 100 and a heat exchanger assembly 200. Typically, the gas turbine engine 100 may include despinning features (e.g., an outlet guide vane arrangement) located upstream of the heat exchanger assembly 200 at a mid-fan location and / or at a low-pressure turbine 134. The heat exchanger assembly 200 is used to exchange heat energy between various fluids within the gas turbine engine 100 for the operation of various components. The despinning feature typically despins the flow upstream of the heat exchanger assembly 200. That is, the despinning feature removes the circumferential component of the flow velocity vector upstream of the heat exchanger assembly 200. However, this arrangement may introduce undesirable pressure drops across the heat exchanger assembly 200, thus affecting engine performance. Therefore, the heat exchanger assembly 200 may include a despinning mechanism arranged to generate a more axially aligned flow through the heat exchanger 200 and around the engine duct 202, without the despinning feature required for the function of the heat exchanger assembly 200. For example, heat exchanger assembly 200 may include one or more aerodynamic features 212 extending into at least one of inlet duct 180, fan duct 172, and / or core duct 142 to improve the efficiency of heat exchanger assembly 200 while adjusting and / or eliminating the circumferential component of the flow velocity vector of the fluid flow. This reduces the pressure drop across heat exchanger assembly 200, thereby contributing to improved engine performance. Furthermore, due to the reduced pressure drop, the axial length of heat exchanger assembly 200 can be reduced, providing benefits for encapsulation.

[0104] Further aspects are provided by the following topics:

[0105] A gas turbine engine defining radial and axial directions, the gas turbine engine comprising: an inlet duct including a splitter; a fan duct downstream of the inlet duct and the splitter; a core duct downstream of the inlet duct and the splitter, the core duct being radially inward of the fan duct; and a heat exchanger assembly extending annularly around at least one of the inlet duct, the fan duct, or the core duct, the heat exchanger assembly comprising: a sheet extending circumferentially around at least one of the inlet duct, the fan duct, and the core duct; and one or more aerodynamic features extending from the sheet, the one or more aerodynamic features being located within at least one of the inlet duct, the fan duct, and the core duct.

[0106] A gas turbine engine according to any of the foregoing clauses, wherein the one or more aerodynamic features include at least one set of fins, wherein each fin in the at least one set of fins defines a fin thickness and a fin chord length.

[0107] A gas turbine engine according to any of the foregoing clauses, wherein the one or more aerodynamic features include a manifold assembly, the manifold assembly including a first manifold defining a manifold thickness and a manifold chord length.

[0108] The gas turbine engine according to any of the foregoing clauses, wherein the manifold assembly further includes: a second manifold, the second manifold being separated from the first manifold by at least a portion of the sheet.

[0109] The gas turbine engine according to any of the foregoing clauses, wherein the one or more aerodynamic features include fins defining fin thickness and fin chord length, and the one or more aerodynamic features further include a manifold defining manifold thickness and manifold chord length.

[0110] In any of the preceding clauses of the gas turbine engine, the ratio of the manifold thickness to the manifold chord length is greater than the ratio of the fin thickness to the fin chord length.

[0111] A gas turbine engine according to any of the foregoing clauses, wherein the manifold defines a manifold height and the fins define a fin height, wherein the manifold chord length is at least twice the manifold height, and wherein the fin chord length is at least twice the fin height.

[0112] The gas turbine engine according to any of the foregoing clauses, wherein the fins and the manifold each include an axial straight section and a curved section.

[0113] The gas turbine engine according to any of the foregoing clauses, wherein the sheet includes a channel assembly.

[0114] According to any of the foregoing clauses, in a gas turbine engine, the first manifold and the second manifold of the manifold assembly each include a corresponding channel assembly, and wherein the channel assembly is fluidly connected to the corresponding channel assembly.

[0115] According to any of the preceding clauses of the gas turbine engine, wherein the heat exchanger assembly defines a section between the first manifold and the second manifold, wherein the heat exchanger assembly includes a set of fins extending circumferentially between the first manifold and the second manifold, and wherein the first manifold, the second manifold and the set of fins are coupled to the sheet.

[0116] According to any of the preceding clauses, the gas turbine engine, wherein the heat exchanger assembly further includes: a third manifold located between the first manifold and the second manifold; a first set of fins extending circumferentially between the first manifold and the third manifold; and a second set of fins extending circumferentially between the third manifold and the second manifold.

[0117] A heat exchanger assembly defining a radial direction, a circumferential direction, and an axial centerline of a gas turbine engine, the heat exchanger assembly comprising: a sheet extending circumferentially about the axial centerline; and one or more aerodynamic features extending from the sheet, the one or more aerodynamic features being located within at least one of an inlet duct, a fan duct, and a core duct.

[0118] The heat exchanger assembly according to any of the foregoing clauses further includes: a manifold assembly comprising a first manifold and a second manifold, the second manifold being separated from the first manifold by at least a portion of the sheet.

[0119] The heat exchanger assembly according to any of the foregoing clauses further includes: a set of fins, wherein the first manifold and the second manifold each define a manifold thickness and a manifold chord length, wherein each fin in the set of fins defines a fin thickness and a fin chord length.

[0120] According to any of the preceding clauses, the ratio of the manifold thickness to the manifold chord length is greater than the ratio of the fin thickness to the fin chord length.

[0121] The heat exchanger assembly according to any of the foregoing clauses, wherein the one or more aerodynamic features further include at least one set of fins.

[0122] The heat exchanger assembly according to any of the foregoing clauses, wherein the set of fins, the first manifold, and the second manifold each include an axial straight section and a curved section.

[0123] The heat exchanger assembly according to any of the foregoing clauses further includes: a third manifold, wherein the third manifold is located between the first manifold and the second manifold; a first set of fins extending circumferentially between the first manifold and the third manifold; and a second set of fins extending circumferentially between the third manifold and the second manifold.

[0124] The heat exchanger assembly according to any of the foregoing clauses, wherein the first manifold and the second manifold each include a channel inlet and a channel outlet, wherein the third manifold is an intermediate manifold.

[0125] A method for cooling fluid in a gas turbine engine, the method comprising: directing a first fluid flow through an engine conduit; using a manifold assembly and a set of fins to deswirl the first fluid flow through the engine conduit; directing a second fluid flow through a sheet; and transferring heat energy between the first fluid flow and the second fluid flow.

[0126] According to any of the foregoing clauses, the method of using a manifold assembly and a set of fins to deswirl the first fluid flow through the engine conduit further includes: guiding the first fluid flow through a plurality of conduits defined by the manifold assembly, the set of fins, and the sheet.

[0127] According to any of the foregoing clauses, guiding the second fluid flow through the sheet further comprises: guiding the second fluid flow through the channel assembly within the sheet, guiding the second fluid flow from the channel assembly to the channel assembly within the manifold assembly; and guiding the second fluid flow through the channel assembly within the manifold assembly.

[0128] According to any of the foregoing provisions, the transfer of thermal energy between the first fluid and the second fluid further comprises: guiding the flow of the second fluid along the surfaces of the manifold assembly and the sheet; and bringing the first fluid flow into thermal contact with the surfaces of the manifold assembly and the sheet.

[0129] A heat exchanger assembly defining a radial direction, a circumferential direction, and an axial centerline of a gas turbine engine, the heat exchanger assembly comprising: a sheet extending circumferentially about the axial centerline; and one or more aerodynamic features extending from the sheet and forming an angle with the sheet, the one or more aerodynamic features being located within at least one of an inlet duct, a fan duct, and a core duct.

[0130] This written description uses examples to disclose this disclosure and also enables any person skilled in the art to practice this disclosure, including making and using any device or system and performing any combined methods. The patentable scope of this disclosure is defined by the claims and may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A gas turbine engine defining radial and axial directions, characterized in that, The gas turbine engine includes: An inlet pipe, the inlet pipe including a diverter; A fan duct, located downstream of the inlet duct and the splitter; A core conduit, located downstream of the inlet conduit and the splitter, and radially inner to the fan conduit; and A heat exchanger assembly extending annularly around at least one of the inlet conduit, the fan conduit, or the core conduit, the heat exchanger assembly comprising: A sheet extending circumferentially around at least one of the inlet duct, the fan duct, and the core duct; and One or more aerodynamic features extending from the sheet and located within at least one of the inlet duct, the fan duct, and the core duct.

2. The gas turbine engine according to claim 1, characterized in that, in, The one or more aerodynamic features include at least one set of fins, wherein each fin in the at least one set of fins defines a fin thickness and a fin chord length.

3. The gas turbine engine according to claim 1, characterized in that, in, The one or more aerodynamic features include a manifold assembly, the manifold assembly including a first manifold defining a manifold thickness and a manifold chord length.

4. The gas turbine engine according to claim 3, characterized in that, in, The manifold assembly further includes: The second manifold is separated from the first manifold by at least a portion of the sheet.

5. The gas turbine engine according to claim 1, characterized in that, in, The one or more aerodynamic features include fins, the fins defining fin thickness and fin chord length, and the one or more aerodynamic features further include a manifold, the manifold defining manifold thickness and manifold chord length.

6. The gas turbine engine according to claim 5, characterized in that, in, The ratio of the manifold thickness to the manifold chord length is greater than the ratio of the fin thickness to the fin chord length.

7. The gas turbine engine according to claim 5, characterized in that, in, The manifold defines a manifold height, and the fin defines a fin height, wherein the manifold chord length is at least twice the manifold height, and wherein the fin chord length is at least twice the fin height.

8. The gas turbine engine according to claim 5, characterized in that, in, The fins and the manifold each include an axial straight section and a curved section.

9. The gas turbine engine according to claim 4, characterized in that, in, The sheet includes a channel assembly.

10. The gas turbine engine according to claim 9, characterized in that, in, The first manifold and the second manifold of the manifold assembly each include a corresponding channel assembly, wherein the channel assembly is fluidly connected to the corresponding channel assembly.

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