Three-flow engine with heat exchanger

Abstract

A three-flow engine is provided. The three-flow engine includes: a fan section; a core engine disposed downstream of the fan section; and a core shroud annularly surrounding the core engine and at least partially defining a core duct. The fan shroud is disposed radially outward from the core shroud and annularly surrounds at least a portion of the core shroud. The fan shroud at least partially defines an inlet duct and a fan duct. The fan duct and the core duct extend axially together at least partially on opposite sides of the core shroud. A heat exchanger is disposed within the fan duct. The heat exchanger provides thermal communication between fluid flowing through the fan duct and kinetic fluid flowing through the heat exchanger.

Description

Technical Field

[0001] This topic generally relates to open rotor and ducted propulsion systems. Specifically, this topic relates to the use of heat exchangers within the airflow path of a propulsion system. Background Technology

[0002] A gas turbine engine typically consists of a fan and a turbine. The turbine typically includes an inlet, one or more compressors, a combustor, and at least one turbine. The compressor compresses air, which is then directed to the combustor, where it is mixed with fuel. The mixture is then ignited to produce hot combustion gases. These combustion gases are directed to the turbine, which extracts energy from the combustion gases to power the compressor and generate useful work to propel an aircraft in flight or power a load such as a generator.

[0003] In at least some embodiments, the gas turbine can employ an open rotor propulsion system, which operates based on the principle of placing the fan outside the engine nacelle (in other words, "non-ducted"). Compared to turbofan engines, this allows for the use of larger fan blades capable of engaging a greater volume of air, thereby improving propulsion efficiency compared to conventional ducted engine designs.

[0004] During the operation of a gas turbine engine (e.g., a gas turbine employing an open rotor propulsion system), various systems can generate a relatively large amount of heat. For example, significant amounts of heat may be generated during the operation of thrust generation systems, electric motors and / or generators, hydraulic systems, or other systems. Therefore, devices for dissipating the heat generated by these various systems without negatively impacting the efficiency of the gas turbine engine would be advantageous in the art. Summary of the Invention

[0005] Aspects and advantages of the invention will be set forth in part in the description which follows, or may be apparent from the description, or may be learned by practice of the invention.

[0006] In one exemplary aspect of this disclosure, a three-flow engine is provided. The three-flow engine includes: a fan section; a core engine disposed downstream of the fan section; and a core shroud annularly surrounding the core engine and at least partially defining a core duct. The fan shroud is disposed radially outward from the core shroud and annularly surrounds at least a portion of the core shroud. The fan shroud at least partially defines an inlet duct and a fan duct. The fan duct and the core duct extend axially together at least partially on opposite sides of the core shroud. A heat exchanger is disposed within the fan duct. The heat exchanger provides thermal communication between fluid flowing through the fan duct and kinetic fluid flowing through the heat exchanger.

[0007] In another exemplary aspect of this disclosure, a method of operating a three-flow engine is provided. The method includes the step of operating a fan section to generate an airflow within an inlet duct. The inlet duct is at least partially defined by a fan shroud. The method further includes the step of directing a first portion of the airflow into a core duct defined at least partially by a core shroud. The core shroud annularly surrounds the core engine. The method further includes directing a second portion of the airflow into a fan duct defined by the core shroud and the fan shroud. The method further includes feeding a portion of the second portion of the flow into a heat exchanger located within the fan duct to cool kinetic fluid traveling through the heat exchanger.

[0008] These and other features, aspects, and advantages of the invention will become more readily understood with reference to the following description and the appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention. Attached Figure Description

[0009] The complete and practical disclosure of the invention, including its preferred mode, is set forth in the description with reference to the accompanying drawings, for those skilled in the art, wherein:

[0010] Figure 1 This is a schematic cross-sectional view of a three-flow engine according to an exemplary embodiment of the present disclosure.

[0011] Figure 2 This is a schematic enlarged cross-sectional view of a three-flow engine according to an exemplary embodiment of the present disclosure.

[0012] Figure 3 This is a schematic enlarged cross-sectional view of a three-flow engine according to an exemplary embodiment of the present disclosure.

[0013] Figure 4 This is an enlarged perspective view of a heat exchanger that can be used in a three-flow engine according to an exemplary embodiment of the present disclosure.

[0014] Figure 5 This is a cross-sectional view of a heat exchanger along the circumferential direction C according to an exemplary embodiment of the present disclosure.

[0015] Figure 6 This is a schematic cross-sectional view of a three-flow engine according to an exemplary embodiment of the present disclosure.

[0016] Figure 7 This is a schematic cross-sectional view of a three-flow engine according to an exemplary embodiment of the present disclosure.

[0017] Figure 8 This is a schematic cross-sectional view of a three-flow engine according to an exemplary embodiment of the present disclosure.

[0018] Figure 9 This is a flowchart of a method for operating a three-flow engine according to an exemplary embodiment of the present disclosure. Detailed Implementation

[0019] Reference will now be made in detail to the present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numbers and letters to refer to features in the drawings. The same or similar reference numerals in the drawings and description have been used to refer to the same or similar parts of the invention.

[0020] The term "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior or better than other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

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

[0022] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and specifically to the normal operating posture of the gas turbine engine or vehicle. For example, in the case of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0023] The terms “upstream” and “downstream” refer to the relative directions of flow within a path. For example, in fluid flow, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction from which the fluid flows. However, as used herein, the terms “upstream” and “downstream” can also refer to electric current.

[0024] The term "fluid" can refer to either a gas or a liquid. The term "fluid connectivity" refers to the ability of fluids to establish connections between specified areas.

[0025] Unless the context clearly indicates otherwise, the singular forms “a,” “a,” and “the” include plural references.

[0026] As used throughout the specification and claims, approximate language is applied to modify any quantitative expression that may allow for variation without altering its underlying function. Therefore, values ​​modified by terms such as “about,” “approximately,” “generally,” and “substantially” are not limited to specified precise values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to a margin of 1%, 2%, 4%, 5%, 10%, 15%, or 20% of the endpoints of a single value, a range of values, and / or a defined range of values.

[0027] Throughout this specification and claims, scope limitations are combined and interchanged, and unless the context or language otherwise indicates otherwise, such scopes are identified and include all subscopes contained herein. For example, all scopes disclosed herein include endpoints, and endpoints may be combined independently of each other.

[0028] According to one or more embodiments described herein, a three-flow engine may be equipped with one or more heat exchangers. Heat exchangers may be provided to cool certain systems of the gas turbine engine or an aircraft equipped with a gas turbine engine. For example, heat exchangers may be provided to cool turbine sections or auxiliary systems, such as lubrication systems, supercritical CO2 systems, and fuel systems. Heat transfer systems can cool (or heat) these systems by cooling (or heating) the fluids (e.g., air or lubricant) delivered to them.

[0029] This document describes systems that extend beyond a three-flow engine. It should be understood that these systems are provided by way of example only, and the claimed systems are not limited to applications using or otherwise combining with these other systems. This disclosure is not intended to be limiting. For example, it should be understood that one or more embodiments described herein may be configured to operate independently or in combination with other embodiments described herein.

[0030] Figure 1 A schematic cross-sectional view of a gas turbine engine according to an example embodiment of the present disclosure is provided. Specifically, Figure 1 It provides a third-flow turbofan engine for aviation, referred to in this article as "Third-Flow Engine 100". Figure 1 The three-flow engine 100 can be installed on an aircraft (such as a fixed-wing aircraft) and can generate thrust for propelling the aircraft. The three-flow engine 100 is called a "three-flow engine" because its architecture provides three different airflows that generate thrust during operation.

[0031] Additionally, as used herein, "third flow" refers to a secondary airflow capable of increasing fluid energy to generate a small portion of the total propulsion system thrust. The pressure ratio of the third flow is higher than that of the primary propulsion flow (e.g., a bypass or propeller-driven propulsion flow). Thrust can be generated via a dedicated nozzle or by mixing the secondary airflow with the primary propulsion flow or core airflow into, for example, a common nozzle. In some exemplary embodiments, the operating temperature of the secondary airflow is below the engine's maximum compressor discharge temperature, and more specifically, may be below 350 degrees Fahrenheit (e.g., below 300 degrees Fahrenheit, such as below 250 degrees Fahrenheit, such as below 200 degrees Fahrenheit, and at least as high as ambient temperature). In some exemplary embodiments, these operating temperatures can facilitate heat transfer to or from the secondary airflow and the separate fluid flow. Furthermore, in some exemplary embodiments, under takeoff conditions, or more specifically, when operating at rated takeoff power at sea level, static flight speed, and an ambient temperature of 86 degrees Fahrenheit, the secondary airflow may contribute less than 50% (and at least, for example, 2%) of the total engine thrust. Additionally, in some exemplary embodiments, aspects of the secondary airflow (e.g., airflow, mixing, or exhaust characteristics) and thus the aforementioned exemplary percentage contribution to the total thrust may be passively adjusted during engine operation or purposefully modified using engine control features (e.g., fuel flow, 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. In the embodiments discussed below, the fan duct 172 of the three-flow engine 100 may be a “third flow” according to the above definition.

[0032] For reference, the three-flow engine 100 defines an axial direction A, a radial direction R, and a circumferential direction C. Furthermore, the three-flow 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 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. The three-flow engine 100 extends, for example, along the axial direction A between a front end 114 and a rear end 116.

[0033] The three-flow engine 100 includes a core engine 120 and a fan section 150 positioned upstream therefrom. Typically, the core engine 120 includes a compressor section, a combustion section, a turbine section, and an exhaust section in a sequential flow order. Specifically, as... Figure 1As shown, the core engine 120 includes a core shroud 122 defining an annular core inlet 124. The core shroud 122 further surrounds the low-pressure system and the high-pressure system. The core shroud 122 may at least partially house a support frame 123, which may provide structural support for the core shroud 122 and various other components of the three-flow engine 100, such as one or more heat exchangers 200. For example, the support frame 123 may be at least partially housed within the core shroud 122 and may be coupled to the interior of the core shroud 122 to provide structural support for the core shroud 122. Furthermore, one or more components of the three-flow engine 100 may extend through the core shroud 122 and be directly coupled to the support frame 123, such as a stationary strut 174 and / or a heat exchanger 200. In many embodiments, the core shroud 122 may surround and support a boost or low-pressure (“LP”) compressor 126 for pressurizing air entering the core engine 120 through the core inlet 124. A high-pressure (“HP”) multistage axial compressor 128 receives pressurized air from an LP compressor 126 and further increases the air pressure. The pressurized air flows downstream to a combustor 130, where fuel is injected into the pressurized air stream and ignited to increase the temperature and energy level of the pressurized air. It should be understood that, as used herein, the terms “high / low speed” and “high / low pressure” are used interchangeably with respect to 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 do not imply any absolute speed and / or pressure values.

[0034] High-energy combustion products flow downstream from combustor 130 to high-pressure turbine 132. High-pressure turbine 128 drives high-pressure compressor 128 via high-pressure shaft 136. At this point, high-pressure turbine 128 is drivably coupled to high-pressure compressor 128. 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. At this point, low-pressure turbine 134 is drivably coupled to components of low-pressure compressor 126 and fan section 150. In this example embodiment, LP shaft 138 is coaxial with HP shaft 136. After driving each of turbines 132, 134, combustion products exit core engine 120 through core exhaust nozzle 140 to generate propulsive thrust. Therefore, core engine 120 defines a core flow path or core conduit 142 extending between core inlet 124 and core exhaust nozzle 140. The core conduit 142 is an annular conduit roughly positioned inside the core cover 122 along the radial direction R.

[0035] Fan section 150 includes fan 152, which in this example embodiment is the main fan. For Figure 1In the illustrated embodiment, fan 152 is an open rotor or non-ducted fan 152. However, in other embodiments, fan 152 may be ducted, for example, by means of a fan housing or nacelle circumferentially surrounding fan 152. As depicted, fan 152 includes an array of fan blades 154. Figure 1 (Only one is shown). For example, fan blade 154 can rotate about longitudinal axis 112. As described above, fan 152 is drivenly connected to low-pressure turbine 134 via LP shaft 138. Fan 152 can be directly connected to LP shaft 138, for example, in a direct drive configuration. Alternatively, as... Figure 1 As shown, the fan 152 can be connected to the LP shaft 138 via a reduction gearbox 155, for example, in an indirect drive or gear drive configuration.

[0036] Furthermore, the fan blades 154 may be arranged at equal intervals around the longitudinal axis 112. Each blade 154 has a root and a tip, and a span defined between them. Each blade 154 defines a central blade axis 156. In this embodiment, each blade 154 of the fan 152 may rotate about its respective central blade axis 156, for example, in unison with each other. One or more actuators 158 may be controlled to tilt the blades 154 about their respective central blade axes 156. However, in other embodiments, each blade 154 may be fixed or may not tilt about its central blade axis 156.

[0037] Fan section 150 also 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 image). In this embodiment, the fan guide vane 162 cannot rotate about the longitudinal axis 112. Each fan guide vane 162 has a root and a tip, and a span defined between them. The fan guide vane 162 can be as follows: Figure 1 The fan guide vanes 162 shown are not obscured, or may be obscured, for example, by an annular shroud spaced outwards from the tips of the fan guide vanes 162 in a radial direction R. Each fan guide vane 162 defines a central blade axis 164. In this embodiment, each fan guide vane 162 of the fan guide vane array 160 may rotate about its respective central blade axis 164, for example, in unison with each other. One or more actuators 166 may be controlled to tilt the fan guide vanes 162 about their respective central blade axes 164. However, in other embodiments, each fan guide vane 162 may be fixed or may not tilt about its central blade axis 164. The fan guide vanes 162 are mounted to the fan shroud 170, or alternatively, the fan guide vanes 162 may be mounted to a support frame 171 housed within the fan shroud 170.

[0038] like Figure 1As shown, in addition to the non-ducted fan 152, a ducted fan 184 is also included behind fan 152, such that the three-flow engine 100 includes both a ducted fan and a non-ducted fan for generating thrust by the movement of air at atmospheric temperature without passing through the core engine 120. The ducted fan 184 is shown at approximately the same axial position as fan blade 162 and radially inward of fan blade 154; in some embodiments, the ducted fan may be approximately radially inward of fan blade 162. Alternatively, the ducted fan 184 may be axially positioned between fan blade 154 and core shroud 122, or further forward of fan blade 154. The ducted fan 184 may be driven by a low-pressure turbine 134 (e.g., coupled to LP shaft 138) or any other suitable rotational source and may be used as a first-stage supercharger or operated independently.

[0039] The fan shroud 170 annularly surrounds at least a portion of the core shroud 122 and is positioned generally radially outward of the core shroud 122. Specifically, a downstream section of the fan shroud 170 extends forward of the core shroud 122 to define a third flow or fan duct 172. Incoming fluid (e.g., air) enters through the fan duct 172 via the fan duct inlet 176 and exits through the fan exhaust nozzle 178 to generate propulsive thrust. The fan duct 172 is an annular duct positioned radially outward of the core duct 142. A support frame 171 may be at least partially housed within the fan shroud 122, and may be coupled to the interior of the fan shroud 170 and provide structural support for the fan shroud 170. Furthermore, one or more components of the three-flow engine 100 may extend through the fan shroud 170 and be directly coupled to the support frame 171, such as the fan guide vanes 162, struts 174, and / or the heat exchanger 200. The fan shroud 170 and the core shroud 122 are connected together and are supported by a plurality of substantially radially extending, circumferentially spaced stationary struts 174. Figure 1 (Only one support is shown in the diagram.) In many embodiments, stationary strut 174 may be coupled to support frame 123 housed within core shroud 122 and support frame 171 housed within fan shroud 170, and may extend between them. Stationary strut 174 may each be aerodynamically shaped to guide airflow therefrom. Other struts besides stationary strut 174 may be used to connect and support fan shroud 170 and / or core shroud 122. In many embodiments, fan duct 172 and core duct 122 may extend at least partially on opposite sides (e.g., opposite radial sides) of core shroud 122 (generally axially). For example, fan duct 172 and core duct 122 may each extend directly from leading edge 144 of core shroud 122 and may extend generally axially on opposite radial sides of core shroud.

[0040] The three-flow engine 100 also defines or includes an inlet duct 180. The inlet duct 180 extends between the engine inlet 182 and the core inlet 124 / fan duct inlet 176. The engine inlet 182 is generally defined at the front end of the fan shroud 170 and positioned along the axial direction A between the array of fan 152 and fan guide vanes 160. The inlet duct 180 is an annular duct positioned radially R inside the fan shroud 170. Air flowing downstream along the inlet duct 180 is diverted (not necessarily uniformly) by a splitter or leading edge 144 of the core shroud 122 into the core duct 142 and the fan duct 172. The inlet duct 180 is wider radially R than the core duct 142. The inlet duct 180 is also wider radially R than the fan duct 172.

[0041] In an exemplary embodiment, the air passing through fan duct 172 may be relatively colder (e.g., at a lower temperature) than one or more fluids used in the core engine 120. In this way, one or more heat exchangers 200 may be disposed within fan duct 172 and utilized to cool one or more fluids from the core engine by the air passing through fan duct 172, thereby improving the efficiency of the entire three-flow engine.

[0042] Figure 2 and Figure 3 A three-flow engine 100 is shown (e.g.) Figure 1 An enlarged cross-sectional view of the three-flow engines shown, each of which includes one or more heat exchangers 200 disposed within a fan duct 172. As shown, particularly... Figure 2 In some embodiments, the heat exchanger 200 may be axially positioned in front of at least one stationary support 174 within the fan duct 172, such that air through the fan duct 172 passes through the heat exchanger 200 before bypassing the stationary support 174. Additionally or alternatively, the heat exchanger 200 may be axially positioned behind at least one stationary support 174 within the fan duct 172, such that air through the fan duct 172 bypasses the stationary support 174 before passing through the heat exchanger 200. In further additional or alternative embodiments, such as... Figure 2 As shown, one or more heat exchangers 200 may be positioned at the same axial location as the stationary support 174 (or at least partially overlap with the support axially). In such an embodiment, as described below, one or more heat exchangers may be at least partially coupled to the stationary support 174.

[0043] Each heat exchanger 200 may include an air inlet 201 and an air outlet 203. The air inlet 201 receives air passing through the fan duct 172 and then directs the air through the heat exchanger 200, where heat is collected from the kinetic fluid passing through the heat exchanger 200. The air outlet 203 then exhausts the used air back to the fan duct 172.

[0044] exist Figure 2 In the illustrated embodiment, the heat exchangers 200 may be axially spaced apart from each other, such that air exiting the air outlet 203 of the first heat exchanger 200 travels an axial distance within the fan duct 172 before entering the air inlet 201 of the second heat exchanger. Additionally or alternatively, such as Figure 4 As shown, one or more heat exchangers 200 may be a first heat exchanger 200a and a second heat exchanger 200b, each disposed within the fan duct 172 and stacked axially with each other. In other words, the air outlet 203 of the first heat exchanger 200a may be directly adjacent to (or connected to) the air inlet 201 of the second heat exchanger 200b, such that all air leaving the first heat exchanger 200a enters the second heat exchanger 200b. This configuration may be advantageous, for example, if the first heat exchanger 200a carries a different kinetic fluid than the second heat exchanger 200b, thereby optimizing heat transfer between the air and the corresponding fluid.

[0045] Figure 4 An enlarged perspective view of a heat exchanger 200 according to an embodiment of the present disclosure is shown. The heat exchanger 200 may be referred to as an "onion" heat exchanger and can be used in a three-flow engine 100. As shown, the heat exchanger 200 may include a first wall manifold 202, a second manifold wall 204 spaced apart from the first wall 202, and one or more blades 206 extending between the first manifold wall 202 and the second manifold wall 204. The heat exchanger 200 described herein may be substantially hollow, such that multiple independent fluid loops are defined within the heat exchanger. Multiple independent fluid loops allow multiple different kinetic fluids (e.g., from various systems of an aircraft engine) to simultaneously pass through the heat exchanger 200 and be in thermal communication with each other and with the air passing through the aircraft engine. For example, the wall manifolds 202, 204, and blades 206 may all include various fluid channels defined therein to allow kinetic fluids to travel through them during operation.

[0046] Manifold walls 202, 204 can act as fluid guiding manifolds, directing kinetic fluid to and from various channels defined within the impeller 206 of the heat exchanger 200. In an exemplary embodiment, the heat exchanger 200 can be used in a three-flow engine 100 (e.g., Figure 1 Within the fan duct 172 (shown), relatively cool air flowing through the fan duct 172 passes through the impeller 206 and between the manifold walls 202, 204 of the heat exchanger 200, and provides cooling (or heating in some embodiments) to one or more kinetic fluids traveling through it.

[0047] As shown in the figure, the first wall manifold 202 can typically be formed as a rectangular prism with a singular surface (e.g., a radially outward surface). Similarly, the second wall manifold 204 can typically be formed as a rectangular prism with a singular surface (e.g., a radially outward surface).

[0048] like Figure 4 As shown, one or more portions of the heat exchanger 200 can typically be curved (or non-straight). For example, as Figure 4 As shown, the impeller 206 can typically be shaped to correspond to the fan duct 172 and / or the circumferential direction C, so as to utilize the airflow within the heat exchanger 200 without creating a wake within the fan duct 172. In some embodiments, the first wall manifold 202 and the second wall manifold 204 can typically taper away from each other in the circumferential direction C as they extend radially. In this way, the circumferential length of the impeller 206 can gradually increase the further radially outward it is positioned on the heat exchanger 200. For example, the circumferential length of the radially innermost impeller 206 can be shorter than the circumferential length of the radially outermost impeller 206. This can be advantageous when operating the heat exchanger 200, for example, if the motive fluid requires more cooling, it can be directed to a fluid loop disposed within the radially outermost impeller 206, thereby providing more cooling due to the relatively increased length of the impeller 206.

[0049] In many embodiments, the heat exchanger 200 described herein can be integrally formed as a single component. That is, each sub-component (e.g., the first wall manifold 202, the second wall manifold 204, and the plurality of blades 206, as well as any other sub-components of the heat exchanger 200) can be manufactured together as a single unit. In exemplary embodiments, this can be accomplished by utilizing additive manufacturing systems and methods (e.g., direct metal laser sintering (DMLS), direct metal laser melting (DMLM), or other suitable additive manufacturing techniques). In other embodiments, other manufacturing techniques, such as casting or other suitable techniques, can be used. In this respect, by utilizing additive manufacturing methods, the heat exchanger 200 can be integrally formed as a single piece of continuous metal, and thus can include fewer sub-components and / or joints compared to existing designs. Integral formation of the heat exchanger 200 by additive manufacturing can advantageously improve the overall assembly process. For example, integral formation reduces the number of individual parts that must be assembled, thereby reducing the associated time and total assembly cost. Additionally, existing problems related to, for example, leakage, the quality of the joints between individual parts, and overall performance can be advantageously reduced. Furthermore, compared to other manufacturing methods, the integral formation of the heat exchanger 200 can advantageously reduce the weight of the heat exchanger 200, thereby reducing the overall weight of the aircraft engine on which the heat exchanger 200 is deployed and improving efficiency.

[0050] Alternatively, the first wall manifold 202 and the second wall manifold 204 can each be integrally formed separately. In such an embodiment, the first wall manifold 202 and the second wall manifold 204 can each be welded to a plurality of impeller blades 206. Manufacturing the wall manifolds 202 and 204 separately can advantageously reduce the production time of the entire heat exchanger 200, thereby significantly reducing manufacturing costs.

[0051] Figure 5 A cross-sectional view of the heat exchanger 200 along the circumferential direction C is shown. In an exemplary embodiment, each of the plurality of blades 206 may include a leading edge 288, a trailing edge 290, and a sidewall 292 extending between the leading edge 288 and the trailing edge 290. Figure 5As shown, multiple blades 206 may be spaced apart from each other in a radial direction R to define an airflow passage 294 between the blades 206. In operation, the leading edge 288 may engage air 400 traveling through the engine (e.g., within the fan flow passage 48 or fan duct 172). The air 400 may then flow into the airflow passage 294 defined between the blades 206 (e.g., specifically radially defined between the sidewalls 292 of adjacent blades 206). Finally, the air 400 may be discharged from the heat exchanger 200 at the trailing edge 290 of the blades 206. For example, the airflow passage 294 defined between the blades 206 of the heat exchanger 200 may radially diverge after the leading edge 288 and then radially converge toward the trailing edge 290. In such an embodiment, the airflow passage 294 may have a larger area in the middle, which reduces the Mach number to reduce pressure drop before gradually converging to pick up speed to maintain thrust capability. This allows most of the heat transfer to occur at the surface in the lower Reynolds number and frictional regions, resulting in a lower pressure drop.

[0052] Although the air 400 is fluidly isolated from the kinetic fluid traveling through each channel defined within the impeller 206 of the heat exchanger 200, the impeller 206 allows for thermal communication between the air 400 and the kinetic fluid within the channels. Figure 5 As shown, each airflow channel 294 can receive and discharge airflow 400 in a direction generally perpendicular to the channel defined within the impeller 206. Figure 5 As shown, the blade 206 may also include one or more ribs 295 that may extend generally radially within the blade 206.

[0053] In an exemplary embodiment, the heat exchanger 200 described herein may be an "onion" type heat exchanger. However, in other embodiments, the heat exchanger 200 may be any suitable type of heat exchanger known in the art, and the invention should not be limited to the "onion" type heat exchanger described herein unless expressly stated in the claims.

[0054] Figure 6-8 A schematic cross-sectional view of a three-flow engine 100 according to an embodiment of the present disclosure is shown, wherein one or more heat exchangers 200 may be arranged circumferentially within a fan duct 172. Although Figure 6-8 Half of the third-generation engine 100 is shown, but it should be understood that... Figure 6-8 The features referenced herein can be applied to the entire engine. As described above, the air flowing through fan duct 172 can travel approximately axially (i.e., relative to...). Figure 6-8 (Enter / exit page). A portion of the air traveling through fan duct 172 may pass between heat exchangers 200, and a portion of the air may pass through heat exchangers 200 (e.g., between the blades 206 of heat exchangers 200).

[0055] exist Figure 6-8 In the illustrated embodiment, heat exchangers 200 may be disposed within fan duct 172 and circumferentially spaced apart from each other. For example, heat exchangers 200 may be equidistant (or unequally spaced) from each other in the circumferential direction C within fan duct 174. In other embodiments (not shown), heat exchangers 200 may be continuous in the circumferential direction C (e.g., around longitudinal axis 112 360°), such that all airflow through fan duct 172 passes through heat exchangers 200. Figure 6-8 As depicted, the core shroud 122 typically surrounds and houses the support frame 123 (shown in crosshairs). Similarly, the fan shroud 170 typically surrounds and houses the support frame 171 (shown in crosshairs). As described above, the support frames 123 and 171 can each provide structural support for the respective shrouds 122 and 170, as well as various other components of the three-flow engine 100. For example, stationary struts 174 can each extend radially between and be connected to the support frames 123 and 171. Furthermore, one or more heat exchangers 200 can be (permanently via welding, or non-permanently via bolts and fasteners) connected to either or both of the support frames 123 and 171.

[0056] The number and size of the heat exchangers 200 can depend on the specific system's cooling (or heating) requirements. In other words, if a large amount of cooling / heating is required, the three-flow engine 100 may employ heat exchangers 200 occupying most of the fan duct 172. In such embodiments, where the system requires a large amount of cooling (or heating), the circumferential spacing between the heat exchangers 200 may be small to none. For example, in some embodiments, 100% of the air flowing through the fan duct 172 may pass through the heat exchangers 200. In such embodiments, the heat exchangers 200 may extend continuously around the longitudinal centerline 112 (or multiple heat exchangers 200 may be adjacent to each other within the fan duct 172, such that no circumferential spacing is provided between the heat exchangers 200).

[0057] In many embodiments, approximately 10% to approximately 100% of the air flowing through fan duct 172 passes through heat exchanger 200. In other embodiments, approximately 20% to approximately 100% of the air flowing through fan duct 172 passes through heat exchanger 200. In various embodiments, approximately 30% to approximately 100% of the air flowing through fan duct 172 passes through heat exchanger 200. In further embodiments, approximately 50% to approximately 100% of the air flowing through fan duct 172 passes through heat exchanger 200. In particular embodiments, approximately 30% to approximately 70% of the air flowing through fan duct 172 passes through heat exchanger 200.

[0058] In various embodiments, the heat exchanger 200 can be coupled to the three-flow engine 100 in a variety of ways. For example, as shown, in some embodiments, the heat exchanger 200 can be coupled to the fan shroud 170 (e.g., in some embodiments, coupled only to the fan shroud 170), such that the heat exchanger 200 is secured within the fan duct 172 by the fan shroud 170. In many embodiments, the heat exchanger 200 can extend at least partially through the fan shroud 170 and be directly coupled to the support structure 171 housed within the fan shroud 170 (e.g., in some embodiments, coupled only to the support structure 171), such that the heat exchanger 200 is secured within the fan duct 172 by the support structure 171.

[0059] In other embodiments, the heat exchanger 200 may be coupled to the core shroud 122 (e.g., coupled only to the core shroud 122 in some embodiments), such that the heat exchanger 200 is secured to the fan duct 172 via the core shroud 122. In many embodiments, the heat exchanger 200 may extend at least partially through the core shroud 122 and be directly coupled to the support structure 123 housed within the core shroud 122 (e.g., coupled only to the support structure 123 in some embodiments), such that the heat exchanger 200 is secured to the fan duct 172 via the support structure 123.

[0060] In a further embodiment, the heat exchanger 200 may be coupled to one or more stationary supports 174 (e.g., in some embodiments, coupled only to stationary supports 174), such that the heat exchanger 200 can be secured within the fan duct by the stationary supports 174. In a further embodiment, one or more heat exchangers may be coupled to any combination of the fan duct 172, support structure 171, core duct 122, support structure 123, and one or more stationary supports 174.

[0061] In a particular embodiment, as described above, each heat exchanger 200 may be connected to a different structure within the fan duct 172 of the three-flow engine 100. For example, as shown, a first heat exchanger 200 may be connected to a fan shroud 170 (and / or to a support structure 171), a second heat exchanger 200 may be connected to a core shroud 122 (and / or to a support structure 123), and a third heat exchanger 200 may be connected to a stationary support 174.

[0062] Between different embodiments, the heat exchanger 200 can extend within the fan duct 172 in a variety of ways. For example, in some embodiments, such as Figure 3As shown, one or more heat exchangers 200 may extend radially inward from the fan shroud 170 into the fan duct 172. In such embodiments, the heat exchangers 200 may be radially spaced from the core shroud 122 such that in some embodiments the heat exchangers 200 do not contact the core shroud in any way. In other embodiments, the heat exchangers 200 may extend radially outward from the core shroud 120 into the fan duct 172. In such embodiments, the heat exchangers 200 may be radially spaced from the fan shroud 170 such that in some embodiments the heat exchangers do not contact the fan shroud 170. In an exemplary embodiment, the heat exchangers 200 may extend entirely radially through the fan duct 172 (e.g., between the core shroud 122 and the fan shroud 170).

[0063] In an exemplary embodiment, the heat exchanger 200 may be mounted at only one end within the fan duct 172, allowing the opposite end of the heat exchanger 200 to thermally expand and contract freely within the fan duct 172, thereby increasing the operational flexibility and lifespan of the heat exchanger 200. For example, as shown, each heat exchanger 200 may extend within the fan duct 172 between a fixed end 208 and a free end 210 to allow thermal expansion of the heat exchanger 200 within the fan duct 172. In embodiments using an "onion" type heat exchanger, the fixed end 208 may be one of walls 202, 204, and the free end may be the other of walls 202, 204. The fixed end 208 of the heat exchanger may be welded, brazed, or otherwise permanently coupled to one or more of the fan shroud 170, support structure 171, core shroud 122, support structure 123, and / or stationary support column 174. Additionally or alternatively, the fixed end 208 of the heat exchanger 200 may be non-permanently coupled to one of the fan shroud 170, support structure 171, core shroud 122, support structure 123, and / or stationary support 174 (e.g., via one or more threaded fasteners, bolts, or any other non-permanent connection that advantageously allows the heat exchanger 200 to be easily removed). In embodiments where the fixed end 210 is coupled to one of the support structures 123 or 171, the fixed end 210 of the heat exchanger 200 may extend through the corresponding shroud 122 or 170 to couple to the support structure 123 or 171. The free end 210 of each heat exchanger 200 may not be coupled to the three-flow engine 100, thereby allowing unrestricted thermal expansion of the heat exchanger 200 within the fan duct 172. In some embodiments, the free end 210 may still contact one or more of the fan shroud 170, core shroud 122 and / or stationary support 174, but may be completely separated from them such that the free end 210 may slide into contact with one or more surfaces defining the fan duct 172 when the heat exchanger 200 thermally expands / contracts.

[0064] Figure 6 and 7A cross-sectional schematic diagram of a three-flow engine 100 is shown, including a motive fluid supply system 249, which provides means for supplying and returning motive fluid 212 to a heat exchanger 200. According to embodiments of this disclosure, by... Figure 6 and Figure 7 The various arrows in the diagram indicate that the kinetic fluid 212 can be directed through one or more heat exchangers 200 positioned together with the fan duct 172.

[0065] As shown, each heat exchanger 200 includes a motive fluid inlet 214, a motive fluid outlet 216, and a motive fluid loop 218 defined between the motive fluid inlet 214 and the motive fluid outlet 216 and within the heat exchanger 200. The motive fluid inlet 214 may be defined within a first wall 202, the motive fluid outlet may be defined within a second wall 204, and the motive fluid loop 218 may be defined within a blade 206. For example, each heat exchanger 200 may receive motive fluid 212 from a motive fluid supply section 250. The motive fluid 212 may then be directed through the motive fluid loop 218 (i.e., through each blade 206), where most of the heat from the motive fluid 212 is transferred to the air traveling through the fan duct 172. Once the motive fluid 212 has passed through the motive fluid loop 218, the motive fluid 212 may be discharged from each heat exchanger 200 via the motive fluid outlet 218 to the motive fluid return loop 252. The power fluid supply unit 250 can supply one or more hot fluids from various thermal systems of the three-flow engine (e.g., one or more lubricants from the lubrication system, one or more fuels from the fuel system, supercritical CO2 from the CO2 system, or other fluids from other fluid systems that require cooling / heating). Similarly, the fluid return loop 252 can return the power fluid 212 to the system that supplied it (and at a lower temperature than when it was supplied).

[0066] exist Figure 7 In the illustrated embodiment, each heat exchanger 200 can be independently fluidly connected to the motive fluid supply system 249 (which may be referred to herein as a "parallel configuration"). For example, each heat exchanger 200 can be independently fluidly connected to the fluid supply section 250 via a corresponding motive fluid inlet 214. Similarly, each heat exchanger 200 can be independently fluidly connected to the motive fluid return section 252 via a corresponding motive fluid outlet 216. In such an embodiment, each heat exchanger can be fluidly isolated from each other relative to the motive fluid 212 traveling through it.

[0067] Figure 8Another embodiment of the three-flow engine 100 is shown, wherein heat exchangers 200 are fluidly connected to each other relative to the motive fluid 212 (which may be referred to herein as a “serial configuration” of the heat exchangers 200). For example, in Figure 8 In the illustrated embodiment, motive fluid 212 may enter the first heat exchanger 260 via motive fluid inlet 214 and travel through one or more intermediate heat exchangers 262 and the final heat exchanger 264 before returning via motive fluid outlet 216 of the final heat exchanger 264. In such an embodiment, motive fluid 212 may travel through each heat exchanger 200 within the fan duct 172 before returning, which may advantageously provide additional heat transfer between the motive fluid 212 and the air flowing through the fan duct 172.

[0068] exist Figure 8 In the illustrated embodiment, the first heat exchanger 262 may receive kinetic fluid 212 from the kinetic fluid supply unit 250. The kinetic fluid outlet 216 of the first heat exchanger 260 of the plurality of heat exchangers 200 may be fluidly connected to the kinetic fluid inlet 216 of a second heat exchanger (e.g., an intermediate heat exchanger 262 of the plurality of heat exchangers 200). Although in Figure 8 Only one intermediate heat exchanger 262 is shown, but multiple intermediate heat exchangers can be fluidly connected to each other in the manner described above before the final heat exchanger 264, wherein the motive fluid is discharged to the motive fluid return section 252 via the motive fluid outlet 216 of the final heat exchanger 264. Figure 8 As shown, each heat exchanger 200 may be fluidly connected to each other via one or more connecting conduits 258, which extend between the outlet 216 of the heat exchanger 200 and the inlet 214 of the adjacent heat exchanger 200.

[0069] like Figure 7 and 8 As shown, multiple heat exchangers 200 can be circumferentially arranged between stationary supports 174. For example, the multiple heat exchangers 200 can be arranged such that the supports are circumferentially located between each of the multiple heat exchangers 200.

[0070] Now for reference Figure 9 The flowchart illustrates a method 800 for operating a three-flow engine, where dashed boxes indicate optional steps of method 800. The three-flow engine can be referenced above. Figures 1 to 8 One or more of the exemplary three-flow engines described are constructed in a similar manner.

[0071] As shown, method 800 generally includes step 802 of operating fan section 150 to generate an airflow within inlet duct 180. Inlet duct 180 is at least partially defined by fan shroud 170. In many embodiments, method 800 may further include step 804 of directing a first portion of the airflow into a core duct 142 defined at least partially by core shroud 122. Core shroud 122 circumferentially surrounds core engine 120. Method 800 may further include step 806 of directing a second portion of the airflow into the fan duct 172 defined by core shroud 122 and fan shroud 170. For example, core shroud 122 may be radially disposed between fan shroud 170 and core engine 120 such that core shroud 122 divides (not necessarily uniformly, but may be uniform in some embodiments or operating modes) the airflow within inlet duct 180 into two separate thrust-generating flows. In particular, the airflow within inlet duct 180 may be divided into two flows by leading edge 144 of core shroud. Two separate airflows can be provided to the core duct 142 and the fan duct 172 after being divided.

[0072] In an exemplary embodiment, method 800 may further include step 808 of feeding a second portion of a flow into a heat exchanger 200 positioned within fan duct 172 to cool kinetic fluid 212 traveling through the heat exchanger 200. For example, the heat exchanger 200 may provide thermal communication between the kinetic fluid 212 and a second portion of the airflow traveling through fan duct 172. For example, the heat exchanger 200 may be (at least partially) constructed of a material with high thermal conductivity (e.g., aluminum, copper, bronze, or other suitable thermally conductive metal). In particular, the heat exchanger 200 may provide thermal communication between the air and the kinetic fluid while fluidly isolating the fluids from each other. In this way, the heat exchanger 200 may advantageously provide heat transfer to the relatively cool air within the third flow or fan duct 172 and one or more kinetic fluids from the thermal systems of the third-flow engine (e.g., lubrication systems, fuel systems, or other systems that benefit from heat reduction).

[0073] In some embodiments, method 800 may further include an optional step 810 of maintaining the temperature of the external heat exchanger 200 to prevent ice formation on the outer surface of the heat exchanger 200. For example, the heat exchanger may maintain a sufficiently warm outer surface via a kinetic fluid 212 traveling through it to prevent ice formation thereon during operation of a three-flow engine. Additionally or alternatively, the outer surface of the heat exchanger 200 may be coated with an anti-icing coating or a suitable de-icing coating, which advantageously increases the operational flexibility and overall lifespan of the heat exchanger 200. In other embodiments, the heat exchanger 200 may include one or more mechanical features, such as an inlet particle separator, to prevent ice formation thereon.

[0074] This written description uses examples to disclose the invention, including the best mode, and also enables any person skilled in the art to practice the invention, including making and using any device or system and performing any combination of methods. The patent scope of the invention is defined by the claims, but 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.

[0075] Further details are provided by the following topics:

[0076] A three-flow engine includes: a fan section; a core engine disposed downstream of the fan section; a core shroud annularly surrounding the core engine and at least partially defining a core duct; a fan shroud radially outwardly disposed from the core shroud and annularly surrounding at least a portion of the core shroud, the fan shroud at least partially defining an inlet duct and a fan duct, the fan duct and the core duct extending axially together at least partially on opposite sides of the core shroud; and a heat exchanger disposed within the fan duct, wherein the heat exchanger provides thermal communication between fluid flowing through the fan duct and kinetic fluid flowing through the heat exchanger.

[0077] The device according to one or more of these clauses further includes at least one stationary support that connects the core shroud to the fan shroud and extends through the fan duct.

[0078] According to one or more of these clauses, the heat exchanger is disposed within the fan duct in front of the at least one stationary support.

[0079] According to one or more of these clauses, the heat exchanger is disposed within a fan duct behind the at least one stationary support.

[0080] According to one or more of these clauses, approximately 10% to approximately 100% of the fluid flowing through the fan duct passes through the heat exchanger.

[0081] According to one or more of these clauses, the heat exchanger extends within the fan duct between a fixed end and a free end to allow for thermal expansion of the heat exchanger.

[0082] According to one or more of these clauses, the fixed end is connected to one of the fan shroud, the core shroud, or a stationary support extending radially through the fan duct.

[0083] According to one or more of these clauses, the heat exchanger is a plurality of heat exchangers arranged circumferentially within a fan duct.

[0084] According to one or more of these clauses, the plurality of heat exchangers are circumferentially spaced apart from each other.

[0085] According to one or more of these clauses, each of the plurality of heat exchangers includes a motive fluid inlet, a motive fluid loop, and a motive fluid outlet.

[0086] According to one or more of these clauses, in the device, the power fluid inlet of each of the plurality of heat exchangers is independently fluidly connected to a power fluid supply unit, and the power fluid outlet of each heat exchanger is independently fluidly connected to a power fluid return unit.

[0087] According to one or more of these clauses, the power fluid outlet of the first heat exchanger of the plurality of heat exchangers is fluidly connected to the power fluid inlet of the second heat exchanger of the plurality of heat exchangers.

[0088] According to one or more of these clauses, the inlet duct extends from an inlet downstream of the fan section to the leading edge of the core shroud.

[0089] According to one or more of these clauses, the fan duct and the core duct each extend from a respective inlet partially defined by the leading edge of the core shroud to a respective outlet.

[0090] According to one or more of these clauses, the turbine further comprises a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine arranged in a serial flow sequence within the core duct.

[0091] According to one or more of these clauses, the heat exchanger is configured to prevent ice from forming thereon during operation of the three-flow engine.

[0092] A method of operating a three-flow engine, the method comprising: operating a fan section to generate an airflow within an inlet duct, the inlet duct being at least partially defined by a fan shroud; directing a first portion of the airflow into a core duct defined at least partially by a core shroud that annularly surrounds the core engine; directing a second portion of the airflow into a fan duct defined by the core shroud and the fan shroud; and feeding a portion of the second portion of the airflow into a heat exchanger located within the fan duct to cool kinetic fluid traveling through the heat exchanger.

[0093] The method according to one or more of these clauses further includes: maintaining the temperature of the external heat exchanger to prevent ice from forming on the outer surface of the heat exchanger.

[0094] According to one or more of these provisions, the heat exchanger extends within the fan duct between a fixed end and a free end to allow for thermal expansion of the heat exchanger.

[0095] According to one or more of the methods described in these clauses, the inlet duct extends from an inlet downstream of the fan section to the leading edge of the core shroud.

Claims

1. A three-flow engine, characterized in that, include: Fan section; The core engine is located downstream of the fan section, and the core engine includes a booster compressor located upstream of the high-pressure compressor. A core shroud that annularly surrounds the core engine and at least partially defines core piping, wherein both the booster compressor and the high-pressure compressor are enclosed within the core shroud; A fan shroud is arranged radially outward from the core shroud and circumferentially surrounds at least a portion of the core shroud. The fan shroud at least partially defines an inlet duct, and the fan shroud and the core shroud at least partially define a fan duct, the fan duct and the core duct extending axially together at least partially on opposite sides of the core shroud. At least one stationary support, the at least one stationary support connecting the core shroud to the fan shroud and extending radially through the fan duct, wherein the at least one stationary support is axially disposed between the boost compressor and the high-pressure compressor; as well as A heat exchanger disposed within the fan duct, the heat exchanger including a first wall and a second wall, the first wall contacting and being coupled to the at least one stationary support, the second wall being positioned on the inner surface of the fan shroud and the outer surface of the core shroud, each of the first wall and the second wall extending radially from the core shroud to the fan shroud and into the fan duct, and the at least one stationary support and the first wall and the second wall being circumferentially spaced apart, wherein the first wall is fixed relative to the at least one stationary support, and the second wall is movable relative to the inner surface and the outer surface to allow thermal expansion of the heat exchanger, and wherein the heat exchanger provides thermal communication between fluid flowing through the fan duct and kinetic fluid flowing through the heat exchanger.

2. The three-flow engine according to claim 1, characterized in that, 10% to 100% of the fluid flowing through the fan duct passes through the heat exchanger.

3. The three-flow engine according to claim 1, characterized in that, The heat exchangers mentioned therein are multiple heat exchangers arranged circumferentially within the fan duct.

4. The three-flow engine according to claim 3, characterized in that, The plurality of heat exchangers are circumferentially spaced apart from each other.

5. The three-flow engine according to claim 3, characterized in that, Each of the plurality of heat exchangers includes a power fluid inlet, a power fluid loop, and a power fluid outlet.

6. The three-flow engine according to claim 5, characterized in that, The power fluid inlet of each of the plurality of heat exchangers is independently fluidly connected to a power fluid supply unit, and the power fluid outlet of each of the heat exchangers is independently fluidly connected to a power fluid return unit.

7. The three-flow engine according to claim 5, characterized in that, The power fluid outlet of the first heat exchanger of the plurality of heat exchangers is fluidly connected to the power fluid inlet of the second heat exchanger of the plurality of heat exchangers.

8. The three-flow engine according to claim 1, characterized in that, The inlet duct extends from the inlet downstream of the fan section to the leading edge of the core shroud.

9. The three-flow engine according to claim 8, characterized in that, The fan duct and the core duct each extend from a corresponding inlet partially defined by the leading edge of the core shroud to a corresponding outlet.

10. The three-flow engine according to claim 9, characterized in that, The core engine further includes a combustion chamber, a high-pressure turbine, and a low-pressure turbine arranged in a serial flow sequence within the core conduit.

11. The three-flow engine according to claim 1, characterized in that, The heat exchanger is coated with an ice-repellent coating.

12. A method for operating a three-flow engine, characterized in that, The three-flow engine includes: Fan section; The core engine is located downstream of the fan section, and the core engine includes a booster compressor located upstream of the high-pressure compressor. A core shroud that annularly surrounds the core engine and at least partially defines core piping, wherein both the booster compressor and the high-pressure compressor are enclosed within the core shroud; A fan shroud is arranged radially outward from the core shroud and circumferentially surrounds at least a portion of the core shroud. The fan shroud at least partially defines an inlet duct, and the fan shroud and the core shroud at least partially define a fan duct, the fan duct and the core duct extending axially together at least partially on opposite sides of the core shroud. At least one stationary support, the at least one stationary support connecting the core shroud to the fan shroud and extending radially through the fan duct, wherein the at least one stationary support is axially disposed between the boost compressor and the high-pressure compressor; and A heat exchanger disposed within the fan duct includes a first wall and a second wall. The first wall contacts and is connected to the at least one stationary support. The second wall is positioned on an inner surface of the fan shroud and an outer surface of the core shroud. Each of the first and second walls extends radially from the core shroud to the fan shroud and into the fan duct. The at least one stationary support and the first and second walls are circumferentially spaced apart. The first wall is fixed relative to the at least one stationary support, and the second wall is movable relative to the inner and outer surfaces to allow thermal expansion of the heat exchanger. The heat exchanger provides thermal communication between fluid flowing through the fan duct and kinetic fluid flowing through the heat exchanger. The method includes: The fan section is operated to generate an airflow within the inlet duct, which is at least partially defined by the fan shroud; A first portion of the airflow is directed into a core duct at least partially defined by the core shroud; The second portion of the airflow is directed into the fan duct, which is at least partially defined by the core shroud and the fan shroud; and A second portion of the airflow is fed into the heat exchanger located within the fan duct to cool the kinetic fluid traveling through the heat exchanger.

13. The method according to claim 12, characterized in that, Further includes: Maintain the temperature of the external heat exchanger to prevent ice from forming on its outer surface.

14. The method according to claim 12, characterized in that, The inlet duct extends from the inlet downstream of the fan section to the leading edge of the core shroud.

15. A gas turbine engine, characterized in that, include: Fan section; The core engine is located downstream of the fan section; A core cover, which is arranged outside the core engine; as well as A fan shroud is arranged radially outward from the core shroud and circumferentially surrounds at least a portion of the core shroud, and the fan shroud and the core shroud at least partially define a fan duct, the fan duct and the core duct extending axially together on opposite sides of the core shroud; At least one stationary support, the at least one stationary support connecting the core shroud to the fan shroud and extending radially through the fan duct; wherein the at least one stationary support is axially disposed between the supercharger and the high-pressure compressor of the gas turbine engine; as well as A heat exchanger disposed within the fan duct, the heat exchanger including a first wall and a second wall, the first wall contacting and being coupled to the at least one stationary support, the second wall being positioned on the inner surface of the fan shroud and the outer surface of the core shroud, each of the first wall and the second wall extending radially from the core shroud to the fan shroud and into the fan duct, and the at least one stationary support and the first wall and the second wall being circumferentially spaced apart, wherein the first wall is fixed relative to the at least one stationary support, and the second wall is movable relative to the inner surface and the outer surface to allow thermal expansion of the heat exchanger, and wherein the heat exchanger provides thermal communication between fluid flowing through the fan duct and kinetic fluid flowing through the heat exchanger.

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