Gas turbine engine with heat recovery system

Abstract

The gas turbine engine includes a fan located forward of the gas turbine engine, a compressor section and a turbine section arranged in series flow order. The compressor section and the turbine section together define a core airflow path. The rotating member is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. The outlet guide vane assembly includes a plurality of outlet guide vanes in the exhaust airflow path downstream of the turbine section. The plurality of outlet guide vanes are circumferentially spaced apart from one another over an angular range of about 360 degrees, and each of the plurality of outlet guide vanes defines a radial range. At least one of the plurality of outlet guide vanes includes a cold fluid passage extending at least partially radially therethrough, through which a fluid coolant flows, and another one of the plurality of guide vanes includes a heated fluid passage extending at least partially radially therethrough, through which a fluid coolant flows. A fluid coolant flows through the heating fluid channel and receives heat from the exhaust gas flow from the core gas flow path.

Description

[0001] This application is a divisional application of the invention patent application with application number 202210292931.8 filed on March 23, 2022 and invention name “Gas turbine engine with heat recovery system”. Technical Field

[0002] The present description relates generally to gas turbine engines and, more particularly, to gas turbine engines including heat recovery systems. Background Art

[0003] Gas turbine engines are often used as part of an aircraft propulsion system. A gas turbine engine may include a compressor section, a combustion section, a turbine section, and an exhaust section. Air is provided by a fan to the compressor section, where it is compressed and delivered to the combustion section. In the combustion section, the air is mixed with fuel and then burned. The combustion gases are then delivered to the turbine section, which drives the turbine section before delivering the combustion gases to the exhaust section.

[0004] During operation, the temperature within the gas turbine engine may increase. In order to manage the temperature increase of the gas turbine engine, various cooling systems may be provided for removing thermal energy from various components of the gas turbine engine. This heat may be used by other engine systems in a beneficial manner. Summary of the invention

[0005] According to an embodiment of the present disclosure, a gas turbine engine includes a fan located at the front of the gas turbine engine, a compressor section and a turbine section arranged in a series flow sequence. The compressor section and the turbine section together define a core airflow path. The rotating member can rotate with at least a portion of the compressor section and at least a portion of the turbine section. The outlet guide vane assembly includes a plurality of outlet guide vanes located in the exhaust gas flow path downstream of the turbine section. The plurality of outlet guide vanes are circumferentially spaced from each other within an angular range of approximately 360 degrees, and each plurality of outlet guide vanes defines a radial extent. At least one of the plurality of outlet guide vanes includes a cold fluid passage extending at least partially radially therethrough, through which a fluid coolant flows, and another guide vane of the plurality of guide vanes includes a heating fluid passage extending at least partially radially therethrough, through which a fluid coolant flows and receives heat from the exhaust gas flow of the core airflow path. "Fluid" is intended to mean a liquid or a gas, or a substance having both gas and liquid properties (i.e., a supercritical fluid).

[0006] According to another embodiment of the present disclosure, a method includes removably attaching an outlet guide vane assembly to a turbine aft frame of a gas turbine engine. The outlet guide vane assembly includes a plurality of outlet guide vanes located in an exhaust gas flow path downstream of a turbine section. The plurality of outlet guide vanes are circumferentially spaced from each other within an angular range of approximately 360 degrees, and each of the plurality of outlet guide vanes defines a radial range. At least one of the plurality of outlet guide vanes includes a cold fluid passage extending at least partially radially therethrough, through which a fluid coolant flows, and another of the plurality of guide vanes includes a heating fluid passage extending at least partially radially therethrough, through which a fluid coolant flows and receives heat from the exhaust gas flow of a core gas flow path. The fluid coolant is conveyed through the cold fluid passage and then through the heating fluid passage. When the fluid coolant is directed through the heating fluid passage, the fluid coolant receives heat from the exhaust gas flow of the core gas flow path.

[0007] According to another embodiment of the present disclosure, a gas turbine engine includes a compressor section and a turbine section arranged in a series flow sequence. The compressor section and the turbine section together define a core airflow path. The rotating member can rotate with at least a portion of the compressor section and at least a portion of the turbine section. The turbine rear frame includes a first outlet guide vane in the exhaust gas flow path downstream of the turbine section. The first outlet guide vanes are circumferentially spaced from each other within an angular range of approximately 360 degrees, and each first outlet guide vane defines a radial range. The outlet guide vane assembly includes a second outlet guide vane, which is located in the exhaust gas flow path adjacent to the first outlet guide vane. The second outlet guide vanes are circumferentially spaced from each other within an angular range of approximately 360 degrees, and each second outlet guide vane defines a radial range. One or both of the first outlet guide vane and the second outlet guide vane are turned, thereby changing the flow direction of the exhaust gas flow from the exhaust gas flow path.

[0008] According to another embodiment of the present disclosure, a gas turbine engine includes a fan located at the front of the gas turbine engine, a compressor section and a turbine section arranged in a series flow sequence. The compressor section and the turbine section together define a core airflow path. The rotating member is capable of rotating with at least a portion of the compressor section and at least a portion of the turbine section. The outlet guide vane assembly includes a plurality of outlet guide vanes located in the exhaust gas flow path downstream of the turbine section. The plurality of outlet guide vanes are circumferentially spaced from each other within an angular range of approximately 360 degrees, and each of the plurality of outlet guide vanes defines a radial range. One or more outlet guide vanes include surface enhancement features that increase the surface area of ​​the side surface of the outlet guide vane.

[0009] Additional features, embodiments, and advantages of the gas turbine engine and methods of using the same described herein will be set forth in the detailed description that follows, and in part will be apparent to those skilled in the art based on the teachings disclosed herein that such features, embodiments, and advantages are anticipated and contemplated to be within the scope of the present disclosure.

[0010] It should be understood that both the foregoing general description and the following detailed description describe various embodiments and are intended to provide an overview or framework for understanding the nature and properties of the subject matter described and claimed herein. The accompanying drawings are included to provide a further understanding of the various embodiments and are incorporated into and constitute a part of this specification. The accompanying drawings illustrate the various embodiments described herein and, together with the description, serve to explain the principles and operation of the subject matter described and claimed herein. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 is a schematic cross-sectional view of a gas turbine engine including an electric machine according to one or more embodiments shown and described herein;

[0012] Figure 2 is a method for Figure 1 Schematic diagram of a heat recovery system in a gas turbine engine;

[0013] Figure 3 is a method for Figure 1 A diagrammatic view of another embodiment of a heat recovery system in a gas turbine engine;

[0014] Figure 4 According to one or more embodiments shown and described herein Figure 1 A schematic cross-sectional view of a gas turbine engine;

[0015] Figure 5 According to one or more embodiments shown and described herein Figure 1 A more detailed schematic cross-sectional view of a gas turbine engine;

[0016] Figure 6 is a method for Figure 5 A schematic cross-sectional view of an outlet guide vane assembly in a gas turbine engine;

[0017] Figure 7 According to one or more embodiments shown and described herein Figure 5 A schematic cross-sectional view of an outlet guide vane assembly;

[0018] Figure 8is a schematic cross-sectional view of another embodiment of an outlet guide vane assembly according to one or more embodiments shown and described herein;

[0019] Fig. 9 is a schematic cross-sectional view of another embodiment of a gas turbine engine according to one or more embodiments shown and described herein;

[0020] Fig.10 is a schematic cross-sectional view of another embodiment of a gas turbine engine according to one or more embodiments shown and described herein;

[0021] Fig.11 is a schematic cross-sectional view of another embodiment of a gas turbine engine according to one or more embodiments shown and described herein;

[0022] Fig.12 According to one or more embodiments shown and described herein Fig.10 A schematic cross-sectional view of an outlet guide vane assembly;

[0023] Fig.13 is a diagrammatic illustration of an outlet guide vane assembly connected to a turbine aft frame according to one or more embodiments shown and described herein;

[0024] Fig.14 is a diagrammatic illustration of an outlet guide vane assembly connected to a turbine aft frame according to one or more embodiments shown and described herein;

[0025] Fig.15 is a diagrammatic illustration of an outlet guide vane assembly connected to a turbine aft frame according to one or more embodiments shown and described herein;

[0026] Fig.16 is a diagrammatic illustration of an outlet guide vane assembly connected to a turbine aft frame according to one or more embodiments shown and described herein;

[0027] Fig.17 is a diagrammatic illustration of an outlet guide vane assembly connected to a turbine aft frame according to one or more embodiments shown and described herein;

[0028] Fig.18 is a diagrammatic illustration of an outlet guide vane assembly connected to a turbine aft frame according to one or more embodiments shown and described herein;

[0029] Fig.19 is a diagrammatic illustration of an outlet guide vane assembly connected to a turbine aft frame according to one or more embodiments shown and described herein;

[0030] Fig. 20is a diagrammatic side view of an exit guide vane including surface enhancement features according to one or more embodiments shown and described herein;

[0031] Fig.21 According to one or more embodiments shown and described herein Fig. 20 a diagrammatic end view of an outlet guide vane;

[0032] Fig. 22 is a diagrammatic side view of an exit guide vane including surface enhancement features according to one or more embodiments shown and described herein;

[0033] Fig.23 According to one or more embodiments shown and described herein Fig. 22 a diagrammatic end view of an outlet guide vane;

[0034] Fig.24 is a diagrammatic side view of an exit guide vane including surface enhancement features according to one or more embodiments shown and described herein;

[0035] Fig.25 According to one or more embodiments shown and described herein Fig.24 a diagrammatic end view of an outlet guide vane;

[0036] Fig.26 is a diagrammatic side view of an exit guide vane including surface enhancement features according to one or more embodiments shown and described herein;

[0037] Fig. 27 According to one or more embodiments shown and described herein Fig.26 a diagrammatic end view of an outlet guide vane;

[0038] Fig.28A is a diagrammatic end view of a surface enhancement feature according to one or more embodiments shown and described herein;

[0039] Fig.28B is a diagrammatic end view of another surface enhancement feature according to one or more embodiments shown and described herein;

[0040] Fig.28C is a diagrammatic end view of another surface enhancement feature according to one or more embodiments shown and described herein;

[0041] Fig.28D is a diagrammatic end view of another surface enhancement feature according to one or more embodiments shown and described herein;

[0042] Fig.29is a diagrammatic side view of an exit guide vane including surface enhancement features according to one or more embodiments shown and described herein;

[0043] Fig.30 is a diagrammatic side view of an exit guide vane including surface enhancement features according to one or more embodiments shown and described herein;

[0044] Fig.31 is a diagrammatic side view of an exit guide vane including surface enhancement features according to one or more embodiments shown and described herein;

[0045] Fig.32 is a diagrammatic side view illustrating a surface enhancement feature in operation according to one or more embodiments shown and described herein;

[0046] Fig.33 is a diagrammatic side view of an exit guide vane including surface enhancement features according to one or more embodiments shown and described herein;

[0047] Fig.34 is a diagrammatic side view of an exit guide vane including surface enhancement features according to one or more embodiments shown and described herein;

[0048] Fig.35 is a diagrammatic side view of an outlet guide vane including a plurality of fluid passages according to one or more embodiments shown and described herein;

[0049] Fig.36 is a diagrammatic side view of an outlet guide vane including a plurality of fluid passages according to one or more embodiments shown and described herein;

[0050] Fig.37 is a diagrammatic side view of an outlet guide vane including a plurality of fluid passages according to one or more embodiments shown and described herein;

[0051] Fig.38 is a diagrammatic end view of a fluid passage of an outlet guide vane according to one or more embodiments shown and described herein;

[0052] Fig.39 is a diagrammatic end view of a fluid passage of an outlet guide vane according to one or more embodiments shown and described herein;

[0053] Fig.40 is a diagrammatic end view of a fluid passage of an outlet guide vane according to one or more embodiments shown and described herein;

[0054] Fig.41 is a diagrammatic end view of a fluid passage of an outlet guide vane according to one or more embodiments shown and described herein;

[0055] Fig.42 is a diagrammatic cross-sectional view of a fluid passage of an outlet guide vane according to one or more embodiments shown and described herein;

[0056] Fig.43 is a diagrammatic cross-sectional view of a fluid passage of an outlet guide vane according to one or more embodiments shown and described herein;

[0057] Fig.44 is a diagrammatic cross-sectional view of a fluid passage of an outlet guide vane according to one or more embodiments shown and described herein;

[0058] Fig.45 is a diagrammatic cross-sectional view of a fluid passage of an outlet guide vane according to one or more embodiments shown and described herein; and

[0059] Fig.46 is a diagrammatic cross-sectional view of a fluid passage of an outlet guide vane according to one or more embodiments shown and described herein. DETAILED DESCRIPTION

[0060] The embodiments described herein are generally directed to a gas turbine engine including a heat recovery system. The gas turbine engine may include a compressor section and a turbine section, which are arranged in a series flow sequence and together define a core gas flow path that leads to an exhaust gas flow path outside the engine. Rotating components such as shafts, spools, etc. may rotate with at least a portion of the compressor section and the turbine section. The motor may be embedded in the gas turbine engine. The motor may rotate with the rotating component and be coaxially positioned with the rotating component at least partially inside the core gas flow path along the radial direction of the gas turbine engine. The motor may be a generator driven by the rotating component.

[0061] The gas turbine engine includes a heat recovery system that collects heat from one or more locations using a relatively low temperature fluid (e.g., a heat transfer fluid). As an example, the heat recovery system can collect heat from the exhaust gas flow path and / or the electric machine. The heat recovery system can be integrated into existing structural components of the gas turbine engine, such as outlet guide vanes, which are formed into suitable structures to carry heat exchange passages therethrough and achieve heat recovery.

[0062] refer to Figure 1, the exemplary gas turbine engine 10 may be configured for mounting on a wing or fuselage of an aircraft. In some embodiments, the gas turbine engine 10 may also be used to provide power. The gas turbine engine 10 includes a fan section 12, a compressor section 16, and a turbine section 18, the fan section 12 including a fan 14. The fan section 12, the compressor section 16, and the turbine section 18 may include one or more rotor disks 20, the rotor disk 20 including rotor blades extending radially therefrom. Air is drawn into the gas turbine engine 10 and accelerated by the fan 14. The air or at least a portion of the air is compressed in the compressor section 16 and delivered to the combustion chamber, where the air is mixed with fuel and combusted, thereby producing hot combustion gases. The combustion gases pass through the turbine section 18, which extracts mechanical work from the combustion gases to rotate the attached compressor section 16, thereby further compressing the upstream air to produce a self-sustaining process. The combustion gases are discharged through the nozzle section 22.

[0063] The gas turbine engine 10 defines an axial direction A extending parallel to the longitudinal centerline 23 , a radial direction R extending perpendicular to the axial direction A, and a circumferential direction C extending about the axial direction A. The gas turbine engine 10 includes a fan section 12 and a core section 24 located downstream of the fan section 12 in the axial direction.

[0064] The gas turbine engine 10 includes a tubular core shroud 30 that at least partially defines an annular inlet 32. The core shroud 30 surrounds a compressor section 16 including a supercharger or low pressure (LP) compressor 34 and a high pressure (HP) compressor 36, a combustion section 38 including a combustion chamber, a turbine section 18 including a high pressure (HP) turbine 40 and a low pressure (LP) turbine 42, and an ejection exhaust nozzle section 22 in a series flow relationship. The compressor section 16, the combustor section 38, and the turbine section 18 together define a core airflow path 44 that extends from the annular inlet 32 ​​through the LP compressor 34, the HP compressor 36, the combustion section 38, and the HP turbine 40. A first shaft or spool 45 drivingly connects the HP turbine 40 to the HP compressor 36. A second shaft or spool 48 drivingly connects the LP turbine 42 to the LP compressor 34 and the fan 14.

[0065] The fan section 12 includes a fan 14 having a plurality of fan blades 46 connected to a disk 49 in a spaced-apart manner. The fan blades 46 extend outwardly from the disk 49 generally in a radial direction R. The disk 49 is covered by a rotatable front hub 50 having an aerodynamic profile to facilitate air flow through the plurality of fan blades 46. The exemplary fan section 12 includes an annular fan casing or outer nacelle 52 that circumferentially surrounds at least a portion of the fan 14 and / or the core section 24. The outer nacelle 52 is supported relative to the core section 24 by a plurality of circumferentially spaced struts that also serve as outlet guide vanes 54. A downstream section 56 of the outer nacelle 52 extends over the exterior of the core cowl 30 to define a bypass airflow passage 58 therebetween.

[0066] The gas turbine engine 10 includes an electric motor 60 that is rotatable with the fan 14 and is located within the tail cone 65. The electric motor 60 is a generator that is coaxially mounted with the second shaft 48 and is rotatable with the second shaft 48. In other embodiments, the axis of the electric motor 60 may be radially offset from the axis of the second shaft 48 and may further be tilted relative to the axis of the second shaft 48, so that the electric motor 60 may be positioned at any suitable location at least partially inside the core airflow path 44. In some embodiments, the electric motor 60 may rotate with the first shaft 45.

[0067] Figure 1 The gas turbine engine 10 depicted in FIG. 1 is provided as an example only. In other exemplary embodiments, the gas turbine engine 10 may be replaced by other types of gas turbine engines utilizing embedded electric machines without loss of clarity. Examples include turboprop engines, turbojets, open rotor or inlet fan engines.

[0068] refer to Figure 2 and 3 , illustrates a heat recovery system where heat is captured and used in different ways. First refer to Figure 2 , the heat recovery system 100 may include a waste heat recovery heat exchanger 102, which is a heat source heat exchanger for capturing heat for specific areas or components of the gas turbine engine 10. As will be described in more detail below, the waste heat recovery heat exchanger 102 may be formed by outlet guide vanes. In this example, the waste heat recovery heat exchanger 102 is directly integrated with a fuel delivery system 104 of the gas turbine engine 10. The fuel delivery system 104 provides fuel to the combustion section 38 located between the HP compressor 36 and the HP turbine 40. The fuel is delivered from the fuel delivery system 104, through the waste heat recovery heat exchanger 102, for preheating the fuel, and then delivered to the combustion section 38. Because the fuel is burned in the combustion section 38, using the waste heat recovery heat exchanger 102 to preheat the fuel can improve the efficiency of the combustion process.

[0069] refer to Figure 3 , another example of a heat recovery system 110 is shown including a waste heat recovery heat exchanger 112 that is indirectly integrated into a fuel delivery system 114 via a heat transfer bus 116. The heat transfer bus 116 includes a heat exchange fluid flowing therethrough. A pump 118 is disposed in the heat transfer bus 116 for generating a flow of heat exchange fluid through the heat transfer bus 116. The pump 118 may be a rotary pump including an impeller, or may be any other suitable pump. The pump 118 may be powered by an electric motor, or may be mechanically connected to and powered by one of the shafts 45 and 48 via an accessory gearbox 120.

[0070] The fuel flow rate controller 122 may include any number of pumps and nozzles for controlling the delivery of fuel to the combustion section 38. Figure 3 1, the fuel flow rate controller 122 is shown separately from the fuel system 124 because the fuel flow rate controller 122 is used to transfer heat to the fuel (e.g., via a radiator heat exchanger) rather than directly through the fuel system 124. Figure 2 The waste heat recovery heat exchanger 112 in the embodiment of the present invention is used. The heated fuel is then provided to the combustion section 38. The radiator heat exchanger 125 can be used to cool the heat exchange fluid upstream of the pump 118.

[0071] refer to Figure 4 , shows a more detailed cross-sectional view of a gas turbine engine 10 including a heat recovery system 100. The exemplary gas turbine engine 10 includes a core casing 30 that surrounds a compressor section 16 including a LP compressor 34 ( Figure 1 ) and HP compressor 36, turbine section 18 includes HP turbine 40 and LP turbine 42. Outer nacelle 52 and core cowl 30 define a bypass airflow passage 58. Outlet guide vanes 54 support outer nacelle 52 relative to core cowl 30.

[0072] The compressor section 16, the combustion section 38, and the turbine section 18 together define at least a portion of the core airflow path 44. The fuel delivery system 104 provides a fuel flow to the combustion section 38. The exemplary fuel delivery system 104 may generally include one or more fuel nozzles 130, as well as a fuel pump 134 and a fuel line 136, the fuel nozzle being configured to provide a mixture of fuel and air to the combustion chamber 132. The fuel pump 134 may provide a fuel flow from a fuel source to the fuel nozzle 130 via the fuel line 136.

[0073] As used herein, the terms "heat source" and "heat sink" describe a heat exchange relationship relative to a heat recovery system, depending on whether the heat exchange relationship provides heat to the heat recovery system or removes heat from the heat recovery system. For example, a heat source heat exchange relationship refers to a heat exchange relationship that provides heat to the heat recovery system through thermal communication between the heat recovery system and the heat source. As used herein, the term "thermal communication" refers to two or more systems being in relatively close proximity to each other to achieve efficient heat transfer between the systems (e.g., a heated fluid contained in an uninsulated pipe immersed in a cold fluid). A radiator heat exchange relationship refers to a heat exchange relationship that removes heat from a heat recovery system.

[0074] Also refer to Figure 5 , the waste heat recovery heat exchanger 102 is in heat source heat exchange relationship with the fuel of the fuel delivery system 104. It can be seen that the fuel line 136 extends to the fuel passage 140, which is formed in the outlet guide vane 142 at the downstream end of the LP turbine 42. In some embodiments, the cold fuel passage 140 can be provided by one of the outlet guide vanes 142, and the heating fuel passage 144 can be provided by the adjacent outlet guide vane, which receives the fuel from the cold fuel passage 140.

[0075] As an example, Figure 6 The diagram shows an outlet guide vane assembly 146, which may or may not be a turbine aft frame 150 ( Figure 5 ) structural part. The outlet guide vane assembly 146 includes a plurality of outlet guide vanes 142, which are spaced apart from each other in the circumferential direction within the core airflow path 44. Each outlet guide vane 142 of at least a plurality of outlet guide vanes 142 includes a heated fuel passage 144 or a cold fuel passage 140. It should be noted that the terms "heated" and "cold" are relative to the highest fuel temperature within the passages 140 and 144, for example, the fuel in the cold fuel passage 140 can be heated, but not heated to a temperature higher than the maximum fuel temperature in the heated fuel passage 144. In some embodiments, the cold fuel passage 140 can be insulated to reduce heat transfer to the fuel in the cold fuel passage 140. In addition, the fuel passages 140 and 144 are illustrated as being straight in the radial direction; however, the fuel passages 140 and 144 can follow any suitable path, such as a serpentine, wavy, or even irregular passage, which depends at least in part on the type of engine, the shape of the guide vanes, the amount of heat exchange required, and the like.

[0076] Each outlet guide vane 142 includes an outer end 148 located at an outer guide vane support 151, an inner end 152 located at an inner guide vane support 154, and opposite sides 156 and 158. Figure 7, the sides 156 and 158 can together form a fin shape with multiple functions, one function is to transfer heat from the core airflow path 44, and then transfer the heat to the fuel in the heated fuel passage 144. Another function can be to guide the airflow as it leaves the gas turbine engine 10. In some embodiments, the shape of the outlet guide vanes 142 can be non-turning or low-turning aligned with the turbine airflow outlet angle, so that there is little effect on the airflow direction. In some embodiments, the shape of the outlet guide vanes 142 can be suitable for changing or rotating the turbine airflow outlet angle. At this point, these outlet guide vanes 142 can be considered to be turning outlet guide vanes 142. Whether turning or non-turning, the size, shape and configuration of the outlet guide vanes 142 can transfer heat from the hot air passing through the core airflow path 44 through the outlet guide vanes 142 to the fuel in the fuel passages 140 and 144 to preheat the fuel.

[0077] exist Figure 7 In the embodiment, the lengths of the outlet guide vanes 142 in the axial direction A are substantially the same, which can have a greater impact on the airflow direction between the outlet guide vanes 142. Figure 8 , another embodiment of the outlet guide vane 162 is shown, in which adjacent outlet guide vanes 162a and 162b have different lengths, which can have a greater impact on the heat exchange efficiency. In this example, the outlet guide vane 162a has a relatively long length and the outlet guide vane 162b has a relatively short length and the outlet guide vane 162a. The shorter length of the outlet guide vane 162b can reduce the amount of area of ​​the shorter length guide vane 162b exposed to the adjacent outlet guide vane 162a, which can have an impact on the fuel temperature in the cold fuel passage 164a. Compared with the cold fuel passage 164a, the shorter length of the outlet guide vane 162b can also reduce the amount of material or distance between the heated fuel passage 164b and the surrounding heated air. In some embodiments, the cold fuel passage 164a can be insulated.

[0078] Reference again Figure 6 , the cold fuel passage 140 may be fluidly coupled to the fuel delivery system 104 at an outer end 148 ( Figure 4) of the fuel line 136. In this regard, relatively cool fuel is provided to the cold fuel passages 140. Each cold fuel passage 140 can be fluidly connected to the heated fuel passage 144 via a connecting conduit 168. The connecting conduit 168 can be any suitable structure for fluidly connecting the fuel passages 140 and 144. In some embodiments, the connecting conduit 168 can also be formed of a material suitable for transferring heat from the heated air to the fuel as the fuel enters the heated fuel passage 144. The heated fuel passage 144 can be coupled to the fuel delivery system 104 ( Figure 4 ) of the fuel line 136. At this point, the heated fuel is provided to the combustion section 38.

[0079] It will be appreciated that the heat exchange relationship between the outlet guide vanes 142 may be referred to as a heat source heat exchange relationship because heat is provided to the fuel as it travels along the cold fuel passage 140 and the heated fuel passage 144. As opposed to separately formed heat exchangers, the outlet guide vanes 142 themselves provide a heat source heat exchange relationship with their integrated fuel passages 140 and 144 extending therethrough. In some embodiments, the fuel passages 140 and 144 may be formed as an integrated and integral part of the outlet guide vanes 142. For example, 3D printing may be used to form the outlet guide vanes 142 and their associated fuel passages 140 and 144. As described in reference Figure 3 As discussed and shown, a heat transfer fluid may be passed through the passages instead of the fuel to transfer heat to the fuel system.

[0080] Reference again Figure 5 , the gas turbine engine 10 may include an electric machine 60. The electric machine 60 is disposed in an aft portion 172 of the gas turbine engine 10 and may be releasably mounted to the turbine aft frame 150 using an aft flange coupler 173 of the turbine aft frame 150 and a support structure 175 of the electric machine 60. The electric machine 60 may also be releasably connected to the LP shaft 48 at a shaft coupler 177. The aft portion 172 is axially disposed downstream of a core section 174 of the gas turbine engine 10.

[0081] The electric machine 60 may be or include a generator that converts mechanical energy generated by the gas turbine engine 10 (e.g., from exhaust gas generated in the core section 174) into electrical energy, which may be used to power electrical devices of the gas turbine engine 10 or components located elsewhere on the aircraft in which the gas turbine engine 10 is installed. Positioning the electric machine 60 in the rear portion 172 of the gas turbine engine 10 may make the electric machine 60 easy to maintain, repair, and replace, and may facilitate removal of the electric machine 60 when necessary. The electric machine 60 may be integrated into the gas turbine engine 10 via releasable couplings 173 and 177, which may be removed without invasively disassembling the entire gas turbine engine 10, such as without removing the gas turbine engine 10 from the wing of the aircraft.

[0082] Positioning the motor 60 in the rear portion 172 provides accessibility, but may create additional design considerations for the gas turbine engine 10. The exhaust gas produced by the core section 174 may be at a relatively high temperature (e.g., in excess of approximately 700° C. or higher in various embodiments), which may make cooling the motor 60 beneficial. Additionally, the rear portion 172 of the gas turbine engine 10 may not be directly connected to the aircraft in which the gas turbine engine 10 is installed. For example, the gas turbine engine 10 may be connected to the aircraft via an external nacelle 52 ( Figure 1 ) is connected to the wing of the aircraft by a pylon extending from the outer nacelle 52, and the outer nacelle 52 is arranged radially outward from the core section 174. In view of this, in order to provide the electricity generated by the motor 60 to other parts of the aircraft, the electricity is transmitted through the gas turbine engine 10.

[0083] In view of the foregoing, a generator service 180 may be delivered through the turbine rear frame 150. The generator service 180 may include a lubrication conduit and a plurality of electrical connectors (e.g., power cables) that conductively connect the motor 60 to the converter. The lubrication conduit may deliver a lubricant (e.g., oil) to the motor 60. The oil may be used as part of a cooling system and used to cool the motor and then taken away, for example, back through the generator service 180.

[0084] The electrical connector connects the motor 60 to the converter. For example, the motor 60 can generate an alternating current ("AC") power signal from the mechanical energy in the rotating LP shaft 48, which is delivered to the converter (located at the front of the engine) via the generator service 180. The converter can generate a direct current (DC) voltage from the alternating current (AC) power signal for communication with an alternative location on the aircraft (e.g., via an electrical communication bus). The generator service 180 can include multiple sets of electrical connectors, each set of electrical connectors including multiple electrical connectors corresponding to the number of phases in the AC power signal generated by the motor 60. The number of electrical connector sets of the generator service 180 can vary depending on the implementation. Incorporating multiple sets of different electrical connectors in the generator service 180 can provide electrical connection redundancy, which is beneficial in providing the AC power signal to the converter even if one of the sets of electrical connectors fails during operation.

[0085] refer to Fig. 9 Another embodiment of the heat recovery system 200 may be incorporated into a device similar to Figure 5 The gas turbine engine 210 of the gas turbine engine 10 is shown in FIG. The gas turbine engine 210 includes a turbine rear frame 212 and an outlet guide vane assembly 214, and the outlet guide vane assembly 214 includes a plurality of outlet guide vanes 216. The outlet guide vane assembly 214 can be used as described above. Figure 5 Aft flange coupler 218 may be releasably coupled to turbine aft frame 212 , or outlet guide vane assembly 214 may be directly coupled to turbine aft frame 212 and be a structurally load bearing portion of turbine aft frame 212 .

[0086] Heat recovery system 200 includes a heat transfer bus 220 including a heat transfer fluid configured to flow therethrough. Exit guide vane 216 includes a heated fluid passage 222 or a cold fluid passage 224 fluidly connected to heat transfer bus 220 such that the heat transfer fluid flows therethrough.

[0087] In this embodiment, the heat recovery system 200 may also be part of a cooling system for cooling an electric machine 226 located in the rear portion 228 of the gas turbine engine 210. As can be seen, the heat transfer bus 220 extends radially toward and away from the electric machine 226. The electric machine 226 may be part of an electric machine assembly 230, which also includes a support structure 232 that connects the electric machine 226 to both the turbine aft frame 212 and the LP shaft 234. The support structure 232 may include, for example, an outer segment 236 that connects the stator of the electric machine to the fixed turbine aft frame 212 and an inner segment 238 that connects the rotor to the LP shaft 234, which rotates the rotor relative to the stator.

[0088] The heat transfer bus 220 can extend alongside and be mounted to the support structure 232, with a cold portion 240 of the heat transfer bus 220 passing through at least a portion of the support structure 232 and / or the motor 226. The heat transfer fluid absorbs heat from the motor 226, which can control the temperature of the motor during use. The heated heat transfer fluid can then be returned via the heated portion 242 and then through the heated fluid channel 222 for transporting the heated heat transfer fluid to another system, such as Figure 3 A fuel delivery system 114 where the waste heat can be used to transfer heat to another system.

[0089] refer to Fig.10 Another embodiment of the heat recovery system 300 may be incorporated into a device similar to Fig. 9 210 of the gas turbine engine 210. The gas turbine engine 310 includes a turbine aft frame 312 and an outlet guide vane assembly 314, which includes a plurality of outlet guide vanes 316. The outlet guide vane assembly 314 may again be releasably coupled to the turbine aft frame 312 using an aft flange coupler 318, or the outlet guide vane assembly 314 may be directly coupled to the turbine aft frame 312 and be a structural load-bearing portion of the turbine aft frame 312.

[0090] As described above, heat transfer bus 320 includes a heat transfer fluid configured to flow therethrough. Exit guide vane 316 includes a heated fluid channel 322 or a cooled fluid channel 324 fluidly connected to heat transfer bus 320 such that the heat transfer fluid flows therethrough.

[0091] In this embodiment, the generator service 326 extends through a passage in the outlet guide vane 316. For example, the generator service 326 may extend through an insulated passage in the outlet guide vane 316 that is distinct from the heated fluid passage 322 and the cold fluid passage 324. The heat transfer bus 320 and the generator service 326 extend radially toward the motor 328. The support structure 340 connects the motor 328 to the turbine aft frame 312 and the LP shaft 342. The generator service 326 and the heat transfer bus 320 may be mounted to the support structure 340. The electrical connection of the generator service 326 back to the engine system may be made outside of the core airflow path 344 (e.g., in the shroud compartment), or may be made in the tail cone 346 below the outlet guide vane 316.

[0092] Fig.11 Shows something like Fig.10An embodiment of a heat recovery system 400 of the heat recovery system 300 is shown. In this embodiment, the outlet guide vane assembly 402 is a structural component that is bolted directly to the turbine aft frame 404 without a rear flange coupler. As described above, the heat transfer bus 420 includes a heat transfer fluid configured to flow therethrough. The outlet guide vane 416 includes a heated fluid passage 422 or a cold fluid passage 424, and a generator service 426 extends through the passage in the outlet guide vane 416. The motor 428 can be accessed through an access panel, or the tail cone 430 along with the motor 428 can be removed as a unit.

[0093] Fig.12 The diagram shows an outlet guide vane assembly 314, which may or may not be part of the turbine aft frame 312. The outlet guide vane assembly 314 includes a plurality of outlet guide vanes 316 that are spaced apart from each other in a circumferential direction within the core airflow path. At least each of the plurality of outlet guide vanes 316 includes a heating fuel passage 322 or a cold fluid passage 324. The generator service 326 may include generator oil supply and return fluid passages 329 and 330 and electrical connector passages 332 and 334. In some embodiments, passages 324, 329, 330, 332, and 334 may be insulated, while the heating fluid passage 322 may be formed of a thermally conductive material. The cold fluid passage 324 leads to the motor 328 to provide a cooling jacket 433, while the heating fluid passage 322 directs the heating fluid away from the motor 328.

[0094] Reference now Fig.13 , an embodiment of an outlet guide vane assembly 500 is illustrated. The outlet guide vane assembly 500 is releasably mounted to a turbine aft frame 502 at a mount 504. A bearing assembly 506 may be provided that allows the turbine 508, LP shaft 510, and motor 512 to rotate relative to the turbine aft frame 502. A cold fluid passage 514 and a hot fluid passage 515 extend through the outlet guide vanes 516 of the outlet guide vane assembly 502 to carry heat away from the motor 512. The cold fluid passage 514 may be provided with an insulator 513 of the outlet guide vanes 516 to carry the cold fluid to the motor 512, and then the heated fluid returns through the heated fluid passage 515, which may be uninsulated to facilitate heat transfer to the fluid.

[0095] In some embodiments, the turbine aft frame 502 may also include a turning or non-turning outlet guide vane 518. In addition, as described above, the outlet guide vanes 516 of the outlet guide vane assembly may be turning or non-turning. The size and shape of the outlet guide vanes 516, 518 of the outlet guide vane assembly 500 and the turbine aft frame 502 may be selected to cooperate to change the flow angle of the heated air as the air passes through the outlet guide vanes 516, 518.

[0096] Reference now Figure 14-17 , showing a plurality of turbine aft frames and exit guide vane assemblies. It should be noted that the shapes and proportions of the guide vane assemblies described herein are not to scale, but represent the general shape of the guide vane assemblies. The turning guide vanes may have, for example, a leading edge less than 30 degrees relative to the direction of airflow exiting the turbine section and a trailing edge less than 5 degrees relative to the direction of airflow. Various shapes, sizes, and turning angles may be used, depending on the specific engine architecture. First refer to Fig.14 , a non-turning or low-turning turbine aft frame 520 includes outlet guide vanes 522. The outlet guide vanes 522 are low-turning or non-turning because they are arranged at approximately the same angle as the airflow exiting the turbine section. The outlet guide vanes 522 direct the heated air toward a turning outlet guide vane assembly 524 located downstream of the outlet guide vanes 522 of the turbine aft frame 520. The outlet guide vane assembly 524 includes outlet guide vanes 526, which are arranged at a certain angle to the airflow exiting the turbine section to change or turn the direction of the airflow. As described above, the outlet guide vanes 526 of the outlet guide vane assembly 524 may include a heating fluid channel and a cold fluid channel.

[0097] refer to Fig.15 , the turning turbine aft frame 530 includes an outlet guide vane 532. The outlet guide vane 532 directs the heated air toward a low turning or non-turning outlet guide vane assembly 534 located downstream of the outlet guide vane 532 of the turbine aft frame 530. The outlet guide vane assembly 534 includes outlet guide vanes 536 that are arranged at approximately the same angle as the airflow exiting the turbine aft frame 530. As described above, the outlet guide vanes 536 of the outlet guide vane assembly 534 may include a heated fluid passage and a cold fluid passage.

[0098] refer to Fig.16, turning to the turbine aft frame 540 includes an outlet guide vane 542. The outlet guide vane 542 directs the heated air to a low turning or non-turning outlet guide vane assembly 544 located inside the outlet guide vane 542 and the turbine aft frame 540. The outlet guide vane assembly 544 includes outlet guide vanes 546 that are arranged at approximately the same angle as the airflow exiting the turbine aft frame 540. As described above, the outlet guide vanes 546 of the outlet guide vane assembly 544 may include a heated fluid passage and a cold fluid passage.

[0099] refer to Fig.17 , the turning outlet guide vane assembly 554 includes an outlet guide vane 556. The outlet guide vane 556 directs the heated air toward the low turning or non-turning turbine aft frame 550 located downstream of the outlet guide vane 556 of the outlet guide vane assembly 554. As described above, the outlet guide vane 556 of the outlet guide vane assembly 54 may include a heating fluid passage and a cooling fluid passage.

[0100] refer to Fig.18 (It is related to Fig.14 The same general turning / non-turning arrangement), in some embodiments, the outlet guide vane assembly 600 can be assembled with multiple packages of individual or multiple vane modules 602. In some embodiments, multiple vane modules 602 can include multiple vane groups to reduce integration complexity and reduce the number of modular groups. The vane modules 602 can each include multiple outlet guide vanes 604a, 604b, which include heating fluid channels 606 and cold fluid channels 608. The vane modules 602 are assembled to form a 360-degree outlet guide vane assembly 600. Each vane module 602 can include a quick disconnect connection (represented by line 610) to enter the heat transfer bus and can be removed individually, such as for repair or replacement. In some embodiments, the outlet guide vane assembly 600 can be pre-assembled and then mounted to the turbine rear frame 612 to form the turbine rear frame and heat exchanger assembly 614. The entire outlet guide assembly 600 can be replaceable as a unit flight line.

[0101] refer to Fig.19 Another embodiment of a turbine aft frame and heat exchanger assembly 620 includes a turbine aft frame 622 including an outlet guide vane 624 and an outlet guide vane assembly 626 including an outlet guide vane 628. The outlet guide vanes 624 of the turbine aft frame 622 may be non-turning or low-turning, while the outlet guide vanes 628 may be turning, such that the outlet guide vanes 624 and 628 act in tandem to change the direction of the airflow. Fig.18Compared to the embodiment of the present invention, the outlet guide vanes 628 of the outlet guide vane assembly 626 all have substantially the same length in the axial direction. The outlet guide vanes 628 are arranged in two staggered rows 632 and 634 so that the outlet guide vanes 628 of row 632 have leading edges 636 aligned in the circumferential direction C, in front of the leading edges 638 of the outlet guide vanes 628 of row 634, which are also aligned in the circumferential direction C. As described above, the guide vanes 628 include a heating fluid channel 640 and a cold fluid channel 642. The increased length of the outlet guide vanes 628 can further enhance the airflow control. In combination with Figure 7 and Fig.18 , any arrangement of guide vanes of equal / different lengths and offset / aligned leading edges may be used.

[0102] Reference now Fig. 20 and 21 Various surface enhancement features, such as fins, dimples, and ribs, may be provided on the surface of the outlet guide vanes to provide more airflow and heat transfer capabilities. Surface enhancement features may be provided on the surface of any outlet guide vane described herein. Fig. 20 and 21 A partial cross-sectional view of an outlet guide vane assembly 650 is shown, which includes an outlet guide vane 652, and the outlet guide vane 652 includes side surfaces 654 and 655, and the side surfaces 654 and 655 include a fin 656 located between an outer guide vane support 658 and an inner guide vane support 660. The fin 656 can have a length that is substantially the same as the length of the outlet guide vane 652. In other embodiments, the length of the fin 656 can be less than the length of the outlet guide vane 652. The fin 656 generally extends in the axial direction A, but can have other orientations, as described below. An array of fins 656 is shown and the fins 656 are spaced apart in the radial direction R along the height of the outlet guide vane 652.

[0103] Fins may refer to structures that generally increase the surface area of ​​the side surfaces of the outlet guide vanes to increase heat transfer. Ribs may refer to shorter and / or thicker surface enhancement features that may be used to increase heat transfer more by inducing turbulence through the outlet guide vanes. Dimple may refer to recesses into the side surfaces that may be used to increase heat transfer more by inducing turbulence through the outlet guide vanes. Inducing turbulence may promote mixing of the air layers, thereby improving heat transfer. These surface enhancement features all increase the surface area over which the air flows.

[0104] Figure 22-32 The additional surface area enhancement features of the outlet guide vanes described herein are shown. Fig. 22 and 23, ribs 662 are illustrated as extending in a radial direction R along the height of outlet guide vane 664. Ribs 662 may have a height in radial direction R that is substantially the same as the height of outlet guide vane 664. In other embodiments, ribs 662 may have a height that is less than the height of outlet guide vane 664. Ribs 662 generally extend in radial direction R. An array of ribs 662 is shown and ribs 662 are spaced apart in axial direction A along the length of outlet guide vane 664.

[0105] refer to Fig.24 and 25 As another example, ribs 670 are shown extending along the height and length of outlet guide vanes 672 in both the axial direction A and the radial direction R. An array of ribs 670 is shown, and the ribs 670 are spaced apart in both the axial direction A and the radial direction R. The ribs 670 may be inclined at any suitable angle relative to the axial direction, such as 30 degrees, 45 degrees, 60 degrees, between 0 and 90 degrees, between 20 and 60 degrees, etc.

[0106] refer to Fig.26 and 27 , ribs 674 are shown extending along the height and length of outlet guide vane 676 in both the axial direction A and the radial direction R. In this embodiment, ribs 674 are arranged in a V-shaped pattern. An array of ribs 674 is shown, and ribs 670 are spaced apart in both the axial direction A and the radial direction R. Ribs 674 can be inclined at any suitable angle relative to the axial direction, such as 30 degrees, 45 degrees, 60 degrees, between 0 and 90 degrees, between 20 and 60 degrees, etc.

[0107] Figures 28A-28D Fins and ribs of various cross-sectional shapes are shown. Suitable shapes include rectangular, triangular, etc. Other suitable shapes may be used, such as wavy or irregular shapes. In some embodiments, the surface enhancement features may be formed as an integral component and formed from the same material as the outlet guide vanes. For example, additive manufacturing may be used to form the surface enhancement features.

[0108] Fins and ribs may be surface enhancement features that protrude outwardly from the surface of the outlet guide vane. The surface of the outlet guide vane may be provided with surface enhancement features, such as dimples, that protrude inwardly from the surface. Fig.29 , the outlet guide vane 680 includes dimples 682 disposed on at least one surface 684 of the outlet guide vane 680. The dimples 682 are formed as recesses in the surface 684 and are also provided to create more turbulence to increase heat transfer.

[0109] The dimple 682 may be any suitable shape, such as circular, oval, rectangular, etc. In the example shown, the dimple 682 is an oval with an elongated circular shape. Fig.29In FIG. 6 , the elongated direction D of the recess 682 extends along the axial direction A. Fig.30 In FIG. 6A , the elongated direction D of the dimple 686 is aligned with the radial direction R. Fig.31 In the embodiment, the elongated direction D of the dimple 688 is inclined relative to the axial direction A, for example, 30 degrees, 45 degrees, 60 degrees, between 40 degrees and 60 degrees, etc. Other configurations are possible, such as a V-shaped elongated direction arrangement.

[0110] refer to Fig.32 , a diagram illustrating the operation of dimples 682. Airflow not affected by dimples 682 tends to be relatively laminar, as indicated by arrows 690. Air entering dimples 682 tends to introduce more turbulence, as indicated by arrows 692, wherein the various layers of air tend to mix.

[0111] refer to Fig.33 and 34 In some embodiments, the outlet guide vanes 700 and 702 may be provided with surface enhancement features 704 and 706 that change the geometry of the trailing edges 708 and 710 of the outlet guide vanes 700 and 702. For example, the surface enhancement features may include fins 704 and 706 disposed at the trailing edges 708 and 710. The fins 704 and 706 may be provided with ( Fig.34 ) or not set ( Fig.33 ) The surface enhancement features described above, such as fins 712, ribs and / or dimples. Surface enhancement features 704 and 706 may be used for noise enhancement to change the sound profile of the exhaust flow.

[0112] refer to Figure 35-37 Various fluid channel structures can be formed according to the required fluid flow characteristics. For example, Fig.35 , the outlet guide vane 714 may be provided with a plurality of fluid passages 716, 718, 720, and 722. In this example, the fluid passages 716, 718, 720, and 722 all direct the fluid to the same direction indicated by arrow 723. Fig.36 In the embodiment, fluid passages 724 and 726 direct fluid radially inwardly as indicated by arrow 725, while fluid passages 728 and 730 direct fluid radially outwardly as indicated by arrow 727. Fewer or more fluid passages may be provided, such as Fig.37 As shown, it includes two fluid channels 732 and 734, one channel 732 directing fluid radially inwardly and the other channel 734 directing fluid radially outwardly.

[0113] Reference now Figure 38-41, the fluid channels 740, 742, 744 and 746 can be provided with surface enhancement features 748, 750, 752 and 754, such as fins, dimples, ribs, dividers, etc. It can be seen that the channels 740, 742, 744 and 746 themselves can be of a predetermined cross-sectional shape, such as circular or rectangular. Fig.42 and 43 , surface enhancement features 748, 750, 752 and 754 may be provided at preselected intervals ( Fig.42 ) or disposed over the entire length of channels 740, 742, 744 and 746 ( Fig.43 ).

[0114] refer to Fig.44 and 45 , the surface enhancement features 760 and 762 can act as turbulators to increase turbulence in the fluid channels 764 and 766. The surface enhancement features 760 and 762 can extend 360 degrees completely around the fluid channels 764 and 766, or they can extend only partially around the fluid channels 764 and 766. In some embodiments, the surface enhancement features 762 can be staggered and alternate in a repeating manner, for example Fig.45 shown. Fig.46 Another embodiment is shown including a fluid channel 770 that includes surface enhancement features in the form of dimples 772. The dimples 772 may also be used to introduce turbulence into the fluid flow.

[0115] The above-described outlet guide vane assembly provides an integrated heat exchanger structure that captures heat and can remove heat from the exhaust gas flow and the motor. The waste heat can then be used to heat other systems, such as fuel for the fuel delivery system. The outlet guide vane assembly can provide a line replaceable unit, thereby achieving dispatch reliability. The generator lubricant and electrical connectors can be separated from the turbine rear frame, which can isolate the system for repair without disassembling the turbomachinery. Damaged vane modules can also be removed and replaced. Combining generator cooling and waste heat removal into one loop can increase the benefits of the heat transfer system. The outlet guide vanes of the outlet guide vane assembly can be used as a steering element behind the non-turning turbine rear frame, which can improve the overall flow path loss. The heat transfer fluid can be used to cool the generator using an independent pump after the engine is shut down, which can improve the heat back-seepage effect on the generator. The outlet guide vane assembly or a portion thereof can be removed with the turbine rear frame attached to the turbine housing, and the engine bearings and oil sump can be unaffected by the removal of the outlet guide vane assembly.

[0116] As used herein, the singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise. Thus, for example, reference to "a" component includes aspects having two or more such components unless the context clearly dictates otherwise.

[0117] Ranges can be expressed herein as from "about" a particular value, and / or to "about" another particular value. When such a range is expressed, another embodiment includes from a particular value and / or to another particular value. Similarly, when a value is expressed as an approximation by using the antecedent "about", it will be understood that the particular value forms another embodiment. It will be further understood that the endpoints of each range are important relative to the other endpoint and independently of the other endpoint. The term "about" may include any value within ten percent of a particular value, such as within five percent of a particular value, such as within two percent of a particular value, such as within one percent of a particular value.

[0118] Unless otherwise expressly stated, directional terms as used herein - such as up, down, right, left, front, rear, top, bottom, higher, lower - are made with reference only to the drawings drawn and are not intended to imply an absolute orientation. The terms "axial" and "longitudinal" both refer to directions parallel to the centerline of the gas turbine engine, while "radial" refers to directions perpendicular to the longitudinal direction. The terms "tangential" and "circumferential" refer to directions that are mutually perpendicular to the radial and longitudinal directions. The terms "forward" or "front" refer to an upstream position of the airflow through or around a component during operation, while the terms "rearward" or "rear" refer to a downstream position during operation. These directional terms are used for convenience of description only, and no specific orientation of the structures described thereby is required.

[0119] Unless otherwise expressly stated, any method described herein is in no way intended to be interpreted as requiring that its steps be performed in a particular order, nor requiring any particular orientation of the apparatus. Thus, if a method claim does not actually state the order in which its steps should be followed, or any apparatus claim does not actually state the order or orientation of individual components, or if there is no other express statement in the claim or specification that the steps are to be limited to a particular order, or if no particular order or orientation of the apparatus components is recited, then no order or orientation is intended to be inferred in any respect. This applies to any possible non-express basis for interpretation, including: logical issues related to the arrangement of steps, operational flow, order of components, or orientation of components; plain meaning derived from grammatical organization or punctuation, and; the number or type of embodiments described in the specification.

[0120] Further aspects of the subject matter are provided in the following clauses:

[0121] 1. A gas turbine engine, the gas turbine engine comprising: a fan, the fan being located at a front portion of the gas turbine engine; a compressor section and a turbine section, the compressor section and the turbine section being arranged in a series flow sequence, the compressor section and the turbine section together defining a core airflow path; a rotating component, the rotating component being capable of rotating together with at least a portion of the compressor section and at least a portion of the turbine section; and an outlet guide vane assembly, the outlet guide vane assembly comprising a plurality of outlet guide vanes located in the exhaust gas flow path downstream of the turbine section, the plurality of outlet guide vanes being circumferentially spaced from each other over an angular range of approximately 360 degrees, and each of the plurality of outlet guide vanes defining a radial extent; wherein at least one of the plurality of outlet guide vanes includes a cold fluid passage extending at least partially radially therethrough, and another of the plurality of guide vanes includes a heating fluid passage extending at least partially radially therethrough, a fluid coolant flowing through the heating fluid passage and receiving heat from the exhaust gas flow of the core airflow path.

[0122] 2. The gas turbine engine according to any of the preceding clauses, wherein at least one outlet guide vane of the plurality of outlet guide vanes comprises a plurality of fluid passages extending at least partially radially therethrough.

[0123] 3. A gas turbine engine according to any of the preceding clauses, further comprising a turbine aft frame supporting the turbine section, the turbine aft frame comprising an exit guide vane assembly.

[0124] 4. A gas turbine engine according to any of the preceding clauses, further comprising a turbine aft frame supporting the turbine section, the outlet guide vane assembly being connected to the turbine aft frame.

[0125] 5. A gas turbine engine according to any of the preceding clauses, wherein the turbine aft frame comprises a plurality of outlet guide vanes located in the exhaust gas flow path downstream of the turbine section, the plurality of outlet guide vanes being circumferentially spaced about 360 degrees from each other.

[0126] 6. A gas turbine engine according to any of the preceding clauses, the plurality of exit guide vanes of the turbine aft frame being low turning or non-turning, and the plurality of exit guide vanes of the exit guide vane assembly being turning.

[0127] 7. A gas turbine engine according to any of the preceding clauses, wherein the plurality of exit guide vanes of the turbine aft frame are turning and the plurality of exit guide vanes of the exit guide vane assembly are low turning or non-turning.

[0128] 8. A gas turbine engine according to any of the preceding clauses, further comprising an electric machine coupled to the rotating member and located at least partially inwardly of the core gas flow path in a radial direction.

[0129] 9. The gas turbine engine according to any of the preceding clauses, further comprising a heat transfer bus, the heat transfer bus comprising a heat transfer fluid, the heat transfer bus providing the heat transfer fluid to the cold fluid channel and the heating fluid channel.

[0130] 10. A gas turbine engine according to any of the preceding clauses, wherein a heat transfer bus extends from the cold fluid passage and the heating fluid passage to the electric machine to carry heat away from the electric machine during operation.

[0131] 11. The gas turbine engine according to any of the preceding clauses, wherein the cold fluid channel and the heating fluid channel are connected to a fuel delivery system, wherein fuel is directed through the cold fluid channel and the heating fluid channel.

[0132] 12. The gas turbine engine according to any of the preceding clauses, wherein the outlet guide vane assembly comprises a plurality of vane modules assembled together, each vane module comprising at least one outlet guide vane of the plurality of outlet guide vanes of the outlet guide vane assembly.

[0133] 13. A gas turbine engine according to any of the preceding clauses, wherein a plurality of outlet guide vanes of the outlet guide vane assembly have different lengths.

[0134] 14. A gas turbine engine according to any of the preceding clauses, wherein a plurality of outlet guide vanes of the outlet guide vane assembly have substantially the same length.

[0135] 15. The gas turbine engine according to any of the preceding clauses, at least one outlet guide vane of the plurality of outlet guide vanes comprising a surface enhancement feature which increases the surface area of ​​a side surface of the outlet guide vane.

[0136] 16. A gas turbine engine according to any of the preceding clauses, wherein the surface enhancement features protrude outwardly from the side surface.

[0137] 17. A gas turbine engine according to any of the preceding clauses, wherein the surface enhancement features are recesses in the side surface.

[0138] 18. A gas turbine engine according to any of the preceding clauses, wherein one or both of the cold fluid passage and the heating fluid passage comprises surface enhancement features extending into one or both of the cold fluid passage and the heating fluid passage.

[0139] 19. The gas turbine engine according to any of the preceding clauses, wherein at least one of the plurality of outlet guide vanes comprises a surface enhancement feature located at a trailing edge of the at least one of the plurality of outlet guide vanes.

[0140] 20. A method, the method comprising: removably attaching an outlet guide vane assembly to a turbine aft frame of a gas turbine engine, the outlet guide vane assembly comprising: a plurality of outlet guide vanes, the plurality of outlet guide vanes being located in an exhaust gas flow path downstream of a turbine section, the plurality of outlet guide vanes being circumferentially spaced from one another over an angular range of approximately 360 degrees, and each of the plurality of outlet guide vanes defining a radial extent; wherein at least one of the plurality of outlet guide vanes comprises a cold fluid passage extending at least partially radially therethrough, a fluid coolant flowing through the cold fluid passage, and another of the plurality of guide vanes comprises a heating fluid passage extending at least partially radially therethrough, the fluid coolant flowing through the heating fluid passage and receiving heat from the exhaust gas flow of a core gas flow path; and conveying the fluid coolant through the cold fluid passage and then through the heating fluid passage, the fluid coolant receiving heat from the exhaust gas flow of the core gas flow path as the fluid coolant is directed through the heating fluid passage.

[0141] 21. The method according to any of the preceding clauses, further comprising a fuel delivery system that delivers fuel to the cold fluid passage and receives fuel from the heated fluid passage.

[0142] 22. The method according to any of the preceding clauses, further comprising a heat transfer bus that delivers heat transfer fluid to the cold fluid channels and receives heat transfer fluid from the hot fluid channels.

[0143] 23. According to a method according to any of the preceding clauses, the gas turbine engine further includes an electric motor, which is connected to the rotating component and is at least partially located inside the core airflow path of the gas turbine engine in a radial direction, and the method further includes delivering a heat transfer fluid to the electric motor, thereby transferring heat from the electric motor to the heat transfer fluid.

[0144] 24. The method according to any of the preceding clauses, further comprising assembling together a plurality of vane modules to form an outlet guide vane assembly, each vane module comprising at least one outlet guide vane of a plurality of outlet guide vanes of the outlet guide vane assembly.

[0145] 25. The method according to any of the preceding clauses, further comprising individually removing one or more vane modules of the plurality of vane modules from the outlet guide vane assembly while the remaining plurality of guide vane modules remain connected to the turbine aft frame.

[0146] 26. The method according to any of the preceding clauses, further comprising replacing one or more blade modules of the plurality of blade modules with one or more different blade modules.

[0147] 27. The method according to any of the preceding clauses, wherein at least one outlet guide vane of the plurality of outlet guide vanes comprises surface enhancement features which increase the surface area of ​​a side surface of the outlet guide vane.

[0148] 28. A method according to any of the preceding clauses, wherein the surface enhancement features protrude outwardly from the side surface.

[0149] 29. A method according to any of the preceding clauses, wherein the surface enhancement features are recesses in the side surface.

[0150] 30. A gas turbine engine, comprising: a fan, the fan being located at a front portion of the gas turbine engine; a compressor section and a turbine section, the compressor section and the turbine section being arranged in a series flow order, the compressor section and the turbine section together defining a core airflow path; a rotating component, the rotating component being capable of rotating together with at least a portion of the compressor section and at least a portion of the turbine section; an outlet guide vane assembly, the outlet guide vane assembly comprising a plurality of outlet guide vanes located in the exhaust airflow path downstream of the turbine section, the outlet guide vanes being circumferentially spaced apart from each other by approximately 360 degrees; wherein one or more outlet guide vanes comprise surface enhancement features, the surface enhancement features increasing the surface area of ​​the side surfaces of the outlet guide vanes.

[0151] 31. A gas turbine engine according to any of the preceding clauses, wherein the outlet guide vanes comprise cold fluid passages extending radially therethrough.

[0152] 32. The gas turbine engine according to any of the preceding clauses, wherein another guide vane of the plurality of guide vanes comprises a heating fluid passage extending radially therethrough, the heating fluid passage being in fluid communication with the cooling fluid passage.

[0153] 33. A gas turbine engine according to any of the preceding clauses, wherein one or both of the cold fluid passages and the heating fluid passages comprises surface enhancement features extending into one or both of the cold fluid passages and the heating fluid passages.

[0154] 34. A gas turbine engine according to any of the preceding clauses, wherein the surface enhancement features protrude outwardly from the side surface.

[0155] 35. A gas turbine engine according to any of the preceding clauses, wherein the surface enhancement features are recesses in the side surface.

[0156] 36. A gas turbine engine according to any of the preceding clauses, wherein the outlet guide vane comprises a plurality of surface enhancement features.

[0157] 37. A gas turbine engine according to any of the preceding clauses, wherein a plurality of surface enhancement features are arranged in an array, wherein adjacent surface enhancement features are spaced apart.

[0158] 30. A gas turbine engine, the gas turbine engine comprising: a compressor section and a turbine section, the compressor section and the turbine section are arranged in a series flow sequence, the compressor section and the turbine section together defining a core airflow path; a rotating component, the rotating component being capable of rotating together with at least a portion of the compressor section and at least a portion of the turbine section; a turbine aft frame, the turbine aft frame comprising a first outlet guide vane located in the exhaust gas flow path downstream of the turbine section, the first outlet guide vanes being circumferentially spaced from each other within an angular range of approximately 360 degrees, and each first outlet guide vane defining a radial extent; and an outlet guide vane assembly, the outlet guide vane assembly comprising a second outlet guide vane, the second outlet guide vane being located in the exhaust gas flow path adjacent to the first outlet guide vane, the second outlet guide vanes being circumferentially spaced from each other within an angular range of approximately 360 degrees, and each second outlet guide vane defining a radial extent; wherein one or both of the first outlet guide vane and the second outlet guide vane are turnable, thereby changing the flow direction of the exhaust gas flow from the exhaust gas flow path.

[0159] 31. A gas turbine engine according to any of the preceding clauses, the first outlet guide vanes being turning or non-turning, arranged at substantially the same angle as the exhaust gas flow, and the second outlet guide vanes being turning.

[0160] 32. A gas turbine engine according to any of the preceding clauses, the first outlet guide vanes being turning and the second outlet guide vanes being low turning or non-turning, arranged at substantially the same angle as the exhaust gas flow.

[0161] 33. The gas turbine engine according to any of the preceding clauses, wherein both the first outlet guide vanes and the second outlet guide vanes are turning.

[0162] It will be apparent to those skilled in the art that various modifications and variations may be made to the embodiments described herein without departing from the spirit and scope of the subject matter claimed for protection. Therefore, this specification is intended to cover modifications and variations of the various embodiments described herein, as long as these modifications and variations fall within the scope of the appended claims and their equivalents.

Claims

1. A gas turbine engine, characterized in that: The gas turbine engine comprises: a compressor section and a turbine section, the compressor section and the turbine section arranged in a series flow sequence, the compressor section and the turbine section together defining a core airflow path; a rotating component rotatable with at least a portion of the compressor section and at least a portion of the turbine section; a turbine aft frame including first outlet guide vanes located in the exhaust gas flow path downstream of the turbine section, the first outlet guide vanes being circumferentially spaced from one another over an angular range of approximately 360 degrees and each defining a radial extent; and an outlet guide vane assembly including second outlet guide vanes positioned adjacent the first outlet guide vane in the exhaust gas flow path, the second outlet guide vanes being circumferentially spaced from one another over an angular range of approximately 360 degrees and each second outlet guide vane defining a radial extent; One or both of the first outlet guide vane and the second outlet guide vane are turnable to change a flow direction of exhaust gas flow from the exhaust gas flow path.

2. The gas turbine engine according to claim 1, characterized in that Wherein the first outlet guide vane is low turning or non-turning, arranged at approximately the same angle as the exhaust gas flow, and the second outlet guide vane is turning.

3. The gas turbine engine according to claim 1, characterized in that Wherein the first outlet guide vane is turning and the second outlet guide vane is low turning or non-turning, arranged at approximately the same angle as the exhaust gas flow.

4. The gas turbine engine according to claim 1, characterized in that The first outlet guide vane and the second outlet guide vane are both turnable.

5. The gas turbine engine according to any one of claims 1 to 4, characterized in that: The turbine aft frame supports the turbine section, and the exit guide vane assembly is connected to the turbine aft frame.

6. The gas turbine engine according to any one of claims 1 to 5, characterized in that: wherein at least one of the second exit guide vanes includes a cold fluid passage extending at least partially radially therethrough, through which fluid coolant flows from a heat transfer bus connected to the liquid coolant source, and another of the second guide vanes includes a heating fluid passage extending at least partially radially therethrough, through which the fluid coolant flows and receives heat from the exhaust gas flow from the core airflow path and returns to the heat transfer bus.

7. The gas turbine engine according to claim 6, characterized in that Wherein said at least one of said second exit guide vanes includes a plurality of fluid passages extending at least partially radially therethrough.

8. The gas turbine engine according to any one of claims 1 to 7, characterized in that: wherein at least one of the first outlet guide vanes includes a cold fluid passage extending at least partially radially therethrough, through which fluid coolant flows from a heat transfer bus connected to the liquid coolant source, and another of the first guide vanes includes a heating fluid passage extending at least partially radially therethrough, through which the fluid coolant flows and receives heat from the exhaust gas flow from the core airflow path and returns to the heat transfer bus.

9. The gas turbine engine according to claim 8, characterized in that Wherein said at least one of said first exit guide vanes includes a plurality of fluid passages extending at least partially radially therethrough.

10. The gas turbine engine according to claim 8 or 9, characterized in that: Further included is a motor coupled to the rotating member and located at least partially inside the core airflow path in a radial direction.

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