Heat Exchanger and Flow Modulation System

Abstract

A propulsion system is provided that includes a first set of blades extending in a radial direction. The first set of blades is configured to rotate relative to a blade axis extending in the radial direction. A second set of blades extends in the radial direction. The second set of blades is positioned rearward in the axial direction of the first set of blades. The second set of blades forms an inlet opening near a leading edge of the second set of blades, and the second set of blades forms an outlet opening near a trailing edge of the second set of blades. The inlet opening and the outlet opening together allow fluid to flow through the second set of blades. A heat exchanger is positioned within the second set of blades. The inlet opening and the outlet opening allow fluid flow to be in fluid communication with the heat exchanger.

Description

Technical Field

[0001] The present subject matter generally relates to heat exchanger systems and systems for flow modulation thereof. The present subject matter particularly relates to heat exchangers and flow modulation systems for gas turbine engines and propulsion systems. Background Art

[0002] Propulsion systems and gas turbine engines face challenges in the thermal management of increasingly high thermal loads. The increasingly high thermal loads are due in part to the increasing energy demands of carriers attached to the propulsion systems and gas turbine engines. The higher energy demands are due in part to the increased electrification of carriers such as aircraft, or the increased power generation capabilities of the propulsion systems and gas turbine engines or the need for greater electrical loads.

[0003] Higher thermal loads may also result from improved engine designs and materials that allow the system to generate and withstand higher temperatures. Higher operating temperatures may require lubricants and fuels to receive larger amounts of heat and thermal energy.

[0004] Importantly, improved engine designs are not adversely offset by inefficient heat exchange systems. Conventional heat exchange systems can operate primarily as a function of engine speed. However, such heat exchange systems may be insufficient under low speed or part power conditions. In addition, such heat exchange systems may reduce engine efficiency under high power conditions or other conditions where less heat transfer performance may be required.

[0005] Conventional heat exchange systems can utilize gates, flaps, scoops, or discharge injectors. However, such systems may adversely increase engine weight, nullifying improved engine designs and materials that can reduce engine weight.

[0006] Accordingly, there is a need for improved heat exchanger systems that can meet the needs resulting from higher thermal loads. Further, there is a need for improved operation of heat exchange systems under part power conditions and high power conditions. Summary of the Invention

[0007] Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.

[0008] A propulsion system is provided in accordance with aspects of the present disclosure. The propulsion system includes a first set of blades that extend in a radial direction. The first set of blades is configured to rotate relative to a blade axis that extends in the radial direction. A second set of blades extends in the radial direction and is positioned rearward in the axial direction of the first set of blades. The second set of blades forms an inlet opening near a leading edge of the second set of blades, and the second set of blades forms an outlet opening near a trailing edge of the second set of blades. The inlet opening and the outlet opening together permit fluid flow through the second set of blades. A heat exchanger is positioned within the second set of blades. The inlet opening and the outlet opening permit fluid flow to be in fluid communication with the heat exchanger.

[0009] These and other features, aspects, and advantages of the present invention will become better understood with reference to the following description and 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. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] A complete and enabling disclosure of the present invention, including the best mode thereof, to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended drawings, in which:

[0011] Figure 1 is a perspective view of an exemplary vehicle including a propulsion system having a heat exchanger system in accordance with aspects of the present disclosure;

[0012] Figure 2 is a schematic cross-sectional view of an exemplary embodiment of a propulsion system having a heat exchanger system in accordance with aspects of the present disclosure;

[0013] Figure 3 is a schematic cross-sectional view of an exemplary embodiment of a propulsion system having a heat exchanger system in accordance with aspects of the present disclosure;

[0014] Figure 4 is a perspective view of an exemplary embodiment of a heat exchanger system in a closed position in accordance with aspects of the present disclosure;

[0015] Figure 5 is of a heat exchanger system in an open position in accordance with aspects of the present disclosure Figure 4 is a perspective view of an exemplary embodiment of the heat exchanger system; and

[0016] Figure 6 is a perspective view of an exemplary embodiment of a heat exchanger system in a closed position in accordance with aspects of the present disclosure;

[0017] Figure 7 is of a heat exchanger system in an open position in accordance with aspects of the present disclosure Figure 6 is a perspective view of an exemplary embodiment of the heat exchanger system; and

[0018] Figure 8A circumferential view of an embodiment of a heat exchanger according to an aspect of the present disclosure.

[0019] Reference numerals reused in this specification and the drawings are intended to represent the same or similar features or elements of the present invention. Detailed Description

[0020] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. Each example is provided by way of explanation of the invention, and not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For example, features shown or described as part of one embodiment can be used with another embodiment to yield yet another embodiment. Accordingly, the present invention is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents.

[0021] As used herein, the terms "first", "second", and "third" may be used interchangeably to distinguish one component from another and are not intended to denote the position or importance of the respective components.

[0022] The terms "upstream" and "downstream" refer to the relative direction with respect to the flow of fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction towards which the fluid flows.

[0023] Embodiments of a heat exchanger and a flow modulation system are provided that can meet the needs associated with higher heat loads and improved operation at part power and full power conditions. Embodiments of an engine including a heat exchanger and a flow modulation system include a first vane at least partially positioned in front of a second vane, wherein the heat exchanger is positioned within the second vane. The first vane is configurable to adjust a fluid flow through an inlet opening at the second vane into thermal communication with the heat exchanger. The configurable first vane adjusts, for example, based on the operating conditions or heat load of the engine, the amount of thermal communication of the fluid flow with the heat exchanger. The first vane may be attached to a variable guide vane system rather than a gate, flap, scoop, or discharge injector to desirably vary the amount of fluid and heat transfer with the heat exchanger.

[0024] Embodiments provided herein can avoid engine weight increase or complex systems, for example, by utilizing a variable vane actuator system such as for a compressor section. The fluid flow through the second vane allows adjustment of the heat exchanger frontal area via tangential flow without significantly modifying the overall flow pattern in the flow path around the vane. A heat exchanger nacelle or pylon within the vane can allow diffusion of the inlet momentum to minimize the cold side pressure drop at the heat exchanger. Positioning the outlet opening at the second vane allows the cooling fluid to flow through the second vane and discharge into a low static pressure region to minimize the undesirable aerodynamic effects on the flow external to the vane passing there.

[0025] Embodiments of an engine, a heat exchanger, and a flow modulation system can allow adaptive cycle operation and performance from a dual - flow engine (e.g., a fan flow and a core flow) using variable first vanes to direct flow towards a heat exchanger at a second vane during a thermal management mode. During a propulsion mode, the first vanes can be linked to allow flow to bypass the heat exchanger substantially.

[0026] Now referring to the drawings, in Figure 1 FIG. 8, an exemplary embodiment of a vehicle 100 including a propulsion system 10 and a heat exchanger system 200 according to aspects of the present disclosure is provided. In an embodiment, the vehicle 100 is an aircraft including an aircraft structure or airframe 105. The airframe 105 includes a fuselage 110, and wings 120 and a tail 130 are attached to the fuselage 110. A propulsion system 10 according to aspects of the present disclosure is attached to one or more portions of the airframe. In various embodiments, the heat exchanger system 200 is a system configured to connect vane structures to desirably supply a cooling fluid (such as air or oxidizer) to a heat exchanger positioned within a downstream vane. The cooling fluid removes heat or thermal energy from one or more fluids (e.g., but not limited to liquid and / or gaseous fuels, lubricants, hydraulic fluids, pneumatic fluids, heat transfer fluids, or cooling fluids for electric motors, electronic devices, computing systems, environmental control systems, gear assemblies, or other systems or structures).

[0027] In some cases, the propulsion system 10 is attached to the rear of the fuselage 110. In some other cases, the propulsion system 10 is attached below, above, or through a portion of the wing 120 and / or the tail 130. In various embodiments, the propulsion system 10 is attached to the airframe 105 via pylons or other mounting structures. In still other embodiments, the propulsion system 10 is housed within the airframe, as can be exemplified in certain supersonic military or commercial aircraft.

[0028] Now referring to the drawings, Figure 2is a schematic partial cross-sectional side view of an exemplary gas turbine engine 10 (referred to herein as "engine 10") that can incorporate various embodiments of the present invention. Engine 10 can be particularly configured as a gas turbine engine for an aircraft. Although further described herein as a turbofan engine, engine 10 can define a turboprop, turbopropeller, or turbojet gas turbine engine, including marine and industrial engines as well as auxiliary power units. As Figure 1 shown, engine 10 has a longitudinal or axial center axis 12 extending therethrough for reference. The axial direction A extends co-directionally with the axial centerline axis 12 for reference. Engine 10 further defines an upstream end 99 and a downstream end 98 for reference. Generally, engine 10 can include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0029] The core engine 16 generally can include a substantially tubular outer casing 18 that defines an annular inlet 20. The outer casing 18 surrounds or at least partially forms in serial flow relationship: a compressor section having a booster or low pressure (LP) compressor 22, a high pressure (HP) compressor 24, a heat addition system 26; an expansion section or turbine section including a high pressure (HP) turbine 28, a low pressure (LP) turbine 30; and an exhaust nozzle section 32. A high pressure (HP) rotor shaft 34 drivingly connects the HP turbine 28 to the HP compressor 24. A low pressure (LP) rotor shaft 36 drivingly connects the LP turbine 30 to the LP compressor 22. The LP rotor shaft 36 can also be connected to a fan shaft 38 of the fan assembly 14. In a particular embodiment, as Figure 1 shown, for example in an indirect drive or geared configuration, the LP rotor shaft 36 can be connected to the fan shaft 38 via a reduction gear 40.

[0030] As Figure 2 shown, the fan assembly 14 includes a plurality of fan blades 42 that are coupled to the fan shaft 38 and extend radially outwardly from the fan shaft 38. An annular fan housing or nacelle 44 can circumferentially surround at least a portion of the fan assembly 14 and / or the core engine 16. Those of ordinary skill in the art will understand that the nacelle 44 can be configured to be supported relative to the core engine 16 by a plurality of circumferentially spaced outlet guide vanes or struts 46. Additionally, at least a portion of the nacelle 44 can extend over an outer portion of the core engine 16 so as to define a fan flow passage 48 therebetween. However, it should be understood that various configurations of engine 10 can omit the nacelle 44, or omit the nacelle 44 from extending around the fan blades 42 so as to provide Figure 3 shown an open rotor or propfan configuration of engine 10.

[0031] It should be understood that the combination of shafts 34, 36, compressors 22, 24 and turbines 28, 30 defines the rotor assembly 90 of the engine 10. For example, the HP shaft 34, HP compressor 24 and HP turbine 28 may define the high speed or HP rotor assembly of the engine 10. Similarly, the combination of the LP shaft 36, LP compressor 22 and LP turbine 30 may define the low speed or LP rotor assembly of the engine 10. Various embodiments of the engine 10 may further include a fan shaft 38 and fan blades 42 as part of the LP rotor assembly. In other embodiments, the engine 10 may further define a fan rotor assembly that is at least partially mechanically separated from the LP spool via the fan shaft 38 and reduction gear 40. Further embodiments may further define one or more intermediate rotor assemblies, which are defined by a medium pressure compressor, a medium pressure shaft and a medium pressure turbine (with respect to the serial aerodynamic flow arrangement) disposed between the LP rotor assembly and the HP rotor assembly.

[0032] During operation of the engine 10, an air flow, schematically shown by arrow 74, enters the inlet 76 of the engine 10 defined by the fan casing or nacelle 44. A portion of the air, schematically shown by arrow 80, enters the core engine 16 through the core inlet 20 defined at least in part by the outer casing 18. The air flow is provided in serial flow through the compressor, heat addition system and expansion section via the core flow path 70. As the air flow 80 passes through successive stages of the compressors 22, 24, the air flow 80 is progressively compressed, as schematically shown by arrow 82. The compressed air 82 enters the heat addition system 26 and is mixed with liquid and / or gaseous fuel and ignited to produce combustion gases 86. It should be understood that the heat addition system 26 may form any suitable system for producing combustion gases, including but not limited to deflagration or detonation combustion systems, or combinations thereof. The heat addition system 26 may include annular, can, can-annular, trapped vortex, involute or vortex, rich burn, lean burn, rotating detonation or pulse detonation configurations, or combinations thereof.

[0033] The combustion gases 86 release energy before being discharged from the jet exhaust nozzle section 32 to drive the rotation of the HP rotor assembly and the LP rotor assembly. The energy release from the combustion gases 86 further drives the rotation of the fan assembly 14 (including the fan blades 42). A portion of the air 74 bypasses the core engine 16 and flows through the fan flow passage 48, as schematically shown by arrow 78.

[0034] Now referring to Figure 3 , another exemplary embodiment of the engine 10 is provided. Figure 3 The construction of the embodiment provided in Figure 2 is substantially similar to that described with respect to Figure 3In [the figure], the engine 10 is configured as a three - flow engine including a fan flow passage 48, a core flow path 70, and a core bypass or third flow 71. The core flow path 70 extends at least through a high - pressure compressor 24, a heat addition system 26, and a high - pressure turbine 32. The core bypass or third - flow path 71 extends from downstream of a low - pressure or medium - pressure compressor 22 and bypasses the core flow path 70 at the HP compressor 24 and the heat addition system 26. In some embodiments, the third - flow path 71 extends into the fluid - communication downstream of the fan blades 46 at the fan flow passage 48.

[0035] It should be understood that Figure 2 a two - flow engine having a fan flow passage 48 and a core flow passage 70 is depicted and described. Figure 2 The embodiment depicted in [the figure] has a nacelle 44 around the fan blades 42 to provide noise attenuation, blade - shedding protection, and other benefits known for nacelles. Figure 3 A three - flow engine having a fan flow passage 48, a core flow passage 70, and a third - flow path 71 is depicted and described. Figure 3 The embodiment depicted in [the figure] is configured with non - ducted fan blades 42 that are not through a nacelle to form an open - rotor engine. In various embodiments, the non - ducted open - rotor engine can form, for example, a two - flow engine as described with respect to Figure 2 Alternatively, a ducted engine including a nacelle 44 can form, for example, a three - flow engine as described with respect to Figure 3 Further embodiments can position the heat exchangers and flow modulation systems further described herein in engines that form a ramjet, a scramjet, a turboprop gas turbine engine, a turboshaft gas turbine engine, or a turbojet engine.

[0036] Now referring to Figures 4 - 7 , a perspective view of an embodiment of a heat exchanger system 200 is provided. An embodiment of the system 200 includes a first vane 210 extending in a radial direction R. The first vane 210 is operatively connected to an actuation system 250 configured to rotate the first vane 210 relative to a vane axis 216 extending in the radial direction R. A second vane 220 extends in the radial direction R. The second vane 220 is positioned rearward in the axial direction A of the first vane 210.

[0037] The vanes generally form airfoils, each airfoil having a leading edge, a trailing edge, a pressure side, and a suction side. The second vane 220 forms an inlet opening 226 near the leading edge 222 of the second vane. The second vane 220 forms an outlet opening 228 near the trailing edge 224 of the second vane. The inlet opening 226 and the outlet opening 228 together allow fluid (e.g., generally with respect to Figures 2 - 3The air or oxidant) flow described for the engine 10 in

[0038] The heat exchanger 230 is positioned within the second row of blades 220. The inlet opening 226 and the outlet opening 228 allow fluid flow to be in fluid communication with the heat exchanger 230. In various embodiments, the heat exchanger 230 includes a supply conduit 234 and a return conduit 232. Each conduit includes a wall that allows a heat load to flow into the heat exchanger 230. The heat exchanger 230 fluidly separates the heat load flow from the fluid flow that is allowed to flow through the second row of blades 220. The supply conduit 234 is configured to supply the heat load flow into the heat exchanger 230. The return conduit 232 is configured to remove the heat load flow from the heat exchanger 230. In a particular embodiment, the supply conduit 234 is positioned adjacent to the trailing edge or the rear edge 224 of the second row of blades 220, while the return conduit 232 is positioned adjacent to the leading edge or the front edge 222 of the second row of blades 220. Thus, the heat load flowing through the heat exchanger 230 is provided in a countercurrent to the fluid flow flowing through the second row of blades 220 in order to improve heat transfer.

[0039] Return reference Figures 2 - 3 And in combination Figures 4 - 7 , in certain embodiments, the engine 10 includes an outer radial wall 205 extending along the axial direction A and an inner radial wall 206 extending generally co - axially with the outer radial wall 205. The outer radial wall 205 and the inner radial wall 206 together form a flow path extending generally along the axial direction A. In various embodiments, the flow path is the fan flow passage 48, the core flow path 70, or the tertiary flow path 71. The first row of blades 210 and the second row of blades 220 extend through the flow path along the radial direction R, respectively.

[0040] In one embodiment, the outer radial wall 205 and the inner radial wall 206 form an inlet section that is configured to receive a fluid flow into the flow path, as depicted and described at the inlet 20 at the compressor section, for example. In such an embodiment, the first row of blades 210 and the second row of blades 220 extend through the core flow path 70. In a particular embodiment, the first row of blades 210 and the second row of blades 220 extend through the core flow path at the compressor section (e.g., at the mid - pressure or low - pressure compressor 22). In yet another embodiment, the first row of blades 210 and the second row of blades 220 may extend through the core flow path 70 between the LP compressor 22 and the HP compressor 24.

[0041] In another embodiment, the outer radial wall 205 is formed at the nacelle 44, as Figure 2As shown. The first blade 210 and the second blade 220 are positioned rearwardly in the axial direction A of the plurality of fan blades 42. The inner radial wall 206 is formed at the outer casing 16 of the core engine 18. The flow path includes at least a portion of the fan flow passage 48. The first blade 210 and the second blade 220 extend through the fan flow passage 48.

[0042] In yet another embodiment, Figure 3 As shown, first vane 210 and second vane 220 extend through the flow path formed by third flow channel 71 .

[0043] In yet another embodiment, the first blade 210 and the second blade 220 extend from the casing 16 of the core engine 18 into the fan flow path 48. Figure 3 In the particular embodiment shown, first blade 210 and second blade 220 extend from outer casing 16 into fan flow passage 48 of the non-ducted rotary engine.

[0044] Various embodiments of the system 200 may include a plurality of first vanes 210 positioned in a circumferential arrangement. The system 200 may further include a plurality of second vanes 220 positioned in a circumferential arrangement. In a particular embodiment, the inlet opening 226 is positioned through a pressure side 227 of the second vane 220. In yet another particular embodiment, the outlet opening 228 is positioned through a suction side 229 of the second vane 220.

[0045] Brief reference Figure 8 , providing a view from upstream Figures 4 - 7 Circumferential view of an exemplary embodiment of system 200. Certain embodiments of system 200 position first vane 210 offset from second vane 220 in circumferential direction C. Thus, first vane 210 and second vane 220 are positioned at different circumferential positions from each other.

[0046] Return to reference Figures 4 - 7 , first vane 210 includes a first vane trailing edge 214 and a first vane leading edge 212. In certain embodiments, first vane trailing edge 214 is coaxial with at least a portion of second vane leading edge 222. In a particular embodiment, first vane trailing edge 214 is coaxial with inlet opening 226 at second vane 210.

[0047] During operation of engine 10 as described above, first vane 210 is configured to actively adjust, modulate, change, or otherwise direct fluid flow into inlet opening 226 (e.g., Figure 5 and Figure 7 ) or away from the inlet opening 226 (as shown Figure 4 and Figure 6as shown). A fluid (such as air or an oxidant) flow is typically provided through flow path 75, for example as described above with respect to fan flow path 48, core flow path 70, or third flow path 71. When the first vane 210 is modulated to the open position, as Figure 4 and Figure 6 shown, the fluid flow schematically depicted by arrow 77a passes through the first vane 210 and the second vane 220 and substantially does not enter the second vane 220 through the inlet opening 226. When the first vane 210 is modulated to the closed position, as Figure 5 and Figure 7 shown, a portion of the fluid flow schematically depicted by arrow 77b is directed into the second vane 220 to be in thermal communication with the heat exchanger 230.

[0048] In various embodiments, the heat load flow passing through the heat exchanger 230 is one or more of a lubricant flow, a fuel flow, a hydraulic fluid flow, or a heat transfer fluid flow, or a combination thereof. During operation of the engine 10, the first vane 210 is actuated along its vane axis 216 to adjust the mass flow or volume flow of the cooling fluid (such as air or an oxidant, typically depicted by arrow 77b) that is directed to be in thermal communication with the heat exchanger 230 within the second vane 220. Heat or thermal energy transfer from the heat load at the heat exchanger 230 is increased by closing the first vane 210 to direct a greater amount of cooling fluid 77b into the second vane 220. The cooling fluid flow is allowed to exit the second vane 220 through the outlet opening 228, for example as depicted by arrow 77c in Figure 5 and Figure 7 .

[0049] Modulation of the first vane 210 allows for changing the aerodynamics at the duct forming the flow path 75, for example to allow the heat exchanger 230 to capture the total pressure and discharge the fluid flow 77c into a relatively low static pressure region at the suction side 228 of the second vane 220. The second vane 220 may include features that trap the fluid flow 77b in static pressure. Such features may include the inlet opening 226, the outlet opening 228, the specific position of the first vane 210 relative to the adjacent second vane 220, or surface roughness, bumps, ridges, protrusions, perturbations, or pits at or within the second vane 220.

[0050] The operating method includes one or more steps as described above. Additional steps can include modulating the first row of vanes 210 to an increased heat attenuation mode by closing the first row of vanes 210 and directing the fluid flow to the inlet opening 226 at the second row of vanes 220. The steps can further include modulating the first row of vanes 210 to a propulsion mode by opening the first row of vanes 210 and directing the fluid flow away from the inlet opening 226. Thus, the heat attenuation mode directs increased flow into thermal communication with the heat exchanger 230, while the propulsion mode directs less flow into thermal communication with the heat exchanger 230. Certain embodiments can correspond the propulsion mode to a high power output of the engine 10 (e.g., takeoff or climb power during a landing-takeoff cycle). Certain embodiments can correspond the heat attenuation mode to a low power or part power output (e.g., idle or cruise condition during a landing-takeoff cycle).

[0051] Embodiments of the heat exchanger 200 provided herein can improve overall engine efficiency and thermal management performance without adversely affecting engine weight or aerodynamics. Embodiments provided herein allow adjustment of the effective frontal area of the heat exchanger 230, for example, by allowing tangential flow through the second row of vanes 220, to indicate heat transfer at the heat exchanger 230, without significantly altering the overall flow pattern of the fluid flow directed downstream.

[0052] Return reference Figures 2 - 3 The system can further include a computing system 210 configured to obtain, measure, or otherwise send and receive signals to modulate, open, close, adjust, rotate, or otherwise selectively actuate the first row of vanes 210 to allow or prohibit air (or generally an oxidizer) flow through the second row of vanes 220 as described herein, for example.

[0053] The computing system 210 can correspond to any suitable processor-based device, including one or more computing devices as described above. In certain embodiments, the computing system 210 is a full authority digital engine controller (FADEC) for a gas turbine engine, or other computing module or controller configured to execute instructions for operating a gas turbine engine. For example, Figure 2 and Figure 3 An embodiment showing suitable components that can be included within the computing system 210 is shown. The computing system 210 can include a processor 212 and associated memory 214 configured to execute various computer-implemented functions.

[0054] As shown, computing system 210 may include control logic 216 stored in memory 214. Control logic 216 may include instructions that, when executed by one or more processors 212, cause the one or more processors 212 to operate. Additionally, computing system 210 may also include a communication interface module 230. In some embodiments, communication interface module 230 may include associated electronic circuitry for sending and receiving data. Thus, the communication interface module 230 of computing system 210 can be used to send data to and / or receive data from engine 10 and heat exchanger system 200. Additionally, communication interface module 230 can also be used to communicate with any other suitable components of heat exchanger system 200 (such as first stage vane 210 or actuation system 250).

[0055] It should be understood that communication interface module 230 can be any combination of suitable wired and / or wireless communication interfaces and can thus be communicatively coupled to one or more components of the compressor section or engine via a wired and / or wireless connection.

[0056] Embodiments of actuation system 250 for first stage vane 210 may include a variable guide vane (VGV) system that includes a synchronizing ring, U-bolt, actuator, and linkage that are commonly available for a compressor section. Other embodiments of actuation system 250 for first stage vane 210 may include a pitch adjustment mechanism that includes a motor, ring, U-bolt, actuator, or linkage that are commonly available for a fan or propeller blade or vane.

[0057] 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 incorporated method. The patent scope of the invention is defined by the claims and may include other examples that occur to those skilled in the art. If these other examples include structural elements that are not different in literal language from the claims, or if they include equivalent structural elements that are not substantially different in literal language from the claims, then these other examples are intended to fall within the scope of the claims.

[0058] Further aspects of the invention are provided by the subject matter of the following clauses:

[0059] 1. A propulsion system that defines an axial centerline axis, an axial direction coaxial with the centerline axis, a radial direction extending from the centerline axis, and a circumferential direction extending relative to the centerline axis, the system comprising: a first vane that extends along the radial direction, and wherein the first vane is configured to rotate relative to a vane axis extending along the radial direction; a second vane that extends along the radial direction, and wherein the second vane is positioned rearward in the axial direction of the first vane, wherein the second vane forms an inlet opening near the leading edge of the second vane, and wherein the second vane forms an outlet opening near the trailing edge of the second vane, wherein the inlet opening and the outlet opening together allow fluid to flow through the second vane; and a heat exchanger positioned within the second vane, wherein the inlet opening and the outlet opening allow the fluid flow to be in fluid communication with the heat exchanger.

[0060] 2. The system according to any one or more of the items herein, wherein the first vane is configured to direct the fluid flow into the inlet opening of the second vane by rotating the first vane along the vane axis to a closed position.

[0061] 3. The system according to any one or more of the items herein, wherein the first vane is configured to direct the fluid flow away from the inlet opening of the second vane by rotating the first vane along the vane axis to an open position.

[0062] 4. The system according to any one or more of the items herein, the system comprising a plurality of the first vanes positioned in a circumferential arrangement.

[0063] 5. The system according to any one or more of the items herein, the system comprising a plurality of the second vanes positioned in a circumferential arrangement.

[0064] 6. The system according to any one or more of the items herein, wherein the inlet opening is positioned to pass through the pressure side of the second vane.

[0065] 7. The system according to any one or more of the items herein, wherein the outlet opening is positioned to pass through the suction side of the second vane.

[0066] 8. The system according to any one or more of the items herein, wherein the first vane is offset from the second vane in the circumferential direction.

[0067] 9. The system according to any one or more of the items herein, wherein the trailing edge of the first vane is at least coaxial with the leading edge of the second vane.

[0068] 10. The system according to any one or more of the items herein, wherein the trailing edge of the first row of blades is coaxial with the inlet opening at the second row of blades.

[0069] 11. The system according to any one or more of the items herein, the system comprising: an outer radial wall extending along the axial direction; and an inner radial wall extending in the same direction as the outer radial wall, wherein the outer radial wall and the inner radial wall together form a flow path extending substantially along the axial direction, and wherein the first row of blades and the second row of blades each extend along the radial direction through the flow path.

[0070] 12. The system according to any one or more of the items herein, wherein the outer radial wall and the inner radial wall form an inlet section configured to receive the fluid flow into the flow path.

[0071] 13. The system according to any one or more of the items herein, the system comprising: a fan section including a plurality of fan blades, wherein a nacelle surrounds the plurality of fan blades, and wherein the outer radial wall is formed at the nacelle, and wherein the first row of blades and the second row of blades are positioned rearward along the axial direction of the plurality of fan blades; and a core engine, wherein a casing surrounds the core engine, and wherein the inner radial wall is formed at the casing.

[0072] 14. The system according to any one or more of the items herein, the system comprising: a compressor section including a plurality of compressor blades extending along the radial direction through the flow path, wherein the plurality of compressor blades are surrounded by the outer radial wall, and wherein the first row of blades and the second row of blades are positioned at the compressor section.

[0073] 15. The system according to any one or more of the items herein, the system comprising: a fan section including a plurality of fan blades, wherein the plurality of fan blades extend along the radial direction through a fan flow channel; and a compressor section including a plurality of compressor blades extending along the radial direction through the flow path, wherein the flow path separates into a core flow path in fluid communication with a heat addition system, and wherein the flow path separates into a third flow path in fluid communication with the fan flow channel downstream of the plurality of fan blades.

[0074] 16. The system according to any one or more of the items herein, the system comprising: a fan section including a plurality of fan blades, wherein the plurality of fan blades extend in the radial direction through a fan flow passage; and a core engine, wherein a housing surrounds the core engine, and wherein the first vane and the second vane extend from the housing behind the plurality of fan blades.

[0075] 17. The system according to any one or more of the items herein, wherein the fan section is ducted-free and wherein the plurality of fan blades form an open rotor configuration.

[0076] 18. The system according to any one or more of the items herein, the system comprising: a supply conduit configured to allow a heat load flow to enter the heat exchanger; and a return conduit configured to remove the heat load flow from the heat exchanger, wherein the fluid flow in fluid communication with the heat exchanger is an oxidizer flow and wherein the heat exchanger allows the oxidizer flow to be in thermal communication with the heat load flow.

[0077] 19. The system according to any one or more of the items herein, wherein the heat load flow is one or more of a lubricant flow, a fuel flow, a hydraulic fluid flow, or a heat transfer fluid flow.

[0078] 20. The system according to any one or more of the items herein, the system comprising: an actuation system configured to rotate the first vane along the vane axis.

Claims

1. A propulsion system that defines an axial centerline axis, an axial direction coaxial with the centerline axis, a radial direction extending from the centerline axis, and a circumferential direction extending relative to the centerline axis, wherein, the system includes: a first vane that extends along the radial direction, and wherein the first vane is configured to rotate relative to a vane axis extending along the radial direction; a second vane that extends along the radial direction, and wherein the second vane is positioned rearward in the axial direction of the first vane, wherein the second vane forms an inlet opening near the leading edge of the second vane, and wherein the second vane forms an outlet opening near the trailing edge of the second vane, wherein the inlet opening and the outlet opening together allow fluid to flow through the second vane; and a heat exchanger that is positioned within the second vane, wherein the inlet opening and the outlet opening allow the fluid flow to be in fluid communication with the heat exchanger.

2. The system according to claim 1, wherein, the first vane is configured to direct the fluid flow into the inlet opening of the second vane by rotating the first vane along the vane axis to a closed position.

3. The system according to claim 2, wherein, the first vane is configured to direct the fluid flow away from the inlet opening of the second vane by rotating the first vane along the vane axis to an open position.

4. The system according to claim 1, wherein, the system includes a plurality of the first vanes positioned in a circumferential arrangement.

5. The system according to claim 4, wherein, the system includes a plurality of the second vanes positioned in a circumferential arrangement.

6. The system according to claim 1, wherein, the inlet opening is positioned to pass through the pressure side of the second vane.

7. The system according to claim 6, wherein, the outlet opening is positioned to pass through the suction side of the second vane.

8. The system according to claim 1, wherein, the first vane is offset from the second vane in the circumferential direction.

9. The system according to claim 8, wherein, the trailing edge of the first vane is at least coaxial with the leading edge of the second vane.

10. The system according to claim 9, wherein, the trailing edge of the first vane is coaxial with the inlet opening at the second vane.

11. The system according to claim 1, wherein, the system includes: an outer radial wall that extends along the axial direction; and an inner radial wall that extends in the same direction as the outer radial wall, wherein the outer radial wall and the inner radial wall together form a flow path that extends substantially along the axial direction, and wherein the first vane and the second vane each extend along the radial direction through the flow path.

12. The system according to claim 11, wherein, Wherein the outer radial wall and the inner radial wall form an inlet section configured to receive the fluid flow into the flow path.

13. The system according to claim 11, wherein, the system comprises: a fan section including a plurality of fan blades, wherein a nacelle surrounds the plurality of fan blades, and wherein the outer radial wall is formed at the nacelle, and wherein the first vane and the second vane are positioned rearward along the axial direction of the plurality of fan blades; and a core engine, wherein a casing surrounds the core engine, and wherein the inner radial wall is formed at the casing.

14. The system according to claim 11, wherein, the system comprises: a compressor section including a plurality of compressor blades extending through the flow path in the radial direction, wherein the plurality of compressor blades are surrounded by the outer radial wall, and wherein the first vane and the second vane are positioned at the compressor section.

15. The system according to claim 11, wherein, the system comprises: a fan section including a plurality of fan blades, wherein the plurality of fan blades extend through a fan flow channel in the radial direction; and a compressor section including a plurality of compressor blades extending through the flow path in the radial direction, wherein the flow path separates into a core flow path in fluid communication with a heat addition system, and wherein the flow path separates into a third flow path in fluid communication with the fan flow channel downstream of the plurality of fan blades.

16. The system according to claim 1, wherein, the system comprises: a fan section including a plurality of fan blades, wherein the plurality of fan blades extend through a fan flow channel in the radial direction; and a core engine, wherein a casing surrounds the core engine, and wherein the first vane and the second vane extend from the casing behind the plurality of fan blades.

17. The system according to claim 16, wherein, the fan section is ducted-free, and wherein the plurality of fan blades form an open rotor configuration.

18. The system according to claim 1, wherein, the system comprises: a supply conduit configured to allow a heat load flow to enter the heat exchanger; and a return conduit configured to remove the heat load flow from the heat exchanger, wherein the fluid flow in fluid communication with the heat exchanger is an oxidant flow, and wherein the heat exchanger allows the oxidant flow to be in thermal communication with the heat load flow.

19. The system according to claim 18, wherein, the heat load flow is one or more of a lubricant flow, a fuel flow, a hydraulic fluid flow, or a heat transfer fluid flow.

20. The system according to claim 1, wherein, the system comprises: an actuation system configured to rotate the first vane along the vane axis.

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