Heat exchanger for gas turbine engine

Abstract

A heat exchanger for a gas turbine engine includes a housing extending between a first end and a second end opposite the first end. The housing defines a first fluid chamber, a first fluid inlet adjacent the first end, and a first fluid outlet adjacent the second end. The housing also defines a first plurality of second fluid inlet openings between the first end and the second end and a second fluid outlet adjacent the second end. The heat exchanger includes a manifold disposed within the housing. The manifold defines a second fluid chamber and a second plurality of second fluid inlet openings. The heat exchanger defines a first fluid path and a second fluid path.

Description

Technical Field

[0001] The present disclosure relates to a heat exchanger for a gas turbine engine. Background Art

[0002] A gas turbine engine generally comprises a turbine and a rotor assembly. A gas turbine engine (e.g., a turbofan engine) can be used for aircraft propulsion. In the case of a turbofan engine, the rotor assembly can be configured as a fan assembly.

[0003] Gas turbine engines typically include one or more heat exchangers to manage the thermal energy of various fluids flowing through various components of the gas turbine engine. However, it would be desirable to have a heat exchanger that can reduce the weight and complexity of a gas turbine engine. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0005] Figure 1 is a perspective view of an exemplary aircraft according to an exemplary embodiment of the present disclosure.

[0006] Figure 2 is a cross-sectional view of a gas turbine engine according to an exemplary aspect of the present disclosure.

[0007] Figure 3 is a schematic diagram of a lubrication system according to an exemplary aspect of the present disclosure.

[0008] Figure 4A is a perspective view of a heat exchanger according to an exemplary aspect of the present disclosure.

[0009] Figure 4B According to an exemplary aspect of the present disclosure Figure 4A Cross-sectional view of a heat exchanger.

[0010] Figure 4C According to an exemplary aspect of the present disclosure Figure 4A Partial top view of a heat exchanger.

[0011] Figure 4D According to an exemplary aspect of the present disclosure Figure 4A Internal view of the heat exchanger.

[0012] Figure 4E According to an exemplary aspect of the present disclosure Figure 4A Internal view of the heat exchanger.

[0013] Figure 5 is a schematic diagram of a combustion section of a gas turbine engine according to an exemplary aspect of the present disclosure.

[0014] Figure 6 is a schematic diagram of a thermal management system according to an exemplary aspect of the present disclosure.

[0015] Figure 7A is a perspective cross-sectional view of a heat exchanger according to an exemplary aspect of the present disclosure.

[0016] Figure 7B According to an exemplary aspect of the present disclosure Figure 7A Detailed cross-sectional view of a heat exchanger.

[0017] Figure 8A is an interior view of a heat exchanger according to an exemplary aspect of the present disclosure.

[0018] Figure 8B is an interior view of a heat exchanger according to an exemplary aspect of the present disclosure.

[0019] Figure 9 is a perspective cross-sectional view of a heat exchanger according to an exemplary aspect of the present disclosure.

[0020] Figure 10 is a perspective cross-sectional view of a heat exchanger according to an exemplary aspect of the present disclosure.

[0021] Figure 11A is a top view of a heat exchanger according to an exemplary aspect of the present disclosure.

[0022] Figure 11B According to an exemplary aspect of the present disclosure Figure 11A Bottom view of the heat exchanger. DETAILED DESCRIPTION

[0023] Reference will now be made in detail to the present embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. The same or similar designations in the drawings and the description have been used to refer to the same or similar parts of the present disclosure.

[0024] As used herein, the word "exemplary" means "serving as an example, instance, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Furthermore, unless expressly stated otherwise, all embodiments described herein should be considered exemplary.

[0025] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise.

[0026] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of each component.

[0027] In addition, the terms "upstream" and "downstream" refer to relative directions relative to the flow of fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid flows, while "downstream" refers to the direction toward which the fluid flows.

[0028] Furthermore, unless otherwise indicated, the terms "low," "high," or their corresponding comparatives (e.g., lower, higher, as applicable) refer to relative speeds, pressures, or temperatures within an engine or thermal management system. For example, a "low-pressure turbine" typically operates at a lower pressure than a "high-pressure turbine." Alternatively, unless otherwise indicated, the above terms may be understood to refer to their superlatives. For example, a "low-pressure turbine" may refer to the turbine with the lowest maximum pressure within a turbine section, while a "high-pressure turbine" may refer to the turbine with the highest maximum pressure within a turbine section.

[0029] Unless otherwise specified herein, the terms "coupled," "fixed," "attached," and the like refer to both direct coupling, fixing, or attachment as well as indirect coupling, fixing, or attachment through one or more intermediate components or features.

[0030] The present disclosure generally relates to heat exchangers for gas turbine engines. Conventional thermal management systems route hot engine fluid to an external heat exchanger for cooling. Routing this hot engine fluid requires additional piping and larger pump sizes to route the engine fluid, which increases the weight of the gas turbine engine. However, incorporating a heat exchanger directly into the fluid or fluid path can reduce the number of routing routes, piping, and pumps required to route the engine fluid through the heat exchanger for cooling.

[0031] Referring now to the accompanying drawings, Figure 1 is a perspective view of an exemplary aircraft 10 according to an exemplary embodiment of the present disclosure.

[0032] The aircraft 10 includes a fuselage 12, wings 14 attached to the fuselage 12, and an empennage 16. The aircraft 10 also includes a propulsion system 18 that generates propulsive thrust to propel the aircraft 10 during flight and taxiing operations. Although the propulsion system 18 is shown as being attached to the wings 14, in other exemplary embodiments, it may additionally or alternatively include one or more aspects coupled to other portions of the aircraft 10 (e.g., the empennage 16, the fuselage 12, or both). Figure 1 The configuration of aircraft 10 shown in FIG. 1 is intended only to place the present subject matter in an exemplary field of use. Thus, the present subject matter may be readily adapted for use in any type of aircraft.

[0033] The propulsion system 18 includes at least one engine. In the exemplary embodiment shown, the aircraft 10 includes a pair of gas turbine engines 20. Each gas turbine engine 20 is mounted to the aircraft 10 in an underwing configuration. Each gas turbine engine 20 is capable of selectively generating propulsive thrust for the aircraft 10. The gas turbine engines 20 can be configured to burn various forms of fuel, including but not limited to jet fuel / aviation turbine fuel and hydrogen fuel (unless otherwise specified).

[0034] Figure 2 is a cross-sectional view of a gas turbine engine according to an exemplary aspect of the present disclosure.

[0035] In at least one exemplary embodiment, gas turbine engine 20 is a multi-spool, high-bypass turbofan jet engine, sometimes also referred to as a “turbofan engine.” Figure 2 As shown, the gas turbine engine 20 defines an axial direction “A” (extending parallel to a longitudinal centerline 22 for reference), a radial direction “R,” and a circumferential direction “C” extending about the longitudinal centerline 22. Generally, the gas turbine engine 20 includes a fan section 24 and a turbine 26 located downstream of the fan section 24.

[0036] The illustrated turbine 26 generally includes an engine casing, housing, or core cover 28 that defines an annular core inlet 30. The core cover 28 at least partially surrounds, in series flow relationship, a compressor section including a booster or low-pressure compressor ("LPC") 32 and a high-pressure compressor ("HPC") 34; a combustion section 36; a turbine section including a high-pressure turbine ("HPT") 38 and a low-pressure turbine ("LPT") 40; and at least a portion of an exhaust nozzle 42. Together, these components or sections comprise the core engine 46 of the turbine 26.

[0037] The turbine 26 includes a high-pressure shaft 44 drivingly connecting the high-pressure turbine 38 to the high-pressure compressor 34, and a low-pressure shaft 43 drivingly connecting the low-pressure turbine 40 to the low-pressure compressor 32. The compressor section, combustion section 36, turbine section, and exhaust injection nozzle 42 collectively define a working gas flow path 50 (also referred to as a core air flow path) through the gas turbine engine 20.

[0038] For the illustrated embodiment, fan section 24 includes a fan 52 having a plurality of fan blades 54 coupled to a disk 56 in a spaced-apart manner. As shown, fan blades 54 extend outwardly from disk 56 generally in a radial direction R. Each fan blade 54 is rotatable with disk 56 about pitch axis P because fan blades 54 are operably coupled to a pitch change mechanism 58 that is configured to jointly change the pitch of fan blades 54, e.g., in unison. Fan blades 54, disk 56, and pitch change mechanism 58 are rotatable together about longitudinal centerline 22 via low-pressure shaft 43.

[0039] In an exemplary embodiment, as Figure 2 As shown, the gas turbine engine 20 also includes a power gearbox or gearbox 60. The gearbox 60 includes a plurality of gears for adjusting the speed of the fan 52 relative to the speed of the low-pressure shaft 43 so that the fan 52 and the low-pressure shaft 43 can rotate at a more efficient relative speed. The gearbox 60 can be any type of gearbox suitable for facilitating the coupling of the low-pressure shaft 43 to the fan 52 while allowing each of the low-pressure turbine 40 and the fan 52 to operate at a desired speed. For example, in some embodiments, the gearbox 60 can be a reduction gearbox. Utilizing a reduction gearbox allows the low-pressure turbine 40 to operate at a relatively high speed while maintaining sufficient fan speed to provide an increased air bypass ratio, thereby allowing efficient operation of the gas turbine engine 20. In addition, utilizing a reduction gearbox can allow for a reduction in the number of turbine stages that would otherwise be present (e.g., in a direct-drive engine configuration), thereby reducing the weight and complexity of the engine.

[0040] Still refer to Figure 2 In the exemplary embodiment of the present invention, the disk 56 is connected to the gearbox 60 via the fan shaft 62 of the gas turbine engine 20. The disk 56 is covered by a front hub 64 (sometimes also referred to as a "spinner") of the fan section 24. The front hub 64 has an aerodynamic profile to facilitate airflow through the plurality of fan blades 54. In addition, the fan section 24 includes an annular fan casing or nacelle 66 that circumferentially surrounds the fan 52 and / or at least a portion of the turbine 26. In the illustrated embodiment, the nacelle 66 is supported relative to the turbine 26 by a plurality of circumferentially spaced struts or outlet guide vanes 68. In addition, a downstream section 70 of the nacelle 66 extends above an outer portion of the turbine 26 to define a bypass airflow passage 72 therebetween.

[0041] In at least one exemplary embodiment, such as the exemplary embodiment shown, aircraft 10 includes a fuel delivery system 200 for providing a fuel flow to the combustors of combustion section 36 of turbine 26. Fuel delivery system 200 includes a fuel source, such as a fuel tank 205, for storing fuel. Although not shown, fuel tank 205 may be located in one or both of wings 14.

[0042] In at least one example embodiment, such as the exemplary embodiment shown, the aircraft 10 may include one or more accessory systems configured to support the operation of the gas turbine engine 20 or the aircraft 10 including the gas turbine engine 20. For example, the gas turbine engine 20 includes a lubrication system 100 configured to provide lubricant to various bearings and gear meshes in the compressor section (including the low-pressure compressor 32 and the high-pressure compressor 34), the turbine section (including the high-pressure turbine 38 and the low-pressure turbine 40), the high-pressure shaft 44, the low-pressure shaft 43, and the gearbox 60. The lubricant provided by the lubrication system 100 may increase the service life of these components and may remove a certain amount of heat from these components.

[0043] Figure 3 FIG. 1 is a schematic diagram of a lubrication system 100 according to an exemplary aspect of the present disclosure. The lubrication system 100 may be configured as described above with reference to FIG. Figure 2 The exemplary lubrication system 100 discussed above is configured in a similar manner.

[0044] In at least one example embodiment, lubrication system 100 includes a first fluid circuit 302 in fluid communication with an oil sump 300, a heat exchanger 305, one or more heat loads 310, and a pump 315. Oil sump 300 is configured to store a thermal fluid, and pump 315 is configured to circulate the thermal fluid through first fluid circuit 302. One or more heat loads 310 may include engine bearings, an accessory gearbox, a reduction gearbox, or a combination thereof. In at least one example embodiment, the thermal fluid is an oil-based lubricant or lubricating oil. Furthermore, first fluid circuit 302 may be formed by one or more fluid conduits.

[0045] In at least one example embodiment, such as the exemplary embodiment shown, the heat exchanger 305 is disposed within the oil sump 300. Thus, the heat exchanger 305 is in direct fluid communication with the hot fluid stored within the oil sump 300 via the first fluid circuit 302, as will be described below. Figures 4A-4E Positioning the heat exchanger 305 in direct fluid communication with the oil sump 300 can reduce the weight and complexity of the gas turbine engine 20. For example, fluid lines associated with the lubrication system 100 can be reduced such that no fluid lines extend through the working gas flow path 50 of the gas turbine engine 20 to the oil sump 300.

[0046] In at least one example embodiment, the second fluid circuit 320 is in fluid communication with the heat exchanger 305. The second fluid circuit 320 is fluidically isolated from the first fluid circuit 302, as will be discussed below in conjunction with Figures 4A-4E305 , which is discussed in more detail. The second fluid circuit 320 may be in fluid communication with one or more components of the gas turbine engine 20. The fluid within the second fluid circuit 320 may be any fluid or mixture of fluids, flowing in a liquid or gaseous state, or in a mixed two-phase state, suitable for meeting the thermal performance requirements within the gas turbine engine 20. For example, cooling air from the low-pressure compressor 32 may flow into the heat exchanger 305 and remove heat from the hot fluid within the heat exchanger 305. The cooling air absorbs heat from the hot fluid and is then directed from the heat exchanger 305 to the high-pressure compressor 34, which may increase the thermal efficiency of the high-pressure compressor 34. Additionally, because heat is removed from the hot fluid, the cooled hot fluid is directed to one or more heat loads 310 downstream of the heat exchanger 305.

[0047] In other exemplary embodiments, the heat exchanger 305 may be disposed or embedded within the core cowl 28, such as within a lower cowl region of the core cowl 28, within the bypass airflow passage 72, or at any other suitable location for cooling components of the gas turbine engine 20. Furthermore, the heat exchanger 305 may include a gas-to-gas heat exchanger, a gas-to-liquid heat exchanger, or a liquid-to-liquid heat exchanger. In other exemplary embodiments, the heat exchanger 305 may include an air-to-air heat exchanger embedded within or in fluid communication with the lower cowl region of the core cowl 28 to cool full authority digital engine control ("FADEC") components.

[0048] Figure 4A is a perspective view of a heat exchanger 305 according to an exemplary aspect of the present disclosure. Figure 4B According to an exemplary aspect of the present disclosure Figure 4A A cross-sectional view of the heat exchanger 305 is shown. Figure 4C According to an exemplary aspect of the present disclosure Figure 4A A partial top view of the heat exchanger 305 is shown. Figure 4D According to an exemplary aspect of the present disclosure Figure 4A An internal view of the heat exchanger 305. Figure 4E According to an exemplary aspect of the present disclosure Figure 4A An internal view of the heat exchanger 305. Figures 4A to 4E The exemplary heat exchanger 305 may be incorporated into the Figure 3 The lubrication system 100 is depicted (eg, as shown with the heat exchanger 305 ).

[0049] In at least one example embodiment, the heat exchanger 305 includes a housing 400 extending between a first end 401 and a second end 402 opposite the first end 401. The housing 400 defines a first fluid chamber 403 (see Figure 4B ), a first fluid inlet 405 adjacent to the first end 401 (see Figure 4A 、 Figure 4B) and a first fluid outlet 410 adjacent the second end 402 (see Figure 4A 、 Figure 4B ). The first fluid inlet 405 and the first fluid outlet 410 are in fluid communication with the first fluid chamber 403. The housing 400 further defines at least a portion of a second fluid outlet 412. For example, the second fluid outlet 412 may extend from at least a portion of the housing 400 adjacent the second end 402, such as Figure 4A In at least one example embodiment, such as the exemplary embodiment shown, housing 400 has a cylindrical shape.

[0050] However, in other exemplary embodiments, the housing 400 may have a triangular, rectangular, or other polygonal shape.

[0051] In at least one example embodiment, such as the example embodiment shown, the housing 400 defines a first plurality of second fluid inlet openings 415 between the first end 401 and the second end 402. The first plurality of second fluid inlet openings 415 may be spaced apart around the circumference of the housing 400. In some example embodiments, such as the example embodiment shown, the first plurality of second fluid inlet openings 415 may be evenly spaced apart around the housing 400.

[0052] However, it should be understood that in other example embodiments, the first plurality of second fluid inlet openings 415 may be unevenly spaced about the housing 400. In some additional example embodiments, the first plurality of second fluid inlet openings 415 may be staggered about the housing 400. For example, rows or columns of the first plurality of second fluid inlet openings 415 may be offset from adjacent rows or columns of the first plurality of second fluid inlet openings 415. In other example embodiments, rows or columns of the first plurality of second fluid inlet openings 415 may be aligned with adjacent rows or columns of the first plurality of second fluid inlet openings 415.

[0053] In at least one example embodiment, the heat exchanger 305 further includes a manifold 420 disposed within the first fluid chamber 403 of the heat exchanger 305 such that the first fluid chamber 403 is defined between the housing 400 and the manifold 420. The manifold 420 defines a second fluid chamber 425 and a second plurality of second fluid inlet openings 430 in fluid communication with the second fluid chamber 425. In at least one example embodiment, an end of the manifold 420 adjacent to the first end 401 of the housing 400 is sealed, and an opposite end of the manifold 420 is in fluid communication with the second fluid outlet 412, as shown. Figure 4B In at least one example embodiment, such as the exemplary embodiment shown, manifold 420 includes a cylindrical shape.

[0054] However, it should be understood that in other example embodiments, the manifold 420 includes a conical shape. For example, the diameter of the manifold can increase or decrease from an end adjacent to the first end 401 to an opposite end adjacent to the second end 402.

[0055] In at least one example embodiment, the second plurality of second fluid inlet openings 430 may be arranged in a spiral pattern around the manifold 420, such as Figures 4D-4E As shown. The heat exchanger 305 may also include a plurality of tubes 435. The plurality of tubes 435 may fluidly couple the first plurality of second fluid inlet openings 415 to the second plurality of second fluid inlet openings 430. In at least one example embodiment, the plurality of tubes 435 include a cylindrical shape extending between the first plurality of second fluid inlet openings 415 and the second plurality of second fluid inlet openings 430.

[0056] In other example embodiments, one or more of the plurality of tubes 435 may include a tortuous, twisted, coiled, or zigzag shape.

[0057] In at least one example embodiment, the heat exchanger 305 includes a plurality of baffles 440. Each of the plurality of baffles 440 is coupled between each of the plurality of tubes 435. Thus, the plurality of tubes 435 and the plurality of baffles 440 may also be arranged in a spiral pattern, such as Figures 4D-4E In addition, the plurality of baffles 440 coupled between each of the plurality of tubes 435 act as tube fins to increase the heat transfer surface area, which improves the efficiency of the heat exchanger 305 .

[0058] In at least one example embodiment, the heat exchanger 305 defines a first fluid path 445 that defines at least a portion of the second fluid circuit 320. The first fluid path 445 extends from the first fluid inlet 405, through the first fluid chamber 403, and to the first fluid outlet 410. Furthermore, the first fluid path 445 extends through the first fluid chamber 403 along a spiral path defined by the plurality of tubes 435 and the plurality of baffles 440, as shown in FIG. Figure 4D In at least one example embodiment, the first fluid path 445 may make two or more turns around the manifold 420, as shown. Figures 4D-4E In additional exemplary embodiments, each of the plurality of tubes 435 and the plurality of baffles 440 can be coupled such that the first fluid path 445 is continuous around the manifold 420. In other exemplary embodiments, the first fluid path 445 can be discontinuous such that one or more of the plurality of tubes 435 is not coupled to one or more of the plurality of baffles 440.

[0059] Heat exchanger 305 further defines a second fluid path 450 that defines at least a portion of first fluid circuit 302. Second fluid path 450 is fluidically isolated from first fluid path 445. Second fluid path 450 extends from first plurality of second fluid inlet openings 415, through second plurality of second fluid inlet openings 430, and to second fluid outlet 412. More specifically, second fluid path 450 is defined by first plurality of second fluid inlet openings 415, plurality of tubes 435, second plurality of second fluid inlet openings 430, and second fluid outlet 412.

[0060] In at least one example embodiment, the first fluid path 445 is configured to receive a first fluid, while the second fluid path 450 is configured to receive a second fluid. The first fluid may include a gas, while the second fluid may include a liquid. For example, the second fluid path 450 may be configured to receive a hot fluid from the oil sump 300 via the first fluid circuit 302 through the first plurality of second fluid inlet openings, and the first fluid path 445 may be configured to receive a cooling air flow from the low-pressure compressor 32 via the second fluid circuit 320 into the first fluid inlet 405. The cooling air flow is configured to circulate through the heat exchanger 305 in a spiral pattern defined by the first fluid path 445. The spiral pattern of the first fluid path 445 enables the cooling air flow to contact a larger surface area of ​​the manifold 420, the plurality of tubes 435, and the plurality of baffles 440, which also act as tube fins, as described above, thereby maximizing heat transfer between the cooling air and the hot fluid. For example, as cooling air flows from the first fluid inlet 405 to the first fluid outlet 410 along the plurality of tubes 435 and the plurality of baffles 440, the cooling air flow is able to absorb more heat from the hot fluid flowing through the second fluid path 450. Furthermore, by increasing the number of turns in the spiral pattern of the first fluid path 445, the heat transfer efficiency is also improved. Therefore, as the cooling air flows through the heat exchanger 305, its temperature increases, such that the temperature of the air exiting through the first fluid outlet 410 is higher than the temperature of the air entering through the first fluid inlet 405.

[0061] Now refer to Figure 5 According to another exemplary aspect of the present disclosure, a schematic diagram of a heat exchanger and combustion section of a gas turbine engine is provided. The heat exchanger 305 may be similar to the one shown in the above reference. Figures 3 to 4E The exemplary heat exchanger 305 discussed above may be configured in a similar manner and the gas turbine engine may be configured in the same manner as described above with reference to FIG. Figure 2 The depicted exemplary gas turbine engine 20 is configured in a similar manner.

[0062] For example, a gas turbine engine includes a combustion section 36 that can operate with a fuel delivery system 200 of, for example, an aircraft incorporating the gas turbine engine. Figure 5In the example embodiment shown in , the heat exchanger 305 is arranged to be in fluid communication with the fuel delivery system 200. Specifically, the combustion section 36 includes one or more fuel nozzles, such as fuel injectors 500, which are configured to receive a flow of liquid fuel from the fuel tank 205 via the fuel delivery system and provide the liquid fuel to the combustion chamber 505 of the combustion section 36 for combustion, as shown by arrow 503. The fuel injector 500 can be any suitable type of fuel injector, nozzle, fuel / air mixer or other liquid fuel distribution device, atomization device or mixing device. In at least one example embodiment, the heat exchanger 305 is in direct fluid communication with the fuel injector 500, as shown in FIG. Figure 6 Positioning the heat exchanger 305 in direct fluid communication with the fuel injectors 500 can reduce the weight and complexity of the gas turbine engine 20. For example, fluid lines associated with the fuel delivery system 200 can be reduced, such that fewer fluid lines extend through the working gas flow path 50 of the gas turbine engine 20 to the fuel tank 205.

[0063] In at least one example embodiment, the combustion section 36 includes an inner liner 510 and an outer liner 515. The inner liner 510 may at least partially define the combustion chamber 505 and may define a fluid path between the inner liner 510 and the outer liner 515. For example, the fluid path between the inner liner 510 and the outer liner 515 may be configured to receive compressed air (indicated by arrow 518) from the high-pressure compressor 34. The inner liner 510 defines a plurality of openings 520 in fluid communication with the combustion chamber 505, such that at least a portion of the compressed air can enter the combustion chamber 505 through the plurality of openings 520.

[0064] Still refer to Figure 5 , the combustion gases 530 flow from the combustion chamber 505 into the turbine section of the gas turbine engine 20. For example, the combustion gases 530 flow into the high pressure turbine 38 and the low pressure turbine 40, as shown in FIG. Figure 2 shown.

[0065] Figure 6 is a schematic diagram of a thermal management system according to an exemplary aspect of the present invention. Figure 6 An exemplary thermal management system may be configured with Figure 5 The exemplary system is configured in a similar manner.

[0066] For example, in the exemplary embodiment shown, the thermal management system includes a heat exchanger 305 and is operable with a fuel delivery system 200 and a gas turbine engine (not shown). The fuel delivery system 200 includes a first fluid path 600 and a second fluid path 605. The first fluid path 600 is in fluid communication with the high pressure compressor 34, the heat exchanger 305, the first pump 610, and the combustor 505 of the gas turbine engine. The first fluid path 600 may also be in fluid communication with the high pressure turbine 38, as shown in FIG. Figure 6 The first pump 610 is configured to move air from the heat exchanger 305 to one or both of the combustion chamber 505 and the high pressure turbine 38 .

[0067] In at least one example embodiment, the second fluid path 605 is in fluid communication with the fuel tank 205, the second pump 615, one or more secondary heat exchangers 620, the heat exchanger 305, and the combustion chamber 505. The second pump 615 is configured to provide a flow of fuel from the fuel tank 205 to the combustion chamber 505. In at least one example embodiment, the flow of fuel may pass through the one or more secondary heat exchangers 620 before entering the heat exchanger 305. The one or more secondary heat exchangers 620 are configured to increase the temperature of the fuel as the fuel flows along the second fluid path 605 to the heat exchanger 305.

[0068] In at least one example embodiment, the heat exchanger 305 is provided in direct fluid communication with the fuel injector 500. For example, the heat exchanger 305 may be integrated with the fuel injector rod and immersed in the working gas flow path 50. As will be appreciated, Figure 6 The heat exchanger 305 can be used in the same manner as above. Figures 4A-4E The exemplary heat exchanger discussed above is configured in substantially the same manner. In such exemplary embodiments, reference is again made to Figures 4A-4E , the first fluid inlet 405 can be configured to receive a flow of fuel through the first fluid inlet 405. The fuel can flow from the first fluid inlet 405 into the first fluid chamber 403 and travel along a spiral path of the first fluid path 445. For example, the fuel can flow through the first fluid inlet 405, along a spiral path defined by the plurality of tubes 435 and the plurality of baffles 440 within the first fluid chamber 403, and out of the first fluid outlet 410 to the combustion chamber 505.

[0069] Still refer to Figures 4A-4E , the first plurality of second fluid inlet openings 415 of the heat exchanger 305 may be configured to be connected to the heat exchanger 305 via the first fluid path 600 ( Figure 6 ) receives compressed air from the high pressure compressor 34. The compressed air can travel along the second fluid path 450. For example, the compressed air can enter the second fluid chamber 425 defined by the manifold 420 through the first plurality of second fluid inlet openings 415, the plurality of tubes 435, and the second plurality of second fluid inlet openings 430. The compressed air then exits the heat exchanger through the second fluid outlet 412.

[0070] In at least one example embodiment, the fuel traveling along the first fluid path 445 within the first fluid chamber 403 absorbs heat from the compressed air flowing along the second fluid path within the second fluid chamber 425. Thus, the fuel acts as a heat sink and absorbs heat from the compressed air before the compressed air is exhausted from the gas turbine engine 20. Furthermore, the temperature of the fuel is increased before the fuel reaches the combustion chamber 505, thereby improving combustion efficiency.

[0071] Now refer to Figure 7A and Figure 7B , Figure 7A is a perspective cross-sectional view of a heat exchanger according to another exemplary aspect of the present disclosure. Figure 7B According to an exemplary aspect of the present disclosure Figure 7A Detailed cross-sectional view of a heat exchanger.

[0072] In at least one example embodiment, heat exchanger 700 includes a core 705, a first fluid inlet manifold 710, a first fluid outlet manifold 715, a second fluid inlet manifold 720, and a second fluid outlet manifold 725. Each of core 705, first fluid inlet manifold 710, first fluid outlet manifold 715, second fluid inlet manifold 720, and second fluid outlet manifold 725 may have a spiral shape extending about a core axis 730 between a first end 701 and a second end 702 of heat exchanger 700. In at least one example embodiment, heat exchanger 700 may include a generally cylindrical shape.

[0073] In at least one example embodiment, the core 705 includes a plurality of cells. The plurality of cells of the core 705 may define a first fluid flow path 735 and a second fluid flow path 740. The first fluid flow path 735 may be fluidically isolated from the second fluid flow path 740. For example, the first fluid flow path 735 may be defined by a first fluid inlet manifold 710, at least a portion of the core 705, and a first fluid outlet manifold 715. The second fluid flow path 740 may be defined by a second fluid inlet manifold 720, at least a portion of the core 705, and a second fluid outlet manifold 725.

[0074] In at least one example embodiment, the heat exchanger 700 includes a second fluid inlet nozzle 755 adjacent to the first end 701 and a second fluid outlet nozzle 750 adjacent to the second end 702. In at least one example embodiment, the second fluid inlet nozzle 755 is fluidically coupled to the second fluid inlet manifold 720, while the second fluid outlet nozzle 750 is fluidically coupled to the second fluid outlet manifold 725. For example, the second fluid inlet manifold 720 can be configured to receive the second fluid via the second fluid inlet nozzle 755, while the second fluid outlet manifold 725 can be configured to discharge the second fluid via the second fluid outlet nozzle 750. In at least one example embodiment, the second fluid includes a gas. For example, the gas can include bleed air from one or both of the low-pressure compressor 32 and the high-pressure compressor 34.

[0075] In at least one example embodiment, the first fluid inlet manifold 710 defines a plurality of first fluid inlets 728. For example, an outer peripheral end of the first fluid inlet manifold 710 defines the plurality of first fluid inlets 728 that extend into the outer shell of the heat exchanger 700. The plurality of first fluid inlets 728 may include a plurality of perforations or openings. In at least one example embodiment, the heat exchanger 700 also includes a first fluid outlet nozzle 733 adjacent to the first end 701. For example, the first fluid outlet nozzle 733 is fluidically coupled to the first fluid outlet manifold 715. In at least one example embodiment, the first fluid inlet manifold 710 receives a first fluid via the plurality of first fluid inlets 728, and the first fluid outlet nozzle 733 is configured to discharge the first fluid from the first fluid inlet manifold 710. The first fluid may include a liquid. For example, the first fluid may include fuel from the fuel tank 205 or a hot fluid, such as oil, from the oil sump 300. In at least one example embodiment, the first fluid inlet manifold 710 includes a first plurality of tubes 760, and the first fluid outlet manifold 715 includes a second plurality of tubes 765. The first plurality of tubes 760 and the second plurality of tubes 765 extend substantially perpendicular to the lengths of the first fluid inlet manifold 710 and the first fluid outlet manifold 715, respectively. The first plurality of tubes 760 and the second plurality of tubes 765 are configured to fluidically couple the second fluid flow path 740 to the core 705. For example, the first plurality of tubes 760 fluidically couples the second fluid inlet manifold 720 to the core 705, while the second plurality of tubes 765 fluidically couples the core 705 to the second fluid outlet manifold 725. Thus, the second fluid flow path 740 is configured to flow through the second fluid inlet manifold 720, the first plurality of tubes 760, the core 705, the second plurality of tubes 765, and the second fluid outlet manifold 725.

[0076] Furthermore, the first plurality of tubes 760 and the second plurality of tubes 765 fluidically isolate the first fluid flow path 735 from the second fluid flow path 740. For example, the first fluid flow path 735 is defined between the first plurality of tubes 760 within the first fluid outlet manifold 715 and between the second plurality of tubes 765 within the first fluid inlet manifold 710. Although the first fluid flow path 735 is fluidically isolated from the second fluid flow path 740, the first and second fluid flow paths 735, 740 are in thermal communication via the first and second plurality of tubes 760, 765. This thermal communication increases the surface area for heat transfer and can reduce the size and weight of the heat exchanger 305. For example, the size, wall thickness, and material type of the first and second plurality of tubes 760, 765 can be designed to determine a desired thermal resistance between the first and second fluid flow paths 735, 740 through the first and second plurality of tubes 760, 765.

[0077] In at least one example embodiment, the heat exchanger 700 may be disposed in an oil sump, such as described above with respect to Figure 3 The oil sump 300 discussed above. In such an embodiment, the second fluid inlet manifold 720 receives a second fluid, such as a cooling airflow from a compressor section of the gas turbine engine 20 (e.g., from the high pressure compressor 34 or the low pressure compressor 32), via a second fluid inlet nozzle 755. The second fluid flows from the second fluid inlet manifold 720 through the first plurality of tubes 760 along a second fluid flow path 740 and flows to the core 705. Additionally, the first fluid inlet manifold 710 is configured to receive a first fluid. For example, the first fluid can be a hot fluid or oil received from the oil sump 300, as described above with respect to Figure 3 . The hot fluid or oil flows from the first fluid inlet manifold 710 along the first fluid flow path 735 and flows into the core 705 via the plurality of first fluid inlets 728. Within the core 705, the second fluid (or cooling air flow) is configured to absorb heat from the first fluid. The spiral pattern of the first fluid flow path 735 and the second fluid flow path 740 around the first fluid inlet manifold 710, the first fluid outlet manifold 715, the second fluid inlet manifold 720, the second fluid outlet manifold 725 and the core 705 maximizes heat transfer because the cooling air flow contacts a larger surface area of ​​the second fluid within the core 705 of the heat exchanger 700. For example, the cooling air flow is able to absorb a greater amount of heat from the first fluid. As a result, the temperature of the cooling air increases, causing the second fluid to have a higher temperature when it flows from the core 705 through the second fluid outlet manifold 725 and out of the heat exchanger 700 via the second fluid outlet nozzles 750. Additionally, the temperature of the first fluid decreases as it exits the core 705 , flows through the first fluid outlet manifold 715 , and exits the heat exchanger 700 via the first fluid outlet nozzle 733 .

[0078] In other example embodiments, the heat exchanger 700 may be in fluid communication with the fuel injector 500 and immersed in the working gas flow path 50, as described with respect to FIG. Figure 6 As discussed. In such an embodiment, the second fluid inlet manifold 720 can be configured to receive fuel from the fuel tank 205 via the second fluid inlet nozzle 755. The fuel can flow from the second fluid inlet manifold 720 into the core 705 along the second fluid flow path 740. In addition, the first fluid inlet manifold 710 can be configured to receive compressed air from the high-pressure compressor 34. The compressed air can flow from the first fluid inlet manifold 710 into the core 705 via the plurality of first fluid inlets 728. Within the core 705, the fuel absorbs heat from the compressed air. Thus, the fuel acts as a heat sink and absorbs heat from the compressed air before the compressed air is discharged from the gas turbine engine 20. In addition, the temperature of the fuel is increased before the fuel reaches the combustion chamber 505, thereby improving combustion efficiency.

[0079] From the core 705, the fuel flows along the second fluid flow path 740 to the second fluid outlet manifold 725, where it is discharged from the heat exchanger 700 via the second fluid outlet nozzle 750. The compressed air, now cooled by the fuel, exits the core 705 and flows along the first fluid flow path 735 to the first fluid outlet manifold 715, where it is discharged from the heat exchanger 700 via the first fluid outlet nozzle 733.

[0080] In at least one example embodiment, the first fluid flow path 735 is configured to flow in a first direction, while the second fluid flow path 740 is configured to flow in a second direction. The second direction can be opposite to the first direction, such that the first fluid flow path 735 and the second fluid flow path 740 are in a counter-current flow arrangement. For example, the first fluid flow path 735 can flow in a spiral pattern about the core axis 730 from the second end 702 to the first end 701 of the heat exchanger 700. The second fluid flow path 740 can flow in a spiral pattern about the core axis 730 from the first end 701 to the second end 702 of the heat exchanger 700.

[0081] In other example embodiments (not shown), the second direction can be the same as the first direction, such as a co-current flow arrangement. For example, the first fluid flow path 735 can flow in a spiral pattern about the core axis 730 from the first end 701 to the second end 702 of the heat exchanger 700. The second fluid flow path 740 can flow in a spiral pattern about the core axis 730 from the first end 701 to the second end 702 of the heat exchanger 700.

[0082] In at least one example embodiment, the core 705, the first fluid inlet manifold 710, the first fluid outlet manifold 715, the second fluid inlet manifold 720, and the second fluid outlet manifold 725 are arranged in a stacked relationship. For example, the first fluid inlet manifold 710 may be adjacent to the second side 712 of the core 705, while the first fluid outlet manifold 715 may be adjacent to the first side 711 of the core 705. Additionally, the second fluid inlet manifold 720 may be adjacent to the first fluid outlet manifold 715, while the second fluid outlet manifold 725 may be adjacent to the first fluid inlet manifold 710. For example, the first fluid inlet manifold 710 may be located between the core 705 and the second fluid outlet manifold 725, while the first fluid outlet manifold 715 may be located between the core 705 and the second fluid inlet manifold 720. In such embodiments, the first fluid outlet manifold 715 and the second fluid inlet manifold 720 may be stacked from the first side 711 of the core 705 , and the first fluid inlet manifold 710 and the second fluid outlet manifold 725 may be stacked from the second side 712 of the core 705 .

[0083] In at least one example embodiment, the heat exchanger 700 includes a plurality of modules 770. For example, each of the plurality of modules 770 may include a core 705, a first fluid inlet manifold 710, a first fluid outlet manifold 715, a second fluid inlet manifold 720, and a second fluid outlet manifold 725. Figure 7A As shown, each of the plurality of modules 770 can be stacked to form the heat exchanger 700. In addition, the core 705, the first fluid inlet manifold 710, the first fluid outlet manifold 715, the second fluid inlet manifold 720, and the second fluid outlet manifold 725 of each of the plurality of modules 770 can be fluidly coupled such that the first fluid flow path 735 and the second fluid flow path 740 are continuous through each of the plurality of modules 770. The plurality of modules 770 allows the size of the heat exchanger 700 to be customized to suit specific needs and based on the desired location of the heat exchanger 700 within the gas turbine engine 20. For example, the size of the heat exchanger 700 can be customized based on whether the heat exchanger 700 is disposed in the oil sump 300 (as described with respect to FIG. 1 ). Figure 3 discussed) or is arranged to be connected to the working gas flow path 50 (as discussed Figure 6 discussed) fluid communication and modified.

[0084] Figure 8A is an internal view of a heat exchanger according to an exemplary aspect of the present disclosure. Figure 8B is an internal view of a heat exchanger according to an exemplary aspect of the present disclosure.

[0085] In at least one example embodiment, the heat exchanger 800 may be similar to the heat exchanger 800 described above. Figures 7A-7BFor example, heat exchanger 800 includes core 705, first fluid inlet manifold 710, first fluid outlet manifold 715, second fluid inlet manifold 720, and second fluid outlet manifold 725. However, unlike the heat exchanger discussed with respect to FIG. Figures 7A-7B Compared to the heat exchanger 700 discussed, Figures 8A-8B The positioning of the first fluid inlet manifold 710 , the first fluid outlet manifold 715 , the second fluid inlet manifold 720 , and the second fluid outlet manifold 725 relative to the core 705 may vary.

[0086] In at least one example embodiment, the core 705, the first fluid inlet manifold 710, the first fluid outlet manifold 715, the second fluid inlet manifold 720, and the second fluid outlet manifold 725 are arranged in a stacked relationship. For example, the second fluid outlet manifold 725 and the first fluid inlet manifold 710 may be adjacent to the first side 711 of the core 705, and the first fluid outlet manifold 715 and the second fluid inlet manifold 720 may be adjacent to the second side 712 of the core 705. Additionally, the second fluid outlet manifold 725 may be located between the core 705 and the first fluid inlet manifold 710. The first fluid outlet manifold 715 may be located between the core 705 and the second fluid inlet manifold 720. In such an embodiment, the second fluid outlet manifold 725 and the first fluid inlet manifold 710 may be stacked from the first side 711 of the core, and the first fluid outlet manifold 715 and the second fluid inlet manifold 720 may be stacked from the second side 712 of the core 705. In other example embodiments, the second fluid inlet manifold 720 may be adjacent to the first side 711 of the core 705, such as located between the core 705 and the first fluid inlet manifold 710, and the second fluid outlet manifold 725 may be adjacent to the second side 712 of the core 705, such that the first fluid outlet manifold 715 is located between the core 705 and the second fluid outlet manifold 725.

[0087] In at least one example embodiment, the heat exchanger 800 includes a plurality of modules 870. Each of the plurality of modules 870 includes a core 705, a first fluid inlet manifold 710, a first fluid outlet manifold 715, a second fluid inlet manifold 720, and a second fluid outlet manifold 725. Figure 8BAs shown, each of the plurality of modules 770 can be stacked to form the heat exchanger 800. In addition, the core 705, the first fluid inlet manifold 710, the first fluid outlet manifold 715, the second fluid inlet manifold 720, and the second fluid outlet manifold 725 of each of the plurality of modules 870 can be fluidly coupled such that the first fluid flow path 735 and the second fluid flow path 740 are continuous through each of the plurality of modules 870. The plurality of modules 870 allows the size of the heat exchanger 800 to be customized to suit specific needs and based on the desired location of the heat exchanger 800 within the gas turbine engine 20. For example, the size of the heat exchanger 800 can be customized based on whether the heat exchanger 800 is disposed in the oil sump 300 (as described with respect to FIG. 1 ). Figure 3 discussed) or is arranged to be connected to the working gas flow path 50 (as discussed Figure 6 discussed) fluid communication and modified.

[0088] In at least one example embodiment (not shown), the heat exchanger 700 may be disposed or embedded within the core cowl 28, such as within a lower cowl region of the core cowl 28, within the bypass airflow passage 72, or at any other suitable location for cooling components of the gas turbine engine 20. Furthermore, the heat exchanger 700 may include a gas-to-gas heat exchanger, a gas-to-liquid heat exchanger, or a liquid-to-liquid heat exchanger. In other example embodiments, the heat exchanger 700 may include an air-to-air heat exchanger embedded within or in fluid communication with the lower cowl region of the core cowl 28 to cool full authority digital engine control ("FADEC") components.

[0089] Now refer to Figure 9 , Figure 9 is a perspective cross-sectional view of a heat exchanger 900 according to another exemplary aspect of the present disclosure. In some exemplary embodiments, the heat exchanger 900 may replace the heat exchanger 700, such as Figures 7A-8B shown.

[0090] In at least one example embodiment, heat exchanger 900 is similar to heat exchanger 700, such as Figures 7A-7B However, heat exchanger 900 includes a first end nozzle 955 adjacent to first end 701 and a second end nozzle 950 adjacent to second end 702. First end nozzle 955 and second end nozzle 950 may each include a divider 903. For example, divider 903 may extend within each of first end nozzle 955 and second end nozzle 950 along core axis 730.

[0091] In at least one example embodiment, the second end nozzle 950 includes a first fluid inlet side 905 on one side of the divider 903 and a second fluid outlet side 910 on the other side of the divider 903. The first fluid inlet side 905 and the second fluid outlet side 910 can be fluidically isolated by the divider 903. The first fluid inlet side 905 can be configured to receive a first fluid and supply the first fluid to the first fluid inlet manifold 710. The second fluid outlet side 910 can be configured to receive a second fluid from the second fluid outlet manifold 725 and discharge the second fluid from the heat exchanger 900.

[0092] In at least one example embodiment, the first end nozzle 955 includes a first fluid outlet side 915 located on one side of the divider 903 and a second fluid inlet side 920 located on the other side of the divider 903. The first fluid outlet side 915 and the second fluid inlet side 920 can be fluidically isolated by the divider 903. The first fluid outlet side 915 can be configured to receive a first fluid from the first fluid outlet manifold 715 and discharge the first fluid from the heat exchanger 900. The second fluid inlet side 920 can be configured to receive a second fluid and supply the second fluid to the second fluid inlet manifold 720.

[0093] In other example embodiments, the first fluid inlet side 905 may discharge a first fluid received from the first fluid outlet manifold 715 and discharge the first fluid from the heat exchanger 900, and the second fluid outlet side 910 may be configured to receive a second fluid and supply the second fluid to the second fluid inlet manifold 720. In such embodiments, the first fluid outlet side 915 may be configured to supply the first fluid to the first fluid inlet manifold 710, and the second fluid inlet side 920 may be configured to receive the second fluid from the second fluid outlet manifold 725 and discharge the second fluid from the heat exchanger 900.

[0094] In at least one example embodiment, the first fluid flow path 735 is configured to flow in a first direction, and the second fluid flow path 740 is configured to flow in a second direction through the heat exchanger 900, in a manner similar to that described above with respect to Figures 7A-8B The heat exchanger 700 discussed above is similar. For example, the second direction may be opposite to the first direction.

[0095] In other embodiments, the first direction and the second direction can be the same, for example, the first fluid flow path 735 and the second fluid flow path 740 are configured to flow in parallel or in the same direction. In this parallel flow arrangement of the heat exchanger 900, the first fluid inlet side 905 of the second end nozzle 950 is configured to supply the first fluid to the first fluid inlet manifold 710, while the second fluid outlet side 910 of the second end nozzle 950 is configured to supply the second fluid to the second fluid inlet manifold 720. Furthermore, the first fluid outlet side 915 of the first end nozzle 955 can be configured to receive the first fluid from the first fluid outlet manifold 715 and discharge the first fluid from the heat exchanger 900, while the second fluid inlet side 920 of the first end nozzle 955 can be configured to receive the second fluid from the second fluid outlet manifold 725 and discharge the second fluid from the heat exchanger 900.

[0096] In other example embodiments, the parallel flow arrangement may flow in opposite directions such that the first fluid outlet side 915 of the first end nozzle 955 is configured to supply the first fluid to the first fluid inlet manifold 710, and the second fluid inlet side 920 of the first end nozzle 955 is configured to supply the second fluid to the second fluid inlet manifold 720. Additionally, the first fluid inlet side 905 of the second end nozzle 950 may be configured to receive the first fluid from the first fluid outlet manifold 715 and discharge the first fluid from the heat exchanger 900, and the second fluid outlet side 910 of the second end nozzle 950 may be configured to receive the second fluid from the second fluid outlet manifold 725 and discharge the second fluid from the heat exchanger 900.

[0097] Now refer to Figure 10 , showing a perspective cross-sectional view of a heat exchanger 1000 according to another exemplary aspect of the present disclosure. In some exemplary embodiments, the heat exchanger 1000 may replace the heat exchanger 700, such as Figures 7A-8B shown.

[0098] In at least one example embodiment, heat exchanger 1000 is similar to heat exchanger 900, such as Figure 9 However, the heat exchanger 1000 includes two different tubes, a first fluid inlet side 905 and a second fluid inlet side 920 instead of the second end nozzle 950, as shown in FIG. Figure 10 Similarly, the first fluid outlet side 915 and the second fluid inlet side 920 of the first end nozzle 955 may include two different tubes, such as Figure 10 The first fluid inlet side 905, the second fluid inlet side 920, the first fluid outlet side 915 and the second fluid inlet side 920 of the heat exchanger 1000 can be the same as those described above. Figure 9The first fluid inlet side 905 , the second fluid inlet side 920 , the first fluid outlet side 915 , and the second fluid inlet side 920 of the discussed heat exchanger 900 function in a similar or analogous manner.

[0099] Figure 11A is a top view of a heat exchanger 1100 according to an exemplary aspect of the present disclosure. Figure 11B According to an exemplary aspect of the present disclosure Figure 11A The bottom view of the heat exchanger 1100. The heat exchanger 1100 can be used with Figures 7A-8B The heat exchanger 700 shown is similar or similar, and the differences are discussed below. In addition, in some exemplary embodiments, the heat exchanger 1100 can replace Figures 7A-8B Heat exchanger 700 is shown.

[0100] In at least one example embodiment, a surface of the heat exchanger 1100 adjacent to the first end 701 defines a first opening 1105, and a surface of the heat exchanger 1100 adjacent to the second end 702 defines a second opening 1110. The first opening 1105 can be in fluid communication with the second fluid inlet manifold 720, and the second opening 1110 can be in fluid communication with the second fluid outlet manifold 725. In at least one example embodiment, the first fluid inlet manifold 710 receives a first fluid via the second fluid outlet nozzle 750. The first fluid flows from the first fluid inlet manifold 710, through the core 705, through the first fluid outlet manifold 715, and out of the heat exchanger 1100 through the second fluid inlet nozzle 755. The second fluid inlet manifold 720 receives a second fluid via the first opening 1105. The second fluid flows from the second fluid inlet manifold 720, through the first plurality of tubes 760, through the core 705, through the second plurality of tubes 765, through the second fluid outlet manifold 725, and out of the heat exchanger 1100 through the second opening 1110. In such an embodiment, the first fluid and the second fluid are in a counter-flow arrangement, as described above with respect to Figures 7A-7B In other example embodiments (not shown), the first fluid and the second fluid may flow through the heat exchanger 1100 in a parallel or co-current flow arrangement.

[0101] Alternatively, second fluid outlet nozzle 750 and second fluid inlet nozzle 755 can be in fluid communication with second fluid inlet manifold 720 and second fluid outlet manifold 725. In such an embodiment, first opening 1105 and second opening 1110 can be in fluid communication with first fluid inlet manifold 710 and first fluid outlet manifold 715.

[0102] In additional exemplary embodiments, the first opening 1105 can be in fluid communication with the first fluid outlet manifold 715, while the second opening 1110 can be in fluid communication with the first fluid inlet manifold 710. For example, the heat exchanger 1100 can include a plurality of tubes, pipes, or conduits extending through the second fluid inlet manifold 720 and the second fluid outlet manifold 725 to fluidically couple the first opening 1105 to the first fluid outlet manifold 715 and the second opening 1110 to the first fluid inlet manifold 710. The plurality of tubes, pipes, or conduits can be similar or analogous to the first plurality of tubes 760 and the second plurality of tubes 765. In such embodiments, the plurality of tubes, pipes, or conduits extending through the second fluid inlet manifold 720 and the second fluid outlet manifold 725 are fluidically isolated from the second fluid inlet manifold 720 and the second fluid outlet manifold 725 to allow fluid communication between the plurality of tubes, pipes, or conduits within the second fluid inlet manifold 720 and the second fluid outlet manifold 725.

[0103] In such an example embodiment, a first fluid enters the first fluid inlet manifold 710 via the second fluid outlet nozzle 750, flows through the core 705 and the first fluid outlet manifold 715, and exits the heat exchanger 1100 through the first opening 1105. A second fluid enters the second fluid inlet manifold 720 via the second fluid inlet nozzle 755, flows through the first plurality of tubes 760, the core 705, the second plurality of tubes 765, and the second fluid outlet manifold 725, and exits the heat exchanger 1100 through the second opening 1110. In such an embodiment, the first and second fluids are in a counter-current flow arrangement, as described above with respect to FIG. Figures 7A-7B In other example embodiments (not shown), the first fluid and the second fluid may flow through the heat exchanger 1100 in a co-flow arrangement.

[0104] Alternatively, second fluid outlet nozzle 750 and first opening 1105 may be in fluid communication with second fluid inlet manifold 720 and second fluid outlet manifold 725. In such an embodiment, second opening 1110 and second fluid inlet nozzle 755 may be in fluid communication with first fluid inlet manifold 710 and first fluid outlet manifold 715.

[0105] In at least one example embodiment, the first opening 1105 and the second opening 1110 may comprise slits. For example, one or both of the first opening 1105 and the second opening 1110 may comprise rectangular or pie-shaped slits located in the surfaces of the heat exchanger 1100 adjacent to the first end 701 and the second end 702, respectively. In other example embodiments, one or both of the first opening 1105 and the second opening 1110 may comprise a plurality of openings or slits.

[0106] Further aspects are provided by the subject matter of the following clauses:

[0107] 14. A heat exchanger for a gas turbine engine, comprising: a housing extending between a first end and a second end opposite the first end, the housing defining a first fluid chamber, a first fluid inlet adjacent the first end, and a first fluid outlet adjacent the second end, the housing further defining a first plurality of second fluid inlet openings between the first end and the second end, and a second fluid outlet adjacent the second end; and a manifold disposed within the housing, the manifold defining a second fluid chamber and a second plurality of second fluid inlet openings; wherein the heat exchanger defines a first fluid path extending from the first fluid inlet, through the first fluid chamber, and to the first fluid outlet; and wherein the heat exchanger further defines a second fluid path extending from the first plurality of second fluid inlet openings, through the second plurality of second fluid inlet openings, through the second fluid chamber, and to the second fluid outlet.

[0108] A heat exchanger as claimed in any preceding clause, wherein the first fluid chamber is defined between the housing and the manifold.

[0109] A heat exchanger as claimed in any preceding clause, wherein: the first fluid path is configured to receive a first fluid; and the second fluid path is configured to receive a second fluid.

[0110] A heat exchanger according to any preceding clause, wherein, when the heat exchanger is installed in the gas turbine engine, the first fluid comprises a cooling air flow from the gas turbine engine and the second fluid comprises lubricating oil.

[0111] A heat exchanger as claimed in any preceding clause, wherein the first fluid comprises fuel and the second fluid comprises compressed air.

[0112] A heat exchanger as claimed in any preceding clause, wherein the first fluid path is fluidly isolated from the second fluid path.

[0113] A heat exchanger as claimed in any preceding clause, wherein the first fluid path is helical.

[0114] A heat exchanger as recited in any preceding clause, wherein: the manifold extends between the first end and the second end; the first end of the manifold is sealed; and the second end of the manifold defines at least a portion of the second fluid outlet.

[0115] A heat exchanger as claimed in any preceding clause, wherein the second plurality of second fluid inlet openings are arranged in a helical pattern around the manifold.

[0116] The heat exchanger of any of the preceding clauses, further comprising a plurality of tubes fluidly coupling the first and second pluralities of second fluid inlet openings, the plurality of tubes defining at least a portion of the second fluid path.

[0117] The heat exchanger of any of the preceding clauses, wherein the plurality of tubes comprises a straight shape, a zigzag shape, a twisted shape, a coiled shape, a zigzag shape, or a combination thereof.

[0118] The heat exchanger of any of the preceding clauses, further comprising a plurality of baffles coupled between each tube of the plurality of tubes and defining at least a portion of the first fluid path.

[0119] A heat exchanger as claimed in any preceding clause, wherein the plurality of baffles comprises tube fins for increasing the surface area of ​​the first fluid path.

[0120] A heat exchanger as claimed in any preceding clause, wherein the plurality of tubes and the plurality of baffles are arranged in a spiral pattern around the manifold.

[0121] A heat exchanger as in any of the preceding clauses, wherein the plurality of tubes and the plurality of baffles are arranged to form the first fluid path having a plurality of turns around the manifold.

[0122] A heat exchanger according to any of the preceding clauses, wherein when the heat exchanger is installed in the gas turbine engine, the heat exchanger is configured to be disposed in an oil sump of a lubrication system of the gas turbine engine.

[0123] A gas turbine engine comprising: a fan; a turbine operably coupled to the fan to drive the fan, the turbine comprising a compressor section, a combustion section, and a turbine section arranged in a series flow order and jointly defining a working gas flow path; an oil sump disposed in the turbine and configured to receive lubricating oil; and a heat exchanger according to any of the preceding clauses, the heat exchanger being disposed in the oil sump; wherein the first fluid path is in fluid communication with the compressor section; and wherein the second fluid path is in fluid communication with the oil sump.

[0124] A gas turbine engine as claimed in any one of the preceding clauses, wherein the second fluid path is in fluid communication with a bearing or gearbox assembly of the gas turbine engine.

[0125] A gas turbine engine comprises: a fan; a turbine operably coupled to the fan to drive the fan, the turbine comprising a compressor section, a combustion section, and a turbine section arranged in a series flow order and jointly defining a working gas flow path; a fuel delivery system comprising a fuel source configured to deliver fuel from the fuel source to the combustion section; and the heat exchanger configured to be in fluid communication with the fuel delivery system; wherein the first fluid path is in fluid communication with the fuel source; and wherein the second fluid path is in fluid communication with the compressor section.

[0126] A gas turbine engine as claimed in any one of the preceding clauses, wherein: the first fluid path is in fluid communication with the combustion section; and the second fluid path is in fluid communication with the combustion section or the turbine section.

[0127] The gas turbine engine of any of the preceding clauses, further comprising one or more secondary heat exchangers in fluid communication with the first fluid path.

[0128] A heat exchanger for a gas turbine engine, comprising: a core including a plurality of cells, the core defining a core axis and having a spiral shape extending around the core axis between a first end and a second end, the core including a first side adjacent to the first end and a second side adjacent to the second end, each of the plurality of cells defining a first fluid flow path and a second fluid flow path; a first fluid inlet manifold in fluid communication with the first fluid flow path; a first fluid outlet manifold in fluid communication with the first fluid flow path; a second fluid inlet manifold in fluid communication with the second fluid flow path, the second fluid inlet manifold defining a plurality of second fluid inlets adjacent to the first end or the second end; a second fluid outlet manifold in fluid communication with the second fluid flow path; and a second fluid inlet nozzle adjacent to the first end and in fluid communication with the second fluid inlet manifold; and a second fluid outlet nozzle adjacent to the second end and in fluid communication with the second fluid outlet manifold; wherein the first fluid inlet manifold, the first fluid outlet manifold, the second fluid inlet manifold and the second fluid outlet manifold each have a spiral shape extending around the core axis between the first end and the second end.

[0129] A heat exchanger as claimed in any preceding clause, wherein the second fluid outlet manifold defines a second fluid outlet opening opposite the plurality of second fluid inlets.

[0130] A heat exchanger according to any of the preceding clauses, wherein: the first fluid inlet manifold is adjacent to the second side of the core; the first fluid outlet manifold is adjacent to the first side of the core; the second fluid inlet manifold is adjacent to the first side of the core; and the second fluid outlet manifold is adjacent to the second side of the core.

[0131] A heat exchanger as claimed in any preceding clause, wherein: the first fluid inlet manifold is located between the core and the second fluid outlet manifold; and the first fluid outlet manifold is located between the core and the second fluid inlet manifold.

[0132] A heat exchanger according to any of the preceding clauses, wherein: the first fluid inlet manifold is adjacent to the first side of the core; the first fluid outlet manifold is adjacent to the second side of the core; the second fluid inlet manifold is adjacent to the second side of the core; and the second fluid outlet manifold is adjacent to the first side of the core.

[0133] A heat exchanger as claimed in any preceding clause, wherein: the second fluid outlet manifold is located between the core and the first fluid inlet manifold; and the first fluid outlet manifold is located between the core and the second fluid inlet manifold.

[0134] A heat exchanger as claimed in any preceding clause, wherein the first and second fluid flow paths are fluidly isolated.

[0135] The heat exchanger of any of the preceding clauses, wherein: the first fluid inlet manifold comprises a first plurality of tubes; the first fluid outlet manifold comprises a second plurality of tubes; and the first and second plurality of tubes define at least a portion of the second fluid flow path.

[0136] A heat exchanger as claimed in any of the preceding clauses, wherein: the first fluid flow path is configured for flow in a first direction; the second fluid flow path is configured for flow in a second direction; and the first direction is opposite to the second direction.

[0137] A heat exchanger as claimed in any preceding clause, wherein: the first direction is from the first end to the second end about the core axis; and the second direction is from the second end to the first end about the core axis.

[0138] A heat exchanger as claimed in any of the preceding clauses, wherein: the first fluid flow path is configured for flow in a first direction; the second fluid flow path is configured for flow in a second direction; and the first direction is the same as the second direction.

[0139] The heat exchanger of any of the preceding clauses, further comprising: a plurality of modules; wherein each of the plurality of modules comprises the core, the first fluid inlet manifold, the first fluid outlet manifold, the second fluid inlet manifold, and the second fluid outlet manifold.

[0140] A heat exchanger as claimed in any preceding clause, wherein the plurality of modules are arranged in a stacked relationship.

[0141] A heat exchanger according to any of the preceding clauses, wherein: the first fluid inlet manifold defines a plurality of first fluid inlets, the plurality of first fluid inlets being adjacent to a peripheral end of the first fluid inlet manifold and configured to receive a first fluid; and the second fluid inlet manifold is configured to receive a second fluid via the second fluid inlet nozzle.

[0142] The heat exchanger of any of the preceding clauses, wherein: the first fluid outlet manifold is configured to discharge a first fluid via a first fluid outlet nozzle; and the second fluid outlet manifold is configured to receive a second fluid via the second fluid outlet nozzle.

[0143] A heat exchanger according to any of the preceding clauses, wherein: the first fluid inlet manifold is configured to receive a first fluid via a first fluid inlet nozzle; and the second fluid inlet manifold is configured to receive a second fluid via the second fluid inlet nozzle.

[0144] This written description uses examples to disclose the present disclosure, including the best mode, and also to enable any person skilled in the art to practice the present disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the present disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.

Claims

1. A heat exchanger, characterized in that: include: a housing extending between a first end and a second end opposite the first end, the housing defining a first fluid chamber, a first fluid inlet adjacent the first end, and a first fluid outlet adjacent the second end, the housing further defining a first plurality of second fluid inlet openings between the first end and the second end, and a second fluid outlet adjacent the second end; as well as a manifold disposed within the housing, the manifold defining a second fluid chamber and a second plurality of second fluid inlet openings; wherein the heat exchanger defines a first fluid path extending from the first fluid inlet, through the first fluid chamber, and to the first fluid outlet; and Wherein, the heat exchanger further defines a second fluid path extending from the first plurality of second fluid inlet openings, through the second plurality of second fluid inlet openings, through the second fluid chamber, and to the second fluid outlet.

2. The heat exchanger according to claim 1, characterized in that in, The first fluid chamber is defined between the housing and the manifold.

3. The heat exchanger according to claim 1, characterized in that in: The first fluid path is configured to receive a first fluid; and The second fluid path is configured to receive a second fluid.

4. The heat exchanger according to claim 3, characterized in that in, When the heat exchanger is installed in the gas turbine engine, the first fluid comprises a cooling air flow from the gas turbine engine, and the second fluid comprises lubricating oil.

5. The heat exchanger according to claim 3, characterized in that in, The first fluid comprises fuel, and the second fluid comprises compressed air.

6. The heat exchanger according to claim 1, characterized in that in, The first fluid path is fluidly isolated from the second fluid path.

7. The heat exchanger according to claim 1, characterized in that in, The first fluid path is helical.

8. The heat exchanger according to claim 1, characterized in that in: the manifold extending between the first end and the second end; The first end of the manifold is sealed; and The second end of the manifold defines at least a portion of the second fluid outlet.

9. The heat exchanger according to claim 1, characterized in that in, The second plurality of second fluid inlet openings are arranged in a spiral pattern around the manifold.

10. The heat exchanger according to claim 1, wherein Further included is a plurality of tubes fluidly coupling the first plurality of second fluid inlet openings and the second plurality of second fluid inlet openings, the plurality of tubes defining at least a portion of the second fluid path.

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