Heat exchanger for a gas turbine engine

Abstract

A heat exchanger for a gas turbine engine includes a core extending axially between a first end and a second end opposite to the second end. The core defines a first fluid domain and a second fluid domain fluidly isolated from the first fluid domain. The second fluid domain defines one or more helical fluid channels defining a pitch (P). The core also defines a diameter (D) extending perpendicular to the axial direction. The heat exchanger further includes a fluid inlet manifold fluidly connected to the first end of the core and in fluid communication with each of the one or more helical fluid channels; and a fluid outlet manifold fluidly connected to the second end of the core and in fluid communication with the second fluid domain.

Description

Priority information

[0001] This application claims priority to Italian patent application serial number 102025000002580, filed on February 11, 2025. Technical Field

[0002] This disclosure relates to a heat exchanger for a gas turbine engine. Background Technology

[0003] Gas turbine engines typically consist of a turbine and a rotor assembly. Gas turbine engines, such as turbofan engines, are used for aircraft propulsion. In turbofan engines, the rotor assembly is configured as a fan assembly.

[0004] Gas turbine engines typically employ one or more thermal management systems, including one or more heat exchangers, to control the thermal energy of various fluids flowing through the various components of the gas turbine engine. However, heat exchangers that can improve the cooling effect of hot fluids are desirable. Attached Figure Description

[0005] The specification sets forth a complete and practical disclosure for those skilled in the art, including its best mode, which is referenced in the accompanying drawings, wherein:

[0006] Figure 1 This is a cross-sectional view of a gas turbine engine according to an exemplary aspect of this disclosure.

[0007] Figure 2 This is a perspective view of a heat exchanger according to an exemplary aspect of this disclosure.

[0008] Figure 3A This is an exemplary aspect of the present disclosure. Figure 2 An internal view of the core of the heat exchanger is shown, illustrating the first and second fluid domains.

[0009] Figure 3B This is an exemplary aspect of the present disclosure. Figure 2 An internal view of the core of the heat exchanger is shown, revealing the second fluid domain.

[0010] Figure 4A This is an exemplary aspect of the present disclosure. Figure 2 The cross-sectional view of the heat exchanger shown illustrates the first fluid domain.

[0011] Figure 4B This is an exemplary aspect of the present disclosure. Figure 2 The cross-sectional view of the heat exchanger shown illustrates the second fluid domain.

[0012] Figure 5This is a graphical representation of the heat exchanger characteristics of different example heat exchangers according to exemplary embodiments of the present disclosure. Detailed Implementation

[0013] Reference will now be made in detail to the present embodiments of this disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerals and letter reference numerals to denote features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to denote similar or analogous portions of this disclosure.

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

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

[0016] In a context such as “at least one of A, B and C”, the term “at least one” means only A, only B, only C, or any combination of A, B and C.

[0017] The term “turbine” refers to a machine that includes one or more compressors, a heating section (such as a combustion section), and one or more turbines, which together produce torque output.

[0018] The term "gas turbine engine" refers to an engine that has a turbine as its power source, in whole or in part. Examples of gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, and hybrid versions of one or more of these engines.

[0019] The term "combustion section" refers to any heat addition system used in a turbine. For example, the term combustion section can refer to a section that includes one or more of a knock combustion assembly, a rotating detonation combustion assembly, a pulse detonation combustion assembly, or other suitable heat addition assembly. In some example embodiments, the combustion section may include an annular burner, a cylindrical burner, a tubular burner, a vortex burner (TVC), or other suitable combustion systems, or combinations thereof.

[0020] Unless otherwise stated, when the terms “low” and “high” or their respective comparative degrees (e.g., lower, higher, where applicable) are used with compressors, turbines, shafts, or spool components, each refers to a relative speed within the engine. For example, “low turbine” or “low-speed turbine” defines a component configured to operate at a rotational speed, such as the maximum permissible rotational speed, below that of the engine’s “high turbine” or “high-speed turbine.”

[0021] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0022] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to the centerline of the gas turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the gas turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends in an arc around the centerline of the gas turbine engine.

[0023] Unless otherwise specified herein, the terms “connection,” “fixed,” “attached to,” etc., refer to direct connection, fixation, or attachment, as well as indirect connection, fixation, or attachment via one or more intermediate components or features.

[0024] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the components.

[0025] The word “proximity” refers to being closer to one end, side, or component than to the opposite end, side, or component. For example, when used with terms like “first end” and “second end”, “proximity to the first end” means a position closer to the first end than the second end.

[0026] Generally, a gas turbine engine consists of a fan and a turbine, with the turbine driving the fan to generate thrust. The turbine includes a compressor section, a combustion section, a turbine section, and an exhaust section, which together define the core gas flow path running through it. Gas turbine engines also include thermal management systems, such as heat exchangers, for dissipating heat loads. Improvements to gas turbine engines for aircraft focus on increasing the uniformity of heat exchanger filling, thereby enhancing heat transfer efficiency.

[0027] The inventors of this disclosure seek a method for effectively cooling a hot fluid flowing through a heat exchanger. The inventors have developed a heat exchanger having a core defining at least one helical fluid path. In designing a gas turbine engine with said heat exchanger, the inventors unexpectedly discovered that, contrary to previous ideas and expectations, in at least some designs, the costs associated with introducing said heat exchanger can be offset by thermal management advantages. Specifically, in designing multiple heat exchangers for gas turbine engines (including the configurations described in detail herein), the inventors discovered a significant relationship between the diameter of the heat exchanger core, the pitch of the helical fluid path, and the axial height of the core's inlet opening. Introducing said heat exchanger according to one or more exemplary aspects described herein can result in net benefits to the overall engine design.

[0028] To obtain an improved gas turbine engine including a heat exchanger capable of providing uniform filling and enhanced heat transfer, the inventors took the following steps: designing heat exchangers for the gas turbine engine with different core diameters, pitches of helical fluid paths, and axial heights of the core inlet openings; examining the operating and heat transfer characteristics of the designed gas turbine engine heat exchangers; redesigning the gas turbine engine heat exchangers to alter the aforementioned characteristics based on their effects on other aspects of the heat exchangers and the gas turbine engine; and further examining the operating and heat transfer characteristics of the redesigned gas turbine engine heat exchangers during the design of several different types of heat exchangers (including the gas turbine engine heat exchangers described herein, which will be described in more detail below).

[0029] Figure 1 This is a schematic cross-sectional view of a gas turbine engine according to an exemplary embodiment of the present disclosure. More specifically, for Figure 1 In the embodiment shown, the gas turbine engine is a high-bypass turbofan jet engine, sometimes also referred to as a "turbofan engine." Figure 1 As shown, the gas turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline 12 for reference), a radial direction R, and a circumferential direction C extending around the longitudinal centerline 12. Generally, the gas turbine engine 10 includes a fan section 14 and a turbine 16 disposed downstream of the fan section 14.

[0030] The illustrated exemplary turbine 16 typically includes a generally tubular outer casing 18 defining an annular inlet 20. The casing 18 surrounds, in a series flow relationship: a compressor section including a turbocharger or low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24; a combustion section 26; a turbine section including a high-pressure (HP) turbine 28 and a low-pressure (LP) turbine 30; and an exhaust nozzle section 32. A high-pressure (HP) shaft 34 (additionally or optionally, a spool) drivesably connects the HP turbine 28 and the HP compressor 24. A low-pressure (LP) shaft 36 (additionally or optionally, a spool) drivesably connects the LP turbine 30 and the LP compressor 22. The compressor section, combustion section 26, turbine section, and exhaust nozzle section 32 collectively define a core gas flow path 37.

[0031] In the described embodiment, fan section 14 includes a fan 38 having a plurality of fan blades 40 spaced apart and coupled to disk 42. As shown, the fan blades 40 extend outward from disk 42 generally in a radial direction R. Each fan blade 40 is rotatable relative to disk 42 about a pitch axis P because the fan blade 40 is operatively coupled to a suitable pitch changing mechanism 44 configured to collectively change the pitch of the fan blade 40, for example, uniformly. Gas turbine engine 10 further includes a power gearbox 46, through which the fan blades 40, disk 42, and pitch changing mechanism 44 are rotatable together about a longitudinal centerline 12 via an LP shaft 36 spanning the power gearbox 46. The power gearbox 46 includes a plurality of gears for adjusting the rotational speed of fan 38 relative to LP shaft 36, thereby allowing fan 38 to rotate at a more efficient fan speed.

[0032] Still referencing Figure 1 In an exemplary embodiment, the disc 42 is covered by a rotatable front hub 48 (sometimes referred to as a "rotor") of the fan section 14. The aerodynamic shape of the front hub 48 is designed to facilitate airflow through the multiple fan blades 40.

[0033] Additionally, the exemplary fan section 14 includes an annular fan housing or outer nacelle 50 that circumferentially surrounds at least a portion of the fan 38 and / or turbine 16. It should be understood that, in the illustrated embodiment, the nacelle 50 is supported relative to the turbine 16 by a plurality of circumferentially spaced outlet guide vanes 52. Furthermore, a downstream section 54 of the nacelle 50 extends over the outer portion of the turbine 16, thereby defining a bypass airflow passage 56 therebetween.

[0034] During operation of the gas turbine engine 10, a certain amount of air 58 enters the gas turbine engine 10 through the nacelle 50 and the corresponding inlets 60 of the fan section 14. As the certain amount of air 58 flows over the fan blades 40, a first portion of air 62 is directed or diverted to the bypass airflow passage 56, and a second portion of air 64 (as indicated by arrow 64) is directed or diverted to the core gas flow path 37, or, more specifically, to the LP compressor 22. The ratio between the first portion of air 62 and the second portion of air 64 is commonly referred to as the bypass ratio. As the second portion of air 64 is diverted through the HP compressor 24 and enters the combustion section 26, its pressure increases, where it mixes with fuel and burns to produce combustion gases 66.

[0035] Combustion gas 66 is guided through HP turbine 28, where a portion of the thermal and / or kinetic energy from the combustion gas 66 is extracted via a successive stage of HP turbine stator blades 68 connected to housing 18 and HP turbine rotor blades 70 connected to HP shaft 34, thereby causing HP shaft 34 to rotate and thus supporting the operation of HP compressor 24. Combustion gas 66 is then guided through LP turbine 30, where a second portion of the thermal and kinetic energy is extracted from the combustion gas 66 via a successive stage of LP turbine stator blades 72 connected to housing 18 and LP turbine rotor blades 74 connected to LP shaft 36, thereby causing LP shaft 36 to rotate and thus supporting the operation of LP compressor 22 and / or the rotation of fan 38.

[0036] Combustion gas 66 is then guided through the injection exhaust nozzle section 32 of turbine 16 to generate propulsive thrust. Simultaneously, as the first portion of air 62 is guided through bypass airflow passage 56 before exiting the fan nozzle exhaust section 76 of gas turbine engine 10, its pressure increases significantly, also generating propulsive thrust. HP turbine 28, LP turbine 30, and injection exhaust nozzle section 32 together define a hot gas path 78 for guiding combustion gas 66 through turbine 16.

[0037] Still referencing Figure 1In at least one exemplary embodiment (such as the exemplary embodiment shown in the figures), the gas turbine engine 10 includes a thermal management system 100. The thermal management system 100 is configured to provide lubricant to various bearings and gear meshes in, for example, the compressor section (including LP compressor 22 and HP compressor 24), the turbine section (including HP turbine 28 and LP turbine 30), HP shaft 34, LP shaft 36, and the power gearbox 46. The lubricant provided by the thermal management system 100 extends the service life of these components and removes a certain amount of heat from them. Furthermore, fuel acts as a radiator, absorbing heat from the lubricant and cooling it. Additionally, or alternatively, a hot fluid (e.g., water glycol and supercritical carbon dioxide (CO2)) is used as a radiator to cool the lubricant.

[0038] Figure 2 This is a perspective view of a heat exchanger 200 according to an exemplary aspect of this disclosure. More specifically, the heat exchanger 200 is incorporated into... Figure 1 The thermal management system 100 of the gas turbine engine 10 shown.

[0039] The heat exchanger 200 includes a core 205 extending along an axial centerline 210 in the axial direction A′ between a first end 201 and a second end 202 opposite to the first end 201. Figure 2 As shown, the core 205 is defined as cylindrical. Additionally, the core 205 of the heat exchanger 200 is configured to receive a first fluid 235 and a second fluid 240. The first fluid 235 enters the core 205 through a first fluid inlet 245 defined by a second end 202 of the core 205 and exits the core 205 through a first fluid outlet 250 defined by a first end 201 of the core 205.

[0040] The heat exchanger 200 includes a fluid inlet manifold 215 and a fluid outlet manifold 220. The fluid inlet manifold 215 is fluidly connected to a first end 201 of the core 205, and the fluid outlet manifold 220 is fluidly connected to a second end 202 of the core 205. Both the fluid inlet manifold 215 and the fluid outlet manifold 220 are cylindrical in shape and extend annularly around the core 205, such that the fluid inlet manifold 215 is a first annular manifold and the fluid outlet manifold 220 is a second annular manifold. For example, the fluid inlet manifold 215 surrounds or encloses the first end 201 of the core 205, and the fluid outlet manifold 220 surrounds or encloses the second end 202 of the core 205. Furthermore, the heat exchanger 200 includes a second fluid inlet 225 in fluid communication with the fluid inlet manifold 215 and a second fluid outlet 230 in fluid communication with the fluid outlet manifold 220. The second fluid inlet 225 and the second fluid outlet 230 include one or more pipes or conduits.

[0041] The second fluid 240 enters the fluid inlet manifold 215 through the second fluid inlet 225. The fluid inlet manifold 215 is in fluid communication with the core 205 and distributes the second fluid 240 to one or more fluid channels within the core 205, such as... Figures 3A-4B As shown. The fluid outlet manifold is also in fluid communication with the core 205, so that the second fluid 240 flows from the fluid inlet manifold 215 through the core 205 to the fluid outlet manifold 220, and then the second fluid 240 leaves the heat exchanger 200 through the second fluid outlet 230.

[0042] The first fluid 235 is configured to exchange heat with the second fluid 240. For example, the first fluid 235 is configured to absorb heat from the second fluid 240 within the core 205, such that the first fluid 235 leaving the core 205 through the first fluid outlet 250 is hotter than the first fluid 235 entering the core 205 through the first fluid inlet 245, and the second fluid 240 leaving the heat exchanger 200 through the fluid outlet manifold 220 is colder than the second fluid 240 entering through the fluid inlet manifold 215. Alternatively, the second fluid 240 is configured to absorb heat from the first fluid 235 within the core 205, such that the second fluid 240 leaving through the fluid outlet manifold 220 is hotter than the second fluid 240 entering through the fluid inlet manifold 215, and the first fluid 235 leaving the core 205 through the first fluid outlet 255 is colder than the first fluid 235 entering the core 205 through the first fluid inlet 245. In at least one exemplary embodiment, the first fluid 235 and the second fluid 240 are different. For example, the first fluid 235 may contain fuel, while the second fluid 240 may contain oil; or, the first fluid 235 may contain oil, while the second fluid 240 may contain fuel. In other exemplary embodiments, the first fluid 235 and the second fluid 240 may be the same.

[0043] Figure 3A This is an exemplary aspect of the present disclosure. Figure 2 An internal view of the core 205 of the heat exchanger 200 shown reveals a first fluid domain 300 comprising multiple fluid paths 310. Figure 3B This is an exemplary aspect of the present disclosure. Figure 2 An internal view of the core 205 of the heat exchanger 200 shown reveals the second fluid domain 305.

[0044] The core component 205 includes a lattice structure defining a first fluid domain 300 and a second fluid domain 305 fluidly isolated from the first fluid domain 300. The first fluid domain 300 includes a first fluid path, and the second fluid domain 305 includes a second fluid path fluidly isolated from the first fluid path of the first fluid domain 300. More specifically, as Figure 3AAs shown, the first fluid domain 300 includes a plurality of fluid paths 310 extending along an axial centerline 210 from a first fluid inlet 245 at a second end 202 to a first fluid outlet 250 at a first end 201. Each of the plurality of fluid paths 310 is configured to receive a first fluid 235 ( Figure 1 ).

[0045] like Figure 3B As shown, the second fluid domain 305 includes one or more helical fluid channels 315. Each of the one or more helical fluid channels 315 is defined and fluid-isolated by one or more boundary walls (such as one or more helical walls 320) having a helical shape. The one or more helical fluid channels 315 and the one or more helical walls 320 extend from the first end 201 to the second end 202 about an axial centerline 210. (Reference) Figure 3B When viewed from the first end 201, the second fluid domain 305 comprises four of one or more helical fluid channels 315 defined by four of four of one or more helical walls 320. Although Figure 3B Only four of the one or more helical fluid channels 315 are shown, but it should be understood that the core 205 may define any number of helical fluid channels. For example, in some exemplary embodiments, the one or more helical fluid channels 315 include one to twenty helical fluid channels. More specifically, the one or more helical fluid channels 315 include four to eight helical fluid channels.

[0046] Furthermore, each of the one or more helical fluid channels 315 defines a helix angle 325. The helix angle 325 is defined between each of the one or more helical fluid channels 315 and the axial centerline 210. For example, the helix angle 325 is defined between one or more helical walls 320 and the axial centerline 210. The selection of the helix angle 325 is based on the number of the one or more helical fluid channels 315 and the desired hydrodynamic characteristics. For example, the helix angle 325 is greater than zero (0) and less than... .

[0047] Figure 4A This is an exemplary aspect of the present disclosure. Figure 2 The cross-sectional view of the heat exchanger 200 shown illustrates the first fluid domain 300. Figure 4B This is an exemplary aspect of the present disclosure. Figure 2 The cross-sectional view of the heat exchanger 200 shown illustrates the second fluid domain 305. More specifically, Figure 4A The flow of the first fluid 235 along the axial centerline 210 from the second end 202 through the core 205 to the first end 201 is shown. Figure 4BThe diagram shows one or more spiral fluid channels 315 along the axial centerline 210 from the first end 201 through the core 205 to the second end 202.

[0048] like Figures 4A-4B As shown, the core 205 of the heat exchanger 200 defines a diameter 405 perpendicular to the axial centerline 210. The diameter 405 is greater than or equal to 20 mm and less than or equal to 300 mm. More specifically, the diameter 405 is greater than or equal to 50 mm and less than or equal to 200 mm. The core 205 also defines a length 410 extending parallel to the axial centerline 210 between a first end 201 and a second end 202. The length 410 is greater than or equal to 50 mm and less than or equal to 1500 mm. The diameter 405 of the core 205 remains constant along the length 410 extending from the first end 201 to the second end 202 of the core 205.

[0049] Furthermore, core 205 defines an inlet opening 415 in fluid communication with a fluid inlet manifold 215, and more specifically, in fluid communication with one or more helical fluid channels 315. The inlet opening 415 is an annular opening disposed in core 205 adjacent to the first end 201 and in fluid communication with the fluid inlet manifold 215. For example, the inlet opening 415 extends about the diameter of core 205 adjacent to the first end 201. The inlet opening 415 defines an axial height 420 extending parallel to the axial centerline 210. Figure 4A As shown, the axial height 420 is along the axial direction A′ ( Figure 2 The length of the inlet opening 415 is measured. The axial height 420 is greater than or equal to 10 mm and less than or equal to 900 mm. More specifically, the axial height 420 is greater than or equal to 25 mm and less than or equal to 300 mm.

[0050] Additionally, the fluid outlet manifold 220 defines a fluid outlet opening 425 in fluid communication with the core 205, and more specifically, in fluid communication with one or more helical fluid channels 315. The fluid outlet opening 425 is an annular opening disposed in the core 205 adjacent to the second end 202, such that the fluid outlet opening 425 extends about the diameter of the core 205 adjacent to the second end 202. Furthermore, the fluid outlet opening 425 defines an axial height similar to or similar to the axial height 420 of the inlet opening 415. For example, the axial height of the fluid outlet opening 425 is along the axial direction A′ (…). Figure 2 The length of the fluid outlet opening 425 is measured.

[0051] As previously mentioned, during the design of heat exchangers for gas turbine engines—specifically, designing heat exchangers for gas turbine engines with different core diameters, helical fluid path pitches, and axial heights of the core inlet openings, and evaluating overall engine and heat transfer performance—the inventors unexpectedly discovered a significant relationship between the core diameter, helical fluid path pitch, and axial height of the core inlet opening. This relationship indicates that the heat exchanger for a gas turbine engine can enhance heat transfer with a second fluid by uniformly filling the core of the heat exchanger with a first fluid. Uniform distribution of the first and / or second fluids within the heat exchanger can enhance heat transfer between the first and second fluids.

[0052] Specifically, the inventors have discovered that for a heat exchanger defining a first fluid domain and a second fluid domain, and defining one or more helical fluid channels for either the first or second fluid domain, the helical fluid channels can guide fluid flow to prevent uneven distribution. Uneven fluid flow distribution is caused by the difference between the size of the inlet opening of the fluid inlet manifold and the length of the heat exchanger's core. Therefore, relating the axial height of the inlet opening of the fluid inlet manifold to the pitch of one or more helical fluid channels can improve the uniform filling of the core and heat transfer within the core, thereby meeting the specific requirements of gas turbine engines.

[0053] Therefore, the discovered relationships described below can be used to identify a heat exchanger for a gas turbine engine having one or more helical fluid channels that enable uniform filling and improved heat transfer, and is suitable for specific mission requirements that take into account efficiency, weight, heat capacity requirements, complexity, reliability, and other factors that influence the optimal selection of a heat exchanger for a gas turbine engine having one or more helical fluid channels.

[0054] In addition to yielding an improved heat exchanger for a gas turbine engine with one or more helical fluid channels, as detailed above, the inventors have discovered that this relationship significantly reduces the number of heat exchanger designs for gas turbine engines that meet the aforementioned design requirements. This facilitates faster selection of heat exchanger designs (with one or more helical fluid channels) for gas turbine engines under development. This advantage allows for a deeper understanding of the specific heat exchanger requirements for a particular gas turbine engine before the specific technology, integration, and system requirements are fully determined. This advantage avoids the need for later redesign.

[0055] The improved gas turbine engine discovered by the inventors is based on a heat exchanger relationship, which can be expressed as:

[0056]

[0057] Generally, the heat exchanger relationship involves the axial height h of the inlet opening 415 of the fluid inlet manifold 215, the pitch P of one or more helical fluid channels 315, and the diameter D of the heat exchanger 200. The axial height h is... Figures 4A-4B The inlet opening 415 of the fluid inlet manifold 215 of the heat exchanger 200 discussed herein has an axial height 420. The axial height h is greater than or equal to 10 mm and less than or equal to 900 mm. More specifically, the axial height h is greater than or equal to 25 mm and less than or equal to 300 mm.

[0058] Diameter D is Figures 4A-4B The core 205 of the heat exchanger 200 discussed herein has a diameter 405. The diameter 405 is greater than or equal to 20 mm and less than or equal to 300 mm. More specifically, the diameter 405 is greater than or equal to 50 mm and less than or equal to 200 mm. Furthermore, the pitch P refers to the height of one or more spiral fluid channels 315 completing a full turn, measured parallel to the axial centerline 210. If one or more spiral fluid channels 315 do not form a complete turn, the pitch P is determined by assuming the one or more spiral fluid channels 315 extend to a complete turn. The pitch P is greater than or equal to 10 mm and less than or equal to 900 mm. More specifically, the pitch P is greater than or equal to 50 mm and less than or equal to 600 mm.

[0059] To achieve uniform filling of the core 205 of the heat exchanger 200, the axial height h is equal to the lateral flow area of ​​one or more helical fluid channels 315. The lateral flow area of ​​the one or more helical fluid channels 315 is based on the helix angle α, which is related to... Figure 3B The helix angle 325 discussed earlier is the same. Therefore, the relationship between the axial height h and the transverse flow area of ​​one or more helical fluid channels 315 can be expressed as follows:

[0060]

[0061] Furthermore, the helix angle α can be expressed as follows:

[0062]

[0063] Using formulas (2)-(3), the ratio of axial height h to diameter D can be expressed as follows:

[0064]

[0065] The ratio of axial height h to diameter D (expressed as...) The ratio is greater than 0 and less than 3.1. More specifically, the ratio... Greater than 0.5 and less than 1.5. Below the ratio. The range of values ​​will result in the axial height 420 being less than the lateral flow area of ​​one or more spiral fluid channels 315, which will lead to flow diffusion and failure to provide uniform filling for the heat exchanger 200.

[0066] Based on fluid dynamics principles, the helix angle α is greater than or equal to 0 and less than or equal to... Therefore, using the above formula (3), the ratio of pitch P to diameter D (expressed as...) This can be represented as follows:

[0067]

[0068] More specifically, ratio Greater than 0 and less than 3.3. For example, the ratio. Greater than 1 and less than 3. When the helix angle α and the ratio When the specified range is exceeded, one or more spiral fluid channels 315 cannot achieve uniform filling. More specifically, when the spiral angle α and the ratio... When the fluid exceeds the specified range, it only partially fills the core 205.

[0069] Furthermore, one or more helical fluid channels 315 are only effective when the axial height h is equal to the pitch P. For example, if the axial height h exceeds the pitch P, uniform filling cannot be achieved due to fluid diffusion. Therefore, based on the diameter D, the following limitations can be derived:

[0070]

[0071] Furthermore, for a given diameter D, reducing the pitch P can reduce the axial height h. Therefore, using formula (4), the pitch P of one or more helical fluid channels 315 can be selected according to the diameter D to meet specific requirements, such as the size of the heat exchanger 200 of a specific gas turbine engine.

[0072] Table 1 below lists the various heat exchanger characteristic values ​​of a gas turbine engine as defined by formulas (1)-(6):

[0073]

[0074] Figure 5 Chart 500 is provided, which depicts the ratio of axial height h to diameter D (expressed as...). The ratio of pitch P to diameter D (expressed as...) The relationship is shown in Figure 500. For example, Figure 500 provides the ratio on the X-axis at 505. The ratio on the Y-axis at 510 Chart 500 includes a first line 515, representing the relationship expressed in formula (4) above. Chart 500 includes a second line 520, representing the relationship expressed in formula (5) above. Chart 500 also includes a third line 525, representing the relationship expressed in formula (6) above. Furthermore, Chart 500 provides a first range 530 between the first line 515, the second line 520, and the third line 525. Within the first range 530, the ratio... The ratio is greater than or equal to 0.5 and less than or equal to 3.3, and the ratio is... Greater than or equal to 0 and less than or equal to 3.1.

[0075] Additionally, chart 500 includes a fourth line 535 and a fifth line 540, which define the ratio. The second range is 545. As shown in the figure, the ratio... Greater than or equal to 1 and less than or equal to 3. Chart 500 contains the sixth line 555 and the seventh line 560, which define the ratio. The third range is 565. As shown in the figure, the ratio... Greater than or equal to 0.5 and less than or equal to 1.5. Furthermore, chart 500 provides a fourth range 570 between the third line 525, the fourth line 535, the fifth line 540, the sixth line 555, and the seventh line 560. Within this fourth range 570, the ratio... Greater than or equal to 1 and less than or equal to 3, and the ratio Greater than or equal to 0.5 and less than or equal to 1.5.

[0076] Values ​​exceeding the first range 530 and the fourth range 570 only partially fill the core 205, causing flow diffusion and thus hindering uniform filling of the core 205. Therefore, this disclosure provides a heat exchanger for a gas turbine engine, the heat exchanger comprising a first fluid domain and a second fluid domain fluidly isolated from the first fluid domain, the first fluid domain for receiving a first fluid and the second fluid domain for receiving a second fluid. The first or second fluid domain includes a plurality of helical fluid channels that enable uniform filling of the heat exchanger, thereby improving heat transfer between the first fluid in the first fluid domain and the second fluid in the second fluid domain.

[0077] Further details are provided by the following topics:

[0078] A heat exchanger for a gas turbine engine, the heat exchanger comprising: a core extending in an axial direction between the first end and the second end, the second end being opposite to the first end; the core defining a first fluid domain and a second fluid domain fluidly isolated from the first fluid domain; wherein the second fluid domain defines one or more helical fluid channels, wherein the one or more helical fluid channels define a pitch (P) measured in millimeters (mm); wherein the core defines a diameter (D) extending perpendicular to the axial direction, measured in mm; a fluid inlet manifold fluidly connected to the first end of the core and in fluid communication with each of the one or more helical fluid channels of the second fluid domain, the fluid inlet manifold defining an inlet opening having an axial height (h) extending in the axial direction, measured in mm; and a fluid outlet manifold fluidly connected to the second end of the core and in fluid communication with the second fluid domain; wherein... ; and among them Less than .

[0079] According to any of the preceding items, the heat exchanger wherein Greater than 0 and less than 3.3.

[0080] According to any of the preceding items, the heat exchanger wherein Greater than 1 and less than 3.

[0081] According to any of the preceding items, the heat exchanger wherein Greater than 0.5 and less than 3.1.

[0082] According to any of the preceding items, the heat exchanger wherein Greater than 0.5 and less than 1.5.

[0083] According to any of the preceding items, the heat exchanger wherein the axial height (h) is greater than or equal to 10 mm and less than or equal to 900 mm.

[0084] According to any of the preceding items, the heat exchanger wherein the axial height (h) is greater than or equal to 25 mm and less than or equal to 300 mm.

[0085] According to any of the preceding items, the heat exchanger has a diameter (D) greater than or equal to 20 mm and less than or equal to 300 mm.

[0086] According to any of the preceding items, the heat exchanger has a diameter (D) greater than or equal to 50 mm and less than or equal to 200 mm.

[0087] According to any of the preceding items, the heat exchanger wherein the pitch (P) is greater than or equal to 10 mm and less than or equal to 900 mm.

[0088] According to any of the preceding items, the heat exchanger wherein the pitch (P) is greater than or equal to 50 mm and less than or equal to 600 mm.

[0089] According to any of the preceding items, in a heat exchanger, wherein the one or more helical fluid channels define a helical angle (α), wherein ; and among them .

[0090] According to any of the preceding items, the heat exchanger wherein the core includes one or more spiral walls that are fluidly isolated from the first fluid domain and the second fluid domain.

[0091] According to any of the preceding items, each of the one or more spiral walls has a spiral shape defining the one or more spiral fluid channels.

[0092] According to any of the preceding items, the heat exchanger includes 4 to 8 spiral fluid channels.

[0093] According to any of the preceding items, the heat exchanger includes one or more helical fluid channels comprising four helical fluid channels.

[0094] The heat exchanger according to any of the preceding items further includes at least one fluid inlet in fluid communication with the fluid inlet manifold and at least one fluid outlet in fluid communication with the fluid outlet manifold.

[0095] According to any of the preceding claims, the fluid inlet manifold is a first annular manifold surrounding the first end of the core, and the fluid outlet manifold is a second annular manifold surrounding the second end of the core.

[0096] According to any of the preceding claims, in a heat exchanger, the second end of the core defines a first fluid inlet configured to receive a first fluid, and the first end of the core defines a first fluid outlet, the first fluid inlet and the first fluid outlet being in fluid communication with the first fluid domain.

[0097] According to any of the preceding items, the heat exchanger wherein the first fluid domain extends in the axial direction between the first end and the second end of the core.

[0098] According to any of the preceding items, the heat exchanger wherein the core defines a cylindrical shape.

[0099] According to any of the preceding claims, the heat exchanger wherein the core defines a lattice structure that defines the first fluid domain and the second fluid domain.

[0100] A gas turbine engine includes: a turbine comprising a compressor section, a combustion section, and a turbine section in a series flow sequence and at least partially defining a core gas flow path; a heat exchanger comprising: a core extending in an axial direction between the first end and the second end, the second end being opposite to the second end, the core defining a first fluid domain and a second fluid domain fluidly isolated from the first fluid domain, wherein the second fluid domain defines one or more helical fluid channels, wherein the one or more helical fluid channels define a pitch (P) measured in millimeters (mm), wherein the core defines a diameter (D) extending perpendicular to the axial direction, measured in mm; a fluid inlet manifold fluidly connected to the first end of the core and in fluid communication with each of the one or more helical fluid channels of the second fluid domain, the fluid inlet manifold defining an inlet opening having an axial height (h) extending in the axial direction, measured in mm; and a fluid outlet manifold fluidly connected to the second end of the core and in fluid communication with the second fluid domain; wherein ;in Greater than 0 and less than 3.3; and where Less than .

[0101] According to any of the preceding items, the gas turbine engine, wherein the core includes one or more helical walls, the one or more helical walls being fluidly isolated from the first fluid domain and the second fluid domain.

[0102] According to any of the preceding items, in a gas turbine engine, each of the one or more spiral walls has a spiral shape defining one or more spiral fluid passages.

[0103] According to any of the preceding items, the gas turbine engine, wherein the one or more helical fluid passages include 4 to 8 helical fluid passages.

[0104] According to any of the preceding items, the gas turbine engine, wherein the one or more helical fluid passages include four helical fluid passages.

[0105] The gas turbine engine according to any of the preceding items further includes at least one fluid inlet in fluid communication with the fluid inlet manifold and at least one fluid outlet in fluid communication with the fluid outlet manifold.

[0106] According to any of the preceding items, in the gas turbine engine, the fluid inlet manifold is a first annular manifold surrounding the first end of the core, and the fluid outlet manifold is a second annular manifold surrounding the second end of the core.

[0107] According to any of the preceding claims, in a gas turbine engine, the second end of the core defines a first fluid inlet configured to receive a first fluid, and the first end of the core defines a first fluid outlet, the first fluid inlet and the first fluid outlet being in fluid communication with the first fluid domain.

[0108] According to any of the preceding items, in the gas turbine engine, the first fluid domain extends in the axial direction between the first end and the second end of the core.

[0109] The gas turbine engine according to any of the preceding items, wherein the core is defined as cylindrical.

[0110] According to any of the preceding items, in a gas turbine engine, wherein the core defines a lattice structure that defines the first fluid domain and the second fluid domain.

[0111] According to any of the preceding claims, in a gas turbine engine, wherein the one or more helical fluid passages define a pitch (P) measured in mm, wherein the core defines a diameter (D) extending perpendicular to the axial direction measured in mm; and the fluid inlet manifold defines an inlet opening having an axial height (h) extending in the axial direction measured in millimeters (mm). ;and Less than or equal to .

[0112] According to any of the preceding items, the gas turbine engine, wherein Greater than 0 and less than 3.3.

[0113] According to any of the preceding items, the gas turbine engine, wherein Greater than or equal to 0.5 and less than or equal to 3.1.

[0114] According to any of the preceding items, the gas turbine engine, wherein Greater than or equal to 0.5 and less than or equal to 1.5.

[0115] The gas turbine engine according to any of the preceding items, wherein the axial height (h) is greater than or equal to 10 mm and less than or equal to 900 mm.

[0116] The gas turbine engine according to any of the preceding items, wherein the axial height (h) is greater than or equal to 25 mm and less than or equal to 300 mm.

[0117] The gas turbine engine according to any of the preceding items, wherein the diameter (D) is greater than or equal to 20 mm and less than or equal to 300 mm.

[0118] The gas turbine engine according to any of the preceding items, wherein the diameter (D) is greater than or equal to 50 mm and less than or equal to 200 mm.

[0119] The gas turbine engine according to any of the preceding items, wherein the pitch (P) is greater than or equal to 10 mm and less than or equal to 900 mm.

[0120] The gas turbine engine according to any of the preceding items, wherein the pitch (P) is greater than or equal to 50 mm and less than or equal to 600 mm.

[0121] According to any of the preceding items, in the gas turbine engine, wherein the one or more helical fluid passages define a helical angle ( ),in ; and among them .

[0122] This specification uses examples to disclose this disclosure, including best practices, and to enable those skilled in the art to implement this disclosure, including making and using any apparatus or system and performing any of the included methods. The patentable scope of this disclosure is defined by the claims, but may include other examples that would occur to those skilled in the art. Such other examples shall be considered to be included within the scope of the claims if they contain structural elements that are not different from the literal language of the claims, or if they contain equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A heat exchanger for a gas turbine engine, characterized by, The heat exchanger includes: The core extends in an axial direction between a first end and a second end, the second end being opposite to the second end. The core defines a first fluid domain and a second fluid domain fluidly isolated from the first fluid domain. The second fluid domain defines one or more helical fluid channels, wherein the one or more helical fluid channels define a pitch (P) measured in millimeters (mm). The core defines a diameter (D) extending perpendicular to the axial direction, measured in millimeters. A fluid inlet manifold, fluidly connected to the first end of the core and fluidly communicating with each of the one or more helical fluid channels in the second fluid domain, the fluid inlet manifold defining an inlet opening having an axial height (h) extending in the axial direction, measured in mm; and A fluid outlet manifold, which is fluidly connected to the second end of the core and fluidly communicates with the second fluid domain; wherein ; and wherein less than .

2. The heat exchanger of claim 1, wherein wherein greater than 0 and less than 3.

3.

3. The heat exchanger of claim 1, wherein wherein greater than 0.5 and less than 3.

1.

4. The heat exchanger of claim 1, wherein in Greater than 0.5 and less than 1.

5.

5. The heat exchanger of claim 1, wherein The axial height (h) is greater than or equal to 10 mm and less than or equal to 900 mm.

6. The heat exchanger of claim 1, wherein The axial height (h) is greater than or equal to 25 mm and less than or equal to 300 mm.

7. The heat exchanger of claim 1, wherein The diameter (D) is greater than or equal to 20 mm and less than or equal to 300 mm.

8. The heat exchanger of claim 1, wherein, The diameter (D) is greater than or equal to 50 mm and less than or equal to 200 mm.

9. The heat exchanger according to claim 1, characterized in that, The pitch (P) is greater than or equal to 10 mm and less than or equal to 900 mm.

10. The heat exchanger of claim 1, wherein in, The pitch (P) is greater than or equal to 50 mm and less than or equal to 600 mm.

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