Crossflow heat exchanger, turbomachine and heat exchanger manufacturing process

Abstract

Crossflow heat exchanger, turbomachine and method of manufacturing the exchanger Crossflow heat exchanger (100) for aeronautical turbomachine configured to exchange heat between a first fluid and a second fluid, comprising: two or more sub-circuits (10) forming a first circuit configured to receive the first fluid (1), said sub-circuits (10) each extending mainly between a respective inlet (10A) and outlet (10E) in a first direction (X), said sub-circuits (10) being fluidically independent; the inlets (10A) and outlets (10E) of said sub-circuits (10) being positioned on a first face (F1) of the exchanger; said sub-circuits (10) being delimited by walls (12,14) configured to effect a heat exchange between the first fluid (1) inside said sub-circuits (10) and the second fluid (2) outside said sub-circuits (10). Figure for the abbreviation: Fig. 2A.

Description

Title of the invention: Cross-flow heat exchanger, turbomachine and method for manufacturing the exchanger. Technical field

[0001] The present disclosure relates to cross-flow heat exchangers, in particular a multi-pass cross-flow heat exchanger. Prior art

[0002] Climate change is a major concern for many legislative and regulatory bodies worldwide. Indeed, various restrictions on carbon emissions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies to both new types of aircraft and those already in service, requiring the implementation of technological solutions to bring them into compliance with current regulations. Civil aviation has been actively working for several years now to contribute to the fight against climate change.

[0003] Technological research efforts have already led to very significant improvements in the environmental performance of aircraft. The Applicant takes into account the impactful factors in all phases of design and development in order to obtain aeronautical components and products that are less energy-intensive, more environmentally friendly, and whose integration and use in civil aviation have moderate environmental consequences, with the aim of improving the energy efficiency of aircraft.

[0004] Consequently, the Applicant is constantly working to reduce its negative climate impact by using methods and operating virtuous development and manufacturing processes that minimize greenhouse gas emissions to the minimum possible in order to reduce the environmental footprint of its activity.

[0005] This sustained research and development work focuses on both new generations of aircraft engines and the weight reduction of aircraft, particularly through the materials used and lighter on-board equipment.

[0006] To this end, the invention is the result of technological research aimed at significantly improving aircraft performance and, in this sense, contributes to reducing the environmental impact of aircraft. For this purpose, the invention relates to a multi-pass cross-flow heat exchanger, in which the fluid circulation circuits have sinuosities that increase the time the fluid spends within the exchanger, and thus increases the thermal efficiency of the exchanger.

[0007] However, increasing the thermal efficiency of the exchanger through these sinuosities may come at the expense of increased pressure losses.

[0008] There is therefore a need for a heat exchanger offering a better compromise between thermal efficiency and pressure losses. Description of the invention

[0009] The present exposition aims to remedy at least some of these drawbacks.

[0010] To this end, the present exposition relates to a cross-flow heat exchanger for an aeronautical turbomachine, configured to exchange heat between a first fluid and a second fluid, comprising: two or more sub-circuits forming a first circuit configured to receive the first fluid, said sub-circuits each extending mainly between a respective inlet and outlet in a first direction, said sub-circuits being fluidly independent; the inputs and outputs of said sub-circuits being positioned on one face of the exchanger; said sub-circuits being delimited by walls configured to achieve heat exchange between the first fluid inside said sub-circuits and the second fluid outside said sub-circuits.

[0011] Hereafter, and unless otherwise indicated, "a" or "1" element (e.g., branch, sub-circuit, etc.) means "at least one" or "each" element. Conversely, the generic use of the plural may include the singular. Hereafter, and unless otherwise indicated, "a plurality" means "at least two".

[0012] By "direction" (in English, "direction") we mean an unoriented axis, and by "orientation" we mean an orientation along an oriented axis.

[0013] Typically, the first direction is the general flow direction of the first fluid in the sub-circuit of the first circuit.

[0014] The terms "inlet" and "outlet" are used in relation to the direction of fluid flow; a conduit or collector is understood to "extend" in a direction when it allows the flow of gas in that direction, regardless of the shape of the cross-section and dimensions in other directions.

[0015] By fluidly independent, it is meant that the sub-circuits do not communicate fluidly with each other, that is to say that in a normal operating mode a fluid entering through the inlet of a sub-circuit can only exit through the outlet of said sub-circuit.

[0016] Such an exchanger lacks a common collection zone or a first fluid collection box inside the exchanger, typically intended to collect the fluid flowing in a given direction and sense in order to redirect it, resulting in significant edge effects and pressure losses.

[0017] Such an exchanger thus presents a reduced volume, a reduction in the risks of poor fluid distribution and a reduction in pressure losses.

[0018] Such an exchanger thus exhibits improved thermal performance for given dimensions and operating conditions.

[0019] Moreover, this structure is particularly suited to additive manufacturing, for example by selective powder bed fusion.

[0020] Typically, the walls extend in a plane comprising the first direction and a second direction perpendicular to the first direction so as to obstruct a movement of the second fluid along a third direction perpendicular to the first and second directions.

[0021] Typically, the second direction is the general flow direction of the second fluid within the exchanger.

[0022] Typically, the walls allow the second fluid to be directed along the second direction.

[0023] Typically, the walls have on the side of the first circuit the first fins, preferably extending along the first direction.

[0024] The first fins help to direct the first fluid in the first direction. The first fins help to improve the efficiency of heat exchange between the first fluid and the exchange walls, and thus between the first fluid and the second fluid, while reducing pressure losses.

[0025] Typically, the exchanger includes channels of a second circuit configured to receive the second fluid, said sub-circuits being separated by all or part of the channels.

[0026] Typically, said sub-circuits are successively arranged along the second direction.

[0027] Typically, the walls have second fins (secondary exchange surfaces) on the side of the second circuit, preferably extending along the second flow direction.

[0028] The second fins help to direct the second fluid along the second flow direction. The second fins help to improve the efficiency of heat exchange between the second fluid and the exchange walls, and thus between the first fluid and the second fluid, while reducing pressure losses.

[0029] More generally, the use of fins increases the exchange surface area and thus improves the performance of the heat exchanger. The fins allow Furthermore, improved control of fluid flow near the walls further enhances fluid distribution. The fins also improve the thermomechanical resistance of the heat exchanger under high-pressure fluid flow conditions.

[0030] Typically, viewed in a cross-section, each sub-circuit comprises a conduit in the general shape of a U extending between the inlet and the outlet of the sub-circuit.

[0031] Typically, the generally U-shaped conduit comprises an inlet branch extending from the inlet and an outlet branch opening onto the outlet.

[0032] Typically, channels of the second circuit are formed between the input and output of the same sub-circuit, typically between the input branch and the output branch of the same sub-circuit.

[0033] Typically, channels of the second circuit are formed between the input and output of adjacent subcircuits, typically between the input branch and the output branch of two adjacent subcircuits.

[0034] The U-shaped design features an elbow that reduces pressure losses, particularly compared to exchangers with a common collector for the inlet and outlet branches.

[0035] Typically, the inputs and outputs of adjacent subcircuits are arranged alternately. Typically, the input and output branches of adjacent subcircuits are arranged alternately.

[0036] This alternative arrangement allows the second fluid to always be in contact with a part of the sub-circuit towards the inlet, that is to say, to always be in contact with the first fluid in its coldest state if the first fluid is a refrigerant fluid, or in its hottest state if the first fluid is a fluid to be heated.

[0037] Typically, the inputs of consecutive subcircuits are arranged consecutively and the outputs of consecutive subcircuits are arranged consecutively. Typically, the input branches of consecutive subcircuits are arranged consecutively and the output branches of consecutive subcircuits are arranged consecutively.

[0038] This consecutive arrangement makes it easier to distribute the first fluid to the inlets and to collect the first fluid from the outlets of the first fluid.

[0039] Typically, the sub-circuits extend along the first direction of the exchanger over a distance greater than 90% of the length of the exchanger along the first direction, typically greater than 95%.

[0040] Typically, the sub-circuits have mechanical reinforcements opposite the first face.

[0041] Typically, mechanical reinforcements include support arches.

[0042] The arches provide mechanical reinforcement without significantly disrupting the circulation of the first fluid.

[0043] Typically, the exchanger includes a manifold configured to split an incoming flow and an outgoing flow to and from the sub-circuits.

[0044] Typically, the exchanger includes a collector configured to split an incoming flow and an outgoing flow to and from adjacent sub-circuits.

[0045] Typically, the collector includes walls having an angle of less than 45° with the first direction.

[0046] Such an angle makes it possible to limit the deflection of the second gas flow at the inlet and outlet of the walls, and to reduce pressure losses compared to known solutions having angles close to 90°.

[0047] The invention also relates to an aeronautical turbomachine comprising a heat exchanger according to the invention.

[0048] Typically, the first circuit is connected to at least one of a turbomachine compressor and a combustion chamber, for example an area located between a compressor outlet and a combustion chamber inlet, and the second circuit is connected on the one hand to a turbine, typically downstream, and on the other hand to an exhaust nozzle.

[0049] Typically, the first circuit is connected to a lubrication circuit and the second circuit is connected to a secondary air stream or a third stream, and an exhaust nozzle.

[0050] The invention also relates to a method for manufacturing a heat exchanger for an aeronautical turbomachine according to the invention comprising at least one powder bed additive manufacturing step. Brief description of the drawings

[0051] Other features and advantages of the subject matter of this presentation will become apparent from the following description of embodiments, given by way of non-limiting examples, with reference to the attached figures.

[0052] [Fig-1] The [Fig. 1] is a cutaway perspective view of a crossflow heat exchanger.

[0053] [Fig.2A] The [Fig.2A] is a schematic view along the section plane II-II of the [Fig.1].

[0054] [Fig.2B] The [Fig.2B] is a schematic view corresponding to the view of the [Fig.2A] where the direction of circulation of the first fluid is modified.

[0055] [Fig.3] The [Fig.3] is an enlargement of part III of the [Fig.2A].

[0056] [Fig.4] [Fig.4] is an enlarged perspective view of part IV of [Fig.1].

[0057] [Fig. 5] Fig. 5 is a perspective view of an example of inlet ducts and exit.

[0058] [Fig.6] Fig.6 is a schematic representation of the integration of the heat exchanger crossflow in a turbomachine. Description of the implementation methods

[0059] Fig. 1 represents a cutaway view of a crossflow heat exchanger 100, hereinafter referred to as the "exchanger".

[0060] In the cutaway view of [Fig.1], some sub-circuits 10 are not shown for the purpose of visualizing the internal structure of the exchanger 100. Furthermore, for the purpose of illustration, the collector 19 is not shown and will be described below in relation to [Fig.5].

[0061] The exchanger 100 is intended to exchange heat (thermal exchange) between a first fluid 1 circulating substantially along a first flow direction X and a second fluid 2 circulating substantially along a second flow direction Y.

[0062] By flow direction, we mean an overall flow direction of the fluid considered, independent of any local disturbances that may affect the flow direction.

[0063] The local flow direction of the first fluid 1 is schematically represented by an unfilled arrow. The local flow direction of the second fluid 2 is schematically represented by a fully filled arrow. For readability, some numeric references, including those of these arrows, are not systematically shown.

[0064] As shown in [Fig.6], the exchanger 100 can receive the first fluid 1 from an element 101, and redirect it to the element 101 after passing through the exchanger 100.

[0065] The exchanger 100 can receive the second fluid 2 from an element 102, and redirect it to an element 103.

[0066] Elements 101, 102, 103 and the exchanger 100 can be integrated into a turbomachine 200.

[0067] The first fluid 1 and the second fluid 2 can be two gases, for example the exchanger 100 receiving and redirecting the respective fluids from or to a turbomachine compressor 101, typically downstream, a combustion chamber 101, typically upstream, or a zone 101 formed between a compressor outlet and a combustion chamber inlet, a turbine 102, and an exhaust nozzle 103, for example in the case where the turbomachine 100 includes a recovered cycle gas turbine.

[0068] For example, the first fluid 1 and the second fluid 2 may respectively comprise a gas and a liquid, in particular oil, for example the exchanger 100 receiving and redirecting the respective fluids to or from a lubrication circuit 101, a secondary air stream 102 or a third stream 102, an exhaust nozzle 103.

[0069] The exchanger 100 comprises two or more sub-circuits 10 forming a first circuit receiving the first fluid 1.

[0070] The sub-circuit 10 will be described in more detail with respect to figures 1, 2A, 2B and 3.

[0071] The sub-circuit 10 extends on one side along the first direction X. The sub- circuit 10 extends further along the second direction Y. Sub-circuit 10 is substantially invariant under translation along the second direction Y, so that the structure of sub-circuit 10 described below extends along the second direction Y.

[0072] Along the path of the first fluid 1, the sub-circuit 10 extends between an input 10A and an output 10E.

[0073] The inputs 10A and outputs 10E of the sub-circuits 10 are typically provided on the same face of the exchanger, for example designated as "first face" Fl illustrated in [Fig.1].

[0074] As shown in the view of Figures 2A and 3, between the input 10A and the output 10E, the circuit may include a conduit in the general shape of a U seen in a plane perpendicular to the second direction Y.

[0075] In particular, along the path of the first fluid 1, the sub-circuit 10 can include, in this order, between the inlet 10A and the outlet 10E: an inlet branch 10B, a half-turn 10C (“U-turn” or 180° flow deflection) and an outlet branch 10D.

[0076] Viewed in a plane perpendicular to the second direction Y (figures 2A and 3), that is to say a plane comprising the first direction X and a third direction Z perpendicular to the first direction X and to the second direction Y, the half-turn 10C takes the form of a 180° elbow redirecting the fluid from the inlet branch 10B to the outlet branch 10D with a common direction and an opposite sense.

[0077] The inlet branch 10B and the outlet branch 10D are each delimited by an inner wall 12 and an outer wall 14.

[0078] Here, interior and exterior are designated with respect to the assembly formed by the sub-circuit 10.

[0079] Typically, the inlet branch 10B and the outlet branch 10D surround a common channel 22 of a second circuit, configured to receive the second fluid 2.

[0080] The inner wall 12 and outer wall 14 thus contribute to the heat exchange between the first fluid 1 and the second fluid 2. The inner wall 12 and outer wall 14 are thus typically exchange walls.

[0081] In the sense of the preceding definition, the channel 22 framed by an input branch 10B and an output branch 10D of the same sub-circuit 10 is thus considered as internal to the sub-circuit 10.

[0082] The input branch 10B and the output branch 10D are each delimited by an inner wall 12. The inner walls 12 which delimit the input branch 10B and the output branch 10D of the same sub-circuit 10 typically delimit the so-called inner channel 22.

[0083] A channel 22 can also be formed between two consecutive sub-circuits 10, that is to say two consecutively arranged sub-circuits 10 in a third direction Z, for example between adjacent outer walls 14 of branches 10B, 10D of two consecutive sub-circuits 10.

[0084] Such a channel 22 formed between two consecutive sub-circuits 10 is thus considered to be external.

[0085] The inner wall 12 and outer wall 14 typically extend in a plane formed by the first direction X and the second direction Y. Thus, the channels 22 typically extend between the first direction X and the second direction Y, thus allowing the circulation of the second fluid 2 along the second direction Y.

[0086] As shown in [Fig. 1], the direction of flow of the first fluid 1 in the sub-circuits 10 can be the same for all the sub-circuits 10. In other words, the inputs 10A and the outputs 10E of the sub-circuits 10 can be arranged alternatively, that is to say, alternatively along the third direction Z. In other words, along the third direction Z, the inputs 10A and the outputs 10E are arranged in an "input - output - input - output" pattern.

[0087] For example, from left to right on [Fig.1] along the third direction Z, are arranged consecutively and in this order an output 10E, an input 10A of a first sub-circuit 10 then an output 10E and an input 10E of a second sub-circuit 10 adjacent to the first sub-circuit 10.

[0088] In such an alternative arrangement between inputs 10A and outputs 10E illustrated in [Fig.2A], a channel 22 is then formed between the outer walls 14 of the respective input branches 10B of two alternative subcircuits 10, or between the outer walls 14 of output branches 10D.

[0089] In the view of [Fig.2B], the directions of circulation of the first fluid 1 have been altered compared to the view of [Fig.2A], corresponding to an alternative embodiment.

[0090] As shown in [Fig. 2B], the direction of flow of the first fluid 1 in the sub-circuits 10 can be reversed between two consecutive sub-circuits 10. In other words, the inputs 10A and the outputs 10E of the sub-circuits 10 can be arranged consecutively, i.e., two inputs 10A are arranged consecutively and that two 10E outputs are arranged consecutively along the third direction Z. In other words, along the third direction Z, the 10A inputs and the 10E outputs are arranged in an "input - output - output - input" pattern.

[0091] In such an alternative arrangement of the inputs 10A and outputs 10E, and thus of the input branches 10B, and output branch 10D, a channel 22 is then formed between the outer walls 14 of an input branch 10B and an output branch 10D of two consecutive sub-circuits 10.

[0092] The sub-circuits 10 can also extend along the second direction Y. In other words, the inner walls 12 and the outer walls 14 can extend substantially in a plane comprising the first direction X and the second direction Y, so as to allow heat exchange between the first fluid 1 and the second fluid 2.

[0093] The inner walls 12 and the outer walls 14 may include fins.

[0094] For example, as illustrated in detail in [Fig.3], the inner walls 12 and the outer walls 14 may have first fins 13 and / or second fins 15.

[0095] The first fins 13 are typically provided on the side of the first circuit, so as to direct the first fluid 1 within the sub-circuit 10.

[0096] For example, the first fins 13 are designed to extend mainly along the first direction X, as well as along the third direction Z, so as to reduce a local movement of the first fluid 1 along the second direction Y, and thus to channel the first fluid 1 locally along the first direction X.

[0097] For example, the second fins 15 are designed to extend mainly along the second direction Y, as well as along the third direction Z, so as to reduce a local movement of the second fluid along the direction X, and thus to channel the second fluid 2 locally along the second direction Y.

[0098] The fins 13,15 also contribute to the heat exchange between the fluids 1,2 and the walls 12,14 in presence.

[0099] The fins 13,15 may or may not extend continuously from one wall 12,14 to the other along the third direction Z, thus defining a honeycomb structure further reducing local fluid movements along the corresponding direction between the first direction X and the second direction Y, i.e. encouraging the circulation of fluids 1,2 along their general flow direction between the first direction X and the second direction Y.

[0100] The fins 13, 15 can extend over all or part of the length of the walls 12, 14 in the direction of flow of the corresponding fluid between the first fluid 1 and the second fluid 2.

[0101] The fins 13, 15 can, for example, be arranged on the walls 12, 14 along the entire path of the respective fluid between the first fluid 1 and the second fluid 2. Typically, the fins 13, 15 can be continuous along the entire direction of flow of the corresponding fluid between the first fluid 1 and the second fluid 2, or they can be discontinuous. If applicable, the discontinuous fins 13, 15 can be arranged in line with each other in the direction of flow of the corresponding fluid between the first fluid 1 and the second fluid 2.

[0102] The sub-circuit 10 may include a mechanical reinforcement 18. The reinforcement 18 typically comprises one or more support arches 18.

[0103] The reinforcement 18 is for example provided in the half-turn 10C.

[0104] An example of a support arch is shown in the enlargement of [Fig.4].

[0105] The support arch 18, for example, has a cross-ribbed shape.

[0106] The reinforcement 18 comprises, for example, a plurality of support arches 18 arranged along the second direction Y, typically regularly arranged along the second direction Y.

[0107] Such a structure makes it possible to ensure a mechanical reinforcement function, in particular of the internal walls 12, and is in particular compatible with manufacturing by additive methods.

[0108] The reinforcement 18 is typically designed to extend along the first direction X between a second face F2 opposite the first face Fl and an end of the channel 22 over a height h, shown in [Fig.1].

[0109] The height h is for example between 1.2 mm and 5 mm. The height h can for example be between 0.5xd4 and 2xd4, where d4 is a dimension (not shown) chosen from the height of a fin 13 measured along the third direction Z, the total height measured along the third direction Z of two fins 13 respectively provided on the walls 12 and 14 in the extension of each other, and the width of the inlet branch 10B or the outlet branch 10D measured along the third direction Z.

[0110] The reinforcement 18 can for example have a length d3 along the third direction Z ([Fig.3]), and a depth pl along the second direction Y ([Fig.4]).

[0111] The length d3 and the length pl can be between 1 mm and 20 mm, for example the length d3 and the depth pl can be equal to each other.

[0112] Such a structure thus makes it possible to ensure structural reinforcement of the channel 22 without significantly reducing the passage cross-section of the first fluid 1.

[0113] Such a structure also makes it possible to provide mechanical support to the exchanger 100 during manufacturing operations by additive methods, in particular reducing the overhang of the supported sub-circuit 10.

[0114] The length (shown vertically in [Fig. 1]) L of the heat exchanger along the first direction X is typically between 30 mm and 400 mm, for example between 100 mm and 300 mm. The length L is measured, for example, between the first face Fl and the second face F2 opposite the first face FL

[0115] The depth P of the heat exchanger along the second direction Y is typically between 50 mm and 1 m, for example between 50 mm and 500 mm, or between 100 mm and 300 mm. For example, the depth P is between 10 mm and 400 mm, for example between 20 mm and 250 mm

[0116] The width dl of a sub-circuit 10 along the third direction Z ([Fig. 2A] and 2B) is typically between 10 mm and 400 mm, for example between 20 mm and 250 mm. The width d2 of the channel 22 along the third direction Z is typically between 10 mm and 250 mm.

[0117] For illustrative purposes, the exchanger 100 has been shown with two sub-circuits 10. It is understood, however, that the exchanger 100 may include more sub-circuits, 10, typically between five and fifty sub-circuits 10.

[0118] The width D along the third direction Z can be equal to the sum of the total widths of the sub-circuits 10 and the channels 22, where the number of channels 22 is less than the number of sub-circuits 10 by one unit.

[0119] For example, the width D of the exchanger along the third direction Z is typically between 50 mm and 1 m, for example between 50 mm and 500 mm, or between 100 mm and 300 mm. For example, the width D is between 10 mm and 400 mm, for example between 20 mm and 250 mm.

[0120] The exchanger 100 may include a manifold 19 intended to divide an incoming flow and an outgoing flow of the first fluid 1 to and from the various sub-circuits 10.

[0121] A collector 19 is shown in [Fig.5]. The collector 19 is typically provided adjacent to the first face Fl, that is to say fluidly in the extension of the subcircuit 10, in particular in the extension of the inlet 10A and the output 10E of the subcircuit 10, in other words in the extension of the inlet branch 10B and the output branch 10D of the subcircuit 10.

[0122] The collector 19 includes, for example, walls 19A, inclined in a plane formed by the first direction X and the second direction Y, configured to direct along the second direction Y an incoming flow and / or an outgoing flow from the sub-circuit 10.

[0123] The collector 19 includes, for example, walls 19B, inclined in a plane formed by the first direction X and the third direction Z, configured to direct along the third direction Z an incoming flow and / or an outgoing flow from the sub-circuit 10.

[0124] The inclination of the walls 19A, 19B is the angle formed between the direction normal to the walls 19A, 19B and the first direction X.

[0125] The walls 19A, 19B may for example have an inclination of less than 45°, for example between 10° and 45°.

[0126] The heat exchanger 100 has a structure that is particularly well-suited to production by additive manufacturing. A manufacturing process for the heat exchanger 100 can therefore be implemented, entirely or partially, by additive manufacturing, for example by a laser powder bed fusion process.

[0127] Although the present invention has been described with reference to specific embodiments, it is evident that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the various embodiments illustrated / mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than a restrictive sense.

Claims

Demands

1. Crossflow heat exchanger (100) for aeronautical turbomachinery, configured to exchange heat between a first fluid and a second fluid, comprising: two or more sub-circuits (10) forming a first circuit configured to receive the first fluid (1), said sub-circuits (10) each extending mainly between a respective inlet (10A) and outlet (10E) in a first direction (X), said sub-circuits (10) being fluidically independent; the inlets (10A) and outlets (10E) of said sub-circuits (10) being positioned on a first face (Fl) of the exchanger; said sub-circuits (10) being delimited by walls (12,14) configured to effect heat exchange between the first fluid (1) inside said sub-circuits (10) and the second fluid (2) outside said sub-circuits (10); the inputs (10A) and outputs (10E) of adjacent sub-circuits (10) being arranged alternately.

2. Crossflow heat exchanger (100) for aeronautical turbomachine according to claim 1, wherein the walls (12,14) extend in a plane comprising the first direction (X) and a second direction (Y) perpendicular to the first direction (X) so as to obstruct movement of the second fluid along a third direction (Z) perpendicular to the first direction (X) and the second direction (Y).

3. Crossflow heat exchanger (100) for aeronautical turbomachine according to claim 1 or 2, wherein the walls (12,14) have on the side of the first circuit of the first fins (13), preferably extending along the first direction (X).

4. Crossflow heat exchanger (100) for aeronautical turbomachine according to any one of claims 1 to 3, comprising channels (22) of a second circuit configured to receive the second fluid (2), said sub-circuits (10) being separated by all or part of the channels (22).

5. Crossflow heat exchanger (100) for aeronautical turbomachine according to claim 4, wherein the walls (12,14) have second fins (15) on the side of the second circuit.

6. Crossflow heat exchanger (100) for aircraft turbomachine according to any one of claims 1 to 5, wherein viewed in a cross section, each subcircuit (10) comprises a generally U-shaped conduit extending between the inlet (10A) and outlet (10E) of the subcircuit (10).

7. Crossflow heat exchanger (100) for aeronautical turbomachine according to any one of claims 1 to 6, wherein the sub-circuits (10) extend along the first direction (X) over a distance greater than 90% of the length of the exchanger along the first direction (X).

8. Crossflow heat exchanger (100) for aeronautical turbomachine according to any one of claims 1 to 7, wherein the sub-circuits (10) have mechanical reinforcements (18) opposite the first face (Fl).

9. Crossflow heat exchanger (100) for aeronautical turbomachine according to any one of claims 1 to 8, comprising a manifold (19) configured to split an inflow and an outflow of the first fluid (1) to and from the subcircuits (10).

10. Aeronautical turbomachine (200) comprising a crossflow heat exchanger (100) for aeronautical turbomachine according to any one of claims 1 to 9.

11. Aeronautical turbomachine (200) according to claim 10, wherein the first circuit is connected to at least one of a turbomachine compressor and a combustion chamber (101) and the second circuit is connected to a turbine (102) and an exhaust nozzle (103).

12. Method of manufacturing a crossflow heat exchanger (100) for an aeronautical turbomachine according to any one of claims 1 to 9, comprising at least one powder bed additive manufacturing step.

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