Heat exchange arrangement

Abstract

The invention relates to a heat exchange arrangement (10) having at least two two heat exchange devices (11), which can each be flowed through by a first fluid (F1) and by a second fluid (F2) and are designed to transfer thermal energy from the first fluid (F1) to the second fluid (F2), and each of the heat exchange devices having an inlet (12) for the second fluid (F2) arranged transverse to an inflow direction (Z) of the second fluid (F2).

Description

[0001] Heat exchanger arrangement

[0002] Funded by the European Union. However, the views and opinions expressed are solely those of the author(s) and do not necessarily reflect those of the European Union or the Clean Aviation Joint Undertaking.

[0003] Neither the European Union nor the licensing authority can be held responsible for them.

[0004] The invention relates to a heat exchange arrangement with at least two heat exchange devices, each of which is permeable to a first fluid and a second fluid and is configured to transfer thermal energy from the first fluid to the second fluid, and each has an inlet for the second fluid arranged transversely to the flow direction of the second fluid. The invention further relates to a turbomachine with at least one such heat exchange arrangement.

[0005] Conventional engine designs are highly mature and can only promise incremental efficiency improvements in the future. Therefore, modifications to the gas turbine cycle are becoming increasingly attractive despite their growing complexity, as they promise significant efficiency gains. For example, the "Water-Enhanced Turbofan (WET)" technology relies on water injection into a combustion chamber. Here, steam is generated in a steam generator located downstream of the engine turbine using exhaust gas energy and is then fed into the combustion chamber. After passing through the steam generator, the moist exhaust gas can flow through further components that serve to separate the water from the exhaust. These WET concepts require heat exchangers, especially condensers, with relatively large inlet areas.

[0006] Starting from this premise, it is an object of the present invention to propose an improved heat exchange arrangement for a turbomachine, particularly for an aircraft propulsion system. Specifically, the heat exchange arrangement should enable a reduction in size, an increase in the frontal area, and / or an improvement in efficiency. According to the invention, this is achieved by the teaching of the independent claim. Advantageous embodiments of the invention are the subject of the dependent claims.

[0007] To solve the problem, a heat exchanger arrangement, particularly for a turbomachine, is proposed, comprising at least two heat exchangers, each capable of being permeated by a first fluid and a second fluid, and configured to transfer thermal energy from the first fluid to the second fluid. Each heat exchanger has an inlet for the second fluid arranged transversely to the inflow direction of the second fluid. The inlets for the second fluid are staggered along the inflow direction of the second fluid to the heat exchanger arrangement, such that an inflow zone of the heat exchanger arrangement transversely to the inflow direction of the second fluid is formed by the staggered inlets.

[0008] In the context of the present invention, a staggered arrangement is understood to mean, in particular, a predetermined, stepped arrangement of the inlets of the heat exchange devices and / or the heat exchange devices themselves (which are then, in particular, identically designed with respect to the arrangement of the inlets) relative to one another or relative to the flow direction of the second fluid. Such a staggered arrangement allows the inlets of the at least two or more heat exchange devices to be offset from one another and, in the flow direction of the second fluid, to be sequentially exposed to the flow of the second fluid, so that the heat exchange devices can be, or are, sequentially exposed to the flow of the second fluid. In particular, this makes it possible for the inlets of the heat exchange devices to be arranged at least partially adjacent to one another transversely to the flow direction.This allows the staggered inlets of the heat exchange devices to be approached or flowed through by different flow streams branched off from the inflow of the second fluid, resulting in flow paths of varying lengths for the different flow streams before they pass through the respective heat exchange device.

[0009] The inflow direction of the second fluid is, in particular, a direction or axis along which the second fluid, or a flow of the second fluid, flows before entering one or more heat exchange devices. The inflow direction may, in particular, differ from the flow path of the second fluid within the heat exchange device(s).

[0010] A heat exchanger is, in particular, a device designed to transfer thermal energy from one fluid stream (the first fluid) to another fluid stream (the second fluid), whereby the first and second fluids can, for example, be guided in a cross-flow. Such a heat exchanger can be used, for example, for an evaporation and / or a condensation process. Such a heat exchanger has an inlet with a flowable cross-section, designed to receive the second fluid for flow through the heat exchanger. The inlets of the heat exchanger together form the inflow region of the heat exchanger arrangement, i.e., the region of the heat exchanger arrangement that serves to receive the second fluid through the heat exchanger.

[0011] The invention is based on the idea of ​​providing several heat exchange devices arranged in series as a heat exchange arrangement, which, via their inlets, can be permeated by a flow or fluid, particularly in series or at least partially parallel to one another. In this way, the flow area of ​​the heat exchange arrangement can be increased, especially in relation to the available installation space and particularly in relation to the installation volume of known heat exchange arrangements.

[0012] In one embodiment, the at least two heat exchange devices each have at least one heat exchanger, wherein the heat exchanger has an inlet surface for the second fluid that forms a predetermined inlet surface angle with the inflow direction. This allows the heat exchanger(s) to be inclined relative to the inflow direction, for example, by increasing the inlet surface area of ​​the heat exchanger compared to an inlet surface arranged perpendicular to the inflow direction. The inlet surface angle can be between 0° and 90°, with the inlet surface angle in some embodiments being, in particular, between 10° and 45°, 15° and 40°, 20° and 35°, and / or approximately 30°.A matrix in the heat exchanger can be arranged at an angle of 45° to the inlet surface of the heat exchanger in order to enable favorable flow through the heat exchanger with the second fluid and / or the first and the second fluid to each other.

[0013] In one embodiment, the at least two heat exchange devices are each configured to guide the second fluid to the inlet surface of the heat exchanger at a predetermined angle. The inlet angle is, in particular, the angle at which the respective flow path of the second fluid meets the inlet surface of the respective heat exchanger. Specifically, an inlet area of ​​the respective heat exchange device can be configured to deflect the second fluid from its flow direction in order to achieve a suitable or predetermined inlet angle. For this purpose, the heat exchange device can, for example, have a predetermined internal geometry to enable such a deflection of the second fluid. The predetermined inlet angle can, for example, be between 40° and 50°, and in particular approximately 45°, in order to reduce pressure losses caused by the deflection.Overall, such a design can make it possible to increase the heat exchanger inlet areas at small deflection angles for the flow or for the second fluid.

[0014] In one embodiment, the at least two heat exchange devices each have a diffuser device through which the second fluid flows. This diffuser device is arranged upstream of the heat exchanger of the heat exchange device in the flow direction of the second fluid. The flow direction is, in particular, the direction or flow path along which the second fluid flows within the heat exchange device. This diffuser device can be arranged in an inlet area, i.e., downstream of the inlet of the heat exchange device. The diffuser device is configured to widen the partial flow of the second fluid entering the respective heat exchange device in order to reduce the flow velocity of the second fluid and thus slow down the flow of the second fluid through the heat exchanger.The diffuser device may have a diffuser ratio, which may be between 2 and 3, and / or may have an opening angle of approximately 10° or less than 10°.

[0015] By using a staggered arrangement that allows for multiple heat exchangers and thus multiple diffusers, the total cross-section covered by the diffuser can be reduced. This is because the multiple diffusers can be shorter and therefore have a smaller cross-section, particularly in their outlet area, compared to a single diffuser. This ensures that the cross-section of the device containing the heat exchanger, such as a turbomachine, remains unobstructed and allows for the free flow of a second fluid.

[0016] In one embodiment, the at least two heat exchangers each have a flow-directing device at their inlet, configured to deflect the second fluid at least partially from its inflow direction by a first angle. In particular, the diffuser device in the inlet of the heat exchanger can be designed such that the second fluid is deflected or redirected by a first angle from its inflow direction. The flow-directing device can, for example, have a slope and / or curvature, particularly with respect to the inflow direction, which is configured to deflect at least one reference or main flow path of a branched flow stream by this first angle. The first angle can be, in particular, 1° to 30°, 10° to 20°, and / or approximately 15°.

[0017] In one embodiment, the at least two heat exchange devices each have a deflection device arranged between the diffuser device and the heat exchanger. This allows, in particular, a partial flow of the second fluid, already deflected by the first angle, to be further deflected to meet the inlet surface of the heat exchanger at a suitable angle. The heat exchange device or the deflection device can have an internal or channel geometry designed to deflect the flow or the second fluid from its original flow path as desired.

[0018] In one embodiment, the deflection device is configured to deflect the second fluid by a second angle in order to supply it to the heat exchanger. In particular, the first and second angles together form the inlet angle of the second fluid at the inlet surface of the heat exchanger. Specifically, the surface(s) or inner surface(s) of the deflection device can have a suitable inclination and / or curvature to achieve the desired second angle. This second angle can be, in particular, between 10° and 40°, between 20° and 35°, or approximately 30°.

[0019] In one embodiment, the at least two heat exchange devices are each permeable to the second fluid, essentially flowing in the direction of the second fluid's inflow. During the flow through the heat exchange device, the second fluid, or a partial flow of the second fluid, can be deflected from the inflow direction by one or more, in particular predetermined, angles, while essentially maintaining the initial or fundamental direction. In particular, there is no reversal of the flow direction. This allows flow losses for the second fluid to be minimized or reduced.

[0020] In one embodiment, the at least two heat exchange devices are each perpendicular to the flow direction of the second fluid, allowing the first fluid to pass through them. This enables a cross-flow configuration for the heat exchanger, thereby improving heat transfer within the heat exchange device or the heat exchanger itself.

[0021] In one embodiment, the at least two heat exchange devices each have a substantially annular cross-section. This allows several heat exchange devices, arranged side by side, particularly in a circumferential direction, to define or encompass a channel or annular space in which, for example, the second fluid can flow. In such an embodiment, the first fluid can be guided in the respective annular segment under a curvature transverse to the inflow and / or flow direction of the second fluid.

[0022] In one embodiment, the at least two heat exchange devices are arranged at a staggered angle to each other, particularly along the inflow direction. This staggered angle can be formed between the respective reference axes of the heat exchange devices, such as an axis lying in the plane of the respective inlet or heat exchanger inlet surface. For example, the staggered angle between the respective inlet surfaces of two adjacent heat exchange devices can be between 1° and 10°, and particularly between 5°. This allows for a conical orientation or arrangement of the heat exchange devices to be achieved, thus improving the flow of the second fluid.

[0023] According to another aspect, a turbomachine for an aircraft propulsion system is proposed, comprising a core engine with a compressor, combustion chamber, and turbine arranged sequentially so that a gas flow can pass through them in the same direction as the core engine, and at least one heat exchanger arrangement as described herein. The staggered arrangement of the heat exchangers and their inlet surfaces allows for a compact design of the turbomachine or engine. Furthermore, the heat exchanger arrangement enables the flow resistance of the turbomachine to be designed in such a way that no significant increase in thrust is required.

[0024] A turbomachine can be designed for use in an aircraft engine and comprises, in particular, a fan, a compressor, a combustion chamber, and a turbine, and can, for example, be designed as a turbofan engine. Ambient air can be drawn in by means of the fan as the working fluid or gas flow for the core engine and compressed in the compressor to increase the pressure, particularly in the direction of flow. In the combustion chamber, located downstream of the compressor in the direction of flow of the engine, the compressed working fluid can be combusted with a fuel to generate combustion gases at high pressure and temperature. The combustion gases flow as a gas stream from the combustion chamber to the turbine, where they expand to perform work. In particular, the expansion of the combustion gases in the turbine section drives a shaft or shaft assembly.For example, a high-pressure turbine can drive a high-pressure compressor via a high-pressure wave, and / or a low-pressure turbine can drive a fan via a low-pressure wave. If the turbomachine utilizes the WET concept, it can have an exhaust gas treatment system downstream of the turbine. This exhaust gas treatment system can include and / or utilize an evaporator and a heat exchanger arrangement as described herein. The heat exchanger arrangement downstream of the evaporator can be designed as a condenser (condenser heat exchanger) or utilize ambient air as a cooling fluid. This air is supplied, for example, by a blower or the fan of the aircraft engine, resulting in liquid water components in the exhaust gas flow that can be separated from it.The liquid water component can be separated from the gas flow in a water separator and supplied to the evaporator for steam generation. At least a portion of the steam generated in the heat exchanger is fed to the combustion chamber of the turbomachine for combustion along with fuel. With such WET concepts, the size and / or flow advantages achievable through the heat exchanger arrangement can be utilized, which can lead to, in particular, a reduction in installation space, an increase in the flow area, and / or an improvement in efficiency.

[0025] In one embodiment, the turbomachine has a number of heat exchanger arrangements whose inlets for the second fluid are arranged in an annular shape, at least in sections, transverse to the inflow direction. This allows the heat exchanger arrangements to form a flow channel in which the second fluid can flow along its direction of flow. In other embodiments, the second fluid can flow in its inflow direction in the outer circumferential region of the channel formed by the heat exchanger arrangements and be received there by the heat exchanger. This allows the second fluid to flow through the heat exchanger arrangements, and in particular, cross-flow (in sections) through the heat exchanger arrangements with the first fluid, is possible.

[0026] In one embodiment, the number of heat exchanger arrangements surrounds a bypass channel of the turbomachine in the circumferential direction. Such a bypass channel can be arranged around the central engine, with an ambient airflow, also known as a "cold bypass," being provided by the fan.

[0027] This allows the "cold bypass" to be used for cooling or heat exchange with the first fluid, for example to enable condensation of the first fluid.

[0028] In one embodiment, the sum of the cross-sectional areas of the inlets of the heat exchange devices, particularly of annularly arranged and especially of at least partially circularly designed heat exchange devices, corresponds essentially to half the cross-sectional area of ​​an inlet of the bypass channel. This allows a flowable cross-section of the bypass channel to be maintained, while simultaneously enabling the use of the flow in the bypass channel for the heat exchange devices.

[0029] In one embodiment, the at least one heat exchanger arrangement is permeable to the first fluid in the circumferential direction of the turbomachine. This allows the flow through the heat exchanger arrangement or heat exchanger to be transverse to the inflow direction of the second fluid, thereby facilitating the transfer of thermal energy. Furthermore, this offers possibilities for reducing the installation space.

[0030] In one embodiment, the first fluid can be guided from the core engine to the heat exchanger by means of at least one strut. A strut is, in particular, a cross member or bracing strip through which fluid flows, connecting the core engine to at least one heat exchanger assembly. Such a strut can also fulfill at least one further, in particular structural, function of the turbomachine. The first fluid can, for example, be a gas flow through the core engine, which can be guided radially outward from the core engine to the at least one heat exchanger assembly or its heat exchanger(s) by means of the at least one strut. Here, the at least one strut can be arranged in the bypass channel, so that a cooling effect of the "cold bypass" can also be utilized.

[0031] In one embodiment, the turbomachine has an evaporator downstream of the core engine. This evaporator can be configured to cool the turbomachine exhaust gas or the core engine gas flow after the turbine, in order to enable the condensation of water contained in the first fluid in the heat exchanger or heat exchange device of the at least one heat exchange arrangement. The evaporator can be arranged around the core engine or in a flow channel downstream of the core engine in the flow direction, so that the gas flow or exhaust gas of the core engine can pass through the evaporator after the turbine before it can be fed to the heat exchange arrangement.

[0032] In one embodiment, the first fluid is an exhaust gas from the turbomachine or the gas flow from the core engine after the turbine. Accordingly, the particularly moist exhaust gas from the gas turbine or the core engine, especially when the core engine is configured as a WET core, can be cooled in the heat exchanger and the water recovered by means of a heat exchanger, particularly one designed as a condenser, in order to be returned to the WET process.

[0033] In one embodiment, the second fluid is ambient air flowing through the bypass channel of the turbomachine. This ambient air can, for example, be drawn in by means of the fan and flow in the bypass channel in the direction of inflow, so that the second fluid can be supplied circumferentially to the at least one heat exchanger arrangement.

[0034] In one embodiment, the second fluid is ambient air flowing along the turbomachine. In another embodiment, the inlets of the heat exchanger arrangement(s) or heat exchanger device(s) are arranged radially outwards in the circumferential direction, allowing flow through the heat exchanger devices radially inwards. This provides a channel inside, particularly in annularly arranged, heat exchanger arrangements for accommodating at least one device, such as, in particular, a drive unit, at least one fuel cell, at least one electric motor, at least one gas turbine, and / or at least one piston engine.

[0035] Further features, advantages, and possible applications of the invention will become apparent from the following description in conjunction with the figures. In general, features of the various exemplary aspects and / or embodiments described herein can be combined with one another, unless this is explicitly excluded in the disclosure.

[0036] Another particularly preferred aspect of the invention, which may be claimed independently, relates to a heat exchanger arrangement with a plurality of heat exchange devices, each of which is permeable to a first fluid and a second fluid and is configured to transfer thermal energy from the first fluid to the second fluid. The heat exchange devices are arranged with respect to the inflow direction such that they overlap in a direction perpendicular to the inflow direction. Preferably, the heat exchange devices overlap by at least 30% of their extent, more preferably by at least 50% of their extent, further preferably by at least 70% of their extent, and most preferably by at least 80% of their extent, with respect to their extension parallel to the overlap direction.According to a further development, the centers of gravity of the individual heat exchanger units are offset in a sectional view both in the direction of inflow and in a direction perpendicular to the direction of inflow. In particular, the heat exchanger units are offset from each other by between 1% and 30%, preferably between 5% and 15%, of their extent perpendicular to the direction of inflow.

[0037] In the following part of the description, reference is made to the figures shown to illustrate specific aspects and embodiments of the present invention. It is understood that other aspects may be used and structural or logical modifications of the illustrated embodiments are possible without departing from the scope of the present invention. The following description of the figures is therefore not to be understood as limiting. It shows

[0038] Fig. 1 shows a schematic sectional view of an exemplary heat exchanger arrangement according to the present disclosure;

[0039] Fig. 2 is a schematic sectional view of a section of the exemplary heat exchanger arrangement from Fig. 1; Fig. 3 is a schematic sectional view of an embodiment of a turbomachine for an aircraft propulsion system according to the present disclosure;

[0040] Fig. 4 shows another schematic sectional view of the exemplary turbomachine from Fig. 3;

[0041] Fig. 5 is a schematic perspective view of the exemplary turbomachine from Fig. 3;

[0042] Fig. 6 shows a schematic sectional view of a further embodiment of a turbomachine for an aircraft propulsion system according to the present disclosure;

[0043] Fig. 7 shows a schematic sectional view of a further embodiment of a turbomachine for an aircraft propulsion system according to the present disclosure;

[0044] Fig. 8 shows a schematic sectional view of an exemplary arrangement of heat exchange arrangements according to the present disclosure;

[0045] Fig. 9 is a schematic sectional view of the operating principle of a heat exchange arrangement according to the present disclosure; and

[0046] Fig. 10 shows another schematic sectional view of the operating principle of a heat exchange arrangement according to the present disclosure.

[0047] Fig. 1 shows an exemplary schematic sectional view of an embodiment of a heat exchanger arrangement 10 according to the invention for a turbomachine in a schematic sectional view.

[0048] The sectional view of the heat exchanger arrangement 10 shows three heat exchange devices 11, each of which is permeable to a first fluid Fi and a second fluid F2 and is configured to transfer thermal energy or heat from the first fluid Fi to the second fluid F2. The heat exchange devices 11 are arranged in a staggered arrangement along an inflow direction Z of the second fluid F2 to the heat exchanger arrangement 10. In this case, this means in particular that the heat exchange devices 11 are arranged in a staggered arrangement relative to each other, whereby the inlets 12 of the heat exchange devices 11 can be arranged at least partially next to or above one another with respect to a transverse direction to the inflow direction Z. This allows for flow paths of different lengths for the various flow streams of the second fluid F2 before they enter an inlet 12 or before they flow through the respective heat exchanger device 11.

[0049] The staggered heat exchange devices 11 are permeable to flow through by the second fluid F2 essentially in the inflow direction Z of the second fluid F2 and by the first fluid Fi essentially transversely to the inflow direction Z of the second fluid F2 (here perpendicular to the plane of the drawing). The heat exchange devices 11 or the heat exchange arrangement 10 can have a substantially annular cross-section, so that several heat exchange arrangements 10 can be arranged adjacent to one another and form a channel, in particular one permeable to flow through by the second fluid F2.

[0050] Along a flow path of the second fluid F2 through the heat exchanger 11, the heat exchanger 11 can have a diffuser 13 downstream of the inlet 12, through which the second fluid F2 flows. The diffuser 13 is designed to widen the flow of the second fluid F2 in order to slow it down. Downstream of the diffuser 13 in the flow direction, the heat exchanger 11 can have a deflector 14, which is designed to deflect the second fluid F2 to a heat exchanger 15 of the heat exchanger 11, enabling heat exchange with the first fluid F2. The heat exchanger 15 can, for example, be designed as a condenser to condense a water component of the first fluid F2 by means of cooling the first fluid F2 by the second fluid F2, and in particular to subsequently separate it.

[0051] Downstream of the heat exchanger 15 in the flow direction is another

[0052] A deflection device 16 is arranged which is configured to direct the cooled second fluid to a nozzle device 17, through which the second fluid F2 can leave the heat exchange device 11 and thus the heat exchange arrangement 10.

[0053] Fig. 2 shows an enlarged view of a section of the sectional view of an exemplary heat exchanger arrangement 10 according to the invention from Fig. 1.

[0054] The at least one heat exchanger 15 of the heat exchanger assembly 11 has an inlet area 115 for the second fluid F2, which forms a predetermined inlet angle α with the inflow direction Z. This inclination of the heat exchanger 15, or rather its inlet area 115, relative to the inflow direction Z allows the inlet area 115, or the flow area for the second fluid F2, to be enlarged, particularly compared to a perpendicular flow, in order to enable improved heat exchange and thus improved condensation of the water content of the first fluid F2. The respective heat exchanger assembly 11 can be configured to guide the second fluid F2 to this inlet area 115 of the heat exchanger 15 at a predetermined inlet angle β.

[0055] The heat exchanger 11 can have a flow deflection device 112 at its inlet 12, which is configured to deflect the second fluid F2 at least partially from its inflow direction Z by a first angle y, so that a flow stream of the second fluid F2 can enter the heat exchanger 11 or the diffuser 13 at this angle y. The deflection device 14 is arranged between the diffuser 13 and the heat exchanger 15, and is configured to deflect the second fluid F2 by a second angle 5 in order to supply the second fluid F2, in particular at the inlet angle β, to the heat exchanger 15 or its inlet surface 115. In the illustrated exemplary embodiment, the deflection device 14 is formed by the wall of the flow channel of the heat exchanger 11.

[0056] In particular, the staggered arrangement of the inlets 12 of the heat exchange devices 11 allows the heat exchange devices 11 to be arranged at a staggered angle 8 to one another. This staggered angle 8 can, for example, be formed between the inlet surfaces 115 of the heat exchangers 15 of two adjacent heat exchange devices 11 and enables the heat exchange arrangement 10 to be staggered in either direction Z with respect to the inflow direction and / or, in particular in the case of a circular arrangement of several heat exchange arrangements 10, to be conically tapered or widening.

[0057] Fig. 3 shows an exemplary representation of an embodiment of a turbomachine 50 according to the invention for an aircraft propulsion system with a heat exchanger arrangement 10 in a schematic sectional view.

[0058] The turbomachine 50 comprises a core engine 51 with a compressor 53, a combustion chamber 54, and a turbine 55, which can be permeated by a gas flow S in a flow direction of the turbomachine 50, or are permeated by the gas flow 50 during operation of the turbomachine 50. The turbomachine 50 also comprises a number of heat exchanger arrangements 10, as described by way of example with reference to Figures 1 and 2. These heat exchanger arrangements 10 surround a bypass channel 58 of the turbomachine 50 circumferentially. Furthermore, the turbomachine comprises a fan 52, which is configured to draw in ambient air U and supply this ambient air U to the core engine 51 and the bypass channel 58 for flow, whereby the ambient air flow U can flow through the bypass channel 58 as a second fluid F2 in the inflow direction Z.

[0059] Downstream of the turbine 50 in the flow direction, the turbomachine 50 has an exhaust gas channel 56, which is circumferentially surrounded by an evaporator 57 and can be configured to generate steam from water using energy from the gas flow S. A flow guide can be arranged downstream of the turbine 55, which is configured to direct the gas flow S radially outwards from the turbine outlet to the evaporator 57. The steam generated there can be fed into the gas flow for combustion in the combustion chamber 54 via a steam supply, particularly together with a fuel (WET technology).

[0060] In the present embodiment, the turbomachine 50 has a number of heat exchanger arrangements 10, each with essentially annular cross-sections, which are arranged in a circular ring shape transversely to the inflow direction Z in order to surround the bypass channel 58 of the turbomachine 50 in the circumferential direction and thus to at least partially limit the bypass channel 58.

[0061] After the evaporator 57, the (exhaust) gas flow S forms the first fluid Fi and can enter the heat exchanger arrangement 10, a heat exchanger unit 11, or a heat exchanger 15 of the respective heat exchanger unit 11, particularly by means of at least one strut (not shown here). Due to the annular arrangement, the first fluid Fi can flow through the number of heat exchanger arrangements 10, essentially in the circumferential direction of the turbomachine 50. The heat exchangers 15 of the respective heat exchanger units 11 can have a condenser designed for cooling with ambient air U or the second fluid F2, or be designed as such to allow the separation of any water present in the first fluid Fi. A water separator can be arranged downstream of the heat exchanger arrangement 10 or the heat exchanger units 11 in one flow direction of the first fluid Fi to collect the water.The remaining first fluid Fi can leave the heat exchanger arrangement 10 or the turbomachine 50 and, in particular, be released into the environment.

[0062] Fig. 4 shows a sectional view of an embodiment of a turbomachine 50 according to the invention from Fig. 3 against the direction of gas flow S.

[0063] It can be seen that the first fluid Fi, or the exhaust gas S of the turbomachine 50, can flow from the evaporator 57 to the annularly arranged heat exchangers 10 by means of struts 59. The struts 59 are arranged radially between the evaporator 57 and the heat exchangers 10 in the bypass channel 58 of the turbomachine 50. In the heat exchangers 10, or their heat exchange devices 11, or heat exchangers 15, the first fluid Fi can flow essentially circumferentially around the turbomachine 50, thus forming a crossflow with the second fluid F2, which flows essentially axially to the turbomachine 50. Water separators 61 can be arranged between the heat exchangers 10, or their heat exchange devices 11, to collect water W separated from the first fluid. Fig.Figure 5 shows a perspective partially opened view of the embodiment of a turbomachine 50 according to the invention from Figures 3 and 4.

[0064] The illustration shows that the struts 59 are arranged radially between the evaporator 57 and the heat exchangers 10 in the bypass channel 58 of the turbomachine 50, allowing the first fluid Fi or the exhaust gas S of the turbomachine 50 to flow from the evaporator 57 to the annularly arranged heat exchangers 10 (not shown here). The struts are arranged offset in the circumferential direction. In other embodiments, the struts 59 can have an increased or decreased axial extent along the turbomachine axis and / or be arranged without axial offset from one another.

[0065] Fig. 6 shows an exemplary representation of a further embodiment of a turbomachine 50 according to the invention for an aircraft propulsion system with a heat exchanger arrangement 10 in a schematic sectional view. The embodiment shown corresponds essentially to the embodiment of Fig. 3, which is why only the differences will be discussed below.

[0066] The circularly arranged heat exchanger assembly 10 is surrounded by a housing 60 in order to form a plenum 117 for nozzle devices 17 of the heat exchanger device 11 of the heat exchanger assemblies 10 or for the second fluid F2 and thus improve the discharge of the second fluid F2.

[0067] Fig. 7 shows an exemplary representation of a further embodiment of a turbomachine 50 according to the invention for an aircraft propulsion system with a heat exchanger arrangement 10 in a schematic sectional view. The embodiment shown corresponds essentially to the embodiments of Fig. 3 and Fig. 6, which is why only the differences will be discussed below.

[0068] The heat exchange devices 11 are arranged in this case with respect to the inflow direction Z such that the inlet surface 115 of the heat exchanger 15, at least of the first heat exchange device 11 in the flow direction, forms an inlet surface angle α with the inflow direction Z that is close to 0°. This inlet surface 115 is therefore arranged approximately in the inflow direction Z. This may result in a different flow direction for the second fluid F2 compared to the previously described arrangements.

[0069] In such an arrangement, a deflection device 16 downstream of the heat exchanger and / or a nozzle device 17 downstream of it can be omitted, whereby the remaining second fluid F2 can leave the heat exchanger arrangement 10 or the turbomachine 50 via the plenum 117 and, in particular, be discharged to the environment. This allows for a space-saving heat exchanger arrangement 10 or turbomachine 50 in a radial direction.

[0070] Fig. 8 shows an exemplary representation of an embodiment of an arrangement of several heat exchanger arrangements 10 according to the invention for a turbomachine 50 in a schematic sectional view.

[0071] The heat exchanger arrangements 10 shown here have a substantially ring-shaped cross-section and are arranged in a circular ring shape, which allows them to form a receiving space 62 for, for example, a drive unit, a fuel cell, an electric motor, a gas turbine and / or a piston engine.

[0072] The respective heat exchange arrangements 10 are essentially designed according to the embodiment shown in Fig. 1 and Fig. 2, but are arranged in such a way that they can be exposed to an ambient air U flowing along the arrangement containing the second fluid F2, whereby the heat exchange arrangements 10 are arranged in a staggered, radially diverging arrangement in the inflow direction Z.

[0073] Figures 9 and 10 illustrate a simplified basic principle of the present invention. Each figure shows a sectional view of several heat exchanger devices 11 forming a heat exchanger arrangement 10 according to the invention. The heat exchanger devices 11 can be planar, hollow cylindrical, curved, or otherwise shaped; this is ultimately not crucial for the operating principle. The individual heat exchanger devices 11 are arranged such that they overlap in a direction transverse to the inflow direction Z. This could also be described as the heat exchanger devices 11 being at least partially, with respect to the inflow direction Z, in the slipstream of the upstream heat exchanger device 11, i.e., there is an overlap Ü of the heat exchanger devices 11 in a direction perpendicular to Z.Another way of describing it would be that the centers of gravity of the individual heat exchanger devices 11 are offset both in the inflow direction Z and by a distance d in the direction perpendicular to Z.

[0074] REFERENCE MARK LIST

[0075] 10 Heat exchanger arrangement

[0076] 11 Heat exchanger

[0077] 12 Admission

[0078] 13 Diffuser device

[0079] 14 Deflection device

[0080] 15 W heat exchanger

[0081] 16 additional deflection devices

[0082] 17 Nozzle assembly

[0083] 50 Turbomachine

[0084] 51 Core engine

[0085] 52 fans

[0086] 53 compressors

[0087] 54 Combustion chamber

[0088] 55 Turbine

[0089] 56 Exhaust duct

[0090] 57 evaporators

[0091] 58 Side channel

[0092] 59 Strut

[0093] 60 cases

[0094] 61 Water separation devices

[0095] 62 Recording room

[0096] 112 Flow control device

[0097] 115 Entrance area

[0098] 117 Plenary

[0099] Fi first fluid

[0100] F2 second fluid

[0101] S Gas flow

[0102] Ambient air

[0103] Water

[0104] X axis of rotation of the turbomachine

[0105] Z Inflow direction a Inlet surface angle ß Inlet angle y First angle

[0106] 5 second angle s staggering angle

Claims

REQUIREMENTS 1. Heat exchange arrangement (10) with at least two heat exchange devices (11), each of which is permeable to a first fluid (Fi) and a second fluid (F2) and is configured to transfer thermal energy from the first fluid (Fi) to the second fluid (F2), and each has an inlet (12) for the second fluid (F2) arranged transversely to an inflow direction (Z) of the second fluid (F2), characterized in that the inlets (12) for the second fluid (F2) are arranged in a staggered manner along the inflow direction (Z) of the second fluid (F2) to the heat exchange arrangement (10), such that an inflow area of ​​the heat exchange arrangement (10) transversely to the inflow direction (Z) of the second fluid (F2) is formed by the staggered inlets (12).

2. Heat exchange arrangement (10) according to claim 1, wherein the at least two heat exchange devices (11) each have at least one heat exchanger (15), wherein the heat exchanger (15) has an inlet surface (115) for the second fluid (F2) which includes a predetermined inlet surface angle (a) with the inflow direction (Z).

3. Heat exchange arrangement (10) according to claim 2, wherein the at least two heat exchange devices (11) are each configured to guide the second fluid F2) at a predetermined inlet angle (β) to the inlet surface (115) of the heat exchanger (15).

4. Heat exchange arrangement (10) according to at least one of claims 2 or 3, wherein the at least two heat exchange devices (11) each have a diffuser device (13) through which the second fluid (F2) can flow, which is arranged upstream of the heat exchanger (15) of the heat exchange device (11) in the direction of flow of the second fluid (F2).

5. Heat exchange arrangement (10) according to at least one of the preceding claims, wherein the at least two heat exchange devices (11) each have a flow control device (112) at their inlet (12) which is configured to direct the second to deflect fluid (F2) at least partially from its inflow direction (Z) by a first angle (y).

6. Heat exchange arrangement (10) according to at least one of claims 4 or 5, wherein the at least two heat exchange devices (11) each have a deflection device (14) have, which are located between the diffuser assembly (13) and the heat exchanger (15) is ordered.

7. Heat exchange arrangement (10) according to claim 6, wherein the deflection device (14) is configured to deflect the second fluid (F2) by a second angle (5) in order to supply the second fluid F2) to the heat exchanger (15).

8. Heat exchange arrangement (10) according to at least one of the preceding claims, wherein the at least two heat exchange devices (11) are each passable through by the second fluid (F2) substantially in the inflow direction (Z) of the second fluid (F2).

9. Heat exchange arrangement (10) according to at least one of the preceding claims, wherein the at least two heat exchange devices (11) are each passable by the first fluid (Fi) substantially transversely to the inflow direction (Z) of the second fluid F2).

10. Heat exchange arrangement (10) according to at least one of the preceding claims, wherein the at least two heat exchange devices (11) each have a substantially annular cross-section.

11. Heat exchange arrangement (10) according to at least one of claims 2 to 10, wherein the at least two heat exchange devices (11) are arranged at a step angle (e) to each other.

12. Turbomachine (50) for a flight propulsion system, comprising a core engine (51) with compressor (53), combustion chamber (54) and turbine (55) arranged successively through which a gas flow (S) can flow in a flow direction of the core engine (51), comprising at least one heat exchanger arrangement (10) according to at least one of the preceding claims.

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