Aircraft turbomachine subassembly with improved architecture and aircraft turbomachine comprising such a subassembly

Abstract

Aircraft turbomachine subassembly (10) comprising: -a heat exchange device (12) comprising an inner casing (14) of longitudinal axis (X) and radial arms (16) extending radially and away from the casing, radial exchanger arms (16a) being configured to radially transport a first fluid (F1) inside the arms, from the casing (14) to one end (16a1) of the arms, the device (12) being configured to be traversed by a second fluid (F2) which flows axially around the casing (14) and between the plurality of radial arms (16), -several fluid collectors (18) each in fluid communication with one end (16a1) of an exchanger arm (16a) in order to collect the first fluid transported by the arm,-a fluid collection and stilling chamber (20) connected to the collectors (18) by a plurality of conduits (22) each configured to transfer a flow fraction (f1) of the first fluid to the chamber (20). Figure for abstract: Fig. 2.,

Description

Title of the invention: Aircraft turbomachine subassembly with improved architecture and aircraft turbomachine comprising such a subassembly Technical field

[0001] The present invention relates to a subassembly of an aircraft turbomachine. Prior art

[0002] Document FR 3 080 652 A1 discloses an aircraft turbomachine with an inverted architecture (also known as a "return engine"). In this document, the airflow downstream of a fan is divided into two airflows, a primary airflow sent to the compressors and a secondary airflow flowing in an annular bypass duct coaxially with the primary airflow. The primary airflow flows through a low-pressure compressor, then a high-pressure compressor in a generally axial direction, in a first direction of circulation. The flow leaving the high-pressure compressor is then directed radially towards the outside of the arrangement, via a radial intake channel, to pass through a heat exchanger before being redirected in a generally axial direction, in a second direction of circulation opposite to the first direction of circulation.The flow then makes a 180° turn before entering a combustion chamber, in the first direction of circulation.

[0003] The flow of gas resulting from the combustion which takes place in the combustion chamber flows in a generally axial direction in the first direction of circulation to pass through a high pressure turbine and a low pressure turbine before passing through the aforementioned heat exchanger. The air leaving the low pressure compressor and admitted into this exchanger is heated by the flow of combustion gas leaving the low pressure turbine. The heat exchanger can be of the plate or tube type.

[0004] An air circulation duct is arranged downstream of the heat exchanger, radially outside the arrangement formed by the combustion chamber and the turbines, and guides the heated air exiting the heat exchanger towards the combustion chamber.

[0005] Although this architecture is satisfactory, there is nevertheless a need to improve it. Statement of the invention

[0006] The present disclosure is the result of technological research aimed at improving the configuration of a turbomachine subassembly capable of being integrated into an architecture such as described above, in particular with regard to the flows of fluid (e.g. air) between the compressor(s) and the combustion chamber.

[0007] A first aspect of the present disclosure relates to an aircraft turbomachine subassembly comprising: -a heat exchange device comprising an inner casing with a longitudinal axis and a plurality of radial arms which extend at the periphery of the inner casing, radially relative to the longitudinal axis and away from the inner casing, at least some radial arms, called exchanger arms, being configured to transport a first fluid inside said exchanger arms, in a radial direction, from the inner casing to an end of said exchanger arms which is radially away from the inner casing, the heat exchange device being configured to be crossed by a second fluid which flows in an axial direction around the inner casing and between the plurality of radial arms, - several fluid collectors which are each in fluid communication with at least one end of one of the exchange arms in order to collect the first fluid which is transported by the exchange arm(s) concerned, -a fluid collection and settling chamber which is connected to the fluid collectors by a plurality of fluid transfer conduits which are each configured to transfer a flow fraction of the first fluid to the fluid collection and settling chamber.

[0008] The configuration of the above subassembly makes it possible to achieve a particularly efficient heat exchange between the first fluid (e.g.: air leaving a compressor) circulating radially in radial exchanger arms and a second fluid passing axially through the annular space in which the arms are arranged around the internal casing. Furthermore, the first fluid leaving the exchanger arms is collected, for each arm (or for several arms at a time), then channeled into transfer conduits individualized from one another at the outlet of the heat exchange device, in a particularly efficient manner. Having transfer conduits spaced apart from one another allows, if necessary, easy access to the equipment arranged radially internal to the conduits and, for example, to dismantle one or more conduits to facilitate access to this equipment.In addition, the conduits transfer the primary fluid to the collection and settling chamber efficiently and without causing any fluid leakage. The chamber allows the pressure of the first fluid entering it to be standardized and the flow to be settled. This results in a more regular and calm flow at the outlet of the chamber (for example, at the inlet of a combustion chamber).

[0009] According to other possible characteristics: -the heat exchange device comprises an outer casing which surrounds, concentrically, the inner casing and is connected to the latter by the plurality of radial arms, the ends of the exchanger arms being fixed to the external casing; -the fluid collectors are arranged circumferentially on the external casing; -each fluid collector comprises a local conformation of the external casing which is configured to be in fluid communication with one or more ends of exchanger arms; -each fluid collector comprises a cover mounted on the local conformation and comprises a fitting for connecting the fluid collector to a fluid transfer conduit; - the local conformations are bosses formed on an external peripheral face of the external casing, each boss being configured to surround one or more ends of exchanger arms; -the plurality of radial arms also includes structural arms; -the fluid collection and stilling chamber has a generally annular shape which is configured, on the one hand, to collect, in a first part of the chamber which is connected to the fluid transfer conduits, the flow fractions of the first fluid transferred by these conduits and, on the other hand, to still, in a second part of the chamber, a flow of the first fluid resulting from the collection of the flow fractions of the first fluid; -the second annular part is located in a radially internal position relative to the first part and in an axial position which is axially offset relative to the first part, the second annular part comprising an axially oriented annular opening through which the flow of the first fluid is discharged; -the fluid transfer conduits are connected to the first part of the chamber on the same side of the chamber as the side where the annular flow discharge opening is arranged, such that the flow of the first fluid opening into the first part with a first geometric orientation performs a 180° turnaround in the chamber before being discharged from it through the annular opening with a second geometric orientation substantially opposite to the first geometric orientation.

[0010] A second aspect of the present disclosure relates to an aircraft turbomachine comprising an aircraft turbomachine subassembly as briefly set forth above.

[0011] The aircraft turbomachine may comprise at least one compressor, a combustion chamber and at least one turbine, the subassembly being integrated downstream of said at least one compressor and upstream of the combustion chamber in the direction of flow of the first fluid, the heat exchange device of the subassembly being arranged both downstream of said at least one compressor in the direction flow of the first fluid and downstream of said at least one turbine in the direction of flow of the second fluid.

[0012] The turbomachine may also comprise, more particularly, a low pressure compressor CPBP, a high pressure compressor CPHP, a high pressure turbine THP and a low pressure turbine TBP, the turbomachine being configured so that the low pressure turbine TBP drives the high pressure compressor CPHP via a direct mechanical connection and the high pressure turbine THP drives the low pressure compressor CPBP via a direct mechanical connection. Brief description of the drawings

[0013] The invention will be better understood and its advantages will appear better, on reading the detailed description which follows, of embodiments represented by way of non-limiting examples. The description refers to the appended drawings which are schematic and aim above all to illustrate the principles of the disclosure.

[0014] In these drawings, from one figure to another, identical or equivalent elements (or parts of elements) are identified by the same reference signs. In these attached drawings:

[0015] [Fig-1] [Fig.l] schematically illustrates an embodiment of a sub- aircraft turbomachine assembly according to the invention.

[0016] [Fig.2] [Fig.2] schematically illustrates in perspective a form of rea possible use of the aircraft turbomachine subassembly of [Fig.l].

[0017] [Fig.3] [Fig.3] is a partial perspective view of a local conformation of the external casing.

[0018] [Fig.4A] [Fig.4A] is a partial perspective view of consecutive local conformations of the external casing, one being closed and the other half-closed.

[0019] [Fig.4B] [Fig.4B] is an enlarged view of the area of ​​[Fig.4A] with the local half-closed conformation.

[0020] [Fig.5] [Fig.5] schematically illustrates a possible application of the aircraft turbomachine subassembly according to the invention. Description of the embodiments

[0021] In order to make the disclosure more concrete, embodiments are described in detail below, with reference to the accompanying drawings. It is recalled, however, that the invention is not limited to these embodiments.

[0022] [Fig. 1] schematically represents the main components of a subassembly 10 of an aircraft turbomachine according to the invention. The production details are omitted in order to highlight the main aspects of this subassembly.

[0023] As shown in [Fig.l], the subassembly 10 comprises a device heat exchange device 12 (in one possible application, this device is called an exchanger turbine casing) comprising an internal casing 14 which is arranged around a longitudinal axis X (for example produced in the form of an axial hub) and a plurality of radial arms 16 which extend at the periphery of the internal casing 14, radially relative to the longitudinal axis X and away from the internal casing 14. The radial direction of extension of the arms is perpendicular to the axial direction X and identified by the letter Y in the figure.

[0024] Among the plurality of radial arms 16, at least some radial arms denoted 16a (these arms are called exchanger arms), are configured to transport a first fluid F1 inside these hollow exchanger arms, in the radial direction Y, from the inner casing 14 to an end 16al of the exchanger arms 16a which is radially distant from the inner casing 14, as indicated by the arrows F1 in the figure. The flow in the arms 16a takes place centrifugally, that is to say from the inner casing 14 to the outside of the heat exchange device 12.

[0025] As illustrated schematically, the heat exchange device 12 is configured to be crossed by a second fluid F2 which flows in the axial direction X around the internal casing 14, passing between the plurality of radial arms 16. This device comes from a system S (in dotted lines) not described here but which will be described later in a possible application illustrated in [Fig. 5]. The device 12 here plays the role of a heat exchanger between the fluids F1 and F2. For example, the fluid F2 is at a temperature higher than that of the fluid FL. Thus, for example, the temperature of the fluid F2 is higher than 500°C and the temperature of the fluid Fl is lower than 450°C and it is a gas for both fluids, for example air: for example, Fl is air used for combustion (exhaust gas) and F2 is compressed air (before passing into the chamber).The fluid Fl is thus heated by the fluid F2 as it passes through the exchanger arms 16a which are bathed in the axial flow of the fluid F2.

[0026] The subassembly 10 also comprises several fluid collectors 18 which are each in fluid communication with at least one end 16al of an exchanger arm 16 in order to collect the first fluid F1 which is transported by the exchanger arm(s) concerned. In the illustration of [Fig.l], only one arm 16a is shown but this does not mean that the fluid collector 18 is associated only with one arm. Advantageously, each fluid collector is generally associated with several exchanger arms whose respective flows it collects, as will be seen later, this in order to simplify the architecture of the subassembly 10 by reducing the number of fluid collectors.

[0027] The subassembly 10 also includes a fluid collection and settling chamber 20 which is connected to the fluid collectors 18 by a plurality of fluid transfer conduits 22 (connecting conduits) which are each configured to transfer a flow fraction fl of the first fluid Fl to the fluid collection and settling chamber 20. The conduits 22 are arranged in a circumferential distribution at the outer periphery of the system S, between the collectors 18 and the radially outer part of the chamber 20. By reducing the number of fluid collectors, the number of conduits 22 is also reduced, which makes it easier to access between the conduits the equipment of the system S located in an internal radial position relative to the radially external position of the conduits 22 relative to the axis X. The reduced number of conduits also makes it easier to dismantle these conduits if necessary in order to access all or part of the aforementioned internal radial space.

[0028] The fluid collection and calming chamber 20 receives the flows or flow fractions fl from the different conduits 22, brings them together within the chamber by gently turning the flow (substantially 180°), that is to say without introducing strong disturbances into this flow, by standardizing the pressure of the fluid, to redirect it in the opposite direction to the direction of arrival of the flow fractions fl in order to form a substantially axial flow Fl'.

[0029] In [Fig. 1], the upstream and downstream of the subassembly 10 relative to the direction of flow of the second fluid F2 are indicated by the respective annotations Am and Av. This orientation will be that used in the application of [Fig.5].

[0030] As shown in more detail in perspective in [Fig. 2], the heat exchange device has a generally annular shape defined by the inner casing 14 and an outer casing 24 arranged concentrically relative to the inner casing. The radial arms 18 which extend radially between the two casings 14 and 24 and connect them together comprise, in addition to the exchanger arms 16a, structural arms 16b which provide a mechanical holding function between the two casings and transmission of forces. These arms can also be hollow and used for services. In the example illustrated, the structural arms 16b are spaced from each other by several exchanger arms 16a and are for example four in number, although this number may differ in other exemplary embodiments. The number of exchanger arms is, for example, between 3 and 20.Generally speaking, this number results from a compromise between the section of an arm and the number of arms that can be installed. Note that the section of an arm dimensions its axial length to have a section that minimizes losses.

[0031] In [Fig.2], the internal casing 14 internally delimits a substantially cylindrical empty space which serves to integrate the part linked to the radial outlet of the high pressure compressor.

[0032] As shown in [Fig.2], the fluid collectors 18 are arranged in a external circumference of the external casing 24 so as to collect the first fluid coming from all the exchanger arms 16a.

[0033] Each fluid collector 18 comprises a local conformation 26 of the external casing 24 which is configured to be in fluid communication with one or more ends 16al of exchanger arms. In this example, two exchanger arms 16a are fluidically connected to each local conformation 26. The external casing is for example formed by an external shell 24a, bordered radially by two peripheral edges 24b, 24c which each extend in a separate radial plane.

[0034] The ends 16al of the exchanger arms are fixed to the external casing 24 and pass in particular through the external shell 24a.

[0035] Each local conformation 26 takes for example the form of a boss formed on an external peripheral face of the external casing, here on the external face of the shell 24a. Each boss is configured to surround and join two ends 16al of exchanger arms 16. A boss 26 takes here the form of a closed wall 26a of radial extension which extends from the shell 24a, away from the latter around an opening O made in the external shell 24a and which opens, below the latter ([Fig.3]), onto a space internal to the external casing 24 and which communicates fluidically with the ends 16al.

[0036] As shown in Figures 4A and 4B, each fluid collector 18 comprises a cover or closing plate 28 mounted on the local conformation 26 (boss) so as to close the opening O of [Fig. 3]. The cover 28 has substantially the same shape as the boss 26.

[0037] [Fig.4A] shows a fluid collector 18 completely closed by its cover 28 fixed on the wall 26a of the boss (for example by screwing into holes 26b provided at intervals on the wall 26a). Depending on requirements, one or more sealing gaskets, for example flat, may be interposed between the cover 28 and the boss 26 and these gaskets have substantially the same shape or contour as the upper face of the wall 26a of the boss.

[0038] [Fig. 4A] also shows an adjacent fluid collector 18 that is partially closed because a portion of its cover 28 has been removed for the purposes of the disclosure. Each fluid collector 18 further comprises a connector 30 mounted on the cover 28 and which is configured to fluidically connect the fluid collector to a fluid transfer conduit 22. As shown in [Fig. 4B], the connector 30 forms an elbow that extends first radially from the boss and the cover, then axially from the cover, away from the collector, in order to divert at approximately 90° the flow of the first fluid F1 from each of the opening ends 16al of the two exchanger arms 16, the resulting flow F1 and which constitutes a flow fraction of the first fluid. The transfer conduit 22 (rigid pipe) is fixed to the connection 30, for example by fitting a portion of conduit into the connection and by connection by centering the diameter and fixing by screws on the plates. It will be noted that the fluid passage section of each conduit 22 is equal to the sum of the passage sections of the exchanger arms (or the ends 16al of the latter) which communicate fluidically with the conduit 22 concerned via the corresponding collector 18.

[0039] As shown in [Fig. 2], the different conduits 22 which are respectively connected to the different fluid collectors 18 are circumferentially spaced from each other (lateral or transverse spacing) and extend in a non-rectilinear shape (generally in an S shape or similar shape), thus giving a certain flexibility to the arrangement of the conduits (routing), which makes it possible to allow movements or expansions of the surrounding parts to which the subassembly 10 is mechanically associated.

[0040] The fluid transfer conduits 22 extend from the fluid collectors 18 to the collection and settling chamber 20 which they join and into which they convey the fractions of first fluid fl ([Fig. 1]).

[0041] As already briefly described with reference to [Fig. 1], the fluid collection and settling chamber 20 illustrated in [Fig. 2] has a generally annular shape which has, for example, a symmetry of revolution around the longitudinal axis X.

[0042] The chamber 20 comprises a part which is generally formed by two wall portions 32a, 32b which each form an annular collar and which are arranged concentrically with respect to one another, one 32a being arranged in an internal radial position and the other 32b being arranged in an external radial position. The two portions 32a, 32b facing one another define between them an annular passage for the air flow F1' of [Fig.l]. These two portions 32a, 32b jointly define at their downstream end an annular opening O' which is oriented downstream, that is to say here in the direction of the heat exchange device 12 ([Fig.2]).

[0043] The two portions 32a, 32b each extend upstream so as to jointly define another part of the chamber 20. More particularly, the radially internal portion 32a extends substantially axially upstream in the form of a portion 32a 1, while the radially external portion 32b extends upstream away from the portion 32a 1 and away radially from the portion 32b so as to adopt an inclination of an angle greater than 0° and less than 90° relative to the axis X. The two extended portions 32a1 and 32b 1 and which define a shape which widens upstream are then joined to each other by a bottom portion 32c which is arranged upstream of the chamber 20 and whose curved shape allows to join the ends of these two extended portions 32al and 32b 1 spaced apart angularly- loosely from each other. The inclined external portion 32b 1 is pierced with circumferentially arranged through openings ol which are intended to be connected each to an end 22a of a conduit 22 which is opposite the end of this same conduit which is secured to the connector 30.

[0044] The configuration of the chamber 20 described above thus defines a first annular part C1 formed by the two extended portions 32a 1 and 32b 1 and the curved bottom portion 32c. This part C1 is connected to the conduits 22 which bring the fluid fractions fl to it (directed in a first geometric orientation from downstream to upstream) and thus makes it possible to collect these different fluid arrivals and to combine them into a single flow. The curved shape of the part C1 makes it possible to deflect the flow by 180° gently (without an abrupt change of direction) in the downstream direction in order to produce a substantially axial flow resulting from the combination of the different fractions fl.

[0045] The configuration of the chamber 20 described above also defines a second part C2 formed by the two wall portions 32a, 32b spaced radially from one another and which jointly define an annular conduit which extends axially downstream to the annular opening O' through which the calmed flow Fl' ([Fig.l]) is evacuated axially.

[0046] The flow Fl' leaving the collection and stilling chamber 20 is ready to be used in an internal system S ([Fig.l]).

[0047] [Fig. 5] represents, in axial half-section, an example of possible use of the subassembly 10 of the preceding figures in an aircraft turbomachine 100. The different elements of the turbomachine can be installed inside a partially represented aircraft nacelle. The nacelle can make it possible to fix the turbomachine to a structural element of an aircraft such as a pylon of an aircraft wing or on the fuselage of an aircraft. The assembly formed by the turbomachine 100 and the nacelle forms for example a propulsion assembly. Alternatively, the fan can be replaced by an unducted propeller and secondary flow.

[0048] In the configuration of [Fig. 5], the turbomachine 100 may comprise a fan 104 which divides, in a known manner, an air flow Fe entering the nacelle into two air flows, a primary air flow Fap directed towards a first central annular duct 106 and a secondary air flow Fas directed towards a second annular bypass duct 108 arranged coaxially with the first central annular duct 106.

[0049] The primary air flow Fap flows in the first central annular duct 106, through a low pressure compressor CPBP, then through a high pressure compressor CPHP, in a generally axial direction relative to the main axis AA of the turbomachine, in a first direction of circulation indicated by the arrows in the duct. The flow leaving the high pressure compressor CPHP is then directed radially towards the outside of the arrangement, via a radial inlet channel Car which delivers a flow denoted Fl.

[0050] More particularly, the turbomachine 100 is configured so that the low pressure turbine TBP drives the high pressure compressor CPHP via a direct mechanical connection (not shown) and the high pressure turbine THP drives the low pressure compressor CPBP via a direct mechanical connection (not shown). The mechanical connections generally each comprise a drive assembly comprising a shaft, the two shafts preferably being counter-rotating. Patent application FR 3 080 652 provides further details on this architecture.

[0051] It will be noted that the fan 104 is preferably driven by the rotor of the THP turbine and by the rotor of the CPBP compressor via a reducer.

[0052] In [Fig.5], the CPBP compressor has been shown schematically in the form of an axial compressor but, preferably, it is a centrifugal compressor.

[0053] The turbomachine subassembly 10 described above is integrated into the turbomachine 100 in such a way that the heat exchange device 12 is arranged downstream of the radial intake channel Car in order to receive the flow Fl to be heated. As shown schematically in [Fig. 5], the heat exchange device 12 is connected, by the fluid transfer conduits 22 to the collection and settling chamber 20 which is arranged upstream of a combustion chamber Ce. Downstream of this chamber are arranged, one after the other, a high pressure turbine THP and a low pressure turbine TBP. The heat exchange device 12 is connected to the outlet pipe of the turbine TBP and forms, on the path of the flow coming from this turbine and denoted F2, what is called an exchanger turbine casing.

[0054] Thus, the gas flow Fl originating from the compression of air in the CPHP compressor passes through the exchanger device 12 via the radial exchanger arms of FIGS. 1 and 2, is collected, at the outlet of these arms, in the fluid collectors 18, then is transported by the conduits 20 (in the form of flow fractions fl) to the collection and settling chamber 20 in the opposite direction to the air circulation through the compressors. The fractions fl are collected, combined into a settled flow in the chamber 20 (reoriented, after a reversal, in the same first circulation direction as the air circulation through the compressors) before being evacuated and injected into the combustion chamber Ce in the form of the flow Fl'.

[0055] The flow of gas from the combustion that occurs in the combustion chamber This flows in a generally axial direction in the first direction of circulation to pass through the high pressure turbine THP and the low pressure turbine TBP (flow F2) before passing through the aforementioned exchanger device 12. The air leaving the low pressure compressor and admitted into this exchanger (flow F1) is thus heated by the flow of combustion gas F2 leaving the low pressure turbine.

[0056] It will be noted that other turbomachine architectures can integrate such a subassembly, in particular architectures with a single compressor and a single turbine, or with more than two compressors and more than two turbines.

[0057] The advantages provided by the subassembly 10 apply fully to the turbomachine that integrates it. Thus, the flow F1 is channeled in a particularly efficient manner through exchanger arms, then collected and conveyed in a sealed manner to the chamber 20 via separate conduits (the flow leaving the exchanger arms is thus separated to be distributed in the different conduits). The presence of these separate conduits around the assembly formed by the combustion chamber and the turbines makes it possible to carry out a visual inspection between the conduits of the zone radially internal to them and also to access it by dismantling the conduit(s) necessary for the maintenance operation (for example to access the engine injectors).Furthermore, the multiplicity of conduits makes it possible to limit the cases of breakdowns: for example, if one of the conduits 22 breaks, the integrity of the other conduits is not necessarily called into question and they can continue to perform their function.

[0058] Although the present invention has been described with reference to specific exemplary embodiments, it is obvious that various modifications and changes may be made to these examples without departing from the general scope of the invention as defined by the claims. Furthermore, individual features of the various embodiments discussed may be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.

Claims

Claims

1. Subassembly (10) of an aircraft turbomachine comprising: - a heat exchange device (12) comprising an inner casing (14) of longitudinal axis (X) and a plurality of radial arms (16) which extend at the periphery of the inner casing, radially relative to the longitudinal axis and away from the inner casing, at least some radial arms, called exchanger arms (16a), being configured to transport a first fluid (F1) inside said exchanger arms, in a radial direction (Y), from the inner casing (14) to an end (16a 1 ) of said exchanger arms which is radially away from the inner casing, the heat exchange device (12) being configured to be crossed by a second fluid (F2) which flows in an axial direction around the inner casing (14) and between the plurality of radial arms (16),-several fluid collectors (18) which are each in fluid communication with at least one end (16al) of one of the exchanger arms (16a) in order to collect the first fluid which is transported by the exchanger arm(s) concerned, -a fluid collection and settling chamber (20) which is connected to the fluid collectors (18) by a plurality of fluid transfer conduits (22) which are each configured to transfer a flow fraction (fl) of the first fluid to the fluid collection and settling chamber (20).,

2. Aircraft turbomachine subassembly (10) according to the preceding claim, in which the heat exchange device (12) comprises an outer casing (24) which surrounds, concentrically, the inner casing (14) and is connected to the latter by the plurality of radial arms (16), the ends (16al) of the exchanger arms (16a) being fixed to the outer casing.

3. Aircraft turbomachine subassembly (10) according to claim 2, wherein the fluid collectors (18) are arranged circumferentially on the outer casing (24).

4. Aircraft turbomachine subassembly according to claim 2 or 3, wherein each fluid collector (18) comprises a local conformation (26) of the external casing which is configured to be in fluid communication with one or more ends (16al) of exchanger arms (16).

5. Aircraft turbomachine subassembly according to the preceding claim, in which each fluid collector (18) comprises a cover (28) mounted on the local conformation (26) and comprises a connector (30) for connecting the fluid collector to a fluid transfer conduit (22).

6. Aircraft turbomachine subassembly according to claim 4 or 5, in which the local conformations are bosses (26) formed on an external peripheral face of the external casing, each boss being configured to surround one or more ends (16al) of exchanger arms.

7. Subassembly according to one of the preceding claims, in which the plurality of radial arms (16) also comprises structural arms (16b).

8. Helicopter turbomachine subassembly according to one of the preceding claims, in which the fluid collection and settling chamber (20) has a generally annular shape which is configured, on the one hand, to collect, in a first annular part (Cl) of the chamber which is connected to the fluid transfer conduits (22), the flow fractions (fl) of the first fluid transferred by these conduits and, on the other hand, to settling, in a second annular part of the chamber (C2), a flow of the first fluid resulting from the collection of the flow fractions of the first fluid.

9. Aircraft turbomachine subassembly according to the preceding claim, in which the second annular part (C2) is located in a radially internal position relative to the first annular part (Cl) and in an axial position which is axially offset relative to the first part, the second annular part comprising an axially oriented annular opening (0') through which the flow of the first fluid is evacuated.

10. Aircraft turbomachine subassembly according to claim 8 or 9, in which the fluid transfer conduits (22) are connected to the first annular part (Cl) of the chamber on the same side of the chamber as the side where the annular flow discharge opening (O') is arranged, in such a way that the flow of the first fluid opening into the first part with a first geometric orientation performs a 180° turnaround in the chamber before being discharged therefrom through the annular opening (O') with a second geometric orientation substantially opposite to the first geometric orientation.

11. Aircraft turbomachine comprising an aircraft turbomachine subassembly according to one of the preceding claims.

12. Aircraft turbomachine according to the preceding claim, wherein the turbomachine comprises at least one compressor (CPBP, CPHP), a combustion chamber (Ce) and at least one turbine (THP, TBP), the subassembly (10) being integrated downstream of said at least one compressor (CPBP, CPHP) and upstream of the combustion chamber (Ce) in the direction of flow of the first fluid (Fl), the heat exchange device (12) of the subassembly being arranged both downstream of said at least one compressor (CPBP, CPHP) in the direction of flow of the first fluid (Fl) and downstream of said at least one turbine (THP, TBP) in the direction of flow of the second fluid (F2).

13. Aircraft turbomachine according to the preceding claim, in which the turbomachine comprises a low pressure compressor (CPBP), a high pressure compressor (CPHP), a high pressure turbine (THP) and a low pressure turbine (TBP), the turbomachine being configured so that the low pressure turbine (TBP) drives the high pressure compressor (CPHP) via a direct mechanical connection and the high pressure turbine (THP) drives the low pressure compressor (CPBP) via a direct mechanical connection.

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