FR3140137A1 - TRIPLE-FLOW TURBOMACHINE WITH HEAT EXCHANGER SUPPORTING AN INTERNAL CELL - Google Patents

Abstract

TRIPLE-FLOW TURBOMACHINE WITH HEAT EXCHANGER SUPPORTING AN INTERNAL CELL The invention relates to a turbomachine, comprising: a second separation nozzle capable of separating a radially internal air flow into a primary flow and a tertiary flow traveling through a stream of tertiary flow radially external to a primary flow vein traversed by the primary flow; a heat exchanger (18) disposed in the tertiary flow vein; an internal casing (28); an internal shell (30) placed downstream of the exchanger; remarkable in that the exchanger comprises a body (32) and a flange (32.1) extending radially internally and projecting from the body, the flange being fixed to the internal casing, the exchanger comprising, downstream of the flange, a downstream part (40) cantilevered, the turbomachine further comprising a flange (60) for fixing the shroud, an upstream end (60.1) of the flange being fixed to the flange (28.1) of the exchanger. (Figure to be published with the abstract: Figure 3)

Description

TRIPLE-FLOW TURBOMACHINE WITH HEAT EXCHANGER SUPPORTING AN INTERNAL CELL

The invention relates to the field of turbomachines and more particularly three-flow turbomachines. The invention relates to the arrangement of a heat exchanger intended for cooling the oil of the turbomachine.

Climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, various restrictions on carbon emissions have been, are or will be adopted by various states. In particular, an ambitious standard applies both to new types of aircraft but also to those in circulation requiring the implementation of technological solutions in order to make them comply with current regulations. Civil aviation has been mobilizing for several years now to make a contribution to the fight against climate change.

Technological research efforts have already made it possible to very significantly improve the environmental performance of aircraft. The Applicant takes into consideration the impacting factors in all phases of design and development to obtain aeronautical components and products that consume less energy, are more respectful of the environment and whose integration and use in civil aviation have moderate environmental consequences with the aim of improving the energy efficiency of aircraft.

Consequently, the Applicant is constantly working to reduce its negative climate impact through the use of methods and the exploitation of virtuous development and manufacturing processes and minimizing greenhouse gas emissions to the minimum possible for reduce the environmental footprint of its activity.

This sustained research and development work concerns new generations of aircraft engines, the reduction of aircraft weight, particularly through the materials used and lightweight on-board equipment, and the development of the use of electrical technologies to ensure propulsion, and, essential complements to technological progress, aeronautical biofuels.

In this context, the invention relates more particularly to aspects linked to the arrangement of heat exchangers in turbomachines. Indeed, in a turbomachine, it is generally necessary to cool the oil in the lubrication circuit. It is known to arrange one or more heat exchanger(s) in the tertiary flow of a three-flow turbomachine, that is to say in the flow radially intermediate between the primary flow directed towards the combustion chamber and the secondary, external flow.

The integration of an exchanger in the third flow, confined between the primary flow and the secondary flow, poses assembly and accessibility difficulties in the event of maintenance but also operational constraints due to the thermal expansion of the exchanger. A “brick” type exchanger inspired by document FR 3 089 248 A1 does not meet these constraints and is therefore not suitable for the third flow.

The integration of an exchanger in a third flow of a three-flow turbomachine therefore presents challenges linked to its size, its assembly, its accessibility, its operation and also the overall mass of the means used to fix it to the casing.

The present invention aims to overcome at least one of the disadvantages of the aforementioned state of the art. More particularly, the invention aims to propose a simple, efficient and economical solution aimed at resolving the disadvantages of the design/manufacture of state-of-the-art turbomachines. In particular, the invention aims to propose a solution which allows effective cooling in a restricted space without adding mass and without hindering the efficiency of the turbomachine, but also by guaranteeing the safety of the turbomachine in the event of fire, and the accessibility of the exchanger during a maintenance operation.

For this, the present invention relates to a turbomachine, comprising:
- a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow, called secondary flow;
- a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow, the latter traveling through a tertiary flow vein radially external to a primary flow vein traversed by the primary flow;
- a heat exchanger placed in the tertiary flow vein;
- an internal casing; And
- an internal shell of the tertiary flow vein located downstream of the exchanger
the turbomachine being remarkable in that the exchanger comprises a body and a flange extending radially internally and projecting from the body, the flange being fixed to the internal casing, the exchanger comprising, downstream of the flange, a downstream part in cantilever, the turbomachine further comprising a flange for fixing the shroud, an upstream end of the flange being fixed to the flange of the exchanger.

Preferably, the internal shroud as well as the internal casing correspond to an inter-blade cowling of the turbomachine which is arranged between the primary flow stream and the tertiary flow stream. Advantageously, the casing and internal shell are in aerodynamic continuity with the tertiary flow vein, and preferably constitute a radially internal guide wall for the tertiary flow.

The downstream part is cantilevered downstream of the fixing flange, because it is devoid of any other fixing, apart from the fixing of the exchanger to the shell at the level of said fixing flange.

According to an advantageous embodiment of the invention, the flange comprises a radial portion in radial overlap with the downstream part of the exchanger, and the radial portion of the flange comprises at least one opening crossed by at least one hydraulic connection connected to the exchanger . The hydraulic connection makes it possible to supply oil to the exchanger and/or to recover the cooled oil from said exchanger.

According to an advantageous embodiment of the invention, the turbomachine comprises a flange extending projecting and downstream from the body of the exchanger, said flange being flush with the shell.

Advantageously, the collar makes it possible to maintain the aerodynamic continuity of the tertiary flow path, so as to avoid any leakage of air radially internally towards the fixing flange.

In addition, the collar makes it possible to thermally insulate and further secure the connection between the shell and the exchanger, so as to constitute a break in the thermal bridge which extends axially from the body of the exchanger to the shell. . In this configuration, the internal shell is protected from the heat that can be released from the exchanger, said internal shell can advantageously be manufactured from a composite material.

According to an advantageous embodiment of the invention, a fire wall is attached to a lower surface of the collar.

Advantageously, the fire wall corresponds to a fire wall making it possible to delay the propagation of a possible fire coming, for example, from the primary flow stream (of the combustion chamber) towards the nacelle of the aircraft. Bringing the fire wall back to the exchanger saves overall space but also facilitates the maintenance of these elements because additional fixing for the fire wall is no longer necessary.

Preferably, the fire wall extends from the flange to the collar, thus forming a thermal shield over the entire downstream part of the exchanger.

According to an advantageous embodiment of the invention, the flange extends axially over at most 10% of a total axial length of the heat exchanger. Advantageously, such an axial length of the collar makes it possible to ensure an axial separation and a distance between the downstream part of the exchanger and an upstream portion of the internal shell, so as to promote the thermal insulation of said internal shell.

According to an advantageous embodiment of the invention, the turbomachine comprises an insulating tongue interposed between the exchanger and the shell, said tongue comprising an upper surface resting on a lower surface of a notch of the exchanger, and a lower surface, attached to the ferrule.

Preferably, the insulating tab acts as an additional fire wall, similar to the fire wall of the downstream part of the exchanger, so as to delay the propagation of the fire towards the tertiary flow vein.

Advantageously, the insulating tab makes it possible to further secure the connection between the shell and the exchanger, so as to constitute with the fire wall, a protection (thermal shield) which extends axially from the fixing flange to the shell. In this configuration, the internal shell is protected from the heat that can be released by the exchanger, said internal shell can advantageously be manufactured from a composite material.

According to an advantageous embodiment of the invention, the turbomachine comprises an insulating seal interposed between the tongue and the exchanger.

The insulating seal makes it possible, on the one hand, to limit the heat transfer from the hot exchanger to the internal shell, and on the other hand allows, by elastic deformation of said seal, expansion deformations in the axial directions. , radial and circumferential. In fact, the mounting of the tongue in the cutout is devoid of any fixing, and avoids creating areas of mechanical stress when the exchanger undergoes thermal expansion.

This seal makes it possible to limit the deformation of the shell which would appear due to thermal conduction with a hot exchanger. Thus, we are freed from stiffening elements (which can be heavy and bulky) of the shell which would aim to prevent its deformation.

According to an advantageous embodiment of the invention, the flange is a fire wall.

According to an advantageous embodiment of the invention, a fire wall is integrated into the exchanger or is fixed to its flange.

Preferably, the fire wall fixed to the flange corresponds to the flange being or comprising the fire wall and fixed to said flange.

According to an advantageous embodiment of the invention, the turbomachine comprises structural arms extending radially through the tertiary flow vein and delimiting between them inter-arm spaces, the turbomachine comprising a heat exchanger in each inter-arm space , each of the exchangers comprising a body and a flange extending radially internally and projecting from the respective body, each flange being fixed to the internal casing, the flange being common to all the exchangers and its upstream end being fixed to each of the flanges of the exchangers . For this purpose, the flange extends circumferentially over 360° around the longitudinal axis of the turbomachine, ensuring effective maintenance of the internal shroud.

At the same time, the fire wall extends circumferentially over 360° around the longitudinal axis, ensuring continuity of thermal insulation capable of protecting an entire upstream and radially exterior part of said turbomachine from possible fire propagation.

The exchanger, in addition to being able to effectively cool the oil by exchanging calories with the air, makes it possible to provide more functions, such as: the arrangement of a fire wall and the supporting flange the ferrule. In this configuration, the number of intermediate parts which would have been introduced to respond separately to the different required functions is greatly reduced, thus making it possible to reduce the mass and the manufacturing cost of the turbomachine of the invention. To this end, the assembly and disassembly of the exchanger are made easier, which thus makes it possible to improve the maintainability of the turbomachine.

In addition, the invention is particularly advantageous, because the positioning of the exchanger at the level of the tertiary flow vein makes it possible to avoid hindering the passage of air in the secondary flow and therefore the efficiency of the engine. This results in energy efficiency and optimized thrust which advantageously reduces fuel consumption and greenhouse gas emissions, thus reducing the environmental impact of aircraft.

It is understood that each detail of an embodiment below may be combined with each other detail of the other embodiments.

represents a longitudinal sectional view of a turbomachine according to the invention, said turbomachine comprising a heat exchanger in a tertiary flow stream;

represents a front view of the tertiary flow vein of the comprising several heat exchangers;

represents a sectional view of an assembly of an internal shell on the exchanger by means of a fixing flange, according to a first embodiment of the invention;

represents a sectional view of mounting the internal shell on the exchanger by means of the fixing flange, according to a second embodiment of the invention;

is an enlarged sectional view of the assembly of the , with the flange comprising at least one hydraulic connection;

schematically illustrates a front view of the flange comprising the at least one hydraulic connection.

detailed description

In the description which follows, the terms “internal” and “external” refer to positioning relative to the longitudinal axis of rotation of a turbomachine. The axial direction corresponds to the direction along the longitudinal axis of rotation of the turbomachine. The radial direction is perpendicular to the longitudinal axis. Upstream and downstream refer to the direction of flow in the turbomachine.

The figures show the elements schematically and are not represented to scale. In particular, certain dimensions are enlarged to facilitate reading of the figures.

There illustrates a turbomachine 2 comprising a propeller 4 secured to a hub 6 rotating around a longitudinal axis 8.

The turbomachine 2 moves in an air flow F whose movement relative to the turbomachine 2 is generated by the rotation of the propeller 4 and the advancement of the aircraft on which the turbomachine 2 is mounted.

The air flow F is separated by a first separation nozzle 10 into a radially internal air flow F' and a radially external air flow F2, called secondary flow F2. The propeller 4 can be placed upstream of the first separation nozzle 10 or downstream.

The radially internal air flow F' passes through a movable wheel 12 which directs the latter towards a second separation nozzle 14 capable of separating the radially internal air flow F' into a primary flow F1 and a tertiary flow F3, the latter is distinct from the secondary flow F2.

The first separation nozzle 10 comprises an internal wall forming a first external guide wall 11 of the radially internal air flow F', said first external guide wall 11 forming a convex profile seen from said radially internal air flow F' .

The second separation nozzle 14 comprises an external wall forming a second external guide wall 13 of the radially internal air flow F' having passed through the movable wheel 12, said second external guide wall 13 forming a convex profile seen from the tertiary flow F3. For this purpose, the second external guide wall 13 corresponds to a radially internal guide wall 13 of the tertiary flow F3.

The tertiary flow F3 enters a tertiary flow vein 16 radially external to said primary flow F1. The tertiary flow F3 passes through a heat exchanger 18, 118 placed in the tertiary flow vein 16.

The heat exchanger 18, 118 extends radially and axially in the tertiary flow vein 16, and preferably in an upstream section 20 of the tertiary flow vein 16, having a longitudinal section divergent in the direction of flow of the tertiary flow F3.

Preferably, the heat exchanger 18, 118 is arranged approximately axially between the high pressure compressor 15 and the low pressure compressor 17, called “booster” 17, to the right of an inter-compressor casing.

The high pressure 15 and low pressure 17 compressors comprise rotating blades and rectifier blades arranged in a primary flow stream 21 crossed by the primary flow F1, the latter heading towards a combustion chamber 23.

A “VBV” channel 19 (Variabe Bleed Valve) opens axially downstream of the heat exchanger 18 into the tertiary vein 16. It ensures a discharge function by returning part of the primary flow F1 to the tertiary flow F3 to avoid jamming of the high pressure compressor 15 when the flow rate of the primary flow F1 becomes too low.

The heat exchanger 18,118 can extend continuously over 360° in the upstream section 20 of the vein 16 around the longitudinal axis 8 of the turbomachine 2. Preferably, the turbomachine 2 comprises several heat exchangers 18,118 extending in the tertiary flow vein 16 and subdividing the vein angularly in a discontinuous manner over 360° around the longitudinal axis 8. Each of said exchangers can independently provide a heat exchange function between air and a fluid.

In this regard, the exchanger 18, 118 can ensure the cooling of the oil used in several components of the aircraft, in particular, an engine, a gearbox, an engine generator and any electronic component requiring cooling.

A single heat exchanger 18, 118 can combine the cooling of several functions or oil circuits of the turbomachine, and this according to different parameters linked to the need for oil cooling, ie inlet temperatures, flow rates, temperature requested output or air conditions, the different circuits can be placed in thermal contact or isolated. The exchanger 18, 118 and in particular its oil passages can withstand a low oil temperature of up to -54°C.

The upstream section 20 of the tertiary flow stream 16 comprises an external fairing 24 and an inter-vein cowling 26, at least one of the external fairing 24 and inter-vein cowling 26 being rigidly linked to the exchanger 18. Preferably, the cowling inter-veins 26 is attached to the exchanger 18. Such attachment will be detailed later in this description.

The inter-vein cowling 26 comprises an internal casing 28 disposed axially between the high pressure compressor 15 and the low pressure compressor 17, and further comprises an internal shroud 30 disposed downstream of the exchanger 18. In this configuration, the internal casing 28 and the internal shell 30 constitute, with the exchanger 18, 118, the radially internal guide wall of the tertiary flow F3.

There is a front view, ie in the direction opposite to the flow of air, of the tertiary flow vein 16 of the comprising several heat exchangers 18, 118. It can be seen that the exchangers 18, 118 are distributed angularly in the tertiary flow stream 16.

The turbomachine 2 comprises structural arms 34 extending radially through the tertiary flow vein 16 and delimiting between them inter-arm spaces 36. Preferably, the turbomachine 2 comprises between 2 and 20 structural arms 34.

At the same time, the inner shell can be in one piece and circumferentially continuous over 360°, or said shell can be subdivided into several internal shells of up to 5 shells.

The exchanger 18, 118 extending circumferentially between two structural arms 34 in each inter-arm space 36.

The exchanger 18, 118 comprises heat exchange surfaces 38 corresponding to oil passages and/or heat exchange surfaces with air extending radially and axially in the inter-arm space 36. example of possible designs is detailed in patent applications BE2021/5978, BE2021/5979, BE2021/5980, BE2021/5982 and BE2021/5983, the design of the heat exchange surfaces 38 or the internal oil passages does not not being the heart of the present invention.

The exchanger 18, 118 comprises a body 32 with a flange 32.1 extending radially internally and projecting from said body 32, so that the flange 32.1 is attached to an annular flange 28.1 belonging to the internal casing 28. Said flange annular 28.1 is preferably continuous over 360° around the longitudinal axis of the turbomachine while the flange 32.1 of the exchanger 18.118 preferably has a restricted extent: the flange 32.1 is in a central position relative to the body 32, in the direction circumferential. This advantageously allows free scope for thermal expansion of the exchanger 18,118 by allowing the latter to extend tangentially in the inter-arm space 36.

The direction of assembly of the exchanger 18.118 in the turbomachine is preferably from downstream to upstream. In this configuration, the fixing of the exchanger 18,118 to the internal casing 28 can be ensured by screwing. Thus, the flange 32.1 can be fixed to the annular flange 28.1 by means of two to six screws, and more preferably by means of three screws.

The exchanger 18, 118 also includes a downstream part 40 disposed downstream of the flange 32.1 and therefore mounted in a cantilever manner. This downstream part 40 has an internal surface with an internal profile 40.1, for example cylindrical or conical around the longitudinal axis of the turbomachine, and a downstream surface having a downstream profile 40.2 substantially perpendicular to the longitudinal axis. Alternatively, the shape of the downstream part 40 can be freer, as inspired by document EP 3 674 531 A1.

Preferably, the downstream surface 40.2 of the exchanger 18 comprises an oil inlet 42 at an angular end of the body 32, and an oil outlet 44 at a circumferentially opposite end.

There represents a sectional view of mounting the internal shell 30 on the exchanger 18 by means of a fixing flange 60, according to the first embodiment of the invention.

The downstream part 40 advantageously comprises a fire wall 46 capable of delaying the propagation of a downstream fire upstream of the turbomachine 2.

The fire wall 46 may preferably correspond to a layer of insulating material such as a high-performance plastic. Preferably, the fire wall 46 is a Vespel® polyimide available from DuPont™. Advantageously, Vespel® polyimide is a plastic resistant to cracking at very high temperatures with excellent friction and wear characteristics. Unlike most plastics, Vespel® does not produce significant off-gassing even at high temperatures.

In reference to the , and to the right of the downstream surface 40.2, and radially externally to the oil inlet 42 and oil outlet 44, the exchanger 18 according to the first embodiment of the invention comprises a flange 54 extending projecting and downstream from the body 32 of the exchanger 18. While the exchanger 118 according to the second embodiment of the invention comprises a notch 154. The different embodiments will be detailed below in this description.

Preferably, the fire wall 46 is fixed to the flange 32.1 and extends from said flange 32.1 to the flange 54 or to a lower surface of the notch 154. The fixing of the fire wall 46 to the body 32 of the exchanger can be ensured by gluing or by screwing.

Alternatively, the fire wall 46 is preferably integrally formed with the body 32. In this regard, the body 32 and the fire wall 46 are both formed from aluminum. In this configuration, the fire wall 46 corresponds to an aluminum wall which can be further thickened compared to the rest of the body 32. In fact, the fire wall 46 is sufficiently thick to ensure resistance to a possible fire.

Preferably, the collar 54 and/or the notch 154 extends circumferentially over the entire circumferential extent of the downstream part 40.

The flange 32.1 of each exchanger 18 is fixed to the internal casing 28, and the fire wall 46 is fixed to each flange 32.1. To this end, the fire walls 46 of all the exchangers 18 extending in the vein advantageously make it possible to form a continuity of circumferential thermal insulation with the structural arms 34, thus protecting the entire upstream part of the turbomachine over 360 °.

In reference to the , we can see that the fixing flange 60 of the ferrule 30 comprises an upstream end 60.1 directly fixed to the flange 32.1. In this regard, the flange 32.1 is preferably fixed by screwing to the internal casing 28, and the upstream end 60.1 is also screwed onto the flange 32.1 by means of the same screws assembling the flange 60 to the internal casing 28.

The flange 60 comprises a downstream end 60.2 opposite the upstream end 60.1, said downstream end 60.2 being rigidly connected to an upstream portion 30.1 of the ferrule 30. Preferably, the rigid connection between the flange 60 and the ferrule 30 corresponds to bolting and/or riveting. In this configuration, the ferrule 30 is attached to the casing via the flange 32.1 of the exchanger 18. This can be the only upstream attachment of the ferrule 30. The suggests a downstream fixing of the ferrule 30 which we will not discuss in detail here.

The downstream part 40 of the exchanger 18 comprises the flange 54 extending towards the ferrule 30, and preferably flush with the upstream portion 30.1. For this purpose, the collar 54 is flush with the radially internal guide wall 13.

Thus, the collar 54 allows the tertiary flow to follow the aerodynamic line 16.1 in the tertiary flow vein 16 illustrated in the . The aerodynamic continuity ensured by the collar 54 makes it possible to avoid air leaks towards an inter-vein compartment 27 of the inter-vein cowling 26 of the .

The collar 54 can be integral with the body 32 and can extend axially to a downstream junction 54.1 over at most 10% of a total axial length of the exchanger 18, and preferably over 5% of said length. .

The downstream part 40 has an axial length of between 10% and 50% of the axial length of the exchanger 18, and preferably between 20% and 50%, and more preferably between 20% and 40%. Such an axial length makes it possible to extend the axial coverage of the fire wall 46 and therefore to further extend the protection axially, without penalizing the mechanical balance of the exchanger: a too imposing downstream part would require other means of fixing in downstream of the exchanger and this would affect the size and simplicity of assembly.

Preferably, the fire wall 46 matches the internal profile 40.1 and the downstream profile 40.2 of the downstream part 40 of the exchanger 18, and extends radially on the flange 32.1 and up to the collar 54. Advantageously, and in addition to protecting the turbomachine from the propagation of fire, the fire wall 46 makes it possible to protect the shell 30 from the high temperatures of the exchanger 18.

Preferably, the fire wall 46 extends to a lower surface 54.1 of the collar 54. This makes it possible to effectively cut the thermal bridge between the shell 30 and the exchanger 18.

The ferrule 30 can advantageously be manufactured from a composite material. For example, the internal ferrule 30 can be made from carbon fiber.

Indeed, the maximum temperature that the collar 54 can reach during the operation of the exchanger 18, in particular at the downstream junction 54.1, is lower than the maximum temperature bearable by the composite material forming the internal shell 30.

The flange 60 can correspond to a second fire wall in addition to the fire wall 46 of the downstream part 40 of the exchanger 18. In this configuration, the protection against fire and the thermal insulation of the components is maximized.

Alternatively, the flange 60 may include the fire wall and the downstream part 40 of the exchanger 18 may be devoid of the fire wall. This makes it possible to simplify the manufacture of exchanger 18.

There represents a sectional view of an assembly of the internal shell 30 on the exchanger 118 by means of the fixing flange 60, according to a second embodiment of the invention.

Elements identical to those of the first embodiment are designated by the same reference numbers, while elements presenting differences will be incremented by 100.

The turbomachine 2 comprises an annular insulating tab 56 interposed between the exchanger 118 and the shell 30, said tab 56 comprising an upper surface 56.1 resting on a lower surface 154.1 of a notch 154 of the exchanger 118, and a lower surface 56.2, fixed to the ferrule 30.

Preferably, a downstream portion of the tongue 56 is fixed by riveting to the upstream portion 30.1 of the ferrule 30.

The tongue 56 is preferably formed from an insulating material, said material possibly corresponding to that of the fire wall, ie Vespel® polyimide.

The lower surface 154.1 of the notch 154 is preferably parallel to the upper surface 56.1 of the tongue 56. Preferably, the contact between the tongue 56 and the exchanger 118 is an indirect contact because a thermal insulating seal 50 is interposed between the lower surface 154.1 of the notch 154 and the upper surface 56.1.

In this configuration, the seal 50 makes it possible to cut the thermal bridge between the shell 30 and the exchanger 18, thus making it possible to minimize the transfer of the heat dissipated by the exchanger 118 towards the shell 30. Also, this allows more freedom during the design of the exchanger 118 and the shell 30, the tongue 56 can serve as an adjustment variable filling the gap between these two elements. This design versatility is illustrated by representing an exchanger 118 on the which is less bulky than that of the .

In this regard, the seal 50 is an elastomer capable of cutting the thermal bridge between the shell 30 and the exchanger 18. Preferably, the seal 50 is a Vespel® polyimide available from DuPont™. This joint 50 can therefore be similar to the material of the fire wall. However, the joint 50 can be obtained from a material different from that of the fire wall.

The tongue 56 includes a low mass, thus allowing the turbomachine of the invention to have a considerably reduced mass compared to state-of-the-art turbomachines.

Advantageously, the fire wall 146 extends in the downstream part 40 of the exchanger 118, from the flange 32.1 and towards the lower surface 154.1 of the notch 154.

The fire wall 146 ensures the cutting of the thermal bridge capable of protecting an entire upstream and radially exterior part of the turbomachine from the propagation of fire.

Being fixed only to the ferrule 30 and being floating in the exchanger 118, the tongue 56 also facilitates the assembly and disassembly of the exchanger, which ensures a saving of time during assembly and improve the maintainability of the turbomachine. Also, this assembly leaves free scope for local deformations (thermal expansion) of the tongue 56.

There is an enlarged sectional view of the assembly of the , with the flange 60 comprising at least one hydraulic connection 58 directly connected to the downstream surface 40.2 of the exchanger 18. It is understood that a comparable design can be made for the variant presented in where the at least one hydraulic connection 58 is connected to the exchanger 118.

The hydraulic connection 58 corresponds to a fluid connection between the exchanger 18 with other components of the turbomachine, ie lubrication group, engine, gearbox, engine generator or any electronic component requiring cooling).

A first connection 58 can be directly connected to the oil inlet 42, and the second connection 58 is connected to the oil outlet 44 illustrated in the .

We can see on the that the flange 60 comprises apertures 62 allowing the passage of the connections 58. These apertures 62 can be arranged on a radial portion 60.3 of the flange 60 which is in radial overlap with the downstream part 40 of the exchanger 18.

There schematically illustrates a front view of the flange 60 comprising two openings 62, each of which is crossed by the hydraulic connection 58.

Preferably, each opening 62 faces the oil inlet 42 or the oil outlet 44.

Alternatively, a seal (not shown) can be integrated between the hydraulic connection 58 and the corresponding opening 62. For this purpose, in the case where the flange 60 corresponds to the fire wall, the flange 60 may be able to provide suitable thermal protection for the turbomachine so as to avoid any fault in line with the opening 62.

Claims (10)

Turbomachine (2), comprising:
- a first separation nozzle (10) capable of separating an incoming air flow (F) into a radially internal air flow (F') and a radially external air flow (F2), called secondary flow (F2) ) ;
- a second separation nozzle (14) capable of separating the radially internal air flow (F') into a primary flow (F1) and a tertiary flow (F3), the latter traveling along a tertiary flow vein (16) radially external to a primary flow vein (21) traversed by the primary flow (F1);
- a heat exchanger (18, 118) arranged in the tertiary flow vein (16);
- an internal casing (28); And
- an internal shell (30) of the tertiary flow vein (16) arranged downstream of the exchanger (18, 118)
the turbomachine (2) being characterized in that
the exchanger (18, 118) comprises a body (32) and a flange (32.1) extending radially internally and projecting from the body (32), the flange (32.1) being fixed to the internal casing (28), the exchanger (18, 118) comprising, downstream of the flange (32.1), a cantilevered downstream part (40), the turbomachine (2) further comprising, a flange (60) for fixing the shroud ( 30), an upstream end (60.1) of the flange (60) being fixed to the flange (32.1) of the exchanger (18, 118). Turbomachine (2) according to claim 1, characterized in that the flange (60) comprises a radial portion (60.3) in radial overlap with the downstream part (40) of the exchanger (18, 118), and the radial portion ( 60.3) of the flange (60) comprises at least one opening (62) crossed by at least one hydraulic connection (58) connected to the exchanger (18, 118). Turbomachine (2) according to one of claims 1 or 2, characterized in that it comprises a flange (54) extending projecting and downstream from the body (32) of the exchanger (18), said collar (54) flush with the ferrule (30). Turbomachine (2) according to the preceding claim, characterized in that a fire wall (46; 146) is attached to a lower surface (54.1) of the collar (54). Turbomachine (2) according to claim 3 or 4, characterized in that the flange (54) extends axially over at most 10% of a total axial length of the heat exchanger (18). Turbomachine (2) according to one of claims 1 to 5, characterized in that it comprises an insulating tongue (56) interposed between the exchanger (118) and the shell (30), said tongue (56) comprising a surface upper surface (56.1) resting on a lower surface (154.1) of a notch (154) of the exchanger (118), and a lower surface (56.2), fixed to the shell (30). Turbomachine (2) according to claim 6, characterized in that it comprises an insulating seal (50) interposed between the tongue (56) and the exchanger (118). Turbomachine (2) according to one of claims 1 to 7, characterized in that the flange (60) is a fire wall. Turbomachine (2) according to one of claims 1 to 7, characterized in that a fire wall (46; 146) is integrated into the exchanger (18, 118) or is fixed to its flange (32.1). Turbomachine (2) according to one of claims 1 to 9, characterized in that it comprises structural arms (34) extending radially through the tertiary flow vein (16) and delimiting interspaces between them. arm (36), the turbomachine (2) comprising a heat exchanger (18, 118) in each inter-arm space (36), each of the exchangers (18, 118) comprising a body (32) and a flange (32.1) extending radially internally and projecting from the respective body (32), each flange (32.1) being fixed to the internal casing (28), the flange (60) being common to all the exchangers (18, 118) and its upstream end ( 60.1) being fixed to each of the flanges (28.1) of the exchangers (18, 118).