Support for a breather tube for an aircraft turbine engine

Abstract

The invention relates to a support (30) for a breather tube for an aircraft turbine engine, the support (30) comprising an annular inner wall (41) internally defining a degassing passage (42) suitable for allowing an exhaust air flow (Fae) coming from a lubrication chamber to flow therethrough, the support (30) comprising an annular outer wall (43) extending directly around the inner wall (41), the outer wall (43) being coaxial with the inner wall (41) and spaced apart from the inner wall (41), the inner and outer walls (41, 43) radially defining between them an annular cooling and thermal insulation passage (44), the outer wall (43) comprising an inlet (45) configured to introduce a compressed air flow (Fac) into the passage (44), the inner wall (41) comprising an outlet (46) connected to an ejection nozzle (34), the ejection nozzle (34) being configured to eject the air flow (Fac) from the passage (44) into the degassing passage (42).

Description

[0001] DESCRIPTION

[0002] TITLE: SUPPORT FOR A DEGASING TUBE FOR AN AIRCRAFT TURBOMACHINE

[0003] Technical field of the invention

[0004] The present invention relates to a support for a degassing tube for an aircraft turbomachine, and to an aircraft turbomachine comprising a degassing tube which includes such a support.

[0005] Technical background

[0006] An aircraft turbomachine includes, in particular, various transmission elements (e.g. gears) and guidance elements (e.g. rolling bearings) which are lubricated with oil in so-called lubrication chambers.

[0007] The enclosures are generally closed via various sealing devices and depressurized at certain operating points so that oil does not escape outside the enclosures through the sealing devices.

[0008] Traditionally, to depressurize the most upstream enclosure of the turbomachine, in which, for example, the fan guide bearings are located, a turbomachine includes a central vent tube (or central ventilation tube) which is also known by the English acronym CVT for "Center Vent Tube".

[0009] More specifically, the degassing tube is connected upstream with the enclosure to collect exhaust air from the enclosure, and includes downstream an ejection opening through which the exhaust air is ejected outside the turbomachine.

[0010] To limit oil discharge outside the turbomachine, each outlet of the enclosure includes an oil separator. Despite the presence of the oil separators, engine manufacturers note that the exhaust air contains oil residues (or traces of oil) at the outlet of the oil separators, which is explained by the inability of the oil separators to capture all the oil present in the exhaust air (and in particular the fine particles or droplets of oil).

[0011] To initiate the depressurization of the chamber, the vent tube includes a jet nozzle consisting of an ejection nozzle that expels compressed air and a constriction in the tube (commonly called a "venturi") into which the compressed air is injected. The injection of compressed air into the constriction creates a negative pressure through the Venturi effect, which draws out the exhaust air, thus depressurizing the chamber.

[0012] For space reasons, the exhaust nozzle is mounted on a tube support, which is itself attached to the turbomachine's exhaust housing. This type of support is also known by the acronym SET, for "Support Exhaust Tube." The support consists of a simple annular wall through which the exhaust air from the housing flows, with the exhaust nozzle attached to this wall. The exhaust housing is positioned axially between a turbine and an exhaust nozzle of the turbomachine. Due to its location, the support is particularly exposed to hot exhaust gases, and more specifically to the thermal stresses caused by convection and radiation generated by these hot gases.

[0013] Engine manufacturers are finding that the support is subjected to significant thermal stresses and is traversed by oil residues, which represents a risk of coking of the oil residues and consequently a risk of progressive fouling (or obstruction) of the support.

[0014] Indeed, beyond a certain temperature threshold, oil oxidizes and cokes. Oil coketion results in the appearance of a blackish deposit, which can accumulate over time on the inner surface of the wall and lead to progressive fouling of the support, which is undesirable. The objective of the present invention is therefore to provide a simple, effective, and economical solution to the aforementioned problem. Prior art also includes documents FR3011583A1, FR3075866A1, FR3114121A1, and US9790856B2.

[0015] Summary of the invention

[0016] The invention thus proposes a support for a degassing tube for an aircraft turbomachine, the support being intended to be fixed to a fixed housing of the turbomachine, the support comprising an annular internal wall around an X axis, the internal wall defining internally a degassing channel suitable for carrying an exhaust air flow from a lubrication chamber of the turbomachine,

[0017] characterized in that the support comprises an annular outer wall which extends directly around the inner wall, the outer wall being coaxial with the inner wall and at a distance from the inner wall, the inner and outer walls defining radially between them an annular passage for cooling and thermal insulation, the outer wall comprising an inlet configured to introduce a flow of compressed air into the passage, the inner wall comprising an outlet which is connected to an ejection nozzle, the ejection nozzle being configured to eject the airflow from the passage to the degassing path.

[0018] The introduction of such a passage in the support not only cools the internal wall through which the exhaust air circulates but also thermally insulates the internal wall against thermal stresses, and consequently minimizes the risks of coking of oil residues present in the exhaust air, and more generally the risks of fouling or obstruction of the degassing path.

[0019] Firstly, the passage is traversed by a flow of compressed air whose temperature is significantly lower than that of the walls, thus effectively cooling them. Secondly, the passage through which the compressed air flows forms an insulating air gap that blocks thermal stresses, particularly convective and radiative heat fluxes, thereby effectively insulating the inner wall. This thermal protection is also active when the turbomachine is stopped.

[0020] In addition, the support retains the ejection nozzle which is necessary to form the jet horn in combination with the narrowing of the tube, and thus ensure the depressurization of the enclosure.

[0021] The support according to the invention may comprise one or more of the following features, taken individually or in combination with each other:

[0022] - the entrance of the outer wall and the exit of the inner wall are diametrically opposed with respect to the X axis;

[0023] - the inlet of the outer wall is oriented radially with respect to the X axis so that the airflow divides at the contact of the inner wall into a first subflow of air which flows in the passage following a first direction of circulation around the X axis and a second subflow of air which flows in the passage following a second direction of circulation around the X axis which is opposite to the first direction of circulation;

[0024] - the outlet of the inner wall is oriented radially with respect to the X axis; - the ejection nozzle includes an ejection outlet which is oriented axially in the degassing path, in the same flow direction as the exhaust airflow;

[0025] - the inner and outer walls each comprise an outer skin which is covered by a layer of insulation against thermal radiation; - the support comprises an annular collar which extends substantially radially with respect to the X axis, the collar comprising an external flange intended to be fixed to a fixed housing of the turbomachine;

[0026] - the internal and external walls are spaced radially apart from each other by a distance D which is less than or equal to 10mm;

[0027] - The distance D is between 7 mm and 10 mm. The present invention also relates to an aircraft turbomachine comprising a degassing tube including:

[0028] - a support such as described previously,

[0029] - an upstream conduit which is positioned upstream of the support and connected with the lubrication chamber;

[0030] - intermediate and downstream ducts which are arranged downstream of the support, the intermediate duct being axially located between the support and the downstream duct, the downstream duct comprising an ejection opening through which the air flows are ejected outside the turbomachine, the intermediate duct comprising internally a narrowing of the flow section, so as to create in combination with the ejection nozzle a depression by venturi effect, and consequently depressurize the lubrication chamber by suction of the exhaust air.

[0031] The turbomachine according to the invention may comprise one or more of the following features, taken individually or in combination with each other:

[0032] - the ejection nozzle includes an ejection outlet which opens into the intermediate conduit;

[0033] - the narrowing includes an upstream convergent portion having a flow cross-section that decreases from upstream to downstream and a downstream divergent portion having a flow cross-section that increases from upstream to downstream;

[0034] - the turbomachine includes an exhaust casing arranged axially between a turbine and an exhaust nozzle of the turbomachine, the support being fixed to the exhaust casing.

[0035] Brief description of the figures

[0036] The invention will be better understood and other details, features and advantages of the invention will become more apparent from the reading of the following description given by way of non-limiting example and with reference to the accompanying drawings in which: [Fig.1] Figure 1 is a schematic axial cross-sectional view of an aircraft turbomachine;

[0037] [Fig.2] Figure 2 is a detailed view of Figure 1 which illustrates in particular a support for a degassing tube;

[0038] [Fig.3] Figure 3 is a detailed view of the support illustrated in Figures 1 and 2;

[0039] [Fig.4] Figure 4 is a cross-sectional view of the support illustrated in Figures 1 to 3.

[0040] Detailed description of the invention

[0041] Figure 1 shows a turbomachine 1 of aircraft 2. Aircraft 2 is, for example, an airplane.

[0042] As illustrated in Figure 1, the turbomachine 1 is here a double-flow turbojet which classically comprises, from upstream to downstream, a shrouded fan 3, a gas generator 4, a power turbine 5 and an exhaust nozzle 6.

[0043] The turbomachine 1 is defined along a longitudinal axis X which corresponds in particular to the axis of rotation of the blower 3, and of the rotors of the gas generator 4 and of the power turbine 5.

[0044] As illustrated in Figure 1, the fan 3 is free to rotate about the X-axis relative to a fixed structure 7 of the turbomachine 1. The fan 3 is driven in rotation by the power turbine 5 via a low-pressure shaft 8, which includes a fan shaft 9 and a drive shaft 10. The fan shaft 9 is guided in rotation by two roller bearings 11a, 11b, which are axially separated from each other. The roller bearings 11a, 11b are housed and lubricated in a lubrication enclosure 12 (hereinafter referred to as the "enclosure"). The enclosure 12 is delimited upstream by a ferrule 13 and downstream by a hub 14 of an intermediate housing 15 of the structure 7. The enclosure 12 also includes a partition 16 that supports the downstream bearing 11b. The bearings 11a, 11b are lubricated with oil through nozzles which spray oil towards the bearings 11a, 11b.The enclosure 12 is ventilated by air inlets and depressurized by means of a degassing tube 17 which discharges an exhaust air flow Fae from the enclosure 12 outside the turbomachine 1. The exhaust air Fae, also called enclosure degassing air, leaves the enclosure 12 via outlets 18 which each include an oil separator, to limit as much as possible the release of oil outside the turbomachine 1.

[0045] As illustrated in Figure 1, the gas generator 4 comprises, from upstream to downstream, a low-pressure compressor 19, a high-pressure compressor 20, a combustion chamber 21, and a high-pressure turbine 22 (or expansion turbine). The high-pressure compressor 20 is driven in rotation by the high-pressure turbine 22 via a high-pressure shaft 23. The low-pressure compressor 19, in turn, is driven in rotation by the blower 3.

[0046] As illustrated in Figure 1, the power turbine 5 drives the blower 3 in rotation via the low pressure shaft 8, the low pressure shaft 8 passing through the high pressure shaft 23 from one side to the other.

[0047] As illustrated in Figure 1, the exhaust nozzle 6 is internally delimited by internal fairings 24 and an ejection cone 25, the internal fairings 24 connecting the ejection cone 25 to an exhaust housing 26. The exhaust housing 26 is part of the structure 7 of the turbomachine 1 and is located axially between the power turbine 5 and the exhaust nozzle 6. The ejection cone 25 is also known by the English term "Plug".

[0048] As illustrated in Figure 1, the airflow F generated by the blower 3 is divided, by the structure 7 of the turbomachine 1, into a primary flow F1 which enters a primary channel 27 to supply the gas generator 4, and into a secondary flow F2 which flows into a secondary channel 28 around the gas generator 4, to provide most of the thrust.

[0049] The primary flow F1 is compressed by compressors 19, 20, then injected into combustion chamber 21 to be mixed with fuel. The air / fuel mixture is burned and expanded in high-pressure turbine 22 and then in power turbine 5 before being expelled from turbomachine 1 through exhaust nozzle 6.

[0050] By convention in this application, the terms "upstream" and "downstream" are defined with respect to the direction of gas flow in the turbomachine 1, when the turbomachine 1 is operating in "propeller" mode.

[0051] In the following description, we will focus more specifically on the degassing tube 17. Such a tube 17 is also known by the English acronym CVT for "Center Vent Tube".

[0052] As illustrated in Figure 1, the degassing tube 17 is fixed and centered on the X-axis. The degassing tube 17 comprises, from upstream to downstream, an upstream conduit 29, a support 30, an intermediate conduit 31, and a downstream conduit 32. More specifically, the upstream conduit 29 is located directly upstream of the support 30 and inside the low-pressure shaft 8. The upstream conduit 29 is connected upstream with the outlets 18 of the enclosure 12 to collect the exhaust air Fae and downstream with the support 30. The upstream conduit 29 is divided into sections and comprises several segments connected to each other. The intermediate conduit 31 is located directly downstream of the support 30 and inside the internal fairings 24 of the exhaust nozzle 6. The intermediate conduit 31 includes internally a flow section constriction 33 (or choke). The constriction 33 is combined with a compressed air ejection nozzle 34 to form a jet horn 35.The function of the jet horn 35 is to create a vacuum by venturi effect in the degassing tube 17, so as to depressurize the enclosure 12 by suction of the exhaust air Fae.

[0053] More specifically, as illustrated in Figure 2, the narrowing 33 comprises an upstream convergent portion 36 having a flow cross-section that decreases from upstream to downstream, an intermediate portion 37 which has a substantially constant flow cross-section and a downstream divergent portion 38 having a flow cross-section that increases from upstream to downstream. The downstream duct 32 is located directly downstream of the intermediate duct 31 and passes through the ejection cone 25. The downstream duct 32 includes, at its downstream end, an axial ejection opening 39 through which the airflows Fae, Fac are ejected outside the turbomachine 1. The ejection opening 39 is located at the downstream end of the ejection cone 25. The downstream duct 32 is also supported relative to the ejection cone 25 by a downstream support 40. In the following description, particular attention will be paid to the support 30 of the degassing tube 17.Such a support 30 is also known by the English acronym SET for "Support Exhaust Tube".

[0054] In the same way as turbomachine 1, support 30 is defined along the X axis.

[0055] In this application, the terms "internal" and "external" are defined with respect to the X-axis of support 30 and turbomachine 1.

[0056] The support 30 is intended to be fixed to a fixed housing 26 of the turbomachine 1. The support 30 includes an internal wall 41 annular around the axis X. The internal wall 41 defines internally a degassing channel 42 suitable for carrying the exhaust air flow Fae, i.e. the degassing air from the lubrication chamber 12 of the turbomachine 1.

[0057] According to the invention, the support 30 comprises an annular outer wall 43 extending directly around the inner wall 41. The outer wall 43 is coaxial with and at a distance from the inner wall 41. The inner and outer walls 41 and 43 radially define an annular passage 44 for cooling and thermal insulation. The outer wall 43 includes an inlet 45 configured to introduce a flow of compressed air Fac into the passage 44. The inner wall 41 includes an outlet 46 connected to an ejection nozzle 34. The ejection nozzle 34 is configured to eject the air flow Fac from the passage 44 to the degassing channel 42.

[0058] The introduction of such a passage 44 in the support 30 not only allows the internal wall 41 in which the Fae exhaust air circulates to be cooled, but also thermally insulates the internal wall 41 against thermal stresses, and consequently minimizes the risks of coking of oil residues present in the Fae exhaust air, and more generally the risks of fouling or obstruction of the degassing path 42.

[0059] Indeed, firstly, passage 44 is traversed by a flow of compressed air Fac whose temperature is much lower than that of the walls 41, 43 in order to cool them effectively.

[0060] Secondly, the passage 44 through which the compressed air Fac flows forms an insulating air gap which obstructs thermal stresses, and more particularly convective and radiative heat fluxes, so as to effectively insulate the internal wall 41. Such thermal protection is also active when the turbomachine 1 is stopped.

[0061] In addition, the support 30 retains the ejection nozzle 34 which is necessary to form the jet horn 35 in combination with the narrowing 33 of the tube 17, and thus ensure the depressurization of the enclosure 12.

[0062] Advantageously, the inlet 45 of the outer wall 43 and the outlet 46 of the inner wall 41 are diametrically opposite with respect to the X axis. Such an arrangement allows the inner wall 41 to be cooled and insulated from the support 30 in a homogeneous manner.

[0063] Advantageously, as illustrated in Figure 4, the inlet 45 of the outer wall 43 is oriented radially with respect to the X-axis, such that the airflow Fac is divided upon contact with the inner wall 41 into a first sub-flow of air Fad, which flows into the passage 44 in a first direction of circulation around the X-axis, and a second sub-flow of air Fac2, which flows into the passage 44 in a second direction of circulation around the X-axis, opposite to the first direction of circulation. This orientation of the inlet 45 allows for the even distribution of the airflow Fac within the passage 44, thus achieving homogeneous cooling and thermal insulation. Advantageously, the outlet 46 of the inner wall 41 is oriented radially with respect to the X axis. Such an orientation of the outlet 46 makes it possible to efficiently collect the first and second sub-flows Fad, Fac2, so as to direct them towards the ejection nozzle 34.

[0064] Advantageously, the ejection nozzle 34 includes an ejection outlet 48 which is axially oriented in the degassing path 42. Such an orientation of the ejection outlet 48 makes it possible to provide the jet necessary for the proper functioning of the jet pump.

[0065] Advantageously, the inner and outer walls 41, 43 each comprise an outer skin (or external surface) covered by a thermal insulation layer 49 (or thermal radiation shielding layer). Such layers 49 provide additional thermal protection, enhancing the thermal insulation of the walls 41, 43. The insulation layer 49 can be, for example, in the form of a coating, sheath, paint, etc. The insulation layer 49 can be reflective to reflect the thermal radiation emitted by the surrounding parts.

[0066] Advantageously, the support 30 comprises an annular flange 50 extending substantially radially about the X-axis. The flange 50 has an external flange 51 for attachment to a fixed housing 26 of the turbomachine 1. The external flange 51 is, for example, attached to the exhaust housing 26 of the turbomachine 1. The flange 50 of the support 30 can be connected to only one of the walls 41, 43 or to both walls 41, 43. Advantageously, as illustrated in Figures 3 and 4, the inner and outer walls 41, 43 are spaced radially apart by a distance D less than or equal to 10 mm. The distance D is preferably between 7 mm and 10 mm. More preferably, the distance D is equal to 7 mm. Such a dimensional characteristic allows passage 44 to fully fulfill its cooling and thermal insulation functions, while remaining compact.

[0067] The passage 44 may internally include disruptors to maximize heat exchange between the airflow Fac and the walls 41, 43 (and in particular with the inner wall 41). The disruptors may take the form, for example, of fins, baffles, bridges, a lattice structure, etc.

[0068] According to the embodiment illustrated in figures, the support 30 is fixed to the exhaust casing 26 of the turbomachine 1.

[0069] The degassing path 42 of the support 30 is connected to the downstream end of the upstream conduit 29 and to the upstream end of the intermediate conduit 31.

[0070] The Fae exhaust air thus flows from the outlets 18 of the enclosure 12 to the outside of the turbomachine 1 via the upstream duct 29, the degassing path 42 of the support 30, the intermediate duct 31 and the downstream duct 32.

[0071] The inner and outer walls 41, 43 of the support 30 are cylindrical and coaxial with the X-axis. The walls 41, 43 are radially connected to each other upstream by an upstream wall 52 and downstream by a downstream wall 53. The upstream wall 52 is frustoconical and flares outwards from downstream to upstream. The downstream wall 53 is discoidal.

[0072] As illustrated in Figures 3 and 4, the internal and external walls 41, 43 each comprise an external skin which is covered by an insulating coating 49 against thermal radiation.

[0073] As illustrated in Figures 3 and 4, the inner and outer walls 41, 43 are radially spaced from each other by a distance D equal to 7 mm. As illustrated in Figures 1 and 2, the inlet 45 of the outer wall 43 is connected to a compressed air supply tube 54. The supply tube 54 passes through the primary flow 27 via the inner cavity of one of the arms of the exhaust housing 26. The compressed air Fac here originates from the high-pressure compressor 20.

[0074] As illustrated in Figure 4, the inlet 45 is oriented radially with respect to the X-axis so that the compressed airflow Fac is divided upon contact with the inner wall 41 into a first subflow of air Fad, which flows into the passage 44 in one direction of circulation around the X-axis, and a second subflow of air Fac2, which flows into the passage 44 in a second direction of circulation around the X-axis. The outlet 46 of the inner wall 41 is diametrically opposite the inlet 45 of the outer wall 43. The outlet 46 of the inner wall 41 is oriented radially with respect to the X-axis. The outlet 46 is connected to an ejection nozzle 34 that extends inside the degassing channel 42. The ejection nozzle 34 is angled and thus includes a axial portion 55 and a radial portion 56 which connects the axial portion 55 to the outlet 46.The ejection nozzle 34 includes an ejection outlet 48 which is axially oriented in the degassing channel 42 and opens into the intermediate duct 31 (and more specifically into the intermediate portion 37). The ejection nozzle 34 delivers a jet of compressed air directed from upstream to downstream, that is, in the direction of the exhaust air flow Fae. As mentioned above, the ejection nozzle 34 is combined with the constriction 33 of the intermediate duct 31 to form a jet horn 35. The function of the jet horn 35 is to create a vacuum by the Venturi effect in the degassing tube 17, so as to depressurize the chamber 12 by drawing in the exhaust air Fae. The ejection nozzle 34 can be attached to the inner wall 41 or be one piece (or monobloc) with the inner wall 41. The support 30 further includes an annular collar 50 which is connected to the outer wall 43.The collar 50 is frustoconical and flares out from downstream to upstream in continuity with the upstream wall 52. The collar 50 has an external flange 51 which is fixed to a web 57 of the exhaust housing 26.

Claims

DEMANDS 1. Support (30) for a degassing tube (17) for an aircraft turbomachine (1) (2), the support (30) being intended to be fixed to a fixed housing (26) of the turbomachine (1), the support (30) comprising an annular inner wall (41) about an axis (X), the inner wall (41) internally defining a degassing channel (42) suitable for carrying an exhaust airflow (Fae) from a lubrication chamber (12) of the turbomachine (1), characterized in that the support (30) comprises an annular outer wall (43) extending directly around the inner wall (41), the outer wall (43) being coaxial with the inner wall (41) and at a distance from the inner wall (41), the inner and outer walls (41, 43) radially defining between them an annular passage (44) for cooling and thermal insulation, the wall external (43) comprising an inlet (45) configured to introduce a flow of compressed air (Fac) into the passage (44),the inner wall (41) comprising an outlet (46) which is connected to an ejection nozzle (34), the ejection nozzle (34) being configured to eject the airflow (Fac) from the passage (44) to the degassing path (42).

2. Support (30) according to claim 1, characterized in that the inlet (45) of the outer wall (43) and the outlet (46) of the inner wall (41) are diametrically opposed with respect to the axis (X).

3. Support (30) according to any one of the preceding claims, characterized in that the inlet (45) of the outer wall (43) is oriented radially with respect to the axis (X) so that the airflow (Fac) is divided at the contact with the inner wall (41) into a first sub-flow of air (Fad) which flows into the passage (44) following a first direction of circulation around the axis (X) and a second sub-flow of air (Fac2) which flows into the passage (44) following a second direction of circulation around the axis (X) which is opposite to the first direction of circulation.

4. Support (30) according to any one of the preceding claims, characterized in that the outlet (46) of the inner wall (41) is oriented radially with respect to the axis (X).

5. Support (30) according to any one of the preceding claims, characterized in that the ejection nozzle (34) comprises an ejection outlet (48) which is axially oriented in the degassing path (42), in the same flow direction as the exhaust airflow (Fae).

6. Support (30) according to any one of the preceding claims, characterized in that the internal and external walls (41, 43) each comprise an external skin which is covered by an insulating layer (49) against thermal radiation.

7. Support (30) according to any one of the preceding claims, characterized in that the support (30) comprises an annular collar (50) which extends substantially radially with respect to the axis (X), the collar (50) comprising an external flange (51) intended to be fixed to a fixed housing (26) of the turbomachine (1).

8. Support (30) according to any one of the preceding claims, characterized in that the internal and external walls (41, 43) are spaced radially apart from each other by a distance (D) which is less than or equal to 10mm.

9. Aircraft turbomachine (1) (2) comprising a venting tube (17) including: - a support (30) according to one of the preceding claims, - an upstream conduit (29) which is positioned upstream of the support (30) and connected with the lubrication chamber (12); - intermediate and downstream conduits (31, 32) which are arranged downstream of the support (30), the intermediate conduit (31) being located axially between the support (30) and the downstream conduit (32), the downstream conduit (32) comprising an ejection opening (39) through which the air flows (Fae, Fac) are ejected outside the turbomachine (1), the intermediate conduit (31) comprising internally a narrowing of the flow section (33), so as to create in combination with the ejection nozzle (34) a depression by venturi effect, and consequently depressurize the lubrication chamber (12) by aspiration of the exhaust air (Fae).

10. Turbomachine (1) according to the preceding claim, characterized in that the ejection nozzle (34) comprises an ejection outlet (48) which opens into the intermediate conduit (31).

11. Turbomachine (1) according to any one of claims 9 or 10, characterized in that the constriction (33) comprises an upstream convergent portion (36) having a flow section which decreases from upstream to downstream and a downstream divergent portion (38) having a flow section which increases from upstream to downstream.

12. Turbomachine (1) according to any one of claims 9 to 11, characterized in that the turbomachine (1) comprises an exhaust casing (26) arranged axially between a turbine (5) and an exhaust nozzle (6) of the turbomachine (1), the support (30) being fixed to the exhaust casing (26).

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