Aircraft turbomachine nacelle comprising a thrust reversing device including an exhaust duct and associated method

Abstract

An aircraft turbomachine nacelle (2) (100), the nacelle (2) extending longitudinally along a nacelle axis (X) and is capable of guiding an upstream to downstream airflow, the nacelle (2) comprising at least one fan cowl (22) comprising at least one ventilation opening (41) configured to supply a fan compartment (32) with a cooling airflow (Fr), at least one thrust reverser device (23) and a partition (24), the thrust reverser device (23) comprising at least one exhaust duct (5) comprising at least one inlet opening (51) formed in the partition (24) and at least one outlet opening (52) formed in a downstream end of the thrust reverser device (23) so as to permit the cooling airflow (Fr) to be exhausted from the fan compartment (32). Figure from the summary: Figure 2

Description

Title of the invention: Nacelle for aircraft turbomachine comprising a thrust reversing device including a discharge duct and associated method. Technical field

[0001] The present invention relates to the field of aeronautics and more particularly to a nacelle for an aircraft turbomachine.

[0002] With reference to [Fig. 1], an aircraft turbomachine 100 is shown on which a nacelle 200 is mounted according to the prior art. The nacelle 200 extends longitudinally along a nacelle axis X oriented from upstream to downstream. The aircraft turbomachine 100 includes a fan (not shown) configured to accelerate an upstream to downstream airflow to provide thrust. The fan is rotatably mounted in a fan housing 102 of the turbomachine 100. The nacelle 200 includes, from upstream to downstream, an upstream air inlet jacket 201, a fan cowl 202, and a thrust reverser 203.

[0003] In a known manner, a circumferential space, designated fan compartment 302, is formed between the fan casing 102 of the turbomachine 100 and the fan cowl 202 of the nacelle 200. The fan compartment 302 provides housing for equipment E of the turbomachine 100, in particular the pumps and electronic control units. In order to supply the equipment E with a cold source, it is known to provide a cooling circuit in the fan compartment 302 which includes an air inlet 401 formed in the fan cowl 202 at an angular position, for example at 12 o'clock, and an air outlet 402, for example a grille, formed in the fan cowl 202 at another angular position, in particular at 5 o'clock.This allows a flow of cooling air Fr, in particular outside air, to circulate circumferentially between the air inlet 401 and the air outlet 402 to cool the equipment E as illustrated in [Fig. 1].

[0004] In accordance with safety standards, the blower compartment 302 includes at its downstream end a separation partition 204 which makes it possible to form a barrier limiting the spread of a fire between the blower compartment 302 and the thrust reversing device 203.

[0005] In order to allow optimal cooling of the blower compartment 302, it is necessary that the flow rate of the cooling air Fr be sufficient. For this purpose, it is necessary that the air inlet 401 and the air outlet 402 have sufficient dimensions.

[0006] In practice, the cooling airflow requirements are constantly increasing, and the dimensions of the air inlet 401 and the air outlet 402 must also be increasingly large, particularly to minimize the pressure in the fan compartment 302. Indeed, the higher the pressure, the more difficult it is to achieve an effective fire barrier. This has the disadvantage of affecting the aerodynamics of the fan cowl 202 by increasing drag. Furthermore, a large air outlet 402 is considered unsightly for a business jet turbomachine, and it is desirable to have a fan cowl 202 with a continuous surface free of openings.

[0007] The invention thus aims to eliminate at least some of these disadvantages by proposing a nacelle for turbomachine which allows optimal cooling of the fan compartment without inducing aerodynamic disturbances and by limiting the size of the outlet openings while minimizing the air pressure in the fan compartment 302. PRESENTATION OF THE INVENTION

[0008] The invention relates to a nacelle for an aircraft turbomachine, the nacelle extending longitudinally along a nacelle axis and is adapted to guide an airflow circulating from upstream to downstream, the nacelle comprising: • At least one blower hood including at least one ventilation opening configured to supply a blower compartment with a cooling airflow, • At least one thrust reversing device mounted downstream of the blower cowling, • a separation partition, extending transversely to the nacelle axis, mounted between the blower hood and the thrust reversing device.

[0009] The invention is remarkable in that the thrust reversing device includes at least one exhaust duct comprising at least one inlet opening formed in the partition wall and at least one outlet opening formed in a downstream end of the thrust reversing device so as to allow the cooling airflow to be evacuated from the blower compartment.

[0010] Thanks to the invention, the aerodynamics and aesthetics of the fan cowl are improved since it is no longer necessary to provide large outlet openings to ensure cooling of the fan compartment. Advantageously, at least part of the cooling flow is directed into the thrust reversing device. An outlet at the downstream end reduces the risk of drag, which is advantageous. This also allows for This creates a low-pressure area downstream, increasing the ventilation flow rate, particularly during ground idling when the aircraft is moving at low or zero speed. This ensures optimal cooling for all phases of turbomachine operation.

[0011] Using the thrust reverser to guide the cooling airflow to the blower compartment goes against the practices of those skilled in the art, who would have provided a partition to thermally isolate the blower compartment from the thrust reverser. The present invention reverses conventional practices by creating at least one inlet opening in the partition, thereby breaking the traditional seal between the blower compartment and the thrust reverser.

[0012] In one aspect, the fan cowl is free of any opening for the cooling airflow. In other words, the cooling airflow is primarily discharged through the thrust reverser. The aerodynamics and aesthetics of the fan cowl are improved.

[0013] According to one aspect, the nacelle comprises at least one distribution element connected to the ventilation opening and configured to circumferentially guide the cooling airflow and inject a plurality of elementary flows into the blower compartment at different angular positions. Cooling of the blower compartment is improved while taking advantage of the positioning of the inlet openings.

[0014] According to one aspect, the nacelle comprises a plurality of outlet openings formed in the downstream end of the thrust reversing device connected to the discharge pipe. This reduces drag.

[0015] According to one aspect, the thrust reversal device comprises at least two doors hinged on two longitudinal beams.

[0016] According to one aspect, at least one exhaust pipe is positioned between a longitudinal beam and a door. This reduces the risk of the longitudinal beam overheating, particularly in the event of a fire, thus improving safety.

[0017] According to one aspect, the exhaust duct includes at least one ventilation outlet dedicated to cooling a door hinge. Thus, the cooling airflow is exhausted, on the one hand, at the outlet openings and, on the other hand, at the ventilation outlet(s). The door hinge is therefore optimally cooled.

[0018] According to one aspect, the nacelle includes at least one thermal protection device positioned at the interface between the discharge pipe and a longitudinal beam of the thrust reversing device. This further reduces the risk of overheating of the longitudinal beam, particularly in the event of a fire, thereby improving safety.

[0019] According to one aspect, each beam is associated with two drainage pipes. This reduces the overall size and facilitates the positioning of the drainage pipes.

[0020] According to one aspect, the drain pipe is radially internal to a movable door. This helps to protect it from impacts.

[0021] According to one aspect, the nacelle comprises a plurality of exit openings formed in the downstream end of the beam.

[0022] According to one aspect, the beam comprises at least one assembly of two walls, the exit openings are formed between the two walls.

[0023] According to one aspect, the thrust reversal device includes at least one discharge notch at the interface between a longitudinal beam and a door, into which the discharge pipe opens. This reduces aerodynamic disturbances while facilitating the manufacture of thin-walled components.

[0024] Preferably, the outlet opening(s) are formed at the trailing edge of the thrust reversing device to limit drag.

[0025] According to one aspect, at least one outlet opening is in the form of a chevron.

[0026] According to one aspect, the thrust reversing device is a grid thrust reversing device.

[0027] According to one aspect, the nacelle includes a cylindrical shell which extends in the downstream extension of the thrust reversing device, the cylindrical shell includes at least one auxiliary evacuation conduit to allow the evacuation of the cooling airflow which is guided by the thrust reversing device.

[0028] The invention also relates to an assembly of a turbomachine and a nacelle as previously described.

[0029] The invention also relates to a method for cooling a blower compartment of a turbomachine and nacelle assembly as described above, the method comprising steps consisting of: • Supply the blower compartment with a flow of cooling air from the ventilation opening in the blower hood, • Evacuate the cooling airflow out of the blower compartment through the thrust reverser device exhaust duct. PRESENTATION OF THE FIGURES

[0030] The invention will be better understood upon reading the following description, given by way of example, and referring to the following figures, given by way of non-limiting examples, in which identical references are given to similar objects.

[0031] Fig. 1 is a schematic representation of a nacelle according to the prior art mounted on a turbomachine.

[0032] Fig. 2 is a schematic representation of a nacelle according to one embodiment of the invention mounted on a turbomachine.

[0033] Fig. 3 is a schematic representation of the gate thrust reversing device of Fig. 2.

[0034] Fig. 4 is a schematic representation of several variants of drainage pipes formed in a door.

[0035] Fig. 5 is a schematic representation of the variants of the evacuation pipes of Fig. 4 with a thermal protection device.

[0036] Fig. 6 is a schematic representation of a drain pipe with cooling of a door hinge.

[0037] Fig. 7 is a schematic representation of a ventilation opening associated with a distribution device.

[0038] Fig. 8 is a schematic representation of a thrust reversal device with gates and discharge pipes mounted in a longitudinal beam.

[0039] Fig. 9 is a schematic representation of the exit openings formed in a trailing edge of a longitudinal beam.

[0040] Fig. 10 is a first schematic representation of an evacuation notch formed in a longitudinal beam.

[0041] The [Fig. 11] is a second schematic representation of an evacuation notch formed in a longitudinal beam.

[0042] The [Fig. 12] is a schematic representation of chevron-shaped outlet openings.

[0043] Fig. 13 is a schematic representation of a nacelle comprising a cylindrical shell downstream of the thrust reversal device.

[0044] Fig. 14 is a close schematic representation of the outlet openings formed in the trailing edge of the cylindrical ferrule.

[0045] Fig. 15 is a schematic representation of a gate thrust reversing device with an evacuation conduit formed in the gate.

[0046] The [Fig. 16] is a schematic cross-sectional representation of a drain pipe beyond [Fig. 15].

[0047] Fig. 17 is a close schematic representation of Fig. 16.

[0048] Figure 18 is a schematic cross-sectional representation of a drain pipe mounted in a grid thrust reversal device in the closed position.

[0049] Fig. 19 is a schematic cross-sectional representation of a discharge pipe mounted in a grid thrust reversal device in the open position.

[0050] Fig. 20 is a schematic perspective representation of a grid thrust reversal device with a discharge pipe.

[0051] Fig. 21 is a schematic perspective representation of the outlet opening of the discharge pipe of the grid thrust reversal device.

[0052] It should be noted that the figures set out the invention in detail to implement the invention, said figures being of course able to serve to better define the invention where appropriate. DETAILED DESCRIPTION OF THE INVENTION

[0053] With reference to [Fig. 2], an aircraft turbomachine 100 is shown on which a nacelle 2 is mounted according to an embodiment of the invention. The nacelle 2 extends longitudinally along a nacelle axis X oriented from upstream to downstream.

[0054] Subsequently, the terms "interior" and "exterior" are defined radially with respect to the axis of nacelle X.

[0055] The aircraft turbomachine 100 includes a fan (not shown) configured to accelerate an upstream to downstream airflow to provide thrust. The fan is rotatably mounted in a fan housing 102 of the turbomachine 100. The nacelle 2 includes, from upstream to downstream, an upstream air inlet jacket 21, a fan cowl 22, and a thrust reverser 23.

[0056] In a known manner, a circumferential space, designated blower compartment 32, is formed between the blower casing 102 of the turbomachine 100 and the blower hood 22 of the nacelle 2. The blower compartment 32 allows to house equipment E of the turbomachine 100 in particular pumps and electronic computers.

[0057] In order to supply the equipment E with a cold source, the blower compartment 32 includes at least one ventilation opening 41 configured to supply the blower compartment 32 with a cooling airflow Fr. In this example, the ventilation opening 41 is in the form of a scoop, but it is understood that it could have a different shape. Preferably, the blower compartment 32 includes two symmetrical ventilation openings 41.

[0058] In accordance with safety standards, the blower compartment 32 includes at its downstream end a partition 24, extending transversely to the nacelle axis X, mounted between the blower hood 22 and the thrust reversing device 23. Such a partition 24 makes it possible to form a barrier limiting the propagation of a fire between the blower compartment 32 and the thrust reversing device 23. The partition 24 makes it possible to offer thermal protection. The partition wall 24 includes, for example, a composite panel, for example, made of carbon fiber of sufficient thickness, typically between 1.5 and 2.5 mm, or a sheet of titanium or steel to limit the spread of fire.

[0059] The invention is remarkable in that the thrust reversing device 23 includes at least one exhaust duct 5 comprising at least one inlet opening 51 formed in the partition 24 and at least one outlet opening 52 formed in a downstream end of the thrust reversing device 23 so as to allow the cooling airflow Fr to be evacuated from the blower compartment 32.

[0060] Thus, thanks to the invention, at least part of the cooling airflow Fr is not discharged through an opening formed in the fan cowl 22 but downstream in the thrust reverser device 23. This makes it possible to limit drag by improving the aerodynamic behavior of the fan cowl 22. Preferably, the outlet opening(s) 52 are formed at the trailing edge of the thrust reverser device 23.

[0061] Several embodiments of the thrust reversal device 23 enabling the guidance of cooling airflow Fr from the blower compartment 32 will now be presented.

[0062] With reference to [Fig. 3], a first embodiment of a thrust reversing device 23 is shown, comprising two longitudinal beams 230 on which two doors 231 are hinged by joints 233. Thus, each door 231 is movable between a closed position (illustrated in Figures 2 and 3) for the nominal operation of the turbomachine 100 and an open position for thrust reversal. During thrust reversal, a portion of the exhaust flow from the turbomachine 100 is guided upstream by the doors 231 in the deployed position.

[0063] In practice, the two doors 231 are both associated with the two longitudinal beams 230. Each door 231 has two circumferential ends, the first circumferential end of which is connected to a longitudinal beam 230 by a hinge 233, and the second circumferential end of which is connected to the other longitudinal beam 230 by another hinge 233.

[0064] The structure of such a thrust reversing device with gates 23 is known to those skilled in the art and will not be described in further detail. The longitudinal beams 230 are fixed relative to the blower housing 102.

[0065] In this example, preferably, the longitudinal beam 230 has a downstream end having a so-called "fish tail" shape in order to allow optimal opening kinematics of the door 231.

[0066] With reference to [Fig.4], a longitudinal beam 230 comprises a beam body 29, preferably of closed and watertight section, and a beam floor 28. The beam floor 28 extends on both sides of the beam body 29.

[0067] With reference to [Fig.3], each drain pipe 5 is associated with a door 231. In this example, each door 231 comprises two drain pipes 5 which extend longitudinally, in particular, at each angular end of said door 231 in a plane transverse to the axis of the gondola X. In other words, the drain pipes 5 extend on either side of each longitudinal beam 230 when the doors 231 are in the closed position as illustrated in [Fig.3].

[0068] With reference to [Fig.4], several variants of the longitudinal beam assembly 230 and door 231 with an evacuation conduit 5 are shown. In this example, the door 231 comprises a radially internal wall 231e, designated internal wall, and a radially external wall 231e, designated external wall 231e.

[0069] In the first variant 4a of [Fig. 4], the exhaust duct 5 is positioned between the inner wall 231i and the outer wall 231e of the door 231. This provides radial protection for the duct. In variant 4b of [Fig. 4], the exhaust duct 5 extends along the entire length of the outer wall 231e of the door 231. In other words, the exhaust duct 5 forms part of the outer surface of the reversing device 23. This increases its cross-section and thus the cooling airflow. In variant 4c of [Fig. 4], the cross-section of the longitudinal beam 230, in particular the beam body 29, is reduced to further increase the cross-section of the exhaust duct 5. Specifically, the longitudinal beam 230 defines a recess into which the exhaust duct 5 extends when the door 231 is in the closed position.In other words, in the closed position, the drain pipe 5 is positioned radially outside the longitudinal beam 230.

[0070] Variants 5a, 5b, and 5c correspond respectively to variants 4a, 4b, and 4c of [Fig. 4] with a thermal protection element 6 positioned in contact with the discharge pipe 5 so as to limit heating of the longitudinal beam 230, in particular the beam body 29. The thermal protection element 6 is positioned at the interface between the discharge pipe 5 and the longitudinal beam 230 in the closed position. This limits the risk of fire propagation in the longitudinal beam 230, which defines the structure of the thrust reversing device 23. Preferably, the thermal protection element 6 is in the form of a mat of insulating material such as quartz wool or a porous material made from ceramic, and encapsulated between sheets of stainless steel.

[0071] According to one aspect of the invention, with reference to [Fig. 6], a drain duct 5 comprises at least one ventilation outlet 54 dedicated to cooling a hinge 233 of a door 231. Thus, the cooling airflow Fr allows to be evacuated, on the one hand, at the level of the exit openings 52 and, on the other hand, at the level of the ventilation outlet(s) 54. Preferably, the evacuation line 5 includes a controllable valve depending on the opening position of the door 231 to control the supply to the ventilation outlet(s) 54.

[0072] The ventilation opening 41 is formed in the blower hood 22 at a predetermined angular position, for example at 12 o'clock as illustrated in [Fig. 2]. According to one aspect, as illustrated in [Fig. 7], the blower hood 22 includes a distribution element 410 connected to the ventilation opening 41 and configured to circumferentially guide the cooling airflow Fr and inject a plurality of elementary flows Fre into the blower compartment 32 at different angular positions. This improves cooling when the partition 24 includes a plurality of inlet openings 51 at different angular positions. The cooling is more homogeneous.

[0073] With reference to [Fig. 8], a second embodiment of a thrust reversal device 23 is shown. In this example, each drain pipe 5 extends into a longitudinal beam 230. In this example, each beam 230 includes a drain pipe 5 that extends longitudinally. The drain pipe 5 is preferably formed in the beam floor 28.

[0074] With reference to [Fig. 9], an exhaust duct 5 is shown according to one aspect of the invention with the doors 231 concealed. In this example, the exhaust duct 5 comprises a unit channel 50a, positioned upstream, which divides into a plurality of elementary channels 50b so as to distribute the cooling airflow Fr to several angularly distributed outlet openings 52. This advantageously reduces the number of inlet openings 51 in the partition wall 24, thereby ensuring optimal protection. A plurality of outlet openings 52 distributes the cooling airflow Fr, thus limiting drag.

[0075] The longitudinal beam 230 comprises an inner wall 230i and an outer wall 230e. In terms of manufacturing, the discharge conduit 5 is formed between the two walls 230i and 230e, which allows for the precise and simple fabrication of the unit channel 50a and the individual channels 50b. In this example, only the outer wall 230e of the longitudinal beam 230 is machined, thus reducing manufacturing costs. It is understood that only the inner wall 230i could be machined.

[0076] It goes without saying that such characteristics also apply to an exhaust duct 5 formed in a door 231. The door 231 could include a unit channel 50a, positioned upstream which divides into a plurality of elementary channels 50b so as to distribute the cooling airflow Fr to several outlet openings 52 distributed angularly at the downstream end of the door 231.

[0077] According to one aspect, with reference to figures 10 and 11, the thrust reversing device 23 comprises, at its downstream end, an evacuation notch 62 at the interface between a longitudinal beam 230 and a door 231 into which the evacuation conduit 5 opens. In this example, the evacuation conduit 5 is delimited in part by a sealing gasket 63. Preferably, the cooling airflow Fr is evacuated tangentially.

[0078] Such an exhaust notch 62 makes it possible to create a dedicated space for the evacuation of the cooling airflow Fr without creating drag, since the evacuation through the exhaust notch 62, which forms the outlet opening 52, avoids turbulence. Furthermore, the formation of an exhaust notch 62 eliminates the need for a very thin longitudinal beam 230 at the downstream end with precise dimensions. Manufacturing is thus simplified.

[0079] Such an evacuation notch 62 also makes it possible to reduce the risk of deformation of the outlet section under the effect of aerodynamic loads on the longitudinal beams 230.

[0080] In Figures 10 and 11, a drainage channel 5 formed in a longitudinal beam 230 and discharged into a drainage notch 62 formed at an angular end of the trailing edge of the longitudinal beam 230 has been shown. It is understood that a drainage notch 62 could also be formed at an angular end of the trailing edge of a door 231 to avoid forming a door 231 of very small thickness when the drainage channel 5 is formed in the door 231.

[0081] According to one aspect of the invention, with reference to [Fig. 12], the outlet openings 52 have a chevron shape so as to improve the evacuation of the cooling airflow Fr. In this example, the outlet openings 52 are formed in the main beam 230, but they could be formed on the doors 231. The chevrons can be formed on either the inner or outer wall. Such a cutout makes it possible to increase the outlet cross-section while maintaining a constant trailing edge thickness.

[0082] With reference to figures 13 and 14, a nacelle 2 is shown which includes a cylindrical ferrule 25 which extends in the downstream extension of the thrust reversing device 23. A thrust reversing device 23 with gates is shown here, but the invention applies to any type of thrust reversing device 23, in particular, with grids.

[0083] Preferably, the cylindrical shell 25 includes auxiliary exhaust ducts 250, preferably longitudinal, to allow the evacuation of the cooling airflow Fr which is guided by the exhaust ducts 5 of the thrust reversing device 23 formed in a longitudinal beam 230 and / or a door 231. Thus, the auxiliary exhaust ducts 250 include openings inlet ports are aligned with the outlet openings 52 of the exhaust ducts 5 of the thrust reversing device 23. Referring to [Fig. 14], the auxiliary exhaust ducts 250 include outlet openings 520 at the downstream end of the cylindrical shell 25, specifically at its trailing edge. Thus, the cylindrical shell 25 allows the exhaust ducts 25 of the reversing device 23 to be extended and even branched in order to optimally evacuate the cooling airflow Fr and reduce drag.

[0084] In a manner analogous to the discharge pipes 5 of the thrust reversing device 23, the auxiliary discharge pipes 250 are preferably formed in the thickness of the cylindrical shell 25.

[0085] With reference to [Fig. 15], a third embodiment of a thrust reversal device 23 is shown. In this example, each discharge pipe 5 extends internally to a door 231.

[0086] With reference to figures 15 to 17, a thrust reversal device 23 with gates is shown in which at least one discharge conduit 5 extends, in part, internally to the gate 231, that is to say, at a distance from its angular ends defined in a plane transverse to the axis X.

[0087] The discharge duct 5 comprises an upstream portion 5a which is fixed and a downstream portion 5b which is movable. The downstream portion 5b preferably belongs to the gate 231. Preferably, a sealing element 53 is mounted at the interface of the upstream portion 5a and the downstream portion 5b to ensure flow with reduced leakage of the cooling airflow Fr. In this example, with reference to [Fig. 15], the downstream portion 5b is in the form of an enclosure that feeds several outlet openings 52.

[0088] Thus, when the door 231 is closed, the cooling airflow Fr flows successively into the upstream portion 5a through the inlet opening 51 and then into the downstream portion 5b before escaping via the outlet opening 52. When the door 231 is open, the cooling airflow Fr flows into the upstream portion 5a through the inlet opening 51 and is then discharged directly at the opening area of ​​the door 231. The cooling airflow Fr advantageously contributes to thrust reversal.

[0089] With reference to figures 18 to 21, a thrust reversal device 23 with grids is shown comprising at least one discharge conduit 5.

[0090] The thrust reversing device 23 comprises an upstream module 23a which is fixed and a downstream module 23b which is movable (also called a "moving cowl"), in particular, configured to translate downstream in order to form an air passage opening between the upstream module 23a and the downstream module 23b. During the translation, a set of deflection flaps 27 is configured to move in the air stream of the turbomachine. This air passage opening includes a set of grids 8 which allows to straighten part of the airflow circulating internally to the thrust reversing device 23.

[0091] With reference to Figures 18 and 19, the discharge pipe 5 comprises an upstream portion 5a integral with the upstream module 23a, which is fixed, and a downstream portion 5b integral with the downstream module 23b, which is movable. Preferably, a sealing element 53 is mounted at the interface of the upstream portion 5a and the downstream portion 5b to ensure flow with reduced leakage of the cooling airflow Fr.

[0092] Thus, when the thrust reversing device 23 is not active, the cooling airflow Fr flows successively into the upstream portion 5a through an inlet 51 and then into the downstream portion 5b before escaping via the outlet 52. When the thrust reversing device 23 is active, an airflow from the turbomachine is guided by the set of deflector flaps 27 into the upstream air passage opening by the set of grilles 8, as illustrated in [Fig. 19]. The cooling airflow Fr flows into the upstream portion 5a through the inlet 51 and is then discharged directly at the air passage opening, since the downstream portion 5b is offset downstream.

[0093] Figures 20 and 21 show one embodiment of a discharge channel 5 which is mounted in a thrust reversal device 23 with grids. The discharge channel 5 extends close to the beam 230.

Claims

Demands

1. Nacelle (2) for an aircraft turbomachine (100), the nacelle (2) extending longitudinally along a nacelle axis (X) and is capable of guiding an upstream to downstream airflow, the nacelle (2) comprising: • At least one fan cowl (22) comprising at least one ventilation opening (41) configured to supply a fan compartment (32) with a cooling airflow (Fr), • At least one thrust reverser device (23) mounted downstream of the fan cowl (22), • a partition (24), extending transversely to the nacelle axis (X), mounted between the fan cowl (22) and the thrust reverser device (23),• Nacelle (2) characterized in that the thrust reversing device (23) comprises at least one discharge duct (5) including at least one inlet opening (51) formed in the partition (24) and at least one outlet opening (52) formed in a downstream end of the thrust reversing device (23) so as to permit the discharge of the cooling airflow (Fr) out of the blower compartment (32).

2. Nacelle (2) according to claim 1, wherein the blower hood (22) is free from an opening for the evacuation of the cooling airflow (Fr).

3. Nacelle (2) according to any one of claims 1 to 2, comprising at least one distribution member (410) connected to the ventilation opening (41) and configured to circumferentially guide the cooling airflow (Fr) and inject a plurality of elementary flows (Fre) into the blower compartment (32) at different angular positions.

4. Nacelle (2) according to any one of claims 1 to 3, wherein the nacelle (2) comprises a plurality of outlet openings (52) formed in the downstream end of the thrust reversing device (23) connected to the discharge line (5).

5. Nacelle (2) according to any one of claims 1 to 4, wherein the thrust reversing device (23) comprises at least two doors (231) hinged on two longitudinal beams (230).

6. Platform (2) according to claim 5, in which at least one discharge pipe (5) is positioned between a longitudinal beam (230) and a door (231).

7. Platform according to any one of claims 5 to 6, wherein the exhaust pipe (5) includes at least one ventilation outlet (54) dedicated to cooling a hinge (233) of a door (231).

8. Nacelle according to any one of claims 1 to 4, wherein the thrust reversing device (23) is a grid thrust reversing device.

9. Nacelle according to any one of claims 1 to 8, comprising a cylindrical shell (25) which extends in the downstream extension of the thrust reversing device (23), the cylindrical shell (25) comprising at least one auxiliary discharge conduit (250) to permit the discharge of the cooling airflow (Fr) which is guided by the thrust reversing device (23).

10. A method for cooling a fan compartment (32) of an aircraft turbomachine (100) and nacelle (2) assembly according to any one of claims 1 to 9, the method comprising steps of: • Supplying the fan compartment (32) with a cooling airflow (Fr) from the ventilation opening (41) of the fan cowl (22), • Evacuating the cooling airflow (Fr) out of the fan compartment (32) through the exhaust duct (5) of the thrust reverser device (23).

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