Air intake of an aircraft turbofan nacelle

Abstract

An intake pipe (1) of an aircraft turbine nacelle, comprising a lip (2), a downstream portion (3), and an inner partition wall (5) separating the lip (2) from the downstream portion (3), the lip (2) defining an annular cavity (24), the downstream portion (3) including a downstream inner wall (31) and a downstream outer wall (32), the intake pipe (1) including a gas delivery pipe (4) for delivering a hot air flow (Fac) into the annular cavity (24), a channel opening (51) formed in the inner partition wall (5), an exhaust opening (34) formed in the downstream outer wall (32), an exhaust pipe (6) installed in the downstream portion (3) for discharging the hot air flow (Fac) and including a first end (7, 9) connected to the inner partition wall (5), a second end (8) connected to the downstream outer wall (32), and a body (61) including at least one flexible portion.

Description

Technical Field

[0001] The present invention relates to the field of aircraft turbines, and more particularly to an intake duct of an aircraft turbine nacelle. Background Art

[0002] It is known that, with reference to Figure 1 , an aircraft includes one or more turbines 100 that extend longitudinally along an axis X and enable the aircraft to move by an inflow air flow F that flows from upstream to downstream in the turbines 1. Hereinafter, the terms "upstream" and "downstream" are defined relative to the axis X that extends from upstream to downstream. Similarly, the terms "inner" and "outer" are defined along a radial direction relative to the axis X.

[0003] As Figure 1 shown, the turbine 100 sequentially includes a compressor 101, a combustion chamber 102, and a turbine 103 that drives the compressor 101 by rotation from upstream to downstream. The turbine 100 further includes a fan 104 located upstream of the compressor 101 and a nacelle 105 that extends radially outward from the fan 104, and the fan 104 rotates around the axis X to accelerate the inflow air flow F along the axis X.

[0004] It is known that the nacelle 105 includes an intake duct 106 that extends upstream of the fan 104, thereby separating the inflow air flow F into an inner air flow Fint that flows toward the fan 104 and an outer air flow Fext that flows to the outside of the nacelle 105. The intake duct 106 includes an upstream portion 107 and a downstream portion 108 that are referred to as "lips" by those skilled in the art. In the Figure 1 example, the lip 107 is separated from the downstream portion 108 by an inner partition wall 109.

[0005] Still with reference to Figure 1 , the lip 107 includes an inner wall 110 facing the axis X and an outer wall 111 opposite to the inner wall 110, and the inner wall 110 and the outer wall 111 are connected by an upstream wall 112 to form an annular cavity 113 that is referred to as a "D-shaped duct" by those skilled in the art with the inner partition wall 109. The downstream portion 108 further includes a downstream inner wall 114 that is an extension of the inner wall 110 of the lip 107 and a downstream outer wall 115 that is an extension of the outer wall 111, and the downstream inner wall 114 and the downstream outer wall 115 jointly define an inner cavity 116, and one or more acoustic attenuation plates are usually installed in the inner cavity 116.

[0006] It is known that during flight of the aircraft, due to temperature and pressure conditions, ice is likely to accumulate at the lip 107 until ice blocks are formed, thereby causing the ice blocks to break off from the lip 107 and be sucked into the turbine 100. In order to improve the service life of the turbine 100 and reduce failures, such suction must be avoided.

[0007] To avoid icing, the pneumatic de-icing devices known in the prior art include ducts for conveying a pressurized hot air flow into the annular cavity 113 for heating walls 110, 111, 112 at the lip 107. The flow of the pressurized hot air mainly comes from the compressor 101 of the turbine 100. Such a de-icing device is specifically disclosed in patent application W02010012899.

[0008] To ensure that the hot air flow fed in is discharged from the annular cavity 113, patent applications EP0922842A1 and US2014263837 disclose exhaust ducts that communicate with the annular cavity 113 and open to the outer wall 115 of the downstream portion 108 of the intake duct 106 to discharge the hot air flow to the outside of the nacelle 105. Refer to Figure 1 , the exhaust duct 200 extends into the inner cavity 116 of the downstream portion 108 of the intake duct 106. In practice, the exhaust duct 200 is in the form of a titanium elbow, one end of which opens to the inner partition wall 109 and the other end opens to the outer wall 115 of the downstream portion 108 of the intake duct 106.

[0009] The disadvantage of such an exhaust duct 200 is that it is quite heavy to withstand significant mechanical forces during the flight of the aircraft, especially the mechanical forces caused by thermal expansion.

[0010] In practice, to achieve a firmly rigid connection, it is known to provide titanium plates at the ends of the exhaust duct 200, which are respectively connected to the inner partition wall 109 and the downstream outer wall 115. Conventionally, seals are also added to the connection interfaces to ensure sealing. The addition of titanium plates and seals is even more disadvantageous to the weight of such an exhaust duct 200.

[0011] Incidentally, patent application US2017 / 191585A1 discloses a method for manufacturing a fiber-reinforced thermoplastic duct through a silicone mandrel.

[0012] Therefore, the present invention aims to simply and efficiently discharge the hot air flow fed into the annular cavity by a system that can withstand mechanical forces and has a small weight. Summary of the Invention

[0013] The present invention relates to an intake duct of an aircraft turbine nacelle, the aircraft turbine extending longitudinally along an axis X, and an air flow flowing from upstream to downstream in the aircraft turbine. The intake duct includes a lip extending upstream, a downstream portion, and an inner partition wall separating the lip from the downstream portion. The lip includes an inner wall facing the axis X, an outer wall opposite to the inner wall, and an upstream wall connecting the inner wall and the outer wall and defining an annular cavity together with the inner partition wall. The downstream portion includes a downstream inner wall and a downstream outer wall that are respectively extensions of the inner wall and the outer wall of the lip, and defines an inner cavity between the downstream inner wall and the downstream outer wall. The intake duct includes:

[0014] i. A de-icing device, comprising at least one conduit for feeding a hot air flow into an annular cavity of the lip;

[0015] ii. At least one channel opening formed in the inner partition wall;

[0016] iii. At least one exhaust opening formed in the outer wall of the downstream portion of the downstream part; and

[0017] iv. At least one exhaust pipe disposed in the inner cavity of the downstream part, configured to guide the hot air flow from the channel opening of the inner partition wall to the exhaust opening of the outer wall of the downstream part, so as to discharge the hot air flow to the outside of the intake pipe, the exhaust pipe including a first end connected to the inner partition wall, a second end connected to the outer wall of the downstream part of the downstream part, and a main body extending between the first end and the second end.

[0018] The remarkable feature of the present invention is that the main body of the exhaust pipe includes at least one flexible portion. By means of the present invention, the exhaust pipe can withstand mechanical forces related to the intake pipe and stresses generated by thermal expansion of the material. In fact, the flexible portion of the main body can be slightly deformed corresponding to the mechanical forces and stresses involved in the intake pipe. The flexible portion advantageously weakens the vibration between the ends of the exhaust pipe. In addition, compared with the titanium pipe of the prior art, this exhaust pipe has a smaller weight. Different from the prior art, this exhaust pipe does not require additional strengthening members at the first end and the second end, thereby further reducing the weight. Since the flexible portion provides a greater assembly tolerance, the assembly is further simplified.

[0019] Preferably, the intake pipe includes an exhaust pipe sufficient to discharge the hot air flow in the annular cavity.

[0020] According to one aspect of the present invention, the flexible portion of the main body includes at least one elastomer, preferably silicone resin. This material can be deformed and withstand the high temperature of the hot air flow up to 300 °C.

[0021] Preferably, the elastomer is reinforced by fibers, preferably by glass fibers or carbon fibers, so as to increase the mechanical strength of the exhaust pipe without affecting its weight.

[0022] According to the first aspect of the present invention, the main body includes a downstream portion and an upstream portion, and the downstream portion is the flexible portion. Preferably, the main body only includes a downstream portion and an upstream portion. Advantageously, the downstream portion connected to the outer wall of the downstream part is the part that bears most of the mechanical forces. The flexible characteristic of the downstream portion enables most of the forces applied to the exhaust pipe to be responded to.

[0023] Preferably, the upstream part of the body is rigid to provide greater mechanical strength to the exhaust pipe. Preferably, the upstream part has a smaller cross-section than the downstream part. The strengthened upstream part enables deformation of the small cross-section to be reduced.

[0024] According to a preferred aspect, the downstream part is sealingly connected to the upstream part, preferably by means of a threaded connection, to ensure that the hot air flow is completely discharged to the outside of the intake pipe.

[0025] According to a second aspect of the invention, the body only comprises a flexible part, which reduces the weight and gives the exhaust pipe greater deformation capacity.

[0026] According to another aspect of the invention, the first end of the exhaust pipe is a first plate, which is preferably a metal plate, preferably a metal plate comprising a titanium alloy. Preferably, the second end of the exhaust pipe is a second plate, which is preferably a metal plate, preferably a metal plate comprising a titanium alloy. This end enables a sealed and rigid connection to the inner partition wall and the downstream outer wall of the downstream part.

[0027] Preferably, the flexible part comprises an outer wall with ribs.

[0028] The invention also relates to an aircraft turbine extending longitudinally along an axis X, in which an air flow flows from upstream to downstream, the turbine comprising a nacelle, the nacelle comprising an intake pipe as described above.

[0029] The invention also relates to a method for discharging a hot air flow, the hot air flow being sent by the de-icing device into an annular cavity at the lip of the intake pipe as described above, wherein the exhaust pipe conveys the hot air flow from the passage opening of the inner partition wall to the exhaust opening of the downstream outer wall so as to discharge the hot air flow to the outside of the intake pipe. Description of the Drawings

[0030] The invention will be better understood from the following description given by way of example only and with reference to the drawings given as non-limiting examples, in which the same reference numerals are used to denote similar objects, wherein:

[0031] Figure 1 is a longitudinal sectional view of an intake pipe of a prior art turbine;

[0032] Figure 2 is a longitudinal sectional view of an intake pipe of a turbine according to the invention;

[0033] Figure 3 is a perspective view of an intake pipe according to a first embodiment of the invention;

[0034] Figure 4 is a perspective view of an intake pipe according to a second embodiment of the invention;

[0035] Figure 5 is a perspective view of the intake duct of an alternative embodiment of the present invention.

[0036] It should be noted that the drawings illustrate the present invention in detail for implementing the present invention, and of course, the drawings can be used to better define the present invention when appropriate. Detailed Embodiments

[0037] Reference Figures 2 to 5 , the present invention enables the hot air flow for preventing icing in the intake duct of an aircraft turbine to be discharged in a simple and effective manner.

[0038] As previously mentioned, reference Figure 2 , the aircraft turbine 10 extends longitudinally along the axis X and enables the aircraft to move through the inflow air flow F flowing from upstream to downstream in the turbine 10. Hereinafter, the terms "upstream" and "downstream" are defined relative to the axis X extending from upstream to downstream. Similarly, the terms "inside" and "outside" are defined along the radial direction relative to the axis X.

[0039] As Figure 2 shown, the turbine 10 sequentially includes a compressor 11, a combustion chamber 12, and a turbine 13 that drives the compressor 11 by rotation from upstream to downstream. The turbine 10 further includes a fan 14 located upstream of the compressor 11 and a nacelle 15 extending radially outward from the fan 14. The fan rotates around the axis X to accelerate the inflow air flow F along the axis X. The nacelle 15 includes an intake duct 1 extending upstream of the fan 14, thereby dividing the inflow air flow F into an internal air flow Fint flowing toward the fan 14 and an external air flow Fext flowing toward the outside of the nacelle 15. The intake duct 1 of the nacelle 15 is described in more detail below.

[0040] Still referring to Figure 2 , the intake duct 1 includes an upstream portion 2, which is referred to as a "lip" by those skilled in the art, and a downstream portion 3. The upstream portion 2 and the downstream portion 3 are separated by an inner partition 5. The intake duct 1 further includes an anti-icing device configured with a gas delivery pipe 4 for feeding a hot air flow Fac ( Figure 3 and Figure 4 ), and the anti-icing device is installed in the lip 2 to heat the lip 2 to avoid icing. The intake duct 1 further includes an exhaust pipe 6 installed in the downstream portion 3 for discharging the hot air flow Fac fed by the gas delivery pipe 4 to the outside of the intake duct 1.

[0041] As Figure 2 , Figure 3 and Figure 4As shown, the lip edge 2 has an inner wall 21 facing the axis X and an outer wall 22 opposite to the inner wall 21. These inner wall 21 and outer wall 22 are connected by an upstream wall 23 to form an annular cavity 24 with an inner partition wall 5. The annular cavity 24 is also known as the "D-shaped duct" by those skilled in the art.

[0042] The air delivery pipe 4 of the hot air flow Fac of the de-icing device is installed in the annular cavity 24. Figure 3 and Figure 4 In the example of, the air delivery pipe 4 is arranged circumferentially around the axis X in the annular cavity 24 and includes a plurality of holes for sending the hot air flow Fac into the entire annular cavity 24, so as to uniformly heat the walls 21, 22, 23 of the lip edge 2. Such an air delivery pipe 4 is known to those skilled in the art.

[0043] As Figure 2 , Figure 3 and Figure 4 shown, the downstream part 3 of the air inlet pipe 1 includes a downstream inner wall 31 and a downstream outer wall 32, which are respectively extension parts of the inner wall 21 and the outer wall 22 of the lip edge 2. The downstream part 3 also includes an inner cavity 33 defined by the downstream inner wall 31, the downstream outer wall 32 and the inner partition wall 5.

[0044] Referring to Figure 3 and Figure 4 , the inner partition wall 5 is additionally provided with a channel opening 51, so that the annular cavity 24 of the lip edge 2 and the inner cavity 33 of the downstream part 3 are in fluid communication. Preferably, the inner partition wall 5 is provided with a plurality of channel openings 51, and these channel openings 51 are in the form of slots. Further preferably, the channel openings 51 are parallel to each other. However, it goes without saying that the inner partition wall 5 can be provided with a channel opening 51 of other sizes and shapes. The inner partition wall 5 can also be provided with a plurality of channel openings 51 distributed at different angular positions in the circumferential direction of the axis X.

[0045] Still referring to Figure 3 and Figure 4 , similar to the inner partition wall 5, the downstream outer wall 32 is provided with an exhaust port 34 for fluidly connecting the inner cavity 33 of the downstream part 3 with the outside of the air inlet pipe 1. Preferably, the downstream outer wall 32 is provided with a plurality of exhaust ports 34, and these exhaust ports 34 are in the form of slots and are parallel to each other. However, it goes without saying that the downstream outer wall 32 can be provided with an exhaust port 34 of other sizes and shapes. The downstream outer wall 32 can also be provided with a plurality of exhaust ports 34 distributed at different angular positions in the circumferential direction of the axis X.

[0046] As Figure 3 and Figure 4 shown, the exhaust pipe 6 is installed in the inner cavity 33 of the downstream part 3 and is configured to fluidly connect the channel opening 51 of the inner partition wall 5 with the exhaust port 34 of the downstream outer wall 32, so as to discharge the hot air flow Fac in the annular cavity 24 to the outside of the air inlet pipe 1.

[0047] In this example, the intake pipe 1 has a channel opening 51 and an exhaust port 34, and the exhaust pipe 6 is configured to fluidly connect the single channel opening 51 of the inner wall 5 to the single exhaust port 34. Of course, depending on the configuration, the exhaust pipe 6 can fluidly connect one or more channel openings 51 of the inner wall 5 to one or more exhaust ports 34 of the downstream outer wall 32. Preferably, the intake pipe 1 includes an exhaust pipe 6 sufficient to discharge the hot air stream Fac. However, it goes without saying that the intake pipe 1 can include a plurality of exhaust pipes 6 distributed at different angular positions circumferentially around the axis X, and each exhaust pipe 6 realizes fluid communication between one or more channel openings 51 and one or more exhaust ports 34.

[0048] Reference Figure 3 and Figure 4 , the exhaust pipe 6 includes a first end 7, 9 connected to the inner partition wall 5, a second end 8 connected to the downstream outer wall 32, and a body 61 extending between the first end 7, 9 and the second end 8. In Figure 3 and Figure 4 's example, the first ends 7, 9 extend substantially in a direction perpendicular to the second end, so that the body 61 is curved to connect the first ends 7, 9 and the second end 8. Preferably, the body 61 is circularly curved to ensure that the hot air stream Fac flows with low pressure loss. In addition, in Figure 3 and Figure 4 's example, the cross-section of the exhaust pipe 6 is rectangular, but it goes without saying that the cross-section can be other shapes, such as circular.

[0049] In this example, the cross-section of the body 61 generally increases from upstream to downstream to facilitate discharge.

[0050] According to the present invention, as Figure 3 and Figure 4 shown, the body 61 of the exhaust pipe 6 has at least one flexible portion 60, 62. As will be elaborated later, according to Figure 3 shown in the first embodiment of the present invention, the body 61 is completely flexible, or for Figure 4 shown in the second embodiment of the present invention, the body 61 is partially flexible. Contrary to the term "rigid", the term "flexible" used here refers to the ability of the body 61 to bend slightly without breaking, that is, the ability to withstand mechanical deformation D. The flexible portion is opposite to the rigid metal portion known in the prior art.

[0051] Preferably, the flexible portions 60, 62 of the body 61 include an elastomer, such as silicone resin, which has good flexibility and can withstand the high temperature of the intake pipe 1. Preferably, the elastomer is reinforced with fibers to increase the mechanical strength of the exhaust pipe 6, and the fibers are preferably glass fibers or carbon fibers.

[0052] Also preferably, as Figure 5As shown, the flexible portion 60 has a ribbed outer wall 66 to increase its mechanical strength. In this example, the ribbed outer wall 66 includes longitudinal ribs 67 extending along the length direction of the flexible portion 60 (in other words, along the curved axis of the flexible portion 60) and transverse ribs 68. In this rectangular example, the transverse ribs 68 extend along the shape of the cross-section of the flexible portion 60 and advantageously enable the shape of the cross-section of the flexible portion 60 to be maintained. For its part, the longitudinal ribs 67 advantageously provide better mechanical bending strength. It goes without saying that the ribbed outer wall 66 may include only longitudinal ribs 67 or only transverse ribs 68, or even ribs in any direction.

[0053] Advantageously, such an exhaust pipe 6 is capable of absorbing the mechanical forces associated with the intake pipe 1 and is capable of compensating for the thermal expansion of the material of the intake pipe 1 by mechanical deformation D. Therefore, compared with the titanium elbows of the prior art, this exhaust pipe 6 has more durable mechanical strength. Specifically, the mechanical stresses applied at the ends 7, 8, and 9 are significantly reduced. In addition, compared with the titanium elbows of the prior art, the exhaust pipe 6 has a very small weight, which is an important advantage for aviation applications. Such an exhaust pipe 6 has better resistance to mechanical vibration and is easier to assemble.

[0054] The fully flexible body 61 according to the first embodiment of the present invention is described below ( Figure 3 ) and the partially flexible body 61 according to the second embodiment of the present invention ( Figure 4 ).

[0055] According to the first embodiment of the present invention, with reference to Figure 3 , the exhaust pipe 6 includes a fully flexible body 61, which provides the exhaust pipe 6 with a large deformation capacity D. In other words, the body 61 is composed of a flexible portion 60.

[0056] In the Figure 3 example, both the first end 7 and the second end 8 are in the form of plates 70, 80 (referred to as the "first plate 70" and the "second plate 80" respectively), and these plates 70, 80 are configured to abut against the inner partition wall 5 and the downstream outer wall 32 respectively. In this example, both the first plate 70 and the second plate 80 are provided with holes around their perimeters, and the holes are configured to receive fastening rods such as screws or nails for connection. It goes without saying that the first plate 70 and / or the second plate 80 can be connected in other ways, such as by adhesion, but screw connection has the advantages of being firm and durable. It goes without saying that the ends can also be in other forms than plates, however, such plates have the advantage of reducing the overall size.

[0057] Preferably, the first plate 70 and / or the second plate 80 are shape-matched with the inner partition wall 5 and / or the downstream outer wall 32 to improve the sealing performance.

[0058] Preferably, the first plate 70 and / or the second plate 80 are metallic in order to have sufficient mechanical strength. In this example, the plates 70, 80 comprise a titanium alloy. Advantageously, such plates 70, 80 are sufficient to ensure the strength of the exhaust pipe 6. Different from the prior art, there is no need to add reinforcing members and / or seals, which further reduces the weight of the exhaust pipe 6. Thus, the exhaust pipe 6 comprises a body 61 connected to a first rigid plate 70 and a second rigid plate 80 which are preferably metallic. Since the flexible portion 60 attenuates the vibration between the ends of the exhaust pipe 6, a balance between flexibility and rigidity is achieved.

[0059] According to a second embodiment of the present invention, referring to Figure 4 , the body 61 of the exhaust pipe comprises a flexible downstream portion 62 and a rigid upstream portion 63. In this example, the upstream portion 63 is metallic and preferably comprises a titanium alloy.

[0060] Advantageously, the downstream portion 62 compensates for the mechanical forces present in the intake pipe 1, while the upstream portion 63 has greater mechanical strength. Considering that the cross-section of the exhaust pipe 6 is smaller upstream, the increased mechanical strength upstream is advantageous. In addition, the overall size is reduced upstream, and the increased mechanical strength reduces any undesirable clearances of the exhaust pipe. Furthermore, the downstream portion of the exhaust pipe 6 corresponds to the area most prone to mechanical failure under mechanical stress. The use of the flexible downstream portion 62 can reduce the risk of rupture.

[0061] Thus, the second embodiment advantageously combines the advantages of a rigid pipe and a flexible exhaust pipe 6.

[0062] As in the first embodiment, the first end 9 and the second end 8 of the exhaust pipe 6 are in the form of plates 90, 80 (referred to as the "first plate 90" and the "second plate 80") respectively. However, as Figure 4 shown, the first end 9 preferably further comprises a reinforcing member to compensate for the rigidity of the upstream portion 63. In the Figure 4 example, the reinforcing member is in the form of a pier 91 that supports the inner partition wall 5. A seal may also be added to the first end 9.

[0063] Still referring to Figure 4 , the downstream portion 62 is sealingly connected to the upstream portion 63. In this example, the upstream portion 63 includes a first connection end opposite the first end 9, and the first connection end is in the form of a plate 65, referred to as the "third plate 65". Similarly, the downstream portion 62 includes a second connection end opposite the second end 8, and the second connection end is in the form of a plate 64, referred to as the "fourth plate 64". As previously described, the third plate 65 and the fourth plate 64 are provided with holes and are configured for a threaded fit. However, it goes without saying that the downstream portion 62 and the upstream portion 63 may be connected in other ways.

[0064] According to a third embodiment (not shown), the upstream portion 63 and the downstream portion 62 may be flexible and connected together in a modular manner. According to a fourth embodiment of the present invention (not shown), the upstream portion 63 is flexible while the downstream portion 62 is rigid. Reinforcements and / or seals are preferably added to the second end 8, but not to the first end 9. According to a fifth embodiment of the present invention (not shown), the body 61 may include more than two different parts. Specifically, the body 61 may include alternating rigid and flexible parts.

[0065] A method for discharging the hot air flow Fac sent into the annular cavity 24 through the air delivery pipe 4 by means of the exhaust pipe 6 as described above will be described below. Referring to Figure 3 and Figure 4 , the pressurized hot air flow Fac flows into the annular cavity 24 to de-ice the walls 21-23 of the lip 1. Then, the pressurized hot air flow Fac in the annular cavity 24 is sucked through the channel opening 51 and then conveyed through the exhaust pipe 6 to the exhaust port 34, where the hot air flow Fac is discharged to the outside of the intake pipe 1.

[0066] With the above-described invention, the hot air flow Fac sent into the annular cavity 24 of the lip 2 can be discharged in a simple and convenient manner through the exhaust pipe 6 with reduced weight. The flexible nature of the exhaust pipe 6 also absorbs mechanical forces in the intake pipe 1 and compensates for the thermal expansion of the material due to the temperature conditions in the intake pipe 1 during flight, making the exhaust pipe 6 more efficient and durable. The assembly is further simplified because the flexible portions 60, 62 provide a greater assembly tolerance.

Claims

1. An air intake pipe (1) of a nacelle (15) of an aircraft turbine (10), the aircraft turbine (10) extending longitudinally along an axis X, an air flow (F) flowing from upstream to downstream in the aircraft turbine (10), the air intake pipe (1) comprising a lip (2) extending upstream, a downstream portion (3), and an inner partition wall (5) separating the lip (2) from the downstream portion (3), the lip (2) comprising an inner wall (21) facing the axis X, an outer wall (22) opposite to the inner wall (21), and an upstream wall (23) connecting the inner wall (21) and the outer wall (22) and defining an annular cavity (24) with the inner partition wall (5), the downstream portion (3) comprising a downstream inner wall (31) and a downstream outer wall (32) which are respectively extension parts of the inner wall (21) and the outer wall (22) of the lip (2), and defining an inner cavity (33) between the downstream inner wall (31) and the downstream outer wall (32), the air intake pipe (1) comprising: - A de-icing device comprising at least one duct (4) for feeding a hot air flow (Fac) into the annular cavity (24) of the lip (2); - At least one channel opening (51) formed in the inner partition wall (5); - At least one exhaust opening (34) formed in the downstream outer wall (32) of the downstream portion (3) of the air intake pipe (1); and - At least one exhaust pipe (6) disposed in the inner cavity (33) of the downstream portion (3), configured to guide the hot air flow (Fac) from the channel opening (51) of the inner partition wall (5) to the exhaust opening (34) of the downstream outer wall (32) to discharge the hot air flow (Fac) to the outside of the air intake pipe (1), the exhaust pipe (6) comprising a first end (7, 9) connected to the inner partition wall (5), a second end (8) connected to the downstream outer wall (32) of the downstream portion (3), and a body (61) extending between the first end (7, 9) and the second end (8), wherein the air intake pipe (1) is characterized in that the body (61) comprises a downstream portion (62) connected to the second end (8) and an upstream portion (63) connected to the first end (7, 9), the downstream portion (62) is flexible, and the upstream portion (63) of the body (61) is rigid.

2. The intake pipe (1) according to claim 1, characterized in that, The flexible portion (62) of the body (61) comprises at least one elastomer.

3. The intake pipe (1) according to claim 1, characterized in that, The downstream portion (62) is sealingly connected to the upstream portion (63).

4. The intake pipe (1) according to claim 1, characterized in that, The first end (7, 9) of the exhaust pipe (6) is in the form of a first plate (70, 90).

5. The intake pipe (1) according to claim 1, characterized in that, The second end (8) of the exhaust pipe (6) is in the form of a second plate (80).

6. An aircraft turbine (10) that extends longitudinally along an axis X, with an air flow (F) flowing from upstream to downstream in the aircraft turbine (10), the turbine (10) comprising a nacelle (15), characterized in that, The nacelle (15) comprises an air intake pipe (1) as claimed in any one of claims 1 - 5.

7. A method for discharging a hot air stream (Fac), the hot air stream being fed by a de-icing device into an annular chamber (24) of a lip (2) of an intake pipe (1) as described in any one of claims 1-5, characterized in that, The exhaust pipe (6) conveys the hot air flow (Fac) from the channel opening (51) of the inner partition wall (5) to the exhaust opening (34) of the downstream outer wall (32) to discharge the hot air flow (Fac) to the outside of the air intake pipe (1).

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