阅读说明：本技术 包括热空气除冰流的通风口的飞行器涡轮喷射引擎短舱的进气管 (Air intake duct of an aircraft turbojet engine nacelle comprising ventilation openings for a flow of ice removed by hot air ) 是由 塞巴斯蒂安·劳伦特·玛丽·帕斯卡 让-米歇尔·保罗·欧内斯特·诺格斯 马克·凡赛伊夫 弗朗索瓦 于 2020-02-05 设计创作，主要内容包括：一种飞行器涡轮喷射引擎短舱的进气管,该短舱沿轴线X延伸,气流在该短舱中从上游向下游流动,进气管包括内壁(21)和外壁(22),内壁(21)和外壁(22)通过前缘(23)和内隔壁(25)连接,以便形成环形腔(24),进气管(2)包括用于将至少一股热气流FAC注入内腔(24)的部件以及至少一个形成在外壁(21)上以在内腔(24)被加热之后排出热气流FAC的通风口(3),进气管包括至少一个声学构件(5),声学构件(5)位于环形腔(24)中并朝向通风口(3),以便调整声学共振频率和/或衰减由通风口(3)在内腔(24)中形成的声波。(An air inlet duct for a turbojet engine nacelle of an aircraft, the nacelle extending along an axis X and in which an air flow flows from upstream to downstream, the air inlet duct comprising an inner wall (21) and an outer wall (22), the inner wall (21) and the outer wall (22) being connected by a leading edge (23) and an inner partition wall (25) so as to form an annular cavity (24), the air inlet duct (2) comprising means for injecting at least one hot air flow FAC into the inner cavity (24) and at least one ventilation opening (3) formed in the outer wall (21) for discharging the hot air flow FAC after the inner cavity (24) has been heated, the air inlet duct comprising at least one acoustic member (5), the acoustic member (5) being located in the annular cavity (24) and facing the ventilation opening (3) so as to adjust an acoustic resonance frequency and/or attenuate acoustic waves formed in the inner cavity (24) by the ventilation opening (3).)

1. An air inlet duct (2) of an aircraft turbojet engine nacelle (1), the nacelle (1) extending along an axis (X) in which an air flow (F) flows from upstream to downstream, the air inlet duct (2) extending circumferentially around the axis (X) and comprising an inner wall (21) directed towards the axis (X) to direct an inner air flow (INT) and an outer wall (22) opposite the inner wall (21) to direct an outer air flow (EXT), the inner wall (21) and the outer wall (22) being connected by a leading edge (23) and an inner partition-shaped cavity (25) so as to form an annular cavity (24), the air inlet duct (2) comprising means for injecting at least one FAC into the annular cavity (24) and at least one ventilation opening (3) formed in the outer wall (21) so as to discharge the hot air Flow (FAC) after the annular cavity (24) has been heated, characterized in that it comprises at least one acoustic member (5, 25 '), said acoustic member (5, 25') being located in said annular chamber (24) and facing said ventilation opening (3), said acoustic member (5) comprising at least one absorbing material (52) to tune the acoustic resonance frequency and/or to attenuate the sound waves formed by said ventilation opening (3) in said annular chamber (24).

2. An air inlet tube (2) according to claim 1, characterized in that the ventilation opening (3) is provided with a normal axis (N), and that the acoustic member (5) comprises at least one acoustic surface (50, 52) extending in a direction perpendicular to the normal (N) of the ventilation opening (3).

3. An air inlet tube (2) according to claim 1 or 2, characterized in that the ventilation opening (3) is provided with a normal axis (N), the projection of the acoustic surface (52) on the plane (P, Q) of the ventilation opening (3) along the normal axis (N) being larger than the ventilation opening (3).

4. An air inlet tube (2) according to any of claims 1 to 3, characterized in that the ventilation opening (3) is provided with a normal axis (N), the acoustic surface (52) being spaced apart from the ventilation opening (3) along the normal axis (N) by a spacing (N5), the spacing (N5) being greater than the length (P3) of the ventilation opening (3).

5. An air inlet tube (2) according to any of claims 1 to 4, characterized in that the ventilation opening (3) is provided with a normal axis (N), the acoustic surface (52) being spaced from the ventilation opening (3) along the normal axis (N) by a spacing (N52), the spacing (N52) being less than twice the length (P3) of the ventilation opening (3).

6. An air inlet tube (2) according to any of the claims 1 to 5, characterized in that the acoustic member (5) is a corner piece comprising an acoustic surface (50, 52) and a mounting surface (51).

7. An air inlet tube (2) according to claim 6, characterized in that the acoustic surface is formed on the absorbing material (52).

8. An air inlet tube (2) according to any of the claims 1 to 7, characterized in that the acoustic member (5) is connected to the inner surface (22b) of the outer wall (22).

9. An air inlet tube (2) according to any of claims 1-8, characterized in that the acoustic member (5) is connected to an inner partition wall (25) of the annular chamber (24).

10. An air inlet tube (2) according to any of claims 1-9, characterized in that the inner partition wall (25) comprises a recess (50') extending in a direction perpendicular to the normal (N) of the ventilation opening (3).

Technical Field

The present invention relates to the field of aircraft turbo-jet engines, and more particularly to the air intake duct of an aircraft turbo-jet engine nacelle comprising a de-icing device.

Background

In a known manner, an aircraft comprises one or more turbojet engines to allow propulsion of the aircraft by accelerating the airflow from upstream to downstream in the turbojet engine.

Referring to fig. 1, there is shown a turbojet engine 100 extending along an axis X and comprising a fan 101 mounted in a nacelle comprising a casing 102 and rotating about the axis X so as to accelerate an air flow F from upstream to downstream. Hereinafter, the terms "upstream" and "downstream" are defined in the flow direction of the gas flow F. The nacelle comprises, at its upstream end, an air inlet duct 200, which air inlet duct 200 comprises an inner wall 201 facing the axis X and an outer wall 202 opposite the inner wall 201, the inner wall 201 and the outer wall 202 being connected by a leading edge 203, also referred to as "inlet duct rim". Thus, the air inlet duct 200 allows to separate the incoming air flow F into an inner air flow INT guided by the inner wall 201 and an outer air flow EXT guided by the outer wall 202. The inner wall 201 and the outer wall 202 are connected by a leading edge 203 and an inner partition wall 205 so as to define an annular cavity 204 referred to as a "D-duct" by those skilled in the art. Hereinafter, the terms "inner" and "outer" are defined in the radial direction of the axis X of the turbojet engine 100.

In a known manner, during the flight of the aircraft, due to temperature and pressure conditions, ice may accumulate on the leading edge 203 and on the inner wall 201 of the air intake conduit 200 and form ice cubes which may be sucked in by the turbojet engine 100. Such ingestion needs to be avoided in order to increase the life of the turbojet engine 100 and reduce failures.

In order to eliminate ice build-up, with reference to fig. 1, it is known to provide a de-icing device comprising an injector 206 injecting a hot air flow FAC into the annular chamber 204. This circulation of the hot air flow FAC makes it possible to heat the inner wall 201, the outer wall 202 and the leading edge 203 by means of heat exchange, so that the ice cubes melt or evaporate during the accumulation process, thus avoiding the ice cubes to accumulate. Referring to fig. 2 and 3, in a known manner, the annular chamber 204 comprises ventilation openings 103 formed on the outer wall 202 of the air inlet duct 200, so as to discharge the hot air flow FAC after the annular chamber 204 has been heated. Referring to fig. 3, as an example, each vent 103 is elongated, preferably rectangular, in shape along the axis X of the turbojet engine.

In practice, noise, in particular hissing and/or resonating, may occur during the circulation of the external air flow EXT through the ventilation opening 103. This noise increases when the de-icing device stops working.

A straightforward solution to eliminate this drawback is to provide a vent tube to connect the annular chamber 204 with the vent opening of the outer wall of the inlet duct. Preferably, such a ventilation duct allows the vent to be located in a region where the external air flow EXT is low in velocity, thereby reducing noise interference. In fact, the addition of the air duct increases the overall size and weight of the turbojet engine, which is undesirable. In addition, the ventilation duct has the disadvantage of emitting a hot air flow FAC in the vicinity of the heat-sensitive downstream region, for example consisting of composite material.

An object of the present invention is to provide an intake duct including a vent hole formed on an outer wall of an intake duct and causing no noise.

Incidentally, a curved guide grate for discharging the hot air flow is disclosed in patent application US5257498, but it has no effect on the noise.

Disclosure of Invention

The invention relates to an air inlet duct for an aircraft turbojet engine nacelle, the nacelle extending along an axis X in which an air flow flows from upstream to downstream, the air inlet duct extending circumferentially about the axis X and comprising an inner wall directed towards the axis X to direct an internal air flow INT and an outer wall opposite the inner wall to direct an external air flow EXT, the inner and outer walls being connected by a leading edge and the inner partition and forming an annular chamber, the air inlet duct comprising means for injecting at least one hot air flow FAC into the annular chamber and at least one ventilation opening formed in the outer wall for discharging the hot air flow FAC after the annular chamber has been heated.

The invention is remarkable in that it comprises at least one perturbation for perturbing the external air flow EXT, which is located upstream of the vent and projects outwards from the external wall. Advantageously, such a perturbation makes it possible to avoid the formation of acoustic pressure fluctuations in the vicinity of the vent.

Preferably, the width of the perturbation is at least half the width of the vent, more preferably the same as the width of the vent.

According to one aspect, the distance between the disruption member and the vent is from 0.5 to 3 times the length of the disruption member.

According to another aspect, the distance between the perturbation and the vent is less than 2 times the length of the vent.

According to another aspect, the height of the perturbation is 0.2-1 times the length of the perturbation.

Preferably, the perturbation is mounted to the outer wall in the form of an insert.

According to one aspect, the outer wall includes a mounting through-hole upstream of the vent. The disturbance element extends through the mounting through-opening, preferably via the interior of the annular chamber.

According to one aspect, the perturbing member is a deflecting member having a hemispherical outer surface, preferably an elliptical outer surface profile. This advantageously allows outside air to be deflected without interacting with the vent at high velocity.

According to another aspect, the disturbance element is a vortex generation element. The formation of vortices, i.e. turbulent aerodynamic structures, can avoid the formation of acoustic waves. In particular, when the dimensions of the turbulent aerodynamic structure are much smaller than those of the ventilation openings, the noise is small.

Preferably, the vortex generating member is a polyhedron, preferably a tetrahedron or a pyramid.

Preferably, the vortex generating member is convex.

Preferably, the vortex generating member comprises a plurality of ribs.

The invention relates to an air inlet duct for an aircraft turbojet engine nacelle, the nacelle extending along an axis X in which an air flow flows from upstream to downstream, the air inlet duct extending circumferentially about the axis X and comprising an inner wall directed towards the axis X to direct an internal air flow INT and an outer wall opposite the inner wall to direct an external air flow EXT, the inner and outer walls being connected by a leading edge and the inner partition and forming an annular chamber, the air inlet duct comprising means for injecting at least one hot air flow FAC into the annular chamber and at least one ventilation opening formed in the outer wall for discharging the hot air flow FAC after the annular chamber has been heated.

The invention is remarkable in that the vent comprises an upstream edge which is discontinuous in circumferential profile in order to generate turbulence and/or a downstream edge whose radial profile is streamlined in order to reduce the formation of pressure fluctuations.

Advantageously, the turbulent aerodynamic structure formed by the upstream edge makes it possible not to interact with the ventilation openings, thus avoiding the generation of acoustic waves. Advantageously, the streamlined radial profile of the downstream edge allows the flow of the external air flow to be moderated, avoiding any hissing.

According to one aspect, the circumferential profile of the upstream edge has at least one point of discontinuity of curvature on it, in the vicinity of which the tangential direction of the profile is adjusted by an angle greater than 60 °, preferably less than 180 °.

Preferably, the upstream edge comprises 1-8 discontinuities of curvature for generating turbulence.

Preferably, the upstream edge comprises at least two turbulence generating patterns, preferably at least four turbulence generating patterns.

Preferably, the turbulence generating pattern is fan-shaped or V-shaped.

According to one aspect, the upstream edge is inscribed in the aerodynamic line of the outer wall.

According to another aspect, the upstream edge includes an outward bulge.

Preferably, the projection forms an angle of less than 45 ° with the entire plane of the vent.

Preferably, the radial profile of the downstream edge is circular, preferably hemispherical.

According to one aspect, the vent defines an aerodynamic line extending along an outer surface of the outer wall of the air inlet duct. The downstream edge is located inside the aerodynamic line.

According to one aspect, the outer wall comprises a through hole for assembly, the vent being formed in a vent located in the through hole for assembly (preferably assembly from the inside).

The invention relates to an air inlet duct for an aircraft turbojet engine nacelle, the nacelle extending along an axis X in which an air flow flows from upstream to downstream, the air inlet duct extending circumferentially about the axis X and comprising an inner wall directed towards the axis X to direct an internal air flow INT and an outer wall opposite the inner wall to direct an external air flow EXT, the inner and outer walls being connected by a leading edge and the inner partition and forming an annular chamber, the air inlet duct comprising means for injecting at least one hot air flow FAC into the annular chamber and at least one ventilation opening formed in the outer wall for discharging the hot air flow FAC after the annular chamber has been heated.

The invention is remarkable in that it comprises at least one acoustic member located in the annular chamber and facing the ventilation opening in order to adjust the acoustic resonance frequency and/or to attenuate the acoustic waves formed in the annular chamber via the ventilation opening.

Such an acoustic member makes it possible to adjust the resonance frequency or attenuate the sound waves, thereby reducing the noise that may be annoying to local inhabitants. Thus achieving the effect of reducing noise.

Preferably, since the vent is provided with a normal axis, the acoustic member comprises at least one acoustic surface extending in a direction perpendicular to the normal of the vent.

Preferably, the projection of the acoustic surface on the vent plane along the normal axis is larger than the vent.

According to one aspect, the vent is provided with a normal axis along which the acoustic surface is spaced from the vent by a distance that is greater than the length of the vent.

According to another aspect, the vent is provided with a normal axis along which the acoustic surface is spaced from the vent by a spacing that is less than twice the length of the vent.

According to one aspect, the acoustic member comprises at least one absorbing material to form an acoustic surface absorbing sound.

According to one aspect, the acoustic member is in the form of a corner comprising the acoustic surface and the mounting surface.

According to one aspect, the acoustic member is coupled to an inner surface of the outer wall.

According to one aspect, the acoustic member is connected to an inner wall of the annular cavity.

According to one aspect, the inner partition wall comprises an upstream convex face facing the vent.

According to one aspect, the inner partition wall comprises a recess extending in a direction perpendicular to a normal of the vent.

By means of the invention, the comfort of the users in the aircraft and of the local inhabitants is increased by treating the noise sources and noise influences associated with the ventilation openings alternately or simultaneously. Advantageously, the invention makes it possible to blend in a high temperature and high heat environment (heat flow cycle) without affecting the exhaust flow rate and/or increasing the aerodynamic resistance.

The invention can be implemented in a practical manner to act on the acoustic frequencies that are desired to be adjusted.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a cutaway view of a prior art turbojet engine;

FIG. 2 is a cross-sectional view of a prior art inlet duct in which hot air flow for deicing flows;

FIG. 3 is a perspective view of a plurality of vents of the prior art;

FIG. 4 is a cutaway view of a turbojet engine of the present invention;

FIG. 5 is a cross-sectional view of an intake manifold including an upstream perturbation of the present invention;

FIG. 6 is a top view of an upstream baffle associated with the vent of the present invention;

FIG. 7 is a schematic view of a first installation of the deflector of the present invention;

FIG. 8 is a schematic view of a second mounting arrangement for the deflector;

FIG. 9 is a cross-sectional view of an intake pipe including an upstream vortex generating member of the present invention;

FIG. 10 is a perspective view of a first embodiment of an upstream vortex generating member of the present invention;

FIG. 11 is a perspective view of a second embodiment of an upstream vortex generating member of the present invention;

FIG. 12 is a top view of a vent perimeter of the prior art;

13A, 13B and 14 are top views of vents having scalloped upstream edges in accordance with the present invention;

FIGS. 15A, 15B and 16 are top views of vents having V-shaped upstream edges according to the present invention;

FIGS. 17 and 18 are top views of vents having upstream lobes of the present invention;

FIG. 19 is a cross-sectional view of a prior art vent;

FIGS. 20-23 are cross-sectional views of vents of the present invention wherein the radial profile of the downstream edge is streamlined;

FIG. 24 is a partial cross-sectional view of the vent of the present invention installed as an insert in a mounting through-hole;

FIGS. 25 and 26 are schematic views of an acoustic member of the present invention mounted to an inner partition wall by a ring cavity;

FIG. 27 is a schematic view of an acoustic member mounted to an outer wall through an annular cavity;

FIG. 28 is a schematic view of an acoustic member integrated into an inner partition wall;

fig. 29 to 31 are schematic views of an acoustic member including an absorbing material;

Detailed Description

The invention will be described with reference to fig. 4, which fig. 4 shows a turbojet engine 1, the turbojet engine 1 extending along an axis X and comprising a fan 11 mounted in a nacelle comprising a casing 12, the fan 11 rotating about the axis X to accelerate an airflow F from upstream to downstream. Hereinafter, the terms "upstream" and "downstream" are defined in the flow direction of the gas flow F. The nacelle comprises, at its upstream end, an air inlet duct 2, which air inlet duct 2 comprises an inner wall 21 facing the axis X and an outer wall 22 opposite the inner wall 21, the inner wall 21 and the outer wall 22 being connected by a leading edge 23, also referred to as "inlet duct rim". The inlet duct 2 thus allows to separate the incoming air flow F into an internal air flow INT guided by the inner wall 21 and an external air flow EXT guided by the outer wall 22. The inner wall 21 and the outer wall 22 are connected by a leading edge 23 and an inner partition wall 25 to define an annular chamber 204 referred to by those skilled in the art as a "D-duct". In the following, the terms "inner" and "outer" are defined in the radial direction of the axis X of the turbojet engine 1.

The inlet pipe 2 comprises a de-icing arrangement comprising means 26, such as an injector, for injecting a hot air flow FAC into the annular chamber 24. This circulation of the hot air flow FAC makes it possible to heat the inner wall 201, the outer wall 202 and the leading edge 203 by means of heat exchange, so that the ice cubes melt or evaporate during the accumulation process, thus avoiding the ice cubes to accumulate. As shown in fig. 4, the annular chamber 24 comprises one or more ventilation openings 3 formed in the outer wall 22 of the inlet pipe 2 in order to exhaust the hot air flow FAC after the annular chamber 24 has been heated. In fact, the ventilation opening 3 is located upstream of the injector 26 with respect to the location of injection of the hot gas flow FAC into the intake pipe 2, where "upstream" here is defined as the circumferential circulation of the hot gas flow from upstream to downstream in the circumferential intake pipe 2.

According to one aspect of the invention, with reference to fig. 5 and 6, the air inlet duct 2 comprises at least one perturbation 4 for perturbing the external air flow EXT, the perturbation 4 being located upstream of the vent 3 and projecting outwards from the outer wall 22. In other words, the turbulence member 4 makes it possible to reduce noise by reducing the influence of external air flow.

The invention will be explained below in the vertical reference frames P, Q, N, with a central axis P extending along the outer wall from upstream to downstream, an axis N extending from inside to outside towards the ventilation opening 3, and an axis Q extending tangentially.

The vents 3 are defined in a vertical reference frame P, Q, N. To this end, as shown in fig. 6, the vent 3 includes a length P3 defined along axis P and a width Q3 defined along axis Q.

In order to be able to optimally influence the upstream external air flow EXT, i.e. the acoustic stimulus, the width Q4 of the perturbation 4 is at least equal to half the width Q3 of the vent 3, preferably equal to the width Q3 of the vent 3, as shown in fig. 6. Preferably, the widths Q3, Q4 are the same in units to reduce aerodynamic disturbances. At the same time, the distance Δ P between the perturbation 4 and the vent 3, defined along the axis P, is 0.5-3 times the length P4 of the perturbation 4. Preferably, the distance Δ P is less than 2 times the length P3 of the vent 3. This advantageously allows the external air flow EXT to be disturbed before it interacts with the vent 3, while reducing air resistance.

[ equation 1]

0,5*P4≤ΔP≤3*P4

[ formula 2]

ΔP≤2*P3

Even more preferably, as shown in FIG. 7, the height N4 of the perturbation 4 defined along the axis N is 0.2-1 times the length P4 of the perturbation 4. This defined height allows to avoid acoustic effects between the external air flow EXT and the ventilation opening 3 while reducing aerodynamic disturbances.

According to one aspect of the invention, referring to FIG. 7, the perturbation 4 is of the same material as the outer wall 22, or is attached to the outer surface 22a of the outer wall 22 in the form of an insert, for example, by bonding, welding, etc. to the outer surface 22a of the outer wall 22. In accordance with another aspect of the invention, referring to fig. 8, the outer wall 22 includes a mounting through-hole 400 located upstream of the vent 3. The interference member 4 passes through the mounting through-hole 400 so as to protrude outwardly from the outer wall 22. As shown in fig. 8, the perturber 4 comprises a mounting base 41, which mounting base 41 is configured to be connected to the inner surface 22b of the outer wall 22, in particular by means of adhesive welding, riveting or the like to the inner surface 22b of the outer wall 22. In other words, depending on the installation and overall size constraints, the perturber 4 can be installed both from the outside (fig. 7) and from the inside (fig. 8).

Two embodiments of the perturbing member 4 will now be described in detail.

Referring to fig. 5 to 8, in the first embodiment, the disturbing member is a deflecting member configured to deflect the external air flow EXT to prevent the external air flow EXT from having grazing incidence during the interaction with the vent 3. The formation of sound pressure fluctuations near the vent 3 is avoided, thereby reducing noise.

Preferably, the deflector has a semi-spherically mounted outer surface 40. This advantageously prevents the flow deviation of the conditioned external gas flow EXTm from being too high. Preferably, the profile of the outer surface 40 is elliptical, i.e., as shown in fig. 5, 7 and 8, the outer surface 40 is inscribed within an elliptical perimeter along an axial cross-sectional plane (N, P). The outer surface 40 allows for adjustment of the flow lines without causing a significant increase in air resistance. The power flow is simply deflected while maintaining minimal disturbances.

Referring to fig. 9 to 11, in the second embodiment, the disturbance is a vortex generation member 4' to generate aerodynamic disturbance. The vortex generating structure is an aerodynamic structure having a turbulent flow characteristic, which prevents sound pressure fluctuations from being generated due to interaction between the external air flow EXT and the vent 3.

The geometrical dimensions of the disturbance element are adapted to the deflection element and the vortex generation element and will not be described in further detail.

As shown in fig. 9 to 11, the vortex generating member 4' is a polyhedron, preferably a tetrahedron (triangular base) or a pyramid (square base). The presence of the faces and/or edges makes it possible to generate vortices EXTv in the external air flow EXT in a plurality of different directions, as illustrated in fig. 9, to generate an external air flow with aerodynamic disturbances.

According to one aspect, with reference to fig. 10, the vortex generating member 4 ' is convex, preferably solid, so as to define a plurality of deflection surfaces 41 ' connected by ridges 42 '. According to another aspect, with reference to fig. 11, the vortex generating member 4 'comprises a plurality of fins 42', these fins 42 'being connected by recesses 43' to significantly disturb the external air flow EXT.

Noise reduction has been described for a single vent 3, but it is understood that a plurality or all of the vents 3 may cooperate with the turbulence members 4, 4' to disturb external air flows having the same or different properties.

When a plurality of turbulence elements 4 and vortex generating members 4' are used together, they may be independent or may be connected together, for example, in a continuous manner between two adjacent ventilation openings 3.

Advantageously, such a turbulence element 4, the vortex generating element 4', makes it possible to act on the source of the noise, i.e. on the external air flow EXT upstream of the vent 3, in order to reduce the generation of acoustic pressure fluctuations.

In a known manner, fig. 12 shows a prior art vent 3, the vent 3 being rectangular and having a length defined by an axis P extending from upstream to downstream. The upstream edge 31 and the downstream edge 32 are curved to reduce mechanical losses.

According to one aspect of the invention, with reference to fig. 13 to 18, the vent 3 comprises an upstream edge 31 and/or a downstream edge 32, the circumferential profile of the upstream edge 31 being discontinuous to generate turbulence, the radial profile of the downstream edge 32 being streamlined to reduce the formation of pressure fluctuations. That is, the edge profile of the vent 3 is improved to reduce acoustic disturbance. The irregular upstream edge 31 makes it possible to form a small turbulent aerodynamic structure which does not generate noise with the ventilation openings 3.

On the one hand, as will be explained later, the circumferential profile of the upstream edge 31 is discontinuous to generate turbulence and thus perturb the upstream external air flow by means of the upstream perturber as previously described. That is, the upstream edge constitutes a disturbance integral to the vent 3. Interaction with the vent 3 is thus avoided.

On the other hand, as will be explained later, the streamlined profile of the downstream edge 32 in the radial direction may reduce the formation of pressure fluctuations. This advantageously prevents the production of hissing sounds. Therefore, the opposing treatment of the opposite edges 31, 32 of the vent 3 alternately or simultaneously makes it possible to cancel the generation of noise.

Preferably, the aspect ratio between the length defined along axis P and the width defined along axis Q of vent 3 is between 2 and 5.

According to one aspect of the invention, the profile of the upstream edge 31 in the circumferential direction has at least one discontinuity 34 of curvature, in the vicinity of which discontinuity 34 of curvature the tangent is modified by an angle Δ T greater than 60 °, preferably less than 180 °. Preferably, the upstream edge 31 comprises at least two, preferably at least four turbulence generating patterns 33. Preferably, the turbulence generating patterns 33 are adjacent to each other. The circumferential profile is defined in a plane (P, Q).

As shown in fig. 13A and 13B, it is shown that the upstream edge 31 including the two fan-shaped turbulence generating patterns 33 defines a curvature discontinuity 34 at the boundary of the two fan-shaped turbulence generating patterns 33, the curvature discontinuity 34 protrudingly extending toward the center of the vent 3. Fig. 13B shows a tangent T1 of the first turbulence generating pattern 33 and a tangent T2 of the second turbulence generating pattern 33, which are separated by an angle Δ T of 160 ° -180 °. This point of curvature discontinuity 34 allows the flow of external air flow EXT to be disturbed before it interacts with downstream edge 32.

According to another embodiment shown in fig. 14, the upstream edge 31 includes four fan-shaped turbulence generating patterns 33 and three curvature discontinuities 34, the three curvature discontinuities 34 protruding and extending toward the center of the vent 3 to generate a large number of aerodynamic disturbances.

Similarly, according to another embodiment illustrated in fig. 15A and 15B, there is shown an upstream edge 31 including two V-shaped turbulence generating patterns 33 'so as to define an interior point of curvature discontinuity 34' while defining a curvature discontinuity 34 'at the intersection with another generating pattern 33'. Also, in this example, the upstream edge 31 includes 3 discontinuities 34 ' of curvature, 1 discontinuity 34 ' of which extends convexly toward the center of the vent 3 and the other 2 discontinuities 34 ' of which extend convexly in opposite directions to generate a large number of aerodynamic disturbances. Similar to fig. 13B, fig. 15B shows a tangent T1 ' of the first turbulence generating pattern 33 ' and a tangent T2 ' of the second turbulence generating pattern 33 ', which are separated by an angle Δ T ' of 90 ° -110 °.

Referring to fig. 16, the upstream edge 31 includes four V-shaped turbulence generating patterns 33 'and 7 discontinuities 34' of curvature, 3 of which discontinuities 34 'protrude toward the center of the vent 3, and the other 4 of which discontinuities 34' protrude in opposite directions to generate a large number of aerodynamic disturbances.

It goes without saying that the number and shape of the turbulence generating patterns 33, 33 'and the number, shape and position of the curvature discontinuities 34, 34' may be varied as desired. Preferably, the upstream edge includes 1 to 8 discontinuities in curvature 34, 34' to create vortices, depending on the desired acoustic effect.

According to one aspect of the invention, the upstream edge 31 is inscribed in, i.e. extends along, the aerodynamic line, which also lies on the plane (P, Q). Such an upstream edge 31 is simple to manufacture. According to another aspect, the upstream edge 31 comprises an outward bulge 35'. As an example, as shown in fig. 17, 18, which shows the upstream edge 31, the upstream edge 31 includes a V-shaped turbulence generating pattern 33 ', and the curvature discontinuity 34 ' protrudes toward the center of the vent 3 and protrudes outward, that is, the curvature discontinuity 34 ' is on the plane (P, Q) in which the vent 3 is located. In other words, the point of discontinuity of curvature 34 'makes it possible to generate turbulence by adjusting the incidence of the external air flow EXT upstream of the vent 3 in the manner of the upstream perturbators 4, 4' as described previously. Preferably, the projection 35' forms an angle θ of less than 45 ° with the entire plane (P, Q) of the vent 3.

Advantageously, the profile of the upstream edge 31 is produced by mechanical cutting, water jet, laser or stamping.

In a known manner, fig. 19 shows with reference to a vent 3 of the prior art, the vent 3 comprising a downstream edge 32, the downstream edge 32 being provided with a rib 320 in the plane (P, Q) of the vent 3, i.e. at the interface with the external air flow EXT sweeping the external wall 22, with the rib 320. This interface line (hereinafter referred to as the "aerodynamic line LA") interacts with the rib 320 of the downstream edge 32 and produces a hissing sound and other noise.

In accordance with one aspect of the invention, as shown in fig. 20-24, the downstream edge 32 has a streamlined profile in the radial direction to reduce the formation of pressure fluctuations, i.e., to avoid shearing of the aerodynamic lines LA by the fins. The radial profile is defined in a plane (P, N).

Preferably, the thickness of the downstream edge 32 is different from the thickness of the upstream edge 31. Preferably, the downstream edge 32 has an increased thickness relative to the upstream edge so as to form a streamlined radial profile. Advantageously, the streamlined radial profile has a continuous curvature, in particular with respect to the aerodynamic line LA, which is not discontinuous. Advantageously, the streamlined radial profile makes it possible to achieve a gradual deflection.

As shown in fig. 20, the downstream edge 32 has an upper streamlined profile 321, in particular a rounded or hemispherical profile, at the aerodynamic line LA. In this embodiment, only the upper portion of the downstream edge 32 is modified.

Referring to fig. 21, the downstream edge 32 is provided as a complete circle or sphere to guide the aerodynamic line LA without turbulence, both inside and outside. As shown in fig. 22 and 23, the downstream edge 32 is inclined towards the inside of the annular chamber 24 to avoid contact between the external air flow EXT and the fins. Referring to fig. 22, the downstream edge 32 is deformed, in particular has an inwardly projecting bulge. Referring to fig. 23, the downstream edge 32 is deformed inwardly so as to be located below the aerodynamic line LA. Preferably, the radial profile of the downstream edge 32 may be formed by local deformation of the material.

According to an aspect of the present invention, referring to fig. 24, the outer wall 22 includes a mounting through-hole 305, and the vent 3 is formed in the vent 300, and the vent 300 is mounted in the mounting through-hole to enable assembly (preferably assembly from the inside). This embodiment is advantageous in that the mounting through-hole 305 can be formed in a simple shape without providing any particular aerodynamic structure to the outer wall 22. Each vent 300 may be manufactured independently and advantageously includes an upstream edge 31 and a downstream edge 32 for reducing acoustic disturbances. As shown in fig. 24, each vent 300, particularly at its upstream and downstream ends 301 and 302, may be connected to the mounting through-hole 305 in the form of an insert. Such an embodiment not only improves the acoustic performance but is also easy to industrialize.

The modification of the upstream edge 31 and/or the downstream edge 32 of the vent 3 enables the vent 3 to be formed with reduced acoustic influence.

The noise reduction of a single vent 3 has been explained, but it will be appreciated that a plurality or all of the vents 3 may include an upstream edge 31 and/or a downstream edge 32 modified in accordance with the present invention.

According to one aspect of the invention, with reference to fig. 25 to 31, the intake pipe 2 comprises at least one acoustic member 5, the acoustic member 5 being mounted in the annular cavity 24 and facing the ventilation opening 3. Towards the vent means that the acoustic member 5 is located away from the vent 3 to avoid alignment with the vent 3 while not disturbing the exit of the hot air flow FAC to achieve processing of the acoustic waves from said vent 3.

Thus, this section handles the acoustic resonance by shifting the frequency out of the resonance region or even by attenuating the sound waves, unlike the way the acoustic stimulus is handled in the first section. Advantageously reducing noise amplification.

As shown in fig. 25 and 26, according to the first embodiment, the acoustic member 5 includes the acoustic surface 50 extending in front of the vent 3. Here, the acoustic surface 50 is substantially planar to improve its efficiency, but curved is also possible. Advantageously, the acoustic surface 50 is acoustically reflective to adjust the acoustic wavelength to reduce resonance. Preferably, the treatment surface 50 is made of a metal or ceramic material to have good high temperature resistance.

As shown in fig. 25, the ventilation opening 3 is provided with a normal axis N, and the projection of the acoustic member 5, the acoustic surface 50, on the plane (P, Q) of the ventilation opening 3 along the normal axis N is larger than the ventilation opening 3 so as to cover all the sound waves entering through the ventilation opening 3. Preferably, the acoustic surface 50 is substantially parallel to the plane (P, Q) of the vent 3. In other words, the acoustic surface 50 extends substantially in a direction perpendicular to the normal N of the vent 3. According to a preferred aspect, as shown in fig. 26, the acoustic surface 50 comprises a curved rim 53 at its circumferential end in order to further guide the hot air flow FAC to be expelled towards the vent 3.

Referring to fig. 25, for optimum acoustic performance, the acoustic member 5 is spaced from the vent 3 along the normal axis by a spacing N5, which spacing N5 is preferably less than 20 mm. This ensures, on the one hand, an optimum hot air discharge and, on the other hand, a frequency shift of the acoustic frequency into a frequency range which is less disturbing to the human ear.

In the embodiment of fig. 25 and 26, the acoustic member 5 is a corner piece defining an acoustic surface 50 and a mounting surface 51. Preferably, the corner piece is L-shaped in cross-section. This simple structure allows to guarantee acoustic efficiency without significantly increasing the mass. As shown in fig. 25, the acoustic member 5 may be connected via its mounting surface 51 to the inner partition wall 25 (fig. 25) of the annular cavity 24 or to the inner surface 22b (fig. 27) of the outer wall 22, such that the acoustic surface 50 extends to the immediate area of the vent 3.

According to another aspect of the invention, with reference to fig. 28, the inner partition wall 25' constitutes the acoustic member 5, which advantageously avoids the addition of an insert. Preferably, the upstream face of the inner partition wall 25 ' comprises a recess 50 ' or flat, which recess 50 ' or flat extends substantially in a direction perpendicular to the normal N of the vent 3, so as to form an acoustic surface for reflecting sound waves entering via the vent 3. In this way, it is advantageous to use the inner partition wall 25' to handle sound waves without increasing the weight of the air inlet tube 20. Preferably, the upstream face of the inner partition wall 25 'is entirely convex and is formed by locally deforming a recess 50' having an acoustic surface.

Referring to fig. 29 to 31, according to one aspect of the invention, the acoustic member 5 comprises at least one absorbing material 52 so as to form an acoustic surface to absorb sound. Preferably, the absorbent material 52 is resistant to high temperatures, for example a high temperature of about 350 ℃, which corresponds to the temperature of the hot air flow FAC used for deicing.

The absorbent material 52 is, for example, porous, in particular metallic, with or without a honeycomb structure. Of course, other materials may be suitable, such as metal foam, ceramic material with a perforated skin, etc.

As shown in fig. 29 and 30, an absorbing material 52 is positioned on the acoustic surface 50 of the embodiment shown in fig. 25 and 27 to significantly reduce noise. In this case, the acoustic surface 50 is conventional and has only a supporting function and is acoustically treated in an absorbing manner together with the absorbing material 52.

In this embodiment, the absorbent material 52 is spaced from the vent 3 along the normal axis by a spacing N52 that is N52 greater than the length P3 of the vent 3. Even more preferably, spacing N52 is less than twice the length P3 of vent 3. This compromise ensures optimum hot air discharge and optimum sound absorption.

Referring to fig. 31, the inner partition wall 25 includes an upstream convex face facing the vent 3, and the absorbent material 52 is directly connected to the inner partition wall 25 facing the vent 3. That is, the acoustic member 5 is formed by the inner partition wall 25 to which the absorbing material 52 is attached.

By means of the invention, the sound waves are treated inside the annular chamber 24, which makes it possible not to affect the overall dimensions of the air inlet tube 2 and of the outer wall 22. The acoustic member makes it possible to keep the acoustic frequencies that may cause noise outside the sensitive range of the human ear.

The reduction of acoustic pollution of a single vent 3 has been explained, but it goes without saying that a plurality or all of the vents 3 can be fitted with acoustic means 5'. When a plurality of acoustic members 5 are used together, the acoustic members may be independent or may be connected together, for example, continuously between two adjacent vents 3.

Advantageously, the various aspects of the invention may be combined with each other for the same vent or for different vents.

Furthermore, the turbulence, deflector or vortex generator may advantageously be associated with a vent 3, the vent 3 having an upstream edge 31 and/or a downstream edge 32, the circumferential profile of the upstream edge 31 being discontinuous to generate turbulence, the radial profile of the downstream edge 32 being streamlined to reduce pressure fluctuations.

Similarly, the perturber, deflector or vortex generator may advantageously cooperate with an acoustic member with or without an absorbing material.

Similarly, an acoustic member with or without absorbent material may be advantageously associated with a vent 3 having an upstream edge 31 and/or a downstream edge 32, the circumferential profile of the upstream edge 31 being discontinuous to generate turbulence, the radial profile of the downstream edge 32 being streamlined to reduce the formation of pressure fluctuations.

According to one aspect of the invention, the acoustic member, with or without absorbent material, can advantageously cooperate in a cumulative manner with the ventilation openings 3 having an upstream edge 31 and/or a downstream edge 32, the circumferential profile of which upstream edge 31 is discontinuous to generate turbulence, and with the turbulence, deflector or vortex generator, the radial profile of which downstream edge 32 is streamlined to reduce the formation of pressure fluctuations.