阅读说明：本技术 用于飞行器的短舱的进气口结构以及相应的短舱和飞行器 (Air intake structure for a nacelle of an aircraft, and corresponding nacelle and aircraft ) 是由 A·波特 J·拉兰纳 F·梅卡 于 2019-09-05 设计创作，主要内容包括：用于飞行器的短舱的进气口结构以及相应的短舱和飞行器。本发明涉及进气口结构,其界定通道,包括：唇缘,具有向后定向的U形截面；第一吸声面板,固定在唇缘后方并界定通道；第二吸声面板,固定在第一吸声面板后方并界定通道。每个吸声面板包括蜂窝状芯部,其固定在内蒙皮与外蒙皮之间,内蒙皮穿有孔并朝向通道定向,外蒙皮沿相反方向定向,其中,第一吸声面板的内蒙皮的厚度大于第二吸声面板的内蒙皮的厚度,内蒙皮中的每一者都包括热源,热源嵌入在内蒙皮的块体中。本发明还涉及包括这种进气口结构的短舱及包括这种短舱的飞行器。这种进气口结构因此可使除冰和吸声表面从进气口唇缘的前部延伸到声学面板的后部。(Air intake structure for a nacelle of an aircraft and corresponding nacelle and aircraft. The present invention relates to an air intake structure defining a channel, comprising: a lip having a rearwardly directed U-shaped cross-section; a first sound absorbing panel secured behind the lip and defining a channel; a second sound absorbing panel secured behind the first sound absorbing panel and defining a channel. Each sound-absorbing panel comprises a honeycomb core fixed between an inner skin perforated with holes and oriented towards the channels and an outer skin oriented in the opposite direction, wherein the thickness of the inner skin of the first sound-absorbing panel is greater than the thickness of the inner skin of the second sound-absorbing panel, each of the inner skins comprising a heat source embedded in a block of the inner skin. The invention also relates to a nacelle comprising such an air intake structure and to an aircraft comprising such a nacelle. Such an air intake structure may thus allow the de-icing and sound absorbing surface to extend from the front of the air intake lip to the rear of the acoustic panel.)

1. An air intake structure (22) for a nacelle (19) of an aircraft (10), the air intake structure (22) defining a passageway (26) and comprising:

a lip (24) having a rearwardly directed U-shaped cross-section,

-a first sound-absorbing panel (28) fixed behind the lip (24) and delimiting the channel (26), and

-a second sound-absorbing panel (30) fixed behind the first sound-absorbing panel (28) and delimiting the channel (26),

wherein each of the first and second sound-absorbing panels (28, 30) comprises a honeycomb core (32, 34) fixed between an inner skin oriented towards the channel (26) and perforated with holes oriented towards the channel (26) and an outer skin oriented in the opposite direction, wherein the inner skin (36) of the first sound-absorbing panel (28) has a thickness greater than the thickness of the inner skin (38) of the second sound-absorbing panel (30), and

wherein each of the inner skins includes a heat source (48, 50) embedded in a block of the inner skin.

2. Air inlet structure (22) according to claim 1, characterized in that the inner skin (36) of the first sound-absorbing panel (28) has a thickness of 3 to 6 mm.

3. Air inlet structure (22) according to claim 1 or 2, characterized in that the inner skin (38) of the second sound-absorbing panel (30) has a thickness of 0.6mm to 2.1 mm.

4. Air inlet structure (22) according to one of claims 1 to 3, characterized in that each honeycomb core (32, 34) has the form of a honeycomb.

5. Air intake structure (22) according to one of claims 1 to 4, wherein the inner skins of the first and second sound absorbing panels (28, 30) form a single-piece element.

6. Air intake structure (22) according to one of claims 1 to 5, characterized in that at least one of the heat sources (48, 50) is supplied with electrical energy and in that the heat source (48, 50) is embedded in an electrical insulator (51, 52).

7. Air intake structure (22) according to one of claims 1 to 5, characterized in that at least one of the heat sources (48, 50) is supplied with electrical energy and in that the heat source (48, 50) incorporates a vibrating element.

8. Air inlet structure (22) according to one of the claims 1 to 5, characterized in that at least one of the heat sources (48, 50) consists of a tube in which a hot fluid flows.

9. Air intake structure (22) according to one of the preceding claims, characterized in that, for each heat source (48, 50), the inner skin comprises an element (54, 56) with heat-conducting properties, which element has one face positioned close to the heat source (48, 50) and one face in contact with the channel (26).

10. A nacelle (19) comprising an air intake structure (22) according to one of the preceding claims at the front.

11. An aircraft (10) comprising at least one nacelle according to claim 10.

Technical Field

The present invention relates to an air intake structure for a nacelle of an aircraft, to a nacelle comprising such an air intake structure and to an aircraft comprising at least one such nacelle.

Background

An aircraft turbine engine includes a nacelle within which an engine assembly is housed. The nacelle having a ring shape has an air inlet structure at the front.

The air intake structure generally comprises an inner face and an outer face in contact with the outside air, while the inner face defines a channel constituting a fan duct. The function of the air intake structure is, in particular, to ensure an aerodynamic flow of air towards the fan duct on the one hand and towards the outside of the nacelle on the other hand.

The air scoop structure conventionally includes an air scoop lip, a front reinforcing frame, and an acoustic panel.

The air intake lip has a rearwardly-opening U-shaped cross-section, forms an outer envelope of the forward portion of the air intake structure and ensures the distribution of air between the portion entering the fan duct and the portion flowing around the nacelle.

The forward reinforcing frame also has a rearwardly opening U-shaped cross-section and is positioned within the air intake lip and at the rear. The forward reinforcing frame provides mechanical strength to the forward portion of the nacelle and helps to maintain its shape and size.

The acoustic panel forms an inner cladding of the nacelle on the fan duct side, behind the air intake lip. The sound-absorbing panel thus forms part of the interior face.

The acoustic panel has a structure suitable for attenuating the noise generated by the engine and in particular by the fan. This acoustic panel is of the composite sandwich type and it integrates a honeycomb core, for example in the form of a honeycomb, between an inner wall and an outer wall. The inner wall defines the fan duct and extends the air intake lip, while the outer wall is oriented inside the air intake structure, but towards the outside of the nacelle.

The volume between the air intake lip and the forward reinforcing frame allows circulation of a hot air flow which provides de-icing of the air intake lip.

While such air intake structures are entirely satisfactory during their use, it is desirable to find a structure that allows for an increased attenuation frequency range and increased de-icing and sound absorbing surfaces.

Disclosure of Invention

The object of the present invention is to propose an air intake structure for an aircraft nacelle, which is provided in particular with large deicing and sound-absorbing surfaces.

To this end, an air intake structure for an aircraft nacelle is proposed, which air intake structure delimits a passage and comprises:

a lip having a rearwardly directed U-shaped cross-section,

-a first sound-absorbing panel fixed behind the lip and delimiting the channel, an

-a second sound absorbing panel fixed behind the first sound absorbing panel and delimiting the channel,

wherein each of the first and second sound absorbing panels comprises a honeycomb core fixed between an inner skin oriented towards the channel and perforated with holes oriented towards the channel and an outer skin oriented in the opposite direction, wherein the inner skin of the first sound absorbing panel has a thickness greater than the thickness of the inner skin of the second sound absorbing panel, and

wherein each of the inner skins includes a heat source embedded over a majority of the inner skin.

This air intake structure thus makes it possible to have a deicing and sound-absorbing surface extending from the front of the air intake lip to the rear of the acoustic panel.

Advantageously, the inner skin of the first sound-absorbing panel has a thickness of 3mm to 6 mm.

Advantageously, the inner skin of the second sound-absorbing panel has a thickness of 0.6mm to 2.1 mm.

Advantageously, each honeycomb core has the form of a honeycomb.

Advantageously, the inner skins of both the first and second sound absorbing panels form a one-piece element.

According to a particular embodiment, at least one of said heat sources is supplied with electrical energy, and said heat source is embedded in an electrical insulator.

According to a particular embodiment, at least one of said heat sources is supplied with electric energy and said heat source integrates a vibrating element.

According to a particular embodiment, at least one of said heat sources is constituted by a tube in which a hot fluid flows.

Advantageously, for each heat source, the inner skin comprises an element having heat-conducting properties, the element having one face positioned close to the heat source and one face in contact with the channel.

The invention also proposes a nacelle comprising, at the front, an air intake structure according to one of the preceding embodiments.

The invention also proposes an aircraft comprising at least one nacelle according to the above embodiments.

Drawings

The above-mentioned features of the invention, as well as others, will appear more clearly on reading the following description of exemplary embodiments, which description is given with reference to the accompanying drawings, in which:

figure 1 shows a side view of an aircraft according to the invention,

figure 2 is a cross-sectional side view of an air intake structure according to the present invention,

figure 3 is a perspective view of detail III of figure 2,

FIG. 4 is a diagrammatic representation of an area of an air intake structure provided with de-icing in accordance with a first embodiment of the present invention, and

fig. 5 is a diagrammatic representation of an area of an air intake structure provided with de-icing in accordance with a second embodiment of the present invention.

Detailed Description

In the following description, position-related terms are referred to an aircraft in a forward-moving position as shown in fig. 1.

FIG. 1 illustrates an aircraft 10 including at least one turbine engine 20.

By convention, throughout the following description, the direction X corresponds to a longitudinal direction of the turbine engine 20, this direction being parallel to the longitudinal axis X of the turbine engine 20. On the other hand, direction Y corresponds to a direction oriented transversely with respect to turbine engine 20, and direction Z corresponds to a vertical or height direction, with these three directions X, Y, Z being orthogonal with respect to each other.

Conventionally, the turbine engine 20 includes a nacelle 19 that includes, at a front portion, an air intake structure 22 that includes lips that define an interior and an exterior of the nacelle 19. The lip extends toward the interior by an inner wall that extends around a channel that directs air toward an engine assembly that includes, among other things, a fan.

Fig. 2 shows an air inlet structure 22 comprising a lip 24 having a rearwardly directed U-shaped cross-section and generally having an annular shape. The air intake structure 22 defines a passage 26 that directs air toward the engine assembly, and in particular toward the fan.

The lip 24 defines an exterior 25 and an interior 26 of the nacelle 19. The interior 26 corresponds to the channel 26.

The air intake structure 22 includes, around the channel 26, a first sound absorbing panel 28 and a second sound absorbing panel 30 that define the channel 26. A first sound absorbing panel 28 is secured behind the lip 24 up to a second sound absorbing panel 30. A second sound absorbing panel 30 is secured behind the first sound absorbing panel 28.

In the case of the present invention, the front reinforcing frame has been dispensed with and the air intake structure 22 of the present invention is reinforced by the presence of the first sound-absorbing panel 28, which also has structural properties.

Each sound-absorbing panel 28, 30 comprises a honeycomb core 32, 34, for example in the form of a honeycomb, which is fixed between an inner skin 36, 38 oriented towards the channel 26 and an outer skin 40, 42 oriented in the opposite direction. The inner skins 36, 38 are perforated with holes that are oriented toward the channel 26 and allow sound waves to propagate into the cores 32, 34 to be attenuated therein.

Fig. 3 shows the bonded area between the first sound-absorbing panel 28 and the second sound-absorbing panel 30, in which each inner skin 36, 38 is penetrated by holes 44, 46.

In general, the inner skin 36 of the first sound absorbing panel 28 has a thickness that is greater than the thickness of the inner skin 38 of the second sound absorbing panel 30.

Thus, the attenuation of sound waves is enhanced compared to the prior art and the frequency range of the attenuation is also increased by using a sound absorbing panel based on two different technologies.

Each of the inner skins 36, 38 includes a heat source 48, 50 embedded in the bulk (mass) of the inner skins 36, 38. This heat source 48, 50 makes it possible to de-ice the face of the inner skin 36, 38 in the channel 26.

Furthermore, the surface of the air intake structure 22 that is thus protected from frost is extended.

According to a particular embodiment, a first sound-absorbing panel 28 is provided to attenuate low frequencies in the range between 400Hz and 500 Hz. For this purpose, the inner skin 36 of the first sound-absorbing panel 28 has a thickness of 4mm to 10mm and the holes 44 therefore also have a length equal to 4mm to 10 mm. Preferably, the thickness is 3mm to 6 mm.

The volume of the cells of the honeycomb core 32 into which the holes 44 open and the length of the holes 44 are such that the frequency to be attenuated can be selected. For example, for a 4mm high duct and a 40mm high cell, a frequency of about 500Hz is attenuated.

A second sound absorbing panel 30 is provided to attenuate high frequencies in the range between 1000Hz and 4000 Hz. For this purpose, the inner skin 38 of the second sound-absorbing panel 30 has a thickness of the order of 0.5 to 2.5mm and the holes 46 therefore also have a length of at least 0.5 to 2.5 mm. Preferably, the thickness is 0.6mm to 2.1 mm.

The face of the inner skin 36 of the first sound-absorbing panel 28 which is oriented towards the channel 26 is flush with the face of the inner skin 38 of the second sound-absorbing panel 30 which is oriented towards the channel 26 in order to create an aerodynamic surface.

According to a particular embodiment, the inner skins 36 and 38 of the two sound-absorbing panels 28 and 30 are the same element and therefore together form a single-piece element.

The heat sources 48, 50 may be powered and may, for example, be resistive elements that heat when current passes through them or may incorporate vibrating elements, such as piezoelectric elements. The heat sources 48, 50 may, for example, be comprised of pipes through which a hot fluid flows.

Fig. 4 shows the inner skins 36 and 38 with embedded heat sources 48 and 50. The amount of heat required may vary along the inner skins 36, 38 depending on deicing requirements. Thus, the size of the heat sources 48, 50 may be different for different locations.

In the case of electric heat sources 48, 50, the heat sources 48, 50 are embedded in electrical insulators 51, 52 that prevent short circuits and contact with technicians, for example, during maintenance.

Fig. 5 shows the inner skins 36 and 38, wherein the elements 54, 56 with heat-conducting properties are arranged in such a way that heat from the heat sources 48, 50 is conducted to the place where it is necessary to dissipate the heat for de-icing, in this case in contact with the channels 26. Each element 54 has a face positioned adjacent to the heat sources 48, 50 and a face in contact with the channel 26.

In the case of non-electrical heat sources 48, 50, element 54 may be in contact with the heat sources 48, 50.

In the case of electrical heat sources 48, 50, the element 54 is spaced from said heat sources 48, 50 by electrical insulators 51, 52.