阅读说明：本技术 笛形管、飞行器除冰装置及飞行器 (Flute venturi tube, aircraft defroster and aircraft ) 是由 孔子成 吴静玮 胡伟学 曾飞雄 白斌 于 2021-08-31 设计创作，主要内容包括：本发明涉及一种用于飞行器除冰的笛形管,该笛形管包括：笛形管本体,笛形管本体具有中空的内部腔体、第一端、第二端以及设置在笛形管本体的周向表面上的多个孔,其中,第一端闭合,而第二端流体连通到热流体源；多个喷管,多个喷管中的每个喷管分别附连到笛形管本体上的多个孔并与中空的内部腔体流体连通。通过该笛形管能增加装置换热效率。在同等防冰功率需求下,本发明较传统笛形管可采用更低的引气温度,对缝翼及前缘材料的热保护会更好,也提供了使用耐热温度更低的复合材料的可能。(The invention relates to a flute tube for deicing an aircraft, comprising: a flute tube body having a hollow interior cavity, a first end, a second end, and a plurality of holes disposed on a circumferential surface of the flute tube body, wherein the first end is closed and the second end is fluidly connected to a source of hot fluid; a plurality of nozzles, each of the plurality of nozzles respectively attached to the plurality of holes on the flute-shaped tube body and in fluid communication with the hollow interior cavity. The heat exchange efficiency of the device can be increased through the flute-shaped pipe. Compared with the traditional flute-shaped pipe, the composite pipe can adopt lower air-entraining temperature under the same anti-icing power requirement, has better thermal protection on slat and leading edge materials, and also provides the possibility of using composite materials with lower heat-resisting temperature.)

1. A flute tube (100) for aircraft de-icing, said flute tube comprising:

a flute tube body (10) having a hollow interior cavity (11), a first end (12), a second end (13), and a plurality of holes (14) disposed on a circumferential surface of the flute tube body (11), wherein the first end (12) is closed and the second end (13) is fluidly connected to a source of hot fluid;

a plurality of nozzles (20), each of the plurality of nozzles being attached to the plurality of holes (14) on the flute-shaped tube body (11) and in fluid communication with the hollow interior cavity (11).

2. The flute-shaped pipe (100) as recited in claim 1, wherein said plurality of holes (14) of said flute-shaped pipe body (10) are arranged in a straight line along a length direction of said flute-shaped pipe body (11), and said plurality of nozzles (20) are arranged in a row in a comb-tooth shape on said flute-shaped pipe body (11).

3. The flute-shaped tube (100) of claim 2 wherein the plurality of nozzles (20) comprise a plurality of rows extending from the flute-shaped tube body (11) parallel to one another.

4. The flute tube (100) of claim 2, wherein the plurality of nozzles (20) comprise a plurality of rows extending from the flute tube body (11) at angles to one another.

5. The flute tube (100) of claim 4 wherein the plurality of nozzles (20) comprises two rows extending from the flute tube body (11) at 30 degrees to each other.

6. The flute-shaped tube (100) of claim 1 wherein the plurality of nozzles (20) are integrally formed with the flute-shaped tube body (10).

7. An aircraft de-icing arrangement (1000) comprising a flute tube (100) according to any one of claims 1-6 and a supply line connected upstream of said flute tube (100), wherein an airfoil anti-icing valve for regulating a fluid flow from a fluid source and a pressure sensor are arranged in said supply line.

8. The aircraft deicing device (1000) according to claim 7, wherein the aircraft deicing device is disposed in an interior space of an aircraft slat cavity (200), and the plurality of nozzles (20) of the flute tube (100) face a leading edge of the slat cavity (200).

9. The aircraft de-icing arrangement (1000) according to claim 8, further comprising an adjustment device attached to the flute tube (100), said adjustment device being capable of adjusting a linear movement of the flute tube (100) along the axis of the flute tube body (10) and/or an angular movement around the axis of the flute tube body (10).

10. An aircraft comprising an aircraft de-icing arrangement (1000) according to any one of claims 7-9.

Technical Field

The invention relates to an anti-icing/deicing element for heating the leading edge of an aircraft wing by spraying hot gas, which heats the leading edge slat of the aircraft in a mode of directly spraying engine bleed hot gas to play the anti-icing/deicing role.

The invention also relates to an aircraft de-icing device and an aircraft comprising such a flute tube.

Background

When an aircraft, such as a civil/commercial aircraft, flies in a cloud containing supercooled water droplets, icing can occur on the lifting surfaces, such as the wings, the windward surface of the empennage, the leading edge of the air inlet, etc., posing a serious threat to the safety of the flight, and therefore reasonable anti-icing and deicing measures are required to prevent ice accumulation that is harmful to the flight. The development of the existing aircraft hot-gas anti-icing technology is very rapid, the civil aircraft mainly adopts hot gas to perform wing anti-icing, and a mature hot-gas anti-icing system also plays a key anti-icing role on various types of aircraft.

In a hot gas anti-icing system, a flute-shaped pipe is widely used as a key part, and the flute-shaped pipe is realized by spraying engine hot bleed air to the inner surface of a protected skin to play a role in heating anti-icing/deicing. The arrangement of the wing leading edge hot gas anti-icing pipeline and the flute-shaped pipe is divided into a parallel connection mode and a series connection mode. Hot bleed air from an engine is distributed into the flute-shaped pipe through a pipeline, and the hot air is sprayed to the inner surface of the skin at the front edge of the wing through small holes in the flute-shaped pipe to heat the upper skin and the lower skin at the front edge of the wing, so that the aim of preventing ice is fulfilled.

In the mode, a flute-shaped pipe with a certain length is needed to spray hot air in the pipe to the inner surface of the skin, and the temperature of the skin is increased through the convection heat exchange between the sprayed hot air and the skin so as to prevent the wing from being frozen. Depending on the water droplet collection characteristics of the wing, different water collection levels may occur at different chord wise locations of the wing, and therefore the flute nozzle is typically directed towards the region of maximum water collection. However, flute tubes on aircraft of various sizes are currently less thermally efficient because they are typically located a distance from the interior surface of the skin and because hot gases from, for example, an aircraft engine, after exiting the nozzles of the flute tubes at high pressure, can quickly spread due to the reduced ambient pressure. At this time, more energy is required to achieve the desired anti-icing/deicing effect.

On the other hand, in a large aircraft project of a certain country model, since the fuselage of the aircraft is largely made of composite materials which, compared with conventional metallic materials, can withstand lower high temperature values, if heated de-icing is carried out using conventional flute tubes, it is generally necessary to carry out jet heating at very high bleed air temperatures, which may cause damage to the composite materials constituting the aircraft wings, for example, or reduce their structural strength/life, thereby impairing flight safety.

There is therefore a great need for a flute tube which enables anti-icing/de-icing operations of the protective skin of an aircraft with a higher heat exchange efficiency, and for a flute tube which enables heating de-icing with a lower bleed air temperature.

Disclosure of Invention

The invention aims to provide a hot air injection device which is arranged in a cavity of a wing slat of an aircraft and can inject hot air to the inner surface of a skin of the wing slat with higher heat exchange efficiency so as to achieve the purposes of heating and deicing.

According to one aspect of the invention, there is provided a flute tube for aircraft de-icing, the flute tube comprising:

a flute tube body having a hollow interior cavity, a first end, a second end, and a plurality of holes disposed on a circumferential surface of the flute tube body, wherein the first end is closed and the second end is fluidly connected to a source of hot fluid;

a plurality of nozzles, each of the plurality of nozzles respectively attached to the plurality of holes on the flute-shaped tube body and in fluid communication with the hollow interior cavity.

By arranging such a structure, for example, in an aircraft slat cavity, hot fluid from a hot air source, for example, an engine, can be distributed through a hollow interior cavity in a flute tube body into a plurality of nozzles and injected through these nozzles into the respective aircraft skin interior (for example, slat skin interior surface), thereby ensuring, on the one hand, as little heat loss as possible of the hot fluid before reaching the skin to be heated, and thus improving the heat exchange efficiency; on the other hand, the nozzle can be directly aligned with the position of the skin to be heated, so that the hot fluid from the hot fluid source can accurately heat the position to be heated without heating the whole skin, and the temperature/pressure of the required hot air source is correspondingly reduced. In an aircraft with a skin made of a compliant material, it is further ensured that the composite skin is not damaged by excessively high bleed air or that the bleed air properties change, ensuring flight safety.

According to the above aspect of the present invention, in order to further increase the efficiency and accuracy of heating, preferably, the plurality of holes of the flute shaped pipe body may be arranged in a straight line along the length direction of the flute shaped pipe body, and the plurality of nozzles are arranged in a row in a comb-tooth shape on the flute shaped pipe body.

In accordance with the above aspect of the invention, the plurality of nozzles may include a plurality of rows extending parallel to one another from the flute tube body for simultaneously more accurately heating a greater range of skin regions.

According to the above aspect of the invention, the plurality of nozzles may alternatively comprise a plurality of rows extending from the fluted tube body at angles to one another, for simultaneously more accurately heating a greater extent of the skin region.

In accordance with the above aspect of the invention, in order to simultaneously heat more accurately the skin region of the aircraft wing leading edge where severe icing is likely, without increasing the structural complexity of the flute tubes, thereby reducing the cost of later replacement and maintenance, it is preferred that the plurality of nozzles comprise two rows extending from the body of the flute tubes at an angle of 30 degrees to one another.

According to the above aspect of the present invention, in order to improve the structural strength of the flute pipe and prevent leakage caused by high pressure during use, the plurality of nozzles may be integrally formed with the flute pipe body.

According to another aspect of the invention, an aircraft de-icing apparatus is proposed, comprising a flute tube as described in the above aspect and a supply line connected upstream of the flute tube, wherein a wing anti-icing valve for regulating the fluid flow from the fluid source and a pressure sensor are arranged in the supply line. The aircraft deicing device can accurately heat the aircraft wing leading edge which is easy to freeze on the aircraft, improves the efficiency of anti-icing/deicing, and reduces the temperature of the fluid of the used hot fluid source.

According to this aspect of the invention, aircraft de-icing apparatus may be provided in the interior space of an aircraft slat cavity with the plurality of nozzles of the flute tube facing the leading edge of the slat cavity, thereby enabling more efficient anti-icing/de-icing operations.

According to this aspect of the invention, preferably, the aircraft de-icing apparatus may further comprise an adjustment device attached to the flute tube, the adjustment device being capable of adjusting the linear movement of the flute tube along the axis of the flute tube body and/or the angular movement about the axis of the flute tube body, in order to adjust the axial position and the circumferential position of the flute tube, if necessary, to perform an anti-icing/de-icing operation on a desired position.

According to another aspect of the invention, an aircraft comprising an aircraft de-icing apparatus as described in the above aspect is also presented.

Compared with the traditional flute-shaped pipe, the invention adds the extension spray pipe device, and the design can increase the heat exchange efficiency of the device. Compared with the traditional flute-shaped pipe, the composite pipe can adopt lower air-entraining temperature under the same anti-icing power requirement, has better thermal protection on slat and leading edge materials, and also provides the possibility of using composite materials with lower heat-resisting temperature.

Drawings

To further illustrate the flute tubes for aircraft de-icing according to the present invention, the invention will be described in detail below with reference to the accompanying drawings and specific embodiments, in which:

FIG. 1 is a schematic perspective view of a flute tube for aircraft de-icing in accordance with a non-limiting embodiment of the present invention;

FIG. 2 is a schematic side view of a flute tube for aircraft de-icing according to a non-limiting embodiment of the present invention;

FIG. 3 is a schematic top view of a flute tube for aircraft de-icing according to a non-limiting embodiment of the present invention;

FIG. 4 is a schematic side view of a flute tube for aircraft de-icing in accordance with another non-limiting embodiment of the present invention;

FIG. 5 is a schematic side view of a flute tube for aircraft de-icing in accordance with yet another non-limiting embodiment of the present invention; and

FIG. 6 is a schematic illustration of the arrangement of an aircraft de-icing apparatus within a slat cavity according to a non-limiting embodiment of the present invention.

Detailed Description

It is to be understood that the invention may assume various alternative orientations and step sequences, except where expressly specified to the contrary. It is also to be understood that the specific devices illustrated in the attached drawings, and described in the specification are simply exemplary embodiments of the inventive concepts disclosed and defined herein. Thus, specific flow paths, directions or other physical characteristics referred to by the various embodiments disclosed should not be considered as limiting, unless expressly stated otherwise.

The flute tube 100 for aircraft de-icing of the present invention is described in detail below with reference to the accompanying drawings.

In a civil aircraft, a flute-shaped pipe belongs to a core component of a wing anti-icing system, and is also called as an anti-icing pipe for wing anti-icing, the flute-shaped pipe is fixed in a cavity of a slat by a flange device, high-temperature and high-pressure gas from engine bleed air is sprayed to a skin at the front edge of the slat through the flute-shaped pipe to heat the front edge of the slat, and the aim of preventing and removing ice is fulfilled. The upper stream of the flute-shaped pipe is connected with a telescopic pipe and an air supply pipe, and the wing anti-icing valve and the pressure sensor are integrated in the air supply pipe to regulate high-temperature and high-pressure gas from an air source.

Fig. 1-3 are schematic perspective, side and top views, respectively, of a flute tube 100 for aircraft de-icing in accordance with a non-limiting embodiment of the present invention. As shown, the flute tube 100 is a comb flute tube including a flute tube body 10 and a plurality of nozzles 20.

The flute tube body 10 has a hollow interior cavity 11, a first end 12, a second end 13, and a plurality of holes 14 disposed on a circumferential surface of the flute tube body 11, wherein the first end 12 is closed and the second end 13 is fluidly connected to a source of hot fluid. It will be appreciated that the flute tube body 10 may be of the same construction as flute tubes used in the prior art and may be secured in aircraft structures such as the slat cavity 200 and connected to upstream telescopic tubes and air supply tubes in a manner known to those skilled in the art. Accordingly, for the sake of brevity, these structures will not be described in detail herein.

With continued reference to fig. 1, the plurality of nozzles 20 of the flute tube 100 are attached to the plurality of holes 14 on the flute tube body 11 and are in fluid communication with the hollow interior cavity 11. The plurality of holes 14 of the flute tube body 10 are arranged in a line along the length direction of the flute tube body 11, and these holes 14 are blocked by the nozzle 20 and are not shown in the drawing. The plurality of nozzles 20 are straight and arranged on the flute-shaped pipe body 11 in a comb-tooth shape in a straight line shape. Although not shown in the drawings, the bore 14 has an inner diameter greater than or equal to the inner diameter of the nozzle 20 to enable smooth discharge of the high pressure bleed air, and preferably, each nozzle 20 has the same length and inner diameter to facilitate machining and assembly.

As used herein, the term "fluid communication" means that fluid is able to flow freely from the hollow interior cavity 11 into the plurality of nozzles 20, which fluid may be, for example, high temperature exhaust gas from an engine, or other fluid from other fluid sources onboard an aircraft.

The flute-shaped pipe body 10 and the nozzles 20 may be made of a lightweight high-temperature-resistant titanium alloy in order to reduce the weight as much as possible while ensuring the strength. Preferably, the flute tube body 10 and the nozzle 20 may be separately formed and then joined together, for example, by welding, and in an alternative embodiment, the flute tube body 10 and the nozzle 20 may be integrally formed. The length, size and number of openings and the size of the inner diameter of the flute tube body 10 and nozzle 20 may be determined according to the flow rate required for the anti-icing system design and the fluid temperature and pressure of the hot fluid source, thereby enabling the flute tube 100 to be adapted for accommodation in the space of the slat cavity 200 or nacelle leading edge of different aircraft models.

In addition, although not shown in detail in the drawings, for better jetting results, the open end of the nozzle 20 facing the slat cavity 200 may be flared, or a nozzle with a tapered opening, as desired, for more precise jet heating.

It should be understood that although the flute tube 100 embodiment shown in the drawings has a plurality of nozzles 20 arranged in a straight line on the flute tube body 11 along the length of the flute tube body 11 with equal spacing therebetween, the nozzles 20 may alternatively be arranged in other types of patterns, such as staggered spaced shapes, helical shapes, etc., without departing from the scope of the invention, and the spacing therebetween may also be different.

Additionally, although in the preferred embodiment shown in fig. 1-3 the spout 20 is shown extending orthogonally to the longitudinal axis of the flute tube body 11, in alternative embodiments the spout 20 may extend from the flute tube body 10 offset relative to the longitudinal axis of the flute tube body 11.

Fig. 4 is a schematic side view of a flute tube 100 for aircraft de-icing in accordance with another non-limiting embodiment of the present invention. As shown, the flute tube 100 includes two rows of nozzles 20 extending from the flute tube body 11, and the two rows of nozzles 20 extend from the flute tube body 11 parallel to each other. In alternative embodiments, the flute tube 100 may include more than two rows of nozzles 20. Obviously, in this case, a corresponding number and size of openings are provided on the circumferential surface of the flute-shaped pipe body 11.

Fig. 5 is a schematic side view of a flute tube 100 for aircraft de-icing in accordance with yet another non-limiting embodiment of the present invention. As shown, the flute tube 100 includes two rows of nozzles 20 extending from the flute tube body 11, and the two rows of nozzles 20 extend from the flute tube body 11 at an angle of 30 degrees to each other. In an alternative embodiment, the two rows of nozzles 20 may also be at an angle of between 15 and 60 degrees to each other, which angle generally corresponds to the skin region where severe icing of the aircraft slat cavity 200 is possible.

Fig. 6 is a schematic diagram of the arrangement of an aircraft de-icing apparatus 1000 within a slat cavity 200 according to a non-limiting embodiment of the present invention. As shown, the aircraft de-icing apparatus 1000 is disposed in the interior space of an aircraft slat cavity 200, and the plurality of nozzles 20 of the flute tubes 100 face the leading edge of the slat cavity 200. The flute tube 100 is designed with a certain installation angle for different slats, and can be generally opposite to the front edge line of the slat, and the flute tube 100 can be fixed with the rib of the slat by a flange device. Hot fluid from the engine (e.g. engine hot exhaust gas) is distributed via the hollow internal cavity 11 into two rows of nozzles 20 arranged at an angle in the flute tube body 11 and is ejected via nozzles towards the skin interior surface of the slat cavity 200. The injected hot gas is directed over the concave surface of the skin interior surface of the slat cavity 200, flowing upwardly toward the protected area first boundary and downwardly toward the protected area second boundary, respectively, so that the hotter fluid exiting the nozzle 20 first heats the heavily icing skin region (i.e., the most icing skin region), and then the lower temperature fluid sequentially heats the less heavily icing skin region in the direction indicated by the arrows, resulting in a higher anti-icing/de-icing efficiency for the comb flute tube 100.

According to a non-limiting embodiment and as a preferred embodiment of the present invention, the aircraft de-icing apparatus 1000 may further comprise an adjustment device attached to the flute tube 100, the adjustment device being capable of adjusting the linear movement of the flute tube 100 along the axis of the flute tube body 10 and/or the angular movement around the axis of the flute tube body 10.

Compared with the traditional flute-shaped pipe deicing device, the exemplary aircraft deicing device 1000 provided by the invention has the additional extension spray pipes, and the heat exchange performance of a specified area is enhanced by adopting a spray pipe jet flow mode, so that the heat exchange efficiency is higher, the energy can be saved, the air entraining temperature is reduced, and the performance of an anti-icing system is improved. And the flute pipe among the prior art, the heat transfer is more extensive, therefore efficiency is lower.

Also, as used herein, the terms "first" or "second", etc., used to indicate a sequence, are only for the purpose of making those skilled in the art better understand the concept of the present invention illustrated in the form of preferred embodiments, and are not intended to limit the present invention. Unless otherwise specified, all sequences, orientations, or orientations are used for the purpose of distinguishing one element/component/structure from another element/component/structure only, and do not imply any particular sequence, order of installation, direction, or orientation, unless otherwise specified. For example, in alternative embodiments, "first end" may be used to represent "second end" and "up flow" may also be used to represent "down flow".

In summary, the flute tube 100 according to embodiments of the present invention overcomes the disadvantages of the prior art and achieves the intended objects.

While the flute tubes of the present invention have been described in connection with preferred embodiments, those of ordinary skill in the art will recognize that the foregoing examples are illustrative only and are not to be construed as limiting the present invention. Therefore, various modifications and changes can be made to the present invention within the spirit and scope of the claims, and these modifications and changes will fall within the scope of the claims of the present invention.