RU2742203C1 - Anti-ice system for aircraft wing slats - Google Patents

Abstract

FIELD: anti-icing devices.

SUBSTANCE: anti-icing system of sliding wing slats of aircraft includes devices for selection of hot air and control of its flow rate. Hot air is fed via telescopic air duct into distribution pipes. Sections (1, 2, 3, 4) of distributing pipes are located in corresponding sections of wing slats and are equipped with fasteners to them. Distribution pipes are equipped with intersectional compensators. Each of intersectional compensators is made with possibility of independent compensation of relative angular, longitudinal, axial and rotary displacements of connected sections of distributing pipes.

EFFECT: compensation of deformations of wing slats is provided due to its bending and twisting, during aircraft operation, as well as exclusion of deformation of distribution pipes.

4 cl, 5 dwg

Description

Technology area

The invention relates to a means for removing or preventing the formation of ice on the outer surfaces of the aircraft by heated gas. An advantageous field of application of the invention is in the protection against icing of retractable slats subject to operational deformation.

In connection with the deformation of the wing, due to its bending and twisting, during the operation of the aircraft, a corresponding deformation of the retractable slats and system elements located in them occurs.

Such deformation can lead to different relative displacements of the connected sections and parts of the sections of the distribution pipes of the system themselves with an emergency violation of the strength of the slats, which is dangerous for the aircraft during its operation.

State of the art

The anti-icing system of aircraft slats according to RF patent No. 2316452 (B64D 15/04) is designed to supply hot air to the movable slat or stabilizer of the aircraft. The system of patent No. 2316452, as well as the anti-icing system of the present application, contains (in terms of the patent description) a receiving branch pipe located on a retractable slat, a supply branch pipe mounted on the wing, and elbows. The branch pipes and elbows are interconnected by bearing assemblies, which include rotary bearings placed in the housings. The elbows are interconnected by a bearing unit equipped with a spherical bearing with a sliding fit along the inner diameter. Significant dimensions of the system according to patent No. 2316452 make it difficult to use it.

The anti-icing system according to the patent of the Russian Federation No. 2529927 (B64D 15/04), as well as the anti-icing system according to the present application, contains means for extracting hot air and regulating its temperature before being fed into the distribution pipes located in the slats. In the description of the invention according to patent No. 2529927, the problems associated with the peculiarities of the supply of hot air in the retractable slats and their deformation during operation, which are the subject of the solution of the invention according to the present application, are not considered.

The analogue closest to the invention according to the present application is a system for protecting the retractable slats of an aircraft from icing, disclosed in the description of the invention to the patent of the Russian Federation No. 2488526 (B64D 13/08). The means of protecting the retractable slats of the aircraft from icing according to patent No. 2488526, as well as the invention according to the present application, contain means for taking hot air and regulating its temperature before supplying hot air through a telescopic air duct into distribution pipes, the sections of which are located in the corresponding sections of the slats and are equipped attachment points to them. In the description of the invention and illustrations to patent No. 2488526, the problems associated with the deformation of the slats during operation are also not considered.

Disclosure of the essence of the invention

The invention solves the problem of improving the reliability and safety of the anti-icing system of retractable slats of the aircraft.

The essence of the invention as a technical solution related to the anti-icing system of retractable slats of an aircraft is that the anti-icing system contains means for extracting hot air and regulating its parameters before supplying hot air through a telescopic air duct to distribution pipes, the sections of which are located in the corresponding sections of the slats and are equipped with attachment points to them and, according to the invention, the distribution pipes are equipped with intersectional compensators, each of which is made with the possibility of independent compensation of relative angular, longitudinal, axial and rotary displacements of the connected sections of distribution pipes.

Technical result

The technical result consists in compensating for the deformations of the wing slats by introducing intersectional expansion joints, which exclude the corresponding deformation of the distribution pipes arising from the bending and twisting of the wing during the operation of the aircraft.

Preferred embodiments of the invention form part of the dependent claims.

It is advisable to connect the hot air sampling means to the engine compressor, and the telescopic air duct to the distribution pipe section located in the slat, the first in the wingspan behind this engine, because in the areas between the fuselage and the engine nacelle, wing deformation is negligible and the slat does not icing.

The distribution pipe sections, in addition to the section located along the wing span in the first slat behind the engine, can be made with nozzle holes directed to the inner part of the slat, the outer surface of which is to be protected from icing. Direct heating of the slat nose increases the efficiency of its protection, increasing the reliability of the aircraft slat anti-icing system.

List of drawing figures

FIG. 1 - slats anti-icing system (isometric view).

FIG. 2 - node "A" of FIG. 1 air inlet (isometric view).

Fig. 3 - node "B" of Fig. 1 - intersectional expansion joint, longitudinal section (isometry).

FIG. 4 - node "C" of FIG. 1 - intermediate expansion joint, longitudinal section (isometric view).

FIG. 5 - Diagram of a slat with a distribution pipe.

Implementation of the invention

The invention is further illustrated by specific examples of its implementation with reference to the accompanying drawings.

FIG. 1 shows the general layout of the anti-icing system of retractable slats of an aircraft, and FIG. 2, fig. 3 and FIG. 4 its nodes, respectively, A, B and C.

As shown in FIG. 1, sections 1, 2, 3, 4 of the distribution pipes are located in the corresponding sections of the slats and are equipped with assemblies (not shown in Fig. 1) for attaching to them. Sections 1, 2, 3, 4 are equipped with intersection compensators (Fig. 3). In addition, each of the sections 1, 2, 3, 4 of the distribution pipes is made with an intermediate compensator (Fig. 4).

FIG. 2 shows an air supply unit, which consists of pipelines 6, 7 for sampling hot air, equipped with a control damper 8, a temperature sensor 9 and sensors 10 and 11 (backup) pressure of hot air. Hot air is supplied to the distribution pipes through a telescopic air duct 12 and nozzles 13 and 14.

FIG. 3 shows an assembly of an intersectional expansion joint, which is configured to independently compensate for relative angular, longitudinal, axial and rotary displacements of the connected sections of distribution pipes. Independent compensation of relative angular, longitudinal, axial and rotary displacements of the connected sections of distribution pipes is provided by intersectional expansion joints made with a spherical or torus tip 15 (18), installed with the possibility of longitudinal movement in a cylindrical tip 16 (19) of distribution pipes 21 (22) ...

Attached to the distribution pipes 21 (22) section of the intersectional expansion joint, made with the possibility of movement, contains rigid cylindrical parts 23 and 24, connected by a connecting pipe 25 made of elastic heat-resistant material.

The connecting pipe 25 by means of clamps 26 and 27 tightly encloses the rigid cylindrical parts 23 and 24 of the intersectional expansion joint. Parts 23 and 24 are spaced apart at a distance L. The distance L is selected from the condition of the possibility of a given axial relative displacement of the connected sections of distribution pipes with elastic deformation of the connecting pipe 25.

Each intermediate expansion joint is made with the possibility of angular and rotary relative displacements of parts 31 and 32 of the distribution pipe section. For this, as shown in FIG. 4, the intermediate expansion joint is made with a spherical or torus tip 28 enclosed in a cylindrical tip 29 of one of the parts of the distribution pipe section, similar to that shown in FIG. 3 for intersection expansion joints.

For intermediate compensators, a bronze insert 30 is pressed into the tip 29, interacting with the spherical or torus tip 28.

As shown in FIG. 1 and FIG. 2, pipelines 6 and 7 for taking hot air are connected to the compressor of the underwing propulsion engine 5, and the telescopic air duct 12 through a branch pipe 14 is connected to the section 1 of the distribution pipes. Section 1 is thermally insulated from the slat.

Sections 2, 3 and 4 of the distribution pipes are made with nozzle openings (not shown) directed to the inner part of the nose slat, the outer surface of which is to be protected from icing.

With a relative angular displacement of the connected sections of distribution pipes or parts of the sections themselves, the spherical or torus tip 15 (18) or 28 rotates relative to the cylindrical surface of the tip 16 (19) of the section to be connected or the cylindrical surface 29 of its part.

With a relative rotational displacement of the connected sections of distribution pipes or parts of the sections themselves due to the twist of the wing, the spherical or torus tip 15 (18) or 28 rotates relative to the cylindrical surface of the tip 16 (19) or 29 of the section to be connected or its part around their common axis.

With a relative longitudinal displacement of the connected sections of distribution pipes, the spherical or torus tip 15 (18) moves along the cylindrical surface of the tip 16 (19).

With a relative axial displacement of the connected sections of the distribution pipes, elastic deformation of the connecting pipe 25 from an elastic heat-resistant material occurs.

Thus, there is a full compensation for possible deformations of the distribution pipes and parts of the sections themselves.

Parts 23 and 24 of the intersectional expansion joint are fastened to its ends from the sides of the connected sections of distribution pipes by means of flanges 33, 34 and 35, 36, between which supports 37, 38 of distribution pipes are installed to the slat, covered from the side of the flanges and the flow channel with heat-insulating gaskets 39, 40 , 41, 42.

FIG. 5 shows a diagram of a slat with a distribution pipe (Piccolo tube) 43, which is designed to supply hot air (through holes) to the de-icing system.

The distribution pipe (Piccolo tube) is made of titanium alloy.

Hot air through the openings of the distribution pipe 43 enters the space located between the skin 44 and the wall of the screen 45, and heats the skin 44 of the leading edge of the slat section.

Then hot air leaves this space through the upper corrugation 46 and the slot 47 enters the space located between the wall of the screen 45 and the screen 48 and exits through the lower corrugation 49 into the atmosphere.

Claims (4)

1. Anti-icing system of aircraft slats, containing means for taking hot air and adjusting its parameters before supplying hot air through a telescopic air duct to distribution pipes, the sections of which are located in the corresponding sections of the slats and equipped with attachment points to them, characterized in that the distribution pipes are equipped with intersectional expansion joints , each of which is configured to independently compensate for relative angular, longitudinal, axial and rotary displacements of the connected sections of distribution pipes. 2. The anti-icing system according to claim 1, characterized in that the hot air bleed means are connected to the compressor of the propulsion engine, and the telescopic air duct is connected to the section of distribution pipes located in the slat, the first in the wingspan behind this engine. 3. The anti-icing system according to claim 2, characterized in that the section of distribution pipes located in the slat, the first one behind the engine along the wing span, is thermally insulated from the slat. 4. The anti-icing system according to claim 3, characterized in that the sections of the distribution pipes, except for the section located along the wingspan in the first slat behind the engine, are made with nozzle holes directed to the inner part of the slat, the outer surface of which is to be protected from icing.

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