Turbojet engine nacelle air intake downstream element and turbojet engine nacelle with said element

FIELD: transport.

SUBSTANCE: invention relates to turbojet engine nacelle air intake edge attached to downstream section of said air intake that comprises anti-acing electrical hearing element, and to appropriate downstream section and turbojet engine nacelle. Downstream element 4b of air intake 4 of nacelle 1 allows air intake edge 4a to attached thereto. Edge 4a comprises anti-icing electrical hearing element 14. Edge 4a consists of identical sections 7 butt-jointed together along perimeter of air intake 4. Said element 14 is furnished with connector assembly 15 secured in front web 18 of downstream element 4b. Said element 4b comprises power supply connector assembly 19 to interact with connector assembly 15 of edge 4a.

EFFECT: simplified replacement of air intake edge.

7 cl, 11 dwg

The invention relates to an edge of the air intake of the nacelle turbojet engine, attached to the back flow section of the air intake and containing at least one de-icing heating element, the invention relates to the appropriate back flow section and to the turbojet engine nacelle, which contains the air intake according to the invention.

The thrust of the aircraft is provided by one or more power units, each of which contains a turbojet engine housed in a cylindrical gondola. Each power unit is attached to the aircraft by a pylon, which is usually under the wing or fuselage.

The design of the gondola usually contains the air intake, located at the flow front of the engine, the middle part, covering the fan turbojet engine, and rear stream in the part that holds the device of reverse thrust and surrounds the combustion chamber of the turbojet engine, and ends, as a rule, jet nozzle, the outlet of which is located behind the turbojet engine.

The air intake on the one hand contains an edge of the air intake is performed so that the air supplied to the fan and the internal compressors, acted in turbotect wny the engine and ran it properly, but on the other hand - rear the flow section, which are attached to the specified edge, providing adequate venting in the direction of the fan blades. This entire site is attached to the flow front of the fan shroud, which is a part of the front stream side of the gondola.

In flight under certain temperature and humidity on the gondola in the area of the edge of the air vent can be formed ice. In the presence of ice or frost are changing the aerodynamic characteristics of the air intake and disrupted the flow of air to the fan. In addition, from the edge of the air intake can sometimes separate the chunks of ice that collide with components of the turbojet engine, in particular with the fan blades.

In addition, the edge of the inlet is exposed to numerous collisions with various external objects, abrasive particles, birds, hail, etc. that violate the aerodynamic integrity of the outer surface and cause premature wear.

Given that the operational characteristics of the turbojet engine are closely related to the quality and quantity of intake air by the intake, you must ensure that damaged the edge was replaced as soon as possible. Such replacement is a rather long and expensive the present operation, maintenance, because damaged may be only part of the edge.

In the first method of removing ice from the edge of the air intake away the hot air in the zone of the compressor turbojet engine and bring it to the edge of the inlet, the walls of which it heats as it flows through the internal channel edges. However, the device of this type requires a system of moving hot air between the turbojet engine and air intake systems and exhaust hot air in the area of the edge of the air intake, which leads to undesirable increase in the weight of the power plant. Additional difficulties of applying such a system lies in the fact that in order to avoid the repeated increase in the number of filings and taps hot air edge air intake runs as a single piece having a continuous inner peripheral channel for the circulation of hot air, and therefore, if damage to the outer profile of this element, it is necessary to change entirely.

Another solution, disclosed in the patent document EP 1495963 is applied to the outer wall flange of the vent special heating resistor. This technology allows the edge of the air intake modular way of several basic elements. Although this system is less complex, yet Zam is on one or more items is quite long due to the need to re-connect means of the power element.

According to EP 1175160 and EP 1175159 replacement edges can be simplified, using the edge of the air intake is configured to attach to the back flow section of the air intake and containing at least one de-icing heating element, characterized in that the heating element comprises at least one electrical connector configured to attach to at least one corresponding power connector on the rear in the stream section. Due to the use of such electrical connectors mounting flange air intake and, in particular, restoring electrical connections much easier because you just need to insert each electrical connector edge connector power supply that will allow you to restore the integrity of the electrical circuit.

The purpose of the present invention is to further facilitate replacement of such edges of the air intake, which prompted the edge of the air intake of the nacelle turbojet engine, configured to mount to the rear along the flow section of the air intake and containing at least one de-icing heating element, and the specified heating element is equipped with at least one electric is named Jack, configured to connect to at least one corresponding power connector on the rear flow element, characterized in that the edge is made of at least two identical sections connected end-to-end around the perimeter of the inlet.

Thus, due to the fact that the edge is made of the same modules, it becomes possible to replace the damaged section of the edge without changing its undamaged sections. In addition, because these sections are the same, the replacement is even simpler as it does not require a large number of parts.

Preferably, the edge is made of four identical sections connected end-to-end.

In accordance with the first embodiment, at least one electrical connector is located essentially in the middle of each section.

In accordance with the second embodiment, at least one electrical connector is located essentially at one end of each section.

Preferably, at least one electrical connector is located at each end of the section, each connector is made with the possibility of installing electrically conductive cap, ensuring the electrical continuity of the connector intended for connection to the corresponding socket.

The invention that the same applies to the back flow element inlet gondola turbojet engine, made with the possibility of joining the edges according to the claimed invention, characterized in that it contains at least one power socket, made interoperable with the corresponding electrical connector edge of the air intake, which is made in the front wall of the rear flow element.

In accordance with the first embodiment, the front wall includes at least one opening for providing access to the socket.

In accordance with the second embodiment connector of the power supply is made on a removable plate, which is part of the front walls.

Preferably, the back flow element contains at least one hole made in the outer wall and providing access to the power connector. The outlet, preferably situated at the junction of the two sections according to the invention.

Alternatively, the back flow section has an outer wall which at least partially associated with movable shutters, which include the middle part of the gondola. Because of this there is no need to run back flow element special service outlets, as access is provided by the disclosure of movable shutters middle part.

Finally, the claimed invention is the gondola turbojet engine, characterized in that it contains the intake containing the back flow element according to the invention, which is fixed to the edge of the inlet.

The invention will become clearer from consideration of the following detailed description, given with reference to the attached drawings,

which figure 1 is a perspective view presents a schematic representation of the gondola;

figure 2 shows in enlarged scale a cross-section of the section of the edge of the air inlet according to the invention;

figure 3 shows in enlarged scale a cross-section of the air intake of the nacelle shown in figure 1;

4 shows a perspective view on an enlarged scale with a spatial separation of the detail view of the edge of the air intake is made of several sections of figure 2;

figure 5 schematically shows a front view of the edge of the inlet in figure 4;

figure 6 is represented in an enlarged scale a cross-section of another intake that contains the back flow element with hatches;

figure 7-figure 11 shows different versions of the electric circuit sections according to figure 2.

The nacelle 1 according to the invention, depicted in figure 1, is a cylindrical housing for a turbojet engine (not shown) and serves to guide created by the decree which authorized the engine air flow. The nacelle 1 is located under the wing 2 to which it is attached by means of the pylon 3. It also has various components required for operation of turbojet engine.

In particular, the nacelle 1 has front downstream portion forming the inlet 4, the middle part 5, containing a fan (not shown) of the turbojet engine, and back on the thread part 6 containing a turbojet engine, which is also the system of the thrust reverser (not shown).

The inlet 4 is divided into two elements, namely an edge 4A, which ensures optimal absorption of air entering the fan and the internal compressors, and its direction towards the turbojet engine, and back flow element 4b, to which is attached the specified edge 4A and which provides adequate venting in the direction of the fan blades. This node is attached to the flow front of the fan shroud, which is a part of the middle part 5 of the nacelle 1.

As shown in more detail in figure 1-5, the edge 4A of the inlet 4 is made with application of sections 7 according to the invention, mounted around the perimeter of the nacelle 1 on the rear flow element 4b. Each section 7 is separated from the adjacent section 7 by a separating element 8 is made as one piece with the back flow of elements stored is 4b.

In this case, the edge 4A of the inlet 4 is made of four sections 7. It is obvious that it can also be done from two sections 7, or as a whole, or more than four sections 7.

Each section 7 contains the wall 10, the form of which is chosen in such a way as to give the edge 4A of the desired profile, and sound-absorbing element 30 cell type in contact with the area of the wall 10 facing the fan inlet and containing a number of holes 11, is made with a uniform pitch.

The wall 10 section 7 has an outer wall 12 facing outward edges 4A, the inner lining 13, facing the inside of the flange 4A and the electric heating element 14 mounted between the inner casing 13 and the outer skin 12. This element is connected with the power supply output 16 of the rear flow element 4b through a connector 15 connected to the cable 15' power. Figure 3 for clarity cable 15' are not shown. It should be noted that the cable 15' can also provide special holders with clamps (not shown).

The outer casing 12 provides aerodynamic outer profile of the edge 4A. It can be made of metal or composite material may be preformed or executed during the installation of the electric heating element 14. The thickness of the Nar is the author of the shell 12 is relatively small, that provides good heat transfer in the direction of the outside edge 4A. For example, the edge thickness can be several tenths of a millimeter.

The inner lining 13 covers the heating element 14 and completes the wall 10. As the outer casing 12, it can be made of metal or composite material may be preformed or executed during the installation of the electric heating element 14. It should be borne in mind that the thickness of the inner shell 13 and the thickness of the outer shell 12 may be different.

The various layers forming the wall 10 of section 7, are connected to each other through a bonding material such as adhesive or resin (not shown).

As the electric heating element 14 can be applied cut-out metal resistor element type. Particularly preferred form of electrical heating resistor 14 is zigzag form. Of course, you must ensure that the surface of the electric heating element 14 allows to achieve the desired de-icing temperature.

As disclosed above, the power to the electric heating element 14 is effected by means of a cable 15'connected to the power source. This cable passes through the inner lining 13 section 7 near its center, and then connect the same way to the power supply back flow element 4b of the inlet 4 through the connector 15. Measures should be taken that the cable 15' was protected during the manufacturing process of the wall 10, especially during the polymerization of the inner shell 13 and the outer shell 12, as well as resins, in the case of organic structures made of composite material.

7-11 presents the different possible configurations of electric heating element 14. It should be noted that you can install multiple parallel connected heating elements 14. Even if one of these elements fails, the others will be able to continue the implementation of anti-icing.

You can also include multiple layers of electrical heating elements 14, which can be mounted with different configuration.

In addition, the back flow element 4b contains a front wall 18, in which for each partition 7 edge 4A is made by the connector 19, and each connector 19 is connected to a power source (not shown) of the nacelle 1 by means of a cable 19' power. Each connector 19 is arranged to interact with the connector 15 of the respective sections 7 through the outlet 16 of the power supply.

In order to provide access to the various electrical elements, which include section 7 of the edges 4A, the connector 19 can be mounted on removable plates 20, representing the Wallpaper and part of the front walls 18, as further shown in Fig.6, which shows one of the embodiments of the nacelle 1 according to the invention. When removing the removable plate 20 or one of several such plates, the operator gains access to the inside of section 7 of the flange 4A.

Alternatively, access to the electric elements can be accessed through holes (not shown)made in the front wall 18 near each connector 19.

Access to the removable plate 20 or to these holes is carried out through the outlets 21, performed on the outer wall 22 of the rear flow element 4b.

Alternatively, the outer wall 22 may be partially connected with the movable leaves of the middle part 5, provides access to the fan shroud. The disclosure of these movable sash opens the outer wall 22 of the rear flow element 4b, which provides access to the front wall 18 and a connector 19.

Figure 5 as an example, one particular embodiment, in order to reduce the number of service outlets 21, performed in the outer wall 22 of the rear flow element 4b, in the area of the two opposite joints of the sections 7 are only two flush-mount unit 21. Each of the hatches 21 provides access to the connectors 19 of two adjacent sections 7.

For this purpose, the outlet 16 of the power supply back flow element 4b have about the time, so they were at least at one end of each section 7.

To allow installation section 7 anywhere on the back of the flow element 4b, section 7 has a socket 15 in the immediate vicinity of each end. Each connector 15 is closed conductive cap 24. Immediately after you install the connector, you just need to remove the conductive cap 24 with the connector 15, which is opposite to the connector 19, leaving in place a conductive cap 24 located on the other connector 15, so as to maintain the electrical continuity of the corresponding electric heating element 14.

Although the above invention has been described with reference to certain specific variants of its implementation, it should be understood that it is in no way limited to these options and covers a variety of technical equivalents are considered here, as well as various combinations thereof, provided that they do not go beyond the scope of the invention.

For example, it should be absolutely clear that the heating element can be placed in a cavity bounded respectively by the edge 4A or each section 7, and not to lay between the two casings 12, 13 section 7.

1. Back on thread element (4b) of the inlet (4) of the nacelle (1) turbojet engine, will the United attaching thereto edges (4A) air intake containing at least one de-icing heating element (14), and the specified heating element is equipped with at least one electrical connector (15), and the specified edge is made of at least two identical sections (7)connected end-to-end around the perimeter of the inlet, characterized in that it contains at least one slot (19) power supply, configured to interact with a corresponding electrical connector (15) edge of the air intake, and specified electrical connector secured in the front wall (18) back flow element.

2. Back on thread element (4b) according to claim 1, characterized in that the front wall (18) has at least one aperture providing access to the connector (19) of the power supply.

3. Back on thread element (4b) according to claim 1, characterized in that the connector (19) of the power supply is mounted on a removable plate (20), which is a part of the front wall (18).

4. Back on thread element (4b) according to any one of claims 1 to 3, characterized in that it contains at least one hatch (21)made in the outer wall (22) and to allow access to the connector (19) of the power supply.

5. Back on thread element (4b) according to claim 4, characterized in that the flap (21) is located at the intersection of two sections (7) edge (4A) air is sabornie.

6. Back on thread element (4b) according to any one of claims 1 to 3, characterized in that it has an outer wall (22)which at least partially connected with movable shutters middle section (5) of the nacelle (1).

7. Gondola (1) turbojet engine, characterized in that it contains an inlet (4), containing the back flow element (4b) according to any one of claims 1 to 6.