Device for restraint and arrangement of auxiliary equipment in turbojet engine with primary and secondary air outflow and removable panel

FIELD: engines and pumps.

SUBSTANCE: invention refers to aviation and particularly to devices for restraint and arrangement of auxiliary equipment in turbojet engines. The device consists of two coaxial rings (12, 14) assembled one into another and connected to each other with hollow radial poles (16, 18, 20 and 22). The pipelines and electrical wires run inside poles. At least one of the side poles (16, 18) bears a removable panel (24, 26) on its side, which after dismounting facilitates an access to the equipment of the turbojet engine arranged radially inside the interior ring (12) in one line with the radial pole (16, 18). Such design of the device provides an access to the equipment, installed in a turbojet engine.

EFFECT: facilitating access to equipment, assembled in a turbojet engine due to arrangement of a restraining device and of auxiliary equipment.

10 cl, 5 dwg

 

The present invention relates to a device for holding and positioning accessories in turbojet engine with the expiration of the primary and secondary air; however, this device comprises two coaxial rings arranged one in the other and United by a hollow radial struts through which the pipelines and electric cables.

This device is installed around the compressor turbojet engine below vozduhonagrevatelej device and above the turbine turbojet engine and can interact through its outer ring with thrust reverser mounted at the bottom of the device.

The space between the outer and inner rings of the device is an annular channel to the expiration of secondary air, which comes from vozduhonagrevatelej device turbojet engine and is designed, in particular, for cooling of structural elements turbojet engine.

In the prior art it is known that the radial rack devices are monobloc, the inner ring contains plates of the parts of the cylinder (located, for example, perpendicular), which are attached by screws to anchor the corner of the console and can be removed to provide access to the equipment installation is presented at the outer compressor casing, for production maintenance.

However, this design does not provide access to the devices located inside the inner ring and along the radial racks, which belong to the category of linear replacement parts (LRU-Line Replaceable Unit), for example, to the power cylinder control adjustment installation of the output angles of the guide vanes of the compressor, which should be removed without disassembly of the rings restraint accessories.

The objective of the invention, in particular, is to develop a simple, effective and inexpensive technical devices of the above type.

For solving the problem of the developed device for holding and placement of auxiliary equipment in a turbojet engine with the expiration of the primary and secondary air containing two coaxial rings arranged one in the other and United by a hollow radial struts through which the pipelines and electric cables, characterized in that the lateral surface, at least one radial rack includes a removable panel, the removal of which provides access to the equipment turbojet engine, located radially inside of the inner ring along the radial supports.

In the device according to the invention, each radial is toyka, above hardware items turbojet engine, which is subject to maintenance, contains on the side of the removable panel, which is secured by screws or equivalent means on the radial rack. Thus, facilitates maintenance of equipment placed along the radial racks; the corresponding operations can be performed directly on the turbojet engine mounted below the wing of the plane.

Removing the removable panels of the radial struts provides access to electric cables and pipelines that run inside radial racks. In this context, it is possible to easily disassemble and replace pipelines and cables.

Another feature of the invention is that the removable panel includes a radial part, mounted on the radial rack, and a cylindrical connection part with the inner ring. This simplifies the process of accessing and diagnosing equipment motor located inside the inner ring, facilitates the use of tools during disassembly and maintenance of this equipment can be used to retrieve some items of equipment with a view to their subsequent replacement.

From a practical point of view, the radial portion of the removable panel is located and fixed, at least some of its edges along the sides of the respective radial racks, and a cylindrical part of these removable panels is located and fixed at least some of its edges along the sides of the respective inner rings.

If the pipeline passes within radial racks located on the circumference of the inner ring, the circumference of the circular part of this pipeline, as a rule, less than the length of the cylindrical portion of the removable panel radial rack that provides access to this pipeline and allows you to retrieve it if necessary from the inner part of the inner ring.

This pipeline, for example, can be used as a channel for the circulation of warm air, one edge of which is open on the side of the compressor turbojet engine to bleed air from the compressor, and a second edge attached to the outer ring and connected with the means of circulation.

The device also includes a seal means, such as sealing gaskets installed at the junction of the removable panel and radial hours and (or) between the removable panel and the inner ring.

These sealing gaskets have good thermal characteristics and allow you to limit and even to prevent the spread in wtorek the om flow in the radial direction towards the periphery of spontaneously occurring inside the engine flame.

According to one embodiments of the invention the device comprises two radial racks, which are located opposite each other relative to the axis of the ring; each of them includes a removable access panel located inside the inner ring of the equipment to which, for example, can be attributed to the power cylinder control of the discharge linear replacement parts (LRU-Line Replaceable Unit) output of the guide vanes with adjustable mounting angles.

The invention also relates to a removable panel previously described device, characterized in that it is made in an L-shaped and includes a flat plate, radially located and attached to the plate, bent in the form of an arc of a circle; this panel contains multiple through holes for bolts along at least one of its longitudinal edges and located along the end edge of the curved plate.

This removable panel along the edges of these radial and curved plates has a generally airtight seal.

The invention will be better understood, and other details, features and advantages of the present invention more apparent after reading the accompanying description are for illustrative purposes only, and with figures of the drawings, in which:

Figure 1 depicts the scheme is practical view in isometric device according to the invention, the holding and positioning accessories in turbojet engine with the expiration of the primary and secondary air;

Figure 2 is a partial, schematic view (zoomed image) with this device, which shows a radial hour, equipped with removable panel;

Figure 3 is another schematic perspective view of the radial rack, shown in figure 2, without the removable panel;

Figure 4 depicts a partial schematic view (on an enlarged scale, of the device shown in figure 1, and represents the other radial rack features a removable panel;

5 is another schematic view in isometric radial rack shown in figure 4, without the removable panel.

1 shows a device 10 according to the invention, intended for holding and positioning accessories in turbojet engine with the expiration of the primary and secondary air, consisting of two coaxially with a cylindrical shape, is placed in one another and interconnected by means of radial struts 16, 18, 20 and 22 of the rings 12, 14; however, some of the racks 16, 18 contain removable side panel 24, 26, which provides access to the equipment turbojet engine located inside the inner ring and partially along the radial hours and allows you to perform maintenance.

This device is installed below vozduhonagrevatelej device turbojet engine is, and the inner ring 12 is located around the outer casing of the compressor turbojet engine without any contact with him, along the axis of the other corps turbojet engine. The space between the inner 12 and outer 14 rings is an annular channel to the expiration of vozduhonagrevatelej device secondary air, which is schematically shown by arrows.

The outer ring 14 at its upper and lower edges has an external annular bead 28 of the bracket (by using appropriate means) to the intermediate casing of the turbojet engine and the thrust reverser, respectively. The outer ring 14 provides power transmission between the intermediate casing and the thrust reverser, which, for example, can be a portal-type.

In this example, we consider four radial racks 16, 18, 20, 22.

Two radial racks 16, 18, when viewed relative to the axis of the device, are located opposite each other and in the vertical plane. By analogy with the time dial, the upper rack 16 is called the "hour of 12 o'clock and the bottom strut 18 - "hour for six hours; the other two radial racks 20, 22 are located on either side of the lower rack 18, at an angle of about 60° to her, and called "hour for four hours and hour for eight hours."

These stand and 16, 18, 20, 22 are hollow and have internal and external sides of the open edges to structural elements, radially on the inside and the outside of the device could be connected to pipelines and electrical cables passing inside the poles.

For example, electrical cables are routed inside the rack 20, the fuel pipe is inside the rack 22, the oil line inside the rack 18, the duct inside the rack 16.

Another duct 23 includes a nozzle mounted in the lower part of the upper rack 16 and elongated parallel to the axis And devices. This tube in the upper part connected to the means of sampling air in a secondary thread, and at the bottom by appropriate means providing circulation of air for cooling the structural elements of the turbojet engine and blowing air of the cockpit turbojet aircraft.

As shown in figure 2-5, radial upper 16 and lower 18 hours contain removable side panel 24, 26, which provides access to structural elements that are mounted on the housing (not shown) of the compressor, located on the radial line of the column.

The removable panel 24 of the rack 16 in L-shaped and includes a flat plate 50 placed on the radial side of the rack 16 and is designed to Zack who set it up; its inner end edge it is connected with the adjacent rack plate 52, the curved shape of the round arch and forming part of the inner ring 12.

The plate 50 is fastened by screws 54 along its upper and lower edges of the respective radial flanges 56, 58, which are disposed respectively along the top 60 and bottom 62 of the side edges 16 hours (see figure 3).

The plate 52 is fastened by screws 54 along its top edge and opposite the front side edges 16, i.e. on the circle Board 64, which is located along the top edge of the ring 12 and the axial Board 66, which on the surface of the ring stretches from top to bottom. Supporting the annular Board 64 of the plate 52 connects the axial Board 66 with the upper radial flange 56 of the rack 16.

Axial Board 66 of the ring 12 on the outer surface has an axial groove 70 in which is sealed gasket (not shown). This gasket is located between the flange 60 of the ring and plate 24 in order to prevent, on the one hand, the flow of secondary air in the radial direction and in contact with the inner part of the inner ring and, on the other hand, the spread in the secondary flow in the radial direction towards the periphery arisen flame.

The removable panel 26 of the rack 18 has the shape of the letter L, but earaser less than panel 24.

The panel 26 is a flat plate 90, which is arranged in the radial direction on the side of the rack 18 has a height two times less than the height of the rack, and connected to the plate 92, curved in the form of a round arch and placed on the inner ring 12.

The plate 90 is fastened by screws 54 along its radial outer edge and its upper edge on the respective sides 96, 98 of the rack. Board 96 is elongated along the axis, from top to bottom along the inner, radially located lateral edge 100 hours, and the Board 98 is elongated in the radial direction along the upper side edges 102 of the rack. The plate 92 is located and mounted on the sides 64, 66 of the ring in the same manner as described previously in the case of plate 52 with reference to figure 3.

Tight gasket (not shown) is fitted in the axial groove 104 of the side 66 of the ring and is compressed between the flange 66 and the plate 26. An airtight gaskets may be provided for the axial grooves of the flanges 96 hours and circular flanges 64 of the ring 12.

In this example, the dismantling of the panels 24, 26 of the uprights 16, 18 allows you to perform maintenance of the power cylinder 30 and the pipe 72, which is mounted on the compressor casing along or around the edges of the uprights 16, 18.

Power cylinders 30 are closer to the top, strictly computers is the super-axis device. The body 32 of each power cylinder is suspended by a bracket, which is attached by screws 36 or equivalent means to the compressor casing.

The piston rod 38 of each power cylinder is connected with the mechanism 40 adjustment installation of the output angles of the guide vanes of the compressor by means of thrust 42, one end of which has a connecting rod connection mechanism 40, and the other is attached to porshneva stem 36 design of the bolt-nut or equivalent means.

The mechanism 40 is attached to the chassis with two screws 46 and is connected by appropriate means 48 with the control ring washers (not shown), which are located around the casing of the compressor and rotate around the axis of the turbojet engine to give axial rotational movement of the output of the guide blades.

Disassembly of the panels 24, 26 provides access to the mounting screws that are located on the same line with the radial struts.

The duct 72 is laid inside the rack 16 and has a radial location; one end located inside the circle is attached to the compressor casing and has an open edge, through which the selection of warm air; the other end located on the outer side of the circle, is fastened to the outer ring 14 and is connected to another pipe 74, which provides SN is Beenie air, for example, gondolas turbojet engine for de-icing.

The pipe 72 has a radial location. He stretched, starting from its outer end, which is attached to the outer ring 14, knee-76, where it connects with the circular part of the pipe 78, which passes inside the inner ring 12 along and on the edge of the circular flanges 64 of the ring 12.

The edge 78 of the pipeline, located in front of the rack 16, connects with another knee 80 axial part 82 of the pipeline, which stretches towards the bottom part and connected to its lower end with a knee 84, on the open edge of which has a flange 86 that is attached by screws 88 to the compressor casing.

Removing the access panel 24 also provides access to the screws 86 securing the pipeline. In this regard, to extract the pipe circumference curved plate 52 of the panel 24 must be greater than the length of the segment 78 of the pipe 72.

1. Device for holding and positioning accessories in turbojet engine with the expiration of the primary and secondary air, consisting of two coaxially placed one in the other and interconnected by means of hollow radial struts (16, 18, 20 and 22) rings (12, 14), inside which are the pipelines (72) and electric cables, different is eat, what lateral side of at least one side of the rack (16, 18) includes a removable panel (24, 26), removal of which provides access to the equipment (30) turbojet engine, located radially inside the inner ring (12) on one line with a radial counter (16, 18).

2. The device according to claim 1, characterized in that the removable panel (24, 26) includes a radial segment, which is secured by screws (54, 94) or similar means to the radial rack (16, 18), and a cylindrical connection part with an inner ring (12).

3. The device according to claim 2, characterized in that the radial cut removable panel (24, 26) is located and fixed at least along some of its edges to the corresponding edges (56, 58, 96, 98) radial rack (16, 18), and the cylindrical portion of the removable panel (24, 26) is located and fixed at least along some of its edges to the corresponding edges (64, 66) of the inner ring (12).

4. Device according to any one of claims 1 to 3, characterized in that it comprises means of seals, including seals between the detachable panel (24, 26) and radial counter (16, 18) and (or) between the detachable panel (24, 26) and an inner ring (12).

5. Device according to any one of claims 1 to 3, characterized in that the pipe (72) is stretched in the radial direction in the radial rack (16) along the access panel (24) and a circle inside HV the inner ring (12), the length of the circular segment (78) of the pipe (72) is less than the length of the cylindrical portion of the removable panel (24).

6. The device according to claim 5, characterized in that the pipe (72) is a duct designed to circulate warm air, one end of which is introduced into the compressor turbojet engine for air sampling, and the other end attached to the outer ring (14) and is connected with the means of circulation.

7. Device according to any one of claims 1 to 3, characterized in that it comprises two radial rack (16, 18)located opposite each other relative to the axis (A) rings (12, 14) and includes each removable access panels to the equipment (30)located within the inner ring (12).

8. Device according to any one of claims 1 to 3, characterized in that the power cylinder (30) of the control regulation the installation of the output angles of the guide vanes is equipment that becomes available after the dismantling of the removable panels (24, 26).

9. Removable panel device according to claims 1 to 8, characterized in that it is made in an L-shaped and includes a flat radial plate (50, 90)connected to curved in the form of a round arch plate (52, 92), while the control panel has several screw holes along at least one of the longitudinal edges and along the end edges from the other plate.

10. The removable panel according to claim 9, characterized in that it comprises a sealed strip installed along the edges of the radial (50, 90) and curved (52, 92) plates.



 

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