RU187488U1 - REVERSE TURBOJET ENGINE - Google Patents

Abstract

The object of the technical solution: a reversing device of a turbojet engine.

Scope: in the aviation industry as equipment for power plants of turbojet bypass engines.

The essence of the technical solution: the reversing device is made in the form of an open cylinder with the possibility of passing on both sides of the pylon during maintenance. The device includes a movable fairing, consisting of external and internal buildings, and a power frame made in the form of sections with deflecting grids. The split reversing device contains end walls that are adjacent to the pylon included in the power circuit of the engine, and are made of plates. The plates contain carriages in contact with the rails located on the pylon for moving the reversing device during maintenance using a movable device. The plates contain longitudinal grooved guides for attaching and moving the movable fairing relative to the pylon in thrust reversal mode and similar guides for attaching and moving the movable nozzle parallel to them. The pylon contains separate transverse elements forming a rigid closed ring structure with the power frame of the reversing device. The sealing of the end walls of the reversing device with the pylon in direct draft mode is made in the form of surfaces located on the plates from the outer housing of the movable fairing, and a tubular rubber seal located opposite these surfaces on the pylon wall. Fastening of the reversing device to the engine flange is carried out by easily accessible quick-release locks with the possibility of mechanical lifting of the device to the engine.

EFFECT: increasing the operability of the reversing device during maintenance of the gas generator of engines with a large bypass ratio by providing access to the gas generator with minimal time and labor, removing the reversing device on an airplane or test bench without removing the engine, and at the same time creating a power plant, fully equipped with all propulsion and aircraft systems. 4 s.p. f-ly, 7 ill.

Description

The claimed technical solution relates to the equipment of power plants of turbojet bypass engines and can be used in the aviation industry.

Known sliding thrust reverser for a turbojet engine (patent RU 2451815, patent holder Aircelle, IPC F02K 1/72, convention priority dated January 15, 2007 FR 0700249), which allows maintenance of the gas generator of the engine. Mentioned thrust reverser, forming part of the tail section of the nacelle of a turbojet engine, contains a frontal frame attached to the fixed part of the nacelle and carrying power cylinders of the drive of the movable hood, and a grid of deflecting blades around the perimeter. The frontal frame has a fixed part, designed to attach the frontal frame to the fixed part of the nacelle and supporting the deflector blades, as well as a part installed with the possibility of translational movement along the axis of the nacelle and on which one of the ends of the power cylinders of the hood drive is fixed. The fixed and movable parts of the frontal frame are equipped with locks, ensuring their mutual engagement and disengagement. This invention allows to simplify the shift of the movable hood during maintenance.

However, the disadvantage of the known design is the excessive weight, which is due to the fact that to ensure the independent actuation of the movable hood using separate power cylinders and locking means.

Also known is the design of a split reversible device, the power cage of which is mounted on an airplane pylon and the reversible device is shifted by an airplane pylon (patent US 7484356, patent holder Aeronautical Concepts of Exhaust, IPC F02K 3/02, application dated July 24, 2006).

The disadvantage of this design is that the reversing device is simultaneously attached to the pylon of the aircraft and to the engine, that is, another engine mount point appears and the power engine mount system becomes statically indefinable. The engine during the flight moves from external forces relative to the wing pylon and these loads can damage the reversing device.

Among the analogues of the claimed device, it is necessary to mention the thrust reverser according to patent RU 2546132 (patentee Aircelle, IPC F02K 1/72, convention priority dated November 18, 2009 FR 0905535). Said thrust reverser of a nacelle of a turbojet engine comprises an external hood and a front frame. The hood is made with the possibility of opening with the transfer to the maintenance position, in which it is pivotally rotated and guided by means of guide means related to the movable hood and located on the pylon to which the nacelle is attached. The front frame in one of its sections is detachably connected to the fan casing and is made with the possibility of translational movement along the guide means after it is disconnected from the casing.

The disadvantage of the described design is that in the thrust reversal mode the piston stroke of the power cylinders is limited by the movement of the outer hood, which is not enough to provide a convenient approach to the gas generator when shifting the front frame, cascades of blades together with the outer hoods. When combining the functions of the power cylinders to move the outer hood in the mode of reversing the thrust and shifting the entire reversing device as a whole during maintenance, complex protection against unauthorized activation of the power cylinders in any situation is necessary. The front frame is connected to the fan casing with the help of connecting means such as "knife support / groove". This type of connection requires complex actions to disengage it.

Closest to the claimed technical solution is the reversing device of a turbojet engine according to patent RU 2474717 (patent holder of MINPROMTORG of RUSSIA, IPC F02K 1/72, B64D 29/06, application dated 10.28.2011). Said reversing device includes a movable fairing, overlapping flaps, a power frame made in the form of a main section with deflecting grids and a connector. The device also contains an additional section installed in the connector of the main section of the power frame and forming a rigid closed annular structure with the main section. The additional section is made in the form of a frame or several separate transverse elements and is attached to the main section of the power frame by a bolted connection. The main or additional section of the power frame is made with fixing elements for mounting on the pylon of the wing of the aircraft.

To shift the reversing device, it is necessary to fix an additional section of the power frame for the pylon of the wing of the aircraft. After that, along the guides located on the additional section, shift the reversing device. This technology is very complex and time-consuming when servicing the engine.

The technical result of the proposed solution is

 increasing the operational manufacturability of the reversing device during maintenance of the engine gas generator by providing access to the gas generator of gas turbine engines with a large bypass ratio with minimal time and labor;

 removal of the reversing device on the plane and on the test bench without removing the engine;

 the simultaneous creation of a power plant, as equipped as possible with all propulsion and aircraft systems.

The claimed technical result is achieved by the fact that the reversing device of the turbojet engine is made in the form of an open cylinder with the possibility of passing on both sides of the pylon during maintenance. The reversing device includes a movable fairing, which consists of an outer and inner case, and a power frame made in the form of sections with deflecting grids located between the inner and outer cases of the moving fairing.

The split reversing device contains end walls that are adjacent to the pylon included in the engine power circuit and are made in the form of separate plates containing carriages that are in contact with rails located on the engine pylon (motor pylon) to allow the reversible device to be moved during technical service using a mobile device. The power of the specified sliding device is provided from a ground source.

The said plates contain longitudinal grooved guides for the possibility of fastening and moving the movable fairing relative to the engine pylon in the thrust reversal mode and similar guides located parallel above them for the possibility of fastening and moving the movable nozzle of the outer contour of the engine.

The engine pylon contains individual transverse elements that form a rigid closed ring structure with the power frame of the reversing device. The sealing of the end walls of the reversing device with the engine pylon in direct traction mode is made in the form of surfaces located on the said plates from the outer housing of the movable fairing, and a tubular rubber seal located opposite these surfaces on the wall of the engine pylon.

Fastening the reversing device to the engine flange is made by easily accessible quick-release locks with the possibility of mechanical lifting of the device to the engine.

In FIG. 1 shows the appearance of a power plant with a gas turbine engine and a reversing device in the forward thrust position.

In FIG. 2 is an external view of a power plant with a gas turbine engine and a reversing device in the thrust reversal position.

In FIG. 3 is an external view of a power plant with a gas turbine engine and shifted reversing device during maintenance of the engine gas generator.

In FIG. 4 is an external view of a gas turbine engine with an engine pylon and with a reversed device and gas generator hoods removed.

In FIG. 5 - remote element I docking the rear flange of the engine and the engine pylon.

In FIG. 6 is a transverse section of the power plant along section AA with elements of the movable parts of the reversing device and their connection with the engine pylon.

In FIG. 7 - remote element II docking reversing device and the engine pylon.

The power plant 1 (see Fig. 1) consists of a gas turbine engine 2, a reversing device 3, a movable nozzle 4 of the external circuit, suspension units of the power plant 1 (see Fig. 4) - front 5 and rear 6 - and parts of aircraft systems ( not shown). The reversing device 3 (see Fig. 2), in turn, contains a movable fairing 7 and a power frame 8. The movable fairing 7 consists of two buildings (see Fig. 6) - external 9 and internal 10, and the power frame 8 ( see Fig. 2) is made in the form of sections with deflecting grids located between the outer 9 and inner 10 bodies of the movable fairing 7 (see Fig. 2, 6, 7). Under the reversing device 3 (see Fig. 3) there are hoods 11 covering the gas generator 12 (see Fig. 4) of the gas turbine engine 2. The main power part of the hoods 11 (see Fig. 3, 6) is the engine pylon 13, which is turned on into the power circuit of a gas turbine engine 2.

The reversing device 3 (see Fig. 6) is made in the form of an open cylinder - in its upper part it has a cut for passing the motor pylon 13. The split reversing device 3 contains two end walls adjacent to the motor pylon 13 and made of plates 14 (see. Fig. 6, 7), on which the fixing elements and the seal are placed. In each of the two plates 14 in its lower part there are longitudinal grooved guides 15 (see Fig. 7). The described guides 15 are intended for fastening and organizing the shift of the outer 9 and inner 10 bodies of the movable fairing 7 (see Fig. 2) in the thrust reversal position. At the same time, in each plate 14 (see Fig. 7) longitudinal grooved guides 16 are installed for fastening and arranging the movement of the sliding nozzle 4 (see Fig. 2) of the outer contour of the gas turbine engine 2. Longitudinal grooved guides 16 (see Fig. 7) are located above the longitudinal grooved guides 15 and parallel to them.

Carriages 17 are fixed to each plate 14 from the side of the outer surface of the motor pylon 13 using brackets 18. The carriages 17 are in contact with the rails 19 (see Figs. 7, 3, 4) fixed on the outer surface of the motor pylon 13. On both sides of the motor pylon 13 (see FIG. 7) and in the upper part of each plate 14, sliding devices 20 are symmetrically arranged. Movable devices 20 (see FIG. 3) provide movement of the reversing device 3 together with a sliding nozzle 4 of the external circuit along the longitudinal axis of the gas turbine engine 2 in side with the jet nozzle 21 for the purpose of providing an approach to the hoods 11 during maintenance of the gas generator 12 (see Fig. 4) of the gas turbine engine 2. The sliding device 20 can be made in various ways, in particular in the form of a nut and a spindle or gear-rack pair . However, to protect against unauthorized shear of the reversing device 3, only the ground source of energy is used in the system of the sliding device 20.

At the same time, on each plate 14 (see Fig. 7), from the side of the inner case 10 of the movable fairing 7, sealing surfaces 22 are made for hermetically sealing the air channel 23 of the external circuit of the gas turbine engine 2 in direct draft mode. Opposite the sealing surfaces 22, a tubular rubber seal 24 is arranged on the wall of the engine pylon 13, which is inflated by air from the compressor of the gas turbine engine 2 only during its operation. At the same time, the pressure in the tubular rubber seal 24 is greater than in the air channel 23. At the moment of shifting the reversing device 3, the tubular rubber seal 24 is not inflated and does not come into contact with the sealing surfaces 22 of the reversing device 3, while ensuring that the reversing device 3 is shifted with minimal resistance.

To organize a closed ring structure of the reversing device 3 (see Fig. 6, 7) and the motor pylon 13 in the pylon 13 transverse elements 25 are made, which provide additional rigidity necessary for reliable operation of the entire structure.

The fastening system of the reversing device 3 (see Fig. 1) kinematically closes on the gas turbine engine 2: the reversing device 3 is attached to the gas turbine engine 2 with quick-release locks 26, which are easily accessible. On the rear flange 27 (see Fig. 3) of the gas turbine engine 2, housings 28 of quick-release locks 26 are evenly arranged around the circumference, and on the front flange 29 of the reversing device 3, grippers 30 of quick-release locks 26 are respectively located. To ensure a stable seal between the rear flange 27 of the gas turbine engine 2 and the front flange 29 of the reversing device 3, as well as for unloading the sliding devices 20, quick-release locks 26 (see Fig. 1) have the ability to mechanically tighten the reversing device 3 to the gas turbine engine to player 2.

At the same time, the engine pylon 13 (see Figs. 3, 4), as the power part of the hoods 11 of the gas generator 12, is attached to the rear flange 27 of the gas turbine engine 2 with a bolt joint 32 with its front flange 31 (see Fig. 5). this, the back of the engine pylon 13 (see Fig. 4) is attached to the bodies of the gas generator 12 of the gas turbine engine 2 through a movable mount 33, which compensates for the thermal movement of the bodies of the gas generator 12.

To shift the reversing device 3 (see Fig. 1) during maintenance of the gas generator 12 of the gas turbine engine 2 (see Fig. 4), quick-release locks 26 are opened on the aircraft or in the workshop. Then manually or using sliding devices 20 (see Fig. 3), which are powered by a ground-based energy source, the reversing device 3 along the rails 19 rolls along the longitudinal axis of the gas turbine engine 2 towards the jet nozzle 21, opening the approach to the hoods 11 of the gas generator 12 of the gas turbine engine 2. At the moment the rolling tubular rubber seals 24 (see Fig. 7) are not inflated and do not come into contact with the sealing surfaces 22 of the reversing device 3, providing a shift of the reversing device 3 with minimal resistance.

The claimed technical solution is intended for a dual-circuit gas turbine engine, which has a complicated approach to the gas generator of the engine during its maintenance, because it is located under the reversing device, in particular for the AI-28 turbojet dual-circuit engine, which is at the stage of layout work.

Claims (6)

1. The reversing device of a turbojet engine, attached to the engine flange with quick-release locks, is made in the form of an open cylinder with the possibility of shifting and passing on both sides of the pylon during engine maintenance, includes a movable fairing, consisting of external and internal cases, a power frame made in the form of sections with deflecting grids located between the inner and outer housings of the movable fairing, as well as guides for the possibility of moving IG Petritskaya cowl and separate transverse elements which form a force-reversing device frame rigid closed annular structure, characterized in that it contains end walls that are adjacent to the engine pylon included in the power circuit of the gas turbine engine, and are made of plates containing a sliding mechanism for moving the reversing device together with the sliding nozzle of the external circuit of the engine during maintenance, which is a carriage in contact with rails located on the motor pylon. 2. The reversing device according to claim 1, characterized in that the longitudinal grooved guides for mounting and moving in reverse mode of the thrust of the movable fairing relative to the motor pylon are located in the lower part of the plates, and parallel to them longitudinal grooved rails are placed for the possibility of mounting and moving the sliding nozzles of the external circuit of a gas turbine engine. 3. The reversing device according to claim 1, characterized in that the hermetic seal of the air channel of the external circuit of the gas turbine engine in direct thrust mode is organized using sealing surfaces made on plates from the side of the inner body of the movable fairing, as well as a tubular rubber seal opposite the sealing surfaces on the wall of the motor pylon. 4. The reversing device according to claim 1, characterized in that the quick-release locks are made easily accessible and provide the ability to mechanically tighten the reversing device to the engine. 5. The reversing device according to claim 1, characterized in that the movement of the reversing device together with the movable nozzle of the external circuit of the gas turbine engine during maintenance is carried out using movable devices that are powered by a ground source.

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