RU2425242C1 - Device for turning traction vector of double-flow jet turbine engine - Google Patents

Abstract

FIELD: engines and pumps. ^ SUBSTANCE: device for turning the traction vector of double-flow jet turbine engine includes central body of gas generator of inner circuit and engine nacelle of fan of outer circuit with annular nozzle at the outlet, which contains reverse and diverting flaps of bucket shape, which are arranged in openings in rear part of engine nacelle along the opening periphery. Reverse flaps are fixed in rear part of each opening of engine nacelle on transverse axes, and each diverting flap is hinged on transverse axis with its reverse flap. Each reverse flap is equipped with an opening in which hollow diverting flap consisting of outer and inner walls with a channel between them is installed. Along longitudinal edges of engine nacelle openings, between engine nacelle and central body of gas generator the path of outer engine circuit is separated with radial pylons contacting reverse and diverting flaps. Each reverse flap is equipped on the outside in front part with fairing made in the form of hollow triangular annular sector. Diverting flap is arranged in reverse flap after fairing and hinged to the drive located in the fairing. ^ EFFECT: invention allows increasing lateral stability, vertical and transverse aircraft sensitivity at high angles of attack and at low flight speeds. ^ 3 cl, 6 dwg

Description

The invention relates to devices for reversing and changing the direction of the thrust vector of aircraft turbojet bypass engines.

It is known that nozzles with upgraded reversing devices (RU) can be used as a means of increasing the level of flight-technical, maneuvering and flight characteristics of aircraft, which ensures controllability in low-speed flight modes, where aerodynamic control elements are not efficient enough.

The use of additional devices for thrust vector deviation (AE) on the aircraft is considered as one of the opportunities to improve the flight performance of promising aircraft.

A deflecting device is known that changes the direction of the exhaust stream, for example, a nozzle with a deviation of the thrust vector of Stage III Technologies L.C. (US Patent No. 6233920 dated 05/22/2001). A casement type design mounted on a nozzle is proposed. On flight and take-off modes, RU shutters form the outer walls of the nacelle fairing. When thrust reverse is turned on, the flaps shift downstream and turn. However, to deviate the exhaust jet of a bypass engine with a high bypass ratio, the use of a rotary nozzle is difficult due to its large mass.

SNECMA Moteurs has developed a reversing device and a turbojet engine nozzle (US Patent No. 6289670 of September 18, 2001). The nozzle flaps in the device provide for large adjustment of the nozzle area and control of the direction of the thrust vector, which makes it possible to use this device on promising supersonic aircraft. However, in this patent, the angle of change of direction of the thrust vector is within small limits.

The closest analogue of the same purpose in design as the claimed technical solution is the “Device for reversing the thrust of a dual-circuit turbojet engine” RF Patent No. 2162537 dated 06.06.1998 from the company ISPANO - SUIZA AEROSTRUCTURE (Fr). The device includes a cylindrical nacelle of the external circuit fan and the central body of the gas generator of the internal circuit of the engine. The device comprises an annular nozzle at the rear of the engine nacelle at the periphery of the window and at the exit. The windows are equipped with reversible and deflecting flaps, which have the shape of a scoop type, where the reversible flaps are hollow and are installed in the rear of each window of the nacelle on the transverse axes. Each deflecting leaf is pivotally connected on its transverse axis with its reversible leaf. In addition, the reversing and deflecting flaps are pivotally connected to controls for their movement. This device performs a predetermined reverse thrust and is relatively simple in design. The main disadvantage of the device is the large loss at high angles of deviation of the exhaust jets in the OBT mode.

Thus, the well-known design of the switchgear can no longer meet modern requirements for ensuring the characteristics of lateral stability and lateral controllability at large angles of attack of modern aircraft with classic aerodynamic control surfaces.

The basis of the invention is the solution to the problem of creating a modern reactor plant with the addition of the functions of OVT.

This will increase the efficiency of lateral stability and lateral controllability of the aircraft at large angles of attack, improve its take-off and landing performance at low flight speeds.

The problem is solved in that the device for turning the thrust vector of a turbojet bypass engine, which includes the central body of the gas generator of the internal circuit and the nacelle of the external circuit fan with an annular outlet, contains in the rear of the nacelle around the periphery of the window and reversible and deflecting shutters placed in the windows shovel type. Reversible flaps are fixed at the rear of each engine nacelle window on the transverse axes. Each deflecting leaf is pivotally connected on its transverse axis with its reversible leaf. In addition, the reversing and deflecting flaps are pivotally connected to controls for their movement.

New in the invention is that each reversible leaf is provided with a window in which a hollow deflecting leaf is installed. The deflecting leaf consists of the outer and inner walls with a channel between them. The outer surface of the outer wall of the deflecting sash in direct traction mode forms part of the outer surface of the nacelle. Along the longitudinal edges of the windows of the nacelle between the nacelle and the central body of the gas generator, the path of the outer circuit of the engine is divided by radial pylons of the aerodynamic profile, which are in contact with reversing and deflecting wings. Means of controlling the movement of reversing and deflecting flaps are made in the form of separate translational drives. Each reversible leaf is pivotally connected with the trailing edge to the engine nacelle behind its window through a drive located in the latter, and is equipped with a cowl in the form of a hollow triangular ring sector outside the front part. The outer edge of the sector in the direct thrust and deflected thrust vector modes forms part of the outer surface of the nacelle, and the other two, respectively, the inner front and rear inclined surfaces of the fairing. In this case, the deflecting sash is placed in the reversing sash behind the cowl and is pivotally connected to the drive located in the cowl. In direct traction mode, the inner surface of the reversing leaf and the inner surface of the inner wall of the deflecting leaf form parts of the inner surface of the engine nacelle of the outer contour of the engine.

The implementation of each reversible and deflecting valves in the form of a scoop type provides a reduction in the spreading of jets when the air flow out of the device.

Providing the reversing sash with a window in which the hollow deflecting sash is installed, allows the use of the engine nacelle window not only for the reversal function, but also for performing the OBT function. This allows, without changing the dimensions of the switchgear, with a slight increase in mass, to obtain a new function of the device.

The implementation of the deflecting sash from the outer and inner walls with a channel between them provides stable flow characteristics of the channel at different positions of the sash.

The separation of the path by the radial pylons of the aerodynamic profile along the longitudinal edges of the windows of the engine nacelle of the outer contour of the engine between the engine nacelle and the central body of the gas generator in contact with reversing and deflecting wings, provides flow separation through the engine nacelle windows in predetermined sectors.

The implementation of the means for controlling the movement of the reversing and deflecting sashes in the form of separate translational motion drives makes it possible to provide control of the switchgear and the reactive current circuit according to a given program.

The connection of each reversible leaf articulated by the trailing edge with the engine nacelle behind its window through a drive located in the latter provides a reduction in aerodynamic losses in the channels of the leaves and the windows of the engine nacelle.

The supply of the reversing shutter outside the front part with a fairing in the form of a hollow trihedral annular sector allows to reduce losses due to the flow of air around the shutters in all modes.

The implementation of the outer edge of the fairing sector in the form of a part of the annular outer surface of the nacelle ensures continuity of the outer surface of the latter.

The implementation of the two other faces of the sector, respectively, the inner front and rear inclined surfaces of the fairing provides clearance-free pairing of the reverse sash with the nacelle and the deflecting sash.

Placing the deflecting leaf in the reversing leaf behind the cowling and its connection with a separate drive located in the cowling allows expanding the control functions of the OBT.

The formation of the inner surface of the reversible sash and the inner surface of the inner wall of the deflecting sash part of the annular inner surface of the nacelle ensures the continuity of the inner surface of the latter in the outer loop in direct draft mode.

The essential features of the invention may have the development and refinement.

The channel deflecting sash can be made with an oblique cut at the entrance. Moreover, the trailing edges of the outer and inner walls should be located in one output cross section of the channel, and the length of the outer wall should be less than the length of the inner wall. This ensures the free movement of the deflecting flap in the reverse and the docking deflecting flap with the back of the annular inclined surface of the fairing in separate modes.

The surface of the trailing edge of the window of the reversing sash can be profiled from two mating parts of the surfaces of the coaxial torus sectors. This reduces flow losses at the trailing edge of the reversing sash window in all modes.

Thus, the task of the invention to create a modern reactor plant with the addition of OVT functions to it has been solved. This technical solution increases the efficiency of lateral stability and lateral controllability of the aircraft at large angles of attack and low flight speeds, improves its takeoff and landing characteristics with a slight increase in the mass of the reversing device.

The present invention is illustrated by the following detailed description of the design and operation of the device with reference to figures 1-6, where:

figure 1 schematically shows a longitudinal section of a device for rotating the thrust vector of the outer contour of a turbojet bypass engine in direct thrust mode;

figure 2 is a section aa in figure 1;

figure 3 - schematically shows a longitudinal section of a device for rotating the thrust vector of the flow of the outer contour of a turbojet bypass engine in thrust reversal mode;

figure 4 - schematically shows a longitudinal section of the device of rotation of the thrust vector deflecting at an angle to the axis of the engine the flow of the external circuit of a turbojet bypass engine in full OVT mode;

figure 5 is a section bB in figure 4;

6 is a schematic longitudinal sectional view of a thrust vector rotation device of a turbojet bypass engine deflecting a part of the air flow of the external circuit in partial OBH mode and simultaneously directing another part of the external circuit flow through the nozzle to provide a direct thrust mode.

The device for turning the thrust vector of a turbojet bypass engine, including (see FIGS. 1, 2) a cylindrical engine nacelle 1 of an external circuit fan 2 and a central body 3 of an internal circuit gas generator, according to the invention, comprises an annular nozzle at the rear of the engine nacelle 1 along the periphery of window 4 and at the outlet 5. In the windows 4 are placed reversible 6 and deflecting 7 wings, having the shape of a soviet type. Reversible 6 flaps are fixed in the rear part of each window 4 on the transverse axes 8, fixed in the engine nacelle 1. Each deflecting flap 7 is pivotally connected 9 on the transverse axis 10 with its reversible 6 flap. In addition, the reversible 6 and deflecting 7 wings are pivotally connected to the means of controlling their movement. Each reversible 6 leaf (see FIG. 2) is provided with a window 11 in which a hollow deflecting leaf 7 is installed. The deflecting wing 7 (see Figs. 1, 6) consists of an outer 12 and an inner 13 walls with a channel 14 between them, in which partitions 15 are installed to prevent lateral spreading of the flow on cylindrical surfaces. The outer surface of the outer wall 12 of the deflecting sash 7 in direct traction mode (see Fig. 1) forms part of the outer surface of the nacelle 1. Between the nacelle 1 and the central body 3 of the gas generator are installed (see Fig. 2, 5) pylons 16 of aerodynamic profile, forming separate channels 17 of the outer circuit 2 of the engine, along which the lateral edges of the leaves 6 are sealed in the mode of reversing the thrust or the edges of the wings 7 when the thrust vector is deflected, and flow spreading and its effect on the operation of adjacent channels 17 are excluded. The movement of the reversible 6 and deflecting 7 shutters is made (see Figs. 1, 6) in the form of separate translational actuators 18 and 19, respectively. In addition, each reversible 6 shutter is hinged 20 by the trailing edge 21 to the nacelle 1 outside its window 4 through the drive 18, and is also equipped in front of the fairing 22 in the form of a hollow trihedral annular sector. In the direct thrust and deflected thrust vector modes (see FIGS. 1, 4), the outer face 23 of the cowl 22 is part of the outer 24 surface of the nacelle 1, and the other two faces 25 and 26 are respectively the inner front and rear inclined surfaces of the cowl 22 of the reversing wing 6. The deflecting leaf 7 is placed in the window 11 of the reversible 6 leaf behind the cowling 22 and is pivotally connected to the separate drive 19 located in the cowling 22. In the direct thrust mode, the inner surface of the reversing shutter 6 and the inner surface of the inner Enki deflecting flaps 7 form part of the inner surface of the outer contour of the nacelle 1 of the engine 2. The channel 14 of the deflecting sash 7 is made with an oblique cut 28 at the inlet for docking with the surface 26 of the fairing 22. The surface of the trailing edge 29 (see Figs. 4, 6) of the window 11 of the reversible 6 sash is made of two interfaced surfaces 30 of the outer and 31 internal coaxial torus sectors. The front inclined surface 25 of the fairing 22 of the leaf 6 (see FIG. 3) is sealed along the inclined surface 32 of the front edge of the window 4, and the rear inclined surface 26 of the fairing 22 is sealed by the front edge 28 of the channel 14 of the deflecting leaf 7. In the OBT mode (see FIG. 4, 5) in the place of contact of the leading edge 33 of the inner wall 13 of the deflecting leaf 7 with the central body 3 of the gas generator of the internal circuit, slots 34 can be provided through which part of the air of the circuit 2 flows out through the nozzle 5. Air leaks can be eliminated by profiling of the front edge 33 of the deflecting flap 7 along the contour of the outer surface of the central body 3.

The device for turning the thrust vector of a turbojet bypass engine does not prevent the passage of air through the channel of the outer circuit 2 in direct thrust mode and works as follows.

When the device is operating in direct traction mode (see Figs. 1, 2), each actuator 18 is retracted and, through a hinge 20 on the trailing edge 21, installs in the window 4 the engine nacelles 1 on the transverse axis 8, a reversing shutter 6 with a stop and a seal on the front oblique surface 25 of the cowl 22 along the inclined surface 32 of the leading edge of the window 4. Each actuator 19 is also retracted, the deflecting wing 7 is placed on the axis 10 with hinges 9 in the window 11 of the reversing wing 6 with emphasis and sealing with the front oblique edge 28 along the rear inclined surface 26 of the cowl 22. Moving alongaruzhnomu circuit 2, the air nozzle 5 through the engine outwardly expires.

When the device is operating in the reverse direction of the thrust vector (see Fig. 3), after giving the command according to the given program, the actuators 18 rotate the reversing flaps 6 in each separate window 4 until their trailing edges 21 stop in the central body 3 of the internal circuit gas generator. Between the inner surface of the forward inclined reversing leaf 6 and the inclined surface 32 of the front edge of the individual window 4 in the plane of the longitudinal axis of the nacelle 1, a channel for air passage is formed.

When the device is operating in full OVT mode (see FIGS. 4, 5), the actuators 19 release each leaf 7 according to a given command until the leading edge 33 of the inner wall 13 stops in the central body 3 of the internal circuit gas generator. A channel 14 is opened in the deflecting flap 7. Between the outer surface of the outer wall 12 of the deflecting flap 7 and the inclined surface 26 of the fairing 22, an additional channel for the passage of air is formed.

When the device is operating in partial OBT mode (see Fig. 6), at the command of each drive 19 is partially released. The shutters 7, moved by the actuators 19, partially overlap the gas path of the external circuit 2 to the nozzle 5. In the deflecting shutter 7 open the channel 14 and direct its exit outward at an acute angle to the axis of the engine. Between the outer surface of the outer wall 12 of each reversible leaf 6 and the inclined surface 26 of the fairing 22 of the window 4 form an additional channel for the passage of air.

Experimental checks of the proposed technical solution have confirmed the efficiency of the thrust vector rotation device in the nacelle of the external circuit of a turbojet dual-circuit engine to increase lateral stability, vertical and lateral controllability of the aircraft at large angles of attack and low flight speeds, reduce losses in forward and rotated air flows, as well as high the capacity of the external circuit path of the engine in reverse and OBT modes.

Claims (3)

1. The device for turning the thrust vector of a turbojet bypass engine, including the central body of the gas generator of the internal circuit and the engine nacelle of the external circuit fan with an annular nozzle at the outlet, containing in the rear of the engine nacelle around the window periphery and reversible and deflecting shutters located in the windows, having the shape of a soviet type, where reversible flaps are fixed in the rear part of each engine nacelle window on the transverse axes, and each deflecting flap is pivotally connected on its transverse axis with its reversible the sash, in addition, the reversing and deflecting sashes are pivotally connected to the means of controlling their movement, characterized in that each reversing sash is equipped with a window in which a hollow deflecting sash is installed, consisting of the outer and inner walls with a channel between them, where the outer surface of the outer the deflecting wing wall in direct traction forms part of the outer surface of the engine nacelle, and along the longitudinal edges of the engine nacelle windows between the engine nacelle and the central body of the gas generator, the external path of the engine contour is divided by radial pylons in contact with the reversing and deflecting flaps, the means for controlling the movement of the reversing and deflecting flaps are made in the form of separate translational motion drives, in addition, each reversing flap is pivotally connected to the engine nacelle behind its window through a drive located in the last , and is equipped externally in front of the fairing in the form of a hollow trihedral annular sector, and the outer face of the sector in direct traction and deflection modes the thrust vector forms part of the outer surface of the engine nacelle, and the other two faces, respectively, the front and rear inclined surfaces of the cowl, respectively, while the deflecting wing is placed in the reversing wing behind the cowl and pivotally connected to the drive located in the cowl, and, in direct traction, the inner the surface of the reversible leaf and the inner surface of the inner wall of the deflecting leaf form parts of the inner surface of the nacelle of the outer contour of the engine. 2. The thrust vector rotation device according to claim 1, characterized in that the deflecting leaf channel is oblique at the inlet, the trailing edges of the outer and inner walls being located in one output cross section of the channel, and the length of the outer wall is less than the length of the inner wall. 3. The thrust vector rotation device according to claim 1, characterized in that the surface of the trailing edge of the reversing sash window is profiled from two conjugated parts of the surfaces of the coaxial torus sectors.

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