Reheat ring for double-flow turbojet engine, reheat device and turbojet engine

FIELD: turbojet engines.

SUBSTANCE: proposed reheat ring for double-flow turbojet engine, in which temperature of flow of exhaust gases in primary circuit exceeds temperature of air flow in second circuit, has turnable axis of symmetry coinciding with axis of rotation of turbojet engine and it is provided with front ring case from one side forming ring channel axially open to side of output, and at other side, ramp of fuel nozzles arranged in ring channel. It is formed by great number of interconnected sectors of ring. Each sector has sector of front ring case being equipped with fuel intake connected with ramp of fuel nozzles. Front surface of front ring case is made for contact with primary flow. Each sector of ring has connecting device arranged in ring channel at input of fuel nozzle ramp for mounting fuel intake at one side, and ventilation chamber at other side, made in ring channel on at least part of length of sector of front ring case and at input of fuel nozzle ramp. Each sector of front ring case is provided with intake of secondary air getting out of ventilation chamber 2 for cooling fuel nozzle ramp. Sector of rear ring case is provided on output of fuel nozzle ramp to protect ramp.

EFFECT: reduced heat stresses, increased efficiency at augmented conditions.

10 cl, 12 dwg

 

The present invention relates to the field of turbojet engines and, in particular, afterburning devices.

Turbofan engines produce a flow of exhaust gases, called the primary circuit, a temperature which exceeds the temperature of the air flow, called secondary circuit. It is known that turbofan engines contain afterburner device. This device has an outer annular housing and the annular exhaust housing located within the outer annular casing at some distance from it and containing the inner and outer annular walls, the rotary axis of symmetry of which coincides with the axis of rotation of the turbojet engine. The outer wall and the outer annular housing define a channel of the secondary circuit, the outer annular wall and an inner annular wall define a channel primary path. For the area of the first combustion, emitting a stream of exhaust gases (primary loop), passing through the turbine of the low and high pressure turbojet engine contains a device that uses the injection of fuel in the primary circuit and the secondary circuit for reuse. Known afterburning device containing an annular burner located in the secondary circuit, and a rack to hold the project for a flame, located in the primary circuit, the gases which are mixed with a part of the gases of the secondary circuit. Also known afterburning device containing an annular burner located in the primary circuit. With this arrangement causes severe thermal stress.

Closest to the present invention is an afterburning device according to patent FR 2696502 containing the outer body, which includes the outlet casing. In the exhaust housing has an external and an internal annular wall and the outer annular wall is removed from the outer casing and forming with it the main channel of the secondary circuit and cross ties connecting the outer and inner walls. The device also contains an annular afterburning wall, placed inside the outer casing, separated from the latter by a given distance to form a space for cooling air and limiting the afterburning chamber. Each cross connection includes a channel provided in the upper part of the hole that communicates with the main channel, and containing unlocking the device, crossing the descending wall of the cross member and in communication with the afterburner chamber.

The present invention is to improve known afterburning device.

The problem is solved in that the proposed Forsan the ring for a bypass turbojet engine, in which the temperature of the stream of exhaust gases, called the primary circuit is higher than the temperature of the air flow, called secondary circuit, and the ring has a rotary axis of symmetry coinciding with the axis of rotation of the turbojet engine, contains, on the one hand, the front annular casing forming an annular channel open in the axial direction of the output side, and, on the other hand, the ramp fuel injector located in the annular channel, and is formed by multiple interconnected ring sectors, each of which contains a sector of the front annular casing, each of which has a fuel inlet connected to the ramp fuel injector, characterized in that the front surface of the front annular casing made with the possibility of contact with the primary flow, each ring sector contains connecting means located in the annular channel at the entrance ramp to the fuel injectors to install, on the one hand, the fuel inlet and, on the other hand, the Plenum is made in the annular channel, at least part of the length of the sector of the front annular casing and on the entrance ramp to the fuel injectors, each sector of the front annular casing equipped with a secondary inlet of the air leaving the ventilation camarilla cooling ramp fuel injector, and on the exit ramp of the fuel injectors includes a sector of the rear annular casing to protect this ramp.

Preferably, in the afterburner ring sector of the rear annular casing formed an annular channel open in the axial direction towards the exit, and was connected by means of fixing means with the sector of the front annular casing.

Preferably, in the afterburner ring sector of the rear annular casing contained the means of restraint, located in the axial direction at the entrance, to keep in place the ramp fuel injectors, Plenum on the inner wall sector of the front annular casing for connection sector of the rear annular casing with an inner wall sector of the front annular casing.

It is preferable that the connecting means contained cavity, forming a socket for the fuel inlet and the inlet of secondary air.

Preferably also, to the Plenum contains two hollow pipe with many holes, and the connecting means contained two holes opposite each other around the circumference on both sides of the cavity, forming the inlet and the first and second tubes held its open end in one of the two openings, and an open end communicating with the cavity, forming Vozduha the nick.

It is advisable that the ring sectors joined together by means of side mounting attachments, contains an item with grooves into which enter the ends of the sectors of the rear annular casing.

It is advisable that the curvature of the front surface of the connecting means corresponds to the curvature of the rear surface of the front cover.

The problem is solved also by the fact that in the afterburning device for a turbojet engine in which the temperature of the stream of exhaust gases, called the primary circuit is higher than the temperature of the air flow, called secondary circuit containing the outer annular casing and outlet annular body is placed inside the outer annular casing at some distance from it and containing the inner and outer annular walls, the rotary axis of symmetry of which coincides with the axis of rotation of the turbojet engine, while the outer wall and the outer annular body forming the channel of the secondary circuit, the outer annular wall and an inner annular wall forming the channel of the primary circuit, and the device additionally contains afterburner hours, according to the invention the outer wall contains openings, and the device contains afterburner ring with the above symptoms, mounted on the outside Koltsevaya thus, to the front surface of the front annular casing was in contact with the primary flow and the secondary air inlet of each sector of the front annular casing coincided with the holes in the outer wall.

It is advisable that the front annular casing rested in the back afterburner racks, and sectors of the front annular casing connected between themselves and with the backs afterburner racks by means of fixing means installed on the mounting nozzle containing an item with grooves into which enter the ends of the sectors of the rear annular casing.

The problem is solved also by the fact that the proposed turbine engine containing the above-mentioned afterburner device.

The accompanying figures illustrate embodiments of the present invention, which are not restrictive.

Figure 1 depicts the turbofan engine in the context.

Figure 2 - part of the turbofan engine shown in figure 1, in the section.

Figure 3 - sector ring burner in the first phase of the Assembly in accordance with the present invention.

Figure 4 - sector ring burner in the second phase of the Assembly in accordance with the present invention.

Figure 5 - section a-a sector of a ring burner, shown in Fig.7.

6 is a sector of a ring burner provided on the anzah mounting nozzle.

7 - on the exit side of the sector ring burner provided at the ends of the mounting nozzle.

Fig - General scheme afterburning device, in this case not containing ring of the burner in accordance with the present invention.

Fig.9 - the front part of the connecting nozzle.

Figure 10 - rear part of the connecting nozzle.

11 - the rear part of the connecting nozzle, which is connected with a Plenum.

Fig - rear part of the connecting nozzle.

Drawings mainly contain certain key elements. In this regard, they can not only help to better understand the description, but also, if necessary, to Supplement the definition of the present invention.

Figure 1 schematically shows a turbofan engine.

First, air is sucked in the intake fan 1, then goes to the low-pressure compressor 12. One part of the compressed air is directed into the high-pressure compressor 14, and the other part - in part 18 turbojet engine. After the combustion chamber 16 and the exhaust gases are directed into a high-pressure turbine, and then in a low-pressure turbine 17 before you get into the outlet casing 23. These waste gases with high temperatures match the primary stream. The flow of cold air part 18 turbojet engine heat is raised from contact with the channel 15 hot air. The heated air flow, called secondary flow.

Further with reference to figv provides a detailed description of the afterburner device 19. Afterburner device 19 includes an outer annular body 25 and the exhaust ring inside the outer ring of the housing and at some distance from him. Both buildings have the same rotary axis of symmetry corresponding to the axis of rotation of the turbojet engine. Prom annular housing has an internal 29 27 and the outer annular wall, the rotary axis of symmetry of which coincides with the axis of rotation of the turbojet engine, and the outer wall 27 and an outer annular housing 25 to form a channel 32 for the secondary stream after its passage through the portion 18 of the turbojet engine, the outer annular wall 27 and the inner annular wall 29 to form a channel 34 for the primary stream after its passage through the turbine 17. The opening 30 in the outer annular wall 27 provides the passage for mixing the secondary flow primary flow in the channel 34. The engine inlet fuel channel 34 provides the ignition of the mixture of the primary flow secondary flow/fuel, and the flame is fixed on the uprights 22 hold the flame. As shown in figure 2, a rack fixed on the outer casing and directed toward the outlet at an angle with respect to PL is skoti, perpendicular to the axis of rotation. In addition, in the secondary circuit is a ring burner 21, consisting of ring sectors located between racks hold of the flame. The front annular casing of this ring protects the burner from the afterburner flame and high temperature (900° (C) primary flow ramp fuel injectors, fuel injection in the direction of exit to ensure afterburning.

To improve the efficiency of the forced mode ring burner placed in the primary circuit. This arrangement produces a very high thermal stress at the level of the annular burner. Therefore, in accordance with the present invention it is carried out in such a way as to reduce thermal stress and to increase the efficiency of the forced mode.

On Fig schematically shown in the cross section afterburning device in accordance with the present invention. This device comprises an annular burner, containing, on the one hand, the front annular casing forming an annular channel open in the axial direction of the output side, and, on the other hand, the ramp fuel injector 4, located in the annular channel with the annular burner is formed by multiple interconnected ring sectors 20, each of which contains a sector 1 front annular casing, with each sector 1 peredne the annular casing is equipped with a fuel inlet 35, communicating with ramp fuel injector 4. The front annular casing may, for example, be a ring dihedral angle, rounded apex which is directed to the entrance, while the inner plate dihedral angle parallel to the axis of rotation, and the outer plate is directed radially outward. As shown in Fig, the outer annular wall 27 in the plane perpendicular to the axis of rotation, includes holes 36 spaced from each other at equal intervals around the entire circumference of the outer annular wall 27. Holes 36 are limited towards the output part 28 of the pipe, this part 28 of the pipe with open ends is made by moulding in a single part, for example, with the inner annular wall 27. Part 28 of the tube is in the direction of exit at an angle relative to the plane perpendicular to the axis of rotation. Each sector of the front annular shroud ring burner, in particular, each outer plate of each sector contains a hole, a limited portion 37 of the pipe, made in the direction of the entrance at an angle relative to the plane perpendicular to the axis of rotation. The opening sector of the front annular casing combined with one of the holes of the outer annular wall 27 and is fixed.

The opening sector of the front annular casing acts as a secondary air inlet the inlet of the fuel in the annular channel, educated sector of the front annular casing. In another embodiment, holes can be performed in such a way as to separate the inlet air from the inlet fuel. The inlet of the fuel, in particular, through the pipe 35, passing through matching holes in the outer ring wall and the sector of the front annular casing. The pipe 35 with its end connected with the connecting head connected to a ramp fuel injector located in the annular channel, a limited sector of the front annular casing. Ramp 4 fuel injectors placed at least on the part of sector 1 front annular casing and made in the form of a pipe with holes on the output side. In order to avoid excessive thermal stresses in high temperature conditions arising from the provisions of the annular burner in the primary circuit, it is necessary to provide ventilation and cooling of each sector of the ring burner. For improved ventilation of the front annular casing and ramp the fuel injectors on the entrance ramp to the fuel injectors set the ventilation chamber 2, which is fed from the air inlet. Figure 3 shows the option to install the Plenum to install a ramp to the fuel nozzles in the annular channel, shown in figure 4. Each vent pipe camera contains a local thickening, called aimie base, to ensure the availability of the annulus between the sector of the front annular casing and Plenum.

Each sector of the ring burner contains a connecting nozzle 3 located in the annular channel at the entrance ramp to the fuel injectors and designed for installation on the one hand, the fuel inlet tube and air inlet and, on the other hand, for installation of the ventilation chamber in the annular channel, at least part of the length of the sector of the front annular casing and on the entrance ramp to the fuel injectors. This connection nozzle shown in detail in figures 9, 10, 11 and 12.

Connecting the nozzle 3 has a shape corresponding to the annular channel formed front annular casing, to allow its installation on the entrance ramp to the fuel injectors. This nozzle includes a main cavity filled with possibility of installation in front of the hole sector of the front ring sector and with the possibility of installing a connection head of the inlet fuel and air intake. The main cavity communicates with the rear opening 45 to allow connection connection head with ramp fuel injector located perpendicularly to the direction of the coupling heads. To avoid turning the coupling heads in the cavity, the message is considered with a rear opening, connecting the nozzle includes a protrusion 48 made in the axial direction and protruding radially outward beyond the rear holes. In addition, the connecting attachment 3 contains a side hole that is opposite the holes drilled around the circumference of the ring on both sides of the main cavity of the air intake. In a preferred embodiment of the ventilation chamber contains two hollow pipe with many holes made with the possibility to retain them open ends in one of the side holes, with their free end communicates with the main cavity. The air entering through the opening sector of the front annular casing, passes into the main cavity, forming the inlet and is directed in the lateral direction and in the circumferential direction in the hollow pipe of the Plenum through their ends mounted in the side holes of the connecting nozzle.

For protection ramp fuel injector and the Plenum from the back of the flame and radiation in the annular channel, a limited sector of the front annular casing, on the exit ramp set sector 5 rear annular casing having in axial section in generally semi-circular shape, wherein the ends of this cross-section is formed, respectively, with the ends of the sector plates front annular casing is analy for fuel, coming from the ramp to the fuel injectors. The sector 5 of the rear annular casing forms sent to the output side of the heat shield ring burner.

Sector the rear annular casing forms an annular channel open in the axial direction of the output side, and is connected by means of fixing means with the sector of the front annular casing. As the fastening means can be used rivets. As shown in figure 5, sector 5 rear annular casing contains means of restraint installed in the axial direction at the entrance of this sector and designed to hold in place the ramp fuel injectors that hold the Plenum to the inner wall sector of the front annular casing and to point connection sector of the rear annular casing with the rear surface of the sector of the front annular casing. These funds hold performed, for example, in the form of pads 54 (for example, on the two tabs on the sector) minor ring width, made by molding as a single part with the sector the rear annular casing at the inlet of the latter. The foot 54 is shown in section in figure 5. Foot 54 has an internal ledge 55, made in the axial direction at the inlet sector of the rear annular casing so that after the correct installation of the sector the rear ring kozuchow annular channel, educated sector of the front annular casing, this inner protrusion 55 has pressed one of the pipes of the Plenum to the bottom of this annular channel. The outer ledge 56 of the tabs 54 restricts together with the inner protrusion 55 a concave cavity for installation of ramp fuel injectors and to hold the latter at a certain distance from the front surface of the sector 5 of the rear annular casing. Thus, the sector 5 of the rear annular casing plays the role of a heat shield. On their inner and outer radial ends of the leg 54 also contains a cavity that is installed in front of the holes made in the sector of the front annular casing with the possibility of mounting bosses 6 passing through holes, with emphasis in the cavity. These lugs 6 are welded for mounting between the front and rear sectors of the annular casing. It is possible to provide other means of securing the front and rear sectors of a circular casing with the possibility of removing the heat shield for the maintenance of the ring burner.

Figure 6 and 7 shows a sector of a ring burner, containing at its lateral ends of the mounting nozzle for the connection of this sector to another sector each end. Thus, the ring sectors are connected to each other by means of side mounting attachments containing detail the , having at the ends opposite the ends of the ring sectors, the grooves into which enter the ends of the sectors of the rear annular casing. In addition, these side mounting nozzles are used for attaching ring sectors to the afterburner poles with pin 8 and pins 9.

The presence of these lateral mounting of nozzles provides free expansion of the ring sectors, as the ends of the latter are not rigidly fixed. However, the rivet 10 is able to hold the entire Assembly in a stationary position.

The present invention is not limited to the above-described variants of execution of the fixing device are provided solely as examples, and may include all options that may be developed by a specialist in the framework of the following claims.

1. Afterburner ring for bypass turbofan engine in which the temperature of the stream of exhaust gases, called the primary circuit is higher than the temperature of the air flow, called secondary circuit, while the ring (21) has a rotary axis of symmetry coinciding with the axis of rotation of the turbojet engine, contains on one side of the front annular casing forming an annular channel open in the axial direction of the output side, and on the other side of the ramp (4) fuel injectors located in the ring of the channel, and formed by multiple interconnected sectors (20) rings, each of which contains a sector (1) front annular casing, each equipped with a fuel inlet (35), connected to the ramp (4) fuel injector, characterized in that the front surface of the front annular casing made with the possibility of contact with the primary flow, and each sector (20) ring contains the connecting means (3)located in the annular channel at the entrance ramp (4) fuel injectors, for installation from one side of the fuel inlet (35) and on the other side of the Plenum (2)made in the annular channel, at least part of the length of the sector of the front annular casing and on the entrance ramp (4) fuel injectors, each sector (1) front annular casing equipped with a secondary air inlet opening of the Plenum (2) for cooling ramp (4) fuel injectors, and on the exit ramp (4) fuel injectors provided for the sector (5) rear annular casing to protect this ramp.

2. Afterburner ring according to claim 1, characterized in that sector (5) rear annular casing forms an annular channel open in the axial direction of the output side, and is connected by means of fixing means with the sector (1) front annular casing.

3. Afterburner ring in one of the previous the point characterized in that sector (5) rear annular casing includes means for retaining located in the axial direction at the entrance, to keep in place the ramp (4) fuel injectors, Plenum (2) on the inner wall of the sector (1) front annular casing for connection sector (5) rear annular casing with an inner wall of the sector (1) front annular casing.

4. Afterburner ring according to one of claims 1 or 2, characterized in that the connecting means (3) contains a cavity, forming a socket for the fuel inlet (35) and the inlet of secondary air.

5. Afterburner ring according to one of claims 1 or 2, characterized in that the air chamber (2) contains two hollow pipe with many holes, while the connecting means (3) comprises two holes opposite each other around the circumference on both sides of the cavity, forming the inlet, the first and second tubes are supported by its open end in one of two holes and the open end communicates with the cavity, forming the air vent.

6. Afterburner ring according to one of claims 1 or 2, characterized in that the sectors (20) rings are interconnected by means of side mounting attachments, contains an item with grooves into which enter the ends of the sectors (5) rear annular casing.

7. Afterburner ring onomous claims 1 or 2, characterized in that the curvature of the front surface of the connecting means (3) corresponds to the curvature of the rear surface of the front cover.

8. Afterburner device for a turbojet engine in which the temperature of the stream of exhaust gases, called the primary circuit is higher than the temperature of the air flow, called secondary circuit containing an outer circular casing (25) and outlet annular casing is placed inside the outer ring of the housing (25) at some distance from it and containing internal (29) and outer (27) of the annular wall, the rotary axis of symmetry of which coincides with the axis of rotation of the turbojet engine, while the outer wall and the outer annular body forming the channel of the secondary circuit, the outer annular wall (27) and the inner annular wall (29) form a channel of the primary circuit, and the device further comprises afterburner rack (22), characterized in that the outer wall (27) contains holes, and the device contains afterburner ring (21) in one of the preceding paragraphs, mounted on the outer annular wall (27) so that the front surface of the front annular casing was in contact with the primary flow and the secondary air inlet of each sector (1) front annular casing of the coin is al with the holes in the outer wall (27).

9. Afterburner device according to claim 9, characterized in that the front annular casing against the back of afterburning racks (22), sectors (1) front annular casing connected with each other and with backs afterburner racks (22) by means of fixing means installed on the mounting nozzle containing an item with grooves into which enter the ends of the sectors (5) rear annular casing.

10. Turbojet engine, containing afterburning device according to one of p and 9.



 

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EFFECT: provision of reliable lighting up in afterburner, improved recirculation of fuel in flow.

13 cl, 8 dwg

FIELD: mechanical engineering; turbojet engines.

SUBSTANCE: mixer of afterburner of turbojet engine relaters to members of afterburners making it possible to increase margin of vibratory combustion. Mixer 4 distributes air of outer loop and behind-the-turbine gas which pass through pockets 6 with lobes 5 and mix on section between end face edges 7 of mixer 4 and flame stabilizers 3. Fuel is delivered to gas through manifolds 2. Fuel-air mixture burn out behind flame stabilizers 3. Each portion of fuel from manifold 2 gets into air flow, each element of which has its momentum and direction. Thanks to it each portion of fuel from manifolds 2 has its own time for preparation to combustion and its own burnout time, so afterburner of double-flow turbojet engine has low tendency to vibratory combustion.

EFFECT: increased margin of vibratory combustion.

Turbojet engine // 2277181

FIELD: aircraft industry.

SUBSTANCE: proposed turbojet engine contains gas generator, nozzle and afterburner with housings forming housing of engine. Afterburner is installed over perimeter of nozzle, being made in form of circular chamber with gas-dynamic resonators connected with chamber and rear wall installed with clearance relative to resonators and connected with nozzle and provided with holes coaxial with gas dynamic resonators. Each gas-dynamic resonator is made in form of shaped member, mainly bowl-shaped, with concave surface pointed to holes in rear wall, and circular nozzle formed by edges of shaped member and hole in rear wall coaxial with circular nozzle. Ejector heads are secured in places of holes on rear wall of afterburner.

EFFECT: increased specific thrust and economy of engine without increasing overall dimensions and weight of engine at constant consumption.

6 cl, 5 dwg

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed afterburner of gas-turbine engine contains prechamber and ring-type flame stabilizer installed in housing. Stabilizer is arranged coaxially relative to vibration absorber made in form perforated fairing. Fairing has two perforated sections. One section is located at outlet of fairing at a distance not exceeding 40% of length of fairing along its axis. Second section is provided with sleeveless perforation in beginning before flame stabilizer and is located at a distance from end of fairing not exceeding 50-59.9% of its length along axis. Fairing can be provided additionally with rim. Holes can be made in fairing and rim connected to fairing forming section with sleeveless perforation.

EFFECT: optimization of operation of afterburner owing to provision of frequency characteristics of oscillation process in inner spaces of afterburner and fairing and thus damping excess pressure fluctuations and velocity of gas.

4 cl, 3 dwg

FIELD: turbojet engines.

SUBSTANCE: proposed reheat ring for double-flow turbojet engine, in which temperature of flow of exhaust gases in primary circuit exceeds temperature of air flow in second circuit, has turnable axis of symmetry coinciding with axis of rotation of turbojet engine and it is provided with front ring case from one side forming ring channel axially open to side of output, and at other side, ramp of fuel nozzles arranged in ring channel. It is formed by great number of interconnected sectors of ring. Each sector has sector of front ring case being equipped with fuel intake connected with ramp of fuel nozzles. Front surface of front ring case is made for contact with primary flow. Each sector of ring has connecting device arranged in ring channel at input of fuel nozzle ramp for mounting fuel intake at one side, and ventilation chamber at other side, made in ring channel on at least part of length of sector of front ring case and at input of fuel nozzle ramp. Each sector of front ring case is provided with intake of secondary air getting out of ventilation chamber 2 for cooling fuel nozzle ramp. Sector of rear ring case is provided on output of fuel nozzle ramp to protect ramp.

EFFECT: reduced heat stresses, increased efficiency at augmented conditions.

10 cl, 12 dwg

FIELD: mechanical engineering; turbojet engines.

SUBSTANCE: reheat unit of turbojet engine contains prechamber and central body arranged one after another indirection of flow. Prechamber is furnished with V-shaped flame stabilizer which burners are arranged, and stabilizer proper is made up of two ring segments arranged at a distance not less than maximum thickness of cross section of central body. Said central body contains fixed housing with flat surfaces from both sides and flat deflecting panels in contact with flat surfaces, thickened inlet part rounded off in cross section and wedge-like outlet part. Wedge-like outlet part and contacting flat surfaces of housing and deflecting panels are coated with radio absorbing material. Flat panels and their hinge joints connecting them with central body housing are made hollow, and they are driven from both sides through hollow springs. Fixed hollow cylindrical rod is arranged inside hollow of each panel. Outer surface of said rod is slide-fitted with inner surfaces of hollow hinge joint. Ends of each hollow cylindrical rod pass inside hollow springs, pylons and are connected with cooling air supply pipelines through side holes in reheat unit wall. Hinge joints and cylindrical rods are provided with two rows of through holes arranged at angle relative to each other so that in nondeflected initial position of panels, holes in rods and hinge joints register in front rows in direction of flow and do not coincide in rear rows, and vise versa, in deflected positions of panels, holes coincide in rear rows and do not coincide in front rows. Inner space of each flat panel is connected at one side through holes with inner space of reheat unit, and at other side, with panels deflected, is connected through registered holes in rod and hinge joint, with inner space of cylindrical rod. Thin-walled streamlined screen is made lengthwise outer surface of hinge joint of each panel. Said screen forms inner space between screen and outer surface of hinge joint. Said space is connected inner space of cylindrical rod through registered holes of front rows of rod and hinge joint when panels are in not deflected initial position, and opposite edges of each flat panel in direction from hinge joint is made in form of ellipse, and at deflection of panels, projection of both panels onto plane of cross section reheat unit is screen in form of circle.

EFFECT: improved reliability of reheat unit, reduced level of infra-red radiation in rear semi-sphere of engine.

8 dwg

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