Duct burning bypass engine with protective screen for nozzle ring fuel manifold, nozzle ring and protective screen

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises primary channel, duct-burning channel and secondary channel extending, at least partially, into primary flow up to duct-burning channel. The latter comprises nozzle ring incorporating flame stabiliser flute that represents a circular section. Part of the latter section is located upstream in secondary flow and incorporates fuel collector and collector protective tubular screen. Said flute comprises upstream recess communicated with secondary flow. Said screen comprises at least one vent hole, made in its upstream section and between screen and collector.

EFFECT: higher efficiency of cooling.

8 cl, 6 dwg

 

The invention relates to a turbojet engine, comprising a channel afterburning primary gas flow, the ring nozzle and shield the fuel manifold ring injectors. The invention also relates to a ring of nozzles and protective screen for turbojet engine.

Turbojet engine with afterburner chamber contain mainly located upstream of the site to below flow area in the direction of flow of gases one or more compressor stages, a combustion chamber, one or more turbine stages, the channel reuse or channel afterburners and injection nozzle. The primary gas stream is compressed in stages of the compressor, takes part in the combustion of fuel in the combustion chamber expands in the turbine stages and provides the possibility of a new combustion by the oxygen still present in the channel afterburning before the extension in the ejector nozzle.

Channel afterburning contains mainly on the input levers of the stabilizer flame, protruding radially into the primary gas stream, and includes a fuel injector that sprays mentioned fuel in the gas flow in a downward direction. The fuel is ignited, and the flame due to the shape of the cross section causing the decompression levers "value" in the walls of the levers.

You can also provide the b ring of nozzles, located concentrically relative to the casing of channel reuse and operates on the same principle. The ring contains mostly the outer shell in the shape of a trench, comprising a U-shaped section opened downward channel afterburning in the primary gas flow stream, in which is located the fuel manifold of circular cross section, as seen in axial section, the purpose of which is to spray fuel down.

Located downstream from the manifold, the fuel is ignited, and the flame is held in the groove of the ring due to the form of the latter. Therefore, recirculation of the gas in the shell chute is a recirculation of very hot gases. To enhance thermal protection of the fuel manifold is surrounded by a screen of suppression of radiation sources. This screen includes the fuel line holes corresponding to the holes of the collector, mainly collected in pairs in the same axial plane at constant angular positions on the ring.

To obtain the benefits already attempted to increase the size of the hole trench. Recirculation of hot gases was increased accordingly, although it was detected deformation, cracks and burn on the screen, the suppression of radiation sources, in particular, between the holes of the fuel line behind the screen, facing the flame is neither. Therefore, in such zones to protect the fuel manifold is less effective, thereby causing the risk of fouling on the header.

The aim of the present invention is to improve the cooling process screen suppression of radiation sources.

To this end according to the invention created turbofan engine including one or more compressor stages, a combustion chamber, one or more turbine stages, the channel reuse the primary flow and the eductor nozzle, the secondary flow at least partially in the primary stream to channel reuse, and channel reuse includes a ring of nozzles containing the trough of the flame stabilizer in the form of an annular section, which is located upstream section is located in the secondary flow having a fuel reservoir and a protective tubular screen collector, characterized in that the groove includes located upstream deepening associated with the secondary flow, and the screen includes, on its being upstream section, at least one vent space located between the screen and the header.

Preferably, since the chute includes located upstream deepening associated with the secondary flux is om, vent means includes at least one vent hole located on the front area of the screen.

Mainly the collector includes at least one pair of fuel spray holes, and the screen includes at least one pair of corresponding openings, and the vent hole drilled in the screen in the same angular position as the pair of holes.

Mainly the screen, which includes a set of pairs of holes, contains a vent hole drilled in the same angular position, and each pair of holes.

The invention also relates to a ring nozzle for a turbojet engine, comprising a trough stabilizer flame, the fuel manifold and shield collector, characterized in that it comprises the above-described features of the ring.

In addition, the invention relates to a protective screen collector ring nozzle for a turbojet engine, characterized in that it contains at least one pair of holes and a vent in the transverse plane of the pair of holes.

Preferably the screen contains many pairs of holes and a vent in the transverse plane of each pair of holes.

<> The invention will be better understood when reading the following description of a preferred variant implementation of the turbojet engine according to the invention with reference to the accompanying drawings, on which:

figure 1 is a view in partial axial section of a preferred variant implementation of the turbojet engine according to the invention, in the area of the ring injector;

figure 2 is a partial view in cross section of a turbojet engine according to the invention;

figure 3 is a perspective view of the fuel manifold ring nozzle turbojet engine according to the invention;

4 is a perspective view of the screen of the suppression of radiation sources ring nozzle turbojet engine according to the invention;

5 is a view in axial section of the ring nozzle turbojet engine according to the invention in the plane that does not contain any pairs of holes, and

6 is a view in axial section of the ring nozzle turbojet engine according to the invention in a plane containing a pair of holes.

Figure 1 shows a turbofan engine according to the invention, taking place mainly along the A axis and containing several compressor stages, a combustion chamber, several turbine stages, channel 1 post-combustion of the primary stream and the eductor nozzle.

With reference to figure 2 it should be noted that WMO is e channel 1 afterburning radial levers are 2 of the fuel injector, the purpose of which is to spray fuel to the arms 3 of the stabilizer flame, located downstream from the hooks 2 of the fuel injector and continuing radially in the channel 1 afterburning.

With the help of levers 3 flame stabilizer secondary flow, i.e. the flow of cold air which does not pass through the combustion chamber, passes into the primary flow. Downstream from the lever 3 is the shell 14, which forms a channel 15 secondary flow. For the shell 14, the secondary stream is mixed, at least partially, with the primary flow in the channel 1 afterburning.

The number of levers 3 stabilizer flame, nine in this case, equal to the number of levers 2 fuel injector, and they are displaced by angle relative to the latter so that, as shown in the front view, each lever 2 fuel injector was located equidistant between two adjacent levers 3 stabilizer flame. The arms 2 of the fuel injector in the radial direction is smaller than the levers 3 stabilizer flame.

Near the shroud channel 1 afterburning levers 3 flame stabilizer support ring 4 injectors. This ring 4 is made of many sections of the ring 4', number nine, passing concentrically to the casing of channel 1 afterburning between two adjacent levers 3 stabilizer flame. Below it will be relative to the change to the ring 4, which actually is a part of the ring 4'and the constituent elements of the ring 4 will be in this case, the items that make up part of the ring 4', and therefore passing only a truncated ring, not a closed annular periphery.

The arms 2 of the fuel injector are in the radial direction perpendicular to the axis of the turbojet engine. The levers 3 stabilizer flame pass in the radial direction with a slope down from their base, with respect to a plane perpendicular to the axis of the turbojet engine, located in the axial plane of the levers 3. The levers 2 fuel injector spray fuel down. The levers 3 stabilizer flame doing the same thing and, in addition, ensure the ignition of the fuel and capture the flame of their external walls with the appropriate dimensions.

Ring 4 injectors includes a groove 5 of the stabilizer flame, forming an open outer shell, which is shown in the form of an axial section of a U-shaped section, the legs of which are directed downwards. The gutter runs along the direction of the ring or forming. The outer leg of the U longer than the inner leg, and the legs of the U are not parallel; this is more like a rounded basis of V, it is referred to below as the U-shaped section.

The groove 5 is located outside, directly behind the cowling 14. Thus, n is confined upstream wall, forming the base of its U-shaped section, is in contact with the secondary cold-flow, as well as its located downstream walls forming the legs of its U-shaped section, the purpose of which is to catch the flame channel 1 afterburning exposed directly to the heat from it.

As shown in figure 3, near the base of the U groove 5 has a fuel manifold 6 of circular cross section, which is visible on the axial section and corresponds to the peripheral shape of the trench 5. Collector 6 supply fuel through the longitudinal system 7 of the tubes connected to him from above the stream. As shown in Fig.6, it has made placed in permanent angular positions of a pair of round holes 8, 8' for spraying fuel. Hole of the same pair of holes 8, 8' are located in the same axial plane and symmetrical to each other relative to the plane perpendicular to the aforementioned axial plane, parallel to the axis And the turbojet engine and the separating section of the collector 6, the angular position of the holes 8, 8', into two equal semicircles. Holes 8, 8' are located in the downstream section of the fuel manifold 6.

As shown in figure 4, the collector 6 is wrapped screen 9 suppression of radiation sources having the same tubular who Orme, that and the collector 6, but the section which forms a circle of larger diameter, the purpose of which is to protect the reservoir 6 from the radiation of the flame, located downstream, in this case, captured by the walls, the respective legs of the U-shaped section of chute 5.

Screen 9 contains, as in the prior art, a pair of round holes 10, 10' fuel line, and each hole 10, 10' is located on the corner over from the center of the circle formed by the axial cross-section of the collector 6, the holes 8, 8', respectively, a pair of holes 8, 8' of the collector 6. Holes 10, 10' screen 9 have a larger diameter than the apertures 8, 8' collector 6 for the adjustment holes for the fuel jet 11, 11', respectively, as shown in Fig.6.

The groove 5 of the ring 4 injector includes at its wall corresponding to the base of its U-shaped section, that is located on the upstream side, a transverse undercut 12, which follows its generatrix. This undercut 12 is in communication with the channel 15 secondary flow turbojet engine. Therefore, the secondary air flow cools the screen 9 suppression of radiation sources through the transverse undercut 12. This undercut 12 may take the form of a continuous cutting for forming the trench 5, the connecting bridges between its outer and inner edges, or it can Zam is the thread number of drillings.

Screen 9 suppression of radiation sources according to the invention differs from the screens according to the prior art by the presence in the same angular position, and a pair of holes 10, 10', located upstream of the round hole 13 for ventilation zone, located between the manifold 6 and the screen 9.

As shown in figure 5, in the area of the screen 9 suppression of radiation sources that do not contain any holes 10, 10', the secondary air flow passes through the cutting trench 5 and acts on the wall of the screen 9 at its located upstream site. Located downstream section of the screen, facing the flame, catch the rear edges of the walls of the trench 5 is cooled by conduction. Indeed, in this area without holes there is continuity between located upstream portion and a downstream flow area of the screen 9; therefore, the cooling effect provided by the impact of the upstream section of the secondary air stream is transferred through conduction to the downstream site. Therefore, the screen 9 is cooled properly and provides thermal protection to the fuel manifold 6.

As shown in Fig.6, in the area of the screen 9 suppression of radiation sources, which includes a pair of holes 10, 10', the secondary air flow passes is it through the undercut trench 5, then through the vent hole 13 of the screen 9. Then he cools not only located upstream areas of the screen 9, located around the ventilation openings 13, but also the space between the manifold 6 and the screen 9, and then treated through this space, located downstream section of the screen 9. Therefore, below the flow area of the screen 9, in particular between two holes 10, 10'is cooled, which makes it possible to avoid the above mentioned disadvantages.

Thanks to the invention is located downstream section of the screen 9 is cooled in areas of the holes 10, 10', which was not possible with the use of screens according to the prior art, since the conduction of heat from the upstream section to the downstream section may not be exercised, taking into account the fact that these plots are not connected continuously because of the holes 10, 10'. In addition, the space between the manifold 6 and the screen 9, is vented in areas containing holes 10, 10'. Get it through boring ventilation holes 13 in the transverse plane relative to the shape of the screen 9, i.e. axially relative to the turbojet engine of each pair contained in the holes 10, 10'.

1. Turbofan jet, the engine, includes channel afterburning primary flow secondary flow at least partially in the primary stream to channel reuse, and channel reuse includes a ring of nozzles containing the trough of the flame stabilizer in the form of an annular section, which is located upstream section is located in the secondary flow having a fuel reservoir and a protective tubular screen collector, wherein the chute includes located upstream deepening associated with the secondary flow, and the screen includes at its located upstream section, at least one vent space located between the screen and the header.

2. Turbojet engine according to claim 1, wherein the manifold includes at least one pair of fuel spray holes, and the screen includes at least one pair of corresponding openings, and the vent hole drilled in the screen in the same angular position as the pair of holes.

3. Turbojet engine according to claim 2, wherein the screen includes many pairs of holes contains a vent hole drilled in the same angular position, and each pair of holes.

4. Ring of nozzles for turboreactor the wow engine, includes gutter stabilizer flame in the shape of a partial ring, the base of which is located upstream, and the fuel manifold and the protective screen collector placed in the chute, wherein the chute includes located upstream of the slot, and the screen includes at its located upstream section, at least one vent space located between the screen and the header.

5. Ring injector according to claim 4, wherein the manifold includes at least one pair of fuel spray holes, and the screen includes at least one pair of corresponding openings, and the vent hole drilled in the screen in the same angular position as the pair of holes.

6. Ring injector according to claim 5, wherein the screen includes many pairs of holes contains a vent hole drilled in the same angular position, and each pair of holes.

7. Protective tubular screen collector ring nozzle for a turbojet engine, characterized in that it contains at least one pair of holes and a vent in the transverse plane of the pair of holes.

8. Protective tubular screen according to claim 7, characterized in that Thu is it includes many pairs of holes and vent opening, located in the transverse plane of each pair of holes.



 

Same patents:

FIELD: engines and pumps.

SUBSTANCE: proposed afterburner chamber comprises outlet channel with its rear accommodating invariable-cross section outer nozzle, flame stabiliser arranged inside channel front part and fuel nozzle arranged inside flame stabiliser to inject fuel therein. Afterburner chamber incorporates also inner ablation nozzle that makes a protective enclosure for outer nozzle and contains combustible material to be fired in afterburner operation.

EFFECT: simplified design of afterburner for supersonic flight.

9 cl, 5 dwg

FIELD: engines and pumps.

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FIELD: engines and pumps.

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14 cl

FIELD: aviation.

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10 cl

FIELD: engines and pumps.

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8 cl, 12 dwg

FIELD: engines and pumps.

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14 cl, 3 dwg

FIELD: engines and pumps.

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9 cl, 6 dwg

FIELD: engines and pumps.

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1 cl, 10 dwg

FIELD: engines and pumps.

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5 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine afterburner chamber incorporates a diffuser arranged in its casing and formed by a part of the behind-the-turbine cowl surface and the cooling screen, each of the said parts representing a body of revolution and a front device. The cooling screen part and, at least, a part of the behind-the-turbine cowl surface in meridian section feature the profiles defined by polynomials. The cooling screen surface features a bend. At the point of the said bend there is an angle a between the tangent to the cooling screen surface and the afterburner chamber lengthwise axis making in meridian section 20 to 35°. The angle β between the tangent to cowl surface part defined by the polynomial at the point of its intersection with the cowl side surface and the afterburner chamber lengthwise axis in meridian section makes 10 to 25°. The diffuser outlet section area-to-diffuser section area at the bent point makes or exceeds 0.8.

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5 cl, 2 dwg

FIELD: turbojet engines.

SUBSTANCE: proposed afterburner of double-flow turbojet engine contains prechamber with ring flame stabilizers arranged at outlet of diffuser formed by its housing and fairing of rear support of turbine, lobe-type mixer of flows of outer and inner loops secured on support. Periphery part of afterburner and space of outer loop communicate through at least three half-wave acoustic waveguides. Outputs of half-wave acoustic waveguides are arranged in plane of prechamber, and inputs, before mixer. Length of acoustic waveguides is determined by protected invention.

EFFECT: enlarged range of effective suppression of tangential and radial modes of fluctuations of gas pressure and velocity, simplified design, reduced mass of afterburner owing to suppression of pressure fluctuations.

3 cl, 4 dwg

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed afterburner of by-pass engine contains behind-the-turbine and fan inlet channels, separating ring ferrule between channels, central body, posts connecting central body with separating ferrule, housing with heat shield, discharge nozzle manifolds and flame stabilizer. Flame stabilizer is installed in end face of separating ferrule. Discharge nozzle manifolds are arranged in behind-the-turbine and fan inlet channels before flame stabilizer.

EFFECT: minimization of length and mass of afterburner, reduced losses of total pressure, improved efficiency of cooling of construction members.

3 dwg

FIELD: turbojet engines.

SUBSTANCE: proposed afterburner of turbojet engine has outer wall and afterturbine channels with fairing, precombustion chamber with V-shaped flame stabilizer accommodating burner nozzles, all arranged in tandem along engine passage. Central body with inner space arranged along longitudinal axis of afterburner is formed by upper and lower flat walls and it provided with thickened rounded off entry and wedge-like outlet part. V-shaped flame stabilizer consists of two ring segments, each being symmetrical to the other relative to longitudinal axis of afterburner, arranged in half-circle of afterburner cross section before central body at distance from other ring segment not less than maximum thickness of cross section of central body. Central body is secured by streamlined pylons on wall of afterburner and is provided with two flat panels hinge-secured to its entry part over and under flat walls to render streamline form to central body. Rear parts of panels from each side are connected with drive, for instance, by articulated leverage to provide their deflection from flat walls. Through holes made on entry part and in flat walls of central body are connected with its inner space which communicates with inner spaces of pylons and further on, through holes in walls of afterburner, with inner space of pipeline to feed cooling air, for instance, from compressor of straight-through engine or from one of outer circuits of multiflow engine.

EFFECT: improved reliability in operation.

3 cl, 6 dwg

FIELD: turbojet engines.

SUBSTANCE: proposed method of creating reactive thrust in turbojet engine provided with compressor connected with turbine is implemented by preliminary compression of air delivered together with fuel into combustion chamber. Gas received at combustion of fuel and air mixture is used to drive turbine. Additional fuel is combustion in second combustion chamber installed after turbine. Gas formed in combustion chambers is directed to nozzle to create reactive thrust. Ring-shaped flow of gas coming out of turbine is formed after turbine uniformly over circumference. Direction of movement of said gas flow is changed by directing it to engine axis line into second combustion chamber after turbine. Radial concentric flows of gas are formed which collide in center of second combustion chamber with relative braking and conversion of kinetic energy of gas into heating and compressing. Additional fuel is combustion in said higher gas compression area. Gas with sufficient amount of oxygen is delivered into second combustion chamber for combustion of additional fuel.

EFFECT: increased reactive thrust.

4 cl, 1 dwg

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed gas-turbine engine has central stage arranged in gas duct of engine from its part arranged higher relative to direction of main gas flow to part lower in direction of main gas flow and provided with exhaust gas cone forming device in direction of main gas flow, and guide arrangement. Gas-turbine engine has group of blades, group of fuel nozzles and group of igniters. Guide arrangement is located in zone of edge of exhaust gas cone-forming device arranged higher relative to direction of main gas flow. Group of blades is located in gas duct out of the limits of central stage. Blades are provided with atomizing guides extending through blades. Fuel nozzles are installed on inner ends of corresponding atomizing guides. Each nozzle is provided with input, output and passage between input and output. Passage has part arranged to direct fuel flow to first part of passage surface located across and widening downwards in direction of flow with subsequent deflection fuel flow by first part of surface and its outlet from nozzle. Igniters are arranged in corresponding atomizing guides for igniting fuel from corresponding fuel nozzle.

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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