Turbojet engine

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

 

The invention relates to the field of aircraft engine industry and can be used to create jet engines, intended for flight of aircraft in the atmosphere.

Known turbine engine containing the gas generator nozzle and afterburner device located between the gas generator and the nozzle (Goskomiisii. Aircraft gas turbine engines. Design and calculation details. M: mechanical engineering, 1969, page 5, RES).

Also known turbofan engine includes an internal circuit formed by series-connected with the gas generator and the nozzle, and the outer contour formed by the buildings of the gas generator and the nozzle and the outer casing of the engine, with the installed afterburner device (Theory turbojet engines and edited Smisljeno and Vaasudeva, M.: mechanical engineering, 1979, p.17,) : figure b).

The disadvantage of this engine is the low efficiency in forced modes of operation of each of them, due to the combustion of the fuel at low pressure in the afterburner combustion. Known engines do not provide sufficient thrust force without significant changes in the size, weight and increasing the necessary air flow.

The challenge aimed proposed the first invention, is to increase the specific thrust and efficiency of the engine without increasing the size and weight of the structure and at constant air flow.

The task is solved in that in a turbojet engine, containing the generator, the nozzle and afterburner device, the latter is placed around the perimeter of the nozzle and is made in the form of an annular chamber with the United with her gasdynamic resonators and set about them with a gap in the rear wall connected to the nozzle and is made with holes coaxially gas resonators, each gas cavity is made in the form of a profiled element, preferably Cup-shaped form, directed its concave surface to the holes in the back wall and the annular nozzle formed by the edges of the profiled element and coaxially him the holes in the back wall.

In addition, the invention may be the following:

- locations of the holes on the back wall of the afterburner device can be fixed ejector nozzle;

the engine is made of double-circuit with an external circuit formed by the buildings of the gas generator, the nozzle and the outer casing of the engine, while afterburning device placed in the bypass duct of the engine with the formation of the channel for supplying secondary air to the gas cavity, RAS is than necessary between the annular chamber afterburner device, the body of the nozzle and the outer casing of the engine and afterburner device has at least one front burner device, installed in its annular chamber, and each of the gas-dynamic resonator placed in the hollow fairing fixed to the annular chamber by means of a pylon with internal air channel connected to an input of the channel for supplying secondary air to the gas cavity, and the output - ring nozzles of gas-dynamic resonators;

- for engines with a variable thrust vector, the nozzle is made rotatable, afterburning device rigidly mounted on the rotary nozzle, and the outer body of the engine at the location of the afterburner device is made of the fixed and movable parts connected to each other via a sealing element to move the movable part along the inner surface of the fixed part.

Run afterburner device in the form of an annular chamber with the United with her gasdynamic resonators provides a higher specific thrust of the engine due to the implementation in the afterburning device izobaricheskogo, until detonation, thermodynamic cycle with a high frequency of repetition of the pulses. This embodiment of the afterburner device allows to increase the specific thrust of the engine and the benefit is are its small dimensions, "fit" it to the specified values of the diameter of the outer casing of the gas turbine engine, and in some cases, by reducing the length of the afterburner device, to reduce the overall length of the engine.

Accommodation afterburning device on the perimeter of the nozzle allows you to place all the necessary structural elements afterburning device in a given volume of the engine without increasing overall its dimensions.

Having a back wall connected to the nozzle and is made with holes coaxially gas resonators provides execution of the outlet openings of the resonators, technologically simplifying manufacturing and allowing the device does not go beyond the given values of the mass-dimensional parameters.

The implementation of each of the gas-dynamic resonator in the form of a profiled element, preferably Cup-shaped form, directed its concave surface to the holes in the back wall, and an annular nozzle formed by the edges of the profiled element and coaxially him the holes in the back wall of the afterburner device provides education self-oscillatory processes with a high pulse frequency.

Mount ejector nasdaw in the places of the holes on the back wall of the afterburner device organizes additional supply of air from the environment to further took the foster traction engine.

For turbojet engines and the placement of burners in the annular chamber afterburner device organizes additional fuel for the regulation of the detonation process occurring in the afterburning device.

Accommodation afterburning device in the outer loop bypass turbofan engine with the formation of the channel for supplying secondary air to the gas cavity and the placement of gas-dynamic cavities in hollow fairings mounted on annular chamber through pylons with internal air channel connected to an input of the channel for supplying secondary air to the gas cavity, and the output from the ring nozzle, provides for the organization of secondary air to the cavity, and, in addition, contributes to the cooling of their profiled walls during operation of the engine.

The possibility of using afterburner device of the said type on engines with thrust vector control provides rigid mounting afterburner device for rotating the nozzle, and execution of the outer casing of the engine at the location of the afterburner device of the fixed and movable parts connected to each other via a sealing element to move the movable part along the inner the second surface of the fixed part.

The invention is illustrated by drawings, where figure 1 shows the single-circuit stated TRD (fragment), Fig 2 presents the claimed TRD with two circuits, Fig 3 - (ukrupnennom) afterburning device claimed GTE, figure 4 - option run-GTE with a variable thrust vector, figure 5 - scheme of the rotation of the afterburner device with rotary nozzle angle ±£ and the direction of the thrust vector.

Turbojet engine includes a gas generator 1, the nozzle 2 and afterburner device 3 placed around the perimeter of the nozzle 2. The housing of the gas generator 1 is connected with the housing afterburning device 3, forming the outer body of the engine placed in it by the nozzle, the gas generator 1 with its output connected to the nozzle 2, and the afterburning device 3. Depending on the type of engine, namely the parameters of the gas turbine, the value of the critical cross-section of traditional nozzles may vary within wide limits.

For turbojet engines, in addition to the gas generator 1 and the nozzle 2, forming the inner contour of the engine, the engine includes an outer circuit 4 of the motor formed by the buildings of the gas generator 1 and the nozzle 2 and the outer casing 5 of the engine, while afterburning device 3 is located in the outer circuit 4. Afterburner device 3 is made in the form of an annular chamber 6 connected to the her gas-dynamic resonators 7 and rear wall 8, made with holes according to the number of gas-dynamic detonation cavity 7. The rear wall 8 is connected to the housing of the nozzle 2 and the outer casing 4 of the engine (for double-circuit motor connection elements 9, which when executed flexible can perform the role of expansion joints.

For dual circuit engine afterburner device is located in the outer circuit 4 so that the annular chamber 6 forms the outer casing 5 of the engine and the housing of the nozzle 2 channel 10 for supplying secondary air to the gas-dynamic detonation resonators 7.

Each gas cavity 7 is designed as a profiled element 11, mostly Cup-shaped form, forming an open cavity 12, and the annular nozzle 13 formed by the edges of the profiled element and coaxially him the holes in the back wall 8. For dual circuit engine gas cavity 7 is placed in the fairing 14, secured to the annular chamber 6 through pylons 15, in the inner cavity of which is made air ducts, tells channel 10 with annular nozzles 13 resonators 7.

On the rear wall 8 afterburning device 3 in the places of the holes according to the number of gas-dynamic detonation cavity 7 is fixed ejector nozzle 16.

In the annular chamber 6 is set, at least single-burner unit 17 (in the presented examples, the structural embodiment of the claimed device (Fig.2-5) in the annular chamber is equipped with two front burners 17).

The device can be equipped with a mechanism for rotating the nozzle 2 with afterburner device 3 made in the form of hydraulic cylinders 18. To enable rotation of the nozzle 2 with afterburner device 5 of the outer casing 4 of the engine consists of movable and fixed parts 19 and 20 are connected to each other via a sealing element 21. The movable part 19 of the housing 4 mounted for movement along the inner surface 22 of the fixed portion 20 of the housing 4. The nozzle body 2 is made with a fixed annular support element with a spherical outer surface 23. The movable part 24 of the nozzle body 2 is connected with the spherical surface 23 through the sealing element 25 can move along it.

The engine is as follows.

One part of the air enters into the combustion chamber of the gas generator 1, where the fuel combustion at constant pressure P=const. The subsequent expansion of the combustion products is carried out at the jet nozzle 2. Another part of the air fed to the inlet of the afterburner device 3 that performs the role of the jet nozzle. The use of gas-dynamic resonators with profiled elements of the Cup-shaped forms that implement self-oscillating process similar to the well known effect of the Hartmann-Sprenger, leads to abnormally in the high growth temperature and pressure, respectively. Thus, the effectiveness of the proposed afterburning device is not inferior to the ideal efficiency of the Laval nozzle.

In a turbofan engine for forced modes in annular chamber 6 together with the air of an external circuit 3 through the burner 17 is supplied fuel. In this chamber, which is essentially a camera conversion, pre-training fuel-to-detonation combustion, namely the decomposition of the components of the air-fuel mixture to chemically active components.

The prepared mixture through an annular nozzle 13 enters the gas cavity 7, which are used for initiating detonation and implementation of heat in the detonation waves. In the resonators 7 occurs oscillatory process in which a high frequency burn chemically active components of the air-fuel mixture, and it is almost instantaneous combustion (explosion), accompanied by a significant increase of the temperature and pressure of the combustion products, far exceeding the levels achieved in the classical resonator Hartmann-Sprenger. This process ensures a supply of heat efficiency of the cycle V=const at higher degrees of pressure increase than in the cycle of R=const.

Interacting with the inner surface of the profiled element is 11 as an obstacle, the detonation wave in the process of collision and reflection passes the resonator element 11 7 impulse forces from excess pressure. Is the explosive impact of the detonation wave on the inner surface of the profiled element 11 that creates cravings and referred to as "traction wall".

After reflection from the traction walls of the detonation wave becomes reflected shock wave, which already burnt mixture moves towards the exit, carrying the products of combustion. The burned mixture is ejected into the surrounding atmosphere, and after emptying the working cavity open cavity 12) there is a rarefaction wave, which ensures the absorption of a new portion of fresh toplivootdachey mixture. Then the cycle repeats.

When installing ejector nasdaw on the rear wall of the afterburner device, due to the fact that the reflected wave is always a fan of rarefaction waves in the output gas stream through the channels 26 is provided to suction air from the environment, which leads to a further increase in thrust. In this case, the engine operates in the same way as described above.

To reject the direction of the thrust vector rigidly mounted on the nozzle 2 afterburning device 3 by hydraulic cylinders 18 together with the nozzle 2 is rotated by the angle £ (figure 4). When this sealing element 21, which connects odijoo and stationary parts 19 and 20 of the outer casing 4 of the engine, moves along the inner surface 22 of the fixed portion 20 of the housing 4, and the sealing element 25, which connects the movable part 24 of the nozzle body 2 with a spherical outer surface 23 of the stationary support element rotatable nozzle 2 moves along a spherical surface 23.

The invention allows, without increasing the dimensions and weight design turbojet engine, and in some cases, and reducing the length of the engine and at a constant air flow, to make changes in the cycle of operation of the engine in the afterburning mode, expanding the range of forcing his thrust and increasing its efficiency.

The invention opens the possibility to modify the engines of previous generations.

1. Turbojet engine, containing the generator, the nozzle and afterburner device blocks forming the motor housing, wherein the afterburner device placed around the perimeter of the nozzle and is made in the form of an annular chamber with the United with her gasdynamic resonators and set about them with a gap in the rear wall connected to the nozzle and is made with holes coaxially gas resonators, each gas cavity is made in the form of a profiled element, preferably Cup-shaped form, directed its concave surface is Yu to the holes in the back wall and the annular nozzle, formed by the edges of the profiled element and coaxially him the holes in the back wall.

2. The engine according to claim 1, characterized in that the locations of the holes on the back wall of the afterburner device fixed ejector nozzles.

3. The engine according to claim 1 or 2, characterized in that it is made of double-circuit with an external circuit formed by the buildings of the gas generator, the nozzle and the outer casing of the engine and afterburner device placed in the bypass duct of the engine.

4. The engine according to claim 3, characterized in that the afterburning device has at least one front burner device, installed in its annular chamber and afterburner device placed in the bypass duct of the engine with the formation of the channel for supplying secondary air to the gas cavity, located between the annular chamber afterburner device, a nozzle body and an outer motor housing, with each of the gas-dynamic resonator placed in the hollow fairing fixed to the annular chamber by means of a pylon with internal air channel connected to an input of the channel for supplying secondary air to the gas cavity, and the output - ring nozzles of gas-dynamic resonators.

5. The engine according to claim 4, characterized in that for engines with a variable thrust vector with the PLO are pivoted, afterburner device rigidly mounted on the rotary nozzle, and the outer body of the engine at the location of the afterburner device is made of the fixed and movable parts connected to each other via a sealing element to move the movable part along the inner surface of the fixed part.



 

Same patents:

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.

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: 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: 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: 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 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

The invention relates to aircraft engine industry, namely to design afterburners GTE

The invention relates to aircraft engine industry, namely to design afterburners GTE

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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