Turbojet engine afterburner

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

 

The invention relates to the field of aircraft engine industry, in particular to the afterburner combustion chambers with masking screens to counter weapons to defeat the enemy.

Known afterburner combustion turbine engine containing Saturninus channel, Saturninus fairing, front-line device with a V-shaped stabilizer flame nozzle of the burner, stand, channels cold air (see Patent of Russia №2028487, IPC 7 F 02 K 3/10, publ. 02.09.1995 year). However, this camera has a large size and substantial blockage of the flow part as increased saturninum Radome, and various kinds of racks, screens, channels for supplying cooling air, turning leaves with their control system, which reduces the level of infrared light in the rear hemisphere of the engine, but leads to increased losses of total pressure in the chamber, to increase the specific fuel consumption, to the separation of flow from the elements afterburners, which causes vibrocoring and decrease the reliability of the camera. In addition, the design of this camera offers no protection from radar exposure in the rear hemisphere of the engine (not reduces the effective reflecting surface).

The objective of the invention is to achieve the optimal combination of reliable operation fo sainoi combustion chamber, values of hydraulic losses, dimensions, mass, and effectively reduce the level of infrared and radar (reflected) radiation in the rear hemisphere of the engine.

This technical result is achieved by the fact that the afterburner combustion chamber of a turbojet engine includes an outer wall and consistently located on the tract of the engine Saturninus channel fairing, front-line device with a V-shaped flame stabilizer, inside of which is placed the nozzle of the burner, and located along the chamber axis of the Central body with an internal cavity formed by upper and lower flat walls and having a thickness in a rounded entrance portion and a wedge-shaped output, with V-shaped flame stabilizer is made of two ring segments, each of which is symmetrical to each other relative to the longitudinal axis of the afterburner combustion chamber, is located in a semicircle cross section afterburner combustion chamber in front of the main body and separated from each other at a distance not less than the maximum thickness of the cross-section of the Central body fixed through streamlined hollow pylons on the wall of the afterburner combustion chamber and provided with two flat panels are articulated to its input side above and below the flat with enkomi to give a streamlined shape of the Central body, and rear panels on each side, for example, articulated lever system connected to the actuator for the implementation of their deviations from flat walls, with the input part and the flat walls of the Central body is a through hole connected to the internal cavity that is in communication with the internal cavities of the pylons and then through the hole in the wall of the afterburner combustion chamber with the inner cavity of the piping for supplying cooling air, for example, from a single compressor of the engine or from one of the outer contours of the contour of the engine.

The cooling air outlet of each of the through-hole is made on the input side of the Central body, carried on the outer surface of the flat panels is not rejected their original position in the direction of gas flow along the path of the camera.

Wedge-shaped output part of the Central body and the outer surface of its flat walls and in contact with the inner surface of the panels is covered with radio absorbing materials, the sizes of each through hole for passage of the cooling air in radio-absorbing material is made in 3...5 times smaller than the wavelength of the radiation.

The implementation of V-shaped flame stabilizer of two ring segments, each including symmetrical to each other relative to the longitudinal axis, situated in a semicircle cross-section of the chamber in front of the main body and separated from each other at a distance not less than the maximum thickness of the cross-section of the Central body, allows the formation of a zone in which there is no burner, and thereby create, along the longitudinal axis for segments of the stabilizer, the space in the afterburning mode freely from the torch flame, and in this space to place the Central body and secure it through the side streamlined hollow pylons on the wall of the afterburner. A Central body with an internal cavity formed by upper and lower flat walls thickened input and wedge-shaped output parts, equipped with two flat panels are articulated to its input side above and below the flat walls to give a streamlined shape of the Central body, and the connection of the rear side panels on each side, for example toggle drive system for the implementation of the deviations from the flat wall, and the presence of through-holes on the input side and on the flat panels, communicated with the inner cavity of the Central body, which in turn is connected with the inner cavity of the hollow pylons and forth from the inner cavity of the piping for supplying cooling air, for example, and the compressor single-engine or from one of the outer contours of the contour of the engine, allow for modes of low visibility, for example, overcoming band air defense, through the deflection of flat panels and simultaneous supply of cooling air through the through holes on flat walls, substantially reduce infrared radiation in the rear hemisphere, and in other modes of engine operation, due to the return of a flat panel in the original position and their contact with the flat walls of the Central body, help to form the Central body streamlined, while maintaining acceptable minimal loss of total pressure in the afterburner combustion, to block the flow of cooling air through the through holes in the flat walls of the Central body and at the same time to open the flow of cooling air on the outer surface of the flat panels, thereby providing a protection film of a Central body cooling air for afterburning operation modes and saving the consumption of compressed air taken from the compressor single-engine or from one of the outer contours of the contour of the engine, and hence providing the most appropriate specific parameters of the engine as a whole.

The coating of radar absorbing materials, such as heat-resistant material on a ceramic base, the external surfaces of the wedge-shaped o the ne part of the Central body and the outer surface of its flat sides, and in contact with the inner surface of the flat panels, rejecting flat panel at a certain angle on the modes, for example, when the bridging strips defense, you can greatly reduce the reflected radar radiation in the rear hemisphere of the engine not only due to the absorption of directional radar beam radar absorbing coating with successive multiple reflections from structural elements, but also due to the withdrawal of a directional radar beam at the sight of his reflection on the part of the capture and maintenance of systems for the military defeat of the enemy, and having overall dimensions of the through holes for the passage of cooling air in stealth coating, made in 3...5 times less than a wavelength of radiation, for example, for a range of wavelengths λ=3...10 cm, do not reduce the efficiency of absorption, as in this case, the structure of radar absorbing material radar signal perceives as a continuous medium. While the application of radar absorbing coating on the inner surface of the flat panel and the outer surface of the Central body and having successive multiple reflections of the radar beam allow to increase the total thickness of the layer of radar absorbing pokr is ment and thereby increase its effectiveness for protection from radar exposure.

The invention is illustrated by drawings.

Figure 1 shows the longitudinal section of the afterburner combustion turbine engine is in the initial position of the panels of the Central body.

Figure 2 presents a longitudinal section of the afterburner combustion turbine engine when the deviation of the Central panels of the body from its initial position to the desired angle.

Figure 3 presents a longitudinal section of the afterburner combustion turbine engine while the top view of the Central body.

4 shows a cross-section of the afterburner combustion turbine engine (cross section a-a).

Figure 5 presents in an enlarged scale schematic diagram of the Central body.

Figure 6 on an enlarged scale presents the input part of the Central body with a supply of cooling air and radioparadise coating on the exterior surfaces of the casing and the inner surfaces of flat panels.

Afterburner chamber 1 turbojet engine includes an outer wall 2, Saturninus channel 3 with fairing 4, the front device 5, a V-shaped stabilizer 6 flame nozzles 7 and the burner device 8, the Central body 9 with an internal cavity 10, the upper and lower flat walls 11 and 12, thickened rounded input part 13 and the wedge output h is d 14, the segments 15 of the stabilizer flame, pylons 16, flat-panel 17, the lever system 19 to the actuators 20, through holes 21 and 22 in the Central body, the inner cavity 23 of the pylons 16, through holes 24 in the outer wall of the internal cavity 25 of the pipes 26, radar absorbing material 27 is placed on the outer surface of the wedge-shaped outlet part 14 of the Central body, on the outer surface of its flat walls 11 and 12 and on the inner surface of its flat panel 17.

The drawings also shows the side holes 28 of the Central body 9, associated with the internal cavity 23 of hollow pillars 16, the channels 29 for supplying cooling air to the through holes 21, the gap 30 formed of a cylindrical surface 31 of the input part 13 of the Central body 9 and the cylindrical surface 32 of the Cam profile flat panel 17, and a jet nozzle 34.

Afterburner combustion chamber of the turbojet single-circuit or multi-circuit engine works as follows.

When the engine at all operating conditions, the cooling air from the compressor is single engine or from one contour, the contour of the engine through pipelines 26 through the holes 24 in the wall 2 afterburning chamber 1 flows into the inner cavity 23 of the piers 16 and then through the side holes 28 of the Central t is La 9 in its inner cavity 10. From the internal cavity 10 through the inlet channels 29 air is supplied to the through holes 21 in the input thickness in a rounded portion 13 of the Central body 9. Next, the cooling air from the through holes 21 enters the gap 30 formed of a cylindrical surface 31 of the input part 13 of the Central body 9 and the cylindrical surface 32 of the Cam profile flat panel 17. Of the gap 30, the air is flowing in the portion of the afterburner combustion chamber 1 in the direction of the gas flow path of the combustion chamber 1 and, by interacting with them, washes the outer surface of the flat panel 17 of the Central body 9, cooling them not rejected their original position. Flat panel 17, while in the initial position, is pressed under the action of lever systems 19 and actuators 20 and contacting their inner surfaces with upper and lower flat walls 12 of the Central body 9, block the cooling air outlet of the through holes 22.

On the modes of low visibility, when you want to reduce the level of infrared and radar reflected radiation, for example in overcoming band air defense (flight of the aircraft with a speed of 900 km/h at ground), when entering from the control system (in the drawing conventionally not shown) of the control signal to the actuator 20 of lever with the system 19 rejects flat panel 17 from its original position relative to the axis of the hinge rod 33 at the required angle (required deflection angle flat panel 17 is determined by experimentation or by calculation from the condition obtain an acceptable loss of total pressure in the chamber and ensure effective reduction in the level of infrared and radar radiation in the rear hemisphere of the engine at low visibility). During rotation from the original position flat panel 17 at the required angle, which in this position perform the role of the mask screen, the curved surface 32 of the panels 17 select clearances 30 and block the flow of cooling air from the through-hole 21, while opening of the through hole 22 on the upper and lower flat walls 11 and 12 of the Central body 9. Through the open through holes 22 of the inner cavity 10 of the Central body 9, the cooling air enters the afterburner combustion chamber 1 in the area formed rejected flat panels 17, the upper and lower flat walls 12 and wedge-shaped output part 14 of the Central body 9. This cooling air, interacting with the inner surfaces of the flat panels 17, cools them, closes the visibility of the hot parts of the engine from the rear hemisphere of the engine and reduces the level of reflected infrared radiation. When the occurrence of the radar signal from a locator from the rear hemisphere of the engine at first he gets on the radio absorbing material 27 of the inner flat surfaces of the panels 17 and, if the absorption is carried out they are not completely the attenuated signal is reflected from the flat panels 17 and gets on the radio absorbing material 27 on the flat walls 11 and 12 or wedge-shaped outlet part 14 of the Central body 9. So, repeatedly reflected and passing through the radio-absorbing material 27 on the flat panels 17, flat walls 11 and 12 and the output unit 14, the radar signal is extinguished and is not returned to the radar station. While the dimensions of the through holes 22 for the passage of cooling air in stealth coating 27 on the flat walls 11 and 12, made in 3...5 times smaller than the wavelength of the radio waves do not reduce the efficiency of absorption, as in this case, the radar signal perceives the structure of radar absorbing material as a continuous medium.

In cases where the reduction of infrared and radar radiation is not required, the actuator 20 actuate lever system 19, flat-panel 17 is returned to its original position in contact with the outer surfaces of the flat walls 11 and 12, block the flow of cooling air through the through holes 22, and simultaneously open the flow of cooling air through the through hole 21, thus forming a streamlined shape of the Central body 9 with the supply of cooling air on the outer surface of the flat panel 17, and DWI is the motor works normally in the layout of all other operating modes.

This embodiment design afterburner combustion chamber of a turbojet engine with a masking screen by combining it functions in a single system using radar absorbing materials and the simultaneous flow of cooling air at low visibility provides effective reduction of the level of infrared and radar reflected radiation in the rear hemisphere of the engine, and hence the effective resistance technical means of reconnaissance of the enemy with the simultaneous achievement of the optimal combination of reliable operation of the afterburner combustion chamber, acceptable values of hydraulic losses, dimensions and mass.

1. Afterburner combustion chamber of the turbojet engine, containing an outer wall and consistently located on the tract of the engine Saturninus channel fairing, front-line device with a V-shaped flame stabilizer, inside of which is placed the nozzle of the burner, and located on the longitudinal axis of the afterburner combustion chamber Central body with an internal cavity formed by upper and lower flat walls and having a thickness in a rounded entrance portion and a wedge-shaped output, with V-shaped flame stabilizer is made of two ring segments, each of which is symmetrical with the Rog other relative to the longitudinal axis of the afterburner combustion chamber, situated in a semicircle cross-section of the afterburner combustion chamber in front of the main body and is separated from the other ring segment at a distance not less than the maximum thickness of the cross-section of the Central body fixed through streamlined hollow pylons on the wall of the afterburner combustion chamber and provided with two flat panels are articulated to its input side above and below the flat walls to give a streamlined shape of the Central body, and the rear panels on each side, for example, a lever system connected to the actuator for the implementation of their deviations from flat walls, with the input part and the flat walls of the Central the body is a through hole connected to the internal cavity that is in communication with the internal cavities of the pylons and then through the hole in the wall of the afterburner combustion chamber with the inner cavity of the piping for supplying cooling air, for example, from a single compressor of the engine or from one of the outer contours of the contour of the engine.

2. Afterburner combustion chamber according to claim 1, characterized in that the cooling air outlet of each of the through-hole is made on the input side of the Central body, carried on the outer surface of the flat panels in not from lananna their original position.

3. Afterburner combustion chamber according to any one of claims 1 and 2, characterized in that the wedge-shaped output part of the Central body and the outer surface of its flat walls and in contact with the inner surface of the flat panels are covered with radio absorbing material, the sizes of each through hole for passage of the cooling air in radio-absorbing material is made in 3...5 times smaller than the wavelength of the radiation.



 

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