Afterburner of double-flow jet turbine engine, double-flow jet turbine engine and bracket of flame stabiliser for afterburner
FIELD: power industry.
SUBSTANCE: afterburner of double-flow jet turbine engine includes cylindrical wall (112) for separation of primary (20) and secondary (16) flows, attachment device of front end of that wall on external casing and support device for rear end of that wall. Support device is provided on brackets (130) of flame stabilisers passing in radial direction in relation to longitudinal axis of afterburner. Wall (112) for separation includes holes (128) or rounded cutouts through which brackets (130) of flame stabilisers pass. Each bracket includes mainly radial flange (150) passing from inside in relation to separation wall. Flange forms support furnace for the edge of the appropriate hole or rounded cutout made in the separation wall. On radial flange (150) there formed is cylindrical protrusion (164) which is mainly coaxial in relation to bracket (130) and passes outwards in radial direction in hole (128) or in rounded cutout of the wall for separation and along the edge of that hole or rounded cutout.
EFFECT: invention allows giving additional rigidity to the wall, thus maintaining easiness and simplicity of the construction.
12 cl, 7 dwg
The present invention relates to a device mounting wall for separating the primary and secondary gas flows in the afterburner turbofan engine.
Wall to separate threads inside the cylindrical casing of the diffuser turbojet engine and delimits, together with the casing, the annular channel flow secondary flow, which is intended for partial mixing with the primary stream flowing from the inside against the wall, the flow behind the afterburners.
The wall separating attached to its front by the thread end on the casing of the diffuser by means of cylindrical pins, which are held in the radial direction in the secondary flow and the outer end of which is fixed to the casing of the diffuser and the inner end has a sealed manner in a corresponding guide sleeve the wall.
The wall contains at its rear downstream end of the rounded cut, oriented in the direction of flow, through which the arms of the flame stabilizers, located in the radial direction and passing from the casing of the diffuser to the inner part of the primary stream. Each bracket stabilizer flame passes at some distance from the edge of the corresponding rounded neckline in stink what separates and defines together with this edge, a cross section of the leakage of the secondary flow in the direction of the primary stream.
Thus, the back flow of the wall mounted cantilever manner and is able to expand freely under the action of temperature rise during the operation of the turbojet engine.
However, the pressure of the secondary flow exceeds the pressure of the primary flow coming from the turbine of the turbojet engine, which results in a considerable effort on the rear flow side of the wall to separate the threads and is expressed in the local deformations of this rear flow side of the wall in the direction of the longitudinal axis of the turbojet engine and to increase the cross-section of the leakage referred to above, thus deteriorating the characteristics of the turbojet engine.
Known technical solution is to give additional rigidity to the wall for separation by increasing its thickness and forming elements of the stiffness in her back downstream end portion. However, this solution is not quite satisfactory, because it is quite complex and expensive to implement and leads to an increase in the total mass of the wall to separate, which by definition represents a significant under who headed the remainder of the aviation industry.
The technical problem of this invention is, in particular, to offer a different technical solution to this problem, a more simple and economical.
For the technical solution according to the invention proposed afterburner chamber bypass turbofan engine, containing essentially cylindrical wall for separating the primary and secondary flows, means mounting the forward flow end of this wall on the outer casing and supporting the tool back on the thread end of this wall, and this reference tool is placed on the brackets stabilizers flame, passing in a radial direction relative to the longitudinal axis of the afterburner, characterized in that the wall of separation flow contains holes or rounded openings through which the arms of the flame stabilizers, each of which contains essentially radial flange which passes from the inside against the wall separates and forms a bearing surface for the edge of the hole or the corresponding rounded cut in the wall for separation, with the above-mentioned flange formed cylindrical protrusion is essentially coaxial with respect to the bracket stabilizer flame, and passing radially outwards in the hole or close the Glenn cutout wall for separating and along the edges of the holes or rounded neckline.
In accordance with the invention the back flow of the wall for separation is supported by structural elements afterburner that allows you to send the efforts of the pressure applied to the rear flow side walls, structural elements and to prevent deformation of the wall for directions inside during operation, while allowing for freedom of thermal expansion of the wall in relation to structural elements.
Thus, it is possible to implement systems burn fuel with a high degree of extraction, able to withstand the considerable efforts of the pressure on either side of the wall to separate threads.
Abutment means formed on the brackets stabilizers flame, which run in the radial direction with respect to the axis of the afterburner through holes or rounded cut is made in the rear flow side of the wall. Each bracket stabilizer flame contains essentially radial flange which passes from the inside against the wall for separating flows and forms a bearing surface for the edges of the respective holes or rounded cut in the wall for separation. Flange accepts the action of the efforts of the pressure applied to the wall, and is in the process of functioning on Bolshom distance from wall to separate so to reduce the cross section of the leakage between the bracket stabilizer flame and wall to separate.
The flange may be formed in one piece with the bracket stabilizer flame or can be attached to the bracket stabilizer flame.
Preferably, the cylindrical protrusion is essentially coaxial with the said bracket formed on the flange and passes radially outwards in the hole or rounded neckline wall for separating and along the edges of the holes or rounded neckline.
A cylindrical protrusion preferably has a height sufficient to prevent the penetration of hot gases coming from the primary stream and passing between the flange and the wall of separation, means of ventilation bracket stabilizer flame.
In accordance with a preferred implementation of the invention, a cylindrical ledge runs along the front of the flow edge of the flange and along at least part of the rear downstream edge of this flange and connected with the side legs of the bracket stabilizer flame to the shell.
Part of the bracket, which runs in the radial direction from the inside toward the flange preferably has a specific aerodynamic profile in order to provide the th unperturbed and sustainable for hot gases, flowing bracket, that is, for without separation and recirculation flow.
When the wall separation takes place, at least partly, inside the cylindrical heat-shirts channel afterburning fuel, rear downstream end wall for separating includes a radial abutment means this shirt is to limit the deformation of the rear downstream end wall to separate outward.
Radial abutment means formed, for example, by means of brackets attached to the back to thread the end walls to separate.
This technical solution allows to significantly improve the dynamic behavior of a wall to separate, while moving back downstream end of the wall is limited in the radial direction inwards and outwards.
In accordance with another variant of realization of the invention afterburning chamber contains a ring heater, and the wall of separation is supported by brackets mounted on the rear edges of the rings of the stabilizer flame.
The present invention relates to turbofan engine, characterized in that it contains afterburning chamber of the above described type.
The present invention relates also to the bracket stabilizer flame for afterburners OPI the data above type, containing in one of its ends of the mounting tabs, and characterized in that it includes at the level of the base of the legs of the fastening essentially radial outer flange formed with a cylindrical protrusion attached to the legs of the bracket. The flange may be formed in one piece with the bracket or can be attached to it.
Other characteristics and advantages of the invention will be better understood from the following description of non-restrictive examples of its implementation, with reference to the drawings, on which:
Figure 1 depicts an axial slit known afterburner turbofan engine;
Figure 2 - General view of the wall for separating, according to the prior art;
Figure 3 - General view of the wall for separating, according to the invention;
4 is a front view of the bracket stabilizer flame from the rear flow side, according to the invention;
Figure 5 - 7 - General view of the device according to the invention.
Figure 1 shows the afterburner chamber 10 turbofan engine, located on the flow behind the turbine and before the weekend jet nozzle of the turbojet engine.
Afterburner chamber 10 contains essentially cylindrical wall 12 (also called the "wall of merger") to separate ervicing and secondary flows, which is installed inside a cylindrical outer casing exhaust 14 and around the cone exit exhaust gases 18 turbojet engine. The wall 12 and the cover 14 limit between an outer annular channel, through which flows cold stream or secondary stream 16 turbojet engine, created by a fan located in the front on the flow turbojet engine parts and serves to increase traction and ventilation elements of this turbojet engine. The wall 12 limits, together with the cone exit exhaust gases 18, the inner annular channel through which flows the hot stream or the primary stream 20 turbojet engine and which is formed with exhaust gases of a combustion turbine engine. The primary stream 20 and the secondary thread 16 partially mixed with each other in the flow behind the wall 12, in order to increase thrust turbojet engine.
The wall 12 is inserted in the axial direction with their front downstream end of the cowling 22 item turbojet engine, located at the flow front of the afterburner chamber 10, and is fixed to the casing of the diffuser 14 through three cylindrical pins 24 passing in the radial direction in the secondary stream 16 between the wall 12 and the casing 14 and are uniformly distributed around the axis 25 of turboreactor the th engine.
Each pin 24 includes an outer radial end fixed with bolts on the casing 14 and the inner radial end, installed a sealed manner in an outer radial guide sleeve 26 formed on the front downstream end portion of the wall 12 (Fig 1 and 2). The inner ends of the pins 24 is made slightly extended, to allow a small slip on type ball joint these ends of the pins in the guide bushings 26 wall during differential thermal expansion between the wall and the casing.
The wall 12 also includes at its rear downstream end of the rounded cut-outs 28 having a U-shaped, the open side of which is oriented along the stream and through which the brackets 30 of the flame stabilizers, and these brackets have some length in the radial direction relative to axis 25 turbojet engine and are inclined relative to the axis, their outer radial ends fixed to the casing of the diffuser 14, and their inner radial ends displaced in the direction of flow and are located on the flow past a cone exit exhaust gases 18. The brackets 30 of the flame stabilizers are rounded in the notches 28 with a certain gap to provide opportunities for the free thermal expansion of the wall 12 with respect to the brackets 30, and define, together with the rounded edges of the cut cross section of the leakage of air from the secondary flow in the direction of the primary stream.
The inner radial portion of each bracket 30, which is held in the primary stream 20, is made in the form of a hollow dihedral angle, an edge whose vertices are oriented toward the front on the flow part afterburners and inside of which is manifold fuel injection (not shown), the outer radial end of which is fixed to the casing of the diffuser 14 and is connected with means for the fuel supply. Bracket stabilizer flame attached to the casing 14 through the side legs 32, which pass between the wall 12 and the casing 14 and between which moves the secondary air stream 16, part of which has the ability to enter into the bracket and can be dispersed on the fuel manifold by means of ventilation (not shown).
The tabs 32 of the mounting contain a rear flow side of the lodgement of the mounting ring nozzle 34 with a C-shaped cross-section, the hole which is oriented in the direction of flow and which comprises a reservoir 36 of the fuel injection, attached to the above-mentioned means of the fuel supply by means of a curved channel 38, passing in the axial direction between the legs 32 kr is the accumulation of brackets.
The cylindrical jacket 39 is fixed, for example, by means of rivets, to the cylindrical channel 15 afterburners on the back to thread the end of the casing of the diffuser 14 for thermal protection of the channel 15 from the temperature increase in the combustion of the mixture of gas and fuel injected into the chamber 10.
During engine operation, the pressure of the secondary stream 16 is higher than the pressure of the primary stream 20, which leads to significant forces acting on the rear downstream end of the wall 12, and is reflected in the occurrence of local deformation of this part of the wall in the direction of the axis 25 turbojet engine and to increase the cross-section of the channel leakage, thus deteriorating the performance characteristics of the turbojet engine.
In accordance with the prior art seek to limit these deformations through the use of reinforcing elements and thickening of the wall. In the example implementation presented in figure 2, the wall 12 is thickened, and its back on the thread part contains give it additional rigidity axial reinforcing elements 40, uniformly distributed around the axis, and rounded cutouts 28 contain edges, protruding towards the inside of the wall.
However, this solution does not give in one satisfactory result, appears to be rather complicated and expensive to implement and entails a substantial increase in the mass of the wall 12.
The present invention can solve the above problem through the use of tools supports the rear downstream end wall of separation, which are provided on the structural parts of the afterburning chamber 10 and are arranged in the radial direction from the inside toward the wall.
In accordance with the proposed alternative implementations of the claimed invention, is schematically presented in figure 3-7, brackets stabilizers 130 flame afterburners contain outer flanges 150, represents a means to support the rear downstream end wall 112 of the separation.
The wall 112 division actually has a biconical shape, and its ends extend in an outward direction (figure 3). Front downstream end of the wall 112 includes radial guide bushing 126, representing cradles to accommodate cylindrical pins 24, intended for fastening the wall to the casing of the diffuser 14 and the openings 127, intended for the passage of the fuel injector.
Back on thread end part of the wall 112 contains openings 128 through which the arms of the stabilizer 130 flame and the edges of which rest on the outer flanges 150 of these CROs is matte.
The outer flange 150 of each bracket is formed at the level of the base of the legs 132 of the mounting and extends 360° around the axis of the bracket from the inside against the wall 112 to form an annular bearing surface for wall 112.
In this example implementation, the flange 150 formed as a single part with the bracket 130 and associated with the dihedral angle of the bracket by means of a rounded section 158, made from the inner side (6). The flange has an essentially polygonal contour and its dimensions exceed the dimensions of the respective openings 128 in the wall 112 so that the edge of the hole is fully supported by this flange. The thickness of the flange 150 is determined in such a way as not to prevent its own deformation in the case when the wall passes on the flange of the efforts of the pressure, the effects of which it is subjected during operation, and has, for example, a thickness greater than the wall thickness and essentially identical to the thickness of the walls of the dihedral angle.
The flange is designed in such a way as to be parallel to the wall 112 and at some little distance from it (Fig.7)to limit the cross-section 160 of the secondary leakage flow in the direction of the primary flow and hot gases from the primary flow in the direction of the secondary flow, and the cross section of the leak has come considerably less than the cross-section of the leakage current level of technology, which was limited to the edge of a rounded neckline, made in the wall, and the bracket, as is schematically represented by arrow 162 7.
The outer cylindrical protrusion 164 is formed on the flange 150 on the side opposite the rounded 158, and is essentially coaxial with respect to the bracket and inside the corresponding holes 128 of the wall 112. Radial distance relative to the axis of the bracket between this cylindrical protrusion 164 and the edge of the hole 128 is defined in such a way as to allow for free thermal expansion of the wall relative to the bracket.
In the described example implementation cylindrical protrusion 164 runs along the front of the stream edge and along the back downstream edge of the flange 150 and is attached to the legs 132 of the mounting bracket to the casing of the diffuser 14.
A cylindrical protrusion 164 has a height or axial dimension relative to the axis of the bracket, which is determined so that the hot gases to penetrate into the secondary flow passing through the above-mentioned cross section of the leakage between the front downstream edge of the flange 150 and the wall 112, rejected this protrusion 164 and rounded bracket, as schematically represented by arrows 166 figure 6, except for the introduction of hot x gases in the means of ventilation, which can disrupt the normal cooling condition of brackets and manifolds fuel injection.
The brackets 130 stabilizers contain flame, the flow behind the dihedral angle in the vicinity of the flange, the lodgement 168 mounting ring burners 34, similar to the ring in figure 1. Part 170 dihedral angle, which runs in the radial direction between the lodgement 168 and the flange 150 has a certain aerodynamic profile, so as not to impede the flow of the primary stream 20 between the ring burners and the flange in order to avoid separation or recirculation flow.
In this example implementation, the wall 112 has an axial dimension greater than the axial dimension of the wall 12 in figure 2, and its front on the thread end is held within a cylindrical jacket 39 thermal protection channel 15 afterburning fuel and contains a bracket 152 mounted on the outer peripheral part and evenly distributed about the longitudinal axis of the wall. The bracket 152 is designed for entry into the radial bearing contact with the face 39 to limit the deformation of the wall towards the outside, while allowing for the passage of the secondary flow between the wall 112 and the jacket 39.
The clip has an Ω-shaped or inverted U-shape and fastened with their ends 156 by welding or soldering to mention the th wall. The number of brackets is, for example, 27 pieces. This secondary flow is able to flow inside brackets or between brackets.
The thickness of the wall 112 has a value smaller than the wall thickness in figure 2, and this value, for example, is in the range from 1 to 2 mm.
During the operation of the wall 112 extends radially outwards and is no longer supported, or partially supported, by means of flanges of the brackets stabilizers flame. The pressure difference between the primary flow and the secondary flow affects the back to thread the end of this wall, which is deformed to a small extent in the direction of inside and enters the radial bearing contact with the flanges of the brackets 130 to limit the deformation of the wall in an outward direction. Support tools and support rear downstream end of the wall allow, therefore, to improve the dynamic behavior of the end wall 112.
Of course, the invention is not limited to the method of its implementation, which has been described above and are given in the Appendix drawings. For example, the wall 112 may contain rounded cut-outs through which the arms of the flame stabilizers are such that the flanges of the brackets was formed by means of a support for the edges of the rounded neckline is C.
It is also possible that the flange was attached and fixed to the bracket using any appropriate technology. The flange is made, for example, made of composite material with a ceramic matrix (CMC) and is fixed by means of rivets or screws on the brackets stabilizers flame, also made of a material SMS.
The flange can also pass along only a part of the edge of the hole or rounded neckline, made in the wall.
There is also the possibility that the lodgement of fastening of a sector of a ring brackets 130 stabilizers flame was provided on the legs of the bracket, as is the case in the known construction in figure 1.
In accordance with another alternative implementation (not shown) afterburning chamber contains a ring heater formed, for example, coaxial rings of flame stabilizers, and means supports the rear downstream end wall formed by brackets mounted on the rear edges of one of the rings of flame stabilizers. These staples can be a bracket of the same type as the bracket 152 mounted on the rear downstream end wall 112.
1. Afterburning chamber (10) turbojet engine, containing essentially cylindrical wall (112) to separate the primary is about (20) and secondary (16) flows, means mounting the forward flow end of this wall on the outer casing (14) and the support means for the rear downstream end of the wall, and support means provided on the bracket (130) of stabilizers, flame, passing in a radial direction relative to the longitudinal axis of the afterburner, characterized in that the wall (112) for separating contains holes (128) or rounded cut-outs through which the bracket (130) of the flame stabilizers, each of which contains essentially radial flange (150), passing from the inside against the wall for separating and forms a bearing surface for the edges of the respective holes or rounded neckline, made in the wall of separation, with a radial flange (150) formed cylindrical protrusion (164), essentially coaxial with respect to the mounting plate (130) and passing radially outwards in the hole (128) or in the rounded neckline of a wall to divide and along the edges of the holes or rounded neckline.
2. Afterburner chamber according to claim 1, characterized in that the cylindrical protrusion (164)formed on the flange (150)has a height sufficient to prevent the penetration of hot gases coming from the primary beam (20), means of ventilation bracket (130) of the stabilizer flame.
3. Orcagna camera according to claim 1, characterized in that the cylindrical protrusion (164) runs along the front of the stream edge flange (150) and along at least some portion of the rear downstream edge of the flange.
4. Afterburner chamber according to claim 1, characterized in that the flange (150) is formed in one piece with the bracket (130) of the stabilizer flame or attached to this bracket stabilizer flame.
5. Afterburner chamber according to claim 1, characterized in that the cylindrical protrusion (164) attached to the side legs (132) mounting bracket (130) of the flame stabilizers on the casing (14).
6. Afterburner chamber according to claim 1, characterized in that the portion of the mounting bracket (130), which runs in the radial direction from the inside towards the flange (150)has a specified aerodynamic profile to ensure undisturbed and stable during the hot gases flowing bracket.
7. Afterburner chamber according to claim 1, characterized in that the rear downstream end wall (112) for the separation takes place inside the cylindrical jacket (39) thermal protection channel (15) post-combustion fuel and provides radial support means on the shirt.
8. Afterburner chamber according to claim 7, characterized in that the radial abutment means are formed by using brackets (152)attached to the back to thread the end wall (112) to separate.
9. Afterburner chamber according to claim 1, characterized in that it contains kolicevo is heated, when the wall separation is supported by brackets mounted on the rear edges of the rings stabilizers flame.
10. Turbofan engine, characterized in that it contains afterburning chamber made in accordance with paragraph 1.
11. Bracket stabilizer flame for afterburner according to claim 1, containing at one of its ends to the legs (132) mounting, characterized in that it contains at the level of the base of the legs of the fastening essentially radial outer flange (150)is formed together with the cylindrical protrusion (164), attached to the legs (132) mount.
12. Bracket stabilizer flame in claim 11, characterized in that the flange (150) is formed in one piece with the bracket (130) or attached to this bracket.
FIELD: power engineering.
SUBSTANCE: method for increasing efficiency factor and completeness of hydrocarbon fuel combustion in combustion chambers of gas turbine engines consists in the fact that gas and air mixture in flame tube of combustion chamber is exposed to simultaneous treatment by electric field of crown discharge and magnetic field by means of placement of electrode on axis of flame tube, to which positive potential of 3.8-6.8 kV is applied. In direct-flow tubular chamber of combustion the electrode is arranged in the form of thin metal rod. In circular combustion chamber electrode is arranged in the form of ring. Magnetic field is developed in tubular chamber with the help of solenoid, and in circular chamber - with the help of toroid coil.
EFFECT: improved combustion temperature, improved process of combustion and reduced content of toxic substances in exhaust gases of gas turbine engine.
2 cl, 3 dwg
FIELD: engines and pumps.
SUBSTANCE: proposed combustion chamber comprises housing and fire tube with convective-film cooling arranged in the housing to make air space there between and intended for receiving air fed by compressor. Fire tube lateral part has two sets of orifices for air to pass into fire tube inner space, first set of orifices being intended for passage into its combustion zone and second set to allows passage into mixing zone. Additionally, combustion chamber incorporates annular web arranged in aforesaid air space between housing and fire tube wall lateral part over all its length to separate said space into two circular channels, i.e. inner and outer. Annular web front edge is bent toward the housing and tightly jointed thereto, while its rear edge is arranged with a gap relative to housing. Said web has orifices, each corresponding to those of fire tube wall lateral part. Aforesaid mating orifices are communicated by tubular elements. Annular combustion chamber (second version) is furnished with two annular webs arranged and communicated with fire tube in similar way.
EFFECT: efficient external cooling of fire tube, higher reliability.
2 cl, 3 dwg
FIELD: engines and pumps.
SUBSTANCE: gas turbine engine annular combustion chamber front device incorporates inner branch pipes, outer branch pipes aligned with the latter, vane air swirlers arranged at the inner branch pipe inlet and fuel nozzles fitted into the swirler sleeves. The inner branch pipe cross section has an inlet cylindrical section and an outlet trapezoid section with the outer ribbed surface. The outer branch pipe and the inner branch pipe surfaces form the spaces constricted by adjacent ribs. The outer branch pipes are furnished with the holes, at least a part of which representing slots arranged with a spacing of 2. to 4.0 of the slot hole length. The slot hole area exceeds the total area of holes arranged between the aforesaid slot holes.
EFFECT: higher cooling efficiency, preventing burn formation on annular combustion chamber front device, increased rigidity of this device.
4 cl, 4 dwg, 3 ex
SUBSTANCE: combustion chamber comprises housing, fire pipe and fuel nozzles mounted within the housing, and air swirlers with aeration members that project inward fire pipe. The fuel nozzles are arranged uniformly over periphery at the front of the fire pipe. The aeration members are made of inner and outer coaxial conical nozzles. The inner nozzles are secured to the air swirlers. The outer nozzles are connected with the heat-reflecting shields on the front wall of the fire pipe through an intermediate member. The ring shaped bushings are mounted on the outer side of the outer nozzles and form two ring spaces for directing cooling air supplied through the openings made in the intermediate members and outer nozzles along the surfaces of both outer nozzles and heat-reflecting shields.
EFFECT: enhanced reliability and prolonged service life.
1 cl, 4 dwg
FIELD: continuous combustion chambers.
SUBSTANCE: combustion chamber comprises fire tube, two-row swirler whose outer row has swirling member with inlet and outlet, and passage that connects the outlet of the swirling member with the inner space of the fire tube. A diaphragm with holes is mounted at the inlet of the swirling member. The area of cross-sections of the holes is less than that of the outlet of the swirling member and that of the cross-section of the passage.
EFFECT: enhanced efficiency.
FIELD: mechanical engineering; gas-gas-turbine engines.
SUBSTANCE: proposed gas-turbine engine contains combustion chamber, compressor with high-pressure chamber, turbine, exhaust manifold and clutch for connection with consumer. Engine is furnished also with air reservoir made of refractory material ands installed inside working combustion chamber. Air reservoir is provided at one end with hole in form of elongated neck which is installed in center of neck of working combustion chamber. Both necks are installed at one level. At other end, air reservoir is provided with hemisphere with cone-shaped refractory material head installed from outer side. Hollow flat blades are installed at side of air reservoir by means of which air reservoir is attached to working combustion chamber. Nozzles of fuel conversion device with gas pass channels are installed on elongated neck of ignition device of combustion chamber from outer side. Air-cooling casing is installed around ignition device of combustion chamber over outer surface of engine. Axial-flow air compressor with low-pressure fan is installed on rear part of engine. Current generator-starter is fitted on one shaft with axial-flow air compressor. Current generator-starter is connected through automatic clutch with gas-air turbine to which buffer device with guide cone is rigidly connected. One of bearings of gas-air turbine shaft is rigidly secured to housing of buffer device. Energy conversion device is installed in intake part of mixing chamber by its third cylinder with maximum diameter of hole. Guide cone of buffer device of gas-air turbine is installed into mixing chamber from other side. Low-pressure air duct and high-pressure air duct are installed over outer surface of engine over entire length of mixing chamber and energy conversion device from axial-flow air compressor and fan.
EFFECT: improved reliability and increased service life of engine.
FIELD: combustion chambers.
SUBSTANCE: ring combustion chamber comprises front device, a number of mixing devices, and inner and outer housings of combustion chamber that are composed of the front and back sections. The front sections of the inner and outer housings of the combustion chamber define precombustion chamber diffuser, and their back sections lined with the heat-resistant plates define the flame tube of the combustion chamber. The walls of the precombustion chamber diffuser are step and provided with steps directed counter air flow. The steps are provided with openings that connect the precombustion chamber diffuser with the space between the heat-resistant plates and back sections of the outer and inner housings of the combustion chamber. The front device is made of perforated shield provided with openings for mixing devices and supplying additional air. The shield is secured within the butt between the front and back sections of one of the housings of the combustion chamber with the use of bolts for permitting free radial thermal expansion in the butt of the front and back sections of the second housing of the combustion chamber.
EFFECT: enhanced efficiency.
1 cl, 1 dwg
FIELD: generating combustion products of high pressure or velocity.
SUBSTANCE: mixing device comprises auxiliary and main mixers. The auxiliary mixer comprises ring casing, fuel nozzle in the casing for distributing fuel drops in the space of the ring casing, and axial swirler arranged concentrically upstream of the fuel nozzle. The axial swirler has blades for swirling air flowing through the swirler to provide mixing air and fuel drops inside the casing. The main mixer comprises ring housing, auxiliary mixer that embraces the ring casing to define the ring space, swirler with blades for swirling air for mixing air and fuel drops distributed over the ring space by means of openings. The openings for inflowing fuel in the ring space of the main mixer are arranged upstream of the swirler and directed to the inner surface of the ring casing of the main mixer. At least one blade of the swirler is provided with the grooves for supplying fuel to the openings of the main mixer and fuel nozzle of the auxiliary mixer.
EFFECT: improved quality of mixing.
FIELD: gas turbine plants.
SUBSTANCE: combustion chamber of gas turbine plant includes outer and inner housings, fire tubes having in their heads air swirlers and gas fuel sprayer secured to outer housing of combustion chamber coaxially relative to air swirlers. Air swirler is radial one. Outlet openings of gas fuel sprayer are also radial ones. Gas fuel spray nozzle is mounted in sprayer body at outer side of outer housing of combustion chamber. Relation of total surface area of outlet openings of gas sprayer to effective surface area of gas fuel spray nozzle of sprayer is in range 2 - 6.
EFFECT: enhanced operational reliability of combustion chamber due to prevention of increased circumferential non-uniformity of gas temperature field at outlet of it at damage of chamber.
FIELD: gas-turbine engines.
SUBSTANCE: proposed device has flame-tube front wall mounting at least one mixing bush, fuel injector, air swirl generator, and heat shield. Inner surface of mixing bush is made in the form of Venturi tube with its diameter disposed in vicinity of front wall. Air swirl generator is mounted at inlet of mixing bush. Heat shield is mounted behind front wall. The latter and heat shield are directly attached to mixing bush with aid of different-diameter annular collars provided on outer surface of bush and separated by annular drilling. Large-diameter front collar is joined with front wall and rear collar, with heat shield.
EFFECT: enhanced cooling efficiency of mixing bush; enhanced reliability and service life of combustion chamber.
6 cl, 7 dwg
FIELD: engines and pumps.
SUBSTANCE: proposed device comprises jet aerodynamic flame stabiliser with fuel nozzle and combustion chamber with fuel-air mix igniter, extra small-size gas turbine engine, as well as air intake branch pipes, exhaust gas discharge device and system of supersonic nozzles. Small-size gas turbine engine compressor is arranged ahead of fuel nozzle and combustion chamber, and its turbine is arranged behind combustion chamber. Proposed method used air jets forced into afterburner chamber gas flow via system of supersonic nozzles, towards it and at an angle to it. Air is bled from engine compressor intermediate stage. Jet pressure required to stabilise flame is produced using said extra small-size gas turbine engine arranged inside afterburner chamber. In compliance with the first version, proposed method differs from known designs in that air is bled from compressor intermediate stage. Note here that jet pressure required to stabilise flame is produced using said extra small-size gas turbine engine arranged inside afterburner chamber. In the case of two-stage turbojet engine, air is bled from the second stage.
EFFECT: reduced pressure loss in afterburner chamber, stable firing at afterburner modes.
3 cl, 2 dwg
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
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.
SUBSTANCE: proposed method, wherein "hot" central primary flow comes into afterburner from turbojet engine turbine along with external "cold" secondary flow, consists in that the ignition zones with ignition element is arranged in the area of secondary flow coming into afterburner and restricted by the flame stabilisation ring. Note here that a portion of primary flow is bled to be introduced into ignition zone to make the temperature therein exceeding that of secondary flow and, thus, to facilitate ignition. Flame stabilisation elements incorporate flame stabilisation ring that features, in fact C-like cross section, one of the ring segments adjoining ignition zone. Afterburner chamber comprises at least one feed channel with its one end connected, to feed a portion of primary flow into ignition zone, with inner surface of separating wall around the hole intended for bleeding aforesaid portion of primary air. Second end opens nearby flame stabilisation ring segment adjoining ignition zone.
EFFECT: improved ignition under unfavorable conditions.
9 cl, 5 dwg
FIELD: engines and pumps.
SUBSTANCE: turbojet engine comprises gas flow heating channel comprising at least one device to inject fuel into gas flow incorporating open chamber with U-shaped section chamber. Aforesaid section has at least one wall, accommodating fuel injection devices to inject fuel in at least one direction. Aforesaid chamber incorporates cooling jacket arranged along the wall that supports U-shaped section. Fuel injection device comprises protection elements arranged between fuel injection elements and aforesaid wall in fuel injection direction and protective shield fitted inside aforesaid chamber. Protection devices are arranged between chamber wall and protective shield.
EFFECT: reliable protection of fuel injection device operated in extremely hot medium, increased service life.
SUBSTANCE: invention is relate to aircraft building, in particular to turbojet bypass engines with augmenter. Turbojet bypass engine with augmenter comprises high pressure compressor, high pressure turbine and low pressure turbine. Engine is arranged with a bypass extent of m≥0.2 and diametre of inlet to engine more than 900 mm with the possibility of its operation provision at augmentation-free mode, traction from range of 7600-11000 kgf, and in augmentation mode - traction from range of 12200-18000 kgf. Part of high pressure compressor parts, high and low pressure turbines parts is made from nickel granular alloy with yield point of σ 02≥95 kg/mm2 and ultimate strength of σ B≥140 kg/mm2.
EFFECT: invention makes it possible to provide traction force to aircraft with such engine, with simultaneous reduction of specific engine weight due to increased frequency of rotor rotation and increased gas temperature upstream turbine, or with preservation of permanent specific mass, higher resource of engine.
FIELD: engines and pumps.
SUBSTANCE: proposed afterburner comprises separated fan and exhaust loops, front device with flame stabiliser that has inner and outer shelves, fuel jets communicating with fuel manifolds and baffle. Aforesaid fan and exhaust loops are separated by built-up hollow deflector. The deflector tail accommodates stabiliser representing interjointed circular and radial elements linked up with inner shelf of circular element and arranged in exhaust loop. Outer shelf of stabiliser circular shelf is arranged in the fan loop. Fuel manifolds are arranged inside deflector. Fuel nozzles are enclosed by heat-resistant casings and arranged in exhaust loop before each aforesaid radial element of stabiliser. Thermal protection baffle seats between front device casing and stabiliser lower shelf, and can additionally comprise carb fuel circular manifold arranged inside aforesaid hollow deflector and carbs arranged inside stabiliser circular and radial elements. Aforesaid carbs represent perforated tubes with air intakes. Carbs fitted in stabiliser circular elements seat fixed, while those in radial elements may be detached. Note here that deflector outer housing has orifices for deflector inside to communicate with aforesaid fan loop. Front device may incorporate additional intercommunicated fuel jets and manifolds. Additional devices are located behind the flame stabiliser at a distance from stabiliser circular element edge making at least the length of circulation zone. Aforesaid elements are attached to afterburner housing outer surface.
EFFECT: optimum fuel distribution over afterburner cross section, reduced pressure losses, weight and overall dimensions.
8 cl, 12 dwg
FIELD: engines and pumps.
SUBSTANCE: fluid pipe fastener in a housing bore of the turbojet case, particularly fuel-feed pipe to a burner ring in an afterburner comprises a screw-and-nut tool between an end cell of the pipe and the housing bore and includes a ring and a nut. The ring is screwed in the housing bore; one of its ends rests against a thrust tool mounted on the pipe. The nut is screwed on the end cell of the pipe so that it presses the ring to the thrust tool of the pipe to attach it to the case.
EFFECT: invention allows mounting the pipe from the case interior and delivering it inside of a flame holder of the afterburner.
14 cl, 3 dwg
FIELD: engines and pumps.
SUBSTANCE: device for supply of air and fuel to ring of nozzles in afterburner in double-circuit turbojet engine comprises multiple blades of flame stabiliser installed in afterburner and passing radially around chamber axis in the main flow from external body. Ring of nozzles is installed in the main flow and is made of ring sectors installed substantially in continuous sequence on blades of flame stabiliser and comprising fuel supply guide and collector chambers, and facilities for air supply in collector chambers and fuel to fuel supply guide. Facilities for air and fuel supply pass between ring of nozzles and external body of afterburner inside blades of flame stabiliser and are connected to collector chambers and fuel supply guide via ends of ring sectors.
EFFECT: increased efficiency of turbojet engine by means of main flow head losses limitation and by means of improvement of conditions, under which fuel is injected into main flow via ring of nozzles.
9 cl, 6 dwg
FIELD: engines and pumps.
SUBSTANCE: jet engine is equipped with stock of granulated mass molded in the form of packet of disks installed into cylindrical casing and external surface of gas supply line arranged in the form of hollow cylinder aligned with cylindrical casing, on the one side by the cover installed with its central slot part on external slot part of gas supply line threaded bushing, with plug and nozzle installed in it, for supply of compressed gas though electropneumatic valve from on-board source, and on the other side, via bearing of gas supply line force part with outlet part of bearing block shaft installed in central part of figure casing installed peripherally via spiral walls of multiturn helical channels of cylindrical power profile, where multiturn header is installed with outlet pipelines, for supply of damaged granulated mass into gas jet of jet engine nozzle block and cylindrical casing of augmenter device, where mechanism is installed for supply of disks packet into area of their damage, in the form of springs packet, packet of cartridges and thrust disk, at that mechanism of disks packet damage consists of threaded cover with channels for passage of compressed gas arranged on front side, spring-loaded impact elements installed into guide casing fixed into force part of gas supply line combined into single block by screws, at that at the outlet part of bearing block connected via gear reducer to electric drive of augmenter device, cams are arranged for spring-loaded impact elements, axial and radial channels for passage of compressed gas into area of disks packet damage into granules. Besides, mechanism is provided for prevention of damage of spring-loaded movable impact elements during damage of the last disk and idle run, as well as device for recharge of augmenter device by packet of disks arranged in the form of screw pair - screw installed with its front threaded part into threaded part of gas supply line threaded busing, with stop device, for cover holding into working position and nut with handles and pressing bushing, with access windows to stop device.
EFFECT: higher thrust of jet engine.
1 cl, 10 dwg
FIELD: engines and pumps.
SUBSTANCE: assembly of joint between gas turbine engine compressor and turbine rotors comprises the shafts of high- and low-pressure compressors, low-pressure turbine shaft, locking tube, intermediate shaft fitted on low-pressure compressor shaft and intershaft ball bearing. Low-pressure turbine shaft is splined radially with low-pressure compressor shaft and coupled axially with it via coupling sleeve. Locking tube is jointed with said coupling sleeve via extra splined joint. Outer race of intershaft ball bearing is fitted in high-pressure compressor rotor journal inner surface while its outer race is jointed to intermediate shaft outer surface. There is an annular groove made in low-pressure compressor shaft splines to receive thrust sleeve locked axially and provided with ledges arranged on its faces. Locking sleeve with grooves is splined on low-pressure compressor shaft. Thrust sleeve ledges enter the locking sleeve grooves and accommodate additional sleeve arranged along its edges and splined thereon. One end of additional sleeve stays in contact with intermediate shaft and another one is furnished with the ledge staying in contact with locking sleeve end face.
EFFECT: reduced deviation of compressor and low-pressure turbine shafts and longer life of bearings.
4 cl, 2 dwg