(57) Abstract:The invention concerns a device afterburning of fuel, using the stabilizer flame carburising type with optimized cooling system. This flame stabilizer includes a housing (34), which runs in the radial direction in the primary flow of gases and is a structure in the form of a V-shaped dihedral angle, containing two side plates (35, 36) having one common unifying their rounded edge (37), the ventilation tube (38) located between two side plates (35, 36), and at least one fuel conduit (44, 45), located at the edge of the ventilation tube (38). Vent pipe (38) has a generally triangular cross-section and includes at its rear on the flow surface of the groove (42) where the fuel pipes (44, 45). Vent pipe (38) also contains holes (41, 46), designed for intensive cooling of the side plates (35, 36) of the structure in the form of a dihedral angle and fuel lines (44, 45). This embodiment of the device afterburning of fuel leads to improved cooling. 2 C.p. f-crystals, 6 ill. Currently, WPI is bugcontrol turbojet engine, containing an outer annular casing, almost with the axis of rotation, the exhaust casing, is positioned inside the outer casing and containing an outer annular wall and an inner annular wall, each of which has the same axis of rotation as the outer casing, and bounding with him the first pass, intended for the flow of secondary air, and the outer annular wall and the inner annular wall of the limit between a second pass, intended for the flow of gaseous products of combustion, and the afterburning device also includes an annular wall of the combustion chamber with the own axis of rotation, and the external casing, and positioned inside the outer casing, being remote from him at a certain distance, thereby to form a passage for cooling air, and limiting the secondary combustion chamber to flow behind the said first and second passages, brackets stabilizers flame, passing in planes radial to the axis of rotation, at least within the second passage, each of which is made in the form of a dihedral angle, limited by two external plates having a common edge connections and forming the days downstream part of the combustion chamber relative to the axial direction of flow of the gaseous products of combustion, each flame stabilizer further comprises a ventilation tube with many holes, intended for cooling the outer plates by means of the cooling air taken in the first passage, and at least one radially located the fuel supply pipes with holes injection of fuel.Ventilation tube described in this document, has a round cross section, is located in the immediate vicinity of the edge or vertex of the dihedral angle and contains openings intended for cooling of the wings of this dihedral angle. Special screen that prevents thermal radiation and having a semicircular cross section, is located downstream behind the fuel supply between the rear downstream edges of the dihedral angle and lateral axial slits intended for the flow of the mixture of fuel with air in the secondary combustion chamber. Hole injection of the fuel supply are holes located in a strictly radial planes, directed towards the inner walls mentioned dihedral angle. The flame stabilizer of this type are called carburising.Bid, medium, small is broken off designs in the form of a dihedral angle and containing the ventilation tube, designed for cooling mentioned dihedral angle.In this last mentioned source of the flame stabilizer does not contain any of the fuel supply, no screen, preventing thermal radiation. In this case, the fuel is injected at the flow front from these stabilizers flame with pipe fuel supply, located on the sides of the connecting brackets, which are located alternately between the stabilizers flame. Injected into the combustion chamber, the fuel flow on the external walls of the flame stabilizers. Cross section of the ventilation tube in this case has a value exceeding the value of the cross-section of the cylindrical tube, referred to in the source FR 2709342 that provides the best conditions for the cooling of the walls mentioned dihedral angle. However, in this case, the channels of the fuel is exposed to heat flow coming from the gaseous products of combustion that can lead to disruption of the normal functioning of the channels due to the danger of coking and steam tube ("vapor-lock").The objective of the invention is to create a device afterburners the above-mentioned technical solutions.The problem posed in the present invention, is achieved by optimizing the device aerodynamic cooling of each of the stabilizer flame.To achieve its tasks in accordance with the invention, the ventilation tube has a generally triangular cross-section and includes two side surfaces are parallel outer plates, and the back flow surface in the form of radial troughs, in which is located the fuel pipe, and many additional holes directed towards this fuel line, made in the wall of the trench in order to provide ventilation and cooling of the fuel pipeline, which provides the injection of fuel in the direction of the flow.Due to the proposed design flow section of the ventilation tube in this case is larger than the round bore of the vent tube, described in French patent FR 2709342. Due to this, the cooling air is increased and the outer plate design in the form of a dihedral angle cooled blows streams of air flowing from the holes formed on the sides of the wire in all ranges of operation of this turbojet engine, what prevents the danger of coking and formation of steam tubes, and also contributes to thermal stability of the fuel pipe and the so-called dry mode, i.e. in the absence of the functioning of the after-burning chamber or afterburner. The location of the holes and the shape of the cross section of the ventilation tube of the stabilizer flame, best adapted to ensure proper ventilation of the wall structure in the form of a dihedral angle and the fuel line.In a preferred implementation of the present invention, the fuel pipe is equipped with fuel injectors aeromechanical type. This solution allows you to provide a satisfactory quality of fuel atomization and control the width of the cone distribution of the droplets of fuel in order to eliminate any risk of collision with the external plates of the aforementioned structure in the form of a dihedral angle of this system afterburning.Other advantages and features of the invention will be better understood from the following description of the example of its practical implementation, where references are given in primogenitor flame in accordance with the current level of technology in this field;
Fig. 2 is a schematic view in section decarburising of the flame stabilizer in accordance with the current level of technology in this field;
Fig. 3 is a schematic view in axial section of half part of the turbojet engine, containing the afterburning of fuel in accordance with the invention;
Fig. 4 is a schematic view in section along the line IV-IV shown in Fig. 3;
Fig. 5 is a partial schematic perspective view of the device of the flame stabilizer in accordance with the invention;
Fig. 6 is a schematic perspective view of the fuel line.In Fig. 1 presents a schematic view in section of the stabilizer flame carburising type, similar to the flame stabilizer described in the patent application published under the number FR 2709342. The flame stabilizer is located radially in the flow of hot gases moving in the channel of this turbojet engine in the direction shown by the arrow G. the stabilizer flame contains sheet metal, bent in the form of V-shaped degranulate downstream portion of the flame stabilizer, relative to the direction of flow of hot gases G, and further comprises a ventilation tube 5, which made many through holes, which is circular in cross section and which is located between the side plates 2 and 3 designs in the form of a dihedral angle near the rounded edge or the top 4 this durannie, the fuel pipe 6 located downstream behind the said vent tube 5, and the screen counter-radiation 7, which has a concave surface facing in the direction of the flow of gases, and which connects the rear flow edges 8 and 9 of the side plates 2 and 3 mentioned dihedral design, forming side slits 10 and 11 designed to drain formed of the mixture of fuel with air.In this case vent tube 5 contains holes 12, intended for blowing clean air coming from the fan of this turbojet engine in the direction of the mentioned plates 2 and 3 and in the direction of the rounded edges 4.Holes 13 of the fuel pipe 6 inject a certain amount of fuel 14 in the direction of the said lateral slots 10 and 11.In Fig. 2 presents schematizes the WMD in the application for patent in France, published under the number 2696502.This stabilizer flame 1' is also made in the form of a design in the form of a dihedral angle having two side plates 2' and 3' connected to a rounded edge or a vertex of this angle 4', oriented in the direction against the flow relative to the axial direction G of the flow of hot gases. Located in the axial direction of the vent pipe 5' is held between the side plates 2' and 3'. This vent pipe 5' has a generally triangular cross-section, the sides 15 and 16 which are arranged in parallel and next to the said side plates 2' and 3' and contain openings 12, which provide the injection of clean air taken in the channel of the secondary air coming from a fan of this turbojet engine in the head part of the ventilation tube 5', in the direction of the inner surfaces mentioned dihedral design. Back on the thread surface of the ventilation tube 5' is made concave and contains 18 holes, designed to supply clean air to flow in the secondary combustion chamber 19.Turbofan engine and its camera dogboy body of rotation with the axis of rotation 21, the casing of lead 22 of the gaseous products of combustion, through which pass the guide vanes of this turbojet engine and where the movement of the gas stream in the direction shown by the arrow G, and the afterburner fuel 23, located on the flow behind the casing of lead 22 of the gaseous combustion products.Casing discharge or exhaust 22 is located inside the outer casing 20 and limits with him the first passage 24, in which the flow of secondary air's coming from a fan of this turbojet engine.Casing discharge or exhaust 22 formed in the outer annular wall 25 with the axis of symmetry 21. This case leads 22, the outer wall 25 and inner wall 26 are connected by means of radial connecting levers, not shown in the Appendix figures.The outer wall 25 and inner wall 26 of the limit between the second passage 27 that is designed for the flow of flow of the gaseous combustion products.The annular wall 28 of the afterburning fuel with the axis of symmetry 21, which is radially more distant from the axis 21 than the outer wall 26 of the afterburner fuel or afterburners 23.The above-mentioned brackets stabilizers flame 30 which are inclined in the radial direction toward the combustion chamber 20, are located on the border of the casing discharge or exhaust 22 and the afterburner 23. Each bracket flame stabilizer 30 is held strictly in a radial plane containing the axis of symmetry 21 or passing through this axis.Each bracket flame stabilizer 30 includes a head portion 31, which intersects the first passage 24, mentioned above, and which holds at its rear flow side of the annular afterburning combustion chamber 32 with the axis of symmetry 21 connected by means of the fuel pipe 33 with the fuel supply line 33a, and the main body 34, which is held inside the second passage 27 and which is the object of the present invention.Thus, as can be seen in Fig. 4, 5 and 6, the main body 34 is made in the form of a dihedral angle having a V-shaped cross-section, and the top of this dihedral angle is oriented against the direction of flow of gases, and its branches are oriented along the flow G these hot gases. This design is in the form of a dihedral angle contains two outer plates 35 and 36 having a common joint is the main body 34. The vent tube 38 is open at its end remote from the axis of symmetry 21 in order to enable the selection of a certain amount of cooling air is R in the first passage 24, and is closed at its lower end. The vent tube contains along its entire length with a number of holes designed to remove selected air outside the tube 38.Vent pipe 38 generally has a triangular cross-section and includes two side walls 39, 40, strictly parallel outer plates 35, 36, which are located at a short distance from these side walls in order to provide opportunity for intensive cooling of the outer plates 39, 40 of the air flowing out of the holes 41. Back on thread surface 42 of the ventilation tube, which is directed towards the inner part of the after-burning chamber or afterburner chamber 23 has a convex shape and contains a groove 43 of the U-shaped cross-section, in which there are two radial fuel pipe 44 and 45, powered by fuel. In the wall bounding the groove 42, the holes 46 through which the cooling air enters in the direction of the above-mentioned fuel lines 44 and 45.Vent pipe 38 of the flame stabilizer 30 performs the function of the structural core and the supply channel a certain amount of air R, coming from a fan of this turbojet engine. The supply of clean air R is performed in the whole range of operation of this turbojet engine in order to prevent the danger of coking and the emergence of the steam tubes in the afterburning mode and dry mode operation.The shape of the vent tube 38, and the location of the holes 41 and 46, is best adapted to provide thermal integrity of the fuel injector.The device in accordance with the proposed invention allows also to provide thermal integrity of the wall structure in the form of a dihedral angle and the system is et to refuse the use of organs injection, installed in the primary stream, in the case of stabilizers, flame not carburising type, which provides a higher reliability of operation in the prevention of the danger of return fire. The proposed solution also allows the use of composite materials for the implementation of these designs in the form of a dihedral angle, which provides a definite advantage in weight referred to the design. 1. Afterburning of fuel that is designed to bypass turbofan engine and containing an outer annular casing (20) having an axis of rotation (21), casing discharge or exhaust (22) that is positioned inside the outer casing (20) and containing an outer annular wall (25) and the inner annular wall (26), each of which has the same axis of rotation or axis of symmetry, and the external casing (20), and bounding together with the external casing of the first passage (24) intended for the flow of secondary air, moreover, the outer annular wall (25) and the inner annular wall (26) limit between the second passage (27), designed for the flow of gaseous products of combustion, and this device daihani nasni casing (20), and inside the outer shell, which is separated from it by a certain distance so as to define a passage for cooling air, and limiting the secondary combustion chamber or afterburner chamber (23) in the flow behind the first (24) and second (27) passes, and the brackets stabilizers flame (30) are in radial planes with respect to the symmetry axis (21), at least within the second passage (27) and each of these brackets is a structure in the form of a dihedral angle, limited by two external plates (35, 36)connected between a common edge (37), and having a cross section U-shaped, the top of which is oriented in the direction against the flow of hot gases in relation to the General direction (G) flow of gaseous products of combustion, and each flame stabilizer (30) further comprises a ventilation tube (38) that contains many holes and designed for cooling the outer plates (35, 36) by means of the streams of the cooling air taken in the first passage (24), and cooling at least one radial fuel line (44, 45), with openings for the injection of fuel, different arnosti (39), (40), strictly parallel outer plates (35, 36), and back along the flow surface (42), which is a radial groove (43), in which is located the fuel pipe (44, 45), and many additional holes (46), oriented in the direction of the fuel pipe, made in the wall (42) of the gutter (43) in order to ensure adequate ventilation of the fuel pipeline, which provides the injection of fuel in the direction of flow of the flow of hot gases.2. The device under item 1, characterized in that the fuel pipe (44, 45) equipped with fuel injectors aeromechanical type (46).3. Device according to any one of paragraphs.1 and 2, characterized in that each of the stabilizers flame (30) contains two fuel pipe (44, 45).
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.
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.
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.
FIELD: the fuel-air burner refers to heat engineering arrangements.
SUBSTANCE: the fuel-air burner of the combustion chamber of a gas turbine engine has a fuel injector, an axle and tangential air swirlers fulfilled in the shape of channels with open butt-ends and blades inside. The fuel-air burner additionally includes a air-inlet-mixer, located between the body of the injector and the input butt-end of the axle swirler. The low along the flow butt-end of the air inlet -mixer is fastened together with the input butt-end of the axle swirler. The upper along the flow butt-end of the air inlet -mixer is made open. The fuel injector is provided with openings of feeding and dispersion of gas fuel located inside the air inlet-mixer before the input edges of the axle swirler.
EFFECT: allows to increase economy, completeness of burning of fuel and reduce ejection of detrimental substances.
2 cl, 1 dwg
FIELD: mechanical engineering; gas turbines.
SUBSTANCE: proposed low-emission combustion chamber of gas turbine operating, mainly, on compressed gas with low effluents of nitrogen oxides and carbon contains prechamber and cylindrical fire tube with air inlet holes arranged over circumference of fire tube. Prechamber consist at least of two modules with space for preliminary mixing of fuel and air. Ration of distance between axes of neighbor modules to inner diameter of fire tube is 0.4-0.5. Ratio of length of preliminary mixing space of each module to diameter of its exit nozzle is 0.6-0.8. Fire tube has fuel-air mixture burning space and space for mixing not gases with air. Fire tube contains solid inner wall and perforated outer envelope with ring channel in between to feed cooling air into mixing space. Ratio of length of burning space to inner diameter of fire tube is 0.9-1.1. Air feed holes are made in mixing space.
EFFECT: reduced emission of harmful substances owing to organization of "rich-lean" burning of fuel by preliminary mixing of fuel with air in prechamber and prevention of delivery of cooling air into burning zone.
2 cl, 2 dwg
FIELD: engines and pumps.
SUBSTANCE: gas turbine combustion chamber consists of an outer and inner casings and a flame tube incorporating a front device made as a tapered blade-type swirler with its blades arranged between its inner and outer walls. The said swirler inner and outer walls are furnished with closed interconnected spaces in the blades with their outer edge provided with an open channel communicating with the aforesaid closed space. The swirler outer wall accommodates a bracket with an open space communicating with the aforesaid swirler outer wall space and a flange to be attached to the combustion chamber outer casing flange.
EFFECT: utilisation of pit-shaft petroleum gas by combusting it in the ground gas turbine combustion chamber.