Afterburner of the two-convention turboreactive engine

FIELD: engines and pumps.

SUBSTANCE: afterburner combustion chamber of turbojet engine contains chassis, connected to the turbine, nozzle, fuel, or fuel-air collectors, injectors are connected with the jets. Before the mixer in the second circuit, an additional collector with sprayers is installed. Sprays of the additional collector are located in the middle of the pockets of the mixer, which ensures the creation of a fuel-air mixture with an air excess factor equal to the same coefficient in the hot gas behind the turbine.

EFFECT: invention makes it possible to obtain a gas flow with the required excess air factor at any point in the section ahead of the front-mounted device of the afterburner, which simplifies the problem of uniform distribution of afterburner fuel in cross section.

2 dwg

 



 

Same patents:

FIELD: engines and pumps.

SUBSTANCE: proposed method consists in the fuel feed into combustion chamber or compressor in amount required for its complete combustion. Besides, extra fuel is fed into combustion chamber in amount required for decrease in the temperature of gases in combustion chamber to safe limit (atmospheric supercharging). At activation of said atmospheric supercharging and exiting from the turbine igniter of whatever type is fired at a time.

EFFECT: perfected process.

2 cl

FIELD: engines and pumps.

SUBSTANCE: turbojet comprises housing accommodating air intake, axial-flow compressor, combustion chamber, turbine vanes and afterburner. Afterburner inner surface is coated by heat-isolation coating with reflection factor at working temperature smaller than unity. Turbine rear support cowl is shaped to direct circular or truncated cone with vertex angle exceeding 90 degrees. Jet nozzle has throat with radius smaller than that of the circle circumscribed by turbine vane ends. Turbojet may be provided with jet nozzle that has the throat with radius equal to or smaller than turbine rear support cowl base. For protection of turbojet its vanes are irradiated simultaneously by microwave-band radio waves and radio waves reflected from rear support cowl via said nozzle and rear support cowl. Note here that radio waves are irradiated outward via het nozzle with decreased amplitude after multiple reflections from heat-protection coating as well as those reflected from turbine vanes.

EFFECT: decreased probability of hitting.

8 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: flame tube head of afterburner of gas-turbine engine includes radial cooled shutters. Cooled shutters have aerodynamic streamlined shaped parts arranged immediately in flow and have the possibility of being turned about their axis; high-drag body in the form of V-shaped stabiliser is formed at synchronous rotation in opposite directions to a certain angle and at joining of a pair of neighbouring radial cooled shutters. Aerodynamically streamlined shaped parts arranged immediately in the flow smoothly pass to cylindrical axes fixed in housing of flame tube head. Turning device in the form of a rotating ring is located outside afterburner and has the possibility of being blown with ambient air during flight. Various internal cavities and radial channels are made inside radial cooled shutters. Internal cavities are connected to flow part by means of cooling openings located on inner surface of V-shaped stabiliser. Radial channels are connected to flow part by means of injectors for spray of afterburner fuel, which are located on outer surface of V-shaped stabiliser at certain angle to the flow.

EFFECT: invention allows reducing total pressure losses in afterburner of aircraft gas-turbine engine in no-afterburning modes.

2 dwg

FIELD: engines and pumps.

SUBSTANCE: control method of fuel flow to afterburner of gas turbine engine consists in the fact that according to measured air temperature at the engine inlet, air pressure after compressor, gas pressure after engine turbine, position of throttle lever and fuel flow to the main combustion chamber (MCC) there controlled is fuel flow to afterburner. In addition, during augmented acceleration, at connection of successive fuel manifold of afterburner, afterburner fuel consumption is increased during its filling through the "previous" manifold by the value of the volume of the successive one. Smooth change of effective fuel consumption and therefore smooth change of engine thrust during acceleration is provided; i.e. ACS operating quality is improved.

EFFECT: higher operating reliability of the engine.

1 dwg

FIELD: engines and pumps.

SUBSTANCE: rear part of airplane turbojet engine comprises an afterburner, limited with an afterburning channel, a thermal protective shell of the afterburner arranged inside it in a radial manner, a unit of diaphragm arranged between the protective thermal shell and the afterburner and defining the throughput section for a ventilation flow of the afterburner. The thermal protective shell is installed on the afterburner by means of fixation elements that ensure angular displacement of the shell relative to the chamber as it expands under thermal exposure. The unit of diaphragm comprises the first and the second circular plates containing multiple windows and covering one another, and arranged accordingly on the afterburner and the thermal protective shell. Windows of both circular plates determine the throughput section. The unit of diaphragm is arranged so that expansion of the thermal protective shell under thermal exposure causes displacement of the second circular plate in angular direction to increase throughput section of windows.

EFFECT: invention makes it possible to optimise and control the secondary cold air coming out of the secondary circular channel of the turbojet engine.

14 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: bracket of flame stabiliser of afterburner duct of gas turbine engine, namely aircraft jet turbine engine includes the housing made in the form of open dihedral angle, and ventilation chamber (24). Ventilation chamber passes inside this housing and has on one of its ends the alignment pin inserted in the hole made in the above housing. Bracket includes fuel header (26) passing inside the housing along ventilation chamber, guide and alignment devices for guiding and alignment of fuel header in relation to ventilation chamber, and heat protection screen (28) fixed on the above housing and closing the open side of dihedral angle. Ventilation chamber includes devices for its fixture in fixed position in the bracket housing, which are independent of heat protection screen. Ventilation chamber of bracket of flame stabiliser includes open end and opposite end made together with axial pin. Pin represents annular projection intended for being supported on the base.

EFFECT: invention allows refusing to use the alignment and fixture projection on ventilation chamber, as well as excluding the following: wear of heat protection screen, wear of pin, and risk of destruction of fuel header.

FIELD: engines and pumps.

SUBSTANCE: afterburner combustion chamber of bypass turbojet engine comprises housing with heat shield to form cooling channel, and mixer of engine outer and inner loops mounted with clearance relative chamber housing. Mixer face butt is furnished with deflector arranged on its outer surface opposite aforesaid heat shield. Deflector height makes 0.5-3.0 while its length makes 2.5-7.0 of cooling channel height.

EFFECT: longer zone of engine loop flows mixing, higher efficiency of engine combustion chamber operation.

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

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: turbojet engines.

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

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

3 cl, 4 dwg

FIELD: mechanical engineering; gas-turbine engines.

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

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

3 dwg

FIELD: turbojet engines.

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

EFFECT: improved reliability in operation.

3 cl, 6 dwg

FIELD: turbojet engines.

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

EFFECT: increased reactive thrust.

4 cl, 1 dwg

FIELD: mechanical engineering; gas-turbine engines.

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

EFFECT: provision of reliable lighting up in afterburner, improved recirculation of fuel in flow.

13 cl, 8 dwg

FIELD: mechanical engineering; turbojet engines.

SUBSTANCE: mixer of afterburner of turbojet engine relaters to members of afterburners making it possible to increase margin of vibratory combustion. Mixer 4 distributes air of outer loop and behind-the-turbine gas which pass through pockets 6 with lobes 5 and mix on section between end face edges 7 of mixer 4 and flame stabilizers 3. Fuel is delivered to gas through manifolds 2. Fuel-air mixture burn out behind flame stabilizers 3. Each portion of fuel from manifold 2 gets into air flow, each element of which has its momentum and direction. Thanks to it each portion of fuel from manifolds 2 has its own time for preparation to combustion and its own burnout time, so afterburner of double-flow turbojet engine has low tendency to vibratory combustion.

EFFECT: increased margin of vibratory combustion.

Turbojet engine // 2277181

FIELD: aircraft industry.

SUBSTANCE: proposed turbojet engine contains gas generator, nozzle and afterburner with housings forming housing of engine. Afterburner is installed over perimeter of nozzle, being made in form of circular chamber with gas-dynamic resonators connected with chamber and rear wall installed with clearance relative to resonators and connected with nozzle and provided with holes coaxial with gas dynamic resonators. Each gas-dynamic resonator is made in form of shaped member, mainly bowl-shaped, with concave surface pointed to holes in rear wall, and circular nozzle formed by edges of shaped member and hole in rear wall coaxial with circular nozzle. Ejector heads are secured in places of holes on rear wall of afterburner.

EFFECT: increased specific thrust and economy of engine without increasing overall dimensions and weight of engine at constant consumption.

6 cl, 5 dwg

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed afterburner of gas-turbine engine contains prechamber and ring-type flame stabilizer installed in housing. Stabilizer is arranged coaxially relative to vibration absorber made in form perforated fairing. Fairing has two perforated sections. One section is located at outlet of fairing at a distance not exceeding 40% of length of fairing along its axis. Second section is provided with sleeveless perforation in beginning before flame stabilizer and is located at a distance from end of fairing not exceeding 50-59.9% of its length along axis. Fairing can be provided additionally with rim. Holes can be made in fairing and rim connected to fairing forming section with sleeveless perforation.

EFFECT: optimization of operation of afterburner owing to provision of frequency characteristics of oscillation process in inner spaces of afterburner and fairing and thus damping excess pressure fluctuations and velocity of gas.

4 cl, 3 dwg

FIELD: turbojet engines.

SUBSTANCE: proposed reheat ring for double-flow turbojet engine, in which temperature of flow of exhaust gases in primary circuit exceeds temperature of air flow in second circuit, has turnable axis of symmetry coinciding with axis of rotation of turbojet engine and it is provided with front ring case from one side forming ring channel axially open to side of output, and at other side, ramp of fuel nozzles arranged in ring channel. It is formed by great number of interconnected sectors of ring. Each sector has sector of front ring case being equipped with fuel intake connected with ramp of fuel nozzles. Front surface of front ring case is made for contact with primary flow. Each sector of ring has connecting device arranged in ring channel at input of fuel nozzle ramp for mounting fuel intake at one side, and ventilation chamber at other side, made in ring channel on at least part of length of sector of front ring case and at input of fuel nozzle ramp. Each sector of front ring case is provided with intake of secondary air getting out of ventilation chamber 2 for cooling fuel nozzle ramp. Sector of rear ring case is provided on output of fuel nozzle ramp to protect ramp.

EFFECT: reduced heat stresses, increased efficiency at augmented conditions.

10 cl, 12 dwg

FIELD: mechanical engineering; turbojet engines.

SUBSTANCE: reheat unit of turbojet engine contains prechamber and central body arranged one after another indirection of flow. Prechamber is furnished with V-shaped flame stabilizer which burners are arranged, and stabilizer proper is made up of two ring segments arranged at a distance not less than maximum thickness of cross section of central body. Said central body contains fixed housing with flat surfaces from both sides and flat deflecting panels in contact with flat surfaces, thickened inlet part rounded off in cross section and wedge-like outlet part. Wedge-like outlet part and contacting flat surfaces of housing and deflecting panels are coated with radio absorbing material. Flat panels and their hinge joints connecting them with central body housing are made hollow, and they are driven from both sides through hollow springs. Fixed hollow cylindrical rod is arranged inside hollow of each panel. Outer surface of said rod is slide-fitted with inner surfaces of hollow hinge joint. Ends of each hollow cylindrical rod pass inside hollow springs, pylons and are connected with cooling air supply pipelines through side holes in reheat unit wall. Hinge joints and cylindrical rods are provided with two rows of through holes arranged at angle relative to each other so that in nondeflected initial position of panels, holes in rods and hinge joints register in front rows in direction of flow and do not coincide in rear rows, and vise versa, in deflected positions of panels, holes coincide in rear rows and do not coincide in front rows. Inner space of each flat panel is connected at one side through holes with inner space of reheat unit, and at other side, with panels deflected, is connected through registered holes in rod and hinge joint, with inner space of cylindrical rod. Thin-walled streamlined screen is made lengthwise outer surface of hinge joint of each panel. Said screen forms inner space between screen and outer surface of hinge joint. Said space is connected inner space of cylindrical rod through registered holes of front rows of rod and hinge joint when panels are in not deflected initial position, and opposite edges of each flat panel in direction from hinge joint is made in form of ellipse, and at deflection of panels, projection of both panels onto plane of cross section reheat unit is screen in form of circle.

EFFECT: improved reliability of reheat unit, reduced level of infra-red radiation in rear semi-sphere of engine.

8 dwg

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