The combustion chamber with the annular ultrasonic oscillator atomization of fuel
(57) Abstract:The combustion chamber with the annular ultrasonic oscillator atomization of the fuel nozzle contains a device that is in communication with the manifold inlet, heating pipe with perforated holes and the flame stabilizer. The nozzle device is made in the form of an annular gas-jet ultrasonic generator, representing the body of rotation, the cross-section size which is much less than the diameter of the axis of the cross section, with an acoustically linked primary and secondary toroidal resonators excited by air entering through the annular nozzle with an oblique cut, passing in an exponential acoustic horn. For disclosure acoustic horn 180° is the ring of the front device generating exponential form and are evenly distributed around the circumference of the perforated holes for passage of the primary air flow. Front-line device connected to the fairing of the flame tube air flow and with the input of fuel, water or iodomethane through evenly distributed around the circumference of the horn sicklemia transverse channels segmental cross-section, spaced at a distance not less than the wavelength of ultraspectral. The stabilizer flame created by the fan plane transverse to the flow of liquid jets from ilersich channels. The invention allows to intensify the process of burning liquid fuel. 1 C.p. f-crystals, 7 Il. Usage: in the aviation and stationary power plants.The inventive annular combustion chamber is mounted an annular ultrasonic oscillator atomization of fuel, water (iodomethane) intensification of the combustion process (SUGARTITS). 8 Il.The invention relates to gas turbine engines, particularly aircraft and stationary power installations.Known combustion chamber, such as aircraft gas turbine engine TV7-117 [1, 2] , containing the heating pipe is perforated with holes, the stabilizer flame, the fuel injector and the housing. To create a uniform field spray fuel into the combustion chamber of the engine TV7-117 18 of the fuel injector.Traditional sprays fuel (kerosene) in the combustion chambers of the traditional GTD and in gazotermichnih serve centrifugal fuel injectors. This method of atomization requires a high pressure system to its submission 70-80 ATM. , Wu unevenness of temperature fields (30%) and total pressure (10%) at the gas outlet from the combustion chamber because of the uneven performance of the fuel injectors in the kit, which significantly increases (twice) due to their zakochany with increasing operating time. The particle size of the droplets of fuel to the various operating modes of the CCD is 200 μm on the mode of "small gas" and 80-100 μm to "off". This disadvantage by 25% reduces the reliability and service life of parts hot parts of the CCD.Another significant drawback of such combustion chambers is high emissions of oxides of nitrogen.The purpose of the invention is to improve the basic parameters of the propulsion gas turbine engines to improve and ultrasonic intensification of the process of combustion of liquid fuel in their combustion chambers.This is achieved by the fact that mounted in the annular combustion chamber SUGARTITS ultrasonic wave disperses supplied liquid fuel into droplets optimal granulation on all operational modes of the CCD, spread them evenly over the cross section of the combustion chamber, and completely burning them in intensified ultrasonic aerothermochemical field of turbulent gas flow.The invention is illustrated in the drawing (Fig. 4), which shows CHARTIES in the cut. It is a body of rotation, the transverse size which is much melodisi 17 and 18. The liner 17 contains the toroidal cavity of the main cavity 19 of round cross-section, a profile part of usadelaware confused ultrasonic annular nozzle with an oblique cut, ending ring back sharp edge cracks (cap) of the main resonator and the front sharp edge of the crack starts at the throat of the exponential horn 27. The liner 18 includes an annular toroid secondary cavity resonator 20 round cross-section, a profile part of usadelaware nozzle with an oblique cut, ending in a sharp edge cracks (cap) secondary resonator, and its sharp front edge is the beginning of the throat exponential horn.The liners 17 and 18, each has on the periphery of the several hundred of longitudinal channels, evenly spaced around the circumference, which are connected to an annular manifold cavity for supplying fuel and water, or iodomethane, when this is required by the conditions of the CCD), respectively, 8 and 10. The longitudinal channels 4 and 5 are connected with gilardini transverse channels 2 and 3, having a segmental cross-section area 10 times smaller cross-sectional longitudinal channels.For the implementation of the axial swirl flow of the combustion products in the flame .Sealing liners 17 and 18 in the housing 1 made of annular spacers 24, 23 of soft annealed red copper.Ring horn parts 21 and 22 through the slot 14 and 15 are screwed into the housing 1 with bracing, where and condense collector channels liners 17 and 18 located annular gaskets.A continuation of the exponential horn 27 to its full disclosure to 180ois the ring of the front device 25. The slots 14 and 15 of the ring parts of the horn at the same time serve as distributors of the primary air flow in the annular gap fairing at the entrance to the combustion chamber.The housing 1 has a bottom part of the oval flange 6 with two holes for mounting, located in the vertical plane. Through these holes are screws 7 SUGARTITS to the paired flange of the bottom power of the ribs of the casing of the combustion chamber. Through the flange 6 implemented supply in the collector cavity 8, 9, 10, respectively, fuel, air, water or iodomethane (Fig. 3). At the entrance to these cavities are strainers. On the housing 1 has two lugs which are at an angle 108oconnected with power ribs of the casing of the combustion chamber through the damping ACO with its outer surface includes a dispenser 12 of the air flow. He quickly removed from its Seating surface due to the presence of folding buckle 13.SUGARTITS works as follows. From the cavity 9 through the nozzle 26 at a small angle enters the air pressure, which is a thin flat jet loop wraps around the inner cavity of the main resonator 19 and creates excessive pressure, and part of the air stream flowing over the neck of the secondary cavity 20, it creates a vacuum. Under the action of these forces thin annular jet of air cyclically deformed so that the coming one after another ring, the wave train forms an ultrasonic wave front in the form of slightly expanding the corrugated shell of a truncated cone, the thickness of the two amplitude, oscillating about the equilibrium position. The deformation of the jet of the main resonator is the excitation of vibrations, and the deformation of the secondary resonator makes it scalebane, resulting Vibroscreen circular conical shell ultrasonic wave front. This front facing on its way jet fan fuel and service when required, to be a fan of the jets of water or iodomethane (Fig. 2, the section m - n), coming under pressure from a number of giruet these jets on a spherical droplet optimal granulation on all operational modes of the CCD. Conical annular flat fan jets segment of the profile at the same time is a stabilizer, limiting the movement of the droplets of fuel only the combustion zone of the flame tube.Wavefront 29, intensificar ultrasound zone of combustion gas turns the drops of fuel into the hot products of combustion, burning them in a turbulent flow of secondary air in the mixing zone of the flame tube 30 diluted tertiary air flow to an acceptable turbine temperature. The way in GTE with oscillator SUGARTITS, is the generation of a hot gas.Specification annular combustion chamber with CHARTIES GTE
N n/n - the Name of the structural element (Fig. 2, 3, 4)
1 - Body oscillator
2 - Cyclery channel for supplying fuel (kerosene)
3 - Cyclery channel for supplying fuel and at the same time when the operational need a supply of water or iodomethane
4 is a Longitudinal channel for supplying fuel
5 is a Longitudinal channel for supplying fuel and, if necessary, at the same time the supply of water or iodomethane, segment section
6 - Oval flange with podwodami fuel, air, water, iodomethane
7 - Screw mounting flange autoctona cavity air
10 is an Annular manifold cavity fuel, water or iodomethane
11 - Sliding support mount SUGARTITS
12 - Ring valve primary air flow
13 - Folding buckle quick removal of the diffuser
14 - Slotted crown of the outer part of the exponential horn
15 - Slotted crown of the inner part of the exponential horn
16 - Ring fairing primary air flow of the flame tube
17 is a Profile liner with toroidal cavity of the main resonator
18 is a Profile liner with toroidal secondary cavity resonator
19 - Main toroidal resonator oscillator ultrasound
20 - Secondary toroid resonator oscillator ultrasound
21 - the Outer part of the ring of exponential horn
22 - the Inner part of the ring of exponential horn
23 is Located a sealing ring
24 is Located a sealing ring
25 - the Ring of the front of the device, revealing the mouthpiece 180o< / BR>26 - Ring oncomelania supersonic nozzle with an oblique cut
27 - Exponential annular mouthpiece SUGARTITS
28 - Throat ring exponential horn
29 - Ogen figures of the invention
Fig. 1. Description CHARTIES in comparison with centrifugal fuel injectors FR-20 for the combustion of kerosene in the combustion chamber theatre AI-20K depending on the granulation of his drops.Fig. 2. Diagram of forces and movement of the element mass medium during operation SUGARTITS.Fig. 3. Design CHARTIES in the flame tube of the combustion chamber of the CCD with a supply of fuel, air, water or iodomethane.Fig. 4. Longitudinal section CHARTIES in the flame tube of the combustion chamber of the CCD. The main parameters obtained during bench testing of the CCD AI-20K, with mounted in the combustion chamber of the oscillator SUGARTITS.Fig. 5. Torches atomization widespreading compartment natural profile CHARTIES in 1/100 of its circumferential length and centrifugal atomizer FR-20 in the idling conditions of the CCD AI-20K.Fig. 6. Experimental full-scale compartment profile CHARTIES in 1/5 of its circumferential length and the results of fire tests in comparison with two centrifugal fuel injectors FR-20 operating modes marching GTE AI-20K.Fig. 7. Experimental full-scale compartment profile CHARTIES in 1/50 of its circumferential length prozrachnosti drops of fuel on the modes "small gas" and "off" and the main parameters SUGARTITS.Techno-economic advantages of the invention SUGARTITS.GTE, in the frontal part of the flame tube of the combustion chamber which is mounted SUGARTITS has a perfect process autogeneration of hot gas in comparison with the process, when the fuel rasplivaetsa centrifugal atomizers.The perfection of the combustion process leads to the increase of the main parameters of aircraft GTE, including:
1. Stable optimal granulation drops of fuel 50-60 µm in all operating modes marching GTE (Fig. 5, 7).2. The intensification of the process of combustion ultrasound increases the effective power (thrust) GTE 2%.3. In all operating modes of the CCD ensures completeness of combustion of the fuel-air mixture of 99% (Fig. 1).4. Circumferential non-uniformity of the temperature field at the exit of the combustion chamber does not exceed 50oC, and the full pressure is not more than 0.05%.5. Structural mass of the fuel system of the CCD is reduced by 5%.6. The presence of the circular ultrasonic front in the combustion chamber of the CCD ensures complete combustion of fuel, no coke, oxidized films on the hot parts of the engine.8. SUGARTITS provides a good starting and stable operation of the CCD at low and high ambient temperature, electric and magnetic fields, because of his working environment - the air is indifferent to their influences.9. SUGARTITS provides low emissions of nitrogen oxides, and toxicity of exhaust gases due to complete combustion of the fuel in a turbulent flow of air in intensified ultrasound the combustion zone (Fig. 6).10. The range of stable operation of the combustor at an altitude of 8-10 km is increased 1.5 times for GTE.11. Fuel consumption for the same power GTE decreased by 1%.12. Efficiency of the CCD is increased by 1%.13. Guaranteed resource GTE increased by 20% by reducing temperature gradients in the hot parts of the engine.14. SUGARTITS characterized by ease of fabrication parts, tech, has a low complexity in manufacturing.Sources of information
1. Patent RU N 2094705 C1, 6 F 23 R 3/18, 1997.2. Brochure TV-117S Turboprop Engine, Moscow, Aviation Publishing Hourse, 1993. 1. The combustion chamber with the annular ultrasonic oscillator atomization of the fuel containing pulsator flame, characterized in that the nozzle device is made in the form of an annular gas-jet ultrasonic generator, representing the body of rotation, the cross-section size which is much less than the diameter of the axis of the cross section, with an acoustically linked primary and secondary toroidal resonators excited by air entering through the annular nozzle with an oblique cut, passing in an exponential acoustic horn, the disclosure of which is 180° is the ring of the front device generating exponential form and are evenly distributed around the circumference of the perforated holes for passage of the primary air stream, which is connected with the fairing of the flame tube air flow, and with input fuel water or iodomethane through evenly distributed around the circumference of the horn sicklemia transverse channels segmental cross-section, spaced at a distance not less than the wavelength of the ultrasound from the mouth of the horn and connected to the ring collector cavities made inside the nozzle device, and a stabilizer flame created by the fan plane transverse to the flow of the jets of fluid from ilersich channels.2. Luggage under item 1, characterized in that the jet
FIELD: gas-turbine plants.
SUBSTANCE: proposed method includes changing of fuel rate depending on power by metering out delivery of fuel into manifolds of coaxially installed pilot and main burners of burner assemblies with preliminary mixing of fuel and air. Burner assemblies are installed in two tiers, and fuel is delivered into burners of both tiers. At starting fuel is fed into manifold of pilot burners of outer tier and before idling, into manifold of pilot, burners of inner tier. At idling amount of fuel fed into pilot burners of outer and inner tiers is maintained equal. Then fuel delivery into pilot burners of outer and inner tiers is increased. Prior to operation under no-load conditions fuel is fed to main burners of outer and inner tiers. In the range from no-load to rated load, fuel delivery into main burners is increased with simultaneously decreasing relative portion of fuel fed through pilot burners. Invention provides reduction of content of nitrogen oxides NOxin exhaust gases of gas-turbine plant.
EFFECT: provision of stable burning of lean mixtures under any operating conditions.
4 cl, 2 dwg
FIELD: gas-turbine engines.
SUBSTANCE: proposed fuel-air burner has fuel injector in the form of body with fuel feed and spray holes as well as axial- and tangential-flow air swirlers, air flow regulator disposed between rear side of injector body and inlet end of axial-flow swirler that forms slit duct together with its inlet end. Axial- and tangential-flow air swirlers are made in the form of open-end channels accommodating blades and each is provided with converging-diverging nozzle having internal and external channel walls. External channel wall of converging part of axial-flow swirler nozzle has curvature inverse relative to internal channel wall of tangential-flow swirler nozzle. Diverging part of axial-flow swirler is made in the form of cone whose vertex is disposed upstream of nozzle critical section. Angle between burner axis and generating line of cone is 30 to 90 deg. Critical section of axial-flow swirler converging-diverging nozzle is disposed upstream of point of intersection between external channel wall and fuel spray cone generating line.
EFFECT: reduced emission of pollutants in exhaust gases, improved starting characteristics and fuel economic efficiency, enhanced reliability of combustion chamber.
1 cl, 2 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: fuel systems.
SUBSTANCE: the fuel-injection nozzle for a turbo-machine combustion chamber outfitted with two fuel-injection nozzle units has the first fuel-supply tube, connected to which is an annular nozzle end for injection of primary fuel into the combustion chamber, the second fuel-supply tube that envelops the mentioned first tube, and connected to which is a cylindrical extension piece for injection of secondary fuel into this combustion chamber. The extension piece has an annular groove, whose diameter exceeds the diameter of the mentioned second fuel supply tube and runs over its entire length. The third tube is provided that envelop the second tube, an connected to which is a tubular separating component introduced in the mentioned annular groove of the cylindrical extension piece in such a way that two annular cavities are formed, in which the cooling agent can circulate up to the end of the fuel-injection nozzle within 360 degrees in the whole cross-section of the mentioned cavities.
EFFECT: provided protection of the fuel systems, prevented clogging of the fuel-injection nozzles with coke due to effective cooling without considerable variations of the nozzle overall dimensions.
8 cl, 3 dwg
FIELD: fuel systems.
SUBSTANCE: the device for supply of fuel to the combustion chamber has at least one main nozzle and one preliminary-injection nozzle, pump, the first actuator valve installed in the first pipe-line connected to the preliminary-injection nozzle, the second actuator valve used for control of fuel consumption in the secondary pipe-line connected to the preliminary-injection nozzle through the first actuator valve rated at a lower consumption rate. The first pipe-line is also connected to the main nozzle for control of consumption of fuel supplied to the nozzle by the first actuator valve, provision is made for a direction- selecting valve installed past the first valve, and an intermediate line connecting the first and second lines that are used for fuel supply to the main nozzle and/or to the preliminary-injection nozzle.
EFFECT: provided stable fuel supply to the combustion chamber.
8 cl, 2 dwg
FIELD: continuous combustion chambers using liquid or gas fuel.
SUBSTANCE: fuel nozzle comprises first valve that closes when the pressure of inflowing fuel reaches a given value and second batching valve mounted at the outlet of the first valve, which is opened under the action of the second given value of fuel pressure. The second valve is open when the pressure increases so that to provide the inflow of fuel to the consumers. The batched fuel flow rate is a function of the flowing sections of the openings made at the level of the second valve. The nozzle is additionally provided with means for individual adjusting of the second threshold value of pressure made so that to provided the uniform injection of fuel to the combustion chamber.
EFFECT: expanded functional capabilities.
4 cl, 6 dwg
FIELD: continuous combustion chambers.
SUBSTANCE: combustion chamber comprises hollow cylindrical housing whose wall receive scroll and air radial swirlers with blades that provide swirling in opposite directions, shells, bushings mounted for permitting movement in radial direction, branch pipe, swirling chambers, and nozzle. Each combined nozzle has centrifugal nozzle whose outer side is in a contact with inner side of the bushing and jet nozzle with cylindrical housing mounted coaxially in the inner space of the branch pipe between the outer wall of the housing of the jet nozzle and inner wall of the branch pipe. The outlet section of the housing of the jet nozzle is bent to the passage of the scroll spiral of the radial swirler. The outlet section of the jet nozzle is parallel to the wall of the inlet section of the branch pipe and is at a distance of 0.8-1.2 of the diameter of the jet nozzle housing from it.
EFFECT: reduced hydraulic drag and oxides emission.
FIELD: engine engineering.
SUBSTANCE: method comprises filling with solder the radial spaces made in the ring nozzle tip provided with the first nozzle openings for injecting primary fuel and in the cylindrical nozzle that embraces the ring nozzle tip and has second nozzle openings for injecting secondary fuel, setting the ring nozzle tip inside the cylindrical nozzle, mounting both of the members on the first fuel supply pipe for primary fuel and second fuel supply pipe for secondary fuel that embraces the first pipe and on the outer wall of the fuel nozzle, and setting the nozzle spryer assembled into the chamber where it is heated to provide adhesion of the members with solder.
EFFECT: expanded functional capabilities and eased assembling.
6 cl, 7 dwg
FIELD: gas-turbine engine engineering.
SUBSTANCE: ring combustion chamber comprises fire tube and vortex burners arranged over periphery of its face and made of fuel-air scroll and air swirlers with outlet conical branch pipe having cylindrical section. The shell is secured to the face coaxially to each branch pipe defining a ring space. The outer side of the end cylindrical section or inner side of the shell located above it is provided with longitudinal ribs distributed uniformly over periphery and defining insulated passages. The through openings connected with the ring space are made in the face of the fire tube under the shell.
EFFECT: enhanced reliability and expanded functional capabilities.
2 cl, 2 dwg
FIELD: gas-turbine engine engineering.
SUBSTANCE: method comprises separating the fuel supply through small fuel nozzle from that through high-flow rate nozzle, with controllable fuel supply realized directly in the device. The device comprises outer housing, high-flow rate nozzle made of outer housing of the small fuel nozzle and secured to it, piston-slide valve, and spring, interposed between the outer housings of the device and high-flow rate nozzles provided with the passages for fuel supply. The fuel supply is controller by opening passages for supplying fuel to the small nozzle and closing the passages for supplying fuel to the high-flow rate nozzle. When the pressure of fuel increases, the passages for supplying fuel to the high-flow rate nozzle are opened, and the passages for supplying fuel to the small nozzle are simultaneously closed.
EFFECT: enhanced efficiency.
2 cl, 5 dwg