Annular combustion chamber of a gas turbine engine
Annular combustion chamber of a gas turbine engine includes a housing and a fixed fuel manifold with nozzles made in the form of two shells forming the channels of the first and second stages. Each of the channels is in communication with the channel of the two-stage nozzle. The covers are placed coaxially. The inner casing is made in the form of two interconnected side walls and the base, forming one piece with the nozzle body. The outer casing is made in the form of a cover connected to the base. This embodiment of the device prevents the formation of coke in the channel of the first cascade of the fuel manifold and the fuel elements of the nozzles of the first stage, which allows to increase the service life of the combustion chamber. 4 C.p. f-crystals, 4 Il. The invention relates to the field of aircraft engine industry, namely the design of the fuel manifold of the combustion chamber GTE.Known annular combustion chamber of a gas-turbine engine comprising a housing and a fixed fuel manifold with injectors .Of the known devices is closest to the invention is annular combustion chamber of a gas-turbine engine comprising a housing and a fixed fuel manifold with nozzles made in view of the crimson two-stage injector .A disadvantage of the known devices is the formation of coke in the channel of the first cascade of the fuel manifold and nozzles. This is due to the large heating the hydrocarbon fuel and its thermal decomposition when blowing air with a high temperature at the inlet into the combustion chamber.Coking of the fuel leads to an increase in the hydraulic resistance of the collector, the deterioration of the start-up and other operational characteristics of the combustion chamber GTE.Object of the invention is to prevent the formation of coke in the channels of the first stage fuel manifold and nozzles of the first stage.This task is solved in that the annular combustion chamber of a gas-turbine engine comprising a housing and a fixed fuel manifold with nozzles made in the form of two shells forming the channels of the first and second stages, each of which is communicated with the corresponding channel of the two-stage nozzles, shrouds installed coaxially, while the inner casing is made in the form of two interconnected side walls and the base, forming one piece with the nozzle body, and an outer casing in the form of a cover connected to the base.This embodiment of the device before the pout cascade by cooling the fuel channel of the second cascade and lack of contact with the stream of hot air entering the combustion chamber.In Fig.1 shows a longitudinal section of an annular combustion chamber GTE;in Fig.2, 3, 4 - embodiments of the fuel manifold of the combustion chamber.Annular combustor includes a housing 1 and a fixed fuel manifold with 2 nozzles 3.In case 4 injectors provided with channels 5 and 6 of the first and second stages. Fuel collector 2 made in the form of inner and outer housings 7 and 8 installed coaxially.The inner casing 7 made in the form of two interconnected by welding the side walls 9 and the base 10, forming one piece with the housing 4 of the nozzle 3 and forming the channel 11 of the first cascade is provided with a channel 5 of the first stage nozzle. The outer casing 8 of the fuel reservoir 2 made in the form of caps connected by welding with the base 10 and forming the channel 12 of the second cascade, communicated with the channel 6 of the second stage nozzle 3.The inner casing 7 may be made in the form of a curved shell 13 (Fig.2) or rectangular shell 14 (Fig.3) attached by welding to the base 10.The fuel manifold 2 may be equipped with a screen 15 (Fig.3) covering an outer casing 8 forming with it an air cavity 16 and serves to reduce heating fuel channel 11 Pervov the t to be filled with insulating material to further reduce fuel heating in the channels 11, 12 first and second stages of the fuel reservoir 2 (Fig.4).When the engine is running the fuel flows into the channel 11 of the first stage fuel manifold 2, and then into channel 5 of the first stage nozzle connected to the nozzle 17, through which the fuel is injected into the combustion zone. Then the fuel flows into the channel 12 of the second cascade of the fuel manifold 2, passes into the channel 6 of the second stage nozzle connected to a nozzle 18 through which fuel is injected into the combustion zone.The proposed device provides cooling the fuel channel of the second cascade and prevents contact of the structural elements at the entrance to the combustion chamber with a stream of hot air, which prevents the formation of coke in the channel of the first cascade of the fuel manifold and the fuel elements of the nozzles of the first stage.The proposed design allows to make the channels of the first and second stages of the fuel manifold of the combustion chamber by turning with subsequent grinding of surfaces with high purity, which further reduces the formation of coke. In addition, the reduced number of joints, which increases the reliability of the collector.The invention allows to improve operational performance and increase re 29.07.68.2. “The construction and design of aircraft gas turbine engines” under the General editorship of Dr technology. Sciences D. C. Hanina, M., "engineering", 1989, page 420.
Claims1. Annular combustion chamber of a gas turbine engine, comprising a housing and a fixed fuel manifold with nozzles made in the form of two shells forming the channels of the first and second stages, each of which is communicated with the corresponding channel of the two-stage injector, characterized in that the covers are placed coaxially, while the inner casing is made in the form of two interconnected side walls and the base, forming one piece with the nozzle body, and an outer casing in the form of a cover connected to the base.2. Annular combustion chamber under item 1, characterized in that the inner casing is made in the form of a curved shell attached to the base of the fuel manifold.3. Annular combustion chamber under item 1, characterized in that the inner casing is made in the form of a rectangular shell attached to the base of the fuel manifold.4. Annular combustion chamber according to any one of paragraphs.1-3, characterized in that the fuel reservoir is equipped with teplosernaya on p. 4, characterized in that the cavity between the outer shell and the heat-shielding screen filled with insulating material.
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