Fuel tube for burner

FIELD: heating.

SUBSTANCE: fuel tube for a burner, and namely for a gas turbine burner, includes an end that has a surface for nozzles, as well as at least two fuel nozzles. The surface for the nozzles is equipped with splines between the fuel nozzles and is made in the form of an annular conical surface. The splines pass through the above surface perpendicular to the circumferential direction of the annular surface. The end is made in the form of a flattened cone. The side surface of the flattened cone forms the surface for the nozzles.

EFFECT: invention is aimed at increasing the nozzle service life.

7 cl, 3 dwg

 

The present invention relates to a fuel tube, for example, for a burner of a gas turbine, in particular the fuel tube for liquid fuel.

Such fuel tubes are used, for example, burners, which can operate on both liquid and gaseous fuels. Typically, the tube is designed for operation on liquid fuel, for example oil. In this case, the oil flows through the tube and at its end through the oil nozzle enters the combustion chamber. After exiting the nozzle, the oil is burned in the combustion chamber, which served well as compressed air. On the contrary, the gaseous fuel is often served through the nozzle in the inlet air channel surrounding the nozzle tube, and there is mixed with the compressed air before the mixture will enter the combustion chamber.

When operating on gaseous fuel, the end of the tube because of the proximity of the flame, as a rule, is heated to high temperatures in the range up to about 1000C. These high temperatures can lead to coking residue of liquid fuel in the fuel tube. Therefore, before switching to liquid fuel, as a rule, cleaning of the fuel passages in the fuel tube cooling water to blur possible deposits. However, the cooling water temperature is about 25C, which can lead to heat stroke in grief is it the fuel tube. Moreover, the region of the nozzles are formed of high temperature gradients, so that at the end of the tube may experience high thermal stress. Due to the repeated occurrence of such thermal stresses in the area of the nozzles can cause cracks, which reduces the number of starts and thus the service life of the fuel injector.

US 2006/0027232 A1 (IPC F23Q 9/00, 2006) discloses a fuel tube with the slots.

EP 1760403 A2 (IPC F23D 11/38, 2007) discloses a fuel injector for a gas turbine.

US 2001/0042798 A1 (IPC WV 1/14, 2001, the nearest equivalent) discloses a fuel tube with the end that has the surface under the nozzle with two fuel injectors, and the surface under the nozzle between a fuel injector provided with slots.

In this regard, the present invention is the creation of a fuel tube for use in a burner, in particular a burner of a gas turbine, which will help to overcome the mentioned disadvantages. Another object of the invention is the creation of a burner, in particular a burner of a gas turbine.

The first task is solved by means of the fuel tube to the burner, in particular for a gas turbine, characterized by signs of paragraph 1 of the claims, the second task is solved by means of the burner, in particular a burner of a gas turbine, characterized by the signs of the paragraph is 7 claims. The dependent claims disclose preferred embodiments of the invention.

The fuel tube to the burner, in particular for a gas turbine, includes an end that has a surface under the nozzle, at least two fuel injectors. The surface under the nozzle between a fuel injector provided with slots. It can be formed, in particular, in the form of an annular surface, approximately in the form of a conical annular surface, and the slots pass through it perpendicular to the direction of the perimeter of the annular surface.

The slots in the under surface of the nozzle allows, thanks to the free deformation of the end to reduce thermal stresses in the end, so that thermal gradient is less than the load of the fuel tube. The slots do not have any significant aerodynamic effect on the air flowing along the fuel pipe or fuel through the fuel injector is injected into the air stream. The slots also means only very minor modification of the fuel tube, which can be implemented with very little cost. Therefore, the existing fuel tube can dooblodates with little cost, thereby increasing the possible number of runs and the life of this fuel tube.

In the end, could the t being provided with channels for cooling air, which pass between the fuel injectors below the surface under the nozzle. For example, using compressed air passing through the channels for the cooling air may at the time of operation of the burner to cool the end of the fuel tube to keep the temperature of the end at a low level, and thus further reduce the occurrence of thermal stresses during flushing of the fuel tube. In this case, the slots ideally extend from the under surface of the nozzle to the corresponding channel for the cooling medium. In other words, the slots form a carrying hole from the surface under the nozzle to the channel for the cooling medium. Such an embodiment provides a particularly high elasticity corresponding area of the material to reduce thermal stresses.

If the annular surface presents a conical annular surface, the end of the fuel tube may be in the form of a truncated cone. In this case, the side surface of the truncated cone forms a surface under the nozzle and the channels for the cooling medium are outlet openings open toward the overlying surface of a truncated cone. Alternatively, or in addition to the mentioned output holes around the fuel injectors on a circle can be executed bandwidth holes, which canadameds the supply of air are in fluidic connection. The compressed air discharged through these openings, in this case, can be used for cooling the ends of the tube, particularly in the area of the nozzles, which are subject to leaching. If there are access holes between the carrying holes adjacent fuel burners may be located, in particular, respectively one slot.

Proposed according to the invention the burner, which, in particular, can be a burner of a gas turbine equipped with a proposed according to the invention the fuel tube. Thus the fuel tube can be used for the supply of liquid fuel, and in addition to the fuel tube can be installed fuel injector for a gaseous fuel.

Application of the proposed according to the invention the fuel tubes in the burner leads due to the increased durability of the fuel tube to the fact that may increase the maintenance interval, which reduces operating costs.

The present invention is illustrated by drawings, which presents the following:

figure 1 is a fragment of the burner, proposed according to the invention, in section;

figure 2 is a perspective view of the end of the nozzle tube, proposed according to the invention the burner of figure 1;

figure 3 - front side end of figure 2.

As the preferred option negotiation is proposed according to the invention the burner shown in figure 1, the burner of the gas turbine. It has a channel 3 for the air supply, limited mainly having the form of a cylinder wall 1, in the center of which passes the fuel pipe 5. At the end of the fuel tube are located fuel nozzle 7 for supplying fuel into the air, announced on channel 3 for the supply of air. In this embodiment, the fuel pipe 5 shows a tube for supplying a liquid fuel.

In addition to the fuel tube burner contains a second system 9 for supplying a fuel, which has an axial input 11 through which bypassed the fuel pipe 5, so that from the system 9 for supplying a fuel is only the tail section 13 of the fuel tube 5. System 9 for supplying a fuel connected with the blades, creating turbulence, which are at the end of the system 9 for supplying a fuel, located downstream, and extend through the channel 3 for the supply of air. Using channels 17 for supplying fuel to the fuel, in this example, the gaseous fuel is supplied to the vanes 15, which creates turbulence, whence it through the nozzle holes 19 is injected into the air flowing through the channel 3 for the supply of air.

In the case shown in figure 1 burner talking about the so-called "Dual Fuel " Brenner", i.e. the burner which can operate on a gaseous fuel and liquid fuel. However, the invention can also be implemented in the framework of the burner, through which the supply of fuel, and through the fuel pipe respectively supplied fuel in the same state of aggregation, i.e. for example in the framework of the burner, through which the supply of fuel, and through the fuel tube, respectively, is supplied with gaseous fuel. For example, in this case, the fuel pipe can be used as a pilot burner.

Perspective view of the end section 13 of the fuel tube 5 shown in figure 2. Figure 3 also shows the front view of the end portion in the direction of the eyes along the axial direction of the fuel pipe 5.

With reference to figures 1 to 3, the end section 13 is described in more detail. The tail section 13 includes mainly having a cylindrical section 20, adjacent has basically the shape of a truncated cone end 21. On the lateral surface 23 having the shape of a truncated cone end 21 with a uniform distribution in the direction of the perimeter there are three fuel injector 7, as, in particular, can be seen in figure 3. Note that the end with three of the fuel injectors is only the preferred embodiment of, and possibly more or fewer fuel injectors or other distribution nozzles on the side.

For cooling the end 21 has a channel 25 for cooling air, which flow into the Central hole 27. They are there where the overlying surface of a truncated cone. Channels 25 for cooling air supplied through the supply hole 29 having a cylindrical section 20 of the end portion 13 of the nozzle tube 5. During burner operation part of the air flowing through the channel 3 for the supply of air through the feed holes 29 enters the channels 25 for the cooling air. This air has a temperature lower than the temperature of the end 21. However, the end 21 when using gas depicts the burner through the flame in the combustion chamber, heated to a temperature of from about 800 to 1000C.

When the mode of operation on Gaza, in which gaseous fuel is supplied through the system 9 for supplying a fuel, it is necessary to switch the mode of operation on liquid fuel, wherein fuel flows through the fuel pipe, cleaning the fuel passages 31 and the fuel injectors 7 fuel tube 5 to prevent coking. This washing is usually done with water that has a temperature of about 25C. Due to the high difference in temperature of the wash water with one hand and the end 21 on the other hand in the end there are thermal voltage, which in a certain way should be reduced. To make possible a certain reduction of thermal stresses, the side surface 23 to the NCA 21, forming the surface under the nozzle, provided with slots 33. In this embodiment, the slots 33 extend through the side surface 23 to channel 25 for cooling air, so that when the burner cooling air can escape through the slots 33 to block them from receiving hot gaseous products of combustion.

In this embodiment, the slots 33 in addition extends to the feed holes 29. But they can be located only on the side surface 23 of a truncated cone, so that no section of the slot does not pass through the shaped cylinder portion 20.

The slots 33 in this embodiment are respectively the middle between two of the fuel injectors 7. Depending on hydrodynamic data in the region of the end (for example, taking into account the turbulence created by the swirl), however, the slots 33 may be shifted clockwise or counterclockwise. It is also possible to provide several slots, if they extend only through the side surface 23 of the truncated cone 21, but not across having the form of a cylinder section 20. Becoming possible through the slots 33, the deformation of the side surface 23 of a truncated cone in the area of the channels 25 for cooling air in this case makes it possible to reduce thermal stresses arising during% the CCA leaching.

In this embodiment, the around the fuel injectors, also available as an option bandwidth holes 30 extending into the channels 25 for cooling air and which make possible the passage of the cooling medium. As a result of this can be achieved particularly effective cooling of the material of the end of the tube in the area subject to the flushing nozzle holes 7, which reduces thermal shock when washing and thus decrease also be reduced thermal stress.

The presence of the slots 33 in the fuel tube is proposed according to the invention the burner allows the preferred way of reducing thermal stress during flushing of the fuel tube of the wash water, thus not adversely impact the slots on aerodynamics at the end of the fuel tube. Improved reduction of thermal stress increases the service life of the fuel tube. Forming slots in the existing fuel tubes without slots can be realized without large costs, so that existing fuel tube can be converted with little cost.

1. Fuel tube (5) for the burner, in particular for a gas turbine containing end (21), which has a surface (23) under the nozzle, and at least two that is cast nozzle (7), moreover, the surface under the nozzle provided with slots (33) between the fuel injector, characterized in that the surface under the nozzle is made in the form of a conical annular surface (23) and the slots (33) pass through it perpendicular to the district towards the annular surface (23)and the end (21) is made in the form of a truncated cone, with the side surface (23) of the truncated cone forms a surface under the nozzle.

2. The fuel tube according to claim 1, characterized in that the end (21) provided with channels (25) for cooling air, which pass between the fuel injectors (7) below the surface (23) under the nozzle, and the slots (33) extends from the surface (23) under the nozzle to the corresponding channel (25) for cooling air.

3. The fuel tube according to claim 2, characterized in that the channels (25) for cooling air are, at least, the holes (27) in the direction of the overlying surface of a truncated cone.

4. The fuel tube according to claim 2 or 3, characterized in that around the fuel injectors (7) in a circle throughput openings (30), which are in fluidic connection with the channel (25) for cooling air.

5. The fuel tube according to claim 4, characterized in that the bandwidth between the holes (30) adjacent the fuel injectors (7) is accordingly one slot (33).

6. Burner, the particular burner of a gas turbine, containing fuel pipe (5) according to any one of claims 1 to 5.

7. Burner according to claim 6, in which the fuel tube (5) is designed for supplying a liquid fuel and includes fuel injectors (19) for gaseous fuels.



 

Same patents:

FIELD: power industry.

SUBSTANCE: method of burner use, comprising an axis and at least one jet nozzle is proposed. One jet nozzle includes centre axis, exit and wall facing to the burner axis in the radial direction starting from the centre axle. The mass flow of fluid medium including fuel, flows through at least one jet nozzle to its outlet. At outlet of jet nozzle between the mass flow of liquid medium activating the fuel and wall facing to burner axis, air film or inert gas is created due to the fact that air or inert gas is injected along the wall facing towards the burner axis at least into one jet nozzle. Another object of the present invention is burner, comprising axis and at least one jet nozzle. One jet nozzle includes centre axis and wall portion extending around the centre axis in the angular range maximum from -135 to +135, and at least from -15 to +15 relative to the radial connecting line between the burner axis and central axis. Exceptionally wall portion extending around the centre axis in the angular range of maximum from -135 to +135 and at least from -15 to +15, includes at least one flow channel for supplying air or inert gas inflowing to jet nozzle. Gas turbine comprising one burner described above is also a subject of invention.

EFFECT: invention permits to optimise the use of air films or films of inert gas for operation of jet burner.

16 cl, 13 dwg

FIELD: power industry.

SUBSTANCE: invention relates to power industry. Burner facility (20) for furnace device for burning liquid fuel mediums and/or inert materials, in particular of liquid fuel and/or furnace gas, besides the following is provided for each fuel type and/or inert substance: at least one mean (1, 2, 8, 9, 12, 13, 16) for supplying medium, mean (3, 4) for supplying air and mean for mixing the medium with air, designed as a stationary blade creating a twist (6, 7), which are formed in the walls of connected metal body of burner, wherein at least one mean (9, 13, 16) for supplying the medium is separated from adjacent zones of burner body along the corresponding separating wall by means of at least one intermediate cavity (33, 43 ) made in the form of recess, so that heat exchange between adjacent zones of the burner body, in particular between the adjacent means (9, 13, 16) for supplying medium is reduced in the zones made in the form of recess of intermediate cavity (33, 43). At least two means (9, 13, 16) for supplying medium are formed as separate attached to each other modular blocks (30, 40, 50) which are connected to each other via the connecting mean next but one, located at least unilaterally contact stud (32, 42) of cross-sectional surface intended for this purpose, wherein the contact stud (32, 42) at least partially covers the intermediate cavity (33, 43) designed in the form of recess.

EFFECT: invention permits to improve the operational reliability of the burner.

13 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: injector unit of gas-turbine engine combustion chamber includes a plate of annular shape with injector modules installed on it in several rows, and a primary fuel collector connected to the plate, collector cavity being connected to fuel channels with injector modules. Injector modules are installed with register ledges inserted into the blind holes made in the plate and provided with mixing chambers of frustum-of-a-cone shape. All the injector modules have central fuel channel. Tangential air swirlers are made between the housing and the central body in the form of inclined blades. The central fuel channel is made blind with inserted tangential holes. Injector modules in rows are installed on the plate in staggered order.

EFFECT: improving fuel combustion completion at all the modes, reducing harmful emissions and providing uniform temperature field at combustion chamber outlet.

5 dwg

FIELD: engines and pumps.

SUBSTANCE: injector unit of gas-turbine engine combustion chamber includes a plate of annular shape with injector modules installed on it in several rows containing fuel and air channels, and a fuel collector connected to the plate, collector cavity being connected to fuel channels with injector modules. Over three concentric rows of injector modules are installed, the modules are installed with register ledge inserted into blind hole made in the plate. The plate is designed convex towards air flow.

EFFECT: invention is meant for improvement of fuel combustion completion, reduction of harmful emissions at all the modes and provision of uniform temperature field at combustion chamber outlet in a circumferential direction at all the modes.

4 cl, 6 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine combustion chamber incorporates deflector secured at combustion chamber bottom wall. It has opening to fit fuel-air mix feeder in place. Said deflector has opening mating that on combustion chamber bottom wall and having circular cylindrical section of fastening to said wall. Said cylindrical part has transverse groove interacting with metal case crosswise teeth engaged with said wall and centering bowl. One of bowl ends is secured at said housing. Said centering bowl includes cylindrical part arranged with clearance inside deflector cylindrical section even at cold combustion chamber. Said clearance can be decreased and even eliminated at the chamber operating chambers.

EFFECT: longer life.

7 cl, 7 dwg

FIELD: power engineering.

SUBSTANCE: front device of a firetube of a circular combustion chamber comprises a circular head with external and internal fuel headers and air figured windows for air supply into the primary zone of combustion, which are made on the circular head between the headers, concentrically and evenly arranged along the circumference in one row, with central holes and stands of burner fixation to the circular head. Along the circumference of the external fuel header there are nozzles of gas supply arranged evenly into the internal cavity of the external header. In the stands there are through channels of gas supply to burners, which via burners connect to each other cavities of external and internal fuel headers. To supply gas to the burners, there are additional channels arranged evenly at two sides, both at the side of the external and the internal fuel headers, in the links between air figured windows, and these channels connect to each other the cavity of the internal fuel header with the external one, with the area of the channel cross section, which is more or equal to the area of the cross section of the channel made in stands. The quantity of channels made in the links is equal to the quantity of channels made in the stands.

EFFECT: reduction of circumferential unevenness of temperature field with exclusion of local combustion zones with high temperature downstream a front device.

2 cl, 1 dwg

FIELD: power engineering.

SUBSTANCE: gas turbine engine (GTE) combustion chamber comprises a body, a flame tube, which has outer and inner walls, and a board of circular shape with nozzle modules installed on it and the main fuel header connected with the board, the cavity of which is connected by fuel channels with nozzle modules, inner and outer bodies. The number of nozzle modules is made as multiple to four. Nozzle modules are installed in two rows: inner and outer. Additionally there are two fuel headers: inner and outer, The cavity of the outer header is connected by fuel channels with each nozzle module via one in the outer row of nozzle modules. The cavity of the inner header is connected with each nozzle module via one in the inner row. The main fuel header is connected with remaining nozzle modules of both rows. Between the board and the outer and inner walls of the flame tube there are accordingly installed outer and inner facilities for supply and swirling of cooling air with the possibility to supply air at sharp angle to the axis of the flame tube, comprising blades installed at the angle to the axis of the combustion chamber. On the walls of the flame tube along the circumference there are "pockets" installed, which are made in the form of hollow streamlined profiles directed towards the axis of the flame tube.

EFFECT: increased completeness of fuel combustion and reduced emission of hazardous substances at all modes, and provision of even temperature field at the outlet of combustion chamber along circumference at all modes.

7 cl, 11 dwg

FIELD: power engineering.

SUBSTANCE: gas turbine engine (GTE) combustion chamber comprising a body, a flame tube, which has outer and inner walls, and a board of circular shape with nozzle modules installed on it and the main fuel header connected with the board, the cavity of which is connected by fuel channels with nozzle modules, inner and outer bodies. The number of nozzle modules is made as multiple to four. Nozzle modules are installed in two rows: inner and outer. Additionally there are two fuel headers: inner and outer, The cavity of the outer header is connected by fuel channels with each nozzle module via one in the outer row of nozzle modules. The cavity of the inner header is connected with each nozzle module via one in the inner row. The main fuel header is connected with remaining nozzle modules of both rows. Between the board and the outer and inner walls of the flame tube there are accordingly installed outer and inner facilities for supply and swirling of cooling air with the possibility to supply air at sharp angle to the axis of the flame tube, which connects the middle of the board and the middle of the output section of the flame tube.

EFFECT: increased completeness of fuel combustion and reduced emission of hazardous substances at all modes, and provision of even temperature field at the outlet of combustion chamber along circumference at all modes.

6 cl, 10 dwg

FIELD: power engineering.

SUBSTANCE: gas turbine engine (GTE) combustion chamber comprises a body, a flame tube, which has outer and inner walls, and a board of circular shape with nozzle modules installed on it and the main fuel header connected with the board, the cavity of which is connected by fuel channels with nozzle modules, inner and outer bodies. The number of nozzle modules is made as multiple to four. Nozzle modules are installed in two rows: inner and outer. Additionally there are two fuel headers: inner and outer, The cavity of the outer header is connected by fuel channels with each nozzle module via one in the outer row of nozzle modules. The cavity of the inner header is connected with each nozzle module via one in the inner row. The main fuel header is connected with remaining nozzle modules of both rows. Between the board and the outer and inner walls of the flame tube there are accordingly installed outer and inner facilities for supply and swirling of cooling air with the possibility to supply air at sharp angle to the axis of the flame tube, which connects the middle of the board and the middle of the output section of the flame tube.

EFFECT: increased completeness of fuel combustion and reduced emission of hazardous substances at all modes, and provision of even temperature field at the outlet of combustion chamber along circumference at all modes.

5 cl, 10 dwg

FIELD: power engineering.

SUBSTANCE: gas turbine engine (GTE) combustion chamber comprises a body, a flame tube, which has outer and inner walls, and a board of circular shape with nozzle modules installed on it and the main fuel header connected with the board, the cavity of which is connected by fuel channels with nozzle modules, inner and outer bodies, inner and outer jackets installed with a gap relative to the inner and outer bodies. The number of nozzle modules is made as multiple to four. Nozzle modules are installed in two rows: inner and outer. Additionally there are two fuel headers: inner and outer, The cavity of the outer header is connected by fuel channels with each nozzle module via one in the outer row of nozzle modules. The cavity of the inner header is connected with each nozzle module via one in the inner row. The main fuel header is connected with remaining nozzle modules of both rows. Between the board and the outer and inner walls of the flame tube there are accordingly installed outer and inner facilities for supply and swirling of cooling air with the possibility to supply air at sharp angle to the axis of the flame tube, comprising blades installed at the angle to the axis of the combustion chamber. On the walls of the flame tube along the circumference there are "pockets" installed, which are made in the form of hollow streamlined profiles directed towards the axis of the flame tube. Holes are made in the outer and inner jackets in the rear part along the flow.

EFFECT: increased completeness of fuel combustion and reduced emission of hazardous substances at all modes, and provision of even temperature field at the outlet of combustion chamber along circumference at all modes, the axis of the nozzle module.

8 cl, 13 dwg

FIELD: machine building.

SUBSTANCE: burner for burning the gaseous and/or liquid fuel comprises full cylindrical body 3, air duct 6 connected with it with an air supply regulator and nosepieces 1 arranged in them for feeding gas and/or nozzle 2 for feeding liquid fuel. Installed in air duct 6 are distribution plates 10 of different length parallel to the axis of body 3 and to each other in such a way that the height of plates 10 decreases in the direction towards air supply regulator, multisectional gate 7 when some edges of plates 10 divide the inlet port of body 3 into parts and the other edges of plates 10 are bent towards gate 7.

EFFECT: increasing efficiency of adjustment of air consumption arriving for combustion, decreasing its resistance during motion and increasing its uniform distribution over the entire flame body volume ensuring a stable and reliable burning by the same.

2 cl, 2 dwg

FIELD: power industry.

SUBSTANCE: invention relates to power industry. Burner facility (20) for furnace device for burning liquid fuel mediums and/or inert materials, in particular of liquid fuel and/or furnace gas, besides the following is provided for each fuel type and/or inert substance: at least one mean (1, 2, 8, 9, 12, 13, 16) for supplying medium, mean (3, 4) for supplying air and mean for mixing the medium with air, designed as a stationary blade creating a twist (6, 7), which are formed in the walls of connected metal body of burner, wherein at least one mean (9, 13, 16) for supplying the medium is separated from adjacent zones of burner body along the corresponding separating wall by means of at least one intermediate cavity (33, 43 ) made in the form of recess, so that heat exchange between adjacent zones of the burner body, in particular between the adjacent means (9, 13, 16) for supplying medium is reduced in the zones made in the form of recess of intermediate cavity (33, 43). At least two means (9, 13, 16) for supplying medium are formed as separate attached to each other modular blocks (30, 40, 50) which are connected to each other via the connecting mean next but one, located at least unilaterally contact stud (32, 42) of cross-sectional surface intended for this purpose, wherein the contact stud (32, 42) at least partially covers the intermediate cavity (33, 43) designed in the form of recess.

EFFECT: invention permits to improve the operational reliability of the burner.

13 cl, 5 dwg

FIELD: power industry.

SUBSTANCE: fuel combustion method involves supply of air flow, supply of fuel flow of the first type via the first channel, ignition of the flow of fuel of the first type so that the first flame is obtained, as well as supply of flow of fuel of the second type via the second annular channel located almost coaxially to the first one and having a variety of side jet outlets in the outlet part to obtain the second flame. The first channel is located in the second channel; supply of air flows and all types of fuel is adjustable; supply of fuel flow of the first type is performed at almost stopped air flow, and supply of fuel flow of the second type is performed via the second channel to obtain the second flame, thus gradually increasing its pressure till it is equal to or is more than pressure of flow of fuel of the first type, at subsequent increase of supplied air flow preventing lift-off of the first and/or the second flames.

EFFECT: invention allows effective combustion of associated petroleum gas of any composition and reducing emissions of hazardous substances to atmosphere.

13 cl, 1 dwg, 1 tbl

Oil-gas burner // 2518759

FIELD: energy industry.

SUBSTANCE: burner for combustion of gaseous and/or liquid fuel is used in steam and hot water boilers. The burner consists of a main burner with a unit for supplying gas fuel and with a device for supplying liquid fuel, a pilot burner and an ignition burner. The pilot burner with forced air supply is located in the housing of the main burner. When operating on the gas fuel the pilot burner is used to control the main burner flame. The sensor of the main burner flame, operating with the fuel oil, the photosensor is used. The ignition burner located in the housing of the main burner is used to ignite the flame of the pilot burner and the flame of the main burner, operating both on the gaseous and liquid fuels.

EFFECT: creation of a safe burner for high power boilers.

4 cl, 4 dwg

FIELD: heating.

SUBSTANCE: invention relates to heat engineering and namely to combined pulverised-coal burners and can be used in power engineering industry on pulverised-coal boilers with supply to burners of high-concentration pulverised coal (HCPC) via pressure pipes. A combined pulverised-coal (PC) burner includes an air duct, channels for PC-and-air mixture (PCAM) and secondary air, a HCPC supply pipe and a HCPC dispersion device. Secondary air and PCAM channels are arranged in a projection onto a vertical plane above each other with a gap between them, and in PCAM channel there is the HCPC supply pipe, after the end face of which there installed is the HCPC dispersion device consisting of a horizontal splitter of an angular type and a vertical splitter arranged after it, the side walls of which divide PCAM channel into two outlet sections of a vertical slit type; besides, external vertical walls of PCAM channel are convergent throughout the burner length till the vertex of the vertical splitter, and after it - convergent in a horizontal plate so that height increases. The secondary air channel is equipped with an atomiser pipe for installation of an oil atomiser and gaseous fuel supply tubes.

EFFECT: reduction of hazardous NOx emissions and fuel incomplete combustion.

2 cl, 2 dwg

Packaged burner // 2494312

FIELD: power industry.

SUBSTANCE: creation of efficient boiler houses using burners without power consumption from external sources is performed by using some part of heat energy of fuel combustion products for generation of electric energy by means of an electric generator. For that purpose, air blower to combustion zone is made in the form of turbine compressor 7, the shaft of which is kinematically connected to electric generator 9 and fuel pump 3; in gas duct at combustion chamber 1 outlet there installed is heat exchanger 10, the inlet and outlet of the heat receiving path of which are connected to compressor outlet and turbine inlet of turbine compressor 7; and turbine outlet is connected to the inlet of the air path to combustion chamber 4.

EFFECT: improving efficiency of small boiler houses.

1 dwg

FIELD: power engineering.

SUBSTANCE: device for realisation of combustion comprises a refractory unit having at least two channels, including the upper channel and the lower channel, a board for burner fixation, and a burner body, besides, the burner body has an inlet for air for combustion, an inlet for oxygen, an inlet for liquid fuel and an inlet for gaseous fuel, besides, the body of the burner is made as capable of mixing of air supplied to the specified inlet for air and oxygen supplied to the specified inlet for oxygen, to create an oxidant and to forward the oxidant to both of the specified at least two channels in the refractory unit, and besides, the burner body is arranged as capable of sending liquid fuel to one of the specified at least two channels and gaseous fuel to another one, from specified at least two channels. The device additionally comprises air supply for combustion, and besides, the air supply for combustion may be adjusted relative to the burner body. The device additionally comprises air supply for combustion connected as capable of disconnection with the inlet for combustion air, oxygen supply connected with the possibility of disconnection with the inlet for oxygen, supply of liquid fuel connected with the possibility of disconnection with liquid fuel inlet, and supply of gaseous fuel connected with the possibility of disconnection with an inlet for gaseous fuel. The inlet for liquid fuel communicates by fluid medium with a tuyere arranged inside one of the upper channel and the lower channel formed in the refractory unit. The device additionally comprises an inlet for spray gas designed to introduce air into liquid fuel.

EFFECT: multi-mode functioning of a burner due to usage of multiple oxidants and multiple sources of fuel.

29 cl, 12 dwg

Burner device // 2491478

FIELD: power engineering.

SUBSTANCE: burner device of a plant for combustion of fluid types of fuel comprises a burner bushing (18), at least one channel (3, 4) for air supply, and at least one channel (9, 13, 19, 23) for supply of the appropriate fuel, at the same time at least one channel (9, 13, 19, 23) for fuel supply is arranged at least partially inside the burner bushing (18), at least in one channel (23) for fuel supply there is a screening wall (30), which is at the distance from the wall (21) of the channel (23) for fuel supply, besides, between the wall (21) of the channel (23) for fuel supply and the screening wall (30) there is an intermediate space (38), which does not relate to the path of the fuel flow passing via the channel (23) for fuel supply, at the same time the screening wall (30) is formed with a case (30) inserted into the channel (23) for fuel supply and equipped with at least one radial positioning facility (33, 35) providing for the distance (s) between the case (30) and the wall (21) of the channel (23) for fuel supply, at the same time at least one radial positioning facility (33, 35) of the case (30) is arranged in the form of at least one circularly arranged positioning ledge (33,35) protruding radially outside.

EFFECT: invention makes it possible to reduce stresses in a burner bushing from received heat.

6 cl, 5 dwg

Burner // 2488041

FIELD: power engineering.

SUBSTANCE: burner comprises vertical slot converging ducts separated with a partition and having vertical confusor-forming walls, roof and hearth slabs, vertical slot windows for inlet and outlet of secondary air and fuel and air mixture, vertical planes of symmetry, a vertical prismatic prechamber with roof and hearth slabs, a front wall, having a vertical-slot window of exhaust combined with the window of fuel and air mixture inlet in the converging duct, with the vertical plane of symmetry combined with the vertical plane of symmetry of the same converging duct, with the rear wall, parallel between each other and the vertical plane of symmetry of the prechamber with side walls, windows and connected to them nozzles of primary air flows with internal vertical planes of symmetry, nozzles of liquid fuel and gas inlet with axes of symmetry. Nozzles for liquid fuel inlet are arranged on the rear wall of the prechamber in vertical rows, and their axes are directed along the vertical plane of symmetry of the prechamber, windows and nozzles for inlet of primary air flows have vertical slot shape and are arranged symmetrically on the side walls of the prechamber, vertical planes of symmetry of the nozzles form with the vertical plane of symmetry and side walls of the prechamber the angle 30-85, roof and hearth slabs of the prechamber and roof and hearth slabs of the convergent fuel and air duct are arranged in common locating horizontal planes of roof and hearth slabs.

EFFECT: invention makes it possible to reduce fuel underburning and concentration of nitrogen oxides in combustion products.

1 cl, 3 dwg

FIELD: power engineering.

SUBSTANCE: flange (20) of a burner support, comprising a surface, which potentially contacts with a flammable material, it comprises the main body (21) made of the main material and an insert (22) made of the corrosion-resistant material, besides, the insert (22) has the outer surface (25) and at least one hole (23), and in the main body (21) there is a hole (26) with the inner surface (24), at the same time the insert (22) is located in the hole (26) of the main body (21) so that the inner surface (24) of the hole (26) in the main body (21) is rigidly connected with the outer surface (25) of the insert (22). The main material for the flange is steel.

EFFECT: invention makes it possible to prevent formation of iron sulfide deposits and to increase operational reliability of a burner.

9 cl, 6 dwg

FIELD: machine building.

SUBSTANCE: atomiser of, primarily, liquid-propellant rocket engine comprises casing with fuel feed adapter. Note here that the latter is arranged inside said case at pylons while its channel is connected with fuel chamber via bores made in said pylons. In includes the sleeve arranged with ring clearance at said case to make circular gaseous oxidiser channel connected with oxidiser chamber via channels in the casing between its wall and fuel feed pylons. Adapter channel is closed at its inlet while its inner chamber communicates with ring gap between adapter and said sleeve via radial bores made at outlet. Note here that sleeve outlet has stepped expansion with its chamber connected with fuel chamber via tangential channels made in sleeve wall. In compliance with one version, sleeve outlet expansion accommodated hollow cylinder making an extension of sleeve inner channel to make ring gap with ring expansion outlet cylindrical surface. Chamber of said dap communicates via tangential bores with fuel chamber. Axial bore is made at adapter end. Stepped expansion is made at adapter outlet. Note here that bores equally spaced in circle and at angle to adapter axis are made at adapter end. Stepped expansion is made at adapter outlet. Note here that bores equally spaced in circle and at angle to adapter axis are made at adapter end located in the plane of sleeve tangential bores.

EFFECT: higher completeness combustion and better mix formation.

5 cl, 11 dwg

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