RU2670483C1 - Combustion chamber of a gas turbine engine - Google Patents

Abstract

FIELD: motors and pumps.SUBSTANCE: combustion chamber of a gas turbine engine contains a flame chamber with holes, nozzles, a fuel line and electrodes connected by high-voltage insulated wires, and a heating chamber. Heating chamber is connected by a channel with a flame chamber. Inside the heating chamber is mounted a heating element and ceramic partitions with holes with the possibility of circulation and heating of air flows. Inside the heating element, chambers are made with the possibility of heating the fuel to a gaseous state. Inputs of the chambers are connected by pipes to the fuel line, and the outlets are connected by pipes with horizontal nozzles mounted in the channel. Channel is equipped with vertical nozzles connected to the fuel line. Inside the horizontal and vertical nozzles placed electrodes. Blade is installed inside the channel. Heating chamber is made in the form of a housing where inside the rings of different diameters are mounted. High-temperature heat-insulating layer is mounted on the inner surfaces of the heating chamber and the channel.EFFECT: invention is aimed to increase the combustion of fuel.8 cl, 5 dwg

Description

The invention relates to the field of engineering, namely to gas turbine installations of internal combustion [F02C 5/02, F02C 3/14].

The prior art CAMERA COMBUSTION GAS TURBINE ENGINE WITH A CONSTANT VOLUME OF COMBUSTION FUEL [patent RU 150723 U1, Pub .: 02.20.2015], comprising a housing installed in it a rotating fire tube, characterized in that the flame tube consists at least of two closed cavities directed along the longitudinal axis of the gas turbine engine, each of which is formed by two adjacent blades, its hub and outer shell, to which the ends of the blades are rigidly attached, as well as the input and intermediate disks, where the disk is equipped with a ignition unit that includes at least two spark plugs, two on-duty flare units made in the form of tubes connecting two adjacent closed cavities, and fuel injection nozzles are installed on the fuel supply unit, and there is a rigidly behind the intermediate disc gas jet turbine associated with a flame tube, behind which an output disk is installed with holes that are offset from the holes of the input and intermediate disks by an angle corresponding to the angle of installation of the gas blades jet turbine, and behind the output disk there is an expansion chamber, purge housings and a purge pipe with inlet openings connecting the internal cavity of the purge housings with the cavity of the purge pipe where a movable central body is placed on the purge pipe forming the output channel device with the outlet part of the combustion chamber casing which is a supersonic nozzle.

The disadvantage of analog is low efficiency, due to the lack of effective interaction of air jets and fuel and inefficient use of the volume of the flame tube near the nozzles of the nozzle.

Also known is a ring-mounted combustion chamber of a gas-turbine engine with a rotating nozzle [Patent RU 117581 U1, Publ. 27.06.2012], which includes a housing inside which a flame tube is installed with an outer and an inner wall, with a hole on at least one of the walls, and rotating nozzle mounted on a shaft, characterized in that a nozzle is mounted in the hole, the axis of which is perpendicular to the plane of the centers of the output sections of the nozzles of the nozzles, and the distance from the plane of the centers of the output sections nozzle nozzles to the center of the outlet section of the nozzle are not more than three diameters of the outlet section of the nozzle, and the distance from the center of the outlet section of the nozzle to the inner surface of the heat pipe wall is not less than half the diameter of the outlet section of the nozzle.

The disadvantage of the analog is the lack of quick start and low combustion efficiency of the fuel on the engine start modes at negative air and fuel temperatures.

The closest in technical essence is the COMBUSTION CHAMBER of a GAS TURBINE ENGINE [Patent RU 2620187 C1, Publ .: 23.05.2017], comprising an outer casing, a flame tube, a nozzle plate and nozzles, an annular manifold mounted in the front cavity on the nozzle plate to which fuel line, characterized in that inside the annular collector there are concentrically made two annular electrodes connected by insulated high-voltage wires to a high-voltage unit.

The main technical problem of the prototype is incomplete combustion of fuel, due to the lack of preliminary preparation of air for the fuel mixture, which leads to increased fuel consumption and reduced engine power.

The objective of the invention is to eliminate the disadvantages of the prototype.

The technical result of the invention is to increase the combustion of fuel.

This technical result is achieved due to the fact that the combustion chamber of a gas turbine engine containing a heat chamber with holes, nozzles, fuel lines and electrodes connected by high-voltage insulated wires, characterized in that it additionally contains a heating chamber connected by a channel with the fire chamber, a heating element is mounted inside the heating chamber element and ceramic partitions with holes with the possibility of circulation and heating of the air flow inside the heating element chambers with the possibility of heating the fuel to a gaseous state, the chambers are connected by pipes to the fuel line, and the outlets are connected by pipes with horizontal nozzles mounted in the channel, vertical nozzles are mounted in the channel connected to the fuel line, while electrodes are mounted inside the horizontal and vertical nozzles, a guide blade is mounted inside the channel, and the heat chamber is made in the form of a casing, inside which rings of different diameters are mounted, on the inner surfaces The high-temperature heat-insulating layer is mounted to the awnings of the heating chamber and the channel.

In particular, stiffening ribs are mounted inside the channel.

In particular, the heating element is designed in the form of a cermet tube with a nichrome spiral mounted on the outer surface.

In particular, the tubes connecting the chambers to the fuel line are made in the form of capillary.

In particular, the horizontal and vertical nozzles are connected to the chambers and the fuel line by fuel tubes.

In particular, fuel filters in the form of bulkheads with small-diameter holes are mounted in the injectors.

In particular, fuel filters are made of metal, ceramic or polymer materials.

In particular, the rings of the flame chamber are made of high-temperature, refractory metal.

Brief description of the drawings.

FIG. 1. shows a front view of the combustion chamber in longitudinal section.

FIG. 2 shows a side view of the engine, heating chambers in cross section.

FIG. H shows a view of the channel in cross section.

FIG. 4 shows a side view of the engine, flame chambers, generator and turbine axes in cross section.

FIG. 5 shows a frontal view of a turbojet engine in longitudinal section.

In the figures: 1 - heating chamber, 2 - heat chamber, 3 - channel, 4 - metal-ceramic tube, 5 - ceramic partitions, 6 - nichrome spiral, 7 - holes, 8 - cameras, 9 - capillary tubes, 10 - fuel tubes , 11 - horizontal nozzles, 12 - vertical nozzles, 13 - fuel cleaning filters, 14 - electrodes, 15 - high-voltage cable, 16 - air tubes, 17 - paddle, 18 - stiffening ribs, 19 - high-temperature heat-insulating layer, 20 - heat body chambers, 21 - rings, 22 - holes of the flame chamber, 23 - electro rter converter, 24 - external shaft, 25 - primary circuit compressor, 26 - high pressure turbine of the primary circuit, 27 - alternator, 28 - high pressure turbine of the second circuit, 29 - secondary compressor shaft, 30 - secondary circuit compressor, 31 - low pressure turbine, 32 - third loop turbine, 33 - third loop shaft, 34 - cooling compressor, 35 - third loop low pressure turbine, 36 - generator, 37 - internal turbine blades, 38 - internal evaporators.

The implementation of the invention.

The combustion chamber of a gas turbine engine contains a heating chamber 1 (see Fig. 1) and a heat chamber 2 interconnected by a channel 3. Inside the heating chamber 1 a cermet tube 4 and ceramic partitions 5 are mounted. A nichrome spiral 6 is mounted on the surface of the cermet tube 4 (see .Fig.2). In ceramic partitions 5, holes 7 are made around the entire circumference of the heating chamber 1 for hot air to circulate inside the heating chamber 1. Inside the cermet tube 4 are oblong shaped chambers 8 connected by capillary tubes 9 to the aircraft side rail (not shown).

The chambers 8 are connected by fuel tubes 10 with horizontal nozzles 11 mounted inside channel 3 (see Fig. 3). Inside the channel, vertical nozzles 12 are mounted. Inside the horizontal 11 and vertical 12 nozzles, fuel cleaning filters 13 are installed, made in the form of metal, ceramic or polymer partitions with holes and firing electrodes 14 connected to each other and to a common electrical network with a high-voltage cable 15. Vertical nozzles 12 are connected to the fuel line of the board by airplanes fuel tubes 10.

To the heating chamber 1 mounted air tubes 16 high pressure.

Inside the channel 3, a blade 17 is mounted and stiffening ribs 18 are made, connecting the heating chamber 1 with the flame chamber 2.

The inner surface of the heating chamber 1 and the channel 3 is covered with a high-temperature insulating layer 19.

The fire chamber 2 consists of a housing 20 (see Fig. 4) within which rings 21 of different diameters of high-temperature, refractory metal are mounted. In the housing 20 of the heat chamber 2, holes 22 are made to discharge cooled air from the engine turbines and to cool the inner rings 21.

Gas turbine three-circuit engine with two high-pressure turbines works as follows.

From the onboard battery serves the voltage on the electric starter-Converter 23 (see Fig.5).

The electric starter-converter 23 begins to operate in the electric motor mode and its anchor drives the outer shaft 24 on which the first-circuit compressor 25, the high-pressure turbine of the primary circuit 26 and the alternator rotor 27 are mounted. When the high-pressure turbine of the primary circuit 26 rotates, the pumps are turned on fuel line (not shown in the figures). The cable 15 serves the voltage from the high voltage converter (not shown in the figures) to the combustion chamber on the electrodes 14 of the horizontal 11 and 12 vertical nozzles. The electrodes 14 are ignited, heated to a state of steam in the chambers 8 of the cermet tube 4, the fuel mixture entering the horizontal nozzles 11 of the chambers 8 through the fuel tubes 10 and the fuel entering the vertical nozzles 12 from the fuel line. The burning flame is directed by the blade 17 into the combustion chamber 3. From the flame chamber 3, the burning flame is directed to the blades of the high-pressure turbine of the primary circuit 26 and, due to the kinetic energy of the flame, the outer shaft 24 is rotated.

From the outer shaft 24, rotational energy is transmitted to the compressor of the first circuit 25 and the rotor of the alternator 27, thereby increasing the speed of the high pressure turbine of the first circuit 26, the temperature increases, after which the high pressure turbine of the second circuit 28 and the shaft 29 are mounted on which the compressor is mounted second circuit 30 and the low pressure turbine 31.

During the set of revolutions of high-pressure turbines of the first 26 and second 28, as well as compressors of the first 25 and second 30 circuits, the turbine of the third circuit 32 begins to rotate, which rotates the shaft of the third circuit 33 with the mounted compressors 34 of the high-pressure turbines 26 and 28 and a low pressure turbine of the third circuit 35.

After a set of speeds on the turbines of the first 26, second 26 and third 32 circuits from the alternator 27, the voltage is applied to the switch, where they disconnect the supply of voltage to the electric starter 23. The alternating voltage from the electric starter-converter 23 is converted by the generator 36 and fed first to the stabilizer unit (on Figures not shown), and then into the general on-board power supply network.

From the common on-board power supply network, an alternating voltage is supplied to the nichrome spiral 6 mounted on the cermet tube 4 of the heating chamber 1. At the same time, the high-pressure line enters the heating chamber 1 through the tubes 16 and serves air where it is heated and fed through the blade 17 in the channel 3 to the fire chamber 2, while the burning flame from the horizontal 11 and vertical 12 nozzles increases the air temperature and thereby increases the temperature in the fire chamber 2, while the high-temperature insulating layer 19 is made On the inner surfaces of the heating chamber 1 and channel 3, the temperature inside the heating chamber 1 and channel 3 is maintained, while through the holes 22 in the housing 20 of the fire chamber 2, the air 26 cooled from the turbines of the first 26, second 28 and third 32 circuits is pumped and cooled by their surfaces rings 21. At the same time, in each of the high-pressure turbines 26 and 28 internal blades 37 are mounted (see Fig. 2), which take cooled air from internal evaporators 38.

The claimed technical result is an increase in fuel combustion due to the fact that the air and fuel injected under high pressure, fed into the heating chamber 1, are heated by a nichrome spiral 6 and fed to channel 3 with horizontal 11 and vertical 12 nozzles, where fuel enters through fuel tubes 10 from the fuel line, are mixed, forming a highly efficient fuel mixture that is ignited by the electrodes 14, while the rate of evaporation of the fuel mixture and the speed of the processes leading to ignition combustion increases and accordingly increases the proportion of fuel burned, which leads ultimately to an increase in the gas temperature at the outlet of the flame chamber 2 and an increase in kinetic energy directed at the turbine rotational movement of the first 26 and second 28 circuit. This high-temperature insulating layer 19 mounted on the inner surface of the heating chamber 1 and channel 3, maintains the temperature of the air inside the heating chamber 1.

Claims (8)

1. Combustion chamber of a gas turbine engine containing a heat chamber with holes, nozzles, fuel lines and electrodes connected by high-voltage insulated wires, characterized in that it also contains a heating chamber connected by a channel with a fire chamber, a heating element and ceramic baffles with holes are mounted inside the heating chamber with the possibility of circulation and heating of the air flow inside the heating element is made of the camera with the possibility of heating the fuel to the gaseous composition The inlets of the chambers are connected by pipes to the fuel line, and the outlets are connected by pipes with horizontal nozzles mounted in the channel, vertical nozzles are mounted in the channel connected to the fuel line, while inside the horizontal and vertical nozzles the electrodes are mounted, inside the channel the guide vanes are mounted, and the heat chamber is made in the form of a housing inside which rings of different diameters are mounted, a high-temperature is mounted on the inner surfaces of the heating chamber and channel thermal insulation layer. 2. The combustion chamber according to claim 1, characterized in that the ribs are mounted inside the channel. 3. The combustion chamber according to claim 1, characterized in that the heating element is designed as a metal-ceramic tube with a nichrome spiral mounted on the outer surface. 4. The combustion chamber according to claim 1, characterized in that the tube connecting the chambers to the fuel line is made in the form of capillary. 5. The combustion chamber according to claim 1, characterized in that the horizontal and vertical nozzles are connected to the chambers and the fuel line by fuel tubes. 6. The combustion chamber according to claim 1, characterized in that in the nozzles are mounted fuel filters in the form of partitions with holes of small diameter. 7. The combustion chamber according to claim 6, characterized in that the fuel filters are made of metal, ceramic or polymeric materials. 8. The combustion chamber according to claim 1, characterized in that the rings of the flame chamber are made of high-temperature, refractory metal.

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