Device to control low emission combustion chamber of gas turbine

FIELD: engines and pumps.

SUBSTANCE: device to control a low emission combustion chamber of a gas turbine, specifically of gas turbine assemblies, comprises case with channels supplying primary and secondary air into a flame tube of the combustion chamber and with a channel for mixing basic fuel with primary air, wherein this channel an axial swirler and synchronous adjustment devices to control consumption of primary and secondary air are installed. The devices of synchronous adjustment of consumption of primary and secondary air are installed in corresponding channels of the case and interconnected with each other so that at an increase or decrease of primary air consumption correspondently causes an increase or decrease of secondary air consumption. An initial portion of the flame tube is made as an intake diffuser. A device to control consumption of primary air is made as a flame stabilizer and installed with a possibility to axial displacement in intake diffuser of the flame tube; at that it is connected to the regulator of basic fuel to maintain ratio of surplus air in the primary air supply channel and in the mixing channel constant or close to constant within ranges from 1.7 to 2.5. The blades of the axial swirler are arranged concentric at an angle to its axis bigger or equal to 30°. A nozzle with a critical section is installed at the outlet from the combustion chamber.

EFFECT: device allows to extend the range of stable operation and adjustment of a combustion chamber, to reduce a possibility of self excited oscillation of pressure in a combustion chamber and to reduce harmful exhaust.

4 cl, 1 dwg

 

The invention relates to the field of energy, primarily to control devices of low-emission combustion chambers of gas turbine installations, using as fuel natural gas or liquid hydrocarbon fuel, and can be used any environmentally friendly heat and power devices for the regulation and production of high temperature and/or high-energy working medium in all processes.

A device for regulating the low emission combustor of a gas turbine, comprising a housing with a channel for mixing fuel with the primary air, which has an axial swirler, and with the input channels of the primary and secondary air into the flame tube of the combustion chamber, the units of flow control primary and secondary air, posted by s the corresponding channels of the body (see U.S. patent No. 6056538, IPC F23C 9/00, publ. 02.05.2000, author Horst Buchner (Horst Büchner) and others). The main disadvantage of the proposed design is, as the author points out, the complexity of the control devices and the high cost of regulation of low-emission combustor of a gas turbine, enabling them to work together in the required synchronized sequence.

A device for regulating nishimaki the Noah hackers combustion gas turbine, comprising a housing with a channel for mixing fuel with the primary air, which has an axial swirler, and with the input channels of the primary and secondary air into the flame tube of the combustion chamber, the units of flow control primary and secondary air, placed in the proper channels of the body (see U.S. patent No. 6732527, IPC F02C 7/00, publ. 11.05.2004, author Christopher Freeman (Christopfer Freeman and others). This device also has a complex structure and high cost.

A device for regulating the low emission combustor of a gas turbine, comprising a housing with a channel for mixing fuel with the primary air, which has an axial swirler, and c the input channels of the primary and secondary air into the flame tube of the combustion chamber, the units synchronous flow control primary and secondary air, placed in the proper channels of the housing and interconnected so that when increasing or decreasing flow of primary air is correspondingly decrease or increase the flow of secondary air (see published application EP No. 0088933, IPC F23R 3/26, publ. 21.09.83, author Bernard Becker (Bernard Becker)). The main disadvantage of the known device is the combination in one unit mixer primary air with the fuel and flame stabilizer made in the ideal ring, placed around the exit of the combustion chamber holes from the mixer primary air with the fuel and creates a recirculation zone. Despite what the author says about low emissions of hydrocarbons and oxides of nitrogen while reducing the likelihood of self-oscillations of the pressure of combustion, emission, emissions and spontaneous fluctuations in pressure cannot be reduced below a certain limit, which is determined by the penetration separate randomly generated medium and large drops of fuel into the combustion chamber due to the presence of a direct, open and unhindered passage in her. Set in the beginning of channel mixing fuel swirl will not be able these drops completely broken, because it doesn't have them direct mechanical contact, because is located in the air flow to injector fuel supply, and only one swirling the flow of air will not be able these drops be crushed to the required size to provide complete evaporation. The removal of individual droplets in the combustion chamber will result in the possibility of fluctuations in the concentration of fuel (local enrichment of the mixture) and consequently to the emergence of the possibility of self-oscillations of the pressure and velocity of flame propagation in the combustion chamber. Also excessive local enrichment of the mixture should lead to the oyavleniy incompletely burnt hydrocarbons and carbon monoxide, and excessive temperature rise will lead to the emergence of nitrogen oxides. Located concentric with the channel mixing stabilizer of the flame creates a great area toroidal zone back flow of high temperature gases, which will heat the wall of the flame tube, and through them the channel mixing, and lead to the possibility of leakage of flame at him. It is obvious that emissions of hydrocarbons and oxides of nitrogen are possible, due to the removal of combustion products from areas fluctating impact of these drops, as they will not be the optimum composition of the mixture, far from stoichiometric or lean fuel that will experience high temperature, sufficient to cause nitrogen oxides, and increased fuel concentration will lead to carbon monoxide. It should also be noted that not modifiable section of the channel mixing when changing the flow of primary air through it will change the quality of fuel atomization and lower consumption of air in it, change the conditions of mixing and will create favorable conditions for direct removal of most large drops of fuel into the combustion chamber, which should further worsen the conditions of combustion.

In addition it should be noted that when used as fuel, combustible gases, such as methane, propanebutane the mixture of the sludge is natural gas homogenization of the mixture is low due to inefficient mixing of the gases, which occurs only through layer-by-layer turbulence in the swirling flow, and the short time allotted for this process, the effectiveness of diffusive mixing is insufficient. The introduction of said gases after the swirl will lead to the practical impossibility of the formation of a homogeneous mixture, as for thorough mixing of fuel gas and oxidant, for example air, required multiple turbulization of the flow or long-term mutual diffusion of the molecules, due to the lack of funds further turbulence and small time spent in short channel mixing cannot occur.

The specified device for regulating the low emission combustor of a gas turbine has the highest number of matching common with the proposed device characteristics and solve the same technical problem. For this reason it is chosen as a prototype.

The objectives of the present proposed invention are:

expansion of the range of stable operation and regulation of the combustion chamber;

the reduced probability of self-oscillations of the pressure in the combustion chamber and reduces harmful emissions;

extending functionality through use as fuel in addition to liquid hydrocarbons and combustible gases.

<> performance engines and installations with the proposed regulation;

reducing emissions of harmful emissions and improving the environmental performance of engines and installations with the proposed regulation;

increase the durability and lifetime of the device.

These technical problems are solved in that the device for regulating the low emission combustor of a gas turbine includes a housing with a channel mixing of the primary fuel with the primary air, which has an axial swirler, and with the input channels of the primary and secondary air into the flame tube of the combustion chamber, the units synchronous flow control primary and secondary air, placed in the proper channels of the housing and interconnected so that when increasing or decreasing flow of primary air is correspondingly decrease or increase the flow of secondary air. In this initial part of the flame tube made in the form of the input cone. Assembly regulating the flow of primary air is made in the form of a flame stabilizer mounted on the axis of the combustion chamber with the possibility of axial movement in the inlet cone of the flame tube, and is connected to the flow regulator of the primary fuel to maintain excess factor in is zdwhu in the feed channel of the primary air channel mixing constant or close to it ranging from 1.7 to 2.5. The blades of the axial swirler mounted concentrically at an angle to its axis greater than or equal to 30°. At the exit of the combustion chamber is installed nozzle critical section.

In the device for regulation of low-emission combustor of a gas turbine units control of the primary and secondary air is made with the possibility of simultaneous changes of the squares of the flow areas of the channels of the primary and secondary air, so that their total area of the cross section remains constant or close to it.

This simplifies the design of the control device of low emission combustion chamber and for this reason, increased durability, the resource of his work and operational characteristics owing to simplify maintenance and regulation.

A device for controlling low-emission combustor of a gas turbine, which has the following sizes:

Dto/dkr≥6;

Lto/Dto≥1,8,

where Dtothe diameter of the flame tube of the combustor;

dkr- the diameter of the critical section of the nozzle at the exit of the combustor;

Lto- the length of the combustion chamber is measured from the plane of arrangement of the turbulent edge to the plane of the critical section of the nozzle.

A device for controlling netcoalition the second combustion chamber of a gas turbine contains (as in the prototype) housing with channel mixing of the primary fuel with the primary air, which has an axial swirler, and with the input channels of the primary and secondary air into the flame tube of the combustion chamber, the units synchronous flow control primary and secondary air, placed in the proper channels of the housing and interconnected, so that when you increase or decrease the flow of primary air is correspondingly decrease or increase the flow of secondary air, which reduces the possibility of self-oscillations of pressure and to reduce to some limit harmful emissions. It is quite a large channel length of mixing will allow for high-quality mixing with the change in the flow rate of the air-fuel mixture through him, and, respectively, through the channel of the primary air. Also this will be facilitated by intense swirling flow of fuel-air mixture in the swirl and subsequent turbulization her in the annular gap between the nozzle and the flame stabilizer, increasing with decreasing cross-sectional area of the annular gap and flow of primary air through it.

Due to these reasons multiple turbulization will be most effective for mixing trudnosmyvaemye combustible gas and air, which, after the above-mentioned process will be to create a homogeneous gaseous toplivo susnow mixture for all operating modes of the device. While at low cost the air-fuel mixture a small annular gap between the expanding part of the diffuser and flame stabilizer would facilitate further turbulence in its swirling flow.

The initial part of the flame tube in the form of the input cone and Assembly regulating the flow of primary air in the form of a flame stabilizer, for example, with a mushroom-like shape of its surface, is installed along the axis of the combustion chamber with the possibility of axial movement in the inlet cone of the flame tube, respectively changes in the area of the transverse bore and maintain the excess air coefficient in the feed channel of the primary air channel mixing constant or close to it ranging from 1.7 to 2.5 synchronous fuel management, which allows to reduce the appearance of zones fluctuations of the concentration of the latter, resulting from penetration into the camera combustion with the flow of air-fuel mixture separate drops of liquid not evaporated fuel and therefore to improve the homogenization of this mixture, as all the drops will fall into the zone of influence of heat from the heated reverse current products of combustion front of the flame stabilizer, and, optionally, meeting with the flow, turbulation Savir the holder will break up and evaporate before they reach the combustion zone. The rest of the flame stabilizer (due to intensive cooling of the cold air-fuel mixture and place it outside of the swirl air) will not overheat this mixture in the channel mixing and this will prevent the possibility of leakage of flame. Intensive evaporation of some of the most large drops of fuel will contribute to the reduction of the flow velocity of the mixture due to the gradual increase in cross-sectional area of the flame tube at its inlet diffuser.

The location of the blades of the axial swirl concentric at an angle to its axis greater than or equal to 30° must provide the necessary high spin flow required for complete homogenization of the mixture due to the centrifugal separation of small and medium-sized drops of fuel and drop them by centrifugal forces to the surface of expanding the input cone of the flame tube of the combustion chamber and subsequent complete evaporation.

The axial location of the flame stabilizer will allow you to get the optimal volume of the recirculation zone and reduce heating of the mixture in the channel mixing primary air and fuel that will prevent reverse leakage flame.

Installed at the exit of the combustor nozzle critical section will allow the fully mix the combustion products "poor mixture with secondary air and docility almost all unburned before the hydrocarbons and carbon monoxide. Low fuel concentration with the specified limits of air excess factor from 1.7 to 2.5 in vysokoorganizovannoi mixture (taking into account the previously mentioned phenomena) cannot lead to the appearance of zones of temperature fluctuations above the temperature of the occurrence of nitrogen oxides. This should improve the environmental performance of the installation with a device for regulating the low emission combustor of the gas turbine.

A device for controlling low-emission combustor of a gas turbine has a stabilizer flame, made with two surfaces, one of which is made extending towards the exit of the combustion chamber and terminating at its widest part the turbulent edge, the second is limited to a specified edge and is made with the possibility of formation of a recirculation zone, and the second surface is at least one nozzle supply pilot fuel. This part of the set of features can improve the stability of the combustion, since the recirculation zone has a toroidal shape, is located in the Central part of the combustion chamber, has an optimal volume, a small area of the heating surfaces of the combustion chamber from the second surface of the stabilizer flame) and a relatively large surface in contact with cold air-fuel mixture, which helps the camera is lnasty existence toroidal vortex in all operating modes of the device and the combustion chamber, heating them coming into the combustion chamber air-fuel mixture without excessive heat, ignite it, and for that reason improves the stability of its value.

A device for controlling low-emission combustor of a gas turbine, in which the flame stabilizer is made with two surfaces, one of which is made extending towards the exit of the combustion chamber and terminating at its widest part the turbulent edge, the second is limited to a specified edge and is made with the possibility of formation of a recirculation zone, reduces aeroservices resistance of the combustion chamber and device regulation. The location on the second surface in the area of recycling, at least one injector supply pilot fuel allows for start-up and transient conditions in terms of the diffusion combustion is most effective to vaporize the fuel with the hot gases, mixed with excess oxidant in them and completely oxidize when mixed with a stream of secondary air.

Simultaneous change of flow sections of aggregates control the flow of primary and secondary air and primary fuel will allow you to change the heat capacity of the combustion chamber without significant changes of the load on the compressor, as the total flow rate of the supplied air practical and should not be changed. That should lead to stabilization of conditions of work and to reduce the dynamic loads on him in transient conditions when the change of heat capacity of the combustion chamber due to a quantitative increase in the submission of a "lean" mixture at constant quality of its composition, that is, when maintaining the excess air coefficient in the feed channel of the primary air channel mixing constant or close to it ranging from 1.7 to 2.5. This will increase the durability and efficiency of the device and/or includes a gas turbine installation.

A device for controlling low-emission combustor of a gas turbine, in which the flame stabilizer is made with a surface extending in the direction of the outlet of the combustion chamber, will further improve the homogenization of the mixture and prevents penetration accidentally created a large droplets of fuel in the combustion zone, because the largest of these will be at the expense of inertial forces to move rectilinearly, to strike against the inclined to the direction of flow of the expanding surface of the stabilizer flame and break into smaller pieces. Small and medium-sized drops, not evaporated before, due to the effects of centrifugal force of the swirling flow will be imposed in the peripheral zone and to evaporate under the influence of heat from the walls of the flame tube and part of the hundred is ilitator flame.

The location on the second, back to the thread surface of the stabilizer flame after the turbulent edge of the at least one injector supply pilot fuel should increase the stability of combustion at start-up and transient conditions due to the increase in the concentration of fuel in the recirculation zone and the extension of the interval of stable combustion of the mixture under varying combustion conditions.

Therefore, the combination of these features will reduce to the limit accidental penetration of drops of fuel in the combustion of the main mass of the air-fuel mixture and the occurrence in it of zones with variable concentration of fuel, contributing to the development or increase of pressure fluctuations and temperature of combustion. Uniform and stable temperature distribution in the flame tube and the critical nozzle will increase the durability and lifetime operation of all control devices, combustion chamber, gas turbine or the heat consumer and/or other devices, installations or units, including his.

The execution units of the regulation of primary and secondary air with the possibility of simultaneous changes of the squares of the flow areas of the channels of the primary and secondary air, so that their total area of the cross section remains constant, allows the most simply calculated the odds and to organize the process described above, because this option is most easy to determine and/or calculate required for complete combustion of the optimal fuel consumption.

A device for controlling low-emission combustor of a gas turbine, in which the flame tube has mentioned previously, the ratio of sizes, to achieve the optimum ratio of the volume of the combustion air-fuel mixture and the volume of the recirculation zone.

The extension of the control range can be achieved by all of the specified set of features and the described sequence of operation of these units control device, as when standing close to optimal (in terms of harmful emissions), the "poor" mixture heat capacity is regulated by its quantity entering the combustion chamber. The total flow or the air supply to the combustion chamber as a whole remains constant. The dilution of the combustion products of the secondary air and its flow into the combustion chamber allows to maintain the mass flow rate of hot gases leaving the combustion chamber (without propellant)that is close to constant with minimal or optimal losses on aeroservices resistance in it. This increases only the energy saturation of these gases passing through a critical nozzle. This should improve reliably the path and the efficiency of the installation and its regulation.

The drawing shows a section of the combustion chamber and a view of the device for regulation of low-emission combustion chambers.

A device for controlling low-emission combustor of a gas turbine includes a housing 1 with a flame tube 2, equipped with a nozzle 3, channels 4 and 5 respectively supply the primary and secondary air into the flame tube 2 of the combustion chamber and the channel 6 of the mixing of the primary fuel with the primary air, which has an axial swirler 7. Units 8 and 9 synchronous regulation, respectively, of costs of primary and secondary air, placed in the proper channels 4 and 5 of the housing 1 and are interconnected so that when increasing or decreasing flow of primary air is correspondingly decrease or increase the flow of secondary air. Thus the unit controlling the flow of primary air is made in the form of the stabilizer 10 flame that is installed along the axis of the combustion chamber with the possibility of axial movement in the input cone 3 of the flame tube 2 and maintain the excess air coefficient in the channel 4 of the primary air and the channel 6 of the mixing constant or close to it ranging from 1.7 to 2.5. For the most simple design of the control units can be used, for example, mechanical traction and kinematically with them wired is the second flame stabilizer 10, rotary or sliding spool 12 mounted with the possibility of full or partial overlap of channel 5 secondary air and the valve 14 for regulating the flow of fuel.

The initial part of the flame tube made in the form of input of the diffuser 3, gradually widening towards the exit of the combustion gases flow through the nozzle 15. Actuators synchronously control the flame stabilizer 10 and the regulator 13 of the supply of the primary fuel, and also unit 9, made with the spool 12, the regulating channel 5 secondary air can have any other known actuator (hydraulic, pneumatic, electromagnetic or otherwise), providing simultaneous regulation of the supply of the primary fuel and both units air supply mode maintain almost constant total flow rate through the combustion chamber.

To start the combustion chamber, igniting an air-fuel mixture and ignition of the flame on the wall of the flame tube has an igniter 11.

Regulation of the supply of pilot fuel into a zone of recirculation is carried out through the nozzle 21 by means of controller 25.

The blades of the axial swirler 7 is installed in the channel 6 concentric at an angle to its axis greater than or equal to 30°.

At the exit of the combustion chamber is installed nozzle 15 with critical széchenyi the m 16.

A device for controlling low-emission combustor of a gas turbine, in which the flame stabilizer 10 is made with two surfaces, one of which 17 is made of an expanding towards the exit of the combustion chamber and terminating at its widest part the turbulent edge 18 and second 19 is limited to a specified edge and is made with the possibility of formation of a recirculation zone 20, and the second surface 19 is at least one nozzle 21 of the supply of pilot fuel. In the most simple form the second surface 19 may be flat, in another more complex form, it can be run as part veroobrazno surface, contributing to the formation in the zone of recirculation sustainable toroidal vortex and creating the least aeroservices resistance to gas movement in it.

The costs of primary and secondary air are determined by the appropriate changing areas of flow sections of units 8 and 9 of the regulation of the channels 5 and 6 respectively of the primary and secondary air, the sum of the components of a constant or close to this value.

A device for controlling low-emission combustion chambers of gas turbines, which have the following properties:

Dto/dkr≥6;

Lto/Dto≥1,8,

where Dto- diameter Zharov the second pipe of the combustion chamber;

dkr- the diameter of the critical section of the nozzle at the exit of the combustor;

Lto- the length of the combustion chamber, measured from the plane of arrangement of the turbulent edge 18 to the plane of the critical section 16 of the nozzle 15.

A device for controlling low-emission combustor of the gas turbine operates as follows.

When you start pre-cooked in the channel 6 mixing "poor" mixture flows into the combustion chamber and using the controller 25 through the nozzle 21 further enriched in the recirculation zone 20 pilot fuel, then the fuel-air mixture is ignited by the igniter 11, starting the combustion chamber and gas turbine.

Further, the device for regulation of low emission combustion chamber operates as follows. Basic liquid or gaseous fuel is fed into the channel 6 of the mixing of the primary fuel with primary air through nozzles 22 of the supply of the primary fuel, in which it flows through the annular fuel manifold 23 through the valve 14 supply regulator primary fuel 13 from the main fuel line 24. When driving on channel 6 mixing sprayed liquid fuel is vaporized and mixed with the primary air. Not evaporated droplets of fuel are on the vanes of the swirler 14 and shatter when struck on their surface. In twisted is the first stream of small and medium-sized drops are fond of this swirling flow and due to centrifugal forces are discarded (separated) and accumulate in its outer part, where they are under the influence of heat from the hot walls of the inlet of the diffuser 3 and the flame stabilizer 10 has evaporated. The largest drops passing through the blades, due to inertia forces flying in the direction of flow and reach the first extending surface of the stabilizer flame, hit it, split up and smaller droplets, and a pair of evaporated fuel fond of the same swirling flow to the walls of the flame tube, where it is completely vaporized. Vysokomineralizirovannaja "poor" mixture is heated, ignited by the high temperature gases coming from the recirculation zone 20, along the flame tube 2, is steadily lit and burns completely. The admission of secondary air to the combustion zone allows docility (douche) randomly generated carbon monoxide, soot and nedoocenivaete hydrocarbons.

With a smooth change of regime gradually increase the flow rate of primary air and the flow of the primary fuel in the channel 6 of their feeding and mixing. Smooth change their spending will not change the fuel concentration in the air, and all combustion processes will be almost the same as previously described.

With a sharp increase in consumption of primary air due to the inertia of the individual elements of the device, the components of the kinematic chain drive units regulirovanie is, possible additional short-term depletion of the mixture in the feed channel 6 and the mixing of the primary main fuel with the primary air and for this reason possible flameout. To prevent this, in the zone of recirculation is necessary to submit additional number of primary or pilot fuel, which stabilizes the combustion in the area of recycling and will support it in the combustion chamber with additional lean.

When using combustible gases change ring gap will cause further turbulence in the fuel-air mixture in it and will provide high-quality mixing on all modes.

1. A device for controlling low-emission combustor of a gas turbine, comprising a housing with input channels of the primary and secondary air into the flame tube of the combustion chamber and channel mixing of the primary fuel with the primary air, which has an axial swirl, aggregates synchronous flow control primary and secondary air, placed in the proper channels of the housing and interconnected so that when increasing or decreasing flow of primary air is correspondingly decrease or increase the flow of secondary air, characterized in that the initial part of the flame tube is made in the de input of the diffuser, Assembly regulating the flow of primary air is made in the form of a flame stabilizer mounted on the axis of the combustion chamber with the possibility of axial movement in the inlet cone of the flame tube, and is connected to the flow regulator of the primary fuel to maintain the excess air coefficient in the feed channel of the primary air channel mixing constant or close to it ranging from 1.7 to 2.5, the blades of the axial swirler mounted concentrically at an angle to its axis, greater than or equal to 30°and at the exit of the combustion chamber is installed nozzle critical section.

2. A device for controlling low-emission combustor of a gas turbine according to claim 1, wherein the flame stabilizer is made with two surfaces, one of which is made extending towards the exit of the combustion chamber and terminating at its widest part the turbulent edge, the second is limited to a specified edge and is made with the possibility of formation of a recirculation zone, and at least one nozzle supply pilot fuel is located on the second surface.

3. A device for controlling low-emission combustor of a gas turbine according to claim 1, characterized in that the aggregates regulation of primary and secondary air is made with the possibility of simultaneous changes in the area of the flow areas of the channels of the primary and secondary air, so their total area of the cross section remains constant or close to it.

4. A device for controlling low-emission combustor of a gas turbine according to claim 1, characterized in that

Dto/dkr≥6;

Lto/dto≥1,8,

where Dtothe diameter of the flame tube of the combustor;

dkr- the diameter of the critical section of the nozzle at the exit of the combustor;

Lto- the length of the combustion chamber (measured from the plane of arrangement of the turbulent edge to the plane of the critical section of the nozzle).



 

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14 cl, 10 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed combustion chamber comprises housing, fire pipe with combustion and dilution zones, fuel feed system, primary and secondary air flows feed system. The latter comprises the device to act on secondary air flow inside circular channel between combustion chamber and fire pipe walls. Besides, it includes fuel-air mix ignition device. Said device to act on secondary air flow inside circular channel comprises laser radiation source, optical fibre and at least two opposed mirrors arranged inside said channel. One of said mirrors has through bore at focal line. Laser radiation source can excite molecular oxygen to singlet state and is connected via optical fibre with through bore of the mirror.

EFFECT: ruled out carbon monoxide, almost completely, from engine exhaust gases, more complete fuel combustion.

10 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed combustion chamber comprises housing accommodating the perforated fire tube with combustion and dilution zones, fuel feed system, air primary and secondary flow feed system and fuel-air mix ignition system. Airflow feed system incorporates primary airflow controller in primary air channel and secondary airflow controller inside circular channel between combustion chamber walls and fire tube. Said controllers include laser radiation source, laser radiation splitter for primary and secondary airflows controllers. Every said controller incorporates optic fibres with inputs connected to laser radiation splitter. Output of primary airflow controller optic fibre is connected via through hole with primary airflow inlet channel equipped with at least two opposed mirrors. Secondary airflow controller comprises at least two opposed mirrors located inside circular channel, one of the mirrors having a through hole at mirror axis in focal plane. Output of secondary airflow controller optic fibre is connected via mirror through hole with circular channel. Laser source can excite oxygen molecules to metastable singlet states.

EFFECT: higher completeness of combustion and chamber efficiency.

16 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: device to burn fuel in a gas turbine engine comprises outer and inner bodies forming a circular cavity, where fixed and mobile flow separators are installed, forming alternating primary and secondary channels. On the outer body of the circular cavity in each primary channel there are symmetrical rectangular cuts corresponding to its size, with fixed flow separators passing through them. In the end part of the circular cavity there are two rings installed as capable of rotation around the longitudinal axis, the diameter of one of which corresponds to the diameter of the outer body, of the second one - the diameter of the inner body. On the outer ring there are 2N slots, where N - natural even number corresponding to the number of primary channels. In each primary channel there are two plates installed, being made according to the profile of the wing and hingedly fixed on the inner ring, with the possibility of displacement along the longitudinal axis of the engine along the slots on the outer ring and around their central axis. The slot length corresponds to plate travel from minimum to maximum size of the primary channel. In each primary channel there are angular flame stabilisers installed with an opening angle of 55-65 degrees in direction of the flow, which are rigidly fixed on the outer and inner rings as equidistant along the circumference. The point of fixation on the outer ring is between the slots of the appropriate channel.

EFFECT: invention is aimed at expansion of the range of combustion chamber stable operation.

3 dwg

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