Separation method of mixture of liquid and gaseous phases of fuel component of liquid-propellant engine, and device for its implementation

FIELD: engines and pumps.

SUBSTANCE: invention can be used during development of liquid-propellant engines (LPI) for carrier rockets (CR). Method consists in the fact that acceleration pulse is created owing to combustion of fuel components in ignition device (ID) and supply of its combustion products to chamber nozzle. Ignition device is tripped after the required pulse is obtained by the mixture in CR tank. At that, combustion products are supplied to the combustion chamber nozzle together with their ballasting, e.g. with fuel which is first passed through the cooling path of the chamber. The proposed method is implemented in LPI containing combustion chamber with ID, nozzle, turbo-pump unit, automation and control units, which, according to the invention, is equipped with an additional line with the valve for ballasting of ID combustion products, which connects the outlet of the cooling path of combustion chamber to its mixing head.

EFFECT: simplifying the design and reducing power consumption.

3 cl, 1 dwg

 

The invention relates to the field of rocketry and can be used in the development of liquid rocket engines (LRE) for launch vehicles (LV).

One of the problems encountered during the creation of LRE for PH, is the problem of separation of the liquid and gaseous phase components and the deposition of the liquid phase component on a fence device tank in zero gravity, because the flow of the gaseous phase component in pump units significantly affects the working conditions of these units and can lead to their failure.

Currently, to separate fuel tanks, for example, boosters on the phase state (the so-called separation modes) are inertial forces, for which use special nozzles that use to get traction compressed gases from on-Board cylinders or motors running on hypergolic propellant components.

There is a method of separation (separation) of fuel, based on the use of inertial forces (see fundamentals of theory and calculation of liquid-propellant rocket engines, M.: Higher school, 1983, str-485 - a prototype), and a device for its implementation (see fundamentals of theory and calculation of liquid-propellant rocket engines, M.: Higher school, 1983, str - prototype)containing the combustion chamber with the firing device, the nozzle.

A disadvantage of the known technical the definition devices is the high cost of energy on the rotation of the fuel and the complexity of the device.

The aim of the invention is to eliminate these disadvantages, namely to simplify the design and reduce energy consumption.

This goal is achieved by the fact that in the known method of separating a mixture of liquid and gaseous phase of the fuel components in zero gravity, is based on giving a mixture of acceleration, according to the invention the pulse acceleration create by burning fuel components in the firing device (MD) and supply its products of combustion into the nozzle chamber, and disabling the ignition device is carried out after obtaining the mixture in the tank PH is necessary momentum and the flow of products of combustion into the nozzle of the combustion chamber exercise jointly with their ballasting, for example, the fuel, which previously passed through a cooling path of the camera.

The mentioned set of features exhibits new properties, which consists in the fact that due to the burning of the required number of components fuel storage, and supply of products of combustion into the nozzle eliminates the need for special devices for imparting rotational motion of the mixture to be separated.

In addition, the implementation of ballasting products of combustion, in oxygen-hydrogen rocket engine, for example, hydrogen increases their mass, creating more cravings, provides cooling of the combustion chamber and nozzle and snige the temperature of the combustion products.

The proposed method is implemented in a rocket engine containing a combustion chamber with ZU, nozzle, turbopump Assembly, plant automation and control, which according to the invention, equipped with an additional line with valve for ballasting products of combustion ZU connecting the exit of the cooling duct of the combustion chamber with its mixing head.

This set of features exhibits new properties, namely, that due to the presence of bolasterone line with the valve raises the possibility of changing the timeline of the operation of the engine in order to use memory not only for its intended purpose, but also to impart the necessary momentum of the mixture components of the fuel in the tank and their separation (sedimentation) on a fence device.

The proposed device is schematically represented in the drawing, where:

1 - combustion chamber;

2 - cooling path of the combustion chamber;

3 - mixing head;

4 - nozzle;

5 - igniter;

6 - turbopump Assembly;

7 - units of automation and control;

8 - highway fuel;

9 - highway oxidant;

10 - additional line;

11 - valve.

Rocket engine comprises a combustion chamber 1 with a cooling duct 2 and the mixing head 3, a nozzle 4, the ignition device 5 mounted on the camera axis, turbopump unit 6, the units and tomatice and control 7, line 8 fuel and oxidizer 9.

In addition, it is equipped with additional bolasterone highway 10 with valve 11, which connects the exit of the cooling duct 2 of the combustion chamber 1 with its mixing head 3.

The operation of the device is as follows. The components of the fuel in the manner determined by the regular sequence diagram, served in the ignition device 5, where they are burned. The combustion products (high-temperature gases enter the combustion chamber 1 of the engine. Through open valve 11, is included in additional highway 10, on which the fuel (hydrogen) from the cooling tract 2 of the combustion chamber 1 is fed into the mixing head 3, by providing the cooling of the combustion chamber and nozzle, and then through the nozzle enters the combustion chamber 1 where it mixes with the combustion products in the firing device 5, reducing their temperature and increasing their mass. Formed in this way, the mixture flows into the nozzle 4, creating the necessary thrust. Thus the second component of the fuel, such as oxygen, into the combustion chamber 1 is not available. After creating the necessary impulse operation of the firing device 5 is stopped, and the valve 11 closes additional highway 10.

Having obtained the required acceleration, liquid and gaseous phase of the fuel separated, with the liquid phase is deposited on a fence device is TBE tank and fed to the inputs in the fuel pumps LRE, providing a cavitation free operation.

Thus, the use of the present invention will simplify the design and reduce the energy consumption for the separation of liquid and gaseous phases of the fuel components in zero gravity.

1. The method of separation of a mixture of liquid and gaseous phases of a fuel component, is based on giving a mixture of acceleration, characterized in that the pulse speed up create by burning fuel components in the ignition device chamber rocket engine and its supply products of combustion into the nozzle chamber, and disabling the ignition device is carried out after obtaining the necessary momentum.

2. The method according to claim 1, characterized in that the flow of combustion products from the ignition device in the nozzle chamber carry out together with supply to them, for example, the fuel to increase the momentum.

3. Liquid propellant rocket engine containing a combustion chamber of the mixing cylinder, cooling system, ignition device, turbopump Assembly, plant automation and control, characterized in that it is provided with an additional line with a valve connecting the outlet of the cooling duct of the combustion chamber with its mixing head.



 

Same patents:

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry, particularly to liquid propellant rocket engines operated on three fuel components, i.e. cryogenic oxidiser, hydrocarbon fuel and liquid hydrogen. Proposed rocket comprises first- and second-stage rocket units connected in parallel, oxidiser and fuel tanks coupled by power assemblies and equipped with at least one first-stage engine and one second-stage engine. In compliance with this invention, second-stage unit comprises second fuel tank, every second-stage engine incorporates combustion chamber and fuel feed turbopump unit. Proposed engine comprises at least one combustion chamber with jet nozzle, regenerative cooling system, gas generator, and two turbopump units comprising turbine, oxidiser pump and fuel pumps. In compliance with this invention, outlets of all pumps communicate, via gas duct, with gas generator outlet communicates with every combustion chamber. Method of operation of above described engine comprises feeding fuel and oxidiser into gas generator and combustion chamber, igniting them and exhausting combustion products via jet nozzle. In compliance with this invention, first fuel utilised, second fuel is fed into gas generator and combustion chamber. Prior to feeding second fuel, fuel pipelines and nozzle regenerative cooling systems are blown down to remove first fuel residues.

EFFECT: higher thrust-to-weight ratio, improved operating performances.

12 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry, particularly to liquid propellant rocket engines operated on three fuel components, i.e. cryogenic oxidiser, hydrocarbon fuel and liquid hydrogen. Proposed engine comprises at least one combustion chamber with jet nozzle, regenerative cooling system, gas generator, and turbopump unit comprising turbine, oxidiser pump and fuel pumps. It differs from known designs in that said turbopump unit comprises two fuels pumps and two extra fuel pumps designed to operate on first fuel and second fuel. Note here that second fuel pump and additional second fuel pump are arranged below oxidiser pump. Downstream of fuel pumps, first and second fuel valves are arranged connected, via electric line, with synchronisation device. Proposed engine incorporates also control unit connected with aforesaid synchronisation device. Method of operation of above described engine comprises feeding fuel and oxidiser into gas generator and combustion chamber, igniting them and exhausting combustion products via jet nozzle. In compliance with this invention, first fuel utilised, second fuel is fed into gas generator and combustion chamber. Prior to feeding second fuel, fuel pipelines and nozzle regenerative cooling systems are blown down to remove first fuel residues.

EFFECT: improved operating performances of liquid propellant engine in wide range of flight conditions at various altitudes.

5 cl, 3 dwg

Rocket engine unit // 2381378

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry and can be used in designing rocker carrier first stages with multi-tank propellant compartments with wrap-around arrangement. Engine unit comprises multi-tank propellant compartment and fluid propellant rocket engines, every engine being communicated, via feed lines, with adjoining tanks. One of the engines communicates, via feed lines and booster pump units, with all tanks.

EFFECT: synchronised utilisation of propellant components from like tanks without introducing disturbing torques to rocket.

1 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: in method for compensation of differences in physical properties of fuel components based on matching of operation modes of universal liquid-propellant rocket engine supply units, according to invention for generator-free engine with separate turbine pump (TP) during its transfer from hydrogen to liquefied natural gas (LNG) (methane), at first fuel (LNG, methane) flow is increased to required value for provision of reliable cooling of chamber, after cooling prior to fuel supply to turbine of TP its total flow is divided into two parts, one of which is supplied to TP turbine, and the other one is discharged, at that after TP passing, fuel fission process is repeated, at that its one part is sent for combustion in combustion chamber, and the other is discharged or sent for further use. Discharged parts of fuel flow may be used as working fluid, for instance, for steering nozzles, for turbine of engine swinging system, for supercharging of tanks, repeatedly as working fluid of chamber fuel and/or propellant pump. Invention provides for operation of engine both on fuel components "oxygen+hydrogen" and also on fuel "oxygen+liquefied natural gas" (methane).

EFFECT: reduced cost of engine and expanded field of its application.

7 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket-propelled vehicles, particularly, to the gas duct of liquid-propellant rocket engines with after-burning. The aforesaid gas duct comprises the outlet manifold of the main turbo-pump unit, a bent pipeline and a swinging assembly. The aforesaid bent pipeline is coupled with the outlet manifold and the said swinging assembly is linked with the engine chamber. Note here that the aforesaid swinging assembly is furnished with a bi-degree universal joint and the joint of the swinging assembly with the engine chamber and bent pipeline represents a flange coupling incorporating a metal T-shape gasket furnished with a load-bearing ring with two flexible springs provided with mountain-like ledges. Note also that the aforesaid one-piece bent pipeline is made from a heat-resistant nickel-alloy, while the bent pipeline flange represents a load-bearing belt with a developed end face surface for the engine frame support to be attached thereto. The aforesaid T-shape taper gasket springs feature the thickness varying over their length, while their length L-to-mean thickness δ ratio makes L/δ ˜8 to 10 and the angle α of the spring taper surface inclination to the flange coupling axis makes 1.5 to 2.5 degrees. The flexible spring OD including the aforesaid mountain-like ledges exceeds the ID of the flange coupling sealing surfaces by 0.1 to 0.2 mm. All parts of the gas duct are made from the EK-61 heat-resistant nickel alloy. The propose invention allows a higher tightness of the fixed joints and pipelines carrying high-temperature high-pressure oxidising medium.

EFFECT: improved performances due to ease of uncoupling gas duct from engine chamber and bent pipeline.

7 cl, 4 dwg

FIELD: aircraft industry; rocketry.

SUBSTANCE: invention relates to design of liquid-propellant rocket engines. Proposed liquid-propellant rocket engine without afterburning of generator gas contains regenerative cooling chamber 1, turbopump set 2 with gas generator 3 to drive turbine 4, two flow rate controls and two nozzles 9, 10 installed in pressure main lines 11, 12 of pumps of turbopump set 2. Sensing elements of spools 5, 6 of controls communicate through pipelines with inputs of nozzles 9, 10 and their minimum sections. According to invention servo-actuate restrictor 14 of control, playing the part of thrust control, installed in feed main line 12 of one of propellant components into gas generator 3. Restricting element of servo-actuated restrictor 14 communicates through pipeline 21 with pressure main line 12 of pump of said component after nozzle 10, and pipeline 22 delivering second component into gas generator 3 is connected with pressure main line 11 of pump of said component after servo-actuated restrictor 13 of control playing the part of propellant components flow rate ratio control.

EFFECT: improved energy-mass ratios of engine, provision of constant propellant components flow rate through engine and thrust irrespective of ratio of components passing through engine.

1 dwg

FIELD: rocket-space equipment, mainly means and methods for water supply to low-orbital spacecraft.

SUBSTANCE: the offered method provides for use of the energy of formation of the raw material, in particular, of water from the fuel components for increasing the efficiency of the means of its injection into orbit. The offered rocket power plant has a chemical reactor, in which the given product is formed, as well as a heat-exchange unit, in which the heat of the chemical reaction is transferred to the fuel components. The latter results in the growth of the power plant specific impulse. The reaction product is cooled, and a condensate (water) is obtained which is accumulated in the storage tank. The offered rocket may use one of the cleared fuel tanks for accumulation of condensate. The offered transportation system includes the offered rocket, orbital station equipped with a system of water processing to fuel components, and means of delivery of the space vehicle to the station together with the non-filled boosting unit. The offered transportation-fueling station includes also an orbital fueling complex. Space vehicles injected into high-altitude orbits, in particular, into a geostationary orbit, as well as space vehicles returning on the Earth, may be refueled there. At injection of the space vehicle into a geostationary orbit the dependence of the efficiency of injection on the latitude of the cosmodrome is essentially reduced (by 2-3 times).

EFFECT: reduced cost of supply of the orbital stations and cost of injection of the space vehicle into a geostationary orbit, as well as into other trajectories, reduced dependence of the cost of injection of the space vehicle into a geostationary orbit on the latitude of the cosmodrome.

19 cl, 3 dwg

FIELD: rocketry and space engineering; rocket pod engine plants.

SUBSTANCE: proposed engine plant includes propeller tanks (oxidizer tank and fuel tank), cruise engine, actuating members and high-pressure gas bottles. Oxidizer and fuel tanks are filled with low-boiling and high-boiling components, respectively. High-pressure gas bottles are installed in oxidizer tank. Rocket pod engine plant is provided with pipe lines mounted on fuel tank by means of brackets forming heat exchange unit. Pipe line inlets are communicated with outlets of high-pressure gas bottles and their outlets are communicated with actuating members of engine plant.

EFFECT: reduced mass and volume of high-pressure gas bottles and consequently reduced mass of rocket pod.

1 dwg

FIELD: rocket technology; heating gases using heat produced in nuclear fusion.

SUBSTANCE: proposed method is characterized in that gas is introduced in at least one chamber. The latter has wall coated with disintegrating material. This material is exposed to neutron flux to induce disintegration into fragments within chamber. Mentioned wall is cooled down on rear end relative to chamber and mentioned coating. In addition, device implementing this method is proposed. Gas heating device has at least one gas holding chamber. It has wall coated with disintegrating material and facility for exposing disintegrating material to neutron flux so as to induce and emit disintegration fragments within chamber. Device is designed to cool down mentioned wall on rear end of chamber and mentioned coating of disintegrating material. In addition, space engine using mentioned method for gas heating is proposed. This space engine has gas heating device and facility for exhausting hot gas into space to afford thrusting. Alternative way is proposed for gas heating by using nuclear fusion reaction suited to space engines for thrusting.

EFFECT: facilitated procedure of gas heating.

42 cl, 24 dwg

Flameless fuel // 2243149
The invention relates to the field of energy and can be used on different types of transport and heating systems of residential buildings and heating in extreme conditions

Separator // 2386470

FIELD: technological processes.

SUBSTANCE: invention is related to devices for treatment of gas and liquid flows from dispersed particles. Separator comprises body with tangential channel of flow supply, cover with nozzle for treated flow discharge, conical bottom with nozzle for discharge of separated phase, separating element. Body, tangential channel of flow supply and separating element are arranged as a whole from sheet coiled into multi-turn spiral, and a clearance is provided between its turns. Sheet sweep has a complicated shape that includes rectangular part that changes into trapezoidal one, besides sheet sweep is coiled into spiral so that number of spiral turns reduces down to zero. Separating element is arranged along the whole length of body, at the same time its lower part is arranged in the bottom, inlet section of tangential channel is arranged along the whole length of body.

EFFECT: improved efficiency of both gas and liquid flow cleaning independently on speed of its entry into inlet channel, provision of flow entry speed reduction starting from 1 m/s, increased efficiency of flow cleaning from finely dispersed particles (1 mcm), reduced discharge losses, power inputs and metal intensity of device, provision of device sensitivity to separation of aerosol and steam-like phase from gas-liquid flow.

10 cl, 3 dwg

FIELD: production processes.

SUBSTANCE: invention is meant for separation of gas phase from liquid and solid particle. Cyclone contains vertical cylindrical body, level cover, inlet and outlet tubes, deflector installed in direction of gas flow rotation, false bottom, vertical separation package consisting of flat separation plates forming slot channels in area of overlapping, flat bottom raised in relation to lower edge of plates with circular radial clearance with respect to them and connected to false bottom by radial junction plates, and holding tank. Through holes in which cylindrical pipe is mounted are located in centre of flat bottom and false bottom. Between inner surface of body and beginning of vertical plate of deflector near inlet tube vertical slot channel is formed. Inside holding tank perforated cylinder is mounted to upper part of which perforated disk is attached. Along centre line of perforated disk moving rod is fastened, on its upper end blind washer is installed. Semicircular gate-type slide valves rotating on the same axis are located below perforated cylinder in upper part of holding tank.

EFFECT: increase of separation efficiency.

3 dwg

FIELD: production processes.

SUBSTANCE: invention refers to gas cleaning from hard particles by wet method and may be used in power industry for cleaning of boilers off gases. Device includes casing with antirust covering, tubes delivering and extracting gas, emulsifier, drop catcher designed as ring-shaped grid with radial blades and conic bottom and admission of hot air. Drop catcher is installed with circular clearance to gas cleaner covering, at that ends of drop catcher blades remote from center are shifted from their radial position in direction opposite to flow twist. Bottom of drop catcher is designed conic, top down with hole in cone top, at that inside conic bottom washing device is installed.

EFFECT: increase of degree of liquid separation from gas flows, decrease of reentrainment of liquid drops, simplicity of device production.

5 cl, 2 dwg

FIELD: process engineering.

SUBSTANCE: invention serves to entrap finely dispersed and aerosol fluid and solid particles and can be used on oil, gas, chemical and other industries. Proposed separator comprises vertical cylindrical housing with upper and lower bottoms, inlet, outlet and discharge branch pipes, deflector with baffle plate, and separation package. Said separation package has a hole accommodating the tube. Lower part of the latter makes, together horizontal baffle, a pocket-trap. Separator comprises also drain tube communicating the space above horizontal web with separator lower part. Separator comprises additionally an adapter arranged above horizontal web. Said adapter is made from coalescing material and accommodates a hollow coalescing channel to communicate aforesaid tube with outlet adapter.

EFFECT: higher efficiency.

9 cl, 2 dwg

Separator // 2376054

FIELD: process engineering.

SUBSTANCE: invention relates to devices intended for separating fluid and solid particles from gases exploiting centrifugal forces originating on swirling gas-fluid flow, and can be used in oil production, petrochemical industry and other branches of national economy. Proposed separator incorporates vertical cylindrical housing with inlet, outlet and discharge branch pipes, horizontal baffle with central hole with separation pack made up of plates arranged its edges, and deflector arranged between separation pack and housing inner wall and communicated with inlet branch pipe. Housing lower part inner surface is made tapered with start of smaller diametre section arranged below deflector, bur above or at the level of separation pack. Note that cylindrical ring is arranged at the housing larger-diametre section.

EFFECT: expanded operating range, reduced pressure losses, higher efficiency of separation.

4 cl, 2 dwg

FIELD: treatment plants.

SUBSTANCE: invention concerns gas-fluid flow separation technology. Centrifugal separation element includes drum with flow swirler and separated fluid trap above the drum rim, in the form of ring with vertical side surfaces forming interconnected annular channels together with external and internal sides of the drum. Trap features guide plates positioned at external side of side surface and oriented in direction of flow whirling by swirler. Pockets for fluid capture and discharge are made along loose ends of plates and can take form e.g. of flanging. Guide plates protrude beyond side surface of trap, feature curved profile and are positioned at tangential to the circle of side surface.

EFFECT: enhanced efficiency of gas separation from liquid and productivity of separation element.

4 cl, 2 dwg

FIELD: process engineering.

SUBSTANCE: thermodynamic separator consists of cylindrical housing, inlet nozzle and outlet diffuser. Aforesaid nozzle houses gas flow swirler. Mixing chamber is arranged between aforesaid nozzle and diffuser to make metered orifices to eject low-pressure gas from the said mixing chamber and to withdraw liquid phase into separating chamber, respectively.

EFFECT: maximum extraction of ethane and methane from condensate; subsequent return of condensate into primary gas flow; simplified procedure, lower metal input and production costs.

3 cl, 4 dwg

FIELD: technological processes.

SUBSTANCE: centrifugal separator may be used for wet cleaning of gases exhausted into atmosphere, and also for separation of water, oil and gas condensate drops from gas flow, in any industry field. Separator comprises cylindrical body with axial nozzles for inlet and outlet of gas flow and units for drain of separated liquid, which are installed in end surfaces of body. Swirler and central perforated pipe with cone displacer are serially installed in body coaxially to the side of gas entry. Separation stage blades are installed between central pipe and cone displacer along its whole length, and hydraulic lock blades are installed at the same level between central pipe and body.

EFFECT: higher efficiency of liquid drops separation from high-speed gas flow, and makes it possible to use separator in any position.

5 cl, 1 dwg

FIELD: production processes.

SUBSTANCE: invention serves for separation of fluid from gas flow. Separator includes cylindrical body with swirling device at inlet, drop catcher at outlet and rotation body - displacer between them - fluid drainage channel. Swirling device is performed from axial swirler and tangential swirler of smaller diametre coaxially arranged at axial swirler and providing the direction of flow swirling to the same side with axial swirler. Axial swirler is multi-stage with arrangement of each stage of smaller diametre at the stage of larger diametre. Displacer is performed in a form of end plug of tangential swirler with diametre larger than displacer diametre and with inclined teeth flanged along the edge towards drop catcher. Drop catcher is made of porous filtering material and performed in a form of cylinder, blind or open at one end, or rotation body expanding gas flow streamwise.

EFFECT: provision of effective liquid separation from swirled gas flow including changing loads for gas and fluid.

4 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates centrifugal separator designed to separate liquid from a gas flow, in particular, to separate water from water steam. The centrifugal separator contains the first pipe accommodating a swirler, and the second pipe arranged behind the latter. Note that the internal diametre of the first end of the second pipe facing the first end of the third pipe that arranged coaxially behind the former exceeds the external diametre of the first end of the third pipe. The second and third pipes are furnished with a jacket arranged at a radial distance to form a separating chamber provided with a liquid drain. The separator comprises also the fourth and fifth pipes fitted behind the third pipe, the fifth pipe being fitted, at least, partially into the fourth pipe to form a radial gap. The fourth and fifth are furnished with an additional jacket arranged at a radial distance to form an additional separating chamber provided with a liquid drain. The centrifugal separator incorporates, at least, one length compensator representing a bellows or an elbow to vary the separator axial length.

EFFECT: proposed separator may be fitted in constrained spaces and increases efficiency of unit it is built in.

16 cl, 4 dwg

FIELD: devices for trapping of finely dispersed liquid and solid particles from a gas stream.

SUBSTANCE: the invention is intended for trapping of finely dispersed liquid and solid particles from a gas stream in a field of centrifugal forces. The separator contains: a vertical cylindrical body, a horizontal partition, an inlet branch-pipe, an outlet branch-pipe, an overflow connecting pipes, a baffle, a vertical separative package consisting of vertical flat bent separative plates. To raise efficiency of the device and to increase its productivity by liquid and gaseous phases the bent ends of the plates are directed to the different sides in respect to the external and internal diameters of the separative package. The axial line of the inlet branch-pipe is shifted in respect to an axial line of the body of the device by Ѕ of the diameter of the inlet branch-pipe. At that the diameter of the inlet branch-pipe does not exceed 1/4 of the body diameter. The baffle installed on a course of rotation of the gas-liquid stream has the maximum possible cross-section. At that along the course of the stream run it converges in level and increases in height and still keeping the cross-sectional area. At the end of the upper converged part of the baffle there is the arch-shaped plate descending along the run of the gas-liquid stream and directed relatively to a horizontal line at an angle of 15°-30°. Along the course of rotation of the gas-liquid stream with a clearance in respect to the inner side of the body there is a bent plate, which lower ends go under the lower cover of the baffle.

EFFECT: the invention ensures a raise of efficiency and productivity of the device by liquid and gaseous phases.

2 dwg

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