RU2303491C2 - Nozzle device - Google Patents

Abstract

FIELD: gas or oil transport engineering.

SUBSTANCE: nozzle device comprises tightly interconnected nozzles. The critical section of the nozzles is no less than that of the first upstream nozzle. The nozzle device is additionally provided with at least one unmovable or axially movable nozzle that is mounted in the nozzle downstream of the first nozzle to define a space. The nozzle is made of a Laval nozzle, or Venturi pipe, or opening, or diverging nozzle, or cylinder, or a combination of diverging nozzle and cylinder, or diverging nozzle.

EFFECT: improved design.

4 cl, 21 dwg

Description

The invention relates to equipment for vacuum cracking of natural gases and oil.

The present invention relates to the field of gas-dispersing and gas-transporting devices, and can also be used as a dispersant of gas-liquid mixtures and gas-dynamic systems of various components in chemical technologies, devices for transporting liquids (gas-liquid) and in many other industries, and can also be used as aerosol-concentrating devices and in other areas of technology where it is necessary to disperse gas, as well as installations using wind energy.

Prototype

A known method of concentrating aerosol particles in the Central part of the accelerated gas stream, when the gas is forcibly pumped through a cavity made in the form of a supersonic ejector.

A device is known that contains supersonic nozzles hermetically connected to each other, and each subsequent supersonic nozzle has a critical section no less than the first nozzle along the gas.

(USSR author's certificate No. 1426642 entitled "Aerosol-concentrating nozzles" by N. A. Shesterenko).

The disadvantage of the prototype is that the device and method operate in the flow mode of the input energy, and the kinetic energy obtained by evacuating the cavities in the ejector mode is used to concentrate aerosol particles in the central part of the stream inside the device. Therefore, the effect of using and extracting energy from the vacuum appears inside the device and is not used outside the device and when converting this energy to other types of energy.

Analog 1

A known method of concentrating aerosol particles in the Central part of the accelerated gas stream, when the gas is forcibly pumped through a cavity made in the form of a supersonic ejector.

A device is known that contains nozzles hermetically connected to each other, and each subsequent nozzle has a critical section no less than the previous nozzle.

(USSR author's certificate No. 1242248 entitled "Aerosol-concentrating nozzles Shesterenko", author N. A. Shesterenko).

The disadvantage of analogue 1 is the same as that of the prototype, and analogue 1 in figure 1 shows the option when only part of the driven air is removed from the reservoir along the vacuum source line, and the other part of the air goes into the nozzle with a smaller critical section than the ejector and the last nozzle has a vacuum source.

Analog 2

A known method of concentrating aerosol particles in the Central part of the accelerated gas stream, when the gas is forcibly pumped through the cavity, made in the form of supersonic ejectors mounted between themselves coaxially with gaps and decreasing in size along the direction of the aerosol stream.

A device is known comprising supersonic nozzles hermetically connected to each other. These devices of at least one are installed one after another with progressive reduction with a gap between each other.

(USSR author's certificate No. 1388097 entitled "Aerosol concentrator" by N. A. Shesterenko).

The disadvantage of analogue 2 is the same as for the prototype, with a progressive reduction in the size of the devices used to increase the concentration of aerosol.

The technical task is to reduce energy at startup mode and operating mode, as well as expanding the scope of the device.

The technical task is performed as follows.

1. The nozzle containing supersonic nozzles hermetically connected to each other, and the critical section of each supersonic nozzle is not less than the critical section of the first supersonic nozzle in the direction of gas movement, characterized in that at least one nozzle is rigidly or axially moved coaxially into the subsequent nozzle in the direction of gas movement with the formation of a cavity and is either in the form of a supersonic nozzle, or in the form of a venturi, or in the form of an opening, or in the form of a tapering nozzle, or in the form of a cylinder, silt and in the form of a combination thereof, or in the form of an expanding nozzle, wherein each cavity (s) is either autonomously sealed or at least one cavity is communicated through an overlapping device or with the environment, or with a vacuum source, or with a piperesressor (containers ), which is communicated through a shutdown device or with a source of forced pumping of gas (vacuum), or with the environment, or with both.

2. Nozzles according to paragraph 1, characterized in that either the inlet or outlet or inlet and outlet section (s) of the nozzle is installed (installed) in the tank (s), which is communicated through an overlap device with a source of forced gas pumping, and the tank is equipped with an orifice or a tapering nozzle or a supersonic nozzle or nozzle, which, in turn, is equipped with an overlap device and has a critical cross section not less than the first nozzle along the gas path, and the overlap device is in communication either with the surrounding medium or the piping installation loopback gas flows through or forced pumping source gas, either directly or with the joint combination.

3. The nozzles according to paragraph 2, characterized in that the line connecting the reservoir to the source of forced pumping (rarefaction) of gas is provided with at least one additional nozzle, with each subsequent additional nozzle in the direction of gas less than the previous one, and the first nozzle of each the subsequent nozzle is communicated with the line of each previous nozzle.

4. The nozzle according to one of paragraphs 1, 2 and 3 is characterized in that in the first nozzle in the direction of gas flow, it is leaky and coaxial or rigid, or with the possibility of axial movement, either a subsonic or supersonic exciting nozzle in communication with a source of increased pressure is installed, or at least once, the exciting nozzle is made in the form of a nozzle according to items either 1, 2, or 3, but smaller in comparison with each subsequent nozzle in the direction of gas movement.

5. Nozzles according to one of paragraphs 1, 2 and 3, characterized in that at least one nozzle is configured to change either the critical section of the nozzle or the angle of inclination of the nozzle generators with respect to the direction of gas flow or a combination thereof.

6. The nozzles according to paragraph 4, characterized in that at least one nozzle is configured to change either the critical section of the nozzle or the angle of inclination of the nozzle generators with respect to the direction of gas flow or a combination thereof.

The supernatant Shesterenko is depicted in figures 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20 and 21.

The device depicted in Fig. 1 consists of a tapering nozzle 1 with a critical section 2, a supersonic Laval nozzle 3 with a critical section 4, a supersonic Laval nozzle 5 with a critical section 6. The nozzle 1 and the Laval nozzle 3 are connected to each other using tight bolts 7 with nuts 8, and Laval nozzles 3 and 5 are connected by a tight connection using bolts 9 with nuts 10. Sealing of the joints is ensured by compression of the rubber gaskets 11 and 12 with bolts 7 and 9.

Between the tapering nozzle 1 and the supersonic Laval nozzle 3 there is a cavity 13. The tapering nozzle 1 has an inlet section 14, and the supersonic Laval nozzle 5 has an outlet section 15.

Figure 2 shows a device in which on a tapering nozzle 1 with bolts 16, nuts 17 and a rubber gasket 18 is installed tapering nozzle 19, which has a critical section 20 and an inlet section 21. Between the tapering nozzles 1 and 19 there is a cavity 22.

Figure 3 shows a variant when a shell 23 is mounted on a tapering nozzle 1, on which, in turn, tapering nozzles 19, 24, 25, 26 are installed, which have critical sections 20, 27, 28, and 29, respectively.

The tapering nozzle 26 has an inlet section 30. There are cavities between the nozzles 22, 31, 32, and 33, respectively. Sealing in the structure is carried out by welding, both in this embodiment and where the sealing method is not specified.

Figure 4 shows a variant when a cylinder 34 with a critical section 35 is mounted on a supersonic Laval nozzle 3. And in the cylinder 34 a venturi 36 is installed hermetically (by welding), which has a critical section 37, an inlet section 38 and an outlet section 39. The sealing between the Laval supersonic nozzle 3 and the cylinder 34 is carried out using a plane 40, bolts and nuts (not shown in Fig.) And a rubber gasket 41. There is a cavity 42 between the Laval supersonic nozzle 3 and the cylinder 34. There is a cavity between the cylinder 34 and the venturi 36 cavity 43.

In figures 1, 2 and 4 between the Laval nozzles 3 and 5 there is a section 44 of the maximum gas expansion in the Laval nozzle 3.

Figure 5 shows a variant when the nozzle (plane) 45 with a critical section 46 in the form of an opening is hermetically mounted on the tapering nozzle 1. Between the nozzle (plane) 45 and the tapering nozzle 1 there is a cavity 47.

Figure 6 shows the option when the tapering nozzle 1 is installed tapering nozzle 19, 24, 25 and 45.

Figure 7 shows another installation option on the tapering nozzle 1 of the critical section 46 (holes). There is a cavity 47 between them. Fig. 8 shows a variant when cylinder 48 is mounted on cylinder 34 and cylinder 49 is mounted on it. Cylinder 49 has a critical section along its entire length 50. Cylinder 48 has a critical section 51. Between the cylinders 34, 48 and 49 there are cavities 52 and 53, respectively. Sealing is carried out using bolts (not shown in FIG.) And rubber gaskets 54 and 55.

Fig. 8 also shows a variant when expanding nozzles 56, 57 and 58 are installed between supersonic Laval nozzles 3 and 5, which form cavities 59, 60, 61 and 62 between themselves. The expanding nozzles 56, 57 and 58 have output sections 63, respectively , 64 and 65.

Figure 9 shows a variant when on the Laval supersonic nozzle 3 using guides 66 and 67, planes 68 and 69, as well as a flexible element 70, which seals with bolts 71, 72, nuts 73, 74, rubber gaskets 75 and 76 , a tapering nozzle 77, which has a critical section 78 provided with a cylinder 79 with a critical section 80, is installed. The tapering nozzle 77 has an inlet section 81. There is a cavity 82 between the tapering nozzle 77 and the Laval supersonic 3. The distance between the critical sections 80 and 4 changes when help adjusting bo that 83, nuts 84 and bursting spring 85 which are mounted on planes 68 and 69.

Figure 10 shows a variant when instead of a tapering nozzle 77, a supersonic Laval nozzle 86 with a critical section 87 and an inlet section 88 is installed. Figure 10 also shows how a supersonic Laval nozzle 5 is installed on the tank 89, which has a line 90, connecting it to a source of forced evacuation 91 with a blocking device 92. The tank 89 is equipped with a Laval nozzle 93 with a critical section 94 and an output section 95, which is equipped with a blocking device consisting of a cover (sashes) 96 and a rod 97 with a mechanism m closing and opening (Fig. not shown). The source of forced evacuation 91 has an electric motor 98. In FIG. 10, there is a cavity 99 between supersonic Laval nozzles 3 and 86. In the reservoir 89 there is a cavity of the reservoir 100. Instead of the Laval nozzle 93, there may be a hole or a narrowing nozzle (not shown in FIG.) With a critical section 94, which is greater than the critical section 87.

Figure 11 shows a variant when the device considered by us is rigidly mounted on the nozzle 1 using the bracket 101, but of a smaller size and with the designation of all elements by the symbol "a".

On the tapering nozzle 1a, an exciting nozzle device consisting of a supersonic Laval nozzle 102 and a gas line 103 in communication with a pressure source (not shown) is coaxially axially mounted for axial movement.

Axial movement is carried out using the adjusting bolt 104, nut 105, spacer spring 106, which are installed on the planes 107 and 108, on which the rails 109 and 110 are mounted. Using the bracket 111, a gas line 103 is installed on the rail 110.

On Fig shows a variant when the highway 90 is equipped with an additional device considered by us in figure 10, but the device with the designation "b" and smaller.

On Fig depicts a variant when the cavity 13 is in communication with the source of forced pumping (vacuum pump) 91, the pipe line 112 having a shutoff device 113.

On Fig depicted the option when the Laval nozzle 5 is hermetically installed Laval nozzle 114, which has a critical section 115 and the output section 116. In Fig.14 Laval nozzle 3 has an input section 117. Section "A" of the Laval nozzle 3 corresponds to the calculated compressor mode during acceleration of the gas flow at the time of start. Section “B” of the Laval nozzle 3 corresponds to energy increment due to increased acceleration in the evacuated part of the Laval nozzle 3. Section “B” corresponds to the deceleration of the gas flow before the critical section 6. Section “G” corresponds to the section of secondary acceleration to supersonic speeds in the Laval nozzle 5. Section “D” corresponds to energy increment due to acceleration of the gas flow to hypersonic speeds in the Laval evacuated nozzle 5. Section “E” corresponds to the deceleration of hypersonic flow before the critical section 115. Section “g” corresponds to It is a part of the secondary acceleration of the gas flow to hypersonic speed.

On Fig depicts a turbojet engine, which consists of an input device 118, a compressor 119, a vacuum energy generator consisting of a Laval nozzle 86, a cavity 99 and a Laval nozzle 3. The turbojet engine also consists of a turbine 120 and a jet nozzle 121.

Fig. 16 shows a variant when the loop gas pipeline 122 communicates all the gas input and output paths of the device, providing a closed process circuit in which a gas turbine 123 with an electric power generator 124 can be installed. The wheel 125 of the turbine 123 is equipped with blades 126. Instead of an electric power generator 124 any drive can be installed, providing movement of various mechanisms (not shown in Fig.). On Fig also shows the electric wire 127, going from the generator 124 to the consumer. Arrows 128 and 1286 show the progress of the mechanism for opening and closing covers 96 and 966.

On Fig shows an option when the subsonic nozzle (tapering) 1, 19, 24, 25 and 45 are installed (on top of each other) hermetically using flexible elements 129, planes 130, 131, 132, 133, 134 and rails 135, 136 , 137, 138, and 139. The distance between critical sections is adjusted using bolts 140, springs 141, and nuts 142.

Fig. 18 shows a variant when the blades 126 are replaced by the devices under consideration, consisting of Laval nozzles 86 and 3, which have a cavity 99. They are mounted on the wheel 125 so that the jet stream rotates the wheel 125 in one direction in the direction of arrow 143. Turbine 123 is connected to the rotor 144 of the generator 124 or the drive of another device.

On Fig depicts a variant when the line 90 is equipped with at least one additional overlapping device 145, which (or which) is communicated (communicated) with the receiver-tank (or tanks) 146. Fig. 19 is also shown as on the Laval nozzle 86 a bell (reservoir) 147 is installed with branches 148 and 149, which are in turn equipped with floor shutoff devices 150 and 151. Branch 148 is connected through a floor shutoff device 150 to a source of forced gas pumping (compressor) 152 having an electric motor 153. The floor shutoff devices 150 and 151 havecritical section is greater than critical section 87.

FIG. 19 also shows an embodiment where a forced pump source (vacuum pump) 91 through a conduit 154 and an overlap device 155 is in communication with a receiver tank 146. At the same time, the receiver tank 146 is connected to the environment through a conduit 156 and an overlap device 157.

In all the figures, already known elements, when they are used in other layouts and combinations with other known elements, are not specified for the second time in the text.

On Fig depicted the option when the slotted (flat) Laval nozzle 158 is equipped with a pipe 159, which is in communication with a source of forced pumping of gas and in which an electric motor 160 is installed, which drives the worm pair 161, which in turn moves the cone 162 in the vertical direction An increase in the critical section area can be achieved by expanding the generators of the Laval nozzle 158 (not shown in FIG.).

FIG. 20 also depicts a variant when a slotted tapering nozzle made of shutters 167 that have hinges 168, 169, as well as worm gears, is sealed on a Laval slot or ring nozzle 158 hermetically using walls 163, 164, 165 and flexible elements 166. 170, 170a, equipped with electric motors 171 and 171a. A narrowing nozzle made of shutters 176, which have hinges 177, 178, as well as worm gears 179, 179a, equipped with electric motors 180 and 180a, is installed on the wall 165 using the walls 172, 173, 174 and flexible elements 175. On the wall 174, walls 181, 182 and 183 are installed with flexible elements 184 that provide a sealed installation of a slotted expansion nozzle made in the form of shutters 185, which are equipped with worm gears 186, 186a and electric motors 187 and 187a. All electric motors are mounted rigidly on the walls. The number of worm gears, electric motors and joints can be increased. Elastic gaskets 188 are involved in sealing. Louvers 185 also have hinges 189 and 190. All worm gears with louvers are connected through hinges.

In Fig. 20, in an annular embodiment, airtight cavities 191, 192 and 193 are formed by walls 163, 164, 165, 172, 173, 174, 181, 182, 183 and shutters 167,176 and 185.

The Laval nozzle 158 has a critical cross section of 194.

Tapering nozzles made of shutters 167 and 176 have critical sections 195 and 196, respectively.

If we are dealing with a variant of slotted nozzles, then the blinds 167, 176 and 185 also have flexible elements connecting them along the entire length with the end walls (which are not shown in Fig.). In this case, all walls are sealed with end walls and the Laval nozzle 158 also has an end wall (not shown). In this embodiment, the end walls participate in the formation of the cavities 191, 192 and 193. If we have the option of annular nozzles, then the end walls are not needed for this. Between the Laval nozzle 158 and the shutters 167 there is a gap (not indicated in FIG. 20) connecting the gas path to the cavity 191. Between the shutters 167 and 176 there is a gap (not indicated in FIG. 20) connecting the gas path to the cavity 192. Between the shutters 176 and 185 there is a gap (not indicated in FIG. 20) connecting the gas path to the cavity 193. All flexible elements are sealed with rubber gaskets and bolts (not shown).

At the same time, it should be noted that the variant depicted in Fig. 20 can also be made in the form of an annular variant with inserted central bodies that change the critical section as is done in gas turbine engines.

In Fig. 20, all electric motors are connected to a control panel (not shown in Fig.).

In Fig.21, the first pair in the direction of the gas nozzles and the cavity between them is made in the form of a phase separator Shesterenko according to the author's certificate of the USSR No. 845065 and No. 920468. In this embodiment, the first nozzle 197 in the direction of travel of the gas is made curved in front of the critical section 198, and the cavity is made in the form of a hopper 199 for accumulating aerosol particles from which the gas is purified. On Fig also shows the option when one of the pair of nozzles as the previous one in the direction of gas movement of the nozzle is made in the form of a supersonic nozzle Shesterenko 200 according to the USSR author's certificate No. 899151, when the supersonic visor 201, in turn, is made in the form of a Prantl- Mayer. In this figure, the cavity going after the visor 201 is made in the form of an accumulation hopper 202, behind which Laval ring nozzles 203 and 204 are installed. Arrows 205 and 206 show the direction of aerosol particle emission, respectively, in the accumulation bins 199 and 202.

Super nozzle Shesterenko works as follows.

Due to the pressure drop (Fig. 1), the gas flow enters the device, passing first the nozzle 1, and then successively the Laval nozzles 3 and 5.

Critical section 2 is the smallest in the device and the gas flow rate in this section at the start-up mode is greatest.

When the pressure drop is sufficient so that in the area between the critical sections 2 and 4, the accelerated air stream works as an ejector, a small vacuum is first created in the cavity 13. It should be noted that the distance between the critical sections 2 and 4, as well as the gap between the walls of the nozzle 1 and the Laval nozzle 3 are selected so that the ejection effect is the best.

As a result, the vacuum in the cavity 13 creates a greater pressure drop in the nozzle 1 than it exists at the inlet and outlet of the device (in sections 14 and 15). Therefore, the velocity of the outflow from the critical section 2 increases with the increase in gas flow. Since critical sections 4 and 6 are no less (and preferably slightly larger), critical section 2, the gas jet does not block in the device, and the accelerated gas stream in critical section 2 inertia leaves critical section 6. An increase in the flow velocity in critical section 2 leads to an increase in the evacuation of the cavity 13. A mutual increase in the evacuation of the cavity 13 and the velocity in the critical section 2 continues until a speed equal to the sound occurs in the critical section 2, after which the gas flow rate increases and the increase in velocity through critical section 2 will cease, and the increase in the evacuation of cavity 13 will lead to an overexpansion of the gas stream beyond critical section 2. As a result, a supersonic stream will appear in the form of an overexpanded barrel beyond critical section 2. The profile of the supersonic nozzle Laval 3 before critical section 4 provides a jump angle compaction with respect to the incident supersonic flow, not exceeding 60 °, which eliminates the transition of supersonic to subsonic velocity in the Laval nozzle 3. Before the occurrence of supersonic In the interior of the Laval nozzles 3 and 5 between the critical sections 4 and 6, drag and then acceleration of the subsonic flow occur.

The supersonic nozzle 5 is shaped similarly to the supersonic nozzle 3, when the oblique shock waves in relation to the incident supersonic flow do not exceed 60 °, which excludes the transition of supersonic velocity to the subsonic velocity in the Laval nozzle 5. As soon as a supersonic flow arises between critical sections 2 and 4, in space between critical sections 4 and 6, a supersonic flow will begin to move, which in turn, due to ejection, almost instantly creates a vacuum in this space, thereby providing the greatest expansion rhenium flow in a supersonic Laval nozzle 3 and accelerating the flow in it to hypersonic speed. It should be noted that the critical section 4 may be less than, equal to or greater than the critical section 6.

If the device is used as an aerosol-concentrating device, then the selection of the ratios of these sections depends on the initial pressure drop in the device, the degree of dustiness of the aerosol stream, the physical properties of the gas, and the size of the aerosol particles that need to be concentrated in the center of the accelerated stream.

Inside the device, aerosol particles are concentrated near the flow axis due to inertial forces, as well as the occurring shock waves in front of critical sections 4 and 6 in Laval nozzles 3 and 5 significantly enhance the effect of cleaning the peripheral part of the air stream. The cutoff due to additional evacuation (not shown in Fig.), The Central stream is diverted for further processing or to the filter, or to another place. The rest of the air, cleaned of particles of aerosol, comes out.

It should be noted that the supersonic part of the Laval nozzle 5, which goes after the critical section 6 along the gas, can be performed depending on technical tasks, either expanding, like a supersonic Laval nozzle, or in the form of a convex surface, like a supersonic Shesterenko nozzle USSR author's certificate No. 899151, either completely absent and end with a critical section 4, or be in the form of a one-sided concave visor (not shown in Fig. 1).

If the device is used as a generator of energy from a vacuum, then instead of a cutoff device, a blade of the impeller or turbine of an electric generator or drive is located in the path of the gas flow, or a gas flow is used to produce reactive force.

It is possible that the nozzle 1 is made in the form of a huge cone with a critical section 2. This cone is installed opposite the wind flow, where there is a wind rose (for example, in a gorge between the mountains). If the method and device perform the role of a gas ramjet engine, the device is installed on an object (aircraft, rocket), which move at high speed, which provides the device with the necessary initial pressure drop in the nozzle 1.

It is necessary to pay special attention to the fact that when there is an increase in the speed and flow rate of gas in section 2 due to the evacuation of cavity 13, the moment the vacuum starts to work with an increasing degree and already the source of forced gas pumping plays absolutely no role. The amount of gas that can pass through critical section 2 with the speed of sound and its further acceleration to hypersonic speed in section 44 require a much larger source of energy than it was at the beginning of the device’s start-up, which ensures the vacuum obtained by ejection in the device during cracking gas.

It should be noted that the devices depicted in FIGS. 2 and 3 due to the evacuation of cavities 13, 22, 31, 32 and 33 create the most stable mode with increasing speed in the subsonic ejector mode.

Figures 4, 5, 6, 7 and 8 show possible design options when, through self-evacuation of cavities in the ejector mode, it is possible to provide access to sound and supersonic modes.

In figure 3, 5, 6 and 7, the supersonic parts of the device to simplify these figures are not shown.

The embodiment depicted in FIG. 8 by evacuating the cavities 59, 60, 61 and 62 provides the best possible expansion of the flow in supersonic mode.

In Fig. 9, a change in the distance between critical sections 80 and 4 makes it possible to approximate them as much as possible, providing an ejection effect in this space with a minimum pressure drop, and after increasing the speed and flow rate, by increasing this distance, it is possible to obtain the best ejection effect even at high speeds .

When the first nozzle has an expanding part at the bottom (this is a Venturi tube, a Laval nozzle; or just a cylinder with an expansion at the bottom), then this part must have a small expansion or a short length so that the jet braking in it still creates an ejection effect. And another feature is that the first and second nozzle in the direction of gas flow must necessarily be an ejector pair.

Figure 10 shows the case when, when starting up the device, the covers 96 must be closed, the overlapping device 92 is open, the motor 98 is turned on, and the source of forced vacuum 91 through line 90, the cavity of the tank 100, critical sections 6, 4 and 87 begin to be sucked into the inlet section 88 ambient air. Since the critical section 87 is the smallest, the highest velocity occurs in it, which, due to ejection, forms a vacuum in the cavity 99. The reservoir 100, the nozzle or pipe 93, and the closure device 97 with the cover 96 play the same role at this moment as the storage tank 202 in FIG. It should be noted that the structural elements can be arbitrarily combined and their image in the figures is not an unshakable truth - these are only options that, for simplicity of the image, do not include all the elements depicted in other figures, but they can be there if necessary. In the embodiment shown in FIG. 11, compressed gas is supplied through a gas line 103 to a Laval supersonic nozzle 102. By placing the latter close to critical section 2a, gas ejection is generated from the environment (or from outside). Gas from the outside, mixed with a supersonic gas stream, enters through the critical section 2a and 4a through the device. Gradually, a rarefaction occurs in the cavity 13a, which eventually begins to accelerate the flow passing through the critical section 2a, and then transfers it to the speed of sound, and then accelerates the mixed gas flow to supersonic speed.

In the outlet section 15a, a hypersonic mixed gas flow rate is established.

A similar occurs in the tapering nozzle 1 and at the exit of the Laval nozzle 5.

Installation is running.

There are several such cascades, and then a sufficiently low-pressure high-pressure source can be used to start the device.

In the embodiment shown in FIG. 12, at the time of starting, the covers 96 and 96b must be closed, the overlapping devices 92 and 92b are open. The critical sections 87 and 4, as well as 87b and 4b, are (respectively) at a minimum distance from each other. The source of forced pumping (rarefaction) 91 is turned on and at the inlet section 88 a compressor (not shown in Fig.). Air passes through the inlet section 88 through the entire device to the highway 90, then through the critical section 87b, where the speed is maximum. The cavity 99b is evacuated. Between the critical sections 87b and 4b, a supersonic flow is created, which evacuates the cavity between the critical sections 4b and 6b. There is a stable supersonic mode.

Then the lid 96b opens (or opens). The distance between the critical sections 87b and 4b increases, bringing to the optimal ejection mode at supersonic speeds.

Between critical sections 87 and 4, due to the ejection and evacuation of cavity 99, a supersonic flow arises, which evacuates the cavity between critical sections 4 and 6. Then, the lid (sash) 96 opens (or opens). This option can be used in preparing gas for transportation through the gas pipeline (which will be discussed in detail below).

On Fig depicted the option when the overlapping device 113 and 92 at the time of launch are open. When a supersonic flow is established between critical sections 2 and 4, as well as 4 and 6, the device 113 is closed. Then, the cover 96 is opened (or slightly opened). This option is similar to the variant of Fig. 12.

On Fig due to the forced differential pressure (the source of the differential pressure in Fig. Not shown) creates a supersonic flow in the Laval nozzle 3, going from the inlet section 117 to the outlet section 116. The cavity between the critical sections 4 and 6 is first vacuumized by the supersonic stream , and then the cavity between the critical sections 6 and 115.

Due to the displacement with respect to the critical section 4 of all elementary perturbations as a result of cracking towards the outlet section 116, the gas will be constantly sucked into the inlet section 117. The volume of the cavity and the distance between critical sections 4 and 6 are less than the volume of the cavity and the distance between critical sections 6 and 115 This allows you to guaranteedly create in the first cavity along the gas motion a minimum, but sufficient mode of increment in the volume of controlled cracking due to an ejection vacuum without disruption and interference with the process perturbations from the outlet cross-section 116. In the second cavity along the gas, the maximum increment of the cracking volume is also achieved due to the ejector vacuum, and in the outlet cross-section 15 (the same and maximum), the gas flow rate reaches its maximum value, i.e. hypersonic speed. Critical section 115 is a sound barrier to external disturbances. In Fig. 14, the energy increment in section "B" is less than in section "D", but this is not necessary. It is possible to confine ourselves only to Laval nozzles 3 and 5, then the energy increments in sections "B" and "G" are combined.

In the embodiment shown in Fig. 15, in a turbojet engine on a fast flying airplane, the oncoming air stream has a fast speed relative to the engine. Before entering the input device 118, the air is inhibited, its speed relative to the engine decreases. At the same time, as the flow decelerates, the pressure in it increases, while the higher the flight speed, the greater the pressure of the air entering the compressor 119. In the compressor 119 (turbocharger), further compression of the air occurs. Compressed air flows from compressor 119 to a vacuum energy generator (or cracking energy), which consists of a Laval nozzle 86, cavity 99 and a Laval nozzle 3. In the Laval nozzle 86, the flow accelerates to a supersonic speed. This flow evacuates the cavity 99 and the space between the critical sections of the Laval nozzles 86 and 3. In this space, the flow accelerates to a hypersonic speed and then, inhibited to supersonic speeds, enters the turbine 120, and then exits through the jet nozzle 121. A sufficient pressure is created in the compressor 119, to create supersonic speed, but hypersonic speed is achieved due to the geometry and, relatively speaking, the increment of the cracked volume of the gas (or, figuratively speaking, vacuum energy).

Thus, without supplying fuel in one vacuum, one can fly an infinitely long time (before wear of the rubbing parts), although this option requires experimental confirmation, but it has the right to life. If you use the energy of a gas jet completely in a turbine, you can get electricity or get other useful mechanical work. When the device is used as a device for heating gas, the number of supersonic nozzles (Fig. 14) is set so that the kinetic energy at the shock waves during braking provides the necessary gas heating. All of the above options, if necessary, can be enclosed in a single gas tight circuit in which the method and device will fulfill one or another process orders. (For example, filling this sealed circuit with gas eliminating the explosion hazard when receiving electricity, if an electric generator is also enclosed in this circuit. With an increase in the ejecting pairs of Laval nozzles, it is possible to melt metal, burn ceramic, etc., without polluting the atmosphere with harmful aerosols and gases) - This option also has the right to life. The proposed device for all options can be made slotted or annular.

As shown in FIG. 16, the device is enclosed in a loop gas line 122. It may be filled with an inert gas or loop harmful gases.

Starting the device according to this embodiment is similar to what we considered in Fig. 12.

It should be noted that in a sealed circuit the gas pressure can be maintained much higher (compressor is not shown in FIG. 16) than atmospheric, which improves the effect of ejector evacuation in the first pair of nozzles. The generator 124 through the wire 127 delivers electricity to the consumer, part of which can be supplied to the battery and through it returned to the source of forced gas transfer (compressor or vacuum pump), which are turned on when the device is restarted or to maintain the transporting pressure differential in the closed loop 127.

As shown in FIG. 17, a minimum distance can be set between several critical sections, providing the optimal conditions for creating an ejection effect with a minimum pressure drop in several cavities at once in the launch mode, and then, increasing these distances, reach the optimal ejection effect at high speeds and expenses arising as a result of ejector self-vacuum and acceleration of gas to supersonic speeds.

In this case, the device depicted in Fig. 17 is, conditionally speaking, a supersonic nozzle, only triggered by a small pressure drop (not sufficient to create a supersonic or sonic velocity in a conventional Laval nozzle) and reaching sound and supersonic speeds only by vacuum cavities 22, 31, 32 and 47. In Fig. 17, each subsequent nozzle in the direction of travel has a critical section larger than the previous one, but there may be an option when one of the nozzles has a critical section smaller than the previous one, but it should always not less than the critical section of the first nozzle in the direction of gas movement. In the latter case, we obtain the braking of the supersonic flow before this critical section, and then the secondary supersonic acceleration of the flow behind this section.

Instead of the blades 126 (Fig. 18), we can install the device under consideration, then the rotor 144 of the electric power generator 124 or the drive will rotate from the jet of the proposed device. Naturally, first you need to start the device and bring them to the operating mode (not shown in Fig. 18). In this embodiment, the operation of a ramjet engine is shown, which can be performed either as an embodiment of FIG. 14 or FIG. 1, etc.

The embodiment depicted in FIG. 19 allows the receiver tank 146 to be used as a source of forced pumping (or vacuum) according to the previously described scheme, moreover, this tank can be pre-evacuated by a vacuum source 91 through a pipe 154, with an open blocking device 155 and closed overlapping devices 157, 145 and 92. The receiver tank 146 can also be evacuated during startup and operation of the device, having previously opened the overlapping device 145. The size of the receiver tank 146 depends on the process Sgiach tasks and can be of enormous size being even float.

A variant is possible to start the device (Fig. 19) using compressor 152. Then, the overlapping devices 151, 113 and 92 are closed. Cover 96 is open. The overlapping device 145 is closed. The overlapping device 150 is open. The electric motor 153 is turned on. The compressor creates the necessary pressure and flow rate so that a supersonic flow occurs in the Laval nozzle 86, after which the device is evacuated by ejecting the cavities 99 and 100. After the operating mode has been established in the device in question, the overlapping device 151 opens. It should be noted that through each overlapping device 150 and 151 in the open state passes a greater amount of air than is required for a critical outflow through the Laval nozzle 86 in critical mode.

Branch 149 is in communication with the environment or with a loop gas line 122. The supersonic and hypersonic flow are kept in vacuum by the vacuum of the cavities 99 and 100, as described previously, in the operating mode. The volume of the receiver tank 146 is selected so as to provide the necessary speed and flow rate of the sampled gas in the first nozzle in the direction of travel at the time of start-up, to provide an ejection effect in the first pair of nozzles and to create a stable vacuum between these nozzles. Between the bell (tank) 147 and the tank 98 in Fig.19, you can install any device from the above options, the startup modes which have already been considered before. Preliminarily evacuating the receiver-reservoir 146 in the operating mode, without additional energy consumption, it is possible to bring the device to the operating mode again and then vacuum it again or remove the cracked gas.

It should be specially noted that there may be several receiver tanks 146. They can be evacuated alternately or all at once. The vacuum receiver tanks 146 can also be used alternately to start, and if necessary, during the operation of the installation or to select the excess cracking products (gases).

Such a need may arise in case of violation of overlapping devices in one of the tanks or, if necessary, create a stable operation mode with sharply changing external factors of influence (changes in environmental pressure or in the process of cracking oil and gases with an increase in gas volume due to cavitation and intense boiling of oil components). You can periodically replace the vacuum (generated) with a portion of fresh gas in the reservoir 146, and then vacuum the cavity with an ejector or one of the methods described above or with a vacuum pump, if necessary. Receiver tanks 146 can play the role of floats: when they are evacuated, the specific gravity of the structure decreases, i.e. you can swim both in water and on water, and in the airspace transferring heavy and large-sized structures to the right places and, finally, lift entire cities by the clouds, if people are closely on the ground or it is necessary to preserve the gene pool during global shocks.

It is possible to combine several of the above options for starting the device and its operation, creating the widest range of applications for the Shesterenko nozzle in various branches of technological processes.

It should be noted that in the device shown in Figs. 14, 15 and 19, the source of forced gas pumping (compressor) does not turn off and creates an increased pressure at the inlet of the installation. In this case, the energy obtained by vacuum cracking of gas significantly exceeds the energy consumption for the compressor. This option also has the right to exist, for example, in a gas turbine engine and other cases when using a polyatomic gas as a working fluid.

In the embodiment shown in Fig. 20, under the pressure necessary to obtain a supersonic speed, the gas enters the Laval nozzle 158. When, due to the ejection effect, the cavities 191, 192 and 193 are evacuated, initially the angles of the blinds 167 and 176 and 185 with respect to to the oncoming flow, they have parameters that ensure the greatest ejection effect during the calculated launch mode. After receiving a hypersonic outflow from the Laval nozzle 158, with the help of worm gears 170, 179, 186, 170a, 179a, 186a, the angle changes, which changes in the direction of increasing all sections to prevent locking of the hypersonic stream and to ensure hypersonic between the blinds 167, 176 and 185 gas flow rate.

After establishing the optimal operating mode at the initial air flow rate, a critical section 194 in the Laval nozzle 158 can gradually increase due to the worm gear 161, raising the cone 162, which increases the gas flow rate at this moment. The initial angle of the blinds 167, 176 and 185 with worm gears controlled by electric motors 171, 180, 187 and 171a, 180a and 187a is synchronously restored, but with a larger critical cross section between the blinds, which ensures an optimal mode of ejection effect at lower supersonic speeds, but with high air consumption. Then, while maintaining a stable vacuum in the cavities 191, 192 and 193, the blinds 167, 176 and 185 with worm gears increase the distance between them and the optimum angle is established when working in hypersonic mode, but already at a higher gas (air) flow rate through the critical section 194. Then all can be repeated, and increasing the gas flow without going into subsonic mode, being constantly in the field of supersonic and hypersonic speeds, each time adding about five to ten percent of the gas flow, you can gradually double the gas flow, it triple, etc.

It is possible that, simultaneously with an increase in the critical section 194 in the hypersonic flow optimization mode, the critical sections 195 and 196 also increase, then the increase in gas flow rate can be much larger than with a gradual increase. In this case, it is possible that all the blinds 167, 176 and 185 are combined into one guide of the Laval nozzle and at the same time their evacuated cavities are combined into one cavity or this combination can be partially implemented.

At the same time, it should be noted that the proposed device can also be started at elevated pressure, when all the cavities (Fig. 19) have excess pressure (for example, 20 atm), then the overlapping devices 151, 113, 145, 92 and 97 are closed and 150 is open and compressor 152 creates pressure throughout the device. Then, the overlapping device 96 is opened. In the Laval nozzles 93, 3 and 86, hypersonic flows are immediately established. Due to ejection, cavities 99 and 100 are evacuated. Then, the overlapping device 151 opens, and 150 then closes. The main role in the further process of gas acceleration and pumping will be played by vacuum (rarefaction) resulting from ejection in cavities 99 and 100, as in all previously considered cases. Similar trigger modes can occur in various designs. In the variants depicted in FIGS. 9, 10 and 20, with such start-up modes, the geometric parameters should be set optimal for hypersonic flows, and only then should the device be started. In addition to the above, it should be noted that the number of evacuated cavities and the number of nozzles in all cases are determined by the tasks, physical properties of the gas, aerosols, and other parameters and operating conditions of the device. Once again, we note that the variant depicted in Fig. 14 may consist of a significantly larger number of nozzles with different alternating volumes of evacuated cavities with different variations of the critical sections determined by the above parameters.

On Fig shows a variant when the first nozzle in the direction of travel of the gas is made curved before the critical section 198, then the gap between the first pair of nozzles turns into a hopper 199 for the accumulation of aerosol particles. The first pair of nozzles is a phase separator, pre-cleaning the gas.

Accelerated to the speed of sound, a gas containing aerosol particles, before the critical section at a subsonic speed, sharply changes direction. Aerosol particles under inertia force are grouped to the outer side of the nozzle rotation and, in the direction of the supersonic expansion, fly out in the direction of arrow 205 from the flow into the storage hopper 199, which is periodically or constantly cleaned (the hopper cleaning mechanism is not shown in FIG. 21).

Then the gas goes to the next pair of Laval nozzles 3 and 5. The remaining small aerosol particles are concentrated near the flow axis.

In the Shesterenko 200 supersonic nozzle 200, the gas flow through the visor 201, made in the form of a Prantl-Mayer surface, sharply turns, following the surface of the visor 201, but already in the supersonic gas expansion section. In this case, the particles of aerosol still remaining in the gas leave the gas flow in the direction of arrows 206, settling in the storage hopper 202 (which can be used when transporting natural gases in the oil and gas industry), which is also periodically or constantly cleaned of aerosol particles (in Fig. shown). The finally purified gas from the particles enters the next pair of Laval ring nozzles 203 and 204, after which a gas turbine can be installed, which drives any mechanism or flow pressure energy can be used at the discretion of the consumer. It should be noted that the proposed device by creating the effect of ejection and evacuation of the cavities schematically repeat the conditions for the initiation of tornadoes and tornadoes. The device’s rigid walls support these conditions indefinitely, and the inertial forces of the accelerated gas flow to supersonic speeds and due to the well-chosen geometry can hold these inertial forces for a long time, as happens with formidable phenomena in nature. Which gives the author the right to argue that if you turn off the source of forced pumping of gas for some time, the gas flow will continue to move for some time or constantly, although the mechanism of these formidable natural phenomena is not fully known to people. Moreover, the number of cascades of nozzles and their geometric combination make the devices more efficient than the known nozzles in terms of converting the existing pressure drop into kinetic energy (flow rate of molecules of the source gas). In all the devices depicted in the figures, gases consisting of different components move with supersonic speed, which include different-atomic gases, liquid vapors, aerosols, gas-liquid dispersions, various foams and liquids, which, when cavitated or partially or completely into a gaseous state, those. have gas-dynamic equivalent features (gas flow compressibility). If the Shesterenko nozzles are used as a dispersant of liquids and gas-liquid systems or as gas-transporting and liquid-conveying devices, then a liquid or gas-liquid mixture is passed through the nozzles under pressure, which, due to cavitation, is boiled and brought into the cascades of nozzles 19 and 1 or 26, 25, 24 and 19 (in FIGS. 2 and 3) to a gas-liquid or vapor mixture, which in turn behave like a gas-dynamic system. In this embodiment, you can use Shesterenko nozzles for cracking oil, and since the volumetric flow rate of the product increases sharply, it is necessary to take this into account when choosing the size of critical sections in subsequent nozzles following the first nozzle in the direction of product movement. 12 and 19 show a variant when the gaseous flow rate excess can be partially or completely discharged either in the container 146 or through the smaller Shesterenko nozzles with the liquid fraction being discharged in one direction and the gaseous one through the vacuum pump 91 in the other direction. It is clear that in these cases, all sources of forced pumping of gas and liquid work continuously, and if there is an energy supply from outside (from vacuum) in these processes, it is all used inside the nozzles to obtain a higher dispersion effect or oil cracking.

The nozzle shown in FIG. 11 allows both to remove excess gas from the nozzle 1 from the nozzle 1 during the cracking process and to supply additional gas-liquid and gaseous components using (of course!) Additional compression or evacuation (not shown in FIG. 11). It is clear that a huge range of technological options can be realized in the Gear head. It should be noted that the device depicted in Fig. 11 differs from any ejectors in that the gas sucked in due to the ejection effect into the nozzle 1 itself is involved in accelerating the flow to supersonic speeds, which also leads to energy saving. Shesterenko nozzles can be widely used as a converter of a natural alternative energy source (wind rose) and this does not require additional evidence.

With equal pressure drops in the proposed devices compared with the known nozzles in our device, the output will always be significantly greater speed, which is very important in many industries.

It should be noted that gases differ from each other in the chemical formula and physical parameters. Considering the work of the Shesterenko nozzle above, we talked about abstract and ideal gas.

Now let's move on to the real gases "that need to be transported from the field to the consumer or to production and see what happens to them in our case. All substances known to people have four phases of the state: solid, liquid, gaseous and plasma. In order to appreciate the invention, we consider a more complex version of the behavior of gas and gases in the invention, relating to devices and processes of chemical technology. With a constant source of forced pumping gas, we take gaseous Cetane at the inlet of the Nadadok Shesterenko. In any of the variants shown in the figures, behind the first critical section in the direction of the first ejecton pair, where there is a vacuum cavity, vacuum cracking occurs, transferring the source gas in various proportions to Octane gas plus Hexane gas, plus Ethylene gas. With the correct geometry of the second and subsequent nozzles in the direction of gas movement, a sharp increase in the volume of moving gases is not blocked. In subsequent ejector vapors, in the presence of evacuated cavities, cracking occurs, but with the resulting gases when they are split into smaller molecules. We get continuous vacuum cracking from the first ejector pair to the last. The boiling point of a straight run residue, i.e. the temperature during vacuum cracking of the complete boiling off of crude oil, until now no one has been able to determine exactly, but it is very low and the oil begins to boil beyond the first critical section, turning into a gaseous state. Therefore, there is no need to preheat the oil in order to transfer it in front of our device (Shesterenko Nozzle) to a gaseous state (but formally or for technological reasons this can be done). From the simple logic of things, Cetane gas at a flow rate of one gallon per unit time in the critical section of the first nozzle of the Shesterenko nozzle has a lower speed than completely converted to ethylene gas or methane gas or their mixture at the outlet of the Shesterenko nozzle, which has a volumetric volume in the same unit of time consumption from 1.4 to 2 or more gallons. It should be noted that at the same time, the same quantity in weight terms passes through each cross section per unit of time (i.e., the mass or number of atoms remains unchanged). With proper profiling, the Shesterenko nozzle, and having organized vacuum cracking inside it, we will inevitably receive an increase in the flow rate of all the initial atoms, but with other molecular bonds. This is one of the main properties of the Shesterenko nozzle and the proposed method of ejector acceleration of gas! The energy balance of vacuum cracking has not been studied and does not correspond to the logic of primitive thermodynamics, although vacuum cracking is used in all oil refineries. There is another feature of the Shesterenko nozzle and the method of ejector acceleration of gas in that when cetane gas is converted to ethylene gas or methane gas, vacuum coke forms coke and sticky residue, which are concentrated in the central part of the gas flow due to shock waves and other geometric features , being essentially particles of an aerosol. These aerosol particles can, as was previously said, be discharged together with the central part of the flow with a shut-off device equipped with a vacuum pump for further processing (not shown in the figures), but a nozzle or nozzle 93 with an ajar overlap device 97 can serve as such a shut-off device Cutoffs can be of various designs - this is not the main thing. A variant is possible (Fig. 11) when a mixture coming from a reforming unit (hydrogen concentrate) or pure Hydrogen is fed through a Laval nozzle 102. Cetane gas enters the nozzle 1a conditionally from the outside due to the ejection effect. At the exit from section 15a, as a result of cracking, we have methane gas. Due to the ejection effect, the next portion of Cetane gas enters the nozzle 1, which in turn will undergo vacuum cracking. The stream flowing at high speed, first behind the Laval nozzle 102, and then over section 15a immediately provides the highest concentration of aerosol particles resulting from vacuum cracking in the central part of the stream. At the exit of the supersonic Laval nozzle 5, we have a gas or a mixture of ethylene and methane gases. The Laval nozzle 5 can serve as an accelerating nozzle like Laval nozzles 102 or 5a. Thus, by repeatedly repeating new cascades from the Shesterenko Nasadki, the required vacuum cracking performance will be achieved, and the coke and sticky residue, coagulating upon collisions with each other, will increase in size and can be easily removed from the flow due to inertial forces, as described in the embodiment Fig.21 or in another way. In order to flexibly respond to changes in the proportions of gases (or grades of oil and source gas) and not to stop the working process, you can use the device shown in Fig.20. As it was said earlier, the start-up and operation of the device can be carried out in a combined mode, as shown in Fig. 19 using a compressor 152 and a vacuum pump 91. The technological need that may arise during vacuum cracking can cause an urgent selection (removal) of excess the volume of the cracked product in the tank 146 either through a vacuum pump 91 or during periodic shutdown of the compressor 152 (Fig. 19) or the compressor in communication with the Laval nozzle 102, but it is better to regulate such emergency situations with lementami depicted in Figure 20. Everything described exactly corresponds to the processes occurring during vacuum cracking. To enhance the effect of vacuum cracking in figure 2, 3, 4, 6 and 8 shows a large number of evacuated cavities of various shapes. Each of these configurations is preferred for a particular case of a proportional combination of gases and aerosol. Compensation for a sharp increase in gas volume is achieved by increasing the cascades of ejector pairs and selecting the geometry parameters of the nozzles 3, 5, and 114, as shown in Fig. 14. Moreover, sections B and D are intensive cracking zones, and if there are a lot of such zones (many ejector pairs), then the Titan gas can be completely converted into Hydrogen gas and coke aerosol. And the cracking effect of the difference in the volumes and the difference in the velocities of the molecules of the Cetane gas and the Methane or Hydrogen gases forms a gap between these volumes in the Shesterenko cavity in the form of a high vacuum (or, relatively speaking, vacuum), which in turn guarantees constant suction of new portions of Cetane and stable operation of the Nozzle Gear in a wide range of changes in pressure drop and even with short-term and relatively long-term shutdowns of the source of forced gas pumping, which is very important when transporting native gas and oil deposits from the tubes to the processing plant. As mentioned earlier, the aerosol of coke and sticky residue is inertially removed from the stream of obtained gases. The critical sections of all subsequent nozzles are not less than the critical section of the first nozzle (i.e., can be equal and large in an unlimited range), and this plug of changes in critical sections allows you to set the necessary gap in the form of a vacuum cavity between the Cetane gas and any gas obtained as a result our cracking. Moreover, for an ideal gas, with the correct profiling of all nozzles, the first and last critical sections should be equal, but for any deviation from the ideal gas and geometric errors, the last critical section, like all intermediate ones, should be greater than the first. It should be noted that the degree of transition of large molecules into smaller ones depends on the number of ejector pairs, and at the same time, an increase in the volume of gas and an increase in the speed of moving molecules and the amount of coke at the exit from the Shesterenko nozzle. Other polyatomic gases behave similarly, decomposing into smaller gases in the Shesterenko nozzle, and a difference in the volumes and velocities of the initial polyatomic and the resulting low-atomic gases also arises. Air in our industrial age is a mixture of not only ideal gases, but also a mixture of polyatomic gases and liquid aerosols, and the technical vacuum obtained due to the ejection effect in the Shesterenko nozzle is, figuratively speaking, a cracking catalyst. However, the shutdown of the compressor or vacuum pump or their joint work is dictated by technological processes. The author only shows the modest possibilities of his invention. The tank 100 (Fig. 10, 12, 13 and 19) with a nozzle or pipe 93 can play the same role as the storage hopper 202 (Fig. 21). However, with the compressors turned on at the inlet of the Shesterenko nozzle and the vacuum pump 98 and with the open (or ajar) overlapping devices 92 and 97, it is possible to provide a continuous coke outlet with part of the gas stream.

The essence of the invention is to create conditions in the Shesterenko nozzle that, with equal pressure drops, accelerate the gas (the atoms that make up the gas) to high speeds compared to known nozzles. In the considered variant, we have a source gas at the inlet, and at the outlet we have a gas with smaller molecules, while the liquid aerosol passes into a gaseous state. The tank 100 (Fig. 10, 12, 13 and 19) with a nozzle or pipe 93 can play the same role as the storage hopper 202 (Fig. 21). However, with the compressors turned on at the inlet of the Shesterenko nozzle and the vacuum pump 98 and with the open (or ajar) overlapping devices 92 and 97, it is possible to provide a continuous coke outlet with part of the gas stream.

It should be noted that the Shesterenko super-nozzle can equally be called a device of the “injector” or simply “acceleration of gas”:

1. The gas acceleration device, consisting of nozzles hermetically mounted to each other, the critical section of each of which is not less than the critical section of the first nozzle in the direction of gas movement, characterized in that at least one nozzle is coaxially inserted into the next one from the first nozzle with the formation between them cavity.

2. The device according to paragraph 1, characterized in that at least one nozzle is installed with the possibility of axial movement.

3. The device according to paragraphs 1 and 2, characterized in that at least one nozzle is made in the form of a tapering nozzle.

4. The device according to paragraphs 1 and 2, characterized in that at least one nozzle is made in the form of an expanding nozzle.

5. The device according to paragraphs 1 and 2, characterized in that at least one nozzle is made in the form of a cylinder.

6. The device according to paragraphs 1 and 2, characterized in that at least one nozzle is made in the form of a venturi.

7. The device according to paragraphs 1 and 2, characterized in that at least one nozzle is made in the form of an opening.

8. The device according to any one of paragraphs 1 to 7, characterized in that in the first nozzle in the direction of movement of the gas, a coaxial nozzle device is installed in communication with the pressure source.

9. The device according to paragraph 8, characterized in that the nozzle device is mounted with axial movement.

10. The device according to paragraph 8, characterized in that at least once the nozzle device is made in the form of a gas acceleration device, but of a smaller size.

11. The device according to paragraph 9, characterized in that at least once the nozzle device is made in the form of a gas acceleration device, but of a smaller size.

The technical effect is that: 1) with a sufficient pressure drop, when you can create only the ejection effect at subsonic speed, conditions are created in the cavities for a gradual increase in speed from subsonic to supersonic speed and the transition of the device to a stable supersonic and hypersonic mode due to created vacuum in ejected cavities, as well as cracking, which dramatically expands the scope of application of the Shesterenko nozzle and reduces energy consumption, and this makes the nozzles attractive for a wide range of applications. CAA technical problems; 2) the use of containers that are pre-evacuated in any way as a vacuum source, as well as connecting them and a vacuum pump to evacuated cavities, allows you to repeatedly stop and start the installation, remove excess cracking product and increases technological capabilities, which expands the scope of the proposed device; 3) changing the operating angles of inclination and the area of the critical sections of the nozzles, as well as changing the distance between the critical sections, expand the maneuverability of the proposed device and its scope; 4) as a result of vacuum cracking inside the nozzle, rupture regions or a rarefaction region (or vacuum) are created between polyatomic and low-atomic gases (the “Shesterenko piston effect” conditionally called by the author), which, in turn, ensures the stability of the operating mode with a large range of pressure differential up to a temporary shutdown of the source of forced pumping of gas.

The technical effect is also as follows.

a) In the cavities 13, 13a (11) due to ejection there is a vacuum, which equally affects the ejection stream. Inevitably, between the critical sections 2 and 4 or 2a 4a (as in the resonance chamber), a resonantly pulsating flow flow occurs, which necessarily takes place in the output sections 15 and 15a. Such a resonant-pulsating flow is inherent in all Shesterenko nozzles. The pulsating active jet coming from the outlet section 15 moves like a wave-like comb, pulling an additional mass of gas into the next Shesterenko nozzle into section 2. From OKKudrin’s book “Pulsating jet nozzle with additional mass attachment” (MAI works, 1958), as well as from the discovery of OI Kudrin, AV Kvasnikov, VN Chelomey, USSR diploma No. 314 “Phenomena an abnormally high increase in thrust in a gas ejector process with a pulsating active jet »1975 (priority from 1951) it is known that when ejecting atmospheric air with a pulsating jet, an abnormal increase in reactive force was experimentally obtained up to 140% of the initial thrust, i.e. traction increased 2.4 times. Therefore, the variant depicted in FIG. 11 is, if not a perpetual motion machine of the second kind (i.e., operating on the pressure energy of the surrounding atmosphere), then probably the most highly efficient device for using the pressure energy supplied to the Laval nozzle 102 through the gas duct 103.

b) The number of Shesterenko nozzles in Fig. 11 can be any, and in each subsequent nozzle there will be an abnormal increase in reactive force by another 140% with respect to the previous pulsating active jet.

Therefore, it is possible to obtain a final stream at the outlet that is able to compensate for the cost of obtaining pressure in the gas duct 103 and provide energy for the consumer.

Claims (5)

1. A nozzle containing nozzles hermetically connected to each other, and the critical section of each nozzle is not less than the critical section of the first nozzle in the direction of gas movement, characterized in that at least one nozzle is rigidly or axially moved coaxially into the subsequent direction of travel gas nozzle with the formation of a cavity and is made in the form of a supersonic nozzle, or in the form of a venturi, or in the form of an opening, or in the form of a tapering nozzle, or in the form of a cylinder, or in the form of a combination thereof, or in the form of expanding la. 2. Nozzles according to claim 1, characterized in that in the first nozzle in the direction of travel of the gas, the excitation nozzle is in communication with the source of high pressure and is not tight or rigid, or with the possibility of axial movement. 3. Nozzles according to claim 1 or 2, characterized in that the inlet or outlet or inlet and outlet sections of the nozzle are installed in tanks, each of which is communicated through an overlap device with a source of forced gas pumping and is equipped with an opening or a tapering nozzle, or a supersonic nozzle, or a nozzle, each of which, in turn, is equipped with an overlapping device and has a critical cross section not less than the first nozzle in the direction of gas movement. 4. Nozzles according to claim 1, characterized in that the line connecting the reservoir to the source of forced pumping due to the rarefaction of the gas is equipped with at least one additional nozzle, and each subsequent additional nozzle in the direction of travel is smaller than the previous one, and the first in the direction of travel The gas nozzle of each subsequent nozzle is communicated with the line of each previous nozzle. 5. Nozzles according to claim 2, characterized in that at least once the exciting nozzle is made in the form of a nozzle containing nozzles hermetically connected to each other, and the critical section of each nozzle is not less than the critical section of the first nozzle in the direction of gas movement, but smaller in comparison with each subsequent nozzle in the direction of gas movement.

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