WO2021146779A1

WO2021146779A1 - Pulse detonation jet engine (propulsor) vujin

Info

Publication number: WO2021146779A1
Application number: PCT/BA2021/000001
Authority: WO
Inventors: Zoran VUJINOVIĆ
Original assignee: Vujinovic Zoran
Priority date: 2020-01-24
Filing date: 2021-01-19
Publication date: 2021-07-29

Abstract

Pulse detonation propulsor Vujin, is a high stage in the development of pulse detonation propulsors. It is intended primarily for the propulsion of aircraft, and with minor modifications it can also be used as a combustion chamber for the propulsion of gas turbines. The construction consists of an inlet (8) with a resonant chamber (10), an air flow regulator (9) of Tesla fluid diodes (8), pulse jet compressors (16) and (17). The detonation chamber (13) in the middle part has a starting injector (11) with a spark plug (12), the front part ends with a traction wall with an integrated detonation stabilizer (2). In the rear is the jet tube (15). Technical solutions and procedures enable wide application of pulse detonation propulsor Vujin, primarily for use in high speed and high altitude regimes. Depending on the operating conditions, it can be used as an aspiration or autonomous propulsor. The field of technology is mechanical engineering.

Description

PULSE DETONATION JET ENGINE (PROPULSOR) VUJIN

1. FIELD OF THE INVENTION TO WHICH THE INVENTION RELATES: According to the International Patent Classification ( MKP, Intel.7) the technical field to which the invention relates is mechanical engineering. It is classified and marked with classification symbols F02K7/04.

2. TECHNICAL ISSUE

Pulse detonation jet engines (hereinafter called pulse detonation propulsors) originated on a pulse propulsor platform. The first patents for a pulse propulsor were obtained independently of each other in 1865 by Charles de Louvier (France), and in 1867 by Nikolai Afanasievich Teleshov (Russia). The first usable design was patented in 1906 by the Russian engineer V.V. Karavodin. The propulsor operating on the real spacecraft was the German Argus As 014, based on the 1931 Munich patent by inventor Paul Schmidt. Argus was created for the "weapon of revenge" - the "V-l" winged bomb. A similar development was created in 1942 by Soviet designer Vladimir Chelomey for the first Soviet 10X cruise missile.

The pulsating propulsor works on the principle of pulsed combustion and exchange of working matter (Humphrey cycle). By combustion, the heat released creates a jet, which creates a thrust to propel the aircraft. This type of propulsor is characterized by simplicity of operation and manufacture. It consists of an air inlet, a combustion chamber, fuel injectors and a nozzle. They can be with or without air intake valves. The key difference between a pulse and a pulse detonation propulsor is in the way it releases heat. In pulsed propulsors, heat is released by a flame wave that moves slower than sound (deflagration), dividing the zone of fuel mixture and combustion products, while in detonation propulsors, heat is released at a rate faster than sound (detonation) with a sudden increase in pressure and temperature.

The development of existing propulsors has reached the limit of its capabilities. Further improvement of their specific characteristics is expected within very small limits. Therefore, the industry is forced to look for new technical solutions. Attempts to overcome the crisis with the help of nuclear power have encountered environmental problems and are still in the development phase, far from being widely used. As an alternative to the new propulsion, due to its superiority, simplicity, low manufacturing costs and technical solutions that are the subject of 2 this Patent application, pulse detonation propulsors are imposed as a solution for propulsion of aircraft in the future.

This type of propulsion has been in the research and development phase for more than seventy years, with no practical results that would lead to mass application of the concept. The solution to a technical problem that enables the practical application of this type of drive becomes a "Challenging Project".

Technical solution of the problem:

The technical problem we are trying to solve with this invention consists of the construction of a completely new pulse detonation propulsor based on different principles of operation compared to the previous ones.

The solution to the technical problem consists of the following technical solutions and procedures:

1. brand new pulse detonation propulsor that is adaptable to the conditions of exploitation in the atmosphere or space, easy to design and manufacture with low manufacturing costs.

2. technical solutions and procedures where one propulsor can be used in the mode of operation as an aspiration (atmospheric), autonomous (rocket) or combined (hybrid) propulsor.

3. technical solutions and procedures that regulate the required number of pulses - frequencies,

4. technical solutions and work procedures without moving parts,

5. technical solutions and procedures for preparation, introduction and compression and detonation of the fuel mixture,

6. technical solutions and procedures that increase the thrust strenght while reducing fuel consumption,

7. technical solutions and procedures that achieve detonation stability,

8. technical solutions and procedures that achieve dynamic balance,

9. technical solutions and procedures that increase the degree of usefulness,

10. technical solutions that increase the reliability and time of exploitation,

11. technical solutions that reduce maintenance costs,

12. technical solutions that enable mass reduction per unit of output power,

13. technical solutions that enable the use of several types of fuel,

A review of the state of technic and patent documentation in the field related to propulsors did not find any similar solution relevant to the subject patent application.

3. STATE OF THE TECHNIC

A chemical pulse propulsor is a heat engine that has the task of converting the chemical energy introduced in the form of propellant into thrust by combustion. Depending on the method of releasing chemically bound energy and converting it into thrust, pulse propulsors can be divided into two groups: Pulse propulsors and pulse detonation propulsors. 3

Pulse propulsors

The pulse propulsor is based on a process in which the intake of air, fuel, combustion and thrust takes place in pulses. The propulsor is of extremely simple construction and consists of a suction cup, a non-return valve system, a combustion chamber, fuel injectors and a nozzle.

They have a very small static thrust and it increases with increasing speed, ie with dynamic pressure. They are developed in variants with and without non-return valves, they work in pulse mode. The initial ignition of the fuel-air mixture is with a spark plug. When the combustion chamber liner is sufficiently heated, the mixture ignites from its warm walls and from the residual sparks from the previous cycle.

Pulse propulsors with valves

Pulse propulsors are developed in variants with and without non-return valves. Non-return valves are the most sensitive part of the system and they limit the operating life, which is why they are the main obstacle for the wider application of valve solutions. The construction of the pulse propulsor consists of a cylindrical combustion chamber, with an extension to the nozzle and with a narrowing. At the front of the combustion chamber, there are fuel injectors. While the pressure in the tank is higher in relation to the chamber, the fuel is injected, and when it is reversed, the non-return valves on them interrupt it and it alternately continues. On the front part of the cylindrical body there is a suction cup for receiving air in the combustion chamber. There is a transverse partition between the combustion chamber and the suction cup, which is also the carrier of the non-return valve system. Valves on the principle of pressure difference let air into the chamber, and prevent the flow of gas from it to the suction, so the gas is forced to flow only through the nozzle after combustion of the mixture.

Pulsating U - shaped jet engine without valve

This is a modified classic version of a pulsating jet propulsor in which there are no moving parts (valves). The construction consists of an inlet, a combustion chamber with injectors and a nozzle. Initial air under a certain dynamic pressure is necessary to start work. The suction cup and the nozzle are parallel to each other in the shape of the letter U, so that part of the thrust is not lost due to the return flow through the suction cup, since it is in the same direction as through the nozzle. They produce thrust in two parts, but in synchrony, with the acceleration of the mass of the flowing gas during discharge through the nozzle and back through the suction tube. It works by mixing the dispersed fuel with the air in the combustion chamber. It ignites with a spark. The explosion of the mixture expels gases through both tubes, but a much smaller mass through a shorter (suction) tube. The pressure in the chamber drops and fresh air enters it through the suction (shorter) tube, while the gases still leave the longer tube (nozzle). The essence of the principle of operation of a pulsating jet propulsor in the shape of the letter U is that the mass of the outlet gas flow tube through the shorter outlet tube is smaller and due to inertia the discharge ends faster through it than through a long nozzle of larger diameter. Due to that fact, due to the longer flow of gas through the nozzle, due to greater inertia, a pressure difference is created behind the gas jet, in the front part of the chamber, due to which the suction 4 through the shorter tube begins. A part of the hot gases remains in the chamber, from which the new mixture is ignited and thus the cycle is repeated.

Pulse detonation propulsor

This type of pulsating propulsor is the latest principle and practically derived from the previous one. It was created with the knowledge that shortening the tube contributes to increasing the thrust. There was a simple construction where the suction and blowing tubes are common and very short. This solution is possible due to the oscillatory behavior of the pulse. One "jar lid opening" can act as an exhaust tube, in the work cycle phase, and as a suction tube during the suction phase. This propulsor construction is of reduced efficiency and is used to clarify the principle of operation in the most primitive form. Due to the absence of a resonant tube, compression and suction are accompanied by strong acoustic waves. However, the device works quite well, even if it is simple, like a jam jar with a lid, on which an opening is made. The jar is partially filled with flammable fuel, which evaporates. From this similarity comes the name of the device, "jamjar". During operation, part of the evaporated fuel mixes with the air, above the surface of the liquid fuel level. This mixture initially ignites with a spark from the outside and a pressure jump and explosion occurs. The burnt and part of the unbumed gases expands abruptly and flows out, at high speed, through the opening of the lid of the jar, creating a thrust. By inertia and due to the cooling of the vessel, the pressure in the chamber ("jar") drops, below the level of the external atmospheric level. Fresh, outside air is sucked into the space above the fuel. Since it was inserted by the return wave, by inertia, its final pressure is slightly higher than the external one. The fuel in the tank heats up and evaporates more intensively. A flammable and explosive gaseous mixture of fuel and air is created again and it ignites from the heated residual filaments, from the previous cycle. The cycle is repeated and the device is temperature stabilized while equalizing the supply and removal of heat.

Detonation propulsors

Detonation propulsors today are divided into two main types: pulse and rotary. The idea of a detonation propulsion was proposed by the Soviet physicist J. B. Zeidovich in an article "On the use of detonation combustion energy", published in the Journal of Technical Physics back in 1940. Along with him, Von Neumann (USA) and Werner Doering (Germany) came to the same conclusion, so that in international science, the model of using detonation combustion is called the CIS. Since then, the possibilities of applying the propulsion of the fiiture have been researched around the world, and this is the first official work in the Republic of Srpska - Bosnia and Herzegovina.

Detonation combustion is a process of instantaneous release of heat caused by the action of a detonation wave that propagates through a mixture of fuel and oxidant at speeds greater than sound. This kind of combustion is so fast that the reaction products do not even have time to expand, so this process proceeds at a constant volume, sharply increasing the pressure and temperature. Inside the combustion chamber, a detonation wave is formed that travels at supersonic speeds. At this compression pressure, a mixture of fuel and oxidant explodes, and 5 from a thermodynamic point of view this process is much more efficient than subsonic fuel combustion. Chemical reactions are so fast that there is no formation of nitrogen oxides in the combustion process, which is very important when assessing environmental acceptability. The principle of operation of pulses with pulsed detonation is based on the principle of previously described pulses. The construction is with the difference that one end of the tube is closed (traction wall) and the other end of the tube is open for the exit of gases and the creation of thrust. By cyclically filling the combustion chamber with the fuel mixture, its successive ignition, the fuel is injected into the combustion chamber, bums in one or more detonation waves, exits at high speed creating a thrust. The problem with these propulsors is the stable initiation of detonation of the mixture, which is tried to be solved in various ways, starting from the input of a strong energy source by initial ignition, to placing various obstacles (Shelkin spiral) in the tube where is flame acceleration and transition from deflation to detonation. The main problem in the development of this type of propulsor is the insufficient number of frequencies, uncontrolled fuel combustion, the problem with starting the detonation, problems in making the mixture, trying to integrate the suction and nozzles. All this keeps this type of propulsion far from practical application.

Rotary detonation propulsors

In pulse propulsors, short explosions of a mixture of fuel and air occur, which are repeated periodically. In rotary combustion, the mixture is formed continuously without stopping. The construction of the propulsor consists of an annular combustion chamber into which the fuel mixture is continuously introduced through radially placed valves. The detonation wave inside the chamber does not move in the axial direction compressing and burning the fuel mixture in front of it and finally pushing the combustion products out of the nozzle in the axial direction. Instead of the pulsation frequency, we get the rotational frequency of the detonation wave, which can reach several thousand Hz per second, the propulsor practically does not work as a pulsating, but as a continuous jet but much more efficient, because it actually detonates the fuel mixture.

The rotary detonation propulsor was first studied in the USSR in the 1950s. The phenomenon of rotating detonation was theoretically predicted by the Soviet physicist from Novosibirsk B. V. Voitsekhovsky in 1960. Almost simultaneously, in 1961, the same idea was put forward by the American J. Nicholls of the University of Michigan. Today, research is being done in all technologically advanced countries of the world.

Detonation propulsors can operate in a wide range of speeds from subsonic to supersonic flight speeds. Detonation releases more chemically bound energy from the same amount of fuel, so detonation propulsors use much less fuel for the same power than conventional jet propulsors. The construction of detonation propulsors is relatively simple, there are no moving parts, so they are reliable in operation and cheaper to manufacture and maintain. 6

4. DISCLOSURE OF THE ESSENCE OF THE INVENTION

The primary object of the invention is to construct a completely new propulsor, without moving parts, which can make better use of the chemical energy of the input fuel, with low harmful emissions, not to use motor oils and thus be more environmentally friendly than existing chemical propulsors.

A secondary object of the invention is to construct a hybrid propulsor, which when it is needed, can be used as an external oxidant from the atmosphere or an internal oxidant in rocket propulsion, while maintaining high performance.

Further objects of the invention are the development of propulsors in the direction of completely pure drive technologies.

By constructing a new pulse detonation propulsor Vujin, on a completely new basis, the problem defined above was solved.

The construction of the Vujin pulse detonation propulsion consists of an air inlet, which has the required length to enable resonant compression of the intake air. The inlet ends with a resonant chamber in which the flow regulators are located, which supply pulse compressors via Tesla's fluid diodes. Starting injectors with spaik plugs are located in the central part of the detonation chamber. At the front of the detonation chamber there is a traction wall in which the detonation stabilizer with the necessary elements is integrated. The jet tube, which performs the execution of the combustion products and the thrust of the aircraft, is integrated in the rear part of the detonation chamber, together with the rear pulse compressor. Pulse jet compressors are located in the front and rear of the detonation chamber, using part of the fuel energy that is introduced into the detonation chamber for its own drive. They are responsible for operational reliability, combustion rate and propulsor power. When the required amount of fuel is introduced into the detonation chamber, which is under atmospheric pressure, via the starting injectors, then the injectors of the pulse compressors and detonation stabilizers also disperse the set amount of fuel. After the given concentrations of the mixture are formed, the spark plug in the detonation chamber ignites the mixture. After ignition in the detonation chamber, there is a sudden jump in pressure and temperature. Part of the gases through the jet tube leaves the chamber making a thrust, and part of the gases goes to the pulse compressors and the detonation stabilizer, increasing the pressure and temperature of the mixture. The hot gases, which flowed at high speed, ignite the mixture in the detonation stabilizer and the drive chambers of the pulse compressors. There is a sudden jump in pressure and temperature. The pressure in the detonation chamber suddenly drops sharply as the gas flows out through the jet tube, so the hot gases from the pulse compressors and detonation stabilizers suddenly flow into the chamber, bringing with them the unburned mixture. The pressure in the chambers drops sharply, so the injectors that are under constant pressure from the common tank disperse the fuel and a part of the fuel enters the detonation chamber with accelerated current, where it mixes with the rest of the mixture and due to sudden forceful hits of detonational waves, jump of the temperature and pressure, there is self-ignition of mixture and detonations or instantaneous combustion. One part of the gases leaves the detonation chamber through the jet tube and makes a thrust and part of the gases flows again into the chambers of pulse compressors and detonation stabilizers and the 7 cycle repeats. Thrust was produced to propel the aircraft. Cooling of the pulse detonation propulsor Vujin is provided by the inlet air. On the way from the air inlet to the entrance to the detonation chamber, fresh air obstructs all the heated elements of the propulsor, taking on the waste heat. The incoming air, taking over the waste heat, enriches itself energetically and increases the energy efficiency of the propulsor, returning the waste heat back to the thermodynamic process.

5. BRIEF DESCRIPTION OF THE DRAWINGS

In order to better understand the invention, to explain it in more detail and realising the invention, a single figure clearly shows a construction with a clear appearance and position of all the essential components. The figure gives a detailed description of at least one of the embodiments of the invention. The invention is in the longitudinal section of a complete assembly consisting of an inlet with a resonant chamber. Pulse jet compressors are powered to Tesla's fluid diodes via a flow regulator. The front part of the detonation chamber ends with a traction wall in which the detonation stabilizer is integrated. The starting injector and spark plug are in the central part of the chamber. In the rear is a jet tube with a rear pulse jet compressor.

6. BRIEF DESCRIPTION OF ONE OF THE MANNERS OF ACHIEVEMENT

The best way to describe one of the embodiments of the invention is to illustrate the presentation with the attached Figure 1, which describes in detail the appearance. In the list for Figure 1, the ordinal numbers for the components are given, which I will use in the description of the method of carrying out the invention. In Figure 1 we have the longitudinal section of the pulsed detonation propulsor Vujin and the appearance of its components. The engine consists of six assemblies consisting of: a resonant chamber inlet, a supply air flow regulator with Tesla fluid diodes, pulse jet compressors, a detonation stabilizer, a detonating chamber and a jet tube for thrusting the aircraft.

Method of describing the operation of a pulse detonation propulsor Vujin:

To describe the mode of operation of the engine, we use Figure 1 and the designations of the parts marked with ordinal numbers from 1 to 17.

Start of pulse detonation propulsor Vujin

The propulsor has a detonation chamber 13 of constant working volume. At rest, the detonation chamber 13 is filled with atmospheric pressure by the surrounding air, which freely enters the interior of the propulsor via the thrust jet 15. By starting the propulsor via the starting injector 8

11 and the injectors with Tesla's fluid diode 3, the required amount of fuel is introduced into the detonation chamber 13, the drive chamber of the pulse jet compressors 6 and the detonation stabilizer chamber 2. Once the set fuel / oxidant ratio has been reached, the mixture is ignited via spark plug 12. In the detonation chamber 13, the pressure and temperature of the combustion products increase sharply. Part of the combustion product flows at high speed into the thrust jet 15 and part of the hot gases under pressure flows at high speed through the inlet of the detonation stabilizer 7 into the detonation chamber 2 in which the dispersed fuel is ignited. Simultaneously with the flow of hot gases into the detonation chamber 2, the hot gases flow through the inlet of the pulse compressors 14 into the working chamber of the pulse compressors 4 where they mix with fresh air increasing the pressure and temperature of the chamber. Tesla's fluid diodes 8 prevent the flow of hot gases towards the resonant chamber 10, so that the hot gases, through the nozzle of the pulse jet compressor 5, flow into the drive chamber of the pulse jet compressor 6, where the dispersed fuel mixes with the hot gases and ignites. The pressure and temperature in the chamber rises sharply. The hot gases from the detonation chamber 13 flow out at high speed through the thrust jet 15, creating a thrust. The large rapidly accelerated mass of gas escaping from the thrust jet 15 in the detonation chamber 13 lowers the pressure, so that the gases in the detonation stabilizer 2 and the drive chamber of the pulse jet compressors 6 are under much higher pressure than the pressure in the detonation chamber 13. Due to the pressure differences hot gases from the detonation stabilizer 2 and the working chambers 6 of the pulse jet compressors flow into the detonation chamber 13 at high speed. The gas jet that is expelled from the working chamber 6 of the pulse jet compressor enters the working chamber 4 at high speed through the nozzle 5. Possessing high speed, the emitted hot gases have a large amount of movement. Due to the high flow rate, the pressure of the hot gas current drops, so that it sucks in the surrounding air from the working chamber 4 giving it part of the energy, slowing itself down and the sucked fresh air particles receiving part of the energy thus accelerating themselves. The fuel mixture flows through the inlet 14 of the pulse compressor into the detonation chamber 13, where the mixture is slowed down and the speed is translated into pressure. Due to the sudden discharge, a vacuum is created in the detonation stabilizer chamber 2 and the drive chamber 6 of the pulse jet compressor. Due to the pressure difference, the injector with Tesla fluid diode 3, which is under constant set pressure from the common tank, re-injects the set amount of fuel into the detonation stabilizer chamber 2 and the drive chamber 6 of the pulse jet compressor. Part of that fuel leaks out of the chambers forming an unbumed mixture in the detonation chamber. The injection lasts until the pressure in the detonation chamber reaches the set value and becomes higher than the fuel injection pressure. Suddenly flowing gases increase the pressure and temperature of the fuel mixture in the detonation chamber 13. Due to the high pressure, three flame fronts collide, one coming from the detonation stabilizer 2, the other front coming from the front pulse jet compressor 16 and the third front coming from the rear jet pulse compressor 17. In this process, a large amount of heat is transferred to die unbumed mixtures of residual combustion products and the mixture itself becomes explosive. Due to the increase in pressure and temperature, high-velocity shock waves are formed locally. The waves quickly reach the walls of the detonation chamber 13, 9 bounce off them, resulting in high-frequency pressure oscillations in the detonation chamber 13. The interaction of the reflected waves leads to their local superposition and formation of a shock wave that causes detonation combustion with immediate release in the detonation chamber 13. Part of the combustion products, at high speed pushes the residual gases inside the detonation chamber 13 and together with them flows into the thrust jet 15, and part of the hot gases under pressure flows at high speed through inlet detonation stabilizator 7 in detonation chamber 2 in which dispersed fuel ignition occurs. In parallel with the flow of hot gases into the detonation stabilizer 2, the hot gases flow through the inlet of the pulse compressors 14 into the working chamber of the pulse compressors 4 where they mix with fresh air increasing the pressure and temperatures of the working chamber 4. Tesla's fluid diodes 8 prevent the flow of hot gases towards the resonant chamber 10, so that the hot gases flow through the nozzle of the pulse jet compressor 5 into the drive chamber 6 of the pulse jet compressor in which the dispersed fuel mixes with hot gases and ignites, and pressure and temperature in the chamber 6 grows rapidly. The hot gases from the detonation chamber 13 flow out at high speed through the thrust jet 15, creating a thrust. The large mass of gas escaping from the thrust jet 15 in the detonation chamber 13 lowers the pressure so that the gases in the detonation stabilizer 2 and the working chamber 6 of the pulse jet compressors are under much higher pressure than the pressure in the detonation chamber 13. Due to the large difference in pressure, hot gases from the detonation stabilizer 2 and the drive chambers 6 of the pulse jet compressors flow at high speed into the detonation chamber 13... and the process is repeated. Pulse detonation propulsor Vujin works.

7. METHOD OF APPLICATION OF THE INVENTION

The Vujin pulse detonation propulsor is intended primarily for the propulsion of aircraft, and with minor modifications it can also be used as a combustion chamber for the propulsion of gas turbines. Technical solutions and procedures enable wide application of pulse detonation propulsor Vujin, primarily for use in high speed and high altitude regimes. Depending on the operating conditions, it can be used as an aspiration or autonomous propulsor. The Vujin pulse detonation propulsor works with high efficiency without moving parts with low harmful emissions and low operating maintenance costs. It can be used in subsonic and supersonic speeds.

Workshop and project documentation for the realization of the invention can be made by experts in the subject field using the description and drawings from the subject Patent application, and the prototype can be made in plants engaged in the production of jet propulsors. ujinovtc Zoran

Claims

10 PATENT REQUIREMENTS

1. Pulse detonation propulsor Vujin, similar to the existing constructions of the pulse propulsor, characterized in that it is set on completely new principles of operation, with forced introduction and compression of the fuel mixture, by pulse jet compressors (16) and (17). Fuel introduction is realized through injectors (3) with integrated fluid Tesla diodes. In each pulse, when the pressure in the detonation chamber (13) is less than the pressure in the injectors (3), fuel is introduced into the process. Injectors (3) under constant pressure. The construction of the Vujin pulse detonation propulsion consists of an air inlet (1) which has the required length to enable resonant compression of the intake air. The inlet (1) ends with a resonant chamber (10) in which the flow regulators (9) are located, which supply the working (4) and operating (6) chambers of the pulse jet compressors (16) and (17) via Tesla fluid diodes (8). Starting injectors (11) with spark plugs (12) are located in the central part of the detonation chamber (13). At the front of the detonation chamber there is a traction wall in which the detonation stabilizer (2) with the necessary elements is integrated. The jet tube (15) which performs the derivation of the combustion products and the thrust of the aircraft is integrated in the rear part of the detonation chamber (13) together with the rear pulse compressor (17).

2. Pulse jet compressor Vujin, similar in construction to existing jet compressors, characterized in that it does not use an external energy source as a drive fluid. For their own drive, they use part of the fuel energy that is introduced into the drive chamber (6). The construction consists of a drive chamber (6) with a nozzle (5) at the rear end of which is an integrated fuel injector (3) with a Tesla fluid diode. The working chamber (4) is supplied with fresh air from the resonant chamber (10) via Tesla's fluid diodes (8) and the flow regulator (9). Through the inlet of the pulse compressor (14), the working chamber (4) is connected to the detonation chamber (13) into which it introduces the fuel mixture under pressure.

3. Technical solution and method of forced introduction and compression of the fuel mixture, characterized in that the pulsed jet compressor Vujin, works in pulses, using part of the energy of the propellant that is introduced into the thermodynamic process for its own drive. After the hot gas from the detonation chamber (13) flows through the working chamber (4) into the drive chamber (6), the dispersed fuel ignites, there is a sudden jump in temperature and pressure. The jet of gas that is expelled from the drive chamber (6) of the pulse jet compressor Vujin, enters the working chamber (4) at high speed through the nozzle (5). Possessing great energy, the emitted hot gases have a large amount of movement. Due to the high flow velocity, the pressure of the hot gas stream drops, so that it sucks in the surrounding air from the working chamber (4), giving it part of the energy, slowing itself down and the sucked fresh air particles are receiving part of the energy, speeding themselves. Through the inlet (14) the jet flows in the detonation chamber (13) where the fuel mixture is slowed down and tjae¾peed is translated into pressure, thereby forcibly introducing the fuel mixture/ Mthout thft. influence of external pressure. / y⁴ Vujinpvij