RU2406865C2 - Intermittent-cycle jet engine in mode of detonation fuel combustion with additional acceleration of gas volume charges with electromagnetic induction force - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: intermittent-cycle jet engine includes the following: operating channel, supply system of fuel components which are supplied through quick-closing valves to two inner detonation combustion chambers directed opposite each other and combined through inner nozzles and operating channel into common device which is made from non-magnetic dielectric material; at that, one of inner detonation combustion chambers is connected to outlet combustion chamber and then to outlet supersonic nozzle which is connected to electromagnetic charged particle accelerator; combustion products are ionised by taking electrons out of combustion chambers through catalytic electrode, high-voltage winding and thermionic electrode owing to high positive voltage on catalytic electrode, and speed of back-and-forth movement of ionised blast wave in the operating channel is maintained at the level required for compression of portions of fuel mixture in those chambers; alternating current voltage which is used in charged particle accelerator for acceleration of ionised blast waves in the outlet channel at the outlet of which fuel combustion products are deionised by means of thermionic electrode is removed from output windings of magnetic conductors enveloping the operating channel.

EFFECT: invention ensures multiple decrease of the weight and dimensions of the proposed device, simplified design and increase of frequency of the generated electric current of more than 600 Hz.

1 dwg

Description

The invention relates to pulsating jet engines based on the energy of detonation combustion of fuel, but differs in high efficiency ratios of more than 50%, pulsation frequency above 400 Hz, additional acceleration by an alternating electromagnetic field of each portion of the products of a chemical reaction ejected from a detonation combustion chamber moving in the form of a high region gas pressure, carrying a space charge of positive polarity.

A known device of a pulsating jet engine according to patent RU 2300005 C2 (class F02K 7/04, 2006).

The specified device contains a cylindrical combustion chamber, a resonator tube, inlet nozzles placed opposite, a nozzle and a spark plug, a vortex pre-chamber in the front of the combustion chamber. The device works due to the intensification of the mass transfer process in the combustion chamber, leading to an increase in the rate of quasi-detonation combustion. The disadvantages of the device include a low pulsation frequency and insufficiently large pressure surges due to incomplete combustion of a portion of the fuel mixture in detonation mode.

The task of the invention is the conversion of the energy of detonation combustion of fuel into the kinetic energy of the reaction products, as well as into electrical energy, which is used to further accelerate the generated space charges. In this case, the pulse repetition rate of the fuel mixture exceeds 400 Hz and can reach a frequency of several kilohertz with a decrease in the linear dimensions of the device. At such frequencies of operation of the device, the vibrations transmitted to the aircraft body are easily eliminated.

The solution to this problem is achieved by the fact that fuel components, such as hydrogen and air, are supplied under pressure to the mixing chambers and through quick-acting mechanical valves to two internal detonation combustion chambers, which are connected into a single device through internal supersonic nozzles and a working channel. One of the internal detonation combustion chambers is connected to the exhaust combustion chamber and then to an external supersonic nozzle. The internal detonation combustion chambers maintain the speed of the shock wave in the working channel at the level necessary to compress the portion of the fuel mixture newly received in them. The energy of detonation combustion of fuel in the exhaust combustion chamber is converted into the kinetic energy of expanding gases in an external supersonic nozzle. Thus, a moving reciprocating shock wave is formed in the working channel between the two internal detonation combustion chambers, the speed of which is maintained at the level necessary to compress a portion of the fuel mixture in these chambers by changing the input pressure of the fuel components. For example, the shock wave velocity necessary for compression for a mixture of hydrogen with air will be 2.5 M local velocity of sound, where M is the Mach number, with a narrowing combustion chamber and no chemical reaction catalyst in it. If a catalytic electrode is introduced into the combustion chambers, then the speed of the shock wave in the working channel, at which the device continues to work, will slightly decrease.

To convert the energy of the reciprocating motion of the shock wave into electrical energy, the high-pressure region in it is saturated with ions by removing electrons from the combustion chamber through a catalytic electrode, a high-voltage winding, and a thermionic electrode at the time of detonation combustion of the fuel mixture. The working channel is surrounded by a magnetic circuit with an output winding, in which an alternating current voltage is induced due to the reciprocating movement of a high pressure region carrying a positive space charge in this channel. By varying the amount of electric energy used, the speed of the shock wave in the working channel is controlled at the maximum fuel mixture flow rate provided for this device, which means that the frequency of the pulsating jet engine is controlled in the desired range.

The output supersonic nozzle is connected to an electromagnetic accelerator of charged particles, which is a pipe segment of non-magnetic dielectric material covered by several magnetic circuits with windings, to each of which an AC voltage with such a phase shift is applied to accelerate the movement of high-pressure regions of gases carrying positive space charge, in the right direction.

Due to the high rate of combustion of the fuel mixture in the overdriven detonation mode, high pressure and temperature jumps are achieved in the combustion chambers, which contributes to ionization of the reaction products, a high frequency of the device above 400 Hz, high fuel efficiency and high specific power of more than 10 MW per liter of volume . The increase in the linear dimensions of the device, the working channel of more than two meters, allows it to operate at a frequency below 400 Hz, but at the same time, the weight and dimensions of the housing, magnetic circuits increase, vibration loads and heat loss increase.

The claimed combination of operations, elements and relationships allows us to solve the problems of the invention by optimizing the process of converting the energy of a moving substance flow into kinetic and electrical energy.

In the study of known technical solutions in this field, the totality of the features that distinguish the claimed invention was not identified. This solution is significantly different from the known ones, does not explicitly follow from the prior art and, accordingly, has an inventive step.

Since the claimed solution can be implemented by modern means and materials, it is industrially applicable.

The accompanying drawings explain the essence of the proposed device.

The drawing shows the main components of a pulsating jet engine. For example, hydrogen is used as fuel.

The drawing indicates:

1 - system for adjusting the pressure of the fuel components,

2 - nozzle of compressed air,

3 - nozzle of compressed hydrogen,

4 - mixing chamber,

5 - high-speed mechanical valve,

6 - internal chamber of detonation combustion,

7 - catalytic electrode,

8 - high voltage winding

9 - high voltage switch,

10 - control device and conversion of electricity,

11 - input winding of the magnetic circuit of the combustion chamber,

12 - magnetic circuit of the combustion chamber,

13 - internal supersonic nozzle,

14 - working channel

15 - output channel

16 - thermionic electrode,

17 - output chamber of detonation combustion,

18 - magnetic circuit,

19 - output winding

20 is a device for compressing atmospheric air,

21 - output supersonic nozzle,

22 - magnetic core of the accelerator of charged particles.

The pulsating jet engine shown in the drawing contains a pressure control system 1 through which fuel components, such as hydrogen and air, are supplied to the respective jets 2 and 3. Further, the fuel components are mixed in the mixing chamber 4 of such volume and geometric shape that are necessary for them high-quality mixing. Through a high-speed mechanical valve 5, the fuel mixture enters the pulse detonation combustion chamber 6, where, with the help of a catalytic electrode 7 and an electric discharge of the required power, the mixture is burned in detonation mode. The magnitude of the electric discharge energy necessary to initiate detonation depends on the initial pressure of the gas mixture, the geometric shape and size of the combustion chamber, the efficiency of the catalyst, the length of the discharge gap, and is limited by the thermal stability of the catalytic electrode and insulator. To form electric discharges, a high-voltage winding 8 is used, one of the outputs of which is connected to the mechanical valve body through the high-voltage switch 9 at the start-up time. Voltage pulses are supplied from the control and energy conversion device 10 to the input winding 11 of the magnetic circuit of the combustion chamber 12. At the initial time of the start-up time electric discharges in two detonation combustion chambers follow with a frequency depending on the distance between these chambers, which determines the initial resonance th frequency device startup.

Two internal detonation combustion chambers are directed towards each other and are connected through supersonic nozzles 13 and the working channel 14 into a single device. The combustion chamber, nozzle and working channel are dielectric coated or made of non-magnetic dielectric material, such as impact-resistant ceramics.

In the process of starting the device in the working channel, energy is accumulated in the form of a moving reciprocating shock wave, the speed of which is increased by simultaneously raising the pressure of the fuel components and the frequency of electric discharges. The speed of the shock wave in less than a few seconds is raised to such a minimum necessary speed at which the energy of movement of this wave is sufficient to compress the newly received fuel mixture. At this moment, the high-voltage switch is opened, and the device switches to the mode of initiation of detonation combustion with the help of a shock wave — the mode of overdriven detonation. For a mixture of hydrogen with air in the absence of a catalyst, the minimum velocity of the shock wave in the working channel will be 2.5 M local velocity of sound, where M is the Mach number. The pressure of the fuel components is regulated so that the speed of the shock wave in the working channel in all operating modes of the device, except for starting, is higher than the minimum.

When a detonation combustion of fuel occurs in any of the chambers, the control system delivers a powerful voltage pulse of several tens of microseconds duration to the input winding of the magnetic circuit of this combustion chamber, while the electromagnetic induction force arises inside the chamber, which accelerates ions towards the working or output channel 15, and electrons towards the catalytic electrode, on which at this moment in time there is a high positive voltage. The catalytic properties of the electrode in combination with electromagnetic forces allow electrons to be output to the output channel through the thermionic electrode 16, where deionization of the exhaust gases takes place. So in the exhaust combustion chamber 17 and in two internal detonation combustion chambers receive a positive space charge of the reaction products. A shock wave in the working channel, having a high-pressure region that carries a space charge, moves back and forth and interacts with the magnetic circuit 18 due to the force of electromagnetic induction inducing an alternating current voltage in the output winding 19.

The obtained electrical energy is used to compress atmospheric air in the corresponding device 20, as well as to form and additionally accelerate the positive charges of the high-pressure regions in the output supersonic nozzle 21 and the output channel by applying voltage pulses to the windings of the magnetic circuits of the charged particle accelerator 22 in the corresponding phase.

According to the claimed invention, the design and simulation of individual components of a pulsating detonation jet engine has been performed.

The scope of the invention is the production of hypersonic jet engines capable of operating, starting from zero speed, using fuel with high efficiency, atmospheric air or an oxidizing agent on board when moving in airless space. The simplicity of design and the high frequency of the generated electric current, above 600 Hz with a working channel length of less than 1 m, can significantly reduce the weight and size of the proposed device. High speed, temperature and pressure during detonation fuel combustion and additional acceleration of gas space charges by electromagnetic induction determine the high efficiency, more than 50%, of the claimed device for producing reactive thrust and electricity.

Claims (1)

A pulsating jet engine containing a working channel, a system for supplying fuel components, which are supplied through two quick valves to two internal detonation combustion chambers, characterized in that the detonation combustion chambers are directed towards each other and connected through internal nozzles and a working channel to a single device made of non-magnetic dielectric material, while one of the internal detonation combustion chambers is connected to the output combustion chamber and then to the output of supersonic the second nozzle, which is connected to an electromagnetic accelerator of charged particles, the combustion products are ionized by removing electrons from the combustion chambers through a catalytic electrode, a high voltage winding and a thermionic electrode due to the high positive voltage on the catalytic electrode, and the speed of the reciprocating movement of the ionized shock wave in the working the channel is maintained at the level necessary to compress portions of the fuel mixture in these chambers from the output windings of the magnetic circuits, covering working channel, remove the AC voltage, which is used in the accelerator of charged particles to accelerate ionized shock waves in the output channel, at the outlet of which the products of fuel combustion are deionized using a thermionic electrode.

Images