RU60145U1 - KNOCKING ENGINE WITH ELECTROMAGNETIC CONTROL DEVICE - Google Patents

Abstract

A detonation engine with an electromagnetic control device relates to pulsating air-jet engines with resonant combustion chambers, to combined ramjet pulsating air-jet engines, as well as to detonation engines. The objective of the utility model is to increase the reliability of the detonation engine and improve the characteristics of the detonation engine due to the organization of a continuous pulse cycle of its operation, the cooling of the walls of the detonation chamber in the region of the front bottom, which excludes the possibility of ignition of the fuel-air mixture at the time of its injection into the detonation chamber, and also by eliminating the penetration of the detonation wave into the fuel supply system. The technical result, which can be obtained using the utility model, is to organize additional ionization of the fuel-air mixture to effectively influence intracameral processes, as well as to organize feedback. The task is achieved in that the detonation engine with an electromagnetic control device consists of a detonation chamber and fuel supply, control and initiation systems. In this case, the initiation system is made in the form of a ring ionization device located in the region of the front bottom of the detonation chamber and inductors and initiators sequentially located behind it, and in the bottom of the detonation chamber there is a pressure sensor connected to the control system, the outputs of which are connected to the inputs of the ring device ionization, inductor and initiator. The combination of a detonation engine with an electromagnetic control device will significantly improve engine performance, including increasing engine efficiency through more complete use of the working fluid energy, as well as organizing a continuous detonation process. In addition, the implementation of this cycle of operation of the detonation engine helps to simplify its design, reduce dimensions and weight, eliminates the possibility of ignition of the fuel-air mixture when it is injected into the detonation chamber by cooling the walls of the detonation engine during its operation, as well as preventing the penetration of the detonation wave into fuel supply system by introducing a ring ionization device and an inductor into the initiation system. 3 ill.

Description

The utility model relates to pulsating air-jet engines with resonant combustion chambers, as well as to combined ramjet pulsating air-breathing engines. There is experience in the development of jet engines in which the accelerating chamber is made in the form of an expanding nozzle. This embodiment of the chamber contributes to supersonic acceleration of the combustion products. Of the chemical rocket engines, pulsed air-jet engines are close to the declared one. However, they have a large specific fuel consumption and a small specific impulse. These engines operate at a fixed frequency, since the combustion of fuel occurs in an acoustic type chamber. For example, the engine according to US patent No. 3727409, 1973.

Partially, these disadvantages are eliminated in RF patent No. 2066778, IPC R 02 K 7/04, 1993. In it, the detonation process is intensified by increasing the frequency of detonation pulses. This is achieved by the fact that the detonation excitation system is a prechamber with a gas-dynamic valve. But this device has limited use, since the process of mixture formation occurs in the chamber after the supply of fuel components, and the operation of the initiation system is associated with the operation of the supply and mixture formation system and is pulsed from an external power source.

The closest to the principle of operation and technical device is "Pulsating detonation engine with a closed cycle" (certificate of the Russian Federation for utility model No. 20549, IPC F 02 K 7/04, F 42 D 1/04, 2001). In it, an increase and regulation of the frequency of detonation pulses was carried out by organizing a closed cycle of the engine, which means such operation of the engine, when it continues to work automatically and autonomously after applying the initial pulse, that is, without using an external energy source. This is achieved by the fact that the initiation system is a magnetogasdynamic generator (MHD generator) located in the area of the nozzle and connected through an amplifying-converting device to the initiator.

The disadvantage of this device is the lack of reliability of the detonation engine associated with the possibility of penetration of the detonation wave into the fuel supply system, the complexity of the design associated with the installation of the MHD generator, as well as the lack of feedback in the operation of the detonation engine.

The objective of the utility model is to increase the reliability of the detonation engine and improve the characteristics of the detonation engine due to the organization of a continuous pulse cycle of its operation, the cooling of the walls of the detonation chamber in the region of the front bottom, which excludes the possibility of ignition of the fuel-air mixture at the time of its injection into the detonation chamber, and also by eliminating the penetration of the detonation wave into the fuel supply system.

The technical result that can be obtained by using the utility model is to organize additional ionization of the fuel-air mixture to effectively influence intracameral processes, as well as to organize feedback.

The task is achieved in that the detonation engine with an electromagnetic control device consists of a detonation chamber and fuel supply, control and initiation systems. In this case, the initiation system is made in the form of a ring ionization device located in the region of the front bottom of the detonation chamber and inductors and initiators sequentially located behind it, and in the bottom of the detonation chamber there is a pressure sensor connected to the control system, the outputs of which are connected to the inputs of the ring device ionization, inductor and initiator.

Figure 1 presents the structural layout of the detonation engine with an electromagnetic control device, figure 2 - the position of the detonation wave at the time of the signal to the initiator, figure 3 - the position of the detonation wave at the time of its approach to the inductive coil. The main elements of the detonation engine include:

1 - detonation chamber,

2 - fuel supply system,

3 - control system,

4 - ring ionization device,

5 - inductive coil,

6 - initiator,

7 - inlet,

8 - pressure sensor.

The detonation chamber 1 is designed to convert the chemical energy of the working fluid into the kinetic energy of detonation products. It is a tubular structure, at one end of which there is a fuel supply system, and from the other, the output of detonation products.

The fuel supply system 2 is intended for high-quality mixing of fuel components in order to form a fuel-air mixture and its regulated supply to the detonation chamber.

The control system 3 is intended for organizing the starting processes, engine operation in a predetermined mode and turning it off, as well as for signaling the operation of the ring ionization device, inductor and initiator.

The ring ionization device 4, the inductor 5 and the initiator 6 form an initiation system, which is designed to excite the detonation process in the detonation chamber 1 and maintain it during engine operation. The elements of the system are located in the following sequence on the detonation chamber 1 in the direction of gas flow: a ring ionization device 4, an inductor 5 and an initiator 6.

The following modes of operation of the detonation engine with the electromagnetic control device are possible: start mode, operating mode and shutdown mode. Let us consider each of them sequentially.

The start mode is carried out by simultaneously supplying a signal from the control system 3 to the fuel supply system 2, as well as to the elements of the initiation system: an ionization ring device 4 and an inductor 5 (Fig. 2).

In this case, the air-fuel mixture with the specified parameter values through the inlet 7 enters the detonation chamber 1. To give it electrical conductivity properties, a ring ionization device 4 is used. For this purpose, easily ionizing substances are introduced into the detonation chamber 1: calcium, sodium or cesium. Subsequently, the ionized fuel-air mixture falls into the internal volume of the inductive coil 5. As a result of the interaction of the magnetic field generated by the inductive coil 5 with the ions of the fuel-air mixture, it narrows.

The degree of filling of the detonation chamber 1 is calculated from its total length, the relative feed rate of the fuel-air mixture and the propagation velocity of the detonation wave.

After the detonation chamber 1 is filled with the fuel-air mixture, the control system 3 sends a signal to the initiator 6, which generates a detonation pulse, under the influence of which the fuel-air mixture located in the detonation chamber 1 is initiated. Upon initiation, two detonation waves are generated (ДВ1 and ДВ2) that move along the fuel-air mixture in different directions (figure 2).

Work mode. It is characterized by a continuous pulsed detonation process, in which the air-fuel mixture is constantly supplied to the detonation chamber 1, and the control system 3 sends signals to trigger the initiator 6.

The detonation wave ДВ1 moves towards the front bottom, and the detonation wave ДВ2 - towards the open end of the detonation chamber 1 with a speed equal to the speed of detonation Chapman-Jouguet (figure 3).

In front of the front of motion of the detonation wave ДВ1 is an ionized fuel-air mixture. Further, the detonation wave ДВ1 is directed along the axis of the detonation chamber 1 and falls into the area of influence of the inductive coil 5. Getting into the region of the magnetic field of the inductive coil 5, the ion concentration is redistributed, which leads to deformation of the form of the detonation wave ДВ1.

In turn, this prevents further movement of the detonation wave ДВ1 and its penetration into the fuel supply system of the fuel-air mixture, which excludes its detonation.

Since the inductive coil 5 contributed to the redistribution of the ratio of the components of the fuel in the cross section of the detonation chamber 1, as a result of this, the air-fuel mixture is concentrated closer to the axis of the detonation chamber 1 with enrichment of fuel, and around the periphery with excess oxidizer (air). This leads to a redistribution of temperature along the cross section of the detonation chamber 1. The highest temperature in the detonation chamber 1 will be on its axis, and the lowest - on the inner surface of the detonation chamber 1, which contributes to its cooling during operation of the detonation engine. In turn, this eliminates the possibility of ignition of the fuel-air mixture when it is injected into the detonation chamber 1.

In addition, this redistribution of the ratio of the components of the fuel in the cross section of the detonation chamber 1 also weakens the intensity of the detonation wave DW1 by its further destruction, which prevents its penetration into the fuel-air mixture fuel supply system and, therefore, excludes its detonation.

The pressure sensor 8 signals the output of the detonation engine to a predetermined mode and its operation in this mode.

When the detonation wave ДВ2 leaves the detonation chamber 1, detonation products with high temperature and pressure remain in it. When the detonation wave DV2 leaves the detonation chamber 1, a pressure drop is formed at the open end. This pressure difference creates a series of rarefaction waves, which, propagating

in the chamber at the speed of sound, detonation products are removed. The rarefaction wave is associated with a decrease in the chamber pressure and prepares the detonation chamber 1 for the arrival of a new portion of the fuel-air mixture. After the completion of this cycle, the voltage from the initiator 6 is removed until the next cycle.

The further detonation cycle is carried out automatically due to the implementation of the intracameral gas-dynamic coupling. As a result, a closed engine operation cycle is created. In this case, the maximum frequency of processes in the detonation chamber is achieved, and, consequently, the maximum thrust.

The engine is turned off by supplying a signal from the control system 3 to the fuel supply system 2 to stop the flow of the fuel-air mixture into the detonation chamber 1.

Thus, the combination of a detonation engine with an electromagnetic control device will significantly improve engine performance, including increasing engine efficiency due to more complete use of the working fluid energy, as well as organizing a continuous detonation process. In addition, the implementation of this cycle of operation of the detonation engine helps to simplify its design, reduce dimensions and weight, eliminates the possibility of ignition of the fuel-air mixture when it is injected into the detonation chamber by cooling the walls of the detonation engine during its operation, as well as preventing the penetration of the detonation wave into fuel supply system by introducing a ring ionization device and an inductor into the initiation system.

Claims (1)

A detonation engine with an electromagnetic control device, consisting of a detonation chamber and fuel supply, control and initiation systems, characterized in that the initiation system is made in the form of a ring ionization device located in the region of the front bottom of the detonation chamber and inductance coil and initiator located in series behind it, and in the bottom of the detonation chamber is a pressure sensor connected to a control system, the outputs of which are connected to the inputs of the annular device Properties of ionization, inductor and initiator.