RU2489595C1 - Traction module of constant detonation combustion of air-vapour fuel mixture - Google Patents

Abstract

FIELD: machine building.

SUBSTANCE: traction module of constant detonation combustion of an air-vapour fuel mixture consists of a hemispherical resonator, a longitudinal tubular gas-dynamic resonator, an annular nozzle, three radial slot nozzles of flat efflux of heated air-vapour fuel mixture under pressure and two stages of the chamber for mixing of air with fuel vapours. The longitudinal tubular gas-dynamic resonator enters with its nozzle the central axial part on the outer side of the hemispherical resonator supplying the flow of high-temperature waste gases. The annular nozzle is located on the edge of the hemispherical resonator and provides due to its design the flow direction of heated explosion-dangerous air-vapour fuel mixture along inner surface of the hemispherical resonator. Three radial slot nozzles of flat efflux of heated air-vapour fuel mixture under pressure are located along external edge of the hemispherical resonator through 120 degrees and directed to a central part of the hemispherical resonator to the efflux place of high-temperature flow of waste gases.

EFFECT: increasing power and operating efficiency of traction modules of detonation combustion.

4 cl, 3 dwg

Description

The invention relates to engine building, in particular to aircraft reactive traction modules for atmospheric use.

The essence of the invention lies in the fact that the traction module of constant detonation combustion can operate from known axial aviation compressors with a special engine located in their internal axial cavity, which ensures rotation of the compressor and air supply with the necessary capacity and pressure and at the same time provides a high-temperature flow of exhaust gases, with temperature of the order of 1200 degrees C and a pressure of the order of 15 atm, through the longitudinal tubular gas-dynamic resonator of the traction mo Uhl to further their expiry through a nozzle into a jet flame in the center of the traction unit hemispherical resonator.

Upon expiration, in the center of the hemispherical resonator of the traction module, a high-temperature gas-flame jet of exhaust gases under pressure (of the order of 15 atm) meets two types of opposing streams of vaporized oxidized and preheated (to the extent necessary) vapor-air, explosive fuel mixture under pressure created by an axial air compressor (about 10 atm).

The technical result, which is aimed at the idea of the invention, is to increase the efficiency of reactive detonation combustion of traction modules, significantly increase their power, master a fundamentally new technology of their work (continuous detonation combustion).

Description of the invention.

Known methods for producing traction in pulsating modules of detonation combustion of the fuel mixture according to the patents of the Russian Federation No. 94031235, 2066426, 2078974, 22822044, which differ in the presence of gas-dynamic resonant tubes of different numbers, located perpendicular to the axis of the main working stream, differ in the presence of varying degrees of pulsation of the traction process module.

Known RF patent No. 2034996 and settlement - experimental study Ph.D. "MAI" Larionova S.Yu. which differ from others in that they organize, before the main air-fuel mixture is fed into the resonator, mixing the products of preliminary combustion of the fuel, with an excess of oxidizing agent, with the main proportion of fuel and air for organizing the detonation process of combustion in a hemispherical resonator.

Also known is the traction module of detonation-pulsating combustion of fuel according to the patent of the Russian Federation No. 2375601, consisting of a hemispherical resonator with an annular nozzle for radial supply of a combustible mixture, an exhaust nozzle of expanding gases, a chamber for mixing fuel and air vapor, associated with the environment, heat exchangers on the resonator and on exhaust nozzle.

No direct analogues and prototype of the device of the traction module using the constant detonation combustion of the steam-air fuel mixture were found. Perhaps today they do not exist yet.

The main disadvantage of the known detonation traction modules is:

- in many of the early ones, this is the need for a direct, significant length of the exhaust pipe section of expanding gases, due to which the occurrence of a supercritical pressure drop and the occurrence of combustion pulsation are mainly ensured;

- the presence of the burning pulsation itself, in which the higher the pulsation the greater the power, and achieving an infinitely high degree of pulsation is constant burning with the maximum possible power;

- high (about 50%) losses of the possible power of the traction modules that occur immediately after the radial flow of the air-fuel mixture from the circular nozzle of the hemispherical resonator when it is divided after the central, diaphragm collision into two streams, one of which going to the side of the exhaust pipe opening is lost to obtain useful traction power, and the second one leaving towards the working surface of the hemispherical resonator, and in the operation of which losses of possible power also occur due to ishnih collision reflections of this flow;

- the use of technology for the production of pyrolysis products for the organization of detonation combustion.

The present invention of the traction module for constant detonation combustion of an explosive vapor-air fuel mixture consists in eliminating the above-mentioned drawbacks of detonation-pulsating traction modules, eliminating a significant length of exhaust pipes, switching from pulsating detonation combustion to constant, eliminating power losses associated with the separation of oncoming flows.

The intended technical result is achieved in that the constant detonation combustion in the proposed traction module is organized by creating high temperature conditions for its occurrence, which occur under high pressure gas-dynamic flow of exhaust gases and a heated, oxidized explosive vapor-air fuel mixture.

The traction module for constant detonation combustion of an air-vapor fuel mixture consists of a hemispherical resonator, a longitudinal tubular gas-dynamic resonator that enters the central axial part outside the cavity hemisphere (supplying a high-temperature exhaust gas flow), and a circular nozzle along the hemispherical resonator edge, which ensures flow direction due to its construction heated, explosive vapor-air fuel mixture along the inner surface of a hemispherical resonance an atomizer, three radially directed slotted nozzles, a flat outflow of a heated steam-air fuel mixture under pressure (located along the outer edge of the hemispherical resonator through 120 degrees and directed to the central part of the hemispherical resonator to the place where the high-temperature stream of exhaust gases flows).

A compressed air (about 10 atm) air is arranged from the air compressor, mixed with fuel vapor emanating under pressure from the fuel evaporator in the first and second stages of the mixing chamber, for subsequent supply of the organized vapor-air fuel mixture to the hemispherical resonator through circular and radial nozzles to the place of detonation combustion.

The invention is illustrated by drawings indicating the main parts of which consists of a traction module for constant detonation combustion of an air-vapor fuel mixture of explosive concentration.

Figure 1 is a longitudinal section of a traction module.

1 - an air-compressor rotation motor-drive, 2 - an air compressor, 3 - a hemispherical resonator, 4 - a tubular gas-dynamic resonator, 5 - a nozzle of a tubular gas-dynamic resonator, 6 - a circular nozzle of a hemispherical resonator, due to its design, providing the direction of flow of the explosive vapor-air fuel mixture on the inner surface of the hemispherical resonator to the point of impact with a high-temperature gas-flame jet of exhaust gases, 7 — radial slotted nozzle of the hemispherical resonator (3 pcs.), 8 - guiding apparatus for swirling the air flow, 9 - piping system supplying fuel under pressure, 10 - fuel evaporator, 11 - the first stage of the mixing chamber of the steam-air fuel mixture in a weight ratio of 1/30 - 1/45, ensuring guaranteed explosion safety and non-flammability in the conditions of the mixing chamber, 12 - the second stage of the mixing chamber of the steam-air fuel mixture, 13 - high-temperature gas-flame jet of exhaust gases, 14 - shock wave of detonation combustion, 15 - guiding lo molasses, ensuring the twisting of the air flow, 16 - the supply of liquid fuel (kerosene) into the tubular gas-dynamic resonator.

Figure 2 - section 1-1 of the guide apparatus for swirling the air flow.

4 - tubular gas-dynamic resonator, 8 - guiding apparatus for swirling the air flow, 10 - fuel evaporator, 15 - guiding blades for swirling the air flow.

Figure 3 is a transverse section 2-2 of a hemispherical resonator.

3 - hemispherical resonator, 5 - nozzle of a tubular gas-dynamic resonator, 6 - circular nozzle of a hemispherical resonator, due to its design, providing the direction of flow of explosive vapor-air fuel mixture along the inner surface of the hemispherical resonator to the point of impact with a high-temperature gas-flame jet of exhaust gases, 7 - radial nozzle hemispherical resonator (3 pcs.) 13 - high-temperature gas-flame jet of exhaust gases 14 - shock wave of detonation gas and I.

The principle of operation of the traction module for constant detonation combustion of a steam-air fuel mixture.

The operation of the traction module for constant detonation combustion of an explosive vapor-air fuel mixture (or other gas) becomes possible as a result of the organization of the supply of several streams of specially prepared steam-air fuel mixture (heated, oxidized), under pressure, towards the high-temperature, under pressure, exhaust stream of the compressor engine exhaust through a gas-dynamic tube resonator.

Air flow, under pressure of about 10 atm. with increased temperature, coming from the axial compressor 2, passing through the guide apparatus 8, is twisted by the guide vanes 15 into a vortex flow around the gas-dynamic tubular resonator 4. and around the fuel evaporator 10, from which the air is additionally heated to the required temperature, and this heating is possible to significant temperatures since the high-temperature exhaust gas flow of the compressor drive motor can have a temperature of up to 1200 degrees C.

Further, the vortex stream of heated air enters the first stage 11 of the chamber for mixing air and fuel vapors flowing out of the evaporator 10 under pressure, where it is mixed into a vapor-air fuel mixture of non-explosive and non-combustible concentration of fuel vapor and air in a weight ratio of the order of 1 / 30-1 / 45 . Then, the oxidized vortex stream of the vapor-air mixture of the first degree of concentration enters the second stage 12 of the mixing chamber, where in a short period of time, before leaving the circular nozzle 6, it is mixed with an additional fraction of the mass of fuel vapor, thereby forming an explosive vapor-air (or other gas) fuel mixture concentration by volume (for example, kerosene from 1% to 7%), and then immediately expires in two ways under pressure from the second stage of the mixing chamber 12.

In the first case, the explosive flow of the vapor-air fuel mixture (or another) from the second stage of the mixing chamber 12 through the circular nozzle 6 under pressure enters the cavity of the hemispherical resonator 3 along its inner working surface.

In the second case, the flow of the vapor-air explosive fuel mixture from the second stage of the mixing chamber 12 through three radial slotted nozzles 7 under pressure rushes into the central part of the hemispherical resonator 3 towards the high-temperature flow of exhaust gases 13 flowing out of the nozzle of the tubular gas-dynamic resonator 4, where when meeting under high pressure four high-temperature flows (especially at the meeting point of a high-temperature gas-flame jet and three flows from radial slotted nozzles) fuel mixture, the conditions for the explosion of an explosive vapor-air fuel mixture with the formation of a supersonic shock wave with a stable detonation combustion front due to:

1. - the maximum possible, pre-prepared temperature of the fuel mixture (about 650 degrees C), ensuring timely destruction of fuel vapor.

2. - high temperature (about 1200 degrees C) of a flame jet of exhaust gases with products of fuel combustion,

3. - pressure of the vapor-air fuel mixture of 10 atm,

4. - pressure of a flame jet of exhaust gases 15 atm,

5. - high turbulization of the vapor-air fuel mixture in the collision of flows,

6. - explosive concentration of fuel vapor within the lower and upper concentration standards.

The detonation combustion that has arisen can continue indefinitely if the detonation combustion rate is balanced with the velocity and volume of the explosive vapor-air fuel mixture supply, as is done in the case of spin detonation in a circular tube with a constant radial flow of fuel and oxidizer in front of the traveling shock wave, only in this case the shock wave, as it were, remains in one place, and its running is compensated by the timely supply with the necessary speed and volume of explosive vapor-air fuel a mixture.

The claimed solution meets the criterion of "inventive step", as it is characterized by a combination of a number of new design and technological solutions that provide detonation combustion with the occurrence of a shock wave and a combustion front, such as:

- the use of an air axial compressor to supply the flow of the required volume of air with the necessary pressure;

- the use of a high-temperature, pressurized flow of exhaust gases, passing them through the nozzle of a tubular gas-dynamic resonator to meet the vapor-air flows of the fuel mixture;

- organization of a meeting of four radial streams of vapor-air fuel mixture under pressure with a high-temperature stream of exhaust gases for the organization of detonation combustion;

- organization of the movement of the flow of vapor-air fuel mixture on the inner surface of a hemispherical resonator through a circular nozzle;

- organization of evaporation under fuel pressure in the evaporator;

- mixing air with fuel vapor in the first stage of the mixing chamber in an explosion-proof and non-flammable concentration of 11 / 30-1 / 45 in a weight ratio, which ensures guaranteed explosion safety and non-flammability in the conditions of the mixing chamber;

- mixing with an additional fraction of the mass of fuel vapor, while forming an air-vapor (or other gas) fuel mixture of explosive concentration.

List of used literature

- Zeldovich Ya.B. "Theory of shock waves."

- Zeldovich Ya.B., Kompaneyets A.S. "Theory of detonation."

- Soloukhin R.I. "Shock waves and detonation in gases."

Claims (4)

1. Traction module for constant detonation combustion of an air-vapor fuel mixture, consisting of a hemispherical resonator, a longitudinal tubular gas-dynamic resonator, entering with its nozzle in the central axial part outside the hemispherical resonator (supplying a stream of high-temperature exhaust gases), a circular nozzle along the edge of the hemispherical resonator, which ensures the direction of flow of the heated explosive vapor-air fuel mixture along the inner surface of the hemispherical resonator, three radial slotted nozzles for the flat outflow of a heated vapor-air fuel mixture under pressure (located along the outer edge of the hemispherical resonator through 120 ° and directed to the central part of the hemispherical resonator to the place where the high-temperature exhaust gas flows), two stages of the chamber for mixing air with fuel vapor. 2. Traction module for constant detonation combustion of the steam-air fuel mixture according to claim 1, characterized in that it has a directing device for supplying compressed air from the compressor. 3. The traction module for constant detonation combustion of the steam-air fuel mixture according to claim 1, characterized in that it has an evaporator of fuel supplied under pressure on a tubular gas-dynamic resonator. 4. The traction module for constant detonation combustion of the steam-air fuel mixture according to claim 1, characterized in that it has two stages of a chamber for mixing air with fuel vapor under pressure, in the first stage, air is mixed into the steam-air fuel mixture in a weight ratio of 1 / 30-1 / 45, which ensures guaranteed explosion safety and non-flammability in the conditions of the mixing chamber, in the second stage of the mixing chamber, the fuel mixture of the first stage is enriched with fuel vapor to the state of explosive concentration of fuel vapor within the lower and upper concentration standards.

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