RU2524591C1 - Scramjet with pulse detonation combustion chamber and hypersonic jet flow combined with supersonic direct flow in "one-in-one" manner - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention aims at perfection of application of rarefaction formed after reflection of impact wave from working surface of hemispherical resonator (known Hartmann-Sprenger effect). Working rarefaction volume is increased for its filling with water-steam or other gas fuel mix at inflammable concentration. Several explosive volumes are produced with their overlap in aircraft lengthwise direction (in direction of sole degree of freedom). This is done for implementation of self-ignition of fuel mix in closed volume of said explosive volumes which ensures an increase in flame propagation rate in direction of infinite increase. Scramjet incorporates pulsating-detonation conical-circular combustion chamber enveloping the uniflow jet working channel. This combines hypersonic jet flow of said conical-circular combustion chamber with supersonic jet flow of direct-flow channel in the "one-in-one" manner. Said conical-circular combustion chamber has air-steam inflammable fuel mix feed circular nozzle, increased rarefaction volume formation and first explosive intake section that makes second explosive section, section of ahead shock wave braking at the outlet of said combustion chamber, its outer conical surface being aligned with inlet nozzle section of first Laval nozzle tightly connected with second one. Hypersonic and supersonic jet flows get as if combined in the mixing chamber at the joint between said two Laval nozzles. Ignition means ignites explosive fuel mix at engine initial starting period. Thermal change is used to heat and purge the combustion chamber, direct-flow channel and to produce ejection air draft. Detonation starting charge serves to form triple shock wave with necessary interval for engine starting.

EFFECT: perfected design, higher efficiency of scramjet operation.

2 cl, 2 dwg

Description

The invention relates to engine building, in particular to jet aircraft, rocket engines, the detonation-pulsating combustion chamber of which is capable of developing hypersonic flame propagation velocities with a conditional increase in the direction of infinite increase.

The technical result of the invention is to further improve and increase the operational efficiency of known detonation-pulsating traction modules, the development of a fundamentally new technology of their work.

The essence of the invention is to further improve the technology of using the rarefied space generated after reflection of a shock wave from the working surface of a hemispherical resonator (the well-known Hartmann-Sprenger effect), in order to increase the working volume of the rarefaction for its subsequent filling with a vapor-air or other gas fuel mixture in explosive concentration with the aim of obtaining several explosive volumes in a row with their mutually reinforcing overlapping in the longitudinal direction SRI aircraft (in the direction of the only available degrees of freedom), with the aim of further possibilities of simultaneous self-ignition portion of the fuel mixture in a closed volume of one of them, which provides the possibility of conditional growth rate of flame propagation in the direction of infinite magnification.

The invention also consists in constructively combining a hypersonic jet stream from a cone-circular detonation-pulsating combustion chamber with a supersonic jet stream of the one-in-one aircraft air channel, i.e. The supersonic jet stream is inside the hypersonic.

Description of the invention

Known methods for producing traction in detonation-pulsating traction modules according to the patents of the Russian Federation No. 94031235, No. 2066426, No. 2078974, No. 22822044, No. 2034996, calculation-experimental study of the Moscow Aviation Institute candidate of technical sciences S. Larionov, which are distinguished by the indispensable presence of gas-dynamic resonant tubes of different numbers, unknown frequency of pulsations of the detonation process.

Closest to the proposed one is a traction detonation-pulsating module, according to RF patent No. 2249121 consisting of a resonator with an annular nozzle for supplying a fuel mixture, a gas generator for burning the air-fuel mixture, a compartment for supplying fuel to the combustion products for organizing the pyrolysis process, followed by mixing pyrolysis products with air flow and feed this final mixture into the resonator through an annular prototype nozzle.

The main disadvantage of the known traction module are: -

- the deliberately planned need for loss (emission into the atmosphere) of at least 50% of the air-fuel mixture.

- it is unknown the effect of a rarefied atmosphere on the performance of the known module in connection with the disruption of the rarefaction wave immediately along the cutoff of the resonator.

The technical result, the achievement of which this invention is directed, is to eliminate the above noted disadvantages of the detonation-pulsating traction module of the prototype, as well as: -

- to increase the working volume of the vacuum for its subsequent filling with a steam-air or other explosive gas fuel mixture,

- in creating conditions for the simultaneous production of several explosive volumes in a row with their mutually reinforcing overlapping,

- the possibility of simultaneous ignition of a part of the fuel mixture in a closed volume to obtain the possibility of a conditional increase in the speed of flame propagation in the direction of infinite increase,

- in creating the conditions for the simultaneous operation of two parallel reactive flows "one in another."

The intended technical result is achieved by the fact that a hypersonic jet engine creates two parallel, “one in another”, working jet flow of combustion of a steam-air fuel mixture.

One stream is a hypersonic one, flowing out of a cone-circular chamber of detonation-pulsating combustion, enclosing a ramjet air channel of the aircraft, the other stream is a supersonic one, flowing out of a nozzle of a direct-flow channel, while the nozzle of a direct-flow channel is the inner circumference of a nozzle for the outflow of hypersonic flow from a conical-circular chamber combustion, as a result of which a direct-flow working supersonic reactive stream is inside a hypersonic working reactive stream flowing from a cone-cr traction combustor. Both working jet streams appear as if in a mixing chamber at the junction of two Laval nozzles, in which a vacuum rarefaction is formed that enhances (additionally accelerates) the jet stream, and it is necessary to bear in mind the mutually supporting ejection effect of both jet streams on each other.

The conical-circular chamber of detonation-pulsating combustion has an annular nozzle displaced from the hemispherical resonator to supply an increased volume of vapor-air explosive fuel mixture (or other) into its rarefied space using the well-known effect (Hartmann-Sprenger) of the formation of a rarefaction wave after reflection of the shock wave from the working surface and the formation of a supercritical pressure drop in the annular nozzle of a hemispherical resonator. The conical outer surface of the conical circular combustion chamber coincides with the inlet nozzle portion of the first Laval nozzle, hermetically connected to the second, to create a vacuum rarefaction enhancing (additionally accelerating) the reaction stream.

The cone-circular chamber of detonation-pulsating combustion is conventionally divided by length into section L-1 - forming an increased rarefaction and suction volume of the first explosive volume of the fuel mixture, and section L-2 - forming a second explosive volume in which thermodynamic conditions are created (pressure increase and temperature) for the simultaneous self-ignition of part of the fuel mixture in a closed volume due to braking of the forward shock wave in the nozzle section, at the exit from the conical-circular combustion chamber, and due to pressure from the side on explosive volume.

A hypersonic, jet engine with a detonation-pulsating combustion chamber has two air flows for the formation of a fuel mixture, working due to the back-up of outside air during the movement of the aircraft. The first flow coming from the tail of the aircraft (air can also be supplied from the bow), provides the creation of an explosive vapor-air fuel mixture, while spraying fuel with nozzles into the cooking chamber as for the operation of a cone-circular chamber of detonation-pulsating combustion fed through an annular nozzle , and for the operation of the direct-flow jet flow fed through the cooling system of the conical-circular combustion chamber and through the annular nozzle of the direct-flow channel. The second air supply stream is carried out through the direct-flow channel of the aircraft, in which, after mixing and cooling from the atomized liquid fuel supplied through the nozzles of the first fuel supply cascade, it is mixed with the vapor-air explosive fuel mixture supplied through the annular nozzle of the direct-flow channel.

In a conical-circular chamber of detonation-pulsating combustion, in its hemispherical part there are: -

- means of ignition, providing ignition of the explosive fuel mixture in the initial period of starting the engine,

- thermal charge for heating and purging the combustion chamber, direct-flow channel and establishing an ejection air draft,

- detonation starting charge for the formation of a triple shock wave with the necessary interval to start the engine.

The invention is illustrated by drawings indicating the main parts that make up a hypersonic, jet engine with a detonation-pulsating combustion chamber.

Figure 1 is a longitudinal section of an aircraft in the area of a hypersonic, jet engine with a detonation-pulsating combustion chamber.

1 - housing of a conical-circular chamber of detonation-pulsating combustion, 2 - working volume of the combustion chamber, 3 - means for igniting the fuel mixture, 4 - annular nozzle of the conical-circular combustion chamber, 5 - chamber for preparing a vapor-air explosive fuel mixture, 6 - unit of hermetically connected two Laval nozzles, 7 — rarefaction zone, 8 — thermal charge for heating and purging the combustion chamber, ramjet and establishing ejection thrust and preparing the engine for starting, 9 — detonation starting charge for the formation of a triple wave with the necessary interval to start the engine, 10 - air intake in the rear of the aircraft, 11 - aircraft body, 12 - fuel supply, 13 - direct-flow channel, 14 - first cascade of nozzles for spraying fuel into the direct-flow channel, 15 - ring a direct-flow channel nozzle providing the supply of steam-air fuel mixture, 16 — cascade of nozzles for supplying atomized fuel to the chamber for preparing the steam-air fuel mixture, L-1 — portion of the increased rarefaction volume and suction of the first explosive the volume of the fuel mixture, L-2 is the section that forms the second explosive volume, in which thermodynamic conditions (pressure and temperature increase) are created for the simultaneous self-ignition of part of the fuel mixture in the closed volume due to braking of the forward shock wave in the nozzle section, at the exit from the cone circular combustion chamber and due to pressure from the first explosive volume.

Figure 2 - technological chain of operation of a hypersonic detonation-pulsating combustion chamber in a cylindrical design.

zone "C" - zone of braking of the next shock wave at the entrance to the nozzle of the expiration from the combustion chamber.

zone "B" is the zone of the next closed explosive volume, where the increased thermodynamic conditions (pressure, temperature) and the simultaneous self-ignition of part of the fuel mixture are formed, which contributes to a conditional increase in the speed of flame propagation in the direction of infinite increase,

zone "A" - the zone of the initial stage of formation of the shock wave of the next explosive volume,

line I - the shock wave of the detonation starting charge passed the annular nozzle of the combustion chamber, leaving a rarefied volume behind it, created a supercritical pressure drop for the suction of the fuel mixture in zone “A”, as a result of which there was an explosive ignition, the formation of a shock wave, a combustion band and a wave rarefaction

line II - the starting shock wave was braked in the nozzle device of zone “C” at the exit from the combustion chamber, behind it in zone “B” a zone of the next closed explosive volume was formed between the braked wave in zone “C” and the shock wave of the explosive volume of zone “A” ".

lines III, IV, V - further advancement of explosive volumes across all technological zones with the formation of a rarefaction zone in zone “D” of lines IV, V when the reactive stream passes through it.

The principle of operation of a hypersonic, jet engine with a detonation-pulsating combustion chamber, combining a hypersonic jet stream with a supersonic once-through “one in another”.

An aircraft equipped with a hypersonic, jet engine with a detonation-pulsating combustion chamber, combining a hypersonic jet stream with supersonic once-through “one in another” is capable of ground launch without a separate compartment of the accelerator engine using a vapor-air, explosive concentration, fuel mixture (for example , with a vapor content of kerosene in 1.5-7.5% of the volume of the mixture) or another mixture of gases. The start is provided by turning on the thermal charge 8, which is located in the hemispherical resonator of the working volume of the cone-circular combustion chamber 2, while heating, purging and preparing the combustion chamber for start-up, purging part of the direct-flow channel 13 and the link of the Laval nozzles 6. During the purging, steam-air preparation of the fuel mixture due to the suction of air through the air intake 10, the supply of fuel by a cascade of nozzles 16 to the chamber for preparing the fuel mixture 5 and due to ejection, a preliminary suction of air is carried out in a conical-circular combustion chamber 2 through an annular nozzle 4. After working out the thermal charge 8, the detonation-starting charge 9 is turned on to generate three shock wave pulses with the necessary intervals, which form the initial rarefaction periods in zone “A” for suction of the vapor-air explosive fuel mixture, filling through the annular nozzle 4 the entire zone “A”, where it is immediately ignited by means of detonation (ignition) 3, the shock wave formed with the flame front and rarefaction wave, passing through the annular 4, behind it again forms a supercritical pressure drop and ensures the suction of the next volume of the fuel mixture into zone “A”, which ignites immediately, and in front of it in zone “B” has its own volume of the fuel mixture and is blocked in the inlet confuser of the Laval nozzle 6 preceding shock wave. As a result, a zone of closed explosive volume was created in zone “B”, where increased thermodynamic conditions (pressure, temperature) are formed that contribute to the simultaneous self-ignition of part of the fuel mixture, which leads to a conditional increase in the speed of flame propagation towards infinity. Further, the described cycle inside the conical-circular combustion chamber is repeated, and the hypersonic shock wave from zone “C”, entering zone “D”, carries out internal ejection of the flow of the fuel mixture from the direct-flow channel 13, which, mixed with atomized fuel from the cascade of nozzles 14 and with fuel vapors from the annular nozzle 15 of the direct-flow channel 13, he approached the place of his supersonic combustion and mixing of two reactive streams from the conical-circular combustion chamber and from the direct-flow channel. The mixed and mutually enhanced reactive stream is additionally accelerated in the rarefaction zone 7 of the joint of two Laval nozzles.

The claimed solution meets the criterion of "inventive step", as it is characterized by a new set of features, such as:

- the elimination of the planned 50% loss of emissions of the fuel mixture into the atmosphere,

- the creation of conditions for the simultaneous receipt of several explosive volumes in a row within the volume of the combustion chamber with the possibility of their mutually reinforcing overlapping,

- the implementation of the simultaneous ignition of part of the fuel mixture in a closed volume to obtain the possibility of a conditional increase in speed in the direction of infinite increase,

- creating the possibility of simultaneous operation of two parallel reactive flows "one in another."

Claims (2)

1. The hypersonic jet engine has a detonation-pulsating conical circular combustion chamber enclosing a ramjet working channel, as a result of which the hypersonic working jet stream of the conical circular combustion chamber and the one-in-one supersonic working jet flow of the ramjet are conical The circular detonation-pulsating combustion chamber has an annular nozzle for supplying a vapor-air explosive fuel mixture, a section for the formation of an increased volume p vzrezheniya and suction of the first explosive volume, the section forming the second explosive volume, the braking section of the forward shock wave at the exit of the conical-circular combustion chamber, the coincidence of the outer conical surface of the conical-circular combustion chamber with the inlet nozzle section of the first Laval nozzle, hermetically connected to the second, forming at the junction of two Laval nozzles a mixing chamber for hypersonic and supersonic working jet streams, an ignition tool that provides ignition of an explosive fuel with Mesi in the initial period of engine start-up, thermal charge for heating and purging the combustion chamber, direct-flow channel and establishing ejection air draft, detonation starting charge for the formation of a triple shock wave with the necessary interval for starting the engine, two air supply flows, for the formation of the fuel mixture, working due to the supply of outside air during the movement of the aircraft, the first stream coming from the tail of the aircraft, creates an explosive vapor-air the fuel mixture, with the simultaneous supply of atomized fuel by a cascade of nozzles into the cooking chamber, both for the operation of the conical-circular chamber of detonation-pulsating combustion, supplied through the annular nozzle, and for the operation of the direct-flow jet flow supplied through the cooling system of the conical-circular combustion chamber and through a direct-flow channel nozzle, a second air supply stream is carried out through the direct-flow channel of the aircraft, in which, having previously been mixed and cooled from the sprayed grease fuel supplied through the nozzles of the first cascade of fuel supply, in the further movement is mixed with a vapor-air explosive fuel mixture supplied through an annular nozzle of a direct-flow channel. 2. The hypersonic jet engine according to claim 1, characterized in that the conical-circular chamber of detonation-pulsating combustion has a zone for realizing the possibility of simultaneous self-ignition of a part of the fuel mixture in a closed volume of a second explosive volume located between the first explosive volume and inhibited by the forward shock wave at the exit from the nozzle of the combustion chamber, which provides a conditional possibility of increasing the speed of flame propagation in the direction of infinite increase.

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