RU2278293C2 - Method of and device for additional compression of air in combustion chamber of reaction engine - Google Patents

Abstract

FIELD: reaction engine.

SUBSTANCE: proposed method comes to delivery of on-coming flows of preliminarily compressed air into combustion chamber of reaction engine and combustion of fuel. Said air is compressed in compressor driven by gas turbine on-coming flows of compressed air getting from compressor are formed in combustion chamber provided with solid bottom arranged at opposite side from its outlet hole. Said on-coming flows collide in central part of combustion chamber with complete braking and converting of kinematic energy into additional compression directly in combustion chamber. Fuel is combusted in said volume of additionally compressed air.

EFFECT: increased engine power and reactive thrust.

4 cl, 1 dwg

Description

The invention relates to jet engine installations, in particular, to devices associated with forcing air into the combustion chambers of said engines, additionally compressing the air directly in said combustion chambers and providing, on this basis, an increase in engine power and an increase in jet propulsion generated by them. The invention can be applied in any jet engines, mainly on turbojet propulsion systems.

A known method of compressing air in a diffuser of a ramjet engine using high-speed pressure at a high flight speed of an aircraft. At the same time, the air flow within the engine is given a direct-flow character (see. "Polytechnical Dictionary" edited by A.Yu. Ishlinsky, ed. "Soviet Encyclopedia", M. - 1980, p. 420 with a diagram on p. 421).

The disadvantage of this method of compressing air, and, accordingly, of the engine as a whole, is the possibility of its practical implementation only at a flight speed of 2-3.5 sound speeds.

There is also known a method of additional compression of air in the combustion chamber of a jet engine, which consists in feeding into the combustion chamber counter flows of pre-compressed air in a compressor driven by a gas turbine and burning fuel (see UK patent 1036677, F 23 P 3/04, 1966).

The disadvantage of this method of air compression is the incomplete use of the kinetic energy of the air flow from the turbine for additional compression directly in the central part of the combustion chamber, where the fuel is burned, and the absence of special tools to ensure the use of gas pressure directly in the combustion chamber with its effect in the direction created jet thrust engine.

A known combustion chamber of a ramjet (ramjet), located behind a diffuser in communication with the inlet, in which air is compressed by braking the oncoming air stream. The specified compressed air in the diffuser is supplied to the combustion chamber. At the same time, the air flow through the entire engine, including the combustion chamber, has a direct-flow character along the line of the engine axis (see the above Polytechnical Dictionary, p. 420).

The disadvantage of the said ramjet combustion chamber, as well as of the entire engine as a whole, is that it compresses air in the direction of free movement of its direct-flow stream, which makes it possible to operate the engine reliably only at an aircraft flight speed of 2-3.5 sound speeds.

Closest to the claimed invention is a device for additional compression of air in the combustion chamber of a jet engine containing a combustion chamber made with an outlet facing the gas turbine, evenly placed on its side walls and directed towards its central part inlet openings pre-compressed air supplied from a compressor connected by a shaft to a gas turbine and an injector for supplying fuel to the combustion chamber (see above e patent of Great Britain 1036677).

The disadvantage of this device for additional air compression in the combustion chamber of a jet engine is that it does not fully utilize the kinetic energy of the compressed air coming from the compressor for additional compression directly in the combustion chamber in the fuel combustion area. Said combustion chamber does not have a special device to ensure the pressure of the gas contained in it towards the thrust generated by the jet engine.

The present invention allows to obtain a technical result, which consists in additional compression directly in the combustion chamber of the air coming from the compressor, which provides an increase in engine power and an increase in the reactive thrust created by it.

The specified technical result according to the method of additional compression of the air in the combustion chamber of a jet engine is to feed into the combustion chamber counter flows of pre-compressed air in a compressor driven by a gas turbine and burning fuel. According to the invention, counter flows of pre-compressed air coming from the compressor are created in a combustion chamber made with a continuous bottom located on the opposite side of its outlet, these counter flows in its central part collide with complete braking and their kinetic energy is converted into additional compression directly into the combustion chamber, and the combustion of fuel is produced in this volume of additional compressed air.

A device for additional compression of air in the combustion chamber of a jet engine comprises a combustion chamber made with an outlet facing the gas turbine, with inlet openings evenly placed on its side walls and directed towards the central part thereof for supplying pre-compressed air supplied from the compressor connected by a shaft to a gas turbine and an injector for supplying fuel to the combustion chamber. According to the invention, the combustion chamber is made in the form of an enclosed space with a continuous bottom located on the opposite side from its outlet, and the inlet openings located on the side surfaces serve for the passage of pre-compressed air from the compressor for burning fuel, the movement of these air flows in the opposite direction directions, colliding them with complete mutual inhibition and the conversion of all kinetic energy of the oncoming flows into additional compression directly in the combustion chamber. In this case, the nozzle for supplying fuel is turned into the region of the above-mentioned additional compressed air.

The inlet openings to the combustion chamber, as a special case of execution, are provided with guide surfaces that enable more accurate direction of air flows to the central part of the combustion chamber.

The outlet of the combustion chamber is made in the form of a jet nozzle.

In the drawing, in section along the axial frontal plane, a general view is shown of the implementation of the method of additional air compression in the combustion chamber of a jet engine using the example of a corresponding device in the form of a combustion chamber. The arrows in the drawing show the direction of movement of air and gas formed from the combustion of fuel.

The combustion chamber 1 of the jet engine, in which additional air compression is carried out, is made with an outlet 2 facing the gas turbine, with inlet openings 3 evenly placed on its side walls and directed towards its central part to supply pre-compressed air supplied from a compressor connected by a shaft to a gas turbine, and an injector 6 for supplying fuel to the combustion chamber. The combustion chamber is made in the form of an enclosed space formed by the walls 4 with a continuous bottom 8 located on the opposite side from its outlet 2. The inlet openings 3 located on the side surfaces serve for the passage of pre-compressed air from the compressor for burning fuel, the movement of these flows air in opposite directions, colliding them with complete braking in the central part 5 of the combustion chamber and turning all the kinetic energy of the oncoming flows into additional ADDITIONAL compression directly into the combustion chamber. In this case, the nozzle 6 for supplying fuel is turned into the region of the aforementioned additional compressed air.

The inlet openings 3 to the combustion chamber 1, as a special case of execution, are provided with guide surfaces 7, which provide the possibility of more accurate direction of air flows to the central part 5 of the combustion chamber.

The outlet 2 of the combustion chamber 1 is made in the form of a jet nozzle.

The above device in the form of a combustion chamber of a jet engine implements the proposed method for additional air compression directly in the combustion chamber as follows.

The air pre-compressed by the engine compressor through the inlet openings 3 is supplied to the combustion chamber 1, where it moves uniformly from all sides from the indicated inlet openings to the central part 5 of the combustion chamber in radial directions, which leads to a collision of oncoming air flows in the central part 5 of the combustion chamber and their mutual complete inhibition. The indicated ordered air movement is facilitated by the guiding surfaces 7, which are combined with the inlet openings 7. When the oncoming air flows collide, their kinetic energy is completely converted to additional compression. In the region of maximum air compression from the nozzle 6, fuel is supplied and sprayed, which ensures its combustion with a maximum temperature increase, which creates increased pressure on the walls 4 and the bottom 8 of the combustion chamber. The resulting gas accelerates under the influence of increased pressure through the outlet 2 towards the gas turbine of the engine while creating a reactive force acting on the bottom 8 of the combustion chamber placed against the outlet 2 in the form of an additional reactive thrust. In this case, the main jet thrust is created when gas flows through the jet nozzle of the engine after passing through a gas turbine.

Claims (4)

1. The method of additional compression of air in the combustion chamber of a jet engine, which consists in feeding into the combustion chamber counter flows of pre-compressed air in a compressor driven by a gas turbine and burning fuel, characterized in that the counter flows of pre-compressed air coming from the compressor are created in a combustion chamber made with a continuous bottom located on the opposite side from its outlet, these oncoming streams in its central part collide with complete braking and the expansion of their kinetic energy into additional compression directly in the combustion chamber, and the combustion of fuel is carried out in this volume of additional compressed air. 2. A device for additional compression of air in the combustion chamber of a jet engine, comprising a combustion chamber made with an outlet facing the gas turbine, with inlet openings uniformly arranged on its side walls and directed toward the central part thereof, for supplying pre-compressed air, supplied from the compressor, connected by means of a shaft with a gas turbine, and an injector for supplying fuel to the combustion chamber, characterized in that the combustion chamber is made in the form of a closed spaces with a solid bottom located on the opposite side from its outlet, and inlet openings located on the side surfaces serve to pass pre-compressed air from the compressor for burning fuel, moving these air flows in opposite directions, colliding them with complete mutual braking and the conversion of all kinetic energy of the oncoming flows into additional compression directly in the combustion chamber, while the nozzle for supplying fuel is facing into the region of said additional compressed air. 3. The device according to claim 2, characterized in that the inlet openings to the combustion chamber are provided with guide surfaces, which enable more accurate air flow direction to the central part of the combustion chamber. 4. The device according to claim 2, characterized in that the outlet of the combustion chamber is made in the form of a jet nozzle.