RU2242629C1 - Detonation combustion jet engine - Google Patents

Abstract

FIELD: mechanical engineering; road and water vehicles and aircraft.

SUBSTANCE: proposed engine contains cylinder liners, pistons, displacement type air super charger, unit injectors, self-contained combustion chamber, housing, charger, link drum, turbine, motor-generator, gear rim, fuel and oil pumps, compression ratio adjuster and cooling system. Detonation combustion of fuel in constant volume takes place in self-contained combustion chamber to which air delivered by air super charger. Air super charger is two-stage piston super charger consisting of carrying cylinder with piston of second stage and air chamber with first stage ring piston installed on carrying cylinder. Plane of beam of second stage piston and plane of ball pins of ring piston of first stage are arranged at angle of 90^o relative to each other. Said pistons move in different sides thus balancing their inertia forces. Spaces of second and first stages are interconnected by channels, and volume of air chamber is twice as great as volume of space of second stage. Carrying cylinder, being support of engine, consists of two liners, one press-fitted into the other. Channels, windows and holes are made in liners to form engine communication system. Charge consists of combustion chamber, phase rings with ball pins, channels and nozzles. Combustion chamber is fastened by flange on carrying cylinder, being connected by intake channels with space of second stage of air super charger. Said channels are closed by phase ring of balls with spherical seats playing the part of shutoff. Outlet channels of combustion chamber are opened by phase ring. Liquid cooling jacket is made in combustion chamber wall. Link drum is made cylindrical, split and it is installed on carrying cylinder on two bearings. Both parts of drum are fixed by pins over perimeter, and axial spherical link to drive pistons of air supercharger and two radial detachable links to drive fuel unit-injectors, oil pumps and ignition distributor are made inside drum. Engine drive turbine is installed outside link drum, being set into action by pressure of exhaust gases through several channels and nozzles. Engine is furnished with compression ratio adjuster consisting of two nuts turned onto link drum and carrying cylinder, and thrust ring.

EFFECT: provision of ecologically clean engine operation on lean mixtures.

2 dwg

Description

The invention relates to mechanical engineering and can be applied on land, water transport, aircraft.

Two-stroke internal combustion engines are known in which kinematic schemes with a crank mechanism and blowing cylinders with air through blowdown windows are used. (Device and car repair. M: Higher school, 1987).

In modern internal combustion engines, an increase in power characteristics is associated with the improvement of electronic systems for preparing and supplying air and fuel to the engine cylinders, cleaning the cylinders of combustion products, increasing the degree of compression, etc. The main problem is the use of the internal energy of the fuel used, the combustion of which under various conditions of pressure and temperature can occur smoothly or have an explosive shock detonation character with the release of additional thermal energy, the appearance of which during the operation of a conventional internal combustion engine is considered harmful and leads to the destruction of crank parts connecting rod mechanism. As a result, anti-knock additives are added to the fuel, various pre-chambers combined with the cylinder of the combustion chamber are used in the engine design, which reduce the detonation and engine stiffness. Thus, the internal energy of the fuel is used only in the initial stage of the chain reaction of the molecules included in it.

The proposed detonation combustion engine uses fuel (gasoline, kerosene, diesel, oil, gas) without anti-knock additives. Fuel combustion occurs at a constant volume in an autonomous combustion chamber, pre-charged with air and fuel and disconnected from the cylinder cavity, has an explosive, detonation character. During detonation combustion, the chain reaction of fuel and air molecules occurs faster and in a deeper stage with the release of additional thermal energy. According to the invention, the engine includes cylinder liners, pistons, a volumetric air blower, pump nozzles, an autonomous combustion chamber in which detonation combustion of fuel occurs at a constant volume, a casing, a charging mechanism, a rocker drum, a turbine, a motor-generator, a gear ring , fuel and oil pumps, compression mechanism and cooling system. Air is supplied to the autonomous combustion chamber using a volume type air blower, which is a two-stage piston blower consisting of a supporting cylinder with a second stage piston and an air chamber mounted on a supporting cylinder with an annular first stage piston. The cavities of the second and first stages are connected by channels, and the volume of the air chamber is two times larger than the volume of the cavity of the second stage. The bearing cylinder is the engine support and consists of two sleeves, pressed one on top of the other, and the sleeves are made channels, windows and holes that make up the engine communications system. The charging mechanism consists of a combustion chamber, phase rings with spherical fingers, channels and nozzles. The hemispherical combustion chamber is flange-mounted to the carrier cylinder and is connected by inlet channels to the cavity of the second stage of the air blower. The inlet channels are closed by an inlet phase ring or balls with spherical seats that act as a shutter. The exhaust channels of the combustion chamber are opened by the exhaust phase ring. A liquid cooling shirt is made in the wall of the combustion chamber. The rocker drum is cylindrical, split, and mounted on a carrier cylinder with two bearings. Both parts of the drum are fixed with pins along the perimeter, and inside the drum there are axial spherical wings of the drive of the pistons of the air blower and two radial removable wings of the drive of fuel pump nozzles, oil pumps and an ignition chopper. Outside the rocker drum, an engine drive turbine is installed, which is driven by the pressure of the exhaust gases through several channels and nozzles. The engine is equipped with a mechanism for changing the compression ratio, which consists of two nuts, screwed onto the rocker drum and the bearing cylinder, and a thrust ring. The plane of the piston beam of the second stage and the plane of the ball fingers of the annular piston of the first stage are located at an angle of 90 ° to each other. The pistons of the second and first stage move in different directions, as a result of which their inertia forces are mutually balanced.

The device of a jet engine of detonation combustion is illustrated by the drawings of figure 1 and figure 2. In Fig.1 shows a section of the engine, and Fig.2 is an embodiment of a locking element for the intake channels of the combustion chamber.

The detonation combustion engine according to the invention consists of a casing, a two-stage piston air blower, a charging mechanism, a rocker drum, a turbine, a motor generator, a gear ring, fuel and oil pumps, nozzles, a compression ratio change mechanism, and a cooling system.

The air blower consists of a carrier cylinder 1 with a communication system, a piston 2 of the second stage, a piston beam 3 with spherical fingers 21 and tips 22, an air chamber 7 with an annular piston 8 of the first stage with o-rings 18, rods 15 and fingers 16, ball tips 17 . In this case, the cavities of the second and first stages are connected by channels "a". The bearing cylinder 1 is a support for the engine and consists of two sleeves 1a and 1e, pressed one on top of the other, the sleeves are made channels, windows and holes that make up the communications system of the engine. The air chamber 7 is mounted on the carrier cylinder 1.

The charging mechanism consists of a combustion chamber 5, a phase ring 6 of air inlet with spherical fingers 9, inlet channels "vp", exhaust channels "vyp" and nozzles 10. The combustion chamber 5 is hemispherical, attached by a flange 11 to the bearing cylinder 1, is connected to the intake channels " VP "with a cavity" B "of the second stage of the air blower. Instead of a phase ring 6, spherical seats 34 with balls 33 can be installed in the channels “B”, which act as a shutter when the pressure drops in the cavity “B” and the combustion chamber 5 (see FIG. 2). The exhaust channels “vyp” are opened by a phase ring 12 with spherical fingers 13 and connected to the nozzles 10. A liquid cooling jacket “H” is made in the wall of the combustion chamber 5.

The rocker drum 4 is cylindrical, detachable mounted on a bearing cylinder 1 on ball bearings 14, both parts of the drum 4 are fixed with pins 19 around the perimeter. Inside the drum 5, an axial spherical linkage K1 of the piston 2 drive and the annular piston 8 is made, as well as radial removable backstage KZ of the drive of the fuel pump nozzles 20 and K2 of the drive of the oil pumps 23 and the breaker of the distributor 24 of the ignition system.

The turbine 25 of the engine drive is installed outside the rocker drum 4 and is driven by the pressure of the exhaust gases through several channels "vyp" and nozzles 10, the ring gear 26 is also installed outside.

The mechanism for changing the compression ratio consists of nuts 27 and 28, screwed onto the rocker drum 4 and the bearing cylinder 1, and a thrust ring 29.

The motor generator consists of coils 30 and an NS magnet and acts as a starter and generator.

The degree of compression in the cavity "B" of the second stage is two times greater than the degree of compression of the air cavity "A" of the first stage, and the volume of the cavity "A" is two times larger than the volume of the cavity "B".

A jet detonation combustion engine operates as follows.

In the initial position, the piston 2 of the second stage is located near the BDC, the purge windows "PO" are open, the annular piston 8 of the first stage is located near the BDC, the compressed air from the cavity "A" passes through the channels "a" into the cavity "B", in the combustion chamber 5 inlet "in" and outlet "vyp" channels are open, the combustion chamber 5 is purged with excess air pressure. Next, the piston 2 moves to the TDC, closes the “PO” purge windows, the “exhaust” exhaust channels are closed in the combustion chamber 5, and the combustion chamber 5 is charged with compressed air. At the same time, fuel is injected into the combustion chamber 5, which is mixed with air and undergoes physical and chemical preparation. An electric spark is supplied to the combustion chamber 5 so that the period of induction of the combustible mixture ends when the piston 2 arrives at the TDC and the intake channels “VP” are closed by a phase ring 8, or balls 33 of the seats 34, acting as a shutter. The air cavity "B" is disconnected from the combustion chamber 5, the latter operates autonomously and does not depend on the position of the piston 2 of the air blower. The process of combustion of the combustible mixture with a constant volume, which is accompanied by an explosive, shock wave and has a detonation character, leading to a sharp increase in temperature and pressure and an additional release of thermal energy. At the end of combustion, the exhaust ports open and the gas expansion process takes place, during which the gases instantly fly out and shoot through the nozzles at high speed, the pulses of the gas reaction force cause traction and rectilinear motion of the engine. Part of the gas rushes to the turbine 25, which rotates the drum 4 and the duty cycle is repeated.

The detonation combustion engine operates in reactive and turbine modes on lean mixtures, is environmentally friendly and can be used as a cassette-type engine module to produce a more powerful engine.

Claims (1)

An engine including cylinder liners, pistons, a volumetric type air blower, pump nozzles, characterized in that it also includes an autonomous combustion chamber in which detonation combustion of fuel occurs at a constant volume and into which air is supplied by an air blower volumetric type, casing, charging mechanism, rocker drum, turbine, motor generator, ring gear, fuel and oil pumps, a mechanism for changing the degree of compression and cooling system, while the air blower represents a two-stage piston supercharger, which consists of a bearing cylinder with a piston of the second stage and an air chamber mounted on the bearing cylinder with an annular piston of the first stage, the cavities of the second and first stages are connected by channels, and the volume of the air chamber is two times the volume of the cavity of the second stage, the bearing cylinder It is a motor support and consists of two sleeves, pressed one on top of the other, the sleeves are made channels, windows and holes that make up the engine communications system, the charging mechanism consists of combustion chambers, phase rings with spherical fingers, channels and nozzles, the combustion chamber is flange-mounted to the carrier cylinder and connected by inlet channels to the cavity of the second stage of the air blower, these channels are closed by a phase ring or balls with spherical seats that act as a shutter, the exhaust channels of the combustion chamber open with a phase ring, a liquid cooling jacket is made in the wall of the combustion chamber, the rocker drum is cylindrical, detachable and mounted on a bearing cylinder with two bearings kach, both parts of the drum are fixed with pins around the perimeter, inside the drum there is an axial spherical link of the drive of the pistons of the air blower and two radial removable wings of the drive of the fuel pump nozzles, oil pumps and an ignition chopper, an engine drive turbine is installed outside the rocker drum, which is driven by pressure exhaust gases through several channels and nozzles, the engine is equipped with a compression ratio change mechanism, which consists of two nuts, screwed onto the rocker drum and bearing cylinder and the thrust ring, the plane of the beam of the second stage piston and the plane of the annular piston ball studs of the first stage are arranged at 90 ° to each other, said pistons move in opposite directions, whereby their inertia forces balance each other.

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