RU2244140C2 - Internal combustion jet-turbine engine - Google Patents

Abstract

FIELD: mechanical engineering; piston internal combustion engines.

SUBSTANCE: proposed engine consists of carrying cylinder with pipe system, piston, link drum, air chamber with ring air supercharger, compression ratio changer, exhaust gas discharge mechanism with nozzles, fuel and oil pumps, ignition system and also turbine and casing. Engine operates according to two stroke cycle with scavenging of cylinder with air at reaction and turboreaction modes. Piston is connected by drive with link of link drum, inertia forces of piston are balanced by ring air supercharger which moves in direction opposite to that of piston. With discharge holes and channels of nozzles opened, compressed gases are ejected outside and expand, and gas reaction pulses execute mechanical work acting onto engine in form of thrust. Or gases expand in turbine. Said engine can be used as module to form more powerful engine by assembling several modules into cluster or holder, for instance, with common turbine.

EFFECT: improved efficiency of engine in operation.

5 dwg

Description

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

Two-stroke internal combustion engines are known in which kinematic circuits with a crankshaft are used and the cylinders are purged with air through the purge windows (Device and car repair, 1987, Higher School, Moscow).

The disadvantages of modern well-known internal combustion engines, despite their significant improvement, the introduction of complex electronic systems, mechanisms and devices for controlling and supplying fuel and air to the engine cylinders, cleaning of combustion products, are their low efficiency, which is much lower than the efficiency of jet engines. The main reason is the lack of effectiveness of the kinematic scheme with a crankshaft used in the engine, in which the average radius of the crank in the active section of the pressure of the piston on the crank is about 0.7 of the actual crank.

The technical task of the claimed invention is to increase the efficiency of the engine.

The problem is solved in that in a two-stroke jet-turbine internal combustion engine containing a bearing cylinder, a piston with a piston pin, an outlet with a nozzle, according to the invention, the piston is connected by a piston pin with a rod and a piston beam with spherical fingers and spherical tips installed in the main link, the engine consists of a split rocker drum with a large and a small axial and radial link mounted on ball bearings on a support cylinder, resistant and adjustable th nuts for moving one detachable part of the rocker drum relative to its other part in order to change the compression ratio, an air chamber with an annular air blower and two rods with spherical fingers and spherical tips located in the large rocker of the rocker drum, a crosspiece with a support, a fuel pump, a feed pump gas, injection and pumping oil pumps, end plate with a support and a phase exhaust gas ring with a beam, spherical fingers and spherical tips located in ma beneath the rocker of the rocker drum, exhaust openings with jet nozzles, a motor generator, an ignition coil with a chopper, a magnet, a spark plug, a turbine with a protective jacket mounted on a console on ball bearings, an engine casing, a bearing cylinder consists of two sleeves, pressed one on another, on the outer surface of the inner sleeve air channels are made, purge windows, suction and discharge holes, fuel, gas and oil pipelines with sprayers and nozzles are laid, The main components of the engine communication system, the plane of the piston beam and the plane of the rod of the annular supercharger located in the main rocker of the rocker drum are offset at an angle of 90 degrees to each other, as a result, the piston and annular supercharger move translationally in opposite directions, their inertia forces are mutually balanced, reactive the turbine internal combustion engine operates in a two-stroke cycle with a straight-through cylinder blowing air with an overpressure of more than one, in the initial position the piston finds near the BDC, the purge windows and gas exhaust openings are open, the air compressed by the annular supercharger and the piston skirt is forced into the purge windows and cleans the cylinder, when the piston moves from the BDC, the gas exhaust holes are closed and fuel is injected or gas is injected before closing the purge windows, then the compression process takes place, the mixture is burned, at the end of the combustion the piston is near the top dead center, at this time the outlet openings, and the compressed gases fly out, shoot through the nozzles at high speed, the process with the expansion of gases, impulses of the reaction force of these gases produce mechanical work, which is transmitted in the form of impulses of the thrust force to the engine, or impulses of the reaction force of gases are transmitted to the blades of the turbine, the jet-turbine internal combustion engine operates in reactive and turbine modes, engine module to obtain a more powerful engine by arranging several modules in a cassette, a cage with or without a common turbine, with minor design changes, the engine module can work It is a conventional internal combustion engine mode.

In the proposed jet-turbine internal combustion engine, the exhaust gases at high speed fly out of the nozzles, act on the turbine blades connected to the transmission of the vehicle. Moreover, M _cr as a whole depends on the diameter of the turbine. Or without a turbine, when the pulses of the reaction force of gases produce mechanical work in the process of their expansion and act as a traction force on the engine. This engine operates in jet and turbine mode. With minor design changes, it can operate in the mode of a conventional internal combustion engine.

The invention is illustrated using the drawings.

Figure 1 presents a longitudinal section of the engine;

figure 2 - scan of the inner cylinder liner;

figure 3 is a section along the turbine of the engine;

figure 4 presents the multi-cylinder (cassette) version of the engine;

figure 5 is a longitudinal section (option).

A jet turbine engine consists of a carrier cylinder 1 with a communications system, a piston 2 with a piston pin 20, a rod 40, a piston beam 3 with ball pins 21 and ball tips 22, a rocker drum 4, a compression ratio mechanism, an air chamber 7, an annular supercharger 8 with o-rings 18, rods 15 and spherical fingers 16 with tips 17, crosses 9 with support 26, fuel pump 27, gas supply pump 28, discharge and pump oil pumps 29, exhaust system, ignition system of the turbine 14 with a protective jacket 36, the ring gear 24, the casing 39 of the engine.

The bearing cylinder 1 consists of an inner sleeve C1, and an outer sleeve C2, pressed one on top of the other. On the outer surface of the inner sleeve Ts1, channels “c” are made for air to enter cylinder 1, blowdown windows PO, air inlet openings, pipelines “b” for supplying gasoline with nozzles “f” and for supplying gas “g” with sprayers “p” directly into the blowdown windows of software, pipeline M for supplying lubricant and pipeline M1 for pumping out excess lubricant, which make up the engine communication system.

The piston 2 is located inside the carrier cylinder 1, is connected by a piston pin 20 to the rod 40, and the beam 3, at the ends of the beam 3 there are spherical pins 21 with spherical tips 22, with which the beam 3 is installed in the large rocker arm K1 of the rocker drum 4.

The rocker drum 4 is detachable into two parts, which are centered around the perimeter of the drum 4 by pins 41, the drum 4 is mounted on two ball bearings 23 on the bearing cylinder 1. On the inner surface of the drum 4 are axial large rocker K1 and small rocker K2, and a radial rocker K3. In the left part of the drum 4, a thrust nut 25 is installed, screwed onto the carrier cylinder 1, and an adjusting nut 6 for changing the compression ratio, screwed onto the drum 4.

The air chamber 7 is mounted on the carrier cylinder 1, inside the chamber 7 there is a supercharger ring 8 with O-rings 18 and connected to two rods 15, which are located in the outer grooves N of the sleeve C2, the rods 15 with their spherical fingers 16 with tips 17 are located in the large wings K1 , the plane of the rods 15 is rotated relative to the plane of the beam 3 of the piston 2 by an angle of 90 degrees, as a result, the piston 2 and the annular supercharger 8 move in opposite directions, their inertia forces are mutually balanced.

The fuel pump 27, the gas supply pump 28, the injection and pumping oil pumps 29 are installed in the crosspiece 9, are driven from the backstage KZ and connected by pipelines (figure 2) to the blowdown windows of the carrier cylinder 1, in which the “p” nozzles are installed and nozzles "f" of fuel and gas. The pressure oil pump 29 supplies oil to each rubbing part through line M, excess grease is pumped out through line M1.

The gas release mechanism consists of an end plate 10 with a support 30, a phase ring 11 with a beam 31, spherical fingers 32 and spherical tips 33, located in the small wings K2, outlet openings with nozzles 34.

The ignition system consists of an ignition coil 12, with a chopper, motor-generator 13, magnet NS. The motor generator acts as a starter and generator, candles.

The turbine 14 (figure 3) with a protective jacket 36 is installed on the console 37 on ball bearings 38.

The gear ring 24 is mounted on the rocker drum 4, designed to manually start the engine and connect the engines to work in a cassette version.

The casing 39 is mounted on the end supports 26 and 30.

The operation of the jet-turbine internal combustion engine (Fig.1, 3, 5). In the initial position, the piston 2 is located near the BDC, the blowdown windows of the software are open, the exhaust openings of the gases are open. The air compressed by the annular supercharger 8 in the air chamber 7 and the piston skirt 2 through the air channels “c” is supplied to the cylinder 1 and purges it. At the beginning of the movement of the piston to the TDC, before closing the blowdown windows of the software, the exhaust openings are closed at this time fuel is injected into the cylinder through the software windows or gas is supplied, after the software windows are closed, the mixture is compressed and burned at a constant volume of the combustion chamber. At the end of combustion, the phase ring 11 opens the outlet "vyp", there is a process of expansion of compressed gases, which fly out and shoot out through nozzles 34 at high speed. Impulses of the reaction forces of these gases produce mechanical work, which is transmitted to the engine in the form of impulses of traction.

The jet-turbine internal combustion engine operates in jet and turbine modes and can be used as an engine module to produce a more powerful engine by arranging several modules in a cartridge, cage (figure 4) with or without a common turbine.

Claims (1)

A two-stroke jet-turbine internal combustion engine containing a bearing cylinder, a piston with a piston pin, an outlet with a nozzle, characterized in that the piston is connected with a piston pin to the rod and the piston beam with spherical fingers and spherical tips installed in the main wings, the engine consists of split rocker drum with a large and small axial and radial wings mounted on ball bearings on the bearing cylinder, thrust and adjusting nuts to move one split hour tee of the rocker drum relative to its other part in order to change the compression ratio, the air chamber with an annular air blower and two rods with spherical fingers and ball tips located in the large rocker of the rocker drum, a spider with support, fuel pump, gas supply pump, discharge and pump oil pumps, an end plate with a support and a phase exhaust gas ring with a beam, spherical fingers and spherical tips located in the small wings of the rocker drum and holes with jet nozzles, a motor generator, an ignition coil with a chopper, a magnet, a spark plug, a turbine with a protective jacket mounted on a console on ball bearings, an engine cover, a bearing cylinder consists of two sleeves, pressed one on top of the other, on the outer surface air ducts, purge windows, suction and discharge openings are made of the inner sleeve, fuel, gas and oil pipelines with sprayers and nozzles that make up the engine communications system are laid, the flatness of the piston beam and the plane of the annular supercharger rods located in the rocker of the rocker drum are offset at an angle of 90 ° to each other, as a result, the piston and annular supercharger move translationally in opposite directions, their inertial forces are mutually balanced, the turbojet internal combustion engine works in a push-pull cycle with straight-through cylinder blowing with air with an overpressure of more than one, in the initial position the piston is located near the BDC, blowdown windows and exhaust openings They are open for gases, the air compressed by the annular supercharger and the piston skirt is pumped into the purge windows and cleans the cylinder, when the piston moves from the BDC, the gas outlet openings are closed and fuel is injected or gas is closed before the purge windows are closed, then the mixture compresses and burns, at the end of combustion, the piston is located near the top dead center, at this time the exhaust openings and compressed gases fly out and shoot through the nozzles at high speed, the process of gas expansion occurs, and the reaction force They perform mechanical work, which is transmitted in the form of impulses of the thrust force to the engine or impulses of the reaction force of gases are transmitted to the turbine blades, the turbojet internal combustion engine operates in the reactive and turbine modes, and can be used as an engine module to produce a more powerful engine by the layout of several modules in a cartridge, a cage with or without a common turbine, with minor structural changes, the engine module can operate in the mode of a conventional internal combustion engine and I.

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