RU2086782C1 - Turborevolving internal combustion engine - Google Patents

Abstract

FIELD: internal combustion engines used in aviation, automobiles, sea fleet. SUBSTANCE: engine has housing 5 where rotor made in the form of revolving drum is rotating; cylinders 4 equipped with nozzle apparatus are located inside drum. Bladed apparatus 6 is also located in housing. During rotation of rotor, each cylinder is periodically matched with fuel supply chambers, combustion chamber, expansion chamber and exhaust chamber. Fan and starter-generator rotate on common shaft with drum. Supply of fuel is effected by means of metering device and ignition of mixture is effected by means of electric plug 1. Working stroke is effected due to interaction of nozzle and bladed apparatuses. Scavenging the cylinders is effected by means of fan via through hole in housing. EFFECT: enhanced efficiency. 1 dwg

Description

 The invention relates to internal combustion engines used in the automotive industry, aviation, navy in stationary and mobile installations, where mechanical energy is obtained by burning liquid, gaseous or solid fuels. The proposed engine is a type of gas turbine and can be used in any of the above areas of technology.

To obtain mechanical energy from gas turbine plants, the following principle of operation is used:
1. The compressor (axial, centrifugal, rotary, etc.) creates an air pressure equal to or somewhat greater than in the combustion chamber, and supplies compressed air to the combustion chamber, where fuel is injected and ignited.

 2. The combustion chamber, where the gases increase in volume during combustion.

 3. Nozzle apparatus, where the energy of gases during expansion is converted into pressure energy on the blades.

 4. The scapula, where the energy of the gas pressure is converted into torque.

 The closest technical solution in its essence and the achievement of the result is a gas turbine internal combustion engine, adopted as a prototype. The US engine by the principle of operation is no different from the well-known gas turbine engines and differs only in the original design, where the axial compressor is replaced by a rotary one, which allows to slightly reduce the initial spin of the axial turbine.

The main disadvantages of this principle of operation are:
the engine cannot operate at low speeds, since it requires high speeds to create pressure in the combustion chamber by the compressor;
energy consumption for air compression in the compressor reaches 70% of engine power;
for starting the engine requires a powerful starting device to spin the compressor to high speeds;
as a rule, the operation mode of a gas turbine engine is several tens of thousands of rpm, while the drive of the working mechanism requires several hundred rpm, therefore, a large reduction gear is required.

 The presence of three bulky mechanisms in a gas turbine installation, such as a spinning device, compressor and gearbox, significantly reduces the advantage of gas turbine engines over other engines (for example, reciprocating, rotary, etc.).

 The technical result of the invention is the creation of a simple, compact and cheap internal combustion engine.

 The essence of the proposed engine is that in its work laid a new principle. In it, air is not compressed by the compressor, but fuel is blown into the cylinders blown with clean air, ignited and burned in a constant volume of the cylinder, which leads to an increase in gas volumes 6-8 times, which determines the degree of "compression" of the engine. Compressor gases do not consume compressor energy to compress gases. The energy of the compressed gases is then realized in the torque in the nozzle and blade devices.

 The drawing shows the proposed engine.

 The engine consists of a housing 5, a rotating turret type drum (BRT) 3, in which cylinders with nozzles 4 are located. A fan and a starter generator are located on the same shaft with the BRT (not shown for simplicity).

 The principle of operation of the engine is illustrated in the diagram (see drawing). In sector B, the cylinders are purged with a fan through a through hole in the housing. In sector D, they are filled with fresh air. In sector A, fuel is fed into cylinders filled with fresh air and mixed. In sector B, ignition of the working mixture by an electric spark 1 in the combustion chamber 2, compression of the mixture during the explosion, and also a “stroke” that implements the energy of the gases from the nozzle apparatus of the rotor cylinders to the blades of the housing 6, due to which there is a torque. Then the gases, expanding, are sent to the exhaust outlet of sector B, where they are removed by a fan, and the cylinders are filled with fresh air. Next, the cycle repeats. If the finished working mixture is fed into the combustion chamber and set on fire, the engine will start to work “from the spot”. The configuration of the cylinders can be of various shapes (round, square, inclined, etc.). The engine operating mode is regulated by electronic equipment.

 The best application of a turbo-turret engine, according to the applicant, is the aviation field, where the engine speed does not change significantly, and the weight per unit of power will allow its use in ultralight aircraft.

Claims (1)

 An internal combustion turbo-revolver engine comprising a housing with a rotor installed in it in the form of a drum with working cylinders arranged around its circumference, a fuel supply, compression, combustion, expansion and exhaust chamber, characterized in that a bypass channel is arranged in each cylinder, which is arranged to periodic communication with the chambers of fuel supply, compression, combustion, expansion and exhaust, located between the housing and the rotor, while the direction of the channel is opposite to the direction of rotation of the rotor .