RU52930U1 - TURBINE INTERNAL COMBUSTION ENGINE - Google Patents

Abstract

An internal combustion turbine engine comprises a housing, a shaft, a disk-shaped turbine, radial blades located on the turbine, a compressor, a combustion chamber, a fuel mixture ignition system, an exhaust system, and at least one gas collection chamber is connected by a channel to at least one nozzle directed to the radial blades of the turbine and the gas flow acting on them. The cross sections of the channels connecting the gas collection chamber to the nozzles increase along the turbine. The nozzle sections increase along the turbine. A turbine internal combustion engine may comprise two turbines interconnected via a gear unit and having different rotational speeds. A turbine internal combustion engine may comprise three or more turbines.

Description

The invention relates to mechanical engineering, in particular to the designs of power plants, including turbine internal combustion engines.

Known gas turbine engine (patent RU No. 2096639), consisting of a housing with working chambers, a shaft, a turbine rotor with blades, a centrifugal compressor, systems for preparing, supplying and igniting a combustible mixture, in its housing having a cylindrical shape, working chambers are evenly distributed around the circumference in an amount multiple of four, the cross-sectional areas of which are shaped, respectively, in planes coinciding with the axis of the casing, rectangles, and in planes perpendicular to this axis, circular sectors, the disk part of the turbine rotor it is made up of uniformly alternating radial blind protrusions and depressions in which the rotor blades are attached, also in the form of circular sectors, and the number of each of them is equal to one second of the number of chambers, and their sum over the circumference of the disk is equal to half (180), in the blind protrusions, to ensure effective cooling of the turbine rotor, through radial cavities are made, and the smooth working surfaces of these blind protrusions are in the same plane with the side surfaces of the rotor blades of the engine and directly enno adjacent to its end with its open side working chambers provided during engine operation consistent closing the two adjacent chambers, which is supplied and combusted combustible mixture.

The disadvantages of this gas turbine engine include the difficulty in manufacturing and low efficiency.

Known compressor-rotor-turbine internal combustion engine (patent RU No. 2109969, 04/27/98, F 02 C 3/04). In the proposed engine on the front side of the disk there are centrifugal compressor blades arranged inside an annular rotor, the outer surface of which has a combustion chamber, the shape of which with the guide hole of the cap ring and the hole of the working ring of the disk is optimally close to the shape of the jet nozzle, whose axis is tangent to the ring rotor and a hollow cone turbine is arranged on the back of the disk, the back of which goes into a cylindrical exhaust nozzle, and the outer

equipped with gas channels, the side walls of which are formed by helical ribs originating from the hole of the disk ring and descending along the perforated part of the cylindrical exhaust nozzle, inside which there is a screw labyrinth with a variable pitch.

The disadvantages of this technical solution is the difficulty in manufacturing and low efficiency.

As a prototype, a gas turbine engine (RU Patent No. 2161714) was selected, comprising a housing, combustion chambers with nozzles, a shaft, a turbine rotor with blades, a centrifugal compressor with at least two stages, a fuel mixture ignition system and a heat exchanger with exhaust pipes, when this number of combustion chambers is a multiple of three, one compressor stage is located around the entire circumference, and the second is made in the form of two sectors symmetrically located relative to each other with a central angle of 90 ° each, and the rotor is made with h with a protrusion located with the possibility of blocking the nozzles of the combustion chambers.

The disadvantage of this technical solution is the low efficiency.

The objective of the invention is to increase engine efficiency.

The technical result is achieved in that the turbine internal combustion engine comprises a housing, a shaft, a disk-shaped turbine, radial vanes located on the turbine, a compressor, a combustion chamber, a fuel supply and ignition system, an exhaust system, and at least one the gas collection chamber is connected by a channel with at least one nozzle directed to the radial blades of the turbine and the gas flow acting on them. The cross sections of the channels connecting the gas collection chamber to the nozzles increase along the turbine. The nozzle sections increase along the turbine. A turbine internal combustion engine may comprise two turbines interconnected via a gear unit and having different rotational speeds. A turbine internal combustion engine may comprise three or more turbines.

The invention is illustrated by drawings.

Figure 1 shows a section of the described turbine internal combustion engine; figure 2 is a section aa of a turbine internal combustion engine; figure 3 is a section of a turbine internal combustion engine containing two turbines in the form of disks connected to each other through a block of gears.

The turbine internal combustion engine comprises a housing 1, a shaft 2, a turbine 3 with radial blades 4, a compressor 5, a combustion chamber 6, an air supply channel 7,

a fuel supply channel 8 and a spark plug 9, an exhaust system consisting of gas collection chambers 10, channels 11, nozzles 12 and a window for exhaust gas 13. The turbine internal combustion engine contains gears 14.

A turbine internal combustion engine operates as follows. When starting the engine and the beginning of rotation of the shaft 2, the compressor 5 pumps air through the air supply channel 7 into the space between the radial blades 4 of the turbine 3 forming the combustion chamber 6. Then, when the turbine 3 rotates, the combustion chamber 6 moves to the fuel supply channel 8, where fuel supply, resulting in a combustible mixture. The combustible mixture, being in the combustion chamber 6, moves to the spark plug 9 and ignites, at this moment there is a sharp increase in gas pressure in the combustion chamber 6. At the time of combining the combustion chamber 6 with the gas collection chamber 10, the latter is filled with working gases. Under the influence of pressure, the working gases pass through the channel 11 and the nozzle 12, acting on the radial blades 4 of the turbine 3. Then, the working gases enter the next gas collection chamber and pass through the channel and the nozzle of large sizes, giving the turbine additional acceleration, which contributes to a further increase in speed and engine power. Working gases that have consumed their energy in rotation are ejected through the window 13 of the exhaust system.

The inventive device with multiple use of working gases can significantly increase the efficiency of a turbine internal combustion engine.

Claims (5)

1. A turbine internal combustion engine comprising a casing, a shaft, a disk-shaped turbine, radial vanes located on the turbine, a compressor, a combustion chamber, a fuel supply and ignition system, an exhaust system, characterized in that it comprises at least one gas collection chamber connected by a channel with at least one nozzle directed to the radial blades of the turbine. 2. The turbine internal combustion engine according to claim 1, characterized in that the cross-sections of the channels connecting the gas collection chamber to the nozzles increase along the turbine. 3. The turbine internal combustion engine according to claim 1, characterized in that the nozzle sections increase along the turbine. 4. The turbine internal combustion engine according to claim 1, characterized in that it contains at least one additional turbine. 5. The turbine internal combustion engine according to claim 1, characterized in that the turbines are interconnected via a gear block and have different rotational speeds.