RU2693550C1 - Internal combustion rotor engine with asymmetric compression and expansion - Google Patents

Internal combustion rotor engine with asymmetric compression and expansion Download PDF

Info

Publication number
RU2693550C1
RU2693550C1 RU2018105063A RU2018105063A RU2693550C1 RU 2693550 C1 RU2693550 C1 RU 2693550C1 RU 2018105063 A RU2018105063 A RU 2018105063A RU 2018105063 A RU2018105063 A RU 2018105063A RU 2693550 C1 RU2693550 C1 RU 2693550C1
Authority
RU
Russia
Prior art keywords
rotor
rotation
eccentric shaft
compression
rotors
Prior art date
Application number
RU2018105063A
Other languages
Russian (ru)
Inventor
Александр Владимирович Яновский
Original Assignee
Александр Владимирович Яновский
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Александр Владимирович Яновский filed Critical Александр Владимирович Яновский
Priority to RU2018105063A priority Critical patent/RU2693550C1/en
Application granted granted Critical
Publication of RU2693550C1 publication Critical patent/RU2693550C1/en

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01CROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C1/00Rotary-piston machines or engines
    • F01C1/22Rotary-piston machines or engines of internal-axis type with equidirectional movement of co-operating members at the points of engagement, or with one of the co-operating members being stationary, the inner member having more teeth or tooth- equivalents than the outer member
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01CROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C11/00Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type
    • F01C11/002Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type of similar working principle
    • F01C11/004Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type of similar working principle and of complementary function, e.g. internal combustion engine with supercharger
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02BINTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • F02B53/04Charge admission or combustion-gas discharge
    • F02B53/08Charging, e.g. by means of rotary-piston pump

Abstract

FIELD: machine building.SUBSTANCE: invention relates to the field of rotary internal combustion engines. Essence of the invention consists in the fact that the working fluid (air or fuel-air mixture) absorption and compression takes place in the compressor section, air-fuel mixture ignition and combustion is in located in the middle engine cover combustion chamber, the working gas expansion and subsequent pushing out is in the turbine section. In the radial direction, the compression and expansion chambers are limited by the compressor and turbine sections stators cylindrical surface, each with its own stator. Compression and expansion chambers volumes changing is provided by rotating around two centres (the eccentric shaft centre of rotation and the rotor on the eccentric shaft centre of rotation) rotors with the main and rotor bearings necks eccentricity. In the axial direction, the compression and expansion chambers are limited by the stator covers (front, middle, rear), in which the eccentric shaft main supports and the rotors rotation synchronizers bearings are located. Working fluid compression degree and the working gas expansion degree are determined by their own section (compressor, turbine) geometrical parameters. Expansion ratio to the compression ratio relationship in range of 2÷10 is achieved by the stators width, the stators working surfaces diameter and the eccentric shaft axis of rotation eccentricity and the rotor axis of rotation changing, either one of these dimensions, or combination thereof.EFFECT: technical result consists in increase in the engine efficiency.3 cl, 9 dwg

Description

The invention relates to the field of internal combustion engines with volumetric compression - the expansion of the working fluid, namely, to rotary internal combustion engines with continued expansion.
With respect to this application, the following generally accepted definitions are accepted:
The working medium is air or an air-fuel mixture admitted into the engine at the intake stroke for further compression.
The working gas is a gas formed as a result of the combustion of fuel in the air medium introduced into the engine at the intake stroke.
The compression ratio is the ratio of the maximum volume of the intake chamber (the volume of air available for compression) to the minimum volume of the compression chamber (includes both the volume of the combustion chamber itself and the “parasitic” volume of air that is not available for participation in combustion).
The degree of expansion is the ratio of the maximum volume of the expansion chamber to the minimum volume of the expansion chamber (includes the volume of the combustion chamber).
The “parasitic” volume of air is a part of the volume of air of the minimum compression chamber that does not enter the combustion chamber and does not participate in further engine operation (the energy expended to compress this part of the air is lost).
All known realized internal combustion engines with volumetric compression - expansion (not gas turbine) have a constructive limitation - the degree of expansion of working gases is equal to the degree of compression of the air-fuel mixture. Since the increase in the compression ratio is limited by the combustion conditions (detonation, high pressure), the expansion ratio is also limited (for petrol engines - 9 ÷ 12, for diesel engines - 16 ÷ 22). As a result, part of the energy of the working gases is not used (up to 30%).
Attempts to re-use the energy of exhaust gases with the help of additional expansion devices (expander engines) lead to a significant increase in the weight and dimensions of the power plant, and most of the additional energy received is spent on the mechanical losses of additional devices.
A rotary internal combustion engine is known, comprising a housing with an epitrochoidal surface in which a fuel injection nozzle is mounted and there are inlet and blow-filling windows located close to each other, in the housing there is a rotor making a planetary movement characterized by the fact that cylindrical grooves with centers at the intersection of straight lines, etc. are made opposite sides of the horizontal axis of the body at a distance of the magnitude of eccentricity from the center of the eccentric shaft guided through the center of the eccentric shaft at angles of 45 ° to the horizontal axis of the housing, and straight lines drawn from a point eccentric to the center of the housing at angles of 22.5 ° to the vertical axis passing through this point, cylindrical sleeves with parallel side slices at the ends that enter the end grooves of the rotor and are in contact with the sites with their side parallel walls, the direction of which coincides with the direction of the longitudinal axes of the end synchronizing slots of the rotor, passing through the center of the rotor at angles of 22.5 ° to the longitudinal axis of the rotor, one at each end of the rotor and the side parallel walls of the synchronizing slots of the rotor are connected by arcs made along radii corresponding to the radius of the outer circumference of the cylindrical surface of the synchronizing sleeves and providing relatively recent movement of the synchronizing the rotor grooves when performing the diameter of the eccentric shaft of a large size (RF patent №2158834, priority from 10.03.1999, publ. 10.11.2000).
Disadvantages of the solution for this patent:
- the engine of this patent works in a two-stroke scheme with all its flaws: since the air inlet and exhaust are in one time period - it is difficult to clean the intake chamber from exhaust gases and not lose the intake air;
- the degree of compression is equal to the degree of expansion and up to 30% of the energy of the working gas for performing useful work is not used.
- the rigidity of synchronization of the rotations of the eccentric shaft and the rotor at the points of uncertainty of each of the synchronizing mechanisms located in the front and rear parts of the rotor and offset relative to each other by 45 ° along the rotor and 90 ° along the covers (proposed in the patent) is two times lower than if this displacement was 90 ° along the rotor and 180 ° along the covers.
Known rotary internal combustion engine, in which the suction and compression of the working fluid occurs in the compressor section of the engine, ignition and combustion of the air-fuel mixture occurs in the combustion chamber located in the middle engine cover, the expansion of the working gas and subsequent ejection occurs in the turbine section of the engine, timely opening and the intake, exhaust and combustion chambers are closed by the rotors of the compressor and turbine sections; the rotor changes the volume of the compression and expansion chambers In the axial direction of compression and expansion chambers bounded stator lids (front, middle, back) in which it is located bearings root supports the eccentric shaft (patent DE 102004023370 A1, publ., 21.10.2004).
Disadvantages of the solution for this patent:
- the proposed design scheme for gas compression / expansion does not have a reliable sealing of the chambers - only a small gap between the stator and the rotor prevents gas from flowing from the compression chamber to the inlet chamber, or, similarly, from the expansion chamber to the exhaust chamber, and such sealing works only on very large speeds (but the valve provided in the combustion chamber can work only at very low speeds);
- the proposed channel system, which provides timely connection of the combustion chamber with the compression chamber and expansion chamber, has a large “parasitic” volume and does not prevent the return of burning gases into the compression chamber (to prevent such a throw, a special additional valve is provided);
- despite the compact combustion chamber, a special valve in the middle cover of the stator preventing the injection of burning gases into the compression chamber does not have a forced drive, which means it will work only at low speeds (this contradicts the operating conditions of the gas seals).
Known rotary engine containing a pair of working chambers, closed variable volumes in which are formed by stators and double-vertex rounded rotors moving in fixed walls and rigidly connected with a movable gear of internal gearing, rolling around an internal fixed gear of half the diameter, characterized by the fact that the stator in section has the shape of a circle of radius R with a center on the starting circle of the internal gear; each pair of chambers consists of an inlet-compression chamber, a working stroke-exhaust chamber "and the mechanism for transferring the compressed charge from the first chamber to the second, made in the form of a hole in the inter-chamber wall, grooves in the walls of the rotors adjacent to the fixed wall and connected to the hole in it with a small variable volume of working chambers, and holes in the middle parts of the rotors, connecting variable volumes of working chambers with grooves, the rounded top of the rotor is movable and has a cross-section view of a rotary sealing shoe with a working surface in the form of a circular arc of radius R, hermetically rotating wok The axis and the stator, which is elastically pressed to the wall, the fresh charge inlet in the first chamber and the burnt charge release in the other are located at the contact points of the respective rotors with the stators, with those rotor positions that form the minimum volumes of the working chambers, the moving gear is eccentrically arranged to rotate in the end bushings, the axis of rotation of which coincides with the axis of the internal fixed gear, one of the bushings is rigidly connected with the gear that transmits the rotation to the power shaft, and the stationary the gear at the ends passes into the cylindrical sections of the shaft; on one movable gear there are several pairs of chambers, the stators of which are rotated relative to each other at a certain angle; the internal cavity between the gears is used for the volume of fluid cooling the engine; the middle part of the recess on both sides to ensure a given degree of charge compression (RF patent No. 22,22624, priority from 15.12.2002, publ. 12/20/2004). This decision is taken as a prototype.
The disadvantages of the prototype:
- the volume of channels in the rotors and the inter-chamber wall, ensuring the overflow of the air charge is so large that the compression ratio necessary for effective combustion can be obtained only with very large working volumes of the section, which is typical of stationary (non-transport) power plants; moreover, the volume of channels of overflow of the air charge is a parasitic volume of air, the compression of which is spent energy, not participating in the further working process of the engine, which leads to a decrease in engine efficiency;
- synchronization of the rotation of the eccentric shaft and rotor in a 2: 1 ratio by the proposed planetary gear mechanism makes it impossible to have a support for the eccentric shaft on the gears side, and the console performance of the main supports of the eccentric shaft leads to reduced rigidity of the structure and overload of the bearings of the main bearings of the eccentric shaft;
- combustion of the air-fuel mixture takes place in a chamber with long narrow slits (nadrorny space), which leads to incomplete combustion due to increased heat sink to the wall.
The technical result of the claimed invention is that due to the compact combustion chamber (cylindrical without long narrow slits), while maintaining the optimum compression ratio for the combustion of the air-fuel mixture and increasing the degree of expansion (continued expansion), it turns out:
- significant, with the same fuel consumption, an increase in the indicator operation removed from the engine (due to additional expansion);
- a significant improvement in the completeness of combustion of fuel (due to the compact combustion chamber);
- a significant reduction in exhaust emission noise (due to a decrease in pressure in the expansion chamber at the time of opening the exhaust channel).
The technical result is achieved by solving a technical problem to create a rotary internal combustion engine, characterized in that the suction and compression of the working fluid occurs in the compressor section of the engine, ignition and combustion of the fuel-air mixture occurs in the combustion chamber located in the middle engine cover between the compressor and turbine sections, expansion the working gas and the subsequent ejection occurs in the turbine section of the engine, in the radial direction of the compression and expansion chamber The cylindrical surface of the stators of the compressor and turbine sections — each with its stator; changing the volumes of the compression and expansion chambers is provided by rotors rotating around the center of rotation of the eccentric shaft and the center of rotation of the rotor on the eccentric shaft with eccentricity of the journals of the main and rotor bearings, in the axial direction of the compression and expansion chamber limited to the front, middle and rear covers of the stator, in which bearings of the main bearings of the eccentric shaft and synchronizers of rotors rotation are located, with This ratio of expansion to compression in the range of 2 ÷ 10 is achieved by changing the stator width, the diameter of the working surfaces of the stators and the eccentricity of the axis of rotation of the eccentric shaft and the axis of rotation of the rotor - either one of these dimensions or their combination, timely opening and closing of the inlet, the exhaust and combustion chambers are performed by the rotors of the compressor and turbine sections, while for the timely opening and closing of the combustion chamber, chamfers are made on the edges of the rotors, forming a channel connecting the cavities above the rotor and on the side of the rotor, the edges of the beginning and end of the chamfer determine the moments of connection of the combustion chamber with the cavities of the compressor and turbine sections so that, in the compressor section, close the combustion chamber at the time "-20 °" ÷ "+ 20 °" turning the eccentric shaft relative to the upper dead point, in the turbine section, the combustion chamber is opened at the moment “-20 ° ÷” + 20 ° ”of the eccentric shaft turning relative to the upper dead point, the axes of rotation of the eccentric rotors have an angular displacement of one relative to the other by“ 0 ° ″ ÷ “+ 20 ° "at the same time The centrifugal compressor rotor is ahead of the eccentric of the turbine rotor in the direction of rotation of the eccentric shaft, the rotational speed of the eccentric shaft is 2 times faster than the rotational speed of the rotor, the synchronization of the rotation of the eccentric shaft and each of the rotors is performed by two synchronizing mechanisms in the form of a cylindrical protrusion in the stator cover and the scenes in the form of a slot in the rotor, each of the synchronizers is located on its side of the rotor and has an offset in the angular direction and, relative to the other, on the rotor by 90 °, on the covers of the stator by 180 °, the axis of the cylindrical surface of the stator and the axis of the synchronizer are located at a distance of eccentricity of the necks of the main and rotor bearings, on one line and on opposite sides of the axis of rotation of the eccentric shaft, ignition-burning workflow can be carried out both in the “Otto” cycle and in the “Diesel” cycle.
The invention relates to rotary internal combustion engines with continued expansion.
The degree of compression of the working fluid (air or air-fuel mixture) is chosen from the conditions for optimizing the ignition and combustion of the air-fuel mixture, and the degree of expansion of the working gas is chosen from the conditions for optimizing the use of the potential energy of the working gas.
The advantages of the above construction according to the present invention in comparison with the prototype are as follows:
- the location of the combustion chamber in the middle, between the rotors, the lid, compared with the combustion chamber in the rotor cavity, significantly reduces the "parasitic" volumes, which consist only of the volume in the face of one rotor instead of the volume in the channels of two rotors and the volume in the channel of the middle cover; significantly reduces the minimum volume of the compression chamber, since the bypass channels, the channel in the middle cover and the nadror space of the turbine section are excluded from the volume; the cylindrical combustion chamber in the middle lid does not have slots specific to the nadrotor space, in which combustion is difficult due to the increased heat sink to the walls;
- synchronization of rotation of the rotors and eccentric shaft by the rocker mechanism, instead of the gear mechanism, by reducing the number of links and separating the functions of synchronization and power transmission, significantly increases the rigidity of the mechanism and its efficiency, since the power is taken from the eccentric shaft, and the rocker mechanism only assumes synchronization forces, and the eccentric shaft has two main supports located on both sides of the rotors.
In addition, the rotary internal combustion engine is characterized by the fact that while maintaining for both rotors a single eccentricity of the axis of rotation of the eccentric shaft and the axis of rotation of the rotor, the synchronizer is pressed into the middle stator cover and synchronizes both rotors at once.
In addition, the rotary internal combustion engine is characterized by the fact that while maintaining for both rotors a single eccentricity of the axis of rotation of the eccentric shaft and the axis of rotation of the rotor, the rotors are assembled on the middle stator cover as a single unit, and two synchronizers are located in the front and rear covers.
The invention is illustrated by drawings, which do not cover and, moreover, do not limit the entire scope of the claims of this technical solution, but are only illustrative materials of a particular case of execution:
FIG. 1 - Rotary internal combustion engine, the scheme of work. Lengthwise cut.
FIG. 2 - Rotary internal combustion engine, the scheme of work. Compressor part: eccentric shaft - turning 0 °; rotor - turn 0 °.
FIG. 3 - Rotary internal combustion engine, the scheme of work. Compressor part: eccentric shaft - turn 90 °; rotor - turn 45 °.
FIG. 4 - Rotary internal combustion engine, the scheme of work. Compressor part: eccentric shaft - turn 180 °; rotor - turn 90 °.
FIG. 5 - Rotary internal combustion engine, the scheme of work. Compressor part: eccentric shaft - 270 ° rotation; rotor - turn 135 °.
FIG. 6 - Rotary internal combustion engine, the scheme of work. Turbine part: eccentric shaft - turning 0 °; rotor - turn 0 °.
FIG. 7 - Rotary internal combustion engine, the scheme of work. Turbine part: eccentric shaft - turn 90 °; rotor - turn 45 °.
FIG. 8 - Rotary internal combustion engine, the scheme of work. Turbine part: eccentric shaft - turn 180 °; rotor - turn 90 °.
FIG. 9 - Rotary internal combustion engine, the scheme of work. Turbine part: eccentric shaft - 270 ° rotation; rotor - turn 135 °.
The main components of the inventive rotary internal combustion engine are presented in FIG. 1. The engine consists of compressor and turbine sections, between which the middle part of the engine is located. The compressor section includes a front cover 1, a compressor stator 2, a middle stator cover 3, a compressor rotor 4. In the middle part there is a combustion chamber 5. The turbine section includes a middle stator cover 3, a turbine stator 6, a rear stator cover 7, a turbine rotor 8. Timely opening and closing of the inlet, exhaust and combustion chamber is carried out by the rotors of the compressor 4 and turbine 8 sections, while for the timely opening and closing of the combustion chamber on the edges of the rotors chamfer 9 is formed, forming a channel connecting the cavity above the rotor and to the side of the rotor, the edges of the beginning and end of the chamfer determine the moments of connection of the combustion chamber with the cavities of the compressor and turbine sections. The change in the volume of the compression and expansion chambers is provided by rotors rotating around two centers: the center of rotation of the eccentric shaft 10 and the center of rotation of the rotor on the eccentric shaft, which is ensured by the eccentricity of the axes of the journals of the main and rotor bearings. The rotation speed of the eccentric shaft 10 is 2 times greater than the speed of rotation of the rotors 4, 8, the synchronization of the rotations of the eccentric shaft and each of the rotors is carried out by two rocker mechanisms, each mechanism consists of a synchronizer 11 in the form of a cylindrical protrusion in the stator cover and the scenes in the form of a slot in the rotor, however, each of the synchronizers is located on its side of the rotor and has an offset in the angular direction, relative to the other, along the rotor by 90 °, along the stator covers by 180 °. In the radial direction, the compression and expansion chambers are bounded respectively by the cylindrical surface of the stator of compressor 2 and the stator of turbine 6. The axis of the cylindrical surface of the stator and the axis of the synchronizer are located at a distance of eccentricity of the axes of the necks of the main and rotor bearings of the eccentric shaft from the axis of the necks of the main bearings of the eccentric shaft, on one line and on opposite sides of the axis of rotation of the eccentric shaft, the radial surface of the rotor is equidistant to the surface of the stator when the rotor is at the top her dead center. In the axial direction, the compression and expansion chambers are limited by stator covers: front 1, middle 3, rear 7, in which bearings of the main supports of the eccentric shaft and synchronizers of rotors rotation are located, while the compression ratio of the working medium and the expansion ratio of the working fluid are determined by the geometrical parameters of their section - compressor, turbine. Changes in the volume of chambers 12-27 provide gas-dynamic cycles (intake, compression, combustion, expansion, release) of engine operation.
Below are the gas-dynamic cycles of the engine and their synchronization. At the same time, the duration of the cycles is theoretical; real - depends on the ratio of the geometric dimensions of structural elements.
• "Intake" of the air-fuel mixture:
- cycle time - 180 ° rotation of the rotor or 360 ° rotation of the shaft - successively chambers 12 (fig. 2), 13 (fig. 3), 14 (fig. 4), 15 (fig. 5), 16 (fig. 2) ;
- radial inlet in the stator of the compressor section; opens and closes with radial seal blades;
- cut-off from the combustion chamber - by the spool mechanism of the rotor of the compressor section.
• "Compression of the air-fuel mixture" (without the participation of the combustion chamber)
- cycle duration - 90 °. rotation of the rotor or 180 ° rotation of the shaft, successively camera 16 (Fig. 2), 17 (Fig. 3), 18 (Fig. 4);
- technical tightness of the compression chamber is provided by radial and face seals.
• "Compression of the air-fuel mixture in the combustion chamber"
- cycle time - 90 ° rotor rotation; 180 ° shaft rotation — in series chamber 18 (Fig. 4), 19 (Fig. 5), 12 (Fig. 2);
- the bypass of the air-fuel mixture into the combustion chamber occurs through the slit of the spool mechanism - chamfer 9 (Fig. 1) on the verge of the rotor of the compressor section;
- the intake of residual gases from the combustion chamber into the compression chamber is hampered by the fact that by the time of their connection the air-fuel mixture is precompressed to a pressure approximately equal to the residual pressure in the combustion chamber;
- cut-off of the combustion chamber from the compression chamber, at the moment of its transition into the “Intake” cycle — chamber 12 (FIG. 2) is produced by the rotary mechanism of the compressor section — the chamfer on the verge of the rotor ends.
• “The ignition of the air-fuel mixture” is performed by an electric spark plug at the moment when the combustion chamber is cut off from the compressor section — produced by the end surface of the compressor rotor 2 (FIG. 2), from the turbine section by the end surface of the turbine rotor 20 (FIG. 6).
• The time for ignition delay and pressure build-up at the moment of ignition start provides an angular advance of the eccentricity of the compressor eccentric with respect to the turbine eccentric (“0 °” ÷ “+ 20 °”).
• "Expansion of the working gas in the combustion chamber"
- cycle time - 90 ° rotation of the rotor - or - 180 ° rotation of the shaft - succession of the chamber 20 (Fig. 6), 21 (Fig. 7), 22 (Fig. 8);
- the bypass of working gases from the combustion chamber into the expansion chamber occurs through the slit of the slide mechanism (chamfer on the verge of the rotor of the turbine section);
- the cut-off of the combustion chamber from the expansion chamber, at the moment of its transition to the “Final Expansion” cycle — chamber 22 (FIG. 8), is produced by the rotary mechanism of the turbine section rotor — the chamfer on the verge of the rotor ends.
• “Final Expansion” (without participation of the combustion chamber):
- cycle time - 90 ° rotor rotation or - 180 ° shaft rotation - chamber 22 (Fig. 8), 23 (Fig. 9), 24 (Fig. 6);
- technical tightness of the expansion chamber is provided by radial and face seals.
• "Exhaust" exhaust gases:
- cycle duration - 180 ° rotor rotation or - 360 ° shaft rotation - chamber 24 (Fig. 6), 25 (Fig. 7), 26 (Fig. 8), 27 (Fig. 9), 20 (Fig. 6) ;
- radial exhaust channel in the stator of the turbine section; opens and closes with radial seal blades;
- shutdown of the exhaust chamber from the combustion chamber is performed by the spool mechanism of the rotor of the turbine section.
Technical and economic advantages of the present invention are that:
- the volume of indicator work of the working cycle has been increased, due to the increase in the degree of expansion of the working gas;
- increased completeness of combustion of fuel due to a compact cylindrical combustion chamber that does not have narrow slit volumes, since at the time of ignition the combustion chamber is cut off by rotors from both the compressor and turbine sections, and the combustion time of the air-fuel mixture increases, as well as the angular advance of the compressor the section relative to the turbine section creates a time interval between the top dead center of compression and the top dead center of expansion;
- reduced exhaust gas noise due to a decrease in pressure in the expansion chamber at the time of opening the exhaust channel, since, due to "continued" expansion, the pressure drop between the expansion chamber and the exhaust system becomes "subcritical" and eliminates "supersonic pressure surges".
- reduced shock loads on the synchronization mechanisms, due to the use of two rocker mechanisms, since the mutual angular displacement of 180 ° across the stator cover gives a minimal discrepancy between the location and speed of the synchronizing elements at the moment of transfer of force from one synchronizer to another.

Claims (3)

1. Rotary internal combustion engine, characterized in that the suction and compression of the working fluid occurs in the compressor section of the engine, ignition and combustion of the air-fuel mixture occurs in the combustion chamber located in the middle engine cover between the compressor and turbine sections, the expansion of the working gas and the subsequent ejection occurs in the turbine section of the engine, in the radial direction of the chamber of compression and expansion are limited by the cylindrical surface of the stators of the compressor and turbine sections - each With its stator, the change in the volumes of the compression and expansion chambers is provided by rotors rotating around the center of rotation of the eccentric shaft and the center of rotation of the rotor on an eccentric shaft with eccentricity of the journals of the main and rotor bearings, in the axial direction of the compression and expansion chambers, in which bearings of main bearings of eccentric shaft and synchronizers of rotor rotation are located, with the ratio of expansion to compression ratio in the range of 2 ÷ 10 being achieved by varying the stator width, the diameter of the working surfaces of the stators and the eccentricity of the axis of rotation of the eccentric shaft and the axis of rotation of the rotor — either one of these dimensions or their combination; timely opening and closing of the inlet, outlet and the combustion chamber are performed by the rotors of the compressor and turbine sections; timely opening and closing of the combustion chamber on the edges of the rotors are chamfering, forming a channel connecting the cavity above the rotor and to the side of the rotor; the edges of the beginning and end of the chamfer determine the moments connected The combustion chamber with the cavities of the compressor and turbine sections in such a way that, in the compressor section, the combustion chamber is closed at the moment “-20 ° ÷” + 20 ° ”of the eccentric shaft turning relative to the top dead center, in the turbine section the combustion chamber is opened at the moment "-20 °" ÷ "+ 20 °" rotation of the eccentric shaft relative to the top dead center, the axis of rotation of the eccentric rotors have an angular displacement of one relative to the other by "0 °" ÷ "+ 20 °", while the eccentric of the compressor rotor is ahead of the eccentric of the turbine rotor in direction The rotation of the eccentric shaft, the speed of rotation of the eccentric shaft is 2 times the rotor speed, the rotation of the eccentric shaft and each of the rotors is synchronized by two slide mechanisms, each mechanism consists of a synchronizer in the form of a cylindrical protrusion in the stator cover and a slot in the form of a slot in the rotor, each of the synchronizers is located on its side of the rotor and has an offset in the angular direction, relative to the other, along the rotor by 90 °, along the stator covers by 180 °, the axis is cylindrical The surface of the stator and the axis of the synchronizer are located at a distance of eccentricity of the necks of the main and rotor bearings, on the same line and on opposite sides of the axis of rotation of the eccentric shaft, while the working process of ignition-burning can be carried out both in the “Otto” cycle and in the “ Diesel.
2. A rotary internal combustion engine according to claim 1, characterized in that while maintaining for both rotors a single eccentricity of the axis of rotation of the eccentric shaft and the axis of rotation of the rotor, the synchronizer is pressed into the middle stator cover and synchronizes both rotors at once.
3. Rotary internal combustion engine under item 1, characterized in that while maintaining for both rotors a single eccentricity of the axis of rotation of the eccentric shaft and the axis of rotation of the rotor, the rotors are assembled on the middle stator cover as a whole, and two synchronizers are located in the front and rear covers.
RU2018105063A 2018-02-09 2018-02-09 Internal combustion rotor engine with asymmetric compression and expansion RU2693550C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2018105063A RU2693550C1 (en) 2018-02-09 2018-02-09 Internal combustion rotor engine with asymmetric compression and expansion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2018105063A RU2693550C1 (en) 2018-02-09 2018-02-09 Internal combustion rotor engine with asymmetric compression and expansion

Publications (1)

Publication Number Publication Date
RU2693550C1 true RU2693550C1 (en) 2019-07-03

Family

ID=67252204

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2018105063A RU2693550C1 (en) 2018-02-09 2018-02-09 Internal combustion rotor engine with asymmetric compression and expansion

Country Status (1)

Country Link
RU (1) RU2693550C1 (en)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE691511C (en) * 1937-09-08 1940-05-29 Rudolf Roemer Capsule pump or blower
DE1426013A1 (en) * 1961-11-28 1969-04-24 Erich Herter Rotary piston engine
GB1340387A (en) * 1970-05-15 1973-12-12 Hyvarinen M J Rotary piston internal combustion engine
US4300874A (en) * 1978-06-12 1981-11-17 Capella Inc. Rotary machine with lenticular rotor and a circular guide member therefor
DE102004023370A1 (en) * 2004-05-12 2004-10-21 Hans-Hermann Bruns Rotary piston engine with joint and cranked movement raises and lowers piston off and back onto support bearing in response to gas and spring pressure affording synchronous movement.
GR1005163B (en) * 2005-04-12 2006-03-21 Ιωαννης Κανελλοπουλος Rotary positive displacement mechanism for fluids
RU2377426C2 (en) * 2008-01-09 2009-12-27 Ольгерд Яковлевич Скрипко Rotary engine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE691511C (en) * 1937-09-08 1940-05-29 Rudolf Roemer Capsule pump or blower
DE1426013A1 (en) * 1961-11-28 1969-04-24 Erich Herter Rotary piston engine
GB1340387A (en) * 1970-05-15 1973-12-12 Hyvarinen M J Rotary piston internal combustion engine
US4300874A (en) * 1978-06-12 1981-11-17 Capella Inc. Rotary machine with lenticular rotor and a circular guide member therefor
DE102004023370A1 (en) * 2004-05-12 2004-10-21 Hans-Hermann Bruns Rotary piston engine with joint and cranked movement raises and lowers piston off and back onto support bearing in response to gas and spring pressure affording synchronous movement.
GR1005163B (en) * 2005-04-12 2006-03-21 Ιωαννης Κανελλοπουλος Rotary positive displacement mechanism for fluids
RU2377426C2 (en) * 2008-01-09 2009-12-27 Ольгерд Яковлевич Скрипко Rotary engine

Similar Documents

Publication Publication Date Title
EP1711686B1 (en) Rotary mechanism
US3855977A (en) Rotary internal-combustion engine
KR20070119689A (en) Radial axis, spherical based rotary machines
EP0510125B1 (en) Rotary internal combustion engine
US5352295A (en) Rotary vane engine
US4057035A (en) Internal combustion engines
AU2011351321A1 (en) Rotary heat engine
US4003349A (en) Rotary piston engine
US3791352A (en) Rotary expansible chamber device
RU2528796C2 (en) Internal combustion engine: six-stroke rotary engine with spinning gates, separate rotor different-purpose sections, invariable volume combustion chambers arranged in working rotors
RU2538990C1 (en) Rotor-piston internal combustion engine
RU2693550C1 (en) Internal combustion rotor engine with asymmetric compression and expansion
RU2351780C1 (en) Rotor-piston internal combustion engine
US8851044B2 (en) Vane-type rotary actuator or an internal combustion machine
US6481410B1 (en) Rotary piston engine/positive displacement apparatus
US3381670A (en) Rotary internal combustion engine
WO2012057838A2 (en) Rotary valve continuous flow expansible chamber dynamic and positive displacement rotary devices
RU2539412C1 (en) Rotary two-chamber internal combustion engine
CN212838062U (en) Conjugate double-cavity shuttle plate rotor engine
RU2477376C2 (en) Internal combustion engine: five-stroke rotary engine with rotary gates, separate working medium compression and expansion sections, and isolated invariable-volume combustion chambers
RU2699864C1 (en) Volumetric type rotary machine
WO2000012867A1 (en) Internal combustion engine
US20120067324A1 (en) Toroidal internal combustion rotary engine
JP2922640B2 (en) Annular super-expansion rotary engine, compressor, expander, pump and method
RU2206759C2 (en) Double-rotor multichamber internal combustion engine