KR20120092075A - Internal combustion engine using the dual turbine - Google Patents

Abstract

PURPOSE: An internal combustion engine using a dual turbine is provided to make an engine structure small by burning fuels in an external contact surface between a power turbine and a stroke turbine. CONSTITUTION: An internal combustion engine using a dual turbine comprises a combustion chamber(100), a turbine phase control unit(200), and a power transmission unit(300). A power turbine and a control turbine synchronizing with the power turbine interlock each other. The fuel flows in between turbines, and burned. The combustion chamber generates power output to the power turbine. The turbine phase control unit control the phase of the control turbine. The power transmission unit delivers power to the turbine phase control unit.

Description

Internal combustion engine using double turbine {INTERNAL COMBUSTION ENGINE USING THE DUAL TURBINE}

The present invention relates to an internal combustion engine using a double turbine, and more particularly, to an internal combustion engine using a double turbine that can improve durability and can significantly improve efficiency while miniaturizing.

In general, the existing internal combustion engine realizes the process of intake, compression, explosion, and exhaust of fuel by using the reciprocating motion of the piston, and converts the linear motion into the rotational motion and uses three or more pistons for smooth engine operation. To distribute the phase angle of the explosive energy.

In addition, the rotary motion internal combustion engine (rotary engine) currently used is a structure that performs suction, compression, explosion, and exhaust processes by using a rotary turbine eccentric to a rotating shaft in an elliptical engine room. By converting the explosion energy into rotational motion.

On the other hand, in the case of an engine using a conventional piston reciprocating motion, a combination of several pistons can be used to realize a smooth rotational motion, and energy loss is inevitably generated during the process of converting the reciprocation motion to a rotational motion, thereby deteriorating efficiency. There is a problem that is difficult to miniaturize the device by installing a plurality of pistons.

In addition, in the case of the eccentric rotating turbine engine of the conventional elliptical engine compartment (applied to a rotary engine), the center of gravity of the rotating body is basically biased, so that it is difficult to maintain the accuracy of the engine compartment and the rotating turbine and to ensure the durability of the engine. There is this.

The present invention was devised to solve the above problems, and provides an internal combustion engine using a double turbine that can control the stroke of the engine in the phase of the control turbine by cross-linking the power turbine and the control turbine synchronized in the same rotation shaft. It aims to do it.

According to an embodiment of the present invention for achieving the above object, as an internal combustion engine generating an output by the rotational motion of the turbine, the power turbine and the control turbine is installed in a state in which the fuel is introduced into the space between the turbine A combustion chamber to combust; A turbine phase control unit controlling a phase of the control turbine; A phase detector for detecting phases of the power turbine and the control turbine; And it provides an internal combustion engine using a double turbine made of a transmission unit for transmitting power to the turbine phase control unit.

According to the invention, all the components rotate about the same axis of rotation, especially the center of gravity in the axis of rotation, the energy loss is generated only in the bearing to reduce the frictional force, the energy loss is low, the combustion is external to the power turbine and the stroke turbine Since the turbine is essentially rotated on the border surface, the internal combustion engine can be miniaturized, and the production process is simple and high durability can be realized.

1 is a main configuration of an internal combustion engine using a double turbine according to the first embodiment of the present invention,
2A to 2I are cross-sectional views showing cross sections of respective parts of an internal combustion engine using a double turbine according to the first embodiment of the present invention;
3 is an operation flowchart of an internal combustion engine using a double turbine according to the first embodiment of the present invention;
4A to 4H are exemplary views showing the structure of an electric motor of an internal combustion engine using a double turbine according to the first embodiment of the present invention.
5A to 5C are exemplary views showing the structure of a combustion chamber turbine of an internal combustion engine using a double turbine according to the first embodiment of the present invention;
6 is a perspective view of a combustion chamber turbine of an internal combustion engine using a double turbine according to the first embodiment of the present invention;
7 is a perspective view of an internal structure of a combustion chamber turbine of an internal combustion engine using a double turbine according to a first embodiment of the present invention;
8A to 8F are configuration diagrams showing a turbine phase controller of an internal combustion engine using a double turbine according to the first embodiment of the present invention;
9 is a conceptual diagram of a turbine phase controller operation of an internal combustion engine using a double turbine according to a first embodiment of the present invention;
10a to 10c is an exemplary view showing the structure of a three-pole combustion chamber turbine of the internal combustion engine using a double turbine according to a second embodiment of the present invention,
11A to 11C are exemplary views showing the structure of a two-pole combustion chamber turbine of an internal combustion engine using a double turbine according to a third embodiment of the present invention.
12a to 12d is a conceptual diagram showing each stroke state when the clockwise and counterclockwise rotation of the internal combustion engine using a double turbine according to the present invention,
13a to 13c is a conceptual diagram for explaining the operation concept of the internal combustion engine using a double turbine of the present invention,
14 is a block diagram showing the internal configuration of the internal combustion engine using a double turbine according to a fourth embodiment of the present invention,
15 is a perspective view showing the configuration of a turbine of an internal combustion engine using a double turbine according to a fourth embodiment of the present invention;
16 is an exploded perspective view showing the configuration of a turbine of an internal combustion engine using a double turbine according to a fourth embodiment of the present invention;
17 is a perspective view showing the inside of a combustion chamber of an internal combustion engine using a double turbine according to a fourth embodiment of the present invention;
18 is a perspective view showing a turbine phase control unit of a combustion chamber of an internal combustion engine using a double turbine according to a fourth embodiment of the present invention;
19 is an exploded perspective view showing a turbine phase control unit of a combustion chamber of an internal combustion engine using a double turbine according to a fourth embodiment of the present invention; and
20 is an exploded perspective view showing an internal configuration of a turbine phase control unit of a combustion chamber of an internal combustion engine using a double turbine according to a fourth embodiment of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

1 to 2I, an internal combustion engine using a double turbine according to the present invention includes a combustion chamber 100, a turbine phase control unit 200, and a transmission unit 300, and at one side of the combustion chamber 100. The power shaft 110 for power transmission is installed.

The motor 300 may be adopted a non-commutator motor, by directly releasing the phase angle control function of the turbine phase control unit 200 by directly connecting the rotational force of the motor 300, and starts the engine by the driving force of the motor, After starting, the phase angle control function is activated, and the rotational force of the electric motor is converted to the stroke control force for the turbine of the combustion chamber 100, and then the fuel (mixed gas) is sucked and ignited to operate the rotary motion internal combustion engine. At this time, since the electric drive unit 300 operates as a power source of the turbine phase control unit 200 of the engine, it operates only with a small amount of energy of suction, compression, and exhaust, and supplies instantaneous energy of a large control torque for preventing reverse rotation only during an explosion. do.

At this time, the electric motor 300 generates a large control torque for the force in the direction to stop, because the amount of change in the rotating magnetic flux of the rotor is greatly reduced, the impedance of the stator coil is sharply reduced, thereby generating a large reverse control torque even with a small voltage Done.

3 and 14, the internal combustion engine using the double turbine of the present invention first releases the four cycle control unit (turbine phase control unit) 200 and drives the electric motor 300 with a small electromotive force to control the turbine and the power turbine ( In FIG. 14, the satellite deviation is detected after closely contacting 150a and 150b (S 10). Subsequently, starting torque is generated by the transmission unit 300 to operate the internal combustion engine (S 20).

The rotational force of the transmission unit 300 is continuously transmitted to the power turbine 150a and all the intake / exhaust valves are closed to close the turbines (S 30). At this time, according to the command of the high speed or the internal combustion engine operation request can be operated at a low speed and high speed (S 40). When the command of the high speed or the operation is transmitted, the turbine phase control unit 200 is activated and the phase of the power turbine 150a is checked to start the phase adjustment of the control turbine 150b in the desired rotational direction (S50).

Subsequently, fuel is sucked into the space between the power turbine 150a and the control turbine 150b (between the spaced turbine blades)-> fuel compression-> fuel ignition-> gas exhaust-> cooling air suction-> cooling air discharge The administration takes place in the following order.

Specifically, the fuel suction checks the phase of the control turbine 150b for fuel suction at the phase reference point O (see FIGS. 12A and 12B), and then opens the suction valve to suck fuel mixed with air (S 60). . In the fuel compression, after the power turbine 150a passes the suction end point at the phase reference point O, the intake valve 450 (see FIG. 14) is blocked and the end of the fuel compression is confirmed by the phase of the control turbine (S 70). The fuel ignition supplies a high torque corresponding to the explosion repulsion force to the control turbine 150b after passing the compression end point at the phase reference point and ignites by supplying a high pressure to the spark plug (S80). When the gas turbine passes through the position of the exhaust valve, the exhaust valve opens the exhaust valve and checks the phase of the control turbine 150b to confirm completion of the gas discharge (S90). Cooling air intake opens the cooling air intake valve for cooling the exploded / exhausted turbine (S 100). The cooling air discharge is switched to the effective turbine stroke after the power turbine 150a passes the suction end point at the phase reference point O, shuts off the suction valve 450 and confirms the cooling air discharge in the phase of the control turbine 150b. S 110).

Subsequently, according to the deceleration or stop request, the above-described stroke may be performed again or decelerated (S 120). In order to decelerate at this stage, the differential force for the target deceleration is substituted to reduce the rotational force of the control turbine 150b and the power turbine 150a by simultaneously supplying fuel and phase control (S 130). In addition, the fuel supply is cut for deceleration or stop, and the deceleration or stop is performed by converting into a charging current suitable for the target deceleration (S 140). In addition, when the stop request is transmitted, the phases of the power turbine 150a and the control turbine 150b are checked, and when the phase reference point is reached, restarting may be prepared (S 150 and S 170).

4A to 4H, the internal structure of the transmission part 300 is shown. The transmission 300 is driven by the stator and the rotor.

5A to 5C, as an example of a combustion chamber turbine having a four-pole turbine blade 113, circular plates on both sides supporting the blades of a power transmission turbine with a double turbine assembled by crossing two turbines having the same structure. (111,112; front and rear) itself is a circular structural wall of the combustion chamber, and the play of the combustion chamber with the inner wall of the combustion chamber body. The moving angle of the control turbine 150b cross-assembled with the power turbine 150a is determined by the number of turbine poles and the blade angle of the turbine (see FIG. 9). Thus, these stroke angles a and b are It is a factor that determines the amount of fuel inhaled, the compression rate, and the displacement.

On the other hand, Figures 10a to 11c is an example of a three-pole and two-pole turbine, it can be seen that by changing the number of valves and the number of spark plugs according to the number of turbine poles can be applied to a variety of design.

8A to 8B, the turbine phase control unit 200 is a four-cycle phase control method including an inner gear 217 having a gear tooth therein and three planetary gears 218 rotating its inner wall. If the number of gear teeth of the inner gear 217 is four times that of the planetary gear 218 and the inner gear 217 is fixed, the planetary gear 218 makes four revolutions when the body of the planetary gear 218 rotates once. Therefore, each time the body of the planetary gear 218 rotates by 90 °, the planetary gear 218 rotates once. When it is connected to the control angle transmission table 215 by the control arm 214, the control angle transmission table 215 reciprocates a predetermined stroke angle every 90 degrees each time the gear body rotates once.

In this example, the blade angle of the turbine is 20 ° in the four-pole turbine, so the stroke angle is 50 °.

When directly transmitting the power of the electric motor 300 to the power shaft 110, if the brake is released to rotate the inner gear 217 as the gear body, the control angle transmission table 215 is a gear without a change in angular motion. Rotating with the body, the power of the motor is directly connected to the engine output.

9, it can be seen that the position change of the control arm and the angle change of the control angle transmitter connected to the rotation of the planetary gear. That is, as shown in FIGS. 8A to 8F, the rotation ratio of the planetary gear 218 is four revolutions per one revolution of the body of the planetary gear 218 rotating inside the inner gear 217, that is, every 90 ° of the body of the planetary gear. 4 cycles of angular movements each round trip.

12A to 12D, the stroke change of the engine combustion chamber according to the number of poles of the turbine is illustrated. The intake, compression, explosion, and exhaust of fuel, along with cooling air intake and exhaust, are applied to the turbine inside the combustion chamber. By cooling the heat directly, the durability of the engine can be improved.

13A to 13C, in the case of a four-pole turbine, the combustion chamber turbine completes 90 ° for fuel intake and compression, 90 ° for explosion and exhaust, 90 ° for cooling intake and exhaust, and 270 ° for one cycle. Switch the turbine to the other two turbines.

The stroke is also simultaneously carried out on two turbines in symmetrical positions, which in turn generate a balanced and powerful torque by simultaneously applying rotational forces on both sides of the axis of rotation.

Furthermore, since there is a cold air intake and an exhaust stroke for cooling the turbine inner wall after the explosion and the exhaust stroke, it is possible to directly cool the temperature inside the combustion chamber and make the heat of cooling available from the outside, thereby enabling the design of a true air-cooled internal combustion engine.

Tables 1 to 3 summarize the operating states of the steps shown in Figs. 13A to 13C as tables.

Referring to Tables 1 to 3 and FIG. 14, the power turbine 150a and the control turbine 150b rotate at essentially the same speed, and only every 90 ° of the control turbine 150b angles the power turbine 150a. It changes within the range of stroke control with respect to the angle of, and the suction, compression, explosion, exhaust, cooling and discharge proceeds so that the energy supplied by the electric part 300 is necessary for the suction, compression, and exhaust of air except for the explosion moment. Since only energy is required, phase synchronization can be realized with very little energy close to no-load rotation. In addition, during deceleration and stop, it is possible to adjust the deceleration amount by stopping fuel intake and changing the amount of charge current converted according to inertia energy without a separate switching device.

The configuration of the valve illustrated in FIGS. 13A to 13C is designed to include reverse rotation, and the present invention enables stable reverse rotation by adding only a few valves as compared to using a separate gear device for reverse rotation when using an existing engine. do.

Therefore, the present invention is very easy to convert to large and small engines and is suitable for realizing high precision by changing the number of poles of the turbine and the position and number of valves according to the design size and the use. Since it can be made easy, it can be applied to various uses, such as a car and a ship.

14 to 20, an internal combustion engine using a double turbine according to another embodiment of the present invention includes a turbine unit 150, a turbine phase control unit 200, and a transmission unit 300.

The turbine unit 150 is mounted in the combustion chamber 100 such that the power turbine 150a and the control turbine 150b are engaged with each other. In addition, a ignition plug 140, an intake valve 450, or an exhaust valve (not shown) may be installed around the combustion chamber 100. Here, reference numeral 420 denotes a suction nozzle.

Referring to FIG. 15, the turbine unit 150 is connected to the power turbine 150a having the power shaft 110, the turbine phase control unit 200, and the connecting shaft 152 to be synchronized with the power turbine 150a. 150b. Specifically, a plurality of guide protrusions 160 are formed on the front surface of the power turbine 150a. The guide protrusion 160 functions as a kind of air cooling impeller that cools the internal temperature by exhausting the internal air to the outside during the rotation of the turbine. The guide protrusion 160 may be applied to the control turbine 150b.

Referring to FIG. 16, the power turbine 150a may be integrally formed with the turbine blades 151a. Preferably, it may be composed of four (four cycles). Meanwhile, the control turbine 150b may be coupled to each other by the turbine blades 151b made of separate members, and may be inserted into and coupled to the connection groove 156c formed in the body of the control turbine 150b. In addition, the turbine blades 151a and 151b may be formed with guide grooves 170 (paired as 170a and 170b) to facilitate the introduction of fuel (mixed gas) supplied to the combustion chamber 100. Can be. In the turbine unit 150 having such a configuration, as shown in FIG. 14, the power shaft 110 and the connection shaft 152 are mounted in the combustion chamber 100 so as to be freely rotated by the bearings 112a and 112b, respectively. In addition, although not shown, the power shaft 110 and the connecting shaft 152 may be equipped with a phase detection sensor to detect the phase of each turbine through the phase detection sensor and phase control through the turbine phase control unit 200. Done.

Referring to FIG. 17, the combustion chamber 100 has a plurality of through holes h1 and h2 formed on an outer circumferential surface thereof, and the intake valves 450 and the exhaust valves (not shown) are respectively formed in the through holes h1 and h2. Can be mounted. In addition, the turbine unit 150 may be positioned and rotated in the internal space h3. As such, the turbine unit 150 is rotated in the combustion chamber 100, and thus, a stroke may be performed as in the above-described embodiment.

Referring to FIG. 18, the turbine phase controller 200 includes a driving shaft 450, a first casing 410, a second casing 420, a deceleration unit 440, and a motor connecting shaft 460. In this configuration, the phase of the power turbine 150a is detected, and the control turbine 150b is driven and controlled along the power turbine 150a. In detail, the turbine phase controller 200 may include a bushing 430 in front of the driving shaft 450. In addition, a plurality of rotating plates 455 may be mounted between the first casing 410 and the second casing 420.

Referring to FIG. 19, the turbine phase control unit 200 is formed by coupling the first casing 410, the second casing 420, and the connecting plate 480 to each other. Meanwhile, a plurality of grooves 411 are formed in the first casing 410, and mounting grooves 425 and protrusions 421 are formed in the second casing 420 to form the first casing 410 and the second casing ( The 420 may be fastened to each other, and the rotating plate 455 may be installed in the mounting groove 425 therein.

Referring to FIG. 20, the drive shaft 450 is engaged with the clutch member 451, which is connected to the clutch bar 410 in FIG. 14. Accordingly, by pushing or pulling the clutch bar 410 back and forth, the clutch member 451 may be inserted into or removed from the through hole of the driving plate 452 and the connection member 453. This is provided to selectively transmit or short the rotational force of the drive unit 300 to the drive shaft 450. Accordingly, in some cases, a clutch connection or a short circuit may be performed to drive the control turbine 152 of the turbine phase control unit 200 (by a simple operation of moving the clutch bar forward and backward). Meanwhile, the reduction unit 440 is positioned at the center of the inner gear 457 with the heavy gear 458 connected to the connecting shaft member 460a. In addition, the heavy gear 458 is geared to the internal gear 457 via a plurality of external gears (456). Accordingly, it is possible to reduce the driving force according to the gear ratio. In addition, the connecting shaft member 460a is coupled to the motor connecting shaft 460 to transmit the driving force of the driving unit 300.

On the other hand, the plurality of outer gear 456 is inserted into the connecting shaft 455b of the rotary plate 455, respectively. In addition, each of the connecting grooves 455a is formed in the rotating plate 455. The connecting groove 455a is equipped with a connecting protrusion 454a of the connecting arm 454, and is coupled to the through hole 453a of the connecting member 453, so that the rotational force transmitted from the driving unit 300 is reduced to the reducing unit 440. By driving the plurality of rotating plates 455 in a decelerated state), the reduced rotational force may be transmitted to the driving plate 452 to rotate the driving shaft 450. Through the deceleration unit 440, it is possible to prevent the control turbine 150b from being pushed in the reverse direction during the explosion stroke of the turbine unit 150. That is, by installing the deceleration unit 440 that decelerates through the gear ratio inside the turbine phase control unit 200, driving control of the control turbine 150b is possible, and at the same time, the support surface during the explosion stroke of the turbine unit 150 ( The inner surface of the wing of the control turbine) can be pushed back and the control turbine 150b can be reversed, or the power turbine 150a can not be pushed out efficiently because it does not properly support the explosive force.

While the present invention has been particularly shown and described with reference to the particular embodiments thereof, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention.

100: combustion chamber 110: power shaft
111: front 112: rear
112a: bearing 112b: bearing
113: turbine blade 120: phase detection unit
121: front 122: thick plate
122a: bearing 123: disc
122b: bearing 130: cooling water groove
140: spark plug 141: inlet
142: exhaust port 150: turbine portion
151: turbine blade 152: connecting shaft
200: turbine phase control unit 210: cycle operation canceling unit
212: phase detection groove 213: disk cancer
214: period control arm 215: control angle transfer table
216: planetary gears 216a, 216b: cyclic motion canceller
217: internal gear 219: cycle gear
222: cycle controller 300: electric drive
300a: front cover 300b: rear cover
310: coolant groove 311: stator
320: stator winding 330: rotating shaft
340: phase detection unit 350: casing

Claims (1)

An internal combustion engine that generates an output by the rotational motion of a turbine,
A combustion chamber in which a power turbine for transmitting power and a control turbine synchronized with the power turbine are installed in engagement with each other so that fuel is introduced into the space between the turbines to burn and explode to generate output to the power turbine;
A turbine phase controller which detects phases of the power turbine and the control turbine and controls phases of the control turbine; And
An internal combustion engine using a double turbine, characterized in that it comprises an electric motor for transmitting power to the turbine phase control unit.

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