WO2018155902A1

WO2018155902A1 - Dual-turbine internal combustion engine comprising phase controller included in turbine assembly

Info

Publication number: WO2018155902A1
Application number: PCT/KR2018/002131
Authority: WO
Inventors: 최영희
Original assignee: 최영희
Priority date: 2017-02-23
Filing date: 2018-02-21
Publication date: 2018-08-30
Also published as: KR20180097397A

Abstract

The present invention relates to a dual-turbine internal combustion engine comprising a power turbine part and a control turbine part disposed in a body part such that turbine blades thereof are meshed with each other, wherein power is generated by triggering an explosion of fuel in the space between the turbine blades. The dual-turbine internal combustion engine further comprises a phase controller connected to the power turbine part so as to receive a rotation of the power turbine part and convert the same into a rotation of the control turbine part, wherein the phase controller is disposed within the power turbine part and the power turbine part.

Description

Dual Turbine Internal Combustion Engine with Phase Controller in Turbine Assembly

The present invention relates to an internal combustion engine, and more particularly, to a double turbine internal combustion engine configured with a phase controller in a turbine assembly.

In general, an internal combustion engine refers to an engine that converts thermal energy of a fuel into mechanical power by burning a fuel and directly applying the combustion gas to a piston or a turbine blade. In particular, a conventional internal combustion engine often refers to a reciprocating engine, but in addition, a gas turbine, a jet engine, a rocket, and the like are a kind of internal combustion engine.

On the other hand, in the related art, a rotary internal combustion engine (also known as a rotary engine) is disclosed as a rotary internal combustion engine in which a piston rotates. This rotary internal combustion engine is an internal combustion engine that realizes strokes of suction, compression, explosion, and exhaust using a triangular rotor that rotates eccentrically in an elliptical engine room, and has an advantage of generating high output even with a small displacement. However, the fuel efficiency is reduced, and the rotor and the center of gravity of the rotor rotates in an eccentric state, so the engine compartment and the rotor must be precisely designed, and the durability of the engine is further deteriorated.

Recently, a vane rotary internal combustion engine using a vane pump is also disclosed. This vane rotary internal combustion engine is provided with the principle of connecting two sets of vane vanes to separate rotary gears and operating the vane vanes by varying the rotation angle of the vane vanes.

The conventional vane type internal combustion engine is configured to generate power through the combustion space formed by controlling the rotation angle of each vane blade by interlocking the connecting shaft and the gear part of the control unit, which is less durable than the conventional internal combustion engine, and the weight of the controller It is difficult to keep the center at the center of rotation, and there is a problem involving vibration.

1. Republic of Korea Patent Publication No. 2016-0129780 (2016.11.09)

2. Republic of Korea Patent Publication No. 2012-0092075 (2012.08.20)

The present invention was devised to solve the above problems, and provides a dual turbine internal combustion engine configured with a phase controller in a turbine assembly capable of reducing vibration while improving durability and miniaturization and weight reduction.

According to one embodiment of the present invention for achieving the above object, the power turbine unit and the control turbine unit is disposed so that the mutual turbine blades mesh with each other inside the main body portion, the fuel explosion in the space between the turbine blades A dual turbine internal combustion engine for generating power by means of: a phase controller connected to the power turbine unit and receiving a rotation of the power turbine unit to convert the rotation into the rotation of the control turbine unit, wherein the phase controller includes the power turbine unit. And a dual turbine internal combustion engine constituting a phase controller in a turbine assembly located inside the power turbine unit.

The phase controller may be arranged in a circumferential direction of the power turbine unit to control the phase angle of the control turbine unit.

The phase controller may include a planetary gear member disposed on an inner circumferential surface of the power turbine unit, a crank member connected to the planetary gear member to adjust the phase angle, and a link member connected to one end of the crank member and connected to a control turbine. It may be made, including.

Guide portions exposing a part of the planetary gear member are respectively formed on both side surfaces of the power turbine part, and cover parts having internal gears are formed on both sides of the main body part, and the planetary gear member is mounted on the internal gear of the cover part. Gears can be connected.

When the planetary gear member rotates in the circumferential direction of the power turbine portion, the phase angle of the control turbine portion is changed by turning the link member at a predetermined angle by a rotational center of rotation biased to one side generated while the crank member rotates. Can be controlled.

According to the present invention, by configuring a phase controller inside the turbine assembly, it is possible to reduce the size of the device and to reduce the number of parts to reduce the weight, and to match the center of gravity of all the rotors with the power shaft, there is a vibration reduction effect. In addition, the present invention does not need to separately configure the control device has an effect that can simplify the overall structure more.

1A is a perspective view of a dual turbine internal combustion engine constituting a phase controller in a turbine assembly according to an embodiment of the present invention;

Figure 1b is a state diagram showing the internal configuration by cutting a portion of the dual turbine internal combustion engine of Figure 1a,

2 is an exploded perspective view of FIG. 1A;

3 is a block diagram showing an internal configuration of a turbine assembly of a dual turbine internal combustion engine constituting a phase controller in the turbine assembly according to an embodiment of the present invention;

4 is an exploded perspective view of a turbine assembly of a dual turbine internal combustion engine constituting a phase controller in the turbine assembly according to an embodiment of the present invention;

5 is a partial configuration diagram showing a configuration of a phase controller of a turbine assembly of a dual turbine internal combustion engine in which a phase controller is configured in a turbine assembly according to an embodiment of the present invention;

6 is an operational state diagram of a turbine assembly of a dual turbine internal combustion engine constituting a phase controller in the turbine assembly according to an embodiment of the present invention;

7 is an operational state diagram of a turbine assembly of a dual turbine internal combustion engine constituting a phase controller in the turbine assembly according to an embodiment of the present invention;

8 is an internal configuration diagram of a turbine assembly of a dual turbine internal combustion engine in which a phase controller is configured in a turbine assembly according to another embodiment of the present invention; and

9 is a configuration diagram of a phase controller of a dual turbine internal combustion engine constituting a phase controller in a turbine assembly according to another embodiment of the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

Prior to this, terms or words used in the present specification and claims should not be construed as being limited to the ordinary or dictionary meanings, and the inventors should properly explain the concept of terms in order to best explain their own inventions. Based on the principle that it can be defined, it should be interpreted as meaning and concept corresponding to the technical idea of the present invention. In addition, unless there is another definition in the technical terms and scientific terms used, it has the meaning commonly understood by those of ordinary skill in the art to which this invention belongs, and the gist of the present invention in the following description and the accompanying drawings. Descriptions of well-known functions and configurations that may be unnecessarily blurred are omitted. The drawings introduced below are provided by way of example so that the spirit of the invention to those skilled in the art can fully convey. Accordingly, the present invention is not limited to the drawings presented below and may be embodied in other forms. Also, like reference numerals denote like elements throughout the specification. It should be noted that the same elements in the figures are represented by the same numerals wherever possible.

Hereinafter, a dual turbine internal combustion engine constituting a phase controller in a turbine assembly according to an embodiment of the present invention will be described. One embodiment of the present invention is a spark ignition type internal combustion engine, a turbine assembly having four turbine blades is fixed to both sides through internal gears, and constitutes a phase controller comprising three sets of planetary gears.

1A and 1B, an embodiment of the present invention includes a main body unit 100, a power turbine unit 10, and a control turbine unit 20.

In the above configuration, the main body 100 has a fuel injection port 170, an intake port 110, a low pressure exhaust port 120, a high pressure exhaust port 130, and a spark plug mounting port 140 through the outer peripheral surface.

In the above configuration, the front cover portion 150 and the rear cover portion 160 are mounted to the front and rear of the body portion 100, respectively. At this time, the phase detection port 151 is formed outside the front cover part 150. This phase detection port 151 is provided for detecting the rotation angle of the phase angle detection plate 155 mounted on the power shaft tip 11a.

In the above-described configuration, the power turbine unit 10 and the control turbine unit 20 are interlocked with each other to form the turbine assembly 200. The power shaft front end 11a and the power shaft rear end 11b are extended to both sides of the turbine assembly 200, respectively, and the power shaft front end 11a and the power shaft rear end 11b are the front cover part 150 and the rear cover. It is exposed to the outside of the unit 160. On the other hand, in the embodiment of the present invention, each component is rotated, the bearing mounting groove is formed to be coupled through the bearing, but the illustration of the bearing is omitted for simplicity of illustration.

Referring to FIG. 2, the front cover plate 157 is mounted in front of the front cover part 150, and the internal gear 156 is formed inside the front cover part 150. Similarly, the rear cover plate 157 'is mounted on the rear cover part 150', and the internal gear 156 'is also formed inside the rear cover part 150'. In addition, in the turbine assembly 20, the power turbine blade 12a of the power turbine unit 10 and the control turbine blade 22a of the control turbine unit 20 are engaged with each other to form a combustion chamber P in the space therebetween. In addition, the front and rear of the turbine assembly 200, guides 10a are respectively formed for guiding rotation of the internal phase controller 30 (see FIG. 4).

A configuration of the phase controller 30 will be described in detail with reference to FIGS. 3 to 5. In the present invention, the phase controller 30 is located inside the turbine assembly 200. First, the power turbine cover plate 10c is fastened to the power turbine unit 10, and the control turbine unit 20 is fitted with the

turbine blades

12a and 22a facing each other inside the power turbine unit 10. Installed in a state.

At this time, the power shaft front end 11a is formed in front of the power turbine part 10, and the other power shaft 11b is formed below the power turbine cover plate 10c. In addition, the power turbine cover plate 10c is provided with a protrusion 15a for fitting along the inner surface, and three guide holes 15b are formed on the outer periphery of the center hole, respectively.

On the other hand, in the control turbine part 20, the control turbine blade | wing 22a of four poles is formed in the outer peripheral surface of the turbine body 10b, respectively. Moreover, the control turbine rotating shaft P4 is formed in the center. Further, first mounting holes h1 are formed around the control turbine rotary shaft P4, respectively. And the control turbine cover plate 25 is attached to the control turbine body 10b. At this time, the control turbine cover plate 25 has a central hole (ho) in the center, the second mounting hole (h2) is formed around the central hole (ho), respectively. Meanwhile, the phase controller 30 may be positioned between the turbine body 10b and the control turbine cover plate 25 to be rotated.

As such, the power turbine portion 10 and the control turbine portion 20 are located on the same centerline of the same structure but are disconnected from each other, so that the control turbine portion 20 when the power turbine portion 10 rotates at a given angular velocity. May rotate while changing the relative angle with the power turbine unit 10 in a certain range.

Meanwhile, referring to FIG. 3, the planetary gear members 31 constituting the phase controller 10 are guided by being seated in guide grooves 25a provided in the guide parts 10a respectively formed in front and rear of the power turbine part 10. Can be rotated. In this case, a part of the guide groove 25a is configured to be open, and a part of the planetary gear member 31 may be exposed to the outside.

4 and 5, the phase controller 30 includes a planetary gear member 31 moving along the internal gears 156 and 156 ', a crank member 32 and a crank member connected to the planetary gear member 31. The link member 33 connected to 32 is constituted by one individual connecting body, and the individual connecting body has a structure in which three are arranged in the circumferential direction between the control turbine cover plate 25 and the turbine body 10b, respectively.

Specifically, the phase controller 10 is composed of a planetary gear member 31, a crank member 32, and a link member 33, the center of the planetary gear member 31 and the crank member 32 through a bearing The other side of the link member 33, which is supported on the inner wall of the power turbine unit 10 and transmits the control angle, is coupled to the coupling groove formed in the center of the control turbine unit 20 through a bearing. As a result, the power turbine unit 10 serves as a support of the phase controller 30, and the center wall of the control turbine unit 20 serves as a transmission table receiving the control angle.

Meanwhile, the planetary gear member 31 rotates gears by engaging the gears 156 and 156 'of the front and

rear cover parts

150 and 160 by exposing the gears to the outer surface (guide part 10a) of the central portion of the power turbine part 10. The crank member 32 is connected to the shaft of the planetary gear member 31.

Referring to the operation of the phase control unit 30 having such a configuration, when the power turbine unit 10 rotates, a plurality of planetary gear members 31 connected to the shaft in the circumferential direction is circumferentially along the internal gear 156,156 '. Direction of rotation. That is, the planetary gear member 31 is rotated in the circumferential direction about the power shaft. At this time, the crank member 32 fixed to the central axis of the planetary gear member 31 is rotated to form a control angle for changing the angular velocity with respect to the power turbine unit 10, through the link member 330 the control turbine unit By connecting to the transmission 20, the relative angle with respect to the power turbine unit 10 is changed.

6 and 7, the operating state of the dual turbine internal combustion engine constituting the phase controller in the turbine assembly of the present invention will be described.

First, the planetary gear members 31 and 31 'having the central axis fixed to the inner wall of the power turbine unit 10 travel in mesh with the gears of the internal gears 156 and 156' in the rotational direction of the power turbine unit 10. The rotational direction of the gear members 31 and 31 'is opposite to the rotational direction of the power turbine unit 10. At this time, the crank member 32 connected to the planetary gear members 31 and 31' has a first pivot point P1. Rotate around. That is, the first pivot point P1 is circumferentially moved along the internal gears 156 and 156 'while the planetary gear members 31 and 31' are rotated.

Meanwhile, the crank member 32 rotates based on the link member 33 and the second pivot point P2. As a result, the second turning point P2 rotates around the first turning point P1 (a2 → d2 in FIG. 6). In this state, the crank member 32 and the link member 33 move while rotating along the gear teeth of the internal gears 156 and 156 'based on the second pivot point P2. At the same time, the end of the link member 33 pivots between the control turbine portion 20 and the control turbine cover plate 25 with respect to the third turning point P3. At this time, the third turning point P3 is fitted into the first mounting hole h1 of the turbine body 10b and the second mounting hole h2 of the control turbine cover plate 25, respectively.

As such, the first pivot point P1 is rotated while moving in the circumferential direction along the internal gears 156 and 156 ', and the third pivot point P3 is changed in angle according to the rotation of the second pivot point P2. Linear movement. At this time, when the linear movement direction of the third turning point P3 is the same as the rotational direction of the power turbine unit 20, it operates in a direction of narrowing the spacing of the turbine, and in the opposite direction, it operates in a direction of widening the spacing of the turbine.

That is, the power turbine unit 10 is rotated at a constant angular speed according to the rotational speed, while the control turbine unit 20 is rotated to follow the rotation while changing to a given angular range at a predetermined period by the phase controller. In the present embodiment, the repetition period is 90 degrees, and the change angle is 45 degrees.

In this way, the control turbine unit 20 follows the power turbine unit 10 so that the combustion chamber formed between the turbine units executes the suction stroke (a1 in FIG. 6; aa in FIG. 7) when the interval is widened, and narrows. When losing, the compression stroke (b1 in FIG. 6; b in FIG. 7) is executed.

In addition, the power turbine unit 10 of the combustion chamber in the explosion state after the compression of the turbine assembly 200 receives the explosion energy in the rotational direction, the control turbine unit 20 receives the explosion energy in the opposite direction, which acts The explosive force in the opposite direction is also transmitted to the planetary gear member 31 through the connection structure of the crank member 32 and the link member 33 and in the rotational direction of the power turbine unit 10 with the action of the internal gears 156 and 156 '. Is converted and transmitted to the power shaft. Accordingly, the explosion energy generated in the

turbine blades

22a and 12a on both sides is transmitted to the power shaft, thereby further improving the output efficiency.

In addition, as shown in FIG. 1B, a phase angle detection plate 155 may be provided to detect a rotational position of the power turbine unit 10. For example, the reference member may be coupled to an outer center of the power turbine unit 10. And a detection member (not shown) can detect the rotational position of the reference member and send the rotational phase of the turbine to the controller. Here, the phase detection unit may be applied to, for example, a photo sensor, a magnetic sensor, etc. as a detection means, and may also be applied to a mechanical device such as a cam mechanism.

Hereinafter, the angle change of the control turbine part 20 according to the rotation angle of the power turbine part 10 is demonstrated. For example, when the power turbine unit 10 rotates counterclockwise, the power turbine unit 10 is fixed to the power output shaft, rotates at a constant angular speed according to the rotational speed, and the control turbine unit 20 is in phase. The controller 30 follows while changing the relative angle with respect to the power turbine unit 10. At this time, a space is formed between the turbine blades due to the angle difference between the power turbine section 10 and the control turbine section, and the four strokes of the suction compression explosion exhaust are realized by the change of the space (combustion chamber; P, see FIG. 2).

6 and 7, the power turbine unit 10 rotates counterclockwise to reach 45 degrees, but the control turbine unit 20 moves linearly in the reverse direction by the operation of the phase controller 30. As a result of overlapping with the moving direction of the power turbine section 10, the change of angle is hardly seen during this time. Air is sucked into the combustion chamber P from the inlet port 110, and fuel mixed with the fuel injection port 170 is sucked into the combustion chamber (suction stroke; a1 in FIG. 6 and a in FIG. 7). As described above, the space of the combustion chamber P is formed by controlling the rotation of the control turbine unit 30 by the phase controller 30 so as to follow the rotating power turbine unit 10 and the relative angle thereof.

Subsequently, as the linear movement direction of the phase controller 30 is in a forward direction while the mixed gas is sucked, the control turbine unit 20 moves toward the ignition while narrowing the distance from the power turbine unit 10. The combustion chamber P between 12a and 22a is compressed (compression stroke; b1 in FIG. 6, b in FIG. 7).

Subsequently, when the power turbine unit 10 and the control turbine unit 20 move 90 degrees from the suction position and reach the ignition hole (ignition plug mounting hole) 140 at this position, the two

turbine wings

12a and 22a are as close as possible. Combustion chamber (P) is in a compressed state, at which time the ignition is ignited through the ignition plug and the mixed gas of the combustion chamber (P) explodes (explosion stroke; c1 in FIG. 6, c in FIG. 7).

As described above, when an explosion occurs in the combustion chamber P, the explosion energy in the reverse direction also acts on the control turbine unit 20 linearly moving in the reverse direction. Accordingly, the turbine blades 12a of the power turbine unit 10 receive explosive force in the same direction as the rotational direction to receive energy directly, while the turbine blades 22a of the control turbine unit 20 have a rotational direction. The explosive force acts in the opposite direction, where the force in the reverse direction is transmitted to the planetary gear member 31 through the link member 33 and the crank member 32 of the phase controller 30 moving linearly in the reverse direction and the internal gear ( 156, 156 'and is converted into the forward rotational force of the power turbine unit 10. That is, even the repulsive force acting in the turbine during the explosion acts as a forward rotational force to the power shaft can improve the energy transfer efficiency.

Subsequently, after the explosion stroke, the power turbine unit continues to rotate counterclockwise, and when the

exhaust ports

120 and 130 reach the exhaust ports, the explosive gas is discharged through the

exhaust ports

120 and 130, and exhausted through the high pressure exhaust port 130 and the low pressure exhaust port 120. After that, the angle of the control turbine unit 20 is narrowed to completely discharge the remaining explosive gas (exhaust stroke; d1 in FIG. 6 and d in FIG. 7).

As described above, the exhaust stroke is completed, and the power turbine unit 10 and the control turbine unit 20 rotate toward the intake port 110 again, and the four strokes of intake-> compression-> explosion-> exhaust are continued.

As described above, each of the

turbine blades

12a and 22a rotates, intakes and compresses in the section of the inlet port 110, and explodes and exhausts in the section of the spark plug mounting hole 140, and mixes the mixed gas. The explosive section is different, and when one turbine blade is compressed by suction, the other turbine blade realizes explosion and exhaust.

The present invention configured as described above can reduce the energy conversion loss because the turbine assembly 200 and the phase control unit 30 are all coaxially rotated. In addition, the center of gravity of all components is coaxial with the power shaft and rotates at the same speed. Accordingly, noise and vibration can be minimized during driving, and all the planetary gear members 31 forming the phase control unit operate in the same phase, thereby distributing and transmitting explosion energy in the turbine, thereby increasing durability of the driving body. .

In addition, according to the present invention, the phase controller 30 is formed by forming the rotational support points of all components of the phase controller 30 on the inner wall or the outer wall of the power turbine unit 10, thereby simplifying the structure by eliminating a separate phase control room. It is possible to improve the manufacturing efficiency, and also to reduce the weight and size of the device.

In addition, the present invention is to generate a power by directly converting the explosion energy of the fuel to the rotational movement of the turbine portion, it is possible to generate a high output with a small displacement. Since all the drive bodies are formed in a circular shape around the output shaft, high manufacturing precision can be realized. Moreover, according to the design of the turbine, simultaneous explosion can be realized in a plurality of combustion chambers P at the same time, so that a power-to-weight ratio can be realized. In addition, as the turbine unit rotates, a separate intake valve unit and an exhaust valve are not required, thereby simplifying the structure and improving durability and maintenance performance.

In addition, although the internal combustion engine of a spark ignition system was demonstrated in this embodiment, when a fuel injector is mounted in the position of a spark plug, and a high pressure fuel pump is applied, it can also be realized as a compression ignition internal combustion engine. Therefore, the present invention can be applied to both a spark ignition system using gasoline or the like and a compression ignition type internal combustion engine using diesel or the like as a fuel.

On the other hand, according to the characteristics of the internal combustion engine as shown in Figs. 8 and 9, the fixed gear can be employed as the outer gear 156, 156 'instead of the inner gear, and the number of poles of the turbine blades can also be variously configured to require more than one rotational speed. Various designs can be selected according to the maximum power required.

Although the present invention has been illustrated and described with respect to specific embodiments thereof, the present invention is not limited to the above-described embodiments, and a person skilled in the art to which the present invention pertains has the present invention described in the following claims. Various changes may be made without departing from the spirit of the technical idea of the invention.

Claims

A turbine assembly comprising a power turbine portion and a control turbine portion is configured to interlock turbine blades with each other within a body portion, and generates a power by causing an explosion of fuel in a space between the turbine blades.

A phase controller connected to the power turbine unit to receive the rotation of the power turbine unit and convert the rotation into the rotation of the control turbine unit;

Wherein said phase controller is located inside said turbine assembly.
The method of claim 1,

The phase controller,

The plurality of turbine internal combustion engine, characterized in that arranged in the circumferential direction of the power turbine portion to control the phase angle of the control turbine portion.
The method of claim 2,

The phase controller,

A planetary gear member disposed on an inner circumferential surface of the power turbine portion,

A crank member connected to the planetary gear member to adjust the phase angle;

And a link member having one end connected to the crank member and the other end connected to the control turbine unit.
The method of claim 3,

At least one side of the power turbine portion is formed with a guide portion exposed part of the planetary gear member,

At least one side of the main body portion is equipped with a cover portion formed with an internal gear,

And the planetary gear member is gear-connected to the internal gear of the cover part.
The method of claim 4, wherein

When the planetary gear member rotates along the circumferential direction of the power turbine portion,

And rotating the link member at a predetermined angle by moving the center of rotation eccentrically to one side generated while the crank member rotates to control the phase angle of the control turbine section.