WO2003056156A1

WO2003056156A1 - Coaxial rotary engine

Info

Publication number: WO2003056156A1
Application number: PCT/JP2001/011478
Authority: WO
Inventors: Yukio Kajino
Original assignee: Yukio Kajino
Priority date: 2001-12-26
Filing date: 2001-12-26
Publication date: 2003-07-10
Also published as: AU2002225366A1

Abstract

A rotary output shaft is born at an eccentric position of a casing arranged with a pair of chambers coaxially. A pair of rotors are fixed, at the center thereof, to the output shaft and arranged eccentrically in respective chambers such that the rotors rotate while sliding, at a part of the circumferential surface thereof, on the inner circumferential surface of the chamber. A shield plate is fitted slidably in the radial direction of the shaft of each rotor and urged resiliently such that the forward end thereof abuts against the inner circumferential wall of the chamber. One chamber has a fuel suction port communicating with a void on one side in the rear of the rotor sliding part, and a compressed gas delivery port communicating with a void on the other side in front of the rotor sliding part. The other chamber has an explosion gas jet port opened to a microgap in the vicinity of the rear end at the rotor sliding part, and a combustion gas exhaust port communicating with a void in front of the rotor sliding part. The compressed gas delivery port and the explosion gas jet port are allowed to communicate through a compressed gas accumulation passage provided with an ignition chamber. Phase angle of the pair of rotors is set such that the shield plate of the other rotor is located in front of the microgap of the explosion gas jet port when the shield plate of one rotor compresses fuel gas at a desired compression ratio.

Description

Description Coaxial rotating engine

Technical field

The present invention relates to a coaxial rotary engine that is lightweight and small, can obtain a relatively large output, and is easy to manufacture.

Background art

Conventional reciprocating engines are relatively large because they use cylinders of a predetermined stroke. Also, since the engine makes one cycle with two reciprocations of the cylinder, there is a problem in output efficiency, and the fuel cost is relatively high.

A rotating disk having a concave and convex curved surface and a non-rotating receiving disk are arranged coaxially in engine casing with the concave and convex curved surfaces facing each other, and fuel is supplied to a pair of variable volume chambers between the concave and convex curved surfaces generated by rotation of the rotating disk. A rotating engine adapted to intake, compress, expand and exhaust has been developed by the present inventor and disclosed in Japanese Patent Application Laid-Open No. H10-2005-344. There are also US Pat. No. 5,836,286 and US Pat. No. 6,326,36 corresponding to the Japanese patent publication.

In the above-described known rotary engine, contraction and exhaust are simultaneously performed by a pair of chambers and expansion and intake are performed simultaneously with the rotation of the rotating disk, but the variable volume chamber is only one stage in the rotation direction. Because the structure was not formed, the power was insufficient when sustaining the energy of expansion (explosion) to the force of the next contraction, and rotation could become unstable.

Also, in the above-mentioned rotary engine, it is necessary to form the confronting surface of the rotating disk and the fixed disk into an uneven curved surface that slides smoothly while maintaining airtightness. Because of the need for technology, there were also issues such as product yield and cost.

Therefore, it is an object of the present invention to provide a light-weight, small-sized, relatively large output, and An object of the present invention is to provide a coaxial rotating engine that is easy to operate. Disclosure of the invention

In order to achieve the above object, a coaxial rotary engine of the present invention comprises: a casing in which a pair of chambers having a circular or elliptical inner peripheral wall of a predetermined width are coaxially arranged via a partition; A rotary output shaft supported in the direction of the casing axis by contributing to the eccentric position of the rotary shaft; and the chamber is also formed of a small-diameter disk. A pair of rotors eccentrically arranged in each chamber so that the parts always rotate while being in airtight sliding contact with the inner peripheral wall of the chamber; and reciprocally slidingly fitted in radial grooves formed in the radial direction of the shaft of each rotor. A shielding plate resiliently biased so that its tip always contacts the inner peripheral wall of the chamber; a fuel gas inlet port communicated with a space on one side behind the rotor sliding portion of the one chamber; Connected to the vacant space on the other side just before the sliding contact part A compressed gas discharge port; and an explosive gas injection port opened in a minute gap near the rear end of the other chamber's sliding contact portion; and combustion connected to a space in front of the sliding contact portion. A gas exhaust port; a compressed gas reservoir passage communicating from the compressed gas discharge port of the one chamber via a check valve to an explosive gas injection port of the other chamber; and the check valve of the compressed gas reservoir passage. And an ignition chamber provided on the downstream side, wherein the phase angle of the pair of rotors is changed, and when the shield plate of one rotor compresses the fuel gas to a desired compression ratio, the shield plate of the other rotor is provided. Is set near the front of the small gap of the explosive gas injection port.

The shield plate of each of the rotors may be provided at one location in the radial direction, whereby one rotation of the rotor may be used as a one-cycle engine. A pair or a plurality of pairs of symmetrically arranged shielding plates are provided, whereby the engine performs a plurality of two-cycle operations with one rotation of the rotor. BRIEF DESCRIPTION OF THE FIGURES

FIG. 1 is a side view showing a schematic configuration of a coaxial rotary engine according to an embodiment of the present invention. FIG. 2 is a diametrical longitudinal sectional view of each chamber when the shielding plate is rotated to the sliding contact portion.

FIG. 3 is a cross-sectional development view of each chamber in FIG.

The fourth country is a diagram corresponding to the second country of another embodiment.

FIG. 5 is a diagram corresponding to FIG. 3 of another embodiment. BEST MODE FOR CARRYING OUT THE INVENTION

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

As shown in FIGS. 1 to 3, a casing 2 of a coaxial rotary engine 1 according to the present invention includes a pair of chambers 4 and 5 partitioned by a partition wall 3 and having a circular or elliptical inner peripheral wall having a predetermined width. (Hereinafter, referred to as a first chamber 4 and a second chamber 5). A rotary output shaft 6 is rotatably arranged in the axial direction of the casing 2 so as to pass through an eccentric position.

In the first and second chambers 4 and 5, rotors 7 and 8 made of disks smaller in diameter than the chambers 4 and 5 are installed so as to be coaxially and integrally rotatable with the center fixed to the rotary output shaft 6. .

In addition, the first and second α-motors 7 and 8 rotate partly in a circular manner in contact with the inner peripheral wall surface of each of the chambers 4 and 5 while rotating a part of the circular outer peripheral surface. The space 9 is provided so as to form a space 9 between the inner peripheral wall surfaces of the chamber.

The first and second rotors 7, 8 are formed with a radial groove 10 extending from the outside toward the center along the axial direction, and are urged outward by a spring 11 in the groove 10. The shielding plate 12 is slidably fitted.

With this configuration, each shielding plate 12 is urged toward the inner peripheral wall of the chamber by the spring 11, and the tip thereof is integrated with each of the rotors 7 and 8 while sliding in airtight contact with the inner peripheral walls of the corresponding chambers 4 and 5. The inside of the chambers 4 and 5 is rotated.

The first chamber 4 has a fuel gas inlet 14 communicating with one side of the chamber space 9 near the rear of the sliding contact portion 13 with the rotor 7. A compressed gas discharge port 15 communicating with the other side of the chamber 9 is formed near this side.

In the embodiment shown in the figure, the rotors 7 and 8 are set clockwise. In the drawing, a suction port 14 communicating with the cavity 9 of the chamber is provided near the right side of the sliding contact portion 13, and the sliding contact portion 13 is provided. A compressed gas discharge port 15 communicating with the cavity 9 of the chamber is provided near the left side of the chamber.

Therefore, in the first chamber 4 of the casing 2, the tip of the shielding plate 12 is brought into airtight contact with the inner peripheral wall of the first chamber 4 by the rotation of the first rotor 7, and the fuel gas is turned off. The suction step and the compression step proceed simultaneously.

On the other hand, the second chamber 5 has an explosion gas injection port 16 opened in a minute gap at the rear end of the sliding contact portion 13 with the rotor 8, and the chamber vacant near the sliding contact portion 13. A combustion gas exhaust port 17 communicating with the place 9 is formed. That is, in the drawing, the explosive gas injection port 16 is opened in a minute gap on the right side of the sliding contact portion 13 with the second rotor 8, and communicates with the chamber 9 in the vicinity of the left side of the sliding contact portion 13. Combustion gas exhaust port 17 is provided.

For this reason, in the second chamber 5 of the casing 2, the rotation of the second rotor 8 causes the tip of the shielding plate 12 to come into contact with the inner peripheral wall of the second chamber 5 in an airtight manner and to rotate, so that the fuel gas Expansion stroke (explosion) and exhaust stroke progress simultaneously.

The compressed gas discharge port of the first chamber 4 and the explosive gas injection port 16 of the second chamber 5 are air-tightly communicated with each other through a compressed gas reservoir passage 18.

A check valve 19 is provided in the vicinity of the explosive gas injection port 16 of the compressed gas reservoir passage 18, and a plug 21 faces the ignition chamber 20 downstream of the check valve 19. The plug 21 is ignited at the moment when the shielding plate 12 of the second rotor 8 passes through the minute gap at the rear end of the sliding portion 13.

As shown in FIG. 3, the phase angle between the first rotor 7 and the second rotor 8 is determined when the shielding plate 12 of the first rotor 7 is at a position where the fuel gas is compressed to a desired compression ratio. In this embodiment, when located near the fuel gas inlet 14, the shielding plate 12 of the second rotor 8 is located slightly forward of the minute gap of the explosive gas injection port 16, The explosion (expansion) of the fuel gas compressed to a desired compression ratio causes the shielding plate of the second rotor 8 to expand. Set 1 2 to receive maximum explosion pressure.

The explosive gas injection port 16 of the second chamber 5 opposes the small gap at the rear end of the sliding contact portion 13 with the second rotor 8, and the passage is restricted, so that the rotor 7 of the first chamber 4 is shielded. The fuel gas compressed by the plate 12 is pushed into the compressed gas reservoir passage 18 and compressed. In this way, when the fuel gas is compressed, the shield plate 12 of the second rotor 8 is located in front of the small gap of the explosion gas injection port 16 and when the plug 21 is ignited, the explosion of the compressed fuel gas causes The second rotor 8 rotates integrally with the first rotor 7 and the output shaft 6.

Thus, the coaxial rotary engine 1 of the present invention includes a first rotor 7 for simultaneously performing an intake stroke and a compression stroke, a second rotor 8 for simultaneously performing an explosion (expansion) stroke and an exhaust stroke, and a suction stroke. The first rotor 7 for simultaneously proceeding the compression stroke is fixed to the common rotation shaft 6 and rotates coaxially, and the compressed gas discharge port 15 and the explosive gas injection port 16 of the first chamber 4 store compressed gas. Since each of the rotors 7 and 8 is provided with one shielding plate 12 because of the communication through the passage 18, one rotation of the mouth 7 and 8 is performed in the embodiment of FIGS. 1 to 3. The four processes of suction, compression, explosion and exhaust are completed simultaneously. Moreover, since the compression of the fuel gas in the first chamber 4 is performed using the explosive power of the second chamber 5, a stable output is generated without stopping the engine due to the compression resistance. In this case, a part of the explosion energy is consumed for the compression of the fuel gas, but the explosion energy of the compression gas per unit is approximately 200 times the energy required for the compression. There is no obstacle.

FIG. 4 and FIG. 5 show another embodiment of the present invention.

In this embodiment, two grooves 10a and 10b are formed symmetrically in two radial directions of each rotor 7 and 8 opposite to each other, and a spring 11 is formed in each groove 10a and 10b. The energized shielding plates 12a and 12b are fitted so that they can slide back and forth.

In this embodiment, the plug 21 is ignited each time the pair of shield plates 12 a and 12 b of the rotor 8 of the second chamber 5 passes through the explosive gas injection port 16. . Therefore, in this embodiment, two explosions (expansion) occur each time the rotors 7 and 8 and the rotary output shaft 6 make one revolution, and two cycles of engine operation work every one revolution. become. In addition, since the pair of shield plates 12a and 12b are provided symmetrically on each of the rotors 7 and 8, the balance during operation is good.

The embodiment of FIGS. 4 to 5 illustrates a case where a pair of shield plates 12 a and 12 b are fitted in two opposite radial directions of the respective rotors 7 and 8. By providing a plurality of pairs or a plurality of shielding plates in the radial directions opposite to each other, the number of engine cycles during one rotation can be proportionally increased.

The embodiment shown in the figure illustrates a case where the coaxial rotary engine of the present invention is used as a gasoline engine, and the plug 21 is used in the ignition chamber 20 of the compressed gas reservoir passage 18. The coaxial rotating engine can be used as a diesel engine, in which case the plug can be omitted.

Further, although the embodiment of the figure illustrates a case where one set of the engines is mounted on a rotating shaft, the present invention provides a composite rotating engine in which the coaxial rotating engine is mounted on a common rotating shaft. It is also possible to increase the engine output. Industrial applicability

In the present invention, the engine cycle of suction, compression, explosion, and exhaust is completed simultaneously with one rotation of the rotor in a compact engine casing, so that a relatively large rotating force can be stabilized with a small and lightweight engine. Output, and the fuel ratio is greatly improved.

When a plurality of shield plates are symmetrically arranged on the rotor, a large output is obtained, and a well-balanced and stable operation is achieved.

As described above, the coaxial rotary engine of the present invention can be widely used as an efficient internal combustion engine.

Claims

The scope of the claims

1. A casing in which a pair of chambers having a circular or elliptical inner peripheral wall of a predetermined width are coaxially arranged via a partition wall;

A rotation output shaft that is supported in the casing axis direction by penetrating the eccentric position of the pair of chambers;

A pair of rotors, each of which has a disk smaller in diameter than the chamber, has its center fixed to the output shaft, and is eccentrically arranged in each chamber so that a part of the circumferential surface always rotates while hermetically sliding against the inner wall of the chamber. When ;

A shielding plate fitted in a radial groove formed in the radial direction of the shaft of each rotor so as to be reciprocally slidable, and elastically biased so that the front end side is always in contact with the inner peripheral wall of the chamber; The fuel gas inlet and the 5

A compressed gas discharge port that communicates with the other space in front of the rotor sliding portion;

An explosive gas outlet opening in a minute gap near the rear end of the other chamber's sliding contact portion;

An exhaust port communicating with a space in front of the rotor sliding portion;

A compressed gas reservoir passage communicating from the compressed gas discharge port of the one chamber to the explosive gas injection port of the other chamber via a check valve;

And an ignition chamber provided on the downstream side of the check valve in the compressed gas reservoir passage, when the phase angle of the pair of rotors is compressed by a shield plate of one of the rotors to a desired compression ratio. A coaxial rotary engine, wherein the shield plate of the other rotor is set near the front of the minute gap of the explosive gas injection port.

2. The coaxial rotary engine according to claim 1, wherein the shield plates of the rotors are arranged symmetrically in pairs in the radial direction of each rotor.

3. The coaxial rotary engine according to claim 1, wherein a plurality of sets of the coaxial rotary engines are mounted on a common rotary shaft.