CN117028021A - Dual-rotor engine - Google Patents

Dual-rotor engine Download PDF

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Publication number
CN117028021A
CN117028021A CN202311017459.8A CN202311017459A CN117028021A CN 117028021 A CN117028021 A CN 117028021A CN 202311017459 A CN202311017459 A CN 202311017459A CN 117028021 A CN117028021 A CN 117028021A
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CN
China
Prior art keywords
working
cylinder
compression
air
air inlet
Prior art date
Legal status (The legal status 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 status listed.)
Pending
Application number
CN202311017459.8A
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Chinese (zh)
Inventor
金建林
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Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to CN202311017459.8A priority Critical patent/CN117028021A/en
Publication of CN117028021A publication Critical patent/CN117028021A/en
Pending legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B55/00—Internal-combustion aspects of rotary pistons; Outer members for co-operation with rotary pistons
    • F02B55/02—Pistons
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00—Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • F02B53/04—Charge admission or combustion-gas discharge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00—Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • F02B53/04—Charge admission or combustion-gas discharge
    • F02B53/06—Valve control therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00—Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • F02B53/04—Charge admission or combustion-gas discharge
    • F02B53/08—Charging, e.g. by means of rotary-piston pump
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00—Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • F02B53/12—Ignition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B55/00—Internal-combustion aspects of rotary pistons; Outer members for co-operation with rotary pistons
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B55/00—Internal-combustion aspects of rotary pistons; Outer members for co-operation with rotary pistons
    • F02B55/08—Outer members for co-operation with rotary pistons; Casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B55/00—Internal-combustion aspects of rotary pistons; Outer members for co-operation with rotary pistons
    • F02B55/16—Admission or exhaust passages in pistons or outer members
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Abstract

The invention discloses a double-rotor engine, and relates to the technical field of engines. Air is sucked into the compression cylinder through the compression air inlet and compressed, the compressed air enters a pipeline which is communicated with the working cylinder at the side of the linkage shaft from the air outlet, after passing through an air inlet check valve of the pipeline, an oil nozzle is opened, fuel oil and compressed air are sprayed out to form mixed gas, a spark plug is started to ignite, the mixed gas is rapidly expanded, the expansion gas pushes the air inlet check valve to close the valve, pushes a rotor of the working cylinder to rotate for working and then is discharged from an air outlet, the air inlet check valve at the side is closed, a link rod is pushed to open the air inlet check valve of the other working cylinder for air inlet, the oil nozzle at the side sprays oil, the spark plug ignites, the mixed gas ignites for working, and the two working cylinders alternately do work, so that the engine is started. The invention improves the power, reduces the energy consumption, has compact structure, small volume, good air tightness, lower cost, high reliability and wide application prospect.

Description

Dual-rotor engine
Technical Field
The invention relates to the technical field of engines, in particular to a double-rotor engine.
Background
Engines of automobiles, helicopters and the like in the market at present usually adopt the ignition of compressed combustible mixed gas, the gas expansion pushes a piston to do repeated motion in a cylinder and then convert the repeated motion into axial motion, the inertia of the final starting point of the repeated motion is large, the additional work for counteracting the repeated motion is large, the useful work is relatively small, and the energy consumption is large. The rotor engine is changed into a rotor engine, although the defects are overcome, the rotor is eccentric, the initial moment is not in the axle center, the useful work is smaller, the energy consumption is larger, the friction between the rotor and the inner wall is larger, the service life of the engine is not long, in addition, the engine of the jet aeroplane has large volume, poor sealing performance, high energy consumption, harsh starting conditions, complex and numerous parts, very limited productivity and high cost. Based on this, it is particularly necessary to develop a dual rotor engine.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide the double-rotor engine which has reasonable structural design, small volume, high air tightness, lower cost and high reliability, greatly reduces energy consumption, improves power and is easy to popularize and use.
In order to achieve the above object, the present invention is realized by the following technical scheme: a dual-rotor engine is composed of compression cylinder, two working cylinders, belt pulley, one-way air inlet valves, oil nozzles and spark plugs, and features that the two synchronous gear-type rotors are linked to each other by said belt pulley and the air outlet of compression cylinder, each of which is linked to the working inlets of two working cylinders via dual-tube, the air inlet check valve, oil nozzle and spark plug are linked to each other, the middle of said connecting rod is a switch fulcrum, the compressed air is sucked into compression cylinder via compression inlet and compressed by said air outlet, and the compressed air is sprayed out from oil nozzle to form a mixed gas.
Preferably, two meshed compression rotors are arranged in the gas hood of the compression cylinder, the rotation of the two compression rotors is synchronous and opposite, the compression rotors are connected with a starting shaft, the starting shaft penetrates through the compression sealing cover and the gas outer cover, the gas outer cover is arranged at two ends of the gas hood, and the gas hood is provided with a compression gas inlet and a gas outlet.
Preferably, the compression rotor consists of two symmetrical first big convex teeth, two symmetrical first big concave teeth and a plurality of first small teeth, wherein the index circles of the first big convex teeth, the first big concave teeth and the first small teeth are the same, the moduli are the same, the tooth tops of the first big convex teeth are provided with an arc which is 5mm wide and is completely attached to the inner wall of the cylinder gas cover, the first big convex tooth tops of the two compression rotors are in arc sections of the inner wall of the gas cover and are attached to the inner wall of the gas cover to rotate in different directions, and a space compression state is formed inside the compression cylinder.
Preferably, two meshed acting rotors are arranged in the shell of the acting cylinder, the two acting rotors rotate synchronously and in opposite directions, the two acting cylinders are connected through a linkage shaft and a power output shaft, acting sealing covers are arranged on two sides of the acting rotors, covers are arranged on two ends of the shell, and an acting air inlet and an acting air outlet are formed in the shell.
Preferably, the working rotor consists of two symmetrical second big convex teeth, two symmetrical second big concave teeth and a plurality of second small teeth, the graduation circles of the second big convex teeth, the graduation circles of the second big concave teeth and the graduation circles of the second small teeth are the same, the modulus is the same, the tooth tops of the second big convex teeth are provided with an arc which is 5mm wide and is completely attached to the inner wall of the cylinder shell, the second big convex tooth tops of the two working rotors are attached to the inner wall of the shell to do opposite rotation, and a space expansion state is formed inside the working cylinder.
Preferably, the rotation speed ratio of the compression cylinder to the working cylinder is 1.6-2:1, the volume ratio of the total volume of the cylinder inner chambers of the compression cylinder to the total volume of the cylinder inner chambers of the two working cylinders is 3.8-5:1, the optimal blasting environment of the fuel oil mixed gas in the combustion chamber at 6-10 atmospheres is satisfied.
The invention has the beneficial effects that: the device adopts a full centrifugal rotor structure, the moment is full-symmetrical, the power is greatly improved, the energy consumption is reduced, the engine structure is compact, the volume is small, the air tightness is good, the cost is lower, the reliability is high, and the application prospect is wide.
Drawings
The invention is described in detail below with reference to the drawings and the detailed description;
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic view of the structure of the compression cylinder of the present invention;
FIG. 3 is an exploded view of the compression cylinder of the present invention;
FIG. 4 is a rear view of FIG. 3;
FIG. 5 is a schematic view of a compression rotor according to the present invention;
FIG. 6 is a schematic diagram of a working cylinder according to the present invention;
FIG. 7 is a rear view of FIG. 6;
FIG. 8 is an exploded view of the work cylinder of the present invention;
fig. 9 is a schematic structural view of the working rotor of the present invention.
Detailed Description
The invention is further described in connection with the following detailed description, in order to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the invention easy to understand.
Referring to fig. 1-9, the present embodiment adopts the following technical scheme: a double-rotor engine comprises a compression cylinder 1, two working cylinders 2, a belt pulley 3, an air inlet one-way valve 4, an oil nozzle 5 and an ignition plug 6, wherein the interior of the compression cylinder 1 and the interior of the two working cylinders 2 are both provided with two synchronous opposite gear type rotor structures in a meshed state, an actuating shaft 7 of the compression cylinder 1 is linked with a linkage shaft 8 of the working cylinders 2 through the belt pulley 3, an air outlet 9 of the compression cylinder 1 is respectively connected with working air inlets 10 of the two working cylinders 2 through double pipelines, each pipeline is internally provided with the air inlet one-way valve 4, the oil nozzle 5 and the ignition plug 6, the two air inlet one-way valves 4 are linked through a link rod 11, and the middle part of the link rod 11 is a switch fulcrum 12.
It is noted that, two meshed compression rotors 101 are arranged in the gas hood 102 of the compression cylinder 1, the rotation of the two compression rotors 101 is synchronous and opposite, the compression rotors 101 are connected with the starting shaft 7, the starting shaft 7 passes through the compression sealing cover 103 and the gas cover 104, the gas cover 104 is arranged at two ends of the gas hood 102, the gas hood 102 is provided with a compression gas inlet 13 and a gas outlet 9, the thermal expansion coefficients of the materials of the components of the compression cylinder 1 are equivalent, and the expansion coefficients are smaller; the compression rotor 101 consists of two symmetrical first big convex teeth 101-1, two symmetrical first big concave teeth 101-2 and a plurality of first small teeth 101-3, wherein the index circles of the first big convex teeth 101-1, the first big concave teeth 101-2 and the first small teeth 101-3 are the same, the moduli are the same, the tooth tops of the first big convex teeth 101-1 are provided with an arc which is 5mm wide and is completely attached to the inner wall of the cylinder gas cover 102, the first big convex teeth 101-1 of the two compression rotors 101 are propped against the arc section of the inner wall of the gas cover 102, are attached to the inner wall of the gas cover to rotate in opposite directions, and form a space compression state in the compression cylinder 1.
In addition, two meshed acting rotors 201 are arranged in a shell 202 of the acting cylinder 2, the two acting rotors 201 rotate in synchronous opposite directions, the two acting cylinders 2 are connected through a linkage shaft 8 and a power output shaft 15, acting sealing covers 203 are arranged on two sides of the acting rotors 201, covers 204 are arranged on two ends of the shell 202, an acting air inlet 10 and an air outlet 14 are formed in the shell 202, and the materials of all parts of the acting cylinder 2 have equal thermal expansion coefficients and smaller expansion coefficients; the working rotor 201 is composed of two symmetrical second large convex teeth 201-1, two symmetrical second large concave teeth 201-2 and a plurality of second small teeth 201-3, the index circles of the second large convex teeth 201-1, the index circles of the second large concave teeth 201-2 and the index circles of the second small teeth 201-3 are identical, the modulus is identical, the tooth tops of the second large convex teeth 201-1 are provided with an arc which is 5mm wide and is completely attached to the inner wall of the cylinder shell 202, the second large convex teeth 201-1 of the two working rotors 201 are propped against the arc section of the inner wall of the shell 202 and are attached to the inner wall of the shell to rotate in opposite directions, and a space expansion state is formed inside the working cylinder 2.
In the specific embodiment, two synchronous opposite gear type rotors in meshed states are arranged in each cylinder, the double rotors of each cylinder rotate synchronously and in opposite directions, the surface of the rotor is designed into a bidirectional slight inclined arc gear, the slight inclined rotation is smoother and more precise, meanwhile, the unilateral axial force caused by the slight inclined rotation can be counteracted in two directions, the air tightness can be increased, the synchronous opposite direction effect is achieved, each rotor is provided with two corresponding big teeth and a plurality of small teeth, the design structure of the big teeth and the small teeth can form the cylinder with obvious large capacity acting force, the scale circles of the big teeth and the small teeth in each cylinder are the same, the top circles are different, a large fall internal space is formed, the cylinder is formed on the inner wall of a shell where each rotor is located, the rotor always rotates in one direction, the big top of the two rotors of the same cylinder can always make opposite rotation on the inner wall circular arc section of the cylinder, and the big top of the two rotors of the same cylinder can always be attached to the inner wall of the shell, so that a space compression state is always formed in the compression cylinder 1, and a space expansion state is always formed in the working cylinder 2.
In the specific embodiment, the compression cylinder 1 and the two working cylinders 2 are connected through one shaft and a belt to form co-rotation, the compression cylinder 1 is an air inlet cylinder, the working cylinders 2 are working cylinders which are connected through double shafts and push gas wheels to rotate through the explosion of high-pressure fuel and air mixed gas, and the rotation speed ratio of the compression cylinder 1 to the working cylinders 2 is 1.6-2:1, the whole size of the compression cylinder 1 is larger and longer than that of the working cylinders 2, and the volume ratio of the total volume of cylinder inner chambers of the compression cylinder 1 to the total volume of cylinder inner chambers of the two working cylinders 2 is 3.8-5:1, the optimal blasting environment of the fuel oil mixed gas in the combustion chamber at 6-10 atmospheres is satisfied.
The working principle of the specific embodiment is as follows: the starting shaft 7 of the compression cylinder 1 is rotated, air is sucked into the compression cylinder 1 through the compression air inlet 13 and compressed, the compressed air enters a pipeline which is communicated with the working cylinders 2 at the side of the linkage shaft 8 from the air outlet 9, after passing through the air inlet check valve 4 of the pipeline, the oil nozzle 5 is opened, fuel oil and compressed air are sprayed to form mixed gas, the ignition of the spark plug 6 is started, the mixed gas is ignited to expand rapidly, the expanding gas pushes the air inlet check valve 4 to close the valve while pushing the rotor of the working cylinders 2 to rotate for doing work and then is discharged from the air outlet 14, the air inlet check valve 4 is closed while pushing the link rod 11 to open the air inlet check valve 4 of the other working cylinder 2, the oil nozzle 5 at the side sprays oil and the spark plug 6 to ignite, the mixed gas is ignited, and the two working cylinders 2 alternately do work to start the engine.
The rotors of the compression and acting cylinders are all axisymmetric to the axial rotation motion of the axle center, the moment is fully symmetric, the work of compressed air and the ignition mixed gas is directly completed on the rotors, the acting force is obvious, the rotation is smooth, the energy consumption can be reduced to the minimum, the power is increased to the maximum, the air tightness is ensured to the maximum degree, the engine is compact in structure, low in cost and high in reliability, and has wide market application prospect.
The foregoing has shown and described the basic principles and main features of the present invention and the advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims (8)

1. A dual-rotor engine is characterized by comprising a compression cylinder (1), two working cylinders (2), a belt pulley (3), an air inlet one-way valve (4), an oil nozzle (5) and a spark plug (6), wherein the inside of the compression cylinder (1) and the inside of the two working cylinders (2) are both provided with synchronous opposite gear type rotor structures in two meshed states, an actuating shaft (7) of the compression cylinder (1) is linked with a linkage shaft (8) of the working cylinder (2) through the belt pulley (3), an air outlet (9) of the compression cylinder (1) is respectively connected with working air inlets (10) of the two working cylinders (2) through double pipelines, each pipeline is internally provided with the air inlet one-way valve (4), the oil nozzle (5) and the spark plug (6), the two air inlet one-way valves (4) are linked through a link rod (11), the middle part of the link rod (11) is provided with a switch fulcrum (12), air is sucked into the compression cylinder (1) through an air inlet (13) and compressed, the compressed air enters the linkage shaft (8) of the working cylinder (2) through the belt pulley (3), the compressed air enters the linkage shaft (9) to the working air inlet (2) on the side of the working cylinders (8) through the air inlet (9), the air nozzle is sprayed out through the air nozzle (4), the air nozzle is mixed with the fuel nozzle (5) through the air nozzle, and the air is sprayed out through the air nozzle (4, starting a spark plug (6) to ignite, igniting mixed gas to expand rapidly, pushing the air inlet check valve (4) to close a valve while pushing the rotor of the working cylinder (2) to rotate for working, then discharging the gas through an exhaust port (14), pushing a link rod (11) to open the air inlet check valve (4) of the other working cylinder (2) to intake while closing the air inlet check valve (4), injecting oil by an oil nozzle (5) at the side, igniting the spark plug (6), igniting the mixed gas for working, and alternately working the two working cylinders (2) to start the engine.
2. The dual-rotor engine of claim 1, wherein two meshed compression rotors (101) are arranged in a gas hood (102) of the compression cylinder (1), the rotation of the two compression rotors (101) is synchronous and opposite, the compression rotors (101) are connected with a starting shaft (7), the starting shaft (7) penetrates through a compression sealing cover (103) and a gas cover (104), the gas cover (104) is arranged at two ends of the gas hood (102), and a compression gas inlet (13) and a gas outlet (9) are formed in the gas hood (102).
3. The dual-rotor engine of claim 2, wherein the compression rotor (101) is composed of two symmetrical first big convex teeth (101-1), two symmetrical first big concave teeth (101-2) and a plurality of first small teeth (101-3), the index circles of the first big convex teeth (101-1), the first big concave teeth (101-2) and the first small teeth (101-3) are identical, the moduli are identical, the first big convex teeth (101-1) of the two compression rotors (101) are propped against the circular arc sections of the inner wall of the gas hood (102), and the first big convex teeth (101-1) are adhered to the inner wall of the gas hood to do opposite rotation, so that a space compression state is formed inside the compression cylinder (1).
4. A twin rotor engine as defined in claim 3, wherein the tip of the first large lobe (101-1) is provided with a circular arc of 5mm width which fully engages the inner wall of the cylinder hood (102).
5. The double-rotor engine according to claim 1, wherein two meshed acting rotors (201) are arranged in a shell (202) of the acting cylinder (2), the two acting rotors (201) rotate synchronously and in opposite directions, the two acting cylinders (2) are connected through a linkage shaft (8) and a power output shaft (15), acting sealing covers (203) are arranged on two sides of the acting rotors (201), covers (204) are arranged on two ends of the shell (202), and an acting air inlet (10) and an air outlet (14) are formed in the shell (202).
6. The dual-rotor engine of claim 5, wherein the working rotor (201) is composed of two symmetrical second big convex teeth (201-1), two symmetrical second big concave teeth (201-2) and a plurality of second small teeth (201-3), the second big convex teeth (201-1), the second big concave teeth (201-2) and the second small teeth (201-3) have the same reference circle and the same modulus, the second big convex teeth (201-1) of the two working rotors (201) are propped against the circular arc section of the inner wall of the shell (202), and are jointed with the inner wall of the shell to rotate in opposite directions, so that a space expansion state is formed inside the working cylinder (2).
7. The dual rotor engine as claimed in claim 6, wherein the tip of the second large lobe (201-1) is provided with an arc of 5mm width which completely abuts the inner wall of the cylinder housing (202).
8. A twin-rotor engine according to claim 1, characterized in that the rotation speed ratio of the compression cylinder (1) to the working cylinder (2) is 1.6-2:1, the volume ratio of the total volume of the cylinder inner chambers of the compression cylinder (1) to the total volume of the cylinder inner chambers of the two working cylinders (2) is 3.8-5:1.
CN202311017459.8A 2023-08-11 2023-08-11 Dual-rotor engine Pending CN117028021A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202311017459.8A CN117028021A (en) 2023-08-11 2023-08-11 Dual-rotor engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202311017459.8A CN117028021A (en) 2023-08-11 2023-08-11 Dual-rotor engine

Publications (1)

Publication Number Publication Date
CN117028021A true CN117028021A (en) 2023-11-10

Family

ID=88601879

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202311017459.8A Pending CN117028021A (en) 2023-08-11 2023-08-11 Dual-rotor engine

Country Status (1)

Country Link
CN (1) CN117028021A (en)

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