US3782340A - Gear-type rotary engine - Google Patents

Gear-type rotary engine Download PDF

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US3782340A
US3782340A US00223474A US3782340DA US3782340A US 3782340 A US3782340 A US 3782340A US 00223474 A US00223474 A US 00223474A US 3782340D A US3782340D A US 3782340DA US 3782340 A US3782340 A US 3782340A
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combustion
rotors
gas
cylinder
chamber
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01CROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C1/00Rotary-piston machines or engines
    • F01C1/08Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing
    • F01C1/12Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type
    • F01C1/14Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons
    • F01C1/20Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with dissimilar tooth forms
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01CROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C11/00Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type
    • F01C11/002Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type of similar working principle
    • F01C11/004Combinations of two or more machines or engines, each being of rotary-piston or oscillating-piston type of similar working principle and of complementary function, e.g. internal combustion engine with supercharger
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02BINTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • F02B53/04Charge admission or combustion-gas discharge
    • F02B53/08Charging, e.g. by means of rotary-piston pump
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00Road transport of goods or passengers
    • Y02T10/10Internal combustion engine [ICE] based vehicles
    • Y02T10/12Improving ICE efficiencies

Abstract

A gear-type rotary engine having partitioned compression and combustion cylinders and communicable through a gas inlet and a ignition chamber positioned therebetween, a set of gear-like rotors accomodated respectively in the compression and combustion cylinders secured fixedly on two different rotor shafts in twisted positions from one another so that the transmission of compressed gas by the set of rotors in the compression cylinder in their respective gear-like rotation in opposite direction coincides with the reception of the compressed gas by the set of rotors in the combustion cylinder in their respective gear-like rotation in the opposite direction.

Description

ilmte tates atet I 1 1 3,782,349
Nam Jan. 1, 1974 GEAR-TYPE ROTARY ENGINE 1,976,761 10/1934 Barels 123/8.4l
[76] Inventor: Joong WooNam, 170-152 Rimoon-dong Dongdaemoon, Seoul, Pnmary sm i gf Gordon South Korea Attorney 1 ram 1 en et a [22] Filed: Feb. 4, 1972 [52] U.S. Cl. 123/8.23, 418/191 [51 1 llnt. Cl. F02b 53/08 [58] Field of Search 123/823, 8.41, 8.49,
[56] References Cited UNlTED STATES PATENTS 2,062,753 12/1936 Linn 123/823 3,366,096 1/1968 Mathews 123/8.41 1,184,650 5/1916 lngraham.... 123/849 1,242,826 10/1917 Llewe11yn.... 123/823 1,688,816 10/1928 Kraus 123/841 ABSTRACT A gear-type rotary engine having partitioned compression and combustion cylinders and communicable through a gas inlet and a ignition chamber positioned therebetween, a set of gear-like rotors accomodated respectively in the compression and combustion cylinders secured fixedly on two different rotor shafts in twisted positions from one another so that the transmission of compressed gas by the set of rotors in the compression cylinder in their respective gear-like rotation in opposite direction coincides with the reception of the compressed gas by the set of rotors in the combustion cylinder in their respective gear-like rotation in the opposite direction.
3 Claims, 5 Drawing'Figures PATEN TED JAN 1 I974 SHEET 1 BF 3 GEAR-TYPE ROTARY ENGINE BACKGROUND OF THE INVENTION 1. Field of Invention The present invention relates generally to internal combustion engine, more particularly to a rotary engine of gear-type for the purpose of being used in automobiles, vessels and other moving apparatus in which power is required in operation thereof.
2. Description of the Prior Art Since the cylinder-gas temperatures in internal combustion engines often reach 5,000 F, it is necessary to provide cooling for the walls of the compression and combustion space. The temperature of the inside surface of the cylinder walls is usually kept below 400 F to prevent deterioration of the oil film. Chemical and physical changes in the oil resulting from high temperature may cause wear and sticking of the piston rings or rotors, scoring of the cylinder walls, or seizure of the piston or rotors.
In known internal combustion engines and particularly, in Wankels engine, the compression and combustion of gas are generally conducted within a single cylinder and the cylinder will naturally absorb the heat out of the double action. An overheated cylinder may lead to overheated spark-plug electrodes, causing preignition, and adverse conditions for the compression of gas, resulting in a loss in overall efficiency.
Being eccentric, Wankels engine is greatly hindered in its rotation by the centrifugal and inertial force exerted by itself, inviting unnecessary vibration and adverse mechanical efficiency and, further resulting in unbalanced and unstabilized rotation. In drawing out the power therefrom, there is no other idealistic means developed so far but those means relying on the principle of the crankshaft which would invite vibration still more.
SUMMARY OF THE INVENTION Advantageous objects can be accomplished by the present invention which embodies among its features compression and combustion cylinders partitioned by a mid partition wall but communicable through a compressed gas inlet and a ignition chamber formed thereon the partition wall, a matching pair of rotors that engages in gear-like relation in their rotation in opposite directions accomodated respectively in the compression cylinder for the exclusive purpose of compressing gas and in the combustion cylinder for the exclusive purpose of combusting gas.
The prime object of the present invention is to provide a rotary engine of gear-type being capable of conducting separately the compression and combustion of gas in partitioned compression cylinder and combustion cylinder respectively, thus avoiding the hindering and adverse conditions caused from overheating and often found in the engines of Wankel, and ensuring high operational efficiency in the engines of the type.
Another object of the invention is to provide a rotary engine being capable of attaining balanced and stabilized rotation without any centrifugal or inertia] force exerted therefrom and, without any, or less, if any, vibration, thereby attaining a high velocity of rotation desired in the capacity of the type.
A further object of the invention is to provide a rotary engine from which power can easily be drawn out of mechanically, that is, directly from the centric power shaft thereof.
BRIEF DESCRIPTION OF THE DRAWINGS Other objects and features of the invention will be more apparent to those skilled in the art from the following disclosure taken in connection with the accompanying drawings, wherein like components throughout the figures thereof are indicated by like numerals, and wherein,
FIG. 1 is a perspective view illustrating the general configuration of the present invention;
FIG. 2 is a longitudinal cross-sectional view of the invention taken on the line A-A in FIG. '1;
FIG. 3 is a longitudinal cross-sectional view of the invention taken on the line BB in FIG. 1;
FIG. 4 is a longitudinal cross-sectional view of the invention taken on the line CC in FIG. 1;
FIG. 5 is an exploded perspective viewof the essential components of the invention shown in FIG. 1, with rotor shafts thereof excluded.
.DESCRIPTION OF THE PREFERRED EMBODIMENT This invention, in accordance with the preferred embodiment, is roughly broken down into five sections, referrring specifically to FIG. 5 of the drawings, that is, a compression cylinder housing 1, a combustion cylinder housing 2, a mid partition wall 3, a side housing 4 and side housing 5.
Of the essential components, with a few exception, most are preferrably made of aluminium alloy or other light metals available.
In said compression cylinder housing 1, a doubled O compression cylinder 6 for the accomodation of a set of two rotors, a convex rotor 8 and a concave rotor 11, is formed in a hollow form of two circles being overlapped and of the two one is slightly larger, and an intake port 7 for the mixture of fuel and air is formed extending upwardly therefrom and in communication therewith said cylinder 6.
In said combustion cylinder housing 2, a doubled O combustion cylinder 14 is formed, being identical with and for identical purpose with that in said compression cylinder 6, and an exhaust port 15 for the ex haust of the mixture of fuel and air is formed extending downwardly therefrom and in communication therewith said cylinder 14.
Said mid partition wall 3 has a set of bores 16 suitably positioned on the wall thereof to support and allow two rotor shafts 2h, 21 running therethrough, a compressed gas inlet 17 formed on the surface thereof opening its mouth to said compression cylinder 6, a ignition chamber 18 formed on the opposite surface thereof in communication with said gas inlet 17 and opening its mouth to said combustion cylinder 14, and a spark plug insert 19 of a contact magnetic ignition system suitably fixed on the ceiling of said ignition chamber 18 for timed ignitions in accordance with the rotations of said rotors 8 and 11.
Said side housings 4 and 5 have a set of shaft bores 22 respectively suitably positioned on the wall thereof to support and allow said two rotor shafts 20, 21 running therethrough.
Said convex rotor 8 has a shaft bore 8' in the center thereof, a set of pole blades (semi-circular protuberances) 9 on the poles of the periphery thereof and sprocket teeth on the rest portion of the periphery thereof, all formed along the axial length thereof.
Said concave rotor 11 has a shaft bore 1 1 in the center thereof, a set of pole indents(semi-circular reduced portions) 12 on the poles of the periphery thereof and semi-circular teeth 13 on the rest portion of the periphery thereof, all formed along the axial length thereof.
Two of said convex rotors 8, 8 secured fixedly onto said rotor shaft in twisted positions from one another, the difference being approximately 60", for the reason to be explained later on and accomodated respectively therein said compression cylinder 6 and said combustion cylinder 14, rotates concentrically while two of said concave rotors 11, 11 secured fixedly onto said rotor shaft 21 in twisted positions likewise adapted in respect to said convex rotors 8, 8 and accomodated respectively therein said compression cylinder 6 and said combustion cylinder 14, rotates concentrically.
Positioned respectively therein said compression cylinder 6 and said combustion cylinder '14, the matching pair of said convex rotor 8 in the larger hollow of said cylinders 6, l4 and said concave rotor 1 l in the smaller hollow of said cylinders 6, 14, respectively secured fixedly on said two different rotor shafts 20, 21, engages in a gear-like relation with said semi-circular protuberances or pole blades 9 and said sprocket teeth 10 formed thereon said convex rotor 8 corresponding with said semi-circular reduced portions or pole indents l2 and said semi-circular teeth 13 formed thereon said concave rotor 11, and as a result said convex rotor 8 rotates counter-clockwisely while said concave rotor 11 clockwisely.
Said rotor shafts 20, 21 are rotatably secured onto and supported by said bores 16 formed thereon said mid partition wall 3 in the center and by said shaft bores 22 formed thereon said side housings 4, 5 at sides, and onto one end thereof prime gears 23 are fixedly secured respectively while onto the other end fly wheels 24 fixedly secured respectively.
Now referring to FIG. 2 of the drawings, a gear housing 25 is provided to be an oil tank for the lubrication of said gears 23, and in order for the lubrication of other moving parts, such as rotor shafts, bearings, rotors and rotor blades, self-lubrication conduits can be provided linking said oil tank or gear housing 25 and oil passage bores formed thereon said rotor shafts 20, 21.
Grooves are provided to hold in place gas seal pieces 26 on the blades and teeth portions and sides of said rotors 8, 8 and 11, 11, and in each of said grooves a plurality of oil passage bores can be formed to give an internal lubrication of said rotors and said cylinders.
Water cooling jackets are provided therein said cylinder housings l, 2 surrounding said cylinders 6, 14 and in addition air cooling fins can well be provided on the outer surfaces of said housings 1, 2, 4, 5.
Now, from the foregoing, it will be readily understood that said compression cylinder 6 and said combustion cylinder 14 are separately provided with said mid partition wall .3 intervening between as a sealing insulator and at the same time a thermal insulator.
And it shall be noted that said compressed gas inlet 17 formed laterally thereon the surface of said mid partition wall 3 facing said compression cylinder 6 is positioned slightly below a level line drawn on the center of said two rotor shafts 20, 21 where said pole blades 9 of said convex rotor 8 and said pole indents 12 of said concave rotor 11 therein said compression cylinder 6 are to meet in their respective rotation in opposite direction, as clearly shown in FIG. 3, while said ignition chamber 18 formed laterally thereon the opposite surface of said mid partition wall 3 facing said combustion cylinder 14 is positioned slightly above a level line drawn on the center of said two rotor shafts 20, 21 where said pole blades 9 of said convex rotor 8 and said pole indents 12 of said concave rotor 11 in said combustion cylinder 14 are to part after their meeting in their respective rotation in opposite direction, as clearly shown in FIG. 4.
It shall further be noted that the sets of said rotors 8, 11 therein said compression cylinder 6 and said combustion cylinder 14 are set in such twisted positions, say, approximately as are shown respectively and comparatively in FIGS. 3 and 4, so as the meeting of said pole blades 9 of said convex rotor 8 and said pole indents 12 of said concave rotor 11 in their respective rotation in opposite direction therein said compression cylinder 6 coincides with the parting after their momentary meeting of said pole blades 9 of said convex rotor 8 and said pole indents 12 of said concave rotor 11 in their respective rotation in opposite direction therein said combustion cylinder 14.
In another word, the meeting of said pole blades 9 of said convex rotor 8 and said pole indents 12 of said concave rotor 11 in their respective rotation therein said compression cylinder 6 takes place at where said compressed gas inlet 17 is formed thereon the wall of said mid partition wall 3 in order to shut off said inlet 17 right after giving a last squeeze to the compressed gas into said inlet 17, as dramatically shown in FIG. 3, and at this very moment, the parting after their meeting of said pole blades 9 of said convex rotor 8 and said pole indents 12 of said concave rotor l 1 in their respective rotation therein said combustion cylinder 14 takes place at where said ignition chamber 18 is formed thereon the wall of said mid partition wall 3 in order to clear the way for the compressed gas to surge in therefrom said ignition chamber 18, as clearly shown in FIG. 4, and a little moment thereafter, to be forcibly parted by the expansion force out of the gas combustion, mainly received by said pole blade 9 of said convex rotor 8, upon the ignition thereof by said spark plug 19 provided concealingly therein said ignition chamber 18, causing accelerated rotation of said rotors 8, 11 therein said cylinder 14 in opposite direction respectively, and at the same time of said concentric rotors 8, l l therein said compression cylinder 6 also, thus, since there formed therein said compression cylinder 6 two chambers A and B sealingly partitioned by said pole blades 9 of said convex rotor 8, causing another compression A and another inhalation B of the gas being in the making in said compression'cylinder 6, as shown in FIG. 3.
From the above, it will be easily noted that said convex rotors 8, 8 therein the larger hollows of said cylinders being prime mover both in compression therein said compression cylinder 6 and in combustion therein said combustion cylinder 14, and that it is therein said larger hollows of said cylinders 6, 14 where compression and combustion of the gas take place respectively.
In operation of the rotary engine according to the present invention, referring now to FIGS. 2, 3 and 4, the mixture of fuel and air supplied from the carburetor entering therethrough said in-take port 7, as shown by the in-coming arrow in the drawings respectively, is inhaled and compressed as the pair of rotors, said convex rotor 8 and concave rotor 11, rotates engagingly therein said compression cylinder 6, mainly by the sweeping action of said pole blades 9 of said convex rotor 8 therein said cylinder 6, as more clearly seen in FIG. 3.
The gas thus compressed therein said compression cylinder 6 enters into said ignition chamber 18 therethrough said compressed gas inlet 17, both formed thereon said mid partition wall 3, a moment before the meeting of said pole blade 9 of said convex rotor 8 and said pole indent 12 of said concave rotor 11 in their respective rotation in opposite direction therein said compression cylinder 6 as shown in FIG. 4 takes place, whereby it is to be ignited by said spark plug insert 19 of said contact magnetic ignition system upon its timed activation by the rotation of said pair of rotors, convex rotor 8 and concave rotor 11, as shown in FIG. 2.
The ignition of the compressed gas by said spark plug 19 is so calculated and timed that the expansion force out of the gas combustion spreads forcibly into between said pole blade 9 of said convex rotor 8 and said pole indent 12 of said concave rotor 11 that are starting to part after their momentary meeting in their respective rotation in opposite direction therein said combustion cylinder 14 as shown in FIG. 4, hitting and sweeping said pole blade 9 of said convex rotor 8 along its path therein said cylinder 14 and finally making itself way out together with the product of the combustion therethrough said exhaust port 15, as shown by the outgoing arrow in the drawings respectively, thereby causing accelerated rotation of all said rotors 8, 8, 11, 11 therein said combustion cylinder 14 and said compression cylinder 6.
From the foregoing, it will be apparent that the rotary engine in accordance with the present invention, with the compression cylinder and combustion cylinder separately provided, excels in the manner of preventing the gas compression cylinder from absorbing too much of heat that is generally considered to be undesirable in engines of the type but often seen in the reciprocating engines, Wankels rotary engines or other type of engines, saving such fussy'and cumbersome arrangements for. quick-cooling of the gas compression cylinders or chambers as in Wankels.
Having two sets of gear-type rotors in the center and a set of fly wheels and a set of prime gears assisting at the ends thereof, all lined up in an alignment, the engine of the present invention is dynamically well balanced and stabilized, thus ensuring a high mechanical efficiency, less vibration and a high velocity of rotation, the most desired factor ever sought in engines of any kind.
For it is being centrical, power can easily be drawn out of and utilized and moreover, unlike in the conventional engines such as reciprocating engine, Wankels rotary engine and others so far developed, inertia in the engine of the present invention means acceleration in the velocity of rotation.
From the above description it will be apparent that various modifications could be devised without departing from the inventive concepts herein disclosed.
While a specific and preferred embodiment of the present invention has been herein described, it is intended to secure by these Letters Patent all other embodiments that are within the scope of the appended claims.
What is claimed is:
1. A rotary internal combustion engine comprising a. a rotary compression chamber having a gas intake port and formed by two longitudinally parallel, partially overlapping hollow cylinders of different radii, both arcuate cylinder walls of which are circumferentially in gas communication with essentially only said gas intake port;
. a rotary combustion chamber having a gas exhaust port and formed by two longitudinally parallel partially overlapping hollow cylinders of different radii, the axes of which cylinders are in longitudinal alignment with corresponding hollow cylinders in said rotary compression chamber, and both arcuate cylinder walls of which are circumferentially in gas communication with essentially only said gas exhaust port;
c. partition means longitudinally separating and thermally insulating said compression chamber from said combustion chamber, said partition means containing an ignition chamber which is offset from a plane common to said cylinder axes on the same side thereof as said gas intake port and adjacent to and axially communicating with said combustion cylinder;
d. a compressed gas conduit extending within said partition means from said ignition chamber to a compressed gas inlet offset from said plane on the opposite side thereof from said gas intake port adjacent to and axially communicating with said compression chamber at a point where the two bases of said hollow cylinders forming said combustion chamber overlap;
e. a combustion gas conduit extending within said partition means from said ignition chamber to a combustion gas outlet offset to the side of said plane opposite said gas exhaust port and axially communicating with said combustion chamber at a point where the two bases of said hollow-cylinders forming said combustion chamber overlap;
f. convex rotors rotatably mounted on a common shaft in the larger hollow cylinders of said compression chamber and said combustion chamber, said convex rotors having along the axial length thereof a set of semicircular protuberances at the poles and a first set of sprocket teeth along the remainder of the periphery thereof;
g. concave rotors rotatably mounted on a second common shaft in the smaller hollow cylinders of said compression chamber and said combustion chamber, said concave rotors having along the axial length thereof a set of semicircular indentations at the poles and a second set of sprocket teeth along the remainder of the periphery thereof which sealingly engage corresponding protuberances and sprocket teeth on said convex rotors;
h. a matching pair of prime gears secured to one end of said rotor shafts; and
i. a pair of flywheels secured to the other end of said rotor shafts.
2. A rotary engine according to claim it wherein the sprocket teeth on said concave rotors are sealingly enclosed by the circumferential walls of said hollow cylinder.
3. A rotary engine according to claim 2 wherein rotors pairs in said compression chamber and said combustion chamber are fixed to said shafts approximately degrees out of radial alignment.

Claims (3)

1. A rotary internal combustion engine comprising a. a rotary compression chamber having a gas intake port and formed by two longitudinally parallel, partially overlapping hollow cylinders of different radii, both arcuate cylinder walls of which are circumferentially in gas communication with essentially only said gas intake port; b. a rotary combustion chamber having a gas exhaust port and formed by two longitudinally parallel partially overlapping hollow cylinders of different radii, the axes of which cylinders are in longitudinal alignment with corresponding hollow cylinders in said rotary compression chamber, and both arcuate cylinder walls of which are circumferentially in gas communication with essentially only said gas exhaust port; c. partition means longitudinally separating and thermally insulating said compression chamber from said combustion chamber, said partition means containing an ignition chamber which is offset from a plane common to said cylinder axes on the same side thereof as said gas intake port and adjacent to and axially communicating with said combustion cylinder; d. a compressed gas conduit extending within said partition means from said ignition chamber to a compressed gas inlet offset from said plane on the opposite side thereof from said gas intake port adjacent to and axially communicating with said compression chamber at a point where the two bases of said hollow cylinders forming said combustion chamber overlap; e. a combustion gas conduit extending within said partition means from said ignition chamber to a combustion gas outlet offset to the side of said plane opposite said gas exhaust port and axially communicating with said combustion chamber at a point where the two bases of said hollow cylinders forming said combustion chamber overlap; f. conveX rotors rotatably mounted on a common shaft in the larger hollow cylinders of said compression chamber and said combustion chamber, said convex rotors having along the axial length thereof a set of semicircular protuberances at the poles and a first set of sprocket teeth along the remainder of the periphery thereof; g. concave rotors rotatably mounted on a second common shaft in the smaller hollow cylinders of said compression chamber and said combustion chamber, said concave rotors having along the axial length thereof a set of semicircular indentations at the poles and a second set of sprocket teeth along the remainder of the periphery thereof which sealingly engage corresponding protuberances and sprocket teeth on said convex rotors; h. a matching pair of prime gears secured to one end of said rotor shafts; and i. a pair of flywheels secured to the other end of said rotor shafts.
2. A rotary engine according to claim 1 wherein the sprocket teeth on said concave rotors are sealingly enclosed by the circumferential walls of said hollow cylinder.
3. A rotary engine according to claim 2 wherein rotors pairs in said compression chamber and said combustion chamber are fixed to said shafts approximately 60 degrees out of radial alignment.
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Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3996899A (en) * 1975-04-03 1976-12-14 Gateway Of Discovery, Inc. Positive displacement continuous combustion engine
US4012903A (en) * 1972-07-24 1977-03-22 Riedl Frank E Internal combustion engine
US4078526A (en) * 1975-05-31 1978-03-14 Josef Gail Rotary piston engine
FR2449786A1 (en) * 1979-02-22 1980-09-19 Defarge Alexis Rotary turbine with parallel rotors - has compression and drive stages on each rotor and inlet and outlet casing ports
US4312629A (en) * 1980-08-22 1982-01-26 General Supply (Constructions) Co. Ltd. Universal rotating machine for expanding or compressing a compressible fluid
EP0046586A2 (en) * 1980-08-22 1982-03-03 General Supply (Constructions) Co., Ltd. Internal combustion engine
US4413486A (en) * 1982-03-15 1983-11-08 Irwin Everett F Rotating cylinder external combustion engine
EP0510125A1 (en) * 1990-01-05 1992-10-28 Le Kim Le Rotary internal combustion engine.
US5682793A (en) * 1993-09-21 1997-11-04 Liao; Zhenyi Engaged rotor
DE10003829A1 (en) * 1999-09-29 2001-04-19 Stefan Hagge Turbine engine for motor vehicles consists of compressor, combustion chamber, and turbine, which are adapted individually to operational demands
US6273055B1 (en) 1999-05-04 2001-08-14 Robert A. White Rotary engine
US6655344B2 (en) * 2002-03-05 2003-12-02 William F. Sager Rotary gear device
RU2292464C8 (en) * 2005-02-28 2007-04-20 Анатолий Васильевич Помогаев Hydropneumatic set
JP2008025582A (en) * 2006-07-21 2008-02-07 Liangfeng Plastic Machinery Co Boosting system and its device
US20080087004A1 (en) * 2006-09-05 2008-04-17 Terry Michael Van Blaricom Open-cycle internal combustion engine
US20090165441A1 (en) * 2007-12-27 2009-07-02 Van Moerkerken Arthur Combustion engine with feedback gear/rotary pump input
US20090255506A1 (en) * 2008-04-14 2009-10-15 Walker S Paul Rotary internal combustion engine
CN101117914B (en) * 2006-07-31 2010-12-08 良峰塑胶机械股份有限公司 Boost system and implement assembly
CN102003215A (en) * 2010-05-13 2011-04-06 石家庄中煤装备制造有限公司 Multistage air motor
JP5218929B1 (en) * 2012-09-11 2013-06-26 武史 畑中 Rotary combustion engine, hybrid rotary combustion engine, and machine equipped with these
US8616176B2 (en) 2010-04-21 2013-12-31 Sumner Properties, Llc Rotary internal combustion engine
US8667950B1 (en) * 2013-02-11 2014-03-11 Thomas Lee Fillios, Sr. Oil-less rotary engine
RU2551718C2 (en) * 2013-04-01 2015-05-27 Евгений Алексеевич Несмеев Rotary internal combustion engine
EP3379026A1 (en) * 2017-03-21 2018-09-26 Fuelsave GmbH Combustion engine and method for operating same

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1184650A (en) * 1915-03-05 1916-05-23 Charles A Ingraham Gas-motor.
US1242826A (en) * 1916-07-11 1917-10-09 David Franklin Llewellyn Engine.
US1688816A (en) * 1927-01-19 1928-10-23 Charles E Kraus Rotary engine
US1976761A (en) * 1929-10-19 1934-10-16 Barels James Engine
US2062753A (en) * 1934-11-09 1936-12-01 Albert W Linn Rotary gasoline engine
US3366096A (en) * 1966-03-11 1968-01-30 Thomas E. Mathews Rotary explosion engine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1184650A (en) * 1915-03-05 1916-05-23 Charles A Ingraham Gas-motor.
US1242826A (en) * 1916-07-11 1917-10-09 David Franklin Llewellyn Engine.
US1688816A (en) * 1927-01-19 1928-10-23 Charles E Kraus Rotary engine
US1976761A (en) * 1929-10-19 1934-10-16 Barels James Engine
US2062753A (en) * 1934-11-09 1936-12-01 Albert W Linn Rotary gasoline engine
US3366096A (en) * 1966-03-11 1968-01-30 Thomas E. Mathews Rotary explosion engine

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4012903A (en) * 1972-07-24 1977-03-22 Riedl Frank E Internal combustion engine
US3996899A (en) * 1975-04-03 1976-12-14 Gateway Of Discovery, Inc. Positive displacement continuous combustion engine
US4078526A (en) * 1975-05-31 1978-03-14 Josef Gail Rotary piston engine
FR2449786A1 (en) * 1979-02-22 1980-09-19 Defarge Alexis Rotary turbine with parallel rotors - has compression and drive stages on each rotor and inlet and outlet casing ports
US4312629A (en) * 1980-08-22 1982-01-26 General Supply (Constructions) Co. Ltd. Universal rotating machine for expanding or compressing a compressible fluid
EP0046586A2 (en) * 1980-08-22 1982-03-03 General Supply (Constructions) Co., Ltd. Internal combustion engine
US4321897A (en) * 1980-08-22 1982-03-30 General Supply (Constructions) Co. Ltd. Internal combustion engine
EP0046586A3 (en) * 1980-08-22 1982-09-08 General Supply (Constructions) Co., Ltd. Internal combustion engine
US4413486A (en) * 1982-03-15 1983-11-08 Irwin Everett F Rotating cylinder external combustion engine
EP0510125A1 (en) * 1990-01-05 1992-10-28 Le Kim Le Rotary internal combustion engine.
EP0510125A4 (en) * 1990-01-05 1992-12-16 Le Kim Le Rotary internal combustion engine
US5682793A (en) * 1993-09-21 1997-11-04 Liao; Zhenyi Engaged rotor
US6273055B1 (en) 1999-05-04 2001-08-14 Robert A. White Rotary engine
DE10003829A1 (en) * 1999-09-29 2001-04-19 Stefan Hagge Turbine engine for motor vehicles consists of compressor, combustion chamber, and turbine, which are adapted individually to operational demands
US6655344B2 (en) * 2002-03-05 2003-12-02 William F. Sager Rotary gear device
RU2292464C8 (en) * 2005-02-28 2007-04-20 Анатолий Васильевич Помогаев Hydropneumatic set
JP4686507B2 (en) * 2006-07-21 2011-05-25 良峰塑膠機械股▲ふん▼有限公司 Booster system and apparatus
US7341042B1 (en) * 2006-07-21 2008-03-11 Liung Feng Industrial Co., Ltd. Rotary positive displacement control system and apparatus
JP2008025582A (en) * 2006-07-21 2008-02-07 Liangfeng Plastic Machinery Co Boosting system and its device
CN101117914B (en) * 2006-07-31 2010-12-08 良峰塑胶机械股份有限公司 Boost system and implement assembly
USRE45397E1 (en) * 2006-09-05 2015-03-03 Terry Michael Van Blaricom Open-cycle internal combustion engine
US20080087004A1 (en) * 2006-09-05 2008-04-17 Terry Michael Van Blaricom Open-cycle internal combustion engine
US8181624B2 (en) * 2006-09-05 2012-05-22 Terry Michael Van Blaricom Open-cycle internal combustion engine
US20090165441A1 (en) * 2007-12-27 2009-07-02 Van Moerkerken Arthur Combustion engine with feedback gear/rotary pump input
US8555611B2 (en) * 2007-12-27 2013-10-15 Arthur Vanmoor Combustion engine with feedback gear/rotary pump input
US20090255506A1 (en) * 2008-04-14 2009-10-15 Walker S Paul Rotary internal combustion engine
US8616176B2 (en) 2010-04-21 2013-12-31 Sumner Properties, Llc Rotary internal combustion engine
CN102003215B (en) * 2010-05-13 2013-05-15 石家庄中煤装备制造股份有限公司 Multistage air motor
CN102003215A (en) * 2010-05-13 2011-04-06 石家庄中煤装备制造有限公司 Multistage air motor
JP5218929B1 (en) * 2012-09-11 2013-06-26 武史 畑中 Rotary combustion engine, hybrid rotary combustion engine, and machine equipped with these
US8667950B1 (en) * 2013-02-11 2014-03-11 Thomas Lee Fillios, Sr. Oil-less rotary engine
RU2551718C2 (en) * 2013-04-01 2015-05-27 Евгений Алексеевич Несмеев Rotary internal combustion engine
EP3379026A1 (en) * 2017-03-21 2018-09-26 Fuelsave GmbH Combustion engine and method for operating same

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