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Publication numberUS1003708 A
Publication typeGrant
Publication dateSep 19, 1911
Filing dateDec 4, 1909
Priority dateDec 4, 1909
Publication numberUS 1003708 A, US 1003708A, US-A-1003708, US1003708 A, US1003708A
InventorsClyde J Coleman
Original AssigneeRockaway Automobile Company
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Rotary impact-engine.
US 1003708 A
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Description  (OCR text may contain errors)

C. J. COLEMAN.

ROTARY IMPACT ENGINE.

APPLICATION FILED D110. 3, 1900. mmnwnn 111:0. 4, 1909.

1,003,708. Patented Se'pt. 19,1911.

2 SHEETS-SHEET 1.

WITNESSES:

W WM?- INVENTOR C. J. COLEMAN.

ROTARY IMPACT ENGINE.

APPLIOATION FILED 1150. a. 1900. RENEWED 111:0. 4, 1909.

1,003,708. Patented Sept. 19,1911.

2 SHEETS-SHEET 2.

WITNESSES: N INVENTOR ATTORNEY UNITED STATES PATENT OFFICE.

or-Yon .1. comm, or raw York, N. Y., nssionon. 'ro nocmwar sn'romonmn comm, or nooxnwnr, new messy, n conrona'rron or new smear.

Specification of letters Patent.

Patented Sept. 19, 1911.

Application filed December 3,1900, Serial Ho. 38,38l. Renewed December 4, 1909, Serial 80'. 581,403-

To all iohom it concern:

Be it known that I, CLYDE J. COLEMAN, d

, citizen oi the United States, and a resident gaseous mixtures.

of the borough of Manhattan, in the county of New York, city of New York,-'and State of New York, have invented new and useful Improvements in Rotary Impact-Engines,

.of which thefollowing' is a specification, referencebelng had to the accompanying drawings, forming part thereof.

This invention relates to improvements in rotary impact engines, wherein rotary movement is directly'produced from and by the combustion of explosive gases or gaseous mixtures, forming the motlve fluid.

The main object of myinvention is to produce rotary motion from practically continuous combustion of explosive gases or Further objects of my invention are the provision of means whereby the motive fluid employed may be permitted to expand before reaching the point of impact, the" prevision of an injector, or injectors, for introducing the motive fluid, and the provision of a blower in connection therewith.

My invention also includes certain novel features of construction and combination of parts, all of which will appear from the following description pf the engine embodying my invention illustrated in the acco'mpan ing drawings.

Figure 1 is a side view, partially in central vertical section of an engine embodying clination to radial lines.

spaces between the blades or vanes are exteriorly entirely uninclosed. Interiorlythey are uninclosed by any stationary part but are arranged opposite to a plurality of turbine blades or vanes 5 with which the rotary part 2 is provided. The annular side plates 3, 3, and the turbine vanes 4 carried thereby, and together forming the stationary part 1, are supported bysuitable brackets 6, 6,

mounted upon a bed-plate 7. The rotary 1. e drawpart is mounted upon a suitable shaft 8 journaled in bearings 9-9 also secured to bedplate 7. The rotary part carries a pluralit of in ectors, the. inner nozzles 10 of whic connect Wlth a supply of motive fluid, in this instance carried 1n through the interior of the shaft 8, made hollow for such purpose,

and the outer nozzles 11 of which communicate with the outer atmosphere or other supply of cooling medium through central openings in the side walls 12, 12, of the rotary part 2. Pipes 13 form suitable connections between the hollow shaft 8 and the, nozzles 10, and further form supports there for. Each of the injectors discharges into one of a plurality of expansion chambers 14, one for each injector, and each of these chambers connects with a number of spaces intervening between a plurality of turbine vanes or blades 5, said turbine vanes forming the outer wall of such expansion chamber.

Intermediate of the injectors and expansion chambers are arranged cooling chambers 15. Each of these cooling chambers connects with the central opening in the side walls 12, and with one or more of the intervening spaces between the turbine vanes or blades 5. The cooling chambers are 'oon-' nected together moreover around thewalls of the expansion chamber, as will be readily.

understood by reference to Fig. 1.

In operation the rotary part 2 revolves rapidly and draws in air or other vapor by the action of centrifugal force through the central openings in the side walls 12, and the air or other vapor thus drawn in, passes to the outer nozzles 11 of the injectors and to the cooling chambers 15. In order to augment this centrifugal force I connect a blower therewith, and in the drawings I have'shown the rotary part 2 as provided with fan blades 16-, these fan blades being arranged opposite both the openings in the side walls 12, and being adapted to act as a blower.

The blades 16 I herein term fanblades for the purpose of distinguishing them from the coacting turbine vanes heretofore described. structurally they may or may not difler from them as may be desired. They are herein shown as radially arra d, but ma if desired, be arranged at an mciina'tion to radiallines.

I have shown a conventional representation of a carbureter the drawings atg1-7,

ventional igniting circuit at 21 for the pur-- pose of igniting the motive fluid in first starting up the enginewhen once started u the flame will pass from one to another oi the interveningspa-ces between the turbine vanes or blades and successive igniting by an independent igniting means will be unnecessary. v

When the engine is running normally, motive fluid will be drawn from the carbureter, through the hollow shaft and through the inner nozzles of the injectors by the action of centrifugal force in the rotary part of the engine. Air or other vapors will be also drawn through the outer nozzles 11 by inductive action, augmented by the fan blades, and the mixture will be deliveredinto the chambers 14. Ignition will take place at the mouths of the inner nozzles 10. The rapid accumulation of pressure however, due to ignition, is greater than is required in the turbines, and much greater than will give the best results. It has been found that a maximum economy is obtained where the speed of a turbine is one half the velocity of the motive fluid at the point of impact. For this reason I permit the ignited motive fluid to expand'in the chambers 14 and thereby reduce both its temperatures and its velocity between the point of combustion and the point of impact. The vanes 5 direct the ignited motive fluid toward the impact vanes 4 and the result isa powerful rotary movement of the part 2 in the direc-' 'tion of the arrow in Fig. 2. The air or other vapors drawn, or forced, in through the central openings in the walls 12 act also as a cooling medium in circulating through the cooling chambers 15 and around the walls of the expansion chambers 14, and further tend, to cool the turbine vanes or impact blades by discharging therethrough and to clear the same of the residual products of combustion Inorder to avoid back-fire I provide the injectors Lwith guards of wire mesh 22 or the like, as clearly shown in ,thedrawings. It is evident that various modifications may be made in the'constructions above particularly deseribed within the. purview of my invention and} that parts of my invention may be embodied in 'otherconstructions than those shownaiid describe What I claim and desire to secure by Letters Patent is I I 1*;

1, A continuous combustion rotary impact engine having a;rotary:.part wherein combustion is and 'wherein 'the motive engine provided with means for producing combustion, a rotary part having expansion chambers wherein the motive fluid is expanded after combustion, impact-receiving means, and means upon the rotary part for completing the expansion chainber and for directing the expanded motive fluid against i a group of impact-receiving means so that.

each part thereof will receive the expanded motive-fluid at the same instant, substantially as set forth.

3. A continuous combustion rotary impact" engine provided with means for producing combustion within the engine, means for supplying an auxiliary power medium in conductive adjacency to the products of com'.

bustion whereby -the auxiliary power medium is commingled therewith and the temperature of the products of combustion lowered, impact-rece ving means,and means for directing the commingled products of combustion and auxiliary power medium against a group" of impact-receiving means so thateach part thereof will receive the motive' ower fluid at the same instant, substantially as set forth.

4; A rotary impact, engine having an injector for the motive medium and an expansion chamber between the injector and the point of impact, a group of impact receiving means and suitable directing means forming the outer walls of said expansion chamber and adapted to direct the expanded-motive medium against each component part. of the group of impact receiving means, substantially as set forth.

5. A rotary impact engine comprising two parts, one stationary and the other rotary, both parts being provided with turbine vanes adapted to coact and the rotary part being also provided with concentric fan blades independent ofthe vanes, substantially as set forth.

6. A continuous combustion rotary impact engine comprising two power-developing members rotatable one relative to the other I and one including impact-receiving surfaces and the other including motive fluid guiding ducts arranged to convey the motive fluid against such impact receiving surfaces,

means for conveying motive fluid into the guiding ducts, and means .for maintaining continuous combustion of the motive fluid-at.

a point anterior to its impact against the impact receivingsurfaces.

'7. A rotary impact engine comprising an outer annular stationary part carrying turbine vanes or" impact blades and an inner revoluble part carrying turbine vanes near its outer edge, and independent concentric fan blades at points nearer its axis of rotation, substantially as set forth.

8. A rotary impact engine comprising two parts, one stationary and the other rotary, the stationary part being provided with impact vanes and the rotary part provided with an injector connecting with a supply of motive medium, and carrying a plurality of concentric fan blades adapted tosupply cooling medium to the injector, substantially as set forth.

9. A rotary impact engine having an expansion chamber for receiving motive medium and encompassed by turbine vanes and permitting the same to expand between the point of combustion and the point of immitting the expansion of motive medium between a point of combustion and a point of impact, and having fan blades for drawing in a cooling medium between the expansion chambers, substantially as set forth.

12. A rotary impact engine comprising two parts, one stationary and the other'rotary, the stationary part being provided with turbine vanes or impact blades and the rotary part with vanes adapted for the mo tive medium, with an injector for the motive medium, an expansion chamber bet-ween the in ector and the turbine vanes said vanes encompassing the expansion chamber and means whereby a circulation of a cooling medium is permitted, substantially as set forth. a Y

13. A' rotary impact engine comprising two parts, one stationary and'the other rotary, the stationary part provided with turbine vanes, and the rotary part with vanes adapted to coact therewith, with injectors for the motive medium and expansion chambersbetWeen the injectors and the turbine vanes, said vanes encompassing) the expansion chamber and passages etween the vanes of the rotary part for the circulation of a cooling medium, such passages dischargingthrough the vanes o the stationary part, substantially as set forth.

14. A rotary impact engine comprising two parts, one stationary and the other rotary, the stationary part being provided with impact receiving vanes, and the rotary partprovided with means for admitting motive medium and in addition thereto, with fan blades concentrically arranged at the periphery of the rotary part to direct the motive medium against the impact receiving vanes.

Signed at New York, N. Y., the,1st day of December, 1900.

CLYDE J. COLEMAN;

Witnesses: A

HENRY D. WILLIAMS, HERBERT H. GIBBS.

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2425904 *Nov 29, 1941Aug 19, 1947James B VernonTurbine
US2448972 *Oct 20, 1944Sep 7, 1948Gizara Edward WInternal-combusstion engine
US2670597 *Oct 9, 1947Mar 2, 1954Jacques VillemejaneRotating jet motor with regulation of power output
US2674421 *Sep 25, 1948Apr 6, 1954Cenzo Herbert A DeJet-driven rotary wing arrangement for jet propelled convertible aircraft
US2777290 *Aug 8, 1955Jan 15, 1957Edward W BaileySpherical internal combustion turbine
US2861776 *Dec 26, 1951Nov 25, 1958Magill Herbert LReaction turbines
US3036428 *Dec 16, 1950May 29, 1962Curtiss Wright CorpSelf-feeding rocket motor
US3077075 *Mar 15, 1957Feb 12, 1963Fuad TuranciolRotary radial flow jet engine
US3230719 *May 6, 1963Jan 25, 1966Williams Res CorpFuel governor
US3727401 *Mar 19, 1971Apr 17, 1973Fincher JRotary turbine engine
US4302683 *Mar 7, 1980Nov 24, 1981Burton Von LReaction engine driven electrical generating system with power load variation control capability
US5408824 *Dec 15, 1993Apr 25, 1995Schlote; AndrewRotary heat engine
US5560196 *Mar 10, 1995Oct 1, 1996Schlote; AndrewRotary heat engine
US5660038 *Jan 21, 1993Aug 26, 1997Stone; Joseph WalterRotary jet engine
US7708522Jan 3, 2006May 4, 2010Innovative Energy, Inc.Rotary heat engine
Classifications
U.S. Classification60/39.35, 60/39.11, 60/745, 60/39.821, 60/39.19, 60/39.281
Cooperative ClassificationF02C3/165