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Publication numberUS1362997 A
Publication typeGrant
Publication dateDec 21, 1920
Filing dateMay 24, 1919
Priority dateMay 24, 1919
Publication numberUS 1362997 A, US 1362997A, US-A-1362997, US1362997 A, US1362997A
InventorsBoris Koleroff
Original AssigneeBoris Koleroff
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Propelling apparatus
US 1362997 A
Abstract  available in
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)




Patented Dee. 21



T 0 all whom it may concern:

Be it known that I, Boris KoLERoFr, a citizen of the Russian Republic, residing at New York, in the county of New York and State of New York, have invented certain new and useful Improvements in Propelling Apparatus, of which the following is a specification. j

This invention relates to the application of a new principle in the propulsion of flying machines, this principle consisting in utilizing theA reaction generated by jets of a gaseous substance discharged from the apparatus through specially provided nozzles, this reaction being increased-by proper entrainment of the outside air.

The entrainment of the air prevailing within the apparatus by the jets of the gaseous substance is due to viscosity and is'responsible for creation of a continuous vacuum in the apparatus. Because of this partial vacuum the outside air is drawn into the apparatus through specially provided guiding surfaces, which impartv to the mo tion of the outside air a direction coinciding with that 0f the jets. l

The addition of momentum of the outside air and the actuating jets of gas in accordance with the law of conservation of momentum will increase the total momentuin of the discharged gas and air mixture and therefore will increase also the reactive force exerted upon the apparatus and equal to this momentum.

rlhe energy required for the entrainment of air is supplied from the kinetic energyof the actuating gas jets discharged through the nozzles. v y

The apparatus does not contain any movable elements such as propeller, motor parts, etc.

This principle is embodied in vthe new construction, consisting in a combination of different parts, described below and shown on the accompanying drawings, forming the essential features of this vdisclosure and where- Figure 1 is a longitudinal section view taken through a single motor element made in accordance with the invention.l

Fig. 2 is a top plan view showing a conventional type of flying machine and indicating one of the possible applications of this invention. Y

Fig. 3 is a front view of the motor element shown on Fig. 1.

Specification of Letters Patent.

Patented Dec. 21, '1920.

Application tiled May 24, 1919. Serial No. 299,622.

Referring to the drawing, a conventional type of yingniachine is indicated generally by the number 10, the saine being provided with horizontal rudders 11 and vertical rudders 12, while at the front is an observation chamber 13, wings 14, extending equally at both sides of the ying machine as is usual. As one of the possible realizations of the invention in practice, the drawing shows the location of the two motor elements on both sides of the flying machine. Starting with the container 15, holding or generating gas, air, steam or any mixture of gaseous substances under high pressure, follows the pipe 16, regulated by the valve 17, this pipe being provided on its continuation with a tee 18, from which a branching off pipe 19 leads to the rear annular container 38 directly feeding the rear set of nozzles 40. The

-fio` straight' pipe 2O starting from the tee 18 is controlled by a separate valve 21 and ends in an'elbow 22, from which a pipe 23 leads to the front annular container 24, having a stream line form, and feeding the front set of 'nozzles 41. The container 24 is located inside the front guiding surface 26 and fastened by brackets 25 at some distance from the outer end 0f' this guiding surface, the remaining (inside) part of this surface forming the first mixing or entraining chamber 42. The front guiding surface 26 projects into the second guiding surface 27 to a certain depth of the latter, thus forming in the remaining (inside) part of the surface 27 the next mixing chamber 43.` The mixing chambers 44 and 45 are formed in the same wa by the narrow (inside) parts of the gui ing surfaces 28 and 29.

All these guiding surfaces` are succeedingly increasing in their dimensions, having a conical and slightly curved shape and being arranged substantially as shown on Fig. 1. v

The last guiding surface 29, through its 'narrow end 30, provided with a suitable support 31, is directly connected with the diffuser 32.

All these guiding surfaces 26, 27 and 28 `are rigidly connected by a plurality of support bars 33, 34 and 35 to the outer end of the guiding surface 29 in such a way that all thesel conically shaped surfaces have the same axial direction. The rear annular container 38, feeding the nozzles 40, is adjacent with its inside surfaceto the guiding surface 28 while its outer surface is connected at its front end to an annular surface 37, shaped in such a Way as to afford a smoother admission of air to the rear set of nozzles 40.

A plurality of strong jets of gas, dis-V charged with great velocity from the rear set of nozzles 40, will entrain air by viscosity in the mixing chamber 4:5 and create there a continuous vacuum. rlhis vacuum will be sustained also in all other mixing chambers 44, 43 and 42, which are directly connected `with chamber 45. 0nA account of this vacuum inside the apparatus the air will be drawn into it from the outside and will enter the mixing chambers 4t2, 43, LMC and 45 in an axial direction through spaces left between the guiding surfaces. rlhe latter may vary in number. llhe air will be led toward the actuating gas jets, in a direction coincid ing with these jets and will acquire a certain velocity and therefore also a momentum before being actually entrained by the jets. The momentum of the air, already drawn in by the action of nozzles 40, will still be in- I creased through entrainment by the front set of nozzles el. This increase of momentum/.will take place in all mixing chambers and the whole mass of air and gas with this increased momentum will enter the chambers 45. rlhere a further increase will take place 'due to addition of moments: ist of the gas jets from the nozzles e0, and 2nd of the air drawn inv between the guiding surface 29 and the annular surface 37, until finally the total mixture is discharged through the diuser 32. A certain amount of kinetic energy is lost by the mixture while leaving the diffuser as it has to overcome the difference between' the atmospheric pressure outside the apparatus and the vacuum inside of it, this amount being approximately equal to that acquired by the air before its entrain ment by the gas jets. Therefore'the loss of energy by the jets takes place only in the mixing chambers. This loss is due to the entrainment process (excluding the loss dueto friction) and is determined by difference in velocities of the jets and entering air. The degree of vacuum in the apparatus and therefore also the. velocity of the entering' air, will depend upon the proper choice of dimensions for the mixing chambers.

The use of more than one set of nozzles (not necessarily two) will increase the velocity of the entering air. The use of the diffuser will serve .thesame purpose by in-` A creasing to a certain extent the vacuum in the apparatus.

As the velocity of the entering air increases, the difference in velocities between air and actuating gas jets will decrease, and as this difference decreases the eliciency of the apparatus will rise.

IThe principle of the apparatus as described above can be embodied in a number of different ways in practical construe tion. I have already stated that the number of nozzle sets as welles the number of guidlng surfaces may vary. rlhe body of liylng machine itself may be constructed as a single large motor element, drawing in the air Sidewise and discharging the mixture from the rear. Finally the guiding surfaces can be drawn outl along the wings of the flying machine and the apparatus placed inside these wings.` Accordingly the arrangement of nozzles may be changed from an annular to one in a straight line, with a suitable rearrangement of the guiding surfaces. ln this case the wings would 'become the seat not only of a lifting force but of a forwardly directed thrust as well.

lVhile l have explained the use of mv invention in connection with a flying malchine, it will be obvious that the apparatrs may be employed for propelling other movable bodies, or for simply imparting motion to a body of air or other fluid, and l desire propelling device comprising mem-V bers presenting air guiding surfaces and ini closing a mixing chamber therewithin, and successively arranged sets of nozzles arranged in the direction of the axis of the apn paratus, and means for causing a gas to be discharged through the said nozzles.

3. A propelling device comprising memberspresenting air guiding surfaces and inclosing a mixing chamber therewithin, and successively arranged sets of nozzles arrc nged in the direction of the axis of the apparatus, and means for causing a gas to be discharged through the said nozzles and a diffuser f or discharging the: final mixture into the atmosphere.` j

4. A propelling device comprising a plurality of tubular members arrangedin tandem fashion -and spaced at their adjacent ends to form an opening allowing Huid to be entrained, and nozzles arranged both in advance and in the rear of the said opening to act successively on the fluid passing throu h said members.

5. l .propelling device comprising a series of annular air conducting members partially nested one within the other, annular sets of nozzles arranged in tandem in said members, and means for discharging gas from said nozzles.

6. A propelling device comprising a series of longitudinally flared annular air conducting members partially nested one with# in the other with their large ends facing forwardly, a series of annularly arranged nozzles in the forward one of said members, a second series -of nozzles arranged in a rear one of said members, and means for discharging gas from said nozzles.

7. A propelling device comprising a series of longitudinally flared annular air conducting members having their large ends facing forwardly, said members being partially nested within one another whereby a series of mixing chambers are formed at the rear ofthe various members, and means for introducing jets of gas into different ones of said members.

8. A propelling device comprising a series of longitudinally flared annular air conrear one of said members being outwardly flared to form a diifuser.

9. A propelling device comprising a series 'of funnel shaped annular air conducting members nested partially one Within the other'said members being of progressively larger size from the .front to the rear one thereof, an annularly arranged series of nozzles within the front member, an annularly -disposed series of nozzles Within the rear member, and means for supplying gas 'oo' each of said series of nozzles.

In testimony whereof I have aflixed lmy signature.


Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2461797 *Oct 23, 1944Feb 15, 1949Aerojet Engineering CorpReaction propelled device for operation through water
US2651452 *Dec 4, 1946Sep 8, 1953Whims Charles CJet pump for jet propulsive apparatus
US2735261 *Sep 8, 1950Feb 21, 1956 Blast director for fluid streams
US3043102 *Aug 1, 1952Jul 10, 1962Orlin William JInlets
US3046732 *Jun 20, 1956Jul 31, 1962Research CorpMethod of energy exchange and apparatus for carrying out the same
US3070328 *Feb 12, 1958Dec 25, 1962Price Nathan CPropulsion system for aircraft
US3411714 *Oct 19, 1965Nov 19, 1968Dynamit Nobel AgMethod and apparatus for atomizing liquids using the propulsion jet of a rocket engine
US3525474 *Dec 9, 1968Aug 25, 1970Us Air ForceJet pump or thrust augmentor
US4332529 *Jan 28, 1980Jun 1, 1982Morton AlperinJet diffuser ejector
US6457305 *Feb 7, 2001Oct 1, 2002James R. SchierbaumTurbo shaft engine with acoustical compression flow amplifying ramjet
U.S. Classification239/265.17, 60/269
International ClassificationF02K7/00, F02K7/12
Cooperative ClassificationF02K7/12
European ClassificationF02K7/12