US2509359A

US2509359A - Rotary jet engine

Info

Publication number: US2509359A
Application number: US602006A
Authority: US
Inventors: Margolis Isadore
Original assignee: Individual
Current assignee: Individual
Priority date: 1945-06-28
Filing date: 1945-06-28
Publication date: 1950-05-30
Anticipated expiration: 1967-05-30

Description

May 30, 1950 l. MARGoLls 2,509,359

` ROTARY JET ENGINE E Filed June 2a, 1945 5 sheetsrsheet 1 [5a/riore 'Ma VyOZz'a lvlayt'o, 1.950 l l. 'MRGOLIS 2,509,359

ROTARY JET ENGINE Filed June 2a.' 1945 asuma-shen- 2 I 5 .f Q 5.

May 30, 1950' l. MARGoLls ROTARY JE'1` ENGINE ?1ed,Jue 28, 1945 5 Sheets-Sheet 4@ SLM www A[uere Ma l. MARGOLIS ROTARY JET ENGINE 5 Sheets-Sheet 5 Filed Jun@ 28, 1945 latented May 30, 1950 UNITED STATES PATENT OFFICE ROTARY JET ENGINE Isadore Margolis, Baltimore, Md.

Application June 28, 1945, Serial No. 602,008

3 claims. l

This invention relates to iet engines.

An object of this invention is to provide a multiple jet engine having the jets radially arranged and supported for rotation about a central bearing,

A further object of this invention is to provide an engine of this type which is of relatively simple construction and provides for building up of fluid pressure in proportion to the speed of rotation of the device.

To the foregoing objects, and others which may hereinafter more fully appear, the invention consists of the novel construction, combination and arrangement of parts, as will be more specifically referred to and illustrated in the accompanying drawings, but it is to be understood that changes, variations, and modifications may be resorted to which fall within the scope of the invention as claimed.

In the drawings:

Figure 1 is a detail front elevation, partly broken away, of a combined jet engine and propeller constructed according to an embodiment of this invention.

Figure 2 is a sectional view taken on the line 2--2 of Figure 1.

Figure 3 is a fragmentary sectional view taken on the line 33 of Figure 2.

Figure 4 is a fragmentary sectional view taken on the line 4-4 of Figure 2.

Figure 5 is a fragmentary sectional view of one of the fuel jet members.

Figure 6 is a plan view of a modified form of this invention.

Figure '7 is a fragmentary sectional view taken on the line l--l of Figure 6.

Figure 8 is a fragmentary sectional view taken on the line 8-8 of Figure 6.

Figure 9 is a detail side elevation oi.' one of the jet housings.

Figure 10 is a fragmentary sectional view, partly in detail, of the rotary fuel feeder.

Figure il is a fragmentary sectional view show ing a portion of the impeller and a means for securing the impeller to the rotary housing.

Referring to the drawings the numeral I5 designates generally a hub housing structure which is constructed of complementary housing members, including a front plate I8 having a longitudinal ilange il, and diametrically opposite bosses I8. A pair of semi-annular housing members I9, formed with flanges 20, are secured together rearwardly of the housing member IE and are provided with forward flanges confronting the flanges I1 and secured thereto by fastening members 2l.

The housing I5 has mounted therein the outer race 22 of an anti-friction bearing, the inner race 23 being secured to a stationary hub structure generally designated as 24. The stationary hub structure 24 includes an annular flange 25 formed with openings 2E by means of which the flange may be secured to a stationary support and a cylindrical bushing 21 extends forwardly from the flange 25 and abuts against the inner race 23. The inner race 23 is mounted about a cylindrical air intake housing 28 which is formed with a forward or inner flange 29 against which the inner race 23 is adapted to abut. The bushing 21 is threaded on the housing 28 and tightly binds the inner race 23 against the flange 29,

The intake housing 28 includes a rear wall 30 formed integral with the cylindrical side wall of housing 28 and an air conducting nipple 3| extends from the rear wall 30. A tubular member 32 is connected at one end to the nipple 3l, and at the other end to the coupling 33 which is carried by the rear end of a tubular member 34. The tubular member 34 is threaded into a central opening 35 formed in the rear wall 30 and an axially disposed jet 36 is carried by the inner end of the tubular member 34. A fuel reservoir 31 extends downwardly from the tubular member 34, and has a suction pipe 38 extending downwardly thereinto to a point close to the bottom wall 39 thereof and the pipe 38 is then extended upwardly and forwarded on an obtuse angle, as` indicated at 40 and terminates Within the tubular member 34. In this manner the forwardly moving air in the tubular member 34 will draw in fuel which rises in the fuel pipe 3B.

A threaded plug 4I is threaded into the rear end of the pipe or tubular member 34. The housing I5 includes oppositely disposed bosses or hub members I8 which are adapted to tightly clamp the inner ends of radially arranged and oppositely extending hollow arms 42. The arms 42 are provided with enlarged inner ends 43 engaging in an annular recess 44 formed in each of the hubs or bosses I3, so that the arms 42 will 'be tightly clamped to the housing I5. The arms 42 are hollow and are provided on their leading sides with an elongated air intake opening or scoop 45. The air is adapted to enter the openings 45 and then move radially inwardly through the arms 42 into the interior of the housing i5. An impeller, generally designated as 46, is mounted centrally of the housing I5, and includes a plurality ci impeller blades 41 secured to a hub 48, and having an outer ring 49 xed relative thereto and firmly secured in the housing I5. The hub 48 is provided with a central bore 50 through which the forwardly moving combined air and gases are adapted to pass and the rear end of the hub 48 is of tapered construction, as indicated at 5I, and rotatably engages a tapered seat 52 formed in the forward end of a bushing 53 which engages about the jet 35.

The combined air and gases which move forwardly in the bore 50, are then adapted to pass through a nipple 54 threaded into the forward end of the impeller hub 48 andthe nipple 54 has extending at right angles therefrom, nipples 88. The gas conducting tube 58 extends axially through the arms 42 and is connected to a nipple 88 by means of a coupling 51. Each arm 42 has secured to the outer end thereof, a substantially ovoidal combustion housing 58 which is closed at its leading end and has connected to the rear or trailing end thereof a substantially conical discharge member 59. The discharge member 88, as shown in Figure 3, has formed integral with the forward end thereof, a trailing end portion 88, of the housing 58, which is threaded into the housing 58, as indicated at 6|. The conical discharge member 59 forms a Venturi tube with the housing 58 so that the exploded gases may be discharged and may expand as they are discharged for forcing the arms 42 to rotate and to carry therewith the housing I5.

The outer ends of the gas conducting tubes 88 are connected to a gas discharge nozzle 62 which is threaded through the housing 58. The nozzle 62, which is shown in greater detail in Figure 5, includes a housing, generally designated as 88, which is formed of a threaded cylindrical body 84 having both internal and external threads whereby the body 64 may be threaded into the housing 58. An annular flange 65 extends from the inner end of the body 64, and is adapted to abut against the outer side of the housing 58. A substantially conical nipple 66 extends inwardly from the ange or nut member 85 and is formed with a tapered valve seat 61 against which a ball valve 68 is normally held by means of a spring 68. The nipple 66 is formed with a central passage or bore 18 which is normally closed when the valve 68 is seated. A let` member 1|, which is formed with a cylindrical body 12, is threaded internally of the body 64, and is provided with va jet opening 13 through which the unburned gases are adapted to be discharged into the housing 58. The spring 68 bears at its upper end against the nozzle 1I and the spring 69 may be tensioned by inward threading of the body 12. Fuel, which is discharged into the combustion chamber 14 formed in the ovoidal housing 58, is adapted to be ignited by means of an igniter 15 in the form of a spark plug. The spark plug 15 has connected thereto a conductor 18 which extends through the arm 42 and is connected to a commutator ring 11 carried by the rear end of thevhousing I5. The commutator ring 11 is insulated from the rear end of the housing I5, by means of an insulating ring 18. A contact member 19 is carried by the flange 25 and connected through a conductor 88 to a source of electric current supply preferably at high tension so that a spark will be generated between the opposed electrodes of the spark plug 15.

The forward side of the housing member I6 has extending therefrom a centrally disposed bolt 8| which is fixed relative to the housing member I6. The hub 82 of a propeller blade structure 83 is mounted on the bolt or shaft 8|, and secured thereon by means of a nut 84 threaded on the bolt or shaft 8|. A washer 85 is interposed between the nut 84 and the hub 82. Preferably the blades of the propeller 83 are disposed at right angles to the arms 42, as shown in Figure 1.

Referring now to Figures 6 to 11 inclusive there is disclosed a modified form of this invention. The engine shown in Figures 6 to l1 inclusive includes a rotary housing Ia which is similar to the housing I5, and which has mounted on the radial boss|8a thereof, the inner ends of a pair ofhollow 'radial arms 42a. The arms 42a are provided with annular ribs 88 engaging iny annular channels 81 formed'in the boss Ila so that the arms 42a will be held against endwile monment. The housing Ila is rotatably mounted on a stationary housing member 88, including a cylindrical body 88 having a forward ange 88 formed with openings 8| for bolted securing of the housing 88 to a stationary support 88a. An anti-friction bearing 82 is interposed between the rear end of the housing Ila, and an inner intake housing 88 of cylindrical configuration. which is similar to the air intake housing 28. The air intake housing 98 has mounted in the forward end thereof impeller blades 84, having a cylindrical outer rim 85. The rim v98 is secured. relative to the housing I5a, by means of set screws 88, as shown in Figure 11. y

The housing 88 includes a rear wall 81 having a rearwardly tapering discharge opening 88 communicating with a pipe 88. The pipe 88 is oonnected to a threaded nipple |88 carried by the rear wall 81 by means of a coupling member III. An L-shaped connector |82 is connected at one side thereof by means of a coupling |88 to the rear end of the air conducting pipe 88 and the other side of the coupling member |82 is connected to a housing |84. The housing |84 is disposed rearwardly of the housing 88 and is connected thereto by means of a threaded connector |85.

The connector I 05 is formed with a central bore |86 through which the air is adapted to pass. The housing |84 includes an `air chamber |81 having an adjustable needle valve |88 disposed therein, which is adjustable relative to a needle valve seat |89. The needle valve |88 is adjust. able by means of a hand1e.||8, extending from the rear' wall I I I of the housing 88. The housing 98 has extending axially from the rear wall 81 thereof, a bushing |I2 formed with a rear wall I3, with which the coupling member is oonnected. The fuel conducting member I I4 is connected at one end to the housing or bushing II2, and communicates with a fuel passage II8 formed in the bushing |I2 and communicates with the interior thereof. The connector I|4 is connected at the rear end thereof to the housing |84 and communicates with a fuel passage II8 formed in the housing |84, which passage is regulated by means of an adjustable needle valve The housing |84 is formed with a fuel chamber I|8 and the fuel supply pipe ||9 is in cbmmunication through a passage |28 with the fuel chamber I8. The impeller 94 includes a central hub |2| formed with a rearwardly extending tapered member |22. An elongated externally threaded fuel forcing or feeding member |28 extends from the rear end of the tapered member |22 and is loosely mounted within the bushing II2. The feeding member |23 has the rear end thereof spaced from the rear wall II3, and the rear end of the feeding member |23 is formed with a recess |24 which communicates with an axial bore |25 extending through the feeding member |23, the tapered member I 22 and the hub I2I. An air nozzle |26 is carried by the connector |85 and extends loosely in the bore |25 and is adapted to discharge air centrally in the bore |25 which forwardly of the nozzle |28 forms a mixing chamber.

As shown in Figures 6 and '1, the arms 42a. have mounted on the outer ends thereof, angularly disposed jet housings |32. The housings |32 include a dome-shaped nose I 33 threadably mounted in a hollow body |34 and a rearwardly flared discharge member |35 communicates with the rear end of the housing |32 and forms a venturi by means of which the exploded gases may expand. The interior of the discharge member |35 is lined by means of a lining |35 and the rear end portion of the housing |34 is also lined as at |31. The linings |36 and |31 are preferably formed of metal which will not readily burn under extreme heat.

The arms 42a are each provided with an intake opening |38 on its leading side adjacent the housings |32, and the opening |38 may have a grill i3!! thereon to prevent large particles from entering the interior of the radial arms 42a. Each arm 42a, also has disposed in the outer end portion thereof, a plurality of inwardly extending arcuate baffles |40 by means of which the incoming air will be directed toward the inner ends of the arms 42a, as these arms rotate or swing.

In the use and operation of this device and referring particularly to Figure 2, the housing structure I5 may be initiallyrotated by suitable power means which will give the device an initial start. As air is drawn into the openings 45, and this air forced through the intake housing 28 by the impeller blades 41, fuel will be drawn through the fuel pipe 38 into the mixing member 34, and this fuel then discharged into the duct or bore 50. As the fuel passes'outwardly through the conducting members 56 this fuel will force the ball valve 68 to unseat and discharge the fuel into the combustion chamber 14. The igniter 15 will ignite the fuel in the chamber 14 which will then discharge through the venturi 59 and the expansion of the discharged fuel or burned gases will effect rotation of the device.

The structure shown in Figures 6 to 1l inclusive will operate in the same manner as the structure shown in Figures 1 to 5, with the exception that in Figures 6 to 11 inclusive the inner ends of the propellers 83a are secured to radial bosses |4| formed on the housing |5a at right angles to the arms 42a. The fuel which is forced outwardly through the fuel conducting pipes |30 and I3| is discharged into the combustion chamber |42 formed in the housing |32 through a jet member |43. The fuel in thecombustion chamber |42 is ignited by means of an igniter |44which is connected by means of a conductor |45 to a commutator ring |46. 'I'he commutator ring |46 is engaged through a contact member or wiper |41 carried by a housing |48 which is fixed relative to the flange 90 and the conductor |40 is connected to the contact |41 and to a source of electric current supply.

What is claimed is:

l. A jet engine of the kind described comprisin a supporting member, a rotatable housing member carried by said supporting member, oppositely extending hollow arms on said housing member. an ovoidal combustion chamber carried by the outer end of said arms, said arms having an air intake opening adjacent the outer ends thereof, a mixing chamber in said supporting member, impeller blades carried by said housing member forcing air from said arms into said mixing chamber, jet means discharging fuel into said mixing chamber for mixture with the air in said chamber, means conducting the fuel charge to said combustion chamber, and means igniting the fuel charge in said `combustion chamber, said fuel discharging means including a cylindrical housing in said supporting member, an elongated fuel feeding member xed on said rotatable housing rotatable in said cylindrical housing, said fuel feeding member formed with an axial bore therethrough and an air jet xed to said supporting member extending into said cylindrical housing for mixing the fuel and air therein.

2. A jet engine 'of the kind described comprising a supporting member, a rotatable housing member carried by said supporting member, oppositely extending hollow arms on said housing member, an ovoidal combustion chamber carried by said arms, said arms having an air intake opening adjacent the puter ends thereof, a hub on said housing member having an axial bore therein, a mixing chamber in said supporting member, means conducting the fuel charge to said combustion chambers, a bushing in said supporting member, said housing member having a tapered member engaging in said bushing, said tapered member formed with a bore therethrough communicating with said mixing chamber and said conducting means, and means igniting said charge in said combustion chambers.

3. A jet engine comprising an annular supporting member, a forwardly opening air intake opening in said supporting member, a concentric `forwardly opening tapered bushing in said houssaid arms formed with an air intake opening adjacent the outer ends thereof, an ovoidal combustion chamber carried by said arms, a. hub on said housing member, a tapered member on said hub extending into said bushing, impeller blades fixed on said hub adjacent said supporting member for forcing air into said intake opening in said supporting member, said hub formed with a concentric bore communicating with said mixing chamber, means conducting the fuel charge from said mixing chamber to said combustion chambers, and means igniting said fuel charge in said combustion chamber.

ISADORE MARGOLIS.

REFERENCES CITED The following references are of record in the file of this patent: