US3330238A

US3330238A - Underwater propulsion unit

Info

Publication number: US3330238A
Application number: US382506A
Authority: US
Inventors: John N Ghougasian
Original assignee: Individual
Current assignee: Individual
Priority date: 1964-07-14
Filing date: 1964-07-14
Publication date: 1967-07-11
Anticipated expiration: 1984-07-11

Description

Julyv 11 1967 J. N.' GHQuGAslAN 3,330,238

UNDERWATER PROPULSION UNIT Filed July 14, 1964 5 Sheets-Sheet l l 22 26H /le /2 Fig. 3

/6 26 F'g' /06 /02v Fig. /2 Q02 Jahn N. Ghougasian llllll/l//I l N VE N TOR.

HY @una Attorney:

July l1 1967 J. N. GHoUGAslAN 3,330,238

UNDERWATER PROPULSION UNIT Filed July 14, 1964 5 SheetS-Sheet 2 Fig. 4

iii-

\ i Y Y John N. Gougas/'an I N VE N TOR BY l aaa/way 1f n Attorneys July 1l, 1967 .,1. N. GHouGAslAN l 3,330,238

UNDERWATER PROPULS ION UNIT Filed July 14, 1964 5 Sheets-Sheet Fig. 6

@6 @ff 3P 8,0 Q2

John N Ghougas/'an INVENTOR.

BY 406k.

United States Patent 3,330,238 UNDERWATER PROPULSION UNIT John N. Ghougasian, 666 W. 188th St., New York, NY. 10040 Filed July 14, 1964, Ser. No. 382,506 Claims. (Cl. 114-20) This invention relates to the propulsion of underwater vehicles or vessels including submarines, torpedoes, underwater missiles, as well as propulsion through lluid medium in general.

It is a primary object of the present invention to provide a method for propelling underwater craft capable of generating therewithin Ia source of gas under high pressure and velocity. The underwater craft, vessel, vehicle or missile employing the method of the present invention, is propelled by reaction thrust produced by axial ow of water and exhaust gas in an annular stream about the craft, such axial flow being conducted within an annular shroud xed to the underwater craft and housing therewithin the propelling unit of the present invention.

An additional object of the present invention therefore, is to provide a propelling unit capable of being readily assembled about a tubular portion of the underwater craft within which exhaust gas pressure generating facilities are located. The exhaust gas generating facilities may be produced by ycombustion utilizing either a solid fuel monopropellant or a biopropellant fuel such as liquid fuel and an oxidizer.

A still further object of the present invention in accordance with the foregoing objects, is to provide a propelling unit for an underwater craft or vehicle wherein exhaust ow of gas is utilized to impart rotation to an impeller assembly in order to induce an axial ow of water through flow modulators, and various blade or vane stages rotatable with the impeller assembly producing a reaction thrust operative to propel the craft on which the propelling unit is mounted.

In accordance with the foregoing objects, the propelling unit of the present invention in addition to the facility with which it may be mounted on an underwater craft, is also operative to produce propelling thrust without reliance upon any gearing and the objectionable noise produced incident thereto, The propelling unit may therefore be ideally suited for missile propelling purposes wherein detection by noise produced in the propelling unit is to be avoided. The propelling unit of the present invention, also is capable of more eihciently coping with the heat problem involved in the use of combustion fuel as the source of propelling energy inasmuch as propulsion is produced in connection with the axial ow of water about the combusion chamber within which the exhaust gas under pressure is generated.

These together with other objects and advantages which will become subsequently apparent reside in the details of construction and operation as more fully hereinafter described and claimed, reference being had to the accompanying drawings forming a part hereof, wherein like numerals refer to like parts throughout, and in which:

FIGURE 1 is a side elevation View of the propelling unit of the present invention installed on one form of underwater craft.

FIGURE 2 is a partial front elevational view of the propelling unit as shown in FIGURE 1.

FIGURE 3 is a partial rear elevational View of the propelling unit as shown in FIGURE l.

FIGURE 4 is an enlarged, partial sectional View taken substantially through a plane indicated by section line 4 4 in FIGURE 2.

FIGURE 5 is a partial sectional view taken substantially through a plane indicated by section line 5 5 in FIGURE 4.

FIGURE 6 is a partial transverse sectional view taken substantially through a plane indicated by section line 6 6 in FIGURE 4.

FIGURE 7 is an enlarged partial sectional view taken substantially through a plane indicated by section line 7 7 in FIGURE 6.

FIGURE 8 is an enlarged partial sectional view taken substantially through a plane indicated by section line 8 8 in FIGURE 4.

FIGURE 9 is an enlarged partial sectional view taken substantially through a plane indicated lby section line 9 9 in FIGURE 1.

FIGURE l0 is a partial side elevational View of a partially assembled propelling unit.

FIGURE 11 is a top plan view of another for-m of underwater craft mounting a pair of propelling unit.

FIGURE l2 is a side sectional view taken substantially through a plane indicated by section line 12-.12 in FIGURE 1l.

Referring now to the drawings in detail, and initially to FIGURES l, 2 and 3, it will be observed that the Ipropelling unit generally referred to by reference numeral 10 is mounted on a torpedo 12 as one form of underwater craft. The torpedo accordingly includes a nose portion 14 within which the explosive warhead is contained and a rear guide fin section 16. The propelling unit is mounted about the tubular housing 18 of the torpedo within an annular shroud 20 axially fixed to the housing intermediate the forward and rear secti-ons. The forward end 22 of the shroud will therefore receive an axial inflow of water through a plurality of circumferentially spaced rows of inlets 24 as the torpedo is propelled forwardly. Propelling thrust is produced by the propelling unit by axial discharge of a mixture of exhaust gas and water from the rearward end 26 of the .propelling unit, the lluid being discharged from the rearward end through a plurality of circumferentially spaced rows of outlets Referring now to FIGURES 4, 7 and 9, it will be observed that the annular guide or shroud 20 may be formed of two substantially hemispherical sections 30 to facilitate assembly .and mounting thereof, the sections 30 having overlapping portions 32 forming an externally ush surface and interconnected by a plurality of axially spaced fasteners 34. The inlets 24 at the forward end of the shroud communicate with a plurality of axial

flow modulator sections

36, 38 and 40 on an impeller side of an intermediate portion of the propelling unit. A plurality of axial

ow modulator sections

42 and 44 are in alinement with the outlets 28 on the rear turbine side of the propelling unit. The

modulator sections

36, 38 and 40 are provided with axial ow passages alined with the inlets 24 so as to conduct an axial flow of water through the shroud preventing any vortical flow thereof. Similarly the

modulator sections

42 and 44 are alined with the outlets 28 for conducting axial flow of fluid, the number of axial flow passages associated with the outlets 28 being greater than those associated with the inlets 24 so as to reduce the restriction to flow imposed by the rear modulator sections as compared to the forward modulator section. Flow of water into the forward end of the unit and discharge of a mixture -of exhaust gas and water from the rear end of the unit in order to produce reaction thrust, is produced by rotation of a rotor assembly generally referred to by reference numeral 46.

The shroud 20 is mounted in radially spaced relation to the external housing 18 of the underwater craft so as to accommodate the rotor assembly. The housing 18 may therefore be provided intermediate the ends thereof, with an annular bearing portion 48. The bearing portion is provided adjacent the opposite axial ends thereof, with end portions on which reinforced packing glands 52 are mounted. The end portions 50 are also provided with internally threaded sections S4 are threadedly receiving the retaining collar members 56. Bearings 5S are seated on the collar members 56 adjacent to the packings 52 so as to provide spaced rotatable support for an axially elongated rotor member 60. The rotor may be provided with heat arresting orifice openings 62 through which a restricted flow of water may be conducted in order to maintain the packings S2 moist and thereby protect the bearings 58. Also mounted by the collar members 56 in abutting relation to the flange portions 64 thereof, are thrust bearings 66 between which the elongated rotor 60 is rotatable. The shroud may therefore be secured to the collar members 56 at the forward and

rear ends

22 and 26 by means of the fasteners 68. Fasteners 7) are also provided so as to secure the collar members 56 to the housing 18 of the underwater craft. Referring therefore to FIGURE l0, it will be apparent that the propelling unit may be assembled by initially securing one of the collar members 56 to the housing after it is threadedly assembled to the intermediate bearing portion 48 after which the rotor 60 may be installed against the thrust bearing 66 and over the packings 52 and bearings 58. The other thrust collar 56 may then be threadedly assembled and secured in place. The sections 30 of the shroud may then be 'mstalled about the rotor, and the sections secured together by the fasteners 34 after which the assembled shroud may be secured to the collar members 56 by the fasteners 68.

Referring now to FIGURES 4, 5, 6 and 8, it will be observed that a turbine assembly is secured to the rotor 60 and includes an intermediate section 70 through which rotation of the rotor assembly is induced. The intermediate section therefore includes a plurality of circumferentially spaced flow passages 72 through which exhaust gas under high pressure and velocity is conducted. Conversion of the high internal energy of the exhaust gas into kinetic energy occurs within circumferentially spaced radial nozzle passages 74 formed in the bearing portion 48. It will therefore be apparent, that the ow passages 72 are designed as impulse blading and the cross-sectional ow area of the passages are varied between the radially inner inlets 76 and axial outlets 78 to substantially convert the kinetic energy of the exhaust gases being discharged from the nozzle passages 74 into rotation of the rotor assembly. The intermediate section 70 of the rotor assembly is also provided with circumferentially spaced axial passage 80 so as to conduct the axial flow of water therethrough from the modulator section 38 to the modulator section 40. The intermediate section 70 of the rotor assembly is therefore disposed between the

stationary modulator sections

38 and 40 and is operative to produce rotation of the entire rotor assembly in response to flow of the exhaust gases through the passages 72 therein discharging into the modulator section 40. Flow of water is induced into the propelling unit through the modulator section 36 by rotation of the impeller blades of compressor blade section S2 secured with the intermediate section 70 to the rotor 60, the blade section 82 being disposed axially between the

stationary modulator sections

36 and 38. Axial flow of gas and water from the modulator section 40 on the other hand, is accelerated by the reaction

turbine blade sections

84 and 86 wherein the exhaust gas undergoes a high pressure drop. The reaction blade sections are disposed axially between the

modulator sections

40 and 42 and between the

modulator sections

42 and 44. A mixture of gas and water therefore emerges through the outlets of modulator section 44 to produce a subtsantial axial thrust for propulsion of the underwater craft upon which the propelling unit is mounted.

Any suitable source of exhaust gas under high pressure and velocity may therefore be generated within the underwater craft. In the form illustrated, the exhaust gas is generated within a combustion chamber 88 having radially outer, circumferentially spaced outlet ports communicating with the discharge nozzle passages 74. Any suitable fuel ignition device 92 may therefore be mounted within the craft for igniting the fuel mixture supplied to the combustion chamber through a one-way valve 94 for example. Accordingly, fuel tanks may be disposed on opposite axial sides of the combustion chamber 88 for supply of the fuel mixture to the combustion chamber. For example, the fuel supply may consist of an inner liquid fuel reservoir 96 supplying liquid fuel through the outlet nozzle 98 for mixing with an oxidizer contained within the annular outer compartment 100. It will of course be appreciated, that other exhaust gas generating facilities and fuel supplies may be provided.

From the foregoing description, the construction, utility and advantages of the propelling unit of the present invention will be apparent. The propelling unit may therefore be mounted with ease and facility in view of the described assembly of parts and the complete absence of any gearing or any other mechanical drive connections. The propelling unit may also be readily associated with any fuel supply arrangement and combustion chamber. Accordingly, the propelling unit will also be versatile as to installational location. For example, a pair of propelling units 102 similar in construction and operation to the propelling unit 10, may be mounted about fuel tanks 104 and supported by lateral guide ns 106 secured to the hull 108 of a submarine craft, as shown in FIGURES l1 and l2. The ability of the propelling units to produce thrust in a noiseless and efficient manner will therefore render it ideally suited for underwater propulsion purposes. The propulsion unit could also be adapted for use in other fluid medium such as air.

The foregoing is considered as illustrative only of the principles of the invention. Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the invention to the exact construction and operation shown and described, and accordingly all suitable modifications and equivalents may be resorted to, falling within the scope of the invention as claimed.

What is claimed as new is as follows:

1. In combination with a vehicle having a combustion chamber adapted to discharge gas under high pressure and velocity a propulsion assembly mounted on the vehicle for propulsion thereof in a uid medium comprising, an annular shroud xedly mounted on the vehicle, a plurality of axially spaced ow modulators ixedly mounted wthin said shroud for limiting flow of fluid in axial directions through the shroud, a rotor rotatably mounted on said vehicle within the shroud, impulse turbine means ixedly mounted on the rotor for imparting rotation to the rotor in response to said disch-arge of gas from the ycombustion chamber of the vehicle, impeller lblade means X- edly mounted on the rotor on one axial side of the impulse turbine means between said axially spaced ow modulators for inducing axial flow of the fluid medium into the shroud, and reaction turbine means secured to the rotor on the other axial side of the impulse turbine means between the axially spaced flow modulators for inducing axial flow yof said gas and uid medium out of the shroud to produce axial thrust for the vehicle.

2. The combination of claim 1 wherein the flow modulators on said one side of the impulse turbine means are more restrictive than the flow modulators on the other side.

3. The -combination of claim 2 wherein said impulse turbine means includes impulse passages movable with the rotor for conducting discharge ow of said gas, said impulse passages having radially inner inlets and axial outlets alined with the reaction turbine means, discharge nozzle means xedly mounted in alinement with the inlets and axial passages movable with the rotor and disposed circumferentially between said impulse passages for conducting ilow of uid medium into the reaction turbine means.

4. The combination of claim 1 wherein said impulse turbine means includes impulse passages movable with the rotor for conducting discharge flow of said gas, said impulse passages having radially inner inlets and axial outlets alined with the turbine means, discharge nozzle means fxedly mounted in alinement with the inlets and axial passages movable with the rotor and disposed circumferentially between said impulse passages for conducting flow of Huid medium into the reaction turbine means.

5. In combination with a vehicle having a combustion chamber adapted to discharge gas under high pressure and velocity, a propulsion assembly mounted on the vehicle for propulsion thereof in a liquid medium comprising, an annular shroud ixedly mounted on the vehicle, annular bearing means fxedly mounted on the vehicle radially spacing the shroud therefrom, an elongated rotor rotatably mounted on the bearing means, a plurality vof axially spaced flow modulators xedly mounted within said shroud for limiting flow of uid in axial directions through the shroud, a turbine assembly secured to said rotor for rotation therewith including impulse passages movable with the rotor for conducting discharge 4flow of said gas, said impulse passages having radially inner inlets and axial outlets and axial passages disposed circumferentially between said impulse passages Ifor conducting il-ow of liquid medium through the turbine assembly, nozzle means mounted in the bearing means for establishing fluid communication between said inlets and the combustion chamber in the vehicle, blade means tixedly mounted on the rotor on one axial side of the turbine assembly -between said axially spaced ow modulators for inducing axial iiow of the liquid medium into the shroud, and reaction turbine means secured to the rotor on the other axial side of the turbine assembly between the axially spaced iiow modulators for accelerating flow of said gas and liquid medium out of the shroud to produce axial thrust for the vehicle.

6. In combination with a vehicle having ya gas generator adapted to discharge gas under high pressure and velocity, a propulsion assembly mounted on the vehicle for propulsion thereof in a il'uid medium comprising, annular guide means iixedly mounted on the vehicle for conducting axial ow of fluid, rotor means responsive to said discharge `of gas -for substantially absorbing the kinetic energy thereof and inducing axial ow of the fluid medium through said annular guide means, and reaction turbine means driven by said rotor means within the annular guide means for accelerating said axial flow of tluid to produce axial thrust in response to discharge of said gas and uid medium from the guide means.

7. The -combination of claim 6 wherein said rotor means includes, compressor -blades inducing inilow of said tluid medium into the annular guide means and impulse tur- 'bine means disposed axially Ibetween the compressor blades and the reaction turbine means through which said gas is discharged from the gas generator.

8. The combination of claim 7 wherein the gas generator includes nozzle means radially discharging said gas into the impulse turbine means in axially spaced relation to the reaction turbine means.

'9. The combination of claim 6 wherein the gas generator includes nozzle means radially discharging said ga's into the rotor means in axially `spaced relation to the reaction turbine means.

10. In combination with a vehicle adapted to be propelled through a fluid medium, combustion means for converting the internal energy of a fuel into kinetic energy of combustion products, a rotor, impulse turbine means for substantially absorbing said kinetic energy of the combustion products to impart rotation to the rotor, com- -pressor means driven by the rotor for inducing flow of said fluid medium through the impulse turbine means, and reaction turbine means `driven by said rotor for accelerating said How of tluid medium emerging from the impulse turbine means to impart propelling thrust to the vehicle.

References Cited UNITED STATES PATENTS 1,315,352 9/1919 Torazzi 114-20 2,402,677 6/ 1946 Davenport 60-35.6 X

BENJAMIN A. IBORCHELT, Primary Examiner. P. A. SHANLEY, Assistant Examiner.

Claims

1. IN A COMBINATION WITH A VEHICLE HAVING A COMBUSTION CHAMBER ADAPTED TO DISCHARGE GAS UNDER HIGH PRESSURE AND VELOCITY A PROPULSION ASSEMBLY MOUNTED ON THE VEHICLE FOR PROPULSION THEREOF IN A FLUID MEDIUM COMPRISING, AN ANNULAR SHROUD FIXEDLY MOUNTED ON THE VEHICLE, A PLURALITY OF AXIALLY SPACED FLOW MODULATORS FIXEDLY MOUNTED WITHIN SAID SHROUD FOR LIMITING FLOW OF FLUID IN AXIAL DIRECTIONS THROUGH THE SHROUD, A ROTOR ROTATABLY MOUNTED ON SAID VEHICLE WITHIN THE SHROUD, IMPULSE TURBINE MEANS FIXEDLY MOUNTED ON THE ROTOR FOR IMPARTING ROTATION TO THE ROTOR IN RESPONSE TO SAID DISCHARGE OF GAS FROM THE COMBUSTION CHAMBER OF THE VEHICLE, IMPELLER BLADE MEANS FIX-