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Publication numberUS2486990 A
Publication typeGrant
Publication dateNov 1, 1949
Filing dateJan 4, 1945
Priority dateJan 4, 1945
Publication numberUS 2486990 A, US 2486990A, US-A-2486990, US2486990 A, US2486990A
InventorsSharpe Catherine D
Original AssigneeFranklin Inst Of The State Of
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Jet propulsion motor
US 2486990 A
Abstract  available in
Previous page
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Claims  available in
Description  (OCR text may contain errors)

Nov. 1, 1949 J. s. SHARPE JET PROPULSION MOTOR Filed Jan. 4, 1945 Patented Nov. 1, 1949 I ET PROPULSION MOTOR John 8. Sharpe, Haverford, Pa.; Catherine D.

Sharpe, executrix of said John S. Sharpe, deceased, assignor to The Franklin Institute of the State of Pennsylvania for the Promotion 01 the Mechanic Arts, Philadelphia, Pa., a corporation Application January 4, 1945, Serial No. 571,324

1 Claim. 1

This invention relates to improvements in jet propulsion devices. and a principal object of the invention is to provide means for avoiding certain limitations inherent in prior applications of the jet propulsion principle and to thereby provide a device capable of taking advantage in fuller degree of the potentalities of said principle.

The foregoing, and other incidental objects of the invention hereinafter appearing, may be attained by means of the devices illustrated in the attached drawing, wherein:

Figure 1 is a front elevational and partial sectional view of a jet propulsion motor made in accordance with my invention;

Figure 2 is a section on the line 2-2, Figure 1;

Figure 3 is a section on the line 3-3, Figure 1;

Figure 4 is a section on the line 4-4, Figure3;


Figure 5 is a fragmentary view in perspective of the motor unit illustrating a detail of construction.

With reference to the drawing, the engine comprises a hollow shaft l upon which is mounted a housing structure 2 which contains the jet generating elements. The housing 2 comprises a centrifugal pump or compressor section designated generally by the reference numeral 3 and consisting of a plurality of radially disposed blades 4 which terminate at their inner ends in a laterally disposed annular intake port 5 and at their outer ends in a laterally disposed annular compression manifold 6. Air is admitted to this compressor section through the port 5 and is compressed by centrifugal action into the manifold 6.

Suitably attached to the housing 2 is a plurality of combustion chambers 8, these chambers being three in number in the present instance and being uniformly distributed about the shaft axis as shown in Figure 1. Each of these chambers communicates with the manifold 6 through a gardless of the position of the valve.

Each of the chambers 8 is provided with two discharge nozzles designated respectively by the reference numerals l5 and i5. Each of these nozzles, in the present instance, is generally of funnel formation, increasing slightly in diameter towards its outer end as best illustrated in Figure 3. The longitudinal axis of the nozzle l5 lies preferably in a plane which parallels the plane of rotation of the housing 2; while the axis of the nozzle l6 extends at an angle of approximately degrees to the axis of the nozzle 15 in the direction of the axis of rotation of said housing. Discharge of gases from the nozzle is will thereby exert a reaction force in a tangential direction tendingto rotate the housing 2 about its axis in the shaft I; while the force exerted by gases discharging at high velocity through the nozzle IE will have components tending respectively to rotate the housing about its axis and to displace the housing in the axial direction.

The connection of nozzles l5 and IS with the interior of the chamber 8 is controlled by a rotary valve element li' which may be moved through a lever arm l8 to open or close the nozzles selectively, the arrangement being such that either of the nozzles may be opened to the exclusion of the other, or both opened in part and in variable relative degrees to permit'escape of gases from the combustion chamber 8.

It will be noted by reference to Figure 3 that the valve 11 is provided with a port IQ for registration with the nozzles l5 and i6, and with a port 2! which registers with the air intake port 9 re- The valve element also comprises a slot 22 through which the spark plug H and the nozzle l3 project and which provides for movement of the valve element without regard to said plug and nozzle. It

port 9. Each of the chambers is also providednected with a source of fuel supply, a source of compressed air, and means for igniting the said fuel.

will be noted by reference to Figures 1 and 2 that the arms I 8 of the respective valves are connected by links 23 with an adjusting ring 24 which is suitably mounted for rotational adjustment on the housing and which may be operatively connected with a servo-motor 25 through the medium of a pinion 26 on the motor shaft, and a cooperating rack 21 at the inner periphery of the said ring. The motor 25 is mounted on the housing 2 and affords a means for adjusting the ring 24 from a remote point,

It is proposed to provide the housing 2 with a suitable streamlining cowl 28 which may be shaped generally as illustrated in Figures 2 and 5. Since the nozzles l5 and I6 terminate in this cowl as shown in Figure 5, the ends of the said ports are shaped to conform to the contour of the cowl at the points of intersection.

In operation, the compressor 3 continuously discharges compressed air into the chambers 8 and fuel is continuously admitted through the nozzles l3. Combustion is initiated by means of the spark plugs II but after ignition has once taken place, the combustion also is continuous. The heat of combustion acts to greatly expand the compressed air in the combustion chambers and the highly compressed gases issue from the chambers through one or both of the nozzles l5 and I 6 in the form of high velocity jets which by reaction, in known manner, exert a propulsive force upon the housing 2. when the jets are discharged through the nozzles l6 this propulsive force will be exerted in a plane normal to the rotary axis of the housing structure and in a direction in each case substantially at right angles to a line in said plane radial to said axis, so that substantially the entire tome is utilized to effect rotation of the structure. When, on the other hand, the jets issue from the nozzles 16, the direction of discharge of each individual jet is such as to create a component tending to displace the structure in the axial direction, a second com.- ponent tending to rotate the structure about the axis as aforesaid.

The device as illustrated is applicable, for example, to an airplane propeller drive wherein the propeller is fixed to the housing structure 2 to rotate with this structure. When the nozzles 45 are employed as described above to the exclusion of the nozzles it, the entire reaction force of the discharge jets is utilized to rotate the propeller in the normal manner. Under the circumstances where jet propulsion is desirable the discharge may be shifted to the nozzles it, whereupon the jets function to propel the airplane, the component of the jet which maintains rotation of the structure being primarily for the purpose of driving the compressor which is required for operation of the jet device as described above.

Since the interior walls of the chambers 8 and valve ll may be lined with a ceramic or other material capable of withstanding high temperak 4 tures for extended periods of time, the device avoidsthe limitations imposed on prior jet propulsion devices arising from the inability of driven parts of the mechanism, such as turbine blades, to withstand the excessive temperatures developed in the combustion chamber for any extended period of time.

It will be understood that the device is subject to material modification without departure from the invention. It is not essential, for example, that the air compressor which is associated with the rotary housing structure 2 be of the centrlfu-' gal type herein illustrated as it may take other 7 forms well known in the art.

I claim:

In a jet propulsion motor, a rotary structure having an annular manifold, a centrifugal impeller in said structure operative by rotation of the latter to supply compressed air to said manifold. a plurality of combustion chambers each connected to said manifold, means for continuous supply of fuel to said combustion chambers, and means for continuously discharging compressed gas from the combustion chambers in a direction to efiect reactive rotation of said structure.


manners err The following references are of record in the file-of this patent:

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Patent Citations
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US855165 *Apr 13, 1906May 28, 1907William Otis CutterDevice for propelling and steering vessels.
US2001529 *Jan 22, 1934May 14, 1935Claude DornierRotor for helicopters
US2024274 *Aug 30, 1932Dec 17, 1935Campini SecondoReaction-propulsion method and plant
US2220066 *Jul 27, 1938Nov 5, 1940Cornell Jr Edward SLiquid fuel burner unit
US2356746 *Feb 26, 1942Aug 29, 1944Boushey Homer AJet propulsion device
FR457182A * Title not available
GB227151A * Title not available
GB439805A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2605608 *Jun 27, 1946Aug 5, 1952Barclay Jr Frank DJet reaction motor
US2709895 *Jul 22, 1949Jun 7, 1955Mount Wadsworth WJet thrust burner power generator
US2943816 *Jul 6, 1954Jul 5, 1960Hiller Aircraft CorpVertical take-off high-speed aircraft
US3680308 *Jun 29, 1970Aug 1, 1972Ward A St JohnInternal combustion turbine engine
US5660038 *Jan 21, 1993Aug 26, 1997Stone; Joseph WalterRotary jet engine
US5709076 *Jun 7, 1995Jan 20, 1998Lawlor; Shawn P.Method and apparatus for power generation using rotating ramjet which compresses inlet air and expands exhaust gas against stationary peripheral wall
US6298653Mar 9, 2000Oct 9, 2001Ramgen Power Systems, Inc.Ramjet engine for power generation
US6334299Dec 16, 1997Jan 1, 2002Ramgen Power Systems, Inc.Ramjet engine for power generation
US6347507May 25, 1999Feb 19, 2002Ramgen Power Systems, Inc.Method and apparatus for power generation using rotating ramjets
US6405703Jun 29, 2001Jun 18, 2002Brian SowardsInternal combustion engine
US6434924Mar 9, 2000Aug 20, 2002Ramgen Power Systems, Inc.Ramjet engine for power generation
US6446425Jun 17, 1999Sep 10, 2002Ramgen Power Systems, Inc.Ramjet engine for power generation
US6907723Oct 10, 2003Jun 21, 2005David HaskinsPulsed turbine rotor engine
WO2011131733A2Apr 20, 2011Oct 27, 2011Desaulniers Jean-Marc JosephVertical take-off and landing multimodal, multienvironment, gyropendular craft with compensatory propulsion and fluidic gradient collimation
WO2013060693A2Oct 23, 2012May 2, 2013Desaulniers Jean-Marc JosephActive geometric exoskeleton with pseudo-rhombohedral annular fairing for gyropendular craft
U.S. Classification60/39.35, 60/39.34, 60/201, 60/39.78
International ClassificationF02K7/00
Cooperative ClassificationF02K7/005
European ClassificationF02K7/00D