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Publication numberUS3527055 A
Publication typeGrant
Publication dateSep 8, 1970
Filing dateApr 15, 1968
Priority dateApr 15, 1968
Publication numberUS 3527055 A, US 3527055A, US-A-3527055, US3527055 A, US3527055A
InventorsRego Jose Dominguez
Original AssigneeRego Jose Dominguez
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Magnetoplasmadynamic jet engine
US 3527055 A
Abstract  available in
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)

Sept. 8, 1970 J. D. REGo 3,527,055

MAGNETOPLASMADYNAMIC JET ENGINE Filed April 15, 1968 2 sheets-sheet 1 FUEL | l l v w? 4 L aways/wei i' {zr/was;-

coMa/J foi ro :mW/anim Mofa/2 Sept. 8, 1970 y l J. D. REGO y y 3,527,055

`MAGNETOPLASMADYNAMIC JET ENGINE Filed AprilI 15, 1968 2 sheets-sheet 2 FUEL j/z/VE'N l71m? dass 17am/Wauw @550 United States Patent Office Patented Sept. 8, 1970 U.S. Cl. 60-224 2 Claims ABSTRACT F THE DISCLOSURE A jet engine comprising a compressor, a combustor and magnetoplasmadynamic means to generate electrical energy for driving the compressor and other auxiliary electrical equipment.`

BACKGROUND OF THE INVENTION The invention relates to an improvement in a jet engine, which improvement eliminates the need for the conventional gas turbine.

A conventional jet engine includes a gas turbine in its exhaust section to generate the power required to drive the compressor as well as electrical power required for auxiliary purposes. The presence of the tunbine, however, limits the efficiency of the jet engine since the heat in the exhaust gases must be kept within a specified limit in order to prevent melting of the turbine blades. Furthermore, the quality of the fuel must meet strict requirements in order to limit the amount and type of solid particles appearing in the exhaust gas and which are harmful to the turbine blades.

The elimination of theturbine from the jet engine removes the present limitations on the heat and quality of the exhaust gases, thereby resulting in increased engine eiciency and permitting the use of cheaper fuels. It also makes possible the construction of a smaller, simpler, more compact and safe jet engine.

SUMMARY OF THE INVENTION A jet engine made in accordance with this invention comprises a compressor driven by an electric motor, a combustor, and a magnetoplasmadynamic means for generation of electrical energy required to power the motor and other auxiliary devices.

An object of this invention is to increase the eiciency of a jet engine by removing the present requirement for limitations on the temperature of the exhaust gas.

An object of this invention is the provision of jet engine suitable for operation with cheaper fuels by removing the present limitations on the quality of the exhaust gases.

An object of this invention is the provision of a jet engine of simple, compact and economical construction, and one which has a longer, more trouble-free operating life than engines of conventional construction.

An object of this invention is the provision of a jet engine wherein the air compressor is driven by an electrical motor, and wherein energy for driving the motor after initial start-up of the engine is developed by a magnetoplasmadynamic device.

The above-stated and other objects and advantages of the invention will become apparent from the following description when taken with the accompanying drawings. It will be understood, however, that the drawings are for purposes of illustration and are not to be construed as defining the scope or limits of the invention, reference being had for the latter purpose to the claims appended hereto.

BRIEF DESCRIPTION OF THE DRAWINGS In the drawings wherein like reference characters denote like parts in the several views:

FIG. 1 is a diagrammatic side view of a jet engine made in accordance with this invention;

FIG. 2 is a corresponding rear view and including a schematic representation of associated electrical circuitry;

FIG. 3 is a diagrammatic side view of a jet engine made in accordance with another embodiment of this invention; and

FIG. 4 is a corresponding rear view thereof and including a schematic representation of associated electrical circuitry.

DESCRIPTION OF THE PREFERRED EMBODIMENT Referring now to the drawings, the numeral 1 denotes an electromagnet encircling the combustor 2. Positioned within the combustor and lying substantially in the median plane of the electromagnet are a pair of electrodes 3. An electric motor 4 is mounted in the compressor 5 and has its drive shaft coupled to the compressor shaft. Switchq gear, generally identified by the numeral 7 comprises suita'ble switches, circuit breakers and electrical metering devices required for the control and distribution of electrical power. One side of the compressor motor is grounded and the other side is connected to the switchgear by the lead 8, whereby the motor can be energized by a voltage source 9 upon the closure of a suita'ble switch of the switchgear. Upon the closure of another switch of the switchgear, the electromagnetic coils 10 are energized through the leads 11, 12 and ground. Other switches of the switchgear control auxiliary electrical equipment con nected to the lead 13. One electrode is connected to the switchgear by the lead 14 and the other electrode is grounded through the lead 15.

The engine is started up by energizing the compressor motor from the external voltage source 9. Once the fuel in the combustor becomes ignited, electrical energy is generated by the magnetoplasmadynarnic device which operates on the principle which requires that the products of combustion be changed into a plasma by injection of seed material into the combustor, or by allowing the combustion to proceed at a high temperature of about 5000 C., thereby causing the gas to become ionized. The gen erated electrical energy is distributed through the switchgear, which facilitates the control and regulation of the energy to the electrical components. More specifically, when the engine is in operation, the switchgear is operated, either manually or automatically in such manner that the power for driving the compressor motor, and for energizingvthe electromagnet and auxiliary devices, is obtained from Ythe magnetoplasmadynamic device. Thus, once the engine has been started it becomes self-sufficient.

A jet engine made in Iaccordance with this invention can comprise a battery of icomibustors as shown in FIGS. 3 and 4. Some of the combustors are equipped with the described magnetoplasmadynamic device fgr the generation of both electrical energy and propulsive thrust. The other combustors are conventional and used only for propulsive thrust. All 0f the combustors are served by a common compressor through air ducts 6 since only one, or several, magnetoplasmadynamic devices generally are sufficient for the generation of all the electrical energy required to power the electrical components of the system. When two or more combustors are provided with magnetoplasmadynamic devices the corresponding electrodes and electromagnetic coils of such devices are connected in parallel.

Having now described the invention -what I wish to protect rby Letters Patent is set forth in the following claims:

1. A jet engine comprising,

(a) a compressor,

3 4 (b) a plurality of combustors arranged to receive References Cited compressed air from the compressor, UNITED STATES PATENTS (c) means for supplying fuel to the combustors,

(d) an electric motor for driving the compressor, 2362283 11/1944 McCollum r* 310""11 2,404,954 7/1946 GOdSey 60--269 (e) means for energlzing the motor from an external r.

0 3,002,383 10/1961 Mlttelmal'l 310-11 voltage source during engine start up,

(f) magnetoplasmadynamic ldevices associated with at 3201-622 8/1965 Thung 60-'202 least one but not all of the combustors, which devices 3311762 3/1967 Crono@ 31o-1 1 are arranged to generate electrical energy upon igni- FOREIGN PATENTS tion of the fuel in the associated combustor, and 10 (g) meansfor energizing the said motor by the elec- 738,511 10/ 1955 Grat Brlam.

trical energy generated by the magnetoplasma- 999,320 10/ 1951 France.

dynamic devices during operation of the engine.

2. The invention as recited in claim 1, wherein the said MARK NEWMAN, Pflmafy Examiner motor is mounted downstreamof the compressor, and 15 D HART, Assistant Examiner wherein the `magnetoplasmadynamic devices comprise an electromagnet encircling the associated combustor, U'S' C1' X'R and electrodes mounted in the associated combustor and 60-202, 269; 310-11 lying in the magnetic field developed -by the associated electromagnet. 20

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2362283 *Dec 16, 1942Nov 7, 1944Mccollum Henry J De NHeating and electrical generating apparatus
US2404954 *Feb 2, 1943Jul 30, 1946Westinghouse Electric CorpAircraft power plant
US3002383 *Dec 28, 1956Oct 3, 1961Eugene MittelmannElectromagnetic induction flowmeter
US3201622 *Feb 29, 1960Aug 17, 1965Nat Res DevGeneration of electricity
US3311762 *Mar 4, 1963Mar 28, 1967Electricite De FranceMagnetohydrodynamic generators, particularly in electrodes therefor
FR999320A * Title not available
GB738511A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3678306 *Jan 14, 1971Jul 18, 1972SnecmaJet propulsion power plant
US4418294 *Jul 2, 1982Nov 29, 1983Rahman Muhammed ASupersonic MHD generator system
US4450361 *Aug 26, 1982May 22, 1984Holt James FCoupling of MHD generator to gas turbine
US4663932 *Jul 26, 1982May 12, 1987Cox James EDipolar force field propulsion system
US4891600 *Apr 30, 1987Jan 2, 1990Cox James EDipole accelerating means and method
US6896480Oct 24, 2003May 24, 2005Hamilton Sundstrand CorporationLong term storage capable damping system for an expendable gas turbine engine
US6942451Jun 3, 2003Sep 13, 2005Hamilton Sundstrand CorporationDamping system for an expendable gas turbine engine
US7194866Jun 20, 2003Mar 27, 2007Hamilton Sundstrand CorporationStatic structure for an expendable gas turbine engine
US8438858Aug 20, 2003May 14, 2013Hamilton Sundstrand CorporationRotational system for an expendable gas turbine engine
U.S. Classification60/224, 60/202, 310/11, 60/269
International ClassificationF02K5/00
Cooperative ClassificationF02K5/00
European ClassificationF02K5/00