US3527055A - Magnetoplasmadynamic jet engine - Google Patents
Magnetoplasmadynamic jet engine Download PDFInfo
- Publication number
- US3527055A US3527055A US721459A US3527055DA US3527055A US 3527055 A US3527055 A US 3527055A US 721459 A US721459 A US 721459A US 3527055D A US3527055D A US 3527055DA US 3527055 A US3527055 A US 3527055A
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- US
- United States
- Prior art keywords
- jet engine
- magnetoplasmadynamic
- compressor
- engine
- motor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K5/00—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
Definitions
- a jet engine comprising a compressor, a combustor and magnetoplasmadynamic means to generate electrical energy for driving the compressor and other auxiliary electrical equipment.
- 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 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.
- 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.
- 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.
- 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.
- FIG. 4 is a corresponding rear view thereof and including a schematic representation of associated electrical circuitry.
- 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.
- the electromagnetic coils 10 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.
- the switchgear 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.
- 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.
- 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.
- a jet engine comprising,
Description
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
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US72145968A | 1968-04-15 | 1968-04-15 |
Publications (1)
Publication Number | Publication Date |
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US3527055A true US3527055A (en) | 1970-09-08 |
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Application Number | Title | Priority Date | Filing Date |
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US721459A Expired - Lifetime US3527055A (en) | 1968-04-15 | 1968-04-15 | Magnetoplasmadynamic jet engine |
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Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3678306A (en) * | 1970-01-15 | 1972-07-18 | Snecma | Jet propulsion power plant |
US4418294A (en) * | 1982-07-02 | 1983-11-29 | Rahman Muhammed A | Supersonic MHD generator system |
US4450361A (en) * | 1982-08-26 | 1984-05-22 | Holt James F | Coupling of MHD generator to gas turbine |
US4663932A (en) * | 1982-07-26 | 1987-05-12 | Cox James E | Dipolar force field propulsion system |
US4891600A (en) * | 1982-07-26 | 1990-01-02 | Cox James E | Dipole accelerating means and method |
US6896480B1 (en) | 2003-06-03 | 2005-05-24 | Hamilton Sundstrand Corporation | Long term storage capable damping system for an expendable gas turbine engine |
US7194866B1 (en) | 2003-06-20 | 2007-03-27 | Hamilton Sundstrand Corporation | Static structure for an expendable gas turbine engine |
JP2012505113A (en) * | 2008-10-08 | 2012-03-01 | シーレイト リミテッド ライアビリティー カンパニー | Hybrid propulsion engine comprising at least one independently rotatable compressor rotor |
US8438858B1 (en) | 2003-08-20 | 2013-05-14 | Hamilton Sundstrand Corporation | Rotational system for an expendable gas turbine engine |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2362283A (en) * | 1942-12-16 | 1944-11-07 | Henry J De N Mccollum | Heating and electrical generating apparatus |
US2404954A (en) * | 1943-02-02 | 1946-07-30 | Westinghouse Electric Corp | Aircraft power plant |
FR999320A (en) * | 1952-01-29 | |||
GB738511A (en) * | 1953-02-28 | 1955-10-12 | Nicholas S Japolsky | Improvements in or relating to internal combustion engines |
US3002383A (en) * | 1956-12-28 | 1961-10-03 | Mittelmann Eugene | Electromagnetic induction flowmeter |
US3201622A (en) * | 1959-03-03 | 1965-08-17 | Nat Res Dev | Generation of electricity |
US3311762A (en) * | 1962-03-13 | 1967-03-28 | Electricite De France | Magnetohydrodynamic generators, particularly in electrodes therefor |
-
1968
- 1968-04-15 US US721459A patent/US3527055A/en not_active Expired - Lifetime
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR999320A (en) * | 1952-01-29 | |||
US2362283A (en) * | 1942-12-16 | 1944-11-07 | Henry J De N Mccollum | Heating and electrical generating apparatus |
US2404954A (en) * | 1943-02-02 | 1946-07-30 | Westinghouse Electric Corp | Aircraft power plant |
GB738511A (en) * | 1953-02-28 | 1955-10-12 | Nicholas S Japolsky | Improvements in or relating to internal combustion engines |
US3002383A (en) * | 1956-12-28 | 1961-10-03 | Mittelmann Eugene | Electromagnetic induction flowmeter |
US3201622A (en) * | 1959-03-03 | 1965-08-17 | Nat Res Dev | Generation of electricity |
US3311762A (en) * | 1962-03-13 | 1967-03-28 | Electricite De France | Magnetohydrodynamic generators, particularly in electrodes therefor |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3678306A (en) * | 1970-01-15 | 1972-07-18 | Snecma | Jet propulsion power plant |
US4418294A (en) * | 1982-07-02 | 1983-11-29 | Rahman Muhammed A | Supersonic MHD generator system |
US4663932A (en) * | 1982-07-26 | 1987-05-12 | Cox James E | Dipolar force field propulsion system |
US4891600A (en) * | 1982-07-26 | 1990-01-02 | Cox James E | Dipole accelerating means and method |
US4450361A (en) * | 1982-08-26 | 1984-05-22 | Holt James F | Coupling of MHD generator to gas turbine |
US6896480B1 (en) | 2003-06-03 | 2005-05-24 | Hamilton Sundstrand Corporation | Long term storage capable damping system for an expendable gas turbine engine |
US6942451B1 (en) | 2003-06-03 | 2005-09-13 | Hamilton Sundstrand Corporation | Damping system for an expendable gas turbine engine |
US7194866B1 (en) | 2003-06-20 | 2007-03-27 | Hamilton Sundstrand Corporation | Static structure for an expendable gas turbine engine |
US8438858B1 (en) | 2003-08-20 | 2013-05-14 | Hamilton Sundstrand Corporation | Rotational system for an expendable gas turbine engine |
JP2012505113A (en) * | 2008-10-08 | 2012-03-01 | シーレイト リミテッド ライアビリティー カンパニー | Hybrid propulsion engine comprising at least one independently rotatable compressor rotor |
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