US3149459A - Electric arc type propulsion motor - Google Patents

Electric arc type propulsion motor Download PDF

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US3149459A
US3149459A US830509A US83050959A US3149459A US 3149459 A US3149459 A US 3149459A US 830509 A US830509 A US 830509A US 83050959 A US83050959 A US 83050959A US 3149459 A US3149459 A US 3149459A
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electrode
working fluid
liquid
cavity
arc
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Ulam Juliusz
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00—Using plasma to produce a reactive propulsive thrust

Definitions

  • Electric arc type propulsion is based on the transformation of electric energy into kinetic energy and the type of motor depends on the process employed to bring about this transformation.
  • electrothermic jet motors the ejected body, said working fluid, is heated electrically.
  • the conversion of the thermal energy transmitted to the working fluid into kinetic energy is then obtained by expansion, according to the usual process.
  • the electric energy simply replaces the chemical energy usually employed in the jet engines to bring the working fluid to a high temperature.
  • the electric ram-jet engines in which air is used as the working fluid, as well as electric rocket motors utilizing a Working fluid contained in tanks.
  • the most eifective means of heating the working fluid is to employ an electric arc, which permits attainment of very high temperatures, impossible to obtain by any other way.
  • the object of the present invention is to provide a device in which the working fluid is supplied through the inside of the electrode or over its surface to the surface on which it is abruptly transformed in vapor, the latter being superheated and ejected at a high velocity.
  • the liquid arrives, preferably parallel to the surface of the foremost part of the electrode, which presents a footing of the arc; the attachment of the arc to the surface of the foremost part of the electrode is due to the locally reduced heat of evaporation and to the lower value of the work of entry of electrons into the liquid.
  • any liquid can be utilized as the working fluid, preferably however a conducting liquid, such as the mercury or an amalgam, a liquid alloy or water acidified or containing some salts.
  • the liquid can arrive on the surface of the foremost part of the electrode through a porous zone or along several flow passages which provide for its arrival parallel to this surface.
  • the attachment of the are on the surface of the electrode spot can be facilitated by a rod of a refractory material placed in the mass of the liquid and having the form e.g. of a point or ring.
  • the cavity by which the liquid arrives can possess the form of a small canal disposed in the axis of the electrode and containing a central rod surrounded by a helical spiral forming the flow passage or a similar arrangement; it can be also constituted by a piece of porous carbon or carbon containing a great number of small canals.
  • FIG. 1 represents a section of a simple form of the essential part of the device.
  • the FIG. 2 represents a section of a form of the whole device.
  • FIGS. 3, 4 and 5 represent three embodiments of the cavity conducting the product to the surface of the foremost part of the electrode.
  • the electrode 1 and the socket 2 provided 3,149,459 Patented Sept. 22, 1964 with a helical canal 3, form a helical flow passage for the liquid which arrives, through the canal 4, to the cavity 5.
  • the liquid is abruptly transformed into vapor by the action of the electric arc, this vapor then being superheated and ejected at a high velocity through the nozzle 7 in the other electrode 7a.
  • Electrode 12 Electrical energy to form the electric arc is provided by energy source 12. As shown in FIG. 1, conducting leads 13 and 14 connect electric energy source 12 to electrodes 1 and 7a, respectively.
  • the liquid, passing through the canal 4 attains the cavity 5, inside of which there is a central rod 10 surrounded by a helical spiral 11; the arrangement composed of the last two parts forms a second helical flow passage which conducts the liquid in such a way as to make it emerge on the surface of the foremost part of the electrode 1 almost parallel to this surface.
  • Electrodes 1 and 7a are insulated from each other by a suitable insulating material 15.
  • FIGURE 3 represents an enlarged sectional view of the second helical flow passage according to FIGURE 2.
  • FIG. 4 represents a section of a drawn rod 16, which can be employed instead of the arrangement described above, to form the second helical flow passage.
  • FIG. 5 represents a section of an arrangement in which the liquid arrives on the surface of the electrode passing through porous walls 18 surrounding the central rod 17.
  • a device for electric jet propulsion characteristic in that the working fluid is supplied to the surface of the electrode through the interior or along the surface of the latter, and transformed abruptly in vapor which is superheated and ejected at a high velocity.
  • the liquid is supplied to the surface of the foremost part of the electrode through several flow passages which cause the liquid to arrive so that it emerges on the surface almost parallel to the surface.
  • the flow passage conducting the liquid to the surface of the foremost part of the electrode is formed by a cylindrical rod surrounded by a helical spiral.
  • the flow passage is formed by a drawn rod.
  • a piece of a refractory material is placed, having, e.g., a form of a point or of a ring.
  • An electrothermic jet motor comprising, in combination, an arc chamber, a first and second electrode disposed in said arc chamber, said electrodes being in line 3 4 with each other and separated by a gap to provide an arc 1,978,424 Gebhard Oct. 30, 1934 discharge therebetween, an inlet for a working fluid, a 2,052,796 Rava Sept. 1, 1936 cavity in said first electrode located in the foremost part 2,459,286 Rabezzana Jan. 18, 1949 of said first electrode adjacent said gap, passageway means 2,587,331 Jordan Feb. 26, 1952 for transporting said Working fluid from said inlet in o 5 2,731,079 Smits Jan. 17, 1956 said cavity and adapted to promote heat exchange be- 2,774,216 Allen Dec.

Description

Sept. 22, 1964 J. ULAM ELECTRIC ABC TYPE PROPULSION MOTOR Filed July 30, 1959 Tia. 5
J INVENTOR.
JUL/0S2 w nrropmsrs United States Patent 3,149,459 ELECTRIC ARC TYPE PROPULSION MOTOR Juliusz Ulam, 20 Rue de Varenne, Paris, France Filed July 30, 1959, Ser. No. 830,509 3 Claims. (Cl. 60-35.5)
Electric arc type propulsion is based on the transformation of electric energy into kinetic energy and the type of motor depends on the process employed to bring about this transformation.
In electrothermic jet motors the ejected body, said working fluid, is heated electrically. The conversion of the thermal energy transmitted to the working fluid into kinetic energy is then obtained by expansion, according to the usual process. In this case, the electric energy simply replaces the chemical energy usually employed in the jet engines to bring the working fluid to a high temperature. Based on this principle it is possible to design the electric ram-jet engines, in which air is used as the working fluid, as well as electric rocket motors utilizing a Working fluid contained in tanks. The most eifective means of heating the working fluid is to employ an electric arc, which permits attainment of very high temperatures, impossible to obtain by any other way.
The problems arising in such case are the method of supplying working fluid as well as the form of arc discharge.
The object of the present invention is to provide a device in which the working fluid is supplied through the inside of the electrode or over its surface to the surface on which it is abruptly transformed in vapor, the latter being superheated and ejected at a high velocity.
The liquid arrives, preferably parallel to the surface of the foremost part of the electrode, which presents a footing of the arc; the attachment of the arc to the surface of the foremost part of the electrode is due to the locally reduced heat of evaporation and to the lower value of the work of entry of electrons into the liquid.
Any liquid can be utilized as the working fluid, preferably however a conducting liquid, such as the mercury or an amalgam, a liquid alloy or water acidified or containing some salts.
By a convenient choice of the form of the flow passages conducting the liquid to the surface of the foremost part of the electrode it is possible to employ this liquid for the cooling of the electrode and also obtain also an initial pre-heating of the liquid.
According to the invention the liquid can arrive on the surface of the foremost part of the electrode through a porous zone or along several flow passages which provide for its arrival parallel to this surface.
The attachment of the are on the surface of the electrode spot can be facilitated by a rod of a refractory material placed in the mass of the liquid and having the form e.g. of a point or ring.
The cavity by which the liquid arrives can possess the form of a small canal disposed in the axis of the electrode and containing a central rod surrounded by a helical spiral forming the flow passage or a similar arrangement; it can be also constituted by a piece of porous carbon or carbon containing a great number of small canals.
The enclosed drawing showsas non-limitating ex amplesseveral ways of realization of the invention.
The FIG. 1 represents a section of a simple form of the essential part of the device.
The FIG. 2 represents a section of a form of the whole device.
The FIGS. 3, 4 and 5 represent three embodiments of the cavity conducting the product to the surface of the foremost part of the electrode.
In the FIG. 1 the electrode 1 and the socket 2, provided 3,149,459 Patented Sept. 22, 1964 with a helical canal 3, form a helical flow passage for the liquid which arrives, through the canal 4, to the cavity 5. In arc chamber 6 the liquid is abruptly transformed into vapor by the action of the electric arc, this vapor then being superheated and ejected at a high velocity through the nozzle 7 in the other electrode 7a.
Electrical energy to form the electric arc is provided by energy source 12. As shown in FIG. 1, conducting leads 13 and 14 connect electric energy source 12 to electrodes 1 and 7a, respectively.
In the FIG. 2 the liquid-contained in a tank not shown in the drawingpasses through the flow passage 8, then through passage 9 constituted by the helical canal 3 formed either in the internal surface of the socket 2 or in the external surface of the electrode 1. From the helical flow canal 3 the liquid, passing through the canal 4, attains the cavity 5, inside of which there is a central rod 10 surrounded by a helical spiral 11; the arrangement composed of the last two parts forms a second helical flow passage which conducts the liquid in such a way as to make it emerge on the surface of the foremost part of the electrode 1 almost parallel to this surface. In arc chamber 6, under the action of the arc, the liquid is abruptly evaporated, the vapor superheated and ejected at a high velocity in the nozzle 7 made in the other electrode 7a. Electrodes 1 and 7a are insulated from each other by a suitable insulating material 15.
FIGURE 3 represents an enlarged sectional view of the second helical flow passage according to FIGURE 2.
The FIG. 4 represents a section of a drawn rod 16, which can be employed instead of the arrangement described above, to form the second helical flow passage.
The FIG. 5 represents a section of an arrangement in which the liquid arrives on the surface of the electrode passing through porous walls 18 surrounding the central rod 17.
Summary The invention concerns:
(1) A device for electric jet propulsion characteristic in that the working fluid is supplied to the surface of the electrode through the interior or along the surface of the latter, and transformed abruptly in vapor which is superheated and ejected at a high velocity.
(2) The embodiments of the device conform to 1, characterized by the following points which can be employed separately or in various combinations:
(a) The liquid arrives at a given place at the foremost part of the electrode which forms the footing of the arc.
(b) The flow passages which conduct the liquid to the surface of the foremost part of the electrode are arranged in the manner which uses the liquid for the cooling of the electrode and causes an initial pre-heating of the liquid.
(0) The liquid is supplied to the surface of the foremost part of the electrode through several flow passages which cause the liquid to arrive so that it emerges on the surface almost parallel to the surface.
(d) The flow passage conducting the liquid to the surface of the foremost part of the electrode is formed by a cylindrical rod surrounded by a helical spiral.
(e) The flow passage is formed by a drawn rod.
(f) The liquid arrives at the surface of the foremost part of the electrode passing through a porous zone.
(g) In the cavity containing the liquid a piece of a refractory material is placed, having, e.g., a form of a point or of a ring.
What is claimed is:
1. An electrothermic jet motor comprising, in combination, an arc chamber, a first and second electrode disposed in said arc chamber, said electrodes being in line 3 4 with each other and separated by a gap to provide an arc 1,978,424 Gebhard Oct. 30, 1934 discharge therebetween, an inlet for a working fluid, a 2,052,796 Rava Sept. 1, 1936 cavity in said first electrode located in the foremost part 2,459,286 Rabezzana Jan. 18, 1949 of said first electrode adjacent said gap, passageway means 2,587,331 Jordan Feb. 26, 1952 for transporting said Working fluid from said inlet in o 5 2,731,079 Smits Jan. 17, 1956 said cavity and adapted to promote heat exchange be- 2,774,216 Allen Dec. 18, 1956 tween said first electrode and said working fluid,'a con- 2,819,423 Clark Jan. 7, 1958 centrically disposed refractory rod in said cavity, fluid 2,850,662 Gilruth Sept. 2, 1958 distribution means surrounding said rod and adapted to 2,862,099 Gage Nov. 25, 1958 emit said working fluid into said gap substantially par 2,880,337 Langmuir Mar. 31, 1959 allel to the surface of said first electrode, said second 2,919,370 Giannini et a1. Dec. 29, 1959 electrode having a jet nozzle therein Whose axis of sym- 2,929,952 Giannini et al Mar. 22, 1960 metry substantially coincides with the direction of propa- 3,013,384 Smith Dec. 19, 1961 gation of said arc discharge, said nozzle being adapted 3,032,978 Kunen May 8, 1962 to convert thermal energy into kinetic energy. 3,041,824 Berhman July 3, 1962 2. The device of claim 1 wherein said fluid distribution 3,056,257 Brunkhardt Oct. 2, 1962 means comprises a helical spiral body. Y 3. The device of claim 1 wherein said fluid distribution FOREIGN PATENTS means comprises a porous refractory material. 20,697 Great Britain Sept 17 1908 20 References Cited in the file Of this patent OTHER REFERENCES UNITED STATES PATENTS Giannini: The Plasma Jet, Scientific American, vol. 684,746 Chapman Oct. 15, 1901 197, No. 2, August 1957, pages -85. 1,363,037 Goddard Dec. 21, 1920

Claims (1)

1. AN ELECTROTHERMIC JET MOTOR COMPRISING, IN COMBINATION, AN ARC CHAMBER, A FIRST AND SECOND ELECTRODE DISPOSED IN SAID ARC CHAMBER, SAID ELECTRODES BEING IN LINE WITH EACH OTHER AND SEPARATED BY A GAP TO PROVIDE AN ARC DISCHARGE THEREBETWEEN, AN INLET FOR A WORKING FLUID, A CAVITY IN SAID FIRST ELECTRODE LOCATED IN THE FOREMOST PART OF SAID FIRST ELECTRODE ADJACENT SAID GAP, PASSAGEWAY MEANS FOR TRANSPORTING SAID WORKING FLUID FROM SAID INLET INTO SAID CAVITY AND ADAPTED TO PROMOTE HEAT EXCHANGE BETWEEN SAID FIRST ELECTRODE AND SAID WORKING FLUID, A CONCENTRICALLY DISPOSED REFRACTORY ROD IN SAID CAVITY, FLUID DISTRIBUTION MEANS SURROUNDING SAID ROD AND ADAPTED TO EMIT SAID WORKING FLUID INTO SAID GAP SUBSTANTIALLY PARALLEL TO THE SURFACE OF SAID FIRST ELECTRODE, SAID SECOND ELECTRODE HAVING A JET NOZZLE THEREIN WHOSE AXIS OF SYMMETRY SUBSTANTIALLY COINCIDES WITH THE DIRECTION OF PROPAGATION OF SAID ARC DISCHARGE, SAID NOZZLE BEING ADAPTED TO CONVERT THERMAL ENERGY INTO KINETIC ENERGY.
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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3270498A (en) * 1963-11-05 1966-09-06 Gen Electric Controllable vaporizing gas accelerator
US3279177A (en) * 1963-06-10 1966-10-18 Giannini Scient Corp Apparatus and method for propelling vehicles in space
US3298179A (en) * 1963-11-12 1967-01-17 Rocket Research Corp Confined parallel rail pulsed plasma accelerator
US3304719A (en) * 1964-07-28 1967-02-21 Giannini Scient Corp Apparatus and method for heating and accelerating gas
US3308623A (en) * 1963-08-19 1967-03-14 Snecma Electro-thermic ejectors
US3350884A (en) * 1963-08-19 1967-11-07 Snecma Propellent supply to electro-thermic ejectors
US3354644A (en) * 1965-06-08 1967-11-28 Electro Optical Systems Inc Liquid protection of electrodes
US4766724A (en) * 1987-06-10 1988-08-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Arcjet power supply and start circuit
US5232384A (en) * 1989-11-27 1993-08-03 Alexandr Klimovitsky Motion drive of marine underwater/abovewater ship

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US684746A (en) * 1900-10-10 1901-10-15 Frank S Chapman Generator of steam.
US1363037A (en) * 1920-12-21 Method of and means fob pbodttcino electbified jets of oas
US1978424A (en) * 1933-03-14 1934-10-30 Louis A Gebhard High power demountable electron tube
US2052796A (en) * 1933-05-15 1936-09-01 Rava Alexander High temperature torch
US2459286A (en) * 1944-05-27 1949-01-18 Gen Motors Corp Combination spark plug and fuel injector
US2587331A (en) * 1947-08-08 1952-02-26 Gen Electric High-frequency electrical heating method and apparatus
US2731079A (en) * 1953-01-22 1956-01-17 Smits Wytze Beye Apparatus for atomizing and igniting substances
US2774216A (en) * 1952-01-21 1956-12-18 Armstrong Siddeley Motors Ltd Rocket motors
US2819423A (en) * 1957-03-11 1958-01-07 Gen Electric Plasma transmitter
US2850662A (en) * 1958-03-04 1958-09-02 Robert R Gilruth Electric arc powered jet
US2862099A (en) * 1957-06-17 1958-11-25 Union Carbide Corp Arc torch process with reactive gases
US2880337A (en) * 1958-01-02 1959-03-31 Thompson Ramo Wooldridge Inc Particle acceleration method and apparatus
US2919370A (en) * 1958-10-28 1959-12-29 Plasmadyne Corp Electrodeless plasma torch and method
US2929952A (en) * 1958-10-20 1960-03-22 Plasmadyne Corp Self-circulating plasma device
US3013384A (en) * 1955-07-15 1961-12-19 Jr Bonnie Smith Jet atomic system
US3032978A (en) * 1958-11-06 1962-05-08 Republic Aviat Corp Magnetic compression engine
US3041824A (en) * 1956-05-01 1962-07-03 Amalgamated Growth Ind Inc Propulsion system
US3056257A (en) * 1959-06-25 1962-10-02 United Aircraft Corp Rocket ignitor construction

Patent Citations (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1363037A (en) * 1920-12-21 Method of and means fob pbodttcino electbified jets of oas
US684746A (en) * 1900-10-10 1901-10-15 Frank S Chapman Generator of steam.
US1978424A (en) * 1933-03-14 1934-10-30 Louis A Gebhard High power demountable electron tube
US2052796A (en) * 1933-05-15 1936-09-01 Rava Alexander High temperature torch
US2459286A (en) * 1944-05-27 1949-01-18 Gen Motors Corp Combination spark plug and fuel injector
US2587331A (en) * 1947-08-08 1952-02-26 Gen Electric High-frequency electrical heating method and apparatus
US2774216A (en) * 1952-01-21 1956-12-18 Armstrong Siddeley Motors Ltd Rocket motors
US2731079A (en) * 1953-01-22 1956-01-17 Smits Wytze Beye Apparatus for atomizing and igniting substances
US3013384A (en) * 1955-07-15 1961-12-19 Jr Bonnie Smith Jet atomic system
US3041824A (en) * 1956-05-01 1962-07-03 Amalgamated Growth Ind Inc Propulsion system
US2819423A (en) * 1957-03-11 1958-01-07 Gen Electric Plasma transmitter
US2862099A (en) * 1957-06-17 1958-11-25 Union Carbide Corp Arc torch process with reactive gases
US2880337A (en) * 1958-01-02 1959-03-31 Thompson Ramo Wooldridge Inc Particle acceleration method and apparatus
US2850662A (en) * 1958-03-04 1958-09-02 Robert R Gilruth Electric arc powered jet
US2929952A (en) * 1958-10-20 1960-03-22 Plasmadyne Corp Self-circulating plasma device
US2919370A (en) * 1958-10-28 1959-12-29 Plasmadyne Corp Electrodeless plasma torch and method
US3032978A (en) * 1958-11-06 1962-05-08 Republic Aviat Corp Magnetic compression engine
US3056257A (en) * 1959-06-25 1962-10-02 United Aircraft Corp Rocket ignitor construction

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3279177A (en) * 1963-06-10 1966-10-18 Giannini Scient Corp Apparatus and method for propelling vehicles in space
US3308623A (en) * 1963-08-19 1967-03-14 Snecma Electro-thermic ejectors
US3350884A (en) * 1963-08-19 1967-11-07 Snecma Propellent supply to electro-thermic ejectors
US3270498A (en) * 1963-11-05 1966-09-06 Gen Electric Controllable vaporizing gas accelerator
US3298179A (en) * 1963-11-12 1967-01-17 Rocket Research Corp Confined parallel rail pulsed plasma accelerator
US3304719A (en) * 1964-07-28 1967-02-21 Giannini Scient Corp Apparatus and method for heating and accelerating gas
US3354644A (en) * 1965-06-08 1967-11-28 Electro Optical Systems Inc Liquid protection of electrodes
US4766724A (en) * 1987-06-10 1988-08-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Arcjet power supply and start circuit
US5232384A (en) * 1989-11-27 1993-08-03 Alexandr Klimovitsky Motion drive of marine underwater/abovewater ship

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