US1405482A - Method of and means for propelling craft navigating a fluid medium - Google Patents

Method of and means for propelling craft navigating a fluid medium Download PDF

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US1405482A
US1405482A US301111A US30111119A US1405482A US 1405482 A US1405482 A US 1405482A US 301111 A US301111 A US 301111A US 30111119 A US30111119 A US 30111119A US 1405482 A US1405482 A US 1405482A
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furnace
air
propulsion
fluid medium
tube
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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
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof

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  • T 0 all whom it may concern.
  • This invention relates to an improved method of and means for propelling air and water craft, the invention being capable of useful application to the propulsion of surface and sub-surface water craft, and also air craft.
  • My present invention is based upon the same broad underlying principle of operation as the invention forming the subject matter of Letters Patent No. 1,305,340, granted to me on the 3rd day of June, 1919, this principle residing in causing a gaseous body, the molecules of which are energized by the heat of combustion or otherwise, to expand continuously and with substantially constant pressure directly between the craft and the fluid medium (water or air) through which the craft travels, without the intervention of any motor, engine or propeller blades or any other moving parts.
  • the present invention constitutes an improved form or embodiment of the basic principle of the invention disclosed and claimed in my aforesaid Letters Patent; and in its physical embodiment comprises an oil tank, a combustion chamber or furnace in which the oil is burned continuously, a propulsion blast tube open at its rear end, and a combustion jet air inducer or injector connecting the furnace and propulsion blast tube and serving to direct the burning products of combustion from the former directly into the latter in the form of one or more jets which also serve as air inducers to induce a large volume of air into the propulsion blast tube, serving to bring the temperature of the resultant mixture of air and furnace gases down to a low temperature, giving a large volume of propulsive blast at reduced pressure which reacts directly upon the fluid medium being navigated.
  • I also employ an oil boiler or Specification of Letters Patent.
  • vaporizer that is preferably heated by the furnace itself, in which the oil from the oil tank is vaporized under high pressure, and a vapor et draft inducer connecting the oil boiler and the furnace and serving the triple function of feeding the furnace with fuel, feeding it with air, and mixing the air and fuel in proper proportions to secure efficient and continuous combustion.
  • Fig. l is a perspective elevation of the complete apparatus, with the furnace shown partly in section, and the propulsion blast tube broken out between its ends;
  • Fig. 2 is a longitudinal section through the oil vapor air inducer or injector
  • Fig. 3 is a longitudinal section through the flame jet air inducer or injector.
  • 10 designates the combustion chamber or furnace which, in the case of water craft, will be so located as to be below the water line of the craft, and may consist, as herein indicated, of a cylindrical body formed of or lined with suitable fire-clay insulation 11 to prevent dissipation of heat, and closed at its forward end excepting for a central funnelshaped air induction opening 12.
  • 13 designates a fuel tank in which a body of hydrocarbon fuel is maintained under high air pressure supplied to the tank from an air compressor conventionally indicated at 14.
  • i delivery pipe 15 from the fuel tank connects with a coil 16 that surrounds the furnace 10, being conveniently embedded in the insulation of the latter.
  • This coil 16 forms an oil boiler -or vaporizer, from the forward end of which the oil vapor flows through a pipe 17 into an oil vapor holder 18 preferably located directly in front of the furnace, From the oil vapor holder 18 there extends an injector pipe 19 into the forward end of the furnace, tlns injector pipe passing centrally into the throat of the air induction opening-12 so that the oil vapor jet which is under a high pressure serves to lnduce or entrain through the opening 12 a sufliclent body of air to mix with and support combustion of the fuel within the furnace, which combustion maybe started by an ordinary electric sparker indicated at 20.
  • a series of injector pipes 21 into the propulsion blast tube indicated at 22 is located directly behind and preferably in line with the furnace and is of considerably greater cross-sectional area than the latter, and of any suitable or desired length.
  • injector pipes 21 In the front wall of the propulsion blast tube 22 are a group of coneshaped openings 23 similar to the opening 12 of the furnace, into the throats of which openings the discharge ends of the injector pipes 21 pass, said openings serving to permit the induction of a considerable volume of air under the'influence of the flame jets discharged from the furnace. This induced air mixes with the products of combustion, reducing the temperature and pressure of the latter.
  • the degree or extent of reduction of pressure would depend partly upon the relative sizes of the vapor container, furnace and blast tube' and partly upon the relative amounts of air induced by the oil vapor injector and the flame jet inducers, these amounts of induced air being governed by the relative diameters of the jet orifices, and the position of the jet orifices relative to the funnel throats.
  • Beneath the oil vapor .boiler 18 I have indicated a gasoline pan 24, which may be used for starting.
  • the air induced into the furnace by the high-pressure vapor jet is compressed without loss of heat such as would occur were the air mechanically condensed by the usual water-jacketed compressor before passing into the furnace, thereby eonducing to the efiiciency of the apparatus. Furthermore, this retained heat of compression of the air in the furnace partly neutralizes the lowering of temperature of the vapor due to its expansion.
  • the large volume of air induced into the propulsion blast tube serves to bring the temperature of the resultant mixture with the furnace gases down to a low temperature, giving a large volume of propulsive blast at reduced pressure.
  • the propulsive eflort obtainable by one or a series of relatively fine jets discharging directly into the fluid medium is far less than the propulsive effort obtainable by expansion of a heated gas in a propulsion tube of substantial cross-sectional area fed by such jets, the reaction taking place against a very considerable area of the fluid medium being navigated, for the reason that loss of heat by conduction and of energy by useless churning of the fluid medium are reduced to the minimum.
  • the present invention is based upon the same broad principle that underlies the invention of my aforesaid Letters Patent; but presents an improvement thereon in the employment of flame jet induction of air into the propulsion tube, and also in the employment of vapor jet induction of air draft into a furnace burning under pressure, the furnace serving as a head for a lower stage inducer into another chamber also under pressure.
  • the herein described method of effecting propulsion of craft navigating a fluid medium which consists in continuously burning fuel in a furnace, continuously discharging the burning products of combustion from said furnace directly in the form of a jet into av propulsion tube that is open at'one end to the fluid medium being navigated, simultaneously injecting air by means of said jet into said propulsion tube, and allowing the mixed products of combustion and air in said propulsion tube to expand and react directly against the fluid medium being navigated.
  • the herein described method of effecting propulsion of craft navigating a fluid medium which consists in continuously burning 'fuel in a furnace, dischargin the burning products of combustion direct y in the form of a pluralit of separate jets into one end of a propulsioutube that is open at its opposite end to the fluid medium being navigated, 'simultanoeusly injectingair by means of said jets into said propulsion tube, and allowing the mixed products of combustion and air in said propulsion tube to expand and react directl against the fluid medium being navigate 3.
  • the herein described method of effecting propulsion of craft navigating a fluid medium which consists in continuously supplying fuel under pressure in the form of ajet into a furnace, simultaneously injecting air into said furnace by means of sa1d .jet to maintain continuous combustion, cont1nuously discharging the burning products of combustionfrom said furnace directly in the form of a jet into a propulsion tube that is open at one end to the fluid medium being navigated, simultaneously inject ng air by means of said jet into said propulsion tube, and allowing the mixed products of combustion and air in said propulsion tube to expand and react directly against the fluid medium being navigated.
  • the herein described method of effecting propulsion of craft navigating a fluid medium which consists in continuously supplying fuel under pressure in the form of a jet into a furnace, simultaneously injecting air into said furnace by means 'of said jet to maintain continuous combustion, continuously discharging the burning products of combustion directly in the form of a plurality of separate jets into one end of a propulsion tube that is open at its opposite endto the fluid medium being navigated, simultaneously injecting air by means of said jets into said propulsion tube, and allowin the mixed products of combustion and air in said propulsion tube toexpand and react directly against the fluid medium being navigated.
  • a propulsion device of the character described the combination of a furnace, a propulsion tube of greater cross-sectional area than said furnace in rear of the latter, said propulsion tube being open at its rear endand having an air openin in its front wall, and an injector pipe lea from the in rear end of said furnace Into said air opening, whereby the products of combustion from said furnace pass in jet form into said propulsion tube and entrain air into the latter through said opening.
  • a propulsion device of the character described the combination of a furnace having an air opening in a wall thereof, a fuel container adapted to hold fuel under pres sure, an injector pipe leading from said fuel container into said air openlng whereby the fuel is delivered in the form of a jet to said furnaceand entrains air through said opening, a propulsion tube in rear of said furnace, said tube being open at its rear end and having an air opening in its front wall, an injector pipe leading from the rear end of said furnace into said last-named air opening, whereby the products of combustion from said furnace pass in the form of a jet into said propulsion tube and entrain fuel is delivered in the form of a jet to said furnace and entrains air through said opening, a propulsion tube of greater cross-sectional area than said furnace in rear of the latter, said tube being open at its rear end and having a plurality of spaced air openings in its front wall, and a corresponding plurality of injector pipes leading from the rear end of said furnace into said last-named air
  • a propulsion device of the character described, the combination of a furnace having an air opening in a wall thereof, an oil tank, an oil vaporizer connected to said oil tank and heated by said furnace, an injector pipe leading from said vaporizer into said air opening whereby the vaporized oil is delivered in the form of a jet to said furnace and entrains air through said opening, a
  • ropu1si0n tube of greater cross-sectional area than said furnace in rear of the latter said tube being 0 en at its rear end and having a. plurality o spaced air openings in its front .wa11,and a'corresponding plurality of injector pipes leadin from the rear end of Sand furnace into sai last-named air openings wliereby produets of combustion from and furnace ere divided and pass in the form of separate jets .intoffiaid pro ulsion 1o tube and entrain' air into. the' kttter t rough s'aid-last-nalned openings.

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  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Description

L. G. BOSTEDO.
METHOD OF AND MEANS FOR PROPELLING CRAFT NAVIGATING A FLUID MEDIUM.
APPLICATION FILED MAYSI, I919.
Patented Feb. 7 1922.
a OM UNITED s'rArEs PATENT OFFHCE.
LOUIS G. BOSTEDO, OF CHICAGO; ILLINOIS.
METHOD OF AND MEANS FOR PROPELLING CRAFT N AVIGATING Application filed May 31,
T 0 all whom it may concern.
Be it known that I, LoUIs G. Bos'rnno, a citizen of the United States, residing at Chicago, in the county of Cook and State of Illinois, have invented certain new and useful Improvements in Methods of and Means for Propelling Craft Navigating a Fluid Medium, of which the following is a specification.
This invention relates to an improved method of and means for propelling air and water craft, the invention being capable of useful application to the propulsion of surface and sub-surface water craft, and also air craft.
My present invention is based upon the same broad underlying principle of operation as the invention forming the subject matter of Letters Patent No. 1,305,340, granted to me on the 3rd day of June, 1919, this principle residing in causing a gaseous body, the molecules of which are energized by the heat of combustion or otherwise, to expand continuously and with substantially constant pressure directly between the craft and the fluid medium (water or air) through which the craft travels, without the intervention of any motor, engine or propeller blades or any other moving parts.
The present invention constitutes an improved form or embodiment of the basic principle of the invention disclosed and claimed in my aforesaid Letters Patent; and in its physical embodiment comprises an oil tank, a combustion chamber or furnace in which the oil is burned continuously, a propulsion blast tube open at its rear end, and a combustion jet air inducer or injector connecting the furnace and propulsion blast tube and serving to direct the burning products of combustion from the former directly into the latter in the form of one or more jets which also serve as air inducers to induce a large volume of air into the propulsion blast tube, serving to bring the temperature of the resultant mixture of air and furnace gases down to a low temperature, giving a large volume of propulsive blast at reduced pressure which reacts directly upon the fluid medium being navigated. In the preferred and most complete form of the invention I also employ an oil boiler or Specification of Letters Patent.
A FLUID MEDIUM.
Patented Feb. 7, 1922.
1919. Serial N0. 301,111.
vaporizer that is preferably heated by the furnace itself, in which the oil from the oil tank is vaporized under high pressure, and a vapor et draft inducer connecting the oil boiler and the furnace and serving the triple function of feeding the furnace with fuel, feeding it with air, and mixing the air and fuel in proper proportions to secure efficient and continuous combustion.
In the accompanying drawings I have illustrated diagrammatically a form of apparatus in and by which the novel method of effecting propulsion forming in part the sub ect matter of the present invention may be carried out; it beingunderstood that this apparatus may be widely varied in detail mechanical features without involving any departure from the novel method of operation, or sacrificing any of the advantages of the invention.
Referring to the drawings,
Fig. l is a perspective elevation of the complete apparatus, with the furnace shown partly in section, and the propulsion blast tube broken out between its ends;
Fig. 2 is a longitudinal section through the oil vapor air inducer or injector;
Fig. 3 is a longitudinal section through the flame jet air inducer or injector.
Referring to the drawings, 10 designates the combustion chamber or furnace which, in the case of water craft, will be so located as to be below the water line of the craft, and may consist, as herein indicated, of a cylindrical body formed of or lined with suitable fire-clay insulation 11 to prevent dissipation of heat, and closed at its forward end excepting for a central funnelshaped air induction opening 12. 13 designates a fuel tank in which a body of hydrocarbon fuel is maintained under high air pressure supplied to the tank from an air compressor conventionally indicated at 14. i delivery pipe 15 from the fuel tank connects with a coil 16 that surrounds the furnace 10, being conveniently embedded in the insulation of the latter. This coil 16 forms an oil boiler -or vaporizer, from the forward end of which the oil vapor flows through a pipe 17 into an oil vapor holder 18 preferably located directly in front of the furnace, From the oil vapor holder 18 there extends an injector pipe 19 into the forward end of the furnace, tlns injector pipe passing centrally into the throat of the air induction opening-12 so that the oil vapor jet which is under a high pressure serves to lnduce or entrain through the opening 12 a sufliclent body of air to mix with and support combustion of the fuel within the furnace, which combustion maybe started by an ordinary electric sparker indicated at 20.
From the rear end wall of the furnace there extend a series of injector pipes 21 into the propulsion blast tube indicated at 22. This latter is located directly behind and preferably in line with the furnace and is of considerably greater cross-sectional area than the latter, and of any suitable or desired length. In the front wall of the propulsion blast tube 22 are a group of coneshaped openings 23 similar to the opening 12 of the furnace, into the throats of which openings the discharge ends of the injector pipes 21 pass, said openings serving to permit the induction of a considerable volume of air under the'influence of the flame jets discharged from the furnace. This induced air mixes with the products of combustion, reducing the temperature and pressure of the latter.
In the operation of the apparatus, there occur substantial decreases or drops of pressure, due to the entrance of the fluid into a region of lower pressure, each time down to about one-seventh, between the vapor jet inducer and the furnace, and between the flame jet inducers and the propulsion blast tube. For instance, assuming that the pressure of the oil vapor in the container 18 is 700 ounds, the pressure in the furnace would lie about 100 pounds, while the resultant working pressure in the propulsion blast tube would be approximately 15 pounds. Of course, the degree or extent of reduction of pressure would depend partly upon the relative sizes of the vapor container, furnace and blast tube' and partly upon the relative amounts of air induced by the oil vapor injector and the flame jet inducers, these amounts of induced air being governed by the relative diameters of the jet orifices, and the position of the jet orifices relative to the funnel throats. There also occurs a large drop in the temperature of the furnace gases as they enter the propulsion tube due to their expansion in the latter, the object being to bring them as near atmospheric temperature as practicable to avoid waste of heat in the exhaust.
Beneath the oil vapor .boiler 18 I have indicated a gasoline pan 24, which may be used for starting.
The air induced into the furnace by the high-pressure vapor jet is compressed without loss of heat such as would occur were the air mechanically condensed by the usual water-jacketed compressor before passing into the furnace, thereby eonducing to the efiiciency of the apparatus. Furthermore, this retained heat of compression of the air in the furnace partly neutralizes the lowering of temperature of the vapor due to its expansion.
The large volume of air induced into the propulsion blast tube serves to bring the temperature of the resultant mixture with the furnace gases down to a low temperature, giving a large volume of propulsive blast at reduced pressure.
I am aware that it has heretofore been proposed to effect propulsion of water craft through th agency of jets of steam or compressed air on the rocket principle discharging directly into the water, but in the case of steam, the sudden reduction of the tem perature from above 225 degrees F. down to or below 60 degrees F. practically kills the propulsive power of the steam jet; while in the case of compressed air, there is neccssarily a large waste of power in the form of heat in effecting the compression. Furthermore, the propulsive eflort obtainable by one or a series of relatively fine jets discharging directly into the fluid medium is far less than the propulsive effort obtainable by expansion of a heated gas in a propulsion tube of substantial cross-sectional area fed by such jets, the reaction taking place against a very considerable area of the fluid medium being navigated, for the reason that loss of heat by conduction and of energy by useless churning of the fluid medium are reduced to the minimum.
As I have hereinabove stated, the present invention is based upon the same broad principle that underlies the invention of my aforesaid Letters Patent; but presents an improvement thereon in the employment of flame jet induction of air into the propulsion tube, and also in the employment of vapor jet induction of air draft into a furnace burning under pressure, the furnace serving as a head for a lower stage inducer into another chamber also under pressure.
I claim:
1. The herein described method of effecting propulsion of craft navigating a fluid medium, which consists in continuously burning fuel in a furnace, continuously discharging the burning products of combustion from said furnace directly in the form of a jet into av propulsion tube that is open at'one end to the fluid medium being navigated, simultaneously injecting air by means of said jet into said propulsion tube, and allowing the mixed products of combustion and air in said propulsion tube to expand and react directly against the fluid medium being navigated.
2. The herein described method of effecting propulsion of craft navigating a fluid medium, which consists in continuously burning 'fuel in a furnace, dischargin the burning products of combustion direct y in the form of a pluralit of separate jets into one end of a propulsioutube that is open at its opposite end to the fluid medium being navigated, 'simultanoeusly injectingair by means of said jets into said propulsion tube, and allowing the mixed products of combustion and air in said propulsion tube to expand and react directl against the fluid medium being navigate 3. The herein described method of effecting propulsion of craft navigating a fluid medium, which consists in continuously supplying fuel under pressure in the form of ajet into a furnace, simultaneously injecting air into said furnace by means of sa1d .jet to maintain continuous combustion, cont1nuously discharging the burning products of combustionfrom said furnace directly in the form of a jet into a propulsion tube that is open at one end to the fluid medium being navigated, simultaneously inject ng air by means of said jet into said propulsion tube, and allowing the mixed products of combustion and air in said propulsion tube to expand and react directly against the fluid medium being navigated.
4. The herein described method of effecting propulsion of craft navigating a fluid medium, which consists in continuously supplying fuel under pressure in the form of a jet into a furnace, simultaneously injecting air into said furnace by means 'of said jet to maintain continuous combustion, continuously discharging the burning products of combustion directly in the form of a plurality of separate jets into one end of a propulsion tube that is open at its opposite endto the fluid medium being navigated, simultaneously injecting air by means of said jets into said propulsion tube, and allowin the mixed products of combustion and air in said propulsion tube toexpand and react directly against the fluid medium being navigated.
5. In a propulsion device of the character described, the combination of a furnace, a propulsion tube open at its rearend and havin an air opening in a Wall thereof, and
an in ector pipe leading from said furnace into said air opening, whereby the products of combustion from said furnace are delivered in jet form into said propulsion tube and entrain air into the latter through said opening.
6. In a propulsion device of the character described, the combination of a furnace, a propulsion tube of greater cross-sectional area than said furnace in rear of the latter, said propulsion tube being open at its rear endand having an air openin in its front wall, and an injector pipe lea from the in rear end of said furnace Into said air opening, whereby the products of combustion from said furnace pass in jet form into said propulsion tube and entrain air into the latter through said opening.
In a propulsion device of the character described, the combination of a furnace, at propulsion tube of greater cross-sectional area than said furnace in rear of the latter, 7
pulsion tube and entrain air into the latter through said openings.
8. n a propulsion device of the character described, the combination of a furnace having an air opening in a wall thereof, a fuel container adapted to hold fuel under pres sure, an injector pipe leading from said fuel container into said air openlng whereby the fuel is delivered in the form of a jet to said furnaceand entrains air through said opening, a propulsion tube in rear of said furnace, said tube being open at its rear end and having an air opening in its front wall, an injector pipe leading from the rear end of said furnace into said last-named air opening, whereby the products of combustion from said furnace pass in the form of a jet into said propulsion tube and entrain fuel is delivered in the form of a jet to said furnace and entrains air through said opening, a propulsion tube of greater cross-sectional area than said furnace in rear of the latter, said tube being open at its rear end and having a plurality of spaced air openings in its front wall, and a corresponding plurality of injector pipes leading from the rear end of said furnace into said last-named air openings, whereby the products of combustion from said furnace are divided and pass in the form of separate jets into said propulsion tube and entrain air into the latter through said last-named openings.
10. In a propulsion device of the character described, the combination of a furnace having an air opening in a wall thereof, an oil tank, an oil vaporizer connected to said oil tank and heated by said furnace, an injector pipe leading from said vaporizer into said air opening whereby the vaporized oil is delivered in the form of a jet to said furnace and entrains air through said opening, a
ropu1si0n tube of greater cross-sectional area than said furnace in rear of the latter, said tube being 0 en at its rear end and having a. plurality o spaced air openings in its front .wa11,and a'corresponding plurality of injector pipes leadin from the rear end of Sand furnace into sai last-named air openings wliereby produets of combustion from and furnace ere divided and pass in the form of separate jets .intoffiaid pro ulsion 1o tube and entrain' air into. the' kttter t rough s'aid-last-nalned openings.
I LOU'IS nosrnno.
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Cited By (27)

* Cited by examiner, † Cited by third party
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US2438858A (en) * 1943-01-21 1948-03-30 Armstrong Siddeley Motors Ltd Liquid-fuel combustion chamber
US2479776A (en) * 1944-04-15 1949-08-23 Lockheed Aircraft Corp Turbo-jet power plant with fuel vaporizer for afterburners
US2483045A (en) * 1945-09-24 1949-09-27 Harold D Harby Jet engine, including a combustion chamber to which gaseous fuel is delivered under pressure
US2485502A (en) * 1945-04-12 1949-10-18 Thelma Mccollum Jet propulsion means for helicopters
US2486967A (en) * 1945-07-25 1949-11-01 United Aircraft Corp Airplane wing with jet propulsion apparatus
US2502332A (en) * 1945-04-12 1950-03-28 Thelma Mccollum Aspirator compressor type jet propulsion apparatus
US2542953A (en) * 1945-09-13 1951-02-20 Stewart Warner Corp Combustion turbine having mixing tube to aspirate, compress, and preheat the air-fuel mixture
US2573471A (en) * 1943-05-08 1951-10-30 Aerojet Engineering Corp Reaction motor operable by liquid propellants and method of operating it
US2573697A (en) * 1945-07-30 1951-11-06 James Y Dunbar Multitube mosaic reso-jet motor
US2632294A (en) * 1948-04-19 1953-03-24 John J Wall Fuel supplying means for jet engines
US2633327A (en) * 1946-03-01 1953-03-31 Packard Motor Car Co Gas turbine wheel with liquid cooling means
US2648192A (en) * 1949-09-27 1953-08-11 United Aircraft Corp Variable capacity jet exhaust augmenter
US2664703A (en) * 1949-06-28 1954-01-05 A V Roe Canada Ltd Preheater and vaporizer for gas turbine engines
US2667741A (en) * 1946-08-23 1954-02-02 Lockheed Aircraft Corp Fuel injection and burner system for reactive propulsion power plants
US2694899A (en) * 1950-06-09 1954-11-23 Westinghouse Electric Corp Liquid fuel vaporizing apparatus
US2721444A (en) * 1948-09-21 1955-10-25 Johnson Horace James Series-type multiple ram jet propulsion system
US2745249A (en) * 1946-10-22 1956-05-15 Ryan Aeronautical Co Reheater and fuel vaporizer for jet propulsion engines
US2763983A (en) * 1946-04-02 1956-09-25 Robert S Kafka Combustion type power generating apparatus
US2794316A (en) * 1949-02-23 1957-06-04 Reaction Motors Inc Operating internal combustion burners of the jet motor type
US2920448A (en) * 1955-07-29 1960-01-12 Sebac Nouvelle Sa Apparatus for imparting rapid speed to a mass of fluid
US3024607A (en) * 1949-08-19 1962-03-13 David A Washburn Sustained operation igniter for ram-jet missiles
US3107485A (en) * 1959-05-27 1963-10-22 Ohio Commw Eng Co Propulsion means and method for space vehicles employing a volatile alkene and metalcarbonyl
US3182445A (en) * 1959-12-21 1965-05-11 Dow Chemical Co Liquid-solid propellant rocket case and method
US3747339A (en) * 1961-11-13 1973-07-24 Texaco Inc Reaction propulsion engine and method of operation
US3933026A (en) * 1974-07-31 1976-01-20 Ham William C Ultrasonic calibration standard
EP0102411A1 (en) * 1982-09-08 1984-03-14 Joseph S. Adams Compression wave former
US20110067995A1 (en) * 2009-09-23 2011-03-24 Lusk James D Ethanol Distillation System and Apparatus

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2438858A (en) * 1943-01-21 1948-03-30 Armstrong Siddeley Motors Ltd Liquid-fuel combustion chamber
US2573471A (en) * 1943-05-08 1951-10-30 Aerojet Engineering Corp Reaction motor operable by liquid propellants and method of operating it
US2479776A (en) * 1944-04-15 1949-08-23 Lockheed Aircraft Corp Turbo-jet power plant with fuel vaporizer for afterburners
US2485502A (en) * 1945-04-12 1949-10-18 Thelma Mccollum Jet propulsion means for helicopters
US2502332A (en) * 1945-04-12 1950-03-28 Thelma Mccollum Aspirator compressor type jet propulsion apparatus
US2486967A (en) * 1945-07-25 1949-11-01 United Aircraft Corp Airplane wing with jet propulsion apparatus
US2573697A (en) * 1945-07-30 1951-11-06 James Y Dunbar Multitube mosaic reso-jet motor
US2542953A (en) * 1945-09-13 1951-02-20 Stewart Warner Corp Combustion turbine having mixing tube to aspirate, compress, and preheat the air-fuel mixture
US2483045A (en) * 1945-09-24 1949-09-27 Harold D Harby Jet engine, including a combustion chamber to which gaseous fuel is delivered under pressure
US2633327A (en) * 1946-03-01 1953-03-31 Packard Motor Car Co Gas turbine wheel with liquid cooling means
US2763983A (en) * 1946-04-02 1956-09-25 Robert S Kafka Combustion type power generating apparatus
US2667741A (en) * 1946-08-23 1954-02-02 Lockheed Aircraft Corp Fuel injection and burner system for reactive propulsion power plants
US2745249A (en) * 1946-10-22 1956-05-15 Ryan Aeronautical Co Reheater and fuel vaporizer for jet propulsion engines
US2632294A (en) * 1948-04-19 1953-03-24 John J Wall Fuel supplying means for jet engines
US2721444A (en) * 1948-09-21 1955-10-25 Johnson Horace James Series-type multiple ram jet propulsion system
US2794316A (en) * 1949-02-23 1957-06-04 Reaction Motors Inc Operating internal combustion burners of the jet motor type
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