US2402826A - Control means for jet propulsion apparatus - Google Patents

Control means for jet propulsion apparatus Download PDF

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Publication number
US2402826A
US2402826A US493801A US49380143A US2402826A US 2402826 A US2402826 A US 2402826A US 493801 A US493801 A US 493801A US 49380143 A US49380143 A US 49380143A US 2402826 A US2402826 A US 2402826A
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United States
Prior art keywords
liquid
liquids
control means
lines
nozzles
Prior art date
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Expired - Lifetime
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US493801A
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Lubbock Isaac
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Asiatic Petroleum Co Ltd
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Asiatic Petroleum Co Ltd
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Publication of US2402826A publication Critical patent/US2402826A/en
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44Feeding propellants
    • F02K9/50Feeding propellants using pressurised fluid to pressurise the propellants
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00Fluid handling
    • Y10T137/1624Destructible or deformable element controlled
    • Y10T137/1632Destructible element
    • Y10T137/1647Explosive actuation
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00Fluid handling
    • Y10T137/1624Destructible or deformable element controlled
    • Y10T137/1632Destructible element
    • Y10T137/1692Rupture disc
    • Y10T137/1714Direct pressure causes disc to burst
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00Fluid handling
    • Y10T137/1624Destructible or deformable element controlled
    • Y10T137/1797Heat destructible or fusible
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00Fluid handling
    • Y10T137/2931Diverse fluid containing pressure systems
    • Y10T137/3003Fluid separating traps or vents
    • Y10T137/3102With liquid emptying means
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00Fluid handling
    • Y10T137/4673Plural tanks or compartments with parallel flow
    • Y10T137/4857With manifold or grouped outlets

Definitions

  • the rapidly acting valve is preferably operated conjointly with the igniter, for example by electrical coupling, so that the apparatus can be started almost instantaneously by the operation,

Description

June 25, 1946. 1. LUBBOCK CONTROL MEANS FOR JET PROPULSION APPARATUS Filed July 7, 1943 euprueqazz q/a/ks /4 Mr M. 1 W m w pm a: a W Z w an 05 g a H a 2 A v .m... W 0 m m e mi. 2 3 an a a "mm I (I Horney Patented June 25, 1946 CONTROL MEANS FOR JET PROPULSION APPARATUS Isaac Lubbock, Great St. Helena, London, England, assignor to The Asiatic Petroleum Company Limited, London, England Application July I, 1043, Serial No. 493,801
In Great Britain November 7, 1941 4 3 Claims. 1
This invention relates to improved control means for the supply of liquids in combustion apparatus, especially jet propulsion apparatus of the type wherein a liquid fuel is used in combination with an oxidant in liquid form such as liquid oxygen.
The object of the invention is to ensure the arrival, timely in relation to the operation the ignition means, and steady feeding of the liquids over the time of operation of the apparatus.
Another object is to secure the regulation of the initial flows to prevent excessive pressure in the combustion chamber.
According to the invention, the operation of the apparatus is initiated by actuating means causing the liquids rapidly to arrive in the combustion chamber in automatic timed relationship coordinated with the actuation of the igniting means.
In carrying out the invention there is preferably employed a rapidly acting valve operated by an explosive charge-for example a valve as described in the specification of co-pending application Serial No. 464,832-which releases a propelling gas such as nitrogen through a reducing valve simultaneously to the vessels containing the respective liquids.
To prevent the possibility of the liquids prematurely mixing with each other. the propelling gas lines to the liquid vessels, and also the liquid feed lines to the burning nozzles, may be fitted with seals or diaphragms which will automatically rupture at pressures substantially below the operating pressures. The rupturing seals or diaphragms in the liquid iced lines. will of course be sufiiciently strong to withstand the gravity heads of the liquids themselves with a margin of safety. Diaphragms may be employed which are constructed as described in the specification of copending application Serial No. 498,442 (now abandoned).
The rapidly acting valve is preferably operated conjointly with the igniter, for example by electrical coupling, so that the apparatus can be started almost instantaneously by the operation,
for example, of a single electrical switch. There will be therefore substantially no delay period such as is usually associated with jet propulsion apparatus of the liquid combustion type. The control means according to the invention will assure the arrival of the liquids in the combustion chamber in a fraction of a second after the valve and igniter have been actuated. The igniter may be constructed as described in the specification of co-pending application Serial No. 464,833.
By using a reducing valve in the gas line leadins to the liquid vessels and by setting this valve at the appropriate pressure for metering the liquids through their respective nozzles against combustion chamber pressure, the change in pres-- sure of the propelling gas, on the high pressure side, as it becomes spent has no eflect on the rates of delivery. The nozzles for the liquids may be constructed as described in the specification of co-pending application Serial No. 493,800.
During the extremely short initial period before full pressure is established in the combustion chamber the nozzles will necessarily pass more than the steady amount but by introducing suitable chokes in the liquid and gas lines the amount of excess pressure at starting can be kept down to negligible proportions apart from the fact that the combustion chamber pressure as it builds up opposes the fiow through the nozzles.
The desired timed relationship of the arrivals of the respective liquids in the combustion chamber is obtainable by setting at calculated distances from the mixing nozzles the burster valves or diaphragms in the respective liquid lines. Preferably the setting is such that the liquid oxidant will arrive just before the liquid fuel.
Water, or other suitable liquid diluent, may be delivered into the combustion chamber to reduce the maximum, temperature of combustion and to improve the thermal efiiciency of the apparatus, a described in the specification of copending application Serial No. 493,802. The means for propelling the diluent liquid may be the same as for propelling the combustion liquids, including, if desired, a burster valve or diaphragm in the diluent liquid line set at a distance from the delivery nozzle or nozzles appropriate for securing delivery in proper timed relation with the deliveries of the combustion liquids.
The invention is illustrated by way of example in the accompanying diagrammatic drawmg.
Referring to the drawing. I indicates a combustion chamber, e. g. a combustion chamber for jet propulsion apparatus. 2 indicates ignition means for initiating combustion of liquids in the combustion chamber. 3 indicate nozzles for admitting liquids into the combustion chamber. 4 is a high pressure gas cylinder containing an inert gas such as nitrogen. 5 is an explosive operated rapidly opening valve such as described in application Serial No. 464,832. 8 is a reducing valve and I is a gas choke. The gas line has branches 66 leading to the liquid containers 8, 3 and It. In
the branch lines are rupturabie diaphragms al, a2, a3. Container 8 contains liquid oxidant, container 9 liquid fuel and container Ill water or other suitable liquid diluent.
From the containers issue liquid lines H, l! and i3 which lead to the nozzles 3.
In these liquid lines respectively are liquid choke Bi, B2, B3, and further along the respective lines are liquid rupturable diaphragms Al, A2, A3. These diaphragms are at different distances from the nozzles.
In operation, the igniting means 2 and valve 5 are conjointly operated by electrical means. The valve 5 rapidly opens and high pressure gas passes through the reducing valve 6 and gas choke i into the gas line whence it proceeds into the branch gas lines and immediately ruptures the diaphragms ai, a2, a3. Thereupon the containers 8, 9 and ID are subjected to high gas pressure and the liquids in'the liquid lines II, I! and I3 burst the rupturable diaphragms Al, A2, A3. The parts of the lines between these diaphragms and the nozzles were originally empty and therefore a very short period of time elapses before the liquids reach the nozzles after the diaphragms have been ruptured. The difierential distancing. of the diaphragms from the nozzles ensures that the liquid oxidant from con-- tainer 8 will be led into the combustion chamber Just before the liquid iuel arrives from the container 0. Very quickly after combustion has been initiated between these liquids. the water or other liquid diluent arrives through its nozzle.
I claim:
1. Control means for the supply of liquids to combustion apparatus comprising a source of propellant gas pressure, a plurality of containers for said liquids, a valve controlling the sup p y or propellant gas from said source to said containers, and lines connecting the respective containers with said apparatus, said lines containing automatically rupturable seals and the seals being located at diflerent distances from said apparatus so that the respective liquids reach said apparatus in a predetermined sequence.
2. Control means as defined in claim 1, said lines comprising liquid chokes located between the respective containers and rupturable seals.
3. Control means as defined in claim 1 wherein one of said containers holds a liquid fuel and another holds a liquid oxidant, the rupturable seal for said fuel being located further from said apparatus than the rupturable seal for said oxidant.
ISAAC LUBBOCK.
US493801A 1941-11-07 1943-07-07 Control means for jet propulsion apparatus Expired - Lifetime US2402826A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB14404/41A GB578262A (en) 1941-11-07 1941-11-07 Improved control means for jet propulsion apparatus

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US2402826A true US2402826A (en) 1946-06-25

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US (1) US2402826A (en)
FR (1) FR933019A (en)
GB (1) GB578262A (en)
NL (1) NL62547C (en)

Cited By (47)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2505798A (en) * 1946-06-20 1950-05-02 Leslie A Skinner Liquid fuel jet propulsion system
US2532708A (en) * 1940-11-19 1950-12-05 Daniel And Florence Guggenheim Scavenging system for rocket motors utilizing liquid nitrogen
US2628473A (en) * 1948-05-03 1953-02-17 Frye Jack Stationary power plant having radially and axially displaced jet engines
US2640529A (en) * 1950-08-01 1953-06-02 Us Army Automatic low pressure venting and signaling check valve for fuel tank pressurizing systems
US2648196A (en) * 1947-03-18 1953-08-11 Experiment Inc Ram jet burner with aqueous injection to promote smooth burning
US2671312A (en) * 1948-11-20 1954-03-09 Onera (Off Nat Aerospatiale) Device for feeding reagents to the mixing chambers of rockets
US2741085A (en) * 1952-05-12 1956-04-10 Phillips Petroleum Co Safety device, including fusible member for rocket engine starting control
US2784959A (en) * 1955-03-02 1957-03-12 Robert M Carson Safety apparatus for fluid-distribution lines
US2789505A (en) * 1951-08-23 1957-04-23 North American Aviation Inc Liquid propellent rocket
US2808080A (en) * 1953-06-23 1957-10-01 Dion-Biro Guy Constant-pressure spraying apparatus
US2808700A (en) * 1953-12-11 1957-10-08 Kretschmer Willi Propellant supply systems for jet reaction motors
US2852916A (en) * 1954-05-25 1958-09-23 Napier & Son Ltd Gas producing apparatus especially for rocket type propulsion devices
US2874539A (en) * 1953-12-28 1959-02-24 Phillips Petroleum Co Continuous combustion power plant
US2880582A (en) * 1956-04-19 1959-04-07 Clement J Turansky Starting assembly for a power plant
US2919543A (en) * 1957-08-06 1960-01-05 Sherman Arthur Fluid flow control means
US2926492A (en) * 1951-01-17 1960-03-01 Bendix Aviat Corp Self contained power plant using liquid decomposed into gaseous products
US2938577A (en) * 1956-10-04 1960-05-31 Air Reduction Method and apparatus for preventing backfire in gas burner systems
US2955413A (en) * 1957-08-19 1960-10-11 Hughes Aircraft Co Fuel supply system
US2959007A (en) * 1957-02-13 1960-11-08 Curtiss Wright Corp Jet engine ignition system utilizing pyrophoric fuel
US2960820A (en) * 1958-05-19 1960-11-22 Kurt K Neuhoefer Propulsion unit with fluid operated automatic stage switch
US2972225A (en) * 1950-12-04 1961-02-21 James M Cumming Motor mechanism for missiles
US2974619A (en) * 1950-01-13 1961-03-14 Walter M Bombl Fluid control system for torpedoes
US2980177A (en) * 1957-08-15 1961-04-18 Hughes Aircraft Co Expulsion-bag tank for liquid propellant
US3000179A (en) * 1959-12-11 1961-09-19 Samms Adolphus Rocket engine pump feed system
US3034293A (en) * 1959-04-06 1962-05-15 De Lacy F Ferris Booster and sustainer thrust devices
US3050940A (en) * 1952-12-12 1962-08-28 North American Aviation Inc Liquid propellant release mechanism
US3067810A (en) * 1960-03-21 1962-12-11 Thompson Ramo Wooldridge Inc Bladder fuel tank
US3073122A (en) * 1959-06-02 1963-01-15 United Aircraft Corp Rocket igniter
US3128601A (en) * 1960-09-15 1964-04-14 United Aircraft Corp Pre-burner rocket control system
US3134228A (en) * 1961-07-27 1964-05-26 Thompson Ramo Wooldridge Inc Propulsion system
US3154093A (en) * 1961-09-08 1964-10-27 Charles M Blackburn Fuel pressurization system
DE1187860B (en) * 1960-11-15 1965-02-25 United Aircraft Corp Control device for a liquid rocket
US3236419A (en) * 1964-02-10 1966-02-22 Continental Aviat & Eng Corp Foam dispenser
US3254488A (en) * 1963-03-27 1966-06-07 Mitsubishi Shipbuilding & Eng System for controlling a starting of an underwater self-propelling missile
US3365890A (en) * 1965-11-19 1968-01-30 Cerlini Eugene Hydraulic propulsion device
US3525217A (en) * 1968-04-29 1970-08-25 United Aircraft Corp Self-pressurized gas generation system
US3638669A (en) * 1970-05-22 1972-02-01 Us Navy Cantilevered breakaway fuel and oxidizer release
US3753349A (en) * 1966-09-05 1973-08-21 R Holmes Hydroplane construction
US3945203A (en) * 1972-10-06 1976-03-23 Lutz Tilo Kayser Liquid-fueled rocket
US4337619A (en) * 1981-05-08 1982-07-06 Vapor Energy, Inc. Hot water system
US4519769A (en) * 1983-06-02 1985-05-28 Akio Tanaka Apparatus and method for the combustion of water-in-oil emulsion fuels
US5709076A (en) * 1992-09-14 1998-01-20 Lawlor; Shawn P. Method and apparatus for power generation using rotating ramjet which compresses inlet air and expands exhaust gas against stationary peripheral wall
US5865207A (en) * 1995-10-30 1999-02-02 Daimler-Benz Aerospace Ag Releasing means
US6298653B1 (en) 1996-12-16 2001-10-09 Ramgen Power Systems, Inc. Ramjet engine for power generation
US6347507B1 (en) 1992-09-14 2002-02-19 Ramgen Power Systems, Inc. Method and apparatus for power generation using rotating ramjets
US6446425B1 (en) 1998-06-17 2002-09-10 Ramgen Power Systems, Inc. Ramjet engine for power generation
US20050150547A1 (en) * 2004-01-14 2005-07-14 Ballenger Devane R. Electric driven, integrated metering and shutoff valve for fluid flow control

Cited By (50)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2532708A (en) * 1940-11-19 1950-12-05 Daniel And Florence Guggenheim Scavenging system for rocket motors utilizing liquid nitrogen
US2505798A (en) * 1946-06-20 1950-05-02 Leslie A Skinner Liquid fuel jet propulsion system
US2648196A (en) * 1947-03-18 1953-08-11 Experiment Inc Ram jet burner with aqueous injection to promote smooth burning
US2628473A (en) * 1948-05-03 1953-02-17 Frye Jack Stationary power plant having radially and axially displaced jet engines
US2671312A (en) * 1948-11-20 1954-03-09 Onera (Off Nat Aerospatiale) Device for feeding reagents to the mixing chambers of rockets
US2974619A (en) * 1950-01-13 1961-03-14 Walter M Bombl Fluid control system for torpedoes
US2640529A (en) * 1950-08-01 1953-06-02 Us Army Automatic low pressure venting and signaling check valve for fuel tank pressurizing systems
US2972225A (en) * 1950-12-04 1961-02-21 James M Cumming Motor mechanism for missiles
US2926492A (en) * 1951-01-17 1960-03-01 Bendix Aviat Corp Self contained power plant using liquid decomposed into gaseous products
US2789505A (en) * 1951-08-23 1957-04-23 North American Aviation Inc Liquid propellent rocket
US2741085A (en) * 1952-05-12 1956-04-10 Phillips Petroleum Co Safety device, including fusible member for rocket engine starting control
US3050940A (en) * 1952-12-12 1962-08-28 North American Aviation Inc Liquid propellant release mechanism
US2808080A (en) * 1953-06-23 1957-10-01 Dion-Biro Guy Constant-pressure spraying apparatus
US2808700A (en) * 1953-12-11 1957-10-08 Kretschmer Willi Propellant supply systems for jet reaction motors
US2874539A (en) * 1953-12-28 1959-02-24 Phillips Petroleum Co Continuous combustion power plant
US2852916A (en) * 1954-05-25 1958-09-23 Napier & Son Ltd Gas producing apparatus especially for rocket type propulsion devices
US2784959A (en) * 1955-03-02 1957-03-12 Robert M Carson Safety apparatus for fluid-distribution lines
US2880582A (en) * 1956-04-19 1959-04-07 Clement J Turansky Starting assembly for a power plant
US2938577A (en) * 1956-10-04 1960-05-31 Air Reduction Method and apparatus for preventing backfire in gas burner systems
US2959007A (en) * 1957-02-13 1960-11-08 Curtiss Wright Corp Jet engine ignition system utilizing pyrophoric fuel
US2919543A (en) * 1957-08-06 1960-01-05 Sherman Arthur Fluid flow control means
US2980177A (en) * 1957-08-15 1961-04-18 Hughes Aircraft Co Expulsion-bag tank for liquid propellant
US2955413A (en) * 1957-08-19 1960-10-11 Hughes Aircraft Co Fuel supply system
US2960820A (en) * 1958-05-19 1960-11-22 Kurt K Neuhoefer Propulsion unit with fluid operated automatic stage switch
US3034293A (en) * 1959-04-06 1962-05-15 De Lacy F Ferris Booster and sustainer thrust devices
US3073122A (en) * 1959-06-02 1963-01-15 United Aircraft Corp Rocket igniter
US3000179A (en) * 1959-12-11 1961-09-19 Samms Adolphus Rocket engine pump feed system
US3067810A (en) * 1960-03-21 1962-12-11 Thompson Ramo Wooldridge Inc Bladder fuel tank
US3128601A (en) * 1960-09-15 1964-04-14 United Aircraft Corp Pre-burner rocket control system
DE1187860B (en) * 1960-11-15 1965-02-25 United Aircraft Corp Control device for a liquid rocket
US3134228A (en) * 1961-07-27 1964-05-26 Thompson Ramo Wooldridge Inc Propulsion system
US3154093A (en) * 1961-09-08 1964-10-27 Charles M Blackburn Fuel pressurization system
US3254488A (en) * 1963-03-27 1966-06-07 Mitsubishi Shipbuilding & Eng System for controlling a starting of an underwater self-propelling missile
US3236419A (en) * 1964-02-10 1966-02-22 Continental Aviat & Eng Corp Foam dispenser
US3365890A (en) * 1965-11-19 1968-01-30 Cerlini Eugene Hydraulic propulsion device
US3753349A (en) * 1966-09-05 1973-08-21 R Holmes Hydroplane construction
US3525217A (en) * 1968-04-29 1970-08-25 United Aircraft Corp Self-pressurized gas generation system
US3638669A (en) * 1970-05-22 1972-02-01 Us Navy Cantilevered breakaway fuel and oxidizer release
US3945203A (en) * 1972-10-06 1976-03-23 Lutz Tilo Kayser Liquid-fueled rocket
US4337619A (en) * 1981-05-08 1982-07-06 Vapor Energy, Inc. Hot water system
US4519769A (en) * 1983-06-02 1985-05-28 Akio Tanaka Apparatus and method for the combustion of water-in-oil emulsion fuels
US6347507B1 (en) 1992-09-14 2002-02-19 Ramgen Power Systems, Inc. Method and apparatus for power generation using rotating ramjets
US5709076A (en) * 1992-09-14 1998-01-20 Lawlor; Shawn P. Method and apparatus for power generation using rotating ramjet which compresses inlet air and expands exhaust gas against stationary peripheral wall
US5865207A (en) * 1995-10-30 1999-02-02 Daimler-Benz Aerospace Ag Releasing means
US6298653B1 (en) 1996-12-16 2001-10-09 Ramgen Power Systems, Inc. Ramjet engine for power generation
US6334299B1 (en) 1996-12-16 2002-01-01 Ramgen Power Systems, Inc. Ramjet engine for power generation
US6434924B1 (en) 1996-12-16 2002-08-20 Ramgen Power Systems, Inc. Ramjet engine for power generation
US6446425B1 (en) 1998-06-17 2002-09-10 Ramgen Power Systems, Inc. Ramjet engine for power generation
US20050150547A1 (en) * 2004-01-14 2005-07-14 Ballenger Devane R. Electric driven, integrated metering and shutoff valve for fluid flow control
US7273068B2 (en) * 2004-01-14 2007-09-25 Honeywell International, Inc. Electric driven, integrated metering and shutoff valve for fluid flow control

Also Published As

Publication number Publication date
FR933019A (en) 1948-04-08
NL62547C (en) 1900-01-01
GB578262A (en) 1946-06-21

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