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Publication numberUS2402826 A
Publication typeGrant
Publication dateJun 25, 1946
Filing dateJul 7, 1943
Priority dateNov 7, 1941
Publication numberUS 2402826 A, US 2402826A, US-A-2402826, US2402826 A, US2402826A
InventorsIsaac Lubbock
Original AssigneeAsiatic Petroleum Co Ltd
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Control means for jet propulsion apparatus
US 2402826 A
Abstract  available in
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)

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.


Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2505798 *Jun 20, 1946May 2, 1950Skinner Leslie ALiquid fuel jet propulsion system
US2532708 *Feb 1, 1946Dec 5, 1950Daniel And Florence GuggenheimScavenging system for rocket motors utilizing liquid nitrogen
US2628473 *May 3, 1948Feb 17, 1953Frye JackStationary power plant having radially and axially displaced jet engines
US2640529 *Aug 1, 1950Jun 2, 1953Us ArmyAutomatic low pressure venting and signaling check valve for fuel tank pressurizing systems
US2648196 *Mar 18, 1947Aug 11, 1953Experiment IncRam jet burner with aqueous injection to promote smooth burning
US2671312 *Nov 14, 1949Mar 9, 1954Onera (Off Nat Aerospatiale)Device for feeding reagents to the mixing chambers of rockets
US2741085 *May 12, 1952Apr 10, 1956Phillips Petroleum CoSafety device, including fusible member for rocket engine starting control
US2784959 *Mar 2, 1955Mar 12, 1957Carson Robert MSafety apparatus for fluid-distribution lines
US2789505 *Aug 23, 1951Apr 23, 1957North American Aviation IncLiquid propellent rocket
US2808080 *Jun 18, 1954Oct 1, 1957Guy Dion-BiroConstant-pressure spraying apparatus
US2808700 *Dec 11, 1953Oct 8, 1957Willi KretschmerPropellant supply systems for jet reaction motors
US2852916 *May 13, 1955Sep 23, 1958Napier & Son LtdGas producing apparatus especially for rocket type propulsion devices
US2874539 *Dec 28, 1953Feb 24, 1959Phillips Petroleum CoContinuous combustion power plant
US2880582 *Apr 19, 1956Apr 7, 1959Pirrone Sylvester JStarting assembly for a power plant
US2919543 *Aug 6, 1957Jan 5, 1960Arthur ShermanFluid flow control means
US2926492 *Jan 17, 1951Mar 1, 1960Bendix Aviat CorpSelf contained power plant using liquid decomposed into gaseous products
US2938577 *Oct 4, 1956May 31, 1960Air ReductionMethod and apparatus for preventing backfire in gas burner systems
US2955413 *Aug 19, 1957Oct 11, 1960Hughes Aircraft CoFuel supply system
US2959007 *Feb 13, 1957Nov 8, 1960Curtiss Wright CorpJet engine ignition system utilizing pyrophoric fuel
US2960820 *May 19, 1958Nov 22, 1960Neuhoefer Kurt KPropulsion unit with fluid operated automatic stage switch
US2972225 *Dec 4, 1950Feb 21, 1961Cumming James MMotor mechanism for missiles
US2974619 *Jan 13, 1950Mar 14, 1961Bombl Walter MFluid control system for torpedoes
US2980177 *Aug 15, 1957Apr 18, 1961Hughes Aircraft CoExpulsion-bag tank for liquid propellant
US3000179 *Dec 11, 1959Sep 19, 1961Adolphus SammsRocket engine pump feed system
US3034293 *Apr 6, 1959May 15, 1962Ferris De Lacy FBooster and sustainer thrust devices
US3050940 *Dec 12, 1952Aug 28, 1962North American Aviation IncLiquid propellant release mechanism
US3067810 *Mar 21, 1960Dec 11, 1962Thompson Ramo Wooldridge IncBladder fuel tank
US3073122 *Jun 2, 1959Jan 15, 1963United Aircraft CorpRocket igniter
US3128601 *Sep 15, 1960Apr 14, 1964United Aircraft CorpPre-burner rocket control system
US3134228 *Jul 27, 1961May 26, 1964Thompson Ramo Wooldridge IncPropulsion system
US3154093 *Sep 8, 1961Oct 27, 1964Blackburn Charles MFuel pressurization system
US3236419 *Feb 10, 1964Feb 22, 1966Continental Aviat & Eng CorpFoam dispenser
US3254488 *Mar 17, 1964Jun 7, 1966Mitsubishi Shipbuilding & EngSystem for controlling a starting of an underwater self-propelling missile
US3365890 *Feb 10, 1966Jan 30, 1968Cerlini EugeneHydraulic propulsion device
US3525217 *Apr 29, 1968Aug 25, 1970United Aircraft CorpSelf-pressurized gas generation system
US3638669 *May 22, 1970Feb 1, 1972Us NavyCantilevered breakaway fuel and oxidizer release
US3753349 *Jul 12, 1971Aug 21, 1973Holmes RHydroplane construction
US3945203 *Oct 4, 1973Mar 23, 1976Lutz Tilo KayserLiquid-fueled rocket
US4337619 *May 8, 1981Jul 6, 1982Vapor Energy, Inc.Hot water system
US4519769 *Nov 15, 1983May 28, 1985Akio TanakaApparatus and method for the combustion of water-in-oil emulsion fuels
US5709076 *Jun 7, 1995Jan 20, 1998Lawlor; Shawn P.Method and apparatus for power generation using rotating ramjet which compresses inlet air and expands exhaust gas against stationary peripheral wall
US5865207 *Oct 22, 1996Feb 2, 1999Daimler-Benz Aerospace AgRocket fuel lines
US6298653Mar 9, 2000Oct 9, 2001Ramgen Power Systems, Inc.Ramjet engine for power generation
US6334299Dec 16, 1997Jan 1, 2002Ramgen Power Systems, Inc.Ramjet engine for power generation
US6347507May 25, 1999Feb 19, 2002Ramgen Power Systems, Inc.Method and apparatus for power generation using rotating ramjets
US6434924Mar 9, 2000Aug 20, 2002Ramgen Power Systems, Inc.Ramjet engine for power generation
US6446425Jun 17, 1999Sep 10, 2002Ramgen Power Systems, Inc.Ramjet engine for power generation
US7273068 *Mar 5, 2004Sep 25, 2007Honeywell International, Inc.Electric driven, integrated metering and shutoff valve for fluid flow control
DE1187860B *Dec 2, 1960Feb 25, 1965United Aircraft CorpSteuereinrichtung fuer eine Fluessigkeitsrakete
U.S. Classification60/39.48, 137/72, 60/39.55, 222/135, 137/266, 137/68.13, 222/394, 251/118, 60/786, 137/203, 60/259, 137/68.23, 60/264
International ClassificationF02K9/00, F02K9/50
Cooperative ClassificationF02K9/50
European ClassificationF02K9/50