US2532708A - Scavenging system for rocket motors utilizing liquid nitrogen - Google Patents
Scavenging system for rocket motors utilizing liquid nitrogen Download PDFInfo
- Publication number
- US2532708A US2532708A US644847A US64484746A US2532708A US 2532708 A US2532708 A US 2532708A US 644847 A US644847 A US 644847A US 64484746 A US64484746 A US 64484746A US 2532708 A US2532708 A US 2532708A
- Authority
- US
- United States
- Prior art keywords
- liquid
- tank
- liquid nitrogen
- combustion
- connections
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/566—Control elements and safety devices, e.g. pressure relief valves
-
- Y—GENERAL 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S60/00—Power plants
- Y10S60/915—Collection of goddard patents
Definitions
- This invention relates to apparatus for feeding combustion liquids to a combustion chamber and is a division of Goddard application Serial No. 366,316, filed November 19, 1940, which issued March 12, 1946 as Patent No. 2,396,567.
- the invention is particularly adapted for use in rocket apparatus or in other jet-propelled apparatus in which continuous combustion takes place in a combustion chamber having a normally open rearward discharge nozzle, and in which the combustion elements are supplied in liquid form and at very low temperatures.
- a combustion chamber having a normally open rearward discharge nozzle
- the combustion elements are supplied in liquid form and at very low temperatures.
- Thepresent application relates particularly to the construction shown in Fig. 15 of said original application and is concerned with the feeding of low-temperature combustion liquids to such a combustion chamber and with the scavenging of the connections to said combustion chamber on discontinuance of feed by filling said connections with an inert liquid or gas.
- the invention is of particular utility where the combustible, oxidizing and scavenging fluids are all liquids but only at very low temperatures.
- liquid propane may be used as the combustible liquid
- liquid oxygen as the oxidizing agent
- liquid nitrogen as the inert scavenging agent. All of these products are normally gaseous and are liquid only at extremely low temperatures.
- a preferred form of the invention is shown in the drawing which is a sectional elevation of one form of apparatus embodying the invention.
- the invention is shown as associated with a combustion chamber C which comprises an inner chamber wall 30, an intermediate wall 3 l, and an outer wall 33, said latter wall being surrounded by a casing 34 spaced therefrom by any suitable insulating material M.
- is designed to receive liquid fuel, as propane, from an inner pressure storage tank 10 and to deliver said fuel to the chamber C in the form of sprays through short nozzle tubes 40.
- the space G between the middle wall 3! and the outer wall 33 is similarly adapted to receive liquid oxygen from the pressure storage space around the tank 10 and within an outer enclosing tank II. The liquid oxygen is fed from the ill space G- to the chamber C in the form of sprays delivered through relatively long tubular noz zles42.
- each nozzle 40 and 42 is shown in the drawing but it will be understood that a multiplicity of such nozzles are provided, as shown and described in the original specification.
- Pipes 35 and 38 connect the tanks 10 and H to the spaces F and G, which latter spaces form in effect jackets for the combustion chamber C. Valves 12 control the feed through the pipes 35 and 38.
- the tanks '56 and H are filled through feed pipes 19 and 8B, and pressure relief valves 82 are provided for safety;
- a small inner storage tank 15 is enclosed with in the fuel tank 10 and is preferably located near the lower end thereof, as clearly shown in the drawing.
- This tank 15 is provided with a filler pipe 8! and with a delivery pipe 16 having branches l1 connected through valves E8 to the outlet portions of the pipes 36 and 38 beyond the valves 12.
- the inner tank 15 contains liquid nitrogen or some other inert low-temperature liquid under pressure. Any usual shut-off valve (not shown) is to be provided above the relief valve in the pipe 82, as the tank 15 must be held under pressure.
- the boiling point of liquid oxygen being somewhat lower than the boiling point of propane, the immersion of the fuel tank 10 in the liquid oxygen maintains the propane below its boiling point and thus prevents formation of vapor which might cause gas-bind in the fuel feed pipe 36.
- the liquid nitrogen from the tank 15 is utilized for scavenging or clearing the portions of the pipes 36 and 38 below the valves 12, and also for neutralizing the jacket spaces F and G surrounding the combustion chamber.
- valves 12 are closed to shut off further combustion, and the valves l8 are then opened to allow liquid nitrogen to flow into the lower ends of the pipes 36 and 38, thus forcing out any remnants of oxygen or propane which may have been left therein.
- the tanks 10 and H may be conveniently filled by first filling the outer tank H with liquid oxygen, and then injecting propane gas into the tank 70, where it is condensed by the very low temperature of the surrounding liquid oxygen.
- feeding apparatus which comprises an outer tank for a low-temperature oxidizing liquid, an inner tank for a low-temperature combustible liquid, feeding connections from said tanks to separate chamber-jacketing spaces, means to control the flow of said liquids to said jacket spaces, feeding connections from said jacket spaces to said combustion chamber, and separate means to supply a low temperature inert liquid to scavenge all of said feeding connections and said jacket spaces after flow of said combustion liquids is discontinued.
- feeding apparatus which comprises an outer tank for a low-temperature oxidizing liquid, an inner tank for a low-temperature combustible liquid, feeding connections from said tanks to separate chamber-jacketing spaces, means to control the flow of said liquids to said jacket spaces, feeding connections from said jacket spaces to said combustion chamber, an auxiliary tank within said inner tank for an inert liquid, and feeding connections from said auxiliary tank to said first-named feeding connections, whereby all of said connections and said jacket spaces are iii) scavenged by said inert liquid after flow of said combustion liquids is discontinued.
- feeding apparatus which comprises an outer tank for a lowtemperature oxidizing liquid, an inner tank for a low-temperature combustible liquid, feeding connections from said tanks to said combustion chamber, valves to control the feed of said liquids through said connections, an auxiliary tank within said inner tank for an inert liquid, pipes connecting said auxiliary tank to said feeding connections beyond said control valves, and additional valves to control the flow of said inert liquid through said pipes, whereby said connections are scavenged after flow of said combustion liquids is discontinued.
Description
Dec. 5, 1950 R. H. GODDARD SCAVENGING SYSTEM FOR ROCKET MOTORS UTILIZING LIQUID NITROGEN Original Filed Nov. 19, 1940 8g REL Ill/Ill 7 REL 82%;;
Patented Dec. 5, 1950 UNITED STATES SCAVENGING SYSTEM FOR ROCKET MO- TORS UTILIZING LIQUID NITROGEN Robert H. Goddard, deceased, late of Annapolis, Md, by Esther C. Goddard, exeoutrix, Paxton, Mass, assignor of one-half to The Daniel and Florence Guggenheim Foundation, New York, N. Y., a corporation of New York Original application November 19, 1940, Serial No. 366,316, new Patent No. 2,396,567, dated March 12, 1946. Divided and this application February 1, 1946, Serial No. 644,847
3 Claims.
This invention relates to apparatus for feeding combustion liquids to a combustion chamber and is a division of Goddard application Serial No. 366,316, filed November 19, 1940, which issued March 12, 1946 as Patent No. 2,396,567.
The invention is particularly adapted for use in rocket apparatus or in other jet-propelled apparatus in which continuous combustion takes place in a combustion chamber having a normally open rearward discharge nozzle, and in which the combustion elements are supplied in liquid form and at very low temperatures. For .a more complete disclosure of such apparatus, reference is made to the Goddard Patent No. 2,396,567, of which this is a divisional application.
Thepresent application relates particularly to the construction shown in Fig. 15 of said original application and is concerned with the feeding of low-temperature combustion liquids to such a combustion chamber and with the scavenging of the connections to said combustion chamber on discontinuance of feed by filling said connections with an inert liquid or gas.
The invention is of particular utility where the combustible, oxidizing and scavenging fluids are all liquids but only at very low temperatures. As an illustrative example, liquid propane may be used as the combustible liquid, liquid oxygen as the oxidizing agent, and liquid nitrogen as the inert scavenging agent. All of these products are normally gaseous and are liquid only at extremely low temperatures.
The invention further relates to arrangements and combinations of parts which will be hereinafter described and more particularly pointed out in the appended claims.
A preferred form of the invention is shown in the drawing which is a sectional elevation of one form of apparatus embodying the invention.
The invention is shown as associated with a combustion chamber C which comprises an inner chamber wall 30, an intermediate wall 3 l, and an outer wall 33, said latter wall being surrounded by a casing 34 spaced therefrom by any suitable insulating material M.
The space F between the inner wall 30 and the middle wall 3| is designed to receive liquid fuel, as propane, from an inner pressure storage tank 10 and to deliver said fuel to the chamber C in the form of sprays through short nozzle tubes 40. The space G between the middle wall 3! and the outer wall 33 is similarly adapted to receive liquid oxygen from the pressure storage space around the tank 10 and within an outer enclosing tank II. The liquid oxygen is fed from the ill space G- to the chamber C in the form of sprays delivered through relatively long tubular noz zles42.
One only of each nozzle 40 and 42 is shown in the drawing but it will be understood that a multiplicity of such nozzles are provided, as shown and described in the original specification.
A small inner storage tank 15 is enclosed with in the fuel tank 10 and is preferably located near the lower end thereof, as clearly shown in the drawing. This tank 15 is provided with a filler pipe 8! and with a delivery pipe 16 having branches l1 connected through valves E8 to the outlet portions of the pipes 36 and 38 beyond the valves 12. The inner tank 15 contains liquid nitrogen or some other inert low-temperature liquid under pressure. Any usual shut-off valve (not shown) is to be provided above the relief valve in the pipe 82, as the tank 15 must be held under pressure.
The boiling point of liquid oxygen being somewhat lower than the boiling point of propane, the immersion of the fuel tank 10 in the liquid oxygen maintains the propane below its boiling point and thus prevents formation of vapor which might cause gas-bind in the fuel feed pipe 36.
As a violently explosive mixture may easily be formed in the combustion chamber C if any remnants of oxygen and propane are left therein after combustion is stopped, the liquid nitrogen from the tank 15 is utilized for scavenging or clearing the portions of the pipes 36 and 38 below the valves 12, and also for neutralizing the jacket spaces F and G surrounding the combustion chamber.
To effect this operation, the valves 12 are closed to shut off further combustion, and the valves l8 are then opened to allow liquid nitrogen to flow into the lower ends of the pipes 36 and 38, thus forcing out any remnants of oxygen or propane which may have been left therein.
As the liquid nitrogen flows into the jacket spaces F and G, it will quickly start to vaporize and will force out of the jacket spaces F and G substantially all oxygen or propane which may have been left therein. If any remnants of oxygen and propane still remain, they will be so di- 3 luted by the inert nitrogen gas as to be incapable of forming an explosive mixture.
The tanks 10 and H may be conveniently filled by first filling the outer tank H with liquid oxygen, and then injecting propane gas into the tank 70, where it is condensed by the very low temperature of the surrounding liquid oxygen.
Having thus described the invention and the advantages thereof, it will be understood that the invention is not to be limited to the details herein disclosed, otherwise than as set forth in the claims, but that what is claimed is:
1. In combustion apparatus including a double jacketed combustion chamber, that improvement in feeding apparatus which comprises an outer tank for a low-temperature oxidizing liquid, an inner tank for a low-temperature combustible liquid, feeding connections from said tanks to separate chamber-jacketing spaces, means to control the flow of said liquids to said jacket spaces, feeding connections from said jacket spaces to said combustion chamber, and separate means to supply a low temperature inert liquid to scavenge all of said feeding connections and said jacket spaces after flow of said combustion liquids is discontinued.
2. In combustion apparatus including a double jacketed combustion chamber, that improvement in feeding apparatus which comprises an outer tank for a low-temperature oxidizing liquid, an inner tank for a low-temperature combustible liquid, feeding connections from said tanks to separate chamber-jacketing spaces, means to control the flow of said liquids to said jacket spaces, feeding connections from said jacket spaces to said combustion chamber, an auxiliary tank within said inner tank for an inert liquid, and feeding connections from said auxiliary tank to said first-named feeding connections, whereby all of said connections and said jacket spaces are iii) scavenged by said inert liquid after flow of said combustion liquids is discontinued.
3. In combustion apparatus including a com-, bustion chamber, that improvement in feeding apparatus which comprises an outer tank for a lowtemperature oxidizing liquid, an inner tank for a low-temperature combustible liquid, feeding connections from said tanks to said combustion chamber, valves to control the feed of said liquids through said connections, an auxiliary tank within said inner tank for an inert liquid, pipes connecting said auxiliary tank to said feeding connections beyond said control valves, and additional valves to control the flow of said inert liquid through said pipes, whereby said connections are scavenged after flow of said combustion liquids is discontinued.
ESTHER C. GODDARD, Ezcecutrix of the Last Will and Testament of Robert H. Goddard, Deceased.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 662,165 Cahill Nov. 20, 1900 694,305 Branch Feb. 25, 1902 1,145,389 Schneider July 6, 1915 1,340,012 Cave et a1 May 11, 1920 1,500,880 Morgan July 8, 1924 1,610,290 Jones et al Dec. 14, 1926 1,735,911 *Sundstrand Nov. 19, 1929 2,396,567 Goddard Mar. 12, 1946 2,397,657 Goddard Apr. 2, 1946 2,402,826 Lubbock June 25, 1946 2,406,926 Summerfield Sept. 3, 1946
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US644847A US2532708A (en) | 1940-11-19 | 1946-02-01 | Scavenging system for rocket motors utilizing liquid nitrogen |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US366316A US2396567A (en) | 1940-11-19 | 1940-11-19 | Combustion apparatus |
US644847A US2532708A (en) | 1940-11-19 | 1946-02-01 | Scavenging system for rocket motors utilizing liquid nitrogen |
Publications (1)
Publication Number | Publication Date |
---|---|
US2532708A true US2532708A (en) | 1950-12-05 |
Family
ID=27003314
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US644847A Expired - Lifetime US2532708A (en) | 1940-11-19 | 1946-02-01 | Scavenging system for rocket motors utilizing liquid nitrogen |
Country Status (1)
Country | Link |
---|---|
US (1) | US2532708A (en) |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2601607A (en) * | 1949-01-03 | 1952-06-24 | Havilland Engine Co Ltd | Propellant injection system for rocket motors |
US2634577A (en) * | 1949-01-03 | 1953-04-14 | Havilland Engine Co Ltd | Compact container arrangement for propellant feeding means of rockets |
US2939778A (en) * | 1956-06-21 | 1960-06-07 | Air Prod Inc | Liquid explosive |
US3011321A (en) * | 1957-12-02 | 1961-12-05 | Texaco Inc | Apparatus for the maintenance of liquefied petroleum products |
US3050936A (en) * | 1959-06-30 | 1962-08-28 | United Aircraft Corp | Purge system for rocket propellant system |
US3085393A (en) * | 1958-06-03 | 1963-04-16 | North American Aviation Inc | Rocket engine starting method |
US3122885A (en) * | 1961-06-19 | 1964-03-03 | Marcus F Heidmann | Injector for bipropellant rocket engines |
US3132482A (en) * | 1959-06-23 | 1964-05-12 | United Aircraft Corp | Injector head for liquid rocket |
US3136121A (en) * | 1960-02-12 | 1964-06-09 | Aerojet General Co | System for pressurizing and expelling cryogenic liquids |
US3350229A (en) * | 1962-01-27 | 1967-10-31 | Siemens Schuckertwerke | Method and apparatus for storing gaseous fuel for the operation of fuel cells |
US4796432A (en) * | 1987-10-09 | 1989-01-10 | Unisys Corporation | Long hold time cryogens dewar |
US5282357A (en) * | 1990-04-19 | 1994-02-01 | Trw Inc. | High-performance dual-mode integral propulsion system |
US5417049A (en) * | 1990-04-19 | 1995-05-23 | Trw Inc. | Satellite propulsion and power system |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US662165A (en) * | 1899-07-01 | 1900-11-20 | Mortimer Cahill | Lamp. |
US694305A (en) * | 1900-09-26 | 1902-02-25 | Joseph G Branch | Means for producing pressure on the hydrocarbon in portable reservoirs. |
US1145389A (en) * | 1914-07-30 | 1915-07-06 | Eugene Schneider | Automobile torpedo. |
US1340012A (en) * | 1918-04-27 | 1920-05-11 | Davis Bournonville Co | Flame-projector apparatus |
US1500880A (en) * | 1923-05-05 | 1924-07-08 | Morgan George Urquhart | Liquid-fuel burner |
US1610290A (en) * | 1923-09-18 | 1926-12-14 | Jones John Paul | Liquid-fuel burner and control means therefor |
US1735911A (en) * | 1925-12-02 | 1929-11-19 | Sundstrand Engineering Company | Automatic oil burner |
US2396567A (en) * | 1940-11-19 | 1946-03-12 | Daniel And Florence Guggenheim | Combustion apparatus |
US2397657A (en) * | 1941-06-23 | 1946-04-02 | Daniel And Florence Guggenheim | Control mechanism for rocket apparatus |
US2402826A (en) * | 1941-11-07 | 1946-06-25 | Asiatic Petroleum Co Ltd | Control means for jet propulsion apparatus |
US2406926A (en) * | 1943-08-06 | 1946-09-03 | Aerojet Engineering Corp | System of jet propulsion |
-
1946
- 1946-02-01 US US644847A patent/US2532708A/en not_active Expired - Lifetime
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US662165A (en) * | 1899-07-01 | 1900-11-20 | Mortimer Cahill | Lamp. |
US694305A (en) * | 1900-09-26 | 1902-02-25 | Joseph G Branch | Means for producing pressure on the hydrocarbon in portable reservoirs. |
US1145389A (en) * | 1914-07-30 | 1915-07-06 | Eugene Schneider | Automobile torpedo. |
US1340012A (en) * | 1918-04-27 | 1920-05-11 | Davis Bournonville Co | Flame-projector apparatus |
US1500880A (en) * | 1923-05-05 | 1924-07-08 | Morgan George Urquhart | Liquid-fuel burner |
US1610290A (en) * | 1923-09-18 | 1926-12-14 | Jones John Paul | Liquid-fuel burner and control means therefor |
US1735911A (en) * | 1925-12-02 | 1929-11-19 | Sundstrand Engineering Company | Automatic oil burner |
US2396567A (en) * | 1940-11-19 | 1946-03-12 | Daniel And Florence Guggenheim | Combustion apparatus |
US2397657A (en) * | 1941-06-23 | 1946-04-02 | Daniel And Florence Guggenheim | Control mechanism for rocket apparatus |
US2402826A (en) * | 1941-11-07 | 1946-06-25 | Asiatic Petroleum Co Ltd | Control means for jet propulsion apparatus |
US2406926A (en) * | 1943-08-06 | 1946-09-03 | Aerojet Engineering Corp | System of jet propulsion |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2634577A (en) * | 1949-01-03 | 1953-04-14 | Havilland Engine Co Ltd | Compact container arrangement for propellant feeding means of rockets |
US2601607A (en) * | 1949-01-03 | 1952-06-24 | Havilland Engine Co Ltd | Propellant injection system for rocket motors |
US2939778A (en) * | 1956-06-21 | 1960-06-07 | Air Prod Inc | Liquid explosive |
US3011321A (en) * | 1957-12-02 | 1961-12-05 | Texaco Inc | Apparatus for the maintenance of liquefied petroleum products |
US3085393A (en) * | 1958-06-03 | 1963-04-16 | North American Aviation Inc | Rocket engine starting method |
US3132482A (en) * | 1959-06-23 | 1964-05-12 | United Aircraft Corp | Injector head for liquid rocket |
US3050936A (en) * | 1959-06-30 | 1962-08-28 | United Aircraft Corp | Purge system for rocket propellant system |
US3136121A (en) * | 1960-02-12 | 1964-06-09 | Aerojet General Co | System for pressurizing and expelling cryogenic liquids |
US3122885A (en) * | 1961-06-19 | 1964-03-03 | Marcus F Heidmann | Injector for bipropellant rocket engines |
US3350229A (en) * | 1962-01-27 | 1967-10-31 | Siemens Schuckertwerke | Method and apparatus for storing gaseous fuel for the operation of fuel cells |
US4796432A (en) * | 1987-10-09 | 1989-01-10 | Unisys Corporation | Long hold time cryogens dewar |
US5282357A (en) * | 1990-04-19 | 1994-02-01 | Trw Inc. | High-performance dual-mode integral propulsion system |
US5417049A (en) * | 1990-04-19 | 1995-05-23 | Trw Inc. | Satellite propulsion and power system |
US5572865A (en) * | 1990-04-19 | 1996-11-12 | Trw Inc. | Satellite propulsion and power system |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2532708A (en) | Scavenging system for rocket motors utilizing liquid nitrogen | |
US2523656A (en) | Combustion apparatus comprising successive combustion chambers | |
US2558483A (en) | Feeding apparatus, including injectors adapted to supply combustion liquids under pressure to a combustion chamber | |
US2683963A (en) | Reaction engine with automatic pressure regulation | |
US2500334A (en) | Jet motor operable by monopropellant and method of operating it | |
US2930184A (en) | Method and apparatus for hydrazine decomposition | |
US6101808A (en) | Cryogenic solid hybrid rocket engine and method of propelling a rocket | |
US2551112A (en) | Premixing combustion chamber | |
US2482260A (en) | Liquid feeding device | |
US2612752A (en) | Feeding apparatus, including injectors adapted to supply combustion liquids under pressure to a combustion chamber | |
US2510572A (en) | Mixing partition for combustion chambers | |
US2749706A (en) | Mechanism for cooling a combustion chamber in propulsion apparatus and for feeding combustion liquids thereto | |
US2396567A (en) | Combustion apparatus | |
US2526222A (en) | Cooling and feeding means for rocket type combustion chambers | |
US3085393A (en) | Rocket engine starting method | |
US2487435A (en) | Fuel and water feeding and steam discharge arrangement for combustion chambers | |
US2654997A (en) | Two-liquid combustion chamber for rocket apparatus | |
US2637161A (en) | Process of ignition for rockets and the like | |
US2395406A (en) | Combustion apparatus | |
US2536597A (en) | Recoil-operated feeding apparatus for a combustion chamber used in aerial propulsion | |
US2555081A (en) | Means for supplying liquids to an annular rotating combustion chamber | |
US2569887A (en) | Combustion apparatus, including flame type ignition means | |
US3533232A (en) | Organic fusible solid fuel binders and stabilizers | |
Stoddard | Experimental Investigation of N 2 O/O 2 Mixtures as Volumetrically Efficient Oxidizers for Small Spacecraft Hybrid Propulsion Systems | |
US2526223A (en) | Pressurized jacket construction for rotating combustion chambers |