US2818914A - System of containers for at least two liquids and a pressure gas - Google Patents

System of containers for at least two liquids and a pressure gas Download PDF

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Publication number
US2818914A
US2818914A US412840A US41284054A US2818914A US 2818914 A US2818914 A US 2818914A US 412840 A US412840 A US 412840A US 41284054 A US41284054 A US 41284054A US 2818914 A US2818914 A US 2818914A
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US
United States
Prior art keywords
containers
pressure gas
pressure
container
gas container
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
Application number
US412840A
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English (en)
Inventor
Thomann Hans
Steck Arnold
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rheinmetall Air Defence AG
Original Assignee
Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Werkzeugmaschinenfabrik Oerlikon Buhrle AG filed Critical Werkzeugmaschinenfabrik Oerlikon Buhrle AG
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Publication of US2818914A publication Critical patent/US2818914A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B11/00—Equalisation of pulses, e.g. by use of air vessels; Counteracting cavitation
    • F04B11/0008—Equalisation of pulses, e.g. by use of air vessels; Counteracting cavitation using accumulators
    • F04B11/0016—Equalisation of pulses, e.g. by use of air vessels; Counteracting cavitation using accumulators with a fluid spring
    • 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
    • F02K9/50—Feeding propellants using pressurised fluid to pressurise the propellants
    • 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
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/605—Reservoirs
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/2931—Diverse fluid containing pressure systems
    • Y10T137/3115—Gas pressure storage over or displacement of liquid
    • Y10T137/3124—Plural units

Definitions

  • Thepresent invention relates to a system of containers for at least two liquids and a pressure gas, for jexample as used in liquid propulsion means for rockets.
  • Such rocket propulsion means operate mostly with self-igniting fuel combinations which consist of the fuel proper and an oxygen caf'rier. These fuel components must be stored separately from one another, and fed through separate pipe lines to the combustion chamber, where they ignite spontaneously upon meeting with one another.
  • the separate arrangement of the containers has the disadvantage of great requirement of space in the interior of the rocket body. It has therefore been suggested, to shape the pressure gas container cylindrically and to arrange it in the axis of the rocket, and to construct the containers for the fuel and for the oxygen carrier as pipe coils, helically wound around the pressure gas container.
  • the present invention has the main objects of overcoming these difficulties and of providing a system of containers for at least two liquids and a pressure gas, which is simple and inexpensive in production, and reliable in operation.
  • a systern of containers for at least two liquids and one pressure gas comprising in combination: a central cylindrical pressure gas container and at least two cylindrical liquid containers coaxially surrounding the said central pressure gas container and one another, annular free pistons shiftably arranged between the outer wall surface of the said central pressure gas container and the inner wall face of the smallest coaxial liquid container, and between the inner and outer Wall surfaces of the surrounding liquid container, respectively, lids attached at both ends of the said central pres-sure gas container, lids common to the said coaxial liquid containers attached at both ends of the latter and anchored to the said central pressure gas container, and ducting means putting the said pressure gas container in controllable communication with the said liquid containers.
  • a central fiangeless tubular pressure rates Patent 0 ice gas container screw-tapped at its end, lids slidably inserted from both sides into the said container, each lid having a shoulder at its inner end and a screw thread at its outer end, a screw-threaded ring screwed into the said screw tapped end, a packing ring having in the initial condition a parallelogram shape cross section and consisting of a soft metal, arranged between the said shoulder and the inner end face of the said screw threaded ring, the said lid being forced outwardly by gas pressure ap lied to the interior of the said pres-sure gas container and deforming the'said packing ring to a rectangular cross section between the said shoulder and the said screw-threaded ring.
  • Fig. 1 is a longitudinal section of the system of containers according to the invention, N
  • Fig. 2 is a transverse section along the line II--II of Fig. 1, partly broken away, and
  • Fig. 3 is a longitudinal section on a larger scale of a lid of the pressure gas container, the upper half of Fig. 3 representing the lid in the position after assembly, and the lower half of Fig. 3 representing the said lid in the sealed position under an operative gas pressure.
  • the central pressure gas container 1 contains for ex ample compressed air under a maximum pressure of about 300 kilograms per square centimetre. It consists of a flangeless tube and two lids 2, which are fixed by means of a screw-threaded ring 3 screwed into the tube and of an annular nut 4 screwed on to the threaded outer end of lid 2. v
  • the sealing is effected by a packingring 5 of rho'mbi'c or parallelogram cross section (see Fig. 3) of a soft metal, for example aluminium, which is inserted between the said screw-threaded ring 3 and a ring flange at the inner end of the lid 2.
  • the packing ring 5 retains its original cross section even after the screwing on of the threaded ring 3 and of the annular nut 4. Thereby a prelimi nary seal is attained.
  • the sealing proper is effected automatically when filling in the compressed air of 300 kilograms per square centimetre, which forces the two lids 2 outwardly into a position as shown in the lower half of Fig. 3.
  • the packing ring 5 is then deformed to a rectangular cross section and secures a faultless seal of the lid 2.
  • This arrangement permits a fiangeless construction of the pressure gas container, and the sealing is effected automatically, while for the preliminary sealing the application of a low force sut'fices when screwing on the annular nut 4.
  • the pressure gas container 1 is filled with pressure gas of at least 300 kg./cm. for a trial, before assembling the exterior acid containers 6 and 7. Thereby the two lids 2 move'to a position as indicated in the lower part of Fig. 3. Thereupon ring 4 is again screwed tight and then the assembly of the exterior acid containers 6 and 7, arranged coaxially to the pressure gas container 1, can be accomplished.
  • These are made of corrosion-resisting material and consist of flangeless tubes, which are closed at both ends by a lid 8 on each side which is common to both of them.
  • the inner container 6 contains the fuel, for example activated kerosene, whereas "the outer container 7 contains the oxygen carrier, for example nitric acid.
  • Two clamp rings 9 and 10 are fastened by screws 22 to the lid 8, with appropriate packings 11, secure the sealing of the two containers.
  • the annular nuts 3 and 4 are provided with bores 23 and 24 into which special keys can be inserted for screwing the nuts tightly onto the tube 1 and the lids 2.
  • the two lids 8 are anchored on the lids 2 of the pressure gas container by means of annular nuts 2, which are screwed on the same thread as the aforesaid annular nut 4.
  • Two collars 12 are riveted or screwed into the ends of outer container 7 to secure the acid container 7 against being shifted relative to the lids 8.
  • annular freepistons 13 and 14 with suitable packings 15, are built, which are slidable over the whole length of the container.
  • the pressure gas container 1 is in communication with the two containers 6 and 7 through a pressure regulator 16 of the usual type and the two pressure pipes 17 and 18, respectively.
  • a pressure regulator 16 of the usual type and the two pressure pipes 17 and 18, respectively.
  • liquid discharge sockets 19 and 20 are arranged which are connected with the fuel pipes to the combustion chamber (not shown).
  • the manner of operation of the device is as follows: With the liquid containers 6 and 7 completely filled, the two free-pistons 13, 14 are in the initial position as shown in Fig. 1.
  • the supply of the compressed air to the pressure regulator 16 is released by suitable valve means (not shown).
  • the said pressure regulator reduces the air pressure from for example 300 kilograms per square centimetre, at the beginning of the supply, to the supply pressure of for example 40 kilograms per square centimetre, and passes the compressed air through the two pressure pipes 17, 18 into the liquid containers 6, 7, where it drives the two free-pistons 13, 14 towards the right hand side in Fig. 1, and thereby forces the contents of the containers through the liquid discharge sockets 19, 20 into the fuel pipes towards the combustion chamber.
  • the pressure regulator 16 keeps the feed pressure of for example 40 kilograms per square centimeter, and accordingly maintains a contant output effect of the free-pistons 13, 14, in spite of the diminishing primary pressure in the pressure gas container 1.
  • a system of containers for at least two liquids and one pressure gas comprising in combination a central flangeless tube threaded internally at each end, two lids slidably inserted one from each end of said tube to form a pressure gas chamber with said tube, each lid having a shoulder at its inner end and a screw thread at its outer end, a screw-threaded ring screwed into each of the said threaded ends of the tube, a packing ring having in the initial condition a parallelogram shape cross section and consisting of a soft metal, arranged between the said shoulder and the inner end face of the said screw threaded ring on each lid, the said lids being forced outwardly by gas pressure applied to the interior of the said pressure gas container and deforming the said packing rings to a rectangular cross section between the said shoulder and the said screw-threaded ring, at least two cylindrical liquid containers coaxially surrounding the said pressure gas container and one another, annular free-pistons arranged between the outer wall surface of the said central pressure gas container and the inner wall surface of'the

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)
US412840A 1953-02-28 1954-02-26 System of containers for at least two liquids and a pressure gas Expired - Lifetime US2818914A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH747286X 1953-02-28

Publications (1)

Publication Number Publication Date
US2818914A true US2818914A (en) 1958-01-07

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ID=4533593

Family Applications (1)

Application Number Title Priority Date Filing Date
US412840A Expired - Lifetime US2818914A (en) 1953-02-28 1954-02-26 System of containers for at least two liquids and a pressure gas

Country Status (6)

Country Link
US (1) US2818914A (enFirst)
BE (1) BE526507A (enFirst)
CH (1) CH312590A (enFirst)
FR (1) FR1100118A (enFirst)
GB (1) GB747286A (enFirst)
NL (2) NL185090B (enFirst)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2975746A (en) * 1957-12-23 1961-03-21 Thompson Ramo Wooldridge Inc Propulsion system
US3077077A (en) * 1959-07-01 1963-02-12 Honeywell Regulator Co Solid propellant pressurizing device
US3112611A (en) * 1958-07-21 1963-12-03 Gen Electric Rocket motor employing a plug type nozzle
US3138929A (en) * 1961-02-16 1964-06-30 Thompson Ramo Wooldridge Inc Multiple stage expulsion piston
US3908933A (en) * 1956-06-26 1975-09-30 Us Navy Guided missile
US4766934A (en) * 1986-08-14 1988-08-30 Alsthom Closure head for a hydraulic tube-testing bench

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2918791A (en) * 1956-08-20 1959-12-29 Experiment Inc Differential area piston pumping system
US2865468A (en) * 1957-03-08 1958-12-23 Mckiernan Terry Corp Pressure fluid operated injector for lubrication and other purposes
US4366919A (en) 1978-05-01 1983-01-04 Coaxial Cartridges, Inc. Composite cartridge and device for metering extrusion of contents
US5301842A (en) * 1991-03-06 1994-04-12 Frank Ritter Multicomponent cartridge for plastic materials
EP3690224B1 (en) 2017-01-13 2025-03-05 Orbital Express Launch Limited Rocket propellant tank arrangement, rocket propulsion unit, and rocket
GB2626317A (en) * 2023-01-16 2024-07-24 Skyrora Ltd Propellant tank arrangement for a launch vehicle

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1560016A (en) * 1923-05-15 1925-11-03 Joseph Goodfellow Combined fire pot and brazing torch
US1623101A (en) * 1926-03-17 1927-04-05 Fisher Oliver Wendell Lubricant pump

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1560016A (en) * 1923-05-15 1925-11-03 Joseph Goodfellow Combined fire pot and brazing torch
US1623101A (en) * 1926-03-17 1927-04-05 Fisher Oliver Wendell Lubricant pump

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3908933A (en) * 1956-06-26 1975-09-30 Us Navy Guided missile
US2975746A (en) * 1957-12-23 1961-03-21 Thompson Ramo Wooldridge Inc Propulsion system
US3112611A (en) * 1958-07-21 1963-12-03 Gen Electric Rocket motor employing a plug type nozzle
US3077077A (en) * 1959-07-01 1963-02-12 Honeywell Regulator Co Solid propellant pressurizing device
US3138929A (en) * 1961-02-16 1964-06-30 Thompson Ramo Wooldridge Inc Multiple stage expulsion piston
US4766934A (en) * 1986-08-14 1988-08-30 Alsthom Closure head for a hydraulic tube-testing bench

Also Published As

Publication number Publication date
FR1100118A (fr) 1955-09-16
NL185090B (nl)
CH312590A (de) 1956-01-31
BE526507A (enFirst) 1900-01-01
NL87924C (enFirst) 1900-01-01
GB747286A (en) 1956-03-28

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