US2693077A - Reaction motor operable by liquid propellants and method of operating it - Google Patents

Reaction motor operable by liquid propellants and method of operating it Download PDF

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US2693077A
US2693077A US182742A US18274250A US2693077A US 2693077 A US2693077 A US 2693077A US 182742 A US182742 A US 182742A US 18274250 A US18274250 A US 18274250A US 2693077 A US2693077 A US 2693077A
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propellants
combustion
nitric acid
operating
fuels
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US182742A
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Frank J Malina
John W Parsons
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Aerojet Rocketdyne Inc
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Aerojet General Corp
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Priority to GB14873/44A priority Critical patent/GB650444A/en
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Priority to US342564A priority patent/US2771739A/en
Priority to US412196A priority patent/US2774214A/en
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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
    • 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
    • F02K9/425—Propellants
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B27/00—Compositions containing a metal, boron, silicon, selenium or tellurium or mixtures, intercompounds or hydrides thereof, and hydrocarbons or halogenated hydrocarbons
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B39/00—Compositions containing free phosphorus or a binary compound of phosphorus, except with oxygen
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B43/00—Compositions characterised by explosive or thermic constituents not provided for in groups C06B25/00 - C06B41/00
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B47/00—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
    • C06B47/02—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
    • C06B47/04—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant a component containing a nitrogen oxide or acid thereof
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B47/00—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
    • C06B47/02—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
    • C06B47/08—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant a component containing hydrazine or a hydrazine derivative

Definitions

  • Our invention relates to jet propulsion and more particularly to propellants which are useful in connection therewith.
  • the present invention relates to fuels, and oxidizers and their combination as propellants and their method of injection into a jet motor.
  • the objects of our invention are: to provide more efficient and eifective propellants for jet propulsion systems; to provide an oxidizing agent which is easily combustible with a suitable fuel and which has a large amount of oxygen available for burning a fuel; to provide propellants, that is, fuels and oxidizers, which are spontaneously combustible; to provide a method for utilizing such propellants to give smooth combustion and to eliminate danger of explosion; to obviate the difficulties attendant upon the use of liquified gases; to eliminate the need of an auxiliary ignition system to ignite the propellants.
  • nitric acid As a result of a thorough investigation of the various oxidizing agents which may be used as propellants we prefer to employ nitric acid. Since water tends to retard combustion of the acid with any fuel, the nitric acid should be substantially free of water. Thus, white fuming 'nitric acid, which normally contains less than about 2% of water by weight, is to be preferred to weaker solutions of nitric acid. However, we have found that more dilute solutions of nitric acid may be utilized provided that nitrogen dioxide is dissolved in the nitric acid; which is a way of increasing the concentration of an otherwise more dilute solution. Preferably the nitric acid should contain at least about 5% N02 but preferably at least about 15 to 20% N02.
  • red fuming nitric acid Such a solution of nitrogen dioxide is known as red fuming nitric acid and almost all red fuming nitric acid which is commercially available in this country contains between about 5% and 20% nitrogen dioxide by weight and less than about 5% water by weight.
  • nitric acid obtainable commercially as white fuming nitric acid, are as follows:
  • white fuming nitric acid as used herein means a nitric acid containing a maximum of about 2% water by weight.
  • red fuming nitric acid as used herein means a nitric acid containing at least about 5% N02 and a maximum of about 5% water, by weight.
  • Nitric acid of all types containing at least 80% HNOs is useful as an oxidizer.
  • liquid nitrogen dioxide is a very satisfactory oxidizer.
  • nitric acid and preferably red fuming nitric acid, substantially free of water, as an oxidizer.
  • Group I.Liquid organic compounds containing at least one amine radical such as,
  • Group II.Highly unsaturated hydrocarbons L1qu1d hydrocarbons of the acetylene type and containing a large fraction of unsaturated (double and triple) carbon bonds, or both, for example, divinyl acetylene, d1propargyl, and propargyl alcohol.
  • Li lithium
  • Be beryllium
  • B boron
  • Al aluminum
  • Mg magnesium
  • P phosphorus
  • K potassium
  • Na sodium
  • oxidizers and fuels may be used together'as' pairs of spontaneously combustible propellants at atmospheric temperature and pressure. However, if desired these oxidizers and fuels" may be used with other fuels (such as gasoline) or other oxidizers (such as liquid oxygen respectively.
  • the propellants may be injected at a greater rate than they are injected initially inasmuch as the time interval between their inection and combustion is reduced because of the higher temperature and pressure of the mixture resulting from prior combustion and the heating of the walls of the combustion chamber by the products of combustion.
  • FIG. 1 shows a jet motor system including tanks and conduits for supplying propellants to the motor.
  • the fuels and oxidizers hereinbefore described are advantageously employed in the propulsion of an aircraft by providing the fuel and oxidizer in separate containers 1'1 and 12 respectively connected in any suitable manner as by pipes 13 and 14 to a jet or combustion chamber. Throttle valves 16 and 17 energized by electrical circuits 18' and 19 are provided in said pipes to control the rates of supply of the fuel and oxidizer respectively to the combustion chamber 15.
  • a receptacle 20 is connected by a conduit 21 having a pressure regulator 22 therein to the receptacles 11 and 12 and is provided with a gas under pressure, preferably a gas inert with respect to either propellant.
  • the container for the fuel and the container for the oxidizer are connected to a source of pressure adapted to force the contents of such containers into the jet or combustion chamber at controlled rates determined by the degree of opening of the valves in said ipes.
  • propellants are supplied atsuch. initial rates, then, when the. propellants are initially injected into the jet motor, the initially burned propellants soon till the combustion chamber with high temperature gases and vapors which heat the incoming propellants thereby vaporizing them and reducing the ignition time lag. Then the subsequently injected propellant-sburnspontaneously without any substantial accumulation of propellants in the liquid phase.
  • the method of developing thrust which comprises ejecting from a reaction chamber the gaseous products; produced by the spontaneous combustion of a compound selected from the group consisting of hydrazine and carbon disulphide containing. phosphorus, and acid selected from the group consisting of red fuming nitric acid and white fuming nitric acid.
  • the method of developing thrust comprisesejecting from a reaction chamber the gaseous products produced by the spontaneous combustion of hydrazine.

Description

Nov. 2, 1954 F. J. MALINA ETAL REACTION MOTOR OPERABLE BY LIQUID PROPELLANTS AND METHOD OF OPERATING IT Original Filed May 8, 1943 INERT GAS JOHN PARSONS FRANK J MAL/NA INVENTOR.
w MW ATTOR E Y Z,693,?7 Patented Nov. 2, 1954 REACTION MOTOR OPERABLE BY LIQUID PRO- PELLANTS AND METHOD OF OPERATING IT Frank J. Malina and John W. Parsons, Pasadena, Calif., assignors, by mesne assignments, to Aerojet-General Corporation, Azusa, Calif, a corporation of Ohio Original application May 8, 1943, Serial No. 486,236, now
Patent No. 2,573,471, dated October 30, 1951. Divided and this application September 1, 1950, Serial No. 182,742
2 Claims. (Cl. 60-35.4)
Our invention relates to jet propulsion and more particularly to propellants which are useful in connection therewith.
This is a division of my copending application Serial No. 486,236, filed May 8, 1943, now U. S. Patent 2,573,471.
While our invention is capable of use in connection with the propulsion of a wide variety of different devices and vehicles, since it finds particular utility in the propulsion of aircraft, its advantages are described with relation to such use, it being understood that our invention is, however, not limited to such use.
Prior to our invention special means were always required to ignite the propellants. For example, when liquid oxygen is used as an oxidizer and gasoline is used as a fuel, some auxiliary ignition means must always be provided to initiate combustion of the propellants. This is objectionable because it requires either a spark plug or other ignitor or means for heating the walls of the combustion chamber above the ignition point of the propellant mixture making this system complex and dependent upon the operation of such ignition system.
While spontaneous combustion is obtained with our preferred combinations of propellants which is especially effective when operating in accordance with our preferred method it will be understood that the propellants we have discovered offer advantages even when operating under other conditions.
The present invention relates to fuels, and oxidizers and their combination as propellants and their method of injection into a jet motor. Among the objects of our invention are: to provide more efficient and eifective propellants for jet propulsion systems; to provide an oxidizing agent which is easily combustible with a suitable fuel and which has a large amount of oxygen available for burning a fuel; to provide propellants, that is, fuels and oxidizers, which are spontaneously combustible; to provide a method for utilizing such propellants to give smooth combustion and to eliminate danger of explosion; to obviate the difficulties attendant upon the use of liquified gases; to eliminate the need of an auxiliary ignition system to ignite the propellants.
Oxidizers As a result of a thorough investigation of the various oxidizing agents which may be used as propellants we prefer to employ nitric acid. Since water tends to retard combustion of the acid with any fuel, the nitric acid should be substantially free of water. Thus, white fuming 'nitric acid, which normally contains less than about 2% of water by weight, is to be preferred to weaker solutions of nitric acid. However, we have found that more dilute solutions of nitric acid may be utilized provided that nitrogen dioxide is dissolved in the nitric acid; which is a way of increasing the concentration of an otherwise more dilute solution. Preferably the nitric acid should contain at least about 5% N02 but preferably at least about 15 to 20% N02. Such a solution of nitrogen dioxide is known as red fuming nitric acid and almost all red fuming nitric acid which is commercially available in this country contains between about 5% and 20% nitrogen dioxide by weight and less than about 5% water by weight. Specifications for nitric acid, obtainable commercially as red fuming nitric acid, are as follows:
Chemical composition:
HNOs 90.5% by wt. min. Water 2.5% by wt. max. N02 7.25% by wt. max.6.50%
by wt. min. Physical properties:
Density 1.5 min.-l.55 max. 70
Melting point -50 F. max.
Color, etc Orange to dark redfumes vigorously when exposed to air.
Specifications for nitric acid, obtainable commercially as white fuming nitric acid, are as follows:
Melting point -45 F. Color, etc Straw yellow to water white; fumes vigorously when exposed to air.
The term white fuming nitric acid as used herein means a nitric acid containing a maximum of about 2% water by weight.
The term red fuming nitric acid as used herein means a nitric acid containing at least about 5% N02 and a maximum of about 5% water, by weight.
Nitric acid of all types containing at least 80% HNOs is useful as an oxidizer. We have also found that liquid nitrogen dioxide is a very satisfactory oxidizer.
To eliminate the requirement for providing the jet motor with special igniting means, we employ nitric acid, and preferably red fuming nitric acid, substantially free of water, as an oxidizer.
Fuels We have discovered a family of fuels which are spontaneously combustible with the oxidizing agents hereinabove mentioned and which are satisfactory for et pro pulsion provided that the propellants are supplied to the combustion chamber under suitable operating conditions. These operating conditions are discussed more in detail hereinbelow.
We have found that the four groups of compounds listed below may be utilized as fuels. These groups are listed in the order of their effectiveness.
Group I.Liquid organic compounds containing at least one amine radical, such as,
A. Aniline, orthotoluidine, and methylamine.
B. Liquid hydrocarbons, containing large percentages of such amine substituted organic compounds.
Group II.Highly unsaturated hydrocarbons: L1qu1d hydrocarbons of the acetylene type and containing a large fraction of unsaturated (double and triple) carbon bonds, or both, for example, divinyl acetylene, d1propargyl, and propargyl alcohol.
Group III .Liquid substances containing the elements having the properties of lithium (Li), beryllium (Be), boron (B), aluminum (Al), magnesium (Mg), phosphorus (P), potassium (K), and sodium (Na). With the exception of phosphorus all of the foregoing elements are particularly useful in fuels because they generate large amounts of heat during combustion, and phosphorus is particularly useful because it has a low ignition temperature.
A. Liquid hydrides of those elements.
B. Liquid organo-metallic compounds containing one or more of such elements.
0 Liquid fuels containing one or more such elements.
D. Liquid fuels containing one or more such elements in suspension.
3 fGroup I V.-Organic compounds having the properties Pyrole Pyridine Pinene Terpene Pinole Terpinola Hydrazine Ozonides Carbon disulphide containing phosphorus.
sow w Method of operation The above mentioned oxidizers and fuels may be used together'as' pairs of spontaneously combustible propellants at atmospheric temperature and pressure. However, if desired these oxidizers and fuels" may be used with other fuels (such as gasoline) or other oxidizers (such as liquid oxygen respectively.
So far as we know we are the first to achieve spontaneous combustion in jet propulsion systems at the temperature and pressure of the medium surrounding the jet motor and while other fuels and oxidizers might be utilized to accomplish such spontaneous combustion we prefer to use the fuels and oxidizers hereinbefore mentioned.
Certain difliculties are encountered when utilizing these propellants for propulsion Unless the propellants are. supplied to the. jet motor under the proper conditions the motor is liable to fail completely, topulsate in its operation, or to explode, even though the propellants are supplied at uniform rates.
These difliculties may be eliminated and certainly smoothness of operation secured by so relating the rates of injection of fuel and oxidizer to the size of the jet chamber and the inherent ignition properties of the mixture that explosion of the combustible mixture is avoided during the initial combustion, and subsequent injection occurs at rates conducive to the combustion of the continuously supplied propellants so as to avoid the accumulation in the jet chamber of any substantial amount of the unburned propellants. To achieve this result, we initially inject propellants into the combustion chamber at rates such that the amount of propellants injected prior to the initiation of combustion is. less than about 20% of the volume of the combustion chamber.
After combustion has been initiated, the propellants may be injected at a greater rate than they are injected initially inasmuch as the time interval between their inection and combustion is reduced because of the higher temperature and pressure of the mixture resulting from prior combustion and the heating of the walls of the combustion chamber by the products of combustion.
In the drawing the figure shows a jet motor system including tanks and conduits for supplying propellants to the motor.
The fuels and oxidizers hereinbefore described are advantageously employed in the propulsion of an aircraft by providing the fuel and oxidizer in separate containers 1'1 and 12 respectively connected in any suitable manner as by pipes 13 and 14 to a jet or combustion chamber. Throttle valves 16 and 17 energized by electrical circuits 18' and 19 are provided in said pipes to control the rates of supply of the fuel and oxidizer respectively to the combustion chamber 15. A receptacle 20 is connected by a conduit 21 having a pressure regulator 22 therein to the receptacles 11 and 12 and is provided with a gas under pressure, preferably a gas inert with respect to either propellant. Preferably the container for the fuel and the container for the oxidizer are connected to a source of pressure adapted to force the contents of such containers into the jet or combustion chamber at controlled rates determined by the degree of opening of the valves in said ipes.
P The practice. of the method of our invention contemplates so relating the rates of injection of the oxidizer and of the fuel to the combustion or jet chamber to their inherent combustion properties and the size and temperature of the chamber that smooth non-explosive combustion occurs initially and throughout the entire operation while providing the desired quantity of propulsive power. Our invention is particularly advantageous when the combustion chamber is initially at atmospheric temperature, or at the temperature of any other medium in which the motor is to operate, as weare able to achieve combustion initially without auxiliary ignition or preheating of the chamber or the propellants.
If. the propellants are supplied atsuch. initial rates, then, when the. propellants are initially injected into the jet motor, the initially burned propellants soon till the combustion chamber with high temperature gases and vapors which heat the incoming propellants thereby vaporizing them and reducing the ignition time lag. Then the subsequently injected propellant-sburnspontaneously without any substantial accumulation of propellants in the liquid phase.
As an example, applied-1 to a combustion chamber having. a length of aboutv 10': inches. and a cross sectional area of about 7 square inches, highly concentrated nitric acid and aniline. operate very satisfactorily when they are injected intothe combustion chamber initially and prior to combustion at the rates of 3.6 lbs. per second and 2.4 lbs. per second respectively.
While these propellants and method of use and the apparatus for their use in propelling aircraft or other de vices,. which are hereinbefore described, are fully capable. of providing. the advantages primarily stated, it will be. recognized by those skilled in the. art that various IllOdlfi cations and alterations may be made therein while still. providing such advantages, and our invention is therefore to be understood as not limited tothe specific embodiments hereinbefore described but as including all m0difi-- cations and variations thereof coming within the scope of the claims which follow- We claim as our invention:
1. The method of developing thrust which comprises ejecting from a reaction chamber the gaseous products; produced by the spontaneous combustion of a compound selected from the group consisting of hydrazine and carbon disulphide containing. phosphorus, and acid selected from the group consisting of red fuming nitric acid and white fuming nitric acid.
2. The method of developing thrust which comprisesejecting from a reaction chamber the gaseous products produced by the spontaneous combustion of hydrazine.
and acid from: the group consisting, of red fuming nitric acid and white fuming nitric: acid.
References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 2,573,471 Malina et a1. Oct. 30, 1951 FOREIGN PATENTS Number Country Date 405,645 Great Britain Jan. 29, 1934 576,227 Great Britain Dec.. 3, 1937 OTHER. REFERENCES Mellor: A Comprehensive Treatise on Inorganic and Theoretical Chemistry, vol. VIII, page 313. Pub. 1928 by Longrnans, Green & Co., New York and London. Copy in Division 59.

Claims (1)

1. THE METHOD OF DEVELOPING THRUST WHICH COMPRISES EJECTING FROM A REACTION CHAMBER THE GASEOUS PRODUCTS PRODUCED BY THE SPONTANEOUS COMBUSTION OF A COMPOUND SELECTED FROM THE GROUP CONSISTING OF HYDRAZINE AND CARBON DISULPHIDE CONTAINING PHOSPHORUS, AND ACID SELECTED
US182742A 1943-05-08 1950-09-01 Reaction motor operable by liquid propellants and method of operating it Expired - Lifetime US2693077A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB14873/44A GB650444A (en) 1943-05-08 1944-08-03 Improvements in or relating to a method of producing hot gases for the purpose of jet propulsion
US182742A US2693077A (en) 1943-05-08 1950-09-01 Reaction motor operable by liquid propellants and method of operating it
US342564A US2771739A (en) 1943-05-08 1953-02-03 Rocket propulsion method
US412196A US2774214A (en) 1943-05-08 1954-02-08 Rocket propulsion method

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US486236A US2573471A (en) 1943-05-08 1943-05-08 Reaction motor operable by liquid propellants and method of operating it
US182742A US2693077A (en) 1943-05-08 1950-09-01 Reaction motor operable by liquid propellants and method of operating it

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2941005A (en) * 1955-07-29 1960-06-14 Phillips Petroleum Co 1, 2-diamino-1-alkene compounds
US3117415A (en) * 1959-04-02 1964-01-14 North American Aviation Inc Propellant and rocket propulsion method
US20050076560A1 (en) * 2001-08-27 2005-04-14 Wiley David B. Alkynylsilanes as fuels and rocket propellants
US7083690B2 (en) 2001-07-03 2006-08-01 Wiley Organics, Inc. Catalyst system for rendering organic propellants hypergolic with hydrogen peroxide
US8894782B2 (en) 2002-09-03 2014-11-25 Wiley Organics, Inc. Hypergolic hydrocarbon fuels

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB405645A (en) * 1932-07-29 1934-01-29 David Hodge Improvements in and relating to cartridges for blasting, also applicable to the discharge of projectiles from guns
GB576227A (en) * 1943-12-07 1946-03-25 George Frederick French Improvements in cycle stands
US2573471A (en) * 1943-05-08 1951-10-30 Aerojet Engineering Corp Reaction motor operable by liquid propellants and method of operating it

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB405645A (en) * 1932-07-29 1934-01-29 David Hodge Improvements in and relating to cartridges for blasting, also applicable to the discharge of projectiles from guns
US2573471A (en) * 1943-05-08 1951-10-30 Aerojet Engineering Corp Reaction motor operable by liquid propellants and method of operating it
GB576227A (en) * 1943-12-07 1946-03-25 George Frederick French Improvements in cycle stands

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2941005A (en) * 1955-07-29 1960-06-14 Phillips Petroleum Co 1, 2-diamino-1-alkene compounds
US3117415A (en) * 1959-04-02 1964-01-14 North American Aviation Inc Propellant and rocket propulsion method
US7083690B2 (en) 2001-07-03 2006-08-01 Wiley Organics, Inc. Catalyst system for rendering organic propellants hypergolic with hydrogen peroxide
US20050076560A1 (en) * 2001-08-27 2005-04-14 Wiley David B. Alkynylsilanes as fuels and rocket propellants
US8894782B2 (en) 2002-09-03 2014-11-25 Wiley Organics, Inc. Hypergolic hydrocarbon fuels

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