US3121992A - Decomposition of nitroparaffins in jet propulsion motor operation - Google Patents

Decomposition of nitroparaffins in jet propulsion motor operation Download PDF

Info

Publication number
US3121992A
US3121992A US163946A US16394661A US3121992A US 3121992 A US3121992 A US 3121992A US 163946 A US163946 A US 163946A US 16394661 A US16394661 A US 16394661A US 3121992 A US3121992 A US 3121992A
Authority
US
United States
Prior art keywords
motor
catalyst
nitroparaffins
decomposition
nitromethane
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
US163946A
Inventor
Zwicky Fritz
Frederick J Ewing
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.)
Aerojet Rocketdyne Inc
Original Assignee
Aerojet Engineering Corp
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
Priority claimed from US528893A external-priority patent/US3048007A/en
Application filed by Aerojet Engineering Corp filed Critical Aerojet Engineering Corp
Priority to US163946A priority Critical patent/US3121992A/en
Application granted granted Critical
Publication of US3121992A publication Critical patent/US3121992A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/68—Decomposition chambers

Definitions

  • Such catalytic surfaces usually in the form of liners, sometimes tend to be brittle or friable and may require frequent replacement.
  • a catalyst may be added continuously to the motor during operation, thus insuring the constant presence of a sufiicient amount of catalyst to cause satisfactory auto-combustion of fuel.
  • the catalyst may be carried out by injecting the catalyst into the motor in the form of a colloidal suspension in a fuel.
  • the finely divided catalyst may be mixed with ethyl alcohol or some similar non-detonating fuel, and injected into the motor through a small slush injector so as to intersect a spray of the fuel which is being injected into the motor.
  • An alternative way of carrying out the invention is to inject the catalyst into the motor in the form of a fluid or of a solution which will break down in the combustion chamber to give one or more catalytic substances.
  • FIG. 1 shows a jet thrust motor in cross section along its longitudinal axis
  • FIG. 2 is an enlarged part view in cross section of the injector end of the motor shown in FIG. 1;
  • FIG. 3 is a part view in cross section of a motor having another type of injector.
  • FIG. 1 we show a jet motor which consists of a tubular combustion chamber 1 suitably threaded on both ends, having in its right hand end an exhaust nozzle 2 threadedly secured, which contains an opening 3 converging to a constricted portion 4 and diverging outwardly forming an exhaust opening 5.
  • a spark plug 6 is inserted into its wall.
  • a plug-shaped member 7 is threadedly secured.
  • Member 7 contains in its center portion an injector plug 8 secured by lock nut 11.
  • the plug 8 has a flared tube connection 56 in its outside end and a concentric hole 9 terminating in an injection nozzle 1i). Injector plug 8 is made leakproo'f by an inserted O ring 12.
  • annular groove 13 Beginning at groove 13 a helical groove 14 is provided around the injector plug and this helical groove terminates in a frusto conical end 15. End 15 is machined to form an annular frusto conical space 16 in the recess 17 of the member 7.
  • Recess 17 has a concentric orifice '18 which permits a spray of fluid from concentric hole 9 flared tube connection '25 is screwed into member '7 in which another blind hole 26 is provided.
  • a smaller angular orifice 27 passes through member 7 from the end of orifice 26. Orifice 27 is so positioned that a fluid stream issuing from it intercepts the stream from injector 3.
  • the liquid fuel such as nitromethane or a mixture of nitromethane and nitroethane
  • a colloidal suspension of catalyst in a non-detonating fuel is injected, through tube 31, flared tube connection Zih holes 21 and 2-2 into groove 13 of injector plug 8 and through helix l4 and frusto conical space 16 into the combustion chamber 1.
  • Catalysts which may be conveniently used comprise iron oxide, chromium oxide, chromium hydroxide, cerium oxide, or mixtures thereof, or other metal oxides colloidally suspended in the nondetonating fuel which may, for example, be an alcohol. It is understood that this invention is not limited to the compounds listed above, but may be also used with other metal oxides catalytically active in the decomposition of suitable self-combustible fuels.
  • oxygen or some other suitable oxidizing agent is injected through tube 32, flared tube connection 25, hole 26 and angular orifice 27 impinging upon the spray of nitromethane and the colloidal suspension of catalyst in a non-detonating fuel respectively as described above.
  • the combined stream or spray is ignited by spark plug 6.
  • injection of the oxidizer may be discontinued.
  • the catalyst may be mixed with this fuel just before injection or may even be stored as a colloidal suspension in this fuel. When this is done care must be taken to guard against explosion.
  • FIG. 3 is a cutaway view of a jet motor showing the injector end.
  • Such an injector may be used instead of the plug 7 of FIG. 2.
  • a catalyst in the form of a fluid which is in itself catalytic or which will breakdown in the motor to provide one or more types of catalytic materials. This avoids the use of a suspension of a solid material and of an injector thereof, and consequently there is no danger of a buildup of solid particles in the orifices and injector with consequent stoppage of the motor. Instead the catalyst 18 injected into the motor as a clear fluid.
  • FIG. 3 part of cylindrical jet motor 1 is shown containing a spark plug 6 in its upper portion and in its lower portion an injector 30 consisting of a pipe plug 32 having a flare tube connection 31 at its outer end.
  • a nozzle 33 is provided in the wall of the motor 1 in line with the injector Stl. This injector is set in such a way that any stream injected therethrough meets a counterstream injected through an injector 25 through plugshaped member 34.
  • Injector plug 35 screws into member 34 and is locked with nut 45, and has a flared tube connection in its outside end.
  • a concentric hole 36 passes through plug 35 and terminates in a hole 37 which is drilled normal to hole 36 in the cylindrical end of the injector.
  • a groove 33 is machined around the surface of member 35 concentric with hole 37.
  • a helical groove 39 around member 35 extends from groove 37 and terminates at the frusto conical cap 40.
  • Cap 40 and the conical recess 41 and orifice 43 contained in member 34 form a frusto conical space 42 through which a single propellant may be injected into the combustion chamber 1.
  • nitroparaflin fuel is injected into the motor through tube 46, injector plug 35, and hole 43. Simultaneously through injector 30 and nozzle 33 a fluid is injected in opposition to the stream of nitroparaflin fuel, which will act as a catalyst either of itself or after reaction in the motor.
  • a fluid is injected in opposition to the stream of nitroparaflin fuel, which will act as a catalyst either of itself or after reaction in the motor.
  • Initiation of combustion may be accomplished by the injection of oxygen or any other suitable oxidizing agent through tube 47, injector plug 25, hole 26, and angular orifice 27 impinging upon the stream of nitroparafiin fuel and the stream of the catalyst.
  • the combined streams are ignited by spark plug 6.
  • Fluids suitable for catalysts may be liquid compounds, liquid solutions, gaseous compounds or gaseous mixtures.
  • liquid compounds may comprise CrO C1 M11207, or Fe(CO) Liquid solutions will include solutions of Ce(NO in methanol or Ca(MnO in water.
  • gases may include Ni(CO) vapor or a mixture of Ni(CO) vapor with oxygen. All of these are fluids and may be easily broken down in the combustion chamber to give products which are catalytically active in the decomposition of suitable self-combustible fuels.
  • This solution may be continuously injected into the motor at a rate normally only a few percent of that of the propellant.
  • the injection is best made in the form of a fine spray in order to obtain maximum catalyst surface.
  • the first thing that occurs in the motor is the evaporation of the spray, yielding water vapor, methyl alcohol vapor, and Ce(NO in the form of fine particles.
  • the CeO is a very active solid catalyst for the decomposition of nitroparaffins, acting by heterogeneous catalysis, while both the O and the N0 increase the rate of decomposition and flame speed of nitroparaflins, acting by homogeneous catalysis. Furthermore, the O and N0 help make up an oxygen deficiency in the nitroparaflins, thus increasing the available enthalpy and specific impulse.
  • the solid CeO particles will in part be ejected through the nozzle and in part adhere to the wall of'the motor, where their catalytic activity will be continued.
  • the fluid catalyst may be injected separately or in solution in the self-combustible propellant. If used in the combustible propellant suitable precautions must be taken to prevent overheating of the catalystcontaining propellant, in order to avoid explosion.
  • the method of operating a jet motor utilizing a self-combustible fuel selected from the nitroparaflins which comprises continuously injecting into the combustion chamber of the motor during operation a fluid which will provide catalyst for the decomposition of the nitroparaflins, said fluid being selected from the group consisting of CrO Cl Mn O Fe(CO) solutions of Ce(NO in methanol and Ca(MnO in water, and Ni(CO) vapor, said nitroparaflins being selected from the group consisting of nitromethane and mixtures of nitromethane and nitroethane, and igniting the said nitroparaflins in the chamber thereby producing gases under pressure which are ejected out the exhaust nozzle.
  • the method of operating a jet motor utilizing a selfcombustible fuel selected from the nitroparaflins which comprises continuously injecting into the combustion chamber of the motor during operation nitroparaflins containing a fluid which on heating will provide catalyst for the decomposition of the nitroparatlins said fluid being selected from the group consisting of CrO Cl Mn O Fe(CO) solutions of Ce(NO in methanol and Ca(.MnO in water, and Ni(CO) vapor and said nitroparaflin being selected from the group consisting of nitromethane and mixtures of nitromethane and nitroethane, and igniting the said nitroparaifins in the chamber thereby producing gases under pressure which are ejected out the exhaust nozzle.
  • the method of operating a jet motor having a combustion chamber and an exhaust nozzle from the chamber which comprises injecting into the combustion chamber nitromethane and a catalyst selected from the group consisting of CrO Cl Mn O Fe(CO) solutions of Ce(NO in methanol and Ca(MnO in water, and Ni(CO) vapor and igniting the nitromethane in the chamber, thereby producing gases under pressure which are ejected out the exhaust nozzle.
  • the process of decomposing nitromethane which comprises heating the nitromethane in the presence of a catalyst selected from the group consisting of CrO Cl M11207, Fe(CO) solutions of Ce(NO in methanol and Ca(MnO in water, and Ni(CO) vapor.
  • a catalyst selected from the group consisting of CrO Cl M11207, Fe(CO) solutions of Ce(NO in methanol and Ca(MnO in water, and Ni(CO) vapor.
  • the method of operating a jet motor having a com- 6 comprises heating the nitroparafiin selected from the group consisting of nitromethane and mixtures of nitromethane and nitroethane in the presence of a catalyst selected from the group consisting of CIO CI Mn O Fe(CO) solutions of Ce(N0 in methanol and Ca(MnO in Water, and Ni(CO) vapor.

Description

tates Patent l'fritz Zwiciry, Pasadena, and Frederick J. Ewing, Attadena, Caiii, assignors to Aerojet Engineering Corporation, Azusa, Califl, a corporation of Delaware Uriginal application Mar. 31, 1944-, Ser. No. $28,893:,now Eatent No. 33483997, dated Aug. '7, i962. Bivided and this application Nov. 21, 1961, Ser. No. 163,945
Claims. (Cl- 60-354) the copending application of Zwicky et a1, Serial No.
526,064, filed March 11, 1944, and now U.S. Patent No. 2,433,943, issued January 6, 1948, as a liquid fuel containing its own oxidizer. Decomposition of such a fuel may be accomplished by a catalyst within the motor, for example, a surface prepared from metal oxides.
Such catalytic surfaces, usually in the form of liners, sometimes tend to be brittle or friable and may require frequent replacement. According to our invention a catalyst may be added continuously to the motor during operation, thus insuring the constant presence of a sufiicient amount of catalyst to cause satisfactory auto-combustion of fuel.
'Our invention may be carried out by injecting the catalyst into the motor in the form of a colloidal suspension in a fuel. For example, the finely divided catalyst may be mixed with ethyl alcohol or some similar non-detonating fuel, and injected into the motor through a small slush injector so as to intersect a spray of the fuel which is being injected into the motor.
An alternative way of carrying out the invention is to inject the catalyst into the motor in the form of a fluid or of a solution which will break down in the combustion chamber to give one or more catalytic substances.
The invention will be better understood from the following detailed description and the accompanying drawing in which:
FIG. 1 shows a jet thrust motor in cross section along its longitudinal axis;
FIG. 2 is an enlarged part view in cross section of the injector end of the motor shown in FIG. 1; and
FIG. 3 is a part view in cross section of a motor having another type of injector.
Similar numerals refer to similar parts throughout the several views.
In FIG. 1 we show a jet motor which consists of a tubular combustion chamber 1 suitably threaded on both ends, having in its right hand end an exhaust nozzle 2 threadedly secured, which contains an opening 3 converging to a constricted portion 4 and diverging outwardly forming an exhaust opening 5. Near the opposite end of member 1 a spark plug 6 is inserted into its wall. In the opposite end of member 1 a plug-shaped member 7 is threadedly secured. Member 7 contains in its center portion an injector plug 8 secured by lock nut 11. The plug 8 has a flared tube connection 56 in its outside end and a concentric hole 9 terminating in an injection nozzle 1i). Injector plug 8 is made leakproo'f by an inserted O ring 12. There is provided an annular groove 13. Beginning at groove 13 a helical groove 14 is provided around the injector plug and this helical groove terminates in a frusto conical end 15. End 15 is machined to form an annular frusto conical space 16 in the recess 17 of the member 7. Recess 17 has a concentric orifice '18 which permits a spray of fluid from concentric hole 9 flared tube connection '25 is screwed into member '7 in which another blind hole 26 is provided. A smaller angular orifice 27 passes through member 7 from the end of orifice 26. Orifice 27 is so positioned that a fluid stream issuing from it intercepts the stream from injector 3.
In operation the liquid fuel, such as nitromethane or a mixture of nitromethane and nitroethane, is injected into the combustion chamber 1 through tube 30, hole 9 and nozzle 16 of the injector plug 8. Simultaneously, a colloidal suspension of catalyst in a non-detonating fuel is injected, through tube 31, flared tube connection Zih holes 21 and 2-2 into groove 13 of injector plug 8 and through helix l4 and frusto conical space 16 into the combustion chamber 1. Catalysts which may be conveniently used comprise iron oxide, chromium oxide, chromium hydroxide, cerium oxide, or mixtures thereof, or other metal oxides colloidally suspended in the nondetonating fuel which may, for example, be an alcohol. It is understood that this invention is not limited to the compounds listed above, but may be also used with other metal oxides catalytically active in the decomposition of suitable self-combustible fuels.
During initiation of operation, oxygen or some other suitable oxidizing agent is injected through tube 32, flared tube connection 25, hole 26 and angular orifice 27 impinging upon the spray of nitromethane and the colloidal suspension of catalyst in a non-detonating fuel respectively as described above. The combined stream or spray is ignited by spark plug 6. After the motor reaches a temperature sufiicient to permit continuous catalytic decomposition of the nitromethane or mixture of nitromethane and nitroethane, injection of the oxidizer may be discontinued.
When suitable precautions are taken to guard against overheating of the self-combustible fuel, the catalyst may be mixed with this fuel just before injection or may even be stored as a colloidal suspension in this fuel. When this is done care must be taken to guard against explosion.
FIG. 3 is a cutaway view of a jet motor showing the injector end. Such an injector may be used instead of the plug 7 of FIG. 2. With this there is utilized a catalyst in the form of a fluid which is in itself catalytic or which will breakdown in the motor to provide one or more types of catalytic materials. This avoids the use of a suspension of a solid material and of an injector thereof, and consequently there is no danger of a buildup of solid particles in the orifices and injector with consequent stoppage of the motor. Instead the catalyst 18 injected into the motor as a clear fluid.
In FIG. 3, part of cylindrical jet motor 1 is shown containing a spark plug 6 in its upper portion and in its lower portion an injector 30 consisting of a pipe plug 32 having a flare tube connection 31 at its outer end. A nozzle 33 is provided in the wall of the motor 1 in line with the injector Stl. This injector is set in such a way that any stream injected therethrough meets a counterstream injected through an injector 25 through plugshaped member 34. Injector plug 35 screws into member 34 and is locked with nut 45, and has a flared tube connection in its outside end. A concentric hole 36 passes through plug 35 and terminates in a hole 37 which is drilled normal to hole 36 in the cylindrical end of the injector. A groove 33 is machined around the surface of member 35 concentric with hole 37. A helical groove 39 around member 35 extends from groove 37 and terminates at the frusto conical cap 40. Cap 40 and the conical recess 41 and orifice 43 contained in member 34 form a frusto conical space 42 through which a single propellant may be injected into the combustion chamber 1.
In operation the nitroparaflin fuel is injected into the motor through tube 46, injector plug 35, and hole 43. Simultaneously through injector 30 and nozzle 33 a fluid is injected in opposition to the stream of nitroparaflin fuel, which will act as a catalyst either of itself or after reaction in the motor. The advantage of injecting the catalyst fluid through in an opposite direction to the main propellant stream is obvious, since breakdown of such catalyst fluid is necessary to obtain maximum catalytic activity. Such breakdown is brought about by the pickup of heat for evaporation and decomposition of the catalyst.
Initiation of combustion may be accomplished by the injection of oxygen or any other suitable oxidizing agent through tube 47, injector plug 25, hole 26, and angular orifice 27 impinging upon the stream of nitroparafiin fuel and the stream of the catalyst. The combined streams are ignited by spark plug 6.
Fluids suitable for catalysts may be liquid compounds, liquid solutions, gaseous compounds or gaseous mixtures. For example, liquid compounds may comprise CrO C1 M11207, or Fe(CO) Liquid solutions will include solutions of Ce(NO in methanol or Ca(MnO in water. Suitable gases may include Ni(CO) vapor or a mixture of Ni(CO) vapor with oxygen. All of these are fluids and may be easily broken down in the combustion chamber to give products which are catalytically active in the decomposition of suitable self-combustible fuels.
As an example of such a catalyst and of its behavior when injected into an operating jet thrust motor, consider the salt Ce(NO dissolved in methyl alcohol. The ordinary commercial form of Ce (N09 containing some Water of hydration, may be liquefied by methyl alcohol in the ratio of 5 grams of the salt to one cubic centimeter of alcohol. The viscosity may be further reduced, if desired, by the addition of more solvent.
This solution may be continuously injected into the motor at a rate normally only a few percent of that of the propellant. The injection is best made in the form of a fine spray in order to obtain maximum catalyst surface.
The first thing that occurs in the motor is the evaporation of the spray, yielding water vapor, methyl alcohol vapor, and Ce(NO in the form of fine particles. The
water vapor cools the motor slightly without substantial effect on performance, and the methyl alcohol vapor burns and serves to some extent as additional fuel.
The Ce(NO decomposes according to the equation:
The CeO is a very active solid catalyst for the decomposition of nitroparaffins, acting by heterogeneous catalysis, while both the O and the N0 increase the rate of decomposition and flame speed of nitroparaflins, acting by homogeneous catalysis. Furthermore, the O and N0 help make up an oxygen deficiency in the nitroparaflins, thus increasing the available enthalpy and specific impulse. The solid CeO particles will in part be ejected through the nozzle and in part adhere to the wall of'the motor, where their catalytic activity will be continued.
In the use of the fluid catalysts, as in the case of the catalyst suspension, the fluid catalyst may be injected separately or in solution in the self-combustible propellant. If used in the combustible propellant suitable precautions must be taken to prevent overheating of the catalystcontaining propellant, in order to avoid explosion.
In some instances it may be desirable to continue the injection of a small stream of oxygen into the combustion chamber in order to obtain higher specific impulses and higher velocities. In such instances it is advantageous to continue the injection of the catalyst along with the small stream of oxygen as more rapid and complete combustion of the self-combustible fuel is thereby obtained.
This application is a division of our copcnding Serial No. 528,893 filed March 31, 1944, now U.S. Patent No. 3,048,007.
We claim:
1. The method of operating a jet motor utilizing a self-combustible fuel selected from the nitroparaflins, which comprises continuously injecting into the combustion chamber of the motor during operation a fluid which will provide catalyst for the decomposition of the nitroparaflins, said fluid being selected from the group consisting of CrO Cl Mn O Fe(CO) solutions of Ce(NO in methanol and Ca(MnO in water, and Ni(CO) vapor, said nitroparaflins being selected from the group consisting of nitromethane and mixtures of nitromethane and nitroethane, and igniting the said nitroparaflins in the chamber thereby producing gases under pressure which are ejected out the exhaust nozzle.
2. The method of operating a jet motor utilizing a selfcombustible fuel selected from the nitroparaflins, the method which comprises continuously injecting into the combustion chamber of the motor during operation nitroparaflins containing a fluid which on heating will provide catalyst for the decomposition of the nitroparatlins said fluid being selected from the group consisting of CrO Cl Mn O Fe(CO) solutions of Ce(NO in methanol and Ca(.MnO in water, and Ni(CO) vapor and said nitroparaflin being selected from the group consisting of nitromethane and mixtures of nitromethane and nitroethane, and igniting the said nitroparaifins in the chamber thereby producing gases under pressure which are ejected out the exhaust nozzle.
3. The method of operating a jet motor having a combustion chamber and an exhaust nozzle from the chamber which comprises injecting into the combustion chamber nitromethane and a catalyst selected from the group consisting of CrO Cl Mn O Fe(CO) solutions of Ce(NO in methanol and Ca(MnO in water, and Ni(CO) vapor and igniting the nitromethane in the chamber, thereby producing gases under pressure which are ejected out the exhaust nozzle.
4. The process of decomposing nitromethane which comprises heating the nitromethane in the presence of a catalyst selected from the group consisting of CrO Cl M11207, Fe(CO) solutions of Ce(NO in methanol and Ca(MnO in water, and Ni(CO) vapor.
5. The method of operating a jet motor having a com- 6 comprises heating the nitroparafiin selected from the group consisting of nitromethane and mixtures of nitromethane and nitroethane in the presence of a catalyst selected from the group consisting of CIO CI Mn O Fe(CO) solutions of Ce(N0 in methanol and Ca(MnO in Water, and Ni(CO) vapor.
References Cited in the file of this patent UNITED STATES PATENTS Stosick Jan. 6, 1948 2,433,943 Zwicky et a1. Jan. 6, 1948

Claims (1)

1. THE METHOD OF OPERATING A JET MOTOR UTILIZING A SELF-COMBUSTIBLE FUEL SELECTED FROM THE NITROPARAFFINS, WHICH COMPRISES CONTINUOUSLY INJECTING INTO THE COMBUSTION CHAMBER OF THE MOTOR DURING OPERATION A FLUID WHICH WILL PROVIDE CATALYST FOR THE DECOMPOSITION OF THE NITROPARAFFINS, SAID FLUID BEING SELECTED FROM THE GROUP CONSISTING OF CRO2CL2, MN2O7, FE(CO)5, SOLUTIONS OF CE(NO3)4 IN METHANOL AND CA(MNO4)2 IN WATER, AND NI(CO)4 VAPOR, SAID NITROPARAFFINS BEING SELECTED FROM THE GROUP CONSISTING OF NITROMETHANE AND MIXTURES OF NITROMETHANE AND NITROETHANE, AND IGNITING THE SAID NITROPARAFFINS IN THE CHAMBER THEREBY PRODUCING GASES UNDER PRESSURE WHICH ARE EJECTED OUT THE EXHAUST NOZZLE.
US163946A 1944-03-31 1961-11-21 Decomposition of nitroparaffins in jet propulsion motor operation Expired - Lifetime US3121992A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US163946A US3121992A (en) 1944-03-31 1961-11-21 Decomposition of nitroparaffins in jet propulsion motor operation

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US528893A US3048007A (en) 1944-03-31 1944-03-31 Decomposition of nitro-paraffins in jet propulsion motor operation
US163946A US3121992A (en) 1944-03-31 1961-11-21 Decomposition of nitroparaffins in jet propulsion motor operation

Publications (1)

Publication Number Publication Date
US3121992A true US3121992A (en) 1964-02-25

Family

ID=26860109

Family Applications (1)

Application Number Title Priority Date Filing Date
US163946A Expired - Lifetime US3121992A (en) 1944-03-31 1961-11-21 Decomposition of nitroparaffins in jet propulsion motor operation

Country Status (1)

Country Link
US (1) US3121992A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6272846B1 (en) * 1999-04-14 2001-08-14 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reduced toxicity fuel satellite propulsion system
US11125993B2 (en) 2018-12-10 2021-09-21 Facebook Technologies, Llc Optical hyperfocal reflective systems and methods, and augmented reality and/or virtual reality displays incorporating same
US11221494B2 (en) 2018-12-10 2022-01-11 Facebook Technologies, Llc Adaptive viewport optical display systems and methods
US11275436B2 (en) 2017-01-11 2022-03-15 Rpx Corporation Interface-based modeling and design of three dimensional spaces using two dimensional representations
US11513356B2 (en) 2016-07-08 2022-11-29 Meta Platforms Technologies, Llc Optical combiner apparatus
US11549475B2 (en) * 2015-06-22 2023-01-10 Doosan Enerbility Co., Ltd. Fuel supply nozzle unit having sealing structure
US11662513B2 (en) 2019-01-09 2023-05-30 Meta Platforms Technologies, Llc Non-uniform sub-pupil reflectors and methods in optical waveguides for AR, HMD and HUD applications
US11863730B2 (en) 2021-12-07 2024-01-02 Snap Inc. Optical waveguide combiner systems and methods

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2433932A (en) * 1944-03-11 1948-01-06 Aerojet Engineering Corp Fuel combustion
US2433943A (en) * 1944-03-11 1948-01-06 Aerojet Engineering Corp Operation of jet propulsion motors with nitroparaffin

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2433932A (en) * 1944-03-11 1948-01-06 Aerojet Engineering Corp Fuel combustion
US2433943A (en) * 1944-03-11 1948-01-06 Aerojet Engineering Corp Operation of jet propulsion motors with nitroparaffin

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6272846B1 (en) * 1999-04-14 2001-08-14 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reduced toxicity fuel satellite propulsion system
US6311477B1 (en) 1999-04-14 2001-11-06 The United States Of America As Represented By The Administrator Of The National Aeronautics Space Administration Reduced toxicity fuel satellite propulsion system including axial thruster and ACS thruster combination
US6314718B1 (en) 1999-04-14 2001-11-13 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reduced toxicity fuel satellite propulsion system including fuel cell reformer with alcohols such as methanol
US6378291B1 (en) 1999-04-14 2002-04-30 The United States Of America As Represented By The Administrator Of The National Aeronatics And Space Administration Reduced toxicity fuel satellite propulsion system including catalytic decomposing element with hydrogen peroxide
US6546714B1 (en) 1999-04-14 2003-04-15 The United States Of America, As Represented By The Administrator Of The National Aeronautics And Space Administration Reduced toxicity fuel satellite propulsion system including plasmatron
US11549475B2 (en) * 2015-06-22 2023-01-10 Doosan Enerbility Co., Ltd. Fuel supply nozzle unit having sealing structure
US11520147B2 (en) 2016-07-08 2022-12-06 Meta Platforms Technologies, Llc Optical combiner apparatus
US11513356B2 (en) 2016-07-08 2022-11-29 Meta Platforms Technologies, Llc Optical combiner apparatus
US11275436B2 (en) 2017-01-11 2022-03-15 Rpx Corporation Interface-based modeling and design of three dimensional spaces using two dimensional representations
US11221494B2 (en) 2018-12-10 2022-01-11 Facebook Technologies, Llc Adaptive viewport optical display systems and methods
US11125993B2 (en) 2018-12-10 2021-09-21 Facebook Technologies, Llc Optical hyperfocal reflective systems and methods, and augmented reality and/or virtual reality displays incorporating same
US11614631B1 (en) 2018-12-10 2023-03-28 Meta Platforms Technologies, Llc Adaptive viewports for a hyperfocal viewport (HVP) display
US11668930B1 (en) 2018-12-10 2023-06-06 Meta Platforms Technologies, Llc Optical hyperfocal reflective systems and methods, and augmented reality and/or virtual reality displays incorporating same
US11662513B2 (en) 2019-01-09 2023-05-30 Meta Platforms Technologies, Llc Non-uniform sub-pupil reflectors and methods in optical waveguides for AR, HMD and HUD applications
US11863730B2 (en) 2021-12-07 2024-01-02 Snap Inc. Optical waveguide combiner systems and methods

Similar Documents

Publication Publication Date Title
US2433943A (en) Operation of jet propulsion motors with nitroparaffin
US2433932A (en) Fuel combustion
US6807804B2 (en) Hybrid rocket motor having a precombustion chamber
US5456065A (en) Injection element of coaxial design for rocket combustion chambers
US3121992A (en) Decomposition of nitroparaffins in jet propulsion motor operation
US3286997A (en) Vortex fuel injector
US3715888A (en) Hybrid rocket
US2706887A (en) Liquid propellant rocket motor
US3048007A (en) Decomposition of nitro-paraffins in jet propulsion motor operation
US2648190A (en) Initiation of propellant decomposition
CN111120148B (en) Premixed propellant injector integrating ignition and anti-backfire functions
US2722100A (en) Apparatus for feeding a liquid fuel, a liquid oxidizer and water to a combustion chamber associated with rocket apparatus
US4350101A (en) Device for treating substances in different phases, such as the treatment of substances in liquid, semi-liquid or paste form, by another notably gaseous phase
US2874539A (en) Continuous combustion power plant
RU2161719C2 (en) Coaxial jet nozzle
US6739121B2 (en) Flame holder for a hybrid rocket motor
US2887844A (en) Rocket motor
US3378596A (en) Process for producing nitrohydrocarbons
US3537650A (en) Two-stage sonic atomizing device
US3174283A (en) Expendable barrier
US3469394A (en) Rocket propellant injection
US3126701A (en) Process for generating gases
US2591422A (en) Liquid fuel and oxidizer jacketed combustion chamber with axial conical fuel spreader
US3182445A (en) Liquid-solid propellant rocket case and method
US3136123A (en) Rocket engine injector