US2612752A - Feeding apparatus, including injectors adapted to supply combustion liquids under pressure to a combustion chamber - Google Patents

Feeding apparatus, including injectors adapted to supply combustion liquids under pressure to a combustion chamber Download PDF

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US2612752A
US2612752A US131461A US13146149A US2612752A US 2612752 A US2612752 A US 2612752A US 131461 A US131461 A US 131461A US 13146149 A US13146149 A US 13146149A US 2612752 A US2612752 A US 2612752A
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combustion chamber
combustion
injector
liquid
chamber
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US131461A
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Esther C Goddard
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DANIEL AND FLORENCE GUGGENHEIM
DANIEL AND FLORENCE GUGGENHEIM FOUNDATION
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DANIEL AND FLORENCE GUGGENHEIM
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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
    • F02K9/44—Feeding propellants
    • 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

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  • This invention relates to apparatus for feeding liquid combustion elements, such as gasoline and liquid oxygen, to a chamber in which combustion is to be maintained, and is a division of prior application Serial No. 536,558 filed May 20, 1944, now Patent No. 2,558,483 dated June 26, 1951.
  • Such combustion chambers are commonly provided with rearwardly-open discharge nozzles and have particular utility in rocket apparatus and in other jet-propelled mechanisms.
  • the injectors are operated by vapors of the liquid fuel and of the liquid oxygen which are evolved in separate combustion chamber jacket spaces.
  • the invention further relates to arrangements and combinations of parts which will be hereinafter described and more particularly pointed out in the. appended claims.
  • FIG. 1 A preferred form of the invention is shown in the drawing, in which the figure is a diagrammatic elevation of the improved feeding apparatus.
  • a combustion chamber CI has a jacket divided by an annular partition 80 into jacket spaces 8
  • Storage tank T5 and T6 are provided for liquid oxygen and for gasoline or other liquid fuel.
  • Injectors are shown at 84 and 85, and each injector may comprise a cylindrical outer casing having an inner transverse partition in which a draft or Venturi tube is mounted.
  • a shut-off valve 86 and a check valve 81 are provided in a feed pipe 88 which connects the tank T5 to the injector 84, and a similar shutoff valve 90 and check valve 9
  • a pipe 94 connects the jacket space BI with the injector 84 and i provided with a check valve 95 and with a pressure control or regulating valve 06.
  • the jacket space 82 is similarly connected by a pipe 9'! to the injector 85 and is provided with a check valve 90 and with a pressure control or regulating valve 99.
  • the discharge or outlet end of the injector 84 is connected by a pipe I00 to the combustion chamber CI and is provided with shut-off valves 2 Claims. (01. 60 39.14)
  • the dischar e end of the injector is similarly connected to the combustion chamber CI by a pipe IIO having shut-off valves III and H2, a check valve '3 and a pressure-responsiverelief valve II4.
  • a pipe Ilii connects the discharge end of the injector 84 to the jacket space 8
  • a tank T7 is connected by pipes I20 and I2I to the pipe I00 previously described and these branch pipes are provided with shut-off valves I22 and I23.
  • the tank T1 contains a supply of liquid oxygen and is preferably under relatively high pressure.
  • a similar tank T8 for fuel under pressure is connected by pipes I30 and I31 to the pipe II-'0 previously described. and these pipes are provided with shutoff valves I32 and I33.
  • a flame-type of igniter GI is provided for the chamber CI and this isniter maybe of the construction shown in Goddard Patent No. 2,090,039.
  • Filler pipes I40 and .14] are provided for the tanks T5 and T6 and are equipped with shut-off valves I42 and I43.
  • the apparatus shown in the drawing may be operated either with or without making use of the pressure. tanks T1 and T8. The operation without using the tanks T1 and T8 will first be described.
  • gasoline vapor will flow through the pipe 91 and valves 98 and 09 to the injector 85 and thence through the pipe IIO to the combus tion chamber CI, and liquid gasoline will flow to the injector 85 as soon as the valve is opened.
  • Ihe Venturi action of the injectors 84 and 85 quickly steps up the liquid pressures from the relatively low storage tank pressures to substantially higher pressures such as 100 lbs. per square inch, and the liquids under the increased pressures are delivered through the pipes I and H0 and check valves I93 and H3 to the combustion chamber CI.
  • the resultant mixture of oxygen and gasoline in the chamber CI will then be ignited by the flame from the igniter GI and increasing amounts of gaseous oxygen and gasoline will be delivered from the jacket spaces ill and 82.
  • the regulating valves 96 and 99 control the rate of flow of these gases to the injectors and thus prevent the injection of undesired amounts of liquid oxygen and gasoline to the chamber CI.
  • and 82 are continuously replenished through the connections H6 and III.
  • the check valves I03 and I I3 are set to open at the high pressures developed by the injectors but not at the relatively low pressure in the tanks T and T6.
  • the check valves 95 and 93 prevent reverse flow in the pipes 94 and S7.
  • the pressure relief valves I04 and H4 are provided to prevent bursting of the pipes I60 and I I0, should evaporation produce dangerous pressure in either of these pipes after the valves IOI and III have been closed to discontinue operations.
  • the pressure tanks T1 and T8 constitute auxiliary starting equipment which may be used should occasion require. These tanks may be filled with liquid at high pressure by temporarily closing the valves 02 and I23 for the tank T1 and opening the valve I22 when the apparatus is in operation. This will cause the liquid oxygen which is under high pressure in the pipe I08 to enter the tank T1 and to compress any gas or vapor in the top of the tank to any desired pressure, which pressure may then be retained by closing the valve I22.
  • a similar procedure may be used to fill the tank T8 with gasoline under high pressure.
  • liquid oxygen under high pressure may be fed direct to the chamber CI, and similarly by opening the valve I33 for the tank T8, gasoline under high pressure may be fed direct to the chamber CI. It is thus possible to start combustion in the chamber Cl very quickly and without waiting for the injectors 84 and 85 to become operative.
  • a combustion apparatus comprising a combustion chamber and low pressure storage tanks for liquid fuel and liquid oxygen, in combination, injectors operative to feed said liquid fuel and liquid oxygen from said tanks to said combustion chamber at relatively higher pressures, and means to render said injectors operative, said means including two separate jacket spaces about said combustion chamber and connections through which each jacket space receives a portion of one of said liquids and delivers the vapor thereof to the corresponding injector under pressure and thereby renders said injector operative to feed its liquid to said combustion chamber at substantially more than storage tank pressure, together with separate high pressure storage tanks connected between each injector and the combustion chamber, and means to render said high pressure tanks selectively and immediately operative to inject the corresponding liquid'to said chamber.
  • a combustion apparatus comprising a combustion chamber and low pressure storage tanks for liquid fuel and liquid oxygen, in combination, injectors operative to feed said liquid fuel and liquid oxygen from said tanks to said combustion chamber at relatively higher pressures, and means to render said injectors operative, said means including two separate jacket spaces about said combustion chamber and connections through which each jacket space receives a portion of one of said liquids and delivers the vapor thereof to the corresponding injector under pressure and thereby renders said injector operative to feed its liquid to said combustion chamber at substantially more than storage tank pressure, together with separate high pressure storage tanks connected between each injector and the combustion chamber, means to render said high pressure tanks selectively and immediately operative to inject the corresponding liquid to said chamber, and a separate pressurerelief valve in the connection between each high pressure storage tank and the combustion chamber to protect the apparatus from excessive pressures developed by evaporation in said connections.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Description

Oct. 7, 1952 R. H. GODDARD 2,612,752
FEEDING APPARATUS, INCLUDING INJECTORS ADAPTED TO SUPPLY COMBUSTION LIQUIDS UNDER PRESSURE TO A COMBUSTION CHAMBER Original Filed May 20, 1944 Z p/Ul /06L 8i TEL I I N V EN TOR.
JPoKMZ Ji oclczc z gg fstizer (ZGoddard, Exec,
Patented Oct. 7, 1952 FEEDING APPARATUS, INCLUDING INJEC- TORS ADAPTED TO SUPPLY COMBUSTION LIQUIDS UNDER PRESSURE TO A COM- BUSTION CHAMBER Robert H. Goddard, deceased, late of Annapolis,
Md., by Esther C. Goddard, .executrix, Worcester, Mass., assignor of one-half to The Daniel and Florence Guggenheim Foundation, New York, N. Y., a corporation of New York Original application May 20, 1944, Serial No. 536,558, now Patent No. 2,558,483, dated June 26, 1951. Divided and this application December 6, 1949, Serial No. 131,461
This invention relates to apparatus for feeding liquid combustion elements, such as gasoline and liquid oxygen, to a chamber in which combustion is to be maintained, and is a division of prior application Serial No. 536,558 filed May 20, 1944, now Patent No. 2,558,483 dated June 26, 1951. Such combustion chambers are commonly provided with rearwardly-open discharge nozzles and have particular utility in rocket apparatus and in other jet-propelled mechanisms.
It is the general object of this invention to provide feeding apparatus involving the use of injectors in such manner that the apparatus is capable of generating much higher feeding pressures then are maintained in the storage or supply tanks.
In the preferred form, the injectors are operated by vapors of the liquid fuel and of the liquid oxygen which are evolved in separate combustion chamber jacket spaces 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, in which the figure is a diagrammatic elevation of the improved feeding apparatus.
Referring to the drawing, a preferred construction is shown in which vapors or gases from the combustion elements are utilized to operate the injectors.
A combustion chamber CI has a jacket divided by an annular partition 80 into jacket spaces 8| and 82. Storage tank T5 and T6 are provided for liquid oxygen and for gasoline or other liquid fuel. Injectors are shown at 84 and 85, and each injector may comprise a cylindrical outer casing having an inner transverse partition in which a draft or Venturi tube is mounted.
A shut-off valve 86 and a check valve 81 are provided in a feed pipe 88 which connects the tank T5 to the injector 84, and a similar shutoff valve 90 and check valve 9| are provided in a feed pipe 92 which connects the tank T6 to the injector 85. A pipe 94 connects the jacket space BI with the injector 84 and i provided with a check valve 95 and with a pressure control or regulating valve 06. The jacket space 82 is similarly connected by a pipe 9'! to the injector 85 and is provided with a check valve 90 and with a pressure control or regulating valve 99.
The discharge or outlet end of the injector 84 is connected by a pipe I00 to the combustion chamber CI and is provided with shut-off valves 2 Claims. (01. 60 39.14)
IOI and I02, a check valve I03 and a pressur'e responsive relief valve I04. The dischar e end of the injector is similarly connected to the combustion chamber CI by a pipe IIO having shut-off valves III and H2, a check valve '3 and a pressure-responsiverelief valve II4.
A pipe Ilii connects the discharge end of the injector 84 to the jacket space 8| and a similar pipe II'I' connects the injector 85 to the jacket space 82. I
For quick starting purposes, a tank T7 is connected by pipes I20 and I2I to the pipe I00 previously described and these branch pipes are provided with shut-off valves I22 and I23. The tank T1 contains a supply of liquid oxygen and is preferably under relatively high pressure. A similar tank T8 for fuel under pressure is connected by pipes I30 and I31 to the pipe II-'0 previously described. and these pipes are provided with shutoff valves I32 and I33. A flame-type of igniter GI is provided for the chamber CI and this isniter maybe of the construction shown in Goddard Patent No. 2,090,039. Filler pipes I40 and .14] are provided for the tanks T5 and T6 and are equipped with shut-off valves I42 and I43.
The apparatus shown in the drawing may be operated either with or without making use of the pressure. tanks T1 and T8. The operation without using the tanks T1 and T8 will first be described.
It is desirable that a certain amount of liquid and? gaseous oxygen be present in the jacket space 8-! and. that a similar amount of liquid or g'aseous'fuel or gasoline be presented in the jacket space 82. The flame igniter GI is then started and the heat of the flame is sumcient to produce Il'Ole gases or vapors in the jacket spaces 81 and 8 The oxygen vapor in the space M will then flow through the pipe 94, regulating valve 96 and check valve 95 to the injector 84 and thence through the pipe I00 and its several valves to the chamber CI, assuming that the valves IN and I02 have been opened and that the valves I22 and I23 are closed. If the valve 86 is then opened, liquid oxygen will flow through the pipe 88 to the injector 84.
Similarly, gasoline vapor will flow through the pipe 91 and valves 98 and 09 to the injector 85 and thence through the pipe IIO to the combus tion chamber CI, and liquid gasoline will flow to the injector 85 as soon as the valve is opened.
Ihe Venturi action of the injectors 84 and 85 quickly steps up the liquid pressures from the relatively low storage tank pressures to substantially higher pressures such as 100 lbs. per square inch, and the liquids under the increased pressures are delivered through the pipes I and H0 and check valves I93 and H3 to the combustion chamber CI.
The resultant mixture of oxygen and gasoline in the chamber CI will then be ignited by the flame from the igniter GI and increasing amounts of gaseous oxygen and gasoline will be delivered from the jacket spaces ill and 82. The regulating valves 96 and 99 control the rate of flow of these gases to the injectors and thus prevent the injection of undesired amounts of liquid oxygen and gasoline to the chamber CI.
The oxygen and gasoline in the jacket spaces 8| and 82 are continuously replenished through the connections H6 and III. The check valves I03 and I I3 are set to open at the high pressures developed by the injectors but not at the relatively low pressure in the tanks T and T6. The check valves 95 and 93 prevent reverse flow in the pipes 94 and S7.
The pressure relief valves I04 and H4 are provided to prevent bursting of the pipes I60 and I I0, should evaporation produce dangerous pressure in either of these pipes after the valves IOI and III have been closed to discontinue operations.
The pressure tanks T1 and T8 constitute auxiliary starting equipment which may be used should occasion require. These tanks may be filled with liquid at high pressure by temporarily closing the valves 02 and I23 for the tank T1 and opening the valve I22 when the apparatus is in operation. This will cause the liquid oxygen which is under high pressure in the pipe I08 to enter the tank T1 and to compress any gas or vapor in the top of the tank to any desired pressure, which pressure may then be retained by closing the valve I22. A similar procedure may be used to fill the tank T8 with gasoline under high pressure. By thereafter opening the valve I23 for the tank T1, liquid oxygen under high pressure may be fed direct to the chamber CI, and similarly by opening the valve I33 for the tank T8, gasoline under high pressure may be fed direct to the chamber CI. It is thus possible to start combustion in the chamber Cl very quickly and without waiting for the injectors 84 and 85 to become operative.
Improved and simplified means is thus provided by which liquid combustion elements may be fed to a combustion chamber under high pressures developed in the feeding apparatus itself and Without requiring auxiliary pumps or other similar apparatus.
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 what is claimed is:
1. In a combustion apparatus comprising a combustion chamber and low pressure storage tanks for liquid fuel and liquid oxygen, in combination, injectors operative to feed said liquid fuel and liquid oxygen from said tanks to said combustion chamber at relatively higher pressures, and means to render said injectors operative, said means including two separate jacket spaces about said combustion chamber and connections through which each jacket space receives a portion of one of said liquids and delivers the vapor thereof to the corresponding injector under pressure and thereby renders said injector operative to feed its liquid to said combustion chamber at substantially more than storage tank pressure, together with separate high pressure storage tanks connected between each injector and the combustion chamber, and means to render said high pressure tanks selectively and immediately operative to inject the corresponding liquid'to said chamber.
2. In a combustion apparatus comprising a combustion chamber and low pressure storage tanks for liquid fuel and liquid oxygen, in combination, injectors operative to feed said liquid fuel and liquid oxygen from said tanks to said combustion chamber at relatively higher pressures, and means to render said injectors operative, said means including two separate jacket spaces about said combustion chamber and connections through which each jacket space receives a portion of one of said liquids and delivers the vapor thereof to the corresponding injector under pressure and thereby renders said injector operative to feed its liquid to said combustion chamber at substantially more than storage tank pressure, together with separate high pressure storage tanks connected between each injector and the combustion chamber, means to render said high pressure tanks selectively and immediately operative to inject the corresponding liquid to said chamber, and a separate pressurerelief valve in the connection between each high pressure storage tank and the combustion chamber to protect the apparatus from excessive pressures developed by evaporation in said connections.
ESTHER C. GODDARD, Executria: 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 Name Date Whittle July 16, 1946 OTHER REFERENCES Number
US131461A 1944-05-20 1949-12-06 Feeding apparatus, including injectors adapted to supply combustion liquids under pressure to a combustion chamber Expired - Lifetime US2612752A (en)

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Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2704438A (en) * 1951-02-10 1955-03-22 Goodyear Aircraft Corp Starting fuel system for jet and rocket motors
US2771741A (en) * 1952-05-16 1956-11-27 Standard Oil Co Low-temperature starting of gas turbine engines
US2785532A (en) * 1953-12-11 1957-03-19 Kretschmer Willi Propellant supply systems for jet reaction motors
US3128601A (en) * 1960-09-15 1964-04-14 United Aircraft Corp Pre-burner rocket control system
US3234728A (en) * 1963-02-08 1966-02-15 Douglas Aircraft Co Inc Zero-gravity propellant feed system
US3254486A (en) * 1963-05-31 1966-06-07 Martin Marietta Corp Zero gravity start device
US3379011A (en) * 1966-11-08 1968-04-23 Air Force Usa Energy exchange device and separator
US3410092A (en) * 1961-07-17 1968-11-12 Marquardt Corp Reliquefaction cycle for liquid air cycle engine
DE1751962B1 (en) * 1968-08-24 1971-03-25 Messerschmitt Boelkow Blohm Fuel delivery system for a rocket combustion chamber
US3672165A (en) * 1968-09-03 1972-06-27 Messerschmitt Boelkow Blohm Method of feeding liquid propellants to gas generators or rocket combustion chambers and feeding system for performing the method
US3910037A (en) * 1973-07-30 1975-10-07 Robert J Salkeld Dual fuel rocket engine
FR2431095A1 (en) * 1978-07-13 1980-02-08 Sperry Rand Ltd FUEL PRESSURE CIRCUIT FOR GAS GENERATOR
US5551230A (en) * 1994-03-14 1996-09-03 Rockwell International Corporation Heat induced high pressure lox pump rocket engine cycle
EP3726136A1 (en) * 2019-04-14 2020-10-21 Hamilton Sundstrand Corporation Distributed fuel modules with hydraulic flow circuit breakers and gaseous flow circuit breakers

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2404335A (en) * 1939-12-09 1946-07-16 Power Jets Res & Dev Ltd Liquid fuel burner, vaporizer, and combustion engine

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2404335A (en) * 1939-12-09 1946-07-16 Power Jets Res & Dev Ltd Liquid fuel burner, vaporizer, and combustion engine

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2704438A (en) * 1951-02-10 1955-03-22 Goodyear Aircraft Corp Starting fuel system for jet and rocket motors
US2771741A (en) * 1952-05-16 1956-11-27 Standard Oil Co Low-temperature starting of gas turbine engines
US2785532A (en) * 1953-12-11 1957-03-19 Kretschmer Willi Propellant supply systems for jet reaction motors
US3128601A (en) * 1960-09-15 1964-04-14 United Aircraft Corp Pre-burner rocket control system
US3410092A (en) * 1961-07-17 1968-11-12 Marquardt Corp Reliquefaction cycle for liquid air cycle engine
US3234728A (en) * 1963-02-08 1966-02-15 Douglas Aircraft Co Inc Zero-gravity propellant feed system
US3254486A (en) * 1963-05-31 1966-06-07 Martin Marietta Corp Zero gravity start device
US3379011A (en) * 1966-11-08 1968-04-23 Air Force Usa Energy exchange device and separator
DE1751962B1 (en) * 1968-08-24 1971-03-25 Messerschmitt Boelkow Blohm Fuel delivery system for a rocket combustion chamber
US3672165A (en) * 1968-09-03 1972-06-27 Messerschmitt Boelkow Blohm Method of feeding liquid propellants to gas generators or rocket combustion chambers and feeding system for performing the method
US3910037A (en) * 1973-07-30 1975-10-07 Robert J Salkeld Dual fuel rocket engine
FR2431095A1 (en) * 1978-07-13 1980-02-08 Sperry Rand Ltd FUEL PRESSURE CIRCUIT FOR GAS GENERATOR
US5551230A (en) * 1994-03-14 1996-09-03 Rockwell International Corporation Heat induced high pressure lox pump rocket engine cycle
EP3726136A1 (en) * 2019-04-14 2020-10-21 Hamilton Sundstrand Corporation Distributed fuel modules with hydraulic flow circuit breakers and gaseous flow circuit breakers
US11286886B2 (en) 2019-04-14 2022-03-29 Hamilton Sundstrand Corporation Distributed fuel modules with hydraulic flow circuit breakers and gaseous flow circuit breakers

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