US2453378A - Liquid-cooled nozzle arrangement for combustion chambers of jet propulsion apparatus - Google Patents

Liquid-cooled nozzle arrangement for combustion chambers of jet propulsion apparatus Download PDF

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Publication number
US2453378A
US2453378A US493800A US49380043A US2453378A US 2453378 A US2453378 A US 2453378A US 493800 A US493800 A US 493800A US 49380043 A US49380043 A US 49380043A US 2453378 A US2453378 A US 2453378A
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United States
Prior art keywords
liquid
nozzle
cooling medium
combustion chamber
jacket
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Expired - Lifetime
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US493800A
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Lubbock Isaac
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Asiatic Petroleum Co Ltd
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Asiatic Petroleum Co Ltd
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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
    • F02K9/52—Injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling

Definitions

  • This invention relates to .iet propulsion apparatus having a combustion chamber in which a liquid fuel isl burnt with an oxidant in liquid form such as liquid oxygen, liquid air, liquefied nitro- ⁇ gen peroxide, nitric or perchloric acid or the like.
  • a central spraying ⁇ nozzle for'the fuel is combined with an. annular l outer nozzle fior the liquid oxidant.
  • the central 'spraying nozzle for the fuel l is preferably of the well-known form embodying a vrtex chamber fed under pressure to give an open spray while surrounding it is an annular passage carrying the oxidant and in virtue Vof the setting of the annular gap providing meter- 'ing means to ensure the correct proportions of fuel to oxidant.
  • the outer annularpass'age' preferably tapers inwards across the outer face of the fuel nozzle to give a spray which by itself forms a node first -in front of the centre -of the fuel nozzle, expanding again vfrom this node to fuel nozzle keeps it cool against the flame radiation.
  • Additional cooling means may be provided by a cooling medium such as water, passed through passages or a coil in or about the head in which the nozzles aremounted. Such cooling medium may be discharged into the combustion chamber to intermingle with the flame products.
  • a cooling medium such as water
  • the cooling means is preferably devised so that the cooling medium will pass over a surface to be cooled in the vicinity of the combustible ingredients discharged from the nozzle, at a far higher speed than that equivalent to the quantity of cooling medium which is discharged into the combustion chamber if the fluid were ⁇ fed in an ordinary manner.
  • the cooling medium is introduced tangentially at a high velocity by passing it through a constriction into a Jacket mounted within ⁇ the combustion chamber so as to surround a space immediately in advance of the nozzle.
  • the jacket may be of substantially triangular form in -cross section.
  • cooling surface is disposed substantially in the form of a cone, the cooling medium being introduced tangentially atA high velocity into an apex of the triangular cross sectional form of the jacket corresponding to the wider "for the passage out products.
  • the invention is. illustrated by way offexample in the accompanying drawing which, is 'a sectional elevation of the head of a combustion chamber in which a liquid fuel is burnt with an oxidant in liquid form.
  • i indicates the head of the shell of the combustion chamber pro'per. 2 indicates refractory lining withinthe combustion chamber shell. The parts I and 2 are shown broken away.
  • the combustion chamber may be constructed generally as described in British Patent No. 578;007.
  • the nozzle comprises the central spray nozzle' into which the liquid fuel is fed tangentially at d to produce a vortex in the known manner.
  • the fuel inlet to the nozzle is fromv the duct 5 and the outlet from the nozzle into the combustion chainber is through the opening B.
  • an oute member 1 Surrounding the central nozzle 3 is an oute member 1 which leaves an annular passage la so that a conical cooling surface I0 is exposed to the space in which the flame products are generated.
  • the cooling medium is introduced at high velocity into the jacket through the tangential port Il which is located at the remote cornerof part of the cone so that the cooling medium in provide for the discharge of cooling medium into the combustion chamber to intermingle with the flame products.
  • said annular passage tapering inwardly toward its outlet Lto said combustion chamber to provide a convergent spray o1 oxidant directed ing surface is disposed substantially in the form of a lcone, means for introducing the cooling medium tangentially at high velocity into an apex of the triangular cross sectional form of the jacket corresponding to the wider part oi the cone so that the cooling medium in the jacket will rotate with a high velocity, orifices in the narrow part of the cone being provided for thepassage out of the jacket of a predetermined amount of cooling medium to enter the combustion chamber in the region of the nozzle and to intermingle at that point with the'iiame products.
  • a central nozzle for admitting the liquid fuel to said chamber comprising a vortex chamber fed under pressure to provide an open spray, an outer nozzle forming an annular passage around said central nozzle for admitting liquid oxidant to said chamber, a jacket mounted within said chamber/so as to surround a space in iront of the nozzles and being of substantially triangular form in cross section so that the cooling surface is disposed substantially in the form of a cone.
  • cooling medium tangentially at high velocity into an apex of the triangular cross sectional form of the jacket corresponding to the wider part of the cone so that the cooling medium in the jacket will rotate with a high velocity
  • orifices being provided in the narrow part of the cone for the passage out of the jacket f a predetermined amount of cooling medium to enter the combustion chamber in the region of the nozzles and to intermingle at thatpoint with the dame products.
  • a central nozzle for. admitting the liquid fuel to said on the spray of iuel from said central nozzle, a jacket mounted within said chamber so as to surround a space in front of the nozzles and being of substantially triangular form in cross section soy thatI the cooling surface is disposed substantially in the form of a cone, means for introducing the cooling medium tangentially at high velocity into an apex of the triangular cross sectional form of the jacket corresponding to the wider-part oi v the cone so that the cooling medium in the jacket will rotate with a high velocity, orifices being provided in the narrow part of the cone for the passageout oi the Jacket of a predetermined amount of cooling medium to enter the combustion chamber in the region of the nozzles and to intermingle at that point with the flame products.

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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

Nov. 9, 1948. LUBBOCK l 2,453,378
y LIQUID-cool@ NozzLE ARRANGEMENT Fon coMBUs'rIoN CHAMBERS 0F JET PRoPULsIoN APPARATUS Filed July '7, 1943 15m Lubbock Mm Patented Nov. 9, 1948 UNrr-ED"y STATE `s PATENT oFFlci-z 'LIQUID-coctel) NozzLa ARRANGEMENT I ron. coMnUs'noN CHAMBERS or mr PROPULSION APPARAT'U Isaac Lubbock. Great St.'` Helens, London, England, a
pany Limited, London, England Application July 7, 1943,-Serial No. 493,800 In Great Britain November 7.11941 (Cl. Bil-48) This invention relates to .iet propulsion apparatus having a combustion chamber in which a liquid fuel isl burnt with an oxidant in liquid form such as liquid oxygen, liquid air, liquefied nitro-` gen peroxide, nitric or perchloric acid or the like.
According'to the invention a central spraying` nozzle for'the fuel is combined with an. annular l outer nozzle fior the liquid oxidant.
The central 'spraying nozzle for the fuel lis preferably of the well-known form embodying a vrtex chamber fed under pressure to give an open spray while surrounding it is an annular passage carrying the oxidant and in virtue Vof the setting of the annular gap providing meter- 'ing means to ensure the correct proportions of fuel to oxidant. The outer annularpass'age' preferably tapers inwards across the outer face of the fuel nozzle to give a spray which by itself forms a node first -in front of the centre -of the fuel nozzle, expanding again vfrom this node to fuel nozzle keeps it cool against the flame radiation. 1
Additional cooling means may be provided by a cooling medium such as water, passed through passages or a coil in or about the head in which the nozzles aremounted. Such cooling medium may be discharged into the combustion chamber to intermingle with the flame products.
The cooling means is preferably devised so that the cooling medium will pass over a surface to be cooled in the vicinity of the combustible ingredients discharged from the nozzle, at a far higher speed than that equivalent to the quantity of cooling medium which is discharged into the combustion chamber if the fluid were` fed in an ordinary manner. For this purpose the cooling medium is introduced tangentially at a high velocity by passing it through a constriction into a Jacket mounted within `the combustion chamber so as to surround a space immediately in advance of the nozzle. v The jacket may be of substantially triangular form in -cross section.
so that the cooling surface is disposed substantially in the form of a cone, the cooling medium being introduced tangentially atA high velocity into an apex of the triangular cross sectional form of the jacket corresponding to the wider "for the passage out products.
saigner to The` Asiatic Petroleum Com- 2 of the jacket of a predetermined amount of cooling medium toenter' a combustion chamber in the lrei'zion of the nozzle and to intermingle at that point with the llame The invention is. illustrated by way offexample in the accompanying drawing which, is 'a sectional elevation of the head of a combustion chamber in which a liquid fuel is burnt with an oxidant in liquid form.
Referring to the drawing, i indicates the head of the shell of the combustion chamber pro'per. 2 indicates refractory lining withinthe combustion chamber shell. The parts I and 2 are shown broken away. The combustion chamber may be constructed generally as described in British Patent No. 578;007.
To the head of the combustion chamber proper is fixed the nozzle and its associated inlet ducts. The nozzle comprises the central spray nozzle' into which the liquid fuel is fed tangentially at d to produce a vortex in the known manner. The fuel inlet to the nozzle is fromv the duct 5 and the outlet from the nozzle into the combustion chainber is through the opening B. v
Surrounding the central nozzle 3 is an oute member 1 which leaves an annular passage la so that a conical cooling surface I0 is exposed to the space in which the flame products are generated. The cooling medium is introduced at high velocity into the jacket through the tangential port Il which is located at the remote cornerof part of the cone so that the cooling medium in provide for the discharge of cooling medium into the combustion chamber to intermingle with the flame products.
By virtue of the high velocity of rotation of the cooling medium within the Jacket. and notwithstanding the limited quantity which is discharged into the combustion chamber, a high rate of cooling'is provided whereby the nozzle is enabled andere to withstand the extremely high temperatures involved.
I claim:
1. In apparatus of the class described for burn triangular form in cross section so that the cool-- chamber comprising a vortex chamber fed under pressure to provide an open spray. an outer nozzle forming an annular passage around .the central nozzle for admitting liqui oxidant to said chamber. said annular passage tapering inwardly toward its outlet Lto said combustion chamber to provide a convergent spray o1 oxidant directed ing surface is disposed substantially in the form of a lcone, means for introducing the cooling medium tangentially at high velocity into an apex of the triangular cross sectional form of the jacket corresponding to the wider part oi the cone so that the cooling medium in the jacket will rotate with a high velocity, orifices in the narrow part of the cone being provided for thepassage out of the jacket of a predetermined amount of cooling medium to enter the combustion chamber in the region of the nozzle and to intermingle at that point with the'iiame products.
2. I n apparatus of the class described for burning a liquid fuel with a liquid oxidant in'a combustion chamber, the combination of a central nozzle for admitting the liquid fuel to said chamber comprising a vortex chamber fed under pressure to provide an open spray, an outer nozzle forming an annular passage around said central nozzle for admitting liquid oxidant to said chamber, a jacket mounted within said chamber/so as to surround a space in iront of the nozzles and being of substantially triangular form in cross section so that the cooling surface is disposed substantially in the form of a cone. means for introducing the cooling medium tangentially at high velocity into an apex of the triangular cross sectional form of the jacket corresponding to the wider part of the cone so that the cooling medium in the jacket will rotate with a high velocity; orifices being provided in the narrow part of the cone for the passage out of the jacket f a predetermined amount of cooling medium to enter the combustion chamber in the region of the nozzles and to intermingle at thatpoint with the dame products.
3. In apparatus of the class described for buming a liquid fuel with a liquid oxidant in a combustion chamber, the combination of a central nozzle for. admitting the liquid fuel to said on the spray of iuel from said central nozzle, a jacket mounted within said chamber so as to surround a space in front of the nozzles and being of substantially triangular form in cross section soy thatI the cooling surface is disposed substantially in the form of a cone, means for introducing the cooling medium tangentially at high velocity into an apex of the triangular cross sectional form of the jacket corresponding to the wider-part oi v the cone so that the cooling medium in the jacket will rotate with a high velocity, orifices being provided in the narrow part of the cone for the passageout oi the Jacket of a predetermined amount of cooling medium to enter the combustion chamber in the region of the nozzles and to intermingle at that point with the flame products.
aaranzucns c'rrED UNITED STATES PATENTS Number Name Date 940,313 Koch ----v.... Nov. 28, 1909 1,100,145 Davis Nov. 13, 1915 1,160,922 Malas Nov. 16, 1915 1,278,314 Dix Sept. 10, 1918 1.391,27? Rushton Sept. 20, 1921 1.433,25@ Binks Oct. 24. 1922` 1,474,603 Morse Nov. 20, 1923 1,483,917 Tucker Feb. 19,1924 i 1,673,203 Reif et al. June 12, 1928 1,750,602 Lalor Mar. 11, 1930 1,814,192 Y Slattengren July 14, 1931 1,828,734 Perrin 1 Oct. 27, 1931 1,938,708 McCutcheon Dec. 12, 1933 2.281%',963 Achterman May 19, 1942 2,325,495 Ferguson July 27, 1943 'QAGN PATENTS Number Country Datel 102,621 Great rltaln July 15, 1905 $17,543
Italy May 15,1931
US493800A 1941-11-07 1943-07-07 Liquid-cooled nozzle arrangement for combustion chambers of jet propulsion apparatus Expired - Lifetime US2453378A (en)

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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2810433A (en) * 1952-01-17 1957-10-22 Texas Co Burner for oil-fired gas generator
US3169368A (en) * 1961-02-07 1965-02-16 Bolkow Entwicklungen Kg Combustion chamber for liquid fuels
US3387462A (en) * 1965-07-29 1968-06-11 Snecma Dual fuel injection device for propulsion motors, more especially for methane-carrying ships
US3546883A (en) * 1967-06-08 1970-12-15 Bolkow Gmbh Liquid fuel rocket engine construction
US3662547A (en) * 1970-03-16 1972-05-16 Nasa Coaxial injector for reaction motors
US3712059A (en) * 1970-12-03 1973-01-23 Textron Inc Reverse flow internally-cooled rocket engine
US6185927B1 (en) * 1997-12-22 2001-02-13 Trw Inc. Liquid tripropellant rocket engine coaxial injector
US6662547B2 (en) * 2000-11-17 2003-12-16 Mitsubishi Heavy Industries, Ltd. Combustor
RU2558489C2 (en) * 2012-07-30 2015-08-10 Федеральное государственное унитарное предприятие "Научно-исследовательский институт машиностроения" (ФГУП "НИИМаш") Combustion chamber of low-thrust liquid-propellant engine
FR3059047A1 (en) * 2016-11-21 2018-05-25 Safran Helicopter Engines COMBUSTION CHAMBER INJECTOR FOR TURBOMACHINE AND METHOD FOR MANUFACTURING THE SAME
US20220333554A1 (en) * 2018-11-15 2022-10-20 Stratolaunch, Llc Swirl preburner system and method

Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190514641A (en) * 1905-07-15 1906-07-14 Arthur Greenwood Improved Method of and Means or Apparatus for Producing Gas Mixtures for Turbines or other Engines Driven by Combustion Gases or a Mixture of Combustion Gases and other Gases.
US940813A (en) * 1908-01-04 1909-11-23 August Koch Liquid-fuel burner.
US1160929A (en) * 1914-06-26 1915-11-16 David Townsend Equalizing oil-burner.
US1160145A (en) * 1915-02-24 1915-11-16 Grant Train Davis Internal-combustion turbine.
US1278314A (en) * 1917-10-22 1918-09-10 Arthur Dix Fluid-pressure generator for turbines.
US1391277A (en) * 1920-09-30 1921-09-20 Edwin E Rushton Hydrocarbon and gas burner
US1433255A (en) * 1920-04-01 1922-10-24 Harry D Binks Two-fluid spray nozzle
US1474603A (en) * 1919-12-31 1923-11-20 Albert W Morse Liquid and gas mixer
US1483917A (en) * 1922-04-17 1924-02-19 Ernest E Tucker Oxyhydrogen steam generator
US1673203A (en) * 1927-09-09 1928-06-12 Reif Allen Frank Hydrocarbon heating apparatus
US1750602A (en) * 1925-02-18 1930-03-11 Fluid Heat Company Device for vaporizing liquids
US1814192A (en) * 1927-08-18 1931-07-14 Henry A Slattengren Power generator
US1828784A (en) * 1923-11-28 1931-10-27 France Etat Pressure fluid generator
US1938708A (en) * 1929-05-04 1933-12-12 American Rolling Mill Co Burner
US2283863A (en) * 1937-09-29 1942-05-19 Ernest Frank Achterman Rocket engine
US2325495A (en) * 1940-01-12 1943-07-27 Nat Airoil Burner Company Inc Oil burner

Patent Citations (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190514641A (en) * 1905-07-15 1906-07-14 Arthur Greenwood Improved Method of and Means or Apparatus for Producing Gas Mixtures for Turbines or other Engines Driven by Combustion Gases or a Mixture of Combustion Gases and other Gases.
US940813A (en) * 1908-01-04 1909-11-23 August Koch Liquid-fuel burner.
US1160929A (en) * 1914-06-26 1915-11-16 David Townsend Equalizing oil-burner.
US1160145A (en) * 1915-02-24 1915-11-16 Grant Train Davis Internal-combustion turbine.
US1278314A (en) * 1917-10-22 1918-09-10 Arthur Dix Fluid-pressure generator for turbines.
US1474603A (en) * 1919-12-31 1923-11-20 Albert W Morse Liquid and gas mixer
US1433255A (en) * 1920-04-01 1922-10-24 Harry D Binks Two-fluid spray nozzle
US1391277A (en) * 1920-09-30 1921-09-20 Edwin E Rushton Hydrocarbon and gas burner
US1483917A (en) * 1922-04-17 1924-02-19 Ernest E Tucker Oxyhydrogen steam generator
US1828784A (en) * 1923-11-28 1931-10-27 France Etat Pressure fluid generator
US1750602A (en) * 1925-02-18 1930-03-11 Fluid Heat Company Device for vaporizing liquids
US1814192A (en) * 1927-08-18 1931-07-14 Henry A Slattengren Power generator
US1673203A (en) * 1927-09-09 1928-06-12 Reif Allen Frank Hydrocarbon heating apparatus
US1938708A (en) * 1929-05-04 1933-12-12 American Rolling Mill Co Burner
US2283863A (en) * 1937-09-29 1942-05-19 Ernest Frank Achterman Rocket engine
US2325495A (en) * 1940-01-12 1943-07-27 Nat Airoil Burner Company Inc Oil burner

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2810433A (en) * 1952-01-17 1957-10-22 Texas Co Burner for oil-fired gas generator
US3169368A (en) * 1961-02-07 1965-02-16 Bolkow Entwicklungen Kg Combustion chamber for liquid fuels
US3387462A (en) * 1965-07-29 1968-06-11 Snecma Dual fuel injection device for propulsion motors, more especially for methane-carrying ships
US3546883A (en) * 1967-06-08 1970-12-15 Bolkow Gmbh Liquid fuel rocket engine construction
US3662547A (en) * 1970-03-16 1972-05-16 Nasa Coaxial injector for reaction motors
US3712059A (en) * 1970-12-03 1973-01-23 Textron Inc Reverse flow internally-cooled rocket engine
US6185927B1 (en) * 1997-12-22 2001-02-13 Trw Inc. Liquid tripropellant rocket engine coaxial injector
US6662547B2 (en) * 2000-11-17 2003-12-16 Mitsubishi Heavy Industries, Ltd. Combustor
RU2558489C2 (en) * 2012-07-30 2015-08-10 Федеральное государственное унитарное предприятие "Научно-исследовательский институт машиностроения" (ФГУП "НИИМаш") Combustion chamber of low-thrust liquid-propellant engine
FR3059047A1 (en) * 2016-11-21 2018-05-25 Safran Helicopter Engines COMBUSTION CHAMBER INJECTOR FOR TURBOMACHINE AND METHOD FOR MANUFACTURING THE SAME
US20220333554A1 (en) * 2018-11-15 2022-10-20 Stratolaunch, Llc Swirl preburner system and method
US11815049B2 (en) * 2018-11-15 2023-11-14 Stratolaunch, Llc Swirl preburner system and method

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