US2529506A - Burner for liquid or gaseous fuels - Google Patents

Burner for liquid or gaseous fuels Download PDF

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Publication number
US2529506A
US2529506A US609532A US60953245A US2529506A US 2529506 A US2529506 A US 2529506A US 609532 A US609532 A US 609532A US 60953245 A US60953245 A US 60953245A US 2529506 A US2529506 A US 2529506A
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US
United States
Prior art keywords
fuel
air
jet
nozzle
flame
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
US609532A
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English (en)
Inventor
Lloyd Peter
Richards Alec David
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.)
Power Jets Research and Development Ltd
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Power Jets Research and Development Ltd
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Filing date
Publication date
Priority claimed from GB7011/44A external-priority patent/GB599257A/en
Application filed by Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
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Publication of US2529506A publication Critical patent/US2529506A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means

Definitions

  • the invention relates to combustion apparatus for liquid or gaseous fuels of the kind in which a nozzle or atomiser injects a jet or spray of fuel upstream into a current of air.
  • the invention has a special reference to combustion apparatus for gas turbines or/and jet propulsion motors which require stabilised burning in a fast moving air stream and with high air/fuel ratios.
  • the description "fast moving as applied to a combustion-supporting air current is used herein to indicate that the mean speed of the air current in its general direction of flow past a combustion zone, calculated from the ratio air volume passing in unit time/cross sectional area of the flow path, is high in relation to the speed of flame propagation in the fuel-air mixture concerned.
  • the speed of flame propagation is considered as being of the order of one foot per second at atmospheric temperature; the invention, on the other hand, is especially applicable to combustion apparatus for gas turbine or/and jet propulsion power units in which the speed of the air current in its general direction of flow past a combustion zone, calculated on the basis indicated, might be from 30 to 300 feet per second or even more, depending on the design.
  • Combustion apparatus for this purpose is also required to maintain stable burning at high rates of fuel injection with a minimum of pressure loss.
  • the flame from a nozzle or atomiser injecting fuel upstream is intrinsically more stable than that from one injecting fuel acres or .down stream, on account of its self-piloting action, the burning gases or/and fuel particles being continually carried back by the air stream into or/and past the jet or spray and thereby tending to kindle the fuel issuing from the nozzle or atomiser.
  • the self-piloting action requires a good supply of oxygen to the base of the flame, because the latter being carried back by the air blast, tends to envelop the jet or spray of fuel and to exclude air therefrom, thereby inhibi lng burning although the issuing fuel is heated to ignition temperature.
  • the flame therefore tends to be self-choking unless its base is adequately fed with oxygen.
  • An object of this invention is to provide means for increasing the intrinsic stability of the flame from a fuel jet or spray directed upstream into a fast moving air stream, and more especially for ensuring adequate oxygen supply to the base of the flame.
  • Another object is to ensure improved mixing of air and fuel in the parts of the flame more remote from the centre of the spray, so as to avoid a concentric Stratification of rich and weak mix.
  • Yet another object of the invention is to provide means for ensuring stable burning at high rates of fuel injection while at the same time minimising pressure loss.
  • means are provided, in association with a nozzle or atomiser delivering fuel upstream (against the general direction of air flow), for delivering a part at least of the primary air supply in a stream directed downstream into a radially inner region of the jet or spray issuing from the nozzle or atomiser.
  • a preferred means for this purpose comprises a hollow baflle of generally conical shape coaxially aligned on the fuel nozzle or atomiser with its apex pointing down stream towards the nozzle or atomiser, said baflle being provided with an opening or openings at or near the apex through which opening(s) a stream or air constituting part of a fast moving air stream is directed into the centre of the jet or spray of fuel issuing from the nozzle or atomiser.
  • the cone shaped baflie may also be provided with other openings or equivalent means for supplying an additional part of the main air stream to radially inner parts of the fuel being burnt at or near the flow reversal region, 1. e. at points more remote from the nozzle or atomiser and for supplying a still further part of the air supply to a radially outer part of the fuel being burnt which is carried back around the fuel nozzle or atomiser.
  • the latter may be of the kind adapted to produce a divergent or conical spray of fuel and the profile of the cone shaped baflie may be such as to conform approximately to the cone angle of the spray.
  • the cone shaped baflle or/and an extension of its upstream edge disposed substantially transversely of the general air stream is/are provided with a number of radial slots admitting air to the upstream end and radially outer portions of the fuel being burnt, whereby the air feeding these parts is supplied alternate rich and weak mixture layers which will operate to break up the concentric mixture stratification that would otherwise be formed.
  • Fig. 1 shows in central longitudinal cross section part of a flame tube of a combustion apparatus containing a fuel injector and conical baille means
  • a hollow transverse supporting member II is secured to the walls III of a flame tube and carries a fuel injection nozzle I2 positioned centrally of the flame tube and directing a jetor spray of fuel upstream, the direction of the air flow being indicated by full line arrows and the direction of ,fuel spray being indicated by dotted lines.
  • Fuel is fed to the nozzle I2 by means of an external pipe I3, banjo union I4 and a passage I5 formed in the interior of the support II.
  • a conical baffle I6 is aligned coaxially'with the fuel nozzle I2 with its apex pointing towards the nozzle and in fairly close proximity thereto.
  • the .base of this conical baflle is open to the air stream and its apex is provided with a cruciform opening I'I through which a part of the main air supply is directed into a radially inner part of the fuel spray issuing from the nozzle I2.
  • the bafiie I6 is also provided with a ring of openings I8, more remote from the nozzle I2'than the opening I1,
  • the bafile member comprises a small extra conical elethem, fed with air through openings 23 in memof the conical baille I6 is provided with a flat rim I9 forming an extension thereof which is provided with a number of radial slots 20 through which further air passes over a path radially within the main airstream in the form inner part of the flame zone and over-weakmixture in the outer part thereof, which would otherwise tend to form.
  • the rim I9 of the conical baflle is attached to ber I 6.
  • the outer cone 22 is provided with a cruciform opening I'I, through which air is fed into the centre of the spray from nozzle I2, as before, and ,air escaping from the rear of the space between the cones I6 and 22 feeds the reversal region of the flame zone.
  • the rim I9 of Figs. 1 and 2 is replaced by a frusto-spherical shield 24, and the radial slots 20 are situated in the basal portion of the cone member I6.
  • nozzles or atomisers are rigidly connected to the baffle means and supported from the walls of the flame tube I 0 by common support means, consisting of the radial supports 2
  • the tubular member 30 is secured to the radial supports H and to the bases of the cone I6 and shield 24 by a clamping member 36 and the ends of the tubular member 30 pass through the walls of the flame tube I0, being secured thereto by collars 3I and nuts 32, and terminate in threaded portions 33, for attachment to the fuel feed lines (not shown),
  • frusto-spherical shield 24 of Figs. 3 and 4 is replaced by a cylindrical shield 24a, connected to the cone member It by means of a conical element 25, of wider angle than the cone I 6 and-forming an extension of the base thereof.
  • Elements 24a and 25 are secured to a shallow conical member 26 by screws 21 and spacing washers 28, leaving an annular opening between the members 25-, 26, through which air is fed. into the interior of the cone I6.
  • All the foregoing embodiments are characterised byupstream injectiom (in the first stage) against the apex of a conical bafile provided with openings for directing primary air into the produce turbulence creating a re-circulation from a radially outer to a radially inner part of the Jet or spray, and also by the provision of radial slots for feeding air into the reversal region and radially outer parts of the flame zone in a number of narrow radial streams, for the purposes already described.
  • the second and third embodiments are also characterised by multi-stage injection with baflle means for stabilising the flame of the first stage only, stabilisation of the succeeding flame or flames being brought about by the flame or flames in front.
  • the second embodiment incorporates the preferred constructional feature of rigid connection and common support of the injector and baflie means, ensuring maintenance of their correct alignment.
  • Combustion apparatus comprising a conduit for the flow of a combustion-supporting air stream therethrough, means for injecting a fuel jet into said conduit directed upstream relative to the general direction of said air stream, and means for leading a first portion of the said air stream through said jet to an inner region thereof located towards the base of the jet, the said jet being located so that the main body of air flows downstream around the jet to cause flow reversal thereof.
  • a combustion apparatus comprising means for leading a second portion of the air stream through said jet to an inner region thereof located further from the base and nearer the flow reversal region of the jet than the first said portion.
  • a combustion apparatus further comprising means for delivering by a path radially within the main air stream a third portion of the air stream to an outer part of the jet located towards the flow reversal region of the Jet.
  • Combustion apparatus comprising a conduit for the flow of a combustion-supporting air stream therethrough, a burner nozzle for injecting a fuel jet within said conduit directed upstream relative to the general direction of said air, stream, and a hollow baflle of generally conical shape having its axis in alignment with said nozzle and its apex pointing downstream towards said nozzle, the wall of said bafile having perforations for delivering a first portion of the air stream through said jet and into an inner region thereof.
  • a combustion apparatus according to claim 4 wherein the conical baffie is provided with a first opening located in the vicinity of its apex.
  • a combustion apparatus according to claim 5 wherein the conical baflle is provided with a second opening further from its apex than said first opening for delivering a second portion of the air stream through said jet and into an inner region thereof located further from the base of the jet than said first portion.
  • a combustion apparatus wherein a baflle is provided with a rim extending transversely to the axis, said rim having a number of radial slots through which a third portion of the airstream is delivered to an outer region of the jet.
  • a combustion apparatus wherein a hollow baflie is provided, in the region of its apex, with an outer cone arranged coaxially therewith and spaced therefrom, said outer cone having perforations for leading air from the space between said outer cone and said hollow baflle to an inner region of the jet.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US609532A 1944-04-15 1945-08-08 Burner for liquid or gaseous fuels Expired - Lifetime US2529506A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB2529506X 1944-04-15
GB7011/44A GB599257A (en) 1945-03-20 1945-04-14 Improvements relating to burners for liquid or gaseous fuels

Publications (1)

Publication Number Publication Date
US2529506A true US2529506A (en) 1950-11-14

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US (1) US2529506A (enrdf_load_stackoverflow)
BE (1) BE463581A (enrdf_load_stackoverflow)
CH (1) CH264718A (enrdf_load_stackoverflow)
NL (1) NL68431C (enrdf_load_stackoverflow)

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2622396A (en) * 1948-11-26 1952-12-23 Lucas Ltd Joseph Fuel vaporizing apparatus for an afterburner
US2625795A (en) * 1946-02-26 1953-01-20 Thermal Res And Engineering Co Combustion stabilization means for high-velocity air streams having a pilot burner and a streamline igniter grill
US2625788A (en) * 1948-12-15 1953-01-20 Mcdonnell Aircraft Corp Flame holder and fuel nozzle supporting mechanism for ram jet engines
US2639581A (en) * 1944-09-14 1953-05-26 Power Jets Res & Dev Ltd Apparatus for burning fuel in a high velocity gas stream
US2651178A (en) * 1951-01-18 1953-09-08 A V Roe Canada Ltd Combination injector and stabilizer for gas turbine afterburners
US2657532A (en) * 1948-09-02 1953-11-03 Power Jets Res & Dev Ltd Liquid fuel atomizer located upstream of a flame stabilizing baffle
US2659195A (en) * 1948-11-01 1953-11-17 Mcdonnell Aircraft Corp Flame holder and fuel distributing mechanism for ram-jet engines
US2667033A (en) * 1947-01-09 1954-01-26 Power Jets Res & Dev Ltd Combustion apparatus for operation in fast-moving air streams
US2682148A (en) * 1947-12-02 1954-06-29 Ralph C Brierly Apparatus for progressive injection of combustibles in peripheral type burners
US2693083A (en) * 1951-03-26 1954-11-02 Roy W Abbott Combination flame-holder and fuel nozzle
US2697910A (en) * 1950-07-29 1954-12-28 Thermal Res And Engineering Co Fluid fuel burner with self-contained fuel vaporizing unit
US2714287A (en) * 1950-01-03 1955-08-02 Westinghouse Electric Corp Flameholder device for turbojet afterburner
US2720754A (en) * 1950-09-29 1955-10-18 Mcdonnell Aircraft Corp Flameholder for ram jet engine
US2726511A (en) * 1950-05-18 1955-12-13 Solar Aircraft Co Afterburners
US2729059A (en) * 1949-05-28 1956-01-03 Onera (Off Nat Aerospatiale) Continuous flow internal combustion engines, in particular aircraft engines
US2729937A (en) * 1951-03-20 1956-01-10 United Aircraft Corp Retractable flameholders for afterburners
US2730863A (en) * 1948-04-16 1956-01-17 Lockheed Aircraft Corp Gaseous fuel turbine power plant having parallel connected compressors
US2740482A (en) * 1951-11-20 1956-04-03 Hiller Helicopters Rotor blade mounted jet engine
US2775867A (en) * 1952-08-22 1957-01-01 Continental Aviat & Engineerin Ram jet engines
DE957003C (de) * 1951-11-20 1957-01-24 Hiller Helicopters Kontinuierlich arbeitendes Staustrahltriebwerk fuer Rotorfluegel von Hubschraubern
US2781637A (en) * 1950-12-15 1957-02-19 Gen Motors Corp Combustion chamber with fuel vaporizer
US2840990A (en) * 1952-07-17 1958-07-01 John P Longwell Multistage fuel injection for ram-jet combustor
US2859588A (en) * 1953-12-16 1958-11-11 Texas Co Flame holder structure for ram jet combustor
DE1045728B (de) * 1953-07-15 1958-12-04 Snecma Verbrennungseinrichtung
DE1049157B (de) * 1956-08-10 1959-01-22 Ernst Heinkel Fahrzeugbau G M Brenn- oder Mischkammer mit Rueckstroemung, insbesondere fuer Strahltriebwerke und Gasturbinen
DE1053873B (de) * 1955-05-13 1959-03-26 Snecma Flammenstabilisierungseinrichtung
US2927427A (en) * 1955-05-10 1960-03-08 Onera (Off Nat Aerospatiale) Continuous flow thermal machines and in particular in ram-jets and turbojets
US2934894A (en) * 1957-07-23 1960-05-03 Orenda Engines Ltd Fuel supply and flame stabilizing apparatus for afterburners for jet engines
DE1097213B (de) * 1958-05-22 1961-01-12 Rolls Royce Verbrennungsanlage fuer Gasturbinentriebwerke
US2999359A (en) * 1956-04-25 1961-09-12 Rolls Royce Combustion equipment of gas-turbine engines
US3029603A (en) * 1951-10-26 1962-04-17 Howard E Brown Air bled fuel injector system
US3102392A (en) * 1959-04-21 1963-09-03 Snecma Combustion equipment for jet propulsion units
US3205658A (en) * 1963-09-16 1965-09-14 Aldo B Vanoni Fuel burner with flame holder
DE1246325B (de) * 1953-06-27 1967-08-03 Snecma Verbrennungseinrichtung
DE1259143B (de) * 1953-06-27 1968-01-18 Snecma Flammenstabilisierungseinrichtung
DE1276414B (de) * 1956-07-13 1968-08-29 Snecma Verbrennungseinrichtung
US4765136A (en) * 1985-11-25 1988-08-23 United Technologies Corporation Gas turbine engine augmentor

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117109029B (zh) * 2023-08-25 2024-02-02 西南科技大学 一种钝体火焰稳定器以及航空发动机燃烧组件

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1434021A (en) * 1922-10-31 Hydbocabbon bubneb
US1542294A (en) * 1921-04-08 1925-06-16 James B Blackburn Burner
US1988456A (en) * 1930-03-24 1935-01-22 Milo Ab Gas turbine system
US2085800A (en) * 1935-11-25 1937-07-06 Robert H Goddard Combustion apparatus
US2111432A (en) * 1935-01-16 1938-03-15 Gen Electric Fuel burning apparatus and air inlet device therefor
US2164225A (en) * 1936-11-23 1939-06-27 Int Harvester Co Liquid fuel burner
US2385833A (en) * 1943-01-27 1945-10-02 Kevork K Nahigyan Fuel vaporizer for jet propulsion units
US2404335A (en) * 1939-12-09 1946-07-16 Power Jets Res & Dev Ltd Liquid fuel burner, vaporizer, and combustion engine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1434021A (en) * 1922-10-31 Hydbocabbon bubneb
US1542294A (en) * 1921-04-08 1925-06-16 James B Blackburn Burner
US1988456A (en) * 1930-03-24 1935-01-22 Milo Ab Gas turbine system
US2111432A (en) * 1935-01-16 1938-03-15 Gen Electric Fuel burning apparatus and air inlet device therefor
US2085800A (en) * 1935-11-25 1937-07-06 Robert H Goddard Combustion apparatus
US2164225A (en) * 1936-11-23 1939-06-27 Int Harvester Co Liquid fuel burner
US2404335A (en) * 1939-12-09 1946-07-16 Power Jets Res & Dev Ltd Liquid fuel burner, vaporizer, and combustion engine
US2385833A (en) * 1943-01-27 1945-10-02 Kevork K Nahigyan Fuel vaporizer for jet propulsion units

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2639581A (en) * 1944-09-14 1953-05-26 Power Jets Res & Dev Ltd Apparatus for burning fuel in a high velocity gas stream
US2625795A (en) * 1946-02-26 1953-01-20 Thermal Res And Engineering Co Combustion stabilization means for high-velocity air streams having a pilot burner and a streamline igniter grill
US2667033A (en) * 1947-01-09 1954-01-26 Power Jets Res & Dev Ltd Combustion apparatus for operation in fast-moving air streams
US2682148A (en) * 1947-12-02 1954-06-29 Ralph C Brierly Apparatus for progressive injection of combustibles in peripheral type burners
US2730863A (en) * 1948-04-16 1956-01-17 Lockheed Aircraft Corp Gaseous fuel turbine power plant having parallel connected compressors
US2657532A (en) * 1948-09-02 1953-11-03 Power Jets Res & Dev Ltd Liquid fuel atomizer located upstream of a flame stabilizing baffle
US2659195A (en) * 1948-11-01 1953-11-17 Mcdonnell Aircraft Corp Flame holder and fuel distributing mechanism for ram-jet engines
US2622396A (en) * 1948-11-26 1952-12-23 Lucas Ltd Joseph Fuel vaporizing apparatus for an afterburner
US2625788A (en) * 1948-12-15 1953-01-20 Mcdonnell Aircraft Corp Flame holder and fuel nozzle supporting mechanism for ram jet engines
US2729059A (en) * 1949-05-28 1956-01-03 Onera (Off Nat Aerospatiale) Continuous flow internal combustion engines, in particular aircraft engines
US2714287A (en) * 1950-01-03 1955-08-02 Westinghouse Electric Corp Flameholder device for turbojet afterburner
US2726511A (en) * 1950-05-18 1955-12-13 Solar Aircraft Co Afterburners
US2697910A (en) * 1950-07-29 1954-12-28 Thermal Res And Engineering Co Fluid fuel burner with self-contained fuel vaporizing unit
US2720754A (en) * 1950-09-29 1955-10-18 Mcdonnell Aircraft Corp Flameholder for ram jet engine
US2781637A (en) * 1950-12-15 1957-02-19 Gen Motors Corp Combustion chamber with fuel vaporizer
US2651178A (en) * 1951-01-18 1953-09-08 A V Roe Canada Ltd Combination injector and stabilizer for gas turbine afterburners
US2729937A (en) * 1951-03-20 1956-01-10 United Aircraft Corp Retractable flameholders for afterburners
US2693083A (en) * 1951-03-26 1954-11-02 Roy W Abbott Combination flame-holder and fuel nozzle
US3029603A (en) * 1951-10-26 1962-04-17 Howard E Brown Air bled fuel injector system
US2740482A (en) * 1951-11-20 1956-04-03 Hiller Helicopters Rotor blade mounted jet engine
DE957003C (de) * 1951-11-20 1957-01-24 Hiller Helicopters Kontinuierlich arbeitendes Staustrahltriebwerk fuer Rotorfluegel von Hubschraubern
US2840990A (en) * 1952-07-17 1958-07-01 John P Longwell Multistage fuel injection for ram-jet combustor
US2775867A (en) * 1952-08-22 1957-01-01 Continental Aviat & Engineerin Ram jet engines
DE1259143B (de) * 1953-06-27 1968-01-18 Snecma Flammenstabilisierungseinrichtung
DE1246325B (de) * 1953-06-27 1967-08-03 Snecma Verbrennungseinrichtung
DE1045728B (de) * 1953-07-15 1958-12-04 Snecma Verbrennungseinrichtung
US2859588A (en) * 1953-12-16 1958-11-11 Texas Co Flame holder structure for ram jet combustor
US2927427A (en) * 1955-05-10 1960-03-08 Onera (Off Nat Aerospatiale) Continuous flow thermal machines and in particular in ram-jets and turbojets
DE1053873B (de) * 1955-05-13 1959-03-26 Snecma Flammenstabilisierungseinrichtung
US2999359A (en) * 1956-04-25 1961-09-12 Rolls Royce Combustion equipment of gas-turbine engines
DE1276414B (de) * 1956-07-13 1968-08-29 Snecma Verbrennungseinrichtung
DE1049157B (de) * 1956-08-10 1959-01-22 Ernst Heinkel Fahrzeugbau G M Brenn- oder Mischkammer mit Rueckstroemung, insbesondere fuer Strahltriebwerke und Gasturbinen
US2934894A (en) * 1957-07-23 1960-05-03 Orenda Engines Ltd Fuel supply and flame stabilizing apparatus for afterburners for jet engines
DE1097213B (de) * 1958-05-22 1961-01-12 Rolls Royce Verbrennungsanlage fuer Gasturbinentriebwerke
US3102392A (en) * 1959-04-21 1963-09-03 Snecma Combustion equipment for jet propulsion units
US3205658A (en) * 1963-09-16 1965-09-14 Aldo B Vanoni Fuel burner with flame holder
US4765136A (en) * 1985-11-25 1988-08-23 United Technologies Corporation Gas turbine engine augmentor

Also Published As

Publication number Publication date
NL68431C (enrdf_load_stackoverflow)
BE463581A (enrdf_load_stackoverflow)
CH264718A (de) 1949-10-31

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