US2704435A - Fuel burning means for a gaseous-fluid propulsion jet - Google Patents

Fuel burning means for a gaseous-fluid propulsion jet Download PDF

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Publication number
US2704435A
US2704435A US224098A US22409851A US2704435A US 2704435 A US2704435 A US 2704435A US 224098 A US224098 A US 224098A US 22409851 A US22409851 A US 22409851A US 2704435 A US2704435 A US 2704435A
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United States
Prior art keywords
casing
fuel
jet
gaseous
jet pipe
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Expired - Lifetime
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US224098A
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English (en)
Inventor
Allen Sidney
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Armstrong Siddeley Motors Ltd
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Armstrong Siddeley Motors Ltd
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    • 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

  • This invention relates to a fuel-burning means, for a gaseous-fluid propulsion jet, of the kind having a flame stabilizing device arranged to provide a flame such as will ensure the combustion of fuelparticularly for after burning in, or re-heating, the oxygen-containing exhaust gas of a gas turbine engine for the propulsion of an aircraft, though the invention can also be applied to the burning of fuel in a ram-jet.
  • a fuel-burning means for a gaseous-fluid propulsion jet, includes a flame stabilizing device which is disposed relatively to a casing, within and spaced annularly from the wall of the jet pipe, so as to be, in end elevation, within the cross-sectional area of the casing, and means for supplying fuel to an appropriate part of the casing to ensure proper combustion of the fuel.
  • Figure 1 is a line diagram of the tail end of the turbine of a gas turbine engine, and of the upstream end of the exhaust or jet pipe thereof incorporating one form of fuel-burning means according to the invention;
  • Figure 2 is a line diagram of the upstream end of a p'pe for a propulstion jet incorporating another form of fuel-burning means;
  • Figure 3 is a sectional elevation of a preferred form of fuel-burning means in a jet pipe of a gas turbine engine, Figure 4 being a sectional view from the right of Figure 3.
  • the reference numeral 11 is applied to the flame stabilizing device, and 12 to a pipe by means of which a pilot supply of fuel can be delivered thereto. It will be observed that the stabilizing device includes a frusto-conical casing with its smaller end upstream.
  • the reference numeral 14 denotes the casing which, according to the invention, is associated with the flame stabilizing device, the upstream end of the casing 14 having an annular manifold 15 round it from which fuel is sprayed into the interior of the easing 14, the fuel being delivered to the manifold 15 by a supply pipe 16.
  • the manifold 15 need not, of course, be exactly at the upstream end of the casing 14, and it may be disposed at any radial position in the annular space between the casing and the stabilizing device.
  • the reference numeral 18 is applied to the wall of the exhaust or jet pipe.
  • Figure 1 indicates at 20 the tail end of the turbine carrying a row of blades 21, and abutting the tail end of the turbine is the usual inner exhaust cone 22 forming with the outer exhaust cone 23 the usual exhaust diffuser passage leading to the upstream end of the jet pipe 18.
  • the stabilizing device shown in Figures 3 and 4 has a centrally-disposed baffle 25 at its upstream end joined to the smaller end of the casing by fixed, swirl-introducing vanes 26-as disclosed in the specification aforesaid.
  • the pilot supply of fuel from the pipe 12 is delivered through nozzle openings 27, on opposite sides of the pipe, into and against the direction of the swirl of the exhaust gases in the stabilizing device.
  • the latter is shown as being supported from the casing 14 by angularly-spaced, streamlined struts 28, and the casing 14 is shown as being supported from the jet pipe wall by means of angularlydisposed, streamlined struts 29.
  • the casing 14 In a simple construction according to the invention, only a single casing 14 (and associated flame stabilizing device) would be used, the casing 14 being cylindrical and of a size (as regards cross-section area) determined by the percentage of exhaust re-heating it is desired to obtain. That is to say, the size of the casing 14 is chosen such that the amount of oxygen-containing gases passing through it will be sufficient to elfect complete burning of the re-heat fuel, the remainder of the exhaust gases passing externally of the casing 14. These exterior gases will not, of course, have their temperatures raised to any dangerous extent, and, in consequence, the jet pipe is protected in the region of the casing 14 where the reheating is being effected.
  • some of the re-heat fuel may be directed onto the interior walls of the casing 14 to promote the cooling thereof, and the lower temperature of the non re-heated exhaust gases outside the casing will also have a cooling effect on the smg.
  • flaming gases pass from the outlet end of the casing 14 ( Figures 2 and 3)
  • these gases will fan out and, in so doing, will mix with the exhaust gases which have passed externally of the casing. It is desirable that a substantially uniform temperature should be obtained across the whole area of the exhaust nozzle 30 ( Figure 3) at the outlet end of the jet pipe.
  • a second casing 14a of larger diameter than the first 14, is arranged downstream, and preferably to overlap the outlet end, of the first casing 14, and is provided, preferably at its upstream end, with its own supply of re-heat fuel, by way of the manifold 15a. If maximum re-heat is required (i.
  • a fuel-burning means for a gaseous fluid propulsion jet, including a jet pipe through which hot jet gases pass, an open-ended casing within and spaced annularly from said jet pipe, a flame stabilizing device disposed relatively to said casing so as to be, in end elevation, within the cross-sectional area of said casing and comprising a hollow diffuser member round and through which the hot jet gases pass and within which is to be burnt a pilot supply of fuel to produce a stable flame issuing at the downstream end, means for supplying fuel to an appropriate part of said casing to ensure proper combustion of the fuel, a second casing, of larger diameter than the first casing, within and spaced annularly from said jet pipe and disposed to be mainly downstream of said first casing, and means for supplying fuel to an appropriate part of said second casing to ensure proper combustion of this fuel.
  • a fuel-burning device for a gaseous fluid propulsion jet engine comprising a jet pipe adapted to have oxygen bearing exhaust gases from the engine flow therethrough, a casing within and spaced annularly from said jet pipe and disposed in the path of at least some of the exhaust gases passing through said jet pipe so that some of said gases will pass through the easing, a flame stabilizing diffuser member of substantially frusto-conical shape disposed relatively to said casing so as to be, in end elevation, within the crosssectional area of said casing and disposed in the path of at least some of the exhaust gases passing through the casing so that some of said gases will pass through said diffuser member, said ditfuser member having its smaller end disposed upstream, pilot fuel supply means for said diffuser member near the smaller end of the diffuser member, said pilot fuel being vaporized by said exhaust gases passing through said diffuser member, means for igniting said pilot supply, means for supplying fuel to an appropriate part of said casing to ensure proper combustion of the fuel, a second casmg of larger diameter
US224098A 1950-07-17 1951-05-02 Fuel burning means for a gaseous-fluid propulsion jet Expired - Lifetime US2704435A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB313855X 1950-07-17

Publications (1)

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US2704435A true US2704435A (en) 1955-03-22

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US224098A Expired - Lifetime US2704435A (en) 1950-07-17 1951-05-02 Fuel burning means for a gaseous-fluid propulsion jet

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US (1) US2704435A (fr)
BE (1) BE503026A (fr)
CH (1) CH313855A (fr)
DE (1) DE887286C (fr)
FR (1) FR1036194A (fr)
GB (1) GB691068A (fr)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2806516A (en) * 1952-03-28 1957-09-17 Thermo Mecanique Soc Combustion apparatus for use with boilers
US2913874A (en) * 1955-03-30 1959-11-24 Gen Electric Tailpipe thrust augmentor
US2974488A (en) * 1956-11-27 1961-03-14 Snecma Combustion devices for continuous-flow internal combustion machines
US2988878A (en) * 1958-07-14 1961-06-20 United Aircraft Corp Fuel nozzle for bypass engine
US2999359A (en) * 1956-04-25 1961-09-12 Rolls Royce Combustion equipment of gas-turbine engines
US3066926A (en) * 1959-04-23 1962-12-04 Air Prod & Chem Air heating method
US3067582A (en) * 1955-08-11 1962-12-11 Phillips Petroleum Co Method and apparatus for burning fuel at shear interface between coaxial streams of fuel and air
US3078666A (en) * 1958-08-29 1963-02-26 Tuval Miron Method and apparatus for the combustion of fuel
US3085401A (en) * 1959-01-22 1963-04-16 Rolls Royce Reheat combustion equipment of gas-turbine engines
US3087301A (en) * 1960-07-13 1963-04-30 United Aircraft Corp Leading edge fuel manifold
US3166904A (en) * 1960-05-18 1965-01-26 Melenric John Alden Combustion chamber for gas turbine engines
DE1193734B (de) * 1960-07-13 1965-05-26 United Aircraft Corp Brennstoffeinspritzvorrichtung fuer Gasturbinen-Strahltriebwerke
US3210928A (en) * 1960-08-19 1965-10-12 Joseph J Zelinski Fuel cooled combustor assembly
US3338051A (en) * 1965-05-28 1967-08-29 United Aircraft Corp High velocity ram induction burner
US4237694A (en) * 1978-03-28 1980-12-09 Rolls-Royce Limited Combustion equipment for gas turbine engines
US4598553A (en) * 1981-05-12 1986-07-08 Hitachi, Ltd. Combustor for gas turbine
US5628192A (en) * 1993-12-16 1997-05-13 Rolls-Royce, Plc Gas turbine engine combustion chamber
US20070089419A1 (en) * 2005-10-24 2007-04-26 Kawasaki Jukogyo Kabushiki Kaisha Combustor for gas turbine engine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1074920B (de) * 1955-07-07 1960-02-04 Ing habil Fritz A F Schmidt Murnau Dr (Obb) Verfahren und \ orrichtung zur Regelung von Gas turbmenbrennkammern mit unterteilter Verbrennung und mehreren Druckstufen
DE1102491B (de) * 1957-10-19 1961-03-16 Bristol Siddeley Engines Ltd Verbrennungseinrichtung fuer ein Gasturbinentriebwerk

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2417445A (en) * 1945-09-20 1947-03-18 Pinkel Benjamin Combustion chamber
US2517015A (en) * 1945-05-16 1950-08-01 Bendix Aviat Corp Combustion chamber with shielded fuel nozzle
US2518000A (en) * 1946-03-01 1950-08-08 Daniel And Florence Guggenheim Auxiliary combustion chambers for reaction jet propulsion apparatus
US2520388A (en) * 1946-11-21 1950-08-29 Power Jets Res & Dev Ltd Apparatus for supporting combustion in fast-moving air streams
US2545495A (en) * 1947-08-06 1951-03-20 Westinghouse Electric Corp Annular combustion chamber air flow arrangement about the fuel nozzle end
US2548087A (en) * 1950-01-21 1951-04-10 A V Roe Canada Ltd Vaporizer system for combustion chambers
US2560207A (en) * 1948-02-04 1951-07-10 Wright Aeronautical Corp Annular combustion chamber with circumferentially spaced double air-swirl burners
US2592110A (en) * 1949-05-21 1952-04-08 Curtiss Wright Corp Orifice type flame holder construction

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2517015A (en) * 1945-05-16 1950-08-01 Bendix Aviat Corp Combustion chamber with shielded fuel nozzle
US2417445A (en) * 1945-09-20 1947-03-18 Pinkel Benjamin Combustion chamber
US2518000A (en) * 1946-03-01 1950-08-08 Daniel And Florence Guggenheim Auxiliary combustion chambers for reaction jet propulsion apparatus
US2520388A (en) * 1946-11-21 1950-08-29 Power Jets Res & Dev Ltd Apparatus for supporting combustion in fast-moving air streams
US2545495A (en) * 1947-08-06 1951-03-20 Westinghouse Electric Corp Annular combustion chamber air flow arrangement about the fuel nozzle end
US2560207A (en) * 1948-02-04 1951-07-10 Wright Aeronautical Corp Annular combustion chamber with circumferentially spaced double air-swirl burners
US2592110A (en) * 1949-05-21 1952-04-08 Curtiss Wright Corp Orifice type flame holder construction
US2548087A (en) * 1950-01-21 1951-04-10 A V Roe Canada Ltd Vaporizer system for combustion chambers

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2806516A (en) * 1952-03-28 1957-09-17 Thermo Mecanique Soc Combustion apparatus for use with boilers
US2913874A (en) * 1955-03-30 1959-11-24 Gen Electric Tailpipe thrust augmentor
US3067582A (en) * 1955-08-11 1962-12-11 Phillips Petroleum Co Method and apparatus for burning fuel at shear interface between coaxial streams of fuel and air
US2999359A (en) * 1956-04-25 1961-09-12 Rolls Royce Combustion equipment of gas-turbine engines
US2974488A (en) * 1956-11-27 1961-03-14 Snecma Combustion devices for continuous-flow internal combustion machines
US2988878A (en) * 1958-07-14 1961-06-20 United Aircraft Corp Fuel nozzle for bypass engine
US3078666A (en) * 1958-08-29 1963-02-26 Tuval Miron Method and apparatus for the combustion of fuel
US3085401A (en) * 1959-01-22 1963-04-16 Rolls Royce Reheat combustion equipment of gas-turbine engines
US3066926A (en) * 1959-04-23 1962-12-04 Air Prod & Chem Air heating method
US3166904A (en) * 1960-05-18 1965-01-26 Melenric John Alden Combustion chamber for gas turbine engines
US3087301A (en) * 1960-07-13 1963-04-30 United Aircraft Corp Leading edge fuel manifold
DE1193734B (de) * 1960-07-13 1965-05-26 United Aircraft Corp Brennstoffeinspritzvorrichtung fuer Gasturbinen-Strahltriebwerke
US3210928A (en) * 1960-08-19 1965-10-12 Joseph J Zelinski Fuel cooled combustor assembly
US3338051A (en) * 1965-05-28 1967-08-29 United Aircraft Corp High velocity ram induction burner
US4237694A (en) * 1978-03-28 1980-12-09 Rolls-Royce Limited Combustion equipment for gas turbine engines
US4598553A (en) * 1981-05-12 1986-07-08 Hitachi, Ltd. Combustor for gas turbine
US5628192A (en) * 1993-12-16 1997-05-13 Rolls-Royce, Plc Gas turbine engine combustion chamber
US20070089419A1 (en) * 2005-10-24 2007-04-26 Kawasaki Jukogyo Kabushiki Kaisha Combustor for gas turbine engine

Also Published As

Publication number Publication date
CH313855A (fr) 1956-05-15
DE887286C (de) 1953-08-20
FR1036194A (fr) 1953-09-04
BE503026A (fr)
GB691068A (en) 1953-05-06

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