EP0041878A2 - Brennstoffeinspritzvorrichtung für Gasturbine - Google Patents

Brennstoffeinspritzvorrichtung für Gasturbine Download PDF

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Publication number
EP0041878A2
EP0041878A2 EP81400797A EP81400797A EP0041878A2 EP 0041878 A2 EP0041878 A2 EP 0041878A2 EP 81400797 A EP81400797 A EP 81400797A EP 81400797 A EP81400797 A EP 81400797A EP 0041878 A2 EP0041878 A2 EP 0041878A2
Authority
EP
European Patent Office
Prior art keywords
injection
fuel
assembly according
orifices
injection assembly
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.)
Granted
Application number
EP81400797A
Other languages
English (en)
French (fr)
Other versions
EP0041878A3 (en
EP0041878B1 (de
Inventor
Bruno Deroide
Philippe Marc Denis Gastebois
Alain Jacques Gérard Jacquet
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0041878A2 publication Critical patent/EP0041878A2/de
Publication of EP0041878A3 publication Critical patent/EP0041878A3/fr
Application granted granted Critical
Publication of EP0041878B1 publication Critical patent/EP0041878B1/de
Expired legal-status Critical Current

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Classifications

    • 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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • 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
    • F23D11/12—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 characterised by the shape or arrangement of the outlets from the nozzle

Definitions

  • the invention relates to a fuel injection assembly for a turbojet combustion chamber, comprising a swirl vane for combustion air and a fuel injector.
  • the devices for injecting fuel into the combustion chambers of a jet engine are generally designed so that they produce a forceful shearing effect on the flow of fuel. This shearing effect is the result of the combined action of air flow, passing through two swirl blades, between which the fuel is introduced.
  • the injector is in the form of an annular nozzle, surrounded by a duct for the passage of a first air flow, the central part of which channels a second air flow.
  • the two air flows as well as the fuel pass through vortex blades and interpenetrate at their exit to form an air fuel mixture in which the latter is finely divided.
  • the injection assembly according to the invention always uses spraying by shearing of the fuel by an air flow, but uses a simplified device.
  • the fuel injection assembly for a turbojet combustion chamber in which the fuel droplets are fractionated by a swirling air flow is remarkable in that it comprises a unique swirl vane.
  • a unique swirl vane for the rotation of the air flow, constituted by a cylindrical centripetal vane whose trailing edges of the vanes define a volume / connected downstream to a cylindro-conical bowl by which the assembly is fixed to the chamber and upstream to the fuel droplet injection device.
  • the fuel droplet injection device consists of a hollow body, the bottom of which has a fuel inlet and the cap of the injection orifices projection for fuel passage.
  • the injection assembly is fixed to the bottom of a combustion chamber and is bathed in a flow of air from the compressors.
  • the assembly comprises a device for injecting fuel droplets 1, onto which is fixed a centripetal blading or "swirler" 2 defining at its center a cylindrical volume extended by a tubular conduit 3.
  • the tubular conduit is connected downstream to a conical bowl 4.
  • the air coming from the compressors passes through the vane 2 and takes a vortex movement as a result of the inclination of the blades.
  • the change in orientation of the air flow entering through the blading is facilitated by the shape of the cap 8 of the injection device 1, projecting into the cylindrical volume.
  • the fuel (arrows in broken lines) sprayed by the nozzles or injection orifices 5 in a direction substantially parallel to the axis of the device, comes to cut off the swirling air flow.
  • the droplets finely pulverized by the meeting of air and fuel flows, mix intimately with the combustion air and form a homogeneous mixture.
  • the injection device 1 consists of a hollow cylindrical body having, according to the embodiment, a frustoconical bottom 6 at the center of which is fixed the tube 7 for the fuel inlet.
  • the cap 8 of the cylindrical body has an approximate / conical shape and carries near its periphery injection orifices 5 distributed in at least one concentric circle. The orifices are arranged so as to be between the trailing edges 9 of the swirl vanes.
  • the cap 8 of the cylindrical body (Fig. 2) has a conical central portion 10 which is connected by a rounded large radius 11 to a flat annular peripheral portion 12 on which are provided the injection orifices 5.
  • the cap 8 which closes the upstream end of the cylindrical volume 3, is not likely to present carbon dep8ts because they are swept by the air of the centripetal vane, and cannot heat up because it is cooled by the penetrating fuel in the cylindrical body.
  • a conical skirt 16 is provided upstream.
  • the injection orifices 5 are distributed on a circle concentric with the axis of the assembly including the diameter is between 0.7 and 0.9 times the diameter of the circle determined by the trailing edges 9 of the swirl vanes 2.
  • the injection orifices 5 project from the surface of the cap 8. According to embodiments, the orifices open at the top of blocks welded to the cap (Fig. 3A), or at the end of the axis tubes parallel to the axis of the assembly (Fig. 3B).
  • the remoteness of the injection orifices 5 from the surface of the cap 8 has two advantages: avoiding the dripping of fuel on the cap, obtaining a flow of fuel perpendicular to the air flow at the level of the injection allowing the obtaining of '' a homogeneous mixture of fine droplets.
  • the number of injection orifices 5 may be different from the number of intervals between the blades, however it must at least be equal to the integer closest to one third of the diameter expressed in mm of the circle on which the orifices are located.
  • the cylindrical volume 3 is extended by a frustoconical bowl 4 which carries on its downstream edge a flange 13.
  • This flange cooperates with a fixing device provided on the chamber and comprising means for allowing the movements of the flange both in the axial direction as in the radial direction.
  • a cylindrical skirt 14 coaxial with the axis of the assembly is fixed near the edge carrying the flange 13. The skirt 14 facilitates the entoncession of the air coming from the compressors towards the injection assembly and forces it to penetrate by one or more rows of holes 15 in the bowl 4 where it mixes with the air fuel flow and allows better combustion at low speeds.
  • the operating mode of the assembly is conventional in the type of aerodynamic injection.
  • the air set in rotation creates a central depression in the axis of the injector which favors a return current in the upstream part of the combustion chamber, and the conditions for good combustion are thus met.
  • This embodiment adapted to machines of small dimensions with the technological simplification obtained has great reliability and an attractive cost.
  • the embodiment described provides a set of performances in terms of ignition, stability, thermal resistance and pollution.
EP19810400797 1980-06-06 1981-05-21 Brennstoffeinspritzvorrichtung für Gasturbine Expired EP0041878B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8012558A FR2484020A1 (fr) 1980-06-06 1980-06-06 Ensemble d'injection de carburant pour chambre de turboreacteur
FR8012558 1980-06-06

Publications (3)

Publication Number Publication Date
EP0041878A2 true EP0041878A2 (de) 1981-12-16
EP0041878A3 EP0041878A3 (en) 1982-09-22
EP0041878B1 EP0041878B1 (de) 1984-08-01

Family

ID=9242761

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19810400797 Expired EP0041878B1 (de) 1980-06-06 1981-05-21 Brennstoffeinspritzvorrichtung für Gasturbine

Country Status (3)

Country Link
EP (1) EP0041878B1 (de)
DE (1) DE3165211D1 (de)
FR (1) FR2484020A1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0548908A2 (de) * 1991-12-24 1993-06-30 Kabushiki Kaisha Toshiba Kraftstoff-Einspritzdüsen-Anordnung zur Verwendung in einer Gasturbinen-Brennkammer
EP2481982A1 (de) * 2011-01-26 2012-08-01 United Technologies Corporation Mischeranordnung für einen Gasturbinenmotor
CN104776430A (zh) * 2015-04-15 2015-07-15 陈民 一种高节能新型环保液体燃烧器
US9920932B2 (en) 2011-01-26 2018-03-20 United Technologies Corporation Mixer assembly for a gas turbine engine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1698258A (en) * 1926-07-16 1929-01-08 Adolf F Haffenreffer Method of combustion
FR1094871A (fr) * 1959-01-22 1955-05-25 Thomson Houston Comp Francaise Perfectionnements aux appareils de combustion à combustible injecté
FR1462091A (fr) * 1965-01-04 1966-12-09 Carrier Corp Stabilisation des flammes
FR2043412A5 (de) * 1969-04-17 1971-02-12 Gen Electric
FR2086476A1 (de) * 1970-04-30 1971-12-31 Gen Electric
FR2300964A1 (fr) * 1975-02-12 1976-09-10 Fascione Pietro Procede d'ali
FR2330871A2 (fr) * 1972-11-13 1977-06-03 Snecma Injecteur de carburant

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1698258A (en) * 1926-07-16 1929-01-08 Adolf F Haffenreffer Method of combustion
FR1094871A (fr) * 1959-01-22 1955-05-25 Thomson Houston Comp Francaise Perfectionnements aux appareils de combustion à combustible injecté
FR1462091A (fr) * 1965-01-04 1966-12-09 Carrier Corp Stabilisation des flammes
FR2043412A5 (de) * 1969-04-17 1971-02-12 Gen Electric
FR2086476A1 (de) * 1970-04-30 1971-12-31 Gen Electric
FR2330871A2 (fr) * 1972-11-13 1977-06-03 Snecma Injecteur de carburant
FR2300964A1 (fr) * 1975-02-12 1976-09-10 Fascione Pietro Procede d'ali

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0548908A2 (de) * 1991-12-24 1993-06-30 Kabushiki Kaisha Toshiba Kraftstoff-Einspritzdüsen-Anordnung zur Verwendung in einer Gasturbinen-Brennkammer
EP0548908A3 (en) * 1991-12-24 1993-08-25 Kabushiki Kaisha Toshiba Fuel jetting nozzle assembly for use in gas turbine combustor
US5351489A (en) * 1991-12-24 1994-10-04 Kabushiki Kaisha Toshiba Fuel jetting nozzle assembly for use in gas turbine combustor
EP0751345A1 (de) * 1991-12-24 1997-01-02 Kabushiki Kaisha Toshiba Kraftstoff-Einspritzdüsen-Anordnung zur Verwendung in einer Gasturbinen-Brennkammer
EP2481982A1 (de) * 2011-01-26 2012-08-01 United Technologies Corporation Mischeranordnung für einen Gasturbinenmotor
US9920932B2 (en) 2011-01-26 2018-03-20 United Technologies Corporation Mixer assembly for a gas turbine engine
US10718524B2 (en) 2011-01-26 2020-07-21 Raytheon Technologies Corporation Mixer assembly for a gas turbine engine
CN104776430A (zh) * 2015-04-15 2015-07-15 陈民 一种高节能新型环保液体燃烧器

Also Published As

Publication number Publication date
EP0041878A3 (en) 1982-09-22
DE3165211D1 (en) 1984-09-06
EP0041878B1 (de) 1984-08-01
FR2484020B1 (de) 1985-05-17
FR2484020A1 (fr) 1981-12-11

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