EP0041878B1 - Ensemble d'injection de carburant pour chambre de turboréacteur - Google Patents

Ensemble d'injection de carburant pour chambre de turboréacteur Download PDF

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Publication number
EP0041878B1
EP0041878B1 EP19810400797 EP81400797A EP0041878B1 EP 0041878 B1 EP0041878 B1 EP 0041878B1 EP 19810400797 EP19810400797 EP 19810400797 EP 81400797 A EP81400797 A EP 81400797A EP 0041878 B1 EP0041878 B1 EP 0041878B1
Authority
EP
European Patent Office
Prior art keywords
injection
orifices
assembly according
fuel
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.)
Expired
Application number
EP19810400797
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0041878A2 (fr
EP0041878A3 (en
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
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 filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0041878A2 publication Critical patent/EP0041878A2/fr
Publication of EP0041878A3 publication Critical patent/EP0041878A3/fr
Application granted granted Critical
Publication of EP0041878B1 publication Critical patent/EP0041878B1/fr
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
    • 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 outlet to form an air fuel mixture in which the latter is finely divided.
  • document FR-A-2 086 476 describes a fuel injection assembly for a combustion chamber of a turbojet engine, this assembly comprising a single swirl vane, for the rotation of a flow of air, consisting of a centripetal blading opening into a cylindrical volume arranged downstream of an injection device so as to fractionate the fuel droplets by the swirling air flow.
  • the document FR-A 1 462 091 provides for a fuel inlet by a flat perforated plate and the air inlet is spaced diametrically from this inlet by a wall and moreover is offset downstream.
  • Document FR-A 2 300 964 also relates to a fuel burner in which a swirl vane is located upstream relative to the fuel inlet.
  • the invention aims to obtain an improvement in the atomization of the fuel and in the homogeneity of the air / fuel mixture while using the principle of spraying by shearing of the fuel by an air flow and in using a simplified device which makes it possible to obtain these results in all the operating phases of the turbojet engine.
  • the fuel injection assembly of the type described, according to the invention is characterized in that said cylindrical volume is extended by a tubular duct connected downstream to a conical bowl and in that the injection device is formed a cylindrical hollow body, the bottom of which has a fuel inlet and the cap of the projecting injection orifices for the passage of fuel so that the transverse plane of outlet of the orifices is very close to the upstream end plane of the 'blading.
  • Figure 1 shows a perspective view and partially broken away of an injection assembly according to the invention.
  • 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 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 approximately 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 the injection orifices are provided 5.
  • the cap 8 which closes the upstream end of the cylindrical volume 3, is not likely to present carbon deposits 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 protrude relative to the surface of the cap 8. According to embodiments, the orifices open out at the top of blocks welded to the cap FIG. 3A), or at the end of 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.
  • the embodiment described provides a set of performances in terms of ignition, stability, thermal resistance and pollution.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
EP19810400797 1980-06-06 1981-05-21 Ensemble d'injection de carburant pour chambre de turboréacteur Expired EP0041878B1 (fr)

Applications Claiming Priority (2)

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

Publications (3)

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

Family

ID=9242761

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19810400797 Expired EP0041878B1 (fr) 1980-06-06 1981-05-21 Ensemble d'injection de carburant pour chambre de turboréacteur

Country Status (3)

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

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2839777B2 (ja) * 1991-12-24 1998-12-16 株式会社東芝 ガスタービン燃焼器用燃料噴射ノズル
US9920932B2 (en) 2011-01-26 2018-03-20 United Technologies Corporation Mixer assembly for a gas turbine engine
US8973368B2 (en) * 2011-01-26 2015-03-10 United Technologies Corporation Mixer assembly for a gas turbine engine
CN104776430B (zh) * 2015-04-15 2017-05-03 陈民 一种高节能环保液体燃烧器

Family Cites Families (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
US3339613A (en) * 1965-01-04 1967-09-05 Carrier Corp Flame stabilization
US3667221A (en) * 1969-04-17 1972-06-06 Gen Electric Fuel delivery apparatus
US3648457A (en) * 1970-04-30 1972-03-14 Gen Electric Combustion apparatus
FR2330871A2 (fr) * 1972-11-13 1977-06-03 Snecma Injecteur de carburant
US4089629A (en) * 1975-02-12 1978-05-16 Pietro Fascione Process and apparatus for controlled recycling of combustion gases

Also Published As

Publication number Publication date
EP0041878A2 (fr) 1981-12-16
DE3165211D1 (en) 1984-09-06
FR2484020B1 (enExample) 1985-05-17
FR2484020A1 (fr) 1981-12-11
EP0041878A3 (en) 1982-09-22

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