EP2014988B1 - Optimierung einer Antikoksschicht in einem Einspritzsystem - Google Patents

Optimierung einer Antikoksschicht in einem Einspritzsystem Download PDF

Info

Publication number
EP2014988B1
EP2014988B1 EP08159886A EP08159886A EP2014988B1 EP 2014988 B1 EP2014988 B1 EP 2014988B1 EP 08159886 A EP08159886 A EP 08159886A EP 08159886 A EP08159886 A EP 08159886A EP 2014988 B1 EP2014988 B1 EP 2014988B1
Authority
EP
European Patent Office
Prior art keywords
holes
main axis
downstream
injection system
injector
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.)
Active
Application number
EP08159886A
Other languages
English (en)
French (fr)
Other versions
EP2014988A1 (de
Inventor
Alain Cayre
Christophe Pieussergues
Jackie Prouteau
Denis Sandelis
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP2014988A1 publication Critical patent/EP2014988A1/de
Application granted granted Critical
Publication of EP2014988B1 publication Critical patent/EP2014988B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent

Definitions

  • the present invention relates to the field of fuel injection systems.
  • the invention more particularly relates to an annular expansion ring centered on a main axis and adapted to be mounted on a fuel injector coaxial with this ring, this ring having holes distributed around this main axis, opening on its upstream face, and allowing the passage of air to the area downstream of this ring.
  • the fuel is injected into a combustion chamber 100 (for example in a combustion chamber of a turbomachine) by an injector 10 which is located at the end of the pipe bringing this fuel .
  • This injector 10 is substantially cylindrical, and has an expansion ring 220 annular with respect to a main axis A and which surrounds a portion of the injector 10, this injector being coaxial with the expansion ring.
  • the expansion ring 220 comprises an axial cylindrical portion 222 whose radially inner surface is in contact with or near the outer surface of the injector 10.
  • this expansion ring 220 The role of this expansion ring 220 is to allow a clearance of the clearance between the injector 10 and the elements of the bottom of the combustion chamber, this game being caused by the thermal stresses to which these parts are subjected. During combustion, it can be created on the downstream end 12 of the injector 10 coke deposits due to improper combustion of the fuel. The coke deposits are undesirable because they degrade the fuel spraying by the injectors 10.
  • upstream and downstream are used in relation to the direction of normal circulation of the fuel at the outlet of the injector (unless specified otherwise), that is to say from the left to the right on the figure 5 .
  • the adjectives "inside” and “outside” are related to the proximity to the main axis A.
  • the expansion ring 220 is pierced with holes 226 oriented substantially axially (that is, in the direction of the main axis A) which allow air to penetrate. axially in the zone located downstream of the injector 10. This air thus penetrates parallel to the circumferential side wall of the injector in the zone upstream thereof and forms a layer or film of air around the injector, which prevents coke is deposited on the downstream end of the injector.
  • these holes 226 are drilled in the radial wall 224 of the expansion ring 220 which extends radially outwardly the downstream end of the cylindrical portion 222 of this ring.
  • the tests and uses in service performed by the Applicant show however that such an air film is the source of disadvantages.
  • parts of the combustion chamber bottom are located immediately downstream of the injector. These include the primary swirler 40, and the venturi 50.
  • the primary swirler 40 is an annular piece coaxial with the injector 10, placed immediately downstream of the expansion ring 220, whose inner diameter is greater than to the diameter of the injector.
  • This primary swirler 40 is pierced around its circumference by primary holes 42 through which the air enters the zone situated downstream of the injector 10.
  • the primary holes 42 are oriented so that their axes lie in a plane radial with respect to the main axis, with a circumferential inclination.
  • the air exiting the primary holes 42 enters the zone downstream of the injector 10 by rotating around the main axis A and forming a swirler or vortex.
  • the venturi 50 Located downstream of the primary swirler 40 is the venturi 50, which is an annular piece coaxial with the injector 10.
  • the venturi 50 has a radial wall which extends downstream (at its inner end) by a convergent 52 , that is to say a conical wall which approaches the main axis A downstream.
  • the convergent 52 is extended by a neck 54, then a divergent 56 which flares downstream.
  • the convergent 52 is therefore downstream of the injector 10, and is located substantially in the axial extension of the holes 226 of the expansion ring 220.
  • the tests carried out by the Applicant have revealed that the air issuing from the holes 226 enters the zone downstream of the injector 10 (and the ring 220) by creating turbulence.
  • the present invention aims to remedy these drawbacks, or at least to mitigate them.
  • the invention aims to provide an injection system according to claim 1 comprising an expansion ring such that the air from the holes which are pierced enters the zone downstream of the injector homogeneously, and without impacting the downstream end of the injector.
  • the expansion ring comprises a conical annular slot converging downstream, open downstream, the holes opening into the upstream portion of this slot, the axis of each of these holes making with the main axis an angle strictly greater than the angle that makes with this main axis the generatrix of the cone defining the annular slot, such so that the air coming out of the holes impacts the inner wall of the annular slot which is closest to the main axis.
  • the air leaving the holes does not penetrate directly into the downstream zone of the injector, but firstly impacts the inner wall of the annular slot, and is then redirected along the annular slot.
  • the air exits the annular slot in a homogeneous manner that is to say that the air velocity at the outlet of the annular slot is substantially uniform over the outlet orifice of the annular slot, the air flow is not turbulent.
  • the angle of the annular slot with the main axis is such that the air exiting the slot does not impact the surface of the injector. Thus, no coke deposit is produced on the surface of the injector.
  • the expansion ring comprises a cylindrical portion around the main axis, and a radial wall which extends radially outwardly the downstream end of this cylindrical portion, and the annular slot opens downstream at the location or the cylindrical portion joins the radial wall.
  • the holes of the expansion ring have a circumferential inclination with respect to the main axis, which gives the air passing through them a rotational movement about the main axis.
  • this inclination causes an air flow clockwise around the main axis in the direction of the flow of fuel.
  • this inclination generates a flow of air in the opposite direction of the clockwise direction around the main axis in the direction of the flow of the fuel.
  • the invention also aims to propose an injection system according to claim 1 comprising an expansion ring such that the air from the holes of this ring does not cause coke deposition on the downstream end of the injector, and does not cause deposit of coke on the convergent venturi, such deposits of coke being undesirable because they degrade the fuel spraying by the injectors.
  • This goal is achieved by the fact that the air leaving the annular slot does not impact the downstream end of the injector and leaves the annular slot in a direction substantially parallel to the direction of flow of the air exiting the primary swirler, so that these two air flows do not mix (or at least only further downstream).
  • the generatrix of the cone defining the annular slot of the expansion ring is with the main axis an angle equal to or greater than the angle made by the convergent of the venturi with this main axis, so that the air coming out of the the annular slot does not impact the convergent of the venturi.
  • the combustion chamber can operate with lower fuel injection rates (lower extinction limit).
  • fuel injection rates lower extinction limit.
  • the figure 1 illustrates a system for injecting a combustion chamber 100 of a turbomachine.
  • This injection system is identical to that shown on the figure 5 , except for the expansion ring.
  • the fuel is injected into a combustion chamber 100 (for example in a combustion chamber of a turbomachine) by an injector 10.
  • This injector 10 is substantially cylindrical, and has an annular expansion ring 20 with respect to a main axis A. and which surrounds a portion of the injector 10, this injector being coaxial with the expansion ring.
  • the expansion ring 20 has a cylindrical portion 22 axial whose radially inner surface is in contact or almost the outer surface of the injector 10.
  • the expansion ring 20 comprises upstream of the cylindrical portion 22 a conical collar 21 which extends this cylindrical portion flaring radially upstream.
  • the cylindrical portion 22 and the flange 21 have a substantially constant thickness.
  • the downstream end of the cylindrical portion 22 of the expansion ring 20 is either slightly upstream or aligned with the downstream end 12 of the injector 10.
  • the downstream end of the cylindrical portion 22 is extended radially outwardly by a radial wall 24, so that the inner face of the cylindrical portion 22 and the downstream face of the radial wall 24 form substantially a right angle.
  • the radial wall 24 has a substantially constant thickness.
  • the expansion ring 20 On the upstream side of the radial wall 24, where this radial wall meets the cylindrical portion 22, the expansion ring 20 has an annular bulge 30 having substantially the shape of a torus.
  • the upstream face of the radial wall 24 is extended upstream by the surface of the annular bulge 30, this surface joining the outer face of the cylindrical portion 22.
  • the line of the upstream face of the radial wall 24 is perpendicular to the main axis A, and extends at right angles upstream by the line of the surface of the annular bulge 30, this line substantially following a quarter circle to the line of the outer face of the cylindrical portion 22.
  • the line of the surface of the annular bulge 30 joins the line of the outer face of the cylindrical portion 22 forming a right angle.
  • the transitions between the surface of the annular bulge 30 and the upstream face of the radial wall 24 or the outer face of the cylindrical portion 22 can also be done with a rounding.
  • the Figures 2 and 3 detail the structure of the expansion ring 20.
  • the annular bulge 30 is hollowed out of a conical annular slot 32 congested downstream, and open at its downstream end 34.
  • the annular slot 32 thus forms a continuous cavity.
  • This annular slot 32 is delimited by an inner wall 38, an outer wall facing the inner wall 38, and a substantially toroidal wall (having the shape of a half-torus whose axis of revolution is the main axis A, and cut in a plane substantially perpendicular to its axis of revolution).
  • the inner and outer walls 38 of the annular slot 32 are substantially parallel and are joined by this substantially toric wall.
  • rectilinear holes 26 distributed around the main axis A open on one side on the substantially toric wall, on the other side on the surface of the annular bulge 30.
  • the holes 26 may to be lights.
  • the axis of each of the holes 26 intersects the main axis A.
  • the holes 26 are not located in the extension of the annular slot 32, that is to say that the axis of each of these holes is not parallel with the generatrix of the cone defining the annular slot 32.
  • the axis of each of the holes 26 is with the main axis at an angle strictly greater than the angle that is made with this main axis the generatrix of the cone defining the annular slot 32, so that the air (coming from outside the combustion chamber) coming out of the holes 26 impacts the inner wall 38 of the annular slot 32.
  • the place of impact on the inner wall 38 of the Outgoing air from the holes 26 is typically in the first upstream third of the annular slot 32.
  • the air is redirected along the annular slot 32, and comes out of it homogeneous.
  • the holes 26 have a diameter of between 0.8 and 1.5 mm, so that the air emerging from these holes in the annular slot 32 has a flow rate and a flow velocity which results in a better homogeneity of the hole. air out of the annular slot 32.
  • the number of holes 26 is between 10 and 20.
  • the height of the slot (distance between the inner wall 38 and the outer wall) is between 1.5 and 3 mm.
  • the length of the slot is between 2 to 3 times its height.
  • the figure 4 is a cross section at holes 26 of an expansion ring 20 according to another embodiment of the invention.
  • the holes 26 comprise a circumferential inclination, that is to say that the axis of each of the holes 26 does not intersect the main axis A.
  • the circumferential inclination angle of the holes 26 is between 20 ° and 45 ° (in absolute value), that is to say that the holes 26 thus inclined generate an air flow in the clockwise direction or in the opposite direction of the clockwise direction around the main axis A in the direction of the fuel flow. On the figure 4 this air flow is generated in a clockwise direction.
  • the downstream end of the inner wall 38 of the annular slot 32 and the downstream end of the inner face of the cylindrical wall 22 meet substantially at one point.
  • the annular slot 32 may have a larger radius (i.e., be further away from the main axis A), the annular bulge 30 being outwardly shifted.
  • the downstream end of the inner wall 38 of the annular slot 32 and the downstream end of the inner face of the cylindrical wall 22 do not meet at the downstream face of the radial wall 24, and are joined by a part of this downstream face.
  • parts of the combustion chamber bottom are located immediately downstream of the injector 10 and the expansion ring 20. These include the primary swirler 40, and the venturi 50.
  • the primary swirler 40 is an annular piece coaxial with the injector 10, placed immediately downstream of the expansion ring 20, whose inner diameter is greater than the diameter of the injector 10.
  • This primary swirler 40 is pierced around its circumference of primary holes 42 through which the air enters the area downstream of the injector 10.
  • the primary holes 42 are oriented so that their axes lie in an axial plane with respect to the main axis, with circumferential inclination.
  • the air exiting the primary holes 42 enters the zone downstream of the injector 10 by rotating around the main axis A and forming a swirler or vortex.
  • the air passed through these holes 26 leaves the annular slot 32 while rotating in the same direction or in the opposite direction to the air coming out of the primary holes 42.
  • the angle that the generatrix of the cone defining the annular slot 32 with the main axis A is such that the air passed through the holes 26 and the air passed through the primary holes 42 do not mix, or at least not immediately.
  • venturi 50 which is an annular piece coaxial with the injector 10.
  • the venturi 50 has a radial wall which extends downstream at its inner end by a convergent 52, which is a conical wall that approaches the main axis A downstream.
  • the convergent 52 is extended by a neck 54, then a divergent 56 which flares downstream.
  • the convergent 52 is therefore downstream of the injector 10.
  • the angle that the generatrix of the cone defining the annular slot 32 with the main axis A is equal to or greater than the angle made by the convergent of the venturi with this main axis A, so that the air passing through the holes 26 of the annular slot 32 does not impact the convergent 52.
  • the inclination of the annular slot 32 is therefore dependent on that of the convergent 52 of the venturi.
  • the angle that the generatrix of the cone defining the annular slot 32 with the main axis A is typically between 30 ° and 60 °.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Claims (12)

  1. Einspritzsystem, umfassend einen Treibstoffinjektor (10) mit der Hauptachse (A), eine zu dem Injektor (10) koaxiale ringförmige Dehnungsbuchse (20), wobei die Buchse um diese Hauptachse verteilte Löcher (26) aufweist, die an der stromaufwärtigen Seite der Buche (20) ausmünden und den Durchgang von Luft in Richtung des Bereichs stromabwärts der Buchse (20) ermöglichen, dadurch gekennzeichnet, daß die Buchse einen axialen zylindrischen Teil (22) umfaßt, dessen radial innere Fläche mit der Außenfläche des Injektors (10) in Kontakt ist, und einen konischen, in stromabwärtiger Richtung konvergenten, in stromabwärtiger Richtung offenen, ringförmigen Schlitz (32) aufweist, wobei die Löcher in den stromaufwärtigen Teil des Schlitzes (32) münden, wobei die Achse eines jeden dieser Löcher (26) mit der Hauptachse (A) einen Winkel bildet, der unbedingt größer ist als der Winkel, den die Mantellinie des den ringförmigen Schlitz (32) definierenden Kegels mit dieser Hauptachse bildet, so daß die aus den Löchern (26) austretende Luft auf die Innenwand (38) des ringförmigen Schlitzes trifft, die der Hauptachse am nächsten liegt, wobei das Einspritzsystem ferner einen zu der Buchse (20) koaxialen, stromabwärts des Injektors angeordneten Primärverwirbler (40) sowie ein stromabwärts des Primärverwirblers angeordnetes Venturi-Rohr (50) umfaßt, wobei die Luft aus dem ringförmigen Schlitz (32) in einer Richtung austritt, die zu der Strömungsrichtung der aus dem Primärverwirbler (40) austretenden Luft im wesentlichen parallel verläuft, so daß diese beiden Luftströme sich nicht vermischen und somit stromabwärts des Injektors (10) weniger Turbulenzen vorhanden sind.
  2. Einspritzsystem nach Anspruch 1, dadurch gekennzeichnet, daß die Dehnungsbuchse (20) einen zylindrischen Teil (22) um die Hauptachse (A) herum sowie eine radiale Wand (24) umfaßt, die das stromabwärtige Ende dieses zylindrischen Teils radial nach außen fortsetzt, und daß der ringförmige Schlitz (32) in stromabwärtiger Richtung an der Stelle ausmündet, an welcher der zylindrische Teil (22) auf die radiale Wand (24) trifft.
  3. Einspritzsystem nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Löcher (26) gegenüber der Hauptachse (A) eine Umfangsneigung aufweisen, die der Luft, die diese durchströmt, eine Rotationsbewegung um die Hauptachse verleiht.
  4. Einspritzsystem nach Anspruch 3, dadurch gekennzeichnet, daß der Umfangsneigungswinkel der Löcher (26) im Bereich zwischen 20° und 45° gegenüber einer radialen Richtung liegt.
  5. Einspritzsystem nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß die Löcher (26) einen Durchmesser zwischen 0,8 und 1,5 mm aufweisen.
  6. Einspritzsystem nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß die Anzahl der Löcher (26) zwischen 10 und 20 liegt.
  7. Einspritzsystem nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß die Höhe des ringförmigen Schlitzes (32) zwischen 1,5 und 3 mm beträgt.
  8. Einspritzsystem nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, daß der Ort des Auftreffens der aus den Löchern (26) der Buchse austretenden Luft auf die Innenwand (38) des ringförmigen Schlitzes (32) im ersten stromaufwärtigen Drittel des ringförmigen Schlitzes liegt.
  9. Einspritzsystem nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, daß der Primärverwirbler (40) Primärlöcher (42) besitzt, über die die Luft in den stromabwärts gelegenen Bereich des Injektors dringt, und daß die Luft aus dem ringförmigen Schlitz (32) in einer Richtung austritt, die zu der Strömungsrichtung der aus dem Primärverwirbler austretenden Luft im wesentlichen parallel verläuft, so daß diese beiden Luftströme sich nicht vermischen.
  10. Einspritzsystem nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, daß das Venturi-Rohr (50) ein in stromabwärtiger Richtung zusammenlaufendes konvergentes Teil (52) besitzt und daß die Mantellinie des den ringförmigen Schlitz (32) definierenden Kegels mit der Hauptachse (A) einen Winkel bildet, der gleich dem oder größer als der Winkel ist, den das konvergente Teil (52) des Venturi-Rohrs mit dieser Hauptachse bildet, so daß die aus dem ringförmigen Schlitz (32) austretende Luft nicht auf den konvergenten Teil des Venturi-Rohrs trifft.
  11. Brennkammer, die mit einem Einspritzsystem nach einem der Ansprüche 1 bis 10 ausgestattet ist.
  12. Turbomaschine, die eine Brennkammer nach Anspruch 11 umfaßt.
EP08159886A 2007-07-12 2008-07-08 Optimierung einer Antikoksschicht in einem Einspritzsystem Active EP2014988B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0756450A FR2918716B1 (fr) 2007-07-12 2007-07-12 Optimisation d'un film anti-coke dans un systeme d'injection

Publications (2)

Publication Number Publication Date
EP2014988A1 EP2014988A1 (de) 2009-01-14
EP2014988B1 true EP2014988B1 (de) 2012-11-21

Family

ID=39047713

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08159886A Active EP2014988B1 (de) 2007-07-12 2008-07-08 Optimierung einer Antikoksschicht in einem Einspritzsystem

Country Status (5)

Country Link
US (1) US8276388B2 (de)
EP (1) EP2014988B1 (de)
CA (1) CA2636923C (de)
FR (1) FR2918716B1 (de)
RU (1) RU2478876C2 (de)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100089022A1 (en) * 2008-10-14 2010-04-15 General Electric Company Method and apparatus of fuel nozzle diluent introduction
US20100089020A1 (en) * 2008-10-14 2010-04-15 General Electric Company Metering of diluent flow in combustor
US8567199B2 (en) * 2008-10-14 2013-10-29 General Electric Company Method and apparatus of introducing diluent flow into a combustor
US9121609B2 (en) 2008-10-14 2015-09-01 General Electric Company Method and apparatus for introducing diluent flow into a combustor
FR2941288B1 (fr) * 2009-01-16 2011-02-18 Snecma Dispositif d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine
US8850819B2 (en) * 2010-06-25 2014-10-07 United Technologies Corporation Swirler, fuel and air assembly and combustor
US10317081B2 (en) * 2011-01-26 2019-06-11 United Technologies Corporation Fuel injector assembly
RU2604260C2 (ru) 2011-05-17 2016-12-10 Снекма Кольцевая камера сгорания для турбомашины
JP5924618B2 (ja) * 2012-06-07 2016-05-25 川崎重工業株式会社 燃料噴射装置
FR2994713B1 (fr) * 2012-08-21 2018-06-29 Snecma Injecteur pour tete d'injection d'une chambre de combustion
JP6351071B2 (ja) * 2014-08-18 2018-07-04 川崎重工業株式会社 燃料噴射装置
GB201506017D0 (en) 2015-04-09 2015-05-27 Rolls Royce Plc Fuel injector system
GB2548585B (en) * 2016-03-22 2020-05-27 Rolls Royce Plc A combustion chamber assembly
GB201617369D0 (en) 2016-10-13 2016-11-30 Rolls Royce Plc A combustion chamber and a combustion chamber fuel injector seal
CN107796016A (zh) * 2017-09-29 2018-03-13 哈尔滨理工大学 一种燃气轮机燃烧室双燃料一体化喷嘴装置
FR3080437B1 (fr) 2018-04-24 2020-04-17 Safran Aircraft Engines Systeme d'injection pour une chambre annulaire de combustion de turbomachine
FR3091574B1 (fr) * 2019-01-08 2020-12-11 Safran Aircraft Engines Systeme d’injection pour turbomachine, comprenant une vrille et des trous tourbillonnaires de bol melangeur
US11378275B2 (en) * 2019-12-06 2022-07-05 Raytheon Technologies Corporation High shear swirler with recessed fuel filmer for a gas turbine engine
FR3106374B1 (fr) 2020-01-21 2022-01-21 Safran Aircraft Engines Circuit d’alimentation en carburant pour une chambre de combustion d’une turbomachine
FR3108162B1 (fr) 2020-03-10 2023-01-13 Safran Aircraft Engines Système d’injection pour une chambre annulaire de combustion de turbomachine
CN116136308A (zh) * 2021-11-16 2023-05-19 通用电气公司 具有压降吹扫通道的旋流器套圈板
US12012918B1 (en) 2023-01-27 2024-06-18 Hamilton Sundstrand Corporation Systems and methods for coking mitigation in fuel supply systems

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4584834A (en) * 1982-07-06 1986-04-29 General Electric Company Gas turbine engine carburetor
RU2083926C1 (ru) * 1993-04-13 1997-07-10 Виноградов Евгений Дмитриевич Фронтовое устройство камеры сгорания
US5412272A (en) 1994-01-24 1995-05-02 Mensching; Herman E. Submersible explosion proof electric brake motor
DE4444961A1 (de) * 1994-12-16 1996-06-20 Mtu Muenchen Gmbh Einrichtung zur Kühlung insbesondere der Rückwand des Flammrohrs einer Brennkammer für Gasturbinentriebwerke
RU2157954C2 (ru) * 1995-09-05 2000-10-20 Открытое акционерное общество "Самарский научно-технический комплекс им. Н.Д.Кузнецова" Топливовоздушная горелка
US6240731B1 (en) * 1997-12-31 2001-06-05 United Technologies Corporation Low NOx combustor for gas turbine engine
US6082113A (en) * 1998-05-22 2000-07-04 Pratt & Whitney Canada Corp. Gas turbine fuel injector
US6412272B1 (en) * 1998-12-29 2002-07-02 United Technologies Corporation Fuel nozzle guide for gas turbine engine and method of assembly/disassembly
US7013649B2 (en) 2004-05-25 2006-03-21 General Electric Company Gas turbine engine combustor mixer

Also Published As

Publication number Publication date
EP2014988A1 (de) 2009-01-14
US20090049840A1 (en) 2009-02-26
FR2918716A1 (fr) 2009-01-16
FR2918716B1 (fr) 2014-02-28
CA2636923A1 (fr) 2009-01-12
CA2636923C (fr) 2015-08-25
US8276388B2 (en) 2012-10-02
RU2008128382A (ru) 2010-01-20
RU2478876C2 (ru) 2013-04-10

Similar Documents

Publication Publication Date Title
EP2014988B1 (de) Optimierung einer Antikoksschicht in einem Einspritzsystem
EP1873455B1 (de) Vorrichtung zum Einspritzen einer Mischung aus Luft und Treibstoff, Brennkammer und Strömungsmaschine, die mit einer solchen Vorrichtung ausgestattet ist
WO2010081940A1 (fr) Dispositif d'injection d'un mélange d'air et de carburant dans une chambre de combustion de turbomachine
WO2012156631A1 (fr) Chambre annulaire de combustion pour une turbomachine
FR2903173A1 (fr) Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
FR2902469A1 (fr) Melangeur a lobes courbes pour tuyere a flux confluents de turbomachine
EP1873456A1 (de) Vorrichtung zum Einspritzen einer Mischung aus Luft und Treibstoff, Brennkammer und Strömungsmaschine, die mit einer solchen Vorrichtung ausgestattet ist
FR3022985B1 (fr) Systeme d'injection pour chambre de combustion de turbomachine configure pour une injection directe de deux nappes de carburant coaxiales
FR3081211A1 (fr) Ensemble pour une chambre de combustion de turbomachine
EP3784958B1 (de) Einspritzsystem für eine annulare verbrennungskammer einer gasturbine
EP3286500B1 (de) Tubomaschinenbrennkammer mit einer luftstromführungsvorrichtung mit bestimmter form
FR3091574A1 (fr) Systeme d’injection pour turbomachine, comprenant une vrille et des trous tourbillonnaires de bol melangeur
FR2958015A1 (fr) Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection de carburant entre deux flux d'air coaxiaux
FR3087847A1 (fr) Melangeur a lobes favorisant le melange de flux confluents
EP3449185A1 (de) Lufteinlassverwirbler für ein turbomaschineneinspritzsystem mit einem aerodynamischen deflektor an seinem einlass
EP3673166B1 (de) Modifizierte akustische sekundärdüse
FR2956725A1 (fr) Systeme d'injection de carburant pour une chambre de combustion de turbomachine
EP4065892A1 (de) Kraftstoffeinspritzsystem für eine turbomaschine, brennkammer mit einem solchen system und zugehörige strömungsmaschine
FR3070187B1 (fr) Ecope inter-veine
FR2893389A1 (fr) Paroi transversale de chambre de combustion munie de trous de multiperforation
FR2975466A1 (fr) Chambre annulaire de combustion pour une turbomachine
FR3117548A1 (fr) Dispositif d’entrainement d’un flux d’air principal pour une turbomachine d’aeronef
FR3123092A1 (fr) Dispositif d’entrainement d’un flux d’air principal pour une turbomachine d’aeronef
FR3095499A1 (fr) Injecteur d’un melange d’air et de carburant pour une chambre de combustion d’une turbomachine
FR2973480A1 (fr) Dispositif d'injection d'air et de carburant pour chambre de combustion

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20080708

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

AKX Designation fees paid

Designated state(s): DE FR GB IT

17Q First examination report despatched

Effective date: 20090924

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602008020206

Country of ref document: DE

Effective date: 20130117

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20130822

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602008020206

Country of ref document: DE

Effective date: 20130822

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20230620

Year of fee payment: 16

Ref country code: FR

Payment date: 20230621

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230620

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20230620

Year of fee payment: 16