EP2667098B1 - INJECTEUR DE CARBURANT Liquide - Google Patents

INJECTEUR DE CARBURANT Liquide Download PDF

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Publication number
EP2667098B1
EP2667098B1 EP13169005.9A EP13169005A EP2667098B1 EP 2667098 B1 EP2667098 B1 EP 2667098B1 EP 13169005 A EP13169005 A EP 13169005A EP 2667098 B1 EP2667098 B1 EP 2667098B1
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EP
European Patent Office
Prior art keywords
swirl
flow
channel
bore
dogleg
Prior art date
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Application number
EP13169005.9A
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German (de)
English (en)
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EP2667098A3 (fr
EP2667098A2 (fr
Inventor
Philip E.O. Buelow
Randall Duane Siders
David H. Bretz
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Rolls Royce PLC
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Rolls Royce PLC
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Publication date
Priority claimed from US13/481,411 external-priority patent/US9310073B2/en
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP2667098A2 publication Critical patent/EP2667098A2/fr
Publication of EP2667098A3 publication Critical patent/EP2667098A3/fr
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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
    • F23R3/02—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
    • 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
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • 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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts

Definitions

  • the present invention relates to liquid fuel injectors turbine engines.
  • Fuel injectors for applications such as gas turbine engines require control over the distribution of the fuel through the injector.
  • fuel is introduced through a single inlet fitting, and then distributed to a plurality of fuel ports, which can be slots or drilled holes, for presentation to a swirl chamber and/or a combustion chamber.
  • the fluid pathway from the single inlet to the plurality of ports can take many different forms.
  • pre-swirl distribution troughs are provided upstream of the fuel ports whereby the fuel exits the inlet fitting region through one or more passages that impart a tangential velocity component to the fuel. These distribution troughs provide a space to balance the fuel distribution prior to entering the fuel ports.
  • An example of this type of swirler is shown and described in US-A-7,506,510 .
  • Another example provides a first full annular region separated from a second full annular region by a restrictive full annular throat region. By taking a pressure drop through the throat feature, the flow is balanced around the circumference of the component prior to the fuel entering the ports.
  • Another example divides the fuel from the fuel inlet region into two or more discrete fuel passages with each passage terminating with one or more fuel ports, as shown and described in U.S. Patent Application No. 12/932,958 . The ultimate extension of this concept has one fuel port for each passage.
  • the fuel-delivery path leading up to the port contributes to the character of the flow entering the port.
  • the direction of the flow as it approaches the port typically has a strong component which is perpendicular to the axis of the port. In this situation, the flow will have a clear tendency to swirl as it enters the port, similar to the way water swirls as it flows down a drain.
  • the fuel may spin in either the clockwise or counterclockwise direction. The clockwise/counter-clockwise direction of swirl can result in different behavior of the flow through and exiting the port.
  • the required driving pressure needed to maintain a specified flow-rate is also affected by whether the flow is swirling, and to what extent. A larger pressure-drop occurs through a hole that has a highly swirling flow therein, as opposed to a non-swirling flow. Therefore a highly swirling flow within a swirl port will require a larger driving pressure to achieve a specified flow rate, when compared to a lower or non-swirling flow.
  • the subject invention is directed to a liquid fuel injector for a gas turbine as defined by claim 1.
  • the liquid fuel injector includes a new and useful flow directing device for imparting swirl on a fluid.
  • the flow directing device includes a flow directing body having a first surface and an opposed second surface.
  • a flow channel is defined in the first surface of the flow directing body for conducting fluids flowing through the flow directing body.
  • the flow channel includes a channel surface set in from the first surface.
  • a swirl bore extends though the flow directing body from the channel surface to the second surface of the flow directing body at an oblique angle relative to the channel surface for imparting a tangential swirl component onto fluids flowing through the swirl bore.
  • the channel surface is a channel floor and the channel includes a sidewall extending from the channel floor to the first surface of the flow directing body.
  • the swirl bore opens at a swirl bore opening within a terminus section of the flow channel.
  • the terminus section of the flow channel can be substantially symmetrical with respect to the flow channel upstream of the terminus section, for example, the terminus section can be circular and the swirl bore opening can be defined at the center of the circular terminus section.
  • the swirl bore opens at a swirl bore opening within a terminus section of the flow channel, wherein the terminus section of the flow channel is asymmetrical with respect to the flow channel upstream of the terminus section to control swirl direction for fluids flowing through the swirl bore.
  • the terminus section of the flow channel can define a dogleg with respect to the flow channel upstream of the terminus section.
  • the dogleg can be angled to impart counter-clockwise swirl in the swirl bore as viewed towards the channel floor, or can be angled to impart clockwise swirl in the swirl bore as viewed towards the channel floor.
  • the dogleg can be angled at about 90° relative to the flow channel upstream of the dogleg. It is also contemplated that the dogleg can be angled at any suitable angle relative to the upstream flow channel, including obliquely. For example, the angle can be between 0° and 180°, or any other suitable angle.
  • the swirl bore can be cylindrical, defining a swirl bore radius.
  • the terminus section can define a semi-circular pad in the channel floor having a radius between about two to about five times the swirl bore radius.
  • the flow channel upstream of the dogleg defines a first axis, the dogleg can define a second axis angled relative to the first axis.
  • the swirl bore opening in the channel floor can have a center that is offset from a radial center point defined by the semi-circular pad in a direction perpendicular to the second axis. This offset can be from about one swirl bore radius to about two times the swirl bore radius. It is also contemplated that in certain embodiments, this offset can be zero or more times the swirl bore radius downstream relative to the flow channel.
  • the center of the swirl bore opening in the channel floor can be offset from the radial center point defined by the semi-circular pad in a direction along a second axis that is angled to the first axis by about one swirl bore radius or less.
  • the invention provides an injector for producing an atomized spray of liquid.
  • the injector includes an annular injector body.
  • An annular first flow directing body is mounted inboard of the injector body, the first flow directing body including an inboard surface and opposed outboard surface.
  • a plurality of flow channels, as described above, are defined in the outboard surface of the first flow directing body with swirl bores for conducting fluids flowing through the first flow directing body.
  • An annular second flow directing body is mounted radially inboard of the first flow directing body.
  • the second flow directing body includes an outboard surface with an annular swirl chamber defined therein for receiving liquid from the swirl bores of the first flow directing body to form a swirling sheet of liquid for atomization downstream of the second flow directing body. It is also contemplated that the flow directing bodies can be configured to form a discrete jet spray for suitable applications.
  • FIG. 4 a partial view of an exemplary embodiment of a flow directing device in accordance with the invention is shown in Fig. 4 and is designated generally by reference character 100.
  • Other embodiments of flow directing devices in accordance with the invention, or aspects thereof, are provided in Figs. 1-3 and 5-20 , as will be described.
  • the system of the invention can be used to control swirl, for example, in fuel swirlers for gas turbine engines.
  • fuel injector 10 is adapted and configured for producing an atomized spray of liquid, such as for delivering fuel to the combustion chamber of a gas turbine engine.
  • Fuel injector 10 is generally referred to as a staged fuel injector in that it includes a pilot fuel circuit, which typically operates during engine ignition and at low engine power and a main fuel circuit, which typically operates at high engine power (e.g., at take-off and cruise) and is typically staged off at lower power operation.
  • Fuel injector 10 includes a generally annular injector body 12, which depends from an elongated feed arm 14, and defines a longitudinal axis y.
  • main and pilot fuel flows are delivered into injector body 12 through concentric fuel feed tubes.
  • these feed tubes include an inner/main fuel feed tube 15 and an outer/pilot fuel feed tube 17 located within the feed arm 14.
  • the fuel feed tubes could be enclosed within an elongated shroud or protective strut extending from a fuel fitting to the nozzle body.
  • combustor discharge air is directed into the inlet end 19 of injector body 12 and directed through a series of main and pilot air circuits or passages, which are shown in Fig. 3 .
  • the air flowing through the main and pilot air circuits interacts with the main and pilot fuel flows from feed arm 14. That interaction facilitates the atomization of the main and pilot fuel issued from the outlet end 21 of injector body 12 and into the combustion chamber of the gas turbine engine.
  • injector body 12 includes a main fuel atomizer 25 that has an outer air cap 16 and a main outer air swirler 18.
  • a main outer air circuit 20 is defined between the outer air cap 16 and the outer air swirler 18.
  • Swirl vanes 22 are provided within the main outer air circuit 20, depending from outer air swirler 18, to impart an angular component of swirl to the pressurized combustor air flowing therethrough.
  • Fuel injector 10 includes a flow directing body 100 mounted inboard of injector body 12, positioned radially inward of the outer air swirler 18. In this position, flow directing body 100 takes the place of a traditional prefilmer. A second flow directing device 26, in the place of a traditional annular main fuel swirler, is mounted radially inward of the flow directing body 100. Flow directing body 100 has a diverging prefilming surface at the nozzle opening. As described in more detail herein below with reference to Figs. 4 and 5 , portions of the fuel circuits, including flow channels and respective swirl ports are defined in the outer diametrical surface of the flow directing device 100 for conducting fluids flowing therethrough.
  • the main fuel circuit receives fuel from the inner feed tube 15 and delivers that fuel into an annular swirl chamber 28 defined in the outboard surface of second flow directing device 26 and located at the outlet end of the main fuel atomizer 25.
  • Swirl chamber 28 receives liquid from swirl ports of flow directing device 100, which are described below, to form a swirling sheet of liquid for atomization downstream of flow directing device 100. It is also contemplated that the flow directing device can be configured to form a discrete jet spray for suitable applications.
  • the main fuel atomizer further includes a main inner air circuit 30 defined between the second flow directing device 26 and a converging pilot air cap 32.
  • Swirl vanes 34 are provided within main inner air circuit 30, depending from pilot air cap 32, to impart an angular component of swirl to the pressurized combustor air flowing therethrough. In operation, swirling air flowing from main outer air circuit 20 and main inner air circuit 30 impinge upon the fuel issuing from swirl chamber 28, to promote atomization of the fuel.
  • Injector body 12 further includes an axially located pilot fuel atomizer 35 that includes the converging pilot air cap 32 and a pilot outer air swirler 36.
  • a pilot outer air circuit 38 is defined between pilot air cap 32 and pilot outer air swirler 36.
  • Swirl vanes 40 are provided within pilot outer air circuit 38, depending from air swirler 36, to impart an angular component of swirl to the air flowing therethrough.
  • a pilot fuel swirler 42 shown here by way of example, as a pressure swirl atomizer, is coaxially disposed within the pilot outer air swirler 36.
  • the pilot fuel swirler 42 receives fuel from the pilot fuel circuit by way of the inner pilot fuel conduit 76 in support flange 78. Pilot fuel conduit 76 is oriented radially, or perpendicularly with respect to longitudinal axis y.
  • Injector body 12 includes a tube mounting section 12a and an atomizer mounting section 12b of reduced outer diameter.
  • Tube mounting section 12a includes radially projecting mounting appendage that defines a primary fuel bowl for receiving concentric fuel tubes 15 and 17 of feed arm 14.
  • a central main bore 52 extends from the fuel bowl for communicating with inner/main fuel tube 15 to deliver fuel to the main fuel circuit.
  • Dual pilot fuel bores communicate with and extend from the fuel bowl for delivering pilot/cooling fuel from outer/pilot fuel tube 17 to the pilot fuel circuit.
  • flow directing device 100 for imparting swirl on a fluid includes a flow directing body 102 having a first surface, i.e., outboard surface 156, and opposed second surface, i.e., inboard surface 154.
  • Flow directing body 100 is an annular ring, configured for use in place of a prefilmer/fuel swirler in a fuel injector as described above.
  • a set of branching flow channels 144 is defined in outboard surface 156 for conducting fluids flowing through flow directing body 102.
  • Each of the flow channels 144 includes a channel surface, namely channel floor 150, and a sidewall 108 extending from channel floor 150 to outboard surface 156.
  • a swirl bore 148 extends though flow directing body 102 from channel floor 150 to inboard surface 154 of the flow directing body 102 at an oblique angle relative to channel floor 150 for imparting a tangential swirl component onto fluids flowing through swirl bore 148.
  • the angle of swirl bore 148 relative to channel floor 150 is shown in cross-section.
  • Swirl bore 148 is cylindrical, with the axis of the cylinder being angled tangentially with respect to axis y, shown in Fig.
  • the swirl bores 148 can be formed by drilling, electrical discharge machining, or any other suitable process. Due to its angle relative to channel floor 150, the opening of swirl bore 148 in channel floor 150 is an ellipse, the minor radius of which is equal in length to the radius of the cylinder defined by swirl bore 148. As shown in Fig. 4 , the plurality of swirl bores 148 in flow directing body 102 are circumferentially spaced apart for imparting swirl on a bulk flow of liquid entering the fuel channels 144 and passing through flow directing body 102 in a generally inward direction through bores 148. In Fig. 4 , the swirl bores 148 are evenly spaced circumferentially, however the spacing can be uneven in suitable applications.
  • each swirl bore 148 opens at a swirl bore opening within a terminus section 146 of the respective flow channel 144.
  • Terminus section 146 is generally symmetrical with respect to the portion of flow channel 144 just upstream of terminus section 146. More particularly, terminus section 146 is circular and the opening of swirl bore 148 in channel floor 150 is at the center of the circular terminus section 146.
  • the conditions upstream of bore 148 impart swirl on the flow as it enters terminus section 146 and passes into bore 148. It has been found that this type of symmetrical terminus section can lead to lack of control of the direction of swirl of flow within the terminus section, be it clockwise or counter-clockwise as viewed in Fig. 5 . In certain applications this can result in unequal pressure losses distributed among the ports, leading to increased flow non-uniformity, for example when the flow from multiple swirl bores 148 produces conflicting swirl directions within a single flow directing device 100.
  • Branching fuel channels 244 end in a plurality of terminus portions 246, each having a swirl bore 248 that is angled tangentially as described above.
  • Flow directing body 202 includes an inboard surface 254 and opposed outboard surface 256. Channels 244 are formed in outboard surface 256, and the swirl bores 248 extend from channel floor 250 through flow directing body 202 to inboard surface 254, as shown in Fig. 10 .
  • Terminus portions 246 each have a dogleg to the right relative to the portion of channel 244 immediately upstream of terminus section 246, as oriented in Fig. 8 .
  • FIG. 9 shows an enlarged view of one of the terminus portions 246 of the channel 244 indicated in Fig. 8 .
  • a tangential component is imparted on the flow direction that causes a swirling flow around the volume within an inboard swirl chamber such as that shown and described in the applications incorporated by reference above.
  • the importance of orienting swirl bores 248 in a predominantly tangential direction is to impart sufficient swirl to the liquid to enhance the mixing of the discrete fuel streams from the individual swirl bores 248 within a common swirl chamber.
  • the enhanced mixing of the fuel streams ensures that the fuel will form a coherent sheet of liquid upon exiting the swirl chamber, and improve the circumferential uniformity of the fuel sheet for a well distributed spray of atomized fuel.
  • one characteristic of the swirl bore configuration in flow directing device 200 is the tendency for a swirling flow to form within the terminus portion 246, much as in the drain-type swirl effect described above.
  • the liquid delivery path leading up to swirl bore 248 contributes to the character of the flow entering swirl bore 248.
  • the direction of the flow as it approaches the bore typically has a strong component which is perpendicular to the axis of the bore, and the same can be said for bores originating on an inner diameter surface. In this situation, the flow will have a clear tendency to swirl as it enters the bore, similar to the way water swirls as it flows down a drain.
  • the liquid may spin in either a clockwise or counter-clockwise direction, which can result in different behavior of the flow through and exiting the bore. Therefore, it is advantageous to control the direction of swirl as it enters the bores.
  • FIG. 9 This swirling flow entering swirl bore 248 is indicated schematically by the flow arrows of Fig. 9 .
  • Figs. 11 and 12 show the asymmetry of terminus section 246 and bore 248 for direct comparison with Figs. 5 and 6 , respectively.
  • the dogleg of terminus section 246 forces the counter-clockwise swirl direction indicated in Fig. 9 .
  • each terminus section 246 around flow directing body 202 has the same dogleg direction
  • each terminus section 246 has the same swirl direction relative to its respective swirl bore 248.
  • This common, controlled swirl direction is in contrast to the swirl directions of flow directing body 102 described above, which vary from channel to channel. Having consistent swirl directions for each of the swirl bores 248 improves pressure drop, fuel distribution, and the strength of the desirable swirl around annular swirl chamber 28 described above.
  • each swirl bore 248 has a length L and diameter D.
  • the effectiveness at generating the desirable tangential swirl component on liquids flowing through swirl bore 248 is a function of the L/D ratio, the higher the ratio, the more effective the swirl bore.
  • the thickness T of flow directing body 202 and the depth of channel 244 can be adjusted as needed to provide an appropriate L/D ratio for a given application.
  • FIG. 13-15 another exemplary embodiment of a flow directing device 300 is shown with a flow directing body 302, branching flow channels 344, and swirl bores 348 similar to those described above.
  • terminus sections 346 are similar to terminus sections 246 described above, but the dogleg direction is opposite. This means that whereas terminus sections 246 described above induce a counter-clockwise swirl as viewed in Fig. 9 , terminus sections 346 induce a clockwise swirl entering swirl bores 348.
  • terminus sections 246 and 346 described above both have dogleg angles of 90° relative to the flow channel 244/344 just upstream of the dogleg, other dogleg angles can be used without departing from the spirit and scope of the invention.
  • Figs. 18 and 19 which can be compared to Figs. 11 and 12 , respectively, show an exemplary channel 444 having a terminus section 446 with a dogleg angle ⁇ of about 45° relative to the portion of channel 444 just upstream of terminus 446.
  • Swirl bore 448 defines a compound angle, having a tangential component as described above plus an axial component that is aligned with the angle ⁇ shown in Fig.
  • swirl bore 248 when swirl forms in a channel terminus such as those described above, the swirl raises pressure drop and reduces the flow number for the swirl bore compared to what the flow would be like with no swirl. In most applications it is desirable to mitigate this type of swirl.
  • the location of swirl bore 248 within terminus section 246 affects the amount of swirl induced on flow passing into swirl bore 248.
  • Terminus section 246 of channel 244 defines a semi-circular pad 255 in the channel floor 250 having a radius R that is about 4.5 times the radius r of swirl bore 248.
  • the semi-circular pad 255 could be any size with a radius R between about 2.0 to about 5.0 times the swirl bore radius r while still attaining the benefits described above.
  • Pad 255, and terminus section 246 in general, should be of sufficient size relative to the respective swirl bore, so that the swirl bore can be placed for controlling the amount of flow through the swirl bore for a given driving pressure.
  • the flow channel upstream of the dogleg defines a first axis y', which is parallel to axis y in Fig. 7 .
  • Semi-circular pad 255 defines a radial center point C.
  • Axis y" runs parallel to axis y' through center point C.
  • the opening of swirl bore 248 in channel floor 250 has a center c that is offset from center point C in a direction parallel to axis y" (i.e. in a direction perpendicular to axis X).
  • This offset is represented in Fig. 16 by distance A.
  • This offset distance A is shown in Fig. 16 as about 1.5 times radius r, and in Fig. 17 as about 1.0 times radius r.
  • offset distance A can be anything from about 1.0 times radius r to about 2.0 times radius r below center point C as oriented in Figs. 16-17 .
  • offset distance A can be zero, i.e., swirl bore 248 can be centered vertically on axis X. If the dogleg axis, axis X, is oblique relative to the first axis y', as in Fig. 20 , then the offset distance A is perpendicular to the oblique axis X.
  • an axis X is defined perpendicular to axis y" along channel floor 250 through center point C.
  • Swirl bore opening center c is also offset from center point C in a direction parallel to axis X, which offset is represented by distance B in Figs. 16-17 .
  • offset distance B is about 0.75 times radius r towards axis y'
  • offset distance B is about 0.5 times radius r away from axis y'.
  • offset distance B can be anything from about 1.0 times radius r to the left of center point C to about 1.0 times radius r to the right of center point C, as oriented in Figs. 16-17 .
  • the offset distance B is parallel to the oblique axis X.
  • region 271 that is depicted in Figs. 16-17 as a generally rectangular area, is a location where swirl is intensified if a swirl bore is located therein. Locating the center of a swirl port in region 271 results in higher driving pressure for a given flow-rate, as well as increased unsteadiness.
  • Swirl port region 271 is generally the area just above the X axis, centered on the y" axis, and about one radius R wide as oriented in Figs. 16-17 .
  • the position of swirl bore 448 can be set using the principles outlined above, wherein the X and y" axes are oriented based on the orientation of terminus section 446, as shown in Fig. 20 .
  • flow directing devices in accordance with the invention can be used in any suitable application, and need not be annular. Directing the flow from an outboard surface through swirl bores to an inboard surface is exemplary, as it is contemplated that flow directing devices in accordance with the invention can direct flow from a radially inner surface out to a radially outboard surface as well.
  • the exemplary embodiments above have channel floors and channel walls, however those skilled in the art will readily appreciate that any suitable channel surface arrangement can be used, for example, a single curved surface can define a channel, without departing from the scope of the invention.
  • any suitable fluid can be used without departing from the scope of the invention as set forth in the appended claims.

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

Claims (13)

  1. Injecteur de carburant liquide (10) pour une turbine à gaz, l'injecteur de carburant liquide étant configuré pour produire une pulvérisation atomisée de liquide, et comprenant :
    a) un corps d'injecteur annulaire (12) ;
    b) un dispositif annulaire d'orientation du flux (100) comprenant :
    i) un premier corps d'orientation du flux (102) présentant une première surface (156) et une deuxième surface (154) opposée ;
    ii) une pluralité de canaux d'écoulement (144) définis dans la première surface (156) du corps d'orientation du flux (102), chaque canal d'écoulement (144) comprenant un fond de canal (150) en retrait par rapport à la première surface (156) et une paroi latérale (108) s'étendant du fond de canal (150) à la première surface (156) du premier corps d'orientation du flux (102) ; et
    iii) un alésage de turbulence (148) s'étendant à travers le premier corps d'orientation du flux (102) de chaque fond de canal (150) à la deuxième surface (154) du premier corps d'orientation du flux (102) à un angle oblique par rapport au fond de canal (150) pour appliquer un composant de turbulence tangentielle sur les fluides s'écoulant dans l'alésage de turbulence (148) ;
    et
    c) un deuxième corps annulaire d'orientation du flux (26) monté radialement à l'intérieur du premier corps d'orientation du flux (102) et comprenant une surface extérieure avec une chambre de turbulence annulaire (28), qui y est définie pour recevoir le liquide des alésages de turbulence (148) du premier corps d'orientation du flux (102) pour former une nappe turbulente de liquide pour l'atomisation en aval du deuxième corps d'orientation du flux (26).
  2. Injecteur de carburant liquide selon la revendication 1, l'alésage de turbulence étant cylindrique.
  3. Injecteur de carburant liquide selon la revendication 1 ou 2, l'alésage de turbulence (148) s'ouvrant à une ouverture d'alésage de turbulence au sein d'une section terminale (146) du canal d'écoulement, la section terminale du canal d'écoulement étant substantiellement symétrique relativement au canal d'écoulement (144) en amont de la section terminale, la section terminale étant circulaire et l'ouverture de l'alésage de turbulence étant définie au centre de la section terminale circulaire.
  4. Injecteur de carburant liquide selon la revendication 1 ou 2, l'alésage de turbulence (248) s'ouvrant à une ouverture d'alésage de turbulence au sein d'une section terminale (246) du canal d'écoulement (244), la section terminale (246) du canal d'écoulement étant asymétrique relativement au canal d'écoulement en amont de la section terminale pour contrôler la direction de la turbulence des fluides s'écoulant à travers l'alésage de turbulence (248).
  5. Injecteur de carburant liquide selon la revendication 4, la section terminale du canal d'écoulement définissant une déviation relativement au canal d'écoulement en amont de la section terminale.
  6. Injecteur de carburant liquide selon la revendication 5, la déviation étant inclinée pour appliquer une turbulence dans le sens antihoraire dans l'alésage de turbulence vu en direction du fond du canal.
  7. Injecteur de carburant liquide selon la revendication 5, la déviation étant inclinée pour appliquer une turbulence dans le sens horaire dans l'alésage de turbulence vu en direction du fond du canal.
  8. Injecteur de carburant liquide selon la revendication 5, la déviation étant inclinée d'environ 90° relativement au canal d'écoulement en amont de la déviation.
  9. Injecteur de carburant liquide selon la revendication 5, la déviation présentant une inclinaison oblique relativement canal d'écoulement en amont de la déviation.
  10. Injecteur de carburant liquide selon une quelconque des revendications 5 à 9, l'alésage de turbulence (248) définissant un rayon d'alésage de turbulence, la section terminale définissant un tampon semi-circulaire (255) dans le fond du canal (250), ayant un rayon mesurant d'environ deux à cinq fois celui de l'alésage de turbulence.
  11. Injecteur de carburant liquide selon la revendication 10, le canal d'écoulement (244) en amont de la déviation définissant un premier axe, la déviation définissant un deuxième axe incliné relativement au premier axe, et l'ouverture de l'alésage de turbulence dans le fond du canal (250) présentant un centre décalé d'un point central radial défini par le tampon semi-circulaire dans une direction perpendiculaire au deuxième axe d'environ un rayon de l'alésage de turbulence, ou davantage, et d'environ deux fois le rayon de l'alésage de turbulence, ou moins.
  12. Injecteur de carburant liquide selon la revendication 10, le canal d'écoulement (244) en amont de la déviation définissant un premier axe, la déviation définissant un deuxième axe incliné relativement au premier axe, et l'ouverture de l'alésage de turbulence dans le fond du canal (250) présentant un centre décalé d'un point central radial défini par le tampon semi-circulaire dans une direction perpendiculaire au deuxième axe de zéro à plus de fois le rayon de l'alésage de turbulence en aval relativement au plancher du canal.
  13. Injecteur de carburant liquide selon la revendication 10, le canal d'écoulement en amont de la déviation définissant un premier axe, et l'ouverture de l'alésage de turbulence dans le fond du canal (250) présentant un centre décalé d'un point central radial défini par le tampon semi-circulaire (255) dans une direction le long d'un deuxième axe incliné relativement au premier axe d'environ un rayon d'alésage de turbulence ou moins.
EP13169005.9A 2012-05-25 2013-05-23 INJECTEUR DE CARBURANT Liquide Active EP2667098B1 (fr)

Applications Claiming Priority (1)

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US13/481,411 US9310073B2 (en) 2011-03-10 2012-05-25 Liquid swirler flow control

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EP2667098A2 EP2667098A2 (fr) 2013-11-27
EP2667098A3 EP2667098A3 (fr) 2015-11-04
EP2667098B1 true EP2667098B1 (fr) 2017-04-12

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Publication number Priority date Publication date Assignee Title
DE10340826A1 (de) * 2003-09-04 2005-03-31 Rolls-Royce Deutschland Ltd & Co Kg Homogene Gemischbildung durch verdrallte Einspritzung des Kraftstoffs
FR2875584B1 (fr) * 2004-09-23 2009-10-30 Snecma Moteurs Sa Injecteur a effervescence pour systeme aeromecanique d'injection air/carburant dans une chambre de combustion de turbomachine
US7506510B2 (en) 2006-01-17 2009-03-24 Delavan Inc System and method for cooling a staged airblast fuel injector
US8220271B2 (en) * 2008-09-30 2012-07-17 Alstom Technology Ltd. Fuel lance for a gas turbine engine including outer helical grooves

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EP2667098A2 (fr) 2013-11-27

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