EP3674608B1 - Einspritzkopf für eine gasturbinenbrennkammer - Google Patents

Einspritzkopf für eine gasturbinenbrennkammer Download PDF

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Publication number
EP3674608B1
EP3674608B1 EP19219662.4A EP19219662A EP3674608B1 EP 3674608 B1 EP3674608 B1 EP 3674608B1 EP 19219662 A EP19219662 A EP 19219662A EP 3674608 B1 EP3674608 B1 EP 3674608B1
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EP
European Patent Office
Prior art keywords
fuel
line
primary
inlet
injection head
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EP19219662.4A
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English (en)
French (fr)
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EP3674608A1 (de
Inventor
Fridolin Heynen
Michael Thomas Maurer
Alexander Sergeevich MYATLEV
Christoph Gaupp
Urs Benz
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Ansaldo Energia Switzerland AG
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Ansaldo Energia Switzerland AG
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Publication of EP3674608A1 publication Critical patent/EP3674608A1/de
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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
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • 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
    • F23R3/36—Supply of different fuels
    • 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 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors

Definitions

  • the present invention relates to an injection head for a gas turbine combustor.
  • combustors have been designed to produce hot gas by burning gaseous or liquid fuel which is delivered in a compressed air through one or more fuel nozzles.
  • One kind of combustor which proved to be effective comprises fuel nozzles arranged radially about a central axis and a fuel delivery system comprising nested fuel feed lines (at least one for each kind of fuel, but possibly two or more) with respective distributor rings and delivery pipes.
  • the delivery pipes extend radially inward from the distributor rings and have respective outer ends connected thereto.
  • the fuel nozzles may be provided at inner ends or on sidewalls of respective delivery pipes.
  • Fuel either gas or liquid, is supplied from the fuel feed lines to the distributor rings, that act as annular plena to equalize pressure and create uniform injection conditions at all the fuel nozzles.
  • connection of the outer ends of the delivery pipes to the distributor rings is quite complicate and expensive, however.
  • delivery pipes need to be individually connected and compensators are required at the outer end of each delivery pipe to damp vibrations and to accommodate stress caused by thermal expansion.
  • Compensators may be e.g. in the form of bellows applied between the distributor rings and the delivery pipes.
  • numerous additional components are necessary for the connections and corresponding welding seams must be accounted for, which may be critical under a mechanical standpoint and makes assembling process more complicate.
  • space required for the distributor rings, which extend around the burner does not allow to provide compact structures and size may be an issue.
  • US 2003/121266 A1 discloses an injection head for a gas turbine combustor that comprises an elongated body, a fuel inlet, extending about a central axis of the elongated body, a plurality of injector fingers extending radially outward from the elongated body plenum assembly and each provided with at least a respective fuel nozzle.
  • a cooling air housing partly encloses the fuel inlet. At least part of the fuel nozzles are fluidly coupled to the primary fuel plenum and to the cooling air plenum.
  • an injection head for a gas turbine combustor comprising:
  • the distribution of fuel to the fingers from the centre to the periphery requires a single connection point to feed the fuel plenum assembly. Accordingly, a single compensator system is to be provided to attenuate adverse effects of mechanical vibrations and thermal expansion. The overall structure is thus simplified, to the benefit of manufacturing process and cost.
  • the concentric structure of the first and second is compact and functional to the central feed system. Effective shielding air is also provided to prevent hot air ingestion.
  • the fuel inlet comprises a primary inlet line, fluidly coupled to the primary fuel plenum, and a secondary inlet line, fluidly coupled to the secondary fuel plenum and at least in part enclosed within the primary inlet line.
  • the injection unit comprises an air inlet line at least in part enclosing the primary inlet line and the secondary inlet line and fluidly coupled to the cooling air plenum.
  • the primary inlet line and the secondary inlet line extend radially between the fuel plenum assembly and the injection manifold.
  • Comact design is favoured by radial arrangement of the fuel inlet lines.
  • the primary inlet line and the secondary inlet line are aligned to a respective one of the injector fingers upstream in an axial direction.
  • the injector fingers are in the form of streamlined bodies with respective leading edges and trailing edges extending radially outward from the fuel plenum assembly and comprise at least an inlet injector finger configured to be coupled to an injection manifold, wherein the primary inlet line and the secondary inlet line are at least partially enclosed within the inlet injector finger.
  • the fuel inlet lines may be enclosed in one of the injector fingers, which therefore has also a fuel supply function for the whole injection head. Aerodynamic efficiency is improved by inclusion in the streamlined finger.
  • the injection head comprises a plurality of primary inlet lines, fluidly coupled to the primary fuel plenum, and of secondary inlet lines, fluidly coupled to the secondary fuel plenum at least in part enclosed within the respective primary inlet line, wherein the injector fingers comprise a plurality of inlet injector fingers, and wherein the primary inlet lines and the secondary inlet lines are at least partially enclosed within respective inlet injector fingers.
  • Flexible design is provided to meet design preferences, e.g. to further increase uniform conditions in the fuel plenum assembly, without significantly increasing complexity of the structure.
  • the primary inlet line and the secondary inlet line feed axially into the fuel plenum assembly.
  • the secondary fuel line tapers at a delivery end, whereby an annular space is provided between the primary fuel line and the respective secondary fuel line at the delivery end.
  • the primary fuel line has through openings at the delivery end, thereby fluidly coupling the shielding air line and the annular space between the primary fuel line and the respective secondary fuel line at the delivery end.
  • the injection head comprise spacers extending radially between the primary fuel line and the respective shielding air line at the delivery end and configured to allow the primary fuel line to axially slide with respect to the shielding air line.
  • the nozzle are thus designed to accommodate different thermal expansion of the primary and secondary fuel lines.
  • the injection unit comprises a compensator between the injection manifold and the injection head, the compensator being configured to allow relative movements of the injection head and of the injection manifold in an axial direction and/or in a radial direction.
  • a gas turbine combustor comprises a least an injection unit as defined above and an injection manifold coupled to the injection head.
  • Figure 1 shows a simplified view of a gas turbine assembly, designated as whole with numeral 1.
  • the gas turbine assembly 1 comprises a compressor section 2, a combustor assembly 3 and a turbine section 5.
  • the compressor section 2 and the turbine section 5 extend along a main axis M.
  • the combustor assembly 3 may be a single-stage combustor assembly or a sequential combustor assembly.
  • the combustor assembly 3 comprises a plurality of sequential can combustors 7, circumferentially arranged about the main axis M.
  • the compressor section 3 of the gas turbine assembly 1 provides a compressed airflow, which is added with fuel and burned in the can combustors 7.
  • the airflow delivered by the compressor section 2 is supplied to the combustor assembly 3 and to the turbine section 5 for the purpose of cooling.
  • the can combustors 7 are coupled to the turbine section 5 through respective transition ducts 8.
  • the can combustor 7 extends along a central axis A and comprises an outer shell 10, a liner 11 defining a flow path 12 for compressed air or hot gas and an injection unit 13 configured to deliver a controlled amount of fuel into air or hot gas in the flow path.
  • the can combustor 7 may be run on different kinds of fuel, depending on conditions. for example, the can combustor 7 may use a gas fuel as a primary fuel and a liquid fuel as a secondary fuel.
  • the injection unit 13 in turn comprises an injection manifold 14, coupled to fuel feed lines (here not shown) for receiving the primary fuel and the secondary fuel, and an injection head 15.
  • the injection manifold 14 is coupled to the injection head 15 through a compensator 17, which is configured to allow relative movements of the injection manifold 14 and of the injection head 15 in an axial direction and/or in a radial direction.
  • the compensator 17 allows to damp vibrations and accommodate thermal expansion and may be in the form of bellows and/or an axial slider.
  • the injection head 15, shown in figures 2 and 3 is arranged about the central axis A of the can combustor 7 and comprises a centre body 18 with a plurality of injector fingers 19, 20 that extend radially outward from the centre body 18 to the periphery of the flow path 12.
  • the injector fingers 19, 20 are arranged across the whole diameter of the flow path 12.
  • the injection head 15 may be a monolithic body obtained by additive manufacturing techniques, such as Selective Laser Melting (SLM).
  • SLM Selective Laser Melting
  • the great advantage of the additive techniques reside in that they are extremely flexible and allow to produce complex objects incorporating a wide variety of features.
  • the injection head can thus be built as a single body. This simplifies assembling of the injection unit, without limiting in any way functionality.
  • the injection head 15 may be formed by assembled parts connected e.g. by a central fixing assembly extending along the central axis A.
  • a cooling housing 21 and a fuel plenum assembly 22 are provided in the centre body 18 and both extend about the central axis A.
  • the cooling housing 21 is provided on an upstream side by an outer casing of the injection head 15 and defines an air plenum that at least partly encloses the fuel plenum assembly 22.
  • the fuel plenum assembly 22 comprises a primary fuel plenum 24 and a secondary fuel plenum 25, both of substantially annular shape about the central axis A.
  • the injector fingers 19, 20 are in the form of streamlined bodies with respective leading edges 19a, 20a and trailing edges 19b, 20b extending radially outward from the plenum assembly 22.
  • the injector fingers 19, 20 have straight trailing edges 19b, 20b.
  • the trailing edges 19b, 20b of the injector fingers 19, 20 may be curved, e.g. lobed, in accordance with design preferences.
  • the injector fingers here designated by numeral 20 (see also figure 5a ), has a special design and provides also a function of inlet for primary and secondary fuel and for shielding air.
  • the inlet injector finger 20 comprises a primary inlet line 27, fluidly coupled to the primary fuel plenum 24, and a secondary inlet line 28, fluidly coupled to the secondary fuel plenum 25 and at least in part enclosed within the primary inlet line 27.
  • the inlet injector finger 20 comprises an air inlet 29, which at least in part encloses the primary inlet line 27 and the secondary inlet line 28 and is fluidly coupled to the cooling air housing 21.
  • the primary inlet line 27 and the secondary inlet line 28 extend radially between the fuel plenum and the injection manifold. In this manner, the primary inlet line 27 and the secondary inlet line 28 are also aligned to the injector finger 20 upstream in an axial direction, to the benefit of uniform airflow. This is not mandatory, however, and inlet lines may not be aligned to any injector finger.
  • each fuel nozzle 30 (one of which is shown in detail in figures 6 to 9a, 9b ) has a respective primary fuel line fluidly 31 coupled to the primary fuel plenum 24, a respective secondary fuel line 32 fluidly coupled to the secondary fuel plenum 25 and a respective shielding air line 33 fluidly coupled to the cooling air housing 21.
  • Fuel nozzle 30 are oriented substantially parallel to the central axis A and discharge fuel in a downstream direction.
  • the fuel nozzle or nozzles of the inlet injector finger 20 may be directly coupled to the primary inlet line 27 and/or secondary inlet line 28, as shown in figure 5b .
  • some of the fuel nozzles 30 may be provided with the primary fuel line 31 only.
  • the primary fuel line 31, the secondary fuel line 32 and the shielding air line 33 are arranged coaxially, with the shielding air line 33 enclosing the primary fuel line 31 and the primary fuel line 31 in turn enclosing the secondary fuel line 32.
  • the primary fuel line fluidly 31, the secondary fuel line 32 and the shielding air line 33 extend substantially radially outward from the fuel plenum assembly 22 outside the nozzle 30 and substantially parallel to the central axis A inside the nozzle 30.
  • Arrangement of the primary fuel line 31, the secondary fuel line 32 and the shielding air line 33 does not need to be coaxial and mutual offset may be present to compensate for thermal expansion in accordance with design preferences.
  • the secondary fuel line 32 tapers at a delivery end 30a of the nozzle 30, so that an annular space 35 is provided between the primary fuel line 31 and the respective secondary fuel line 32.
  • the primary fuel line 31 has through openings 37 that fluidly couple the shielding air line 33 and the annular space 35.
  • the annular space 35 is open toward the outside, so that shielding air flowing through the openings 37 is discharged downstream. Accordingly, a first shielding airflow F1 is delivered around the primary fuel line 31 and a second shielding airflow F2 is delivered between the primary fuel line 31 and the secondary fuel line 32 ( figure 8 ).
  • Radial spacers 38 are provided between the primary fuel line 31 and the shielding air line 33 at the delivery end 30a of the nozzle 30.
  • the spacers 38 are integral with one of the primary fuel line 31 and the shielding air line 33 and axial sliding relative movement therebetween.
  • an injection unit has substantially the structure already described except in that an injection head 115 comprises a plurality of inlet injection fingers 120 equally spaced in a circumferential direction about the central axis A.
  • an injection head 115 comprises a plurality of inlet injection fingers 120 equally spaced in a circumferential direction about the central axis A.
  • three injection fingers 120 at 120° with respect to one another are provided.
  • the inlet injection fingers 120 include respective nested shielding air lines, primary inlet lines and secondary inlet lines as already described (here not shown for the sake of simplicity). In embodiments not illustrated herein, the inlet injection fingers 120 may not be equally spaced in the circumferential direction.
  • an injection head 215 of an injection unit 213 has substantially the structure of the injection head 15 of figure 3 , except in that primary fuel, secondary fuel and cooling air are supplied axially.
  • the primary inlet line 227 and the secondary inlet line 228 feed axially directly into the fuel plenum assembly
  • an injection manifold 214 is connected to the injection head 215 at the central axis and feeds directly into the primary fuel plenum 224 and the secondary fuel plenum 225.
  • Air inlet is axially arranged as well and encloses in part primary inlet line 227 and the secondary inlet line 228.
  • Inlet injector fingers with special design are not required in this case.

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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)

Claims (13)

  1. Injektionskopf für einen Gasturbinenbrenner, wobei der Injektionskopf (15; 115; 215) umfasst:
    eine Brennstoffverteileranordnung (22), die sich um die zentrale Achse (A) erstreckt und einen primären Brennstoffverteiler (24; 224) aufweist;
    mehrere Injektorfinger (19, 20; 120), die sich von der Brennstoffverteileranordnung (22) radial nach außen erstrecken und jeweils mit wenigstens einer entsprechenden Brennstoffdüse (30) versehen sind;
    einen Brennstoffeinlass (27, 28), der mit der Brennstoffverteileranordnung (22) in Fluidverbindung steht;
    ein Kühlluftgehäuse, das die Brennstoffverteileranordnung (22) wenigstens teilweise umschließt und einen Kühlluftverteiler (21) definiert;
    wobei wenigstens ein Teil der Brennstoffdüsen (30) entsprechende primäre Brennstoffleitungen (31) aufweist, die mit dem primären Brennstoffverteiler (24; 224) in Fluidverbindung stehen, und entsprechende Abschirmluftleitungen (33), die mit dem Kühlluftverteiler (21) in Fluidverbindung stehen;
    dadurch gekennzeichnet, dass die Brennstoffverteileranordnung (22) einen sekundären Brennstoffverteiler (25; 225) umfasst, der sich um die zentrale Achse (A) erstreckt und wenigstens teilweise von dem primären Brennstoffverteiler (24; 224) umschlossen ist, wobei ein Teil der Brennstoffdüsen (30) jeweilige sekundäre Brennstoffleitungen (32) aufweist, die wenigstens teilweise von den jeweiligen primären Brennstoffleitungen (31) umschlossen sind und mit dem sekundären Brennstoffverteiler (25; 225) in Fluidverbindung stehen, und wobei in jeder Brennstoffdüse (30) die jeweilige Abschirmluftleitung (33) die jeweilige primäre Brennstoffleitung (31) und die jeweilige sekundäre Brennstoffleitung (32) umschließt.
  2. Injektionskopf nach Anspruch 1, wobei der Brennstoffeinlass (27, 28) eine primäre Einlassleitung (27) umfasst, die mit dem primären Brennstoffverteiler (24; 224) in Fluidverbindung steht, und eine sekundäre Einlassleitung (28), die mit dem sekundären Brennstoffverteiler (25; 225) in Fluidverbindung steht und wenigstens teilweise von der primären Einlassleitung (27) umschlossen ist.
  3. Injektionskopf nach Anspruch 2, der einen Lufteinlass (29) umfasst, der wenigstens teilweise die primäre Einlassleitung (27) und die sekundäre Einlassleitung (28) umschließt und mit dem Kühlluftverteiler (21) in Fluidverbindung steht.
  4. Injektionskopf nach Anspruch 2 oder 3, wobei die primäre Einlassleitung (27) und die sekundäre Einlassleitung (28) radial zwischen der Brennstoffverteileranordnung (22) und dem Injektionsverteilerrohr (14; 214) verlaufen.
  5. Injektionskopf nach Anspruch 4, wobei die primäre Einlassleitung (27) und die sekundäre Einlassleitung (28) jeweils auf einen der Injektorfinger (19, 20; 120) stromaufwärts in axialer Richtung ausgerichtet sind.
  6. Injektionskopf nach Anspruch 5, wobei die Injektorfinger (19, 20; 120) die Form von stromlinienförmigen Körpern mit entsprechenden Vorderkanten (19a, 20a) und Hinterkanten (19b, 29b) aufweisen, die sich von der Brennstoffverteileranordnung (22) radial nach außen erstrecken, und wenigstens einen Injektorfinger (20) umfassen, der dazu konfiguriert ist, mit einem Injektionsverteilerrohr (14; 214) gekoppelt zu sein, wobei die primäre Einlassleitung (27) und die sekundäre Einlassleitung (28) wenigstens teilweise von dem Einlassinjektorfinger (20) umschlossen sind.
  7. Injektionskopf nach Anspruch 6, umfassend mehrere primäre Einlassleitungen (27), die mit dem primären Brennstoffverteiler (24; 224) in Fluidverbindung stehen, und sekundäre Einlassleitungen (28), die mit dem sekundären Brennstoffverteiler (25; 225) in Fluidverbindung stehen und wenigstens teilweise von der jeweiligen primären Einlassleitung (27) umschlossen sind, wobei die Injektorfinger (1; 20; 120) mehrere Einlassinjektorfinger (1; 20; 120) umfassen, und wobei die primären Einlassleitungen (27) und die sekundären Einlassleitungen (28) wenigstens teilweise von den jeweiligen Injektorfingern (19, 20; 120) umschlossen sind.
  8. Injektionskopf nach Anspruch 2 oder 3, wobei die primäre Einlassleitung (27) und die sekundäre Einlassleitung (28) axial in die Brennstoffverteileranordnung (22) einspeisen.
  9. Injektionskopf nach einem der vorangehenden Ansprüche, wobei sich die sekundäre Kraftstoffleitung (32) an einem Abgabeende (30a) verjüngt, wodurch ein ringförmiger Raum (35) zwischen der primären Kraftstoffleitung (31) und der jeweiligen sekundären Kraftstoffleitung (32) am Abgabeende (30a) bereitgestellt wird.
  10. Injektionskopf nach Anspruch 9, wobei die primäre Kraftstoffleitung (31) am Abgabeende (30a) Durchgangsöffnungen (37) aufweist, wodurch die Abschirmluftleitung (33) und der ringförmige Raum (35) zwischen der primären Kraftstoffleitung (31) und der jeweiligen sekundären Kraftstoffleitung (33) am Abgabeende (30a) in Fluidverbindung stehen.
  11. Injektionskopf nach Anspruch 9 oder 10, Abstandshalter (38) umfassend, die sich radial zwischen der primären Kraftstoffleitung (31) und der jeweiligen Abschirmluftleitung (33) am Abgabeende (30a) erstrecken und dazu konfiguriert sind, ein axiales Gleiten der primären Kraftstoffleitung (31) bezüglich der Abschirmluftleitung (33) zu ermöglichen.
  12. Injektionskopf nach einem der vorangehenden Ansprüche, einen Kompensator (17) zwischen dem Injektionsverteilerrohr (14; 214) und dem Injektionskopf (15; 115; 215) umfassend, wobei der Kompensator (17) dazu konfiguriert ist, relative Bewegungen des Injektionskopfes (15; 115; 215) und des Injektionsverteilerrohrs (14; 214) in axialer Richtung und/oder in radialer Richtung zu ermöglichen.
  13. Gasturbinenbrenner, der wenigstens einen Injektionskopf (15; 115; 215) nach einem der vorangehenden Ansprüche und ein mit dem Injektionskopf (15; 115; 215) gekoppeltes Injektionsverteilerrohr (14; 214) umfasst.
EP19219662.4A 2018-12-25 2019-12-24 Einspritzkopf für eine gasturbinenbrennkammer Active EP3674608B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2018146134A RU2769616C2 (ru) 2018-12-25 2018-12-25 Инжекционная головка для камеры сгорания газовой турбины

Publications (2)

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EP3674608A1 EP3674608A1 (de) 2020-07-01
EP3674608B1 true EP3674608B1 (de) 2022-12-07

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CN (1) CN111380075B (de)
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EP3076084B1 (de) * 2015-03-30 2021-04-28 Ansaldo Energia Switzerland AG Kraftstoffinjektorvorrichtung
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Publication number Publication date
EP3674608A1 (de) 2020-07-01
CN111380075B (zh) 2023-04-18
RU2018146134A3 (de) 2022-02-15
RU2769616C2 (ru) 2022-04-04
RU2018146134A (ru) 2020-06-25
CN111380075A (zh) 2020-07-07

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