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EP2589875B1 - Appareil d'injection - Google Patents

Appareil d'injection Download PDF

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Publication number
EP2589875B1
EP2589875B1 EP12190273.8A EP12190273A EP2589875B1 EP 2589875 B1 EP2589875 B1 EP 2589875B1 EP 12190273 A EP12190273 A EP 12190273A EP 2589875 B1 EP2589875 B1 EP 2589875B1
Authority
EP
European Patent Office
Prior art keywords
injection
injection hole
annular base
injection apparatus
tubular body
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.)
Not-in-force
Application number
EP12190273.8A
Other languages
German (de)
English (en)
Other versions
EP2589875A1 (fr
Inventor
Lucas John Stoia
Patrick Benedict Melton
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2589875A1 publication Critical patent/EP2589875A1/fr
Application granted granted Critical
Publication of EP2589875B1 publication Critical patent/EP2589875B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation

Definitions

  • the subject matter disclosed herein relates to an injection apparatus and, more particularly, to an injection apparatus for attachment to an outer vessel disposed about an inner vessel formed to define a main flowpath.
  • a typical turbomachine such as a gas turbine engine, includes a compressor, a combustor and a turbine.
  • the compressor compresses inlet gas to produce compressed gas, which is transmitted to the combustor.
  • the compressed gas is mixed with fuel and combusted to produce high temperature fluids. These high temperature fluids are then directed to the turbine for power and/or electricity generation.
  • a transition piece may be disposed between the combustor and the turbine such that the high temperature fluids flow through the transition piece prior to entering the turbine.
  • LLI late lean injection
  • US 7000396 describes a combustor for a gas turbine including a combustor body having an aperture and a casing enclosing the combustor body and defining a passageway therebetween for carrying compressor discharge air. At least one injection tube supplies an amount of the compressor discharge air into the combustor body and the injection tube is disposed between the aperture and through the casing. A collar having a plurality of openings is disposed at the passageway and surrounds the injection tube so that the injection tube passes through the collar. A gap is disposed between the collar and the injection tube.
  • an injection apparatus 10 is provided.
  • the injection apparatus 10 is attachable to an outer vessel 11, such as an impingement sleeve or a flow sleeve of an exemplary turbomachine transition piece.
  • the outer vessel 11 may be disposed about an inner vessel 12, which may be the turbomachine transition piece and may be formed to define a main flowpath 120.
  • high temperature fluids are produced in a combustor and directed toward a turbine by way of the turbomachine transition piece. The flow of the high temperature fluids thus proceeds along the main flowpath 120 of the inner vessel 12. It is, however, to be understood that the injection apparatus 10 may be attachable to other vessels in the turbomachine and/or other systems.
  • the injection apparatus 10 may be attachable to a forward end of the impingement sleeve (i.e., proximate to the axial injection flow sleeve), the aft end of the impingement sleeve or to a flow sleeve of the combustor.
  • the injection apparatus 10 includes a ring-shaped or annular base 20 and a tubular body 40.
  • the annular base 20 is configured to be fastened to the outer vessel 11 by one or more of bolting, welding, sealing and butt welding.
  • the annular base 20 has a first surface 21 that is formed to define an injection hole location 200 and a protrusion 25.
  • the protrusion 25 protrudes from an interior facing surface 26 of the annular base 20 and extends perimetrically about the injection hole location 200 such that the protrusion 25 is axisymmetric about a centerline of the inner vessel 12.
  • the protrusion 25 includes a first part 27 and a connector 30.
  • the first part 27 protrudes from the interior facing surface 26 such that the first part 27 is axisymmetric about the centerline of the inner vessel 12.
  • the connector 30 has a first end 31, which is configured to be fastened by, for example, welding to a distal end of the protrusion 25 perimetrically about the injection hole location 200, and a second end 32.
  • the first end 31 and the second end 32 supportively meet at bend 33, which may be angular or curved, such that the second end 32 defines a secondary injection hole location 201, which may correspond to the injection hole location 200.
  • the injection hole location 200 and the secondary injection hole location 201 may be round or, in some cases, substantially circular.
  • the protrusion 25, the connector 30 and the tubular body 40 may also have round or, in some cases, substantially circular cross-sections (i.e., they may be ring-shaped) in correspondence with the shape of the injection hole location 200 and the secondary injection hole location 201.
  • the tubular body 40 has sufficient length to extend across an annulus defined between the outer vessel 11 and the inner vessel 12 and has an interior facing surface 41 that is formed to define a tubular injection hole 400.
  • the tubular body 40 is sealably fastened to the first surface 21 of the annular base 20 at the injection hole location 200 by way of, for example, bolt 42 that engages with the annular base 20.
  • the tubular body 40 also has a protrusion 45 that may be sealably fastened to the second end 32 of the connector 30 at the secondary injection hole location 201. Seals 46, such as o-rings or c-seals, may be sealably disposed between the tubular body 40 and the first surface 21 and between the protrusion 45 and the second end 32 of the connector 30.
  • the tubular injection hole 400 permits fluid communication between an exterior of the outer vessel 11 and the main flowpath 120.
  • the tubular body 40 may include a flange 47.
  • the annular base 20 may include an exterior facing surface 28 that faces radially outwardly and away from the main flowpath 120. This exterior facing surface 28 may have a fastening surface 280 formed thereon at the injection hole location 200 where the exterior facing surface 28 is machined to be flat and/or smooth and therefore configured for mating with the flange 47.
  • bolt 42 is employed to fasten the tubular body 40 to the annular base 20, the bolt 42 extends through both the flange 47 and the fastening surface 280 of the exterior facing surface 28.
  • the tubular body 40, the connector 30, the protrusion 25 and the annular base 20 may cooperatively define a plenum 50.
  • the tubular body 40 is further formed to define an additional injection hole 401 for permitting fluid communication between an interior of the plenum 50 and the tubular injection hole 400.
  • the additional injection hole 401 may be defined as a plurality of additional injection holes 401, which are arrayed about the tubular injection hole 400 of the tubular body 40 at the plenum 50. Separation between adjacent additional injection holes 401 may be uniform or non-uniform.
  • the plenum 50 may be supplied with fuel and the exterior of the outer vessel 11 may include compressed air, such as compressor discharge air that is produced by a compressor of the turbomachine.
  • the compressed air flows through the tubular injection hole 400 and entrains a flow of the fuel from the plenum 50 into the tubular injection hole 400.
  • the fuel is thereby mixed with the compressed air and injected into the main flowpath 120 as a fuel/air mixture.
  • the injection apparatus 10 may be employed as part of an axially staged injection system of a turbomachine or, more particularly, as part of a late lean injection (LLI) system of the turbomachine.
  • the fuel/air mixture may be lean such that combustion of the fuel/air mixture within the main flowpath 120 serves to reduce the production and subsequent emission of pollutants, such as oxides of nitrogen (NOx).
  • NOx oxides of nitrogen
  • the annulus defined between the outer vessel 11 and the inner vessel 12 is generally supported by support structures 60, such as a-spacers arrayed about the inner vessel 12.
  • these support structures 60 may be disposed between an exterior facing surface of the inner vessel 12 and the interior facing surface 26 of the annular base 20.
  • the injection hole location 200 (and the accompanying structures as described above) may be provided as a plurality of injection hole locations 200.
  • the plural injection hole locations 200 may be arrayed about the outer vessel 11 and the inner vessel 12 as non-axisymmetric features. Separation between adjacent injection hole locations 200 may be uniform or non-uniform.
  • four injection hole locations 200 may be clustered about respective lower portions of the outer vessel 11 and the inner vessel 12.

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 (13)

  1. Un appareillage d'injection, comprenant :
    une base annulaire (20) ménageant un endroit pour un orifice d'injection (200) et ayant une protubérance (25) autour de l'endroit de l'orifice d'injection (200) ; ladite protubérance (25) s'étendant de la surface tournée vers l'intérieur (26) de la base annulaire (20) et sur le périmètre autour de l'endroit de l'orifice d'injection (200) ;
    un connecteur (30) ayant une première extrémité (31) fixée à une extrémité distale de la protubérance (25) sur le périmètre autour de l'endroit de l'orifice d'injection troué (200) et une seconde extrémité (32) ; et
    un corps tubulaire (40) formé pour définir un orifice d'injection (400), le corps tubulaire (40) étant fixé de manière étanche à la base annulaire (20) à l'endroit de l'orifice d'injection (200) et ayant une protubérance (45) fixée de manière étanche à la seconde extrémité (32) du connecteur (30) ; dans lequel
    le corps tubulaire (40), le connecteur (30), la protubérance (25) de la base annulaire (20) et la base annulaire (20) coopèrent pour définir un plenum (50) qui est en communication avec l'orifice d'injection (400).
  2. L'appareillage d'injection selon la revendication 1, dans lequel la base annulaire (20) inclut une surface tournée vers l'extérieur (28) ayant une surface de fixation (280) formée dessus à l'endroit de l'orifice d'injection (200).
  3. L'appareillage d'injection selon la revendication 1 ou 2 comprenant en outre des joints (46) disposés entre le corps tubulaire (40) et la base annulaire (20) et entre le connecteur (30) et la protubérance (45) du corps tubulaire (40).
  4. L'appareillage d'injection selon une quelconque des revendications 1 à 3, dans lequel le corps tubulaire est en outre formé pour définir une pluralités d'orifices d'injection additionnels (401) configurés pour une communication fluidique entre un intérieur du plenum (50) et l'orifice d'injection (400).
  5. L'appareillage d'injection selon la revendication 4, dans lequel les orifices d'injection additionnels (401) sont alignés le long d'une circonférence de l'orifice d'injection (400) défini par le corps tubulaire (40).
  6. L'appareillage d'injection selon une quelconque des revendications 1 à 5, comprenant en outre une enceinte extérieure (11) disposée autour d'un enceinte intérieure (12) formé pour définir un trajet de flux principal (120), où la base annulaire (20) est fixée à l'enceinte extérieure (11) et l'orifice d'injection (400) permet la communication entre un extérieur de l'enceinte extérieure (11) et le trajet de flux principal (120).
  7. L'appareillage d'injection selon la revendication 6, dans lequel l'enceinte extérieure (11) comprend un manchon de heurt d'une pièce de transition de turbomachine.
  8. L'appareillage d'injection selon la revendication 6 ou 7, dans lequel le plenum (50) est alimenté en carburant et l'extérieur de l'enceinte extérieure (11) comprend de l'air comprimé.
  9. L'appareillage d'injection selon une quelconque des revendications 6 à 8, dans lequel la base annulaire (20) est fixée à l'enceinte extérieure (11) par l'un ou l'autre d'un vissage, soudage, scellement et soudage bout-à-bout.
  10. L'appareillage d'injection selon une quelconque des revendications 6 à 9, comprenant en outre des structures supports (60) pour monter la base annulaire (20) sur l'enceinte interne (12).
  11. L'appareillage d'injection selon une quelconque des revendications précédentes, comprenant en outre une pluralité d'orifices d'injection (200) définis dans la base annulaire (20).
  12. L'appareillage d'injection selon la revendication 11, dans lequel les endroits des orifices d'injection (200) sont non uniformément séparés l'un de l'autre.
  13. L'appareillage d'injection selon la revendication 11, dans lequel les endroits des orifices d'injection (200) sont groupés.
EP12190273.8A 2011-11-01 2012-10-26 Appareil d'injection Not-in-force EP2589875B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/286,744 US20130104553A1 (en) 2011-11-01 2011-11-01 Injection apparatus

Publications (2)

Publication Number Publication Date
EP2589875A1 EP2589875A1 (fr) 2013-05-08
EP2589875B1 true EP2589875B1 (fr) 2014-12-10

Family

ID=47172421

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12190273.8A Not-in-force EP2589875B1 (fr) 2011-11-01 2012-10-26 Appareil d'injection

Country Status (3)

Country Link
US (1) US20130104553A1 (fr)
EP (1) EP2589875B1 (fr)
CN (1) CN103090412A (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9097130B2 (en) * 2012-09-13 2015-08-04 General Electric Company Seal for use between injector and combustion chamber in gas turbine
US20150052905A1 (en) * 2013-08-20 2015-02-26 General Electric Company Pulse Width Modulation for Control of Late Lean Liquid Injection Velocity
WO2015030927A1 (fr) 2013-08-30 2015-03-05 United Technologies Corporation Passages de dilution profilés pour chambre à combustion de turbine à gaz
US20160047317A1 (en) * 2014-08-14 2016-02-18 General Electric Company Fuel injector assemblies in combustion turbine engines
US20170268783A1 (en) * 2016-03-15 2017-09-21 General Electric Company Axially staged fuel injector assembly mounting
US10816203B2 (en) * 2017-12-11 2020-10-27 General Electric Company Thimble assemblies for introducing a cross-flow into a secondary combustion zone
US11137144B2 (en) 2017-12-11 2021-10-05 General Electric Company Axial fuel staging system for gas turbine combustors
US12066188B2 (en) * 2021-03-26 2024-08-20 Rtx Corporation Modular injector bolt for an engine
US12072101B2 (en) 2022-02-18 2024-08-27 Rtx Corporation Fuel injector with splash plate for an engine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20010049932A1 (en) * 1996-05-02 2001-12-13 Beebe Kenneth W. Premixing dry low NOx emissions combustor with lean direct injection of gas fuel
US7000396B1 (en) * 2004-09-02 2006-02-21 General Electric Company Concentric fixed dilution and variable bypass air injection for a combustor
FR2919672B1 (fr) * 2007-07-30 2014-02-14 Snecma Injecteur de carburant dans une chambre de combustion de turbomachine
US7665309B2 (en) * 2007-09-14 2010-02-23 Siemens Energy, Inc. Secondary fuel delivery system
US8261554B2 (en) * 2008-09-17 2012-09-11 General Electric Company Fuel nozzle tip assembly
US8701383B2 (en) * 2009-01-07 2014-04-22 General Electric Company Late lean injection system configuration
US8701382B2 (en) * 2009-01-07 2014-04-22 General Electric Company Late lean injection with expanded fuel flexibility
US8281594B2 (en) * 2009-09-08 2012-10-09 Siemens Energy, Inc. Fuel injector for use in a gas turbine engine
US8991192B2 (en) * 2009-09-24 2015-03-31 Siemens Energy, Inc. Fuel nozzle assembly for use as structural support for a duct structure in a combustor of a gas turbine engine

Also Published As

Publication number Publication date
US20130104553A1 (en) 2013-05-02
EP2589875A1 (fr) 2013-05-08
CN103090412A (zh) 2013-05-08

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