EP3067626A1 - Écran d'air pour un injecteur de carburant d'une chambre de combustion - Google Patents

Écran d'air pour un injecteur de carburant d'une chambre de combustion Download PDF

Info

Publication number
EP3067626A1
EP3067626A1 EP16158421.4A EP16158421A EP3067626A1 EP 3067626 A1 EP3067626 A1 EP 3067626A1 EP 16158421 A EP16158421 A EP 16158421A EP 3067626 A1 EP3067626 A1 EP 3067626A1
Authority
EP
European Patent Office
Prior art keywords
inlet
air shield
neck
section
channel
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.)
Withdrawn
Application number
EP16158421.4A
Other languages
German (de)
English (en)
Inventor
Reena Bhagat
Jun Cai
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 EP3067626A1 publication Critical patent/EP3067626A1/fr
Withdrawn legal-status Critical Current

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
    • F23R3/28—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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/26—Controlling the air flow

Definitions

  • the field of the disclosure relates generally to a fuel injector for a combustor of a rotary machine, and more particularly to an air shield to control air flow to a fuel injector.
  • At least some known combustors used with rotary machines, such as gas turbines include at least one secondary fuel injector, often referred to as a "late lean injector," located downstream from a primary fuel nozzle. At least some known late lean injectors mix a fuel supply with a supply of air, such as from a compressor discharge casing. However, if the supply of air includes low velocity or recirculation zones, unintended flameholding at the late lean injector may result.
  • an air shield for an injector of a combustor includes a first section that extends axially from a first end to a second end.
  • the first section includes at least one side wall and a top wall.
  • the at least one side wall and the top wall at least partially define a channel configured to distribute a channel airflow to the injector.
  • the air shield also includes at least one first inlet defined through the at least one side wall and at least one second inlet defined through the top wall.
  • the at least one first inlet and the at least one second inlet are configured to receive a portion of a surrounding airflow to at least partially form the channel airflow.
  • a combustor for a gas turbine in another aspect, includes a liner that defines a primary combustion zone, a sleeve that substantially circumscribes the liner, a secondary combustion zone downstream from, and in flow communication with, the first combustion zone, and an injector coupled to the sleeve upstream from the secondary combustion zone.
  • the injector includes at least one transfer tube in flow communication with the primary combustion zone.
  • the combustor also includes an air shield coupled to the sleeve.
  • the air shield includes a first section that extends axially from a first end to a second end.
  • the first section includes at least one side wall and a top wall.
  • the at least one side wall and the top wall at least partially define a channel configured to distribute a channel airflow to the injector.
  • the air shield also includes at least one first inlet defined through the at least one side wall and at least one second inlet defined through the top wall. The at least one first inlet and the at least one second inlet are configured to receive a portion of a surrounding airflow of the combustor to at least partially form the channel airflow.
  • the exemplary systems and methods described herein overcome at least some of the disadvantages associated with known late lean injectors for combustors of rotary machines.
  • the embodiments described herein include an air shield configured to cover a late lean injector.
  • the air shield defines a channel that provides an airflow to the late lean injector.
  • the airflow enters the channel through at least one first inlet defined in a side wall of the air shield, and through at least one second inlet defined in a top wall of the air shield.
  • the first and second inlets cooperate to reduce low velocity and/or recirculation zones and improve flow uniformity through the late lean injector.
  • the air shield may enclose at least a portion of a fuel supply line to the late lean injector.
  • first, second, etc. are used herein merely as labels, and are not intended to impose ordinal, positional, or hierarchical requirements on the items to which these terms refer. Moreover, reference to, e.g., a “second” item does not require or preclude the existence of, e.g., a "first” or lower-numbered item, and/or, e.g., a "third" or higher-numbered item.
  • FIG. 1 is a schematic view of an exemplary gas turbine 10 in which embodiments of the air shield of the current disclosure may be used.
  • gas turbine 10 includes an intake section 12, a compressor section 14 coupled downstream from intake section 12, a combustor section 16 coupled downstream from compressor section 14, and a turbine section 18 coupled downstream from combustor section 16.
  • Turbine section 18 is coupled to compressor section 14 via a rotor shaft 17. It should be noted that, as used herein, the term “couple” is not limited to a direct mechanical, electrical, and/or communication connection between components, but may also include an indirect mechanical, electrical, and/or communication connection between multiple components.
  • intake section 12 channels air towards compressor section 14.
  • Compressor section 14 compresses the air to a higher pressure and temperature and discharges the compressed air towards combustor section 16.
  • the compressed air is mixed with fuel and ignited to generate combustion gases that are channeled towards turbine section 18.
  • combustor section 16 includes at least one combustor 20, in which a fuel, for example, natural gas and/or fuel oil, is injected into the air flow, and the fuel-air mixture is ignited to generate high temperature combustion gases that are channeled towards turbine section 18.
  • a fuel for example, natural gas and/or fuel oil
  • Turbine section 18 converts the thermal energy from the combustion gas stream to mechanical rotational energy, as the combustion gases impart rotational energy to at least one rotor blade 19 coupled to rotor shaft 17 within turbine section 18.
  • Rotor shaft 17 may be coupled to a load (not shown) such as, but not limited to, an electrical generator and/or a mechanical drive application.
  • the exhausted combustion gases exit turbine section 18.
  • FIG. 2 is a schematic section view of an exemplary embodiment of combustor 20 that may be used with gas turbine 10.
  • combustor 20 may be any suitable combustor that enables embodiments of the present disclosure to function as described herein.
  • combustor 20 includes a head end 22.
  • a liner 24 extends axially, with respect to a longitudinal axis 40 of combustor 20, from head end 22 to an opposite aft end 46.
  • Liner 24 is substantially circumscribed by a sleeve 26.
  • a forward portion 45 of sleeve 26 proximate to head end 22 is circumscribed by a sleeve housing 30.
  • Liner 24 also extends circumferentially about longitudinal axis 40 to generally define a primary combustion zone 23.
  • a secondary combustion zone 33 extends downstream from, and is in flow communication with, primary combustion zone 23.
  • Head end 22 includes a plurality of primary fuel nozzles 21 that are configured to mix fuel and air in any suitable fashion for combustion within primary combustion zone 23.
  • the combustion of the mixture of fuel and air in primary combustion zone 23 produces combustion gases that flow into secondary combustion zone 33 and are channeled towards turbine section 18 (shown in FIG. 1 ).
  • Combustor 20 also includes at least one secondary, or late lean, injector 32.
  • each at least one late lean injector 32 is coupled to sleeve 26 upstream from secondary combustion zone 33.
  • the at least one late lean injector 32 is a plurality of late lean injectors 32 that are spaced circumferentially around liner 24.
  • Each at least one late lean injector 32 receives fuel from a corresponding fuel supply line 29.
  • each fuel supply line 29 extends generally axially along a radially outer surface of sleeve housing 30 and a radially outer surface of sleeve 26 to the corresponding late lean injector 32.
  • fuel supply line 29 may be at least partially defined within at least one of sleeve housing 30 and sleeve 26. Additionally or alternatively, fuel supply line 29 may be at least partially offset radially outwardly from at least one of sleeve housing 30 and sleeve 26.
  • Each at least one late lean injector 32 is configured to mix fuel delivered from fuel supply line 29 and air drawn from an airflow 44 that surrounds combustor 20.
  • surrounding airflow 44 is a compressed air flow supplied from compressor section 14 (shown in FIG. 1 ).
  • each at least one late lean injector 32 includes at least one transfer tube 34 that is in flow communication with primary combustion zone 23.
  • the at least one late lean injector 32 is configured to inject the mixed fuel and air through the at least one transfer tube 34 into primary combustion zone 23.
  • the fuel injected by the at least one late lean injector 32 is combusted in secondary combustion zone 33.
  • Each at least one late lean injector 32 may be of any suitable design to enable combustor 20 to function as described herein.
  • the at least one late lean injector 32 may be at least one of a bell-mouth injector, a tube-in-tube injector, a swirl injector, a rich catalytic injector, and a shower-head type multi-tube injector.
  • FIG. 3 is a perspective view of a first exemplary embodiment of an air shield 100 coupled to combustor 20.
  • the at least one late lean injector 32 is a plurality of four circumferentially spaced late lean injectors 32, and a corresponding plurality of four circumferentially spaced air shields 100 is coupled to combustor 20 such that each air shield 100 covers a corresponding late lean injector 32.
  • the at least one late lean injector 32 is any suitable number of circumferentially spaced late lean injectors 32, and a corresponding plurality of circumferentially spaced air shields 100 is coupled to combustor 20 such that each air shield 100 covers a corresponding late lean injector 32.
  • each air shield 100 is formed from a partially transparent plastic material. In alternative embodiments, air shield 100 may be formed from any suitable material.
  • Each air shield 100 includes a first section 102 that extends axially from a first end 101, configured to be disposed proximate the corresponding late lean injector 32, to a second end 103, configured to be disposed proximate sleeve housing 30.
  • each air shield 100 extends circumferentially along combustor 20 for a maximum distance of about one times to about three times a diameter of the corresponding late lean injector 32.
  • each air shield 100 extends circumferentially along combustor 20 for a maximum distance of about two times the diameter of the corresponding late lean injector 32.
  • each air shield 100 extends circumferentially along combustor 20 for a maximum distance of greater than about three times the diameter of the corresponding late lean injector 32.
  • Air shield 100 at least partially defines a channel 112 when air shield 100 is coupled to combustor 20.
  • Channel 112 is configured to receive a channel airflow 144 that is a portion of surrounding airflow 44, and to distribute channel airflow 144 to late lean injector 32.
  • first section 102 is coupled to sleeve 26, and air shield 100 also includes a second section 104 coupled to sleeve housing 30. Second section 104 is in flow communication with first section 102. In alternative embodiments, second section 104 may be omitted. Also in the illustrated embodiment, first section 102 includes a neck 106 proximate to second end 103 and a pair of shoulder regions 108 that extend from neck 106. In the illustrated embodiment, first section 102 also includes a dome region 110 proximate first end 101, such that dome region 110 is configured to be disposed radially outwardly from late lean injector 32. Neck 106, pair of shoulder regions 108, dome region 110, and other portions of first section 102 are shaped in any suitable fashion that enables channel 112 to distribute a predetermined channel airflow 144 to late lean injector 32.
  • FIG. 4 is a schematic section view of a first particular embodiment of late lean injector 32 covered by air shield 100, as shown in FIG. 3 .
  • late lean injector 32 includes a bell-mouth air inlet 114, in addition to a central spindle inlet 146.
  • Channel airflow 144 approaches bell-mouth air inlet 114 within channel 112 from second end 103.
  • air shield 100 may be used with any suitable late lean injector 32, and is not limited to use with the particular embodiment of late lean injector 32 shown in FIG. 4 .
  • a perimeter of a rim 118 of inlet 114 is generally circular in the illustrated embodiment, it should be understood that the perimeter of rim 118 may have other suitable shapes.
  • late lean injector 32 includes spindle inlet 146 in the illustrated embodiment, certain other embodiments of late lean injector 32 do not include spindle inlet 146.
  • FIG. 5 is another perspective view of air shield 100.
  • air shield 100 includes at least one side wall 105 that extends generally radially outwardly, with respect to longitudinal axis 40, from sleeve 26 of combustor 20.
  • the at least one side wall 105 includes a pair of opposing side walls 105 that each extend from second end 103 to first end 101, and that are connected at first end 101 by an end wall 111 of channel 112.
  • the at least one side wall 105 includes any suitable number of side walls 105 having any suitable configuration that enables air shield 100 to function as described herein.
  • Air shield 100 also includes a top wall 107 that extends generally circumferentially, with respect to longitudinal axis 40, from the at least one sidewall 105.
  • top wall 107 extends between the pair of opposing side walls 105 to define a top wall of channel 112, while sleeve 26 defines a bottom wall of channel 112.
  • top wall 107 has any suitable configuration that enables air shield 100 to function as described herein.
  • Air shield 100 further includes at least one first inlet 120 defined through side wall 105 of first section 102, and at least one second inlet 122 defined through top wall 107 of first section 102.
  • the at least one first inlet 120 and the at least one second inlet 122 are each configured to receive a portion of surrounding airflow 44 of combustor 20 to at least partially form channel airflow 144.
  • each first inlet 120 and second inlet 122 is located generally proximate second end 103.
  • each first inlet 120 and second inlet 122 is located on at least one of neck 106 and shoulder regions 108.
  • at least one first inlet 120 and/or second inlet 122 is located other than generally proximate second end 103.
  • the at least one first inlet 120 includes an opposing pair of first inlets 120 each defined along one of pair of shoulder regions 108.
  • the size and position of the pair of first inlets 120 on opposite shoulder regions 108 is configured to direct channel airflow 144 in a generally axial direction defined from second end 103 towards first end 101 of first section 102.
  • the at least one first inlet 120 includes any suitable number of first inlets 120 each positioned at any suitable location on side wall 105 that enables air shield 100 to function as described herein.
  • a location of air shield 100 on combustor 20 relative to a source of surrounding airflow 44 inhibits first inlets 120 from providing a suitable channel airflow 144.
  • the source of surrounding airflow 44 is located below combustor 20.
  • a downward facing shoulder region 108 of each of the two uppermost air shields 100 is subject to a different pressure as compared to a respective upward facing shoulder region 108 of each of the two uppermost air shields 100.
  • the at least one second inlet 122 is configured to reduce or eliminate the potential for recirculation zones and/or low velocity within channel 112 of air shield 100.
  • the at least one second inlet 122 includes at least one top window 124 defined in top wall 107 along neck 106 of first section 102. At least one of a size and a position of the at least one top window 124 is configured to enhance the component of channel airflow 144 that flows in the axial direction defined from second end 103 towards first end 101 of first section 102. For example, in the exemplary embodiment shown in FIG.
  • the at least one second inlet 122 includes a single top window 124 defined in top wall 107 along neck 106 of first section 102, and the single top window 124 is centered with respect to opposing shoulder regions 108 to facilitate equalizing a potential pressure difference within channel 112 between opposing first inlets 120.
  • a size of top window 124 relative to a size of the at least one first inlet 120 is selected to reduce non-axial components of channel airflow 144 as it approaches late lean injector 32.
  • each air shield 100 is configured to enclose at least a portion of the corresponding fuel supply line 29.
  • air shield 100 is configured to protect fuel supply line 29 from damage during at least one of shipping, installation, and maintenance of the combustor.
  • air shield 100 may have a suitable strength and stiffness to absorb accidental impacts that otherwise potentially could damage fuel supply line 29.
  • air shield 100 is not configured to enclose at least a portion of the corresponding fuel supply line 29.
  • FIG. 6 is a perspective view of a second exemplary embodiment of air shield 100 that is substantially similar to the embodiment of FIG. 5 in most respects, and similar features are given the same reference numbers.
  • the at least one second inlet 122 includes a pair of top windows 124 defined in top wall 107 along neck 106 of first section 102.
  • At least one of a size and a position of the pair of top windows 124 on top wall 107 along neck 106 is configured, for example, to enhance the component of channel airflow 144 that flows in the axial direction defined from second end 103 towards first end 101 of first section 102.
  • pair of top windows 124 is centered with respect to opposing shoulder regions 108 to facilitate equalizing a potential pressure difference within channel 112 between opposing first inlets 120.
  • a size of pair of top windows 124 relative to a size of the at least one first inlet 120 is selected to reduce non-axial components of channel airflow 144 as it approaches late lean injector 32.
  • a central portion 109 of top wall 107 between the pair of top windows 124 remains intact, facilitating increased protection of fuel line 29.
  • FIG. 7 is a perspective view of a third exemplary embodiment of air shield 100 that is substantially similar to the embodiment of FIG. 5 in most respects, and similar features are given the same reference numbers.
  • the at least one second inlet 122 includes a plurality of neck apertures 128 defined in top wall 107 along neck 106 of first section 102.
  • at least one of a size and a position of the plurality of neck apertures 128 on top wall 107 along neck 106 is configured, for example, to enhance the component of channel airflow 144 that flows in the axial direction defined from second end 103 towards first end 101 of first section 102.
  • plurality of neck apertures 128 is centered with respect to opposing shoulder regions 108 to facilitate equalizing a potential pressure difference within channel 112 between opposing first inlets 120.
  • a size of plurality of neck apertures 128 relative to a size of the at least one first inlet 120 is selected to reduce non-axial components of channel airflow 144 as it approaches late lean injector 32.
  • a central portion 109 of top wall 107 between the each of the plurality of neck apertures 128 remains intact, facilitating increased protection of fuel line 29.
  • the at least one second inlet 122 further includes a plurality of shoulder apertures 126 defined in top wall 107 proximate shoulder regions 108 of first section 102.
  • the plurality of shoulder apertures 126 includes a pair of shoulder apertures 126 each defined on a corresponding shoulder region. At least one of a size and a position of shoulder apertures 126 is configured to receive a portion of channel airflow 144 into channel 112 near shoulder regions 108 such that a tendency of channel airflow 144 to separate near shoulder regions 108 is reduced or eliminated.
  • the at least one second inlet 122 does not include shoulder apertures 126.
  • the at least one second inlet 122 includes any suitable number of second inlets 122, such as but not limited to any suitable number of top windows 124, shoulder apertures 126, and/or neck apertures 128, each positioned at any suitable location on top wall 107 that enables air shield 100 to function as described herein.
  • first section 102 includes a telescoping portion 134 at second end 103 that is configured to extend at least partially over second section 104. More specifically, telescoping portion 134 is configured for sliding movement over second section 104 in a direction generally parallel to longitudinal axis 40 of combustor 20, such that air shield 100 accommodates relative motion parallel to longitudinal axis 40 between sleeve 26 and sleeve housing 30. For example, in certain embodiments, upon initiation of operation of gas turbine 10, sleeve 26 expands axially towards head end 22 relative to sleeve housing 30. Because first section 102 is coupled to sleeve 26, first section 102 moves towards second section 104.
  • Telescoping portion 134 slides over second section 104 towards head end 22 to maintain an integrity of channel 112.
  • sleeve 26 retracts axially from sleeve housing 30, and telescoping portion 134 slides over second section 104 away from head end 22 to maintain an integrity of channel 112.
  • first section 102 does not include telescoping portion 134.
  • second section 104 includes an aperture 130 configured to receive fuel line 29.
  • aperture 130 also is configured to receive a portion of surrounding airflow 44 into channel 112 to at least partially form channel airflow 144.
  • aperture 130 is configured to receive fuel line 29 such that little or none of channel airflow 144 is received through aperture 130.
  • second section 104 does not include aperture 130.
  • method 800 includes disposing 802 a first end, such as first end 101, of a first section of an air shield, such as first section 102 of air shield 100, proximate an injector, such as late lean injector 32.
  • Method 800 also includes disposing 804 a second end, such as second end 103, of the air shield upstream of the first end.
  • Method 800 further includes coupling 806 the air shield to a sleeve, such as sleeve 26, such that a channel, such as channel 112, is defined.
  • the channel is configured to distribute a channel airflow, such as channel airflow 144, to the injector.
  • the channel includes at least one first inlet, such as the at least one first inlet 120, defined through at least one side wall of the first section, such as the at least one side wall 105, and at least one second inlet, such as the at least one second inlet 122, defined through a top wall of the first section, such as top wall 107.
  • the at least one first inlet and the at least one second inlet are configured to receive a portion of a surrounding airflow of the combustor to at least partially form the channel airflow.
  • an air shield configured to cover a late lean injector of a combustor are described above in detail.
  • the embodiments provide an advantage in reducing low velocity and/or recirculation zones and improving flow uniformity through the late lean injector.
  • embodiments of the air shield include at least one first inlet defined in a side wall of the air shield and at least one second inlet defined in a top wall of the air shield that cooperate to enhance an axial component of a channel airflow through the air shield, reducing a potential for unintended flameholding at the late lean injector.
  • the embodiments also provide an advantage in that the air shield may enclose at least a portion of a fuel supply line to facilitate protecting the fuel supply line during, for example, shipping, installation, and maintenance of the combustor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP16158421.4A 2015-03-10 2016-03-03 Écran d'air pour un injecteur de carburant d'une chambre de combustion Withdrawn EP3067626A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/643,778 US20160265782A1 (en) 2015-03-10 2015-03-10 Air shield for a fuel injector of a combustor

Publications (1)

Publication Number Publication Date
EP3067626A1 true EP3067626A1 (fr) 2016-09-14

Family

ID=55451128

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16158421.4A Withdrawn EP3067626A1 (fr) 2015-03-10 2016-03-03 Écran d'air pour un injecteur de carburant d'une chambre de combustion

Country Status (4)

Country Link
US (1) US20160265782A1 (fr)
EP (1) EP3067626A1 (fr)
JP (1) JP2016166729A (fr)
CN (1) CN105972641A (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
US9803555B2 (en) * 2014-04-23 2017-10-31 General Electric Company Fuel delivery system with moveably attached fuel tube
US10203114B2 (en) 2016-03-04 2019-02-12 General Electric Company Sleeve assemblies and methods of fabricating same
US10228141B2 (en) 2016-03-04 2019-03-12 General Electric Company Fuel supply conduit assemblies
US20170260866A1 (en) * 2016-03-10 2017-09-14 Siemens Energy, Inc. Ducting arrangement in a combustion system of a gas turbine engine
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
US12044411B2 (en) 2021-06-17 2024-07-23 Ge Infrastructure Technology Llc Combustor having fuel sweeping structures
US11435080B1 (en) * 2021-06-17 2022-09-06 General Electric Company Combustor having fuel sweeping structures
US11898753B2 (en) 2021-10-11 2024-02-13 Ge Infrastructure Technology Llc System and method for sweeping leaked fuel in gas turbine system

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2375167A2 (fr) * 2010-04-12 2011-10-12 General Electric Company Contrôle du profil de température en sortie de chambre de combustion à l'aide une injection étagée du combustible et procédé associé
EP2660519A1 (fr) * 2012-04-30 2013-11-06 General Electric Company Conduit de transition avec injection pauvre tardive pour une turbine à gaz
US20140260272A1 (en) * 2013-03-18 2014-09-18 General Electric Company System for providing fuel to a combustor
US20140260264A1 (en) * 2013-03-18 2014-09-18 General Electric Company System for controlling a flow rate of a compressed working fluid to a combustor fuel injector

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8117845B2 (en) * 2007-04-27 2012-02-21 General Electric Company Systems to facilitate reducing flashback/flame holding in combustion systems
US20090173074A1 (en) * 2008-01-03 2009-07-09 General Electric Company Integrated fuel nozzle ifc
US8104286B2 (en) * 2009-01-07 2012-01-31 General Electric Company Methods and systems to enhance flame holding in a gas turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2375167A2 (fr) * 2010-04-12 2011-10-12 General Electric Company Contrôle du profil de température en sortie de chambre de combustion à l'aide une injection étagée du combustible et procédé associé
EP2660519A1 (fr) * 2012-04-30 2013-11-06 General Electric Company Conduit de transition avec injection pauvre tardive pour une turbine à gaz
US20140260272A1 (en) * 2013-03-18 2014-09-18 General Electric Company System for providing fuel to a combustor
US20140260264A1 (en) * 2013-03-18 2014-09-18 General Electric Company System for controlling a flow rate of a compressed working fluid to a combustor fuel injector

Also Published As

Publication number Publication date
CN105972641A (zh) 2016-09-28
US20160265782A1 (en) 2016-09-15
JP2016166729A (ja) 2016-09-15

Similar Documents

Publication Publication Date Title
EP3067626A1 (fr) Écran d'air pour un injecteur de carburant d'une chambre de combustion
EP3067623A1 (fr) Écran d'air pour un injecteur de carburant d'une chambre de combustion
US8646276B2 (en) Combustor assembly for a turbine engine with enhanced cooling
US8726631B2 (en) Dual walled combustors with impingement cooled igniters
EP3282191B1 (fr) Buse de prémélange pilote et un ensemble de buse de combustible
EP2669580B1 (fr) Ensemble d'injection de carburant à utiliser dans les moteurs à turbine et procédé d'assemblage correspondant
US8534040B2 (en) Apparatus and method for igniting a combustor
US20140033718A1 (en) Combustor
EP2613083A2 (fr) Ensemble de chambre à combustion à utiliser avec un moteur à turbine et son procédé d'assemblage
EP2375161B1 (fr) Chambre de combustion dotée d'un manchon d'écoulement
US20100212324A1 (en) Dual walled combustors with impingement cooled igniters
US8550809B2 (en) Combustor and method for conditioning flow through a combustor
US8596069B2 (en) Rational late lean injection
CA2926402A1 (fr) Combustor de moteur de turbine a gaz
CN104748151A (zh) 延迟贫喷射歧管混合系统
US8555645B2 (en) Fuel nozzle centerbody and method of assembling the same
EP2520766A1 (fr) Joint annulaire, ensemble de chambre de combustion de turbine à gaz et procédé de refroidissement correspondant
US9322553B2 (en) Wake manipulating structure for a turbine system
US20120031099A1 (en) Combustor assembly for use in a turbine engine and methods of assembling same
US8813501B2 (en) Combustor assemblies for use in turbine engines and methods of assembling same
US9677766B2 (en) Fuel nozzle for use in a turbine engine and method of assembly
US9739201B2 (en) Wake reducing structure for a turbine system and method of reducing wake
EP2045527B1 (fr) Ensembles de dôme à facettes pour chambres de combustion de turbines à gaz
EP3220048B1 (fr) Refroidissement d'une chemise de combustion
EP2629015A2 (fr) Interface de conditionneur d'écoulement d'entrée de buse de carburant externe et de coiffe d'extrémité

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

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: BA ME

17P Request for examination filed

Effective date: 20170314

RBV Designated contracting states (corrected)

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

17Q First examination report despatched

Effective date: 20171205

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

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20180417