US20160348914A1 - Swirler for a burner of a gas turbine engine - Google Patents

Swirler for a burner of a gas turbine engine Download PDF

Info

Publication number
US20160348914A1
US20160348914A1 US15/116,590 US201515116590A US2016348914A1 US 20160348914 A1 US20160348914 A1 US 20160348914A1 US 201515116590 A US201515116590 A US 201515116590A US 2016348914 A1 US2016348914 A1 US 2016348914A1
Authority
US
United States
Prior art keywords
fuel
swirler
gas turbine
turbine engine
injection ports
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.)
Abandoned
Application number
US15/116,590
Other languages
English (en)
Inventor
Ghenadie Bulat
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIEMENS INDUSTRIAL TURBOMACHINERY LIMITED
Assigned to SIEMENS INDUSTRIAL TURBOMACHINERY LIMITED reassignment SIEMENS INDUSTRIAL TURBOMACHINERY LIMITED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BULAT, GHENADIE
Publication of US20160348914A1 publication Critical patent/US20160348914A1/en
Abandoned 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
    • F23R3/286—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
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • F23D11/26—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space with provision for varying the rate at which the fuel is sprayed
    • 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
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

  • the present invention is related to a fuel injection means for a swirler of a burner of a gas turbine engine, the swirler comprising a plurality of vanes and a plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel to a radially inner end of the mixing channel, the fuel injection means comprising at least two injection ports to inject fuel into the channelled air.
  • the invention is related to a swirler for a burner of a gas turbine engine, comprising fuel injection means, a plurality of vanes and plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel to a radially inner end of the mixing channel, the fuel injection means comprising at least two injection ports to inject fuel into the channelled air, further to a burner of a gas turbine engine, comprising a swirler and a combustion chamber and further to a gas turbine engine, comprising at least one burner.
  • Modern gas turbine engines are commonly used in industrial applications. Such gas turbine engines can comprise a pilot burner with a pilot burner fuel delivery arrangement described in U.S. 2003/106320 A1.
  • the gas turbine engine is operated in a DLE-combustion mode (DLE: Dry Low Emission) producing low emissions, especially low NOx-emissions.
  • DLE Dry Low Emission
  • a good and uniform mixing of air and fuel in a burner of the gas turbine engine has to be achieved.
  • swirlers are used for this task. Such a swirler arrangement is for instance described in U.S. Pat. No. 5,983,642 A1.
  • FIG. 1 shows a sectional view of an example of a gas turbine engine 10 .
  • the terms upstream and downstream refer to the flow direction of the air flow and/or working gas flow through the engine unless otherwise stated.
  • the terms forward and reward refer to the general flow of gas through the engine.
  • the term axial, radial and circumferential are made with reference to a rotational axis 20 of the gas turbine engine 10 .
  • the gas turbine engine 10 comprises, in flow series, an inlet 12 , a compressor section 14 , a combustor section 16 and a turbine section 18 which are generally arranged in flow series and generally in the direction of a longitudinal or rotational axis 20 .
  • the gas turbine engine 10 further comprises a shaft 22 which is rotatable about the rotational axis 20 and which extends longitudinally through the gas turbine engine 10 .
  • the shaft 22 drivingly connects the turbine section 18 to the compressor section 14 .
  • air 24 which is taken in through the air inlet 12 , is compressed by the compressor section 14 and delivered to the combustion or burner section 16 .
  • the burner section 16 comprises an array of combustors each having a combustor axis 17 and arranged thereabout a burner plenum 26 , one or more combustion chambers 28 , defined by a double wall can 27 and at least one burner 30 fixed to each combustion chamber 28 .
  • the combustion chambers 28 and the burners 30 are located inside the burner plenum 26 .
  • the compressed air 24 passing through the compressor 14 and the diffuser 32 is discharged from the diffuser 32 into the burner plenum 26 from where a portion of the air enters the burner 30 and is mixed with a gaseous or liquid fuel.
  • the air/fuel-mixture is then burned and the combustion gas 34 or working gas from the combustion is channelled via a transition duct 35 to the turbine section 18 .
  • the turbine section 18 comprises a number of blade-carrying discs 36 attached to the shaft 22 .
  • two discs 36 each carry an annular array of turbine blades 38 .
  • the number of blade-carrying discs 36 could be different, i.e. only one disc or more than two discs.
  • guiding vanes 40 which are fixed to a stator 42 of the gas turbine engine 10 , are disposed between the turbine blades 38 . Between the exit of the combustion chamber 28 and the leading turbine blades 38 inlet guiding vanes 44 are provided.
  • the combustion gas 34 from the combustion chamber 28 enters the turbine section 18 and drives the turbine blades 38 which in turn rotate the shaft 22 .
  • the guiding vanes 40 , 44 serve to optimize the angle of the combustion or working gas on the turbine blades 38 .
  • the compressor section 14 comprises an actual series of guide vane stages 46 and rotor blade stages 48 .
  • the aforesaid object is achieved by a fuel injection means for a swirler of a burner of a gas turbine engine, the swirler comprising a plurality of vanes and a plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel to a radially inner end of the mixing channel, the fuel injection means comprising at least two injection ports to inject fuel into the channelled air.
  • the fuel injection means according to the invention is characterized in that the fuel injection means is enabled to change the number of injection ports used for the fuel injection.
  • the swirler described in the preamble is used in a burner of a gas turbine engine to produce an air/fuel mixture. This air/fuel mixture is afterwards burned in a combustion chamber of the burner.
  • the fuel injection means used to inject fuel into the channelled air in the mixing channel comprises at least two injection ports. These injections ports are distributed along the fuel injection means and may differ in size. By providing more than one injection port it is possible to achieve a more uniform distribution of the air/fuel mixture.
  • the fuel injection means is enabled to change the number of injection ports used for the fuel injection. Therefore it is possible, to use many, especially all, injection ports for an operation of the gas turbine engine at full load. For an operation of the gas turbine engine at a part load only a few, even down to one, injection ports can be used. This feature allows to provide fuel by a fuel injection means at such a high pressure that a good atomization of the fuel into the air can always be secured.
  • fuel injection means according to the invention can be characterized in that the fuel injection means comprises a spring loaded mechanism to change the number of injection ports used for the fuel injection.
  • a spring loaded mechanism is especially a mechanical easy way to change the number of used injection ports.
  • no other driving means are necessary and/or used to change the number of used injection ports.
  • no external engine such as an electric motor or a hydraulic system is necessary to achieve the change of the number of used injection ports.
  • the spring loaded mechanism is enabled to be driven by the pressure of the fuel to be injected.
  • the force of the spring loaded mechanism can be directed against the pressure of the fuel.
  • a spring loaded mechanism enabled to be driven by the pressure of the fuel to be injected is a very easy way to control such a spring loaded mechanism.
  • a fuel injection means can be characterized in that at least two injection ports share a common feeding pipe wherein a spring loaded mechanism comprises a piston arranged in the common feeding pipe.
  • a feeding pipe can be used to feed the fuel to the several injection ports.
  • the injection ports are arranged at the feeding pipe, especially in a linear way.
  • the piston is arranged inside the feeding pipe and separates the fuel in the feeding pipe from a spring of the spring loaded mechanism. For an operation at higher load more fuel is needed to be burned in the burner of the gas turbine engine. Therefore, in the fuel system of the gas turbine engine higher pressure is present. Through the force of the fuel at this higher pressure the piston is driven back inside the feeding pipe and consequently more injection ports are opened for injecting fuel into the air. By doing so, the number of used injection ports is automatically adapted to the load level of the operation of the gas turbine engine.
  • fuel injection means according to the invention can be characterized in that the fuel injection means are enabled to be arranged at a trailing edge of one of the vanes of the swirler.
  • the trailing edges of the vanes of the swirler are positioned at the end of the respective mixing channel.
  • the injection of the fuel into the channelled air is carried out at the end of the mixing channels and at the beginning of the burner plenum.
  • a very good mixture can be achieved and especially the positioning of fuel at the boundaries of the mixing channel can be prohibited.
  • a fuel injection means can be characterized in that the fuel injection means are constructed as a fuel injection lance.
  • a fuel injection lance can be positioned inside the mixing channel.
  • the positioning of the fuel injection lance inside the mixing channel can be done at the radially outer end of the mixing channel, at the radially inner end of the mixing channel or in between. Therefore it is possible, to choose the position of the fuel injection lance inside the mixing channel to meet the demands of the gas turbine engine to be used in.
  • fuel injection means can be characterized in that the injection ports are arranged in a counter-flow or a co-flow or a vertical spiral direction in respect to a direction of the channelled air.
  • a swirler for a burner of a gas turbine engine comprising fuel injection means, a plurality of vanes and a plurality of mixing channels between the vanes to channel air from a radially outer end of the mixing channel to a radially inner end of the mixing channel, the fuel injection means comprising at least two injection ports to inject fuel into the channelled air.
  • a swirler according to the invention is characterized in that the fuel injection means is constructed according to the first aspect of the invention. The use of such a fuel injection means provides the same advantages, which have been discussed in detail according to the fuel injection means according to the first aspect of the invention.
  • a burner of a gas turbine engine comprising a swirler and a combustion chamber.
  • a burner according to the invention is characterized in that the swirler is constructed according to the second aspect of the invention.
  • the use of such a swirler provides the same advantages which have been discussed in detail according to a swirler according to the second aspect of the invention.
  • a gas turbine engine comprising at least one burner.
  • a gas turbine engine according to the invention is characterized in that the burner is constructed according to the third aspect of the invention.
  • the use of such a burner provides the same advantages, which have been discussed in detail according to a burner according to the third aspect of the invention.
  • FIG. 1 a sectional view of a gas turbine according to prior art
  • FIG. 2 a, b fuel injection means according to prior art
  • FIG. 3 a, b, c fuel injection means according to the invention.
  • FIGS. 1, 2 a, b and 3 a, b, c Elements having the same functions and mode of action are provided in FIGS. 1, 2 a, b and 3 a, b, c with the same reference signs.
  • FIG. 2 a 2 b parts of a swirler 52 according to prior art are shown.
  • one of the vanes 54 and a mixing channel 56 is shown.
  • air 24 is channelled from a radially outer end 58 to a radially inner end 60 of the mixing channel 56 .
  • a fuel injection means 50 is placed inside the mixing channel 56 .
  • This fuel injection means 50 is in this embodiment constructed as a fuel injection lance 74 .
  • an injection port 62 is located at the end of the fuel injection lance 74 .
  • a fuel injection 66 of fuel 64 into the air 24 is carried out.
  • the shown fuel injection lance 74 is optimized and designed for a full load operation of the gas turbine engine 10 . Therefore, at part load operations of the gas turbine engine less fuel 64 is injected 66 into the air 24 . An atomization of the complete fuel 64 cannot be secured.
  • FIG. 3 a , 3 b , 3 c an embodiment of fuel injection means 50 according to the invention is shown.
  • the fuel injection means 50 comprises a feeding pipe 70 in which a spring loaded mechanism 68 is placed.
  • the spring loaded mechanism 68 comprises at its end a piston 72 which separates the spring loaded mechanism 68 and the fuel 64 in the feeding pipe 70 .
  • the three FIGS. 3 a , 3 b , 3 c show different fuel injections 66 for different load levels of the gas turbine engine 10 .
  • FIG. 3 a a low level operation is carried out.
  • the pressure of the fuel 64 in a fuel system of the gas turbine engine 10 is low. Therefore the pressure of the fuel 64 which carries out a force on the piston 72 is small.
  • FIG. 3 b a mid-level load operation of the gas turbine engine 10 is shown. The pressure in the fuel system has risen and therefore the piston 72 is pressed further against the spring level mechanism 68 inside the feeding pipe 70 . A second injection port 62 is opened and more fuel 64 is injected into the channelled air 24 in the mixing channel 56 .
  • FIG. 3 c a full load operation of the gas turbine engine 10 is shown. The pressure of the fuel inside the feeding pipe 70 is high enough that all of the injection ports 62 are opened. A maximum amount of fuel 64 can be injected 66 into the channelled air 24 in the mixing channel 56 .
  • FIGS. 3 a , 3 b , 3 c show that a fuel injection means 50 according to the invention allows a fuel injection 66 of fuel 64 into air 24 in a mixing channel 56 adapted to the load level of the gas turbine engine 10 .
  • a good atomization of the fuel 64 can be secured at each load level of the operation of the gas turbine engine 10 .
  • carbon build-up on internal surfaces of the gas turbine engine 10 especially on injection ports 62 , can be prohibited.
  • the fuel injection means 50 can vary the height above a base 57 of the mixing channel 56 or the axial extent 59 of the fuel injection 64 from the fuel injection ports 62 .
  • the fuel is injected over a relatively small axial extent from one or the first fuel injection port 62 A (see FIG. 3B ).
  • the next or second fuel injection port 62 B is exposed and fuel is released into the mixing channel 56 .
  • This increases the height above the base 55 or the axial extent 57 over which the fuel 64 can mix with the air passing through the mixing channel 56 .
  • a further increase in fuel pressure forces the spring 68 to compress still further and expose the third fuel injection port 62 C; the fuel now being injected over the greatest axial extent 57 or height above the base 55 .
  • variable fuel injection means 50 can inject fuel over a greater axial extent and vary the extent than prior art systems and ensure a higher degree of atomisation of the fuel in the air flow along with a better distribution of the fuel/air mixture. This results in improved mixing of fuel and air, better combustion characteristics, increased efficiency and therefore reduced emissions.
  • the spring loaded mechanism 68 has a generally linear bias such that the fuel pressure and position of the piston 72 in the common feeding pipe 70 have a linear relationship.
  • the spring loaded mechanism 68 has a non-linear bias and an increase in fuel pressure has an increasing bias the further the spring loaded mechanism 68 is compressed or forced away from the base 57 .
  • a relatively small change in fuel pressure causes a relatively large movement of the piston at part load operation. This is particularly advantageous at part load operation where small variations in pressure usually occur and the effect of fuel mixing is important on combustion performance of the system. For example and referring to FIGS. 3A-3C , when operating at low-load the first injection port 62 A is exposed as shown in FIG.
  • a first increase in fuel pressure then exposes the second injection port 62 B as shown in FIG. 3B ; to expose the third injection port 62 C a second increase in fuel pressure is required and which is greater than the first increase in fuel pressure to move the piston 72 as shown in FIG. 3C .
  • the positions or heights of the injection ports 62 A, 62 B, 62 C are set based on the air flow characteristics through the channel 56 .
  • the non-linear bias or stiffness of the spring mechanism 68 may be achieved in a number of ways.
  • One way is to have a spring with a helix having a variable tightness.
  • Another way is to have a spring with a varying thickness and therefore stiffness of the wire the helix is formed from.
  • Another way is to have a second spring or further springs extending part of the length of the main spring 68 .
  • a helical spring is shown in the figures, other spring or resilient means may be utilised which could be mechanical or field derived.
  • the term spring mechanism is not intended to be restricted to helical wire springs.
  • the injection ports 62 are located at axially spaced apart locations.
  • the injection ports 62 are located along an axial line, that is to say they are aligned in the axial direction of combustor axis 17 .
  • the injection ports 62 may be located at a radial offset from one another with respect to the combustor axis 17 .
  • at least one of the injector ports 62 A, 62 B, 62 C is closer to the combustor axis 17 than the others. This radial offset can ensure the injection of fuel 64 is placed into the best possible location of the air flowing through the mixing channel 56 .
  • the common feeding pipe 70 is shown extending parallel to the combustor axis 17 , the common feeding pipe 70 could be angled from the combustor axis 17 so as to enable one or more of the injector ports 62 A, 62 B, 62 C to be radially offset.
  • the three (or more) injection ports 62 A-C may be unequally spaced such that D 1 >D 2 or D 1 ⁇ D 2 .
  • D 1 >D 2 at low loads it may be beneficial to require a greater fuel pressure to expose the middle or second injection port 62 such that the fuel is particularly well atomised by virtue of a high fuel mass flow and therefore velocity passing through the first injector port 62 A to give a wider range of low load performance or improve combustion characteristics to reduce emissions.
  • D 1 ⁇ D 2 greater flexibility at lower loads may also be realised where a lesser fuel pressure exposes the first and second injection ports 62 A, 62 B.
  • the injection ports 62 A-C have similar outlet areas and therefore issue approximately the same amount of fuel when they are all fully exposed.
  • the outlet areas may be different such that different quantities of fuel are issue from one or all the injection ports 62 A-C.
  • This can be beneficial to tailor the delivery of fuel into the different areas 64 of heights above the base 57 for different load demands while assuring good fuel atomisation.
  • the first injection port 62 A may have a smaller area than second and third injection ports 62 B, 62 C.
  • the injection port 62 A is sized for the respective fuel pressure to deliver an optimised fuel/air mixture.
  • the fuel pressure is sufficient to urge the piston 72 to expose the second injection port 62 B where its larger outlet area gives the combination of the first and second outlet areas a wider range of operability.
  • the fuel pressure is sufficient to urge the piston 72 to expose the third injection port 62 C where its outlet area, larger that the first injection port 62 A, gives the combination of the first, second and third outlets a wider range of operability.
  • the common feeding pipe 70 and the spring loaded mechanism 68 could be arranged the opposite way to that shown in FIGS. 3A-3C such that rather than fuel being supplied axially outwardly in a direction from the base 57 , the fuel may be supplied axially inwardly in a direction towards the base 57 and from the axially outward part of the vane 54 . Therefore the spring loaded mechanism 68 may be located between the base 57 and the piston 72 . An increase in the fuel pressure would then drive the piston 72 towards the base.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US15/116,590 2014-02-11 2015-01-27 Swirler for a burner of a gas turbine engine Abandoned US20160348914A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP14154756.2 2014-02-11
EP14154756 2014-02-11
PCT/EP2015/051612 WO2015121063A1 (fr) 2014-02-11 2015-01-27 Coupelle de turbulence pour brûleur de turbine à gaz

Publications (1)

Publication Number Publication Date
US20160348914A1 true US20160348914A1 (en) 2016-12-01

Family

ID=50071520

Family Applications (1)

Application Number Title Priority Date Filing Date
US15/116,590 Abandoned US20160348914A1 (en) 2014-02-11 2015-01-27 Swirler for a burner of a gas turbine engine

Country Status (3)

Country Link
US (1) US20160348914A1 (fr)
EP (1) EP3105507A1 (fr)
WO (1) WO2015121063A1 (fr)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4751815A (en) * 1986-08-29 1988-06-21 United Technologies Corporation Liquid fuel spraybar
US5983642A (en) * 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
US6532726B2 (en) * 1998-01-31 2003-03-18 Alstom Gas Turbines, Ltd. Gas-turbine engine combustion system
US6666029B2 (en) * 2001-12-06 2003-12-23 Siemens Westinghouse Power Corporation Gas turbine pilot burner and method
US6962055B2 (en) * 2002-09-27 2005-11-08 United Technologies Corporation Multi-point staging strategy for low emission and stable combustion
GB2437977A (en) * 2006-05-12 2007-11-14 Siemens Ag A swirler for use in a burner of a gas turbine engine
US20140199643A1 (en) * 2013-01-16 2014-07-17 A. O. Smith Corporation Modulating Burner

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2978870A (en) * 1957-12-26 1961-04-11 Gen Electric Fuel injector for a combustion chamber
US2963862A (en) * 1960-03-21 1960-12-13 Orenda Engines Ltd Fuel systems
JP4220558B2 (ja) * 2007-04-05 2009-02-04 川崎重工業株式会社 ガスタービンエンジンの燃焼装置
GB2453114B (en) * 2007-09-25 2009-08-26 Siemens Ag A Swirler for use in a burner of a gas turbine engine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4751815A (en) * 1986-08-29 1988-06-21 United Technologies Corporation Liquid fuel spraybar
US5983642A (en) * 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
US6532726B2 (en) * 1998-01-31 2003-03-18 Alstom Gas Turbines, Ltd. Gas-turbine engine combustion system
US6666029B2 (en) * 2001-12-06 2003-12-23 Siemens Westinghouse Power Corporation Gas turbine pilot burner and method
US6962055B2 (en) * 2002-09-27 2005-11-08 United Technologies Corporation Multi-point staging strategy for low emission and stable combustion
GB2437977A (en) * 2006-05-12 2007-11-14 Siemens Ag A swirler for use in a burner of a gas turbine engine
US20140199643A1 (en) * 2013-01-16 2014-07-17 A. O. Smith Corporation Modulating Burner

Also Published As

Publication number Publication date
WO2015121063A1 (fr) 2015-08-20
EP3105507A1 (fr) 2016-12-21

Similar Documents

Publication Publication Date Title
CN106524222B (zh) 燃气轮机燃烧器
JP4578800B2 (ja) タービン内蔵システム及びそのインジェクタ
EP3320268B1 (fr) Brûleur pour turbine à gaz et procédé d'exploitation du brûleur
EP1795802B1 (fr) Contrôle indépendant du carburant pilote dans une buse secondaire d'injection
JP2014181903A (ja) ガスタービンにおける下流側燃料及び空気噴射に関連する方法
US10247155B2 (en) Fuel injector and fuel system for combustion engine
KR20130066691A (ko) 노즐 및 가스 터빈 연소기, 가스 터빈
US10240795B2 (en) Pilot burner having burner face with radially offset recess
US11578871B1 (en) Gas turbine engine combustor with primary and secondary fuel injectors
US11668464B2 (en) Fuel nozzle assembly having the leading edges of neighboring swirler vanes spaced at different distances
EP3486569B1 (fr) Turbine à gaz pour centrale électrique
EP3220050A1 (fr) Brûleur pour turbine à gaz
KR102071324B1 (ko) 연소기용 노즐, 연소기 및 이를 포함하는 가스 터빈
US20170051919A1 (en) Swirler for a burner of a gas turbine engine, burner of a gas turbine engine and gas turbine engine
KR102343002B1 (ko) 연소기용 노즐, 이를 포함하는 연소기, 및 가스 터빈
CA3010044C (fr) Chambre de combustion pour turbine a gaz
KR20190136383A (ko) 연소기용 노즐, 연소기 및 이를 포함하는 가스 터빈
US10837639B2 (en) Burner for a gas turbine
US11906165B2 (en) Gas turbine nozzle having an inner air swirler passage and plural exterior fuel passages
US8726671B2 (en) Operation of a combustor apparatus in a gas turbine engine
US20160348914A1 (en) Swirler for a burner of a gas turbine engine
KR20200038699A (ko) 노즐 어셈블리, 연소기 및 이를 포함하는 가스터빈
KR102096579B1 (ko) 액체 연료 노즐 및 이를 포함하는 가스 터빈 연소기
KR102164621B1 (ko) 연료 노즐 어셈블리 및 이를 포함하는 가스 터빈용 연소기
KR102189309B1 (ko) 연소기 및 이를 포함하는 가스 터빈

Legal Events

Date Code Title Description
AS Assignment

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SIEMENS INDUSTRIAL TURBOMACHINERY LIMITED;REEL/FRAME:039342/0172

Effective date: 20160711

Owner name: SIEMENS INDUSTRIAL TURBOMACHINERY LIMITED, UNITED

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:BULAT, GHENADIE;REEL/FRAME:039570/0839

Effective date: 20160701

STPP Information on status: patent application and granting procedure in general

Free format text: ADVISORY ACTION MAILED

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION