EP3147569A1 - Wirbelgenerator und kraftstoffeinspritzsystem einer gasturbine mit solch einem wirbelgenerator - Google Patents

Wirbelgenerator und kraftstoffeinspritzsystem einer gasturbine mit solch einem wirbelgenerator Download PDF

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Publication number
EP3147569A1
EP3147569A1 EP15187052.4A EP15187052A EP3147569A1 EP 3147569 A1 EP3147569 A1 EP 3147569A1 EP 15187052 A EP15187052 A EP 15187052A EP 3147569 A1 EP3147569 A1 EP 3147569A1
Authority
EP
European Patent Office
Prior art keywords
vortex generator
vortex
partial
generators
fuel
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Withdrawn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
EP15187052.4A
Other languages
English (en)
French (fr)
Inventor
Madhavan Narasimhan Poyyapakkam
Yang Yang
Khawar Syed
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.)
Ansaldo Energia Switzerland AG
Original Assignee
General Electric Technology GmbH
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 Technology GmbH filed Critical General Electric Technology GmbH
Priority to EP15187052.4A priority Critical patent/EP3147569A1/de
Priority to US15/278,773 priority patent/US20170089584A1/en
Priority to CN201610857906.4A priority patent/CN106958835A/zh
Publication of EP3147569A1 publication Critical patent/EP3147569A1/de
Withdrawn legal-status Critical Current

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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Definitions

  • the present invention relates to vortex generators. It refers to a vortex generator according to the preamble of claim 1.
  • the present invention further refers to a fuel injection system of a gas turbine with a vortex generator.
  • FIG. 1 A current fuel injection system of a gas turbine with vortex generators (VGs) mounted on perpendicular flutes is shown in Fig. 1 .
  • the fuel injection system 20 comprises a plurality of flutes 23 extending between a lower plate 21 and an upper plate 22. Each flute 23 has a leading edge 24 and a trailing edge 25 with respect to the gas flowing through the flute arrangement.
  • the vortex generators (VGs) 27 are of a standard type (triangular prism with one trailing edge) designed to generate two strong vortices, which are expected to mix axially with the fuel injected by means of fuel injectors 28.
  • Document US 8,677,756 B2 discloses a burner, such as for a secondary combustion chamber of a gas turbine with sequential combustion having first and second combustion chambers, including an injection device for introducing at least one gaseous fuel into the burner.
  • the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the gaseous fuel into the burner.
  • the body is configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner.
  • the at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body.
  • the body has two lateral surfaces substantially parallel to the main flow direction.
  • At least one vortex generator is located on at least one lateral surface upstream of the at least one nozzle.
  • Document US 8,402,768 B2 relates to a burner for a combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner.
  • the at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body, and with reference to a central plane of the streamlined body, the trailing edge is provided with at least two lobes extending in opposite transverse directions.
  • Document US 2012/285173 A1 discloses a swirler including an annular housing with limiting walls. At least two vanes are arranged in the annular housing including the sidewalls of the swirler.
  • the leading edge area of each vane has a profile, which is oriented parallel to a main flow direction prevailing at the leading edge position, wherein the profiles of the vanes turn from the main flow direction prevailing at the leading edge position to impose a swirl on the flow, and wherein, with reference to a central plane of the vanes the trailing edges are provided with at least two lobes in opposite transverse directions.
  • a burner for a combustion chamber of a gas turbine including such a swirler and at least one nozzle having its outlet orifice at or in a trailing edge of the vane and to a method of operation of such a burner.
  • Document US 2012/297787 A1 discloses a combined flow straightener and mixer as well as a burner for a combustion chamber of a gas turbine having such a mixing device.
  • At least two streamlined bodies are arranged in a structure comprising the side walls of the mixer.
  • the leading edge area of each streamlined body has a profile, which is oriented parallel to a main flow direction prevailing at the leading edge position, and with reference to a central plane of the streamlined bodies, the trailing edges are provided with at least two lobes in opposite transverse directions. The periodic deflections forming the lobes from two adjacent streamlined bodies are out of phase.
  • the mixing and injection device includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies, each extending in a first transverse direction into the gas-flow channel.
  • Each streamlined body has two lateral surfaces that are arranged essentially parallel to the main-flow direction, the lateral surfaces being joined to one another at their upstream side to form a leading edge of the body and joined at their downstream side to form a trailing edge of the body.
  • Each streamlined body has a cross-section perpendicular to the first transverse direction that is shaped as a streamlined profile.
  • At least one of the streamlined bodies is provided with a mixing structure and with at least one fuel nozzle located at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction into the flow channel, wherein at least two of the streamlined bodies have different lengths along the first transverse direction such that they may be used for a can combustor.
  • Document US 8,490,398 B2 relates to a burner for a single combustion chamber or first combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner.
  • the at least one body is located in a first section of the burner with a first cross-sectional area at a leading edge of the at least one body with reference to a main flow direction prevailing in the burner, wherein downstream of said body a mixing zone is located with a second cross-sectional area, and at and/or downstream of said body the cross-sectional area is reduced, such that the first cross-sectional area is larger than the second cross-sectional area.
  • a vortex generator especially for a fuel injection system of a gas turbine, comprises a base area and a vortex generator body extending in a tapering fashion from said base area with a predetermined height.
  • said vortex generator body forms at least two partial vortex generators, whereby each of said at least two partial vortex generators has its own trailing edge.
  • said base area has the form of a triangle.
  • said at least two partial vortex generators are arranged at different heights with respect to said base area.
  • Said at least two partial vortex generators may be arranged one above the other with respect to said base area, said upper partial vortex generator having a first height and said lower partial vortex generator having a second height.
  • said at least two partial vortex generators are arranged in a predetermined angle to each other.
  • Said predetermined angle between said two partial vortex generators may vary between 0° and 45°.
  • said at least two partial vortex generators each have an associated attack and sweep angle.
  • Said at least two partial vortex generators may be arranged one above the other with respect to said base area, said upper partial vortex generator having a first height and said lower partial vortex generator having a second height, and said upper partial vortex generator may have a higher attack and sweep angle than said lower partial vortex generator.
  • a fuel injection means is provided between said at least two partial vortex generators.
  • Said fuel injection means may be located with different distances between said location and said at least two partial vortex generators.
  • said at least two partial vortex generators have a leading edge, and the leading edge of said at least two partial vortex generators has a predetermined shape.
  • the fuel injection system of a gas turbine according to the invention comprises at least one vortex generator, whereby said at least one vortex generator is a vortex generator according to the invention.
  • Fig. 2 shows a standard vortex generator (VG) 16, as it is used in the fuel injection system 20 of Fig. 1 .
  • This vortex generator 16 has a simple triangular base area 17 and a vortex generator body 16a in form of a simple triangular prism with a trailing edge 18 ending in an upper end 19.
  • a vortex generator according to an embodiment of the invention is shown in comparison in Fig. 3 .
  • the vortex generator 10 of Fig. 3 involves splitting the standard vortex generator 16 of Fig. 2 along a joining plane 15 into two partial vortex generators VG1 and VG2 rotated by a certain angle (see the two arrows in Fig. 3 ).
  • the size of this "lobed" VG design is much larger than the standard designs thereby reducing the number of VGs mounted on the flutes.
  • the number of fuel nozzles can be reduced in relation to the number of VGs.
  • the upper partial vortex generator VG1 has a respective trailing edge 12a with a lower end 14 and an upper end 13a.
  • the lower partial vortex generator VG2 has a respective trailing edge 12b starting at base area 11 and having an upper end 13b.
  • Fig. 4 shows in comparison a conceptual description of a standard VG ( Fig. 4a ) and the new lobed VG design ( Fig. 4b ).
  • the standard VG 16 has two strong vortices V1 and V2, which traverse axially and mix with the fuel injected by fuel injector 26 at an appropriate axial location ( Fig. 4a ).
  • the lobed VG 10 produces four smaller vortices V3-V6, which are circumferentially traversing due to a vortex sheet VS emanating from the lobed flow ( Fig. 4b ).
  • the lobed VG design there is a possibility to produce a higher number of large scale and small scale vortices.
  • the lobed VG design can reduce significantly the number of mixing devices or vortex generators (VGs) required in a fuel injector.
  • Fig. 5 shows in comparison (in a plane perpendicular to the flow direction) the flow structures from the standard ( Fig. 5a ) and lobed VG design ( Fig. 5b ) at the exit of the respective VG.
  • the streamline plots show that the lobed VG design produces four distinct vortices. The size of the vortices needs to be controlled by optimizing the design features of the lobed-VG concept.
  • Fig. 6 shows in comparison the velocity distribution for the standard VG ( Fig. 6a ) and lobed VG designs ( Fig. 6b ) in form of the axial velocity vectors near the VG trailing edge.
  • the lobed VG's ( Fig. 6b ) with their leading edge 29 and their trailing edges 12a and 12b (see also Fig. 7b ) produce multiple small scale vortices when compared to the two simple vortex structures produced by the standard VGs ( Fig. 6a ).
  • the locations of vortices are in addition circumferentially spread for the lobed VG configuration. The circumferential spread of the vortices helps in reaching the fuel much faster.
  • Fig. 7 shows in comparison the flow structures and fuel distribution for the standard VG ( Fig. 7a ) and lobed VG design ( Fig. 7b ).
  • the lobed VG design ( Fig. 7b ) produces a flow field spread circumferentially resulting in improved mixing of the fuel with hot gases.
  • Fig. 8 shows the angle between the two (partial) VGs VG1 and VG2 of the lobed VG design, which can be allowed to vary between 0 to 45 degrees.
  • the height h1 and h2 of the (two) VG trailing edges 12a and 12b can be varied so as to control hot gas mass flow. This also ensures the vortex breakdown characteristics of the lobed flow.
  • Fig. 9 shows another embodiment of the VG according to the invention, wherein fuel can be injected by means of a fuel injector 28 between the (partial) VGs.
  • a novel lobed vortex generator based fuel injection system is proposed to introduce rapid mixing at allowable pressure drops for higher firing temperature gas turbines.
  • This invention targets towards accomplishing fuel-air mixing within short burner-mixing length or time scales.
  • the concept includes aerodynamically facilitated axial fuel injection with mixing promoted by multiple vortices and lobed flow structures produced by a new lobed-VG design.
  • the burner is designed to operate at increased hot gas temperature (2000K or more) or fuel flexibility without suffering on high NOx emissions or flashback.
  • the proposed lobed-VG concept when compared to previous concepts is simpler, lower cost with less number of complex VG structures. The fuel distribution is much better for lobed-VG design due to reduced number of nozzles.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP15187052.4A 2015-09-28 2015-09-28 Wirbelgenerator und kraftstoffeinspritzsystem einer gasturbine mit solch einem wirbelgenerator Withdrawn EP3147569A1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP15187052.4A EP3147569A1 (de) 2015-09-28 2015-09-28 Wirbelgenerator und kraftstoffeinspritzsystem einer gasturbine mit solch einem wirbelgenerator
US15/278,773 US20170089584A1 (en) 2015-09-28 2016-09-28 Vortex generator, and fuel injection system of a gas turbine with such vortex generator
CN201610857906.4A CN106958835A (zh) 2015-09-28 2016-09-28 涡流发生器和带涡流发生器的燃气涡轮机的燃料喷射系统

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15187052.4A EP3147569A1 (de) 2015-09-28 2015-09-28 Wirbelgenerator und kraftstoffeinspritzsystem einer gasturbine mit solch einem wirbelgenerator

Publications (1)

Publication Number Publication Date
EP3147569A1 true EP3147569A1 (de) 2017-03-29

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EP15187052.4A Withdrawn EP3147569A1 (de) 2015-09-28 2015-09-28 Wirbelgenerator und kraftstoffeinspritzsystem einer gasturbine mit solch einem wirbelgenerator

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US (1) US20170089584A1 (de)
EP (1) EP3147569A1 (de)
CN (1) CN106958835A (de)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10151325B2 (en) * 2015-04-08 2018-12-11 General Electric Company Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same
EP3115693B1 (de) * 2015-07-10 2021-09-01 Ansaldo Energia Switzerland AG Sequentielle brennkammer und verfahren zum betrieb davon
US11242806B2 (en) * 2017-11-20 2022-02-08 Power Systems Mfg., Llc Method of controlling fuel injection in a reheat combustor for a combustor unit of a gas turbine
KR102787680B1 (ko) * 2020-03-31 2025-03-28 지멘스 에너지 글로벌 게엠베하 운트 코. 카게 버너의 버너 구성요소 및 이러한 유형의 버너 구성요소를 갖는 가스 터빈의 버너
US12181151B2 (en) 2021-07-29 2024-12-31 General Electric Company Mixer vanes having a waveform profile
US12123596B2 (en) 2021-07-29 2024-10-22 General Electric Company Mixer vanes

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5058837A (en) * 1989-04-07 1991-10-22 Wheeler Gary O Low drag vortex generators
US6263660B1 (en) * 1998-08-17 2001-07-24 Ramgen Power Systems, Inc. Apparatus and method for fuel-air mixing before supply of low pressure lean pre-mix to combustor for rotating ramjet engine driving a shaft
US20120285173A1 (en) 2011-05-11 2012-11-15 Alstom Technology Ltd Lobed swirler
US20120297787A1 (en) 2011-05-11 2012-11-29 Alstom Technology Ltd Flow straightener and mixer
US8402768B2 (en) 2009-11-07 2013-03-26 Alstom Technology Ltd. Reheat burner injection system
US8490398B2 (en) 2009-11-07 2013-07-23 Alstom Technology Ltd. Premixed burner for a gas turbine combustor
US8677756B2 (en) 2009-11-07 2014-03-25 Alstom Technology Ltd. Reheat burner injection system
US20140109588A1 (en) 2012-10-23 2014-04-24 Alstom Technology Ltd Burner for a can combustor
US20140328692A1 (en) * 2013-05-02 2014-11-06 General Electric Company Attachment system and method for wind turbine vortex generators
US20150010407A1 (en) * 2013-07-08 2015-01-08 Alonso O. Zamora Rodriguez Reduced noise vortex generator for wind turbine blade

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5058837A (en) * 1989-04-07 1991-10-22 Wheeler Gary O Low drag vortex generators
US6263660B1 (en) * 1998-08-17 2001-07-24 Ramgen Power Systems, Inc. Apparatus and method for fuel-air mixing before supply of low pressure lean pre-mix to combustor for rotating ramjet engine driving a shaft
US8402768B2 (en) 2009-11-07 2013-03-26 Alstom Technology Ltd. Reheat burner injection system
US8490398B2 (en) 2009-11-07 2013-07-23 Alstom Technology Ltd. Premixed burner for a gas turbine combustor
US8677756B2 (en) 2009-11-07 2014-03-25 Alstom Technology Ltd. Reheat burner injection system
US20120285173A1 (en) 2011-05-11 2012-11-15 Alstom Technology Ltd Lobed swirler
US20120297787A1 (en) 2011-05-11 2012-11-29 Alstom Technology Ltd Flow straightener and mixer
US20140109588A1 (en) 2012-10-23 2014-04-24 Alstom Technology Ltd Burner for a can combustor
US20140328692A1 (en) * 2013-05-02 2014-11-06 General Electric Company Attachment system and method for wind turbine vortex generators
US20150010407A1 (en) * 2013-07-08 2015-01-08 Alonso O. Zamora Rodriguez Reduced noise vortex generator for wind turbine blade

Also Published As

Publication number Publication date
CN106958835A (zh) 2017-07-18
US20170089584A1 (en) 2017-03-30

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