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EP2905539A1 - Veilleuse avec aubes axiales pour turbine à gaz - Google Patents

Veilleuse avec aubes axiales pour turbine à gaz Download PDF

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Publication number
EP2905539A1
EP2905539A1 EP14154321.5A EP14154321A EP2905539A1 EP 2905539 A1 EP2905539 A1 EP 2905539A1 EP 14154321 A EP14154321 A EP 14154321A EP 2905539 A1 EP2905539 A1 EP 2905539A1
Authority
EP
European Patent Office
Prior art keywords
inlet pipe
pilot burner
air inlet
fuel
gas turbine
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Withdrawn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
EP14154321.5A
Other languages
German (de)
English (en)
Inventor
Claes Isaksson
Erik Munktell
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP14154321.5A priority Critical patent/EP2905539A1/fr
Priority to PCT/EP2015/050462 priority patent/WO2015117794A1/fr
Publication of EP2905539A1 publication Critical patent/EP2905539A1/fr
Withdrawn legal-status Critical Current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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • 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
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • the present invention relates to a pilot burner for a gas turbine, comprising an annular base body with a fuel inlet pipe, an air inlet pipe and a mixture outlet pipe connected at a connection section. Furthermore, the present invention relates to a gas turbine comprising a compressor, a turbine, a combustion chamber and a pilot burner of the kind above.
  • a pilot burner and a gas turbine as presented above are generally known. Air and fuel are mixed to form a flammable mixture, which is ignited and forms a pilot flame for a burner in the combustion chamber. It is not just about generating a flame, but also strict environmental rules have to be taken care of. For this reason, air and fuel shall be mixed well what sometimes is done by radial swirlers or not at all.
  • known solutions suffer of rather poor pre-mixing of fuel and air, comparably high material temperatures in the burner body going hand in hand with a short life time and risk of flashback, where fuel is injected into the combustion systems.
  • a pilot burner as disclosed in the opening paragraph, wherein said fuel inlet pipe and said air inlet pipe comprise separate means for axially swirling of the transported media.
  • a gas turbine comprising a compressor, a turbine, a combustion chamber and a pilot burner of the kind above.
  • said swirling means are embodied as helical grooves and/or fins.
  • a straight pipe may be used for swirling.
  • any other shape of the pipe is applicable as well, as swirling is done by the helical grooves and/or fins.
  • said swirling means are embodied as a helically shaped part of said fuel inlet pipe and/or said air inlet pipe.
  • a pipe with a smooth inner surface may be used as swirling is done by the course of the pipe.
  • rotational directions of the swirling means of said fuel inlet pipe and said air inlet pipe are unidirectional. In this way, a quite long interphase transfer area improves the mixing of the fluids, i.e. air and fuel.
  • rotational directions of the swirling means of said fuel inlet pipe and said air inlet pipe are counter-directional. In this way, quite intense turbulences improve the mixing of the fluids, i.e. air and fuel.
  • the pilot burner comprises a cooling chamber respectively cooling grid connected to the air inlet pipe and to cooling air outlets in the region of the mixture outlet pipes.
  • the pilot burner can be cooled.
  • air is tapped before mixing with fuel, goes through the entire burner tip and later is released into the combustion chamber. The taken measures keep most of the tip at the same temperature as the incoming air by the insulation effect of the air in the grid.
  • Fig. 1 shows a schematic oblique view of an exemplary pilot burner 1 from the front side.
  • Fig. 1 shows an annular base body 2 of the pilot burner 1 with mixture outlet pipes 3 and cooling air outlets 4.
  • the mixture outlet pipes 3 for fuel and the cooling air outlets 4 may be arranged such that they end at a conical section of the annular base body 2.
  • Particularly outlet holes of the mixture outlet pipes 3 may be distributed over the circumference of the conical section.
  • Particularly outlet holes of the cooling air outlets 4 may be distributed over the circumference of the conical section.
  • the mixture outlet pipes 3 and the cooling air outlets 4 may be arranged alternately.
  • Fig. 2 furthermore shows a front view of the pilot burner of Fig. 1 also showing the mixture outlet pipes 3 and cooling air outlets 4.
  • Fig. 3 shows a back view of the pilot burner of Fig. 1 , in particular fuel inlet pipes 5 and air inlet pipes 6.
  • the fuel inlet pipes 5 and the air inlet pipes 6 may be arranged alternately over the circumference.
  • Fig. 4 shows a side view of the pilot burner of Fig. 1 .
  • the mixture outlet pipes 3 and cooling air outlets 4 are shown again.
  • Fig. 5 now shows an oblique view of the mixture outlet pipes 3, the cooling air outlets 4, the fuel inlet pipes 5 and the air inlet pipes 6 of the pilot burner 1 of Fig. 1 shown separately from its annular base body 2 from the front side. That means that Fig. 5 is just a "virtual" view through the material of the annular base body 2, meaning that the hollow pipes are shown as concrete objects. The annular base body 2 is not shown directly. As it can be seen the mixture outlet pipes 3, the cooling air outlets 4, the fuel inlet pipes 5 and the air inlet pipes 6 of the pilot burner 1 are substantially passages through the annular base body 2.
  • Fig. 6 shows a detail view of the arrangement shown in Fig. 5 from the front side
  • Fig. 7 shows a detail view of the arrangement shown in Fig. 5 from the back side.
  • Figs. 5 to 7 disclose a connection section 7 connecting a fuel inlet pipe 5, an air inlet pipe 6 and a mixture outlet pipe 3. Furthermore, helical fins 8 of the fuel inlet pipe 5 and a helically shaped part 9 of the air inlet pipe 6 is shown.
  • Figs. 1 to 7 disclose a pilot burner 1 for a gas turbine, comprising an annular base body 2 with a fuel inlet pipe 5, an air inlet pipe 6 and a mixture outlet pipe 3 connected at a connection section 7.
  • the fuel inlet pipe 5 and the air inlet pipe 6 comprise separate means 8, 9 for axially swirling of the transported media.
  • said swirling means of the fuel inlet pipe 5 are embodied as helical fins 8.
  • helical grooves may be applicable instead or in addition as well.
  • a straight pipe may be used for swirling.
  • more or less any other shape of the pipe is applicable as well, as swirling is done by the helical grooves and/or fins 8.
  • the means 8 i.e. the helical grooves and/or fins 8) provide individually a swirl to the fuel.
  • the swirling means of the air inlet pipe 6 are embodied as a helically shaped part 9 of said air inlet pipe 6. In this way, a pipe with a smooth inner surface may be used as swirling is done by the course of the pipe.
  • the means 9 i.e. the helically shaped part 9 provide individually a swirl to the air.
  • swirling means of the air inlet pipe 6 are embodied as helical grooves and/or fins 8 and the swirling means of the fuel inlet pipe 5 are embodied as a helically shaped part 9 of the same.
  • rotational directions of the swirling means 8, 9 of said fuel inlet pipe 5 and said air inlet pipe 6 are unidirectional. In this way, a quite long interphase transfer area improves the mixing of the fluids, i.e. air and fuel.
  • the rotational directions of the swirling means 8, 9 of said fuel inlet pipe 5 and said air inlet pipe 6 may also be counter-directional. In this way, quite intense turbulences improve the mixing of the fluids, i.e. air and fuel.
  • Fig. 8 now shows a cross section of the pilot burner 1 of the Figs. 1 to 7 in the connection section 7 respectively mixing section. Furthermore, a cooling chamber 10 respectively cooling grid is shown in the annular base body 2. That means that the connection section 7 (or mixing section) and the cooling chamber 10 (or cooling grid) may also each be passages within the annular base body 2.
  • Fig. 9 furthermore shows a cross section of the pilot burner 1 of Fig. 1 in a cooling air tapping section 11, by which a part of the air entering the air inlet pipe 6 is guided through the cooling chamber 10 and finally through cooling air outlets 4. In this way, the pilot burner 1 can be cooled.
  • the cooling chamber 10 may cool the material of the annular base body 2, particularly cooling internal surfaces of the annular base body 2. Furthermore cooling air can also exit via cooling air outlets 4 allowing to cool an external front surface of the annular base body 2.
  • Fig. 10 finally shows a schematic view of an exemplary gas turbine 12.
  • the gas turbine 12 (also called gas turbine engine) comprises a compressor 13, a combustion chamber 14 and a turbine 15 as it is known per se.
  • the pilot burner 1 of the kind presented above may be used, being arranged in the region of the combustion chamber 14.
  • the pilot burner 1 is particularly present to provide pilot fuel for start-up or transient mode of operations to stabilize the flame and/or combustion.
  • the pilot fuel may be gaseous fuel. In another embodiment pilot fuel may be liquid fuel.
  • the shape of the channels can keep the fluid at a speed over the flame speed at all times. In this way, no combustion can take place inside the burner which prevents flashback.
  • a mix of fuel and an oxidizer has a possibility to react and cause a flashback.
  • a higher velocity of the jet out of the pilot tip may keep the pilot flame further away from the tip and therefore also make the metal less hot.
  • the complex structures within the annular base body 2 as disclosed in this text may be produced by 3D printing or additive manufacturing, e.g. via selective laser sintering, selective laser melting and similar methods.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP14154321.5A 2014-02-07 2014-02-07 Veilleuse avec aubes axiales pour turbine à gaz Withdrawn EP2905539A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14154321.5A EP2905539A1 (fr) 2014-02-07 2014-02-07 Veilleuse avec aubes axiales pour turbine à gaz
PCT/EP2015/050462 WO2015117794A1 (fr) 2014-02-07 2015-01-13 Brûleur à flamme pilote à coupelles de turbulence axiales pour turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14154321.5A EP2905539A1 (fr) 2014-02-07 2014-02-07 Veilleuse avec aubes axiales pour turbine à gaz

Publications (1)

Publication Number Publication Date
EP2905539A1 true EP2905539A1 (fr) 2015-08-12

Family

ID=50068899

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14154321.5A Withdrawn EP2905539A1 (fr) 2014-02-07 2014-02-07 Veilleuse avec aubes axiales pour turbine à gaz

Country Status (2)

Country Link
EP (1) EP2905539A1 (fr)
WO (1) WO2015117794A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3301367A1 (fr) * 2016-09-30 2018-04-04 Siemens Aktiengesellschaft Composant de machine, en particulier composant de turbomachine, avec des éléments de refroidissement et procédé de fabrication et de fonctionnement
WO2018118466A1 (fr) * 2016-12-22 2018-06-28 Siemens Aktiengesellschaft Manifold de carburant dans une chambre de combustion pour moteur à turbine à gaz
CN113494361A (zh) * 2020-04-08 2021-10-12 通用电气公司 燃烧器冷却结构

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2641365A1 (fr) * 1988-12-30 1990-07-06 Pillard Chauffage Procedes et dispositifs pour pulveriser finement un combustible liquide et bruleurs equipes de ces dispositifs
US20040067461A1 (en) * 2000-11-27 2004-04-08 Harald Ranke Burner and method for the chemical reaction of two gas streams
US20090158743A1 (en) * 2007-12-19 2009-06-25 Rolls-Royce Plc Fuel distribution apparatus
EP2110601A1 (fr) * 2008-04-15 2009-10-21 Siemens Aktiengesellschaft Brûleur
US20100162713A1 (en) * 2008-12-31 2010-07-01 Shui-Chi Li Cooled flameholder swirl cup
US20100330521A1 (en) * 2008-01-29 2010-12-30 Tobias Krieger Fuel Nozzle Having a Swirl Duct and Method for Producing a Fuel Nozzle
DE102011116317A1 (de) * 2011-10-18 2013-04-18 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner eines Fluggasturbinentriebwerks

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2641365A1 (fr) * 1988-12-30 1990-07-06 Pillard Chauffage Procedes et dispositifs pour pulveriser finement un combustible liquide et bruleurs equipes de ces dispositifs
US20040067461A1 (en) * 2000-11-27 2004-04-08 Harald Ranke Burner and method for the chemical reaction of two gas streams
US20090158743A1 (en) * 2007-12-19 2009-06-25 Rolls-Royce Plc Fuel distribution apparatus
US20100330521A1 (en) * 2008-01-29 2010-12-30 Tobias Krieger Fuel Nozzle Having a Swirl Duct and Method for Producing a Fuel Nozzle
EP2110601A1 (fr) * 2008-04-15 2009-10-21 Siemens Aktiengesellschaft Brûleur
US20100162713A1 (en) * 2008-12-31 2010-07-01 Shui-Chi Li Cooled flameholder swirl cup
DE102011116317A1 (de) * 2011-10-18 2013-04-18 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner eines Fluggasturbinentriebwerks

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3301367A1 (fr) * 2016-09-30 2018-04-04 Siemens Aktiengesellschaft Composant de machine, en particulier composant de turbomachine, avec des éléments de refroidissement et procédé de fabrication et de fonctionnement
WO2018060200A1 (fr) * 2016-09-30 2018-04-05 Siemens Aktiengesellschaft Composant de machine, en particulier composant de turbomachine, avec éléments de refroidissement et procédé de fabrication et de fonctionnement
US11371438B2 (en) 2016-09-30 2022-06-28 Siemens Energy Global GmbH & Co. KG Machine component, particularly a turbomachine component, with cooling features and a method for manufacturing and of operation
WO2018118466A1 (fr) * 2016-12-22 2018-06-28 Siemens Aktiengesellschaft Manifold de carburant dans une chambre de combustion pour moteur à turbine à gaz
CN113494361A (zh) * 2020-04-08 2021-10-12 通用电气公司 燃烧器冷却结构
EP3892921A1 (fr) * 2020-04-08 2021-10-13 General Electric Company Structures de refroidissement de brûleur
JP2021167712A (ja) * 2020-04-08 2021-10-21 ゼネラル・エレクトリック・カンパニイ バーナ冷却構造
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures

Also Published As

Publication number Publication date
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