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EP2189720A1 - Agencement de brûleur - Google Patents

Agencement de brûleur Download PDF

Info

Publication number
EP2189720A1
EP2189720A1 EP08020335A EP08020335A EP2189720A1 EP 2189720 A1 EP2189720 A1 EP 2189720A1 EP 08020335 A EP08020335 A EP 08020335A EP 08020335 A EP08020335 A EP 08020335A EP 2189720 A1 EP2189720 A1 EP 2189720A1
Authority
EP
European Patent Office
Prior art keywords
carrier
nozzle
fuel
nozzle lance
arrangement according
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.)
Ceased
Application number
EP08020335A
Other languages
German (de)
English (en)
Inventor
Erfindernennung liegt noch nicht vor Die
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 EP08020335A priority Critical patent/EP2189720A1/fr
Priority to PCT/EP2009/062442 priority patent/WO2010057709A1/fr
Publication of EP2189720A1 publication Critical patent/EP2189720A1/fr
Ceased 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
    • F23R3/28—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
    • F23D—BURNERS
    • F23D23/00—Assemblies of two or more burners
    • 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
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts

Definitions

  • the present invention relates to a burner assembly and more particularly to a burner assembly for gas turbines.
  • a gas turbine comprises as essential components a compressor, a turbine with moving blades and at least one combustion chamber.
  • the blades of the turbine are arranged as blade rings on a shaft extending mostly through the entire gas turbine, which is coupled to a consumer, such as a generator for power generation.
  • the shaft provided with the blades is also called turbine runner or rotor. Between the blade rings are vanes, which serve as nozzles for guiding the working fluid through the turbine.
  • the combustion chamber is supplied with compressed air from the compressor.
  • the compressed air is mixed with a fuel, such as oil or gas, and the mixture burned in the combustion chamber.
  • the hot combustion exhaust gases are finally supplied as a working medium via a combustion chamber outlet of the turbine, where they transmit momentum to the blades under relaxation and cooling and thus do work.
  • the vanes serve to optimize the momentum transfer.
  • a typical burner assembly for gas turbines as shown in US 6,082,111 is described and how it is used in particular in so-called tube combustion chambers, usually has an annular support with uniformly distributed around the circumference of the ring nozzle lances.
  • fuel nozzle openings are arranged, with which fuel can be injected into an air supply channel.
  • the fuel nozzles represent a main stage of the burner, which is used to generate a premix flame, ie a flame, in which the air and the fuel mix before igniting become, serve.
  • premix burners are operated with lean air-fuel mixtures, ie with mixtures which contain relatively little fuel.
  • pilot burner which is designed as a diffusion burner, i. it produces a flame in which the fuel is injected directly into the flame without first being mixed with air.
  • the pilot burner in addition to starting the gas turbine, also serves to stabilize the premix flame which, to minimize emissions, is often operated in a range of air to fuel mixing ratio which could lead to flame instabilities without assisting the pilot flame.
  • a burner assembly such as the burner assembly described, typically includes a number of nozzle lances machined from a metal block and welded to the carrier.
  • Each nozzle lance has a gas supply passage extending from its wearer-side end to the nozzle openings. Through the gas supply passage also extends a liquid fuel supply piping leading to fuel nozzles for injecting the liquid fuel.
  • the carrier has corresponding bushings for the fuel piping and gas passages.
  • the gas passages are typically milled by machine into a cylindrical carrier blank and then covered with welded-on elements.
  • the bushings for the pipelines are machined into the carrier blank.
  • the carrier blank and thus the subsequent carrier must have a certain minimum thickness. This increases the weight of the burner assembly and the material costs. In addition, machine incorporation is laborious.
  • a burner arrangement comprises a carrier, which in particular can be designed as an annular carrier, and a number of nozzle lances each containing at least one fuel nozzle opening.
  • a fuel supply system extends to the fuel nozzle openings.
  • At least two nozzle lance elements are attached to the carrier, each of which comprises a carrier-side section and at least two nozzle lances extending from the carrier-side section and formed integrally therewith.
  • the inventive design of the burner assembly makes it possible to reduce the number of fuel passages and feedthroughs in the carrier compared to the prior art, since only one passage or passage is required by the carrier for each nozzle lance element.
  • the branching of the passages and passages then takes place only in the carrier-side section of the nozzle lance element.
  • the material thickness of the carrier can be reduced, whereby weight and cost can be saved.
  • the number of connections is reduced at the side facing away from the nozzle lances of the burner, which reduces the effort when connecting the burner assembly to the fuel system of the gas turbine.
  • the requirements for the installation space of the burner assembly in the region of the side facing away from the nozzle lances side of the carrier in comparison to State of the art less strict. Overall, the machining of the carrier is simplified.
  • the fuel supply system may include gaseous fuel fuel passages in the nozzle lance elements extending from the carrier to the nozzle orifice of the nozzle lance through the nozzle lance elements.
  • the sections of the fuel passages extending through the individual nozzle lances open into a single common fuel passage section in the carrier-side section of the respective nozzle lance element.
  • the fuel supply system may include fuel tube outputs in the nozzle lance elements extending from the carrier to the respective nozzle orifice of the nozzle lances through the nozzle lance elements.
  • the extending through the individual nozzle lances portions of the fuel pipes then open in the carrier-side portion of the respective nozzle lance element in a single common pipe section, which can then be passed through the carrier.
  • the fuel piping may be disposed inside the fuel passages.
  • This configuration makes it possible in particular to provide only a single fuel passage for gaseous fuel per nozzle lance element in the carrier through which the fuel pipeline is also guided.
  • the carrier for each nozzle lance element only has to be provided with a single bore, which significantly reduces the cost and expense when editing the carrier.
  • the blank may be formed for the carrier as a relatively flat annular disc, which reduces material and cost in producing the carrier.
  • the carrier-side sections of the nozzle lance elements may have a carrier-side opening provided with a cover, wherein the opening is large enough to possibly pass the fuel piping through the opening can. It is then possible to produce the branched fuel pipelines outside the nozzle lance elements and then introduce them through the large opening in the nozzle lance elements. Producing the branched fuel pipelines outside the nozzle lance elements is simpler than connecting the individual sections of the fuel pipelines when they are already inside the nozzle lance elements.
  • the cover can be soldered to the respective nozzle lance element after introduction of the fuel piping. Brazing methods are particularly suitable for soldering, ie soldering methods in which the liquidus temperature of the solder is above 450.degree. The soldering offers the advantage over welding that there is no deformation of the nozzle lance element or of the carrier plate compared with welding, so that post-processing after the connection is not necessary. The same applies to the connection of the individual pipe sections in the fuel supply system.
  • the cover has a pipe piece projecting in the direction of the support, the end remote from the cover having a first fastening element.
  • the tube piece is guided through a through hole in the carrier, and the corresponding nozzle lance element is fixed to the carrier by means of a second fastening element cooperating with the first fastening element.
  • This embodiment makes it possible to design the fixation on the carrier releasably, for example, in which the first fastening element is an external thread of the pipe section and the second fastening element is a nut.
  • the inner volume of the pipe section can also be used simultaneously as a fuel passage, through which the fuel pipe can be guided.
  • a single bore present in the carrier can thus be used to fix a nozzle lance element on the carrier and a gaseous and a liquid fuel to the individual nozzle lances of the nozzle lance element supply.
  • the removal and replacement of a nozzle lance element can then be done in a simple manner by loosening the screw and by separating the fuel pipe.
  • the carrier-side portions of the nozzle lance elements carrier side each have a contact surface, with which they on a corresponding contact surface abut the wearer.
  • At least one seal is preferably present between a nozzle lance element and the carrier.
  • a seal may in particular be designed as a c-ring seal. These are particularly well suited as seals due to their springback properties. In principle, however, other resilient seals such as o-ring seals are possible. Due to the elasticity of the seal, excessive restrictions on relative movements, which could occur, for example, due to the operational heating of the components, can be avoided.
  • the seal may, for example, be arranged between the carrier and the pipe section in the region of the through hole.
  • the nozzle lance elements of the burner assembly according to the invention may be formed instead of machined parts, in particular as castings. Compared to machined parts, castings are characterized by their less laborious production. In addition, castings are mass-produced and therefore inexpensive to manufacture.
  • Fig. 1 a burner assembly for a gas turbine shown in perspective.
  • the burner assembly comprises an annular support with a central opening and - in the present embodiment - four arranged on the support 1 around the central opening around and fixed nozzle lance elements 3.
  • Each nozzle lance element 3 has a carrier-side section 5, with which it is attached to the carrier 1 and two From the carrier-side portion outgoing nozzle lances 7, at which the carrier-side section 5 remote ends swirl generator (Swirler) 9 are attached.
  • the fuel supply system includes gas supply passages 11 (in FIG Fig. 1 not visible) for gaseous fuels, as well as pipelines for liquid fuels, such as oil, both of which extend through the support plate 1 and the nozzle lance elements 3 to gas nozzles 17 and nozzles 15 for liquid fuels in the nozzle lances 7 ( Fig. 2 ).
  • Fig. 2 shows a sectional view through the support plate 1 and a nozzle lance element 3.
  • the carrier plate 1 is essentially a machined solid workpiece formed in which for the passage of fuel supply lines to the nozzle lance elements 3 and for attaching the nozzle lance elements 3 to the support plate 1 through holes in the form of holes 19 are present.
  • the holes 19 have on the side of the support plate 1, on which the nozzle lance elements 3 are arranged, a section 21 with an enlarged cross section.
  • the nozzle lance elements 3 with the nozzle lances 7 are formed as one-piece, hollow-cast components.
  • the carrier-plate-side section 5 of the nozzle lance elements 3 has a planar contact surface 23, with which it bears against a corresponding planar contact surface 25 of the carrier plate 1.
  • In the center of the contact surface 23 is an opening 26 in the carrier plate-side section 5, through which the pipes 13 for the liquid fuel can be passed.
  • This opening 26 is closed by a cover plate 27, which can be connected in particular to the edge of the opening 26 by a brazing.
  • a tube 29 is inserted therethrough, which in the axial direction of the cover plate 27, starting from a section 31 having a wide outer diameter and a portion 33 having a smaller outer diameter.
  • the tube 29 also has at its located in the interior of the carrier-side section 5 of the nozzle lance element 7 end a flange 37, with which it bears against the inside of the cover plate 27.
  • the tube 29 may be bolted to the support plate 27 or advantageously be connected by a braze with the cover plate 27. The brazing is particularly advantageous in view of the gas tightness of the compound.
  • the tube 29 is inserted through the bore 19 in the support plate 1, wherein it protrudes with the free end of the tube 34 from the support plate 1.
  • the pipe end 34 which can also serve as a connection for fuel supply lines, is provided with an external thread 35, so that a nut 39 is screwed can be to fix the nozzle lance element 3 to the support plate 1.
  • the contact surface 23 serves to stabilize the position of the nozzle lance element 3 relative to the carrier plate 1.
  • the axial length of the large-diameter pipe portion 31 corresponds to the axial length of the enlarged-section bore portion 21.
  • annular surface 41 is formed, which has a groove 43 for receiving a seal 45.
  • the seal is formed in the present embodiment as a c-ring seal 45 which is inserted with its open side in the groove 43.
  • other seals could also be used, for example o-ring seals.
  • C-ring seals are particularly suitable because of their very good spring properties.
  • the seal 45 serves to prevent leakage of compressor air.
  • a cavity 51 in the carrier plate side portion 5 of the hollow-die-cast nozzle lance element 3 together with the free volume 52 of the nozzle lance 7 serves as a gas passage to the gas nozzles 17
  • the pipeline 13 has two branch lines 53 which extend through the respective nozzle lance 7 as far as the nozzle openings for liquid fuels 15.
  • the running through the nozzle lances 7 pipe sections 53 are connected in the present embodiment via a brazed joint 57 with a T-shaped connecting portion 55 of the pipe 13, but also a one-piece design of the pipe 13 with the pipe sections 53 is basically possible.
  • the burner assembly according to the invention allows a particularly simple embodiment of the carrier 1, namely as an annular support plate, in which only through holes for the passage of the tubes 29 must be introduced.
  • the tubes 29 are then used both for gas supply and for the supply of liquid fuels by means of pipes 29 guided through the pipes 13.
  • the fact that the nozzle lance elements 3 are connected to the support plate 1 only by means of a screw connection (external thread in the section 35 and nut 39) enables easy removal and replacement of the nozzle lance elements 3. If a nozzle lance element 3 is to be replaced, only the screw connection is required to be solved and the pipe 13 to be separated from the outside of the burner assembly located feed lines. A stable fixation of the position of the nozzle lance elements can be achieved by the contact surface 23 on the nozzle lance element 3 in cooperation with the system 25 of the support plate 1.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP08020335A 2008-11-21 2008-11-21 Agencement de brûleur Ceased EP2189720A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP08020335A EP2189720A1 (fr) 2008-11-21 2008-11-21 Agencement de brûleur
PCT/EP2009/062442 WO2010057709A1 (fr) 2008-11-21 2009-09-25 Agencement de brûleur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08020335A EP2189720A1 (fr) 2008-11-21 2008-11-21 Agencement de brûleur

Publications (1)

Publication Number Publication Date
EP2189720A1 true EP2189720A1 (fr) 2010-05-26

Family

ID=40561844

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08020335A Ceased EP2189720A1 (fr) 2008-11-21 2008-11-21 Agencement de brûleur

Country Status (2)

Country Link
EP (1) EP2189720A1 (fr)
WO (1) WO2010057709A1 (fr)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2362141A1 (fr) * 2010-02-19 2011-08-31 Siemens Aktiengesellschaft Agencement de brûleur
WO2012072659A1 (fr) * 2010-12-01 2012-06-07 Siemens Aktiengesellschaft Ensemble turbine à gaz et méthode associée
JP2014173841A (ja) * 2013-03-12 2014-09-22 General Electric Co <Ge> 燃料プリナムを備えた燃焼器端部カバー
EP2980483A1 (fr) * 2014-08-01 2016-02-03 Mitsubishi Hitachi Power Systems, Ltd. Chambre de combustion de turbine à gaz
EP3073198A1 (fr) * 2015-03-27 2016-09-28 General Electric Technology GmbH Système de distribution bicarburant intégré
US9488105B2 (en) 2010-12-01 2016-11-08 Siemens Aktiengesellschaft Gas turbine assembly and method therefor
US10197283B2 (en) 2015-03-27 2019-02-05 Ansaldo Energia Switzerland AG Integrated dual fuel delivery system
EP4015910A1 (fr) * 2020-12-17 2022-06-22 Collins Engine Nozzles, Inc. Dispositif d'allumage continu à montage interne et à orientation axiale : buse amovible
US11421602B2 (en) 2020-12-16 2022-08-23 Delavan Inc. Continuous ignition device exhaust manifold
US11473505B2 (en) 2020-11-04 2022-10-18 Delavan Inc. Torch igniter cooling system
US11486309B2 (en) 2020-12-17 2022-11-01 Delavan Inc. Axially oriented internally mounted continuous ignition device: removable hot surface igniter
US11608783B2 (en) 2020-11-04 2023-03-21 Delavan, Inc. Surface igniter cooling system
US11635210B2 (en) 2020-12-17 2023-04-25 Collins Engine Nozzles, Inc. Conformal and flexible woven heat shields for gas turbine engine components
US11635027B2 (en) 2020-11-18 2023-04-25 Collins Engine Nozzles, Inc. Fuel systems for torch ignition devices
US11680528B2 (en) 2020-12-18 2023-06-20 Delavan Inc. Internally-mounted torch igniters with removable igniter heads
US11692488B2 (en) 2020-11-04 2023-07-04 Delavan Inc. Torch igniter cooling system
JP2023110852A (ja) * 2022-01-28 2023-08-09 ドゥサン エナービリティー カンパニー リミテッド 燃焼器用ノズル、燃焼器およびこれを含むガスタービン
US11913646B2 (en) 2020-12-18 2024-02-27 Delavan Inc. Fuel injector systems for torch igniters
US12092333B2 (en) 2020-12-17 2024-09-17 Collins Engine Nozzles, Inc. Radially oriented internally mounted continuous ignition device

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11230976B2 (en) * 2017-07-14 2022-01-25 General Electric Company Integrated fuel nozzle connection

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB901442A (en) * 1961-05-12 1962-07-18 Gen Electric Improvements in fuel injection system for a combustion chamber of a gas turbine engine
DE2946393A1 (de) * 1978-11-20 1980-05-22 Rolls Royce Brenneinrichtung fuer gasturbinentriebwerke
US5437158A (en) * 1993-06-24 1995-08-01 General Electric Company Low-emission combustor having perforated plate for lean direct injection
US5771696A (en) * 1996-10-21 1998-06-30 General Electric Company Internal manifold fuel injection assembly for gas turbine
WO2000022347A1 (fr) * 1998-10-09 2000-04-20 General Electric Company Ensemble d'injection de combustible pour chambre a combustion de turbine a gaz
US6082111A (en) 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors
US6354085B1 (en) * 2000-01-13 2002-03-12 General Electric Company Fuel injector with a fuel filter arrangement for a gas turbine engine
US20040129797A1 (en) * 2002-10-10 2004-07-08 Volvo Aero Corporation Fuel injector
EP1843099A2 (fr) * 2001-08-29 2007-10-10 Hitachi, Ltd. Chambre de combustion de turbine à gaz et procédé de fonctionnement
EP1990580A1 (fr) * 2007-05-10 2008-11-12 Siemens Aktiengesellschaft Composants d'un brûleur pour un brûleur de turbine à gaz

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB901442A (en) * 1961-05-12 1962-07-18 Gen Electric Improvements in fuel injection system for a combustion chamber of a gas turbine engine
DE2946393A1 (de) * 1978-11-20 1980-05-22 Rolls Royce Brenneinrichtung fuer gasturbinentriebwerke
US5437158A (en) * 1993-06-24 1995-08-01 General Electric Company Low-emission combustor having perforated plate for lean direct injection
US5771696A (en) * 1996-10-21 1998-06-30 General Electric Company Internal manifold fuel injection assembly for gas turbine
US6082111A (en) 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors
WO2000022347A1 (fr) * 1998-10-09 2000-04-20 General Electric Company Ensemble d'injection de combustible pour chambre a combustion de turbine a gaz
US6354085B1 (en) * 2000-01-13 2002-03-12 General Electric Company Fuel injector with a fuel filter arrangement for a gas turbine engine
EP1843099A2 (fr) * 2001-08-29 2007-10-10 Hitachi, Ltd. Chambre de combustion de turbine à gaz et procédé de fonctionnement
US20040129797A1 (en) * 2002-10-10 2004-07-08 Volvo Aero Corporation Fuel injector
EP1990580A1 (fr) * 2007-05-10 2008-11-12 Siemens Aktiengesellschaft Composants d'un brûleur pour un brûleur de turbine à gaz

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2362141A1 (fr) * 2010-02-19 2011-08-31 Siemens Aktiengesellschaft Agencement de brûleur
US9488105B2 (en) 2010-12-01 2016-11-08 Siemens Aktiengesellschaft Gas turbine assembly and method therefor
WO2012072659A1 (fr) * 2010-12-01 2012-06-07 Siemens Aktiengesellschaft Ensemble turbine à gaz et méthode associée
CN103228993A (zh) * 2010-12-01 2013-07-31 西门子公司 燃气轮机组件和为此的方法
CN103228993B (zh) * 2010-12-01 2016-11-09 西门子公司 燃气轮机组件和为此的方法
JP2014173841A (ja) * 2013-03-12 2014-09-22 General Electric Co <Ge> 燃料プリナムを備えた燃焼器端部カバー
EP2980483A1 (fr) * 2014-08-01 2016-02-03 Mitsubishi Hitachi Power Systems, Ltd. Chambre de combustion de turbine à gaz
US10385780B2 (en) 2015-03-27 2019-08-20 Ansaldo Energia Switzerland AG Integrated dual fuel delivery system
US10197283B2 (en) 2015-03-27 2019-02-05 Ansaldo Energia Switzerland AG Integrated dual fuel delivery system
CN106050431A (zh) * 2015-03-27 2016-10-26 安萨尔多能源瑞士股份公司 一体式双燃料输送系统
EP3073198A1 (fr) * 2015-03-27 2016-09-28 General Electric Technology GmbH Système de distribution bicarburant intégré
US11982237B2 (en) 2020-11-04 2024-05-14 Collins Engine Nozzles, Inc. Torch igniter cooling system
US11719162B2 (en) 2020-11-04 2023-08-08 Delavan, Inc. Torch igniter cooling system
US11692488B2 (en) 2020-11-04 2023-07-04 Delavan Inc. Torch igniter cooling system
US11473505B2 (en) 2020-11-04 2022-10-18 Delavan Inc. Torch igniter cooling system
US11608783B2 (en) 2020-11-04 2023-03-21 Delavan, Inc. Surface igniter cooling system
US12123355B2 (en) 2020-11-04 2024-10-22 Collins Engine Nozzles, Inc. Surface igniter cooling system
US12313005B2 (en) 2020-11-18 2025-05-27 Collins Engine Nozzles, Inc. Fuel systems for torch ignition devices
US11635027B2 (en) 2020-11-18 2023-04-25 Collins Engine Nozzles, Inc. Fuel systems for torch ignition devices
US11421602B2 (en) 2020-12-16 2022-08-23 Delavan Inc. Continuous ignition device exhaust manifold
US11891956B2 (en) 2020-12-16 2024-02-06 Delavan Inc. Continuous ignition device exhaust manifold
US11486309B2 (en) 2020-12-17 2022-11-01 Delavan Inc. Axially oriented internally mounted continuous ignition device: removable hot surface igniter
US11754289B2 (en) 2020-12-17 2023-09-12 Delavan, Inc. Axially oriented internally mounted continuous ignition device: removable nozzle
US12092333B2 (en) 2020-12-17 2024-09-17 Collins Engine Nozzles, Inc. Radially oriented internally mounted continuous ignition device
US11635210B2 (en) 2020-12-17 2023-04-25 Collins Engine Nozzles, Inc. Conformal and flexible woven heat shields for gas turbine engine components
EP4015910A1 (fr) * 2020-12-17 2022-06-22 Collins Engine Nozzles, Inc. Dispositif d'allumage continu à montage interne et à orientation axiale : buse amovible
US11913646B2 (en) 2020-12-18 2024-02-27 Delavan Inc. Fuel injector systems for torch igniters
US11680528B2 (en) 2020-12-18 2023-06-20 Delavan Inc. Internally-mounted torch igniters with removable igniter heads
JP2023110852A (ja) * 2022-01-28 2023-08-09 ドゥサン エナービリティー カンパニー リミテッド 燃焼器用ノズル、燃焼器およびこれを含むガスタービン
US12270547B2 (en) 2022-01-28 2025-04-08 Doosan Enerbility Co., Ltd. Combustor nozzle, combustor, and gas turbine including same

Also Published As

Publication number Publication date
WO2010057709A1 (fr) 2010-05-27

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