EP2423597B1 - Brûleur à prémélange pour une turbine à gaz - Google Patents

Brûleur à prémélange pour une turbine à gaz Download PDF

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Publication number
EP2423597B1
EP2423597B1 EP11178196.9A EP11178196A EP2423597B1 EP 2423597 B1 EP2423597 B1 EP 2423597B1 EP 11178196 A EP11178196 A EP 11178196A EP 2423597 B1 EP2423597 B1 EP 2423597B1
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EP
European Patent Office
Prior art keywords
premix burner
injection
diameter
injection openings
premix
Prior art date
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EP11178196.9A
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German (de)
English (en)
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EP2423597A3 (fr
EP2423597A2 (fr
Inventor
Frank Grimm
Fulvio Magni
Weiqun Geng
Douglas Anthony Pennell
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Ansaldo Energia IP UK Ltd
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General Electric Technology GmbH
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Classifications

    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • 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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D91/00—Burners specially adapted for specific applications, not otherwise provided for
    • 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
    • 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
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49716—Converting

Definitions

  • the present invention relates to the field of gas turbines. It relates to a premix burner for a gas turbine according to the preamble of claim 1 and to a method for reworking such premix burners according to the preamble of claim 10.
  • the present invention is based on a premix burner for a gas turbine in the form of a so-called "double-cone burner", as it is known for example from document EP 0 851 172 A2 is known.
  • the first figure of this application is here as Fig. 1 played.
  • the premix burner 10 according to Fig. 1 consists of two extending along one axis (29 in Fig. 2 ) extending hollow Operakegelschalen 11, 12, which are nested one behind the other.
  • the displacement of the respective center axis or longitudinal axis of symmetry of the partial cone shells 11, 12 generates on both sides, in mirror image arrangement, in each case a tangential air inlet channel 18, 19, through which combustion air 20 flows into the conical interior 30 of the burner.
  • the two partial cone shells 11, 12 each have an initial part in the form of a cylinder 14, 15.
  • a nozzle 24 for atomizing a preferably liquid fuel 23 is housed, which forms a flame front 28 after ignition together with the injected combustion air 20.
  • the partial cone shells 11, 12 further each have a fuel line 16, 17 which are arranged along the tangential air inlet channels 18, 19 and provided with injection openings 21 in the form of linear rows of holes through which a gaseous fuel 22 injected into the combustion air 20 flowing past there becomes, as is symbolized by arrows.
  • These fuel lines 16, 17 are preferably at the latest at the end of the tangential inflow, before entering the interior 30, placed in order to ensure an optimal air / fuel mixture.
  • the premix burner 10 has a front plate 13 serving as an anchoring for the partial cone shells 11, 12 with a number of bores 26, through which cooling air 27 can be supplied to the front part of the combustion chamber 25 as required.
  • the design and arrangement of the injection openings 21 for the gaseous fuel 22 has a considerable influence on the mixing of the fuel with the combustion air 20.
  • the fuel 22 is injected into the air inlet channel 18, 19 of the premix burner 10 perpendicular to the air flow.
  • the mixture of the fuel 22 with the air is from both the place of Injection 21 and influenced by the flow rate of the gaseous fuel.
  • injection openings 21 are used, which in Fig. 2 are shown as a row of holes R1, wherein each of the two air inlet ducts 18, 19 each associated with such a row of holes.
  • R1 when natural gas is used as the gaseous fuel, 32 injection ports 21 having a small discharge diameter are arranged.
  • DE 100 29 607 A1 discloses a pre-mixing double-cone burner in which two rows of holes extending transversely to the flow direction of the combustion air are arranged on the outer walls of the air inlet ducts.
  • the respective outlet openings may have different diameters, whereby the fuel penetrates at different depths into the air flow.
  • the object is solved by the entirety of the features of claim 1.
  • the inventive solution is that the injection openings are enlarged in diameter.
  • this magnification must be limited to an optimal range.
  • it has been shown that it is not the absolute size of the diameters to achieve good results that is decisive, but in each case a diameter ratio of the diameter of the injection opening 21 to the effective discharge diameter of the premix burner 10.
  • the effective exit diameter of the premix burner is to be understood as the diameter of a circle which forms the same area as the outlet opening of the premix burner.
  • a typical conventional hole diameter of a high methane natural gas burner resulted in the use of the newly introduced ratio of diameter of the injection port 21 to effective exit diameter of the premix burner 10 to a diameter ratio of 0.0086.
  • a diameter ratio of diameter of the injection port 21 to effective exit diameter of the premix burner 10 of 0.0097 was used.
  • a range of diameter ratios of diameter of the injection port to effective exit diameter of the premix burner which is between 0.011 and 0.015, has now been determined.
  • an extended range of diameter ratios of diameter of the injection port to effective exit diameter of the premix burner is proposed to be greater than 0.015 and less than 0.017 , Overall, this results in an advantageous range of diameter ratios from 0.011 to 0.017.
  • the distance between the injection openings or the total number of injection openings decreases.
  • the injection ports have been kept as small as possible to allow for good mixing.
  • a minimum size was required in order to keep the pressure losses, which occur during the injection of the fuel, small.
  • Another aspect of the disclosure is to specify a height of the air inlet ducts into which the fuel gas 2 is introduced into the premix burner in a region adapted to the injection opening, which leads to a good mixing with low pressure loss and stable combustion.
  • a ratio of the diameter of the injection opening to the height of the air inlet channel which is between 0.097 and 0.153, is advantageous in each case.
  • a ratio of the sum of the areas of the injection openings to the effective exit diameter of the premix burner in an advantageous range is to be selected. This range is between 0.0051 and 0.0097 for the proposed hole diameter ranges.
  • all injection openings of a row of holes have the same diameter and are equidistant.
  • Another embodiment of the invention is characterized in that the distance between adjacent injection openings of a row of holes is approximately 16 mm.
  • an advantageous range of the ratio of diameter of the injection opening to the height of the air inlet channels can be further specified, which is between 0.109 and 0.124.
  • two particularly advantageous partial regions of the ratio of the diameter of the injection opening to the height of the air inlet channels have been determined. These are the ranges from 0.109 to 0.112 and 0.119 to 0.124.
  • Another embodiment of the invention is characterized in that the premix burner is provided for operation with natural gas as gaseous fuel, and that the ratio of hole diameter of the injection ports to the effective exit diameter of the premix burner is 0.012 each.
  • Another embodiment of the invention is characterized in that the premix burner is designed for operation with a gaseous fuel having a calorific value which is at least 20% below the calorific value of methane, and that the injection openings each have a diameter ratio of diameter of the injection port to have effective premix burner exit diameter of 0.0137.
  • an advantageous range of the ratio of diameter of the injection port to the height of the air inlet ports can be further specified, which is between 0.123 and 0.140.
  • two particularly advantageous subregions of the ratio of the diameter of the injection opening to the height of the air inlet channels are indicated. These are the ranges from 0.123 to 0.128 and 0.134 to 0.140.
  • the fuel gas velocity in the injection openings must be high enough to achieve good mixing, on the other hand, it should be deep to keep the pressure losses in the fuel gas system low and thus, depending on the pressure level of the gas supply system, necessary compression of the fuel gas before the introduction avoid or minimize it.
  • the fuel gas velocity in the injection openings is proportional to the amount of gas and inversely proportional to the sum of the areas of the injection openings of a burner. Typically, the amount of fuel gas introduced into a burner is also proportional to the burner size.
  • a ratio of between 0.005 and 0.008 was found to be the favorable ratio of the sum of the areas of the injection ports to the effective exit area of the premix burner.
  • a ratio of between the sum of the areas of the injection ports and the effective exit area of the premix burner has been determined to be between 0.007 and 0.010 lies.
  • two parallel rows of holes with a double hole spacing between the injection openings are provided per air inlet channel, the holes are arranged offset from one another. Due to the different injection positions, the combustion stability can be positively influenced.
  • one row of holes with injection openings is provided per air inlet channel.
  • a method for reworking such Vormischbrenner according to claim 10 is the subject of the invention.
  • the object of the method is to rework a conventional premix burner with small injection openings with minimal effort in such a way that a novel premix burner with larger injection openings is obtained.
  • it is proposed to close every second hole of a row of holes of injection openings and to increase the diameter of the remaining injection opening.
  • To close the holes for example, welded or soldered.
  • a small closure can also be used.
  • An embodiment of the invention is characterized in that the ejection opening closest to the outlet of the premix burner to the combustion chamber is closed. Starting from there, a hole is drilled out alternately and a hole is closed.
  • An embodiment of the invention is characterized in that the injection opening closest to the outlet of the premix burner is bored to the combustion chamber. Starting from there, a hole is closed alternately and a hole drilled out.
  • the diameter of the remaining injection opening is increased so that its exit area doubles.
  • a premix burner 10 is shown in the double cone type, as used in large gas turbines. Visible is the cone character of the premix burner 10, which towards the combustion chamber (in Fig. 2 right) is limited by a front panel 13. Visible is also an air inlet channel 18, on the outside of which a fuel line 16 for the gaseous fuel is arranged transversely.
  • the gaseous fuel is injected into the air inlet channel 18 through injection openings 21, which form the illustrated row of holes R1 in shape and arrangement.
  • injection openings 21 which form the illustrated row of holes R1 in shape and arrangement.
  • the row of holes R1 has a distance a1 of 15 mm.
  • the row of holes R1 is replaced by the row of holes R2 or R3, in which only 16 injection openings 21 are provided with an enlarged diameter ratio of 0.011 and a distance d of 16 mm.
  • the sum of all flow cross sections of the injection openings with respect to the row of holes R1 remains the same, but the fewer individual beams are stronger and thus reach deeper into the flow of combustion air and lead to a significant improvement in the mixing.
  • the distance of the row of holes to the front plate 13 can remain unchanged with respect to the row of holes R1 (row of holes R2, distance a1); However, it is also conceivable to increase this distance from 15 mm to 23 mm (hole row R3, distance a2), which shifts the range of stable combustion to lower temperatures.
  • the diameter ratio of 0.012 for the injection ports 21 of the rows of holes R2 and R3 is provided for the use of natural gas. If, instead of natural gas, a gaseous fuel having a calorific value less than 80% of the calorific value of methane is injected, the injection openings 21 preferably all have a diameter ratio of 0.014.
  • two parallel rows of holes with staggered injection openings are provided, so that the two rows of holes are positioned "in gap" relative to each other.
  • the distance between the holes of a row of holes is doubled to 2 x d.
  • Essential for the improved mixing, combustion and pollutant emission is the distribution of the mass flow of the gaseous fuel to significantly less injection openings with a larger diameter. Contrary to the expectation that a large number of small injection holes with a correspondingly high pressure loss during injection would lead to improved mixing for better mixing, the emissions can be reduced due to the higher penetration depth with larger holes. It goes without saying that the diameters and distances of the injection openings 21 in a row of holes in the context of the invention may have certain variations in order to be able to compensate for irregularities in the combustion air flow.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Claims (14)

  1. Brûleur de pré-mélange (10) pour une turbine à gaz, sous la forme d'un brûleur à double cône, qui comprend deux coques coniques doubles (11, 12) disposées de manière imbriquée l'une dans l'autre, qui forment entre elles des canaux d'entrée d'air (18, 19), à travers lesquels l'air de combustion (20) s'écoule de l'extérieur vers un espace interne conique (30) du brûleur de pré-mélange (10), des séries de trous linéaires (R2, R3, R4) d'ouvertures d'introduction (20), s'étendant transversalement à la direction d'écoulement de l'air de combustion, étant disposées au niveau des parois extérieures des canaux d'entrée d'air (18, 19), à travers lesquelles un combustible gazeux (22) est introduit dans l'air de combustion (20) s'écoulant transversalement, caractérisé en ce que les ouvertures d'introduction (21) présentent un rapport de diamètre entre le diamètre de l'ouverture d'introduction (21) et le diamètre de sortie effectif du brûleur de pré-mélange entre 0,011 et 0,015 ou supérieur à 0,015 et inférieur à 0,017.
  2. Brûleur de pré-mélange selon la revendication 1, caractérisé en ce que les ouvertures d'introduction (21) présentent un rapport entre le diamètre de l'ouverture d'introduction (21) et la hauteur (H) du canal d'entrée d'air (18, 19) entre 0,097 et 0,153.
  3. Brûleur de pré-mélange selon l'une des revendications 1 ou 2, caractérisé en ce que les ouvertures d'introduction (21) présentent un rapport entre la somme des surfaces des ouvertures d'introduction (21) et la surface de sortie effective du brûleur de pré-mélange entre 0,0051 et 0,0097.
  4. Brûleur de pré-mélange selon l'une des revendications 1 à 3, caractérisé en ce que toutes les ouvertures d'introduction (21) d'une série de trous (R2, R3, R4) sont équidistantes et présentent le même diamètre.
  5. Brûleur de pré-mélange selon l'une des revendications 1 à 4, caractérisé en ce que la distance entre des ouvertures d'introduction (21) d'une série de trous (R2, R3, R4) est d'environ 16 m2m.
  6. Brûleur de pré-mélange selon l'une des revendications 1 à 5, caractérisé en ce que le brûleur de pré-mélange (10) est prévu pour fonctionner avec du gaz naturel en tant que combustible gazeux (22) et en ce que les ouvertures d'introduction (21) présentent un rapport entre le diamètre de l'ouverture d'introduction (21) et la hauteur (H) des canaux d'entrée d'air (18, 19) entre 0,109 et 0,124.
  7. Brûleur de pré-mélange selon l'une des revendications 1 à 5, caractérisé en ce que le brûleur de pré-mélange (10) est prévu pour fonctionner avec un combustible gazeux (22) qui présente un pouvoir calorifique inférieure à celui du gaz naturel, et en ce que les ouvertures d'introduction (21) présentent un rapport entre le diamètre de l'ouverture d'introduction (21) et la hauteur (H) des canaux d'entrée d'air (18, 19) entre 0,123 et 0,140.
  8. Brûleur de pré-méiange selon l'une des revendications 1 à 5, caractérisé en ce que le brûleur de pré-mélange (10) est prévu pour fonctionner avec du gaz naturel en tant que combustible gazeux (22) et les ouvertures d'introduction (21) présentent un rapport entre la somme des surfaces des ouvertures d'introduction (21) et la surface de sortie effective du brûleur de pré-mélange entre 0,005 et 0,008 ou en ce que le brûleur de pré-mélange (10) est prévu pour fonctionner avec un combustible gazeux (22) qui présente un pouvoir calorifique inférieure à celui du gaz naturel et en ce que les ouvertures d'introduction (21) présentent un rapport entre la somme des surfaces des ouvertures d'introduction (21) et la surface de sortie effective du brûleur de pré-mélange entre 0,007 et 0,010.
  9. Brûleur de pré-mélange selon l'une des revendications 1 à 8, caractérisé en ce que, pour chaque canal d'entrée d'air (18, 19), sont prévues deux séries de trous parallèles (R5) avec des ouvertures d'introduction (21) décalées les unes par rapport aux autres.
  10. Procédé de reprise de brûleurs de pré-mélange (10) pour une turbine à gaz, sous la forme d'un brûleur à double cône, qui comprend deux coques coniques doubles (11, 12) disposées de manière imbriquée l'une dans l'autre, qui forment entre elles des canaux d'entrée d'air (18, 19), à travers lesquels l'air de combustion (20) s'écoule de l'extérieur vers un espace interne conique (30) du brûleur de pré-mélange (10), des séries de trous linéaires (R1) d'ouvertures d'introduction (21), s'étendant transversalement à la direction d'écoulement de l'air de combustion, étant disposées au niveau des parois extérieures des canaux d'entrée d'air (18, 19), à travers lesquelles un combustible gazeux (22) est introduit dans l'air de combustion (20) s'écoulant transversalement, caractérisé en qu'un trou sur deux d'une série de trous (R1) d'ouvertures d'introduction (21) est fermé et le diamètre de l'ouverture d'introduction (21) restante est agrandi de façon à ce que les ouvertures d'introduction (21) présentent un rapport entre le diamètre de l'ouverture d'introduction (21) et la surface de sortie effective du brûleur de pré-mélange entre 0,011 et 0,015 ou supérieure à 0,015 et inférieur à 0,017.
  11. Procédé de reprise de brûleurs de pré-mélange (10) pour une turbine à gaz selon la revendication 10, caractérisé en ce que les ouvertures d'introduction sont soudées ou brasées pour leur fermeture.
  12. Procédé de reprise de brûleurs de pré-mélange (10) pour une turbine à gaz selon la revendication 10 ou 11, caractérisé en ce que l'ouverture d'introduction (21) la plus proche de la sortie du brûleur de pré-mélange (10) vers la chambre de combustion est fermée et, à partir de là, en alternance, une ouverture d'introduction (21) est percée et une ouverture d'introduction (21) est obturée.
  13. Procédé de reprise de brûleurs de pré-mélange (10) pour une turbine à gaz selon la revendication 10 ou 11, caractérisé en ce que l'ouverture d'introduction (21) la plus proche de la sortie du brûleur de pré-mélange (10) vers la chambre de combustion est percée et, à partir de là, en alternance, une ouverture d'introduction (21) est obturée et une ouverture d'introduction (21) est percée.
  14. Procédé de reprise de brûleurs de pré-mélange (10) pour une turbine à gaz selon l'une des revendications 10 à 13, caractérisé en ce que le diamètre des ouvertures d'introduction (21) restantes est agrandi de façon à ce que leur surface de sortie soit doublée.
EP11178196.9A 2010-08-27 2011-08-19 Brûleur à prémélange pour une turbine à gaz Active EP2423597B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH01389/10A CH703655A1 (de) 2010-08-27 2010-08-27 Vormischbrenner für eine gasturbine.

Publications (3)

Publication Number Publication Date
EP2423597A2 EP2423597A2 (fr) 2012-02-29
EP2423597A3 EP2423597A3 (fr) 2012-08-15
EP2423597B1 true EP2423597B1 (fr) 2016-08-17

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Country Status (5)

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US (1) US9170022B2 (fr)
EP (1) EP2423597B1 (fr)
KR (1) KR101525463B1 (fr)
AU (1) AU2011213841B2 (fr)
CH (1) CH703655A1 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2685160B1 (fr) 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
EP2685162A1 (fr) * 2012-07-10 2014-01-15 Alstom Technology Ltd Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz et procédé de fonctionnement d'un tel brûleur
EP2685163B1 (fr) 2012-07-10 2020-03-25 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
EP2685161B1 (fr) 2012-07-10 2018-01-17 Ansaldo Energia Switzerland AG Agencement de chambre de combustion, en particulier pour turbine à gaz
CA2824124C (fr) * 2012-08-24 2016-10-04 Alstom Technology Ltd. Methode de melange d'air de dilution dans un systeme de combustion sequentielle d'une turbine a gaz
EP3299720B1 (fr) 2016-09-22 2020-11-04 Ansaldo Energia IP UK Limited Ensemble avant de chambre de combustion pour turbine à gaz
US11242804B2 (en) 2017-06-14 2022-02-08 General Electric Company Inleakage management apparatus
KR101990767B1 (ko) 2017-08-09 2019-06-20 한국기계연구원 이중 원추형 가스터빈용 버너 및 이 버너에 공기를 공급하는 방법
CN108006640B (zh) * 2017-12-21 2024-02-13 靖江博鑫柯曼燃烧器制造有限公司 一种多用富氧烧嘴
KR102065582B1 (ko) 2018-03-16 2020-01-13 두산중공업 주식회사 가스 터빈 연료 공급 장치, 이를 구비한 연료 노즐 및 가스 터빈
CN112922744B (zh) * 2021-03-05 2023-01-06 中国空气动力研究与发展中心空天技术研究所 一种壁面嵌入式的飞行器燃料输送装置

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EP2423597A3 (fr) 2012-08-15
EP2423597A2 (fr) 2012-02-29
US9170022B2 (en) 2015-10-27
AU2011213841B2 (en) 2014-10-23
CH703655A1 (de) 2012-02-29
AU2011213841A1 (en) 2012-03-15
KR20120021213A (ko) 2012-03-08
KR101525463B1 (ko) 2015-06-03

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