EP0335978A1 - Bruleur de turbine a gaz - Google Patents

Bruleur de turbine a gaz Download PDF

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Publication number
EP0335978A1
EP0335978A1 EP88907798A EP88907798A EP0335978A1 EP 0335978 A1 EP0335978 A1 EP 0335978A1 EP 88907798 A EP88907798 A EP 88907798A EP 88907798 A EP88907798 A EP 88907798A EP 0335978 A1 EP0335978 A1 EP 0335978A1
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EP
European Patent Office
Prior art keywords
main
nozzles
mixed gas
auxiliary
mixed
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.)
Granted
Application number
EP88907798A
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German (de)
English (en)
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EP0335978A4 (fr
EP0335978B1 (fr
Inventor
Yasuo Iwai
Shigeru Azuhata
Kenichi Sohma
Kiyoshi Narato
Hironobu Kobayashi
Tooru Inada
Tadayoshi Murakami
Norio Arashi
Yoji Ishibashi
Michio Kuroda
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Hitachi Ltd
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Hitachi Ltd
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
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Publication of EP0335978A1 publication Critical patent/EP0335978A1/fr
Publication of EP0335978A4 publication Critical patent/EP0335978A4/fr
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Publication of EP0335978B1 publication Critical patent/EP0335978B1/fr
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Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/26—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid with provision for a retention flame
    • 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

Definitions

  • the present invention relates to a gas turbine combustor, and more specifically to a gas turbine combustor of a pre-mixed combustion type in which a fuel and the air are mixed together prior to being burned.
  • Thermal NOx formed by the oxidation of nitrogen in the air for combustion in a high-temperature atmosphere occupy a majority proportion of nitrogen oxides (NOx) that generate when a gaseous fuel containing small amounts of nitrogen such as liquefied natural gas (LNG) burns.
  • NOx nitrogen oxides
  • LNG liquefied natural gas
  • the flame temperature must be lowered.
  • the flame temperature can be lowered by a method according to which water or vapor is blown into the combustion chamber to forcibly lower the temperature, or by a method according to which the fuel is burned under the condition where the mixing ratio of the fuel and the air is extremely increased to be greater than the theoretical air requirement or, conversely, is decreased.
  • the method of blowing water or vapor involves a new problem, i.e., decrease in the turbine efficiency.
  • a so-called diffused flame takes place in which the fuel and the air are injected from separate nozzles, and are mixed together in the combustor and are burned, in order to stabilize the flame and to prevent backfire.
  • the air ratio ratio of the air flow rate to the theoretical air requirement
  • a combustion apparatus which uses pre-mix flame in which the air in excess of the theoretical air requirement and the fuel are mixed together in advance and are injected into the combustor.
  • the pre-mix flame having a high air ratio, the region where the temperature becomes locally high is prevented from taking place and NOx are emitted in reduced amounts.
  • the pre-mix flame remains most stable when the air ratio is close to 1, but tends to be blown out when the injection speed increases. when the injection speed is low, furthermore, flame enters into the nozzle to cause backfire.
  • the pre-mix gas consisting of the fuel and the air must be injected at a high speed of, usually, 40 m/s to 70 m/s, but the flame is not easily formed under such high injection speed conditions.
  • a combustor Japanese Patent Laid-Open No. 22127/1986 in which the fuel is supplied in a divided manner, part of it being used for forming diffused flame and the remainder being used for forming pre-mix flame, and relatively stable diffused flame or combustion gas of a high temperature formed by the diffused flame is used for igniting the pre-mix flame.
  • the above combustor makes it possible to decrease the amount of NOx compared with the conventional combustor that utilizes the diffused flame.
  • the amount of NOx can be decreased if the flow rate of the fuel used for the diffused flame is decreased and the fuel flow rate of pre-mixed flame is increased.
  • the flame loses stability if the rate of pre-mixing increases, and limitation is imposed on decreasing the amount of NOx emission.
  • the amount of NOx generated from the gas turbine combustor can be decreased if unstable pre-mix flame is stabilized and if the gas turbine combustion system is of the type of completely pre-mixed combustion.
  • the air for combustion is supplied in large amounts compared with the fuel flow rate during the small-load operation conditions, whereby the fuel becomes lean and is difficultly ignited.
  • both the fuel supply and the air flow rate are increased, whereby the flow rate of the pre-mixed gas is further increased causing the pre-mix flame to be blown out.
  • the object of the present invention is to provide a gas turbine combustor which is capable of stably burning a lean pre-mixed gas having an air ratio of greater than 1 from low load through up to high load of the gas turbine, and a method of combustion.
  • a gas turbine combustor which comprises main cylindrical nozzles provided in the end wall on the upstream side of a cylindrical combustion chamber, auxiliary nozzles formed around the circumference of said main nozzles, main pre-mixed gas supply means for supplying a pre-­mixed gas to said main nozzles, and auxiliary pre-mixed gas supply means for supplying a pre-mixed gas having an air ratio smaller than that of said main pre-mixed gas to said auxiliary nozzles.
  • the object is further achieved even by a method of pre-mixed combustion for a gas turbine combustor in which the pre-mixed gas injected from the openings of the main cylindrical nozzles is burned with a pre-mixed flame formed around the outer circumferences of the openings of said main nozzles.
  • the gas turbine combustion system is of the completely pre-mixed combustion type. Hence, if lean combustion is carried out while setting the air ratio of the fuel-air mixture gas for main flame to be greater than 1.0, it is allowed to decrease the amounts of NOx and CO that are polluting substances generated from the gas turbine combustor.
  • Fig. 1 is a section view of a gas turbine combustor embodying the present invention.
  • An inner cylinder 20 is arranged concentrically in an outer cylinder 10, and annular space defined between the outer cylinder 10 and the inner cylinder 20 constitutes an air path 12 for guiding the air blown from the compressor to the head portion of the inner cylinder.
  • Double end walls 11 and 12 are provided at the head of the inner cylinder 20, and in the inner end wall 11 are formed main nozzles 14 and surrounding auxiliary nozzles 15 over the entire surface thereof as shown in Fig. 2.
  • the main nozzles 14 are formed at the right end of pre-mixing cylinders 16 that extend on the side of the outer end wall 12 penetrating therethrough.
  • the pre-mixing cylinders l6 introduce the air from an air chamber 17 formed on the left side of the end wall 12.
  • Fuel supply pipes 18 are inserted in the pre-­mixing cylinders 16, and the fuel injected from the ends of the fuel supply pipes 18 is mixed with the air as it flows through the cylinders 16 thereby to form a pre-mixed gas.
  • Auxiliary nozzles 15 are communicated with auxiliary pre-mixing chambers 30 formed between the end walls 11 and 12.
  • the chambers 30 are served with a uniformly pre-mixed gas from a venturi-type mixer 31.
  • the air of a high pressure is introduced into the mixer 31 by an introduction board 26 via an air adjusting valve 40, and the fuel adjusted under the atmospheric pressure is sucked to form a uniformly pre-mixed gas.
  • the fuel supply pipes 18 are communicated with a main fuel adjusting valve 60 via stop valves 50 provided for each of the pipes 18.
  • the valves 50 and 60 are controlled according to instructions from a controller 70 which receive load of the gas turbine and rotational speed signals.
  • the stop valves 50 are fully opened upon receipt of an open signal from the controller 70 and are fully closed in other cases.
  • Fig. 1 illustrates only four stop valves.
  • the stop valves are provided for all fuel supply pipes 18. In this embodiment, there are provided 19 stop valves.
  • the number of stop valves that open increases with the increase in the load of the turbine as shown in Fig. 4.
  • the opening degree of the adjusting valve 60 varies nearly in proportion to the turbine load.
  • the adjusting valve 40 maintains nearly a constant opening degree (about 10%) irrespective of the turbine load.
  • the pre-mixed air to be introduced into the auxiliary pre-mixing chambers 30 is uniformly pre-mixed in the mixer 31 so as to have an air ratio over a range of from 0.8 to 1.2. Further, the air adjusting valve 40 is so adjusted that the speed of injection from the auxiliary nozzles 15 will become nearly equal to the speed of combustion.
  • the air adjusting valve 40 for auxiliary flame is opened to form the auxiliary pre-mixed gas through the mixer 31.
  • the pre-mixed gas injected from the auxiliary nozzles 15 is ignited by ignition plugs that are not shown.
  • the auxiliary pre-mixed gas has an air ratio which is close to 1, i.e., which lies from 0.8 to 1.2, and the speed of injection is nearly equal to the speed of combustion, i.e., 0.4 m/s. Therefore, the auxiliary pre-mixed gas is reliably ignited and stably sustains the combustion after it is ignited.
  • the stop valves 50 are mostly closed, and the air only is injected from the main nozzles 14.
  • the opening degree of the adjusting valve 60 gradually increases in response to load signals of the turbine, and the stop valves 50 are opened according to a predetermined order.
  • a pre-mixed gas is formed in the pre-mixing cylinders 16 and is injected at high speeds from the main nozzles 14.
  • the pre-mixed gas injected from the main nozzles 14 is ignited by auxiliary flame 80 (Fig. 3) formed around thereof thereby to establish a main flame 90.
  • the stop valves 50 are opened successively, the number of flames formed by the main nozzles 14 increases gradually, and the flames are formed by all main nozzles 14 under the rated load condition.
  • the turbine rotates at a constant speed from 0% to 100%s of load, and the air supplied to the combustor flows nearly at a constant rate. Therefore, the air flows nearly at a constant rate from the air chamber 17 into the pre-mixing cylinders 16.
  • the amount of fuel that flows through the adjusting valve 60 varies nearly in proportion to the turbine load.
  • the number of stop valves 50 that open varies depending upon the amount of fuel, the amount of fuel supplied to the pre-mixing cylinders remains nearly the same per a stop valve that is open, and the air ratio of the mixture gas formed in the pre-mixing cylinders 16 does noit much change. In this embodiment, therefore, the air ratio is set to lie from 1.2 to 2.5.
  • the air ratio of the pre-mixed gas in the auxiliary nozzles 15 is set near to 1 to favorably maintain the flame, there is no likelihood that the flame is blown out even when the pre-mixed gas is injected from the main nozzles 14 at a speed greater than 20 m/s and, preferably, at a speed of 40 m/s to 70 m/s. Further, since the air is constantly injected from the main nozzles 14 at a speed of 20 m/s to 70 m/s, there takes place no backfire, either.
  • the combustion is stably sustained owing to the auxiliary flame.
  • Figs. 5(a), 5(b) and 6(a), 6(b) illustrate relationships between the amount of NOx generated and the amounts of H2 and CO generated when the pre-mixed gas is burned while changing its air ratio.
  • Fig. 5 (a), (b) shows the analyzed results of exhaust gas from the combustion cylinder of when the pre-mix flame is formed in the combustion cylinder having an inner diameter of 90 mm and a height of 346 mm
  • Fig. 6(a), (b) shows the analyzed results of exhaust gas from the combustion cylinder of when the pre-mix flame is formed in the combustion cylinder having an inner diameter of 208 mm and a height of 624 mm, both under the same combustion conditions.
  • Fig. 6(a), (b) shows the analysis of exhaust gas of up to the region of an air ratio of as high as 3.6.
  • the amount of NOx is less than 100 ppm as indicated by a curve 221, and CO and H2 are not almost formed as indicated by curves 231 and 241.
  • Oxygen exhibits behaviour as represented by a curve 251, as a matter of course.
  • the fuel gas is sampled and is analyzed at a point 5 mm away from the main nozzle (having an inner diameter of about 26 mm) in the direction of downstream by moving the sampling probe in the radial direction from the center of the nozzle, to examine the combustion condition in the main flame and near the auxiliary flame.
  • CH4 is not almost burned in the main flame but burns toward the auxiliary flame and burns by l00% over the auxiliary flame nozzle. This fact indicates that the flame is reliably transferred from the auxiliary flame of auxiliary nozzle to the pre-mixed gas of the main nozzle.
  • the size of the burner used in this embodiment is as follows: i.e., the main nozzle has an inner diameter of 26 mm, the spacer surrounding the main nozzle has a thickness of 2 mm, and the auxiliary nozzle has a width of 2 mm.
  • Fig. 8 illustrates a gas turbine combustor in which a plurality of main nozzles provided in the end wall on the head side of the inner cylinder of the combustor are classified into three groups, and the amounts of fuel supplied to the nozzle groups are independently increased or decreased such that the air ratio of the fuel-air mixture injected from the main nozzles will lie from 1.2 to 2.5 when the turbine load is varied over a range of 20% to 100%, in order to suppress the amounts of NOx and CO generated from the combustor.
  • Numerals on the main nozzles in the front view of the combustor of Fig. 9 represent classification numbers of the main nozzles grouped into three. Each nozzle group has four main nozzles.
  • Reference numerals 61, 62 and 63 denote flow-rate adjust valves; i.e., 61 denotes the adjust valve for increasing or decreasing the amount of fuel supplied to the second nozzle group, 62 denotes the adjust valve for the first nozzle group and 63 denotes the adjust valve for the third nozzle group.
  • Reference numeral 19 denotes a burner for diffused flame for igniting the pilot flame formed by the auxiliary nozzles. After the pilot flame is formed for the auxiliary nozzles, the fuel is no more supplied to the burner 19 and its flame is extinguished.
  • Fig. 10 shows changes in the amounts of fuel supplied to the nozzle groups when the load of the gas turbine combustor of Fig. 8 is changed.
  • the fuel is supplied to the first nozzle group only over the turbine load of from 0% to 39%.
  • the supply of fuel is decreased such that the air ratio becomes 2.5.
  • the fuel is supplied to the second nozzle group so that the air ratio becomes 2.5, and the amount of fuel supplied to the first nozzle group is increased under the condition where the amount of fuel supplied to the second nozzle group is maintained constant, in order to increase the turbine load from 39% to 60%.
  • the supply of fuel is decreased such that the air ratio of the first nozzle group becomes 2.5.
  • the fuel is supplied to the third nozzle group such that the air ratio becomes 2.5, and the amounts of fuel supplied to the first, second and third nozzle groups are increased proportionally from 60% to 100% of the turbine load.
  • the gas turbine combustor is so operated that the air ratio of the fuel-air mixture injected from the first, second and third nozzles will be 1.5.
  • the air ratio of the fuel-air mixture injected from the first, second and third nozzle groups lies from 1.25 to 2.50 over the turbine load range of from 20% to 100%.
  • the amount of NOx generated is smaller than about 100 ppm over the air ratio range of from 1.25 to 2.50, and unburned components that include CO, H2 and CH4 are generated in very small amounts. It can therefore be said that the method of operating the gas turbine combustor can be effectively employed for the gas turbine combustion system that permits NOx to generate little.
  • the auxiliary flame injected at a low speed is used for igniting the pre-mixed flame (main flame) that is injected at high speeds and for maintaining the flame. Therefore, the pre-mixed gas for forming the pilot flame that works to maintain the flame is injected at a speed which is the same as the speed of combustion, i.e., injected at a speed of about 0.4 m/s. Furthermore, the air ratio is set to lie from 0.8 to 1.2 to suppress the generation of NOx and to prevent the blow out. The entire circumference of the pre-­mixed gas injected at high speeds is surrounded by the auxiliary flame for maintaining the flame, so that the heat generated by the flame for maintaining the flame is efficiently transferred to the main flame.
  • a spacer is provided between the burner for main flame and the burner for auxiliary flame, so that vortex current is stably formed between the burner injecting the pre-mixed gas for main flame and the burner injecting the pre-mixed gas for auxiliary flame due to a difference in the speed of injection between them.
  • This helps promote the mixing of the pre-mixed gas of a high air ratio for main flame and the combustion gas from the auxiliary flame of a high temperature, enabling the main flame to be ignited more easily.
  • the auxiliary flame is blown out too under the condition where the flow of auxiliary flame is seriously affected by the ejection of the main flame and where the main flame is blown out.
  • the spacer being provided, however, the main flame and the auxiliary flame do not directly mix with each other near the burner outlet, but the two are only partly mixed with each other in the vortex current formed on the spacer portion. Accordingly, the auxiliary flame is stably formed at all times without being affected by the main flame, contributing to increasing the range of flow speed or air ratio in which the main flame can be stably formed.

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

Abstract

Un brûleur de turbine à gaz, qui fait partie d'un système de combustion avec mélange préalable et dans lequel un combustible et de l'air sont mélangés et brûlés, se compose d'un ajutage principal cylindrique disposé sur une paroi terminale amont d'une chambre de combustion cylindrique, un ajutage auxiliaire formé autour de l'ajutage principal, un organe principal d'alimentation en gaz prémélangé, servant à alimenter en gaz prémélangé l'ajutage principal, et un organe auxiliaire d'alimentation en gaz prémélangé qui sert à alimenter l'ajutage auxiliaire avec un gaz prémélangé dont la proportion d'air excédentaire est inférieure à celle du gaz prémélangé principal. Grâce à cet agencement, un gaz prémélangé pauvre ayant une proportion d'air excédentaire supérieure à 1 peut être brûlée de façon stable dans des conditions de charges d'une turbine à gaz allant d'un niveau faible à un niveau élevé.
EP88907798A 1987-09-04 1988-08-31 Bruleur de turbine a gaz Expired - Lifetime EP0335978B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP220206/87 1987-09-04
JP62220206A JP2528894B2 (ja) 1987-09-04 1987-09-04 ガスタ―ビン燃焼器
PCT/JP1988/000870 WO1989002052A1 (fr) 1987-09-04 1988-08-31 Bruleur de turbine a gaz

Publications (3)

Publication Number Publication Date
EP0335978A1 true EP0335978A1 (fr) 1989-10-11
EP0335978A4 EP0335978A4 (fr) 1989-12-13
EP0335978B1 EP0335978B1 (fr) 1995-11-08

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EP88907798A Expired - Lifetime EP0335978B1 (fr) 1987-09-04 1988-08-31 Bruleur de turbine a gaz

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EP (1) EP0335978B1 (fr)
JP (1) JP2528894B2 (fr)
CN (1) CN1011064B (fr)
DE (1) DE3854666T2 (fr)
WO (1) WO1989002052A1 (fr)

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* Cited by examiner, † Cited by third party
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US5097666A (en) * 1989-12-11 1992-03-24 Sundstrand Corporation Combustor fuel injection system
WO1993010400A1 (fr) * 1991-11-14 1993-05-27 United Technologies Corporation COMBUSTION A FAIBLE NIVEAU DE NOx PILOTEE PAR DES VEILLEUSES A EMISSION REDUITE DE NO¿x?
EP1531305A1 (fr) * 2003-11-12 2005-05-18 United Technologies Corporation Injecteur de carburant multi-point
US6962055B2 (en) 2002-09-27 2005-11-08 United Technologies Corporation Multi-point staging strategy for low emission and stable combustion
US7797942B2 (en) 2004-11-17 2010-09-21 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor having multiple independently operable burners and staging method thereof
US10088163B2 (en) 2013-03-13 2018-10-02 Siemens Aktiengesellschaft Jet burner with cooling duct in the base plate
WO2023214129A1 (fr) * 2022-05-02 2023-11-09 Safran Procede d'injection de melange hydrogene-air pour bruleur de turbomachine

Families Citing this family (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2518986Y2 (ja) * 1989-01-20 1996-12-04 川崎重工業株式会社 ガスタービンの燃焼器
JPH03260518A (ja) * 1990-03-08 1991-11-20 Advance Koojienereeshiyon Syst Gijutsu Kenkyu Kumiai ガスタービン触媒燃焼システム
JP2564022B2 (ja) * 1990-06-07 1996-12-18 川崎重工業株式会社 ガスタービンの燃焼器
JPH05196232A (ja) * 1991-08-01 1993-08-06 General Electric Co <Ge> 耐逆火性燃料ステージング式予混合燃焼器
US5361586A (en) * 1993-04-15 1994-11-08 Westinghouse Electric Corporation Gas turbine ultra low NOx combustor
US5359847B1 (en) * 1993-06-01 1996-04-09 Westinghouse Electric Corp Dual fuel ultra-flow nox combustor
US5636510A (en) * 1994-05-25 1997-06-10 Westinghouse Electric Corporation Gas turbine topping combustor
US5491970A (en) * 1994-06-10 1996-02-20 General Electric Co. Method for staging fuel in a turbine between diffusion and premixed operations
US6298667B1 (en) * 2000-06-22 2001-10-09 General Electric Company Modular combustor dome
US6755024B1 (en) * 2001-08-23 2004-06-29 Delavan Inc. Multiplex injector
US6813889B2 (en) * 2001-08-29 2004-11-09 Hitachi, Ltd. Gas turbine combustor and operating method thereof
JP4418442B2 (ja) * 2006-03-30 2010-02-17 三菱重工業株式会社 ガスタービンの燃焼器及び燃焼制御方法
US7966820B2 (en) * 2007-08-15 2011-06-28 General Electric Company Method and apparatus for combusting fuel within a gas turbine engine
US20090223227A1 (en) * 2008-03-05 2009-09-10 General Electric Company Combustion cap with crown mixing holes
DE102008032265B4 (de) * 2008-07-09 2010-06-10 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verbrennungsvorrichtung
US8327642B2 (en) * 2008-10-21 2012-12-11 General Electric Company Multiple tube premixing device
US20110048022A1 (en) * 2009-08-29 2011-03-03 General Electric Company System and method for combustion dynamics control of gas turbine
US8613197B2 (en) * 2010-08-05 2013-12-24 General Electric Company Turbine combustor with fuel nozzles having inner and outer fuel circuits
US20120055163A1 (en) * 2010-09-08 2012-03-08 Jong Ho Uhm Fuel injection assembly for use in turbine engines and method of assembling same
US8707672B2 (en) * 2010-09-10 2014-04-29 General Electric Company Apparatus and method for cooling a combustor cap
US8991187B2 (en) * 2010-10-11 2015-03-31 General Electric Company Combustor with a lean pre-nozzle fuel injection system
US20130036743A1 (en) * 2011-08-08 2013-02-14 General Electric Company Turbomachine combustor assembly
US8966906B2 (en) * 2011-09-28 2015-03-03 General Electric Company System for supplying pressurized fluid to a cap assembly of a gas turbine combustor
US8966907B2 (en) * 2012-04-16 2015-03-03 General Electric Company Turbine combustor system having aerodynamic feed cap
US20130283802A1 (en) * 2012-04-27 2013-10-31 General Electric Company Combustor
US10101032B2 (en) * 2015-04-01 2018-10-16 General Electric Company Micromixer system for a turbine system and an associated method thereof
JP6423760B2 (ja) * 2015-06-24 2018-11-14 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器の燃料ノズル構造
JP6074090B1 (ja) * 2016-02-02 2017-02-01 大口 元気 ポンプディスペンサー付き液体容器
CN106016362B (zh) * 2016-05-16 2018-10-09 中国科学院工程热物理研究所 一种燃气轮机柔和燃烧室及其控制方法
CN109424976B (zh) * 2017-09-05 2021-07-02 深圳意动航空科技有限公司 扁形航改燃机燃气喷嘴
JP2019128125A (ja) * 2018-01-26 2019-08-01 川崎重工業株式会社 バーナ装置
JP7489759B2 (ja) * 2018-11-20 2024-05-24 三菱重工業株式会社 燃焼器及びガスタービン
JP2021055971A (ja) * 2019-10-01 2021-04-08 三菱パワー株式会社 ガスタービン燃焼器
KR102433706B1 (ko) * 2021-01-07 2022-08-19 두산에너빌리티 주식회사 노즐 어셈블리, 연소기 및 이를 포함하는 가스터빈
KR102437976B1 (ko) * 2021-01-14 2022-08-30 두산에너빌리티 주식회사 노즐 어셈블리, 연소기 및 이를 포함하는 가스터빈

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3048014A (en) * 1955-07-07 1962-08-07 Fritz A F Schmidt Combustion chamber for jets and similar engines
CH407653A (de) * 1962-07-24 1966-02-15 Prvni Brnenska Strojirna Brenner für gasförmigen und flüssigen Brennstoff, insbesondere für Gasturbinen
US3919840A (en) * 1973-04-18 1975-11-18 United Technologies Corp Combustion chamber for dissimilar fluids in swirling flow relationship
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
EP0095788A1 (fr) * 1982-05-28 1983-12-07 BBC Aktiengesellschaft Brown, Boveri & Cie. Chambre de combustion d'une turbine à gaz et sa méthode
GB2146425A (en) * 1983-09-08 1985-04-17 Hitachi Ltd Method of supplying fuel into gas turbine combustor
EP0169431A1 (fr) * 1984-07-10 1986-01-29 Hitachi, Ltd. Chambre de combustion pour turbine à gaz

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5857656A (ja) * 1981-09-30 1983-04-05 Toshiba Corp 制御ル−プの切換え装置
JPH0630589Y2 (ja) * 1989-04-19 1994-08-17 石川島播磨重工業株式会社 走行台車に於ける吊りフレームの支持装置

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3048014A (en) * 1955-07-07 1962-08-07 Fritz A F Schmidt Combustion chamber for jets and similar engines
CH407653A (de) * 1962-07-24 1966-02-15 Prvni Brnenska Strojirna Brenner für gasförmigen und flüssigen Brennstoff, insbesondere für Gasturbinen
US3919840A (en) * 1973-04-18 1975-11-18 United Technologies Corp Combustion chamber for dissimilar fluids in swirling flow relationship
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
EP0095788A1 (fr) * 1982-05-28 1983-12-07 BBC Aktiengesellschaft Brown, Boveri & Cie. Chambre de combustion d'une turbine à gaz et sa méthode
GB2146425A (en) * 1983-09-08 1985-04-17 Hitachi Ltd Method of supplying fuel into gas turbine combustor
EP0169431A1 (fr) * 1984-07-10 1986-01-29 Hitachi, Ltd. Chambre de combustion pour turbine à gaz

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO8902052A1 *

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5097666A (en) * 1989-12-11 1992-03-24 Sundstrand Corporation Combustor fuel injection system
WO1993010400A1 (fr) * 1991-11-14 1993-05-27 United Technologies Corporation COMBUSTION A FAIBLE NIVEAU DE NOx PILOTEE PAR DES VEILLEUSES A EMISSION REDUITE DE NO¿x?
US5318436A (en) * 1991-11-14 1994-06-07 United Technologies Corporation Low NOx combustion piloted by low NOx pilots
US6962055B2 (en) 2002-09-27 2005-11-08 United Technologies Corporation Multi-point staging strategy for low emission and stable combustion
EP1531305A1 (fr) * 2003-11-12 2005-05-18 United Technologies Corporation Injecteur de carburant multi-point
US7797942B2 (en) 2004-11-17 2010-09-21 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor having multiple independently operable burners and staging method thereof
DE102005054442B4 (de) * 2004-11-17 2011-04-07 Mitsubishi Heavy Industries, Ltd. Brennkammer für eine Gasturbine
US10088163B2 (en) 2013-03-13 2018-10-02 Siemens Aktiengesellschaft Jet burner with cooling duct in the base plate
WO2023214129A1 (fr) * 2022-05-02 2023-11-09 Safran Procede d'injection de melange hydrogene-air pour bruleur de turbomachine

Also Published As

Publication number Publication date
JP2528894B2 (ja) 1996-08-28
EP0335978A4 (fr) 1989-12-13
EP0335978B1 (fr) 1995-11-08
DE3854666D1 (de) 1995-12-14
WO1989002052A1 (fr) 1989-03-09
CN1011064B (zh) 1991-01-02
CN1032230A (zh) 1989-04-05
JPS6463721A (en) 1989-03-09
DE3854666T2 (de) 1996-04-25

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