WO1989002052A1 - Bruleur de turbine a gaz - Google Patents

Bruleur de turbine a gaz Download PDF

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Publication number
WO1989002052A1
WO1989002052A1 PCT/JP1988/000870 JP8800870W WO8902052A1 WO 1989002052 A1 WO1989002052 A1 WO 1989002052A1 JP 8800870 W JP8800870 W JP 8800870W WO 8902052 A1 WO8902052 A1 WO 8902052A1
Authority
WO
WIPO (PCT)
Prior art keywords
premixed
main
nozzle
air
auxiliary
Prior art date
Application number
PCT/JP1988/000870
Other languages
English (en)
Japanese (ja)
Inventor
Yasuo Iwai
Shigeru Azuhata
Kenichi Sohma
Kiyoshi Narato
Hironobu Kobayashi
Tooru Inada
Tadayoshi Murakami
Norio Arashi
Yoji Ishibashi
Michio Kuroda
Original Assignee
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
Application filed by Hitachi, Ltd. filed Critical Hitachi, Ltd.
Priority to DE3854666T priority Critical patent/DE3854666T2/de
Priority to EP88907798A priority patent/EP0335978B1/fr
Publication of WO1989002052A1 publication Critical patent/WO1989002052A1/fr

Links

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 particularly to a premixed combustion type gas turbine combustor in which fuel and air are mixed in advance and burned.
  • N0X Nitrogen oxides (N0X) generated during the combustion of fuel are generated by oxidizing nitrogen in the combustion air in a high-temperature atmosphere and producing NO. x makes up the majority.
  • the production of thermal N ⁇ x has a large temperature dependence, and the production increases as the flame temperature increases, and especially when the temperature exceeds 150 ° C, the production may increase rapidly.
  • the flame temperature changes depending on the mixture ratio of fuel and air, and becomes the highest when the fuel is burned near the stoichiometric amount of air where there is no excess or shortage to completely burn the fuel. In order to suppress the amount of NOx generated, it is necessary to lower the flame temperature.
  • a combustion device that uses a premixed flame in which an excess amount of air and fuel is mixed in advance with a theoretical amount of air and then injected into a combustor.
  • Premixed flames with a high air-to-air ratio can prevent the formation of locally high-temperature regions, which can reduce NOx emissions.
  • premixed flames have an air-to-air ratio of 1 It is most stable in the vicinity, and tends to blow out when the ejection speed is high, and at low ejection speed, the flame easily enters the nozzle and flashes back.
  • N 0 X The emission of N 0 X can be reduced.
  • reducing the flow rate of the fuel used for the diffusion flame and increasing the fuel flow rate of the premixed flame can reduce NOx, but increasing the premixed rate makes the flame unstable, so NOX emissions There is a limit to reducing the volume.
  • a problem when the gas turbine combustion system is completely premixed combustion is that a large amount of combustion air flows compared to the fuel flow rate during low-load operation, so the fuel becomes lean and ignites.
  • the flow rate of the premixed gas further increased in order to increase the supply material and the air flow rate, and there was a problem that the premixed flame was likely to blow and disappear. Disclosure of the invention
  • An object of the present invention is to provide a gas turbine combustor and a combustion method capable of stably burning a lean premixed air having an air ratio greater than 1 from a low load to a high load on a gas turbine. It is in.
  • a cylindrical main nozzle, an auxiliary nozzle formed on an outer peripheral portion of the main nozzle, a main premix air supply means for supplying a premix air to the main nozzle, and the main premix to the auxiliary nozzle This is achieved by a gas Durbin combustor characterized by comprising auxiliary premixed gas supply means for supplying a premixed gas having an air ratio smaller than that of air. Furthermore, a premixed combustion method for a gas turbine combustor, characterized in that premixed gas ejected from an opening of a cylindrical main nozzle is burned by a premixed flame formed on an outer periphery of the opening of the raw nozzle. Is also achieved.
  • the main flame which burns at high speed can be maintained by forming a stable auxiliary flame constantly at the base of the high air ratio combustion flame.
  • the gas turbine combustion system can be completely premixed combustion, and if the air ratio of the fuel-air mixture gas for the main flame is set from 1.0 to the high air ratio side to perform lean combustion, the gas turbine It has the effect of reducing the environmental pollutants NOx and CO generated from the combustor.
  • FIG. 1 is a partial cross-sectional view of a gas turbine combustor embodying the present invention
  • FIG. 2 is a cross-sectional view taken along the line ⁇ — ⁇ in FIG. 1
  • FIG. 3 is a detailed cross-sectional view of a nozzle portion in FIG.
  • Fig. 4 is a graph showing the relationship between the turbine load and the opening of each valve shown in Fig. 1, and Figs. 5 (a) and (b) show changes in the air ratio of the premixed gas.
  • Ete graph showing the relationship between the generated amount of the burned Kino NO x generation amount and the H 2, CO, FIG.
  • FIG. 6 (a) and (b) the air ratio obtained by using the combustor of the present invention 3.6 7 is a graph showing the composition of the exhaust gas in the radial direction of the flame nozzle, and FIG. 8 is a graph showing another embodiment of the gas turbine combustor of the present invention.
  • Fig. 9 is a simplified cross-sectional view along the line E-K in Fig. 8, and
  • Fig. 10 is a characteristic diagram showing the relationship between load fluctuation and fuel supply system in the gas turbine combustor in Fig. 8. It is.
  • FIG. 1 is a cross-sectional view of a gas turbine combustor embodying the present invention.
  • An inner cylinder 20 is arranged concentrically inside the cylindrical outer cylinder 10, and a rectangular space formed between the outer cylinder 10 and the inner cylinder 20 is discharged from a compressor (not shown).
  • An air passage 12 is formed to guide air to the head of the inner cylinder.
  • double end walls 11 and 12 are provided at the head of the inner cylinder 20 .
  • Auxiliary nozzles 15 are open so that they surround the surroundings.
  • the main nozzle 14 is formed at the right end of a cylindrical premix cylinder 16 extending through the end wall 12 to the outer end wall 12 side, and the left end of the premix cylinder 16 is formed at the end wall 1 Air is taken in from the air chamber 17 formed on the left side of 2.
  • a fuel supply pipe 18 is inserted into each premixing cylinder 16, and an end of the fuel supply pipe 18 is provided. When fuel flows out of the cylinder 16, it mixes with air to generate a premixed gas.
  • the auxiliary nozzle 15 communicates with an auxiliary premixing chamber 30 formed between the end walls 11 and 12, and the chamber 30 is provided with a uniform premixing chamber from a bench lily mixer 31. An air-fuel mixture is supplied.
  • the fuel adjusted to atmospheric pressure is sucked into Generates a premixed gas.
  • the fuel supply pipes 18 are communicated with the main fuel regulating valve 60 via stop valves 50 provided on the respective pipes.
  • the valves 50 and 60 are controlled by a command from the controller 70.
  • the controller 70 receives the gas turbine load and rotation speed signals.
  • the stop valve 50 is fully opened when an open signal is given from the controller 70, and is kept fully closed otherwise. Although only four stop valves are shown in FIG. 1, they are provided in all fuel supply pipes 19, and in this embodiment there are 19 stop valves, and FIG. As shown, as the load on the turbine increases, the number of open stop valves increases. On the other hand, the opening of the regulating valve 60 increases almost in proportion to the turbine load. The regulating valve 40 maintains an almost constant opening (about 10%) regardless of the turbine load. Thus, the premixed gas introduced into the auxiliary premixing chamber 30 becomes a uniform premixed gas in the mixer 31 and has an air ratio in the range of 0.8 to 1.2. The air adjusting valve 40 is adjusted so that the air blowing rate is set to a certain value and the ejection speed from the auxiliary nozzle 15 is almost the same as the combustion speed.
  • the auxiliary flame air regulating valve 40 When operating the gas turbine, first, the auxiliary flame air regulating valve 40 is opened, and the auxiliary premixed gas is generated by the mixer 31. Next, a premixed gas ejected from the auxiliary nozzle 15 is ignited by an ignition plug (not shown).
  • the air ratio of the auxiliary premixed gas is set to around 1, that is, 0.8 to 1.2, and the injection speed is 0.4 m, which is almost the same as the combustion speed, so ignition is reliable and stable after ignition Burn.
  • the stop valves 50 are sequentially opened, the number of flames formed in the main nozzles 14 also increases, and at the rated load, flames are formed in all the main nozzles 14.
  • the turbine rotation speed is constant from 0% to 100% load, so the air supplied to the combustor is Almost constant. Therefore, the amount of air flowing into the premix cylinder 16 from the air chamber 17 is substantially constant.
  • the number of open stop valves 50 changes according to the amount of fuel.
  • the amount of fuel supplied to the premix cylinder is substantially constant, and the air ratio of the air-fuel mixture generated in the premix cylinder 16 does not change significantly. Therefore, in this embodiment, the air ratio is from 1.2 to 2. 5 is set.
  • the premixed air of the auxiliary nozzle 15 is set to a range in which the air ratio is close to 1 and the flame holding property is good, the premixed air from the main nozzle 14 is 20 mZ s or more.
  • the premixed air from the main nozzle 14 is 20 mZ s or more.
  • the main nozzle 14 constantly blows air at a high speed of 20 m / s to 70 ms, there is no danger of flashback.
  • the premixed gas from the main nozzle 14 is stably burned by the auxiliary flame, even if the air ratio is lean such as 1.5 or more.
  • Fig. 5 (a), (b) and 6th (a), (b) show the NOx and CO emissions when the premixed air is burned with the air ratio changed. It shows the relationship.
  • the inner diameter of the combustion cylinder is ⁇ 90 ran, height 7 '; mm
  • Fig. 5 (b) shows the combustion cylinder when the premixed flame is formed under the same combustion conditions when the inside diameter of the combustion cylinder is 0 2 O 8 ran and the height is 6 24. This is the result of analysis of the exhaust gas.
  • Fig. 5 (b) shows the analysis of exhaust gas up to the high air ratio range of 3.6.
  • the main flame has an air ratio of 1.5 or more, so the amount of N0X generated is markedly small and small as shown in 181, CO, CO, H 2 is almost zero, as seen in 1991 and 201 respectively.
  • 02 shows a characteristic like 211. .
  • the air ratio of the premixed gas in the auxiliary nozzle is close to 1, so the amount of generated NOx increases, but the fuel ratio of the auxiliary flame is about 10% at the rated load, so the overall Therefore, the amount of N ⁇ X generated is reduced.
  • Fig. 7 shows the sampling and probe movement from the center of the nozzle to the five thighs in the downstream direction from the main nozzle (inner diameter of about 26 mm), and sampling and analysis of the fuel gas from the center of the nozzle.
  • This is a study of the combustion state near, and the auxiliary flame.
  • CH4 burns as it approaches the auxiliary flame, and above the auxiliary flame nozzle, CH4 burns 100%.
  • the main flame starts from the auxiliary flame of the auxiliary nozzle. It can be seen that the nozzle was surely transferred to the premixed gas.
  • the dimension of the wrench used in this example is 26 for the main nozzle inner diameter, the spacer thickness around the main nozzle is 2 ran, and the auxiliary nozzle is 2 nm.
  • Fig. 8 shows that the main nozzles provided on the end wall on the head side of the combustor inner cylinder are divided into three groups, and the main nozzles blow out when the turbine load is varied in the range of 20% to 100%.
  • the amount of fuel supplied to each nozzle group is independently increased or decreased so that the air ratio of the fuel-air mixture becomes within the range of 1 * 2 to 2,5.
  • This is an example of a gas turbine combustor that suppresses the amount of NOx and CO generated.
  • the numbers given to the main nozzles in the combustor ⁇ front view shown in Fig. 9 are the classification numbers of the main nozzle group divided into three. The number of main nozzles in each nozzle group was four.
  • 6 1, 6 2, 6 3 are flow regulating valves, 61 increases / decreases the amount of fuel supplied to the second nozzle group, 62 is the first nozzle group, and ⁇ 63 is the third nozzle group. Adjustment valve.
  • Reference numeral 19 denotes a diffusion flame parner for igniting a pilot frame formed in the auxiliary nozzle, which stops supplying the feed after forming the pilot frame in the auxiliary nozzle. And the flame is extinguished.
  • Fig. 10 shows the change in the amount of fuel supplied to each nozzle group when the load on the gas turbine combustor in Fig. 8 was changed. Things.
  • Turbine load From 0% to 39%, fuel was supplied only to the first nozzle group, and when the air ratio of the dominate-air premixed gas ejected from the main nozzle became 1.25. Then, the fuel supply is reduced until the air ratio becomes 2.5, and at the same time, 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 second nozzle group is fixed.
  • the turbine load increases from 39% to 60%.
  • the auxiliary flame having a low ejection speed is used as an auxiliary flame for igniting and maintaining a premixed flame (main flame) having a high ejection speed. Therefore, the injection speed of the premixed gas to form a pilot flame for flame holding is set to approximately 0.4 m / s, the same as the combustion speed, and by setting the air ratio to 0.8 to 1.2, NO x And to prevent blowout.
  • the vortex formed by the velocity difference of the jet of the fuel stably flows between the main flame auxiliary and the auxiliary flame parner, and between the main flame premixed air and the auxiliary flame premixed air.
  • the main flame and the auxiliary flame are separated by a thin wall such as a knife edge without using a spacer, the flow of the auxiliary flame is determined by the jet of the main flame. In the experiment where the main flame was blown out and the main flame blown out, the auxiliary flame also went out. It is clear.
  • the main flame and the auxiliary flame do not directly mix near the burner outlet, and some of the rainy people mix in the vortex formed by the spacer. Since the auxiliary flame can always be stably formed without being affected by the main flame, the effect of increasing the range of the flow velocity or air ratio at which the main flame is stably formed can also be obtained.

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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.
PCT/JP1988/000870 1987-09-04 1988-08-31 Bruleur de turbine a gaz WO1989002052A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE3854666T DE3854666T2 (de) 1987-09-04 1988-08-31 Gasturbinenbrenner.
EP88907798A EP0335978B1 (fr) 1987-09-04 1988-08-31 Bruleur de turbine a gaz

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP62/220206 1987-09-04
JP62220206A JP2528894B2 (ja) 1987-09-04 1987-09-04 ガスタ―ビン燃焼器

Publications (1)

Publication Number Publication Date
WO1989002052A1 true WO1989002052A1 (fr) 1989-03-09

Family

ID=16747549

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP1988/000870 WO1989002052A1 (fr) 1987-09-04 1988-08-31 Bruleur de turbine a gaz

Country Status (5)

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

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EP0691511A1 (fr) * 1994-06-10 1996-01-10 General Electric Company Méthode de régulation pour une chambre de combustion d'une turbine à gaz

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EP1531305A1 (fr) * 2003-11-12 2005-05-18 United Technologies Corporation Injecteur de carburant multi-point
JP4015656B2 (ja) * 2004-11-17 2007-11-28 三菱重工業株式会社 ガスタービン燃焼器
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
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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
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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
DE102013204307A1 (de) 2013-03-13 2014-09-18 Siemens Aktiengesellschaft Strahlbrenner mit Kühlkanal in der Grundplatte
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
FR3135114A1 (fr) * 2022-05-02 2023-11-03 Safran Procede d’injection de melange hydrogene-air pour bruleur de turbomachine

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Also Published As

Publication number Publication date
EP0335978A1 (fr) 1989-10-11
CN1032230A (zh) 1989-04-05
EP0335978B1 (fr) 1995-11-08
CN1011064B (zh) 1991-01-02
EP0335978A4 (fr) 1989-12-13
JP2528894B2 (ja) 1996-08-28
JPS6463721A (en) 1989-03-09
DE3854666D1 (de) 1995-12-14
DE3854666T2 (de) 1996-04-25

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