JP2010133339A - Operating method of gas turbine and gas turbine combustor - Google Patents

Operating method of gas turbine and gas turbine combustor Download PDF

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JP2010133339A
JP2010133339A JP2008310376A JP2008310376A JP2010133339A JP 2010133339 A JP2010133339 A JP 2010133339A JP 2008310376 A JP2008310376 A JP 2008310376A JP 2008310376 A JP2008310376 A JP 2008310376A JP 2010133339 A JP2010133339 A JP 2010133339A
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fuel
gas turbine
hydrogen
burner
starting
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JP4997217B2 (en
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Tomohiro Asai
智広 浅井
Shohei Yoshida
正平 吉田
Hiromi Koizumi
浩美 小泉
Tomoki Koganezawa
知己 小金沢
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Hitachi Ltd
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Abstract

<P>PROBLEM TO BE SOLVED: To cut down fuel cost by reducing the use amount of starting fuel. <P>SOLUTION: In an operating method of a gas turbine, a burner including a fuel nozzle for injecting fuel into a combustion chamber and an air nozzle for supplying combustion air to the combustion chamber is provided with a starting fuel supply system which supplies starting fuel employed for ignition and start-up of the gas turbine. When igniting the gas turbine, the starting fuel and fuel through the fuel nozzle are supplied to the combustion chamber. The supply of the starting fuel is stopped before the gas turbine reaches the no-load rotation speed. Therefore, the use amount of starting fuel is reduced to cut down the fuel cost. <P>COPYRIGHT: (C)2010,JPO&INPIT

Description

本発明は、ガスタービンの運転方法及びガスタービン燃焼器に関する。   The present invention relates to a gas turbine operating method and a gas turbine combustor.

近年、資源有効利用や発電コスト低減の観点から、製油所で発生するオフガスや製鉄所で発生するコークス炉ガスなどの副生燃料をガスタービンに利用することが検討されている。これらは安価な燃料であり、高効率なガスタービンで利用できれば燃料費を大幅に削減できる。   In recent years, from the viewpoint of effective use of resources and reduction of power generation costs, use of by-product fuel such as off-gas generated at refineries and coke oven gas generated at ironworks for gas turbines has been studied. These are inexpensive fuels, and if they can be used in highly efficient gas turbines, the fuel costs can be greatly reduced.

これらの副生燃料は、一般に水素を多く含むため、ガスタービン燃料として扱うには注意が必要である。ガスタービンの主要燃料として使用されている液化天然ガス（ＬＮＧ）などに比べ、水素は燃焼速度が速く、可燃範囲が広いうえに、火炎温度が高いという特徴をもつ。特に、燃焼速度が速いことから、予混合燃焼では逆火ポテンシャルが高くなる。そのため、特許文献１に示されているような拡散燃焼方式を採用するのが一般的である。しかし、拡散燃焼では局所的に火炎温度が高くなる領域が存在し、ＮＯｘ濃度が高くなるため、蒸気や窒素を噴射してＮＯｘ低減を図っている。   Since these by-product fuels generally contain a large amount of hydrogen, they must be handled with care as gas turbine fuels. Compared to liquefied natural gas (LNG), which is used as a main fuel for gas turbines, hydrogen has a high combustion speed, a wide flammable range, and a high flame temperature. In particular, since the combustion speed is high, the flashback potential is high in the premixed combustion. For this reason, it is common to employ a diffusion combustion system as disclosed in Patent Document 1. However, in diffusion combustion, there is a region where the flame temperature locally increases, and the NOx concentration becomes high. Therefore, steam and nitrogen are injected to reduce NOx.

これに対して、特許文献２では蒸気や窒素を使用しない低ＮＯｘ燃焼器の構造が開示されている。この燃焼器は、バーナ出口に多数設けられた空気ノズル、及びこの空気ノズルの上流側に設けられた燃料ノズルが配置されている。そして、空気ノズル内部では、燃料流の外周側に環状の空気流が形成される。空気ノズルから噴出した燃料流と空気流は、燃焼室で急速に混合することで、ＮＯｘ低減を図っている。このバーナは燃料と空気の予混合距離が短いために逆火ポテンシャルが低く、高カロリー燃料から燃焼速度の速い水素含有ガス燃料まで幅広い燃料の低ＮＯｘ燃焼に有効である。   On the other hand, Patent Document 2 discloses a structure of a low NOx combustor that does not use steam or nitrogen. In this combustor, a number of air nozzles provided at the burner outlet and a fuel nozzle provided upstream of the air nozzle are arranged. In the air nozzle, an annular air flow is formed on the outer peripheral side of the fuel flow. The fuel flow and air flow ejected from the air nozzle are rapidly mixed in the combustion chamber to reduce NOx. This burner has a low flashback potential due to the short premixing distance between fuel and air, and is effective for low-NOx combustion of a wide range of fuels, from high-calorie fuels to hydrogen-containing gas fuels with high combustion rates.

特開２００７−３３０２２号公報JP 2007-33022 A 特開２００３−１４８７３４号公報JP 2003-148734 A

上述のように水素含有ガス燃料は可燃範囲が広いため、特にガスタービン着火・起動時には安全面で注意を要する。燃焼器において、着火失敗や着火遅れ（着火に要する時間が長くなる）が発生すると、ガスタービン下流の排気ダクト内で空気と燃料の混合気が可燃範囲に達する可能性がある。そこで、このような課題を回避するため、起動用燃料として液体燃料や液化天然ガス（ＬＮＧ）などの他種燃料によりガスタービンを起動し、低負荷条件で水素含有ガス燃料に切り替える方法を採用している。   As described above, since hydrogen-containing gas fuel has a wide flammable range, care must be taken in terms of safety, particularly during gas turbine ignition and startup. In the combustor, when ignition failure or ignition delay (the time required for ignition becomes long) occurs, the air-fuel mixture may reach the combustible range in the exhaust duct downstream of the gas turbine. Therefore, in order to avoid such problems, a method is adopted in which the gas turbine is started with other types of fuel such as liquid fuel or liquefied natural gas (LNG) as the starting fuel and switched to hydrogen-containing gas fuel under low load conditions. ing.

しかし、この方法では水素含有ガス燃料に切り替える負荷条件まで起動用燃料を供給する必要があり、起動用燃料の費用がかかるという課題が残る。   However, in this method, it is necessary to supply the starting fuel up to the load condition for switching to the hydrogen-containing gas fuel, and there remains a problem that the cost of the starting fuel is high.

そこで、本発明は起動用燃料の使用量を減らし、燃料費を低減することを目的としている。   Therefore, the present invention has an object of reducing the fuel consumption by reducing the amount of start-up fuel used.

本発明は、ガスタービン着火の際に、起動用燃料と燃料ノズルからの燃料を燃焼室に供給し、ガスタービンの無負荷回転数に達する前に、起動用燃料の供給を停止することを特徴とする。   The present invention is characterized in that, when the gas turbine is ignited, the starting fuel and the fuel from the fuel nozzle are supplied to the combustion chamber, and the supply of the starting fuel is stopped before reaching the no-load rotational speed of the gas turbine. And

本発明によれば、起動用燃料の使用量を減らし、燃料費を低減することが可能である。   According to the present invention, it is possible to reduce the usage amount of the starting fuel and reduce the fuel cost.

ガスタービンの燃料供給システムおよび着火・運転方法について、図面で説明する。   A gas turbine fuel supply system and ignition / operation method will be described with reference to the drawings.

図２は拡散燃焼方式を採用したガスタービン燃焼器を含むガスタービンプラントの概略構成図である。まず、ガスタービンプラントの概要を説明する。ガスタービンプラント１は、大気より吸入空気１０１を吸入して圧縮する空気圧縮機２、空気圧縮機２により圧縮された燃焼用空気１０２と水素含有ガス燃料２０１を燃焼させ、燃焼ガス１１０を生成する燃焼器３、発生した燃焼ガス１１０を導いて駆動するタービン４、タービン４により回転し発電する発電機６、およびガスタービン起動時に空気圧縮機２を起動するガスタービン起動用モータ８を備える。タービン４を駆動した後の燃焼ガス１１０は、排気ガス１１１となってタービン４から排出される。   FIG. 2 is a schematic configuration diagram of a gas turbine plant including a gas turbine combustor employing a diffusion combustion system. First, the outline of the gas turbine plant will be described. The gas turbine plant 1 generates combustion gas 110 by burning an air compressor 2 that sucks and compresses intake air 101 from the atmosphere, combustion air 102 compressed by the air compressor 2, and hydrogen-containing gas fuel 201. A combustor 3, a turbine 4 that guides and drives the generated combustion gas 110, a generator 6 that rotates by the turbine 4 and generates electric power, and a gas turbine activation motor 8 that activates the air compressor 2 when the gas turbine is activated are provided. The combustion gas 110 after driving the turbine 4 becomes exhaust gas 111 and is exhausted from the turbine 4.

次に、バーナ１３の構造を説明する。バーナ１３は、起動用燃料２００を燃焼室５内に噴射する起動用燃料ノズル２０が、燃焼器３の軸中心部に設けられている。本実施例では、起動用燃料として灯油や軽油などの油燃料や、液化天然ガス（ＬＮＧ）や液化石油ガス（ＬＰＧ）、メタンなどの高カロリガス燃料を想定する。起動用燃料ノズル２０の外周には、燃料を微粒化するための噴霧空気１０３を噴射する噴霧空気ノズル２１を設置している。噴霧空気ノズル２１は、起動用燃料２００が油燃料の場合に使用する。噴霧空気１０３は、空気圧縮機２から抽気した抽気空気１０４を、昇圧圧縮機７により昇圧した後に、噴霧空気ノズル２１に供給される。噴霧空気ノズル２１の外周には水素含有ガス燃料ノズル２２を備えている。水素含有ガス燃料２０１は、水素含有ガス燃料孔１８を通って燃焼室５に噴射する。水素含有ガス燃料は、製油所あるいは化学プラントで発生するオフガスや、製鉄プロセスで発生するコークス炉ガス，石炭や重質油を原料としそれらを酸素でガス化して得られるガス化ガスなどのガス燃料を想定する。水素含有ガス燃料ノズル２２の外周には、火炎安定化のために燃焼用空気１０２ａに旋回を与える空気旋回器１７を備えている。燃焼用空気１０２ａは、空気圧縮機２から燃焼器３に供給され、主室ライナ１２を冷却した後に、空気旋回器１７を通って燃焼室５に供給される。   Next, the structure of the burner 13 will be described. The burner 13 is provided with a starting fuel nozzle 20 for injecting the starting fuel 200 into the combustion chamber 5 at the axial center of the combustor 3. In this embodiment, oil fuel such as kerosene and light oil, and high calorie gas fuel such as liquefied natural gas (LNG), liquefied petroleum gas (LPG), and methane are assumed as the starting fuel. A spray air nozzle 21 for injecting spray air 103 for atomizing the fuel is installed on the outer periphery of the starting fuel nozzle 20. The atomizing air nozzle 21 is used when the starting fuel 200 is oil fuel. The atomizing air 103 is supplied to the atomizing air nozzle 21 after boosting the extracted air 104 extracted from the air compressor 2 by the boosting compressor 7. A hydrogen-containing gas fuel nozzle 22 is provided on the outer periphery of the atomizing air nozzle 21. The hydrogen-containing gas fuel 201 is injected into the combustion chamber 5 through the hydrogen-containing gas fuel hole 18. Hydrogen-containing gas fuels are gas fuels such as off-gas generated at refineries or chemical plants, coke oven gas generated during the iron-making process, and gasified gas obtained by gasifying coal or heavy oil as raw materials with oxygen. Is assumed. An air swirler 17 is provided on the outer periphery of the hydrogen-containing gas fuel nozzle 22 to swirl the combustion air 102a for flame stabilization. Combustion air 102 a is supplied from the air compressor 2 to the combustor 3, cools the main chamber liner 12, and then is supplied to the combustion chamber 5 through the air swirler 17.

図３は、比較例におけるガスタービンプラントの着火・運転方法である。比較例では、負荷併入前まで起動用燃料のみでガスタービンを運転させ、負荷併入と同時に水素含有ガス燃料の供給を開始する例を示す。本図は、比較例の着火・運転方法において、ガスタービンの着火から定格負荷条件までの起動用燃料２００と水素含有ガス燃料２０１の流量の時間変化を示す概念図である。図中の３００は起動用燃料２００の流量変化、３０１は水素含有ガス燃料２０１の流量変化を示している。また、ａ〜ｄ，ｎの状態は、
ａ）着火
ｂ）無負荷定格回転数
ｃ）負荷併入
ｄ）定格負荷条件
ｎ）起動用燃料の供給停止
の時期を示している。 FIG. 3 shows an ignition / operation method of a gas turbine plant in a comparative example. In the comparative example, an example is shown in which the gas turbine is operated only with the starting fuel before the load is introduced, and the supply of the hydrogen-containing gas fuel is started simultaneously with the loading. This figure is a conceptual diagram showing temporal changes in the flow rates of the starting fuel 200 and the hydrogen-containing gas fuel 201 from the ignition of the gas turbine to the rated load condition in the ignition / operation method of the comparative example. In the figure, 300 indicates a change in the flow rate of the starting fuel 200, and 301 indicates a change in the flow rate of the hydrogen-containing gas fuel 201. Also, the states of a to d, n are
a) Ignition b) No-load rated speed c) Load loading d) Rated load condition n) Indicates the timing of stopping the supply of starting fuel.

起動時、ガスタービンはガスタービン起動用モータ８などの外部動力によって駆動する。燃焼器の着火条件に相当するガスタービン回転数まで上昇させた後、回転数を一定に保持することで、燃焼器３に着火相当の燃焼用空気１０２が供給され、着火条件が成立する。そこで、点火栓を作動させ、起動用燃料２００を供給し着火する（ａ点）。着火後、起動用燃料２００の流量を増加させることにより昇速させ、無負荷定格回転数の状態に達する（ｂ点）。その後、負荷を併入し（ｃ点）、起動用燃料２００の流量を減少させつつ、水素含有ガス燃料２０１の供給を開始する。そして、燃料を切り替えながら負荷を上昇させ、定格負荷条件に達する（ｄ点）。なお、起動用燃料２００の供給は、定格負荷条件に達するまでに停止する（ｎ点）。   At startup, the gas turbine is driven by external power such as a gas turbine startup motor 8. After raising the rotational speed of the gas turbine corresponding to the ignition condition of the combustor and holding the rotational speed constant, the combustion air 102 corresponding to the ignition is supplied to the combustor 3 and the ignition condition is satisfied. Therefore, the ignition plug is operated, the starting fuel 200 is supplied and ignited (point a). After ignition, the flow rate of the starting fuel 200 is increased to increase the speed and reach the state of the no-load rated rotational speed (point b). Thereafter, the load is added (point c), and the supply of the hydrogen-containing gas fuel 201 is started while the flow rate of the starting fuel 200 is decreased. Then, the load is increased while the fuel is switched to reach the rated load condition (point d). The supply of the starting fuel 200 is stopped until the rated load condition is reached (n point).

しかし、比較例の方法では水素含有ガス燃料２０１に切り替える条件まで起動用燃料２００を供給する必要がある。製油所で副生するオフガスなどの安価な水素含有ガス燃料に対し、起動用燃料は一般に価格が高い。そのため、比較例の着火・運転方法では燃料費がかかるという課題があった。   However, in the method of the comparative example, it is necessary to supply the starting fuel 200 up to the condition for switching to the hydrogen-containing gas fuel 201. Start-up fuels are generally more expensive than cheap hydrogen-containing gas fuels such as off-gas produced as a by-product at refineries. For this reason, the ignition / operation method of the comparative example has a problem that fuel costs are required.

そこで、本実施例における着火・運転方法を図１で説明する。図中の３１０は起動用燃料２００の流量変化、３１１は水素含有ガス燃料２０１の流量変化を示している。また、ａ〜ｄ、ｎの状態は上記の通りである。図１では、着火の際に起動用燃料２００と水素含有ガス燃料２０１を同時に供給する。燃焼器３に着火相当の燃焼用空気１０２を供給した着火条件において、点火栓を作動させて、起動用燃料２００と同時に水素含有ガス燃料２０１を供給し、着火する（ａ点）。ここで、本実施例における「同時」とは、起動用燃料２００を供給し着火した直後を意味する。また、起動用燃料２００を供給し燃焼器３の着火を確認した後、直ちに水素含有ガス燃料２０１を供給することも含む。水素含有ガス燃料２０１は起動用燃料２００とともに供給されるので、着火失敗や着火遅れは発生せず、ガスタービン下流の排気ダクト内で空気と燃料の混合気が可燃範囲になることを回避できる。着火後、起動用燃料２００の流量を減少させつつ、水素含有ガス燃料２０１の流量を増加させ、昇速させて、無負荷定格回転数の状態にする（ｂ点）。なお、起動用燃料２００の供給は無負荷定格回転数の状態（ｂ点）に達するまでに停止する（ｎ点）。その後、負荷を併入し（ｃ点）、水素含有ガス燃料２０１の流量を増加させることにより、負荷を上昇させ、定格負荷条件に達する（ｄ点）。このように、水素含有ガス燃料への着火を早期に行うことで、ガスタービンの無負荷回転数に達する前に、起動用燃料の供給を停止することができる。   The ignition / operation method in this embodiment will be described with reference to FIG. In the figure, 310 indicates a change in the flow rate of the starting fuel 200, and 311 indicates a change in the flow rate of the hydrogen-containing gas fuel 201. The states a to d and n are as described above. In FIG. 1, the starting fuel 200 and the hydrogen-containing gas fuel 201 are simultaneously supplied at the time of ignition. Under the ignition condition in which combustion air 102 corresponding to ignition is supplied to the combustor 3, the spark plug is operated, the hydrogen-containing gas fuel 201 is supplied simultaneously with the starting fuel 200, and ignition is performed (point a). Here, “simultaneous” in this embodiment means immediately after the start-up fuel 200 is supplied and ignited. Further, it also includes supplying the hydrogen-containing gas fuel 201 immediately after supplying the starting fuel 200 and confirming the ignition of the combustor 3. Since the hydrogen-containing gas fuel 201 is supplied together with the start-up fuel 200, ignition failure or ignition delay does not occur, and it is possible to avoid the mixture of air and fuel in the combustible range in the exhaust duct downstream of the gas turbine. After ignition, the flow rate of the hydrogen-containing gas fuel 201 is increased while the flow rate of the starting fuel 200 is decreased, and the flow rate is increased to achieve a no-load rated rotational speed (b point). The supply of the starting fuel 200 is stopped (point n) before reaching the state of the no-load rated speed (point b). Thereafter, the load is added (point c), and the load is increased by increasing the flow rate of the hydrogen-containing gas fuel 201 to reach the rated load condition (point d). In this way, by igniting the hydrogen-containing gas fuel at an early stage, the supply of the starting fuel can be stopped before reaching the no-load rotational speed of the gas turbine.

このように、起動用燃料２００の供給開始（ａ点）から停止（ｎ点）までの時間を短縮でき、その燃料費を節約することが可能である。なお、起動用燃料２００の供給に関して、油燃料の場合は簡易的な燃料タンク、またガス燃料の場合は簡易的なガスボンベを設置し、それらから燃料を供給してもよい。   In this manner, the time from the start (point a) to the stop (point n) of supply of the starting fuel 200 can be shortened, and the fuel cost can be saved. Regarding the supply of the starting fuel 200, a simple fuel tank may be installed in the case of oil fuel, and a simple gas cylinder may be installed in the case of gas fuel, and the fuel may be supplied therefrom.

本実施例は、特許文献２で開示されている、蒸気や窒素を使用しない低ＮＯｘ燃焼器の着火方法に関する。   The present embodiment relates to an ignition method of a low NOx combustor that does not use steam or nitrogen, which is disclosed in Patent Document 2.

図４，図５は予混合低ＮＯｘ燃焼器の正面図および側面図を燃料供給系統とともに示している。燃焼器３は多缶で構成されるが、図４では点火栓缶３ａと、隣接する燃焼器３ｂ、３ｃのみを示している。また、燃焼器３は、隣接する燃焼器３ｂ，３ｃへの火移り・着火を行うためのクロスファイヤー管９０を備えている。点火栓缶３ａにて着火後、圧力の上昇によって隣接する燃焼器３ｂ，３ｃにクロスファイヤー管９０を通じて燃焼ガス１１０が流れ、着火する。燃焼器３は、燃料を燃焼室５に供給する燃料ノズル３０と、燃料ノズル３０の下流側に配置され、燃焼用空気１０２を供給する空気孔３１（空気ノズル）が多数配置されたバーナを複数個備えている。空気孔３１（空気ノズル）は、空気孔プレートに配置されている。このような燃料ノズル及び空気孔（空気ノズル）の配置により、空気孔において燃料流の外周側に環状の空気流が流れる。本図には、燃焼器の軸中心部に中央バーナ５１ａを１つ、その外周に外周バーナを６つ（５１ｂ〜５１ｇ）備えた状態を示している。このような構造により、燃料と空気を急速に混合することで希薄予混合燃焼によるＮＯｘ低減を図っている。   4 and 5 show a front view and a side view of the premixed low NOx combustor together with the fuel supply system. Although the combustor 3 is composed of multiple cans, FIG. 4 shows only the spark plug can 3a and the adjacent combustors 3b and 3c. In addition, the combustor 3 includes a cross fire tube 90 for transferring and igniting the adjacent combustors 3b and 3c. After ignition in the spark plug can 3a, the combustion gas 110 flows through the cross fire pipe 90 to the adjacent combustors 3b and 3c due to the increase in pressure, and ignites. The combustor 3 includes a fuel nozzle 30 that supplies fuel to the combustion chamber 5, and a plurality of burners that are arranged on the downstream side of the fuel nozzle 30 and that have a large number of air holes 31 (air nozzles) that supply combustion air 102. I have one. The air hole 31 (air nozzle) is disposed in the air hole plate. Due to the arrangement of the fuel nozzle and the air hole (air nozzle), an annular air flow flows on the outer peripheral side of the fuel flow in the air hole. This figure shows a state in which one central burner 51a is provided at the axial center of the combustor and six outer peripheral burners (51b to 51g) are provided on the outer periphery thereof. With such a structure, fuel and air are rapidly mixed to reduce NOx by lean premixed combustion.

次に、本実施例の燃料供給系統を説明する。本実施例では、中央バーナ５１ａには水素含有ガス燃料２０１を供給し、外周バーナ５１ｂ〜５１ｇには水素含有ガス燃料２０１および起動用燃料２００を供給する燃料供給系統を備えている。図中には水素含有ガス燃料供給系統として、中央バーナ５１ａに燃料を供給する系統６０ａ、および外周バーナを２つずつ組み合わせて燃料を供給する系統６０ｂ，６０ｃ，６０ｇの合計４系統を示している。また、起動用燃料供給系統として、外周バーナ５１ｂ〜５１ｇに起動用燃料を供給する系統７０ｂ，７０ｃ，７０ｇの３系統を示している。そして、それぞれの燃料供給系統には、燃料流量を調整する燃料流量調整弁６１ａ，６１ｂ，６１ｃ，６１ｇ，７１ｂ，７１ｃ，７１ｇ、及び緊急時に燃料を遮断する遮断弁６２ａ，６２ｂ，６２ｃ，６２ｇ，７２ｂ，７２ｃ，７２ｇを備えている。   Next, the fuel supply system of the present embodiment will be described. In the present embodiment, a hydrogen supply gas fuel 201 is supplied to the central burner 51a, and a fuel supply system that supplies the hydrogen-containing gas fuel 201 and the starting fuel 200 to the outer peripheral burners 51b to 51g is provided. In the figure, as a hydrogen-containing gas fuel supply system, a total of four systems including a system 60a for supplying fuel to the central burner 51a and systems 60b, 60c and 60g for supplying fuel by combining two outer burners are shown. . In addition, three systems of systems 70b, 70c, and 70g that supply the startup fuel to the outer peripheral burners 51b to 51g are shown as the startup fuel supply system. Each of the fuel supply systems includes fuel flow rate adjusting valves 61a, 61b, 61c, 61g, 71b, 71c, 71g, and cutoff valves 62a, 62b, 62c, 62g for shutting off the fuel in an emergency. 72b, 72c, 72g.

本実施例の着火・運転方法を図６で説明する。図中の３２０は外周バーナ５１ｂ〜５１ｇに供給する起動用燃料２００の流量（外周バーナ５１ｂ〜５１ｇの合計）の時間変化、３２１は中央バーナ５１ａに供給する水素含有ガス燃料２０１の流量変化、また３２２は外周バーナ５１ｂ〜５１ｇに供給する水素含有ガス燃料２０１の流量（外周バーナ５１ｂ〜５１ｇの合計）の変化を示している。図中のａ〜ｄ，ｎの状態は実施例１で説明した通りである。   The ignition / operation method of the present embodiment will be described with reference to FIG. In the figure, 320 is a time change of the flow rate of the starting fuel 200 supplied to the outer peripheral burners 51b to 51g (total of the outer peripheral burners 51b to 51g), 321 is a flow rate change of the hydrogen-containing gas fuel 201 supplied to the central burner 51a, and Reference numeral 322 denotes a change in the flow rate of the hydrogen-containing gas fuel 201 supplied to the outer peripheral burners 51b to 51g (the total of the outer peripheral burners 51b to 51g). The states a to d, n in the figure are as described in the first embodiment.

本実施例では、上述の低ＮＯｘ燃焼器および燃料供給システムにおいて、着火の際に起動用燃料２００と水素含有ガス燃料２０１を同時に供給する。燃焼器３に着火相当の燃焼用空気１０２を供給した着火条件において、点火栓缶３ａの点火栓を作動させて、外周バーナ５１ｂ〜５１ｇに起動用燃料２００を供給し、それと同時に中央バーナ５１ａに水素含有ガス燃料２０１も供給し着火する（ａ点）。ここで、「同時」とは、起動用燃料２００を供給し着火した直後を意味する。また、起動用燃料２００を供給し燃焼器３の着火を確認した後、直ちに水素含有ガス燃料２０１を供給することも含む。外周バーナ５１ｂ〜５１ｇでは起動用燃料２００により着火して燃焼ガスが形成される。一方、中央バーナ５１ａでは、外周バーナ５１ｂ〜５１ｇで形成された燃焼ガスを火種にして、水素含有ガス燃料２０１により着火するため着火の失敗はなく、ガスタービン下流において、燃料と空気の混合気が可燃範囲となることを回避できる。また、点火栓缶３ａの外周バーナ５１ｂおよび５１ｄで形成された燃焼ガスが、クロスファイヤー管９０を通じて隣接する燃焼器３ｂ，３ｃに移り、隣接する燃焼器３ｂ，３ｃにおいても着火が起こる。本実施例では、外周バーナ５１ｂ〜５１ｇのすべてに起動用燃料２００を供給している。しかし、外周バーナ５１ｂと５１ｄにのみ起動用燃料２００を供給しても、隣接する燃焼器３ｂ，３ｃへの火移りが可能である。そのため、燃焼器３ｂ，３ｃのみに起動用燃料を供給することで、起動用燃料の使用量を更に低減でき、より効果的である。また、燃焼器３ｂ，３ｃのみに起動用燃料を供給する場合、起動用燃料供給系統は７０ｂの１系統のみあればよいため、初期設備コストの低減も可能である。   In this embodiment, in the above-described low NOx combustor and fuel supply system, the starting fuel 200 and the hydrogen-containing gas fuel 201 are simultaneously supplied at the time of ignition. Under the ignition condition in which combustion air 102 corresponding to ignition is supplied to the combustor 3, the ignition plug of the ignition plug can 3a is operated to supply the starting fuel 200 to the outer peripheral burners 51b to 51g, and at the same time to the central burner 51a. Hydrogen-containing gas fuel 201 is also supplied and ignited (point a). Here, “simultaneously” means immediately after the start-up fuel 200 is supplied and ignited. Further, it also includes supplying the hydrogen-containing gas fuel 201 immediately after supplying the starting fuel 200 and confirming the ignition of the combustor 3. The peripheral burners 51b to 51g are ignited by the starting fuel 200 to form combustion gas. On the other hand, in the central burner 51a, the combustion gas formed by the outer peripheral burners 51b to 51g is used as a fire type and ignited by the hydrogen-containing gas fuel 201. Therefore, there is no failure in ignition. It is possible to avoid becoming a flammable range. In addition, the combustion gas formed by the outer peripheral burners 51b and 51d of the spark plug can 3a moves to the adjacent combustors 3b and 3c through the crossfire tube 90, and ignition occurs in the adjacent combustors 3b and 3c. In this embodiment, the starting fuel 200 is supplied to all of the outer peripheral burners 51b to 51g. However, even if the starting fuel 200 is supplied only to the outer peripheral burners 51b and 51d, it is possible to transfer to the adjacent combustors 3b and 3c. Therefore, by supplying the starting fuel only to the combustors 3b and 3c, the amount of the starting fuel used can be further reduced, which is more effective. In addition, when starting fuel is supplied only to the combustors 3b and 3c, only one starting fuel supply system 70b is required, so that the initial equipment cost can be reduced.

このような方法で着火した後、外周バーナ５１ｂ〜５１ｇに供給していた起動用燃料２００の流量を減少させつつ、中央バーナ５１ａの水素含有ガス燃料２０１の流量を増加させながら昇速させ、無負荷定格回転数の状態に達する（ｂ点）。なお、起動用燃料２００の供給は無負荷定格回転数の状態（ｂ点）に達するまでに停止する（ｎ点）。その後、負荷を併入し（ｃ点）、中央バーナ５１ａの水素含有ガス燃料２０１の流量を減らしつつ、外周バーナ５１ｂ〜５１ｇに水素含有ガス燃料２０１を供給して、その流量を増加させる。そして、負荷を上昇させ、定格負荷条件に達する（ｄ点）。   After ignition by such a method, while increasing the flow rate of the hydrogen-containing gas fuel 201 in the central burner 51a while increasing the flow rate of the starting fuel 200 supplied to the outer peripheral burners 51b to 51g, the speed is increased. The state of the load rated speed is reached (point b). The supply of the starting fuel 200 is stopped (point n) before reaching the state of the no-load rated speed (point b). Thereafter, a load is added (point c), the hydrogen-containing gas fuel 201 is supplied to the outer peripheral burners 51b to 51g while the flow rate of the hydrogen-containing gas fuel 201 of the central burner 51a is reduced, and the flow rate is increased. Then, the load is increased to reach the rated load condition (point d).

このように、外周バーナ５１ｂ〜５１ｇにおける起動用燃料２００と、中央バーナ５１ａにおける水素含有ガス燃料２０１を同時に供給することにより、起動用燃料２００の供給開始（ａ点）から停止（ｎ点）までの時間を短縮できるため、その燃料費を節約することが可能である。   Thus, by simultaneously supplying the starting fuel 200 in the outer peripheral burners 51b to 51g and the hydrogen-containing gas fuel 201 in the central burner 51a, from the start of supply of the starting fuel 200 (point a) to the stop (point n). Therefore, the fuel cost can be saved.

図７は、本実施例における低ＮＯｘ燃焼器の正面図を燃料供給系統とともに示す。燃焼器３の構造およびバーナ配置などは、実施例２と同様である。燃料供給系統では、中央バーナ５１ａに水素含有ガス燃料２０１および起動用燃料２００を供給する系統、及び外周バーナ５１ｂ〜５１ｇに水素含有ガス燃料２０１のみを供給する系統を備えている。図中の水素含有ガス燃料供給系統は、中央バーナ５１ａに燃料を供給する系統６０ａ、および外周バーナを２つずつ組み合わせて燃料を供給する系統６０ｂ，６０ｃ，６０ｇの合計４系統がある。また、起動用燃料供給系統は、中央バーナ５１ａに燃料を供給する系統７０ａの１系統がある。   FIG. 7 shows a front view of the low NOx combustor in this embodiment together with the fuel supply system. The structure and burner arrangement of the combustor 3 are the same as those in the second embodiment. The fuel supply system includes a system that supplies the hydrogen-containing gas fuel 201 and the starting fuel 200 to the central burner 51a, and a system that supplies only the hydrogen-containing gas fuel 201 to the outer peripheral burners 51b to 51g. The hydrogen-containing gas fuel supply system in the figure includes a total of four systems: a system 60a that supplies fuel to the central burner 51a, and systems 60b, 60c, and 60g that supply fuel by combining two outer peripheral burners. The starting fuel supply system includes one system 70a that supplies fuel to the central burner 51a.

上記の構成をもつガスタービンの着火・運転方法について、図８で説明する。図中の３３０は中央バーナ５１ａに供給する起動用燃料２００の流量変化、３３１は中央バーナ５１ａに供給する水素含有ガス燃料２０１の流量変化、また３３２は外周バーナ５１ｂ〜５１ｇに供給する水素含有ガス燃料２０１の流量（外周バーナ５１ｂ〜５１ｇの合計）の変化を示している。図中のａ〜ｄ，ｎの状態は上述の通りである。燃焼器３に着火相当の燃焼用空気１０２を供給した着火条件において、点火栓缶３ａの点火栓を作動させて、中央バーナ５１ａに起動用燃料２００を供給し、それと同時に外周バーナ５１ｂ〜５１ｇに水素含有ガス燃料２０１を供給し着火する（ａ点）。ここで、「同時」とは、起動用燃料２００を供給し着火した直後を意味する。また、起動用燃料２００を供給し燃焼器３の着火を確認した後、直ちに水素含有ガス燃料２０１を供給することも含む。中央バーナ５１ａでは起動用燃料２００により着火して燃焼ガスが形成され、外周バーナ５１ｂ〜５１ｇでは、中央バーナ５１ａで形成された燃焼ガスを火種にして水素含有ガス燃料２０１により着火するため、着火の失敗はない。また、点火栓缶３ａの中央バーナ５１ａで形成された燃焼ガスがクロスファイヤー管９０を通じて、隣接する燃焼器３ｂ，３ｃに移り、隣接燃焼器においても着火が起こる。   The ignition / operation method of the gas turbine having the above-described configuration will be described with reference to FIG. In the figure, 330 is a flow rate change of the starting fuel 200 supplied to the central burner 51a, 331 is a flow rate change of the hydrogen-containing gas fuel 201 supplied to the central burner 51a, and 332 is a hydrogen-containing gas supplied to the outer peripheral burners 51b to 51g. A change in the flow rate of the fuel 201 (the total of the outer peripheral burners 51b to 51g) is shown. The states a to d, n in the figure are as described above. Under ignition conditions in which combustion air 102 equivalent to ignition is supplied to the combustor 3, the ignition plug of the ignition plug can 3a is operated to supply the starting fuel 200 to the central burner 51a, and at the same time to the outer peripheral burners 51b to 51g. Hydrogen-containing gas fuel 201 is supplied and ignited (point a). Here, “simultaneously” means immediately after the start-up fuel 200 is supplied and ignited. Further, it also includes supplying the hydrogen-containing gas fuel 201 immediately after supplying the starting fuel 200 and confirming the ignition of the combustor 3. The central burner 51a is ignited by the starting fuel 200 to form combustion gas, and the outer peripheral burners 51b to 51g are ignited by the hydrogen-containing gas fuel 201 using the combustion gas formed by the central burner 51a as a fire type. There is no failure. Further, the combustion gas formed by the central burner 51a of the spark plug can 3a moves to the adjacent combustors 3b and 3c through the cross fire tube 90, and ignition occurs in the adjacent combustors.

このように着火した後、中央バーナ５１ａの起動用燃料２００の流量を減少させつつ、外周バーナ５１ｂ〜５１ｇの水素含有ガス燃料２０１の流量を増加させる。そして、昇速させ、無負荷定格回転数の状態にする（ｂ点）。なお、起動用燃料２００の供給は無負荷定格回転数の状態（ｂ点）に達するまでに停止する（ｎ点）。その後、負荷を併入し（ｃ点）、外周バーナ５１ｂ〜５１ｇにおける水素含有ガス燃料２０１の流量は引き続き増やすとともに、中央バーナ５１ａに水素含有ガス燃料２０１を供給し流量を増加させる。そして、負荷を上昇させ、定格負荷条件に達する（ｄ点）。   After ignition in this way, the flow rate of the hydrogen-containing gas fuel 201 in the outer peripheral burners 51b to 51g is increased while the flow rate of the starting fuel 200 in the central burner 51a is decreased. Then, the speed is increased to a no-load rated rotational speed (point b). The supply of the starting fuel 200 is stopped (point n) before reaching the state of the no-load rated speed (point b). Thereafter, a load is added (point c), the flow rate of the hydrogen-containing gas fuel 201 in the outer peripheral burners 51b to 51g is continuously increased, and the hydrogen-containing gas fuel 201 is supplied to the central burner 51a to increase the flow rate. Then, the load is increased to reach the rated load condition (point d).

このように、中央バーナ５１ａにおける起動用燃料２００と、外周バーナ５１ｂ〜５１ｇにおける水素含有ガス燃料２０１を同時に供給することにより、起動用燃料２００の供給開始（ａ点）から停止（ｎ点）までの時間を短縮でき、起動用燃料２００の費用を節約することが可能である。   Thus, by simultaneously supplying the starting fuel 200 in the central burner 51a and the hydrogen-containing gas fuel 201 in the outer peripheral burners 51b to 51g, from the start of supply of the starting fuel 200 (point a) to the stop (point n). It is possible to reduce the cost of the start-up fuel 200.

実施例１におけるガスタービン着火・運転方法を示す概念図である。1 is a conceptual diagram illustrating a gas turbine ignition / operation method in Embodiment 1. FIG. 実施例１における燃焼器を含むガスタービンプラント概略構成図である。1 is a schematic configuration diagram of a gas turbine plant including a combustor in Embodiment 1. FIG. 拡散燃焼方式を採用する燃焼器を含むガスタービンの着火・運転方法を示す概念図である。It is a conceptual diagram which shows the ignition / operation method of the gas turbine containing the combustor which employ | adopts a diffusion combustion system. 実施例２における予混合低ＮＯｘ燃焼器および燃料供給系統の正面図である。6 is a front view of a premixed low NOx combustor and a fuel supply system in Embodiment 2. FIG. 実施例２における予混合低ＮＯｘ燃焼器および燃料供給系統の側面図である。6 is a side view of a premixed low NOx combustor and a fuel supply system in Embodiment 2. FIG. 実施例２におけるガスタービン着火・運転方法を示す概念図である。It is a conceptual diagram which shows the gas turbine ignition and operation method in Example 2. FIG. 実施例３における予混合低ＮＯｘ燃焼器および燃料供給系統の正面図である。6 is a front view of a premixed low NOx combustor and a fuel supply system in Example 3. FIG. 実施例３におけるガスタービン着火・運転方法を示す概念図である。6 is a conceptual diagram illustrating a gas turbine ignition / operation method in Embodiment 3. FIG.

符号の説明Explanation of symbols

１ ガスタービンプラント
２ 空気圧縮機
３ 燃焼器
４ タービン
５ 燃焼室
６ 発電機
７ 昇圧圧縮機
８ ガスタービン起動用モータ
１２ 主室ライナ
１３ バーナ
１７ 空気旋回器
１８ 水素含有ガス燃料孔
２０ 起動用燃料ノズル
２１ 噴霧空気ノズル
２２ 水素含有ガス燃料ノズル
３０ 燃料ノズル
３１ 空気孔
５１ａ 中央バーナ
５１ｂ，５１ｃ，５１ｄ，５１ｅ，５１ｆ，５１ｇ 外周バーナ
９０ クロスファイヤー管
１０１ 吸入空気
１０２，１０２ａ 燃焼用空気
１０３ 噴霧空気
１０４ 抽気空気
１１０ 燃焼ガス
１１１ 排気ガス
２００ 起動用燃料
２０１，２０１ａ 水素含有ガス燃料 DESCRIPTION OF SYMBOLS 1 Gas turbine plant 2 Air compressor 3 Combustor 4 Turbine 5 Combustion chamber 6 Generator 7 Booster compressor 8 Gas turbine starting motor 12 Main chamber liner 13 Burner 17 Air swirler 18 Hydrogen-containing gas fuel hole 20 Starting fuel nozzle 21 Atomizing air nozzle 22 Hydrogen-containing gas fuel nozzle 30 Fuel nozzle 31 Air hole 51a Central burner 51b, 51c, 51d, 51e, 51f, 51g Outer peripheral burner 90 Cross fire pipe 101 Intake air 102, 102a Combustion air 103 Spray air 104 Extraction Air 110 Combustion gas 111 Exhaust gas 200 Starting fuel 201, 201a Hydrogen-containing gas fuel

Claims (6)

燃焼室に燃料を噴射する燃料ノズルと、燃焼用空気を供給する空気ノズルを有するバーナを備え、
前記バーナは、ガスタービンの着火・起動に用いる起動用燃料の供給が可能な起動用燃料供給系統を備えたガスタービンの運転方法であって、
ガスタービン着火の際に、前記起動用燃料と前記燃料ノズルからの燃料を前記燃焼室に供給し、
ガスタービンの無負荷回転数に達する前に、前記起動用燃料の供給を停止することを特徴とするガスタービンの運転方法。 A fuel nozzle for injecting fuel into the combustion chamber, and a burner having an air nozzle for supplying combustion air;
The burner is a method for operating a gas turbine provided with a starting fuel supply system capable of supplying a starting fuel used for ignition and starting of the gas turbine,
Upon gas turbine ignition, supplying the starting fuel and fuel from the fuel nozzle to the combustion chamber,
A method of operating a gas turbine, characterized in that the start-up fuel supply is stopped before reaching the no-load rotational speed of the gas turbine. 燃焼室に水素含有ガス燃料を噴射する燃料ノズルと、該燃料ノズルの下流側に位置し、燃焼用空気を供給する空気ノズルを複数備えた中央バーナ、及び該中央バーナの外周側に配置された複数の周囲バーナとを備え、
ガスタービンの着火・起動に用いる起動用燃料を供給する起動用燃料供給系統が前記周囲バーナに配置されると共に、前記水素含有ガス燃料を供給する燃料供給系統が前記中央バーナと前記周囲バーナに配置されたガスタービンの運転方法であって、
ガスタービンの着火の際に、前記周囲バーナに前記起動用燃料を供給し、前記起動用燃料の供給と同時に前記中央バーナに前記水素含有ガス燃料も供給することを特徴とするガスタービンの運転方法。 A fuel nozzle for injecting hydrogen-containing gas fuel into the combustion chamber, a central burner located downstream of the fuel nozzle and provided with a plurality of air nozzles for supplying combustion air, and an outer peripheral side of the central burner With multiple surrounding burners,
A startup fuel supply system for supplying startup fuel used for ignition and startup of the gas turbine is disposed in the peripheral burner, and a fuel supply system for supplying the hydrogen-containing gas fuel is disposed in the central burner and the peripheral burner. A method for operating a gas turbine, comprising:
An operation method of a gas turbine, characterized in that, when the gas turbine is ignited, the starting fuel is supplied to the peripheral burner, and the hydrogen-containing gas fuel is supplied to the central burner simultaneously with the supply of the starting fuel. . 請求項２に記載のガスタービンの運転方法であって、
前記着火の後、前記外周バーナの前記起動用燃料の流量を減少させつつ、前記中央バーナの前記水素含有ガス燃料の流量を増加させながら設定条件まで昇速させ、
設定条件に到達後、前記中央バーナの前記水素含有ガス燃料の流量を減らしつつ、前記外周バーナに前記水素含有ガス燃料を供給して流量を増やしながら、負荷を上昇させ、定格負荷条件に到達させることを特徴とガスタービンの運転方法。 A method for operating a gas turbine according to claim 2,
After the ignition, while increasing the flow rate of the hydrogen-containing gas fuel of the central burner while increasing the flow rate of the hydrogen fuel gas in the central burner while increasing the flow rate of the starting fuel of the outer peripheral burner,
After reaching the set conditions, while reducing the flow rate of the hydrogen-containing gas fuel in the central burner, supplying the hydrogen-containing gas fuel to the outer peripheral burner and increasing the flow rate, the load is increased to reach the rated load condition Characteristic and operation method of gas turbine. 燃焼室に水素含有ガス燃料を噴射する燃料ノズルと、該燃料ノズルの下流側に位置し、燃焼用空気を供給する空気ノズルを複数備えた中央バーナ、及び該中央バーナの外周側に配置された複数の周囲バーナとを備え、
ガスタービンの着火・起動に用いる起動用燃料を供給する起動用燃料供給系統が前記中央バーナに配置されると共に、前記水素含有ガス燃料を供給する燃料供給系統が前記中央バーナと前記周囲バーナに配置されたガスタービンの運転方法であって、
ガスタービンの着火の際に、前記中央バーナに前記起動用燃料を供給し、前記起動用燃料の供給と同時に前記外周バーナに前記水素含有ガス燃料も供給することを特徴とするガスタービンの運転方法。 A fuel nozzle for injecting hydrogen-containing gas fuel into the combustion chamber, a central burner located downstream of the fuel nozzle and provided with a plurality of air nozzles for supplying combustion air, and an outer peripheral side of the central burner With multiple surrounding burners,
A startup fuel supply system for supplying startup fuel used for ignition and startup of the gas turbine is disposed in the central burner, and a fuel supply system for supplying the hydrogen-containing gas fuel is disposed in the central burner and the peripheral burners. A method for operating a gas turbine, comprising:
An operation method for a gas turbine, characterized in that, when the gas turbine is ignited, the starting fuel is supplied to the central burner, and the hydrogen-containing gas fuel is supplied to the outer peripheral burner simultaneously with the supply of the starting fuel. . 請求項４に記載のガスタービンの運転方法であって、
前記着火の後、前記中央バーナの前記起動用燃料の流量を減少させつつ、前記外周バーナの前記水素含有ガス燃料の流量を増加させながら、設定条件まで昇速させ、
設定条件に到達後、前記外周バーナの前記水素含有ガス燃料の流量を増やしつつ、前記中央バーナに前記水素含有ガス燃料を供給して流量を増やしながら、負荷を上昇させ、定格負荷条件に到達させることを特徴とするガスタービンの運転方法。 A method for operating a gas turbine according to claim 4,
After the ignition, while increasing the flow rate of the hydrogen-containing gas fuel of the outer peripheral burner while increasing the flow rate of the hydrogen-containing gas fuel of the outer peripheral burner while decreasing the flow rate of the starting fuel of the central burner,
After reaching the set condition, while increasing the flow rate of the hydrogen-containing gas fuel of the outer peripheral burner, increasing the load while supplying the hydrogen-containing gas fuel to the central burner and increasing the flow rate, to reach the rated load condition A gas turbine operating method characterized by the above. 燃焼室に水素含有ガス燃料を噴射する燃料ノズルと、燃焼用空気を供給する空気ノズルを有するバーナを備え、
前記バーナは、ガスタービンの着火・起動に用いる起動用燃料の供給が可能な起動用燃料供給系統を備えたガスタービン燃焼器であって、
ガスタービンの着火の際に、前記起動用燃料の供給と同時に、前記水素含有ガス燃料の供給を開始するために、前記燃料ノズルに燃料を供給する燃料供給系統に燃料流量調整弁を設けることを特徴とするガスタービン燃焼器。 A fuel nozzle for injecting hydrogen-containing gas fuel into the combustion chamber, and a burner having an air nozzle for supplying combustion air;
The burner is a gas turbine combustor provided with a starting fuel supply system capable of supplying a starting fuel used for ignition and starting of a gas turbine,
In order to start the supply of the hydrogen-containing gas fuel simultaneously with the supply of the start-up fuel when the gas turbine is ignited, a fuel flow rate adjusting valve is provided in a fuel supply system for supplying fuel to the fuel nozzle. Characteristic gas turbine combustor.
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