JP5926641B2 - Gas turbine combustor - Google Patents
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- JP5926641B2 JP5926641B2 JP2012163216A JP2012163216A JP5926641B2 JP 5926641 B2 JP5926641 B2 JP 5926641B2 JP 2012163216 A JP2012163216 A JP 2012163216A JP 2012163216 A JP2012163216 A JP 2012163216A JP 5926641 B2 JP5926641 B2 JP 5926641B2
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- 239000000446 fuel Substances 0.000 claims description 123
- 238000002485 combustion reaction Methods 0.000 claims description 47
- 238000002347 injection Methods 0.000 claims description 30
- 239000007924 injection Substances 0.000 claims description 30
- 230000002093 peripheral effect Effects 0.000 claims description 27
- 238000002156 mixing Methods 0.000 claims description 6
- 238000011144 upstream manufacturing Methods 0.000 claims description 6
- 239000007788 liquid Substances 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 217
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 16
- 229910002091 carbon monoxide Inorganic materials 0.000 description 16
- 230000007423 decrease Effects 0.000 description 13
- 239000000567 combustion gas Substances 0.000 description 11
- 230000001965 increasing effect Effects 0.000 description 7
- RNFJDJUURJAICM-UHFFFAOYSA-N 2,2,4,4,6,6-hexaphenoxy-1,3,5-triaza-2$l^{5},4$l^{5},6$l^{5}-triphosphacyclohexa-1,3,5-triene Chemical compound N=1P(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP=1(OC=1C=CC=CC=1)OC1=CC=CC=C1 RNFJDJUURJAICM-UHFFFAOYSA-N 0.000 description 6
- 239000003245 coal Substances 0.000 description 6
- 239000000571 coke Substances 0.000 description 6
- 239000003063 flame retardant Substances 0.000 description 6
- 238000002309 gasification Methods 0.000 description 5
- 239000003949 liquefied natural gas Substances 0.000 description 5
- 230000004048 modification Effects 0.000 description 4
- 238000012986 modification Methods 0.000 description 4
- 230000035515 penetration Effects 0.000 description 4
- 239000002028 Biomass Substances 0.000 description 3
- 230000003993 interaction Effects 0.000 description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 239000007858 starting material Substances 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000006227 byproduct Substances 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 238000009751 slip forming Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000009628 steelmaking Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
Description
本発明は、ガスタービン燃焼器に係るものであり、特に、難燃性ガスで、且つ、発熱量が低いガスを安定に燃焼するためのガスタービン燃焼器のバーナ構造に関する。 The present invention relates to a gas turbine combustor, and more particularly to a burner structure of a gas turbine combustor for stably combusting a flame-retardant gas and a gas having a low calorific value.
一般に発熱量の低い燃料は、ガスタービンの主要燃料であるLNG（Liquefied Natural Gas）に比べて火炎温度が低く燃焼速度が遅いため、燃えにくい燃料である。また、燃焼の際にNOx排出量が少ないことも特徴の一つである。このような低カロリーガスの代表例として、高炉ガスが挙げられる。高炉ガスは製鉄プロセスにおいて高炉から発生する副生ガスで、近年、このガスをガスタービン燃料として利用したいというニーズが高まっている。 In general, a fuel with a low calorific value is a fuel that is difficult to burn because its flame temperature is low and combustion speed is slow compared to LNG (Liquefied Natural Gas), which is the main fuel of gas turbines. Another feature is that NOx emissions are small during combustion. A typical example of such a low calorie gas is blast furnace gas. Blast furnace gas is a by-product gas generated from the blast furnace in the steelmaking process, and in recent years, there is an increasing need to use this gas as a gas turbine fuel.
高炉ガスは一酸化炭素（CO）や水素（H2）を主要可燃成分とし、その他に不活性ガスとしてN2やCO2を多量に含む難燃性のガスである。このため、ガスタービンの着火から定格負荷範囲を高炉ガス専焼で運転することは難しく、着火から燃焼温度の低い部分負荷範囲を安定に運転（燃焼）するには、水素を含むコークス炉ガスなどを高炉ガスに混合し発熱量を高くして運転（増熱）するか、液体燃料などの起動用燃料を別に設ける必要がある。また、難燃性ガスを安定に燃焼する必要があるため、ガスタービン燃焼器では、燃料と空気を別々の流路から供給する拡散燃焼方式を採用するのが一般的である。 Blast furnace gas is a flame retardant gas containing carbon monoxide (CO) and hydrogen (H 2 ) as main combustible components and in addition a large amount of N 2 and CO 2 as inert gases. For this reason, it is difficult to operate the rated load range from igniting the gas turbine with blast furnace gas-only firing, and in order to stably operate (combust) the partial load range where the combustion temperature is low from ignition, coke oven gas containing hydrogen, etc. It is necessary to mix with blast furnace gas and increase the calorific value to operate (heat increase) or to provide a separate starting fuel such as liquid fuel. In addition, since it is necessary to burn the flame-retardant gas stably, the gas turbine combustor generally employs a diffusion combustion system in which fuel and air are supplied from separate flow paths.
一方、低カロリーガス焚きバーナの構造例として、特許文献１には、バーナの半径方向中心部に起動用の油ノズルを備え、その外周にガス噴孔を配置し、さらにその外周にガス噴孔と空気噴孔を交互に配置した構造が開示されている。 On the other hand, as an example of the structure of a low calorie gas burning burner, Patent Document 1 includes an activation oil nozzle at the center in the radial direction of the burner, a gas injection hole disposed on the outer periphery thereof, and a gas injection hole on the outer periphery thereof. And a structure in which air nozzle holes are alternately arranged is disclosed.
一般に、旋回噴流によって保炎するバーナにおいて、火炎を保持するためにはバーナの半径方向中心部近傍に、燃焼ガスが循環しバーナより噴出する燃料と空気に熱を与えるための循環ガス領域を形成する必要がある。特許文献１の構造は、循環ガス領域を形成するために低カロリーガスを積極的に利用したものである。内周スワラにガス噴孔のみを配置し、内周スワラに供給する燃料流量を増やすことで大量の低カロリーガスの運動量を利用して、強い旋回流を形成する。そして、これにより保炎を強化することを特徴としている。 Generally, in a burner that holds flames by a swirling jet, in order to hold the flame, a circulation gas region is formed in the vicinity of the center of the burner in the radial direction to circulate the combustion gas and to give heat to the fuel and air ejected from the burner. There is a need to. The structure of Patent Document 1 actively uses a low calorie gas in order to form a circulation gas region. Only gas nozzle holes are arranged in the inner swirler, and a strong swirling flow is formed by utilizing the momentum of a large amount of low calorie gas by increasing the flow rate of fuel supplied to the inner swirler. And it is characterized by strengthening flame holding by this.
特許文献１のバーナ構造において、石炭ガス化ガスに比べてCO2含有量の多い高炉ガスを燃焼する場合には、バーナ（内外周スワラ）に形成される火炎の温度が低くなる。特に、内周スワラの火炎温度の低下は、循環ガス領域の火炎温度低下につながり、それに伴い外周スワラの火炎温度も低下する。このため燃焼反応が緩慢となり、燃焼器出口におけるCO排出濃度が増加しやすかった。さらに、高炉ガスの燃焼において、高炉から発生するガスの発熱量が低下したときには、火炎が吹き飛びやすくなる場合もあった。 In the burner structure of Patent Document 1, when burning blast furnace gas having a higher CO 2 content than coal gasification gas, the temperature of the flame formed in the burner (inner and outer swirlers) is lowered. In particular, a decrease in the flame temperature of the inner swirler leads to a decrease in the flame temperature in the circulating gas region, and accordingly, the flame temperature of the outer swirler also decreases. For this reason, the combustion reaction was slow, and the CO emission concentration at the combustor outlet was likely to increase. Further, in the combustion of blast furnace gas, when the calorific value of the gas generated from the blast furnace decreases, the flame may be easily blown off.
本発明の目的は、CO2を多量に含む高炉ガスなどの難燃性ガスで、且つ、発熱量が低いガスをも安定に燃焼できるガスタービン燃焼器を提供することにある。 An object of the present invention is to provide a gas turbine combustor that can stably burn even a flame-retardant gas such as a blast furnace gas containing a large amount of CO 2 and a low calorific value.
上記課題を解決するために、本発明は、燃料と空気を混合して燃焼するための燃焼室と、前記燃焼室のガス流れ方向上流に設けられた、前記燃焼室内に燃料と空気を供給して火炎を保持するためのバーナとを備え、前記バーナが、燃料を噴射する複数のガス噴孔と空気を噴射する複数の空気噴孔とがその円周方向に交互に配置された第１のスワラ（内周スワラ）と、前記第１のスワラの外周に設けられた、燃料を噴射するガス噴孔が複数配置された第２のスワラ（外周スワラ）とを有し、前記第１のスワラに配置されたガス噴孔内が、燃料の噴出速度の異なる複数の流路に分割されていることを特徴とする。 In order to solve the above problems, the present invention provides a combustion chamber for mixing and burning fuel and air, and supplying fuel and air into the combustion chamber provided upstream in the gas flow direction of the combustion chamber. And a burner for holding a flame, wherein the burner has a plurality of gas injection holes for injecting fuel and a plurality of air injection holes for injecting air alternately arranged in the circumferential direction. A swirler (inner circumferential swirler) and a second swirler (outer circumferential swirler) provided on the outer circumference of the first swirler and provided with a plurality of gas injection holes for injecting fuel, the first swirler The inside of the gas nozzle hole arranged in is divided into a plurality of flow paths having different fuel ejection speeds.
本発明によれば、CO2を多量に含む高炉ガスなどの難燃性ガスで、且つ、発熱量が低いガスをも安定に燃焼できるガスタービン燃焼器を提供することができる。 According to the present invention, it is possible to provide a gas turbine combustor that can stably burn even a flame-retardant gas such as a blast furnace gas containing a large amount of CO 2 and a low calorific value.
以下に示す本発明の実施例は、高炉ガスや石炭ガス化ガス、バイオマスガス化ガスなど窒素（N2）や二酸化炭素（CO2）含有量の多い難燃性ガスで、且つ、発熱量が低いガスを安定に燃焼するためのガスタービン燃焼器のバーナ構造に関する。 Examples of the present invention shown below are flame retardant gases having a high nitrogen (N 2 ) or carbon dioxide (CO 2 ) content, such as blast furnace gas, coal gasification gas, and biomass gasification gas, and have a calorific value. The present invention relates to a burner structure of a gas turbine combustor for stably burning a low gas.
高炉ガス以外の代表的な低カロリーガスとして、石炭やバイオマスのガス化ガスが挙げられる。これらの石炭やバイオマスを原料とした燃料も資源有効利用の観点から、ガスタービン燃料として利用したいというニーズは高まっている。石炭あるいは木屑などを原料として空気でガス化して得られた燃料は、Ｎ2を多量に含む低カロリーガスである。 Typical low calorie gas other than blast furnace gas includes coal and biomass gasification gas. From the viewpoint of effective utilization of resources, there is an increasing need to use fuels made from these coal and biomass as raw materials as gas turbine fuels. A fuel obtained by gasifying with air using coal or wood chips as a raw material is a low calorie gas containing a large amount of N 2 .
一般に、低カロリーガスは、LNGなどの高カロリー燃料に比べて火炎温度が低く燃焼速度が遅いため、燃えにくい燃料である。したがって、ガスタービン燃焼器においては、低カロリーガスの安定燃焼技術が重要な課題となる。また、発熱量が低いために、LNGなどの高カロリーガスと同等の燃焼ガス温度を得るためには、燃焼器に供給する燃料流量を増加させる必要がある。このため、低カロリーガス焚き燃焼器では供給する燃料流量が多くなる。 Generally, low-calorie gas is a fuel that is difficult to burn because it has a lower flame temperature and a slower combustion speed than high-calorie fuels such as LNG. Therefore, in a gas turbine combustor, a stable combustion technique of low calorie gas becomes an important issue. Further, since the calorific value is low, it is necessary to increase the flow rate of fuel supplied to the combustor in order to obtain a combustion gas temperature equivalent to a high calorie gas such as LNG. For this reason, in the low calorie gas fired combustor, the fuel flow rate to be supplied increases.
特許文献１のような従来のバーナ構造において、石炭ガス化ガスに比べてCO2含有量の多い高炉ガスを燃焼させた場合、バーナ（内外周スワラ）に形成される火炎の温度が低くなる。特に、内周スワラの火炎温度の低下は、循環ガス領域の温度低下につながり、それに伴い外周スワラの火炎温度も低下するため燃焼反応が緩慢となり、燃焼器出口におけるCO排出濃度が増加しやすかった。さらに、燃焼器の出口ガス温度が低くなる部分負荷条件では、燃料流量が少なくなるためバーナ近傍の火炎温度も低くなる。その場合、特に、高炉ガスの燃焼においては、燃料にCO2を含むために密度が大きくなり、保炎のための強い旋回に対し慣性力によって燃料が外側に貫通しやすくなるため、循環ガス領域内の燃料濃度が低くなり、火炎が吹き飛びやすくなるという課題もある。 In a conventional burner structure such as Patent Document 1, when a blast furnace gas having a higher CO 2 content than the coal gasification gas is burned, the temperature of the flame formed in the burner (inner and outer swirler) becomes lower. In particular, a decrease in the flame temperature of the inner swirler led to a decrease in the temperature of the circulating gas region, and the flame temperature of the outer swirler also decreased accordingly, so the combustion reaction was slow and the CO emission concentration at the combustor outlet was likely to increase. . Further, under partial load conditions where the exit gas temperature of the combustor is low, the fuel flow rate is low, so the flame temperature near the burner is low. In that case, especially in the combustion of blast furnace gas, the density increases because the fuel contains CO 2 , and it becomes easy for the fuel to penetrate to the outside by the inertial force against the strong swirl for flame holding. There is also a problem that the fuel concentration inside becomes low and the flame easily blows away.
上記の課題を解決するためには、内周スワラに形成する火炎温度を高くし、燃焼反応を促進させるとともに、循環ガス領域内の燃料濃度を高める必要がある。このためには、内周スワラにガス噴孔と空気噴孔を設けガス燃料と空気の混合によって火炎温度を高めるとともに、内周スワラから噴出する燃料の流速を適正化し、密度の大きいガス燃料が旋回による慣性力で外周側へ貫通することを抑えることが重要である。 In order to solve the above problems, it is necessary to increase the flame temperature formed in the inner swirler to promote the combustion reaction and to increase the fuel concentration in the circulating gas region. For this purpose, gas nozzles and air nozzles are provided in the inner swirler to increase the flame temperature by mixing gas fuel and air, and to optimize the flow rate of the fuel ejected from the inner swirler so that high density gas fuel can be obtained. It is important to suppress penetration to the outer peripheral side due to the inertial force due to turning.
そこで、以下に示す本発明の各実施例は、内周スワラと外周スワラで構成する２重旋回バーナにおいて、内周スワラにはガス噴孔と空気噴孔を設けそれらを交互に配置するとともに、内周スワラに設けた複数のガス噴孔を第1と第2の2つの流路に分けることを基本構成とする。 Therefore, in each embodiment of the present invention shown below, in the double swirl burner constituted by the inner swirler and the outer swirler, the inner swirler is provided with gas injection holes and air injection holes, and they are alternately arranged. The basic configuration is to divide a plurality of gas nozzle holes provided in the inner swirler into first and second flow paths.
さらに、前記第１のガス流路は、燃焼室に面するガス噴孔出口の面積よりも上流側の入口面積を小さくすることで燃料の噴孔出口流速を低下させ、ガス燃料の貫通を抑制するように供給する。それによって、循環ガス領域内に低流速のガス燃料が取り込まれ、燃料濃度の増加によって前記領域の火炎温度が上昇し、保炎を強化することが可能となる。 Further, the first gas flow path reduces the fuel nozzle outlet flow velocity by reducing the inlet area upstream of the area of the gas nozzle outlet facing the combustion chamber, thereby suppressing the penetration of gas fuel. To supply. As a result, the low-flow-rate gas fuel is taken into the circulating gas region, and the flame temperature in the region increases due to the increase in the fuel concentration, thereby making it possible to enhance flame holding.
そして、以下に示す実施例によれば、安定燃焼範囲が狭くなる部分負荷条件でも、保炎を賄う内周スワラから噴出する燃料の貫通を抑制できるため、循環ガス領域の燃料濃度が高くなり火炎温度の上昇によってCO2を多量に含む高炉ガスの専焼が可能である。 And, according to the embodiment shown below, since the penetration of the fuel ejected from the inner swirler that covers the flame holding can be suppressed even under the partial load condition where the stable combustion range becomes narrow, the fuel concentration in the circulating gas region becomes high and the flame Blast furnace gas containing a large amount of CO 2 can be exclusively fired by increasing the temperature.
以下、本発明の実施例について図面を参照して説明する。 Embodiments of the present invention will be described below with reference to the drawings.
（燃焼器の構成）
図１に、本発明の第１の実施例に係るガスタービンの系統と燃焼器の拡大断面図を示す。ガスタービン5は、圧縮機2、燃焼器3、タービン4、発電機6、及び起動用モータ8等で構成される。
(Combustor configuration)
FIG. 1 shows an enlarged cross-sectional view of a gas turbine system and a combustor according to a first embodiment of the present invention. The gas turbine 5 includes a compressor 2, a combustor 3, a turbine 4, a generator 6, a starting motor 8, and the like.
ガスタービン5では、圧縮機2が大気より吸込んだ空気101を圧縮して得られる燃焼空気102をガスタービン燃焼器3に供給する。燃焼器3は、圧縮機2による燃焼空気102と低カロリーガスである高炉ガス60にコークス炉ガス80を混合した増熱ガス70（着火〜部分負荷範囲で供給）とが混合して燃焼し、タービン4に供給される燃焼ガス140を発生させる。タービン4は燃焼ガス140の供給により回転動力が与えられ、タービン4の回転動力が圧縮機2及び発電機6に伝達される。圧縮機2に伝えられた回転動力は圧縮動力に用いられ、発電機6に伝えられた回転動力は電気エネルギーに変換される。 In the gas turbine 5, combustion air 102 obtained by compressing the air 101 sucked from the atmosphere by the compressor 2 is supplied to the gas turbine combustor 3. In the combustor 3, the combustion air 102 produced by the compressor 2 and the heat increasing gas 70 (mixed in the ignition to partial load range) in which the coke oven gas 80 is mixed with the blast furnace gas 60 that is a low calorie gas are mixed and burned, A combustion gas 140 supplied to the turbine 4 is generated. The turbine 4 is supplied with rotational power by supplying the combustion gas 140, and the rotational power of the turbine 4 is transmitted to the compressor 2 and the generator 6. The rotational power transmitted to the compressor 2 is used as compression power, and the rotational power transmitted to the generator 6 is converted into electric energy.
燃焼器3においては、圧力容器である外筒10内に燃料と空気を混合して燃焼するための燃焼室12を備え、燃焼室12の外周に燃焼室冷却用のフロースリーブ11を備える。 The combustor 3 includes a combustion chamber 12 for mixing and burning fuel and air in an outer cylinder 10 that is a pressure vessel, and a flow sleeve 11 for cooling the combustion chamber on the outer periphery of the combustion chamber 12.
また、燃焼室12の燃焼ガス流れ方向上流には、燃焼室12内に燃料と空気を供給して火炎を保持するためのバーナ300を配置している。燃焼器3に供給された燃焼空気102は、フロースリーブ11と燃焼室12との間の空間内を流れ、燃焼室12を冷却しながら燃焼室の側壁に設けた燃焼空気孔13、およびバーナ300に設けた空気噴孔402等より燃焼室12内に供給される。 Further, a burner 300 for supplying fuel and air into the combustion chamber 12 and holding a flame is disposed upstream of the combustion chamber 12 in the flow direction of the combustion gas. Combustion air 102 supplied to the combustor 3 flows in a space between the flow sleeve 11 and the combustion chamber 12, and while the combustion chamber 12 is cooled, a combustion air hole 13 provided in a side wall of the combustion chamber, and a burner 300 Is supplied into the combustion chamber 12 through an air injection hole 402 or the like provided in the combustion chamber 12.
バーナ300は、第１のスワラである内周スワラ201と、内周スワラ201の外周に設けられた第2のスワラである外周スワラ202で構成される2重旋回構造を採用している。内周スワラ201、および外周スワラ202に供給する低カロリーガスの流量および発熱量は、ガスタービンの負荷条件によって変化可能とすることを特徴とする。ガスタービンの着火から部分負荷範囲は、高炉ガス60にコークス炉ガス80を混合した増熱ガス70を供給し、燃料流量を増加させ燃焼温度が高くなるにつれて負荷が上昇し、高負荷条件（たとえば中間負荷から定格負荷範囲）になると、高炉ガス60のみの供給も可能である。 The burner 300 employs a double swirl structure including an inner swirler 201 that is a first swirler and an outer swirler 202 that is a second swirler provided on the outer periphery of the inner swirler 201. The flow rate and calorific value of the low-calorie gas supplied to the inner swirler 201 and the outer swirler 202 can be changed depending on the load condition of the gas turbine. The partial load range from the ignition of the gas turbine is to supply a heat increasing gas 70 obtained by mixing the coke oven gas 80 with the blast furnace gas 60, increase the fuel flow rate and increase the load as the combustion temperature rises. In the range from the intermediate load to the rated load), only the blast furnace gas 60 can be supplied.
低カロリーガスの供給圧力は燃料系統に設けた圧力調整弁150によって調整が可能であり、その下流には、内周スワラ201に内周燃料201ｆを供給するための第1の燃料系統51と、外周スワラ202に外周燃料202ｆを供給する第2の燃料系統52を備える。各燃料系統は、それぞれ、第1の燃料流量調節弁41、および第2の燃料流量調節弁42を備えており、制御装置200によって、ガスタービンの着火や負荷条件に応じて、第１の燃料系統および第2の燃料系統に供給する燃料流量を制御することが可能である。 The supply pressure of the low calorie gas can be adjusted by a pressure regulating valve 150 provided in the fuel system, and downstream thereof, a first fuel system 51 for supplying the inner peripheral fuel 201f to the inner peripheral swirler 201, A second fuel system 52 for supplying the outer peripheral fuel 202f to the outer peripheral swirler 202 is provided. Each fuel system includes a first fuel flow rate control valve 41 and a second fuel flow rate control valve 42, and the control device 200 controls the first fuel flow rate control valve 41 and the second fuel flow rate control valve 42 according to the ignition and load conditions of the gas turbine. It is possible to control the flow rate of fuel supplied to the system and the second fuel system.
（バーナ構造１）
図２にバーナ300の正面図を示す。この図は、バーナ300を下流から見たものである。本実施例のバーナは、内周スワラ201と外周スワラ202で構成する2重旋回バーナ構造であり、CO2を多量に含む高炉ガスの燃焼でも内周スワラの火炎温度を高めるため、内周スワラ201にはガス噴孔401と空気噴孔402を円周方向に交互に配置し、その外側に設けた外周スワラ202には、ガス噴孔403のみを配置したことを特徴とする。それぞれの噴孔には、図２のＡ−Ａ断面図に示すような旋回角θが設けられており、旋回成分を与えることでバーナの半径方向中心部近傍は負圧となり、低速となる保炎領域（循環ガス領域）が形成され燃焼安定性を強化できる。
(Burner structure 1)
FIG. 2 shows a front view of the burner 300. This figure shows the burner 300 as viewed from the downstream. The burner of the present embodiment has a double swirl burner structure composed of an inner swirler 201 and an outer swirler 202, and the inner swirler increases the flame temperature of the inner swirler even when burning blast furnace gas containing a large amount of CO 2. 201 is characterized in that gas injection holes 401 and air injection holes 402 are alternately arranged in the circumferential direction, and only the gas injection holes 403 are arranged on the outer peripheral swirler 202 provided on the outer side thereof. Each nozzle hole is provided with a swivel angle θ as shown in the AA cross-sectional view of FIG. A flame region (circulation gas region) is formed, and combustion stability can be enhanced.
また、前述のように、高炉ガスはCO2を多量に含むためLNGに比べて燃料の密度が大きく、旋回によって保炎するバーナにおいては慣性力によって燃料が外周側に貫通しやすくなる。その場合、バーナの半径方向中心部近傍に形成する循環ガス領域の燃料濃度が低下するため、保炎性能が低下する恐れがある。 Further, as described above, since the blast furnace gas contains a large amount of CO 2 , the fuel density is larger than that of LNG, and in the burner that holds the flame by turning, the fuel is likely to penetrate to the outer peripheral side due to inertial force. In that case, since the fuel concentration in the circulating gas region formed in the vicinity of the center portion in the radial direction of the burner is lowered, there is a possibility that the flame holding performance is lowered.
このため、本実施例では図２に示すように、内周スワラ201に設けた複数のガス噴孔401において、噴孔内を内周スワラ201の半径方向について２つの流路に分割し、それらのうち半径方向内側に設けた第1のガス流路（噴孔501a）から噴出するガスの流速を第2のガス流路（噴孔502a）から噴出する流速よりも遅くすることを特徴とする。内周スワラのガス噴孔内に設けた2つのガス流路のうち、第１のガス流路より噴出するガス流速を低下させることで、燃料の貫通を抑え循環ガス領域の濃度低下を防止し、安定燃焼を可能としている。 For this reason, in this embodiment, as shown in FIG. 2, in the plurality of gas injection holes 401 provided in the inner swirler 201, the inside of the injection hole is divided into two flow paths in the radial direction of the inner swirler 201. The flow rate of the gas ejected from the first gas flow path (injection hole 501a) provided radially inside is made slower than the flow speed of the gas ejected from the second gas flow path (injection hole 502a). . Of the two gas flow paths provided in the gas nozzle hole of the inner swirler, by reducing the gas flow velocity ejected from the first gas flow path, the fuel penetration is suppressed and the decrease in the concentration of the circulating gas region is prevented. , Enabling stable combustion.
即ち、燃料の噴出速度の異なる複数の流路に分割することで、必要な燃料流量は確保しつつ、燃料流速の遅い流路から供給される燃料が循環ガス領域における燃料濃度の低下を防止し、高炉ガスのような燃料をも安定に燃焼させることができる。そして、内周側の流路の燃料噴出速度が、外周側の流路の燃料噴出速度よりも遅くなるようにガス噴孔401に流路が形成されていることにより、内周スワラ201に形成される火炎温度の低下を防止し、より安定した燃焼を可能となる。 That is, by dividing the fuel flow into a plurality of flow paths having different fuel ejection speeds, the fuel supplied from the flow path with a slow fuel flow rate is prevented from lowering the fuel concentration in the circulating gas region while ensuring the necessary fuel flow rate. In addition, fuel such as blast furnace gas can be stably burned. Then, the flow path is formed in the gas injection hole 401 so that the fuel ejection speed of the inner circumferential side flow path is slower than the fuel ejection speed of the outer circumferential side flow path, thereby forming the inner circumferential swirler 201. The flame temperature is prevented from being lowered, and more stable combustion is possible.
一方、図１に示したように、外周スワラ202においては、ガス噴孔403よりガス燃料202fが供給される。ガス燃料202fは内周スワラ201から供給される空気102aや、燃焼空気孔13から供給されるバーナ近傍の空気と混合し、内周スワラ201に形成される火炎（内周火炎）を基点に、外周スワラに火炎（外周火炎）が形成される。外周火炎の形成によって、内周火炎周囲の温度は高くなるため、さらに保炎を強化できる。特に、高炉ガスのようなCO2を多量に含む低カロリーガスの燃焼には有効である。 On the other hand, as shown in FIG. 1, in the outer swirler 202, gas fuel 202 f is supplied from the gas injection hole 403. The gas fuel 202f is mixed with the air 102a supplied from the inner peripheral swirler 201 and the air in the vicinity of the burner supplied from the combustion air hole 13, and based on the flame (inner peripheral flame) formed in the inner peripheral swirler 201, A flame (peripheral flame) is formed on the outer swirler. Since the temperature around the inner flame becomes higher due to the formation of the outer flame, flame holding can be further strengthened. In particular, it is effective for combustion of low calorie gas containing a large amount of CO 2 such as blast furnace gas.
次に、図３にバーナ300の断面図を示す。内周スワラ201、および外周スワラ202は、ガス燃料をバーナに供給するためのボディー（配管）125を固定するためのフランジ126に接続している。内周スワラ201に供給するガス燃料201fは、ボディー125の中心部に設けた配管を通って供給され、内周スワラの空気102aは外周スワラ202の側面に設けた空気導入孔402aより供給される。 Next, FIG. 3 shows a cross-sectional view of the burner 300. The inner swirler 201 and the outer swirler 202 are connected to a flange 126 for fixing a body (pipe) 125 for supplying gas fuel to the burner. The gas fuel 201f supplied to the inner swirler 201 is supplied through a pipe provided in the center of the body 125, and the air 102a of the inner swirler is supplied from an air introduction hole 402a provided in the side surface of the outer swirler 202. .
内周スワラ201に供給されたガス燃料201fは、ガス噴孔内に設けた第１と第2の2つのガス流路501と502とに分配される。第１のガス流路501は出口面積A2に対し上流側の入口面積A1が小さく、第２のガス流路は出口面積A4と入口面積A3を同等としている。供給された燃料は、第１のガス流路で面積が最も小さいA1と、第２のガス流路の出口面積A4（またはＡ3）との比率で分配される。第１のガス流路では入口面積A1よりも出口面積A2が大きいため、第１のガス流路を流下する燃料の流速は入口から出口にかけて徐々に低下する。そのため、第１のガス流路出口の燃料流速Uf1は、第２のガス流路出口の燃料流速Uf2よりも遅くなる。 The gas fuel 201f supplied to the inner swirler 201 is distributed to the first and second gas flow paths 501 and 502 provided in the gas injection hole. The first gas flow channel 501 has a smaller inlet area A1 on the upstream side than the outlet area A2, and the second gas flow channel has the same outlet area A4 and inlet area A3. The supplied fuel is distributed at a ratio of A1 having the smallest area in the first gas flow path and the outlet area A4 (or A3) of the second gas flow path. Since the outlet area A2 is larger than the inlet area A1 in the first gas channel, the flow rate of the fuel flowing down the first gas channel gradually decreases from the inlet to the outlet. Therefore, the fuel flow rate Uf1 at the first gas flow path outlet is slower than the fuel flow speed Uf2 at the second gas flow path outlet.
これらのガス流路内で分配された燃料201fおよび空気102aには旋回成分が与えられ、これによりバーナの半径方向中心部は負圧となり、バーナの前面には循環ガス領域30が形成される。 A swirl component is given to the fuel 201f and the air 102a distributed in these gas flow paths, whereby the radial center portion of the burner becomes negative pressure, and a circulating gas region 30 is formed on the front surface of the burner.
特に、本実施例では、第２のガス流路502より噴出する燃料201f-2の運動量を利用して、強い旋回により保炎を強化する構造としている。循環ガス領域30は、内周スワラ201から噴出するガス燃料201f-1、201ｆ-2、および空気102aに火炎からの熱を連続的に与えるため、火炎250が連続的に形成され保炎に至る。 In particular, in this embodiment, the structure is such that the flame holding is strengthened by a strong swirl using the momentum of the fuel 201f-2 ejected from the second gas flow path 502. The circulating gas region 30 continuously applies heat from the flame to the gas fuels 201f-1, 201f-2 and the air 102a ejected from the inner peripheral swirler 201, so that the flame 250 is continuously formed and the flame is held. .
また、本実施例では、第１のガス流路出口の燃料流速を第２のガス流路出口の燃料流速よりも遅くしているため、例えば、発熱量が低下し燃料流量を増加させ同一負荷運転を維持しようとした場合でも、慣性力によって燃料が外周側に貫通することを抑えることが可能であり、保炎強化に重要な循環ガス領域内の燃料濃度の低下を防止できる。 Further, in this embodiment, the fuel flow rate at the first gas flow path outlet is made slower than the fuel flow speed at the second gas flow path outlet. Even when the operation is to be maintained, it is possible to suppress the fuel from penetrating to the outer peripheral side due to the inertial force, and it is possible to prevent a decrease in the fuel concentration in the circulating gas region, which is important for enhancing flame holding.
一方、外周スワラ202のガス燃料202fは、ボディー125の外側に設けた配管より供給される。外周スワラ202に供給されたガス燃料202fには旋回成分が与えられ、内周スワラ201で形成された循環ガス領域30を包み込むように、循環ガス領域31が形成される。 On the other hand, the gas fuel 202f of the outer peripheral swirler 202 is supplied from a pipe provided outside the body 125. A swirling component is given to the gas fuel 202f supplied to the outer peripheral swirler 202, and a circulating gas region 31 is formed so as to wrap around the circulating gas region 30 formed by the inner peripheral swirler 201.
ガス燃料202fは、内周火炎250より連続的に熱が与えられ、外周火炎260が形成される。循環ガス領域31によって、外周火炎260の燃焼ガスの一部が循環ガス領域30に取り込まれ、内周スワラ201と外周スワラ202で形成する火炎（250、260）の相互作用によって、火炎が安定化される。また、本実施例では外周スワラ202よりガス燃料202fを供給しているため、内周スワラ201において、空気噴孔402周囲（半径方向外側）の燃料濃度低下を防止でき、火炎温度の高い領域を増加できるため、火炎安定化に寄与できる。 The gas fuel 202f is continuously heated by the inner peripheral flame 250, and the outer peripheral flame 260 is formed. A part of the combustion gas of the outer flame 260 is taken into the circulation gas region 30 by the circulating gas region 31, and the flame is stabilized by the interaction between the inner swirler 201 and the outer swirler 202 (250, 260). Is done. Further, in this embodiment, the gas fuel 202f is supplied from the outer swirler 202. Therefore, in the inner swirler 201, it is possible to prevent a decrease in fuel concentration around the air injection holes 402 (outside in the radial direction). Since it can increase, it can contribute to flame stabilization.
さらに、本実施例では増熱ガス70によるガスタービンの着火、負荷変化を想定して説明してきたが、２重旋回バーナの半径方向中心部（内周スワラ201の半径方向中心部）に、液体燃料用の油ノズルを配置して、更なる安定燃焼を図ることも可能である。 Further, in the present embodiment, the description has been made on the assumption that the gas turbine is ignited and the load is changed by the heat-increasing gas 70. It is also possible to arrange an oil nozzle for fuel to achieve further stable combustion.
（運転方法）
以上述べてきたバーナ構造の運転方法について、図１をもとに説明する。始動時、ガスタービンは起動用モータ8などの外部動力によって駆動される。ガスタービンの回転数を燃焼器の着火条件相当の回転数に保持することで、燃焼器３には着火に必要な燃焼空気102が供給され、着火条件が成立する。高炉ガス60にコークス炉ガス80を混合し、増熱ガス70をバーナ300に供給することで、燃焼器3内で着火が可能となる。
(how to drive)
The operation method of the burner structure described above will be described with reference to FIG. At startup, the gas turbine is driven by external power such as a starter motor 8. By maintaining the rotational speed of the gas turbine at a rotational speed corresponding to the ignition condition of the combustor, the combustion air 102 necessary for ignition is supplied to the combustor 3, and the ignition condition is satisfied. By mixing the blast furnace gas 60 with the coke oven gas 80 and supplying the heating gas 70 to the burner 300, ignition in the combustor 3 becomes possible.
燃焼器の着火後、燃焼ガス140がタービン4に供給され、増熱ガス70の流量増加とともにタービン4が昇速、起動用モータ8の離脱によりガスタービンは自立運転に入り、無負荷定格回転数に到達する。ガスタービンが無負荷定格回転数に到達後は、発電機6の併入、さらには増熱ガス70の流量増加によりタービン4の入口ガス温度が上昇し、負荷が上昇する。負荷の上昇に伴い、燃焼器出口の燃焼ガス温度が高くなると燃焼安定性が増加するため、増熱用に供給していたコークス炉ガスの供給を停止することが可能となる。バーナにおいては、内周スワラ201に形成される火炎250と外周スワラ202に形成される火炎260の相互作用によって、高炉ガス60の専焼条件であっても火炎を安定に保持できる。 After the combustor is ignited, the combustion gas 140 is supplied to the turbine 4, the turbine 4 is accelerated as the flow rate of the heat-increasing gas 70 increases, and the gas turbine enters the self-sustaining operation by the release of the starting motor 8, and the no-load rated rotational speed To reach. After the gas turbine reaches the no-load rated rotation speed, the inlet gas temperature of the turbine 4 rises due to the addition of the generator 6 and the increase in the flow rate of the heat-increasing gas 70, and the load rises. As the load increases, the combustion stability increases as the combustion gas temperature at the combustor outlet increases, so that the supply of coke oven gas that has been supplied for heat increase can be stopped. In the burner, the flame can be stably maintained even under the exclusive firing conditions of the blast furnace gas 60 by the interaction between the flame 250 formed on the inner swirler 201 and the flame 260 formed on the outer swirler 202.
（変形例）
なお、図５に示す変形例のように、第１のガス流路に縮流部を設けるような構成としても良い。この場合、第１のガス流路で面積が最も小さい縮流部面積A5と、第２のガス流路の出口面積A4（またはA3）との比率で分配される。第１のガス流路では宿流部面積A5よりも出口面積A2が大きいため、宿流部から出口にかけて燃料流速が低下する。したがって、第１のガス流路出口の燃料流速Uf1は、第２のガス流路出口の燃料流速Uf2よりも遅くなる。そのため、図３に示した第一の実施例に係るバーナ同様、空気噴孔402周囲（半径方向外側）の燃料濃度低下を防止でき、火炎の安定化が可能である。
(Modification)
In addition, it is good also as a structure which provides a contraction part in a 1st gas flow path like the modification shown in FIG. In this case, the flow is distributed at a ratio of the contracted area A5 having the smallest area in the first gas flow path and the outlet area A4 (or A3) of the second gas flow path. Since the outlet area A2 is larger than the stagnation area A5 in the first gas flow path, the fuel flow velocity decreases from the stagnation area to the outlet. Therefore, the fuel flow rate Uf1 at the first gas flow path outlet is slower than the fuel flow speed Uf2 at the second gas flow path outlet. Therefore, similarly to the burner according to the first embodiment shown in FIG. 3, it is possible to prevent a decrease in fuel concentration around the air injection hole 402 (outside in the radial direction) and to stabilize the flame.
また、図６に示す他の変形例は、第１のガス流路501の上流側にガス燃料201fの流れを阻害するプレート510を備えている。プレート510を備えることによって第１のガス流路501へのガス燃料201fの流入が抑制され、第１のガス流路501に流入するガス燃料201fの流量が低下する。これにより、第１のガス流路出口の燃料流速Uf1はさらに低下するため、慣性力によって燃料が外周側に貫通することを抑制し、保炎強化に重要な循環ガス領域内の燃料濃度の低下を防止することができる。 6 includes a plate 510 that inhibits the flow of the gas fuel 201f on the upstream side of the first gas flow path 501. By providing the plate 510, the inflow of the gas fuel 201f into the first gas channel 501 is suppressed, and the flow rate of the gas fuel 201f flowing into the first gas channel 501 is reduced. As a result, the fuel flow rate Uf1 at the outlet of the first gas flow path further decreases, so that the fuel is prevented from penetrating to the outer peripheral side due to the inertial force, and the fuel concentration in the circulating gas region, which is important for flame holding, is reduced Can be prevented.
（バーナ構造2）
図４に、本発明の第２の実施例であるバーナの断面図を示す。本実施形態が第１の特徴と異なる点は、内周スワラ201の第1のガス流路501に半径中心方向の傾斜角を設けたことにある。
(Burner structure 2)
FIG. 4 shows a cross-sectional view of a burner according to a second embodiment of the present invention. The present embodiment is different from the first feature in that an inclination angle in the radial center direction is provided in the first gas flow path 501 of the inner swirler 201.
内周スワラ201のガス噴孔に設けた2つのガス流路は、図２および図３で説明したように、ガス燃料および空気に旋回を与えるための旋回角を設けている。これにより、バーナの半径方向中心部近傍が負圧となり、燃焼ガスが循環する逆流領域（循環ガス領域）を形成し安定燃焼が可能となる。 As described with reference to FIGS. 2 and 3, the two gas flow paths provided in the gas injection holes of the inner swirler 201 have a turning angle for turning the gas fuel and air. As a result, the pressure in the vicinity of the central portion in the radial direction of the burner becomes negative pressure, and a reverse flow region (circulation gas region) in which the combustion gas circulates is formed, thereby enabling stable combustion.
本発明の第２の特徴では、内周スワラ201のガス噴孔に設けた第１のガス流路501において、旋回流路の入口面積A1よりも出口面積A2を大きくし、ガス燃料201f-1の噴出流速を低下させ、前記循環ガス領域内に燃料が取り込まれるように噴射したことに加え、図4aの部分拡大図に示すように、前記第1のガス流路501にはバーナの半径中心方向にガス燃料201f-1を噴射するための傾斜角αを設けたことを特徴とする。 In the second feature of the present invention, in the first gas flow path 501 provided in the gas injection hole of the inner peripheral swirler 201, the outlet area A2 is made larger than the inlet area A1 of the swirl flow path, and the gas fuel 201f-1 The first gas flow path 501 has a radial center of the burner as shown in the partially enlarged view of FIG. An inclination angle α for injecting the gas fuel 201f-1 in the direction is provided.
これにより、第1のガス流路より供給する燃料201f-1が循環ガス領域30内にさらに取り込まれやすくなり、循環ガス領域30内の燃料濃度が高くなる。燃料濃度の上昇によって循環ガス領域内の火炎温度は高くなり、内周スワラ201に安定した火炎が形成できる。また、内周スワラ201に形成する内周火炎250により、外周スワラ202にも外周火炎260が安定に形成され、外周スワラ202の旋回によって形成する循環ガス領域31により、高温の燃焼ガスが循環ガス領域30内に取り込まれる。すなわち、２重旋回の内外周火炎の相互作用によって、CO2を多量に含む高炉ガスの安定燃焼が可能となる。 As a result, the fuel 201f-1 supplied from the first gas passage is more easily taken into the circulating gas region 30, and the fuel concentration in the circulating gas region 30 is increased. As the fuel concentration increases, the flame temperature in the circulating gas region increases, and a stable flame can be formed on the inner swirler 201. In addition, the inner flame 250 formed on the inner swirler 201 stably forms the outer flame 260 on the outer swirler 202. The circulation gas region 31 formed by the swirling of the outer swirler 202 causes the high-temperature combustion gas to circulate. Captured in region 30. That is, the blast furnace gas containing a large amount of CO 2 can be stably burned by the interaction between the inner and outer flames of the double swirl.
2 圧縮機
3 燃焼器
4 タービン
5 ガスタービン
6 発電機
8 起動用モータ
10 外筒
11 フロースリーブ
12 燃焼室
13 燃焼空気孔
30 内周スワラの循環ガス領域
31 外周スワラの循環ガス領域
41 第１の燃料流量調節弁（内周燃料系統）
42 第２の燃料流量調節弁（外周燃料系統）
51 第１の燃料系統（内周燃料系統）
52 第２の燃料系統（外周燃料系統）
60 高炉ガス
70 増熱ガス
80 コークス炉ガス
101 空気
102 燃焼空気
102ａ 内周スワラの燃焼空気
125 燃料ノズルボディー（配管）
126 ノズルボディーフランジ
140 燃焼ガス
150 圧力調整弁
200 制御装置
201 内周スワラ
201ｆ 内周燃料
201ｆ-1 第１のガス流路より噴出する内周燃料
201ｆ-2 第2のガス流路より噴出する内周燃料
202 外周スワラ
202ｆ 外周燃料
250 内周火炎
260 外周火炎
300 バーナ
401 内周スワラのガス噴孔
402 内周スワラの空気噴孔
402a 内周スワラの空気導入孔
403 外周スワラのガス噴孔
500 内周スワラのガス燃料に旋回を与えるための助走区間
501 内周スワラのガス噴孔内に設けた第１のガス流路
501a 内周スワラのガス噴孔内に設けた第１のガス流路の出口噴孔
502 内周スワラのガス噴孔内に設けた第2のガス流路
502a 内周スワラのガス噴孔内に設けた第2のガス流路の出口噴孔
A１ 内周スワラのガス噴孔に設けた第１のガス流路の入口面積
A2 内周スワラのガス噴孔に設けた第１のガス流路の出口面積
A3 内周スワラのガス噴孔に設けた第2のガス流路の入口面積
A4 内周スワラのガス噴孔に設けた第2のガス流路の出口面積
2 Compressor
3 Combustor
4 Turbine
5 Gas turbine
6 Generator
8 Starter motor
10 outer cylinder
11 Flow sleeve
12 Combustion chamber
13 Combustion air hole
30 Circulating gas area of inner swirler
31 Circulating gas area of outer swirler
41 First fuel flow control valve (inner fuel system)
42 Second fuel flow control valve (peripheral fuel system)
51 First fuel system (inner fuel system)
52 Second fuel system (peripheral fuel system)
60 Blast furnace gas
70 Heat increase gas
80 Coke oven gas
101 air
102 Combustion air
102a Combustion air of inner swirler
125 Fuel nozzle body (piping)
126 Nozzle body flange
140 Combustion gas
150 Pressure regulating valve
200 control unit
201 inner swirler
201f Inner fuel
201f-1 Inner perimeter fuel ejected from the first gas flow path
201f-2 Inner peripheral fuel ejected from the second gas flow path
202 Perimeter swirler
202f Perimeter fuel
250 inner flame
260 Peripheral flame
300 burners
401 Gas hole in inner swirler
402 Air hole of inner swirler
402a Air introduction hole of inner swirler
403 Gas hole of outer swirler
500 Run-up section for swirling gas fuel of inner swirler
501 1st gas flow path provided in the gas injection hole of the inner periphery swirler
501a Outlet nozzle hole of first gas flow path provided in gas nozzle hole of inner swirler
502 2nd gas flow path provided in gas nozzle of inner swirler
502a Outlet hole of the second gas flow path provided in the gas hole of the inner swirler
A1 Entrance area of the first gas flow path provided in the gas nozzle of the inner swirler
A2 Outlet area of the first gas flow path provided in the gas injection hole of the inner swirler
A3 Entrance area of the second gas flow path provided in the gas nozzle of the inner swirler
A4 Outlet area of the second gas flow path provided in the gas nozzle of the inner swirler
Claims (6)
前記バーナが、燃料を噴射する複数のガス噴孔と空気を噴射する複数の空気噴孔とが円周方向に交互に配置された第１のスワラと、前記第１のスワラの外周に設けられた、燃料を噴射するガス噴孔が複数配置された第２のスワラとを有し、
前記第１のスワラに配置されたガス噴孔内が、燃料の噴出速度の異なる複数の流路に分割されていることを特徴とするガスタービン燃焼器。 A combustion chamber for mixing and burning fuel and air, and a burner provided upstream of the combustion chamber in the gas flow direction for supplying fuel and air into the combustion chamber to hold a flame A gas turbine combustor comprising:
The burner is provided on a first swirler in which a plurality of gas injection holes for injecting fuel and a plurality of air injection holes for injecting air are alternately arranged in a circumferential direction, and on an outer periphery of the first swirler. And a second swirler having a plurality of gas injection holes for injecting fuel,
The gas turbine combustor, wherein the gas injection hole arranged in the first swirler is divided into a plurality of flow paths having different fuel injection speeds.
前記第１のスワラに配置されたガス噴孔内が、前記第１のスワラの半径方向について複数の流路に分割され、
前記複数の流路は、内周側の流路が、外周側の流路よりも燃料の噴出速度が遅くなるように構成されていることを特徴とするガスタービン燃焼器。 The gas turbine combustor according to claim 1.
The first arrangement gas injection hole to the swirler, the radial direction of the first swirler is divided into a plurality of flow paths,
The gas turbine combustor, wherein the plurality of flow paths are configured such that an inner peripheral flow path has a fuel ejection speed slower than an outer peripheral flow path.
前記第１のスワラのガス噴孔内が、第１のガス流路と、外周側の第２のガス流路の２つの流路に分割され、
前記第1のガス流路は、流路面積が最小となる最小断面積部を有すると共に、出口面積が前記最小断面積部の面積よりも大きいことを特徴としたガスタービン燃焼器。 The gas turbine combustor according to claim 1 or 2,
The gas nozzle hole of the first swirler is divided into two flow paths, a first gas flow path and an outer peripheral second gas flow path,
The gas turbine combustor, wherein the first gas flow path has a minimum cross-sectional area that minimizes a flow area, and an outlet area is larger than an area of the minimum cross-sectional area.
前記最小断面積部は、前記第1のガス流路の入口であることを特徴としたガスタービン燃焼器。 The gas turbine combustor according to claim 3.
The gas turbine combustor, wherein the minimum cross-sectional area portion is an inlet of the first gas flow path.
前記第１のスワラのガス噴孔内に設けた第1のガス流路には、前記第１のスワラの半径方向内周側に向けてガス燃料を噴射するための傾斜角が設けられていることを特徴とするガスタービン燃焼器。 The gas turbine combustor according to claim 3 or 4,
The first gas flow path provided in the gas nozzle hole of the first swirler is provided with an inclination angle for injecting gas fuel toward the radially inner periphery of the first swirler. A gas turbine combustor.
前記第１のスワラの半径方向中心部に、液体燃料を微粒化して噴射する油ノズルを配置したことを特徴とするガスタービン燃焼器。 The gas turbine combustor according to any one of claims 1 to 5,
A gas turbine combustor, wherein an oil nozzle for atomizing and injecting liquid fuel is disposed at a central portion in a radial direction of the first swirler.
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