JPH0139016B2 - - Google Patents
Info
- Publication number
- JPH0139016B2 JPH0139016B2 JP11076082A JP11076082A JPH0139016B2 JP H0139016 B2 JPH0139016 B2 JP H0139016B2 JP 11076082 A JP11076082 A JP 11076082A JP 11076082 A JP11076082 A JP 11076082A JP H0139016 B2 JPH0139016 B2 JP H0139016B2
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- combustion
- combustion chamber
- low
- gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
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- 238000002485 combustion reaction Methods 0.000 claims description 149
- 239000000446 fuel Substances 0.000 claims description 109
- 239000007789 gas Substances 0.000 claims description 57
- 239000000567 combustion gas Substances 0.000 claims description 8
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 38
- 238000006243 chemical reaction Methods 0.000 description 10
- 230000000694 effects Effects 0.000 description 5
- 229910017464 nitrogen compound Inorganic materials 0.000 description 5
- 150000002830 nitrogen compounds Chemical class 0.000 description 5
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 4
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- 230000007423 decrease Effects 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 3
- 239000001301 oxygen Substances 0.000 description 3
- 229910052760 oxygen Inorganic materials 0.000 description 3
- 229910021529 ammonia Inorganic materials 0.000 description 2
- 239000003245 coal Substances 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 229910052757 nitrogen Inorganic materials 0.000 description 2
- 239000003208 petroleum Substances 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
Classifications
-
- 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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Description
【発明の詳細な説明】
本発明は、低カロリーガス燃料を燃料対象とし
たガスタービン燃焼器に関する。低カロリーガス
燃料とは、例えば石炭ガス化燃料などの、比較的
発熱量の小さいガス燃料を称する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a gas turbine combustor that uses low-calorie gas fuel as fuel. Low-calorie gas fuel refers to gas fuel with a relatively low calorific value, such as coal gasified fuel.
従来よりガスタービンは石油燃料などの高カロ
リーの燃料を使用するのが通常であるが、低カロ
リーガス焚のものも開発されており、例えば第１
図に示すようなガスタービン燃焼器が提案されて
いる。この燃焼器は、燃料ノズル１と外筒２と内
筒３とを有し、燃料ノズルからの燃料１０がスワ
ーラ５からの圧縮空気９と混合し、更に空気孔
６，７，８からの空気と混合して、内筒３内で燃
焼する。４は外筒２を塞ぐ端板である。 Conventionally, gas turbines have typically used high-calorie fuel such as petroleum fuel, but low-calorie gas-fired ones have also been developed;
A gas turbine combustor as shown in the figure has been proposed. This combustor has a fuel nozzle 1, an outer cylinder 2, and an inner cylinder 3, in which fuel 10 from the fuel nozzle is mixed with compressed air 9 from a swirler 5, and further air from air holes 6, 7, and 8 is mixed with compressed air 9 from a swirler 5. It is mixed with and combusted in the inner cylinder 3. 4 is an end plate that closes the outer cylinder 2.
しかしこの従来のガスタービン燃焼器は、燃焼
効率や窒素酸化物発生という面で低カロリーガス
燃料を用いるにはなお問題があるものである。こ
の問題につき更に述べると、以下の通りである。 However, this conventional gas turbine combustor still has problems in terms of combustion efficiency and nitrogen oxide generation when using low-calorie gas fuel. A further explanation of this problem is as follows.
一般にガスタービンの実用運転範囲は広く、回
転数一定の発電用ガスタービンでは空気流量が一
定のため、無負荷から100％負荷までの範囲で燃
空比が３倍以上変化する。例えば燃空比ｆ／ａが
0.005から0.022の範囲で変化する（ｆは燃料、ａ
はエアである）。従つて、理論燃焼温度が高く燃
焼速度も大きい高カロリー燃料を使用する場合で
も、低負荷状態においては空気過剰率が高く、未
燃成分が増す傾向にある。未燃成分として一酸化
炭素COに着目してみれば、第２図に破線で示
す如く、高カロリーガスでもCO濃度はやや上昇
傾向にある。 In general, gas turbines have a wide practical operating range, and in power generation gas turbines with a constant rotational speed, the air flow rate is constant, so the fuel-air ratio changes by more than three times from no load to 100% load. For example, the fuel-air ratio f/a
varies from 0.005 to 0.022 (f is fuel, a
is air). Therefore, even when using a high-calorie fuel with a high theoretical combustion temperature and a high combustion rate, the excess air ratio tends to be high and the amount of unburned components increases under low load conditions. Focusing on carbon monoxide CO as an unburned component, as shown by the broken line in Figure 2, the CO concentration tends to rise slightly even with high-calorie gas.
これに対し低カロリーガス燃料は、第２図に実
線で示すように、この傾向が極めて著しい。即
ち低カロリーガス燃料は、過剰空気が供給される
と火炎が冷却され、燃焼効率が急激に低下する特
性を持つ。上記は第１図に示したような単一燃焼
室構造の燃焼器で燃焼した場合であるが、低カロ
リーガス燃料特に低位発熱量が1200kcal／Ｎm3以
下の燃料は、理論燃焼温度が低く、燃焼速度も小
さいために、過剰空気が供給されて火炎が冷却さ
れると燃焼効率が急激に低下するわけであり、こ
れが未燃成分の増加につながる。ガスタービンの
負荷変化に対するCO濃度も第２図に示すように、
25％負荷以下で急激に増加する。結局、低カロリ
ーガス燃料は、ガスタービンの低負荷条件におい
ては、その完全燃焼が達成できないという難点を
有するのである。 On the other hand, with low-calorie gas fuel, this tendency is extremely remarkable, as shown by the solid line in FIG. That is, low-calorie gas fuel has a characteristic that when excess air is supplied, the flame is cooled and the combustion efficiency is sharply reduced. The above is a case of combustion in a combustor with a single combustion chamber structure as shown in Fig. 1, but low-calorie gas fuels, especially fuels with a lower calorific value of 1200 kcal/Nm 3 or less, have a low theoretical combustion temperature. Since the combustion speed is also low, when excess air is supplied and the flame is cooled, the combustion efficiency decreases rapidly, which leads to an increase in unburned components. As shown in Figure 2, the CO concentration with respect to gas turbine load changes is
It increases rapidly below 25% load. After all, low calorie gas fuels have the disadvantage that their complete combustion cannot be achieved under low load conditions of the gas turbine.
更に、石炭ガス化低カロリーガス燃料にはアン
モニアが含まれる可能性が高いが、このアンモニ
アは燃焼により、公害成分である窒素酸化物に変
換するものである。よつてかかる窒素酸化物への
変換率を低減する必要がある。ところが第１図の
ような従来からの通常の拡散燃焼形式では、その
変換率が高い。また高カロリー燃料を用いる場合
には、燃料中窒素分の窒素酸化物への変換率を低
くするため燃料過剰・燃料希薄２段燃焼を行うこ
とができるが、低カロリーガス燃料ではこの適用
が困難である。前記した如く、保炎性能が低下し
てしまうためである。従つて低カロリーガス燃料
にあつては、燃料中の窒素化合物が窒素酸化物に
変換することを抑えきれないという問題も残つて
いる。 Furthermore, coal gasified low-calorie gas fuel is likely to contain ammonia, which is converted into nitrogen oxides, which are polluting components, through combustion. Therefore, it is necessary to reduce the conversion rate to nitrogen oxides. However, in the conventional diffusion combustion type shown in FIG. 1, the conversion rate is high. Furthermore, when using high-calorie fuel, it is possible to perform two-stage combustion with excess fuel and lean fuel to lower the conversion rate of nitrogen in the fuel to nitrogen oxides, but this is difficult to apply with low-calorie gas fuel. It is. This is because, as described above, the flame holding performance deteriorates. Therefore, with low-calorie gas fuels, there remains the problem that conversion of nitrogen compounds in the fuel to nitrogen oxides cannot be suppressed.
上記事情に鑑み、本発明は、低カロリーガス燃
料をガスタービンの低負荷条件においても完全燃
焼化し、かつ、燃料中窒素化合物の窒素酸化物へ
の変換率を低減することができ、これにより低カ
ロリーガス燃料使用の隘路となつていた諸問題を
解決した、有利な低カロリーガス焚ガスタービン
燃焼器を提供することを目的とする。 In view of the above circumstances, the present invention enables complete combustion of low-calorie gas fuel even under low load conditions of the gas turbine, and reduces the conversion rate of nitrogen compounds in the fuel to nitrogen oxides, thereby reducing the It is an object of the present invention to provide an advantageous low-calorie gas-fired gas turbine combustor that solves various problems that have been a bottleneck in the use of calorie gas fuel.
この目的を達成すべく、本発明の低カロリーガ
ス焚ガスタービン燃焼器は、内部で燃料が燃焼す
る内筒と、内筒の外側に空気通路を形成する外筒
と、燃料を供給する燃料ノズルとを具備させて構
成し、この燃焼器に２個の燃焼室、つまりガスタ
ービン全作動範囲内で燃料の少なくとも一部分を
空気過剰条件で燃焼する第１燃焼室と、該第１燃
焼室の後流に位置して残り燃料を第１燃焼室燃焼
ガスと混合して燃焼するものであると共に、少な
くとも定格負荷条件では燃料過剰燃焼と燃料希薄
燃焼との２段燃焼を実現する第２燃焼室との２室
を配置して構成する。 In order to achieve this object, the low-calorie gas-fired gas turbine combustor of the present invention includes an inner cylinder in which fuel is burned, an outer cylinder that forms an air passage outside the inner cylinder, and a fuel nozzle that supplies fuel. the combustor comprises two combustion chambers, a first combustion chamber in which at least a portion of the fuel is combusted in air excess conditions within the entire operating range of the gas turbine; a second combustion chamber which is located in the flow and combusts the remaining fuel by mixing it with the combustion gas of the first combustion chamber, and which realizes two-stage combustion of excess fuel combustion and fuel lean combustion at least under rated load conditions; It consists of two rooms:
このように構成すると、まず第１燃焼室では所
定の空気過剰条件で、安定かつ燃焼速度の大きい
燃焼を行わせることができる。次に、第２燃焼室
は、第１燃焼室の後流に位置する結果第１燃焼室
での燃焼排ガスによりその入口空気温度は十分に
上昇させられる。従つて第２燃焼室は燃焼性が向
上し、この第２燃焼室で安定な燃料過剰燃焼・燃
料希薄燃焼の２段燃焼が可能となり、これにより
燃料中窒素化合物の窒素酸化物への変換率を低減
できるようになる。 With this configuration, combustion can be performed stably and at a high combustion rate in the first combustion chamber under a predetermined excess air condition. Next, since the second combustion chamber is located downstream of the first combustion chamber, the temperature of the inlet air thereof is sufficiently increased by the combustion exhaust gas in the first combustion chamber. Therefore, the combustibility of the second combustion chamber is improved, and stable two-stage combustion of fuel excess combustion and fuel lean combustion is possible in this second combustion chamber, which increases the conversion rate of nitrogen compounds in the fuel to nitrogen oxides. can be reduced.
結局、それぞれ燃空比変動幅の狭い２つの燃焼
室を燃焼器内に直列に配置したので、各々燃焼速
度を大きくでき、かつ、後流の第２燃焼室は第１
燃焼室により加熱される形になるので、該第２燃
焼室での２段燃焼が可能となり、窒素酸化物の低
減と、燃焼効率の上昇との双方を達成することが
できる。 In the end, two combustion chambers, each with a narrow range of fuel-air ratio fluctuations, were arranged in series in the combustor, so the combustion speed of each could be increased, and the second combustion chamber in the wake was connected to the first combustion chamber.
Since it is heated by the combustion chamber, two-stage combustion is possible in the second combustion chamber, and it is possible to achieve both a reduction in nitrogen oxides and an increase in combustion efficiency.
この発明は、低カロリーガスも高カロリーガス
と同様、理論混合気近傍で燃焼速度が大きく、こ
の領域のみで燃焼器を作動させれば燃焼効率が高
いという特性に着目したものであり、上記のよう
に２つの燃焼室を設けることにより、これを達成
したものである。 This invention focuses on the characteristic that low-calorie gas, like high-calorie gas, has a high combustion speed near the stoichiometric mixture, and that combustion efficiency is high if the combustor is operated only in this region. This was achieved by providing two combustion chambers.
以下、本発明に係る燃焼器の一実施例を、第３
図乃至第５図を参照して説明する。 Hereinafter, one embodiment of the combustor according to the present invention will be described in the third embodiment.
This will be explained with reference to FIGS. 5 to 5.
第３図は本例燃焼器の断面図であるが、これを
参照して、まず本実施例の概略につき説明する。 FIG. 3 is a cross-sectional view of the combustor of this example, and with reference to this, the outline of this example will first be explained.
この燃焼器は内筒３と、外筒２と、燃料ノズル
１，１１とを有する。内筒３は、その内部で燃料
が燃焼するものであり、この中に第１燃焼室１
２、第２燃焼室１３が構成される。外筒２は、該
内筒３の外側に、空気流路を形成する。燃料ノズ
ル１，１１は、内筒３に燃料を与える。 This combustor has an inner cylinder 3, an outer cylinder 2, and fuel nozzles 1 and 11. The inner cylinder 3 is one in which fuel is combusted, and the first combustion chamber 1 is located inside the inner cylinder 3.
2. The second combustion chamber 13 is configured. The outer cylinder 2 forms an air flow path outside the inner cylinder 3. The fuel nozzles 1 and 11 supply fuel to the inner cylinder 3.
第１燃焼室１２は、ガスタービン全作動範囲内
で、燃焼がなされる。よつて着火から定格負荷ま
で、常時燃焼する。ここでは、燃料の少なくとも
一部分は空気過剰条件で燃焼する。この結果、第
１燃焼室１２での燃空比ｆ／ａは、第５図に示す
ように、範囲程度の変動に抑えることができ
る。空気過剰率で言えば、第４図に′で示す程
度の変動である。 Combustion occurs in the first combustion chamber 12 within the entire operating range of the gas turbine. Therefore, it burns constantly from ignition to rated load. Here, at least a portion of the fuel is combusted in air excess conditions. As a result, the fuel-air ratio f/a in the first combustion chamber 12 can be suppressed to fluctuate within a range, as shown in FIG. In terms of excess air ratio, the fluctuation is as shown by '' in Figure 4.
次に第２燃焼室１３は、該第１燃焼室１２の後
流に位置し、第１燃焼室１２の燃焼ガスを受けて
これを残り燃料と混合して、燃焼を行う。この第
２燃焼室１３は、少なくとも定格負荷条件では燃
料過剰燃焼と燃料希薄燃焼との２段燃焼を行う
が、これは前述のように高温の第１燃焼室１２か
らの燃焼排ガスを受けるので、室内が高温にな
り、燃焼条件が良くなつているためにかかる２段
燃焼が実現されるものである。 Next, the second combustion chamber 13 is located downstream of the first combustion chamber 12, receives the combustion gas from the first combustion chamber 12, mixes it with the remaining fuel, and performs combustion. This second combustion chamber 13 performs two-stage combustion of fuel excess combustion and fuel lean combustion at least under rated load conditions, but this is because it receives combustion exhaust gas from the high temperature first combustion chamber 12 as described above. This two-stage combustion is realized because the temperature inside the room has become high and the combustion conditions have improved.
従つてこの２段燃焼の結果窒素酸化物の発生を
低く抑えることができ、また第１燃焼室１２での
空気過剰率変化を小さくできるため、低負荷での
燃焼効率低下を防止できるという効果をもたらし
得る。 Therefore, as a result of this two-stage combustion, the generation of nitrogen oxides can be suppressed to a low level, and the change in the excess air ratio in the first combustion chamber 12 can be reduced, which has the effect of preventing a decrease in combustion efficiency at low loads. can bring about
本実施例の更に詳しい構成及びその作用効果を
説明すると、下記の通りである。 A more detailed explanation of the configuration and effects of this embodiment is as follows.
本例燃焼器は着火から定格負荷まで常時燃焼す
る第１燃焼室１２と、部分負荷から定格負荷まで
燃焼する第２燃焼室１３とから成る内筒３；コン
プレツサ（図示せず）で圧縮された空気を内筒に
導く外筒２；外筒２端面を閉じるためのエンドプ
レート４；内筒３に燃料を供給する第１燃料ノズ
ル１及び第２燃料ノズル１１；燃料ノズル１，１
１への燃料流量をタービンの回転数や負荷に応じ
て制御する燃料制御弁開度指示器２２；燃料制御
弁１８，２１；本図に記載しない点火装置等から
成る。 The combustor of this example has an inner cylinder 3 consisting of a first combustion chamber 12 that constantly burns from ignition to rated load, and a second combustion chamber 13 that burns from partial load to rated load; Outer cylinder 2 that guides air to the inner cylinder; End plate 4 for closing the end face of the outer cylinder 2; First fuel nozzle 1 and second fuel nozzle 11 that supply fuel to the inner cylinder 3; Fuel nozzles 1, 1
The fuel control valve opening indicator 22 controls the fuel flow rate to the turbine 1 according to the rotational speed and load of the turbine; the fuel control valves 18, 21; and an ignition device not shown in this figure.
この燃焼器は前述の如く、従来燃焼器では運転
範囲が限定されていた低カロリーガスの燃料過
剰・燃料希薄２段燃焼をより広い範囲で運転する
ことをも目的として、燃焼室を２つに分ける構成
をとるが、まず第１燃焼室１２では次のような燃
焼がなされる。 As mentioned above, this combustor has two combustion chambers for the purpose of operating over a wider range of fuel-rich/fuel-lean two-stage combustion of low-calorie gas, which was limited in the operating range of conventional combustors. First, the following combustion occurs in the first combustion chamber 12.
即ち第１燃焼室１２では、コンプレツサからの
圧縮空気９をスワーラ５、空気孔６から導入し、
一方燃料制御弁１８で制御された低カロリーガス
を配管１９を通して燃料ノズル１から導入し、点
火装置によりこれに着火して、燃焼を開始・進行
する。着火以後の第１燃焼室１２での燃焼過程
は、第４図のグラフに符号で示す。このグラフ
はガスタービン負荷と空気過剰率との関係を表わ
しているが、第１燃焼室１２では負荷Ａまでは燃
料を順次増加し、この時空気量は一定であるから
結局空気過剰率は図示の如く低下して行く。負荷
Ａ以上では燃料流量を一定として、第１燃焼室１
２の空気過剰率変化を小さくする。負荷Ａでの空
気過剰率は1.0以上であり、全範囲に亘つて空気
過剰条件での燃焼が行われる。 That is, in the first combustion chamber 12, compressed air 9 from the compressor is introduced through the swirler 5 and the air hole 6,
On the other hand, low-calorie gas controlled by the fuel control valve 18 is introduced from the fuel nozzle 1 through the pipe 19, and is ignited by the ignition device to start and proceed with combustion. The combustion process in the first combustion chamber 12 after ignition is indicated by symbols in the graph of FIG. This graph shows the relationship between the gas turbine load and the excess air ratio.In the first combustion chamber 12, the fuel is gradually increased until the load A, and at this time the amount of air is constant, so the excess air ratio is not shown in the graph. It goes down like this. When the load is above A, the fuel flow rate is kept constant, and the first combustion chamber 1
2. Reduce the change in excess air ratio. The excess air ratio at load A is 1.0 or more, and combustion is performed under the excess air condition over the entire range.
第２燃焼室１３は、負荷Ａ以上で燃焼を行う。
前述の第１燃焼室１２はこの第２燃焼室１３に対
して、パイロツト的に燃焼するものということが
できる。第２燃焼室１３の燃料は、第２燃料ノズ
ル１１から供給される。この第２燃料ノズル１１
は、第１燃焼室１２の出口近傍の空気孔７中に、
その中心付近に噴口部１１ａを設けて成るもので
ある。ノズル１１を正面から見た図、つまり第３
図の方向矢視図を第６図に示すが、図示のよう
に噴口部１１ａの周囲が空気孔７で囲まれる様に
なつている。（尚、第６図では空気孔７、噴口部
１１ａともに同心の円形になつているが、形状は
これに限らない）。かかる第２燃料ノズル１１か
ら、燃料制御弁２１を介し配管１４で供給される
低カロリーガスを第２燃焼室１３用に供給する。
ここでの供給は、第１燃焼室１２の燃焼を阻害し
てはならないので、その燃焼性能に影響を及ぼさ
ないように行う。第２燃料ノズル１１から供給さ
れた燃料（矢印２５）は、空気孔７からの空気
（矢印２６）とともに、第１燃焼室燃焼ガス２７
と混合する。第１燃焼室燃焼ガスは、燃焼後の排
ガスであるからその温度は充分に高い。従つてこ
れと燃料２５、空気２６との混合気は燃料の発火
点よりも高く、第２燃焼室入口２４では第１燃焼
室１２での燃焼に続いて燃焼が進行する。 The second combustion chamber 13 performs combustion under load A or higher.
The first combustion chamber 12 described above can be said to perform combustion in a pilot manner with respect to the second combustion chamber 13. Fuel to the second combustion chamber 13 is supplied from the second fuel nozzle 11. This second fuel nozzle 11
is in the air hole 7 near the outlet of the first combustion chamber 12,
A nozzle portion 11a is provided near the center. A view of the nozzle 11 from the front, that is, the third
A directional view of the figure is shown in FIG. 6, and as shown in the figure, the periphery of the nozzle portion 11a is surrounded by air holes 7. (In FIG. 6, both the air hole 7 and the nozzle part 11a are concentric circles, but the shape is not limited to this). From the second fuel nozzle 11, low calorie gas is supplied to the second combustion chamber 13 through the pipe 14 via the fuel control valve 21.
The supply here must not interfere with combustion in the first combustion chamber 12, so it is carried out so as not to affect its combustion performance. The fuel (arrow 25) supplied from the second fuel nozzle 11 is transferred to the combustion gas 27 of the first combustion chamber together with the air (arrow 26) from the air hole 7.
Mix with. Since the first combustion chamber combustion gas is exhaust gas after combustion, its temperature is sufficiently high. Therefore, the mixture of this, fuel 25, and air 26 is higher than the ignition point of the fuel, and combustion proceeds at the second combustion chamber inlet 24 following combustion in the first combustion chamber 12.
この第２燃焼室１３での燃焼につき、第４図を
用いて説明する。上述した第２燃焼室入口２４に
おけるガスタービン負荷と平均の空気過剰率との
関係は図中の符号で示すが、負荷がＡに至るま
では燃焼せず、Ａ点で第２燃料ノズル１１が作動
開始して燃焼が始まり、爾後負荷がそれより大き
い範囲でこの燃焼が継続する。負荷が増大してＢ
以上になると、第２燃焼室入口２４の未燃混合気
の空気過剰率は１以下となり、平均空気過剰率
も１に近づく。このためガス温度は高く、低カ
ロリーガスの燃焼であつても、燃焼安定性が確保
され、第２燃焼室１３での２段燃焼が可能とな
る。この例では該Ｂ点以上の負荷で２段燃焼が可
能となつており、定格負荷条件（100％負荷）で
は当然その２段燃焼が行われる。 Combustion in the second combustion chamber 13 will be explained using FIG. 4. The relationship between the gas turbine load and the average excess air ratio at the second combustion chamber inlet 24 described above is indicated by the reference numeral in the figure, but combustion does not occur until the load reaches A, and at point A the second fuel nozzle 11 When the engine starts operating, combustion begins, and then this combustion continues as long as the load is greater than that. B due to increased load
In this case, the excess air ratio of the unburned mixture at the second combustion chamber inlet 24 becomes less than 1, and the average excess air ratio also approaches 1. Therefore, the gas temperature is high, and even when low-calorie gas is burned, combustion stability is ensured, and two-stage combustion in the second combustion chamber 13 becomes possible. In this example, two-stage combustion is possible at a load above point B, and naturally the two-stage combustion is performed under rated load conditions (100% load).
なお本実施例では、第２燃料ノズル１１が作動
開始するＡ点の時点において、第１燃焼室１２の
出口温度つまり排ガス温度は供給燃料の発生点以
上となるように設定して、これにより上記安定燃
焼を確実ならしめている。（但し、必ずしもＡ点
で発火点以上の排ガス温度でなければならないと
いうわけではない）。 In this embodiment, at point A when the second fuel nozzle 11 starts operating, the outlet temperature of the first combustion chamber 12, that is, the exhaust gas temperature is set to be equal to or higher than the point of generation of the supplied fuel. This ensures stable combustion. (However, the exhaust gas temperature at point A does not necessarily have to be higher than the ignition point).
第３図に、符号１３ａにて第１段の燃料過剰燃
焼領域を示し、１３ｂにて第２段の燃料希薄燃焼
領域を示す。それぞれほぼ破線で囲う部分に該当
する。１２ａにて第１燃焼室１２の燃焼領域も概
略示しておく。 In FIG. 3, reference numeral 13a indicates a first stage fuel excess combustion region, and reference numeral 13b indicates a second stage fuel lean combustion region. Each roughly corresponds to the area surrounded by the broken line. The combustion region of the first combustion chamber 12 is also schematically shown at 12a.
上記の如く高負荷時に大部分の燃焼を行う第２
燃焼室１３において、このような２段燃焼を安定
に達成できるので、燃料中窒素化合物の窒素酸化
物への変換率を低減できる。燃料中の窒素分はア
ンモニアNH3となり、これが酸素が十分にある
と酸化して一酸化窒素NOとなつて種々の窒素酸
化物NOxを発生させるのであるが、第２燃焼室
１３での第１段燃焼領域１３ａは燃料過剰条件で
あるため酸素不足の状態であるから、NH3→NO
という変化が抑止される。これを次段の第２段燃
焼領域１３ｂでの酸素過剰の低温燃焼（低温であ
るから反応速度は小さく、NOxへの変換も少な
い）と組合わせて、全体的にNOxの発生を小な
らしめたものである。 As mentioned above, the second combustion engine performs most of the combustion during high loads.
Since such two-stage combustion can be stably achieved in the combustion chamber 13, the conversion rate of nitrogen compounds in the fuel to nitrogen oxides can be reduced. The nitrogen content in the fuel turns into ammonia NH 3 , which oxidizes to nitrogen monoxide NO when there is sufficient oxygen and generates various nitrogen oxides NOx. Since the stage combustion region 13a is in an oxygen-deficient state due to the fuel excess condition, NH 3 →NO
This change is suppressed. This is combined with low-temperature combustion with excess oxygen in the second-stage combustion region 13b (low temperature, so the reaction rate is low and conversion to NOx is also low) to reduce overall NOx generation. It is something that
また、本実施例にあつては第６図の如く、空気
孔７内にノズル噴出口１１ａを設ける構成を採つ
たので、第２燃料ノズル１１の作動開始直後の燃
料噴射速度が遅い条件においても、空気孔からの
空気の貫通力を利用して、前段燃焼室燃焼ガス中
に燃料を供給でき、従つて燃焼効率の低下を防止
できる。 In addition, in this embodiment, as shown in FIG. 6, since the nozzle outlet 11a is provided in the air hole 7, even under conditions where the fuel injection speed is slow immediately after the second fuel nozzle 11 starts operating, By utilizing the penetration force of air from the air holes, fuel can be supplied into the combustion gas in the pre-stage combustion chamber, thus preventing a decrease in combustion efficiency.
また、第５図にて説明した如く第１燃焼室１２
の燃空比幅が従来燃焼器よりも小さいため、ガ
スタービン低負荷条件においても燃焼効率を高く
保つことが可能である。この燃空比幅を小さく抑
えることも、燃焼室を２室１２，１３にした効果
であつて、従来は第５図のＣ点からＤ点までの広
範囲を要していたのに対し、当初の燃空比をＣ点
からＥ点、つまり0.005程度から0.01程度に上げ
ることができたものである。従来例の特性を符号
、本実施例の特性をで示す。第２燃焼室１３
はＡ点以後作動するが、その燃空比は第５図に符
号で示す通りである。 Further, as explained in FIG. 5, the first combustion chamber 12
Since the fuel-air ratio range of the combustor is smaller than that of conventional combustors, it is possible to maintain high combustion efficiency even under low load conditions of the gas turbine. Keeping this fuel-air ratio width small is also an effect of having two combustion chambers (12 and 13). It was possible to raise the fuel-air ratio from point C to point E, that is, from about 0.005 to about 0.01. The characteristics of the conventional example are shown by symbols, and the characteristics of this embodiment are shown by . Second combustion chamber 13
operates after point A, and the fuel/air ratio is as indicated by the symbols in FIG.
更に本実施例では、第３図に示す如くタービン
出力信号２３を燃料制御弁開度指示器２２に入力
し、タービン出力に応じて該指示器２２が指示信
号を出力することにより、主燃料制御弁１８と第
２燃料制御弁２１とをそれぞれに開度制御し、こ
れをもつて出力制御を行うようになつている。 Furthermore, in this embodiment, as shown in FIG. 3, the turbine output signal 23 is input to the fuel control valve opening indicator 22, and the indicator 22 outputs an instruction signal according to the turbine output, thereby controlling the main fuel control. The opening degrees of the valve 18 and the second fuel control valve 21 are controlled individually, and the output is controlled using these controls.
なお本実施例では、ガスタービンの起動時等に
低カロリーガス燃料が供給されない場合を考慮し
て、各燃料ノズル１，１１は、石油燃料などの液
体燃料噴射機能をも有する構成にしてある。 In this embodiment, each fuel nozzle 1, 11 is configured to also have a liquid fuel injection function such as petroleum fuel, in consideration of the case where low calorie gas fuel is not supplied at the time of starting the gas turbine or the like.
上述の如く、本発明によれば、第２燃焼室にお
いては前段で燃料を第１燃焼室燃焼ガスと混合す
ることにより昇温させて燃料過剰条件での燃焼を
安定に達成でき、後段で燃料希薄燃焼を行つて、
このように２段燃焼を可能としたことによつて燃
料中窒素化合物の窒素酸化物への変換率を低減で
きる効果がある。また、第１燃焼室の空気過剰率
変化を小さくでき、よつて燃空比変化を小さくで
きるために、低負荷での燃焼効率低下を防止でき
る効果がある。従つて本発明により、低カロリー
ガスを燃料として用いても、有利にガスタービン
駆動を達成できるものである。 As described above, according to the present invention, in the second combustion chamber, the temperature can be increased by mixing the fuel with the combustion gas of the first combustion chamber in the first stage, thereby stably achieving combustion under fuel excess conditions, and in the second stage, the fuel can be mixed with the combustion gas in the first combustion chamber. By performing lean burn,
By enabling two-stage combustion in this manner, there is an effect that the conversion rate of nitrogen compounds in the fuel to nitrogen oxides can be reduced. Further, since the change in the excess air ratio of the first combustion chamber can be reduced, and therefore the change in the fuel/air ratio can be reduced, there is an effect of preventing a decrease in combustion efficiency at low loads. Therefore, according to the present invention, even if low calorie gas is used as fuel, gas turbine drive can be advantageously achieved.
なお当然のことではあるが、本発明は図示の実
施例にのみ限定されるものではない。 It should be noted that, as a matter of course, the present invention is not limited to the illustrated embodiment.
第１図は従来形低カロリーガス焚ガスタービン
燃焼器の断面図、第２図は従来形低カロリーガス
焚ガスタービンの排ガス特性を示すグラフであ
る。第３図は本発明のガスタービン燃焼器の一実
施例の断面図、第４図はその燃焼器内空気過剰率
特性を示すグラフ、第５図は同じく燃空比特性を
示すグラフ、第６図は第３図における方向矢視
拡大略示図である。
１……第１燃料ノズル、２……燃焼器外筒、３
……内筒、１１……第２燃料ノズル、１２……第
１燃焼室、１３……第２燃焼室、１３ａ……燃料
過剰燃焼領域、１３ｂ……燃料希薄燃焼領域、２
４……第２燃焼室入口。
FIG. 1 is a sectional view of a conventional low-calorie gas-fired gas turbine combustor, and FIG. 2 is a graph showing exhaust gas characteristics of the conventional low-calorie gas-fired gas turbine. FIG. 3 is a sectional view of an embodiment of the gas turbine combustor of the present invention, FIG. 4 is a graph showing the excess air ratio characteristics in the combustor, FIG. 5 is a graph showing the fuel-air ratio characteristics, and FIG. The figure is a schematic enlarged view in the direction of the arrows in FIG. 3. 1...First fuel nozzle, 2...Combustor outer cylinder, 3
... Inner cylinder, 11 ... Second fuel nozzle, 12 ... First combustion chamber, 13 ... Second combustion chamber, 13a ... Fuel excess combustion region, 13b ... Fuel lean combustion region, 2
4...Second combustion chamber inlet.
Claims (1)
に空気通路を形成する外筒と、燃料を供給する燃
料ノズルとを有する低カロリーガス焚ガスタービ
ン燃焼器において、ガスタービン全作動範囲内で
燃料の少なくとも一部分を空気過剰条件で燃焼す
る第１燃焼室と、該第１燃焼室の後流に位置して
残り燃料を第１燃焼室燃焼ガスと混合して燃焼す
るものであると共に、少なくとも定格負荷条件で
は燃料過剰燃焼と燃料希薄燃焼との２段燃焼を実
現する第２燃焼室とから成ることを特徴とする低
カロリーガス焚ガスタービン燃焼器。 ２ 第２燃焼室用の燃料ノズル作動開始時におけ
る前記第１燃焼室の出口ガス温度は、供給燃料の
発火点以上としたものであることを特徴とする特
許請求の範囲第１項に記載の低カロリーガス焚ガ
スタービン燃焼器。 ３ 第２燃焼室用の燃料ノズルは、これを空気孔
中心近傍に設置して、少なくとも燃料流量の少な
い範囲では燃料を該空気孔からの空気主流と混合
して供給する構成としたものであることを特徴と
する特許請求の範囲第１項に記載の低カロリーガ
ス焚ガスタービン燃焼器。[Claims] 1. A low-calorie gas-fired gas turbine combustor that has an inner cylinder in which fuel is burned, an outer cylinder that forms an air passage outside the inner cylinder, and a fuel nozzle that supplies fuel. a first combustion chamber in which at least a portion of the fuel is combusted in air-excess conditions within the entire operating range of the gas turbine; and a first combustion chamber located downstream of the first combustion chamber to mix the remaining fuel with the first combustion chamber combustion gas. A low-calorie gas-fired gas turbine combustor characterized by comprising a second combustion chamber that combusts and realizes two-stage combustion of excess fuel combustion and fuel lean combustion at least under rated load conditions. 2. The temperature of the outlet gas of the first combustion chamber at the time when the fuel nozzle for the second combustion chamber starts operating is set to be equal to or higher than the ignition point of the supplied fuel. Low calorie gas fired gas turbine combustor. 3 The fuel nozzle for the second combustion chamber is installed near the center of the air hole, and is configured to supply fuel mixed with the main air flow from the air hole, at least in a range where the fuel flow rate is low. A low-calorie gas-fired gas turbine combustor according to claim 1, characterized in that:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11076082A JPS594823A (en) | 1982-06-29 | 1982-06-29 | Gas turbine combustor for low calory gas |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11076082A JPS594823A (en) | 1982-06-29 | 1982-06-29 | Gas turbine combustor for low calory gas |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS594823A JPS594823A (en) | 1984-01-11 |
| JPH0139016B2 true JPH0139016B2 (en) | 1989-08-17 |
Family
ID=14543866
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP11076082A Granted JPS594823A (en) | 1982-06-29 | 1982-06-29 | Gas turbine combustor for low calory gas |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS594823A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009047415A (en) * | 2007-08-21 | 2009-03-05 | General Electric Co <Ge> | Turbine engine fuel delivery system and system |
| CN101936224A (en) * | 2009-06-30 | 2011-01-05 | 通用电气公司 | Method and apparatus for burner fuel circuits for ultra-low calorific fuels |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS63150428A (en) * | 1986-12-16 | 1988-06-23 | Sakio Yoneda | High speed gas turbine |
| JP4725039B2 (en) * | 2004-06-14 | 2011-07-13 | 株式会社ジェイテクト | Drive shaft |
| WO2023162375A1 (en) | 2022-02-25 | 2023-08-31 | 株式会社Ihi | Combustion device and gas turbine |
-
1982
- 1982-06-29 JP JP11076082A patent/JPS594823A/en active Granted
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009047415A (en) * | 2007-08-21 | 2009-03-05 | General Electric Co <Ge> | Turbine engine fuel delivery system and system |
| CN101936224A (en) * | 2009-06-30 | 2011-01-05 | 通用电气公司 | Method and apparatus for burner fuel circuits for ultra-low calorific fuels |
| JP2011012673A (en) * | 2009-06-30 | 2011-01-20 | General Electric Co <Ge> | Method and apparatus for combustor fuel circuit for ultra low calorific fuel |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS594823A (en) | 1984-01-11 |
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