JP3482718B2 - Gas turbine combustor - Google Patents
Gas turbine combustorInfo
- Publication number
- JP3482718B2 JP3482718B2 JP32663494A JP32663494A JP3482718B2 JP 3482718 B2 JP3482718 B2 JP 3482718B2 JP 32663494 A JP32663494 A JP 32663494A JP 32663494 A JP32663494 A JP 32663494A JP 3482718 B2 JP3482718 B2 JP 3482718B2
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- inner cylinder
- combustion
- gas turbine
- air
- 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 - Fee Related
Links
Description
【０００１】[0001]
【産業上の利用分野】本発明はガスタービン燃焼器にお
ける希薄予混合気形成方法および燃焼方法に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a lean premix formation method and a combustion method in a gas turbine combustor.
【０００２】[0002]
【従来の技術】希薄予混合燃焼を主体とするガスタービ
ン燃焼器の一例は実願平1−5663 号に示されており、そ
の概略図を図３に示す。内筒１８２の中心軸上の燃料ノ
ズル１３１からは拡散燃焼用の燃料が噴射されて燃焼安
定性を高める働きをし、その外周の各予混合室１５２，
１５３，１５４からは燃料希薄予混合気が旋回して供給
され、燃料ノズル１３１からの拡散燃料によって補助さ
れながら燃焼する。燃焼室１９３は１５００℃以上の高
温になるので内筒１８２の壁面温度が高くなり、通常の
耐熱金属材料の許容温度を超える。したがって、図示し
ない空気孔を多数設けて内筒１８２と外筒１８１の間を
流れる空気の一部を流して冷却している。燃焼器出口平
均ガス温度の高いガスタービン燃焼器では燃焼域の局所
温度を燃焼反応を安定保持できる限界まで下げてＮＯｘ
の生成を抑制しようとするために、予混合室１５２，１
５３，１５４へ供給する空気割合をできるだけ多くしよ
うとしている。一方、内筒１８２の壁面温度は燃焼域の
温度および燃焼器出口平均ガス温度が上昇すると高くな
る傾向にあり、高温ガスタービンになるほど内筒冷却に
必要な空気流量は増加する。したがって高温ガスタービ
ン燃焼器では、燃焼用空気と冷却用空気とを分け、燃焼
用空気のみに燃料を予混合して燃焼する方法では燃焼域
の局所温度を必要温度まで下げることができなくなり、
ＮＯｘ生成量が多くなると考えられる。2. Description of the Related Art An example of a gas turbine combustor mainly composed of lean premixed combustion is shown in Japanese Patent Application No. 1-5663, and its schematic diagram is shown in FIG. Fuel for diffusion combustion is injected from the fuel nozzle 131 on the central axis of the inner cylinder 182 to serve to enhance combustion stability.
A lean fuel mixture is swirled and supplied from 153 and 154, and burns while being assisted by the diffusion fuel from the fuel nozzle 131. Since the combustion chamber 193 has a high temperature of 1500 ° C. or higher, the wall temperature of the inner cylinder 182 becomes high, which exceeds the permissible temperature of the ordinary heat-resistant metal material. Therefore, a large number of air holes (not shown) are provided to flow a part of the air flowing between the inner cylinder 182 and the outer cylinder 181 for cooling. In a gas turbine combustor with a high average gas temperature at the combustor outlet, the local temperature in the combustion region is lowered to the limit at which the combustion reaction can be stably maintained and NOx
In order to suppress the formation of
We are trying to maximize the proportion of air supplied to 53,154. On the other hand, the wall surface temperature of the inner cylinder 182 tends to increase as the temperature in the combustion zone and the average gas temperature at the combustor outlet increase, and the air flow rate required for cooling the inner cylinder increases as the temperature of the high temperature gas turbine increases. Therefore, in the high temperature gas turbine combustor, it is impossible to lower the local temperature of the combustion region to the required temperature by the method of dividing the combustion air and the cooling air and premixing the fuel only with the combustion air to burn it.
It is considered that the amount of NOx produced will increase.
【０００３】[0003]
【発明が解決しようとする課題】上記従来技術は、高温
ガスタービンの高負荷時に燃焼域の火炎温度を下げて、
ＮＯｘ生成を抑制するために必要な空気を確保できな
い。SUMMARY OF THE INVENTION In the above-mentioned prior art, the flame temperature in the combustion region is lowered when the high temperature gas turbine is under heavy load,
It is not possible to secure the air required to suppress NOx generation.
【０００４】本発明の目的は従来の燃焼域に供給する燃
料流量を減少し、残りの燃料を従来の燃焼域の下流側の
ガス温度がわずかに低下した領域で、局所的な火炎温度
の上昇を防止しつつ燃焼させる方法を提供することであ
る。The object of the present invention is to reduce the flow rate of fuel supplied to the conventional combustion zone and to increase the remaining fuel in a region where the gas temperature on the downstream side of the conventional combustion zone is slightly lowered, thereby locally increasing the flame temperature. It is to provide a method of burning while preventing.
【０００５】[0005]
【課題を解決するための手段】内筒と外筒で形成される
空気流路を流れる空気すなわち燃焼用空気および冷却用
空気に燃料を供給，混合するための複数の燃料ノズルと
燃料供給配管および流量制御機構を設け、燃焼器全体燃
料流量の一部を供給する。A plurality of fuel nozzles for supplying and mixing fuel to air flowing in an air passage formed by an inner cylinder and an outer cylinder, that is, combustion air and cooling air, and a fuel supply pipe, and A flow rate control mechanism is provided to supply a part of the total fuel flow rate of the combustor.
【０００６】また、内筒冷却用空気に燃料を供給，混合
するための複数の燃料ノズルと燃料供給配管および流動
制御機構を設け、燃焼器全体燃料流量の一部を供給す
る。Further, a plurality of fuel nozzles for supplying and mixing fuel to the inner cylinder cooling air, a fuel supply pipe and a flow control mechanism are provided to supply a part of the entire combustor fuel flow rate.
【０００７】[0007]
【作用】内筒と外筒で形成される空気通路を流れる空気
に少量の燃料を混合し、燃焼器入口空気温度条件では発
火しない希薄予混合気を形成する。従来の燃焼域に供給
される希薄予混合気は新たに燃料を供給され、予混合燃
焼又は一部が拡散燃焼する。この結果、燃焼域では１５
００℃以上の高温ガスが生成される。この高温ガスに対
して内筒壁面穴を介して供給される内筒冷却用希薄予混
合気は内筒を冷却した後に高温燃焼ガスと混合する。こ
の混合ガスの温度は燃焼域よりも低いが、可燃ガスが燃
焼反応を進行させるために必要な温度よりも十分に高い
ため、冷却空気中に混合した燃料は局所的に急激な温度
上昇をしないで燃焼する。The small amount of fuel is mixed with the air flowing through the air passage formed by the inner cylinder and the outer cylinder to form a lean premixed mixture that does not ignite under the conditions of the air temperature at the inlet of the combustor. The lean premixture supplied to the conventional combustion zone is newly supplied with fuel, and premixed combustion or partial diffusion combustion is performed. As a result, 15
A high temperature gas of 00 ° C. or higher is generated. The lean premixed air for cooling the inner cylinder, which is supplied to the high temperature gas through the inner wall surface hole, is mixed with the high temperature combustion gas after cooling the inner cylinder. Although the temperature of this mixed gas is lower than that in the combustion region, the combustible gas is sufficiently higher than the temperature necessary for the combustion reaction to proceed, so the fuel mixed in the cooling air does not have a sharp local temperature rise. Burns at.
【０００８】燃焼域供給空気と内筒冷却空気との通路が
分離している場合には、内筒冷却空気に燃料を混合して
希薄混合気を形成すると前述と同様の働きを期待でき
る。In the case where the passages for the combustion zone supply air and the inner cylinder cooling air are separated, if the inner cylinder cooling air is mixed with fuel to form a lean air-fuel mixture, the same function as described above can be expected.
【０００９】[0009]
【実施例】本発明の一実施例を図１に示す。燃焼室１９
３を形成する内筒１８２と、その外周の熱遮蔽効果と内
筒冷却性能の調節機能を有する内筒フロースリーブ１８
３と、その外周の燃焼器部全体を収納する圧力容器であ
る外筒１８１と、内筒182の端部中心の第１燃料ノズル
１３１と、その外周の空気供給用のスワーラ１５１と、
更にその外周の第１予混合室１５２，第２予混合室１５
３と、各予混合室内の第２燃料ノズル１３２，第３燃料
ノズル１３３と、各予混合室出口近傍外周壁の第１保炎
器１６２，第２保炎器１６３と、各燃料ノズルへ燃料を
供給する配管１１１，１１２，１１３と途中の流量制御
弁１２１，１２２，１２３に加えて、内筒１８２と内筒
フロースリーブ１８３の間を流れる空気に燃料を供給す
る第４燃料ノズル１３５と、燃料を供給する配管１１５
と、その途中の流量制御弁125、更に内筒１８２と図示
しないタービンノズルとを接続する尾筒１８４とそのフ
ロースリーブ１８５によって燃焼器部を構成している。
図示しない圧縮機から燃焼器部へ供給される空気は尾筒
１８４と尾筒フロースリーブ１８５とによって形成され
る環状通路および内筒１８２と内筒フロースリーブ１８
３とによって形成される環状通路１９１内を矢印２０１
の方向に全量が進み、途中で内筒１８２の冷却効果を高
めるために設けられた冷却空気孔１９２を通って燃焼室
１９３に流入する空気流２０５がまず分岐し、更に矢印
２０２，２０３のように燃焼用空気が分岐した後に、予
混合燃焼空気は予混合室１５２，１５３を通り、拡散燃
焼空気はスワーラ１５１を通って燃焼室１９３へと供給
される。一方、拡散燃焼する第１燃料ノズル１３１用燃
料Ｆ1 は配管１１１と流量制御弁１２１を介して供給さ
れ、予混合燃焼する第２燃料ノズル１３２用燃料Ｆ2 は
配管１１２と流量制御弁１２２を介して供給され、予混
合燃焼する第３燃料ノズル１３３用燃料Ｆ3 は配管１１
３と流量制御弁１２３を介して供給され、空気全体と予
混合する第４燃料ノズル１３５用燃料Ｆ4 は配管１１５
と流量制御弁１２５を介して供給される。FIG. 1 shows an embodiment of the present invention. Combustion chamber 19
3, the inner cylinder 182 forming the inner cylinder 182, and the inner cylinder flow sleeve 18 having a heat shielding effect on the outer circumference and a function of adjusting the inner cylinder cooling performance.
3, an outer cylinder 181, which is a pressure vessel that houses the entire combustor portion on the outer periphery thereof, a first fuel nozzle 131 at the center of the end of the inner cylinder 182, and a swirler 151 for supplying air on the outer periphery thereof.
Further, the first premixing chamber 152 and the second premixing chamber 15 on the outer periphery thereof
3, the second fuel nozzle 132 and the third fuel nozzle 133 in each premix chamber, the first flame stabilizer 162, the second flame stabilizer 163 on the outer peripheral wall near the outlet of each premix chamber, and the fuel to each fuel nozzle. In addition to the pipes 111, 112, 113 for supplying the air and the flow control valves 121, 122, 123 on the way, a fourth fuel nozzle 135 for supplying fuel to the air flowing between the inner cylinder 182 and the inner cylinder flow sleeve 183, Pipe 115 for supplying fuel
The flow control valve 125 in the middle thereof, the tail cylinder 184 connecting the inner cylinder 182 and the turbine nozzle (not shown), and the flow sleeve 185 thereof constitute a combustor section.
The air supplied from the compressor (not shown) to the combustor section has an annular passage formed by the transition piece 184 and the transition piece flow sleeve 185, and the inner cylinder 182 and the inner cylinder flow sleeve 18.
The inside of the annular passage 191 formed by
, The air flow 205 that flows into the combustion chamber 193 through the cooling air holes 192 provided to enhance the cooling effect of the inner cylinder 182 on the way is first branched, and as shown by arrows 202 and 203. After the combustion air is branched, the premixed combustion air passes through the premixing chambers 152 and 153, and the diffusion combustion air passes through the swirler 151 and is supplied to the combustion chamber 193. On the other hand, the fuel F 1 for the first fuel nozzle 131, which diffuses and burns, is supplied through the pipe 111 and the flow rate control valve 121, and the fuel F 2 for the second fuel nozzle 132, which performs premix combustion, passes through the pipe 112 and the flow rate control valve 122. The fuel F 3 for the third fuel nozzle 133, which is supplied via
3 and the fuel F 4 for the fourth fuel nozzle 135, which is supplied through the flow control valve 123 and is premixed with the entire air, is connected to the pipe 115.
And a flow rate control valve 125.
【００１０】この燃焼器はガスタービン負荷によって燃
料供給系統及び流量を図２に示すように制御しており、
その詳細を以下に記す。ガスタービン負荷Ｏ〜Ａ％の低
負荷では、第１燃料ノズル１３１から噴射される燃料Ｆ
1 がスワーラ１５１から供給される旋回空気中で拡散燃
焼し、火炎１７１を形成する。ガスタービン負荷がＡ％
に達すると、燃料Ｆ1 をｆからｅまで減少し、第１予混
合室１５２内へ第２燃料ノズル１３２から燃料Ｆ2 をｆ
ｅだけ供給する。この条件では、拡散火炎171からの熱
供給があるために、第１予混合室１５２から燃焼室１９
３へ噴射される混合気は燃焼しやすくなっており、第１
保炎器１６２によって保炎され、第１予混合火炎１７２
を形成する。ガスタービン負荷がＡ％以上になると、燃
料Ｆ1 とＦ2 を増す。燃料が増すとＮＯｘ生成量も増
し、ＮＯｘが許容値に達するガスタービン負荷Ｂ％で
は、燃料Ｆ1とＦ2を減少し、第２予混合室１５３内へ第
３燃料ノズル１３３から燃料Ｆ3 をｊｉだけ供給して混
合気を形成し、この混合気は拡散火炎１７１と第１予混
合火炎１７２から熱供給されて燃焼しやすくなるので、
第２保炎器１６３によって保炎され、第２予混合火炎１
７３を形成する。ガスタービン負荷がＢ％以上ではＮＯ
ｘ生成量の多い拡散燃焼に使われる燃料Ｆ1 は安定燃焼
に必要な一定量とし、ＮＯｘ生成の少ない予混合燃焼に
使われる燃料Ｆ2,Ｆ3 を増加する。そして、内筒１８２
の内筒冷却孔１９２から流入する内筒冷却空気２０５に
燃料Ｆ4 が混合し、その燃料Ｆ4 が尾筒１８４内部を流
れる時間内で燃焼反応が完了する尾筒１８４の出口ガス
温度約１２００℃に相当するガスタービン負荷Ｃ％に達
すると、燃焼器部空気全体に対して第４燃料ノズル１３
５から燃料Ｆ4 を供給する。燃料Ｆ4 の一部は、内筒冷
却空気２０５と混合して、内筒１８２の側面に設けた冷
却孔１９２から内筒内部に流入し上流の拡散火炎171,第
１予混合火炎１７２と第２予混合火炎１７３によって生
成された高温燃焼ガスと混合して燃焼する。この際に内
筒１８２の外周環状流路１９１で形成される予混合気
は、内筒１８２の外側の空気温度，圧力，水分濃度条件
では燃焼できない燃料希薄予混合気とする。従って、内
筒冷却空気２０５に混合した燃料Ｆ4 が尾筒１８４内部
で燃焼する場合でも、上流側の火炎１７１，１７２，１
７３の温度よりも低く、ＮＯｘ生成はほとんどゼロであ
る。この燃料Ｆ4 で形成される予混合気濃度条件を満足
しつつ、ガスタービン負荷１００％まで燃料流量を増加
する。この結果、燃料Ｆ4 を別系統から内筒１８２の内
部へ流したことにより、ガスタービン負荷１００％にお
ける第１予混合火炎１７２への燃料Ｆ2 と第２予混合火
炎１７３への燃料Ｆ3 は少なくなっており、火炎温度も
低下している。In this combustor, the fuel supply system and the flow rate are controlled by the gas turbine load as shown in FIG.
The details will be described below. At a low load of gas turbine load O to A%, the fuel F injected from the first fuel nozzle 131 is injected.
1 diffuses and burns in the swirling air supplied from the swirler 151 to form a flame 171. Gas turbine load is A%
The fuel F 1 is reduced from f to e and the fuel F 2 is fed from the second fuel nozzle 132 into the first premix chamber 152.
Only e is supplied. Under this condition, since heat is supplied from the diffusion flame 171, the first premixing chamber 152 to the combustion chamber 19
The air-fuel mixture injected into No. 3 is easy to burn.
The first premixed flame 172 is flame-preserved by the flame stabilizer 162.
To form. When the gas turbine load exceeds A%, the fuels F 1 and F 2 are increased. When the amount of fuel increases, the amount of NOx produced also increases, and at the gas turbine load B% at which NOx reaches the allowable value, the fuels F 1 and F 2 are reduced, and the fuel F 3 flows from the third fuel nozzle 133 into the second premix chamber 153. To form a mixture, and this mixture is supplied with heat from the diffusion flame 171 and the first premixed flame 172 to facilitate combustion.
The flame is maintained by the second flame stabilizer 163, and the second premixed flame 1
73 is formed. NO when the gas turbine load is B% or more
The fuel F 1 used for diffusion combustion with a large amount of x generation is a fixed amount required for stable combustion, and the fuels F 2 and F 3 used for premixed combustion with a small amount of NOx generation are increased. And the inner cylinder 182
The fuel F 4 is mixed with the inner cylinder cooling air 205 flowing from the inner cylinder cooling hole 192 of the inner cylinder cooling hole 192, and the combustion reaction is completed within a time period during which the fuel F 4 flows inside the rear cylinder 184. When the gas turbine load C% corresponding to ℃ is reached, the fourth fuel nozzle 13 is supplied to the entire combustor section air.
Fuel F 4 is supplied from 5. A part of the fuel F 4 mixes with the inner cylinder cooling air 205, flows into the inner cylinder through a cooling hole 192 provided on the side surface of the inner cylinder 182, and enters the upstream diffusion flame 171, the first premixed flame 172, and the first premixed flame 172. 2 It mixes with the high temperature combustion gas generated by the premixed flame 173 and burns. At this time, the premixed gas formed in the outer peripheral annular flow path 191 of the inner cylinder 182 is a lean fuel premixed fuel that cannot be burned under the conditions of air temperature, pressure and moisture concentration outside the inner cylinder 182. Therefore, even when the fuel F 4 mixed with the inner cylinder cooling air 205 burns inside the transition piece 184, the flames 171, 172, 1 on the upstream side are generated.
Below the temperature of 73, NOx production is almost zero. The fuel flow rate is increased to 100% of the gas turbine load while satisfying the premixed gas concentration condition formed by the fuel F 4 . As a result, by flowing the fuel F 4 from another system into the interior of the inner cylinder 182, the fuel F 3 of the fuel F 2 to the first premixed flame 172 in the gas turbine load 100% to the second premixed flame 173 Is low and the flame temperature is low.
【００１１】予混合火炎の保炎方法が異なる、他の一実
施例を図４に示す。第１予混合室１５２の環状出口端の
流路中心近傍にブラフボディ型の第１保炎器１６２を設
け、第２予混合室１５３の環状出口端の流路中心近傍に
ブラフボディ型の第２保炎器１６３を設けている。機能
上は図１と同じであるが、１つの保炎器の内周側と外周
側に火炎が分割されて形成される点が異なる。しかし、
ガスタービン負荷に対する燃料供給系統及び流量の制御
は、図２に従って行うことが可能であり、燃料Ｆ4 を供
給する効果は図１の構造と同じである。FIG. 4 shows another embodiment in which the flame holding method of the premixed flame is different. A first bluff body type flame stabilizer 162 is provided near the center of the flow passage at the annular outlet end of the first premixing chamber 152, and a bluff body type first flame stabilizer 162 is provided near the center of the flow passage at the annular outlet end of the second premixing chamber 153. Two flame stabilizers 163 are provided. Although it is functionally the same as that of FIG. 1, it is different in that the flame is divided and formed on the inner peripheral side and the outer peripheral side of one flame stabilizer. But,
The control of the fuel supply system and the flow rate with respect to the gas turbine load can be performed according to FIG. 2, and the effect of supplying the fuel F 4 is the same as the structure of FIG.
【００１２】また、予混合火炎の保炎方法が異なる、別
の一実施例を図５に示す。第１予混合室１５２の環状出
口端の流路中心近傍にはブライボディ型の第１保炎器１
６２を有するが、第２予混合室１５３の環状出口端には
保炎器を有しない。この構造において、メタンガスを燃
焼する場合、燃料Ｆ1 から燃料Ｆ2 の燃焼によって、尾
筒１８４の出口平均ガス温度が約１２００℃（メタンガ
ス燃焼時）に達した後に、第２予混合室１５３内へ第３
燃料ノズル１３３から燃料Ｆ3 を供給して予混合気とし
て、燃焼室１９３へ供給することにより、尾筒１８４の
出口端に達する前に燃料Ｆ3 は燃焼を完了することがで
き、燃焼温度が通常の保炎器で保炎される火炎の温度よ
りも低いために、ＮＯｘはほとんど生成しない。そし
て、燃焼器全体空気に第４燃料ノズル１３５から燃料Ｆ
4 を噴射して混合気を作り、その一部が内筒冷却空気２
０５として内筒冷却孔１９２から燃焼室１９３に流入
し、上流の約１２００℃以上の燃焼ガスと混合して燃焼
する場合も前記の燃料Ｆ3 の燃焼と同様であり、燃焼温
度が通常の保炎器で保炎される火炎の温度よりも低いた
めにＮＯｘはほとんど生成しない。FIG. 5 shows another embodiment in which the flame holding method of the premixed flame is different. In the vicinity of the center of the flow path at the annular outlet end of the first premixing chamber 152, the first bridging flame stabilizer 1 is provided.
62, but without the flame stabilizer at the annular outlet end of the second premixing chamber 153. In this structure, when combusting methane gas, the average gas temperature at the outlet of the transition piece 184 reaches about 1200 ° C. (during combustion of methane gas) by the combustion of the fuel F 1 to the fuel F 2 , and then the inside of the second premixing chamber 153. To third
By supplying the fuel F 3 from the fuel nozzle 133 as a premixed gas to the combustion chamber 193, the fuel F 3 can complete combustion before reaching the outlet end of the transition piece 184, and the combustion temperature is Since the temperature is lower than that of the flame held by a normal flame stabilizer, NOx is hardly generated. Then, the fuel F is discharged from the fourth fuel nozzle 135 to the combustor whole air.
4 is injected to create a mixture, part of which is the inner cylinder cooling air 2
In the case where the fuel F 3 flows from the inner cylinder cooling hole 192 into the combustion chamber 193 and mixes with the upstream combustion gas of about 1200 ° C. or higher and burns, the combustion temperature is the same as the combustion of the fuel F 3 described above, and the combustion temperature is maintained at a normal level. Almost no NOx is produced because it is lower than the temperature of the flame held by the flame.
【００１３】以上の実施例において、尾筒１８４の外周
に、燃焼器部全体空気を流すためのフロースリーブ１８
５を有する構造の場合には、第４燃料ノズル１３５を尾
筒１８４とフロースリーブ１８５とによって形成される
空間に設けることにより、同様の機能・効果が得られ
る。In the above-described embodiment, the flow sleeve 18 for flowing the entire air in the combustor section is provided around the outer periphery of the transition piece 184.
In the case of the structure having 5, the similar function and effect can be obtained by providing the fourth fuel nozzle 135 in the space formed by the transition piece 184 and the flow sleeve 185.
【００１４】また、さらに別の一実施例として、内部冷
却空気通路を燃焼空気通路と分離した構造を図６に示
す。この構造では、第４燃料ノズル１３５を内筒１８２
とフロースリーブ１８３によって形成される内筒冷却空
気通路２１１に設け、図示しない尾筒１８４の出口平均
ガス温度が約１２００℃（メタンガス燃焼時）以上の条
件で燃料Ｆ4 を第４燃料ノズル１３５から噴射し、混合
気を形成した後に内筒冷却孔１９２から燃焼室１９３へ
供給することにより、尾筒１８４の途中で燃焼が完了す
る。燃料Ｆ4 と内筒冷却空気を予混合した混合気は内筒
１８２の外周の空気温度，圧力，水分濃度条件では燃焼
できない燃料希薄予混合気であり、燃焼室１９３で燃焼
している火炎温度よりも低い温度で燃焼するためには、
ＮＯｘはほとんど生成しない。又、予混合燃料Ｆ2，Ｆ3
が減少し、予混合火炎１７２，173の温度が低下するの
で、ＮＯｘの生成は減少する。As yet another embodiment, FIG. 6 shows a structure in which the internal cooling air passage is separated from the combustion air passage. In this structure, the fourth fuel nozzle 135 is connected to the inner cylinder 182.
Is provided in the inner cylinder cooling air passage 211 formed by the flow sleeve 183 and the flow sleeve 183, and the fuel F 4 is supplied from the fourth fuel nozzle 135 under the condition that the outlet average gas temperature of the unillustrated transition piece 184 is about 1200 ° C. (during methane gas combustion) or more. Combustion is completed in the middle of the transition piece 184 by injecting and forming an air-fuel mixture and then supplying the mixture from the inner cylinder cooling hole 192 to the combustion chamber 193. The air-fuel mixture in which the fuel F 4 and the inner cylinder cooling air are pre-mixed is a lean fuel pre-mixture that cannot be burned under the air temperature, pressure, and water concentration conditions of the outer circumference of the inner cylinder 182, and the flame temperature burning in the combustion chamber 193. In order to burn at a lower temperature,
Almost no NOx is produced. Also, the premixed fuels F 2 , F 3
Is reduced and the temperature of the premixed flames 172, 173 is reduced, so that the production of NOx is reduced.
【００１５】なお、燃料Ｆ4 を空気と均一混合しやすく
するために、Ｆ4 燃料ノズル１３５は図１に示す先端開
口のパイプ状の他に、側面開口のパイプ状のものを複数
本、放射状に配置する形式や、環状空気通路１９１，２
１１に対応した環状パイプを設け、その側面に複数の開
口を有する形式が可能である。In order to facilitate the uniform mixing of the fuel F 4 with air, the F 4 fuel nozzle 135 has a plurality of side-opening pipe-shaped nozzles, in addition to the tip-opening pipe-shaped nozzle shown in FIG. And the annular air passages 191 and 2
A form having an annular pipe corresponding to No. 11 and having a plurality of openings on its side surface is possible.
【００１６】[0016]
【発明の効果】本発明によれば、従来の燃焼域に供給す
る燃料が、全体燃料流量から内筒冷却空気に予混合する
燃料流量を差し引いた流量となるので、従来の燃焼域の
燃料流量と空気流量の比すなわち火炎温度を下げること
が可能となり、火炎温度に支配されることが公知である
ＮＯｘの生成を抑制できる。そして従来の燃焼域の下流
で内筒冷却空気中の燃料が燃焼するが、低温燃焼であ
り、ＮＯｘの生成はほとんどないので、燃焼器全体での
ＮＯｘ生成を抑制できる。According to the present invention, since the fuel supplied to the conventional combustion zone is the total fuel flow rate minus the fuel flow rate premixed with the inner cylinder cooling air, the fuel flow rate in the conventional combustion zone is reduced. The ratio of the air flow rate to the air flow rate, that is, the flame temperature can be lowered, and the generation of NOx, which is known to be governed by the flame temperature, can be suppressed. Then, the fuel in the inner cylinder cooling air burns downstream of the conventional combustion region, but since it is low-temperature combustion and almost no NOx is produced, NOx production in the entire combustor can be suppressed.
【００１７】特に高温ガスタービン燃焼器で、冷却空気
を除いた燃焼空気と燃料を予混合燃焼する場合には低温
燃焼するための燃焼空気が不足するのでＮＯｘ生成が多
くなる傾向にあり、本発明の効果は大である。Particularly, in a high temperature gas turbine combustor, when premixed combustion of combustion air excluding cooling air and fuel, there is a shortage of combustion air for low temperature combustion, so that NOx production tends to increase, and the present invention Has a great effect.
【図１】本発明の一実施例の縦断面図。FIG. 1 is a vertical sectional view of an embodiment of the present invention.
【図２】本発明の燃料制御図。FIG. 2 is a fuel control diagram of the present invention.
【図３】従来例の縦断面図。FIG. 3 is a vertical sectional view of a conventional example.
【図４】本発明の他の一実施例の縦断面図。FIG. 4 is a vertical cross-sectional view of another embodiment of the present invention.
【図５】本発明の別の一実施例の縦断面図。FIG. 5 is a vertical sectional view of another embodiment of the present invention.
【図６】本発明の更に別の一実施例の縦断面図。FIG. 6 is a vertical sectional view of still another embodiment of the present invention.
１３１…第１燃料ノズル、１３２…第２燃料ノズル、１
３３…第３燃料ノズル、１３５…第４燃料ノズル、１５
１…スワーラ、１５２…第１予混合室、１５３…第２予
混合室、１８１…外筒、１８２…内筒、１８３…内筒フ
ロースリーブ、１８４…尾筒。131 ... First fuel nozzle, 132 ... Second fuel nozzle, 1
33 ... 3rd fuel nozzle, 135 ... 4th fuel nozzle, 15
DESCRIPTION OF SYMBOLS 1 ... Swirler, 152 ... 1st premixing chamber, 153 ... 2nd premixing chamber, 181 ... Outer cylinder, 182 ... Inner cylinder, 183 ... Inner cylinder flow sleeve, 184 ... Tail cylinder.
───────────────────────────────────────────────────── フロントページの続き (72)発明者 岩井 一躬 茨城県土浦市神立町502番地 株式会社 日立製作所 機械研究所内 (56)参考文献 特開 平１−114623（ＪＰ，Ａ) 特開 昭62−174539（ＪＰ，Ａ) (58)調査した分野(Int.Cl.7，ＤＢ名) F23R 3/20,3/28 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor, Ichiman Iwai 502 Jinritsucho, Tsuchiura City, Ibaraki Prefecture Machinery Research Laboratory, Hitachi, Ltd. (56) Reference JP-A-1-114623 (JP, A) JP-A-62 -174539 (JP, A) (58) Fields investigated (Int.Cl. 7 , DB name) F23R 3 / 20,3 / 28
Claims (2)
又は予混合室を経て燃料を供給する燃料ノズルと、これ
らを収納する外筒より成るガスタービン燃焼器におい
て、前記内筒と外筒とによって形成される空間に燃料供
給部材を設け、前記燃料供給部材から燃焼器全体燃料供
給量の一部を供給し、内筒冷却空気を含む全体空気と混
合して、内筒外部条件における不燃希薄混合気を形成
し、前記燃焼室で生成された高温ガスと混合するよう
に、前記不燃希薄混合気を前記内筒の壁面穴を介して前
記燃焼室に供給するよう構成したことを特徴とするガス
タービン燃焼器。1. A gas turbine combustor comprising an inner cylinder forming a combustion chamber, a fuel nozzle for supplying fuel to the inner cylinder directly or through a premixing chamber, and an outer cylinder housing the same. A fuel supply member is provided in the space formed by the outer cylinder and the outer cylinder, and a part of the total fuel supply amount of the combustor is supplied from the fuel supply member and mixed with the whole air including the inner cylinder cooling air, To form a non-combustible lean mixture under certain conditions
And mix with the hot gases produced in the combustion chamber
The unburnt lean mixture through the wall hole of the inner cylinder.
A gas turbine combustor characterized by being configured to supply to the combustion chamber .
又は予混合室を経て燃料を供給する燃料ノズルと、これ
らを収納する外筒より成るガスタービン燃焼器におい
て、前記内筒と、その外周の内筒冷却空気フロースリー
ブとによって形成される空間に燃料供給部材を設け、前
記燃料供給部材から燃焼器全体燃料供給量の一部を供給
し、内筒冷却空気と混合して、内筒外部条件における不
燃希薄混合気を形成し、前記燃焼室で生成された高温ガ
スと混合するように、前記不燃希薄混合気を前記内筒の
壁面穴を介して前記燃焼室に供給するよう構成したこと
を特徴としたガスタービン燃焼器。2. A gas turbine combustor comprising an inner cylinder forming a combustion chamber, a fuel nozzle for supplying fuel to the inner cylinder directly or through a premixing chamber, and an outer cylinder accommodating the fuel nozzle and the inner cylinder. And a fuel supply member provided in a space formed by the inner cylinder cooling air flow sleeve on the outer periphery of the combustor and supplying a part of the total fuel supply amount of the combustor from the fuel supply member to mix with the inner cylinder cooling air. Supplying an unburnt lean mixture to the combustion chamber through a wall hole of the inner cylinder so as to form an unburnt lean mixture under the condition outside the inner cylinder and mix with the high temperature gas generated in the combustion chamber. A gas turbine combustor characterized by being configured as described above.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP32663494A JP3482718B2 (en) | 1994-12-28 | 1994-12-28 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP32663494A JP3482718B2 (en) | 1994-12-28 | 1994-12-28 | Gas turbine combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH08178291A JPH08178291A (en) | 1996-07-12 |
| JP3482718B2 true JP3482718B2 (en) | 2004-01-06 |
Family
ID=18189988
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP32663494A Expired - Fee Related JP3482718B2 (en) | 1994-12-28 | 1994-12-28 | Gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3482718B2 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0976982B1 (en) * | 1998-07-27 | 2003-12-03 | ALSTOM (Switzerland) Ltd | Method of operating the combustion chamber of a liquid-fuel gas turbine |
| JP2006144759A (en) * | 2004-11-25 | 2006-06-08 | Toyota Central Res & Dev Lab Inc | Premixing combustor for gas turbine and its fuel supply control method |
| CN103791517B (en) * | 2012-10-31 | 2016-08-10 | 中航商用航空发动机有限责任公司 | Combustor fuel oil jet mixing device |
-
1994
- 1994-12-28 JP JP32663494A patent/JP3482718B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JPH08178291A (en) | 1996-07-12 |
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