JPH08178291A - Gas turbine burner - Google Patents
Gas turbine burnerInfo
- Publication number
- JPH08178291A JPH08178291A JP32663494A JP32663494A JPH08178291A JP H08178291 A JPH08178291 A JP H08178291A JP 32663494 A JP32663494 A JP 32663494A JP 32663494 A JP32663494 A JP 32663494A JP H08178291 A JPH08178291 A JP H08178291A
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- inner cylinder
- air
- combustion
- gas turbine
- 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.)
- Granted
Links
Abstract
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 is branched first, 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) due to 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 discharged 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 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Ichiman Iwai Inventor, Ichiman Iwai 502 Kintatemachi, Tsuchiura City, Ibaraki Pref.
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す
る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, A gas turbine combustor, which is characterized by forming an unburned lean mixture under the conditions.
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気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する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 for the air 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. , A gas turbine combustor characterized by forming a non-combustible lean air-fuel mixture under the conditions of the inner cylinder.
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 true JPH08178291A (en) | 1996-07-12 |
JP3482718B2 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) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2000046332A (en) * | 1998-07-27 | 2000-02-18 | Asea Brown Boveri Ag | Method and system for operating gas turbine with gaseous fuel |
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 |
CN103791517A (en) * | 2012-10-31 | 2014-05-14 | 中航商用航空发动机有限责任公司 | Combustion chamber fuel injecting and mixing device |
-
1994
- 1994-12-28 JP JP32663494A patent/JP3482718B2/en not_active Expired - Fee Related
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2000046332A (en) * | 1998-07-27 | 2000-02-18 | Asea Brown Boveri Ag | Method and system for operating gas turbine with gaseous fuel |
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 |
CN103791517A (en) * | 2012-10-31 | 2014-05-14 | 中航商用航空发动机有限责任公司 | Combustion chamber fuel injecting and mixing device |
Also Published As
Publication number | Publication date |
---|---|
JP3482718B2 (en) | 2004-01-06 |
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