JP2003074855A - Dual combustion nozzle and combustion equipment for gas turbine - Google Patents
Dual combustion nozzle and combustion equipment for gas turbineInfo
- Publication number
- JP2003074855A JP2003074855A JP2001259744A JP2001259744A JP2003074855A JP 2003074855 A JP2003074855 A JP 2003074855A JP 2001259744 A JP2001259744 A JP 2001259744A JP 2001259744 A JP2001259744 A JP 2001259744A JP 2003074855 A JP2003074855 A JP 2003074855A
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- swirler
- gas
- dual
- liquid
- 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.)
- Pending
Links
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、液体（油）燃料と
気体（ガス）燃料を燃焼用空気と混合して予混合気をつ
くり、燃焼させるように構成されたデュアル燃料ノズル
に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a dual fuel nozzle configured to mix a liquid (oil) fuel and a gas (gas) fuel with combustion air to form a premixed mixture for combustion.
【０００２】[0002]
【従来の技術】ガスタービン燃焼装置は、図５に示すよ
うに、中心のパイロットノズル２のまわりに複数本の予
混合ノズル３が配設されて構成された燃焼器１が１０数
個円周上に並べられて配置されている。４はスワラ（旋
回羽根）で、予混合ノズル３内のデュアル燃料ノズル５
から噴出された燃料と混合されて予混合気を形成する空
気に対し旋回力を与えるために設けられている。予混合
ノズル３内のデュアル燃料ノズル５からは、スワラ４の
直ぐ後流位置で気体燃料が噴出され、更にその後流位置
で液体燃料が噴出されるように構成されている。2. Description of the Related Art In a gas turbine combustion apparatus, as shown in FIG. 5, a dozen combustors 1 each having a plurality of premixing nozzles 3 arranged around a central pilot nozzle 2 are arranged around a circle. They are arranged side by side. 4 is a swirler (swirl vane), which is a dual fuel nozzle 5 in the premixing nozzle 3.
It is provided in order to give a swirling force to the air that is mixed with the fuel ejected from and forms a premixed gas. From the dual fuel nozzle 5 in the premixing nozzle 3, gaseous fuel is ejected at a position immediately downstream of the swirler 4 and liquid fuel is further ejected at a position downstream thereof.
【０００３】デュアル燃料ノズル５の構造例を図６に示
してある。図６において、６は、デュアル燃料ノズル５
を構成する棒状体で、棒状体６内には軸心方向に液体燃
料（油）流路７と気体燃料（ガス）流路８が形成されて
いる。液体燃料流路７を流れた液体燃料は、棒状体６の
先端部に形成された液体燃料噴出孔９から噴出されるよ
うに構成され、一方、気体燃料流路８を流れた気体燃料
はスワラ４の直ぐ後流側の位置に設けられた気体燃料噴
出孔１０から噴出されスワラ４によって旋回流となった
燃焼用空気と混合される。なお、図で１１は円筒状予混
合ノズルを示している。An example of the structure of the dual fuel nozzle 5 is shown in FIG. In FIG. 6, 6 is a dual fuel nozzle 5.
A liquid fuel (oil) flow path 7 and a gas fuel (gas) flow path 8 are formed in the rod-shaped body 6 in the axial direction. The liquid fuel flowing through the liquid fuel flow path 7 is configured to be ejected from a liquid fuel ejection hole 9 formed at the tip of the rod-shaped body 6, while the gaseous fuel flowing through the gas fuel flow path 8 is swirler. 4 is mixed with the combustion air that has been swirled by the swirler 4 and has been ejected from the gaseous fuel ejection hole 10 provided immediately downstream of the swirler 4. In the figure, reference numeral 11 indicates a cylindrical premixing nozzle.
【０００４】従来の油・ガスデュアル燃料ノズル５は、
以上説明したように、気体燃料、液体燃料共に棒状体６
に設けられた数個の気体燃料噴出孔１０、液体燃料噴出
孔９から噴出されていて、液体燃料の微粒化が不充分で
あって、気体燃料及び燃焼用空気との混合が充分でな
く、所定濃度の均一な予混合気の形成が不充分となって
いるという問題があり、そのため、低ＮＯX 化に限界を
生じていた。The conventional oil / gas dual fuel nozzle 5 is
As described above, the rod-shaped body 6 is used for both the gas fuel and the liquid fuel.
Is ejected from the several gas fuel ejection holes 10 and the liquid fuel ejection holes 9 provided in, the atomization of the liquid fuel is insufficient, and the mixing with the gas fuel and the combustion air is not sufficient, There is a problem that formation of a uniform premixture of a predetermined concentration has become insufficient, therefore, it had occurred a limit to the low NO X reduction.
【０００５】[0005]
【発明が解決しようとする課題】本発明は、ガスタービ
ンの燃焼器に適用される液体燃料と気体燃料を使うデュ
アル燃料ノズルにおいて、液体燃料を気流で微粒化して
気体燃料及び燃焼用空気との混合を良くして低ＮＯX 化
を達成することを課題としている。SUMMARY OF THE INVENTION The present invention relates to a dual fuel nozzle that uses a liquid fuel and a gas fuel, which is applied to a combustor of a gas turbine. The challenge is to improve mixing and achieve low NO x .
【０００６】[0006]
【課題を解決するための手段】本発明は、前記課題を解
決するため、液体燃料流路と気体燃料流路とを有する燃
料供給管を空気流の流路に沿って配置し、前記空気流に
旋回を与える複数枚のスワラを前記燃料供給管のまわり
に配設してなるデュアル燃料ノズルにおいて、前記スワ
ラに前記気体燃料流路及び液体燃料流路と連通された燃
料噴出孔を設けたデュアル燃料ノズルを提供する。In order to solve the above problems, the present invention provides a fuel supply pipe having a liquid fuel flow path and a gas fuel flow path along an air flow path, In a dual fuel nozzle in which a plurality of swirlers that give swirl to each other are arranged around the fuel supply pipe, a dual fuel nozzle in which the swirler is provided with a fuel injection hole communicating with the gas fuel flow path and the liquid fuel flow path Provide a fuel nozzle.
【０００７】本発明によるデュアル燃料ノズルでは、燃
料供給管のまわりに配置されたスワラに燃料噴出孔を設
け、そこから液体燃料と気体燃料とを空気流中に噴出さ
せるので、噴出された燃料は、スワラで旋回を与えられ
る空気と良く混合され、均一な混合気を形成することが
できる。予混合ノズルにおいて、スワラが設置されてい
る個所は流路断面積が小さくなっていて空気流速が大き
く、スワラに設けた噴出孔からそこに液体燃料を噴射す
ると液体燃料と空気流との相対速度が大きいため液体燃
料の微粒化が促進される。また、スワラで空気流に対し
て噴射された燃料は、燃焼されるまでの流路が従来より
も長くとれるので、液体燃料の蒸発が促進され、また、
空気及び気体燃料との混合が促進される。こうして、本
発明のデュアル燃料ノズルによれば均一な混合気が得ら
れ低ＮＯX 化が達成される。In the dual fuel nozzle according to the present invention, the swirler disposed around the fuel supply pipe is provided with the fuel ejection holes, and the liquid fuel and the gaseous fuel are ejected into the air flow from the holes, so that the ejected fuel is , It is well mixed with the air swirled to form a uniform air-fuel mixture. In the premixing nozzle, the location where the swirler is installed has a small flow passage cross-sectional area and a high air velocity, and when the liquid fuel is injected from the ejection holes provided in the swirler, the relative velocity between the liquid fuel and the air flow Is large, the atomization of the liquid fuel is promoted. Further, the fuel injected into the air flow by the swirler has a longer flow path until it is burned than before, so that evaporation of the liquid fuel is promoted, and
Mixing with air and gaseous fuel is facilitated. Thus, dual according to the fuel nozzle homogeneous mixture is obtained a low NO X of the present invention are achieved.
【０００８】本発明のデュアル燃料ノズルにおいて、ス
ワラに対する気体燃料の噴出孔と液体燃料の噴出孔の設
置は、例えば、スワラの翼表面（背側，腹側又は両面）
に気体燃料噴出孔、スワラの後縁（トレーリングエッ
ジ）に液体燃料噴出孔を設けた構造としてよい。In the dual fuel nozzle of the present invention, the gas fuel jet holes and the liquid fuel jet holes are installed on the swirler, for example, on the blade surface (back side, ventral side or both sides) of the swirler.
It is also possible to provide a structure in which a gas fuel injection hole is provided and a liquid fuel injection hole is provided at the trailing edge of the swirler.
【０００９】或いは、後縁に前記液体燃料流路と連通さ
れた液体燃料噴出孔を設けたスワラ翼と、翼表面に前記
気体燃料流路と連通された気体燃料噴出孔を設けたスワ
ラ翼を周方向に配置した構成としてもよい。Alternatively, a swirler blade having a liquid fuel jet hole communicating with the liquid fuel flow passage at a trailing edge and a swirler blade having a gas fuel jet hole communicating with the gas fuel flow passage on the blade surface are provided. It may be arranged in the circumferential direction.
【００１０】このように、液体燃料噴出孔を設けたスワ
ラ翼と、気体燃料噴出孔を設けたスワラ翼とを別に構成
し、これらのスワラ翼を周方向に、例えば交互に配置し
た構造にするとスワラ翼の構造が簡単になり製造が容易
になる。As described above, when the swirler blades having the liquid fuel jet holes and the swirler blades having the gas fuel jet holes are separately configured, and these swirler blades are arranged in the circumferential direction, for example, alternately. The structure of the swirler wing is simplified and manufacturing is facilitated.
【００１１】或いはまた、スワラを２段に構成し、上流
側のスワラの翼表面に気体燃料流路と連通された気体燃
料噴出孔を設け、下流側のスワラの後縁に前記液体燃料
流路と連通された液体燃料噴出孔を設けた構造にしても
よい。Alternatively, the swirler is configured in two stages, the gas fuel injection hole communicating with the gas fuel flow path is provided on the blade surface of the swirler on the upstream side, and the liquid fuel flow path is provided on the trailing edge of the swirler on the downstream side. The structure may be such that a liquid fuel injection hole communicating with the liquid fuel injection hole is provided.
【００１２】このように、スワラを２段にして、その２
段のスワラから気体燃料、液体燃料を噴出させると、そ
れぞれの段で多数の噴出孔から燃料を周方向に分散させ
て噴出させることができるので、均一な予混合気が得ら
れ易くなる。特に、この場合に、１段目、２段目のスワ
ラの旋回方向を互いに逆向きとすると液体燃料と気体燃
料及び燃料と空気の混合が促進され、低ＮＯX 化を達成
する上で好ましい。In this way, the swirler has two stages, and
When the gaseous fuel and the liquid fuel are ejected from the swirlers of the steps, the fuel can be ejected while being dispersed in the circumferential direction from a large number of ejection holes in each step, so that a uniform premixed gas can be easily obtained. In particular, in this case, the first stage, when the turning direction of the second-stage swirler is opposite to each other mixing of the liquid and gaseous fuels and the fuel and air is promoted, preferably in achieving low NO X reduction.
【００１３】以上説明した本発明のデュアル燃料ノズル
のいずれかを中心又はその円周上に配置し、そのデュア
ル燃料ノズルの１つの先端に気体燃料又は液体燃料によ
る保炎用パイロットを形成するように構成したガスター
ビン用燃焼器とすると、低ＮＯX 化されたガスタービン
用燃焼器が提供される。Any one of the above-described dual fuel nozzles of the present invention is arranged at the center or on the circumference of the dual fuel nozzle, and a flame holding pilot by gas fuel or liquid fuel is formed at one tip of the dual fuel nozzle. When configured gas turbine combustor, low NO X reduction gas turbine combustor is provided.
【００１４】[0014]
【発明の実施の形態】以下、本発明によるデュアル燃料
ノズルを図示した実施の形態に基づいて具体的に説明す
る。なお、以下の実施形態において、図５、図６に示し
た従来の構造と同じ部分には同じ符号を付して、それら
についての重複する説明は省略する。BEST MODE FOR CARRYING OUT THE INVENTION A dual fuel nozzle according to the present invention will be specifically described below based on the illustrated embodiment. In the following embodiments, the same parts as those of the conventional structure shown in FIGS. 5 and 6 are designated by the same reference numerals, and the duplicated description thereof will be omitted.
【００１５】（第１実施形態）まず、図１に示した第１
実施形態によるデュアル燃料ノズルについて説明する。
図１において、１４はスワラで、ガスタービン用燃焼器
におけるメインノズルとしてのデュアル燃料ノズルにお
ける円筒状予混合ノズル１１内に設置されている。スワ
ラ１４の翼表面（背側、腹側、又はその両側）には、小
孔１５が設けられ、この小孔１５は、スワラ１４内に形
成された気体燃料流路部１６によって気体燃料供給通路
８と連通され、気体燃料を噴出する気体燃料噴出孔を形
成している。また、スワラ１４の後縁には、スリット状
の液体燃料噴出孔１７が形成され、その液体燃料噴出孔
１７はスワラ１４内に設けられた液体燃料流路部１８に
よって液体燃料供給路７と連通されている。(First Embodiment) First, the first embodiment shown in FIG.
The dual fuel nozzle according to the embodiment will be described.
In FIG. 1, 14 is a swirler and is installed in the cylindrical premixing nozzle 11 in the dual fuel nozzle as the main nozzle in the combustor for gas turbines. A small hole 15 is provided on the wing surface of the swirler 14 (dorsal side, abdominal side, or both sides thereof), and the small hole 15 is provided by a gas fuel flow passage portion 16 formed in the swirler 14 to supply a gas fuel supply passage. And a gas fuel injection hole for ejecting a gas fuel is formed. In addition, a slit-shaped liquid fuel ejection hole 17 is formed at the rear edge of the swirler 14, and the liquid fuel ejection hole 17 communicates with the liquid fuel supply passage 7 by a liquid fuel flow passage portion 18 provided in the swirler 14. Has been done.
【００１６】図１に示したデュアル燃料ノズルは以上の
構成を有しており、スワラの翼表面に設けた小孔１５が
形成する気体燃料噴出孔から噴出される気体燃料と、ス
ワラ１４の後縁に設けた液体燃料噴出孔１７から噴出さ
れる液体燃料とが、スワラ１４によって旋回されつつ流
れる空気流と良く混合され、均一な予混合気を形成する
ことができる。The dual fuel nozzle shown in FIG. 1 has the above-mentioned configuration, and the gas fuel ejected from the gas fuel ejection hole formed by the small hole 15 provided on the blade surface of the swirler and the rear of the swirler 14. The liquid fuel ejected from the liquid fuel ejecting hole 17 provided at the edge is well mixed with the airflow flowing while being swirled by the swirler 14, and a uniform premixed gas can be formed.
【００１７】（第２実施形態）次に、図２に示した第２
実施形態によるデュアル燃料ノズルについて説明する。
図２において、２４は円筒状予混合ノズル１１内に配設
されたスワラで、このスワラ２４は、翼表面に気体燃料
噴出用の小孔１５を設けたスワラ翼２５と、後縁に液体
燃料噴出孔１７を設けたスワラ翼２６の２種類のスワラ
翼２５，２６を円周方向に交互に同数配置して構成され
ている。スワラ翼２５の小孔１５は気体燃料流路８に連
通され、液体燃料噴出孔１７は液体燃料流路７と連通さ
れている。(Second Embodiment) Next, the second embodiment shown in FIG.
The dual fuel nozzle according to the embodiment will be described.
In FIG. 2, reference numeral 24 denotes a swirler disposed in the cylindrical premixing nozzle 11. The swirler 24 includes a swirler blade 25 having a small hole 15 for jetting a gaseous fuel on the blade surface and a liquid fuel at the trailing edge. Two types of swirler blades 25 and 26 of the swirler blade 26 provided with the ejection holes 17 are alternately arranged in the circumferential direction. The small hole 15 of the swirler blade 25 communicates with the gas fuel flow passage 8, and the liquid fuel ejection hole 17 communicates with the liquid fuel flow passage 7.
【００１８】なお、以上の説明では、気体燃料噴出孔と
なる小孔１５を設けたスワラ翼２５と液体燃料噴出孔１
７を設けたスワラ翼２６を交互に同数配置した場合につ
いて説明したが、スワラ翼２５と２６の数はそれぞれ任
意に選定してよいし、その配列態様も上記したものに限
らない。この第２実施形態のものでは、気体燃料噴出孔
となる小孔１５をもつスワラ翼２５と液体燃料噴出孔１
７をもつスワラ翼２６を別々のものとして構成し、各ス
ワラ翼における燃料流路の加工を容易にしている。In the above description, the swirler blade 25 provided with the small holes 15 serving as the gas fuel ejection holes and the liquid fuel ejection hole 1 are provided.
Although the case where the same number of the swirler blades 26 provided with 7 are arranged alternately has been described, the number of the swirler blades 25 and 26 may be arbitrarily selected, and the arrangement mode thereof is not limited to the above. In the second embodiment, the swirler blade 25 having the small holes 15 serving as the gas fuel ejection holes and the liquid fuel ejection hole 1 are provided.
The swirler blades 26 having the number 7 are configured as separate ones to facilitate the processing of the fuel flow path in each swirler blade.
【００１９】（第３実施形態）次に、図３に示した本発
明の第３実施形態によるデュアル燃料ノズルについて説
明する。図３において、２５は、第２実施形態によるデ
ュアル燃料ノズルで用いたと同様に気体燃料噴出用の小
孔１５を設けたスワラ翼で、この位置でのスワラ翼は全
周に亘ってこの構造のものを採用している。このスワラ
翼２５の小孔１５は気体燃料流路８と連通されていて気
体燃料噴出孔として働く。(Third Embodiment) Next, a dual fuel nozzle according to a third embodiment of the present invention shown in FIG. 3 will be described. In FIG. 3, reference numeral 25 denotes a swirler blade provided with a small hole 15 for injecting gaseous fuel, similar to that used in the dual fuel nozzle according to the second embodiment, and the swirler blade at this position has this structure over the entire circumference. The thing is adopted. The small hole 15 of the swirler blade 25 communicates with the gas fuel flow path 8 and functions as a gas fuel ejection hole.
【００２０】このスワラ翼２５からなるスワラが配設さ
れた位置の後流には第２実施形態で用いたスワラ翼２６
と同様に後縁に液体燃料噴出孔１７を形成したスワラ翼
２６が全周に亘って設けられており、それらの液体燃料
噴出孔１７は液体燃料流路７と連通されている。本実施
形態におけるスワラ翼２５と２６は共に空気が同じ方向
に旋回されるように構成されている。The swirler blade 26 used in the second embodiment is provided downstream of the position where the swirler composed of the swirler blade 25 is disposed.
Similarly, a swirler blade 26 having a liquid fuel ejection hole 17 formed at the trailing edge is provided over the entire circumference, and these liquid fuel ejection holes 17 are communicated with the liquid fuel flow path 7. The swirler blades 25 and 26 in this embodiment are both configured so that the air is swirled in the same direction.
【００２１】この第３実施形態によるデュアル燃料ノズ
ルによると、気体燃料と液体燃料は、それぞれ、円筒状
予混合ノズル１１内で空気流内に全周に亘って噴出され
るので、空気流との混合が良く、均一な予混合気が得ら
れる。According to the dual fuel nozzle according to the third embodiment, since the gaseous fuel and the liquid fuel are respectively jetted into the air flow in the cylindrical premixing nozzle 11 over the entire circumference, the gas fuel and the liquid fuel are separated from the air flow. Good mixing and uniform premixed air can be obtained.
【００２２】（第４実施形態）前記した第３実施形態に
よるデュアル燃料ノズルでは、気体燃料を噴出するスワ
ラ翼２５と、液体燃料を噴出するスワラ翼２６が同じ方
向に空気流を旋回させる構成となっているが、この第４
実施形態は、スワラ翼２５とスワラ翼２６の旋回方向が
互いに逆向きにして構成されている。このように、気体
燃料を噴出するスワラ翼２５と液体燃料を噴出するスワ
ラ翼２６の旋回方向を互いに逆向きとすることによって
気体燃料、液体燃料及び空気との混合が更に促進され、
より均一な予混合気が得られる。(Fourth Embodiment) In the dual fuel nozzle according to the third embodiment, the swirler blade 25 for ejecting the gaseous fuel and the swirler blade 26 for ejecting the liquid fuel swirl the air flow in the same direction. This is the fourth
In the embodiment, the swirler blade 25 and the swirler blade 26 are configured so that the turning directions thereof are opposite to each other. As described above, the swirler blades 25 ejecting the gas fuel and the swirler blades ejecting the liquid fuel are made to rotate in opposite directions to each other, whereby the mixing with the gas fuel, the liquid fuel and the air is further promoted.
A more uniform premixed gas can be obtained.
【００２３】（第５実施形態）この実施形態は、前記し
た第１実施形態〜第４実施形態のデュアル燃料ノズルを
用いてガスタービン用燃焼器を構成したものである。図
４において、２７はメイン燃料ノズルとしてのデュアル
燃料ノズルで、このノズルは前記した第１実施形態〜第
４実施形態によるデュアル燃料ノズルのいづれかを採用
し円周方向に８個配設する。２８はパイロット燃料ノズ
ルであり、このノズル２８も、前記した第１実施形態〜
第４実施形態によるデュアル燃料ノズルのいづれかであ
ってよい。(Fifth Embodiment) In this embodiment, a combustor for a gas turbine is constructed by using the dual fuel nozzles of the first to fourth embodiments described above. In FIG. 4, 27 is a dual fuel nozzle as a main fuel nozzle, and this nozzle adopts any one of the dual fuel nozzles according to the first to fourth embodiments, and eight nozzles are arranged in the circumferential direction. 28 is a pilot fuel nozzle, and this nozzle 28 is also the first embodiment described above.
It may be either of the dual fuel nozzles according to the fourth embodiment.
【００２４】そして、その中の１本の燃料ノズルを図
（ｂ）のようにスワラ翼２９から気体燃料または液体燃
料を噴出させ、棒状体６の先端に気体燃料または液体燃
料による保炎用パイロット３０を構成する。このように
構成したガスタービン用燃焼器は、燃料と空気の混合が
均一で、ＮＯ X 発生が少ない。Then, one of the fuel nozzles is shown in FIG.
As shown in (b), the swirler vanes 29 are used to burn gas fuel or liquid fuel.
Gas is ejected, and the tip end of the rod-shaped body 6 is gas fuel or liquid fuel.
The flame holding pilot 30 is constructed. in this way
The combustor for the gas turbine that was constructed has a mixture of fuel and air.
Uniform and NO XOccurrence is low.
【００２５】以上、本発明を第１実施形態〜第５実施形
態に基づいて説明したが、本発明がこれらの実施形態に
何ら限定されないことはいうまでもなく、本出願の特許
請求の範囲に記載された本発明の範囲内で種々の変更、
変形を加えてよい。例えば、実施形態に示された気体噴
出孔の数はもとより、その形を種々変えてよく、例え
ば、燃料噴出孔の形は小孔の外、スリット、焼結金属の
多孔を用いるもの或いはこれらの組み合わせなど種々選
択可能である。Although the present invention has been described based on the first to fifth embodiments, it goes without saying that the present invention is not limited to these embodiments, and it is within the scope of the claims of the present application. Various modifications within the scope of the described invention,
Modifications may be added. For example, not only the number of gas ejection holes shown in the embodiment but also the shape thereof may be variously changed. For example, the shape of the fuel ejection hole may be a shape other than a small hole, a slit, a porous sintered metal, or the like. Various combinations and the like can be selected.
【００２６】[0026]
【発明の効果】以上説明したように、本発明は、液体燃
料流路と気体燃料流路とを有する燃料供給管を空気流の
流路に沿って配置し、前記空気流に旋回を与える複数枚
のスワラを前記燃料供給管のまわりに配設してなるデュ
アル燃料ノズルにおいて、前記スワラに前記気体燃料流
路及び液体燃料流路と連通された燃料噴出孔を設けたデ
ュアル燃料ノズルを提供する。As described above, according to the present invention, a plurality of fuel supply pipes having a liquid fuel flow path and a gas fuel flow path are arranged along an air flow path to swirl the air flow. A dual fuel nozzle having a plurality of swirlers arranged around the fuel supply pipe, wherein the swirler is provided with a fuel injection hole communicating with the gaseous fuel flow path and the liquid fuel flow path. .
【００２７】本発明によるデュアル燃料ノズルでは、燃
料供給管のまわりに配置されたスワラに燃料噴出孔を設
け、そこから液体燃料と気体燃料とを空気流中に噴出さ
せるので、噴出された燃料は、スワラで旋回を与えられ
る空気と良く混合され、均一な混合気を形成することが
でき、低ＮＯX 化が達成される。In the dual fuel nozzle according to the present invention, the swirler disposed around the fuel supply pipe is provided with the fuel ejection holes from which the liquid fuel and the gaseous fuel are ejected into the air flow, so that the ejected fuel is , Which is well mixed with the air swirled by the swirler to form a uniform air-fuel mixture, and achieves low NO x .
【００２８】本発明のデュアル燃料ノズルにおいて、ス
ワラの後縁（トレーリングエッジ）に前記液体燃料流路
と連通された液体燃料噴出孔を設けたスワラ翼と、翼表
面に前記気体燃料流路と連通された気体燃料噴出孔を設
けたスワラ翼を周方向に配置した構成としたものでは、
スワラ翼の構造が簡単になり製造が容易になる。In the dual fuel nozzle of the present invention, a swirler blade having a liquid fuel injection hole communicating with the liquid fuel flow passage at the trailing edge of the swirler, and the gas fuel flow passage on the blade surface are provided. In the configuration in which the swirler blades provided with the communicating gas fuel ejection holes are arranged in the circumferential direction,
The structure of the swirler wing is simplified and manufacturing is facilitated.
【００２９】また、本発明のデュアル燃料ノズルにおい
て、スワラを２段に構成し、上流側のスワラの翼表面に
気体燃料流路と連通された気体燃料噴出孔を設け、下流
側のスワラの後縁に前記液体燃料流路と連通された液体
燃料噴出孔を設けた構造にしたものでは、それぞれの段
で多数の噴出孔から燃料を周方向に分散させて噴出させ
ることができるので、均一な予混合気が得られ易くな
る。In addition, in the dual fuel nozzle of the present invention, the swirler is configured in two stages, the gas fuel injection hole communicating with the gas fuel flow path is provided on the blade surface of the upstream swirler, and the swirler after the downstream swirler is provided. In the structure in which the liquid fuel ejection holes communicating with the liquid fuel flow path are provided at the edge, the fuel can be dispersed and ejected in the circumferential direction from a large number of ejection holes at each stage, so that it is uniform. A premixed gas can be easily obtained.
【００３０】特に、この場合に、１段目、２段目のスワ
ラの旋回方向を互いに逆向きとしたものでは、液体燃料
と気体燃料及び燃料と空気の混合が促進され、低ＮＯX
化を達成することができる。Particularly, in this case, when the swirling directions of the first and second swirlers are opposite to each other, mixing of liquid fuel and gas fuel and fuel and air is promoted, and low NO X
Can be achieved.
【００３１】以上説明した本発明のデュアル燃料ノズル
のいずれかを中心又はその円周上に配置し、そのデュア
ル燃料ノズルの１つの先端に気体燃料又は液体燃料によ
る保炎用パイロットを形成するように構成して、低ＮＯ
X 化されたガスタービン用燃焼器を提供することができ
る。Any one of the dual fuel nozzles of the present invention described above is arranged at the center or on the circumference of the dual fuel nozzle, and a flame holding pilot by gas fuel or liquid fuel is formed at one tip of the dual fuel nozzle. Configure and low NO
It is possible to provide a combustor for a gas turbine that has been converted to X.
【図１】本発明の第１実施形態によるデュアル燃料ノズ
ルを示す図面で、（ａ）は縦断面図、（ｂ）は（ａ）図
のＢ−Ｂ線に沿う断面図。1A and 1B are views showing a dual fuel nozzle according to a first embodiment of the present invention, in which FIG. 1A is a vertical sectional view and FIG. 1B is a sectional view taken along line BB in FIG.
【図２】本発明の第２実施形態によるデュアル燃料ノズ
ルを示す縦断面図。FIG. 2 is a vertical sectional view showing a dual fuel nozzle according to a second embodiment of the present invention.
【図３】本発明の第３実施形態によるデュアル燃料ノズ
ルを示す縦断面図。FIG. 3 is a vertical sectional view showing a dual fuel nozzle according to a third embodiment of the present invention.
【図４】本発明の実施形態によるガスタービン用燃焼器
を示す図面で、（ａ）はその燃料ノズルの配置、説明
図、（ｂ）はその１つのデュアル燃料ノズルの構造を示
す縦断面図。FIG. 4 is a view showing a combustor for a gas turbine according to an embodiment of the present invention, in which (a) is an arrangement and an explanatory view of its fuel nozzle, and (b) is a longitudinal sectional view showing the structure of one of the dual fuel nozzles. .
【図５】ガスタービン用燃焼器の構造を示す縦断面図。FIG. 5 is a vertical cross-sectional view showing the structure of a gas turbine combustor.
【図６】図５のガスタービン用燃焼器におけるデュアル
燃料ノズルを示す縦断面図。FIG. 6 is a vertical cross-sectional view showing a dual fuel nozzle in the gas turbine combustor of FIG.
１ 燃焼器 ２ パイロットノズル ３ 予混合ノズル ４ スワラ（旋回羽根） ５ デュアル燃料ノズル ６ 棒状体 ７ 液体燃料流路 ８ 気体燃料流路 ９ 液体燃料噴出孔 １０ 気体燃料噴出孔 １１ 円筒状予混合ノズル １４ スワラ １５ 小孔（気体燃料噴出孔） １６ 気体燃料流路部 １７ 液体燃料噴出孔 １８ 液体燃料流路部 ２４ スワラ ２５ 小孔を設けたスワラ翼 ２６ 液体燃料噴出孔を設けたスワラ翼 ２７ デュアル燃料ノズル ２８ パイロット燃料ノズル ２９ スワラ翼 ３０ 保炎用パイロット 1 combustor 2 pilot nozzle 3 premixing nozzle 4 swirler (swirl blade) 5 dual fuel nozzle 6 Rods 7 Liquid fuel flow path 8 Gas fuel flow path 9 Liquid fuel injection holes 10 Gaseous fuel injection holes 11 Cylindrical premixing nozzle 14 Swallow 15 small holes (gaseous fuel injection holes) 16 Gas fuel flow path 17 Liquid fuel injection holes 18 Liquid fuel flow path 24 swirls Swirler wing with 25 small holes 26 Swirler blade with liquid fuel injection holes 27 dual fuel nozzle 28 Pilot fuel nozzle 29 Swala Wings 30 Flame holding pilot
フロントページの続き (72)発明者 稲田 満 兵庫県高砂市荒井町新浜２丁目１番１号 三菱重工業株式会社高砂研究所内 (72)発明者 萬代 重実 兵庫県高砂市荒井町新浜２丁目１番１号 三菱重工業株式会社高砂研究所内 (72)発明者 田中 克則 兵庫県高砂市荒井町新浜２丁目１番１号 三菱重工業株式会社高砂製作所内Continued front page (72) Inventor Mitsuru Inada 2-1-1 Niihama, Arai-cho, Takasago, Hyogo Prefecture Takasago Laboratory, Mitsubishi Heavy Industries, Ltd. (72) Inventor Shigemi Bandai 2-1-1 Niihama, Arai-cho, Takasago, Hyogo Prefecture Takasago Laboratory, Mitsubishi Heavy Industries, Ltd. (72) Inventor Katsunori Tanaka 2-1-1 Niihama, Arai-cho, Takasago, Hyogo Prefecture Takasago Works, Mitsubishi Heavy Industries, Ltd.
Claims (6)
燃料供給管を空気流の流路に沿って配置し、前記空気流
に旋回を与える複数枚のスワラを前記燃料供給管のまわ
りに配設してなるデュアル燃料ノズルにおいて、前記ス
ワラに前記気体燃料流路及び液体燃料流路と連通された
燃料噴出孔を設けたことを特徴とするデュアル燃料ノズ
ル。1. A fuel supply pipe having a liquid fuel flow path and a gas fuel flow path is arranged along an air flow path, and a plurality of swirlers that swirl the air flow are provided around the fuel supply tube. In the dual fuel nozzle, the swirler is provided with a fuel injection hole communicating with the gas fuel flow path and the liquid fuel flow path.
と連通された気体燃料噴出孔、後縁に前記液体燃料流路
と連通された液体燃料噴出孔を設けたことを特徴とする
請求項１に記載のデュアル燃料ノズル。2. The swirler blade surface is provided with a gas fuel ejection hole communicating with the gas fuel flow passage, and a trailing edge provided with a liquid fuel ejection hole communicating with the liquid fuel flow passage. Item 2. The dual fuel nozzle according to Item 1.
と連通された液体燃料噴出孔を設けたスワラと、翼表面
に前記気体燃料流路と連通された気体燃料噴出孔を設け
たスワラを周方向に配置して構成したことを特徴とする
請求項１に記載のデュアル燃料ノズル。3. The swirler is provided with a swirler having a liquid fuel ejection hole communicating with the liquid fuel flow passage at a trailing edge, and a gas fuel ejection hole communicating with the gas fuel flow passage on a blade surface. The dual fuel nozzle according to claim 1, wherein swirlers are arranged in the circumferential direction.
ワラの翼表面に気体燃料流路と連通された気体燃料噴出
孔を設け、下流側のスワラの後縁に前記液体燃料流路と
連通された液体燃料噴出孔を設けたことを特徴とする請
求項１に記載のデュアル燃料ノズル。4. The swirler is configured in two stages, a gas fuel injection hole communicating with the gas fuel flow passage is provided on a blade surface of the upstream swirler, and the liquid fuel flow passage is provided at a trailing edge of the downstream swirler. The dual fuel nozzle according to claim 1, further comprising a liquid fuel ejection hole that is in communication with the dual fuel nozzle.
を互いに逆向きとしたことを特徴とする請求項４に記載
のデュアル燃料ノズル。5. The dual fuel nozzle according to claim 4, wherein the swirling directions of the upstream and downstream swirlers are opposite to each other.
ノズルを中心又はその円周上に配置し、そのデュアル燃
料ノズルの１つの燃料供給管の先端に気体燃料又は液体
燃料による保炎用パイロットを形成したガスタービン用
燃焼器。6. The dual fuel nozzle according to claim 1, which is arranged at the center or on the circumference of the dual fuel nozzle, and at the tip of one fuel supply pipe of the dual fuel nozzle, for flame holding by gas fuel or liquid fuel. Combustor for gas turbines that formed a pilot.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001259744A JP2003074855A (en) | 2001-08-29 | 2001-08-29 | Dual combustion nozzle and combustion equipment for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001259744A JP2003074855A (en) | 2001-08-29 | 2001-08-29 | Dual combustion nozzle and combustion equipment for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2003074855A true JP2003074855A (en) | 2003-03-12 |
Family
ID=19087067
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2001259744A Pending JP2003074855A (en) | 2001-08-29 | 2001-08-29 | Dual combustion nozzle and combustion equipment for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2003074855A (en) |
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