JPH01267325A - Gas turbine combustor for low calorie gas - Google Patents
Gas turbine combustor for low calorie gasInfo
- Publication number
- JPH01267325A JPH01267325A JP9546288A JP9546288A JPH01267325A JP H01267325 A JPH01267325 A JP H01267325A JP 9546288 A JP9546288 A JP 9546288A JP 9546288 A JP9546288 A JP 9546288A JP H01267325 A JPH01267325 A JP H01267325A
- Authority
- JP
- Japan
- Prior art keywords
- combustion chamber
- gas
- combustion
- air
- auxiliary
- 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
- 238000002485 combustion reaction Methods 0.000 claims abstract description 123
- 239000000446 fuel Substances 0.000 claims abstract description 51
- 238000002347 injection Methods 0.000 claims abstract description 27
- 239000007924 injection Substances 0.000 claims abstract description 27
- 239000000919 ceramic Substances 0.000 claims abstract description 15
- 239000000203 mixture Substances 0.000 claims abstract description 11
- 238000004891 communication Methods 0.000 claims description 2
- 238000005507 spraying Methods 0.000 abstract 2
- 239000007921 spray Substances 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 71
- 239000003245 coal Substances 0.000 description 11
- 238000002309 gasification Methods 0.000 description 9
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 7
- 239000001301 oxygen Substances 0.000 description 7
- 229910052760 oxygen Inorganic materials 0.000 description 7
- 239000002737 fuel gas Substances 0.000 description 4
- 239000003921 oil Substances 0.000 description 4
- 235000019198 oils Nutrition 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 229910052581 Si3N4 Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 239000001294 propane Substances 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 235000015112 vegetable and seed oil Nutrition 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Abstract
Description
【発明の詳細な説明】
（産業上の利用分野）
本発明はガスタービン燃焼器に関する。更に詳述すると
、本発明は低カロリーガス例えば石炭ガス化ガス等を燃
料とする低カロリーガス用ガスタービン燃焼器に関する
。DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to gas turbine combustors. More specifically, the present invention relates to a gas turbine combustor for low-calorie gas that uses low-calorie gas, such as coal gasified gas, as fuel.
（従来の技術）
現在、石炭転換利用技術の開発として石炭のガス化ない
し液化技術の開発が提唱され、各国で推し進められてい
る。そして、この開発の一環として、石炭ガス化によっ
て生成されたガス（以下石炭ガス化ガス若しくは生成ガ
スと言う）、特に２ −０００ ｋｃａｌ／ Ｎｒｇ
３未満の低カロリーガスを燃料とする低カロリーガス
用ガスタービン燃焼器の開発が要求されている。(Conventional technology) Currently, the development of coal gasification or liquefaction technology has been proposed as a means of developing coal conversion and utilization technology, and is being promoted in various countries. As part of this development, gas produced by coal gasification (hereinafter referred to as coal gasification gas or produced gas), especially 2-000 kcal/Nrg
There is a need for the development of a gas turbine combustor for low-calorie gas that uses low-calorie gas as fuel.
即ち、従来のガスタービン燃焼器（コンパスタ−）は、
圧縮空気の気流中に燃料を噴射して連続的に燃焼させる
装置で、■燃焼室内の圧力が高い、■燃焼室内の空気流
速が速い、■燃焼負荷率が高い等の特徴を有するもので
あり、天然ガス（ＬＮＧ）やプロパンガス（ＬＰＧ）
、油等の高カロリー燃料の使用を前提としている。In other words, the conventional gas turbine combustor (compaster) is
It is a device that injects fuel into a stream of compressed air and burns it continuously, and has the following characteristics: ■ High pressure in the combustion chamber, ■ High air velocity in the combustion chamber, and ■ High combustion load rate. , natural gas (LNG) and propane gas (LPG)
, assumes the use of high-calorie fuel such as oil.
一方、石炭ガス化ガス特に大型発電に適している空気吹
きの噴流床石炭ガス化炉から供給される石炭ガス化ガス
はＣ０１Ｈ２、Ｎ２ 、Ｃ’０２ 、Ｎ２０等を成分と
する約１０００ ｋｃａｌ／ Ｎ ｍ３の低カロリーガ
スであり、しかもその主成分のｃｏ、Ｎ２のうちの大半
が燃え難いＣＯガスである。このなめ、着火し難く火炎
安定性に欠ける問題があり、ガスタービン用燃料として
は好ましくない。On the other hand, coal gasification gas supplied from an air-blown entrained bed coal gasification furnace, which is especially suitable for large-scale power generation, has a content of approximately 1000 kcal/N containing components such as CO1H2, N2, C'02, and N20. It is a low calorie gas of m3, and most of its main components, co and N2, are hard to burn CO gas. This slickness makes it difficult to ignite and lacks flame stability, making it undesirable as a fuel for gas turbines.
しかも１０００〜２０００ ｐＨｌのＮＨ９が不純物と
して含まれており、これが燃焼過程でＮＯｘを発生させ
ることとなる。ましてや高負荷燃焼にすると火炎伝播速
度を上回る速度で燃料ガスが流れるなめ益々火がつき難
い状態となる。加えて、低カロリーガスを使用する場合
、従来に比べて燃料の量が飛躍的に増大するため、燃焼
量を変化させるということ、即ち燃料供給量を変えると
いうことは燃焼ガスの流れ（フローパターン）自体を変
えることとなり、火炎の安定性を大きく左右してしまい
、高カロリーガスを使用するなめに燃焼用空気によって
流れが決定される従来のガスタービンとは本質的に燃料
の燃焼性に対する影響に違いがある。Moreover, it contains 1000 to 2000 pHl of NH9 as an impurity, which generates NOx during the combustion process. Furthermore, when high-load combustion is performed, the fuel gas flows at a speed higher than the flame propagation speed, making it increasingly difficult to ignite. In addition, when using low-calorie gas, the amount of fuel increases dramatically compared to conventional gases, so changing the amount of combustion, or in other words, changing the amount of fuel supplied, changes the flow pattern of the combustion gas. ) itself, which greatly affects the stability of the flame, and which is different from conventional gas turbines in which the flow is determined by the combustion air even though high-calorie gas is used.This essentially affects the combustibility of the fuel. There is a difference.
このため、従来の一般的なタービン燃焼器に、石炭ガス
化ガスのような低カロリーガスを燃料として使用する場
合、着火不良、失火、燃焼の不安定化を招いてしまう。For this reason, when low-calorie gas such as coal gasified gas is used as fuel in a conventional general turbine combustor, ignition failure, misfire, and combustion instability may occur.
そこで、この低カロリーガスを燃料として使用する場合
、燃焼の不安定を解消するなめ、点火用に限定して油や
ＬＮＧ等の補助燃料を使用して種用油の供給管と酸素供
給管との２１１管とから成り。Therefore, when using this low-calorie gas as a fuel, in order to eliminate combustion instability, an auxiliary fuel such as oil or LNG is used only for ignition to connect the seed oil supply pipe and oxygen supply pipe. It consists of 211 tubes.
内側から油、外側から酸素が夫々ガスタービン燃焼器の
燃焼室内に供給される。このパイロットバーナから噴出
される燃料及び酸素は、イグナイターによって着火され
、低カロリーガスの着火用種火として利用される。そし
て、着火後は油の供給は停止され、燃焼不安定に陥った
ときにのみ適量の酸素のみがパイロットバーナから補給
され安定燃焼の維持が図られている。Oil is supplied from the inside and oxygen is supplied from the outside into the combustion chamber of the gas turbine combustor. The fuel and oxygen ejected from the pilot burner are ignited by an igniter and used as a pilot flame for igniting low-calorie gas. After ignition, the supply of oil is stopped, and only when combustion becomes unstable, only an appropriate amount of oxygen is supplied from the pilot burner to maintain stable combustion.
（発明が解決しようとする課題）
しかしながら、この従来のタービン燃焼器のパイロット
バーナは、燃料と酸素の混合速度が遅い上に燃焼室内に
大量でかつ流速の速い低カロリーガスと一緒に噴射され
るなめ、相当量の高カロリーガスを燃焼させなければ定
格燃焼時に種火として残すことは困難である。また、こ
の欠点を解消するため、補助燃料を遮断する定格燃焼時
に燃焼状態が不安定になった場合、燃焼室内に直接酸素
を供給することによって燃焼状態の安定を図ろうとして
いるが、燃焼室の上流側即ち燃料噴射ノズル付において
ツユエルリッチ燃焼を実現することができず、Ｎ Ｏｘ
の発生を低減することができないし、むしろ酸素の供給
によりＮＯｘの発生が増大することとなる。また、燃料
供給系に水やその他の異物が混入する等の事故によって
起る失火に対して効果的でない、特に、高圧高温の複合
発電用セラミックタービンを使用する場合、失火によっ
て冷たい燃焼用空気がタービン側に流れ込むと、セラミ
ック静翼に熱応力による破壊が生じる虞があることから
、失火を確実に回避することが不可欠となり、無視でき
ない重要な問題となる。(Problems to be Solved by the Invention) However, in the pilot burner of this conventional turbine combustor, the mixing speed of fuel and oxygen is slow, and a large amount of low-calorie gas is injected into the combustion chamber together with a high flow rate. Unless a considerable amount of high-calorie gas is burned, it is difficult to leave it as a pilot flame during rated combustion. In addition, to overcome this drawback, if the combustion condition becomes unstable during rated combustion by cutting off the auxiliary fuel, attempts are made to stabilize the combustion condition by directly supplying oxygen into the combustion chamber. It is not possible to achieve fuel-rich combustion on the upstream side of the fuel injection nozzle, which means that NOx
It is not possible to reduce the generation of NOx, and on the contrary, the supply of oxygen increases the generation of NOx. In addition, it is not effective against misfires caused by accidents such as water or other foreign matter getting into the fuel supply system, especially when using ceramic turbines for high-pressure, high-temperature combined cycle power generation. If it flows into the turbine side, there is a risk that the ceramic stator blades will be destroyed by thermal stress, so it is essential to reliably avoid misfires, which is an important problem that cannot be ignored.
そこで本発明は、ＮＯｘを発生させずにしかも燃え難い
低カロリーガスを燃焼させるガスタービン燃焼器の提供
にある。SUMMARY OF THE INVENTION Therefore, the present invention provides a gas turbine combustor that burns a low-calorie gas that is difficult to burn without generating NOx.
（課題を解決するための手段）
かかる目的を達成するため、本発明の低カロリーガス用
ガスタービン燃焼器は、主燃焼室の入口側に補助バーナ
を装備するセラミックス製副燃焼室を設けると共に該副
燃焼室の出口周囲に主燃料噴射ノズルと一次燃焼用空気
噴射ノズルを配置する一方、前記補助バーナの燃料流路
と一次燃焼用空気の流路とを部分的に連通させてこの連
通部近傍において燃料流路を絞りエゼクタ作用によって
燃料流量に対応する量の燃焼用空気を吸引して−定の空
気比の混合気として前記副燃焼室内に噴射させるように
している。(Means for Solving the Problems) In order to achieve the above object, the gas turbine combustor for low-calorie gas of the present invention is provided with a ceramic sub-combustion chamber equipped with an auxiliary burner on the inlet side of the main combustion chamber, and a ceramic sub-combustion chamber equipped with an auxiliary burner. A main fuel injection nozzle and a primary combustion air injection nozzle are arranged around the outlet of the auxiliary combustion chamber, while the fuel flow path of the auxiliary burner and the primary combustion air flow path are partially communicated with each other in the vicinity of this communication portion. The fuel flow path is throttled and an amount of combustion air corresponding to the fuel flow rate is sucked in by the ejector action and injected into the sub-combustion chamber as a mixture having a constant air ratio.
また、本発明は、副燃焼室では主燃焼室内において燃焼
させる低カロリーガスより高カロリーのガスを燃焼させ
ることを特徴としている。Further, the present invention is characterized in that the sub-combustion chamber combusts a gas having a higher calorie than the low-calorie gas combusted in the main combustion chamber.
また、本発明は、主燃焼室で総発生熱量の９０％以上の
低カロリーガスを燃焼させると共に副燃焼室で総発生熱
量の１０％未満の高カロリーガスを燃焼させることを特
徴としている。Furthermore, the present invention is characterized in that the main combustion chamber burns low-calorie gas that accounts for 90% or more of the total generated heat, and the sub-combustion chamber burns high-calorie gas that accounts for less than 10% of the total generated heat.
（作用）
したがって、燃料即ち高カロリーガスの速度エネルギー
によって燃焼用空気が補助バーナ内に吸引され、燃料の
量即ち燃焼量に関係なく一定の空気比の混合気を得る。(Operation) Therefore, the combustion air is drawn into the auxiliary burner by the velocity energy of the fuel, that is, the high-calorie gas, and a mixture with a constant air ratio is obtained regardless of the amount of fuel, that is, the amount of combustion.
しかも、副燃焼室はセラミックス製であるため、冷却用
の燃焼用空気を必要とせず、上記混合気の空気比λは０
．８〜１．０に設定できる。そして、混合気は高温の火
炎となって副燃焼室内を旋回しながら主燃焼室内へ噴出
し、主燃焼室内の主燃焼域の再循環流（ｒｊＡ炎ａｍ：
の外側に広がる。Moreover, since the auxiliary combustion chamber is made of ceramics, it does not require combustion air for cooling, and the air ratio λ of the mixture is 0.
．． It can be set between 8 and 1.0. Then, the air-fuel mixture turns into a high-temperature flame and blows out into the main combustion chamber while swirling in the sub-combustion chamber, creating a recirculation flow (rjA flame am:
spread outside.
（実施例）
以下、本発明の構成を図面に示す実施例に基づいて詳細
に説明する。(Example) Hereinafter, the configuration of the present invention will be described in detail based on an example shown in the drawings.
第１図に本発明の一実施例を中央ｌｆＩ断面図で示す、
このガスタービン燃焼器は、主燃焼室１の入口側にセラ
ミックス製副燃焼室２を設け、該副燃焼室２の出口周囲
に主燃料噴射ノズル３と一次燃焼用空気噴射ノズル４と
を配置して主燃料なる低カロリーガスの低カロリーガス
ヘッダを構成すると共に前記副燃焼室２内に補助燃料た
る高カロリーガスと燃焼用空気との混合気を噴射する補
助バーナノズル５を設け、副燃焼室２内に形成された高
温火炎を旋回させて主燃焼室１１１１１へ噴射させるよ
うにして成る。FIG. 1 shows an embodiment of the present invention in a central lfI cross-sectional view.
This gas turbine combustor is provided with a ceramic sub-combustion chamber 2 on the inlet side of a main combustion chamber 1, and a main fuel injection nozzle 3 and a primary combustion air injection nozzle 4 arranged around the outlet of the sub-combustion chamber 2. An auxiliary burner nozzle 5 is provided, which constitutes a low-calorie gas header for low-calorie gas as the main fuel, and injects a mixture of high-calorie gas as auxiliary fuel and combustion air into the auxiliary combustion chamber 2. The high temperature flame formed inside is swirled and injected into the main combustion chamber 11111.
燃焼器は、通常、ケーシング６とライナー７との二重筒
構造が採られ、ライナー７とゲージング６との間に燃焼
用空気の流路８が形成されライナー７の内側が主燃焼室
１とされている。ライナー７の前半部には二次空気孔９
及び必要あれば三次空気孔１０が円周方向に多数段けら
れ、ケーシング６とライナー７の間の流路８に供給され
る燃焼用空気を二次空気及び必要によっては三次空気と
して燃焼室ｌ内に噴出させ、二次燃焼及び必要あれば燃
焼ガスの冷却が為される。また、ケーシング６には二次
空気供給用ダクト１１が接続され、燃焼用圧縮空気供給
源に接続される供給口１２を経て燃焼用空気を流路８に
導入するように設けられている。また□、ライナー７に
は低カロリーガスヘッダの一次燃焼用空気噴射ノズル４
を囲繞する一次空気供給ダクト１３が二次空気供給ダク
ト１１内を貫通するようにして接続され、燃焼用圧縮空
気供給源に接続される供給口１４を経て一次空気を主燃
料噴射ノズル３の周りの一次燃焼用空気噴射ノズル４か
ら噴射させるように設けられている。尚、−次燃焼用空
気噴射ノズル４には、必要に応じてスワラ−が装備され
、噴射空気に旋回をかけることがある。The combustor usually has a double-tube structure consisting of a casing 6 and a liner 7, with a combustion air passage 8 formed between the liner 7 and gauging 6, and the inside of the liner 7 forming the main combustion chamber 1. has been done. There are secondary air holes 9 in the front half of the liner 7.
If necessary, a large number of tertiary air holes 10 are arranged in the circumferential direction, and the combustion air supplied to the flow path 8 between the casing 6 and the liner 7 is used as secondary air and, if necessary, tertiary air, to the combustion chamber l. Secondary combustion and cooling of the combustion gas is performed if necessary. Further, a secondary air supply duct 11 is connected to the casing 6 and is provided so as to introduce combustion air into the flow path 8 through a supply port 12 connected to a combustion compressed air supply source. In addition, the liner 7 is equipped with an air injection nozzle 4 for primary combustion of the low calorie gas header.
A primary air supply duct 13 surrounding the main fuel injection nozzle 3 is connected so as to pass through the secondary air supply duct 11, and supplies the primary air around the main fuel injection nozzle 3 through a supply port 14 connected to a compressed air supply source for combustion. The air is injected from the primary combustion air injection nozzle 4. Note that the secondary combustion air injection nozzle 4 may be equipped with a swirler, if necessary, to swirl the injection air.
前記副燃焼室２は、主燃焼室工の入日側に設けられてお
り、主燃料噴射ノズル３の内側の中央に設置されている
。この副燃焼室２は全体がセラミックスの、あるいはセ
ラミックスの内張によって被覆された筒状容器、通常円
筒によって構成されているものである。セラミックスと
しては、例えば炭化ケイ素系セラミックス、窒化ケイ素
系セラミックス、サイアロン等の使用が好ましい、尚、
この副燃焼室２は例えば押え金具２４によって一次空気
供給用ダクト１３に取付けられている支持板２５に固定
されている。この支持板２５は燃焼用空気を低カロリー
ガスヘッダの一次燃焼用空気噴射ノズル４側に流通させ
るための貫通孔２６が設けられている。また、この副燃
焼室２には補助バーナ５が設けられ、主燃焼室１に供給
される燃料ガスに比べて高カロリーなガス例えばＬＮＧ
やＬＰＧ等を燃料として燃焼させるように設けられてい
る。高カロリーガスはあらがしめ燃焼用空気と一定の空
気比で混合され、副燃焼室２内に旋回するように噴射さ
れるように設けられている。したがって、その燃焼ガス
は副燃焼室２内で旋回し主燃焼室１１１！Ｉへ急速に広
がるように噴出する６例えば本実施例の場合、燃料ガス
と燃焼用空気とをバーナ内で予め混合し、その混合気体
を旋回させて噴射する構造のバーナが採用されている。The auxiliary combustion chamber 2 is provided on the sun entry side of the main combustion chamber, and is installed at the center inside the main fuel injection nozzle 3. The auxiliary combustion chamber 2 is constituted by a cylindrical container, usually a cylinder, made entirely of ceramic or covered with a ceramic lining. As the ceramic, it is preferable to use, for example, silicon carbide ceramics, silicon nitride ceramics, sialon, etc.
This auxiliary combustion chamber 2 is fixed to a support plate 25 attached to the primary air supply duct 13 by, for example, a holding metal fitting 24. This support plate 25 is provided with a through hole 26 for circulating combustion air to the primary combustion air injection nozzle 4 side of the low calorie gas header. In addition, an auxiliary burner 5 is provided in the auxiliary combustion chamber 2, and a gas having a higher calorie than the fuel gas supplied to the main combustion chamber 1, such as LNG, is used.
It is installed to burn fuel such as LPG or LPG. The high-calorie gas is mixed with the combustion air at a constant air ratio and is injected into the sub-combustion chamber 2 in a swirling manner. Therefore, the combustion gas swirls within the sub-combustion chamber 2 and enters the main combustion chamber 111! For example, in the case of this embodiment, a burner is used in which fuel gas and combustion air are mixed in advance in the burner, and the mixed gas is swirled and injected.
具体的にはバーナチップの噴射軸が内側から外側に向け
て４５°程度振られたバーナチップが採用されている。Specifically, a burner chip is used in which the ejection axis of the burner chip is swung approximately 45 degrees from the inside to the outside.
また、この補助バーナ５は燃焼量の如何に拘らず高温火
炎を形成するため、燃料噴射量に応じて燃焼用空気量が
変化して一定の空気比を自動的に取り得る構造に設けら
れている１例えば本実施例の補助バーナ５の場合、燃料
噴射ノズル１５とその内部中央に設置しているイグナイ
ター（点火装置）１６との間に鼓状の絞り簡１７と仕切
板１８とから成るエゼクタを設ける一方、燃料噴射ノズ
ル１５に給気孔１９を穿孔すると共に該給気口Ｊ９の周
囲に一次空気供給用ダクト１３内を流れる燃焼用空気の
吸入を容易にするための導入管２３が設置され、補助燃
料ガスの速度エネルギーを利用したエゼクタ効果によっ
て燃焼用空気を吸引し一定の混合比を得るように設けら
れている。混合比λは、通常、最高火炎温度を得るため
０．８〜１．０に設定されている。尚、この副燃焼室２
の出口は円錐面状に広げられ、主燃焼室１内に火炎が噴
出する際に広がり易いように設けられている。In addition, since this auxiliary burner 5 forms a high-temperature flame regardless of the amount of combustion, it is provided with a structure that allows the amount of combustion air to change depending on the amount of fuel injection and automatically maintain a constant air ratio. For example, in the case of the auxiliary burner 5 of this embodiment, there is an ejector consisting of a drum-shaped diaphragm 17 and a partition plate 18 between the fuel injection nozzle 15 and the igniter 16 installed in the center of the interior thereof. At the same time, an air supply hole 19 is bored in the fuel injection nozzle 15, and an introduction pipe 23 is installed around the air supply port J9 to facilitate the intake of combustion air flowing through the primary air supply duct 13. The combustion air is sucked in by an ejector effect using the velocity energy of the auxiliary fuel gas to obtain a constant mixing ratio. The mixing ratio λ is usually set at 0.8 to 1.0 in order to obtain the maximum flame temperature. Furthermore, this auxiliary combustion chamber 2
The outlet of the main combustion chamber 1 is widened into a conical shape so that the flame can easily spread when ejected into the main combustion chamber 1.
また、この副燃焼室２の周囲には主燃料噴射ノズル３が
形成されている。この主燃料噴射ノズル３は本実施例の
場合、第・３図に示すように外側から内側に向けて傾斜
しかつ円周方向に傾いた噴射口を円周上に多数設け、副
燃焼室２から噴射される補助火炎と衝突するように設け
られている。主燃料噴射ノズル３には環状のヘッダ２０
が接続され、低カロリーガス供給源例えば石炭ガス化炉
から供給される低カロリーガスを全周から均等に噴射さ
せるように設けられている。ヘッダ２０は連結管２１を
介して一次空気供給ダクト１１内の環状ヘッダ２２と接
続され、ガス化炉等に接続されている。Further, a main fuel injection nozzle 3 is formed around this sub-combustion chamber 2 . In the case of this embodiment, the main fuel injection nozzle 3 is provided with a large number of injection ports on the circumference, which are inclined from the outside to the inside, and which are inclined in the circumferential direction, as shown in FIG. It is provided so that it collides with the auxiliary flame injected from the flame. The main fuel injection nozzle 3 has an annular header 20
are connected so that low-calorie gas supplied from a low-calorie gas supply source, such as a coal gasification furnace, is evenly injected from the entire circumference. The header 20 is connected to an annular header 22 in the primary air supply duct 11 via a connecting pipe 21, and is connected to a gasification furnace or the like.
副燃焼室２に供給される高カロリーガスは、定格出力時
において総発生熱量の１０％未満、即ち低カロリーガス
を含めた燃料全体の燃料によって発生する総熱量に占め
る割合が１０％未満となる量に抑えることが好ましい。The high-calorie gas supplied to the sub-combustion chamber 2 accounts for less than 10% of the total heat generated at rated output, that is, the proportion of the total heat generated by the entire fuel including low-calorie gas is less than 10%. It is preferable to keep the amount to a minimum.
低カロリーガス供給系と高カロリーガス供給系とは別々
に制御されており、相互に独立した二系統の燃料系統を
有する。The low-calorie gas supply system and the high-calorie gas supply system are controlled separately, and have two mutually independent fuel systems.
以上のように構成したので、低カロリーガス例えば石炭
ガス化ガスを安定燃焼させ得る。まず、総発生熱量の１
０％未満の高カロリーガス例えばＬＰＧ若しくはＬＮＧ
を副燃焼室２に供給し、イグナイタ１６によって着火す
る０次いで、主燃焼室ｌ側に総発生熱量の９０％以上の
石炭ガス化ガスを供給し、高カロリーガスの高温火炎を
火種として低カロリーガスを着火・燃焼させる。燃焼用
空気は、低カロリーガスと高カロリーガスとが主燃焼室
の上流側においてツユエルリッチ燃焼となるような空気
比の量が供給口１４から供給される。With the above configuration, low calorie gas such as coal gasification gas can be stably combusted. First, 1 of the total amount of heat generated
Less than 0% high calorie gas such as LPG or LNG
is supplied to the auxiliary combustion chamber 2, and ignited by the igniter 16.Next, coal gasification gas containing 90% or more of the total generated heat is supplied to the main combustion chamber 1 side, and low-calorie gas is ignited using the high-temperature flame of the high-calorie gas as the ignition source. Ignites and burns gas. Combustion air is supplied from the supply port 14 at an air ratio such that low-calorie gas and high-calorie gas are subjected to fuel-rich combustion on the upstream side of the main combustion chamber.
しかし、補助バーナ５側に供給される燃焼用空気はエゼ
クタ効果によって吸入されるため、高カロリーガスは０
．８〜１．０の一定空気比であらかじめ混合されて副燃
焼室２内に旋回噴射される。したがって、副燃焼室から
噴射される火炎は高温の種火となって主燃焼室の入口側
に広がり噴出され、高温の燃焼帯域を形成する。よって
、元来燃え難い上にツユエルリッチ燃焼状態のためより
一層燃え難くなっている低カロリーガスでも容易に着火
し、安定的に燃焼する。However, since the combustion air supplied to the auxiliary burner 5 side is sucked in by the ejector effect, the high calorie gas is 0.
．． The mixture is mixed in advance at a constant air ratio of 8 to 1.0 and then swirl-injected into the sub-combustion chamber 2. Therefore, the flame injected from the sub-combustion chamber becomes a high-temperature pilot flame, spreads toward the entrance side of the main combustion chamber, and is ejected, forming a high-temperature combustion zone. Therefore, even low-calorie gas, which is inherently difficult to burn and even more difficult to burn due to its thuer-rich combustion state, is easily ignited and stably combusted.
（発明の効果）
以上の説明より明らかなように、本発明の低カロリーガ
ス用ガスタービン燃焼器は、燃料の速度エネルギーによ
って燃焼用空気を補助バーナ内に吸引して、燃料の量即
ち燃焼量に関係なく一定の空気比の混合気を得、かつ副
燃焼室をセラミックスで形成して冷却用の燃焼用空気を
省き混合気の空気比λを０，８〜１．０に設定すること
によって高温の火炎を形成する一方、この火炎を副燃焼
室内において旋回させて主燃焼室側へ噴出させ主燃焼室
内の主燃焼域の再循環流（保炎機構）の外側に広がるよ
うにしているので、少量のガスによって主燃焼域の保炎
機構を破壊せずに高温の種火を形成できる。特に高カロ
リーガスを使用する場合、少量のガスで安定した高温の
種火をつくることができる。(Effects of the Invention) As is clear from the above explanation, the gas turbine combustor for low-calorie gas of the present invention sucks combustion air into the auxiliary burner using the velocity energy of the fuel, thereby reducing the amount of fuel, that is, the amount of combustion. By obtaining a mixture with a constant air ratio regardless of the temperature, by forming the auxiliary combustion chamber with ceramics, omitting combustion air for cooling, and setting the air ratio λ of the mixture to 0.8 to 1.0. While a high-temperature flame is formed, this flame is swirled in the sub-combustion chamber, ejected toward the main combustion chamber, and spread outside of the recirculation flow (flame holding mechanism) in the main combustion area within the main combustion chamber. , a small amount of gas can form a high-temperature pilot flame without destroying the flame-holding mechanism in the main combustion zone. Especially when using high-calorie gas, a stable high-temperature pilot flame can be created with a small amount of gas.
したがって、低カロリーガスの着火性を良くすると共に
火炎安定性を向上させ、また安定な火種があるため主燃
焼域の燃焼用空気の供給を少なくしてツユエルリッチ燃
焼とし、ＮＯｘの発生を低く抑えることができる。しか
も、本発明によると、燃焼量の制御が燃料系の制御だけ
で簡単におこな得るし、燃焼量が変化しても高温の種火
を維持できる。Therefore, it is possible to improve the ignitability of low-calorie gas and improve flame stability, and because there is a stable spark, the supply of combustion air to the main combustion zone is reduced to achieve twin-rich combustion, thereby suppressing the generation of NOx. I can do it. Moreover, according to the present invention, the combustion amount can be easily controlled only by controlling the fuel system, and even if the combustion amount changes, a high temperature pilot flame can be maintained.
第１図は本発明の低カロリーガス用タービン燃焼器の一
実施例を示す中央縦断面図、第２図は副燃焼室部分の拡
大断面図、第３図は第２図の■矢示図、第４図は従来の
ガスタービン燃焼器の概略図である。
１・・・主燃焼室、２・・・副燃焼室、３・・・主燃料
噴射ノズル、
４・・・−次燃焼用空気噴射ノズル、
５・・・補助バーナ、
１７’、１８・・・エゼクタを構成する絞り間及び仕切
り板、
１９・・・給気口。
特許出願人 財団法人 電力中央研究所第“３図
第４図Fig. 1 is a central vertical sectional view showing an embodiment of the low-calorie gas turbine combustor of the present invention, Fig. 2 is an enlarged sectional view of the auxiliary combustion chamber portion, and Fig. 3 is a view indicated by the ■ arrow in Fig. 2. , FIG. 4 is a schematic diagram of a conventional gas turbine combustor. DESCRIPTION OF SYMBOLS 1... Main combustion chamber, 2... Sub-combustion chamber, 3... Main fuel injection nozzle, 4... Secondary combustion air injection nozzle, 5... Auxiliary burner, 17', 18... - Throttle space and partition plate that constitute the ejector, 19...Air supply port. Patent applicant: Central Research Institute of Electric Power Industry (Figure 3) Figure 4
Claims (3)
ックス製副燃焼室を設けると共に該副燃焼室の出口周囲
に主燃料噴射ノズルと一次燃焼用空気噴射ノズルを配置
する一方、前記補助バーナの燃料流路と一次燃焼用空気
の流路とを部分的に連通させてこの連通部近傍において
燃料流路を絞りエゼクタ作用によって燃料流量に対応す
る量の燃焼用空気を吸引して一定の空気比の混合気とし
て前記副燃焼室内に噴射させることを特徴とする低カロ
リーガス用ガスタービン燃焼器。(1) A ceramic auxiliary combustion chamber equipped with an auxiliary burner is provided on the inlet side of the main combustion chamber, and a main fuel injection nozzle and a primary combustion air injection nozzle are arranged around the outlet of the auxiliary combustion chamber, while the auxiliary burner The fuel flow path and the primary combustion air flow path are partially communicated with each other, and the fuel flow path is narrowed near this communication portion, and an amount of combustion air corresponding to the fuel flow rate is sucked in by the ejector action, thereby producing a constant amount of air. A gas turbine combustor for low-calorie gas, characterized in that the mixture is injected into the sub-combustion chamber as a mixture at a specific ratio.
低カロリーガスより高カロリーのガスを燃焼させること
を特徴とする請求項１記載の低カロリーガス用ガスター
ビン燃焼器。(2) The gas turbine combustor for low-calorie gas according to claim 1, wherein the auxiliary combustion chamber combusts a gas having a higher calorie than the low-calorie gas combusted in the main combustion chamber.
リーガスを燃焼させると共に副燃焼室で総発生熱量の１
０％未満の高カロリーガスを燃焼させることを特徴とす
る請求項２記載の低カロリーガス用ガスタービン燃焼器
。(3) The main combustion chamber burns low-calorie gas that accounts for 90% or more of the total generated heat, and the auxiliary combustion chamber burns 1 of the total generated heat.
The gas turbine combustor for low-calorie gas according to claim 2, characterized in that less than 0% of high-calorie gas is combusted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63095462A JP2565980B2 (en) | 1988-04-20 | 1988-04-20 | Gas turbine combustor for low-calorie gas |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP63095462A JP2565980B2 (en) | 1988-04-20 | 1988-04-20 | Gas turbine combustor for low-calorie gas |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH01267325A true JPH01267325A (en) | 1989-10-25 |
| JP2565980B2 JP2565980B2 (en) | 1996-12-18 |
Family
ID=14138334
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP63095462A Expired - Lifetime JP2565980B2 (en) | 1988-04-20 | 1988-04-20 | Gas turbine combustor for low-calorie gas |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2565980B2 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010133699A (en) * | 2008-12-04 | 2010-06-17 | General Electric Co <Ge> | Combustor housing for combustion of low btu fuel gases and methods of making and using the same |
| JP2010159757A (en) * | 2009-01-07 | 2010-07-22 | General Electric Co <Ge> | Method and apparatus to facilitate cooling of diffusion tip within gas turbine engine |
| CN103292355A (en) * | 2012-02-28 | 2013-09-11 | 株式会社日立制作所 | Gas turbine combustor and method for operating same |
| WO2014103607A1 (en) * | 2012-12-26 | 2014-07-03 | 三菱重工業株式会社 | Combustion burner and pressurized gasification furnace |
| CN110160040A (en) * | 2019-01-08 | 2019-08-23 | 北京永博洁净科技有限公司 | Combustion apparatus |
-
1988
- 1988-04-20 JP JP63095462A patent/JP2565980B2/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010133699A (en) * | 2008-12-04 | 2010-06-17 | General Electric Co <Ge> | Combustor housing for combustion of low btu fuel gases and methods of making and using the same |
| JP2010159757A (en) * | 2009-01-07 | 2010-07-22 | General Electric Co <Ge> | Method and apparatus to facilitate cooling of diffusion tip within gas turbine engine |
| CN103292355A (en) * | 2012-02-28 | 2013-09-11 | 株式会社日立制作所 | Gas turbine combustor and method for operating same |
| CN103292355B (en) * | 2012-02-28 | 2015-12-23 | 三菱日立电力系统株式会社 | Gas turbine burner and method of operation thereof |
| WO2014103607A1 (en) * | 2012-12-26 | 2014-07-03 | 三菱重工業株式会社 | Combustion burner and pressurized gasification furnace |
| JP2014126278A (en) * | 2012-12-26 | 2014-07-07 | Mitsubishi Heavy Ind Ltd | Combustion burner and pressurized gasification furnace |
| CN104903651A (en) * | 2012-12-26 | 2015-09-09 | 三菱重工业株式会社 | Combustion burner and pressurized gasification furnace |
| CN110160040A (en) * | 2019-01-08 | 2019-08-23 | 北京永博洁净科技有限公司 | Combustion apparatus |
| CN110160040B (en) * | 2019-01-08 | 2024-05-31 | 北京永博洁净科技有限公司 | Combustion apparatus |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2565980B2 (en) | 1996-12-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5836164A (en) | Gas turbine combustor | |
| CN102175045B (en) | Low-emission combustion chamber with main combustible stage head part multi-point slant oil taking | |
| JP3477274B2 (en) | Method of operating a combustor for a gas turbine | |
| US5201181A (en) | Combustor and method of operating same | |
| US7181916B2 (en) | Method for operating a reduced center burner in multi-burner combustor | |
| US6983605B1 (en) | Methods and apparatus for reducing gas turbine engine emissions | |
| US5729968A (en) | Center burner in a multi-burner combustor | |
| US5259184A (en) | Dry low NOx single stage dual mode combustor construction for a gas turbine | |
| JP3459449B2 (en) | Gas turbine combustor and method for suppressing combustion dynamic pressure during transition from primary operation mode to premix operation mode | |
| US5285628A (en) | Method of combustion and combustion apparatus to minimize Nox and CO emissions from a gas turbine | |
| CN101981374B (en) | Burner | |
| CN107525095B (en) | A kind of axially staged can burner of gas turbine | |
| JPH02208417A (en) | Gas-turbine burner and operating method therefor | |
| JP2009047410A (en) | Method and device for burning fuel in gas turbine engine | |
| JP2831641B2 (en) | Diffusion-premix nozzle and gas turbine combustor | |
| JPH0776621B2 (en) | Double dome combustor and its usage | |
| CN109668171A (en) | A kind of radial grading subregion high temperature rise combustor head | |
| EP0488556B1 (en) | Premixed secondary fuel nozzle with integral swirler | |
| WO2023030467A1 (en) | Combustion chamber having double fuel pipes and gas turbine | |
| CN107559882B (en) | A kind of axially staged low pollution combustor | |
| JPS63156926A (en) | Combustion chamber for gas turbine and operating method of said combustion chamber | |
| KR102429643B1 (en) | System and method for improving combustion stability of gas turbine | |
| JPH01267325A (en) | Gas turbine combustor for low calorie gas | |
| JPH0443220A (en) | Combustion device for gas turbine | |
| JP2755603B2 (en) | Gas turbine combustor |