JPS5847928A - Gas turbine combustor - Google Patents
Gas turbine combustorInfo
- Publication number
- JPS5847928A JPS5847928A JP14616981A JP14616981A JPS5847928A JP S5847928 A JPS5847928 A JP S5847928A JP 14616981 A JP14616981 A JP 14616981A JP 14616981 A JP14616981 A JP 14616981A JP S5847928 A JPS5847928 A JP S5847928A
- Authority
- JP
- Japan
- Prior art keywords
- combustion
- fuel
- combustion chamber
- air
- chamber
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
Description
【発明の詳細な説明】
本発明はガスタービン燃焼器に係シ、特に、低発熱量の
燃料を使用する場合に、安定で良好な燃焼を図る燃焼器
に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a gas turbine combustor, and particularly to a combustor that achieves stable and good combustion when using fuel with a low calorific value.
従来の燃焼器は液体、気体燃料を問わず、高発熱量の燃
料を対象としているが、その燃焼器に低発熱量の燃料を
使用すれば、種々の問題を生じる。Conventional combustors are intended for high calorific value fuels, whether liquid or gaseous, but if low calorific value fuels are used in the combustor, various problems arise.
偶発“熱量燃料として、石炭のガス化によって生成され
る石炭ガスを列にとる。メタンガスと比較すると発熱量
は約９分の１で火炎温度も低い。石炭ガスは可燃物質で
ある水素、−酸化炭素、メタン等が窒素で希釈されてい
るため、燃焼速度が遅く、従って燃焼反応も遅い。また
、可燃限界もメタンに比ミて狭く、燃空比の小さいとこ
ろでは火炎は形成されない。このように、低発熱量の石
炭ガスは燃料としては極めて特性が悪い。この低発熱量
ガスをガスタービン燃焼器の燃料として使用して、メタ
ンガス使用と同じガスタービン性能を得る際、大きな障
害となるのは燃料流量が非常に増え、体積流量比でメタ
ンの約８倍遍にもなることである。Coal gas produced by gasification of coal is used as an accidental calorific fuel.Compared to methane gas, the calorific value is about 1/9th and the flame temperature is lower.Coal gas is a combustible substance, hydrogen, - oxidation Since carbon, methane, etc. are diluted with nitrogen, the combustion rate is slow, and therefore the combustion reaction is also slow.The flammability limit is also narrower than that of methane, and no flame is formed at low fuel-air ratios. Coal gas, which has a low calorific value, has extremely poor properties as a fuel.This is a major obstacle when using this low calorific value gas as fuel for a gas turbine combustor to achieve the same gas turbine performance as using methane gas. This means that the fuel flow rate increases significantly, reaching about 8 times that of methane in terms of volumetric flow rate ratio.
このような燃料流量を１つの燃料ノズルから噴射するに
は、従来の燃焼器では燃料流速が速すぎて。The fuel flow rate is too high in conventional combustors to inject such a fuel flow rate from a single fuel nozzle.
保炎ができなくなる。このため、燃料を多段に分散させ
て注入するか、燃料ノズルの噴９面積を大きくする方法
がある。後者の方法では、たとえ流速は遅くなっても、
空気との混合が困難となる。Flame holding is no longer possible. For this reason, there is a method of injecting the fuel by dispersing it in multiple stages or increasing the spray area of the fuel nozzle. In the latter method, even if the flow velocity is slower,
Difficult to mix with air.
壕だ、従来の燃焼器の構造では、１つの燃料ノズルだけ
で安定範囲の狭い低発熱量燃料を全負荷にわたって良好
な燃焼を貸なわせることは非常に困稚である。前者の方
法では、燃焼領域を軸方向に直列に２段並べる方法があ
るが、２段目の燃焼が１段目の燃焼の影響をうけること
や、２段目の着。However, with the conventional combustor structure, it is very difficult to provide good combustion of low calorific value fuel with a narrow stability range over the entire load using only one fuel nozzle. The former method involves arranging the combustion regions in two stages in series in the axial direction, but the combustion in the second stage is affected by the combustion in the first stage, and the combustion in the second stage is affected by the combustion in the second stage.
火が困難なことが問題となっている。The problem is that fire is difficult.
以上のように、低発熱量燃料をガスタービン全負荷範囲
にわたって良好な燃焼を行なわせるには、従来の燃焼器
構造や燃焼方法では到底不可能であり、新しい構造、方
式が必要である。As described above, it is completely impossible to achieve good combustion of low calorific value fuel over the entire gas turbine load range using conventional combustor structures and combustion methods, and new structures and methods are required.
本考案の目的は、低発熱量燃料を使用しても、ガスター
ビン全負荷範囲で、安定な燃焼が可能な燃焼器の燃焼機
構を提供することにある。An object of the present invention is to provide a combustion mechanism for a combustor that can perform stable combustion over the entire gas turbine load range even when using low calorific value fuel.
安定燃焼範囲の狭い低発熱量気体燃料を、ガスタービン
の全負荷範囲にわたって安定燃焼を行なわせるためには
、できるだけ理論空燃比付近で燃焼を行なわせることが
非常に有効なことが明らかとなっている。発明者等は、
特に、空気過剰率で２．２以下にすれば、良好な燃焼が
得られることを実験により確認している。そこで燃焼領
域を２つに分け、低負荷条件のときは１つの燃焼領域だ
けで燃焼させ、高負荷条件のときは２つの燃焼領域で燃
焼させる。低負荷条件、高負荷条件いずれの場合も、で
きるだけ理論空燃比に近い燃焼を行なわせることが必要
となるので、低負荷条件のときは燃焼させないもう一方
の燃焼室に燃焼に余分な空気を導入させ、燃焼反応の終
った燃焼器後部で合流させ、燃焼に悪い影響を及ぼさな
いようにする。高負荷時には両燃焼室で、理論空燃比に
近いところで燃焼すればよいが、第２の燃焼室でうまく
着火させなければならない。着火しても最初は燃料が少
ないために、不安定な燃焼になったシ、燃焼効率が下が
る可能性があるので、２系統の燃料ラインを制御する方
法と、第２の燃焼が最初の第１の燃焼領域に悪い影響を
及ぼさないようにする必要がある。このため、発明者等
は、２つの燃焼室を含む燃焼器の構造、それに伴う燃料
流量の制御法、着火方法を発明した。It has become clear that in order to ensure stable combustion of low calorific value gaseous fuels, which have a narrow stable combustion range, over the entire load range of a gas turbine, it is extremely effective to perform combustion as close to the stoichiometric air-fuel ratio as possible. There is. The inventors, etc.
In particular, it has been confirmed through experiments that good combustion can be obtained if the excess air ratio is set to 2.2 or less. Therefore, the combustion area is divided into two, and combustion is performed in only one combustion area when the load is low, and combustion is performed in two combustion areas when the load is high. In both low-load and high-load conditions, it is necessary to perform combustion as close to the stoichiometric air-fuel ratio as possible, so extra air is introduced into the other combustion chamber that does not burn during low-load conditions. and merge at the rear of the combustor where the combustion reaction has finished, so as not to adversely affect combustion. At high loads, it is sufficient to combust in both combustion chambers at a near stoichiometric air-fuel ratio, but it is necessary to successfully ignite the fuel in the second combustion chamber. Even if the ignition occurs, there is little fuel at first, resulting in unstable combustion and the combustion efficiency may decrease. It is necessary to avoid having a negative effect on the combustion region of No. 1. For this reason, the inventors invented a combustor structure including two combustion chambers, a fuel flow rate control method, and an ignition method.
以下、本発明の一実施例を第１図により説明す□
る。ガスタービン燃焼器の外筒１の内部に第−燃焼室２
、第二燃焼室３が設けられている。ガス燃料はガス燃料
ライン４から燃料ノズル５に入り、旋回器６から、空気
７とともに燃焼領域８に入るものと、燃料ライン４から
分かれ、燃料ライン９を通って、燃料ノズル１０に入り
、旋回器１１から空気“１２とともに燃焼領域１３に入
る二系統になっている。第一燃焼室には、燃焼用−次空
気孔１４、同二次空気孔１５、第２燃焼室３には燃焼用
−次空気孔１６、同二次空気孔１７、希釈空気孔１８，
１９、そして、第一燃焼室２、第二燃焼室３の後流部に
共通の希釈空気孔２０を備えている。An embodiment of the present invention will be described below with reference to FIG. A first combustion chamber 2 is provided inside the outer cylinder 1 of the gas turbine combustor.
, a second combustion chamber 3 is provided. The gas fuel enters the fuel nozzle 5 from the gas fuel line 4, enters the combustion zone 8 together with the air 7 from the swirler 6, and splits from the fuel line 4, passes through the fuel line 9, enters the fuel nozzle 10 and swirls. There are two systems in which air enters the combustion area 13 from the combustion chamber 11 together with air 12.The first combustion chamber has a secondary air hole 14 for combustion and a secondary air hole 15, and the second combustion chamber 3 has a combustion air hole 14 and a secondary air hole 15 for combustion. - secondary air hole 16, secondary air hole 17, dilution air hole 18,
19, and a common dilution air hole 20 is provided at the downstream portion of the first combustion chamber 2 and the second combustion chamber 3.
次に、第２図の運転条件に従ってその操作を説明する。Next, the operation will be explained according to the operating conditions shown in FIG.
まず空気量配分を、燃焼器ライナの冷却空気、希釈空気
孔２０から流入する空気流量２３を除いた残りの空気流
量を、第一燃焼室に６５％、第二燃焼室に３５％の割合
とするように、開口面積が決定されている。本実施例に
おいては、定格負荷において、燃料１に対し空気は６（
重量比）入ることになっており、そのうちの約３分の２
は希釈空気２３と冷却空気であり残りは、第一燃焼 室
２の旋回器６、空気孔１４，１５、第二燃焼室３の旋回
器１１．空気孔１６．１７，１８．１９から流入する。First, the air amount distribution is determined so that the remaining air flow rate excluding the cooling air of the combustor liner and the air flow rate 23 flowing in from the dilution air hole 20 is set at a ratio of 65% to the first combustion chamber and 35% to the second combustion chamber. The opening area is determined as follows. In this example, at the rated load, the air is 6 (
(weight ratio), of which approximately two-thirds
are dilution air 23 and cooling air, and the rest is the swirler 6 of the first combustion chamber 2, the air holes 14, 15, and the swirler 11 of the second combustion chamber 3. It flows in from air holes 16.17 and 18.19.
スタート時から、無負荷咄では補助燃料として、軽油を
用いる。ガス燃料だけでは、空燃比が高すぎ保炎できな
いためである。このとき、ガス燃料ライン９に設置され
た流量弁２１は閉じているため、燃料は燃料ライン４に
設置されている流量制御バルブ２２によって第一燃焼室
２にのみ注入されることになる。無負荷から２５％負荷
までは空気過剰率が２．７３から１．５５となり、比較
的良好な燃焼が得られる。さらに、燃料の７０％までを
第一燃焼室２で燃焼を行なわせる。Light oil is used as auxiliary fuel during no-load operation from the start. This is because the air-fuel ratio is too high and flame cannot be held with gas fuel alone. At this time, since the flow valve 21 installed in the gas fuel line 9 is closed, fuel is injected only into the first combustion chamber 2 by the flow control valve 22 installed in the fuel line 4. From no load to 25% load, the excess air ratio is from 2.73 to 1.55, and relatively good combustion can be obtained. Furthermore, up to 70% of the fuel is combusted in the first combustion chamber 2.
このときの燃焼領域８の空気過剰率はお・よそ１．０で
、燃焼速度も速く、最適な燃焼状態である。この状態で
は第二燃焼室３は空気だけが流れている。At this time, the excess air ratio in the combustion region 8 is approximately 1.0, the combustion speed is fast, and the combustion state is optimal. In this state, only air is flowing through the second combustion chamber 3.
、燃料が７０％を越えるとき、流量弁２１が開き、第二
燃焼室３に燃料が注入される。第一燃焼室２と第二燃焼
室３へ流入するおのおのの燃料流量の比は予め設定され
ておシ、本実施しリでは５対２である。第二燃焼室の着
火は、第一と第二燃焼室を継ぐ火炎伝は管２３Ｖｃよっ
て行なわれる。流量弁２１が開くことにより第一燃料は
全体の７０％から５０％に減少するが燃焼領域８におけ
る空気過剰率は１．３〜１．４で燃焼に問題はな“い。, when the fuel exceeds 70%, the flow valve 21 opens and fuel is injected into the second combustion chamber 3. The ratio of the respective fuel flow rates flowing into the first combustion chamber 2 and the second combustion chamber 3 is set in advance, and in this embodiment is 5:2. Ignition of the second combustion chamber is carried out through the flame transmission pipe 23Vc connecting the first and second combustion chambers. When the flow rate valve 21 opens, the first fuel decreases from 70% to 50% of the total amount, but the excess air ratio in the combustion region 8 is 1.3 to 1.4, so there is no problem in combustion.
第二燃焼室３の着火は空気過剰率にして１．２−” １
．３になるように燃焼用空気孔１６．１７、旋回器１１
の開口面積と希釈用空気孔１８．１９の開口「萌積を決
定しているので、軽油を用いなくても着火は可能である
。燃料７０％から定格負荷時の１００％までは、流量調
節バルブ２２だけで調節する。定格負荷時は両燃焼領域
とも空気過剰率で１．０近傍で燃焼が行なわれる。The ignition of the second combustion chamber 3 is carried out at an excess air ratio of 1.2-" 1
．． Combustion air holes 16 and 17, swirler 11 so that
Since the opening area of the dilution air hole 18 and the opening of the dilution air hole 18. Adjustment is made only by the valve 22. At rated load, combustion takes place at an excess air ratio of around 1.0 in both combustion regions.
本実施例のように、燃焼領域を２つに分けることにより
、全負荷範囲にわたってそれぞれの燃焼室内で安定な燃
焼が得られる空燃比範囲を形成することが可能となる。By dividing the combustion region into two as in this embodiment, it is possible to form an air-fuel ratio range in which stable combustion can be obtained in each combustion chamber over the entire load range.
また、燃料ノズルも２つになるので、使用燃料流量範囲
が狭まることになり、単一ノズルより保炎機構の°設計
が容易となる。本実１１Ｊでは、従来の２段燃焼方式と
は違い、２つの燃焼領域、とくに第二燃焼室が充分に長
い構造となっているので、両燃焼室がお互いに燃焼の妨
げとなる干渉作用もなく、両燃焼室で燃焼が完全に行な
われる。また２つの燃焼室を半径方向に並列に並べたこ
とにより、径及び燃焼室容積が小さくなり燃料と空気の
混合効果が促進され、燃焼反応がより早くすすむ効果が
ある。Furthermore, since there are two fuel nozzles, the usable fuel flow rate range is narrowed, and the design of the flame holding mechanism is easier than with a single nozzle. Unlike the conventional two-stage combustion system, the Honjitsu 11J has a structure in which the two combustion regions, especially the second combustion chamber, are sufficiently long, so that there is no interference between the two combustion chambers that interferes with combustion. combustion takes place completely in both combustion chambers. Furthermore, by arranging the two combustion chambers in parallel in the radial direction, the diameter and volume of the combustion chambers are reduced, the mixing effect of fuel and air is promoted, and the combustion reaction proceeds more quickly.
燃料の制（財）も本実施例によれば、流量弁２１は０Ｎ
−ＯＦＦの制御だけでよく、あとは従来と同じ燃料コン
トロールバルブの操作だけなので比較的容易な制御とな
る。According to this embodiment, the fuel control is also performed, and the flow valve 21 is set to 0N.
-OFF control is all that is required, and all that is left to do is operate the fuel control valve, which is the same as before, making the control relatively easy.
スタートアップから無負荷時、２５％負荷時においても
比較的、燃空比は従来燃焼器よりも高くなっているので
、軽油を減らしてできるだけ燃料ガスを使用することが
可能となり、軽油の節約にもなる。Since the fuel-air ratio is relatively higher than that of conventional combustors, even at startup, no load, and 25% load, it is possible to reduce diesel oil and use fuel gas as much as possible, which also saves diesel oil. Become.
本発明によれば、燃焼室を２つに分けることによって、
全負荷にわたって、高燃空比あるいは理論燃空比に近い
燃焼が可能となるので、安定で良能
好な燃焼−一；得られる。According to the present invention, by dividing the combustion chamber into two,
Since combustion is possible at a high fuel-air ratio or close to the stoichiometric fuel-air ratio over the entire load, stable and efficient combustion can be obtained.
第１靴は本発明の燃焼器の外筒内部の燃焼器ライナ部の
断面図、第２図は本発明の燃焼器の運転条件を示す図で
ある。
２・・・第一燃焼室、３・・・第二燃焼室、１４，１５
゜１６．１７・・・燃焼用空気孔、４・・・第一燃料ラ
イン、９・・・第二燃料ライン、２１・・・燃料オン−
オフ制御バルブ、２２・・・燃料流量調整弁、２３・・
・火炎伝は気 １図The first shoe is a sectional view of the combustor liner inside the outer cylinder of the combustor of the present invention, and FIG. 2 is a diagram showing operating conditions of the combustor of the present invention. 2... First combustion chamber, 3... Second combustion chamber, 14, 15
゜16.17... Combustion air hole, 4... First fuel line, 9... Second fuel line, 21... Fuel on-
Off control valve, 22...Fuel flow rate adjustment valve, 23...
・Fire den is Ki 1 figure
Claims (1)
において、燃料が燃焼する領域を二室に分離し、これら
二つの燃焼室を平行に並べ、第一の燃焼室には燃焼用空
気孔を設け、第二の燃焼室には燃焼用空気孔と希釈用空
気孔を設け、その最後尾が前記第一燃焼室の後部に接続
され、その後に、前記各燃焼室に共通の希釈空気孔を設
けたことを特徴とするガスタービン燃焼器、1. In a gas turbine combustor that uses gaseous fuel with a low calorific value, the region where the fuel burns is separated into two chambers, these two combustion chambers are arranged in parallel, and the first combustion chamber has combustion air holes. The second combustion chamber is provided with a combustion air hole and a dilution air hole, the rear end of which is connected to the rear part of the first combustion chamber, and the second combustion chamber is provided with a dilution air hole common to each combustion chamber. A gas turbine combustor characterized by being provided with a
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14616981A JPS5847928A (en) | 1981-09-18 | 1981-09-18 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14616981A JPS5847928A (en) | 1981-09-18 | 1981-09-18 | Gas turbine combustor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS5847928A true JPS5847928A (en) | 1983-03-19 |
Family
ID=15401687
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP14616981A Pending JPS5847928A (en) | 1981-09-18 | 1981-09-18 | Gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5847928A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5261239A (en) * | 1991-02-28 | 1993-11-16 | Societe Nationale D'etude Et De Construction De Motors D'aviation | Lean premixture combustion-chamber comprising a counterflow enclosure to stabilize the premixture flame |
| US5473882A (en) * | 1993-06-03 | 1995-12-12 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Combustion apparatus for a gas turbine having separate combustion and vaporization zones |
| WO1996027766A1 (en) * | 1995-03-08 | 1996-09-12 | Bmw Rolls-Royce Gmbh | Axially stepped double-ring combustion chamber for a gas turbine |
-
1981
- 1981-09-18 JP JP14616981A patent/JPS5847928A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5261239A (en) * | 1991-02-28 | 1993-11-16 | Societe Nationale D'etude Et De Construction De Motors D'aviation | Lean premixture combustion-chamber comprising a counterflow enclosure to stabilize the premixture flame |
| US5473882A (en) * | 1993-06-03 | 1995-12-12 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Combustion apparatus for a gas turbine having separate combustion and vaporization zones |
| WO1996027766A1 (en) * | 1995-03-08 | 1996-09-12 | Bmw Rolls-Royce Gmbh | Axially stepped double-ring combustion chamber for a gas turbine |
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