JPH03102118A - Gas turbine combustor - Google Patents
Gas turbine combustorInfo
- Publication number
- JPH03102118A JPH03102118A JP23706289A JP23706289A JPH03102118A JP H03102118 A JPH03102118 A JP H03102118A JP 23706289 A JP23706289 A JP 23706289A JP 23706289 A JP23706289 A JP 23706289A JP H03102118 A JPH03102118 A JP H03102118A
- Authority
- JP
- Japan
- Prior art keywords
- combustion
- temperature
- gas turbine
- combustor
- flame
- 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 133
- 239000000446 fuel Substances 0.000 claims abstract description 46
- 230000002159 abnormal effect Effects 0.000 claims abstract description 19
- 238000001514 detection method Methods 0.000 claims description 6
- 238000011144 upstream manufacturing Methods 0.000 claims description 2
- 238000012544 monitoring process Methods 0.000 claims 1
- 239000007789 gas Substances 0.000 abstract description 41
- 239000000567 combustion gas Substances 0.000 abstract description 10
- 238000000034 method Methods 0.000 abstract description 4
- 230000000149 penetrating effect Effects 0.000 abstract 1
- 230000005856 abnormality Effects 0.000 description 8
- 230000007423 decrease Effects 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 4
- 230000003247 decreasing effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 238000009841 combustion method Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000003745 diagnosis Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000002459 sustained effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Landscapes
- Regulation And Control Of Combustion (AREA)
- Control Of Combustion (AREA)
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の運転作動状態を監視する
ものであり、特に、二段燃焼方式による低ＮＯ．化を図
るガスタービン燃焼器の頭部，後部燃焼室の燃焼状態，
正常，異常を監視し、異常運転がないような燃焼状態を
維持するガスタービン燃焼器に関する。DETAILED DESCRIPTION OF THE INVENTION [Industrial Field of Application] The present invention monitors the operational status of a gas turbine combustor, and particularly monitors the operating state of a gas turbine combustor, and particularly monitors the operating state of a gas turbine combustor. Combustion conditions in the head and rear combustion chambers of gas turbine combustors,
This invention relates to a gas turbine combustor that monitors whether it is normal or abnormal and maintains a combustion state that prevents abnormal operation.
大気を汚染しない燃焼機関とすることが、近年、要求さ
れ、とくに，汚染物質である窒素酸化物（ＮＯ！）の発
生を大巾に抑えたガスタービンとし、Ｎｏア燃焼器を装
備することが急務であり、このようなことがガスタービ
ン設置の条件となっている。In recent years, there has been a demand for combustion engines that do not pollute the atmosphere, and in particular, it is necessary to use gas turbines that greatly suppress the generation of nitrogen oxides (NO!), which are pollutants, and to be equipped with NO combustors. This is an urgent need, and these are the conditions for installing gas turbines.
ＮＯ８を大巾に低減するためには，従来のシングルノズ
ルにより拡散燃焼技術のみでは対応出来ず、予混合燃焼
技術をとり入れた新たな二段燃焼方式を採用した二段燃
焼器の開発が行なわれ、実現しつつある。これは特開昭
５７−４１５２４号に示すように一段目燃料を燃焼させ
る頭部燃焼室とこの燃焼室の後流にあって高負荷帯で二
段目燃料を燃焼させる後部燃焼室とを備え，着火よい１
／４負荷程度までの低負荷帯は一段ｇ燃料のみを供給し
、それ以上の負荷帯では低ＮＯ０化を図りながら、負荷
上昇を図るため、一段目燃料に加えて二段目燃料を併用
する。二段目の燃料は頭部の燃焼火炎を着火源として二
段目燃料への着火を行なう。火炎の検出は最大約１８缶
におよび複数個の同一形状燃焼器を装備しているガスタ
ービンでは複数缶燃焼器のうちの二缶に火炎検出器を備
え，着火の確認を行っている。そして、燃焼器の異常、
正常の検出は，ガスタービン排ガス温度偏差の大小によ
って判断するか、あるいは、排ガス中の未燃焼分布によ
り判断する方法を用いていた。又，従来技術では燃焼器
の状態変化に対し制御するすべを持っておらず．ａ焼器
間の変差を修正するような制御は出来ず、したがって、
Ｎｏよ，ｃｏ ａ度変化に対する修正制御はできない欠
点があった。In order to significantly reduce NO8 emissions, a two-stage combustor that adopts a new two-stage combustion method that incorporates premix combustion technology has been developed, since the conventional single-nozzle diffusion combustion technology cannot be used alone. , is becoming a reality. As shown in Japanese Patent Application Laid-Open No. 57-41524, this has a head combustion chamber that burns the first stage fuel and a rear combustion chamber located downstream of this combustion chamber that burns the second stage fuel in a high load range. , Good ignition 1
In the low load range up to /4 load, only the first stage g fuel is supplied, and in the higher load range, the second stage fuel is used in addition to the first stage fuel in order to increase the load while maintaining low NO0. . The second stage fuel is ignited using the combustion flame at the head as an ignition source. Flame detection is possible for up to 18 cans.In gas turbines equipped with multiple combustors of the same shape, two of the multiple combustors are equipped with flame detectors to confirm ignition. And abnormalities in the combustor,
Normality has been detected by determining the magnitude of the gas turbine exhaust gas temperature deviation, or by determining the unburned distribution in the exhaust gas. Furthermore, conventional technology has no way to control changes in the state of the combustor. It is not possible to control the variation between a-wares, and therefore,
No, there was a drawback that corrective control for changes in COA was not possible.
二段燃焼器では二段目燃料を投入した時の，着火の検出
が必要である。さらに，一，二段目の併用燃焼で一段目
が点火検出が必要であるが、とくに一段目が失火した時
一段目燃料は頭部燃焼室では燃焼せず二段目の火炎によ
り再燃焼するための従来技術による排ガス温度による偏
差は生じず又、未燃焼ガスの生或はないために従来技術
による方法では一段目燃焼の異常は判断出来ない。従っ
て、一段目の燃焼正常，異常を検出することにより、燃
焼状態を診断する機能をもち、異常時にはガスタービン
を停止させるなどガスタービンの異常運転をなくし、常
に、正常な運転を行なうことを目的とする。さらに，常
に燃焼状態を一定に保持しＮＯ０およびＣ○発生のない
低公害燃焼運転を推持することを目的とする。In a two-stage combustor, it is necessary to detect ignition when the second stage fuel is introduced. Furthermore, in the combined combustion of the first and second stages, ignition detection is required in the first stage, but especially when the first stage misfires, the first stage fuel is not combusted in the head combustion chamber but is re-burned by the second stage flame. According to the conventional method, no deviation due to exhaust gas temperature occurs, and since no unburned gas is produced, abnormalities in the first stage combustion cannot be determined by the method according to the prior art. Therefore, it has the function of diagnosing the combustion state by detecting whether the combustion is normal or abnormal in the first stage, and the purpose is to eliminate abnormal operation of the gas turbine by stopping the gas turbine in the event of an abnormality, and to ensure normal operation at all times. shall be. Furthermore, the purpose is to always maintain a constant combustion state and maintain low-pollution combustion operation without NO0 and C○ generation.
前記目的を達成するためには、圧縮機からの空気を燃焼
用空気として上流側の頭部燃焼室と，下流側の後部燃焼
室とを備えた二段燃焼器をもち、この燃焼器から出た燃
焼ガスをタービンに導き、かつ，排気タクトより排気を
行なうガスタービンにおいて頭部燃焼室および後部燃焼
室それぞれの燃焼を検出するため、頭部，後部燃焼室そ
れぞれの燃焼室壁面を貫通し内部に突出した温度センサ
を取付け燃焼ガス温度を検出することにより燃焼の有無
を検出する。In order to achieve the above objective, a two-stage combustor is used, which uses air from the compressor as combustion air, and has a head combustion chamber on the upstream side and a rear combustion chamber on the downstream side. In order to detect combustion in the head combustion chamber and the rear combustion chamber in a gas turbine that guides the combustion gas into the turbine and exhausts it from the exhaust tact, a The presence or absence of combustion is detected by attaching a protruding temperature sensor to the combustion gas and detecting the temperature of the combustion gas.
このように，ガス温度値より夫々の燃焼器における頭部
，後部燃焼室の燃焼状態の正常，異常を判定する機能を
備えるようにしたものである。さらに温度センサによる
信号を基にして判定処理を行ない温度変化信号大時およ
び異常判定時にそれぞれの燃焼器への一段，二段目燃料
流量修正制御を行なうように、あるいは、ガスタービン
停止等の機能を備えるようにしたものである。In this way, the system is equipped with a function to determine whether the combustion state of the head and rear combustion chambers in each combustor is normal or abnormal based on the gas temperature value. Furthermore, judgment processing is performed based on the signal from the temperature sensor, and when the temperature change signal is large or an abnormality is determined, functions such as first and second stage fuel flow correction control to each combustor or gas turbine shutdown etc. It is designed to have the following.
頭部燃焼室と後部燃焼室とを備えた二段燃焼器では通常
安定燃焼時には頭部，後部の燃焼ガス温度の検出値より
判定出来る。又、頭部，後部が燃焼している状態で頭部
のみが失火し、さらに後部で再燃焼した場合でも、頭部
燃焼室に備えた温度センサの温度値が低下するので頭部
燃焼室の燃焼の異常を検出出来るようになり、頭部燃焼
室異柑のまま運転を継続することはなくなり、異常時に
おけるガスタービン運転を行なうことがなくなるため、
ガスタービンに及ぼすダメージを最小に抑えることが出
来る．
さらに頭部，後部燃焼温度検出値が大、あるいは、異常
値である時はそれぞれの燃焼温度を一定とするようにそ
れぞれの燃焼器へ供給する一，二段目，燃料流量を燃焼
温度検出値を基にして制御するようになるので、常に、
一定の正常燃焼，ＮＯＸ，Ｃｏ濃度変化を抑えたガスタ
ービン燃焼器の運転を行なうことができるようになる。In a two-stage combustor equipped with a head combustion chamber and a rear combustion chamber, stable combustion can usually be determined from the detected values of the combustion gas temperatures at the head and rear. In addition, even if only the head misfires while the head and rear parts are burning, and further combustion occurs again in the rear part, the temperature value of the temperature sensor installed in the head combustion chamber will drop, so the temperature value of the head combustion chamber will decrease. Since combustion abnormalities can now be detected, operation will no longer continue with the head combustion chamber malfunctioning, and the gas turbine will no longer operate during abnormal conditions.
Damage to the gas turbine can be minimized. Furthermore, when the head and rear combustion temperature detection values are large or abnormal values, the first and second stage fuel flow rates that are supplied to each combustor are adjusted to the combustion temperature detection values to keep the respective combustion temperatures constant. Since it will be controlled based on
It becomes possible to operate a gas turbine combustor with constant normal combustion and suppressed changes in NOX and Co concentrations.
第２図は本発明の適用されるガスタービンプラントの系
統図である。FIG. 2 is a system diagram of a gas turbine plant to which the present invention is applied.
ガスタービンは圧縮機１，タービン２および複数個の燃
焼器３からなる主要構戒物によって形威されている。圧
縮ｆｉｌで圧縮された空気４は車室５を通過し、それぞ
れの燃焼器３へ導かれる６燃焼器３は内筒６と外筒７を
もち、頭部燃焼室へ一段目燃料８が供給され、後部燃焼
室へ二段目燃料９が供給される。A gas turbine has a main structure consisting of a compressor 1, a turbine 2, and a plurality of combustors 3. Air 4 compressed by the compressor fil passes through a casing 5 and is guided to each combustor 3 6 The combustor 3 has an inner cylinder 6 and an outer cylinder 7, and first stage fuel 8 is supplied to the head combustion chamber. The second stage fuel 9 is supplied to the rear combustion chamber.
空気と混合し燃焼した燃焼ガス１０−４ま尾筒１１を介
してタービン２へ導かれる。タービン２は静翼１２ａ，
ｂ，ｃおよび動翼１３ａ，ｂ，ｃをもつ。燃焼ガス１０
はこれらの翼を通過する間に仕事を行ない，図示してい
ないが発電機を駆動して発電を行なうのである。タービ
ン２を通過した燃焼ガス１４は排気整流板１５により整
流された後に排気ダクト１６より大気中に排出されるか
、もしくは、蒸気タービンとの複合プラントでは排熱回
収ボイラに導かれる。複数個の燃焼器３はガスタービン
の軸方向同一位置の同一円周′上に配置され、それぞれ
の燃焼器３へ，一段目燃料８および二段目燃料９がそれ
ぞれのマニホールド１７ａ，１７ｂを介し、さらに、そ
れぞれの流調弁３７，３８を介して供給される。燃焼器
３には頭部燃焼室の温度を検出する一個あるいは二個以
上のセンサ１８ａと後部燃焼室の温度を検出する一個あ
るいは二個以上のセンサ１８ｂが備えられ、これらの信
号１９ａ，ｂは燃焼の異常，正常を判定し、ガスタービ
ン燃焼状態の診断を行なうことができ，さらに、異常時
には燃料を遮断し、ガスタービン停止に到らしめるなど
ガスタービンの制御を行なう制御判定器２０を備えてい
る。一方，燃焼温度を取込むｆｌｉｌＪ９１１判定器２
０は温度入力信号１９ａ，ｂを用い平均温度偏差等の処
理を行ない、偏差大の燃焼温度を示しているものに対し
ては、平均温度が偏差内に入るように判定器からの信号
を３９，４０に変換し、それぞれの燃焼器の一，二段目
燃料８，９流量を流調弁３７ａ，３８ａによって制御し
，常に一定の燃焼を維持する。The combustion gas 10-4 mixed with air and combusted is guided to the turbine 2 via the transition piece 11. The turbine 2 has stationary blades 12a,
b, c and rotor blades 13a, b, c. combustion gas 10
works while passing through these blades, and drives a generator (not shown) to generate electricity. The combustion gas 14 that has passed through the turbine 2 is rectified by an exhaust straightening plate 15 and then discharged into the atmosphere from an exhaust duct 16, or is guided to an exhaust heat recovery boiler in a combined plant with a steam turbine. A plurality of combustors 3 are arranged on the same circumference at the same position in the axial direction of the gas turbine, and the first stage fuel 8 and the second stage fuel 9 are delivered to each combustor 3 through respective manifolds 17a and 17b. , and are further supplied via respective flow control valves 37 and 38. The combustor 3 is equipped with one or more sensors 18a for detecting the temperature of the head combustion chamber and one or more sensors 18b for detecting the temperature of the rear combustion chamber, and these signals 19a, b are It is capable of determining whether combustion is abnormal or normal and diagnosing the combustion state of the gas turbine, and further includes a control determination device 20 that controls the gas turbine by cutting off fuel and bringing the gas turbine to a halt in the event of an abnormality. ing. On the other hand, the flilJ911 determiner 2 that takes in the combustion temperature
0 uses the temperature input signals 19a and 19b to process the average temperature deviation, etc., and if the combustion temperature shows a large deviation, the signal from the determiner is changed to 39 so that the average temperature falls within the deviation. , 40, and the flow rates of the first and second stage fuels 8 and 9 of the respective combustors are controlled by flow control valves 37a and 38a to maintain constant combustion.
第ｌ図に本実施例における二段燃焼器の構造を示す。燃
焼器３は頭部燃焼室２工とその後流に後部燃焼室２２と
をもち、頭部燃焼室２１の内部には内筒２３が装着され
、頭部燃焼室２１中央部への高温度燃焼部の形戊をなく
し低ＮＯ、化を図っている。FIG. 1 shows the structure of the two-stage combustor in this embodiment. The combustor 3 has two head combustion chambers and a rear combustion chamber 22 downstream thereof, and an inner cylinder 23 is installed inside the head combustion chamber 21 to direct high-temperature combustion to the center of the head combustion chamber 21. We aim to reduce NO by eliminating the shape of the parts.
頭部燃焼室２１の内部へ突出した複数個の一段燃料ノズ
ル２４により噴出した燃料８は燃焼し火炎２５を形或す
る。そして，この温度を検出するためのセンサ２６は空
気流ガイドであるフロースリーブ３３を貫通し、さらに
、頭部燃焼室壁を貫通し、内壁面より若干内側に突出し
取付けられる。The fuel 8 ejected by the plurality of single-stage fuel nozzles 24 protruding into the head combustion chamber 21 is combusted to form a flame 25. The sensor 26 for detecting this temperature passes through the flow sleeve 33, which is an air flow guide, and further penetrates the wall of the head combustion chamber, and is attached so as to protrude slightly inward from the inner wall surface.
燃焼ガス温度は壁面より内部の方がより高いためのセン
サ２６の突出し量が大きいと、焼損してしまうこのため
突出量は内壁面より３〜Ｌｏａｎ程度が最適であり，３
〜１０ｍであれば、燃焼の有無の検出が充分に出来る。Since the temperature of the combustion gas is higher inside than on the wall surface, if the amount of protrusion of the sensor 26 is large, it will be burnt out. Therefore, the amount of protrusion is optimally about 3~Loan from the inner wall surface.
~10 m, it is possible to sufficiently detect the presence or absence of combustion.
一方、二段目燃料９は二段目燃料ノズル２７より供給さ
れ、二段目燃焼用空気２８と混合器２９の内部で混合し
，予混合燃料となり、主室ライナ３０で囲まれた後部燃
焼室２２の内部で燃焼を行なう。二段目の予混合ガス３
１は一段目の火炎２５を着火源としている。後部燃焼室
２２における燃焼火炎３５温度を検出するセンサ３２は
混合器２８の後流に位置し、頭部燃焼火炎を検出するセ
ンサ２６と同様に空気流ガイドであるフロースリーブ３
４を貫通し、さらに、主室ライナ２９の壁を貫通し、内
壁面より３〜１０画突出た位置に設置される。そして、
温度を検出しその信号を判定器２０に導きガスタービン
の制御信号に用いる。On the other hand, the second-stage fuel 9 is supplied from the second-stage fuel nozzle 27 and mixed with the second-stage combustion air 28 inside the mixer 29 to become premixed fuel, which is then used for rear combustion surrounded by the main chamber liner 30. Combustion takes place inside the chamber 22. Second stage premixed gas 3
1 uses the first stage flame 25 as the ignition source. A sensor 32 for detecting the combustion flame 35 temperature in the rear combustion chamber 22 is located downstream of the mixer 28, and a sensor 32 for detecting the head combustion flame is located downstream of the flow sleeve 3 which is an air flow guide.
4, and further penetrates the wall of the main room liner 29, and is installed at a position protruding from the inner wall surface by 3 to 10 spaces. and,
The temperature is detected and the signal is sent to the determiner 20 and used as a control signal for the gas turbine.
第３図に温度センサ２６取付けの一例を示す。FIG. 3 shows an example of how the temperature sensor 26 is attached.
外筒壁に温度センサ２６を取付ける。このセンサはフロ
ースリーブ３３を貫通し、さらに、頭部燃焼室を形成す
る内筒６を貫通し、頭部燃焼火炎２５に温度センサを突
出する。温度センサの先端３６は熱電対方式を採用した
例であり、測温抵抗体等でも可能である場合によっては
、火炎検知器でも良い。又、センサの信頼性を向上する
ため、あるいは、誤動作等を妨ぐため第４図に示すよう
に、夫々の燃焼室に二ヶ以上複数個のセンサ２６ａ，２
６ｂを取付けることにより精度の良い燃焼温度の検出が
出来るものであり、燃焼器の燃焼状態診断を行なうこと
が出来る。A temperature sensor 26 is attached to the outer cylinder wall. This sensor passes through the flow sleeve 33 and further through the inner cylinder 6 forming the head combustion chamber, and projects into the head combustion flame 25 as a temperature sensor. The tip 36 of the temperature sensor is an example in which a thermocouple type is adopted, and a temperature measuring resistor or the like may be used. Depending on the case, a flame detector may also be used. In addition, in order to improve the reliability of the sensor or to prevent malfunctions, two or more sensors 26a, 2 are installed in each combustion chamber, as shown in FIG.
By attaching 6b, the combustion temperature can be detected with high accuracy, and the combustion state of the combustor can be diagnosed.
第５図にガスタービンの運転状態を示す。FIG. 5 shows the operating state of the gas turbine.
ガスタービン起動、すなわち、着火から約１７４負荷ま
では、Ｇで示すように、一段目燃料８のみで行ない約１
／４負荷において、１段目燃料を減少Ｇ′させ、これに
見合う二段目燃料９Ｈを投入する，いわゆる、燃料切換
が行なわれる。これ以上の負荷では一段目と二段目の燃
料をＧ，Ｈの様に共に増大させ、負荷の上昇を図る。一
方，Ｃ線に示すように、空気流量は着火と共にタービン
回転数が上昇し、０／４負荷でタービン回転数が１００
％となるため空気流量は１００％となる、そして、それ
以上の負荷では空気流量一定となる。Gas turbine startup, that is, from ignition to approximately 174 loads, is performed using only the first stage fuel 8, as shown by G, and approximately 1
/4 load, so-called fuel switching is performed in which the first stage fuel is decreased G' and the second stage fuel 9H corresponding to this is supplied. If the load is higher than this, the fuel in the first stage and second stage are both increased like G and H to increase the load. On the other hand, as shown in line C, the air flow rate increases as the turbine rotation speed increases with ignition, and the turbine rotation speed reaches 100 at 0/4 load.
%, the air flow rate becomes 100%, and at higher loads, the air flow rate becomes constant.
また、本発明のポイントとなる、頭部、および、後部に
おける燃焼ガス温度は，まず頭部の火炎は着火と同時に
、Ａ線で示すように上昇する。そしてＨｔのように二段
目燃料が投入されるまでは燃料増加に伴い，上昇傾向と
なる。又、１／４負荷では一段目燃料がＧｌのように減
少するため、温度は低下し、１／４負荷以上では、Ｇｚ
に示すように、燃料流量の増加と共に火炎温度はＢ１に
示すように上昇の傾向となる。一方、後部燃焼室の火炎
温度は二段目燃料の投入と同時に増加し負荷上昇に伴い
予混合器内の燃料と空気流量比が一定となるように、燃
料，空気の増加を行なうため混合比一定の燃焼を行うた
め燃焼温度は、Ｃ２に示すように、一定となる。一方，
ここで１７４負荷で、頭部燃焼が失火した場合には、Ｂ
２に示すように温度が低下し、空気温度と同レベルの温
度になることにより異常、あるいは、失火の判定が出来
る。又、複数缶装備した燃焼器の燃焼温度レベルを比較
することにより、夫々、燃焼器間の偏差が把握でき異常
現象の早期発見が可能となる。Furthermore, the temperature of the combustion gas at the head and the rear, which is a key point of the present invention, rises as shown by line A at the same time as the flame at the head ignites. Then, like Ht, it tends to rise as fuel increases until the second stage fuel is introduced. Also, at 1/4 load, the first stage fuel decreases like Gl, so the temperature decreases, and at 1/4 load or more, Gz
As shown in B1, as the fuel flow rate increases, the flame temperature tends to rise. On the other hand, the flame temperature in the rear combustion chamber increases at the same time as the second-stage fuel is input, and as the load increases, the mixture ratio is increased to keep the fuel and air flow rate ratio in the premixer constant. Since constant combustion is performed, the combustion temperature is constant as shown at C2. on the other hand,
Here, if the head combustion misfires at 174 load, B
As shown in 2, when the temperature decreases and reaches the same level as the air temperature, an abnormality or a misfire can be determined. Furthermore, by comparing the combustion temperature levels of combustors equipped with a plurality of cans, deviations between the combustors can be grasped and abnormal phenomena can be detected early.
このようにＡｔ Ｂ ＋ Ｃａｌ Ｂ ２等の温度レベ
ルにより頭部，後部燃焼室の燃焼正常，異常を判定する
ことが出来、燃焼状態の診断が可能となる。In this way, it is possible to determine whether the combustion in the head and rear combustion chambers is normal or abnormal based on the temperature level of At B + Cal B 2, etc., and the combustion state can be diagnosed.
この結果、異常燃焼運転を阻止でき、ガスタービンの安
全運転を継続することが出来る。As a result, abnormal combustion operation can be prevented and safe operation of the gas turbine can be continued.
本発明は、さらに．ＮＯＸ，Ｃｏ を常に低く抑える
ような燃料制御を行むう。The present invention further includes: Perform fuel control to keep NOX and Co low.
それぞれの燃焼器における頭部燃焼室温度、および、後
部燃焼室温度を代表した燃焼温度の時間経過傾向を第６
図に示す。The trend over time of the combustion temperature representing the head combustion chamber temperature and the rear combustion chamber temperature in each combustor is shown in the sixth graph.
As shown in the figure.
燃焼温度が平均レベル範囲Ｋおよび○内にある時は、全
缶燃焼器は正常に運転されていることを示す。ところが
、ある点（図中Ｋ′ポイント）から特定の燃焼現象が生
じ特定した燃焼器の頭部、あるいは，後部の燃焼温度が
Ｍ範囲において上昇している。この原因には頭部燃焼温
度の場合では燃料が過剰に供給されており、この結果、
頭部燃焼室で高温燃焼に起因しＭ範囲でＮ Ｏ ｘが多
く発生しているものであり、このＮ Ｏ ｘを低下する
ため燃焼温度レベルを規定範囲内に抑えるように温度高
となって燃焼器への一段目の燃料を減少するように流調
弁を制御する。この結果、Ｎを経てＮＯ０上昇が抑えら
れる。○に示す正常な燃焼に復起するこのような温度上
昇傾向が生じた場合の制御は，後部燃焼室における燃焼
状態変化にも通じるものであり．Ｎｏ．濃度を規制値レ
ベルに抑えるには特有な燃焼器が高温度になっているこ
とであり、平均燃焼温度レベル内に燃焼温度を低下する
ように判定器からの信号を用い二段目の燃料流量を制御
し、正常燃焼状態の運転を行なうものである。When the combustion temperature is within the average level ranges K and O, it indicates that the full can combustor is operating normally. However, a specific combustion phenomenon occurs from a certain point (point K' in the figure), and the combustion temperature at the specified head or rear part of the combustor increases in the M range. The cause of this is the excessive supply of fuel at the head combustion temperature;
A large amount of NO x is generated in the M range due to high temperature combustion in the head combustion chamber, and in order to reduce this NO x, the temperature is raised to keep the combustion temperature level within the specified range. The flow regulating valve is controlled to reduce the first stage fuel to the combustor. As a result, the increase in NO0 after N is suppressed. Control when a temperature rise trend like this, which returns to normal combustion as shown in ○, occurs, also applies to changes in the combustion state in the rear combustion chamber. No. In order to suppress the concentration to the regulation value level, the specific combustor must be at a high temperature, and the signal from the determiner is used to reduce the fuel flow rate in the second stage so as to lower the combustion temperature to within the average combustion temperature level. This is to control the combustion conditions and operate under normal combustion conditions.
一方、第７図に示すように燃焼温度が平均レベル範囲か
ら特定の燃焼器の頭部，後部燃焼温度が低くなった現象
を示す。この結果は、空気が増加したか、あるいは、燃
料が減少し、Ｍ＠囲に示すように、温度が低下している
ものである。しかし，それぞれの燃焼器への空気流量偏
差は非常に小さいものであり、燃料流量変化に起因する
ものである。燃焼温度低の傾向は空気過剰となり燃焼性
能が低下し，一酸化炭素（ＧＯ）や未燃焼或分（ＵＨＣ
）が発生し、ガスタービン効率低下の要因となる。さら
に、この温度降下が大になると燃焼を持続することは出
来ず、失火ｃｏｄ度限界にＣＯ濃度が大となると失火に
到ることになる。従って温度降下傾向が生じたら判定器
からの信号をそれぞれの燃料供給系に設けた燃料流量制
御弁に作用させ燃焼温度を平均レベル範囲となるように
燃料流量の増加制御を行なう。このように、それぞれの
燃焼器に設けた温度センサからのイ３号は燃焼状態の診
断が出来るばかりでな＜．ＮＯｘ発生や，ＣＯ発生を抑
制する制御信号として用い、ガスタービンの安全運転、
および，低公害安定運転を実現するガスタービン燃焼器
となる。On the other hand, as shown in FIG. 7, there is a phenomenon in which the combustion temperature at the head and rear parts of a particular combustor becomes lower than the average level range. The result is that the air has increased or the fuel has decreased and the temperature has decreased as shown in the M@ circle. However, the deviation in air flow rate to each combustor is very small and is caused by changes in fuel flow rate. The tendency of low combustion temperature is due to excess air, which reduces combustion performance and causes carbon monoxide (GO) and unburned fraction (UHC) to decrease.
), which causes a decrease in gas turbine efficiency. Furthermore, if this temperature drop becomes large, combustion cannot be sustained, and if the CO concentration reaches the COD degree limit for misfire, misfire will occur. Therefore, when a tendency for the temperature to decrease occurs, the signal from the determiner is applied to the fuel flow control valve provided in each fuel supply system to increase the fuel flow rate so that the combustion temperature falls within the average level range. In this way, No. 3 from the temperature sensor installed in each combustor can not only diagnose the combustion state. Used as a control signal to suppress NOx and CO generation, ensuring safe operation of gas turbines.
In addition, it becomes a gas turbine combustor that achieves low-pollution, stable operation.
本発明によれば、従来技術では判定出来なかったそれぞ
れの燃焼器の頭部，後部燃焼室の火炎温度を検出するこ
とができるので着火、および、失火，正常燃焼，異常燃
焼の判定が出来る。とくに，頭部燃焼室の燃焼異常が正
確に検出されるのでガスタービンの異常運転を避けるこ
とができる。According to the present invention, since it is possible to detect the flame temperature of the head and rear combustion chambers of each combustor, which could not be determined with the prior art, it is possible to determine ignition, misfire, normal combustion, and abnormal combustion. In particular, abnormal operation of the gas turbine can be avoided because combustion abnormalities in the head combustion chamber are detected accurately.
さらに夫々燃焼器における頭部，後部燃焼の変化を短時
間で把握できるので燃焼器の正確な状態診断を行なうこ
とができ、常に正常な状態を保つように制御することが
できる。Furthermore, since changes in head and rear combustion in each combustor can be ascertained in a short time, accurate diagnosis of the condition of the combustor can be performed, and control can be performed to maintain a normal condition at all times.
一方，頭部，後部の燃焼温度レベルを時間経過で評価す
ることにより燃焼温度レベルが平均レベルより外れた場
合に平均温度レベル内に，常に、維持するように，それ
ぞれの燃焼器へ供給する一段目，二段目燃料流量を修正
制御することにより、Ｎｏ．，Ｃ○発生を抑える低公害
燃焼運転を行なうことができる。On the other hand, by evaluating the combustion temperature levels of the head and rear parts over time, if the combustion temperature level deviates from the average level, one stage is supplied to each combustor so as to always maintain it within the average temperature level. By correcting and controlling the second stage fuel flow rate, No. It is possible to perform low-pollution combustion operation that suppresses the generation of , C○.
第１図は本発明の一実施例の断面図、第２図はガスター
ビンの系統図，第３図，第４図は本発明の実施例センサ
取付部の断面図、第５図はガスタービンの運転状態の特
性図、第６図，第７図は制御例の説明図である。
１・・・圧縮機，２・・・タービン、３・・・燃焼器、
２１・・・頭部燃焼室，２２・・・後部燃焼室、２６・
・・温度セン茶２
圀
葛
５
昭
がスクーヒ゛ン貞ｒ１（％ノ
第３
囲
茶４の
第乙困
粒遁咋同
経ゑ時肉Fig. 1 is a sectional view of an embodiment of the present invention, Fig. 2 is a system diagram of a gas turbine, Figs. 3 and 4 are sectional views of a sensor mounting part of an embodiment of the invention, and Fig. 5 is a gas turbine. 6 and 7 are explanatory diagrams of control examples. 1...Compressor, 2...Turbine, 3...Combustor,
21... Head combustion chamber, 22... Rear combustion chamber, 26.
...Temperature Sencha 2 Kokuzu 5 Akira is Sukuhien Tei r1 (% no 3rd Ikucha 4's 1st difficulty grain release time)
Claims (1)
焼室とその下流側に後部燃焼室を備えた複数缶の二段燃
焼器において、 複数缶燃焼器のすべての前記頭部燃焼室と前記後部燃焼
室に燃焼火炎を検出し燃焼状態を監視するセンサを一個
所あるいは二個所以上に取付けたことを特徴とするガス
タービン燃焼器。 ２、請求項１において、燃焼火炎を検出するセンサは温
度を検出するもの、あるいは、火炎を検知するものであ
ることを特徴とするガスタービン燃焼器。 ３、請求項２において、燃焼火炎検出の信号を用い正常
あるいは異常の燃焼状態診断を行なうガスタービン燃焼
器。 ４、請求項３において、燃焼火炎の異常値検出時にガス
タービンを停止させることを特徴とするガスタービン燃
焼器。 ５、請求項３において、燃焼火炎レベルを常に一定範囲
内に保持するようにそれぞれの燃焼器の一段，二段目燃
料流量を火炎温度検出の信号を用いて制御することを特
徴とするガスタービン燃焼器。 ６、請求項３において、燃焼火炎を検出した信号処理し
、ＮＯ＿ｘ，ＣＯ濃度を常に一定にするようにおのおの
燃焼器の一，二段目燃料流量を対応する燃焼火炎信号を
基に制御することを特徴とするガスタービン燃焼器。[Scope of Claims] 1. In a multi-can two-stage combustor that uses air from a compressor as combustion air and has a head combustion chamber on the upstream side and a rear combustion chamber on the downstream side thereof, A gas turbine combustor characterized in that a sensor for detecting a combustion flame and monitoring a combustion state is installed at one or more locations in all of the head combustion chambers and the rear combustion chamber. 2. The gas turbine combustor according to claim 1, wherein the sensor for detecting combustion flame is one for detecting temperature or one for detecting flame. 3. The gas turbine combustor according to claim 2, wherein the combustion state is diagnosed as normal or abnormal using a combustion flame detection signal. 4. The gas turbine combustor according to claim 3, wherein the gas turbine is stopped when an abnormal value of the combustion flame is detected. 5. The gas turbine according to claim 3, wherein the first and second stage fuel flow rates of each combustor are controlled using a flame temperature detection signal so as to always maintain the combustion flame level within a certain range. combustor. 6. In claim 3, the combustion flame detected signal is processed and the first and second stage fuel flow rates of each combustor are controlled based on the corresponding combustion flame signal so that the NO_x and CO concentrations are always constant. A gas turbine combustor featuring:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1237062A JP2972236B2 (en) | 1989-09-14 | 1989-09-14 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1237062A JP2972236B2 (en) | 1989-09-14 | 1989-09-14 | Gas turbine combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH03102118A true JPH03102118A (en) | 1991-04-26 |
| JP2972236B2 JP2972236B2 (en) | 1999-11-08 |
Family
ID=17009856
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1237062A Expired - Fee Related JP2972236B2 (en) | 1989-09-14 | 1989-09-14 | Gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2972236B2 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109556709A (en) * | 2018-12-02 | 2019-04-02 | 陕西航空电气有限责任公司 | A kind of aero-engine ionic flame detector of composite structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5669424A (en) * | 1979-11-08 | 1981-06-10 | Hitachi Ltd | Controller for flow rate of fuel for gas turbine |
| JPS5692326A (en) * | 1979-12-26 | 1981-07-27 | Hitachi Ltd | Method of and apparatus for controlling combustion of gas turbine |
| JPS62267529A (en) * | 1986-05-16 | 1987-11-20 | Hitachi Ltd | Gas turbine combustor |
| JPH01159423A (en) * | 1987-12-16 | 1989-06-22 | Hitachi Ltd | Combustion safety device for combustor |
-
1989
- 1989-09-14 JP JP1237062A patent/JP2972236B2/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5669424A (en) * | 1979-11-08 | 1981-06-10 | Hitachi Ltd | Controller for flow rate of fuel for gas turbine |
| JPS5692326A (en) * | 1979-12-26 | 1981-07-27 | Hitachi Ltd | Method of and apparatus for controlling combustion of gas turbine |
| JPS62267529A (en) * | 1986-05-16 | 1987-11-20 | Hitachi Ltd | Gas turbine combustor |
| JPH01159423A (en) * | 1987-12-16 | 1989-06-22 | Hitachi Ltd | Combustion safety device for combustor |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109556709A (en) * | 2018-12-02 | 2019-04-02 | 陕西航空电气有限责任公司 | A kind of aero-engine ionic flame detector of composite structure |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2972236B2 (en) | 1999-11-08 |
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