JPH0264232A - Monitor display device of gas turbine combustor - Google Patents
Monitor display device of gas turbine combustorInfo
- Publication number
- JPH0264232A JPH0264232A JP21605988A JP21605988A JPH0264232A JP H0264232 A JPH0264232 A JP H0264232A JP 21605988 A JP21605988 A JP 21605988A JP 21605988 A JP21605988 A JP 21605988A JP H0264232 A JPH0264232 A JP H0264232A
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- combustor
- exhaust gas
- combustors
- exhaust
- 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
- 238000012544 monitoring process Methods 0.000 claims description 6
- 238000010793 Steam injection (oil industry) Methods 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 abstract description 4
- 230000002159 abnormal effect Effects 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 4
- 230000005856 abnormality Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000001514 detection method Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000001747 exhibiting effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012806 monitoring device Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Landscapes
- Feeding And Controlling Fuel (AREA)
Abstract
Description
【発明の詳細な説明】
[産業上の利用分野]
本発明は、ガスタービンの燃焼器の監視表示装置に係り
、とくに異常燃焼を起こしている燃焼器を示すのに好適
な監視表示装置に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a monitoring and displaying device for a combustor of a gas turbine, and particularly to a monitoring and displaying device suitable for indicating a combustor that is experiencing abnormal combustion.
[従来の技術]
ガスタービンの燃焼器は環状に配置され、缶型の複数の
燃焼ライナの中で燃料を燃焼させて、概ね環状の熱ガス
流をタービンを駆動させるために発生する。BACKGROUND OF THE INVENTION A gas turbine combustor is annularly arranged and burns fuel in a plurality of can-shaped combustion liners to produce a generally annular stream of hot gas to drive a turbine.
ガスタービン燃焼器は圧力ならびに温度が極めて高い状
態にあるため、燃焼器に係る比較的小さな問題でも、こ
れを気づかずに見過ごすと、ガスタービンの重大な損傷
にまで発展することがある。Because gas turbine combustors are subject to extremely high pressures and temperatures, even relatively minor combustor problems, if left unnoticed, can lead to serious damage to the gas turbine.
このため燃焼監視装置として、例えば、特公昭59−1
2851号等に記載のものが知られている。これは、ガ
スタービン排ガスの温度分布の最大値と最小値の差を検
知して、それが広がりすぎた場合に、燃焼器に異常あり
と判定するものである。For this reason, as a combustion monitoring device, for example,
Those described in No. 2851 and the like are known. This detects the difference between the maximum value and the minimum value of the temperature distribution of gas turbine exhaust gas, and if the difference becomes too wide, it is determined that there is an abnormality in the combustor.
[9!明が解決しようとする課M]
上記従来技術は、環状に配置した複数の燃焼器のうち、
どれが異常であるかを特定することについては考慮され
ておらず、故障燃焼器の特定のためには全燃焼器の分解
点検等をせざるを得ないとい問題があった。[9! [Problem M to be solved by Akira] In the above conventional technology, among a plurality of combustors arranged in an annular manner,
No consideration was given to identifying which combustor is abnormal, and there was a problem in that in order to identify a malfunctioning combustor, all combustors had to be disassembled and inspected.
本発明の目的は、複数のガスタービン燃焼器のどれが異
常であるかを表示し、以って迅速な保守を行えるように
することである。An object of the present invention is to display which of a plurality of gas turbine combustors is abnormal, thereby allowing quick maintenance.
[課題を解決するための手段]
上記目的を達成するため、本発明は環状配置された複数
の燃焼器を具えたガスタービンの排気ガス流路中に環状
に配置された複数の排気ガス温度検出器と、燃焼器から
見た該温度検出器位置での排気、ガスの旋回角度をガス
タービン運転条件に基づいて計算する演算手段と、該演
算手段の出力および上記各温度検出器の出力を受けて1
表示画面上に排気ガス温度分布と上記旋回角度で補正さ
れた燃焼器位置・とを対応づけたグラフィック表示をす
る表示′r段とからなる、ガスタービン燃焼器の監視表
示装置を提供するものである。[Means for Solving the Problems] In order to achieve the above object, the present invention provides a plurality of exhaust gas temperature detection systems arranged annularly in the exhaust gas flow path of a gas turbine including a plurality of annularly arranged combustors. a calculation means for calculating the rotation angle of the exhaust gas and gas at the temperature detector position as seen from the combustor based on gas turbine operating conditions; and a calculation means that receives the output of the calculation means and the output of each of the temperature sensors. te1
This invention provides a gas turbine combustor monitoring and display device comprising a display 'r stage that graphically displays on a display screen the exhaust gas temperature distribution and the combustor position corrected by the rotation angle. be.
[作 用]
燃焼器から出るガスは、タービンを通り、排気デイフユ
ーザを通って、排気ダクトに出る。この間にガスは軸方
向に旋回する。その角度は土としてガスタービン出力に
比例し、一般に、例えば定格負荷で0°の場合には、無
負荷では100″程度に変化するものである。[Operation] Gas exiting the combustor passes through the turbine, passes through the exhaust diffuser, and exits into the exhaust duct. During this time, the gas swirls in the axial direction. The angle is proportional to the gas turbine output, and generally, for example, when the angle is 0° at rated load, it changes to about 100'' at no load.
この旋回角度はガスタービン出力、大気温度。This turning angle is determined by the gas turbine output and atmospheric temperature.
燃焼器への蒸気噴射量、人口案内翼開度から近似計算を
することができる。それによって、成る燃焼器から出た
ガスが、排気ダクト内に環状に配置された温度検知器の
ところでは、何処に相当する位置に流れてきたかを表示
することができる。Approximate calculations can be made from the amount of steam injected into the combustor and the opening of the guide vanes. As a result, the temperature sensor, which is arranged annularly within the exhaust duct, can indicate to which position the gas coming out of the combustor has flowed.
したがって運転員は、この表示を見て温度の高い、ある
いは低い温度検出器が、どの燃焼器から出たガスを測定
しているかを知ることができる。Therefore, by looking at this display, the operator can know which combustor's gas is being measured by the high or low temperature sensor.
これにより、異常のある燃焼器の位置を特定rることか
できる8
[実 施 例コ
以下、本発明の一実施例を第1図により説明する。、1
はpI焼器、4はガスタービン、6は排気デイフユーザ
、5は排気ダクトである。2は排気ダクトに環状分布で
配置した排気温度検出用の温度センサ(熱電対など)で
ある。As a result, the position of the combustor with an abnormality can be specified.[Embodiment] Hereinafter, an embodiment of the present invention will be described with reference to FIG. 1. ,1
4 is a gas turbine, 6 is an exhaust diffuser, and 5 is an exhaust duct. Reference numeral 2 denotes temperature sensors (thermocouples, etc.) for detecting exhaust temperature, which are arranged in an annular distribution in the exhaust duct.
さてカスタービン出力L (MW)、大気温度TA(K
)、燃焼器への蒸気噴射量S+(kg/S)、入口案内
y開度α(deg)、タービン排気圧力PI!1の関数
としてガスの旋回角(燃焼器からのカスがガスタービン
を通過することによって旋回する角度)δを演算装置7
で計算する。Now, the cast turbine output L (MW), the atmospheric temperature TA (K
), steam injection amount to the combustor S+ (kg/S), inlet guide y opening α (deg), turbine exhaust pressure PI! The calculation device 7 calculates the gas swirl angle (the angle at which the waste from the combustor swirls as it passes through the gas turbine) δ as a function of 1.
Calculate with.
δ:チ (LITAI SIT (!+ Pgx
)本実施例では次の式を用いた。δ:chi (LITAI SIT (!+ Pgx
) In this example, the following equation was used.
δ=に1L +に、TA+に4Sl十に、α+LI)
□上式の作成方法は、各種条件での実機試験を実施し、
それによく合う近似式となるように上式の各係数を定め
るものである。この実機は1本の燃焼器の燃料流量を、
他の燃焼器に対して数〜数10%増加させることによる
。そうすれば排気温度の分布に変化が現われるので、こ
れを基に上記式の各係数を定めるのである。δ= to 1L +, TA+ to 4Sl +, α+LI)
□The method for creating the above formula is based on actual machine tests under various conditions.
The coefficients of the above equation are determined so that the approximate equation fits well. This actual machine calculates the fuel flow rate of one combustor,
This is due to an increase of several to several tens of percent compared to other combustors. This will cause a change in the exhaust gas temperature distribution, and each coefficient in the above equation is determined based on this change.
前記演算装置7の演算結果および各熱電対2の出力はC
RT装置3に与えられる。C,RT装置3のグラフィッ
ク画面上には、後方より一現た燃焼器1の配置と、排気
ダクト5の各熱電対2でalll定した排気温度とが表
示される。グラフィック画面上での燃焼器1の配置は、
上記の計算した旋回角δの分だけ図上で右回りに回転さ
せて表示される。The calculation result of the calculation device 7 and the output of each thermocouple 2 are C
It is given to the RT device 3. C. On the graphic screen of the RT device 3, the arrangement of the combustor 1 seen from the rear and the exhaust gas temperature determined by each thermocouple 2 of the exhaust duct 5 are displayed. The placement of combustor 1 on the graphic screen is
It is displayed rotated clockwise on the diagram by the angle of rotation δ calculated above.
各熱電対2で測定した排気温度は円状の折線グラフとし
て表示される。The exhaust gas temperature measured by each thermocouple 2 is displayed as a circular line graph.
一例として右斜下の位置■に位置する熱電対2の温度が
400℃以下に下がった場合を第1図に示す。このとき
他の熱電対2の温度は正常な温度である400℃〜50
0℃の間にある。この場合、この低い温度のガスを発生
している燃焼器はNα3燃焼器であると判断される。そ
して警報を発生し。As an example, FIG. 1 shows a case where the temperature of the thermocouple 2 located at position (3) on the lower right side drops to 400° C. or less. At this time, the temperature of the other thermocouple 2 is a normal temperature of 400℃~50℃.
It is between 0℃. In this case, the combustor generating this low temperature gas is determined to be the Nα3 combustor. and generate an alarm.
CRTliff3の画面の下部に[Nα3ネンショウキ
イジョウ!」の表示がなされる。At the bottom of the screen of CRTliff3 is [Nα3 Nensho Kiijyou! " is displayed.
なお図中点線で示した丸は旋回角が0°のときの燃焼器
Nα1の位置である。Note that the circle indicated by a dotted line in the figure is the position of the combustor Nα1 when the rotation angle is 0°.
以上は極端な排気温度変化が発生したときの説明である
が、運転中に徐々に排気温度分布が拡大する場合には、
CRT装置3の画面を長期にM察することにより、故障
部位を推定することができる。 すなわち、起動時、停
止時、あるいは日時の異なる別の運転条件では負荷が変
化する。したがって燃焼器の位置も旋回角が変わるので
グラフィック画面上で動く。このとき、少し異常な温度
を示す熱電対が、燃焼器の動きと同期して回転するか否
かに注目する。もし同期して回転すれば、こ扛は当該燃
焼器の故障と判定される。もし同期せず常に同じ位置の
熱電対2が異常な温度を示すのであれば、これは熱電対
2の故障と判定される。The above is an explanation when extreme exhaust temperature changes occur, but if the exhaust temperature distribution gradually expands during operation,
By observing the screen of the CRT device 3 over a long period of time, the location of the failure can be estimated. That is, the load changes when starting, stopping, or under other operating conditions with different dates and times. Therefore, the position of the combustor also moves on the graphic screen as the rotation angle changes. At this time, attention is paid to whether the thermocouple exhibiting a slightly abnormal temperature rotates in synchronization with the movement of the combustor. If they rotate synchronously, this is determined to be a failure of the combustor. If the thermocouple 2, which is not synchronized and always at the same position, shows an abnormal temperature, this is determined to be a failure of the thermocouple 2.
さらに、その中間の半分程度熱電対の位置が回転するの
であれば、これはタービン4や排気デイフユーザ6の故
障であると判定される。Furthermore, if the position of the thermocouple rotates about half way in the middle, it is determined that this is a failure of the turbine 4 or the exhaust differential user 6.
本実施例によれば、CRT装置上に排気温度の分布と、
それに対応する燃焼器の位置を表示し、異常のある燃焼
器を特定でき、警報もCRT画面上に表示できる。従っ
て運転員は、全ての燃焼器を調べることなく、故障して
いる燃焼器を特定し。According to this embodiment, the exhaust temperature distribution on the CRT device,
The position of the corresponding combustor can be displayed, the combustor with the abnormality can be identified, and an alarm can also be displayed on the CRT screen. Therefore, operators can identify the malfunctioning combustor without inspecting all combustors.
迅速に保守ができるという効果がある。This has the effect of allowing quick maintenance.
尚、前記温度センサ(熱電対)2の数は燃焼器1の数と
必ずしも同じである必要はなく、実用−Lは、それと同
数もしくはそれ以上であるとするのが好ましい。Note that the number of temperature sensors (thermocouples) 2 does not necessarily have to be the same as the number of combustors 1, and it is preferable that practical-L is the same number or more.
なお、前記実施例ではCRT装置のグラフィック画面上
に燃焼器の位置および各熱電対の検出温度の両者を円グ
ラフとして表示したが1円グラフに限らず、両者を対応
づけた適宜のグラフ(例えば直交座標グラフ)として表
示してもよい。In the above embodiment, both the position of the combustor and the temperature detected by each thermocouple are displayed as a pie chart on the graphic screen of the CRT device. It may also be displayed as a Cartesian coordinate graph).
[発明の効果]
本発明によれば、ガスタービンの複数の燃焼H)のどれ
が異常であるかを表示、警報できる。従って、燃焼器の
迅速な保守、修理時間の短縮に寄!jできるという優れ
た効果がある。[Effects of the Invention] According to the present invention, it is possible to display and warn which of the plurality of combustions H) of the gas turbine is abnormal. Therefore, it helps to quickly maintain the combustor and shorten repair time! It has the excellent effect of being able to do the following.
第1図は本発明の実施例の概要図である。
1・・・燃焼器 2・・・排気温度センサ3・・
・CRT装置 4・・・ガスタービン5・・・排気ダ
クト 6・・・排気デイフユーザ第1図FIG. 1 is a schematic diagram of an embodiment of the present invention. 1... Combustor 2... Exhaust temperature sensor 3...
・CRT device 4...Gas turbine 5...Exhaust duct 6...Exhaust differential user Figure 1
Claims (1)
の排気ガス流路中に環状に配置された複数の排気ガス温
度検出器と、燃焼器から見た該温度検出器位置での排気
ガスの旋回角度をガスタービン運転条件に基づいて計算
する演算手段と、該演算手段の出力および上記各温度検
出器の出力を受けて、表示画面上に排気ガス温度分布と
上記旋回角度で補正された燃焼器位置とを対応づけたグ
ラフィック表示をする表示手段とからなる、ガスタービ
ン燃焼器の監視表示装置。 2 前記グラフィック表示が円グラフ表示である請求項
1記載のガスタービン燃焼器の監視表示装置。 3 前記の計算に用いるガスタービン/運転条件として
ガスタービン出力、大気温度、蒸気噴射量、入口案内翼
開度、ガスタービン排気圧力を用いる請求項1又は2記
載のガスタービン燃焼器の監視表示装置。[Claims] 1. A plurality of exhaust gas temperature detectors arranged annularly in the exhaust gas flow path of a gas turbine including a plurality of annularly arranged combustors, and the temperature detectors as seen from the combustors. a calculating means for calculating the turning angle of the exhaust gas at the position based on the gas turbine operating conditions; and receiving the output of the calculating means and the output of each of the above-mentioned temperature detectors, and displaying the exhaust gas temperature distribution and the above-mentioned turning on the display screen. A monitoring and display device for a gas turbine combustor, comprising a display means for graphically displaying the combustor position in correspondence with the angle-corrected combustor position. 2. The gas turbine combustor monitoring and display device according to claim 1, wherein the graphic display is a pie chart display. 3. The gas turbine combustor monitoring and display device according to claim 1 or 2, wherein gas turbine output, atmospheric temperature, steam injection amount, inlet guide vane opening, and gas turbine exhaust pressure are used as the gas turbine/operating conditions used in the calculation. .
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP21605988A JPH0264232A (en) | 1988-08-30 | 1988-08-30 | Monitor display device of gas turbine combustor |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP21605988A JPH0264232A (en) | 1988-08-30 | 1988-08-30 | Monitor display device of gas turbine combustor |
Publications (1)
Publication Number | Publication Date |
---|---|
JPH0264232A true JPH0264232A (en) | 1990-03-05 |
Family
ID=16682632
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP21605988A Pending JPH0264232A (en) | 1988-08-30 | 1988-08-30 | Monitor display device of gas turbine combustor |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH0264232A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5148667A (en) * | 1990-02-01 | 1992-09-22 | Electric Power Research Institute | Gas turbine flame diagnostic monitor |
US6460346B1 (en) * | 2000-08-30 | 2002-10-08 | General Electric Company | Method and system for identifying malfunctioning combustion chambers in a gas turbine |
EP1510656A1 (en) * | 2003-09-01 | 2005-03-02 | Siemens Aktiengesellschaft | Method and system for identifying an operational mode of a gas turbine |
JP2014058967A (en) * | 2012-09-14 | 2014-04-03 | General Electric Co <Ge> | Methods and systems for substance profile measurement in gas turbine exhaust |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5493708A (en) * | 1978-01-06 | 1979-07-25 | Hitachi Ltd | Protector for gas turbine combustor |
-
1988
- 1988-08-30 JP JP21605988A patent/JPH0264232A/en active Pending
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5493708A (en) * | 1978-01-06 | 1979-07-25 | Hitachi Ltd | Protector for gas turbine combustor |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5148667A (en) * | 1990-02-01 | 1992-09-22 | Electric Power Research Institute | Gas turbine flame diagnostic monitor |
US6460346B1 (en) * | 2000-08-30 | 2002-10-08 | General Electric Company | Method and system for identifying malfunctioning combustion chambers in a gas turbine |
US6778937B2 (en) * | 2000-08-30 | 2004-08-17 | General Electric Company | Method and system for identifying malfunctioning combustion chambers in a gas turbine |
EP1510656A1 (en) * | 2003-09-01 | 2005-03-02 | Siemens Aktiengesellschaft | Method and system for identifying an operational mode of a gas turbine |
WO2005028814A1 (en) * | 2003-09-01 | 2005-03-31 | Siemens Aktiengesellschaft | Method and device for identifying the operating condition of a turbine |
US7899647B2 (en) | 2003-09-01 | 2011-03-01 | Siemens Aktiengesellschaft | Method and device for identifying the operating condition of a turbine |
JP2014058967A (en) * | 2012-09-14 | 2014-04-03 | General Electric Co <Ge> | Methods and systems for substance profile measurement in gas turbine exhaust |
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