JP2003065081A - Control method and estimation method for gas turbine inlet temperature - Google Patents
Control method and estimation method for gas turbine inlet temperatureInfo
- Publication number
- JP2003065081A JP2003065081A JP2001254677A JP2001254677A JP2003065081A JP 2003065081 A JP2003065081 A JP 2003065081A JP 2001254677 A JP2001254677 A JP 2001254677A JP 2001254677 A JP2001254677 A JP 2001254677A JP 2003065081 A JP2003065081 A JP 2003065081A
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- Japan
- Prior art keywords
- temperature
- turbine
- exhaust gas
- compressor
- inlet temperature
- 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.)
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Links
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- Control Of Turbines (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、ガスタービンにお
けるタービンの入口温度の制御方法および推定方法に関
する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for controlling and estimating a turbine inlet temperature in a gas turbine.
【０００２】[0002]
【従来の技術】ガスタービンを良好に運転しかつその寿
命を長く維持するためには、タービンの入口温度を監視
して、この入口温度を適正な値に維持する必要がある。
そこで、従来においては、上記タービンの入口温度を所
定値に設定するためのタービン排ガス温度−圧縮機出口
圧力特性を、前記ガスタービンの圧縮機の吸気温度をパ
ラメータとして設定しておき、圧縮機の出口圧力に対応
する前記特性上の排ガス温度と実排ガス温度との偏差が
なくなるようにガスタービンの燃焼器を制御するととも
に、上記偏差に基づいてタービンの入口温度を推定して
いた。2. Description of the Prior Art In order to operate a gas turbine well and to maintain its long life, it is necessary to monitor the inlet temperature of the turbine and maintain the inlet temperature at an appropriate value.
Therefore, conventionally, the turbine exhaust gas temperature-compressor outlet pressure characteristic for setting the inlet temperature of the turbine to a predetermined value is set with the intake air temperature of the compressor of the gas turbine as a parameter, and The combustor of the gas turbine is controlled so as to eliminate the deviation between the exhaust gas temperature and the actual exhaust gas temperature corresponding to the outlet pressure, and the turbine inlet temperature is estimated based on the deviation.
【０００３】例として、タービン入口温度の制御につい
て図２を参照して説明する。図中の一点鎖線がタービン
の入口温度を１４５０℃に設定するための排ガス温度−
圧縮機出口圧力特性である。従来は、圧縮機の出口圧力
Ｐ１に対応する該特性上の排ガス温度と実排ガス温度と
の偏差ΔＴ℃’がなくなるようにガスタービンの燃焼器
を制御していた。As an example, the control of the turbine inlet temperature will be described with reference to FIG. The alternate long and short dash line in the figure indicates the exhaust gas temperature for setting the turbine inlet temperature to 1450 ° C.
It is a compressor outlet pressure characteristic. Conventionally, the combustor of the gas turbine has been controlled so as to eliminate the deviation ΔT ° 'between the exhaust gas temperature and the actual exhaust gas temperature on the characteristic corresponding to the outlet pressure P1 of the compressor.
【０００４】[0004]
【発明が解決しようとする課題】しかし、上記特性に
は、大気圧やガスタービンの圧縮機の吸気温度等の環境
要因が加味されていない。このため、特に圧力比の高い
ガスタービンにおいては、上記特性に基づいてタービン
入口温度を精度良く制御し推定することが困難になる。However, environmental characteristics such as atmospheric pressure and intake temperature of the compressor of the gas turbine are not taken into consideration in the above characteristics. Therefore, particularly in a gas turbine having a high pressure ratio, it becomes difficult to accurately control and estimate the turbine inlet temperature based on the above characteristics.
【０００５】本発明の課題は、このような状況に鑑み、
タービン入口温度の制御および推定精度を向上すること
ができるガスタービン入口温度の推定方法および制御方
法を提供することにある。In view of such a situation, an object of the present invention is to
An object of the present invention is to provide a gas turbine inlet temperature estimation method and control method capable of improving control and estimation accuracy of the turbine inlet temperature.
【０００６】[0006]
【課題を解決するための手段】本発明に係るガスタービ
ン入口温度の制御方法は、ガスタービンにおけるタービ
ンの入口温度を所定値に設定するためのタービン排ガス
温度−圧縮機出口圧力／大気圧力特性を、前記ガスター
ビンの圧縮機の吸気温度をパラメータとして設定するス
テップと、前記ガスタービンの運転時における圧縮機の
出口圧力に対応する前記特性上の排ガス温度と実排ガス
温度との偏差がなくなるように前記ガスタービンの燃焼
器を制御するステップと、を含んでいる。SUMMARY OF THE INVENTION A gas turbine inlet temperature control method according to the present invention provides a turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristic for setting a turbine inlet temperature in a gas turbine to a predetermined value. And a step of setting the intake air temperature of the compressor of the gas turbine as a parameter, so that there is no deviation between the exhaust gas temperature and the actual exhaust gas temperature on the characteristic corresponding to the outlet pressure of the compressor during operation of the gas turbine. Controlling the combustor of the gas turbine.
【０００７】また、本発明に係るガスタービン入口温度
の制御方法は、ガスタービンにおけるタービンの入口温
度を所定値に設定するためのタービン排ガス温度−圧縮
機出口圧力／大気圧力特性を、前記圧縮機のＩＧＶ開度
をパラメータとして設定するステップと、前記ガスター
ビンの運転時における圧縮機の出口圧力に対応する前記
特性上の排ガス温度と実排ガス温度との偏差がなくなる
ように前記ガスタービンの燃焼器を制御するステップ
と、を含んでいる。Further, in the method for controlling the gas turbine inlet temperature according to the present invention, the turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristic for setting the turbine inlet temperature in the gas turbine to a predetermined value is determined by the compressor. Setting the IGV opening as a parameter, and the combustor of the gas turbine so that there is no deviation between the exhaust gas temperature and the actual exhaust gas temperature in the characteristic corresponding to the outlet pressure of the compressor during operation of the gas turbine. And a step of controlling the.
【０００８】本発明に係るガスタービン入口温度の推定
方法は、ガスタービンにおけるタービンの入口温度を所
定値に設定するためのタービン排ガス温度−圧縮機出口
圧力／大気圧力特性を、前記ガスタービンの圧縮機の吸
気温度をパラメータとして設定するステップと、前記ガ
スタービンの運転時における圧縮機の出口圧力に対応す
る前記特性上の排ガス温度と実排ガス温度との偏差に基
づいて前記入口温度を推定するステップと、を含んでい
る。In the method for estimating the gas turbine inlet temperature according to the present invention, the turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristic for setting the turbine inlet temperature in the gas turbine to a predetermined value is calculated as follows: Setting the intake air temperature of the engine as a parameter, and estimating the inlet temperature based on the deviation between the exhaust gas temperature on the characteristic and the actual exhaust gas temperature corresponding to the outlet pressure of the compressor during operation of the gas turbine And, are included.
【０００９】上記吸気温度をパラメータとしてタービン
排ガス温度−圧縮機出口圧力／大気圧力特性を設定する
ステップは、少なくとも２つの吸気温度に対応する特性
に基づいて他の吸気温度に対応する特性を補間設定する
ステップを含むことができる。In the step of setting the turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristics using the intake air temperature as a parameter, the characteristics corresponding to other intake air temperatures are interpolated based on the characteristics corresponding to at least two intake air temperatures. Can be included.
【００１０】本発明に係るガスタービン入口温度の推定
方法は、ガスタービンにおけるタービンの入口温度を所
定値に設定するためのタービン排ガス温度−圧縮機出口
圧力／大気圧力特性を、前記圧縮機のＩＧＶ開度をパラ
メータとして設定するステップと、前記ガスタービンの
運転時における圧縮機の出口圧力に対応する前記特性上
の排ガス温度と実排ガス温度との偏差に基づいて前記入
口温度を推定するステップと、を含んでいる。According to the gas turbine inlet temperature estimating method of the present invention, the turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristic for setting the turbine inlet temperature in the gas turbine to a predetermined value is determined by the IGV of the compressor. A step of setting the opening degree as a parameter, and a step of estimating the inlet temperature based on a deviation between the exhaust gas temperature and the actual exhaust gas temperature on the characteristic corresponding to the outlet pressure of the compressor during operation of the gas turbine, Is included.
【００１１】[0011]
【発明の実施の形態】図１において、ガスタービンＧＴ
は、入口部位に吸気量を調整するＩＧＶ（インレット・
ゲート・ベーン）１ａを設けた空気圧縮機１、燃焼器２
およびタービン３によって構成され、燃焼器２によって
生成された高温の燃焼ガスの膨張作用によってタービン
３を回転駆動する。DESCRIPTION OF THE PREFERRED EMBODIMENTS In FIG. 1, a gas turbine GT is shown.
Is an IGV (inlet
Gate / vane) Air compressor 1 and combustor 2 provided with 1a
And the turbine 3, and the turbine 3 is rotationally driven by the expansion action of the high-temperature combustion gas generated by the combustor 2.
【００１２】大気圧検出センサ４は大気圧を、吸気温度
検出センサ５は圧縮機１の吸気温度を、開度検出センサ
６は圧縮機１のＩＧＶ１ａの開度を、圧縮機出口圧力検
出センサ７は圧縮機１の出口圧力を、また、排ガス温度
検出センサ８はタービン３の排ガスの温度をそれぞれ検
出するものである。そして、各センサ４〜８の検出信号
は、インタフェース部９を介して処理部１０に入力され
る。The atmospheric pressure detecting sensor 4 detects the atmospheric pressure, the intake temperature detecting sensor 5 detects the intake temperature of the compressor 1, the opening detecting sensor 6 detects the opening of the IGV1a of the compressor 1, and the compressor outlet pressure detecting sensor 7 operates. Indicates the outlet pressure of the compressor 1, and the exhaust gas temperature detection sensor 8 detects the temperature of the exhaust gas of the turbine 3. Then, the detection signals of the sensors 4 to 8 are input to the processing unit 10 via the interface unit 9.
【００１３】図２における実線は、タービン入口温度を
所定の値（例えば、１４５０℃）に維持させるためのタ
ービン３のタービン排ガス温度−圧縮機出口圧力／大気
圧特性（温度調節特性）を圧縮機１の吸気温度をパラメ
ータとして示したものであり、この例では、パラメータ
となる吸気温度が−１℃，１５℃および３０℃である。The solid line in FIG. 2 indicates the turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristic (temperature adjusting characteristic) of the turbine 3 for maintaining the turbine inlet temperature at a predetermined value (for example, 1450 ° C.). The intake air temperature of 1 is shown as a parameter, and in this example, the intake air temperatures that are the parameters are -1 ° C, 15 ° C, and 30 ° C.
【００１４】また、この図２における点線は、同様のタ
ービン排ガス温度−圧縮機出口圧力／大気圧特性（温度
調節特性）を圧縮機１のＩＧＶ１ａの開度をパラメータ
として示したものであり、この例では、パラメータとな
るＩＧＶ１ａの開度が４°，１０°および１９°であ
る。なお、この図２の関係は、実測によって得たもので
あり、上記処理部に内蔵された図示していないメモリに
記憶されている。The dotted line in FIG. 2 shows a similar turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristic (temperature control characteristic) using the opening of the IGV 1a of the compressor 1 as a parameter. In the example, the opening degrees of the IGV 1a serving as parameters are 4 °, 10 °, and 19 °. The relationship shown in FIG. 2 is obtained by actual measurement, and is stored in a memory (not shown) built in the processing unit.
【００１５】−１℃（予想される下限吸気温度），１５
℃および３０℃（予想される上限吸気温度）の各吸気温
度についての温度調節特性は、互いにほぼ平行する関係
にある。したがって、−１℃と１５℃間の吸気温度につ
いての特性は、これらの吸気温度−１℃，１５℃につい
ての各特性に基づいて補間設定することができ、また、
吸気温度１５℃と吸気温度３０℃間の吸気温度について
の温度調節特性は、これらの吸気温度１５℃，３０℃に
ついての各温度特性に基づいて補間設定することができ
る。-1 ° C (expected lower limit intake air temperature), 15
The temperature adjustment characteristics for each intake air temperature of 30 ° C. and 30 ° C. (expected upper limit intake air temperature) are substantially parallel to each other. Therefore, the characteristic of the intake air temperature between -1 ° C and 15 ° C can be interpolated and set based on these characteristics of the intake air temperature -1 ° C and 15 ° C.
The temperature adjustment characteristic for the intake air temperature between the intake air temperature of 15 ° C. and the intake air temperature of 30 ° C. can be set by interpolation based on the temperature characteristics for the intake air temperatures of 15 ° C. and 30 ° C.
【００１６】以下、上記吸気温度−１℃，１５℃および
３０℃についての温度調節特性を利用したタービン入口
温度の制御および推定手順について説明する。いま、例
えば、吸気温度検出センサ５によって吸気温度が１５℃
であることが検出されると、処理部１０においてこの吸
気温度１５℃についての温度調節特性が設定される。こ
のとき、圧縮機出口圧力検出センサ７によって検出され
た圧縮機出口圧力がＰ１であるとすると、処理部４は、
この圧縮機出口圧力Ｐ１と上記温度調節特性とによって
決定される目標タービン排ガス温度が得られるように制
御部１１を介して燃焼器２の燃焼状態を制御する。すな
わち、上記目標タービン排ガス温度と、排ガス温度検出
センサ８によって検出される実排ガス温度との偏差ΔＴ
℃がなくなるように燃焼器２への燃料供給量等を制御
し、これによって、タービン入口温度を目標温度１４５
０℃に近づける。The procedure for controlling and estimating the turbine inlet temperature using the temperature adjustment characteristics for the intake air temperatures -1 ° C, 15 ° C and 30 ° C will be described below. Now, for example, the intake air temperature sensor 5 detects that the intake air temperature is 15 ° C.
When it is detected that, the temperature adjusting characteristic for the intake air temperature of 15 ° C. is set in the processing unit 10. At this time, if the compressor outlet pressure detected by the compressor outlet pressure detection sensor 7 is P1, the processing unit 4
The combustion state of the combustor 2 is controlled via the control unit 11 so that the target turbine exhaust gas temperature determined by the compressor outlet pressure P1 and the temperature adjustment characteristic is obtained. That is, the deviation ΔT between the target turbine exhaust gas temperature and the actual exhaust gas temperature detected by the exhaust gas temperature detection sensor 8
The fuel supply amount to the combustor 2 and the like are controlled so that the temperature of the turbine inlet is not reached to the target temperature 145.
Close to 0 ° C.
【００１７】一方、処理部４は、排ガス温度検出センサ
８によって検出された実排ガス温度に基づいて、タービ
ン入口温度の推定手順を実行する。すなわち、圧縮機出
口圧力Ｐ１と上記温度調節特性とによって決定される目
標タービン排ガス温度に対する上記実排ガス温度の偏差
−ΔＴ℃を算出する。On the other hand, the processing unit 4 executes the procedure for estimating the turbine inlet temperature based on the actual exhaust gas temperature detected by the exhaust gas temperature detection sensor 8. That is, the deviation −ΔT ° C. of the actual exhaust gas temperature with respect to the target turbine exhaust gas temperature determined by the compressor outlet pressure P1 and the temperature adjustment characteristic is calculated.
【００１８】タービン３においては、タービン入口温度
の温度変化がタービン排ガス温度に１／Ｋ倍（通常は、
Ｋ＝２と近似することができる。）の温度変化をもたら
すことになる。実タービン入口温度は、目標タービン入
口温度１４５０℃に上記偏差−ΔＴ℃をＫ倍した温度を
加算することによって得られる。そこで、処理部４は、
１４５０℃＋Ｋ・（−ΔＴ℃）という推定演算を実行し
て、実タービン入口温度を推定する。In the turbine 3, the temperature change of the turbine inlet temperature is 1 / K times the turbine exhaust gas temperature (normally,
It can be approximated as K = 2. ) Will bring about a temperature change. The actual turbine inlet temperature is obtained by adding the target turbine inlet temperature 1450 ° C. to the temperature obtained by multiplying the deviation −ΔT ° C. by K times. Therefore, the processing unit 4
The actual turbine inlet temperature is estimated by executing the estimation calculation of 1450 ° C. + K · (−ΔT ° C.).
【００１９】なお、処理部４は、推定された実タービン
入口温度を表示部１２に表示させるとともに、タービン
３の寿命等を判定するための運転記録の１つとして実タ
ービン入口温度を図示していないメモリに記憶させる。
また、実タービン入口温度が異常値を示す場合に、図示
していない警報手段を作動させる。The processing unit 4 displays the estimated actual turbine inlet temperature on the display unit 12 and illustrates the actual turbine inlet temperature as one of the operation records for determining the life of the turbine 3 and the like. Not stored in memory.
Further, when the actual turbine inlet temperature shows an abnormal value, an alarm means (not shown) is activated.
【００２０】以上では、吸気温度が１５℃の場合につい
て説明したが、吸気温度が１５℃と３０℃の間にある時
は、その吸気温度についての温度調節特性が吸気温度１
５℃および３０℃の各温度調節特性に基づいて補間設定
され、また、吸気温度が１５℃と−１℃の間にある時
は、その吸気温度についての温度調節特性が吸気温度１
５℃および−１℃の各温度調節特性に基づいて補間（内
挿）設定される。そしてその補間設定された温度調節特
性を用いたタービン入口温度の調節手順および推定手順
が実行される。Although the case where the intake air temperature is 15 ° C. has been described above, when the intake air temperature is between 15 ° C. and 30 ° C., the temperature adjustment characteristic for the intake air temperature is the intake air temperature 1
Interpolation is set based on the temperature control characteristics of 5 ° C. and 30 ° C. When the intake air temperature is between 15 ° C. and −1 ° C., the temperature control characteristic for the intake air temperature is the intake air temperature 1
Interpolation (interpolation) is set based on the temperature adjustment characteristics of 5 ° C. and −1 ° C. Then, the adjustment procedure and estimation procedure of the turbine inlet temperature using the temperature adjustment characteristic set by the interpolation are executed.
【００２１】なお、吸気温度−１℃および３０℃につい
ての温度調節特性のみを実測設定して、これらの温度調
節特性から−１℃，３０℃間の吸気温度についての温度
調節特性を補間設定することも当然可能である。また、
−１℃，３０℃間の多数の吸気温度についての温度調節
特性をメモリに格納しておき、実吸気温度に近似する吸
気温度についての温度調節特性を実吸気温度についての
温度調節特性として設定することも可能である。It should be noted that only the temperature control characteristics for the intake air temperatures -1 ° C. and 30 ° C. are actually set, and the temperature control characteristics for the intake air temperature between -1 ° C. and 30 ° C. are interpolated from these temperature control characteristics. Of course it is possible. Also,
The temperature adjustment characteristics for a large number of intake temperatures between -1 ° C and 30 ° C are stored in a memory, and the temperature adjustment characteristics for the intake temperature that approximates the actual intake temperature are set as the temperature adjustment characteristics for the actual intake temperature. It is also possible.
【００２２】上記実施形態では、吸気温度と該吸気温度
をパラメータとする温度調節特性とを用いてタービン入
口温度の調節手順および推定手順を実行しているが、Ｉ
ＧＶ１ａの開度と該開度をパラメータとする温度調節特
性とを用いてタービン入口温度の調節手順および推定手
順を実行することも可能である。このＩＧＶ１ａの開度
に基づく上記各手順は、吸気温度に基づくそれに準じて
いるので、ここではそれについての説明を省略する。In the above embodiment, the turbine inlet temperature adjustment procedure and the estimation procedure are executed using the intake air temperature and the temperature adjustment characteristic having the intake air temperature as a parameter.
It is also possible to execute the adjustment procedure and the estimation procedure of the turbine inlet temperature by using the opening degree of the GV1a and the temperature adjustment characteristic having the opening degree as a parameter. Since each of the above procedures based on the opening degree of the IGV 1a is similar to that based on the intake air temperature, description thereof will be omitted here.
【００２３】[0023]
【発明の効果】請求項１および２に係る発明によれば、
それぞれ圧縮機の吸気温度およびＩＧＶの開度の影響を
受けることなくタービン入口温度を精度良く制御するこ
とができる。また、請求項３，４に係る発明によれば、
圧縮機の吸気温度の影響を受けることなくタービン入口
温度を精度良く推定することができる。さらに、請求項
５に係る発明によれば、圧縮機のＩＧＶの開度の影響を
受けることなくタービン入口温度を精度良く推定するこ
とができる。According to the inventions of claims 1 and 2,
The turbine inlet temperature can be accurately controlled without being affected by the intake air temperature of the compressor and the opening degree of the IGV. Further, according to the inventions of claims 3 and 4,
The turbine inlet temperature can be accurately estimated without being affected by the intake air temperature of the compressor. Further, according to the invention of claim 5, the turbine inlet temperature can be accurately estimated without being affected by the opening degree of the IGV of the compressor.
【図１】本発明に係る方法を実施するための装置構成を
例示したブロック図。FIG. 1 is a block diagram illustrating an apparatus configuration for performing a method according to the present invention.
【図２】吸気温度をパラメータとする温度調節特性と、
ＩＧＶの開度をパラメータとする温度調節特性を例示し
たグラフ。FIG. 2 is a temperature control characteristic using intake air temperature as a parameter,
The graph which illustrated the temperature control characteristic which makes the opening of IGV a parameter.
１ 圧縮機 １ａ ＩＧＶ ２ 燃焼器 ３ タービン ４ 大気圧検出センサ ５ 吸気温度検出センサ ６ 開度検出センサ ７ 圧縮機出口圧力検出センサ ８ 排ガス温度検出センサ １０ 処理部 １１ 制御部 １２ 表示部 1 compressor 1a IGV 2 Combustor 3 turbine 4 Atmospheric pressure detection sensor 5 Intake temperature detection sensor 6 Opening detection sensor 7 Compressor outlet pressure detection sensor 8 Exhaust gas temperature detection sensor 10 Processing unit 11 Control unit 12 Display
Claims (5)
度を所定値に設定するためのタービン排ガス温度−圧縮
機出口圧力／大気圧力特性を、前記ガスタービンの圧縮
機の吸気温度をパラメータとして設定するステップと、 前記ガスタービンの運転時における圧縮機の出口圧力に
対応する前記特性上の排ガス温度と実排ガス温度との偏
差がなくなるように前記ガスタービンの燃焼器を制御す
るステップと、を含むことを特徴とするガスタービン入
口温度の制御方法。1. A step of setting a turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristic for setting an inlet temperature of a turbine in a gas turbine to a predetermined value, using an intake air temperature of the compressor of the gas turbine as a parameter. Controlling the combustor of the gas turbine so that there is no deviation between the characteristic exhaust gas temperature corresponding to the compressor outlet pressure during operation of the gas turbine and the actual exhaust gas temperature. Control method of gas turbine inlet temperature.
度を所定値に設定するためのタービン排ガス温度−圧縮
機出口圧力／大気圧力特性を、前記圧縮機のＩＧＶ開度
をパラメータとして設定するステップと、 前記ガスタービンの運転時における圧縮機の出口圧力に
対応する前記特性上の排ガス温度と実排ガス温度との偏
差がなくなるように前記ガスタービンの燃焼器を制御す
るステップと、を含むことを特徴とするガスタービン入
口温度の制御方法。2. A step of setting a turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristic for setting a turbine inlet temperature in a gas turbine to a predetermined value, using an IGV opening of the compressor as a parameter, Controlling the combustor of the gas turbine so that there is no deviation between the exhaust gas temperature on the characteristics and the actual exhaust gas temperature corresponding to the outlet pressure of the compressor during operation of the gas turbine. Gas turbine inlet temperature control method.
度を所定値に設定するためのタービン排ガス温度−圧縮
機出口圧力／大気圧力特性を、前記ガスタービンの圧縮
機の吸気温度をパラメータとして設定するステップと、 前記ガスタービンの運転時における圧縮機の出口圧力に
対応する前記特性上の排ガス温度と実排ガス温度との偏
差に基づいて前記入口温度を推定するステップと、を含
むことを特徴とするガスタービン入口温度の推定方法。3. A step of setting a turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristic for setting a turbine inlet temperature in a gas turbine to a predetermined value, using an intake air temperature of the compressor of the gas turbine as a parameter. And a step of estimating the inlet temperature based on a deviation between the exhaust gas temperature on the characteristic corresponding to the outlet pressure of the compressor during operation of the gas turbine and the actual exhaust gas temperature. Inlet temperature estimation method.
力／大気圧力特性を設定するステップが、少なくとも２
つの吸気温度に対応する特性に基づいて他の吸気温度に
対応する特性を補間設定するステップを含むことを特徴
とする請求項３に記載のタービン入口温度の推定方法。4. The step of setting the turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristic comprises at least 2.
The method for estimating the turbine inlet temperature according to claim 3, further comprising the step of interpolating a characteristic corresponding to another intake air temperature based on a characteristic corresponding to one intake air temperature.
度を所定値に設定するためのタービン排ガス温度−圧縮
機出口圧力／大気圧力特性を、前記圧縮機のＩＧＶ開度
をパラメータとして設定するステップと、 前記ガスタービンの運転時における圧縮機の出口圧力に
対応する前記特性上の排ガス温度と実排ガス温度との偏
差に基づいて前記入口温度を推定するステップと、を含
むことを特徴とするガスタービン入口温度の推定方法。5. A step of setting a turbine exhaust gas temperature-compressor outlet pressure / atmospheric pressure characteristic for setting a turbine inlet temperature in a gas turbine to a predetermined value, using an IGV opening of the compressor as a parameter, Gas turbine inlet temperature, the step of estimating the inlet temperature based on a deviation between the actual exhaust gas temperature and the exhaust gas temperature on the characteristic corresponding to the outlet pressure of the compressor during operation of the gas turbine. Estimation method.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012062833A (en) * | 2010-09-16 | 2012-03-29 | Honda Motor Co Ltd | Temperature estimation apparatus for aeroplane gas turbine engine |
| CN105240130A (en) * | 2014-07-11 | 2016-01-13 | 阿尔斯通技术有限公司 | Method for the control and protection of a gas turbine and gas turbine using such method |
| KR102079565B1 (en) | 2018-11-12 | 2020-02-20 | 한국전력공사 | Turbine inlet temperature measurement system and measurement method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58107819A (en) * | 1981-12-22 | 1983-06-27 | Toshiba Corp | Gas turbine control device |
| JPS6397835A (en) * | 1986-10-13 | 1988-04-28 | Hitachi Ltd | Gas turbine temperature control device |
| JPS63110639A (en) * | 1986-10-28 | 1988-05-16 | Nec Corp | Manufacture of integrated circuit device |
| JPH1172029A (en) * | 1997-06-30 | 1999-03-16 | Hitachi Ltd | Gas turbine having output increasing mechanism by water atomization |
-
2001
- 2001-08-24 JP JP2001254677A patent/JP4773646B2/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58107819A (en) * | 1981-12-22 | 1983-06-27 | Toshiba Corp | Gas turbine control device |
| JPS6397835A (en) * | 1986-10-13 | 1988-04-28 | Hitachi Ltd | Gas turbine temperature control device |
| JPS63110639A (en) * | 1986-10-28 | 1988-05-16 | Nec Corp | Manufacture of integrated circuit device |
| JPH1172029A (en) * | 1997-06-30 | 1999-03-16 | Hitachi Ltd | Gas turbine having output increasing mechanism by water atomization |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012062833A (en) * | 2010-09-16 | 2012-03-29 | Honda Motor Co Ltd | Temperature estimation apparatus for aeroplane gas turbine engine |
| CN105240130A (en) * | 2014-07-11 | 2016-01-13 | 阿尔斯通技术有限公司 | Method for the control and protection of a gas turbine and gas turbine using such method |
| CN105240130B (en) * | 2014-07-11 | 2019-03-26 | 安萨尔多能源瑞士股份公司 | Control and protect the method for gas turbine and the gas turbine using such method |
| US10465552B2 (en) | 2014-07-11 | 2019-11-05 | Ansaldo Energia Switzerland AG | Method for the control and protection of a gas turbine and gas turbine using such method |
| KR102079565B1 (en) | 2018-11-12 | 2020-02-20 | 한국전력공사 | Turbine inlet temperature measurement system and measurement method |
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|---|---|
| JP4773646B2 (en) | 2011-09-14 |
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