JPH0350089B2 - - Google Patents
Info
- Publication number
- JPH0350089B2 JPH0350089B2 JP60098988A JP9898885A JPH0350089B2 JP H0350089 B2 JPH0350089 B2 JP H0350089B2 JP 60098988 A JP60098988 A JP 60098988A JP 9898885 A JP9898885 A JP 9898885A JP H0350089 B2 JPH0350089 B2 JP H0350089B2
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- stage
- regulating valve
- air
- flow rate
- 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.)
- Expired - Lifetime
Links
- 239000000446 fuel Substances 0.000 claims description 189
- 230000001105 regulatory effect Effects 0.000 claims description 60
- 238000002485 combustion reaction Methods 0.000 claims description 59
- 238000009792 diffusion process Methods 0.000 claims description 14
- 238000011144 upstream manufacturing Methods 0.000 claims description 8
- 239000000203 mixture Substances 0.000 claims description 2
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 37
- 239000007789 gas Substances 0.000 description 26
- 238000010586 diagram Methods 0.000 description 9
- 230000001276 controlling effect Effects 0.000 description 5
- 238000002347 injection Methods 0.000 description 5
- 239000007924 injection Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 238000009841 combustion method Methods 0.000 description 3
- 230000007423 decrease Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000809 air pollutant Substances 0.000 description 1
- 231100001243 air pollutant Toxicity 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
Description
【発明の詳細な説明】
〔発明の利用分野〕
本発明はガスタービンの燃料制御装置に係り、
特に大気汚染物質である窒素酸化物（以下NOx
という。）等の発生を抑制し得るガスタービン燃
料制御装置に関する。[Detailed Description of the Invention] [Field of Application of the Invention] The present invention relates to a fuel control device for a gas turbine.
In particular, nitrogen oxides (NOx) are air pollutants.
That's what it means. ) and the like.
ガスタービン燃焼器において発生するNOxの
低減を図るためには、燃焼過程において燃料と空
気の混合を均一化、あるいはNOxの生成時間の
短縮を図ることにより、均一低温度燃焼を行わせ
ることが必要である。
In order to reduce NOx generated in gas turbine combustors, it is necessary to achieve uniform low-temperature combustion by equalizing the mixture of fuel and air during the combustion process or by shortening the NOx generation time. It is.
この燃焼形態を確立するための手段として、燃
料と空気を予め混合して燃焼器に供給する方式
（予混合燃焼方式）と、燃料を燃焼器で拡散燃焼
させる方式（拡散燃焼方式）とを組み合わせて行
う２段燃焼構造をもつ燃焼器が知られている（特
開昭57−41524号公報参照）。 As a means to establish this combustion form, we combine a method in which fuel and air are mixed in advance and supplied to the combustor (premix combustion method), and a method in which the fuel is diffusely combusted in the combustor (diffusion combustion method). A combustor having a two-stage combustion structure is known (see Japanese Patent Laid-Open No. 57-41524).
ここで、２段燃焼構造を用いる理由を以下に説
明する。 Here, the reason for using the two-stage combustion structure will be explained below.
まず、第５図にガスタービン発電所の主要機器
構成を示す。空気圧縮機１、燃焼器２、タービン
３、発電機４で構成されたガスタービン発電所に
おいて発電された電力は遮断器５を経て送電系統
へ供給される。このガスタービン発電所における
電力制御は燃料調整弁６によつて行われる。 First, Figure 5 shows the main equipment configuration of a gas turbine power plant. Electric power generated in a gas turbine power plant including an air compressor 1, a combustor 2, a turbine 3, and a generator 4 is supplied to the power transmission system via a circuit breaker 5. Power control in this gas turbine power plant is performed by a fuel regulating valve 6.
次に、燃焼器２に供給される燃料と空気の比率
（空燃比）とNOx発生量の関係を第６図に示す。
通常の拡散燃焼では、噴射された燃料の周囲の空
気が多くても安定燃焼に必要な空気が使われ、残
りの空気は希釈に使用される。この拡散燃焼は低
燃空比でも安定に燃焼できるが、NOxの発生は
多い。一方、予混合燃焼では予め燃料を空気と混
合しておくため、燃料と空気の混合度が良くな
り、空燃比を希薄にでき、低NOx化が可能とな
る。 Next, FIG. 6 shows the relationship between the ratio of fuel and air (air-fuel ratio) supplied to the combustor 2 and the amount of NOx generated.
In normal diffusion combustion, even if there is a lot of air surrounding the injected fuel, only enough air is used for stable combustion, and the remaining air is used for dilution. Although this diffusion combustion allows stable combustion even at low fuel-air ratios, it generates a lot of NOx. On the other hand, in premix combustion, fuel is mixed with air in advance, so the degree of mixing between fuel and air is improved, the air-fuel ratio can be made lean, and NOx can be reduced.
そこで、実際の燃焼器では、低空燃比域で安定
性の高い拡散燃焼を用い、高空燃比域で低NOx
化が可能な予混合燃焼を追加し、低空燃比域から
高空燃比域までNOx量を一定値以下に抑制する
という手法をとる。この様な制御方式を空熱比を
パラメータとして示すと第７図の如くなる。 Therefore, in actual combustors, diffusion combustion, which is highly stable in the low air-fuel ratio range, is used, and NOx is reduced in the high air-fuel ratio range.
The method is to add premixed combustion that can be used to reduce the amount of NOx below a certain value from the low air-fuel ratio range to the high air-fuel ratio range. FIG. 7 shows such a control system using the air/heat ratio as a parameter.
第７図ｂにおいて、F1は拡散燃焼を行うため
の燃料の変化、F2は予混合燃焼を行うための燃
料の変化を示したものである。この第７図ａ，ｂ
からわかるように、低空燃比域における拡散燃焼
によつて空燃比の増大に伴ないNOxの発生量が
増加する。そこで、規制すべきNOxの発生量の
臨界点において、供給する燃料の一部を予混合燃
焼に初換える。その比率は第７図ａでは約１／２
に設定している。この切換えにより、第７図ｂの
ように、高空燃比域でのNOx発生量を規制値以
下に下げることができる。 In FIG. 7b, F 1 shows the change in fuel for performing diffusion combustion, and F 2 shows the change in fuel for performing premix combustion. This figure 7 a, b
As can be seen, the amount of NOx generated increases as the air-fuel ratio increases due to diffusion combustion in the low air-fuel ratio region. Therefore, at a critical point in the amount of NOx that should be regulated, a portion of the supplied fuel is switched to premix combustion for the first time. The ratio is approximately 1/2 in Figure 7a.
It is set to . By this switching, as shown in FIG. 7b, the amount of NOx generated in the high air-fuel ratio region can be lowered to below the regulation value.
ところで、このような低NOx化のための２段
燃焼構造の燃焼器においては、燃焼室が前段側、
後段側の二つに分かれており、基幹燃料配管を二
つに分岐して各燃焼室に配設する構成をとる。こ
の場合、従来では前記基幹燃料配管に一つの燃料
流量調整弁を設け、この燃料流量調整弁により燃
料を制御し、したがつて発電量を制御するもので
あつた。そのため、第２段（後段）燃料投入時に
第２段燃料ノズル分の開口面積が増えることとな
つて燃料流量に影響を与え、結果的には電力系統
へ負荷変動をもたらすこととなるものであつた。 By the way, in such a combustor with a two-stage combustion structure for reducing NOx, the combustion chamber is located on the front stage side,
It is divided into two on the rear stage side, and the main fuel pipe is branched into two and installed in each combustion chamber. In this case, conventionally, one fuel flow regulating valve was provided in the main fuel pipe, and this fuel flow regulating valve controlled the fuel and therefore the amount of power generation. Therefore, when the second stage (latter stage) fuel is injected, the opening area for the second stage fuel nozzle increases, which affects the fuel flow rate and ultimately causes load fluctuations to the power system. Ta.
なお、上記公知技術は燃焼器単体としての低
NOx化技術であり、発電所に設置されて電力系
統の一部として負荷制御を行う場合の燃料系統お
よびその具体的な制御方法については検討されて
いない。 In addition, the above-mentioned known technology has a low
This is a NOx reduction technology, and the fuel system and its specific control method when installed in a power plant and performs load control as part of the power system have not been studied.
本発明の目的は拡散燃焼、予混合燃焼の二つの
燃焼方式を用いた燃焼器を有するガスタービンに
おいて、電力系統へ負荷変動を与えない燃料制御
装置を提供することにある。
An object of the present invention is to provide a fuel control device that does not cause load fluctuations to the electric power system in a gas turbine that has a combustor that uses two combustion methods: diffuse combustion and premix combustion.
上記目的を達成するために、第１の発明は、基
幹燃料配管を２系統に分岐し、前段側燃焼室には
ガス燃料を低空燃比域で拡散燃焼させる第１段の
燃料を投入し、後段側燃焼室には高空燃比域でガ
ス燃料と空気とを予め混合して燃焼させる第２段
の燃料を追加して投入し、拡散燃焼と予混合燃焼
とを組み合わせて行う２段燃焼構造を有する発電
機ガスタービン燃焼器の、各燃焼室に供給するガ
ス燃料の流量を制御するガスタービンの燃料制御
装置において、前記分岐配管のそれぞれに、上流
側に燃料圧力調整弁を、後流側に燃料流量調整弁
を独立して設け、トータル燃料要求値と燃料室空
気量とに基づく空燃比、或いは発電機出力から第
１及び第２段の燃料要求値を求め、これらの値に
よつて第１及び第２段側の前記燃料流量調整弁を
制御するとともに、前記ガスタービンの実回転数
に基づく圧力設定値により第１及び第２段側の前
記燃料圧力調整弁を制御することにより、拡散燃
焼から予混合燃焼を投入する際、およびそれ以降
の燃料供給の変動を防止するようにしたものであ
る。
In order to achieve the above object, the first invention branches the main fuel piping into two systems, injects the first-stage fuel that diffusely burns gas fuel in a low air-fuel ratio region into the front-stage combustion chamber, and A second stage of fuel is added to the side combustion chamber in which gas fuel and air are pre-mixed and combusted in a high air-fuel ratio range, resulting in a two-stage combustion structure that combines diffusion combustion and premix combustion. In a gas turbine fuel control device that controls the flow rate of gas fuel supplied to each combustion chamber of a generator gas turbine combustor, each of the branch pipes has a fuel pressure regulating valve on the upstream side and a fuel pressure regulating valve on the downstream side. A flow rate adjustment valve is provided independently, and the first and second stage fuel requirements are determined from the air-fuel ratio based on the total fuel requirement value and the fuel chamber air amount, or from the generator output, and these values are used to determine the first and second stage fuel requirements. By controlling the fuel flow rate regulating valve on the second stage side and controlling the fuel pressure regulating valve on the first and second stage sides with a pressure setting value based on the actual rotation speed of the gas turbine, diffusion combustion is achieved. This is to prevent fluctuations in fuel supply when starting premix combustion and thereafter.
第２の発明は、基幹燃料配管を２系統に分岐
し、前段側燃焼室にはガス燃料を低空燃比域で拡
散燃焼させる第１段の燃料を投入し、後段側燃焼
室には高空燃比域でガス燃料と空気とを予め混合
して燃焼させる第２段の燃料を追加して投入し、
拡散燃焼と予混合燃焼とを組み合わせて行う２段
燃焼構造を有する発電機ガスタービン燃焼器の、
各燃焼室に供給するガス燃料の流量を制御するガ
スタービンの燃料制御装置において、前記基幹燃
料配管に上流側に燃料圧力調整弁を、後流側に燃
料流量調整弁を独立して設け、且つ前記分岐配管
のいずれか一方に燃料流量調整弁を設け、トータ
ル燃料要求値により前記基幹燃料配管に設けた燃
料流量調整弁を制御するとともに、トータル燃料
要求値と燃料室空気量とに基づく空燃比、或いは
発電機出力から第１又は第２段側の燃料要求値を
求め、この値によつて前記分岐配管に設けた燃料
流量調整弁を制御し、前記ガスタービンの実回転
数に基づく圧力設定値により前記燃料圧力調整弁
を制御することにより、拡散燃焼に予混合燃焼を
投入することによる燃料供給の変動を防止するよ
うにしたものである。 The second invention branches the main fuel piping into two systems, injects the first-stage fuel that diffusely burns gas fuel in a low air-fuel ratio region into the front-stage combustion chamber, and injects the first-stage fuel that diffusely burns gas fuel in a low air-fuel ratio region into the rear-stage combustion chamber. Add and inject the second stage fuel which pre-mixes gas fuel and air and combusts it.
A generator gas turbine combustor with a two-stage combustion structure that combines diffusion combustion and premix combustion.
In a fuel control device for a gas turbine that controls the flow rate of gas fuel supplied to each combustion chamber, the main fuel pipe is independently provided with a fuel pressure adjustment valve on the upstream side and a fuel flow rate adjustment valve on the downstream side, and A fuel flow regulating valve is provided on either one of the branch pipes, and the fuel flow regulating valve provided in the main fuel pipe is controlled according to the total fuel demand value, and the air-fuel ratio is controlled based on the total fuel demand value and the fuel chamber air amount. Alternatively, a fuel requirement value on the first or second stage side is determined from the generator output, and this value is used to control a fuel flow rate regulating valve provided in the branch pipe, and pressure setting is performed based on the actual rotation speed of the gas turbine. By controlling the fuel pressure regulating valve according to the value, fluctuations in fuel supply due to input of premix combustion into diffusion combustion are prevented.
次に、本願の各発明の実施例を図面に基づいて
説明する。
Next, embodiments of each invention of the present application will be described based on the drawings.
−第１発明−
まず、第１図に第１発明の実施例を示す。第１
図に示すように、燃焼器２の頭部に第１段燃焼室
が設けられ、その後流側に第２段燃焼器が形成さ
れている。図示しないが、第１、第２の各燃焼室
にはそれぞれ燃料噴射ノズルが設けられている。
そして、各燃料噴射ノズルには、基幹燃料配管１
０から二つに分岐された第１、第２の分岐配管２
０，３０が配設されている。-First invention- First, FIG. 1 shows an embodiment of the first invention. 1st
As shown in the figure, a first stage combustion chamber is provided at the head of the combustor 2, and a second stage combustor is formed on the downstream side. Although not shown, each of the first and second combustion chambers is provided with a fuel injection nozzle.
Each fuel injection nozzle has a main fuel pipe 1.
First and second branch piping 2 branched into two from 0
0,30 are arranged.
第１分岐配管２０には、上流側より第１オリフ
イス１０１および第１流量発振器１０２からなる
流量計、第１圧力調整弁１０３、第１圧力発振器
１０５、および第１流量調整弁１０４が設けられ
ている。 The first branch pipe 20 is provided with, from the upstream side, a flow meter consisting of a first orifice 101 and a first flow oscillator 102, a first pressure regulating valve 103, a first pressure oscillator 105, and a first flow regulating valve 104. There is.
第２分岐配管３０には、同様に、上流側より第
２オリフイス１０６および第２流量発振器１０７
からなる流量計、第２圧力調整弁１０８、第２圧
力発振器１０９、および第２流量調整弁１１０が
それぞれ設けられている。 Similarly, the second branch pipe 30 includes a second orifice 106 and a second flow rate oscillator 107 from the upstream side.
A flow meter consisting of a second pressure regulating valve 108, a second pressure oscillator 109, and a second flow regulating valve 110 are each provided.
以上の構成において、基幹燃料配管１０から送
給される燃料流量（トータル燃料値）をF0、第
１分岐配管２０を経て第１段燃焼室の噴射ノズル
から噴射される拡散燃焼用燃料流量（以下、第１
段燃料値）をF1、第２分岐配管３０を経て第２
段燃焼室の噴射ノズルから噴射される予混合燃焼
用燃料流量（以下、第２段燃焼値）をF2で示す。 In the above configuration, the fuel flow rate (total fuel value) fed from the main fuel pipe 10 is F 0 , and the diffusion combustion fuel flow rate ( Below, the first
stage fuel value) to F 1 and the second branch pipe 30 to the second
The premix combustion fuel flow rate (hereinafter referred to as second stage combustion value) injected from the injection nozzle of the stage combustion chamber is indicated by F2 .
このような系統において燃料量のトータル要求
値であるいわゆるガバナ信号は一つであるので、
このガバナ信号を第１段側の燃料値F1および第
２段側の燃料値F2に割り振る必要がある。第２
図に上記燃料系統における制御ブロツク図を示
す。 In such a system, there is only one so-called governor signal, which is the total required value of fuel quantity, so
It is necessary to allocate this governor signal to the fuel value F 1 on the first stage side and the fuel value F 2 on the second stage side. Second
The figure shows a control block diagram of the above fuel system.
第２図において、ガバナよりのトータル燃料要
求値F0と測定された室空気量Ａから、演算要素
１３０によつて空燃比を演算する。その関数を
f4(x)で示す。求められた空燃比から演算要素１２
１によつて第１段燃料値F1と第２段燃料値F2の
比（F1／F2）を算出する。ここで、F1／F2を算
出するには空燃比が最適であるが、排出NOx量
の精度を気にしなくても良い場合は空燃比の代り
に発電機出力を用いることができる。この関数は
第７図の燃料比率と同じである。次に演算要素１
２２においてトータル燃料値F0とF1／F2から第
２段燃料値F2のみを算出する。この算出された
第２段燃料値F2が第２流量調整弁１１０に対す
る燃量要求信号となる。ここで演算要素１２２に
おける演算式は(1)式で表わされる。 In FIG. 2, the air-fuel ratio is calculated by the calculation element 130 from the total fuel demand value F 0 from the governor and the measured room air amount A. that function
Denote by f 4(x) . Calculation element 12 is calculated from the obtained air-fuel ratio.
1 to calculate the ratio (F 1 /F 2 ) between the first stage fuel value F 1 and the second stage fuel value F 2 . Here, the air-fuel ratio is optimal for calculating F 1 /F 2 , but if the accuracy of the exhaust NOx amount is not a concern, the generator output can be used instead of the air-fuel ratio. This function is the same as the fuel ratio in FIG. Next, calculation element 1
In step 22, only the second stage fuel value F2 is calculated from the total fuel value F0 and F1 / F2 . This calculated second stage fuel value F 2 becomes the fuel amount request signal for the second flow rate regulating valve 110 . Here, the arithmetic expression in the arithmetic element 122 is expressed by equation (1).
F2＝F0／１＋F1／F2 …(1)
次に演算要素１２３はトータル燃料値F0と上
記算出された第２段燃料値F2より第１流量調整
弁１０４に対する燃量要求信号であるF1を次の
(2)式により算出する。 F 2 = F 0 /1 + F 1 /F 2 (1) Next, the calculation element 123 generates a fuel demand signal to the first flow rate regulating valve 104 from the total fuel value F 0 and the second stage fuel value F 2 calculated above. Let F 1 be the following
Calculated using formula (2).
F1＝F0−F2 …(2)
これらの燃料要求値F1，F2は加算演算器１２
４，１２７において、各流量発振器１０２，１０
７により検出された実流量F1，F2と比較される。
得られた偏差値は演算器１２５，１２８により比
例（Ｐ）−積分(I)演算され、その制御信号がサー
ボ弁ドライバ１２６，１２９に与えられる。その
操作信号により第１、第２の燃料調整弁１０４，
１１０が制御される。 F 1 =F 0 −F 2 …(2) These fuel requirement values F 1 and F 2 are calculated by the addition calculator 12
4,127, each flow oscillator 102,10
The flow rate is compared with the actual flow rates F 1 and F 2 detected by 7.
The obtained deviation values are subjected to proportional (P)-integral (I) calculations by calculation units 125 and 128, and the control signals thereof are given to servo valve drivers 126 and 129. The operation signal causes the first and second fuel adjustment valves 104,
110 is controlled.
第１圧力調整弁１０３は起動時の第１流量調整
弁１０４の弁開度を大きくして制御性を良くする
ために、ガスタービン回転数に比例させて第１流
量調整弁１０４の後圧制御を行うものである。Ｎ
はガスタービン実回転数を示し、演算器１４１に
より比例演算（Ｋは比例ゲイン）を行い、加算要
素１４２でバイアスを加えたものを圧力設定値と
する。この設定値は第１流量調整弁１０４の後の
圧力発振器１０５で検出した実圧力P21と加算要
素１４３で比較される。得られた偏差値は演算器
１４４により比例積分演算され、得られた制御信
号はサーボ弁ドライバー１４５により操作信号に
変換されて第１圧力調整弁１０３を制御する。 The first pressure regulating valve 103 controls the afterpressure of the first flow regulating valve 104 in proportion to the gas turbine rotation speed in order to increase the valve opening degree of the first flow regulating valve 104 at startup and improve controllability. This is what we do. N
indicates the actual rotational speed of the gas turbine, a proportional calculation is performed by the calculating unit 141 (K is a proportional gain), and a bias is added by the addition element 142 to obtain the pressure set value. This set value is compared with the actual pressure P 21 detected by the pressure oscillator 105 after the first flow rate regulating valve 104 by the addition element 143 . The obtained deviation value is subjected to a proportional integral calculation by the calculator 144, and the obtained control signal is converted into an operation signal by the servo valve driver 145 to control the first pressure regulating valve 103.
第２圧力調整弁はガスタービンが定格回転数と
なつてから第２流量調整弁１１０を制御するため
の定値制御で良い。圧力設定値は設定器１５１に
より設定され（SGは定数）、第２圧力調整弁１０
８の圧力発振器１０９で検出された実後圧力P22
と加算要素１５２により比較される。得られた偏
差値は演算器１５３により比例積分演算され、そ
の制御信号はサーボ弁ドライバ１５４によつて操
作信号に変換されて第２圧力調整弁１０８を制御
する。 The second pressure regulating valve may be a constant value control for controlling the second flow regulating valve 110 after the gas turbine reaches the rated rotation speed. The pressure setting value is set by the setting device 151 (SG is a constant), and the second pressure regulating valve 10
Actual pressure P 22 detected by pressure oscillator 109 of No. 8
is compared by addition element 152. The obtained deviation value is subjected to proportional-integral calculation by the calculator 153, and the control signal is converted into an operation signal by the servo valve driver 154 to control the second pressure regulating valve 108.
本実施例によれば、第１圧力調整弁１０３、第
２圧力調整弁１０８の後圧を各々制御しているた
めに、第１段燃料値F1、第２段燃料値F2を独立
に制御できるので、負荷運転の途中で第２段燃料
F2を投入するときに第２段燃焼室のノズル開口
面積の増大によりF1流量が影響されることがな
いため負荷変動を与えずNOx低減が可能である。 According to this embodiment, since the after pressures of the first pressure regulating valve 103 and the second pressure regulating valve 108 are controlled respectively, the first stage fuel value F 1 and the second stage fuel value F 2 are independently controlled. Since it can be controlled, the second stage fuel is removed during load operation.
Since the F 1 flow rate is not affected by the increase in the nozzle opening area of the second stage combustion chamber when F 2 is introduced, NOx can be reduced without causing load fluctuations.
−第２発明−
次に、第３図に第２発明の実施例を示す。第３
図において燃焼器２、第１、第２段燃焼室、各噴
射ノズルの配置、燃料配管の構成については同様
であり、同一部分には同一の符号を附してその詳
細な説明は省略する。-Second invention- Next, FIG. 3 shows an embodiment of the second invention. Third
In the figures, the combustor 2, the first and second stage combustion chambers, the arrangement of each injection nozzle, and the configuration of the fuel piping are the same, and the same parts are given the same reference numerals and detailed explanations thereof will be omitted.
基幹燃料配管１０には、上流側から第１オリフ
イス２０１および第１流量発振器２０５からなる
流量計、圧力調整弁２０２、圧力発振器２０６、
および第１流量調整弁２０３が設けられている。 The main fuel pipe 10 includes, from the upstream side, a flow meter consisting of a first orifice 201 and a first flow oscillator 205, a pressure regulating valve 202, a pressure oscillator 206,
and a first flow rate regulating valve 203 are provided.
第２分岐配管３０には、第２オリフイス２０４
および第２流量発振器２０７からなる流量計、第
２流量調整弁２０８が設けられている。なお、こ
れら第２オリフイス２０４、第２流量発振器２０
７、第２流量調整弁２０８は第１分岐配管２０に
設けてもよい。F0はトータル燃料値、F1は第１
段燃料値、F2は第２段燃料値を示し、第１段燃
料値F1が拡散燃焼用、第２段燃料値F2が予混合
燃焼用であることは第１図の実施例と同じであ
る。 The second branch pipe 30 has a second orifice 204.
A flow meter consisting of a second flow rate oscillator 207 and a second flow rate regulating valve 208 are provided. Note that these second orifices 204 and second flow rate oscillators 20
7. The second flow rate regulating valve 208 may be provided in the first branch pipe 20. F 0 is the total fuel value, F 1 is the first
The stage fuel value F 2 indicates the second stage fuel value, and the fact that the first stage fuel value F 1 is for diffusion combustion and the second stage fuel value F 2 is for premix combustion is similar to the embodiment shown in FIG. It's the same.
第４図に本燃料制御系統における制御ブロツク
図を示す。本実施例では第１流量調整弁２０３は
トータル燃料流量F0を制御し、第２流量調整弁
２０８は第１段燃料値F1と第２段燃料値F2の燃
料分割化を制御する。 FIG. 4 shows a control block diagram of this fuel control system. In this embodiment, the first flow rate adjustment valve 203 controls the total fuel flow rate F 0 , and the second flow rate adjustment valve 208 controls fuel division of the first stage fuel value F 1 and the second stage fuel value F 2 .
まず、第２流量調整弁２０８の制御について説
明する。 First, control of the second flow rate regulating valve 208 will be explained.
演算要素（関数g3(x)）２２１は実トータル燃料
F0と実空気流量A0から空燃比を算出する。次い
で、演算要素（関数g1(x)）２２０は算出された空
燃比から第１段燃料値F1と第２段燃料値F2との
比（F1／F2）を算出する。本実施例でも空燃比
の代りに発電機出力を用いることができる。この
関数は第１図の燃料比率と同じである。演算要素
（関数g3 (x)）２２２は実トータル燃料F0とF1／F2
から第２段燃料値F2のみを算出する。g2(x)は前述
の(2)式で表わされる。第２段燃料流量値F2は実
燃料流量F2と可算要素２２３において比較され、
演算器２２４により比例、積分演算され、サーボ
弁ドライバ２２５を介して第２流量調整弁２０８
を制御する。 The calculation element (function g3 (x) ) 221 is the actual total fuel
Calculate the air-fuel ratio from F 0 and actual air flow rate A 0 . Next, the calculation element (function g 1(x) ) 220 calculates the ratio (F 1 /F 2 ) between the first stage fuel value F 1 and the second stage fuel value F 2 from the calculated air-fuel ratio. Also in this embodiment, the generator output can be used instead of the air-fuel ratio. This function is the same as the fuel ratio in FIG. The calculation element (function g 3 (x) ) 222 is the actual total fuel F 0 and F 1 /F 2
From this, only the second stage fuel value F2 is calculated. g 2(x) is expressed by equation (2) above. The second stage fuel flow value F2 is compared with the actual fuel flow rate F2 at countable element 223;
Proportional and integral calculations are performed by the calculator 224, and the second flow rate regulating valve 208 is operated via the servo valve driver 225.
control.
その結果、F1＝F0−F2であるのでトータル燃
料値F0、第２段燃料値F2を制御すれば第１段燃
料値F1は自ずと定まる。 As a result, since F 1 =F 0 −F 2 , the first stage fuel value F 1 is automatically determined by controlling the total fuel value F 0 and the second stage fuel value F 2 .
本実施例の燃料系統では、第２流量調整弁２０
８が負荷運転中に開いたときに、第２段燃料値
F2分のノズルの開口面積が増えるため第１流量
調整弁２０３の後圧が下がる。トータル流量F0
は圧力調整弁２０２の後圧、第１流量制御弁２０
３の後圧およびその開度で定まるため、第１流量
調整弁２０３の後圧が下がるとトータル流量F0
が増加し負荷電圧を引き起こしてしまう。これを
防止するため圧力調整弁２０２は第２流量調整弁
２０８の実燃料流量F2により補正を行う。なお、
この補正は実燃料流量F2ではなく、第２流量調
整弁２０８の開度調整によつても可能である。 In the fuel system of this embodiment, the second flow rate regulating valve 20
8 opens during load operation, the second stage fuel value
Since the opening area of the nozzle for F2 increases, the back pressure of the first flow rate regulating valve 203 decreases. Total flow rate F 0
is the back pressure of the pressure regulating valve 202, the first flow control valve 20
Since it is determined by the after pressure of 3 and its opening degree, when the after pressure of the first flow rate adjustment valve 203 decreases, the total flow rate F 0
increases, causing load voltage. In order to prevent this, the pressure regulating valve 202 performs a correction based on the actual fuel flow rate F 2 of the second flow regulating valve 208 . In addition,
This correction can also be made by adjusting the opening degree of the second flow rate regulating valve 208 instead of the actual fuel flow rate F2 .
圧力調整弁２０２の制御は次のようになる。ガ
スタービン回転数Ｎに基づき演算要素２２６によ
り比例演算（Ｋは比例ゲイン）を行い、これに演
算要素（関数g3(x)）２２８により前述の実燃料流
量F2による補正を加えて圧力調整弁２０２の後
圧の設定値とする。そして、この設定値と、実圧
力P2とを加算要素２３０で比較する。その偏差
値について演算器２３１により比例積分演算を行
い、サーボ弁ドライバ２３２を介して圧力調整弁
２０２を制御する。 The pressure regulating valve 202 is controlled as follows. A calculation element 226 performs a proportional calculation (K is a proportional gain) based on the gas turbine rotation speed N, and a calculation element (function g 3(x) ) 228 adds correction based on the aforementioned actual fuel flow rate F 2 to adjust the pressure. This is the set value of the after pressure of the valve 202. Then, this set value and the actual pressure P 2 are compared by the addition element 230. The calculation unit 231 performs a proportional integral calculation on the deviation value, and the pressure regulating valve 202 is controlled via the servo valve driver 232.
第１流量調整弁２０３はトータル流量F0を制
御するため、従来のガバナの制御信号を用いれば
よく、サーボ弁ドライバ２５３によつて制御され
る。 In order to control the total flow rate F 0 , the first flow rate regulating valve 203 may use a conventional governor control signal and is controlled by a servo valve driver 253 .
本実施例によれば第１の実施例で必要であつた
第２流量調整弁（第１図）の前側の第２圧力調整
弁１０８が不要である。また、ガバナの制御信号
が従来のものをそのまま使用できる。その上、第
２段燃料投入時の負荷変動を抑えることができ
る。 According to this embodiment, the second pressure regulating valve 108 on the front side of the second flow regulating valve (FIG. 1), which was necessary in the first embodiment, is unnecessary. Furthermore, the conventional governor control signal can be used as is. Moreover, load fluctuations during second-stage fuel injection can be suppressed.
第１及び第２の発明明によれば、分岐配管それ
ぞれのガス燃料の流量を制御できるので、燃料切
換時の負荷変動を防止することができる。
According to the first and second aspects of the invention, the flow rate of gas fuel in each branch pipe can be controlled, so load fluctuations during fuel switching can be prevented.
また、そのために、負荷変動をもたらすことな
く排気ガス中のNOxを低減する効果がある。 Furthermore, this has the effect of reducing NOx in exhaust gas without causing load fluctuations.
第１図は第１発明の一実施例の燃料系統図、第
２図は第１発明の一実施例の制御ブロツク図、第
３図は第２発明の実施例の燃料系統図、第４図は
第２発明の実施例の制御ブロツク図、第５図はガ
スタービン発電所の主要機器構成図、第６図は空
燃比とNOx発生量を示す説明図、第７図は制御
の概要を示す説明図である。
１…空気圧縮機、２…燃焼器、３…タービン、
４…発電機、５…遮断器、６…燃料調整弁、１０
１…第１オリフイス、１０２…第１流量発信器、
１０３…第１圧力調整弁、１０４…第１流量調整
弁、１０５…第１圧力発信器、１０６…第２オリ
フイス、１０７…第２流量発信器、１０８…第２
圧力調整弁、１０９…第２圧力発信器、１１０…
第２流量調整弁、１２１…演算要素、１２２…演
算要素、１２３…演算要素、１２４…加算要素、
１２５…比例積分演算器、１２６…サーボ弁ドラ
イバ、１２７…加算点、１２８…比例積分演算
器、１２９…サーボ弁ドライバ、１３０…演算要
素、１４１…比例演算器、１４２…加算要素、１
４３…加算要素、１４４…比例積分演算、１４５
…サーボ弁ドライバ、１５１…設定器、１５２…
加算要素、１５３…比例積分演算器、１５４…サ
ーボ弁ドライバ、２０１…第１オリフイス、２０
２…圧力調整弁、２０３…第１流量調整弁、２０
４…第２オリフイス、２０５…第２流量発信器、
２０６…第２圧力発信器、２０７…第２流量発信
器、２２０…演算要素、２２１…演算要素、２２
２…演算要素、２２３…加算要素、２２４…比例
積分演算器、２２５…サーボ弁ドライバ、２２６
…比例演算要素、２２７…加算要素、２２８…演
算要素、２２９…加算要素、２３０…加算要素、
２３１…比例積分演算要素、２３２…サーボ弁ド
ライバ、２３３…サーボ弁ドライバ。
FIG. 1 is a fuel system diagram of an embodiment of the first invention, FIG. 2 is a control block diagram of an embodiment of the first invention, FIG. 3 is a fuel system diagram of an embodiment of the second invention, and FIG. is a control block diagram of the embodiment of the second invention, FIG. 5 is a diagram of the main equipment configuration of the gas turbine power plant, FIG. 6 is an explanatory diagram showing the air-fuel ratio and NOx generation amount, and FIG. 7 is an overview of the control. It is an explanatory diagram. 1...Air compressor, 2...Combustor, 3...Turbine,
4... Generator, 5... Circuit breaker, 6... Fuel adjustment valve, 10
1...first orifice, 102...first flow transmitter,
103...First pressure regulating valve, 104...First flow regulating valve, 105...First pressure transmitter, 106...Second orifice, 107...Second flow transmitter, 108...Second
Pressure regulating valve, 109...Second pressure transmitter, 110...
2nd flow rate adjustment valve, 121... calculation element, 122... calculation element, 123... calculation element, 124... addition element,
125... Proportional integral calculator, 126... Servo valve driver, 127... Addition point, 128... Proportional integral calculator, 129... Servo valve driver, 130... Calculating element, 141... Proportional calculating unit, 142... Adding element, 1
43... Addition element, 144... Proportional integral operation, 145
...Servo valve driver, 151...Setter, 152...
Addition element, 153... Proportional integral calculator, 154... Servo valve driver, 201... First orifice, 20
2...Pressure regulating valve, 203...First flow regulating valve, 20
4...Second orifice, 205...Second flow transmitter,
206...Second pressure transmitter, 207...Second flow rate transmitter, 220...Calculation element, 221...Calculation element, 22
2... Arithmetic element, 223... Addition element, 224... Proportional integral calculator, 225... Servo valve driver, 226
...proportional calculation element, 227... addition element, 228... calculation element, 229... addition element, 230... addition element,
231... Proportional integral calculation element, 232... Servo valve driver, 233... Servo valve driver.
Claims (1)
室にはガス燃料を低空燃比域で拡散燃焼させる第
１段の燃料を投入し、後段側燃焼室には高空燃比
域でガス燃料と空気とを予め混合して燃焼させる
第２段の燃料を追加して投入し、拡散燃焼と予混
合燃焼とを組み合わせて行う２段燃焼構造を有す
る発電機ガスタービン燃焼器の、各燃焼室に供給
するガス燃料の流量を制御するガスタービンの燃
料制御装置において、 前記分岐配管のそれぞれに、上流側に燃料圧力
調整弁を、後流側に燃料流量調整弁を独立して設
け、トータル燃料要求値と燃料室空気量とに基づ
く空燃比、或いは発電機出力から第１及び第２段
の燃料要求値を求め、これらの値によつて第１及
び第２段側の前記燃料流量調整弁を制御するとと
もに、前記ガスタービンの実回転数に基づく圧力
設定値により第１及び第２段側の前記燃料圧力調
整弁を制御することを特徴とするガスタービンの
燃料制御装置。 ２ 基幹燃料配管を２系統に分岐し、前段側燃焼
室にはガス燃料を低空燃比域で拡散燃焼させる第
１段の燃料を投入し、後段側燃焼室には高空燃比
域でガス燃料と空気とを予め混合して燃焼させる
第２段の燃料を追加して投入し、拡散燃焼と予混
合燃焼とを組み合わせて行う２段燃焼構造を有す
る発電機ガスタービン燃焼器の、各燃焼室に供給
するガス燃料の流量を制御するガスタービンの燃
料制御装置において、 前記基幹燃料配管に上流側に燃料圧力調整弁
を、後流側に燃料流量調整弁を独立して設け、且
つ前記分岐配管のいずれか一方に燃料流量調整弁
を設け、トータル燃料要求値により前記基幹燃料
配管に設けた燃料流量調整弁を制御するととも
に、トータル燃料要求値と燃料室空気量とに基づ
く空燃比、或いは発電機出力から第１又は第２段
側の燃料要求値を求め、この値によつて前記分岐
配管に設けた燃料流量調整弁を制御し、前記ガス
タービンの実回転数に基づく圧力設定値により前
記燃料圧力調整弁を制御することを特徴とするガ
スタービンの燃料制御装置。[Scope of Claims] 1. The main fuel piping is branched into two systems, and the first-stage fuel that diffusely burns gaseous fuel in a low air-fuel ratio region is input into the first-stage combustion chamber, and the second-stage fuel is charged into the second-stage combustion chamber with a high air-fuel ratio. This is a generator gas turbine combustor with a two-stage combustion structure that combines diffusion combustion and premix combustion by adding second-stage fuel that premixes gas fuel and air and combusts the mixture. , in a fuel control device for a gas turbine that controls the flow rate of gas fuel supplied to each combustion chamber, in each of the branch pipes, a fuel pressure regulating valve is independently provided on the upstream side, and a fuel flow regulating valve is independently provided on the downstream side. The fuel requirement values for the first and second stages are determined from the air-fuel ratio based on the total fuel requirement value and the fuel chamber air amount, or from the generator output, and these values are used to determine the fuel requirement values for the first and second stages. A fuel control device for a gas turbine, characterized in that it controls a fuel flow rate regulating valve and also controls the fuel pressure regulating valves on the first and second stage sides based on a pressure setting value based on the actual rotational speed of the gas turbine. 2 The main fuel piping is branched into two systems, and the first-stage fuel, which diffusely burns gas fuel in a low air-fuel ratio range, is input into the front-stage combustion chamber, and the gas fuel and air are injected into the rear-stage combustion chamber at a high air-fuel ratio range. A second-stage fuel that is premixed and combusted is added and supplied to each combustion chamber of the generator gas turbine combustor, which has a two-stage combustion structure that combines diffusion combustion and premix combustion. In a fuel control device for a gas turbine that controls the flow rate of gas fuel, the main fuel pipe is independently provided with a fuel pressure regulating valve on the upstream side and a fuel flow regulating valve on the downstream side, and any of the branch pipes is provided with a fuel pressure regulating valve on the upstream side and a fuel flow regulating valve on the downstream side. A fuel flow rate adjustment valve is provided on one side, and the fuel flow rate adjustment valve provided in the main fuel pipe is controlled based on the total fuel requirement value, and the air-fuel ratio or generator output is controlled based on the total fuel requirement value and the fuel chamber air amount. The fuel demand value on the first or second stage side is determined from A fuel control device for a gas turbine, characterized in that it controls a regulating valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9898885A JPS61258929A (en) | 1985-05-10 | 1985-05-10 | Fuel controller for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9898885A JPS61258929A (en) | 1985-05-10 | 1985-05-10 | Fuel controller for gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS61258929A JPS61258929A (en) | 1986-11-17 |
| JPH0350089B2 true JPH0350089B2 (en) | 1991-07-31 |
Family
ID=14234374
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP9898885A Granted JPS61258929A (en) | 1985-05-10 | 1985-05-10 | Fuel controller for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS61258929A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2758301B2 (en) * | 1991-11-29 | 1998-05-28 | 株式会社東芝 | Gas turbine combustor |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS556973A (en) * | 1978-06-30 | 1980-01-18 | Victor Co Of Japan Ltd | Indication unit for interference distortion amount of eliminating device for interference distortion occurring in modulation signal due to mutual interference of fm wave signal |
| JPS5569732A (en) * | 1978-11-22 | 1980-05-26 | Hitachi Ltd | Fuel system of gas turbine intended for long continuous use |
| JPS5741524A (en) * | 1980-08-25 | 1982-03-08 | Hitachi Ltd | Combustion method of gas turbine and combustor for gas turbine |
| JPS5847232U (en) * | 1981-09-29 | 1983-03-30 | 株式会社日乃本錠前 | Trunk and bag handles |
| JPS5880422A (en) * | 1981-11-02 | 1983-05-14 | ウエスチングハウス エレクトリック コ−ポレ−ション | Combustor for combustion turbine device |
| JPS6057131A (en) * | 1983-09-08 | 1985-04-02 | Hitachi Ltd | Fuel feeding process for gas turbine combustor |
-
1985
- 1985-05-10 JP JP9898885A patent/JPS61258929A/en active Granted
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS556973A (en) * | 1978-06-30 | 1980-01-18 | Victor Co Of Japan Ltd | Indication unit for interference distortion amount of eliminating device for interference distortion occurring in modulation signal due to mutual interference of fm wave signal |
| JPS5569732A (en) * | 1978-11-22 | 1980-05-26 | Hitachi Ltd | Fuel system of gas turbine intended for long continuous use |
| JPS5741524A (en) * | 1980-08-25 | 1982-03-08 | Hitachi Ltd | Combustion method of gas turbine and combustor for gas turbine |
| JPS5847232U (en) * | 1981-09-29 | 1983-03-30 | 株式会社日乃本錠前 | Trunk and bag handles |
| JPS5880422A (en) * | 1981-11-02 | 1983-05-14 | ウエスチングハウス エレクトリック コ−ポレ−ション | Combustor for combustion turbine device |
| JPS6057131A (en) * | 1983-09-08 | 1985-04-02 | Hitachi Ltd | Fuel feeding process for gas turbine combustor |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS61258929A (en) | 1986-11-17 |
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