JP4627289B2 - Gas turbine and gas turbine combustor start control method - Google Patents

Gas turbine and gas turbine combustor start control method Download PDF

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JP4627289B2
JP4627289B2 JP2006265953A JP2006265953A JP4627289B2 JP 4627289 B2 JP4627289 B2 JP 4627289B2 JP 2006265953 A JP2006265953 A JP 2006265953A JP 2006265953 A JP2006265953 A JP 2006265953A JP 4627289 B2 JP4627289 B2 JP 4627289B2
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JP2008082302A (en
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健治 七瀧
俊文 笹尾
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Hitachi Ltd
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本発明は、ガスタービン及びガスタービンの燃焼器始動制御方法に関する。   The present invention relates to a gas turbine and a combustor start control method for the gas turbine.

従来一般に採用されているガスタービン燃焼器は、圧力制御弁によって流量制御弁前圧（流量制御弁の上流側圧力）を一定の値に保った状態で、圧力制御弁の下流側に設けた流量制御弁によって燃料流量を制御する。この種のものでは、良好な着火性能を確保するために、着火時には圧力制御弁の開度が予め設定された値に保たれるのが通常である（特許文献１等参照）。   The gas turbine combustor that has been generally used in the past is a flow rate provided downstream of the pressure control valve while maintaining the pressure before the flow control valve (upstream pressure of the flow control valve) by the pressure control valve. The fuel flow rate is controlled by a control valve. In this type, in order to ensure good ignition performance, the opening degree of the pressure control valve is usually maintained at a preset value during ignition (see Patent Document 1).

特開平３−２５８９２７号公報JP-A-3-258927

通常、上記のように構成されたガスタービン燃焼器では、着火時は流量制御弁前圧が十分に昇圧していないため、流量制御弁の開度ではなく圧力制御弁の開度で燃料流量が決まる。しかしながら、このようにして着火時の燃料流量が一定に保たれるのに対し、燃料に混合する空気圧縮機からの空気流量は大気温度によって変化する。したがって、大気温度が低下すれば空気流量が増大して着火時の空燃比が下がるため、着火不具合が生じる恐れがある。反対に、大気温度が上昇すれば空気流量が低下して点火時の空燃比が上がるため、燃料温度が上昇し燃焼室やガスパスに臨む高温部品の熱応力が大きくなる可能性がある。   Normally, in the gas turbine combustor configured as described above, the fuel flow rate is not determined by the opening of the flow control valve but the opening of the pressure control valve because the pressure before the flow control valve is not sufficiently increased during ignition. Determined. However, while the fuel flow rate at the time of ignition is kept constant in this way, the air flow rate from the air compressor mixed with the fuel varies depending on the atmospheric temperature. Therefore, if the atmospheric temperature is lowered, the air flow rate is increased and the air-fuel ratio at the time of ignition is lowered, which may cause an ignition failure. On the other hand, if the atmospheric temperature rises, the air flow rate decreases and the air-fuel ratio at the time of ignition rises. Therefore, the fuel temperature rises and there is a possibility that the thermal stress of the high-temperature components facing the combustion chamber and gas path increases.

本発明はこれを鑑みなされたもので、大気温度によらずスムーズに着火することができるガスタービン及びガスタービンの燃焼器始動制御方法を提供することを目的とする。   This invention is made in view of this, and it aims at providing the combustor starting control method of the gas turbine which can be ignited smoothly irrespective of atmospheric temperature.

（１）上記目的を達成するために、本発明のガスタービンは、吸い込んだ空気を圧縮する空気圧縮機と、燃料を供給する燃料供給源と、この燃料供給源からの燃料を昇圧するガス圧縮機、このガス圧縮機からの燃料の圧力を制御する圧力制御弁、この圧力制御弁の下流側で燃料流量を制御する流量制御弁、及び燃料を噴射する燃料ノズルを有し、前記燃料ノズルからの燃料を前記空気圧縮機からの圧縮空気とともに燃焼する燃焼器と、この燃焼器からの燃焼ガスにより回転動力を得るタービンと、前記燃焼器の着火時における前記圧力制御弁の開度を大気温度に応じて変化する設定値で一定に保つ制御装置とを備えたことを特徴とする。   (1) In order to achieve the above object, a gas turbine according to the present invention includes an air compressor that compresses sucked air, a fuel supply source that supplies fuel, and a gas compression that pressurizes fuel from the fuel supply source. A pressure control valve for controlling the pressure of the fuel from the gas compressor, a flow rate control valve for controlling the fuel flow rate downstream of the pressure control valve, and a fuel nozzle for injecting fuel. A combustor that combusts the fuel with compressed air from the air compressor, a turbine that obtains rotational power from the combustion gas from the combustor, and the opening of the pressure control valve when the combustor is ignited. And a control device that keeps constant at a set value that changes according to the above.

（２）上記（１）において、好ましくは、前記圧力制御弁と前記流量制御弁の間に設けられ、前記流量制御弁の上流側の燃料圧力を検出する圧力センサをさらに備え、前記制御装置は、前記燃焼器の着火後、前記圧力センサの検出値が前記流量制御弁の上流側の燃料圧力の目標値に近付くように前記圧力制御弁の開度を制御することを特徴とする。   (2) In the above (1), preferably, the control device further includes a pressure sensor provided between the pressure control valve and the flow rate control valve for detecting a fuel pressure upstream of the flow rate control valve. The opening degree of the pressure control valve is controlled so that the detected value of the pressure sensor approaches the target value of the fuel pressure upstream of the flow control valve after ignition of the combustor.

（３）上記（１）又は（２）において、また好ましくは、前記制御装置は、前記流量制御弁の開度を大気温度に応じて制御することを特徴とする。   (3) In the above (1) or (2), preferably, the control device controls the opening degree of the flow rate control valve in accordance with an atmospheric temperature.

（４）上記目的を達成するために、また本発明は、吸い込んだ空気を圧縮する空気圧縮機と、燃料を供給する燃料供給源と、この燃料供給源からの燃料を昇圧するガス圧縮機、このガス圧縮機からの燃料の圧力を制御する圧力制御弁、この圧力制御弁の下流側で燃料流量を制御する流量制御弁、及び燃料を噴射する燃料ノズルを有し、前記燃料ノズルからの燃料を前記空気圧縮機からの圧縮空気とともに燃焼する燃焼器と、この燃焼器からの燃焼ガスにより回転動力を得るタービンとを備えたガスタービンの燃焼器始動制御方法において、前記燃焼器の着火時における前記圧力制御弁の開度を大気温度に応じて変化する設定値で一定に保つことを特徴とする。   (4) In order to achieve the above object, the present invention also includes an air compressor that compresses sucked air, a fuel supply source that supplies fuel, and a gas compressor that boosts the fuel from the fuel supply source, A pressure control valve for controlling the pressure of fuel from the gas compressor, a flow rate control valve for controlling a fuel flow rate downstream of the pressure control valve, and a fuel nozzle for injecting fuel; In a combustor start-up control method for a gas turbine, comprising: a combustor that combusts together with compressed air from the air compressor; and a turbine that obtains rotational power from combustion gas from the combustor. The opening degree of the pressure control valve is kept constant at a set value that changes according to the atmospheric temperature.

本発明によれば、圧力制御弁の開度を大気温度に応じて決定することにより、着火時の燃料流量を大気温度に応じた値とすることができるので、大気温度によらずガスタービン燃焼器においてスムーズに着火することができる。   According to the present invention, by determining the opening degree of the pressure control valve according to the atmospheric temperature, the fuel flow rate at the time of ignition can be set to a value according to the atmospheric temperature. Can be ignited smoothly in the vessel.

以下に図面を用いて本発明の実施の形態を説明する。
図１は本実施の形態のガスタービンの概略構成を表す概念図である。
図１に示すように、本実施の形態のガスタービンは、吸い込んだ空気を圧縮する空気圧縮機１０、この空気圧縮機１０からの圧縮空気とともに燃料を燃焼する燃焼器２０、この燃焼器２０からの燃焼ガスにより回転動力を得るタービン３０、燃焼器２０に燃料を供給する燃料供給源４０、及び燃焼器２０による燃料流量（燃料噴射量）を制御する制御装置５０を備えている。 Embodiments of the present invention will be described below with reference to the drawings.
FIG. 1 is a conceptual diagram showing a schematic configuration of a gas turbine according to the present embodiment.
As shown in FIG. 1, the gas turbine of the present embodiment includes an air compressor 10 that compresses sucked air, a combustor 20 that combusts fuel together with compressed air from the air compressor 10, and a combustor 20. A turbine 30 that obtains rotational power from the combustion gas of the fuel, a fuel supply source 40 that supplies fuel to the combustor 20, and a control device 50 that controls the fuel flow rate (fuel injection amount) by the combustor 20.

図２は本実施の形態のガスタービンに備えられた燃焼器とその燃料供給系統を表すブロック図である。
燃焼器２０は、図２に示すように、燃料を昇圧するガス圧縮機３、燃料の圧力を制御する圧力制御弁１、燃料の流量を制御する流量制御弁２、及び燃料を噴射する燃料ノズル５を備えている。本実施の形態においては、流量制御弁２として複数の流量制御弁２ａ〜２ｅを設け、各流量制御弁２ａ〜２ｅがそれぞれ対応の燃料ノズル５ａ〜５ｅに接続しているが、流量制御弁２及び燃料ノズル５はそれぞれ一つずつとすることもできる。 FIG. 2 is a block diagram showing the combustor and its fuel supply system provided in the gas turbine of the present embodiment.
As shown in FIG. 2, the combustor 20 includes a gas compressor 3 that boosts the fuel, a pressure control valve 1 that controls the pressure of the fuel, a flow control valve 2 that controls the flow rate of the fuel, and a fuel nozzle that injects the fuel. 5 is provided. In the present embodiment, a plurality of flow control valves 2a to 2e are provided as the flow control valve 2, and each flow control valve 2a to 2e is connected to the corresponding fuel nozzle 5a to 5e. The number of the fuel nozzles 5 may be one.

ガス圧縮機３は、燃料供給源４０から圧力制御弁１への燃料配管の途中に設けられており、圧力制御弁１の下流側にて燃料配管が５つに分岐してそれぞれ各流量制御弁２ａ〜２ｅに接続している。圧力制御弁１と流量制御弁２の間の燃料配管には、流量制御弁前圧（流量制御弁２の上流側の燃料の圧力）を検出する圧力センサ６が設けられている。上記制御装置５０には、図示しない対応のセンサから入力される大気温度やタービン３０の回転数、ガスタービン出力、燃料温度等の検出信号Ｓや圧力センサ６からの流量制御弁前圧Ｐ２が入力される。流量制御弁２の開度は、検出信号Ｓに基づいて制御装置５０により制御される。   The gas compressor 3 is provided in the middle of the fuel pipe from the fuel supply source 40 to the pressure control valve 1, and the fuel pipe branches into five on the downstream side of the pressure control valve 1, and each flow control valve It is connected to 2a to 2e. A fuel pipe between the pressure control valve 1 and the flow control valve 2 is provided with a pressure sensor 6 that detects a pre-flow control valve pressure (fuel pressure upstream of the flow control valve 2). The control device 50 is input with a detection signal S such as the atmospheric temperature, the rotational speed of the turbine 30, the output of the gas turbine, the fuel temperature, etc. input from a corresponding sensor (not shown) and the flow control valve pre-pressure P 2 from the pressure sensor 6. Is done. The opening degree of the flow control valve 2 is controlled by the control device 50 based on the detection signal S.

特に本実施の形態において、制御装置５０は、圧力センサ６により検出された流量制御弁前圧Ｐ２を入力し、Ｐ２が予め定められた目標値に追従するように圧力制御弁１の開度を制御する。また、圧力制御弁１は、着火時には開度を設定開度（一定値）に保つように制御装置５０により制御される。このとき、着火時の圧力制御弁１の設定開度が固定値ではなく、大気温度に応じて決定されることが本実施の形態の大きな特徴である。   Particularly in the present embodiment, the control device 50 inputs the flow control valve pre-pressure P2 detected by the pressure sensor 6, and adjusts the opening of the pressure control valve 1 so that P2 follows a predetermined target value. Control. Further, the pressure control valve 1 is controlled by the control device 50 so as to keep the opening at a set opening (a constant value) at the time of ignition. At this time, a major feature of the present embodiment is that the set opening degree of the pressure control valve 1 at the time of ignition is determined according to the atmospheric temperature instead of a fixed value.

上記構成の本実施の形態に係るガスタービンにおいて、燃焼器２０の着火、すなわち燃焼器２０の始動は次のように行われる。
まず、空気圧縮機１０からの圧縮空気を燃焼空気として燃焼器２０（燃料ノズル５の下流側）に供給する一方で、燃料供給源４０からの燃料をガス圧縮機３に送って燃料を昇圧する。次に、点火栓（図示せず）を燃焼器２０の図示しない燃焼室内に挿入し、点火栓に通電しアークを生じさせる。これに前後して流量制御弁２と圧力制御弁１を順次開放し、燃料を燃料ノズル５に供給することで燃料ノズル５から噴射され燃料と空気圧縮機１０からの燃焼空気を混合気体とする。これにより燃焼室内で点火栓のアークによって混合気体に点火されると、燃焼室内において燃料ノズル５の下流側に火炎が形成される。この燃焼反応により燃焼室内で発生した燃焼ガスはタービン３０に供給され、タービン３０はこの燃焼ガスの流体エネルギーを回転動力に変換する。なお、流量制御弁２ａ〜２ｅの開放順序や開放数は、ガスタービン設備毎に予め定められる。 In the gas turbine according to the present embodiment having the above-described configuration, the ignition of the combustor 20, that is, the start of the combustor 20, is performed as follows.
First, the compressed air from the air compressor 10 is supplied as combustion air to the combustor 20 (downstream of the fuel nozzle 5), while the fuel from the fuel supply source 40 is sent to the gas compressor 3 to boost the fuel. . Next, an ignition plug (not shown) is inserted into a combustion chamber (not shown) of the combustor 20, and the ignition plug is energized to generate an arc. Before and after this, the flow rate control valve 2 and the pressure control valve 1 are opened sequentially, and fuel is supplied to the fuel nozzle 5 to inject the fuel and the combustion air from the air compressor 10 into a mixed gas. . As a result, when the gas mixture is ignited by the arc of the spark plug in the combustion chamber, a flame is formed on the downstream side of the fuel nozzle 5 in the combustion chamber. The combustion gas generated in the combustion chamber by this combustion reaction is supplied to the turbine 30, and the turbine 30 converts the fluid energy of the combustion gas into rotational power. The opening order and the number of opening of the flow control valves 2a to 2e are determined in advance for each gas turbine facility.

ここで、図３は一般的なガスタービンの始動時における圧力制御弁前圧Ｐ１、流量制御弁前圧Ｐ２、流量制御弁後圧Ｐ３の関係を表す図である。
図３において、横軸の左半分は、運転開始後にタービンで得られる回転動力が空気圧縮機の駆動力とつり合うまでタービンの回転数が上昇する過程を、右半分は、その後ガスタービン負荷が増大する過程を表している。 Here, FIG. 3 is a diagram showing the relationship among the pressure control valve pre-pressure P1, the flow control valve pre-pressure P2, and the flow control valve post-pressure P3 when starting a general gas turbine.
In FIG. 3, the left half of the horizontal axis shows the process in which the rotational speed of the turbine increases until the rotational power obtained by the turbine after the start of operation balances with the driving force of the air compressor, and the right half increases the load of the gas turbine thereafter. Represents the process.

この種のガスタービンの燃焼器においては、圧力制御弁前圧（圧力制御弁１の上流側の燃料圧力）Ｐ１が図３に示すようにガス圧縮機によって概ね一定に保たれるが、流量制御弁後圧（流量制御弁２の下流側の燃料圧力）Ｐ３は実際にはガスタービンの運転状態によって変化するため流量制御弁前圧の目標値もそれに伴って変化する。   In this type of gas turbine combustor, the pressure control valve pre-pressure (the fuel pressure upstream of the pressure control valve 1) P1 is maintained substantially constant by the gas compressor as shown in FIG. Since the post-valve pressure (fuel pressure downstream of the flow control valve 2) P3 actually changes depending on the operating state of the gas turbine, the target value of the flow control valve pre-pressure also changes accordingly.

通常、ガスタービン着火時は流量制御弁前圧Ｐ２が低いため、流量制御弁ではなく圧力制御弁の開度で燃料流量が決まる。流量制御弁の開度は大気温度によって制御されるが、圧力制御弁の開度は大気温度によらずある値に保たれるため、大気温度によらず燃料流量は一定となる。   Normally, when the gas turbine is ignited, the flow control valve pre-pressure P2 is low, so the fuel flow rate is determined by the opening of the pressure control valve, not the flow control valve. Although the opening degree of the flow control valve is controlled by the atmospheric temperature, the opening degree of the pressure control valve is maintained at a certain value regardless of the atmospheric temperature, so that the fuel flow rate is constant regardless of the atmospheric temperature.

図４は大気温度と空気流量の関係を示す図である。
この図４に示すように、空気流量は大気温度によって変化する。したがって、着火時において、燃料流量は大気温度によらず一定に保たれるため、大気温度が低くなった場合、空気流量が多くなって点火時空燃比が下がるため、点火不具合が生じる可能性がある。一方、大気温度が高い場合は、空気流量が少なくなり、点火時空燃比が上がるため、熱応力が大きくなる可能性がある。 FIG. 4 is a diagram showing the relationship between the atmospheric temperature and the air flow rate.
As shown in FIG. 4, the air flow rate varies depending on the atmospheric temperature. Therefore, at the time of ignition, the fuel flow rate is kept constant regardless of the atmospheric temperature. Therefore, if the atmospheric temperature becomes low, the air flow rate increases and the ignition air-fuel ratio decreases, which may cause an ignition failure. . On the other hand, when the atmospheric temperature is high, the air flow rate decreases and the ignition air-fuel ratio increases, so that the thermal stress may increase.

また、図５は本発明の比較例のガスタービンの燃焼器始動制御方法による着火時の燃料流量を示す図である。
一般に流量制御弁の開度は大気温度に応じて制御されるが、圧力制御弁の開度は、着火時には一定値（固定値）に保たれ、その後、流量制御弁前圧を一定に保つように制御されることが行われてきた。仮にこのような始動制御方法を図１及び図２に示したガスタービンに適用した場合、大気温度により空気流量が変動すると、圧力制御弁１の制御が開度一定制御からＰ２圧制御に切り替わる際、図５に示したように燃料流量が大きく変動する可能性がある。 FIG. 5 is a diagram showing the fuel flow rate at the time of ignition by the combustor start control method of the gas turbine of the comparative example of the present invention.
In general, the opening of the flow control valve is controlled according to the atmospheric temperature, but the opening of the pressure control valve is kept at a constant value (fixed value) at the time of ignition, and then the pressure before the flow control valve is kept constant. It has been done to be controlled. If such a start control method is applied to the gas turbine shown in FIGS. 1 and 2, when the air flow rate fluctuates due to the atmospheric temperature, the control of the pressure control valve 1 is switched from the constant opening degree control to the P2 pressure control. As shown in FIG. 5, the fuel flow rate may fluctuate greatly.

そこで、本実施の形態では、大気温度によらず良好な着火性能が確保されるように、燃料流量を次のように制御する。
着火後の通常運転時には、流量制御弁前圧Ｐ２が一定の目標値となるように圧力制御弁１の開度を制御した状態で、大気温度に応じて流量制御弁２を制御し燃料流量を調整する。つまり、圧力制御弁１は流量制御弁前圧（検出値）Ｐ２と目標値との偏差が小さくなるように制御装置５０により制御される。流量制御弁２は、圧力制御弁１の制御によって流量制御弁前圧Ｐ２が目標値に保たれることを前提として、大気温度の他、ガスタービン出力、回転数、燃料温度等を基に制御装置５０により制御される。 Therefore, in the present embodiment, the fuel flow rate is controlled as follows so that good ignition performance is ensured regardless of the atmospheric temperature.
During normal operation after ignition, the flow rate control valve 2 is controlled according to the atmospheric temperature and the fuel flow rate is controlled with the opening degree of the pressure control valve 1 controlled so that the flow rate control valve pre-pressure P2 becomes a constant target value. adjust. That is, the pressure control valve 1 is controlled by the control device 50 so that the deviation between the flow control valve pre-pressure (detected value) P2 and the target value becomes small. The flow control valve 2 is controlled based on the gas turbine output, the rotation speed, the fuel temperature, etc. in addition to the atmospheric temperature, on the assumption that the flow control valve pre-pressure P2 is maintained at the target value by the control of the pressure control valve 1. It is controlled by the device 50.

しかし、着火時は流量制御弁前圧Ｐ２が目標値に対して低いため、上記のような通常運転時と同様の制御を行った場合、流量制御弁前圧Ｐ２と目標値との偏差が大きく制御が不安定になる可能性がある。したがって、制御装置５０は、一定の設定開度に圧力制御弁１の開度を制御する。このとき、本実施の形態では、圧力制御弁１の設定開度を、例えば予め格納されたテーブルや関数に基づき、検出された大気温度に対応した値に決定する。つまり着火時の圧力制御弁１の設定開度は可変である。圧力制御弁１の着火時の設定開度の決定は、例えば空気圧縮機１０の吸気口近傍に設けた温度センサ（図示せず）により検出された大気温度を基に、予め定められた大気温度−設定開度の関係に従って制御装置５０でなされるようにしても良いし、外気温を基にオペレータが設定することも考えられる。   However, at the time of ignition, the flow control valve pre-pressure P2 is lower than the target value. Therefore, when the same control as during normal operation as described above is performed, the deviation between the flow control valve pre-pressure P2 and the target value is large. Control may become unstable. Therefore, the control device 50 controls the opening degree of the pressure control valve 1 to a constant set opening degree. At this time, in the present embodiment, the set opening degree of the pressure control valve 1 is determined to a value corresponding to the detected atmospheric temperature, for example, based on a table or function stored in advance. That is, the set opening degree of the pressure control valve 1 at the time of ignition is variable. The set opening degree at the time of ignition of the pressure control valve 1 is determined by, for example, a predetermined atmospheric temperature based on an atmospheric temperature detected by a temperature sensor (not shown) provided in the vicinity of the intake port of the air compressor 10. -It may be made by the control device 50 in accordance with the relationship of the set opening, or it may be set by the operator based on the outside air temperature.

図６は本実施の形態のガスタービンの燃焼器始動制御方法による着火時の燃料流量を示す図である。
上記した本実施の形態のガスタービンの燃焼器始動制御方法によれば、着火時において、圧力制御弁１の開度を大気温度によって変化させることで、着火時に圧力制御弁開度に依存する燃料流量を大気温度に応じて調節することができる。そのため、大気温度によって燃料と燃焼空気の比率が大きく変化することがなく空燃比を適正に保つことができ、図６に示すように、圧力制御弁開度一定制御からＰ２圧制御に切り替わる際の燃料流量の変動を抑制することができる。したがって、大気温度によらずスムーズに着火することができる。 FIG. 6 is a diagram showing the fuel flow rate at the time of ignition by the combustor start control method of the gas turbine of the present embodiment.
According to the gas turbine combustor start control method of the present embodiment described above, the fuel that depends on the pressure control valve opening at the time of ignition is changed by changing the opening of the pressure control valve 1 according to the atmospheric temperature at the time of ignition. The flow rate can be adjusted according to the atmospheric temperature. Therefore, the ratio of the fuel and the combustion air does not change greatly depending on the atmospheric temperature, and the air-fuel ratio can be maintained appropriately. As shown in FIG. 6, when switching from pressure control valve opening constant control to P2 pressure control, Variations in the fuel flow rate can be suppressed. Accordingly, ignition can be performed smoothly regardless of the atmospheric temperature.

本発明の一実施の形態に係るガスタービンの概略構成を表す概念図である。It is a conceptual diagram showing schematic structure of the gas turbine which concerns on one embodiment of this invention. 本発明の一実施の形態に係るガスタービンに備えられた燃焼器とその燃料供給系統を表すブロック図である。It is a block diagram showing the combustor with which the gas turbine which concerns on one embodiment of this invention was equipped, and its fuel supply system. 一般的なガスタービンの始動時における圧力制御弁前圧、流量制御弁前圧、流量制御弁後圧の関係を表す図である。It is a figure showing the relationship of the pressure control valve pre-pressure at the time of starting of a general gas turbine, the flow control valve pre-pressure, and the flow control valve pre-pressure. 大気温度と空気流量の関係を示す図である。It is a figure which shows the relationship between atmospheric temperature and an air flow rate. 本発明の比較例のガスタービンの燃焼器始動制御方法による着火時の燃料流量を示す図である。It is a figure which shows the fuel flow rate at the time of ignition by the combustor starting control method of the gas turbine of the comparative example of this invention. 本発明の一実施の形態に係るガスタービンの燃焼器始動制御方法による着火時の燃料流量を示す図である。It is a figure which shows the fuel flow rate at the time of ignition by the combustor start-up control method of the gas turbine which concerns on one embodiment of this invention.

符号の説明Explanation of symbols

１ 圧力制御弁
２，２ａ〜ｅ 流量制御弁
３ ガス圧縮機
５，５ａ〜ｅ 燃料ノズル
６ 圧力センサ
１０ 空気圧縮機
２０ 燃焼器
３０ タービン
４０ 燃料供給源
５０ 制御装置
Ｐ１ 圧力制御弁前圧
Ｐ２ 流量制御弁前圧
Ｐ３ 流量制御弁後圧 DESCRIPTION OF SYMBOLS 1 Pressure control valve 2, 2a-e Flow control valve 3 Gas compressor 5, 5a-e Fuel nozzle 6 Pressure sensor 10 Air compressor 20 Combustor 30 Turbine 40 Fuel supply source 50 Controller P1 Pressure control valve pre-pressure P2 Flow rate Pressure before control valve P3 Pressure after flow control valve

Claims (4)

吸い込んだ空気を圧縮する空気圧縮機と、
燃料を供給する燃料供給源と、
この燃料供給源からの燃料を昇圧するガス圧縮機、このガス圧縮機からの燃料の圧力を制御する圧力制御弁、この圧力制御弁の下流側で燃料流量を制御する流量制御弁、及び燃料を噴射する燃料ノズルを有し、前記燃料ノズルからの燃料を前記空気圧縮機からの圧縮空気とともに燃焼する燃焼器と、
この燃焼器からの燃焼ガスにより回転動力を得るタービンと、
前記燃焼器の着火時における前記圧力制御弁の開度を大気温度に応じて変化する設定値で一定に保つ制御装置と
を備えたことを特徴とするガスタービン。 An air compressor that compresses the inhaled air;
A fuel supply source for supplying the fuel;
A gas compressor for boosting the fuel from the fuel supply source, a pressure control valve for controlling the pressure of the fuel from the gas compressor, a flow rate control valve for controlling the fuel flow rate downstream of the pressure control valve, and a fuel A combustor having a fuel nozzle for injecting, and combusting fuel from the fuel nozzle together with compressed air from the air compressor;
A turbine that obtains rotational power from combustion gas from the combustor;
A gas turbine comprising: a control device that keeps the opening degree of the pressure control valve constant at a set value that changes according to the atmospheric temperature when the combustor is ignited. 請求項１のガスタービンにおいて、
前記圧力制御弁と前記流量制御弁の間に設けられ、前記流量制御弁の上流側の燃料圧力を検出する圧力センサをさらに備え、
前記制御装置は、前記燃焼器の着火後、前記圧力センサの検出値が前記流量制御弁の上流側の燃料圧力の目標値に近付くように前記圧力制御弁の開度を制御する
ことを特徴とするガスタービン。 The gas turbine of claim 1.
A pressure sensor provided between the pressure control valve and the flow rate control valve and detecting a fuel pressure upstream of the flow rate control valve;
The control device controls the opening degree of the pressure control valve so that the detected value of the pressure sensor approaches the target value of the fuel pressure upstream of the flow control valve after the combustor is ignited. Gas turbine. 請求項１又は２のガスタービンにおいて、前記制御装置は、前記流量制御弁の開度を大気温度に応じて制御することを特徴とするガスタービン。   3. The gas turbine according to claim 1, wherein the control device controls an opening degree of the flow rate control valve in accordance with an atmospheric temperature. 吸い込んだ空気を圧縮する空気圧縮機と、燃料を供給する燃料供給源と、この燃料供給源からの燃料を昇圧するガス圧縮機、このガス圧縮機からの燃料の圧力を制御する圧力制御弁、この圧力制御弁の下流側で燃料流量を制御する流量制御弁、及び燃料を噴射する燃料ノズルを有し、前記燃料ノズルからの燃料を前記空気圧縮機からの圧縮空気とともに燃焼する燃焼器と、この燃焼器からの燃焼ガスにより回転動力を得るタービンとを備えたガスタービンの燃焼器始動制御方法において、
前記燃焼器の着火時における前記圧力制御弁の開度を大気温度に応じて変化する設定値で一定に保つ
ことを特徴とするガスタービンの燃焼器始動制御方法。 An air compressor that compresses the sucked air, a fuel supply source that supplies fuel, a gas compressor that boosts the fuel from the fuel supply source, a pressure control valve that controls the pressure of the fuel from the gas compressor, A combustor having a flow rate control valve for controlling a fuel flow rate downstream of the pressure control valve, and a fuel nozzle for injecting fuel, and combusting fuel from the fuel nozzle together with compressed air from the air compressor; In a combustor start-up control method for a gas turbine comprising a turbine for obtaining rotational power by combustion gas from the combustor,
A combustor start-up control method for a gas turbine, characterized in that the opening degree of the pressure control valve at the time of ignition of the combustor is kept constant at a set value that changes according to the atmospheric temperature.
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Citations (2)

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Publication number Priority date Publication date Assignee Title
JPS60187719A (en) * 1984-02-13 1985-09-25 ドレツサ−・インダストリ−ズ・インコ−ポレ−テツド Automatic temperature compensation type fuel flow amount stabilizing method and apparatus
JPH06146930A (en) * 1992-10-30 1994-05-27 Toshiba Corp Fuel pressure control device of gas turbine facility

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60187719A (en) * 1984-02-13 1985-09-25 ドレツサ−・インダストリ−ズ・インコ−ポレ−テツド Automatic temperature compensation type fuel flow amount stabilizing method and apparatus
JPH06146930A (en) * 1992-10-30 1994-05-27 Toshiba Corp Fuel pressure control device of gas turbine facility

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