阅读说明：本技术 用于运行具有气态燃料的燃气轮机设施的方法 (Method for operating a gas turbine plant with gaseous fuel ) 是由 比约恩·贝克曼 尼克拉斯·瑙贝尔 马尔滕·奥弗 于 2019-05-16 设计创作，主要内容包括：一种用于运行具有气态燃料的燃气轮机设施的方法,所述气态燃料通过气体管路(6)被运输到所述燃气轮机设施、在燃烧室(4)中燃烧并且紧接着被输送给燃气轮机。在所述气体管路(6)中装入有至少一个阀门(12a,12b),用于进行至燃烧室(4)的燃料的流量调节,其中对于所述阀门(12a,12b)定义临界打开位置(S_(krit))。关于用于运行燃气轮机设施的改进方法,其中在气体管路(6)中的压力不足的情况下燃气轮机设施的功率(P)尽可能长时间地保持最高,提出：当所述阀门(12a,12b)在此要超过临界打开位置(S_(krit))时,降低所述气体管路(6)中的燃料的温度(TB)。(A method for operating a gas turbine plant with a gaseous fuel which is transported to the gas turbine plant via a gas line (6), is burned in a combustion chamber (4) and subsequently fed to a gas turbine. At least one valve (12a, 12b) is inserted into the gas line (6) for regulating the flow of fuel to the combustion chamber (4), wherein a critical opening position (S) is defined for the valve (12a, 12b) krit )。With regard to an improved method for operating a gas turbine installation, in which the power (P) of the gas turbine installation is kept highest for as long as possible in the event of an insufficient pressure in the gas line (6), it is proposed that: when the valve (12a, 12b) is in this position above a critical opening position (S) krit ) While reducing the Temperature (TB) of the fuel in the gas line (6).)

1. A method for operating a gas turbine plant with a gaseous fuel which is transported to the gas turbine plant via a gas line (6), is burned in a combustion chamber (4) and is subsequently fed to a gas turbine,

characterized in that at least one valve (12a, 12b) is inserted into the gas line (6) for regulating the flow of fuel to the combustion chamber (4), wherein a critical opening position (S) is defined for the valve (12a, 12b)_krit) And when the valve (12a, 12b) is to exceed the critical opening position (S)_krit) While reducing the temperature (T) of the fuel in the gas line (6)_B)。

2. The method of claim 1, wherein the first and second light sources are selected from the group consisting of,

characterized by a critical opening position (S) of the valve (12a, 12b)_krit) Greater than 70% of the maximum open position.

3. The method according to any one of the preceding claims,

characterized in that the gas turbine plant has a preheating system for the fuel and in that the temperature (T) of the fuel in the gas line (6) is reduced by reducing the heat supplied to the fuel in the preheating system_B)。

4. The method according to any one of the preceding claims,

characterized in that the lowest temperature (T) of the fuel is determined taking into account the current values of the operating parameters for the gas turbine plant_B) Threshold value (T) of_min) And when said threshold value is reached, the temperature (T) of the fuel in the gas line (6) is stopped_B) Is reduced.

5. The method according to any one of the preceding claims,

characterized in that a plurality of valves (12a, 12b) are incorporated in the gas line (6) and the position of each of the valves (12a, 12b) is taken into account.

6. The method according to any one of the preceding claims,

characterized in that the turbine power (P) is reduced supplementally.

7. A control device (18) comprising means for performing the method according to any of the preceding claims.

8. A gas turbine plant having a control apparatus (18) according to claim 7.

Technical Field

The invention relates to a method for operating a gas turbine plant with a gaseous fuel which is transported to the gas turbine plant via a gas line, burned in a combustion chamber and subsequently supplied to a gas turbine. The invention also relates to a control device for carrying out the method and to a gas turbine installation having such a control device.

Background

Natural gas is typically supplied as fuel to the gas turbine facility via a gas pipeline. In this case, the optimum operation of the gas turbine plant is dependent on the quality of the fuel, the correct pressure and the correct temperature. The minimum required pressure which is specified as a prerequisite for operating the gas turbine installation and which must be ensured is likewise associated with different use and environmental conditions, for example turbine load, ambient temperature, ambient pressure, gas composition, gas temperature, etc. However, due to different conditions, the pressure in the gas line may be insufficient, for example due to the following reasons: pressure fluctuations in the local gas network; faults in piping leading to and in the gas turbine facility; failure of the gas compressor, if any; fluctuations in gas mass; pressure loss along the gas piping system; the improvement of firepower and the like. In the case of gas turbine combustion, which is associated with a precise distribution of the mass flow of fuel to two or more stages (e.g. main burner and pilot burner), the combustion stability in the above-described situation can no longer be ensured.

It is known from EP 1730444B 1 to reduce the fuel temperature in order to ensure that the supply pressure in the gas line is higher than the pressure in the combustion chamber. However, this is always done in combination with other measures for suppressing the increase in the power of the gas turbine, which have a higher priority than reducing the fuel temperature. The motivation here is to avoid backfiring by stabilizing the fuel supply pressure, which would jeopardize the operational safety of the entire fuel supply and would cause the gas turbine installation to malfunction over a considerable period of time. The measures for reducing the power output and, if necessary, the gas temperature are initiated as a function of the specified pressure curve or pressure characteristic curve. The pressure profile must rely on design calculations and/or empirical values for other machines. If the combustion chamber pressure is taken into account in relation to the power, the gas pressure is an approximate measure for the maximum settable fuel quantity volume flow. Due to computational inaccuracies and due to natural fluctuations between the machines (for example due to manufacturing tolerances) and to the time-dependent pressure loss coefficients (wear or contamination) on the gas system and the burner, the maximum settable fuel volume flow is subject to a certain dispersion for a specific gas pressure.

Disclosure of Invention

The invention is therefore based on the object of eliminating the disadvantages of the prior art and of providing an improved method for operating a gas turbine installation, in which the power of the gas turbine installation is kept highest for as long as possible in the event of an insufficient pressure in the gas line.

According to the invention, the object is achieved by a method for a gas turbine plant having a gas fuel which is transported to the gas turbine plant via a gas line, is combusted in a combustion chamber and is subsequently supplied to a gas turbine, wherein at least one valve is inserted into the gas line for regulating the flow of the fuel to the combustion chamber, wherein a critical opening position is defined for the valve, and the temperature of the fuel in the gas line is reduced when the valve is to exceed the critical opening position.

Furthermore, according to the invention, the object is also achieved by a control device comprising means for carrying out such a method.

Finally, according to the invention, the object is achieved by a gas turbine installation having such a control device.

The advantages and preferred embodiments explained below with regard to the method can be similarly transferred to the control device and the gas turbine installation.

A valve in this case denotes any device for controlling or regulating the mass flow in a gas line. The valve can in particular completely block the gas line in the closed state, so that the gas flow is interrupted. The valve is preferably designed as a control or regulating valve, but it can also be formed in the type of a flap, a slide or a tap.

The invention is based on the following knowledge: by using the state of the flow valve as a criterion for when the fuel temperature needs to be reduced, a particularly reliable controllability of the gas turbine is achieved. The position of the valve is a direct measure for the pressure actually required upstream of the combustion chamber or for how much the fuel mass flow can also be increased in response to an underpressure in the gas line. In this case, the intervention is only carried out when it is actually necessary, so that the set desired power of the gas turbine is kept constant for as long as possible. In contrast to the prior art, the method is characterized in particular in that it is load-independent, i.e. the valve position associated with the critical opening position is a fixed criterion and is independent of the operating point.

The current position of the valve is always known, since the mass flow in the gas line of which the valve is a part is known. In particular, the state of the valve is set according to the mass flow. The mass flow is measured directly or determined indirectly from different parameters. If the valve is in the critical open position, but the pressure in the gas line is not sufficient, in particular because of an increased demand for pressure or a drop in pressure in the line, the first action to be taken is to reduce the gas temperature in order to maintain the desired power. The temperature of the fuel has a substantial effect on the pressure in the gas line. By lowering the gas temperature, the density of the gas is increased, which causes less pressure loss in the fuel system.

Preferably, the critical opening position of the valve is in the range of more than 70% of the maximum opening position. The maximum open position is a state in which the mass flow in the gas line is maximum. The critical, critical opening position of the valve is therefore not necessarily the maximum opening position of the valve (however, the critical opening position can also be defined by the maximum opening position), but a state in which the flow is slightly minimized. In this case, it is advantageous to be able to react to rapid, short-term changes in operating parameters, such as fluctuations in the quality of the fuel, by further opening the valve. Furthermore, by changing the critical opening position during operation, it can subsequently be adapted to the operating conditions.

The temperature of the fuel can be reduced via active cooling measures. However, the gas turbine installation preferably has a preheating system for the fuel and the temperature of the fuel in the gas line is reduced by reducing the heat delivered to the fuel in the preheating system. This is a particularly simple and efficient method approach for reducing the temperature, which does not require any additional hardware and is not accompanied by energy expenditure.

According to a preferred embodiment, a threshold value for the minimum temperature of the fuel is determined taking into account the operating parameters of the gas turbine plant, and the temperature of the fuel in the gas line is stopped being reduced when the threshold value is reached. There may be potential limitations in a gas turbine facility such that compliance with a minimum gas temperature can be required. At low gas temperatures, for example, problems with respect to combustion stability and/or emissions can occur. Such an operating parameter is, for example, the NOx value in the exhaust gas, which is an additional criterion on the basis of which it is decided whether to start or continue the method according to the invention. In the case of gases with an increased proportion of higher hydrocarbons, a fixed minimum value of the temperature of the fuel can be monitored, since the risk of condensate formation occurs when the gas temperature is low. Furthermore, in very cold locations, there is a risk of icing when the gas temperature is low, in which case a fixed minimum of 5 ℃ has proved to be advantageous. In this case, stopping the lowering of the fuel temperature is used to standardly indicate that the process is interrupted if it has already started. Alternatively, if the cooling of the fuel is not yet active when the threshold value for emissions has been reached, the gas cooling is abandoned as long as the emissions value corresponds to the threshold value.

Expediently, a plurality of valves are installed in the gas line, and the position of each of the valves is taken into account. In multistage burners, a valve for regulating the flow is usually provided in each case in the lines to the individual stages, for example to the main burner and the pilot burner. As already explained, the temperature of the fuel in the gas line is reduced if at least one of the valves is in the critical open position and is no longer able to react to a further increased mass flow demand.

In the case where fluctuations in gas quality are the cause of insufficient pressure in the gas line, it is generally sufficient to reduce the fuel temperature. However, if the reduced fuel temperature does not meet the pressure requirement, it is preferable to supplement this reduced turbine power. The turbine power is only reduced in a regulated manner, in particular by presetting the reduced power setpoint value, if the pressure requirement cannot be met despite the reduced temperature if the critical opening position of the valve is reached. In an emergency situation, a gas turbine shutdown may even be possible. In this case, the two measures of reducing the gas temperature and reducing the power should be combined with one another in such a way that the power remains constant as long as possible or as high as possible, with care always being taken that the valve does not exceed a critical opening position. In this case, the priority of the two measures is important, i.e. they are started simultaneously if necessary, but the turbine power is increased again as soon as possible. If merely lowering the fuel temperature is not sufficient to counteract the pressure gradient, the reduction in the starting turbine power serves in particular as a rapid reaction to particularly large pressure gradients.

Drawings

An embodiment of the invention is explained in more detail on the basis of the drawings. In which is shown:

FIG. 1 shows a fuel system of a gas turbine plant in a schematic and extremely simplified manner, and

fig. 2 shows time profiles of various parameters of a gas turbine installation in a schematic diagram.

In the drawings like reference numerals have the same meaning.

Detailed Description

In fig. 1, the configuration of a fuel system 2 is schematically shown, which is part of a gas turbine plant, not shown in detail, in which natural gas is used as fuel. A gas turbine installation generally comprises a compressor, a combustion chamber 4 and a gas turbine, to which, for example, an electrical generator for generating electrical current is coupled.

The fuel system 2 comprises a gas line 6 via which gaseous fuel is fed to the combustion chamber 4. In particular, a plurality of burners, which in the exemplary embodiment shown are designed in multiple stages and which are symbolically shown in the drawing by a main burner 8 and a pilot burner 10, are arranged in the combustion chamber 4. A sub-line 6a, 6b branches off to each of the burner stages 8, 10, in which a regulating valve 12a, 12b is installed. The gas line 6 also contains an emergency valve 14. Upstream of the emergency valve 14, a heat exchanger 16 is also arranged on the gas line 6, which heat exchanger is part of a preheating system for preheating the fuel in the gas line 6.

The gas turbine installation further comprises a control or regulating device 18, which in particular regulates the position of the regulating valves 12a, 12 b. In this case, a threshold opening position for the control valves 12a, 12b is stored in the control device 18, which is, for example, 80% of the maximum opening position of the control valves 12a, 12 b. The critical opening position can also be, for example, 70%, 75%, 85%, 90%, 95% of the maximum opening position of the control valves 12a, 12b or correspond to the maximum opening position.

The progress of the method according to the invention can be seen from fig. 2. It is generally appropriate to always set the position of the respective regulating valve 12a, 12b via a regulating circuit in the control or regulating device 18 such that the gas turbine is operated according to a predetermined power or combustion temperature. Thus, the gas turbine automatically reacts indirectly to fluctuations in the following variables: natural gas supply pressure, natural gas temperature, natural gas quality, ambient conditions, pressure losses via the natural gas supply system and the combustor (fouling/wear), and/or efficiency of the gas turbine (wear). All these parameters are possible interference factors, on the basis of which the position of the regulating valves 12a, 12b is adjusted in order to set the turbine power P in particular as a result.

In fig. 2, the reduced fuel supply pressure BD, i.e. the natural gas supply pressure, is considered as a disturbance variable. Instead of a reduced natural gas pressure, a deteriorated gas quality, a reduced ambient temperature, an increased ambient air humidity, an increased ambient pressure, a pollution of the burner or the natural gas system components, a reduced gas turbine efficiency, etc. can alternatively be used.

According to fig. 2, the fuel supply pressure BD is measured from the point in time t₀To a time point t₁Is constant and the regulating valve state RV is in the critical opening position S_kritThe following. Temperature T of fuel_BAnd the turbine power P is kept stable over its desired value (turbine power Ps).

From t₁To t₂The fuel supply pressure BD in the gas pipe 6 decreases. In order to keep the turbine power P (or the fuel mass flow) constant, the respective regulating valve or the two regulating valves 12a, 12b are opened further until a critical opening position S is reached_krit。

At a time from t₂To t₃The fuel supply pressure BD further decreases in the period of time (3). The control valves 12a, 12b reach their predetermined critical opening position S_kritWhereby said regulating valve is self-t₃Is not opened any further but remains at S_kritIn (1). To keep the power P (or fuel mass flow) constant, the gas temperature T is reduced_B。

From t₃From here, the fuel supply pressure BD continues to decrease with a steeper gradient. Too large a gradient to pass the fuel temperatureDegree T_BTo compensate for the slow changes in the pressure. Temperature T of fuel_BContinuing to decrease at its maximum gradient, the gas turbine power P is also reduced slightly in order to keep the control valves 12a, 12b in the critical open position S_kritIn (1).

At t₄And t₅In between, the fuel supply pressure BD stabilizes at a lower level than initially. The regulating valves 12a, 12b continue to be in the critical opening position S_kritIn (1). From t₃At the beginning, the turbine power P is always lower than the desired power value Ps, however, with the fuel temperature T_BIn parallel, the gas turbine power P is again ramped up to the desired value Ps. It is to be noted here that the fuel temperature T_BIs kept at a minimum threshold T_minAbove, wherein the threshold value T_minFor example, NOx emissions or other operating parameters of the gas turbine facility.

From t₅And then stable operation is achieved again. The gas turbine power P again reaches its desired value Ps and the gas turbine is operated at a reduced fuel temperature T_BAnd continuing to operate. Only when the regulating valves 12a, 12b occupy the position in which they are in the critical open position S_kritIn the following state RV, the fuel temperature T is increased again_B(this case is not depicted).