Fuel supply system for power generation system

Abstract

The invention relates to a fuel supply system (10) for a power generation system (1), in particular for a micro gas turbine system. The fuel supply system (10) includes a fuel supply line (110), a fuel main line (120) and a fuel distribution line (130), a fuel compressor (200) and a decoupling container (300). A fuel supply line (110) is fluidly connected with the fuel compressor (200) and may be connected with a fuel source (11) for supplying fuel from the fuel source (11) to the fuel compressor (200). The decoupling tank (300) is arranged downstream of the fuel compressor (200) and is fluidly connected to the fuel compressor (200) via a fuel main line (120). A fuel distribution line (130) is arranged downstream of and fluidly connected to the decoupling vessel (300). The fuel distribution line (130) can be fluidly connected to at least one combustion unit (20) of the power generation system (1) and is designed to supply the at least one combustion unit (20) with fuel from the decoupling container (300).

Description

Field of the Invention

[0001] The present invention relates to a fuel supply system for a power generation system, in particular for a (micro) gas turbine system. Furthermore, the present invention also relates to a power generation system having such a fuel supply system, in particular a (micro) gas turbine system, and a method for controlling the fuel supply system of a power generation system. Background Art

[0002] Power generation systems (in particular gas turbine systems or micro gas turbine systems) are used to generate electrical power and / or thermal energy by burning gaseous or liquid fluids (in particular fuels). The medium burned in the combustion unit can expand in the turbine, which in turn can be functionally connected to a generator for generating electrical power. Additionally or alternatively, a heat exchanger can be provided to utilize the waste heat generated by the combustion. Depending on the need, the power generation system can have one or more (micro) gas turbines, each with a combustion unit. The gas turbines can each provide the same power or different powers. In particular, for a power generation system including multiple (micro) gas turbines (each with a combustion unit), each gas turbine requires its own fuel supply system based on different operating states (such as transient operation) and / or different load states. Therefore, each combustion unit is supplied by its own fuel supply system so as to be able to supply fuel corresponding to the respective power, operating state, and / or load state to each combustion unit at a specific pressure, specific temperature, and / or specific mass flow rate (or flow rate). Most each fuel supply system has multiple components, such as pipelines, seals, valves, and pumps or compressors. Some of these components can be actively controlled, such as operable valves, to provide fuel with specific parameters (such as flow rate). Other components can be safety components that meet specific safety standards of the entire system and should ensure that no serious accidents occur. The safety standards allow various configurations of the fuel supply system here. However, known fuel supply systems, especially those for each gas turbine, in addition to a pre-compressor, also require a main gas compressor, with which a specific pressure or mass flow rate can be provided to the corresponding combustion unit. A power generation system having one or more known fuel supply systems requires a large number of components, which results in high costs, high space requirements, and high complexity. In addition, the application range of known fuel supply systems is also limited.

[0003] It is an object of the present invention to provide an improved fuel supply system for a power generation system, in particular for a (micro) gas turbine system. Summary of the Invention

[0004] The present invention relates to a fuel supply system for a power generation system, in particular for a gas turbine system or a micro gas turbine system, as claimed in claim 1. Furthermore, the present invention also relates to a power generation system having such a fuel supply system, in particular a (micro) gas turbine system, as claimed in claim 10, and to a method for controlling the fuel supply system of a power generation system, as claimed in claim 16. The dependent claims describe advantageous design solutions for the fuel supply system, the power generation system and the method.

[0005] According to a first aspect of the present invention, a fuel supply system for a power generation system, in particular for a gas turbine system or a micro gas turbine system, comprises a fuel supply line, a fuel main line and a fuel distribution line. Furthermore, the fuel supply system also comprises a fuel compressor and a decoupling vessel. The fuel supply line is fluidly connected to the fuel compressor and can be connected to a fuel source in order to supply fuel from the fuel source to the fuel compressor. The decoupling vessel is arranged downstream of the fuel compressor and is fluidly connected to the fuel compressor via the fuel main line. The fuel distribution line is arranged downstream of the decoupling vessel and is fluidly connected to the decoupling vessel. The fuel distribution line can be fluidly connected to at least one combustion unit of the power generation system and is designed to supply fuel from the decoupling vessel to the at least one combustion unit.

[0006] Based on the fuel supply system according to the present invention, one or more combustion units can be reliably supplied with fuel. In particular, by providing the decoupling vessel, even under different load states, operating states (such as transient operation) and / or different power levels, one or more combustion units can be supplied using only a single fuel supply system. The target pressure required in the decoupling vessel can be provided by the fuel compressor, which in particular enables component reduction in a power generation system having multiple (micro) gas turbines. This can also reduce costs and / or the complexity of the system. Since only a fuel compressor and a decoupling vessel are required, the structural space or space requirements can be reduced. More precisely, with the decoupling vessel in the fuel supply system, many other components can be dispensed with, such as a separate main gas compressor and / or pre-compressor (especially compared to multiple fuel supply systems). Furthermore, the decoupling vessel and the fuel compressor can be provided outside the combustion unit, which simplifies the system (in known systems, they are usually integrated into the respective combustion unit). The corresponding separate fuel supply devices for additional components such as the main gas compressor and / or pre-compressor can be dispensed with. In addition, the application range of the fuel supply system can be extended.

[0007] The decoupling container can also be referred to as a decoupling tank. "Decoupling container or decoupling tank" shall mean in this context that an (intermediate) component is provided between one or more compressors and at least one downstream consumer of the compressed fuel, in particular at least one combustion unit. The decoupling container enables the supply of one or more consumers, in particular one or more combustion units, from the decoupling container of the fuel supply system. This is provided in such a way that fuel with target values of fuel parameters, in particular a target value of fuel pressure, can be provided and / or stored in the decoupling container. The target value of fuel pressure can correspond here to the highest required target value of fuel pressure of one or more combustion units. In other words, the fuel line in which the fuel is compressed by the compressor is not directly connected to one or more consumers, but is "decoupled" from one or more consumers by means of an intermediate component in the form of a decoupling container. Of course, the supply of fuel to the consumer can also be influenced or prohibited by means of a shut-off valve or a throttle valve, but in this case, the fuel storage function cannot be provided and / or the fuel cannot be set to have target values of fuel parameters. In particular, it is also not possible to supply a plurality of consumers or combustion units from the decoupling container, and these consumers or combustion units can at least partly have different target values of fuel parameters (such as a target value of fuel pressure) (for example, based on different load states, operating states and / or power levels). In a design, the fuel supply line can be optional, for example, in the case where the fuel compressor is directly connectable to or connected to the fuel source.

[0008] In a design, the fuel supply system can include exactly one fuel compressor, in particular a high-pressure fuel compressor. The fuel can be a gaseous fuel, in particular propane, natural gas, hydrogen or biogas.

[0009] In a design, the fuel distribution line can be fluidly connected to at least two combustion units of the power generation system and can be designed to supply fuel from the decoupling container to the at least two combustion units. For example, the at least two combustion units can have different power levels, different load states and / or different operating states. The at least two combustion units may require different values of fuel parameters, such as different values of fuel pressure. The decoupling container can be designed to supply fuel with the respective required values of fuel parameters to the at least two combustion units. Fuel with target values of fuel parameters can be provided in the decoupling container, and the target values of fuel parameters correspond to the highest required values of fuel parameters of the at least two combustion units. The fuel distribution line can include at least two sub-lines, each of which is connected to the at least two combustion units.

[0010] In a design solution, the power generation system may include at least one gas turbine having at least one combustion unit. A fuel distribution line may be fluidly connected to the combustion unit of at least one gas turbine of the power generation system and may be designed to supply fuel from a decoupling container to the combustion unit of the at least one gas turbine.

[0011] In a design solution, the power generation system may include at least two gas turbines, each having a combustion unit. A fuel distribution line may be fluidly connected to the respective combustion units of at least two gas turbines of the power generation system and may be designed to supply fuel from a decoupling container to the respective combustion units of the at least two gas turbines.

[0012] In a design solution, the fuel supply system may include at least one fuel heat exchanger. The at least one fuel heat exchanger may be arranged in the main fuel line, downstream of the fuel compressor, and may be designed to dissipate heat from the main fuel line.

[0013] In a design solution, the fuel supply system may include at least one exhaust line that fluidly connects the main fuel line and the atmosphere outlet of the exhaust line or the fuel supply system.

[0014] In a design solution, the fuel supply system may include at least one exhaust valve located in at least one exhaust line. The exhaust line may be designed to discharge fuel from the main fuel line when the at least one exhaust valve is in the open position.

[0015] In a design solution, the at least one exhaust line may be fluidly connected to a combustion unit supply line and may be designed to discharge fuel from the combustion unit supply line.

[0016] In a design solution, the fuel supply system may include exactly one decoupling container. In a design solution, multiple decoupling containers may also be provided. They may be arranged in parallel with each other. In multiple gas turbines with significantly different power levels, energy optimization can be provided thereby. In a design solution, they may also be arranged in series. In a design solution, the decoupling container may include multiple container cavities. Alternatively, the decoupling container may include exactly one container cavity. In a design solution, the decoupling container may include at least two container cavities. The fuel distribution line may include at least two independent sub-lines. Each container cavity may be independently fluidly connected to the respective combustion unit through the corresponding sub-line. The main fuel line may include at least two sub-lines, each of which connects the main fuel line to the respective container cavity.

[0017] In a design solution, the fuel supply system may include a decoupling container bypass that fluidly connects the fuel main line and the fuel distribution line. The decoupling container bypass may be designed to supply fuel around the decoupling container from the fuel main line to the fuel distribution line. The decoupling container bypass can be used especially when multiple combustion units each having the same (low) power level of multiple gas turbines are supplied, or when only the combustion unit of one gas turbine is fuel-supplied.

[0018] In a design solution, the fuel supply system may include at least one check valve disposed in the fuel main line upstream of the decoupling container. The check valve can prevent the compressed fuel from flowing back from the decoupling container, especially when the fuel compressor is not operating or operating at a low speed (thus only establishing a pressure lower than the pressure in the decoupling container).

[0019] In a design solution, the fuel compressor may be designed to provide fuel with a target value of fuel parameters, especially a target value of fuel pressure, in the decoupling container.

[0020] In a design solution, the fuel supply system may include a fuel compressor bypass that fluidly connects the fuel supply line and the fuel main line and is designed to supply fuel around the fuel compressor from the fuel supply line to the fuel main line. For example, fuel with a certain pressure level can already be provided to the fuel source. If this pressure level corresponds at least to the target value of the fuel pressure in the decoupling container (for example when at least one combustion unit is in a low-load state), the fuel compressor bypass can be opened.

[0021] In a design solution, the fuel supply system may include at least one first shut-off valve disposed in the fuel main line downstream or upstream of the fuel compressor. The shut-off valve can be used to quickly and centrally shut down or prohibit fuel supply, for example, in case of danger, emergency, or maintenance.

[0022] In a design solution, the fuel supply system may include at least one filter device disposed in the fuel supply line upstream of the fuel compressor. In a design solution, the fuel supply system may include at least one pressure reducing valve disposed in the fuel distribution line downstream of the decoupling container.

[0023] In a design solution, the fuel supply system may include at least one first pressure sensor and / or a first temperature sensor, and the first pressure sensor and / or the first temperature sensor are arranged in a fuel supply line, a main fuel line, and / or a fuel distribution line. In a design solution, the fuel supply system may include at least one first mass flow sensor, and the at least one first mass flow sensor is arranged in the main fuel line, upstream of the decoupling container, and is designed to measure the mass flow in the main fuel line before the decoupling container.

[0024] In a design solution, the fuel source may be a supply network, especially a supply network for decentralized energy supply, for example. In another design solution, the fuel source may be a fuel storage tank.

[0025] According to a second aspect of the present invention, a power generation system, especially a gas turbine system or a micro gas turbine system, includes a fuel supply system according to a first aspect of the present invention and at least one combustion unit. The at least one combustion unit is arranged downstream of the fuel supply system and is fluidly connected to the decoupling container through a fuel distribution line, wherein fuel from the decoupling container is supplied to the at least one combustion unit. The above-mentioned advantageous effects of the power generation system can also be provided by this system. A micro gas turbine system is understood to be a system having one or more micro gas turbines, and each micro gas turbine can provide a power of 30 kW to 500 kW. However, the design solutions described herein can also be used for gas turbine systems with greater power.

[0026] In a design solution, the power generation system may include at least one (micro) gas turbine having at least one combustion unit. The fuel distribution line may be fluidly connected to the combustion unit of at least one gas turbine of the power generation system and supply fuel from the decoupling container to the combustion unit of the at least one gas turbine.

[0027] In a design solution, the power generation system may include at least two combustion units, which are arranged downstream of the fuel supply system and are fluidly connected to the decoupling container through a fuel distribution line. Fuel from the decoupling container can be supplied to the at least two combustion units. The fuel distribution line may have multiple sub-lines, and then each of these sub-lines branches from the fuel distribution line to the corresponding combustion unit. In another design solution, the fuel distribution line may have multiple sub-lines, which are set to be independent of each other and connect the corresponding combustion units to the decoupling container independently.

[0028] In a design solution, the power generation system may include at least two (micro) gas turbines, each of which has a combustion unit. The fuel distribution pipeline may be fluidly connected to the respective combustion units of at least two gas turbines of the power generation system and supply fuel from the decoupling container to the respective combustion units of the at least two gas turbines.

[0029] In a design solution, at least one combustion unit may include a combustion unit supply pipeline and at least one burner. The combustion unit supply pipeline may fluidly connect the burner to the fuel distribution pipeline. In a design solution, at least one burner may include a main burner and a pilot burner.

[0030] In a design solution, the fuel supply system may include at least one exhaust pipeline that fluidly connects the combustion unit supply pipeline and the atmosphere outlet of the exhaust pipeline, especially of the fuel supply system.

[0031] In a design solution, at least two (micro) gas turbines may provide the same power or different powers.

[0032] In a design solution, the combustion unit may have at least one second mass flow sensor arranged in the combustion unit supply pipeline and designed to measure the mass flow in the combustion unit supply pipeline.

[0033] In a design solution, the combustion unit may have at least one pressure regulating element arranged in the combustion unit supply pipeline and designed to regulate the fuel parameter value of the fuel in the combustion unit supply pipeline, especially the fuel pressure value. In a design solution, the at least one pressure regulating element may be designed to maintain the fuel parameter value, especially the fuel pressure value, between a lower pressure threshold and an upper pressure threshold.

[0034] In a design solution, the combustion unit may include at least one second pressure sensor and / or a second temperature sensor arranged in the combustion unit supply pipeline.

[0035] In a design solution, the power generation system may include a first proportional valve and at least one second proportional valve. The first proportional valve may be arranged in a first sub-pipeline of the combustion unit supply pipeline, upstream of the main burner. The second proportional valve may be arranged in a second sub-pipeline of the combustion unit supply pipeline, upstream of the pilot burner. The first proportional valve and the at least one second proportional valve may be designed to control the fuel ratios that should be supplied to the main burner and the pilot burner respectively.

[0036] In a design, at least one gas turbine may include a compressor unit, which is arranged upstream of the combustion unit and is fluidly connected to the combustion unit. In a design, the compressor unit may be fluidly connected to the mixing zone of at least one burner and may be designed to supply compressed air to the mixing zone. The mixing zone may be designed to mix fuel and compressed air.

[0037] In a design, at least one gas turbine may include a turbine unit, which is arranged downstream of the combustion unit and is fluidly connected to the combustion unit. In a design, at least one gas turbine may include a generator unit, which is operatively coupled to the turbine unit. In a design, the gas turbine may include a shaft, which is rotatably supported in a bearing housing. The rotor of the generator unit may be non-rotatably coupled to the turbine unit via the shaft. In a design, the turbine unit may be non-rotatably coupled to the compressor unit via the shaft.

[0038] In a design, at least one gas turbine may have a first gas turbine line and a second gas turbine line. The first gas turbine line may fluidly connect the turbine unit to the combustion unit. The second gas turbine line may be arranged downstream of the turbine unit and be fluidly connected to the turbine unit. The second gas turbine line may be designed to discharge the expanded fluid from the turbine unit. In a design, at least one gas turbine may include a third gas turbine line, which fluidly connects the compressor unit to the combustion unit and is designed to supply compressed air to the combustion unit.

[0039] In a design, at least one gas turbine may include at least one recuperator unit. The at least one recuperator unit may be arranged in the first gas turbine line and the second gas turbine line and is configured to transfer thermal power from the first gas turbine line to the second gas turbine line. In a design, the at least one recuperator unit may also be arranged between the third gas turbine line and the second gas turbine line and is configured to transfer thermal power from the third gas turbine line to the second gas turbine line. The at least one recuperator unit may also include a first recuperator unit and a second recuperator unit arranged at the above positions.

[0040] According to a third aspect of the present invention, a method for controlling a fuel supply system of a power generation system, in particular for controlling the fuel supply system according to the first aspect of the present invention, the method may include:

[0041] a) Query and obtain at least one target value of a fuel parameter related to the fuel in the decoupling container,

[0042] b) Determine at least one operating parameter value of a fuel compressor fluidly connected to the decoupling container based on the at least one target fuel parameter value.

[0043] c) Operate the fuel compressor based on the at least one operating parameter value so as to provide fuel having the at least one target fuel parameter value in the decoupling container.

[0044] The method can provide the above-mentioned advantageous effects of the fuel supply system and the power generation system. The method can be similarly used to control a power generation system according to the second aspect of the present invention. According to one aspect of the present invention, a method for controlling a power generation system, in particular a method for controlling a (micro) gas turbine system according to the second aspect of the present invention, can thus include all steps and features of the method. The fuel supply system and the power generation system can include the above-mentioned features or design solutions.

[0045] In a design solution, the method can further include:

[0046] Supply at least one combustion unit with fuel having the at least one target fuel parameter value from the decoupling container.

[0047] In a design solution, the at least one target fuel parameter value can be a target fuel pressure value in the decoupling container. In a design solution, the at least one operating parameter value can be the rotational speed of the fuel compressor.

[0048] In a design solution, the power generation system can include a first gas turbine and at least one second gas turbine. Querying and obtaining at least one target fuel parameter value can include:

[0049] Obtain a required first fuel parameter value related to the fuel required to supply the combustion unit of the first gas turbine;

[0050] Obtain at least one required second fuel parameter value related to the fuel required to supply the combustion unit of at least one second gas turbine;

[0051] Determine which fuel parameter value among the required first fuel parameter value and the required at least one second fuel parameter value has the highest fuel parameter value; and

[0052] Specify the target fuel parameter value such that it corresponds at least to the required highest fuel parameter value.

[0053] In a design solution, the method can further include:

[0054] Query and obtain at least one second target fuel parameter value related to the fuel in the fuel distribution pipeline, wherein the fuel distribution pipeline is arranged downstream of the decoupling container and is fluidly connected to the decoupling container;

[0055] Determine at least one operating parameter value of the fuel compressor based on the at least one second fuel parameter target value;

[0056] Operate the fuel compressor based on the at least one operating parameter so as to provide fuel having the at least one second fuel parameter target value in the fuel distribution line.

[0057] In a design solution, the at least one second fuel parameter target value may be a fuel mass flow target value in the fuel distribution line.

[0058] In a design solution, the method may be a computer-implemented method. Supplying fuel having the at least one fuel parameter target value to at least one combustion unit may be achieved herein by correspondingly controlling at least one discharge valve element, which is for example arranged between the decoupling container and the fuel distribution line. Operating the fuel compressor based on the at least one operating parameter may be achieved herein by controlling a drive device (such as an electric motor) that is coupled to the rotatable compressor impeller of the fuel compressor.

[0059] According to a fourth aspect of the present invention, a computer system is configured to implement the computer-implemented method according to the third aspect of the present invention.

[0060] According to a fifth aspect of the present invention, a computer program is configured to implement the computer-implemented method according to the third aspect of the present invention.

[0061] According to a sixth aspect of the present invention, a computer-readable medium or signal is provided, which stores the computer program according to the fifth aspect of the present invention. Description of the Drawings

[0062] Figure 1 Shows a schematic view of a fuel supply system for a power generation system according to the present invention, which is connected to at least one combustion unit;

[0063] Figure 2 is Figure 1 A detailed view of the fuel supply system and at least one combustion unit according to the present invention in;

[0064] Figure 3 Shows a power generation system according to the present invention having a fuel supply system and at least one gas turbine;

[0065] Figure 4 Shows a schematic flowchart of a method according to the present invention for controlling a fuel supply system;

[0066] Figure 5Shows a fuel supply system according to the invention with a decoupling container, which can have a plurality of container chambers. Detailed Description

[0067] Figure 1 Shows a schematic view of a fuel supply system 10 for a power generation system 1, in particular for a gas turbine system or a micro gas turbine system, according to an aspect of the invention.

[0068] The fuel supply system 10 includes a fuel supply line 110, a fuel main line 120, and a fuel distribution line 130. In addition, the fuel supply system further includes a fuel compressor 200 and a decoupling container 300. As Figure 1 schematically shown, the fuel supply line 110 is fluidly connected to the fuel compressor 200 at one end. At the other end, the fuel supply line 110 can be fluidly connected to a fuel source 11 to supply fuel from the fuel source 11 to the fuel compressor 200. In Figure 1 the shown fuel supply line 110 is fluidly connected to the fuel source 11. The decoupling container 300 is arranged downstream of the fuel compressor 200 and is fluidly connected to the fuel compressor 200 through the fuel main line 120. The fuel distribution line 130 is arranged downstream of the decoupling container 300 and is fluidly connected to the decoupling container at the first end. The fuel distribution line 130 can be fluidly connected to at least one combustion unit 20 of the power generation system 1, in particular a (micro) gas turbine system, at the second end, and is designed to supply fuel from the decoupling container 300 to the at least one combustion unit 20. In Figure 1 the fuel distribution line 130 is fluidly connected to at least one combustion unit 20.

[0069] Based on the fuel supply system 10 according to the present invention, one or more combustion units 20 can be reliably supplied with fuel. In particular, by providing a decoupling container 300, even at different loads, operating states (such as transient operation) and / or different power levels, one or more combustion units 20, 20a, 20b, 20c, 20d can be supplied using only a single, unique fuel supply system 10. The fuel compressor 200 is designed to provide fuel with a fuel pressure target value in the decoupling container 300. Thus, the fuel compressor 200 can provide the target pressure required for supply (or fuel with a fuel pressure target value) in the decoupling container 300, which can in particular enable component reduction in a power generation system 1 with multiple (micro) gas turbines 2, 2a, 2b. This can also reduce costs and / or the complexity of the overall system. Since only the fuel compressor 200 and the decoupling container 300 are required, the structural space or space requirements can be reduced. More precisely, many other components, such as a separate main gas compressor and / or pre-compressor (especially compared to having multiple separate fuel supply systems for each combustion unit), can be dispensed with by means of the decoupling container 300 in the fuel supply system 10. In addition, the decoupling container 300 and the fuel compressor 200 can be provided outside the combustion unit 20, which can simplify the system (in known systems, they are typically integrated into the respective combustion unit). The corresponding separate fuel supply devices for additional components, such as the main gas compressor and / or pre-compressor, can also be dispensed with. In addition, the application range of the fuel supply system 10 can be extended.

[0070] The decoupling container 300 can also be referred to as a decoupling tank. "The decoupling container 300 or the decoupling tank" shall mean, in this context, that there is an (intermediate) component provided between one or more compressors 200 and at least one downstream consumer of the compressed fuel, in particular at least one combustion unit 20. The decoupling container 300 enables the supply of one or more consumers, in particular one or more combustion units 20, from the decoupling container 300 of the (sole) fuel supply system 10. This is achieved in the following way: fuel with target values of fuel parameters, in particular a target value of fuel pressure, can be provided and / or stored in the decoupling container 300. The target value of the fuel parameter can correspond here to at least one maximum fuel pressure value required by one or more combustion units 20. In other words, the fuel line in which the fuel is compressed by a fuel compressor may not be directly connected to one or more consumers, but is "decoupled" from one or more consumers by an intermediate component in the form of the decoupling container 300. Of course, it is also possible to influence or prohibit the supply of fuel to the consumers by means of a shut-off valve or a throttle valve, but in this case, the fuel storage function cannot be provided and / or the fuel cannot be set to have target values of fuel parameters for multiple consumers, in particular combustion units 20. Sometimes it is also not possible to supply multiple consumers or combustion units 20 from the decoupling container 300, which at least partially require another fuel parameter value (such as a fuel pressure value) (for example, based on different load states, operating states, and / or power levels). In a design, the fuel supply line 110 can be optional, for example, in the case where the fuel compressor 200 is directly connectable to or connected to the fuel source 11. The decoupling container 300 can include at least one discharge valve element by means of which the discharge of fuel from the decoupling container 300 to the fuel distribution line 130 can be regulated.

[0071] The fuel can be a gaseous fuel, in particular propane, natural gas, hydrogen, or biogas. In a design, the fuel can also be liquid. In a design, a pre-evaporator can be provided in the fuel supply line, which is designed to convert the fuel into a gaseous form. The fuel source 11 can be a supply network, in particular a supply network for decentralized energy supply, for example. In a further design, the fuel source 11 can be a fuel storage tank.

[0072] Figure 2 is Figure 1 A detailed view of the fuel supply system 10 and at least one combustion unit 20 according to the present invention. As shown in Figure 1 and Figure 2As shown, the fuel supply system 10 can include exactly one fuel compressor 200, in particular a high-pressure fuel compressor. Since only one fuel compressor 200 is required (even when supplying fuel to multiple combustion units 20, 20a, 20b, 20c, 20d), components can be saved. Similarly, costs can be reduced and the complexity of the entire power generation system 1 can be decreased. In a design, the fuel compressor 200 can be a first fuel compressor, and the fuel supply system 10 can include at least one second fuel compressor (not shown in the figure), which can in particular be arranged downstream in the fuel main line 120 of the first fuel compressor. For example, at least one second fuel compressor can be provided to improve the redundancy of the system and / or to achieve the target pressure in the decoupling container through at least one intermediate pressure. For example, the first fuel compressor can be a low-pressure compressor and the at least one second fuel compressor can be a high-pressure compressor. For example, an intermediate cooling device can be provided between the two compressors to improve efficiency.

[0073] In a design, the fuel supply system 10 can include a fuel compressor bypass 160 that fluidly connects the fuel supply line 110 and the fuel main line 120 and is designed to supply fuel around the fuel compressor 200 from the fuel supply line 110 to the fuel main line 120. For example, the fuel source 11 can already provide fuel at a certain pressure level or include a pre-compressor that provides fuel at a certain pressure level. If this pressure level at least corresponds to the target fuel pressure value in the decoupling container 300 (for example when at least one combustion unit 20 is in a low-load state), the fuel compressor bypass 160 can be opened by means of a bypass valve element or closed again if necessary.

[0074] As Figure 1 and Figure 2 As schematically shown, the fuel distribution line 130 can be fluidly connected (or fluidly coupled) to at least two combustion units 20, 20a, 20b, 20c, 20d of the power generation system 1 and can be designed to supply fuel from the decoupling container 300 to the at least two combustion units 20, 20a, 20b, 20c, 20d. In Figure 1 and Figure 2The fuel distribution line 130 shown in [the figure] is connected to the at least two combustion units 20, 20a, 20b, 20c, 20d. In other words, it is possible to provide only one (separate) fuel supply system 10, which can supply fuel to multiple combustion units 20, 20a, 20b, 20c, 20d. This can be achieved by means of a decoupling container 300. The fuel distribution line 130 can in particular include at least two sub-lines 130a, 130b, 130c, 130d, each of which is connected to the at least two combustion units 20, 20a, 20b, 20c, 20d. The at least two sub-lines 130a, 130b, 130c, 130d can each branch off from the fuel distribution line 130 and fluidly connect the fuel distribution line 130 to the corresponding combustion units 20, 20a, 20b, 20c, 20d.

[0075] Refer to Figure 1 , Figure 2 and Figure 5, in the design solution, the fuel distribution pipeline 130 can have multiple or at least two sub-pipelines 130a, 130b, 130c, which are set to be independent of each other and connect the corresponding combustion units 20, 20a, 20b, 20c, 20d to the decoupling container 300 independently. In this design solution, the decoupling container 300 can include at least two container cavities 310a, 310b, 310c, which are set to be fluid-separated from each other. The container cavities 310a, 310b, 310c can each have the same volume or different volumes. Alternatively, multiple decoupling containers can also be provided, and each decoupling container has exactly one container cavity 310a, 310b, 310c. In still another design solution, multiple decoupling containers with multiple container cavities can also be provided. Each container cavity 310a, 310b, 310c can be connected to the corresponding independent sub-pipeline 130a, 130b, 130c of the fuel distribution pipeline 130. Therefore, each container cavity 310a, 310b, 310c can be independently connected to the corresponding combustion units 20, 20a, 20b, 20c, 20d through the corresponding sub-pipelines 130a, 130b, 130c. In these design solutions, the main fuel pipeline 120 can have at least two sub-pipelines 120a, 120b, 120c, and these sub-pipelines are each connected to the container cavities 310a, 310b, 310c. These at least two sub-pipelines 120a, 120b, 120c can each branch out from the main fuel pipeline 120 and connect the main fuel pipeline 120 to the corresponding container cavities 310a, 310b, 310c. Therefore, in these design solutions, each combustion unit can be fluidly connected or connected to the corresponding container cavity 310a, 310b, 310c through the independent sub-pipelines 130a, 130b, 130c of the fuel distribution pipeline 130, and each container cavity 310a, 310b, 310c is connected to the main fuel pipeline 120 through the corresponding sub-pipelines 120a, 120b, 120c of the main fuel pipeline 120. In the design solution, there can be exactly two, three, or four sub-pipelines 120a, 120b, 120c of the main fuel pipeline 120, exactly two, three, or four sub-pipelines 130a, 130b, 130c of the fuel distribution pipeline 130, and correspondingly two, three, or four container cavities 310a, 310b, 310c.

[0076] In all of the above embodiments (see Figure 2 and Figure 5), distribution valve elements 170a, 170b, 170c, 170d can be provided in at least one or each of at least two sub - pipelines 130a, 130b, 130c, 130d of the fuel distribution pipeline 130. The distribution valve element can be designed to control the fuel ratio to be supplied to the corresponding combustion unit among at least two combustion units 20, 20a, 20b, 20c, 20d. At least one distribution valve element 170a, 170b, 170c, 170d can be provided as an addition to or an alternative to the pressure regulating element 24 (to be elaborated further below) in at least one combustion unit 20. The distribution valve elements 170a, 170b, 170c, 170d can also be used as throttle valves and / or proportional valves. In a design, the distribution valve elements 170a, 170b, 170c, 170d can also act as pressure regulating elements. In another design, at least one distribution valve element 170a, 170b, 170c, 170d can be omitted. In one design, the fuel distribution pipeline 130 can be connected to only one combustion unit 20. In this design, only one distribution valve element can be provided. In another design, the pressure regulating element 24 in the combustion unit 20 may be sufficient, so the distribution valve element can be omitted. In a design where the fuel main pipeline 120 has at least two sub - pipelines 120a, 120b, 120c (see, for example Figure 5 ), distribution valve elements 121a, 121b, 121c can be provided in at least one or all of at least two sub - pipelines 120a, 120b, 120c of the fuel main pipeline 120. By means of the distribution valve elements 121a, 121b, 121c, fuel with specific fuel parameter values, especially fuel pressure, can be provided in the corresponding container cavities 310a, 310b, 310c. In other words, the corresponding fuel parameter values can be set in the corresponding container cavities 310a, 310b, 310c by the distribution valve elements 121a, 121b, 121c. If the distribution valve elements 121a, 121b, 121c are not provided, the same fuel parameter target values (for example, the fuel parameter values provided in the fuel main pipeline 120) can be set in each container cavity 310a, 310b, 310c.

[0077] In the design solution, the fuel distribution line 130 can be fluidly connected (or in fluid communication) with at least three combustion units 20a, 20b, 20c or at least four combustion units 20a, 20b, 20c, 20d, and can be designed to supply fuel from the decoupling container 300 to at least three combustion units 20a, 20b, 20c or at least four combustion units 20a, 20b, 20c, 20d. In one design solution, exactly one combustion unit 20, 20a can also be provided. The fuel distribution line 130 can be fluidly connected (or in fluid communication) with it and can be designed to supply fuel from the decoupling container 300 to it. As Figure 1 shown, exactly four combustion units 20a, 20b, 20c, 20d can be provided. As Figure 2 shown, exactly three combustion units 20a, 20b, 20c can be provided. In the design solution, exactly two combustion units 20a, 20b can be provided. The number of combustion units 20 can depend on the total power to be provided by the power generation system 1 (which will be further described below). Therefore, more than four combustion units can also be provided and supplied with fuel from the decoupling container 300.

[0078] The fuel supply system 10 can include exactly one decoupling container 300 (see, for example, Figure 1 or Figure 2 ). In the design solution, multiple decoupling containers 300 can also be provided. They can be arranged in parallel with each other, especially each connected to the fuel main line 120 and the fuel distribution line 130. In multiple gas turbines 2, 2a, 2b with greatly different power levels, energy optimization can be provided thereby. As described above, in the design solution, the decoupling container 300 can include multiple container cavities. Alternatively, the decoupling container 300 can include exactly one container cavity. In all design solutions, as Figure 2 shown, the fuel supply system 10 can include a decoupling container bypass 150 that fluidly connects the fuel main line 120 and the fuel distribution line 130 and is designed to supply the fuel around the decoupling container 300 from the fuel main line 120 to the fuel distribution line 130. In particular, a first bypass valve can be arranged in the decoupling container bypass 150. If multiple combustion units are supplied, and each of these combustion units includes the same power level and / or operating state or load state at a certain moment, the decoupling container bypass 150 can be used. If at least one combustion unit is operating at a low load state, the decoupling container bypass 150 can be used. If fuel is supplied to only one combustion unit 20, the decoupling container bypass 150 can also be used. If at least two independent sub-lines 130a, 130b, 130c of the fuel distribution line 130 are provided (see Figure 5), the decoupling container bypass 150 can connect the fuel main line 120 to the respective independent sub-lines 130a, 130b, 130c. In this case, the bypass can have multiple bypass sub-lines. They can each have a bypass valve.

[0079] As Figure 1 and Figure 2 shown, the fuel supply system 10 can include a fuel heat exchanger 400. The fuel heat exchanger can be arranged in the fuel main line 120, downstream of the fuel compressor 200, and can be designed to dissipate heat from the fuel main line 120. In particular, it may be necessary to limit the fluid temperature (e.g., gas temperature) in the fuel main line 120 within the maximum valve fluid temperature range. Correspondingly, the heat flow of the cooling medium (e.g., oil, gas, water or air) entering the heat exchanger from the fluid in the fuel main line 120 can be adjusted.

[0080] The fuel supply system 10 can include at least one exhaust line 140 that fluidly connects the fuel main line 120 and the atmosphere outlet 141 of the exhaust line 140 (or the fuel supply system 10) (see Figure 2 ). The fuel main line 120 can be exhausted through at least one exhaust line 140 so as to be able to reach the defined system state of the fuel supply system 10. At least one exhaust valve 142 can be provided in at least one exhaust line 140. The exhaust line 140 is designed to derive fuel from the fuel main line 120 when the at least one exhaust valve 142 is in the open position. At least one exhaust line 140 can be fluidly connected (or fluidly joined) to the combustion unit supply line 21 and can be designed to derive fuel from the combustion unit supply line 21. As Figure 2 shown, at least one exhaust line 140 can include a first exhaust line 140a that fluidly connects the fuel main line 120 and the atmosphere outlet 141 at a position between the fuel heat exchanger 400 and the fuel compressor 200. A first exhaust valve 142a can be arranged in the first exhaust line 140a. At least one exhaust line 140 can include a second exhaust line 140b that fluidly connects the fuel main line 120 and the atmosphere outlet 141 at a position between the fuel heat exchanger 400 and the decoupling container 300. A second exhaust valve 142b can be arranged in the second exhaust line 140b. At least one exhaust line 140 can include at least one third exhaust line 140c that fluidly connects the combustion unit supply line 21 of at least one combustion unit 20 and the atmosphere outlet 141. A third exhaust valve 142c can be arranged in at least one third exhaust line 140c.

[0081] As Figure 2As shown, the fuel supply system 10 may include at least one check valve 510 disposed in the fuel main line 120 upstream of the decoupling container 300. The check valve 510 may prevent compressed fuel from flowing back from the decoupling container 300, especially when the fuel compressor 200 is not operating or operating at a low speed (thus only establishing a pressure lower than the pressure in the decoupling container 300). In a design where there are at least two sub-lines 120a, 120b, 120c of the fuel main line 120 (see, for example Figure 5 ), check valves 510a, 510b, 510c may be alternatively or additionally provided in each of the sub-lines 120a, 120b, 120c.

[0082] Furthermore, the fuel supply system 10 may also include at least one first shut-off valve 520 disposed in the fuel main line 120 downstream of the fuel compressor 200. Alternatively or additionally, the shut-off valve may be disposed upstream of the fuel compressor 200. The first shut-off valve 520 may be used to quickly and centrally shut down or prohibit fuel supply, for example, in case of danger, emergency or maintenance.

[0083] As Figure 2 schematically shown, the filter device 600 may be disposed in the fuel supply line 110 upstream of the fuel compressor 200. Especially when the fuel is gaseous, the filter device 600 may especially be a gas filter device. Impurities may be separated from the fuel by the filter device 600.

[0084] The fuel supply system 10 may include at least one pressure reducing valve 530 disposed in the fuel distribution line 130 downstream of the decoupling container 300 (especially before any of the sub-lines 130a, 130b, 130c). The pressure reducing valve 530 may be used to adjust the pressure level directly downstream of the decoupling container 300. In a design where there are at least two independent sub-lines 130a, 130b, 130c of the fuel distribution line 120 (see, for example Figure 5 ), pressure reducing valves may be alternatively or additionally provided in each of the sub-lines 130a, 130b, 130c.

[0085] The fuel supply system 10 may include at least one first pressure sensor 700, 700a, 700b and / or first temperature sensor 710, 710a, 710b, which are arranged in the fuel supply line 110, the fuel main line 120 and / or the fuel distribution line 130. In a design, the fuel supply system 10 may include at least one first mass flow sensor 720, which is arranged in the fuel main line 120, upstream of the decoupling container 300, and is designed to measure the mass flow in the fuel main line 120 in front of the decoupling container 300. The fuel compressor 200 may be controlled by the sensor data of at least one pressure sensor, temperature sensor and / or mass flow sensor. In a design with at least two independent sub-lines 130a, 130b, 130c of the fuel distribution line 120 and / or at least two sub-lines 120a, 120b, 120c of the fuel distribution line 120 (see, for example Figure 5 ), pressure sensors, mass flow sensors and / or temperature sensors may be provided in the corresponding sub-lines.

[0086] Figure 3 Shown is a power generation system 1 according to the invention having a fuel supply system 10 and at least one gas turbine 2, 2a, 2b. The power generation system 1 includes a fuel supply system 10 according to the invention and at least one combustion unit 20. The at least one combustion unit 20 is arranged downstream of the fuel supply system 10 and is fluidly connected to the decoupling container 300 via the fuel distribution line 130, wherein the at least one combustion unit 20 is supplied with fuel from the decoupling container 300 (see also Figure 2 ).

[0087] The power generation system 1 (especially a gas turbine system or a micro gas turbine system) may include at least one (micro) gas turbine 2 having at least one combustion unit 20. The fuel distribution line 130 may be fluidly connected (or fluidly linked) to the combustion unit 20 of at least one gas turbine 2 of the power generation system 1 and may be designed to supply the combustion unit 20 of the at least one gas turbine 2 with fuel from the decoupling container 300. As Figure 3 shown, the power generation system 1 may include at least two (micro) gas turbines 2, 2a, 2b, each having combustion units 20, 20a, 20b. The fuel distribution line 130 may be fluidly connected (or fluidly linked) to the respective combustion units 20, 20a, 20b of at least two gas turbines 2, 2a, 2b of the power generation system 1 and may be designed to supply the respective combustion units 20, 20a, 20b of the at least two gas turbines 2, 2a, 2b with fuel from the decoupling container 300.

[0088] In the design, at least two gas turbines 2, 2a, 2b can provide the same power or different powers. In the design, the power generation system 1 can provide a total power of 1 MW. In a first example, the power generation system 1 can include three gas turbines, each with a power of 333 kW, to provide the total power. In this case, all gas turbines provide the same power (e.g., electrical power and / or thermal power). Fuel with a substantially the same pressure level and / or mass flow rate can be supplied from the decoupling container 300 to the respective combustion units 20a, 20b, 20c. In another example, four gas turbines can be provided, two of which each have a power of 200 kW and two of which each have a power of 300 kW, so as to be able to provide a total power of 1 MW. Thus, four gas turbines can be used, and these four gas turbines operate at least partially at different operating points or load states. The gas turbines with higher power may have a greater fuel demand (or require fuel with a higher pressure and / or mass flow rate) than the gas turbines with lower power. The decoupling container 300 can provide fuel with a fuel pressure target value that at least corresponds to the highest required fuel pressure value of the four gas turbines or the combustion units of the gas turbines. In the design, the decoupling container 300 can have a volume of approximately 2000 liters. The respective fuel demands (or fuel with required fuel parameter values, in particular fuel pressure and / or mass flow rate) of the respective combustion units 20 of the gas turbines 2, 2a, 2b can be adjusted by at least one pressure regulating element 24 (described further below), the corresponding proportional valve 22, and / or at least one distribution valve element 170a, 170b, 170c, 170d. For such a power generation system 1 with multiple gas turbines 2, 2a, 2b, only the (unique) fuel supply system 10 with the decoupling container 300 according to the present invention is required to supply the corresponding fuel. Thus, especially for a system with multiple gas turbines 2, 2a, 2b, there is no need to provide a fuel supply system 10 for each combustion unit 20 or gas turbine 2, so components can be saved, the required space requirements can be reduced, the complexity can be reduced, and / or the cost can be reduced. In this example, the highest required fuel pressure value in at least one of the gas turbines 2, 2a, 2b is approximately 12 bar. The fuel source 11 can provide fuel with a pressure value of approximately 5 bar. The fuel supply system 10 can preset the fuel pressure target value in the decoupling container 300 to be approximately 14 bar. This can be higher than the highest required fuel pressure value to take possible losses into account. The fuel compressor 200 can be correspondingly adjusted so as to provide the fuel with a pressure of approximately 5 bar from the fuel source 11 as approximately 14 bar in the decoupling container 300. The method 800 described below can be used to control the fuel supply system 10 and / or the power generation system 1.The above also applies to a design in which a plurality of container cavities 310a, 310b, 310c are provided (see Figure 5 ). These container cavities are fluidly connected to corresponding combustion units of the gas turbine via separate sub-lines 130a, 130b, 130c. Fuel having the required fuel parameter values corresponding to the respective gas turbine can be provided in the respective container cavities 310a, 310b, 310c by means of the said components (such as a pressure regulating element (to be described further below), a corresponding proportional valve and / or distribution valve element).

[0089] As Figure 2 shown, at least one combustion unit 20 can include a combustion unit supply line 21 and at least one burner 22, wherein the combustion unit supply line 21 fluidly connects the burner 22 to the fuel distribution line 130 (or the corresponding sub-line). At least one burner 22 can include a main burner 22a and a pilot burner 22b. The combustion unit 20 can have at least one second mass flow sensor 23, 23a, 23b, which is arranged in the combustion unit supply line 21 and is designed to measure the mass flow in the combustion unit supply line 21. In a design, a first mass flow sensor 23a can be provided at a first end of the combustion unit supply line 21, which first end is connected to the fuel distribution line 130. A second mass flow sensor 23b can be provided in the combustion unit supply line 21, in front of the burner 22.

[0090] As briefly mentioned above and schematically shown in Figure 2 , at least one combustion unit 20 can have at least one pressure regulating element 24, 24a, 24b, which is arranged in the combustion unit supply line 21 and is designed to adjust the required fuel parameter values of the fuel (such as fuel having a fuel pressure value) in the combustion unit supply line 21. The at least one pressure regulating element 24 can be designed to keep the fuel parameter values (especially the fuel pressure value) between a lower limit and an upper limit of a pressure threshold. In a design, the required fuel parameter values can correspond to a fuel pressure target value. In particular, a first pressure regulating element 24a and a second pressure regulating element 24b can be provided. The first pressure regulating element 24a can be designed to keep the fuel pressure value at or above the lower limit of the pressure threshold. The second pressure regulating element 24b can be designed to keep the fuel pressure value at or below the upper limit of the pressure threshold. Here, the first pressure regulating element 24a can be arranged in the combustion unit supply line 21, upstream of the second pressure regulating element 24b.

[0091] At least one combustion unit 20 may include at least one second pressure sensor 25 and / or a second temperature sensor 26, which are arranged in the combustion unit supply line 21. In addition, at least one combustion unit 20 may further include a first proportional valve 28a and at least one second proportional valve 28b. The first proportional valve 28a may be arranged in a first sub-line of the combustion unit supply line 21, upstream of the main burner 22a. The second proportional valve 28b may be arranged in a second sub-line of the combustion unit supply line 21, upstream of the pilot burner 22b. The first proportional valve 28a and at least one second proportional valve 28b are designed to control the fuel ratios that should be supplied to the main burner 22a and the pilot burner 22b, respectively. Alternatively or additionally, the fuel mass flow rate in the combustion unit supply line 21 and / or the fuel distribution line 130 may be adjusted according to the adjustable pressure value (especially the fuel pressure target value) in the fuel compressor 200, especially by means of the adjustable rotational speed of the fuel compressor 200.

[0092] In a design, at least one combustion unit 20 may have at least one second shut-off valve 27, 27a, 27b, which is arranged in the combustion unit supply line 21. At least one second shut-off valve 27, 27a, 27b may be arranged downstream of the pressure regulating element 24. As Figure 2 shown, two shut-off valves 27a, 27b may be arranged in the combustion unit supply line 21. Between these two shut-off valves 27a, 27b, a third exhaust line 140c may be connected to the combustion unit supply line 21. Similarly, a second pressure sensor 25 may be provided between the two shut-off valves 27a, 27b in order to control the third exhaust valve 142c according to the pressure sensor data.

[0093] In a design, as Figure 2 and Figure 3 shown, at least one gas turbine 2 may include a compressor unit 30, which is arranged upstream of the combustion unit 20 and is fluidly connected to the combustion unit. The fluid to be compressed (especially air) may be supplied to the compressor unit through the compressor unit supply line 71. The compressor unit 30 may be fluidly connected to the mixing zone of at least one burner 22 and may be designed to supply compressed air to the mixing zone. The mixing zone may be designed to mix fuel and compressed air. In a design, a mixing zone may be provided here in front of or in a section of the combustion chamber of at least one burner 22. The fuel may be preheated by the compressed hot air, thereby promoting the reaction kinetics in the mixing zone, especially in the combustion chamber.

[0094] At least one gas turbine 2 may include a turbine unit 40, which is arranged downstream of the combustion unit 20 and is fluidly connected to the combustion unit. As further shown in Figure 3 , at least one gas turbine 2 may include a generator unit 50, which is operatively coupled to the turbine unit 40. At least one gas turbine 2 may include a shaft 60, which is rotatably supported in a bearing housing. The rotor of the generator unit 50 may be non-rotatably coupled to the turbine impeller of the turbine unit 40 via the shaft 60. "Operatively (Betriebsmäßig)" means that the turbine unit can generate a rotational movement of the shaft by the expansion of the fluid from the combustion unit and then transfer this rotational movement to the rotor of the generator unit (the generator unit then generates electrical power). In a design, the turbine unit 40 may be non-rotatably coupled to the compressor unit 30 via the shaft 60. In a design, the electrical power generated by the generator unit 50 may be used to supply the compressor unit 30 to drive the compressor impeller. The fuel compressor 200 of the fuel supply system 10 may also be provided with the same function.

[0095] As Figure 3 shown, at least one gas turbine 2 may have a first gas turbine line 70a and a second gas turbine line 70b. The first gas turbine line 70a may fluidly connect the turbine unit 40 to the combustion unit 20. The second gas turbine line 70b may be arranged downstream of the turbine unit 40 and is fluidly connected to the turbine unit. The second gas turbine line 70b is designed to discharge the expanded fluid from the turbine unit 40.

[0096] In a design, at least one gas turbine 2 may include a third gas turbine line 70c, which fluidly connects the compressor unit 30 to the combustion unit 20 and is designed to supply the combustion unit 20 with the air compressed by the compressor unit 30.

[0097] In a design, at least one gas turbine 2 may include at least one recuperator unit 90. The at least one recuperator unit 90 may be arranged in the first gas turbine line 70a and the second gas turbine line 70b and is configured to transfer thermal power from the first gas turbine line 70a to the second gas turbine line 70b (not shown in Figure 3 ). Alternatively or additionally, the at least one recuperator unit 90 may be arranged between the third gas turbine line 70c and the second gas turbine line 70b and may be configured to transfer thermal power from the second gas turbine line 70b to the third gas turbine line 70c, in particular to the section of the third gas turbine line 70c between the recuperator 90 and the combustion unit 20 (as Figure 3As shown). The thermal power transferred through the recuperator 90 can be used to further heat the compressed air before the combustion unit, especially before the combustion chamber of the burner. Thereby, the efficiency of the power generation system 1 can be increased because the energy supplied by the heat supply no longer needs to be supplied by fuel energy. The recuperator unit can also include a first recuperator unit and a second recuperator unit arranged at the above positions. In one example, the following temperature sequence can occur under the rated load of the power generation system 1: In the third gas turbine pipeline 70c, the temperature of the air before entering the recuperator 90 (arranged as shown in Figure 3 shown) can be approximately 250°C. At the outlet of the recuperator 90, the temperature of the air can be approximately 500°C. At the outlet of at least one combustion chamber 20, 20a in the first gas turbine pipeline 70a, the fluid (especially the exhaust gas) can have a temperature of approximately 1050°C. After coming out of the turbine unit 40, the temperature of the expanded fluid in the second gas turbine pipeline 70b before entering the recuperator 90 can be approximately 700°C. At the outlet of the recuperator 90, the fluid in the second gas turbine pipeline 70b can have a temperature of approximately 550°C.

[0098] As further shown in Figure 3 , the second gas turbine pipeline 70b is thus fluidly connected to the fluid outlet 72. In a design, at least one additional heat exchanger 80 can be provided in the second gas turbine pipeline 70b. It can be arranged between the second gas turbine pipeline 70b downstream of at least one recuperator 70 and the external pipeline 73, and can be designed to transfer thermal power from the second gas turbine pipeline 70b to the external pipeline 73.

[0099] Figure 4 Shows a schematic flowchart of a method for controlling a fuel supply system 10 for a power generation system, especially a gas turbine system or a micro gas turbine system, according to the present invention. The fuel supply system 10 according to the present invention and the power generation system 1 including the fuel supply system 10 can be controlled by this method.

[0100] The method 800 for controlling the fuel supply system 10 according to the present invention includes:

[0101] a) Querying and obtaining 810 at least one fuel parameter target value related to the fuel in the decoupling container 300,

[0102] b) Determining 820 at least one operating parameter value of the fuel compressor 200 fluidly connected to the decoupling container 300 based on the at least one fuel parameter target value,

[0103] c) Operating the 830 fuel compressor 200 based on the at least one operating parameter so as to provide fuel having the at least one fuel parameter target value in the decoupling container 300.

[0104] The method 800 can provide the above-described advantageous effects of the fuel supply system 10 and the power generation system 1. In addition, optimized and customized control of the fuel supply system 10 or the power generation system 1 can be provided by means of the method 800. The method 800 can be similarly used to control the power generation system 1. Thus, according to one aspect of the present invention, a method for controlling a power generation system 1, in particular a (micro) gas turbine system, may include all the steps and features of the method 800. The fuel supply system 10 and the power generation system 1 may include the above-described features or design solutions. The fuel distribution line 130 is particularly arranged downstream of the decoupling container 300 and is fluidly connected to the decoupling container. The fuel distribution line 130 is fluidly connectable (or fluidly connected) to at least one combustion unit 20 of the power generation system 1 and is designed to supply fuel having the at least one fuel parameter target value from the decoupling container 300 to the at least one combustion unit 20.

[0105] The method 800 may further include supplying 840 fuel having the at least one fuel parameter target value from the decoupling container 300 to at least one combustion unit 20. The at least one fuel parameter target value may be a fuel pressure target value of the fuel in the decoupling container 300. The at least one operating parameter value may be the rotational speed of the fuel compressor 200.

[0106] As described above, the power generation system 1 may include the first gas turbines 2, 2a and at least one second gas turbine 2, 2b. Querying and obtaining 810 at least one fuel parameter target value may include:

[0107] Obtaining the required first fuel parameter value related to the fuel required to supply the combustion units 20, 20a of the first gas turbines 2, 2a, and

[0108] Obtaining the required at least one second fuel parameter value related to the fuel required to supply the combustion units 20, 20b of at least one second gas turbine 2, 2b.

[0109] In addition, querying and obtaining 810 at least one fuel parameter target value may further include:

[0110] Determining which fuel parameter value among the required first fuel parameter value and the required at least one second fuel parameter value has the required highest fuel parameter value, and

[0111] Specifying the fuel parameter target value to correspond at least to the required highest fuel parameter value.

[0112] In other words, the target value of the fuel parameter can be specified in the following manner: the target value of the fuel parameter is equal to or greater than the required maximum fuel parameter value. The required first fuel parameter value and the required at least one second fuel parameter value can each be the required fuel pressure value.

[0113] In the design, the method 800 may further include:

[0114] Querying and obtaining 850 at least one target value of a second fuel parameter related to the fuel in the fuel distribution line 130, where the fuel distribution line 130 is arranged downstream of the decoupling container 300 and is fluidly connected to the decoupling container;

[0115] Determining at least one operating parameter value of the fuel compressor 200 based on the at least one target value of the second fuel parameter, and

[0116] Operating the fuel compressor 200 based on the at least one operating parameter so as to provide fuel having the at least one target value of the second fuel parameter in the fuel distribution line 130.

[0117] The at least one target value of the second fuel parameter may be the fuel mass flow rate in the fuel distribution line 130. In the design, the at least one target value of the second fuel parameter may also be the fuel mass flow rate in the fuel supply line 21 of at least one combustion unit 20. In this case, the method may include querying and obtaining 850 at least one target value of a second fuel parameter related to the fuel in the fuel supply line 21 of the combustion unit, where the fuel supply line 21 of the combustion unit is arranged downstream of the decoupling container 300 and is fluidly connected to the fuel distribution line 130.

[0118] Additionally or alternatively, in a design where there are at least two container chambers 310a, 310b, 310c each fluidly connected to at least two combustion units, querying and obtaining 810 at least one target value of a fuel parameter may include:

[0119] Querying and obtaining 810 the target value of the fuel parameter related to the fuel in the first container chamber 310a of the decoupling container 300,

[0120] Querying and obtaining 810 at least one additional target value of a fuel parameter related to the fuel in at least one second container chamber 310b, 310c of the decoupling container 300.

[0121] In these designs, querying and obtaining 810 at least one target value of a fuel parameter may further include:

[0122] Obtain the required first fuel parameter values related to the fuel for the combustion units 20, 20a that are needed to supply the first gas turbines 2, 2a, wherein the first combustion units 20, 20a are connected to the first container cavity 310a, and

[0123] Obtain the required at least one second fuel parameter values related to the fuel for the combustion units 20, 20b that are needed to supply at least one second gas turbine 2, 2b, wherein the at least one second combustion units 20, 20b are connected to the at least one second container cavity 310a.

[0124] Since the respective combustion units 20, 20a, 20b are connected to the respective container cavities, the required first fuel parameter values can be associated with the fuel parameter target values in the first container cavity, and the required at least one second fuel parameter values can be associated with at least one further fuel parameter target values in the at least one second container cavity. Additionally, querying and obtaining 810 at least one fuel parameter target value may further include:

[0125] Determine which of the required first fuel parameter values and the required at least one second fuel parameter values has the required highest fuel parameter value, and

[0126] Specify the fuel parameter target value such that it corresponds at least to the required highest fuel parameter value.

[0127] Since the respective required fuel parameter values are associated with the respective fuel parameter target values, set the highest fuel parameter target value in the container cavity connected to the combustion unit having the required highest fuel parameter value. Then, at least one operating parameter value of the fuel compressor 200 that is fluidly connected to the first container cavity 310a and the at least one second container cavity can be determined accordingly (step 820). Additionally, the fuel compressor 200 can be operated based on the at least one operating parameter so as to provide fuel having the at least one fuel parameter target value in the first container cavity 310a and / or the at least one second container cavity 310b, 310c of the decoupling container 300. If the distribution valve elements 121a, 121b, 121c are not provided in the above-mentioned independent sub-lines 120a, 120b, 120c of the fuel main line, the same (highest) fuel parameter target value can be set in each container cavity. If the distribution valve elements 121a, 121b, 121c are provided, the method may include actuating these distribution valve elements 121a, 121b, 121c so as to set the fuel parameter target values corresponding to the respective required fuel parameter values in the respective container cavities 310a, 310b, 310c. In this case, the fuel compressor 200 is also operated such that the fuel compressor provides a fuel parameter target value that is equal to or greater than the required highest fuel parameter value.

[0128] In the design solution, the method 800 can be a computer-implemented method. Supplying 840 the fuel having the target value of the at least one fuel parameter to at least one combustion unit 20 can be achieved here by correspondingly controlling at least one discharge valve element, which is arranged, for example, between the decoupling container 300 and the fuel distribution line 130 (or the corresponding sub-lines 130a, 130b, 130c). Operating 830 the fuel compressor 200 based on at least one operating parameter can be achieved here by controlling a drive device (such as an electric motor) that is coupled to the rotatable compressor impeller of the fuel compressor 200.

[0129] According to another aspect of the invention, a computer system can be configured to implement the computer-implemented method. According to one aspect, a computer program can be configured to implement the computer-implemented method. In addition, a computer-readable medium or signal can be provided, which stores the computer program.

[0130] The computer-implemented method described above may include a computer or a computer network, or may be implemented by a computer or a computer network, where the computer or the computer network includes at least one processing unit (e.g., a processor) and at least one data memory (i.e., a memory). The program logic may be stored in at least one data memory in the form of executable code and implemented by at least one processing unit. Systems and subsystems (e.g., the power generation system 1 and / or the fuel supply system 10, and individual components such as fuel compressors and sensors) may send data to the at least one processing unit and, in an example, may also receive instructions from the at least one processing unit. The processing unit may in turn send queries initiated by the user and / or automatically generated to the power generation system 1 and / or the fuel supply system. The power generation system 1 and / or the fuel supply system are not limited to a specific hardware environment. Thus, the techniques described herein may be implemented by distributed devices connected via a network. The present disclosure also includes electrical signals and computer-readable media that define instructions which, when executed by a processing unit, implement the techniques described herein. As described above, the power generation system 1 and / or the fuel supply system may include at least one database. Alternatively or additionally, the power generation system 1 and / or the fuel supply system 10 may access a database in the cloud (via a communication interface). The power generation system 1 and / or the fuel supply system 10 may include (at least one) communication interface for coupling to various elements of the processing unit and / or the database. The communication interface may include one or more of the following elements: a network, the Internet, a local area network, a wireless local area network, a cellular broadband network, and / or a wired network. In an example, the power generation system 1 and / or the fuel supply system 10 may be associated with one or more functions via a server hosted in the cloud. The power generation system 1 and / or the fuel supply system 10 may also be connected to an external control and / or monitoring facility.

[0131] Although the invention has been described above and defined in the appended claims, it should be understood that the invention can alternatively be defined according to the following embodiments:

[0132] 1. A fuel supply system (10) for a power generation system (1), in particular for a micro gas turbine system, the fuel supply system comprising:

[0133] A fuel supply line (110), a fuel main line (120), and a fuel distribution line (130),

[0134] A fuel compressor (200), and

[0135] A decoupling container (300),

[0136] Wherein, a fuel supply pipeline (110) is fluidly connected to a fuel compressor (200) and can be connected to a fuel source (11) to supply fuel from the fuel source (11) to the fuel compressor (200).

[0137] Wherein, a decoupling container (300) is arranged downstream of the fuel compressor (200) and is fluidly connected to the fuel compressor (200) through a main fuel pipeline (120).

[0138] Wherein, a fuel distribution pipeline (130) is arranged downstream of the decoupling container (300) and is fluidly connected to the decoupling container, and

[0139] Wherein, the fuel distribution pipeline (130) can be fluidly connected to at least one combustion unit (20) of the power generation system (1) and is designed to supply fuel from the decoupling container (300) to the at least one combustion unit (20).

[0140] 2. The fuel supply system (10) according to Embodiment 1, wherein the fuel supply system (10) includes exactly one fuel compressor (200), especially a high-pressure fuel compressor.

[0141] 3. The fuel supply system (10) according to Embodiment 1 or Embodiment 2, wherein the fuel is a gaseous fuel, especially propane, natural gas, hydrogen or biogas.

[0142] 4. The fuel supply system (10) according to any one of the foregoing embodiments, wherein the fuel distribution pipeline (130) can be fluidly connected to at least two combustion units (20, 20a, 20b) of the power generation system (1) and is designed to supply fuel from the decoupling container (300) to the at least two combustion units (20, 20a, 20b).

[0143] Especially wherein, the fuel distribution pipeline (130) includes at least two sub-pipelines (130a, 130b), each of these sub-pipelines is connected to the at least two combustion units (20, 20a, 20b), and wherein, a distribution valve element (170a, 170b) is provided in at least one or each of these sub-pipelines (130a, 130b).

[0144] 5. The fuel supply system (10) according to any one of the foregoing embodiments, wherein the power generation system (1) includes at least one gas turbine (2) having at least one combustion unit (20), and wherein the fuel distribution line (130) can be fluidly connected to the combustion unit (20) of at least one gas turbine (2) of the power generation system (1) and is designed to supply fuel from the decoupling container (300) to the combustion unit (20) of the at least one gas turbine (2).

[0145] 6. The fuel supply system (10) according to any one of the foregoing embodiments, wherein the power generation system (1) includes at least two gas turbines (2, 2a, 2b), each having a combustion unit (20, 20a, 20b), and wherein the fuel distribution line (130) can be fluidly connected to the respective combustion units (20, 20a, 20b) of at least two gas turbines (2, 2a, 2b) of the power generation system (1) and is designed to supply fuel from the decoupling container (300) to the respective combustion units (20, 20a, 20b) of the at least two gas turbines (2, 2a, 2b).

[0146] 7. The fuel supply system (10) according to any one of the foregoing embodiments, the fuel supply system including a fuel heat exchanger (400) arranged in the fuel main line (120) downstream of the fuel compressor (200) and designed to dissipate heat from the fuel main line (120).

[0147] 8. The fuel supply system (10) according to any one of the foregoing embodiments, the fuel supply system including at least one exhaust line (140) fluidly connecting the fuel main line (120) and the atmosphere outlet (141) of the exhaust line (140).

[0148] 9. The fuel supply system (10) according to embodiment 8, wherein at least one exhaust valve (142) is provided in the at least one exhaust line (140), and wherein the exhaust line (140) is designed to discharge fuel from the fuel main line (120) when the at least one exhaust valve (142) is in the open position.

[0149] 10. The fuel supply system (10) according to embodiment 8 or embodiment 9, wherein the at least one exhaust line (140) can be fluidly connected to the combustion unit supply line (21) and is designed to discharge fuel from the combustion unit supply line (21).

[0150] 11. The fuel supply system (10) according to any one of the foregoing embodiments, the fuel supply system comprising exactly one decoupling container (300).

[0151] 12. The fuel supply system (10) according to any one of the foregoing embodiments 6 to 11, wherein the decoupling container (300) comprises at least two container chambers (310a, 310b, 310c), and wherein the fuel distribution line (130) comprises at least two independent sub-lines (130a, 130b, 130c), wherein each container chamber (310a, 310b, 310c) can be independently fluidly connected to a corresponding combustion unit (20, 20a, 20b) via a corresponding sub-line (130a, 130b, 130c), and in particular wherein the fuel main line (120) comprises at least two sub-lines (120a, 120b, 120c), each of which connects the fuel main line (120) to a corresponding container chamber (310a, 310b, 310c).

[0152] 13. The fuel supply system (10) according to any one of the foregoing embodiments, the fuel supply system comprising a decoupling container bypass (150), which fluidly connects the fuel main line (120) and the fuel distribution line (130) and is designed to supply fuel around the decoupling container (300) from the fuel main line (120) to the fuel distribution line (130).

[0153] 14. The fuel supply system (10) according to any one of the foregoing embodiments, the fuel supply system comprising at least one check valve (510), which is arranged in the fuel main line (120) upstream of the decoupling container (300).

[0154] 15. The fuel supply system (10) according to any one of the foregoing embodiments, wherein the fuel compressor (200) is designed to provide fuel with a target fuel pressure in the decoupling container (300).

[0155] 16. The fuel supply system (10) according to any one of the foregoing embodiments, the fuel supply system comprising a fuel compressor bypass (160), which fluidly connects the fuel supply line (110) and the fuel main line (120) and is designed to supply fuel around the fuel compressor (200) from the fuel supply line (110) to the fuel main line (120).

[0156] 17. The fuel supply system (10) according to any one of the foregoing embodiments, the fuel supply system comprising at least one first shut-off valve (520), the at least one first shut-off valve being arranged in the fuel main line (120), downstream or upstream of the fuel compressor (200).

[0157] 18. The fuel supply system (10) according to any one of the foregoing embodiments, the fuel supply system comprising a filter device (600), the filter device being arranged in the fuel supply line (110), upstream of the fuel compressor (200).

[0158] 19. The fuel supply system (10) according to any one of the foregoing embodiments, the fuel supply system comprising at least one pressure reducing valve (530), the at least one pressure reducing valve being arranged in the fuel distribution line (130), downstream of the decoupling container (300).

[0159] 20. The fuel supply system (10) according to any one of the foregoing embodiments, the fuel supply system comprising at least one first pressure sensor (700, 700a, 700b) and / or a first temperature sensor (710, 710a, 710b), the first pressure sensor and / or the first temperature sensor being arranged in the fuel supply line (110), the fuel main line (120) and / or the fuel distribution line (130), and in particular comprising at least one first mass flow sensor (720), the at least one first mass flow sensor being arranged in the fuel main line (120), upstream of the decoupling container (300), and being designed to measure the mass flow in the fuel main line (120) in front of the decoupling container (300).

[0160] 21. The fuel supply system (10) according to any one of the foregoing embodiments, wherein the fuel source (11) is a supply network.

[0161] 22. A power generation system (1), in particular a micro gas turbine system, the power generation system comprising:

[0162] The fuel supply system (10) according to any one of the foregoing embodiments, and

[0163] At least one combustion unit (20),

[0164] Wherein the at least one combustion unit (20) is arranged downstream of the fuel supply system (10) and is fluidly connected to the decoupling container (300) via the fuel distribution line (130), wherein the at least one combustion unit (20) is supplied with fuel from the decoupling container (300).

[0165] 23. The power generation system (1) according to embodiment 22, wherein the power generation system (1) includes at least one gas turbine (2), the gas turbine having at least one combustion unit (20), and wherein the fuel distribution line (130) is in fluid connection with the combustion unit (20) of at least one gas turbine (2) of the power generation system (1) and supplies fuel from the decoupling container (300) to the combustion unit (20) of the at least one gas turbine (2).

[0166] 24. The power generation system (1) according to embodiment 22 or embodiment 23, the power generation system including at least two combustion units (20, 20a, 20b), which are arranged downstream of the fuel supply system (10) and are in fluid connection with the decoupling container (300) through the fuel distribution line (130), wherein fuel from the decoupling container (300) is supplied to the at least two combustion units (20, 20a, 20b).

[0167] 25. The power generation system (1) according to any one of embodiments 22 to 24, wherein the power generation system (1) includes at least two gas turbines (2, 2a, 2b), each of the gas turbines having a combustion unit (20, 20a, 20b), and wherein the fuel distribution line (130) is in fluid connection with the respective combustion units (20, 20a, 20b) of at least two gas turbines (2, 2a, 2b) of the power generation system (1) and supplies fuel from the decoupling container (300) to the respective combustion units (20, 20a, 20b) of the at least two gas turbines (2, 2a, 2b).

[0168] 26. The power generation system (1) according to any one of embodiments 22 to 25, wherein the at least one combustion unit (20) includes a combustion unit supply line (21) and at least one burner (22), wherein the combustion unit supply line (21) fluidly connects the burner (22) with the fuel distribution line (130).

[0169] 27. The power generation system (1) according to embodiment 26, wherein the at least one burner (22) includes a main burner (22a) and a pilot burner (22b).

[0170] 28. The power generation system (1) according to embodiment 26 or embodiment 27, wherein the fuel supply system (10) includes at least one exhaust line (140), the at least one exhaust line fluidly connecting the combustion unit supply line (21) and the atmosphere outlet (141) of the exhaust line (140).

[0171] 29. The power generation system (1) according to any one of embodiments 25 to 28, wherein the at least two gas turbines (2, 2a, 2b) provide the same power or different powers.

[0172] 30. The power generation system (1) according to any one of embodiments 26 to 29, wherein the combustion unit (20) has at least one second mass flow sensor (23, 23a, 23b) which is arranged in the combustion unit supply line (21) and is designed to measure the mass flow in the combustion unit supply line (21).

[0173] 31. The power generation system (1) according to any one of embodiments 26 to 30, wherein the combustion unit (20) has at least one pressure regulating element (24, 24a, 24b) which is arranged in the combustion unit supply line (21) and is designed to regulate the fuel parameter value, in particular the fuel pressure value, of the fuel in the combustion unit supply line (21), and in particular wherein the at least one pressure regulating element (24) is designed to maintain the fuel pressure value between a lower pressure threshold and an upper pressure threshold.

[0174] 32. The power generation system (1) according to any one of embodiments 26 to 31, wherein the combustion unit (20) includes at least one second pressure sensor (25) and / or a second temperature sensor (26) which are arranged in the combustion unit supply line (21).

[0175] 33. The power generation system (1) according to any one of embodiments 27 to 32, the power generation system includes a first proportional valve (28a) and at least one second proportional valve (28b), wherein the first proportional valve (28a) is arranged in a first sub-line of the combustion unit supply line (21) upstream of the main burner (22a), and wherein the second proportional valve (28b) is arranged in a second sub-line of the combustion unit supply line (21) upstream of the pilot burner (22b),

[0176] In particular, wherein the first proportional valve (28a) and the at least one second proportional valve (28b) are designed to control the fuel ratios to be supplied to the main burner (22a) and the pilot burner (22b) respectively.

[0177] 34. The power generation system (1) according to any one of embodiments 22 to 33, wherein the at least one gas turbine (2) includes a compressor unit (30) which is arranged upstream of the combustion unit (20) and is fluidly connected to the combustion unit.

[0178] 35. The power generation system (1) according to embodiment 34, which is subordinate to embodiment 26, wherein the compressor unit (30) is fluidly connected to the mixing zone of at least one burner (22) and is designed to supply compressed air to the mixing zone, in particular wherein the mixing zone is designed to mix fuel and compressed air.

[0179] 36. The power generation system (1) according to any one of embodiments 22 to 35, wherein the at least one gas turbine (2) comprises a turbine unit (40), which is arranged downstream of the combustion unit (20) and is fluidly connected to the combustion unit.

[0180] 37. The power generation system (1) according to embodiment 36, wherein the at least one gas turbine (2) comprises a generator unit (50), which is operatively coupled to the turbine unit (40).

[0181] 38. The power generation system (1) according to embodiment 37, which is subordinate to embodiment 34, wherein the gas turbine (2) comprises a shaft (60), which is rotatably supported in a bearing housing, wherein the rotor of the generator unit (50) is non-rotatably coupled to the turbine unit (40) via the shaft (60), and in particular wherein the turbine unit (40) is non-rotatably coupled to the compressor unit (30) via the shaft (60).

[0182] 39. The power generation system (1) according to any one of embodiments 36 to 38, wherein the at least one gas turbine (2) has a first gas turbine line (70a) and a second gas turbine line (70b), wherein the first gas turbine line (70a) fluidly connects the turbine unit (40) to the combustion unit (20), and wherein the second gas turbine line (70b) is arranged downstream of the turbine unit (40) and is fluidly connected to the turbine unit, wherein the second gas turbine line (70b) is designed to discharge the expanded fluid from the turbine unit (40).

[0183] 40. The power generation system (1) according to any one of embodiments 34 to 39, wherein the at least one gas turbine (2) comprises a third gas turbine line (70c), which fluidly connects the compressor unit (30) to the combustion unit (20) and is designed to supply the combustion unit (20) with air compressed by the compressor unit (30).

[0184] 41. The power generation system (1) according to embodiment 39 or embodiment 40, wherein the at least one gas turbine (2) includes at least one recuperator unit arranged between a first gas turbine pipeline (70a) and a second gas turbine pipeline (70b) and configured to transfer thermal power from the first gas turbine pipeline (70a) to the second gas turbine pipeline (70b), and / or the at least one recuperator unit is arranged between a third gas turbine pipeline (70c) and the second gas turbine pipeline (70b) and configured to transfer thermal power from the third gas turbine pipeline (70c) to the second gas turbine pipeline (70b).

[0185] 42. A method (800) for controlling a fuel supply system (10) of a power generation system (1), in particular for controlling the fuel supply system (10) according to any one of embodiments 1 to 21, the method comprising:

[0186] a) Querying and obtaining (810) at least one target value of a fuel parameter related to the fuel in the decoupling container (300),

[0187] b) Determining (820) at least one operating parameter value of a fuel compressor (200) fluidly connected to the decoupling container (300) based on the at least one target value of the fuel parameter,

[0188] c) Operating (830) the fuel compressor (200) based on the at least one operating parameter so as to provide fuel having the at least one target value of the fuel parameter in the decoupling container (300).

[0189] 43. The method (800) according to embodiment 42, the method further comprising:

[0190] Supplying (840) fuel having the at least one target value of the fuel parameter from the decoupling container (300) to at least one combustion unit (20).

[0191] 44. The method (800) according to embodiment 42 or embodiment 43, wherein the at least one target value of the fuel parameter is a target value of the fuel pressure in the decoupling container (300).

[0192] 45. The method (800) according to any one of embodiments 42 to 44, wherein the at least one operating parameter value is the rotational speed of the fuel compressor (200).

[0193] 46. The method (800) according to any one of embodiments 42 to 45, wherein the power generation system (1) includes a first gas turbine (2, 2a) and at least one second gas turbine (2, 2b), and wherein querying and obtaining (810) at least one fuel parameter target value includes:

[0194] obtaining a required first fuel parameter value related to the fuel required to supply the combustion unit (20, 20a) of the first gas turbine (2, 2a),

[0195] obtaining at least one required second fuel parameter value related to the fuel required to supply the combustion unit (20, 20b) of at least one second gas turbine (2, 2b),

[0196] determining which of the required first fuel parameter value and the at least one required second fuel parameter value has the highest fuel parameter value, and

[0197] specifying the fuel parameter target value to correspond at least to the required highest fuel parameter value.

[0198] 47. The method (800) according to any one of embodiments 42 to 46, the method further comprising:

[0199] querying and obtaining (850) at least one second fuel parameter target value related to the fuel in the fuel distribution line (130), wherein the fuel distribution line (130) is arranged downstream of the decoupling container (300) and is in fluid connection with the decoupling container,

[0200] determining (820) at least one operating parameter value of the fuel compressor (200) based on the at least one second fuel parameter target value,

[0201] operating (830) the fuel compressor (200) based on the at least one operating parameter to provide fuel having the at least one second fuel parameter target value in the fuel distribution line (130),

[0202] In particular, wherein the at least one second fuel parameter target value is the fuel mass flow rate in the fuel distribution line (130).

[0203] 48. The method (800) according to any one of embodiments 42 to 47, wherein the method is a computer-implemented method.

[0204] 49. A computer system configured to implement the computer-implemented method according to embodiment 48.

[0205] 50. A computer program configured to implement the computer-implemented method according to Embodiment 48.

[0206] 51. A computer-readable medium or signal storing the computer program of Embodiment 50.

Claims

1. A fuel supply system (10) for a power generation system (1), the fuel supply system comprising: A fuel supply pipeline (110), a fuel main pipeline (120) and a fuel distribution pipeline (130), a fuel compressor (200), and Decoupling container (300), The fuel supply pipeline (110) is fluidically connected to the fuel compressor (200) and can be connected to a fuel source (11) so as to supply fuel from the fuel source (11) to the fuel compressor (200). The decoupling container (300) is arranged downstream of the fuel compressor (200) and is fluidically connected to the fuel compressor (200) via the main fuel line (120). wherein the fuel distribution pipeline (130) is arranged downstream of the decoupling container (300) and is fluidically connected to the decoupling container, and The fuel distribution line (130) is fluidically connectable to at least one combustion unit (20) of the power generation system (1) and is designed to supply the at least one combustion unit (20) with fuel from the decoupling container (300).

2. The fuel supply system (10) according to claim 1, wherein: The fuel supply system (10) comprises exactly one fuel compressor (200).

3. The fuel supply system (10) according to claim 1, wherein: The fuel distribution line (130) can be fluidically connected to at least two combustion units (20, 20a, 20b) of the power generation system (1) and is designed to supply the at least two combustion units (20, 20a, 20b) with fuel from the decoupling container (300).

4. The fuel supply system (10) according to claim 3, wherein: The fuel distribution pipeline (130) comprises at least two sub-pipelines (130a, 130b), each of which is connected to the at least two combustion units (20, 20a, 20b), and wherein a distribution valve element (170a, 170b) is arranged in at least one or each of the sub-pipelines (130a, 130b).

5. The fuel supply system (10) of claim 1, comprising exactly one decoupling container (300).

6. The fuel supply system (10) according to claim 3, wherein: The decoupling container (300) comprises at least two container cavities (310a, 310b, 310c), and the fuel distribution pipeline (130) comprises at least two independent sub-pipelines (130a, 130b, 130c), and each container cavity (310a, 310b, 310c) can be independently connected to the fluid of the corresponding combustion unit (20, 20a, 20b) through the corresponding sub-pipeline (130a, 130b, 130c), and the main fuel pipeline (120) comprises at least two sub-pipelines (120a, 120b, 120c), and the sub-pipelines respectively connect the main fuel pipeline (120) to the corresponding container cavity (310a, 310b, 310c).

7. The fuel supply system (10) according to claim 1, wherein: The fuel compressor (200) is designed to provide fuel having a fuel pressure target value in the decoupling container (300).

8. The fuel supply system (10) according to claim 1, wherein: The fuel source (11) is a supply network.

9. The fuel supply system (10) according to claim 1, wherein: The fuel is propane, natural gas, hydrogen or biogas.

10. A power generation system (1), comprising: A fuel supply system (10) according to any one of claims 1 to 9, and at least one combustion unit (20), The at least one combustion unit (20) is arranged downstream of the fuel supply system (10) and is fluidically connected to the decoupling container (300) via the fuel distribution line (130), wherein the at least one combustion unit (20) is supplied with fuel from the decoupling container (300).

11. The power generation system (1) according to claim 10, wherein: The power generation system (1) comprises at least two gas turbines (2, 2a, 2b), each of the gas turbines having a combustion unit (20, 20a, 20b), and wherein the fuel distribution pipeline (130) is fluidically connected to the corresponding combustion units (20, 20a, 20b) of the at least two gas turbines (2, 2a, 2b) of the power generation system (1) and supplies the corresponding combustion units (20, 20a, 20b) of the at least two gas turbines (2, 2a, 2b) with fuel from the decoupling container (300).

12. The power generation system (1) according to claim 11, wherein: The at least two gas turbines (2, 2a, 2b) provide the same power or different powers.

13. A power generation system (1) according to any one of claims 10 to 12, wherein: The combustion unit (20) has at least one pressure regulating element (24, 24a, 24b), which is arranged in the combustion unit supply line (21) and is designed to regulate a fuel parameter value of the fuel in the combustion unit supply line (21), and wherein the at least one pressure regulating element (24) is designed to maintain the fuel pressure value between a lower pressure threshold and an upper pressure threshold.

14. The power generation system (1) according to claim 10, wherein: At least one gas turbine (2) comprises a turbine unit (40) which is arranged downstream of the combustion unit (20) and is fluidically connected to the combustion unit, and wherein the at least one gas turbine (2) comprises a generator unit (50) which is operatively coupled to the turbine unit (40).

15. The power generation system (1) according to claim 10, wherein: The power generation system (1) is a micro gas turbine system.

16. A method (800) for controlling a fuel supply system (10) of a power generation system (1), the method comprising: a) querying and obtaining (810) at least one fuel parameter target value associated with the fuel in the decoupling container (300), b) determining (820) at least one operating parameter value of a fuel compressor (200) fluidically connected to the decoupling container (300) based on the at least one fuel parameter target value, c) operating (830) the fuel compressor (200) based on the at least one operating parameter so as to provide fuel having the at least one fuel parameter target value in the decoupling container (300).

17. The method (800) of claim 16, wherein: The at least one fuel parameter target value is a fuel pressure target value in the decoupling container (300), and wherein the at least one operating parameter value is a rotational speed of the fuel compressor (200).

18. The method (800) of claim 16 or claim 17, wherein: The power generation system (1) comprises a first gas turbine (2, 2a) and at least one second gas turbine (2, 2b), wherein querying and obtaining (810) at least one fuel parameter target value comprises: obtaining a required first fuel parameter value related to the fuel required to supply a combustion unit (20, 20a) of the first gas turbine (2, 2a), obtaining at least one required second fuel parameter value related to the fuel required to supply a combustion unit (20, 20b) of the at least one second gas turbine (2, 2b), determining which of the desired first fuel parameter value and the desired at least one second fuel parameter value has a highest fuel parameter value, and The fuel parameter target value is defined so as to correspond to at least the desired maximum fuel parameter value.

19. The method (800) of claim 16, wherein: The method is a computer-implemented method.

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