FUEL SUPPLY SYSTEM FOR A POWER GENERATION SYSTEM

Abstract

Fuel supply system (10) for a power generation system (1), comprising: a fuel supply line (110), a main fuel line (120) and a fuel distribution line (130), a fuel compressor (200), and a decoupling tank (300), wherein the fuel supply line (110) is fluidically connected to the fuel compressor (200) and can be connected to a fuel source (11) in order to supply fuel from the fuel source (11) to the fuel compressor (200), wherein the decoupling tank (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 line (130) is arranged downstream of the decoupling tank (300) and fluidically connected to it, and wherein the fuel distribution line (130) is fluidically connectable 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 tank (300), characterized in that the decoupling container (300) comprises at least two container chambers (310a, 310b, 310c) and that the fuel distribution line (130) comprises at least two separate partial lines (130a, 130b, 130c), wherein each container chamber (310a, 310b, 310c) can be fluidically connected separately to a respective combustion unit (20, 20a, 20b) via a corresponding partial line (130a, 130b, 130c).

Description

Technical field

[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 relates to a power generation system, in particular a (micro) gas turbine system, comprising such a fuel supply system, and to a method for controlling the fuel supply system for a power generation system. background

[0002] Power generation systems, particularly gas turbine systems or micro gas turbine systems, are used to generate electrical power and / or heat by burning a gaseous or liquid fluid (especially fuel). The medium burned in a combustion unit can be expanded in a turbine, which in turn can be functionally connected to a generator to produce electrical power. Additionally or alternatively, a heat exchanger can be provided to utilize the waste heat generated by combustion. Depending on the requirements, power generation systems can have one or more (micro) gas turbines, each with its own combustion unit. The gas turbines can each provide the same power output or different power outputs.Especially for power generation systems comprising multiple (micro) gas turbines, each with a combustion unit, a separate fuel supply system is required for each turbine due to differing operating conditions (e.g., transient operation) and / or varying load conditions. Consequently, each combustion unit is supplied by its own fuel supply system to provide fuel at a specific pressure, temperature, and / or mass flow rate (or flow rate) to each individual combustion unit, tailored to the corresponding power output, operating condition, and / or load condition.

[0003] Document US 3,766,734 A describes a fuel control system for a gas turbine for the simultaneous combustion of a liquid fuel and a gaseous fuel, according to the availability of the gaseous fuel and with preference for it. The gas turbine can be used as a marine propulsion system for a tanker. The system allows operation with two fuels in a selected ratio between the fuels or automatic transition to single-fuel operation if one of the two fuels falls below a minimum value. Furthermore, EP 4,102,040 A1 relates to a system for an aircraft engine. Reference is also made to CN 2,175,584,288 U, which deals with a fuel system for a micro gas turbine; JP 2002-195,055 A, which deals with a micro gas turbine; and CN 2,058,585,495 U, which deals with an internal combustion engine.

[0004] Each fuel supply system typically comprises several components such as lines, seals, valves, and pumps or compressors. Some components, like actuated valves, can be actively controlled to supply fuel with specific parameters such as a flow rate. Other components may be safety components, designed to meet specific safety standards for the overall system and ensure that no critical incidents occur. These safety standards allow for various fuel supply system configurations. However, known fuel supply systems, and in particular one fuel supply system per gas turbine, require not only a pre-compressor but also a main gas compressor to deliver a specific pressure or mass flow rate to the respective combustion units.Power generation systems with one or more known fuel supply systems require a large number of components, resulting in high costs, a large footprint, and high complexity. Furthermore, the application range of known fuel supply systems is limited.

[0005] The object of the present invention is to provide an improved fuel supply system for a power generation system, in particular for a (micro) gas turbine system. Summary of the invention

[0006] 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, according to claim 1. Furthermore, the present invention relates to a power generation system, in particular a (micro) gas turbine system, with such a fuel supply system according to claim 8, and to a method for controlling a fuel supply system for a power generation system according to claim 12. The dependent claims describe advantageous embodiments of the fuel supply system, the power generation system, and the method.

[0007] 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 main fuel line, and a fuel distribution line. The fuel supply system further comprises a fuel compressor and a decoupling tank. The fuel supply line is fluidically connected to the fuel compressor and can be connected to a fuel source to supply fuel from the fuel source to the fuel compressor. The decoupling tank is arranged downstream of the fuel compressor and fluidly connected to the fuel compressor via the main fuel line. The fuel distribution line is arranged downstream of the decoupling tank and fluidly connected to it.The fuel distribution line is fluidically connectable to at least one combustion unit of a power generation system and is designed to supply this combustion unit with fuel from the decoupling tank. The decoupling tank comprises at least two chambers. The fuel distribution line comprises at least two separate sections. Each chamber is separately fluidically connectable to a respective combustion unit via a corresponding section.

[0008] The fuel supply system according to the invention enables the reliable supply of fuel to one or more combustion units. In particular, the inclusion of a decoupling tank allows one or more combustion units to be supplied with a single fuel supply system, even under varying load conditions, operating conditions (e.g., transient operation), and / or power levels. The fuel compressor provides the required target pressure in the decoupling tank, which, especially in power generation systems with multiple (micro) gas turbines, leads to a reduction in the number of components. This also reduces costs and / or the complexity of the system. Since only one fuel compressor and decoupling tank are required, the installation space can be reduced.More precisely, the decoupling tank in the fuel supply system eliminates the need for many other components, such as individual main gas compressors and / or pre-compressors (especially compared to multiple fuel supply systems). Furthermore, the decoupling tank and the fuel compressor can be located outside the combustion unit, simplifying the system (in conventional systems, these are often integrated into the respective combustion units). Additional components, such as separate oil supplies for the main gas compressors and / or pre-compressors, can be omitted. This also expands the application range of the fuel supply system.

[0009] The decoupling tank can also be referred to as a decoupling reservoir. In this context, "decoupling tank" means an (intermediate) component located between one or more compressors and at least one downstream consumer (in particular, the at least one combustion unit) of compressed fuel. The decoupling tank enables one or more consumers, especially one or more combustion units, to be supplied from the decoupling reservoir of the fuel supply system. This is achieved by providing and / or storing fuel with a target fuel parameter value, in particular a target fuel pressure value, in the decoupling tank. The target fuel pressure value can correspond to the highest required target fuel pressure value of the one or more combustion units.In other words, a fuel line in which fuel is compressed by a compressor is not directly connected to one or more consumers, but is "decoupled" from them via an intermediate component in the form of a decoupling tank. Of course, the fuel supply to a consumer can also be influenced or stopped by a shut-off valve or throttle valve; however, in this case, the fuel storage function and / or the provision of fuel with the target fuel parameter value cannot be guaranteed. In particular, it is not possible to supply multiple consumers or combustion units from the decoupling tank, each of which may have at least partially different target fuel parameter values ​​(e.g., fuel pressure values) due to different load conditions, operating states, and / or performance levels.In some designs, the fuel supply line may be optional, for example if the fuel compressor can be directly connected to or is connected to the fuel source.

[0010] In some configurations, the fuel supply system can comprise 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.

[0011] In certain configurations, the fuel distribution line can be fluidically connected to at least two combustion units of the power generation system and designed to supply these units with fuel from the decoupling tank. For example, the two combustion units may have different power levels, different load conditions, and / or different operating conditions. They may also require different fuel parameter values, such as different fuel pressures. The decoupling tank can be designed to supply each of the two combustion units with fuel at the required fuel parameter value. The decoupling tank can also contain fuel with a target fuel parameter value that corresponds to the highest required fuel parameter value of each of the two combustion units.The fuel distribution line can comprise at least two sub-lines, each of which is connected to at least two combustion units.

[0012] In various configurations, the power generation system can include at least one gas turbine, which has at least one combustion unit. The fuel distribution line can be fluidically connected to the combustion unit of the at least one gas turbine of the power generation system and designed to supply the combustion unit of the at least one gas turbine with fuel from the decoupling tank.

[0013] In various configurations, the power generation system can comprise at least two gas turbines, each with a combustion unit. The fuel distribution line can be fluidically connected to the respective combustion unit of the at least two gas turbines of the power generation system and designed to supply the respective combustion units of the at least two gas turbines with fuel from the decoupling tank.

[0014] In some configurations, the fuel supply system may include at least one fuel heat exchanger. This can be located in the main fuel line downstream of the fuel compressor and designed to dissipate heat from the main fuel line.

[0015] In some configurations, the fuel supply system may include at least one vent line which fluidically connects the main fuel line and an atmospheric outlet of the vent line or the fuel supply system.

[0016] In some configurations, the fuel supply system may include at least one vent valve in the at least one vent line. The vent line may be designed to discharge fuel from the main fuel line when the at least one vent valve is open.

[0017] In some configurations, at least one vent line can be fluidically connected to a combustion unit supply line and designed to remove fuel from the combustion unit supply line.

[0018] In some configurations, the fuel supply system can comprise exactly one decoupling tank. Other configurations can include multiple decoupling tanks, which can be connected in parallel. This allows for energy optimization when multiple gas turbines have significantly different power outputs. In other configurations, the decoupling tanks can also be connected in series. The main fuel line can comprise at least two sub-lines, each connecting the main fuel line to a specific tank chamber.

[0019] In some configurations, the fuel supply system can include a decoupling tank bypass that fluidically connects the main fuel line and the fuel distribution line. The decoupling tank bypass can be designed to supply fuel from the main fuel line to the fuel distribution line around the decoupling tank. In particular, the decoupling tank bypass can be used when supplying multiple combustion units of gas turbines, each with the same (low) power levels, or when only the combustion unit of a single gas turbine is being supplied with fuel.

[0020] In some embodiments, the fuel supply system may include at least one check valve located upstream of the decoupling tank in the main fuel line. The check valve can prevent backflow of compressed fuel from the decoupling tank, particularly when the fuel compressor is not operating or is operating at low speeds (and thus only a pressure is built up that is lower than the pressure in the decoupling tank).

[0021] In some configurations, the fuel compressor can be designed to supply fuel with a target fuel parameter value, in particular a target fuel pressure value, in the decoupling tank.

[0022] In some configurations, the fuel supply system can include a fuel compressor bypass that fluidically connects the fuel supply line and the main fuel line and is designed to divert fuel from the fuel supply line to the main fuel line around the fuel compressor. For example, fuel can already be supplied to the fuel source at a certain pressure level. If this pressure level corresponds at least to the target fuel pressure value in the decoupling tank, e.g., during low-load conditions of at least one combustion unit, the fuel compressor bypass can be opened.

[0023] In some configurations, the fuel supply system can include at least one initial shut-off valve, which is located in the main fuel line downstream or upstream of the fuel compressor. This shut-off valve allows for a quick and centralized shutdown or interruption of the fuel supply, for example, in a hazardous, emergency, or maintenance situation.

[0024] In some embodiments, the fuel supply system can include at least one filter device arranged in the fuel supply line upstream of the fuel compressor. In other embodiments, the fuel supply system can include at least one pressure reducing valve arranged in the fuel distribution line downstream of the decoupling tank.

[0025] In some embodiments, the fuel supply system may include at least one first pressure sensor and / or one first temperature sensor, which is arranged in the fuel supply line, the main fuel line, and / or the fuel distribution line. In other embodiments, the fuel supply system may include at least one first mass flow sensor, which is arranged in the main fuel line upstream of the decoupling tank and is designed to measure a mass flow in the main fuel line upstream of the decoupling tank.

[0026] In some configurations, the fuel source can be a supply network, in particular a supply network of, for example, a decentralized energy supply. In other configurations, the fuel source can be a fuel storage device.

[0027] According to a second aspect of the present invention, a power generation system, in particular a gas turbine system or a micro gas turbine system, comprises a fuel supply system according to the 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 fluidically connected to the decoupling tank via the fuel distribution line, the at least one combustion unit being supplied with fuel from the decoupling tank. This system can also provide the advantageous effects of the power generation system described above. A micro gas turbine system is understood to be a system comprising one or more micro gas turbines, each capable of providing a power output of 30 kW to 500 kW.However, the designs described here can also be applied to higher-power gas turbine systems.

[0028] In various configurations, the power generation system can include at least one (micro) gas turbine, which has at least one combustion unit. The fuel distribution line can be fluidically connected to the combustion unit of the at least one gas turbine of the power generation system and supply the combustion unit of the at least one gas turbine with fuel from the decoupling tank.

[0029] In some embodiments, the power generation system can comprise at least two combustion units, which are arranged downstream of the fuel supply system and are fluidically connected to the decoupling tank via the fuel distribution line. The at least two combustion units can be supplied with fuel from the decoupling tank. The fuel distribution line can have several sub-lines, each branching off from the main fuel distribution line to the respective combustion units. In other embodiments, the fuel distribution line can have several sub-lines that are separate from each other and connect the respective combustion units separately to the decoupling tank.

[0030] In various configurations, the power generation system can comprise at least two (micro) gas turbines, each with a combustion unit. The fuel distribution line can be fluidically connected to the respective combustion unit of the at least two gas turbines of the power generation system and supply the respective combustion units of the at least two gas turbines with fuel from the decoupling tank.

[0031] In some embodiments, the at least one combustion unit can comprise a combustion unit supply line and at least one burner. The combustion unit supply line can fluidically connect the burner to the fuel distribution line. In other embodiments, the at least one burner can comprise a main burner and a pilot burner.

[0032] In some embodiments, the fuel supply system can include at least one vent line which fluidically connects the combustion unit supply line and an atmosphere outlet of the vent line, in particular of the fuel supply system.

[0033] In various configurations, at least two (micro) gas turbines can provide the same power output, or different power outputs.

[0034] In some embodiments, the combustion unit may have at least one second mass flow sensor, which is arranged in the combustion unit supply line and is designed to measure a mass flow in the combustion unit supply line.

[0035] In certain embodiments, the combustion unit can have at least one pressure-regulating element, which is arranged in the combustion unit supply line and is designed to adjust a fuel parameter value, in particular a fuel pressure value, in the combustion unit supply line. In certain embodiments, the at least one pressure-regulating element can be designed to maintain the fuel parameter value, in particular the fuel pressure value, between a lower and an upper pressure threshold value.

[0036] In some embodiments, the combustion unit can include at least a second pressure sensor and / or a second temperature sensor, which is arranged in the combustion unit supply line.

[0037] In various configurations, the power generation system can comprise a first proportional valve and at least one second proportional valve. The first proportional valve can be arranged upstream of the main burner in a first section of the combustion unit feed line. The second proportional valve can be arranged upstream of the pilot burner in a second section of the combustion unit feed line. The first proportional valve and the at least one second proportional valve can be configured to control a fuel fraction that is to be supplied to the main burner and the pilot burner, respectively.

[0038] In some embodiments, the at least one gas turbine can include a compressor unit, which is arranged upstream of the combustion unit and fluidically connected to it. In other embodiments, the compressor unit can be fluidically connected to a mixing zone of the at least one burner and configured to supply compressed air to the mixing zone. The mixing zone can be configured to mix the fuel and the compressed air.

[0039] In certain embodiments, the at least one gas turbine can comprise a turbine unit arranged downstream of the combustion unit and fluidically connected to it. In certain embodiments, the at least one gas turbine can comprise a generator unit operationally coupled to the turbine unit. In certain embodiments, the gas turbine can comprise a shaft rotatably mounted in a bearing housing. A rotor of the generator unit can be rotationally fixed to the turbine unit via the shaft. In certain embodiments, the turbine unit can be rotationally fixed to the compressor unit via the shaft.

[0040] In certain embodiments, the at least one gas turbine can have a first gas turbine line and a second gas turbine line. The first gas turbine line can fluidically connect the turbine unit to the combustion unit. The second gas turbine line can be arranged downstream of the turbine unit and fluidically connected to it. The second gas turbine line can be designed to discharge expanded fluid from the turbine unit. In certain embodiments, the at least one gas turbine can include a third gas turbine line, which fluidically connects the compressor unit to the combustion unit and is designed to supply compressed air to the combustion unit.

[0041] In some embodiments, the at least one gas turbine can include at least one recuperator unit. This recuperator unit can be arranged and configured in the first and second gas turbine lines to transfer heat from the first to the second. In other embodiments, the recuperator unit can also be arranged and configured between the third and second gas turbine lines to transfer heat from the third to the second. Alternatively, the recuperator unit can comprise a first and a second recuperator unit arranged in the positions described above.

[0042] According to a third aspect of the present invention, a method for controlling a fuel supply system for a power generation system, in particular a fuel supply system according to the first aspect of the present invention, may comprise: a) Querying and obtaining at least one fuel parameter target value that is linked to fuel in a decoupling tank, b) Determining at least one operating parameter value of a fuel compressor which is fluidically connected to the decoupling tank, based on at least one target fuel parameter value, c) Operating the fuel compressor based on at least one operating parameter to provide fuel with at least one fuel parameter target value in the decoupling tank.

[0043] This method can provide the advantageous effects of the fuel supply system and the power generation system described above. The method can be applied analogously to the control of the 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 (micro) gas turbine system according to the second aspect of the present invention, can therefore comprise all the steps and features of the described method. The fuel supply system and the power generation system can comprise the features and configurations described above.

[0044] In its various forms, the procedure may also include: Supply at least one combustion unit with fuel with at least one target fuel parameter value from the decoupling tank.

[0045] In some configurations, at least one target value for a fuel parameter can be a target fuel pressure value in the decoupling tank. In other configurations, at least one operating parameter value can be a speed of the fuel compressor.

[0046] In various configurations, the power generation system can include a first gas turbine and at least one second gas turbine. Requesting and receiving at least one target value for a fuel parameter can include: Obtaining an initial required fuel parameter value, which is linked to the fuel needed to supply a combustion unit of the first gas turbine; Obtain at least one second required fuel parameter value, which is linked to fuel required to supply a combustion unit of at least one second gas turbine; Determine which of the first required fuel parameter values ​​and of at least one second required fuel parameter value has the highest fuel parameter value; and Set the fuel parameter target value such that it corresponds at least to the highest required fuel parameter value.

[0047] In its various forms, the procedure may also include: Querying and obtaining at least one second fuel parameter target value, which is linked to fuel in a fuel distribution line, wherein the fuel distribution line is located downstream of the decoupling tank and fluidically connected to it; Determining at least one operating parameter value of the fuel compressor based on at least one second target fuel parameter value; Operating the fuel compressor based on at least one operating parameter to provide fuel with at least one second fuel parameter target value in the fuel distribution line.

[0048] In some configurations, at least one second fuel parameter target value can be a fuel mass flow target value in the fuel distribution line.

[0049] In some embodiments, the method can be computer-implemented. Supplying at least one combustion unit with fuel at the target value of at least one fuel parameter can be achieved by appropriately controlling at least one outlet valve element, which is located, for example, between the decoupling tank and the fuel distribution line. Operating the fuel compressor based on the target value of at least one operating parameter can be achieved by controlling a drive device (e.g., an electric motor) coupled to a rotatable compressor wheel of the fuel compressor.

[0050] According to a fourth aspect of the present invention, a computer system is configured to execute the computer-implemented method according to the third aspect of the present invention.

[0051] According to a fifth aspect of the present invention, a computer program is configured to execute the computer-implemented method according to the third aspect of the present invention.

[0052] According to a sixth aspect of the present invention, a computer-readable medium or signal is provided that stores the computer program according to the fifth aspect of the present invention. Brief description of the characters Fig. Figure 1 shows a schematic view of a fuel supply system according to the invention for a power generation system connected with at least one combustion unit; Fig. 2 is a detailed view of the fuel supply system according to the invention and of the at least one combustion unit made of Fig. 1; Fig. Figure 3 shows a power generation system according to the invention with the fuel supply system and at least one gas turbine; Fig. Figure 4 shows a schematic flowchart of the inventive method for controlling the fuel supply system; Fig. Figure 5 shows the fuel supply system according to the invention with a decoupling container which can have several container chambers. Detailed description

[0053] Fig. 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 one aspect of the present invention.

[0054] The fuel supply system 10 comprises a fuel supply line 110, a main fuel line 120, and a fuel distribution line 130. The fuel supply system also includes a fuel compressor 200 and a decoupling tank 300. As shown in Fig. As shown schematically in Figure 1, the fuel supply line 110 is fluidically connected at one end to the fuel compressor 200. At the other end, the fuel supply line 110 can be fluidically connected to a fuel source 11 in order to supply fuel from the fuel source 11 to the fuel compressor 200. Fig. Figure 1 shows the fuel supply line 110 fluidically connected to the fuel source 11. The decoupling tank 300 is arranged downstream of the fuel compressor 200 and fluidically connected to the fuel compressor 200 via the main fuel line 120. The fuel distribution line 130 is arranged downstream of the decoupling tank 300 and fluidically connected to the decoupling tank at a first end. The fuel distribution line 130 is fluidically connectable at a second end to at least one combustion unit 20 of a power generation system 1, in particular a (micro) gas turbine system, and is designed to supply the at least one combustion unit 20 with fuel from the decoupling tank 300. Fig. 1 The fuel distribution line 130 is fluidically connected to at least one combustion unit 20.

[0055] The fuel supply system 10 according to the invention enables one or more combustion units 20 to be reliably supplied with fuel. In particular, by providing the decoupling tank 300, one or more combustion units 20, 20a, 20b, 20c, 20d can be supplied with only a single fuel supply system 10, even under different loads, operating conditions (e.g., transient operation), and / or different power levels. The fuel compressor 200 is designed to provide fuel at a target fuel pressure value in the decoupling tank 300. Consequently, the fuel compressor 200 can provide the required target pressure (or fuel at a target fuel pressure value) in the decoupling tank 300, which can lead to a reduction in the number of components, especially in power generation systems 1 with multiple (micro) gas turbines 2, 2a, 2b.This also reduces costs and / or the complexity of the overall system. Since only one fuel compressor 200 and the decoupling tank 300 are required, the installation space can be reduced. More precisely, the decoupling tank 300 in the fuel supply system 10 eliminates the need for many other components, such as individual main gas compressors and / or pre-compressors (especially compared to multiple individual fuel supply systems per combustion unit). Furthermore, the decoupling tank 300 and the fuel compressor 200 can be located outside the combustion unit 20, which simplifies the system (in known systems, these are often integrated into the respective combustion units). Additional components, such as separate oil supplies for the main gas compressor and / or pre-compressor, can also be omitted.Furthermore, the application range of the fuel supply system 10 can be expanded.

[0056] The decoupling container 300 can also be referred to as a decoupling tank. In this context, "decoupling container 300" or "decoupling tank" means that an (intermediate) component is provided between one or more compressors 200 and at least one downstream consumer (in particular, the at least one combustion unit 20) of compressed fuel. The decoupling container 300 enables one or more consumers, in particular one or more combustion units 20, to be supplied from the decoupling container 300 of the (single) fuel supply system 10. This is achieved by providing and / or storing fuel with a target fuel parameter value, in particular a target fuel pressure value, in the decoupling container 300. The target fuel parameter value can correspond to at least one of the highest required fuel pressure values ​​of the one or more combustion units 20.In other words, the fuel line, in which fuel is compressed by the fuel compressor, cannot be directly connected to one or more consumers, but can be "decoupled" from the one or more consumers via the intermediate component in the form of the decoupling tank 300. Of course, the fuel supply to a consumer can also be influenced or prevented by a shut-off valve or throttle valve – however, in this case, the fuel storage function and / or the provision of fuel with the target fuel parameter value for multiple consumers, especially combustion units 20, cannot be provided. In some cases, it is also not possible to supply multiple consumers or combustion units 20 that require at least a partially different fuel parameter value (e.g., a different fuel pressure value).(due to different load conditions, operating conditions and / or performance levels), are supplied from the decoupling tank 300. In some configurations, the fuel supply line 110 may be optional, for example, if the fuel compressor 200 can be directly connected to or is connected to the fuel source 11. The decoupling tank 300 may include at least one outlet valve element, by means of which the outlet of fuel into the fuel distribution line 130 from the decoupling tank 300 can be regulated.

[0057] The fuel can be a gaseous fuel, in particular propane, natural gas, hydrogen, or biogas. In some embodiments, the fuel can also be liquid. In some embodiments, a pre-evaporator can be provided in the fuel supply line, which is designed to convert the fuel into gaseous form. The fuel source 11 can be a supply network, in particular a supply network, e.g., for a decentralized energy supply. In other embodiments, the fuel source 11 can be a fuel storage device.

[0058] Fig. Figure 2 is a detailed view of the fuel supply system 10 according to the invention and the at least one combustion unit 20. Fig. 1. As in Fig. 1 and Fig. As shown in Figure 2, the fuel supply system 10 can comprise exactly one fuel compressor 200, in particular a high-pressure fuel compressor. Components can be saved because only one fuel compressor 200 is required, even if several combustion units 20, 20a, 20b, 20c, 20d are supplied with fuel. Costs can also be reduced, as can the complexity of the entire power generation system 1. In embodiments, the fuel compressor 200 can be a first fuel compressor, and the fuel supply system 10 can comprise at least one second fuel compressor (not shown in the figures), in particular one that can be arranged downstream in the main fuel line 120 of the first fuel compressor.For example, at least one second fuel compressor may be provided to improve system redundancy and / or to achieve a target pressure in the decoupling tank via at least one intermediate pressure. For example, the first fuel compressor may be a low-pressure compressor, and the second or subsequent fuel compressor a high-pressure compressor. Intercooling may also be provided between the two compressors to increase efficiency.

[0059] In some embodiments, the fuel supply system 10 can include a fuel compressor bypass 160, which fluidically connects the fuel supply line 110 and the main fuel line 120 and is designed to supply fuel from the fuel supply line 110 to the main fuel line 120 around the fuel compressor 200. 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 corresponds at least to the target fuel pressure value in the decoupling tank 300, e.g., in low-load conditions of the at least one combustion unit 20, the fuel compressor bypass 160 can be opened by means of a bypass valve element, or closed again as required.

[0060] As in the Fig. 1 and Fig. As shown schematically in Figure 2, the fuel distribution line 130 can be fluidically connected (or connected) to at least two combustion units 20, 20a, 20b, 20c, 20d of the power generation system 1 and can be designed to supply the at least two combustion units 20, 20a, 20b, 20c, 20d with fuel from the decoupling tank 300. Fig. 1 and Fig. Figure 2 shows the fuel distribution line 130 connected to the at least two combustion units 20, 20a, 20b, 20c, 20d. In other words, only one (single) fuel supply system 10 can be provided to supply several combustion units 20, 20a, 20b, 20c, 20d with fuel. This is made possible by the decoupling tank 300. In particular, the fuel distribution line 130 can comprise 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 partial lines 130a, 130b, 130c, 130d can each branch off from the fuel distribution line 130 and fluidically connect the fuel distribution line 130 with the respective combustion unit 20, 20a, 20b, 20c, 20d.

[0061] With reference to Fig. 1, Fig. 2 and Fig. In embodiment 5, the fuel distribution line 130 can have several, or at least two, sub-lines 130a, 130b, 130c, which are provided separately from each other and connect a respective combustion unit 20, 20a, 20b, 20c, 20d separately to the decoupling tank 300. In this embodiment, the decoupling tank 300 can comprise at least two tank chambers 310a, 310b, 310c, which are fluidically separated from each other. The tank chambers 310a, 310b, 310c can each have the same volume or different volumes. Alternatively, several decoupling tanks, each with exactly one tank chamber 310a, 310b, 310c, can be provided. In yet other embodiments, several decoupling tanks, each with several tank chambers, can be provided. Each tank chamber 310a, 310b, 310c can be connected to a respective separate sub-pipe 130a, 130b, 130c of the fuel distribution line 130.Thus, each reservoir chamber 310a, 310b, 310c can be separately connected to a respective combustion unit 20, 20a, 20b, 20c, 20d via the corresponding partial line 130a, 130b, 130c. In these configurations, the main fuel line 120 can have at least two partial lines 120a, 120b, 120c, each of which is connected to a reservoir chamber 310a, 310b, 310c. The at least two partial lines 120a, 120b, 120c can each branch off from the main fuel line 120 and connect the main fuel line 120 to a corresponding reservoir chamber 310a, 310b, 310c. In these configurations, each combustion unit can therefore be fluidically connected to a container chamber 310a, 310b, 310c by means of a separate partial line 130a, 130b, 130c of the fuel distribution line 130.connected, and each reservoir chamber 310a, 310b, 310c is connected to the main fuel line 120 by means of a respective sub-line 120a, 120b, 120c of the main fuel line 120. In embodiments, exactly two, three or four sub-lines 120a, 120b, 120c of the main fuel line 120, exactly two, three or four sub-lines 130a, 130b, 130c of the fuel distribution line 130 and correspondingly two, three or four reservoir chambers 310a, 310b, 310c can be present.

[0062] In all embodiments described above (see Fig. 2 and Fig. 5) A distribution valve element 170a, 170b, 170c, 170d can be provided in at least one or each of the at least two partial lines 130a, 130b, 130c, 130d of the fuel distribution line 130. This element can be designed to control a portion of the fuel to be supplied to each of the at least two combustion units 20, 20a, 20b, 20c, 20d. The at least one distribution valve element 170a, 170b, 170c, 170d can be provided in addition to or as an alternative to a pressure regulating element 24 in the at least one combustion unit 20 (explained in more detail below). The distribution valve element 170a, 170b, 170c, 170d can also function as a throttle valve and / or proportional valve. In some embodiments, the distribution valve element 170a, 170b, 170c, 170d can also function as a pressure adjusting element. In other embodiments, at least one distribution valve element 170a, 170b, 170c, 170d may not be provided.In one embodiment, the fuel distribution line 130 can be connected to only one combustion unit 20. In this embodiment, only one distribution valve element can be provided. In other embodiments, the pressure regulating elements 24 in the combustion unit 20 may be sufficient, so that the distribution valve element can be omitted. In embodiments in which the main fuel line 120 has at least two sub-lines 120a, 120b, 120c (see e.g. ). Fig. 5) A distribution valve element 121a, 121b, 121c can be provided in at least one or all of the at least two partial lines 120a, 120b, 120c of the main fuel line 120. By means of the distribution valve element 121a, 121b, 121c, fuel with a specific fuel parameter value, in particular fuel pressure, can be supplied to the respective reservoir chamber 310a, 310b, 310c. In other words, a specific fuel parameter value can be supplied to the respective reservoir chamber 310a, 310b, 310c by means of the distribution valve element 121a, 121b, 121c. If no distribution valve element 121a, 121b, 121c is provided, the same fuel parameter target value can be provided in each reservoir chamber 310a, 310b, 310c (e.g. the fuel parameter value which is provided in the main fuel line 120).

[0063] In various embodiments, the fuel distribution line 130 can be fluidically connected (or connected) to at least three combustion units 20a, 20b, 20c or at least four combustion units 20a, 20b, 20c, 20d and be designed to supply these combustion units with fuel from the decoupling tank 300. Alternatively, in one embodiment, only exactly one combustion unit 20, 20a may be provided. The fuel distribution line 130 can be fluidically connected (or connected) to this unit and be designed to supply it with fuel from the decoupling tank 300. As described in Fig. As shown in Figure 1, exactly four combustion units 20a, 20b, 20c, 20d can be provided. As shown in Figure 1. Fig. As shown in Figure 2, exactly three combustion units 20a, 20b, 20c can be provided. In some configurations, exactly two combustion units 20a, 20b can be provided. The number of combustion units 20 can depend on the total power output to be provided by the power generation system 1 (described below). Accordingly, more than four combustion units can also be provided and supplied with fuel from the decoupling tank 300.

[0064] The fuel supply system 10 can comprise exactly one decoupling tank 300 (see e.g. Fig. 1 or Fig. 2) In some embodiments, several decoupling tanks 300 can be provided. These can be arranged parallel to one another and, in particular, each can be connected to the main fuel line 120 and the fuel distribution line 130. This allows for energy optimization at significantly different power levels of several gas turbines 2, 2a, 2b. As described above, in some embodiments the decoupling tank 300 can comprise several tank chambers. Alternatively, the decoupling tank 300 can comprise exactly one tank chamber. In all embodiments, as described in Fig. Figure 2 shows that the fuel supply system 10 comprises a decoupling tank bypass 150, which fluidically connects the main fuel line 120 and the fuel distribution line 130 and is designed to supply fuel from the main fuel line 120 to the fuel distribution line 130 around the decoupling tank 300. In particular, a first bypass valve can be arranged in the decoupling tank bypass 150. The decoupling tank bypass 150 can be used when several combustion units are supplied, each of which has the same power levels and / or operating states or load conditions at any given time. The decoupling tank bypass 150 can be used when at least one combustion unit is operating in a low-load condition. The decoupling tank bypass 150 can also be used when only one combustion unit 20 is supplied with fuel.Are at least two separate sub-lines 130a, 130b, 130c of the fuel distribution line 130 provided (see . Fig. 5) The decoupling tank bypass 150 can connect the main fuel line 120 to the respective separate sub-lines 130a, 130b, and 130c. In this case, the bypass can have several bypass sub-lines. Each of these can have a bypass valve.

[0065] As in Fig. 1 and Fig. As shown in Figure 2, the fuel supply system 10 can include a fuel heat exchanger 400. This can be arranged in the main fuel line 120 downstream of the fuel compressor 200 and designed to dissipate heat from the main fuel line 120. In particular, it may be necessary to limit the fluid temperature (e.g., a gas temperature) in the main fuel line 120 to a maximum valve fluid temperature. Accordingly, a heat flow from the fluid in the main fuel line 120 to a cooling medium (e.g., oil, gas, water, or air) in the heat exchanger can be controlled.

[0066] The fuel supply system 10 can include at least one vent line 140, which fluidically connects the main fuel line 120 and an atmospheric outlet 141 of the vent line 140 (or of the fuel supply system 10) (see Fig. 2) The main fuel line 120 can be vented via at least one vent line 140 so that a defined system state of the fuel supply system 10 can be achieved. At least one vent valve 142 can be provided in the at least one vent line 140. The vent line 140 is designed to discharge fuel from the main fuel line 120 when the at least one vent valve 142 is open. The at least one vent line 140 can be fluidically connected to (or connected to) a combustion unit supply line 21 and designed to discharge fuel from the combustion unit supply line 21. As described in Fig. As shown in Figure 2, the at least one vent line 140 can comprise a first vent line 140a, which fluidically connects the main fuel line 120 at a position between the fuel heat exchanger 400 and the fuel compressor 200 and the atmosphere outlet 141. A first vent valve 142a can be arranged in the first vent line 140a. The at least one vent line 140 can comprise a second vent line 140b, which fluidically connects the main fuel line 120 at a position between the fuel heat exchanger 400 and the decoupling tank 300 and the atmosphere outlet 141. A second vent valve 142b can be arranged in the second vent line 140b. The at least one vent line 140 can include at least one third vent line 140c, which fluidically connects the combustion unit supply line 21 of the at least one combustion unit 20 and the atmosphere outlet 141.A third venting valve 142c can be arranged in at least one third venting line 140c.

[0067] As in Fig. As shown in Figure 2, the fuel supply system 10 can include at least one check valve 510, which is arranged upstream of the decoupling reservoir 300 in the main fuel line 120. The check valve 510 can prevent backflow of compressed fuel from the decoupling reservoir 300, particularly when the fuel compressor 200 is not operating or is operating at low speeds (and thus only a pressure is built up that is lower than the pressure in the decoupling reservoir 300). In embodiments in which at least two partial lines 120a, 120b, 120c of the main fuel line 120 are provided (see, for example, Figure 2), the check valve 510 can prevent backflow of compressed fuel from the decoupling reservoir 300, particularly when the fuel compressor 200 is not operating or is operating at low speeds (and thus only a pressure is built up that is lower than the pressure in the decoupling reservoir 300). Fig. 5), alternatively or additionally, a check valve 510a, 510b, 510c may be provided in each sub-pipe 120a, 120b, 120c.

[0068] Furthermore, the fuel supply system 10 can include at least one first shut-off valve 520, which is arranged in the main fuel line 120 downstream of the fuel compressor 200. Alternatively or additionally, the shut-off valve can be arranged upstream of the fuel compressor 200. The first shut-off valve 520 allows the fuel supply to be quickly and centrally shut off or stopped, for example, in a hazardous, emergency, or maintenance situation.

[0069] As in Fig. As shown schematically in Figure 2, a filter device 600 can be arranged in the fuel supply line 110 upstream of the fuel compressor 200. In particular, the filter device 600 can be a gas filter device, especially if the fuel is gaseous. The filter device 600 can separate impurities from the fuel.

[0070] The fuel supply system 10 can include at least one pressure reducing valve 530, which is arranged in the fuel distribution line 130 downstream of the decoupling tank 300 (and in particular upstream of any sub-lines 130a, 130b, 130c). The pressure reducing valve 530 allows a pressure level to be set directly downstream of the decoupling tank 300. In embodiments in which at least two separate sub-lines 130a, 130b, 130c of the fuel distribution line 120 are provided (see, e.g., [reference]) Fig. 5), alternatively or additionally, a pressure reducing valve may be provided in each sub-pipe 130a, 130b, 130c.

[0071] The fuel supply system 10 can include at least one first pressure sensor 700, 700a, 700b and / or one first temperature sensor 710, 710a, 710b, which is arranged in the fuel supply line 110, the main fuel line 120, and / or in the fuel distribution line 130. In embodiments, the fuel supply system 10 can include at least one first mass flow sensor 720, which is arranged in the main fuel line 120 upstream of the decoupling tank 300 and is designed to measure a mass flow in the main fuel line 120 upstream of the decoupling tank 300. The fuel compressor 200 can be controlled based on sensor data from the at least one pressure sensor, temperature sensor, and / or mass flow sensor. In embodiments in which at least two separate 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 are provided (see e.g. ). Fig. 5), a pressure sensor, mass flow sensor and / or temperature sensor may be provided in the corresponding sub-pipe.

[0072] Fig. Figure 3 shows a power generation system 1 according to the invention, comprising the fuel supply system 10 and at least one gas turbine 2, 2a, 2b. The power generation system 1 includes the 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 fluidically connected to the decoupling tank 300 via the fuel distribution line 130, wherein the at least one combustion unit 20 is supplied with fuel from the decoupling tank 300 (see also Fig. 2).

[0073] The power generation system 1, in particular the gas turbine system or micro gas turbine system, can comprise at least one (micro) gas turbine 2, which has at least one combustion unit 20. The fuel distribution line 130 can be fluidically connected (or connected) to the combustion unit 20 of the at least one gas turbine 2 of the power generation system 1 and be designed to supply the combustion unit 20 of the at least one gas turbine 2 with fuel from the decoupling tank 300. As shown in Fig. As shown in Figure 3, the power generation system 1 can comprise at least two (micro) gas turbines 2, 2a, 2b, each of which has a combustion unit 20, 20a, 20b. The fuel distribution line 130 can be fluidically connected (or connected) to the respective combustion unit 20, 20a, 20b of the at least two gas turbines 2, 2a, 2b of the power generation system 1 and can 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 tank 300.

[0074] In various embodiments, the at least two gas turbines 2, 2a, 2b can provide the same power output or different power outputs. In some embodiments, the power generation system 1 can provide a total power output of 1 MW. In a first example, the power generation system 1 can comprise three gas turbines, each with a power output of 333 kW, to provide the total power output. In this case, all gas turbines deliver the same power output (e.g., electrical power and / or thermal power). The respective combustion units 20a, 20b, 20c can be supplied from the decoupling tank 300 with fuel at approximately the same pressure level and / or mass flow rate. In another example, four gas turbines can be provided, with two gas turbines having a power output of 200 kW and two gas turbines having a power output of 300 kW, to provide the total power output of 1 MW.Consequently, four gas turbines can be used, which are operated at least partially at different operating points or load conditions. The gas turbines with the higher power output may have a greater fuel requirement (or require fuel with a higher pressure and / or mass flow rate) than the gas turbines with the lower power output. The decoupling tank 300 can provide fuel with a target fuel pressure value that corresponds at least to the highest required fuel pressure value of the four gas turbines or combustion units of the gas turbines. In some configurations, the decoupling tank 300 can have a capacity of approximately 2000 liters. The respective fuel requirement (or mass flow rate) can be controlled via the at least one pressure control element 24 (described below), corresponding proportional valves, and / or the at least one distribution valve element 170a, 170b, 170c, 170d.Fuel with a required fuel parameter value (in particular a fuel pressure and / or mass flow rate) to the individual combustion units 20 of the gas turbines 2, 2a, 2b is then regulated. For such power generation systems 1 with multiple gas turbines 2, 2a, 2b, only one (single) fuel supply system 10 according to the invention with the decoupling tank 300 is required to provide the corresponding fuel. Particularly for systems with multiple gas turbines 2, 2a, 2b, components can therefore be saved, the required space reduced, the complexity reduced, and / or costs reduced because no fuel supply system 10 needs to be provided for each combustion unit 20 or gas turbine 2. In this example, the highest required fuel pressure value in at least one of the gas turbines 2, 2a, 2b can be approximately 12 bar. The fuel source 11 can provide fuel with a pressure value of approximately 5 bar.The fuel supply system 10 can specify a target fuel pressure of approximately 14 bar in the decoupling tank 300. This can be higher than the highest required fuel pressure to account for potential losses. The fuel compressor 200 can be controlled accordingly to increase the fuel pressure from approximately 5 bar at the fuel source 11 to approximately 14 bar in the decoupling tank 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 configurations in which multiple tank chambers 310a, 310b, 310c are provided (see Figure 1). Fig. 5), which are fluidically connected to the respective combustion units of the gas turbines via the separate partial lines 130a, 130b, 130c. Fuel with a required fuel parameter value for the respective gas turbine can be supplied to the respective storage chamber 310a, 310b, 310c via the components described (such as pressure control elements (described below), corresponding proportional valves, and / or distribution valve elements).

[0075] As in Fig. As shown in Figure 2, the at least one combustion unit 20 can comprise a combustion unit supply line 21 and at least one burner 22, wherein the combustion unit supply line 21 fluidically connects the burner 22 to the fuel distribution line 130 (or corresponding partial lines). The at least one burner 22 can comprise 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 a mass flow in the combustion unit supply line 21. In embodiments, a first mass flow sensor 23a can be provided at a first end of the combustion unit supply line 21, which is connected to the fuel distribution line 130. A second mass flow sensor 23b can be provided in the combustion unit supply line 21 upstream of the burner 22.

[0076] As briefly mentioned above and in Fig. As shown schematically in Figure 2, the at least one combustion unit 20 can have at least one pressure adjusting element 24, 24a, 24b, which is arranged in the combustion unit supply line 21 and is designed to set a required fuel parameter value of the fuel (e.g., fuel with a fuel pressure value) in the combustion unit supply line 21. The at least one pressure adjusting element 24 can be designed to maintain the fuel parameter value (in particular the fuel pressure value) between a lower and an upper pressure threshold value. In embodiments, the required fuel parameter value can correspond to the target fuel pressure value. In particular, a first pressure adjusting element 24a and a second pressure adjusting element 24b can be provided. The first pressure adjusting element 24a can be designed to maintain the fuel pressure value at or above a lower pressure threshold value.The second pressure adjusting element 24b can be designed to maintain the fuel pressure at or below an upper pressure threshold. The first pressure adjusting element 24a can be arranged upstream of the second pressure adjusting element 24b in the combustion unit supply line 21.

[0077] The at least one combustion unit 20 can include at least one second pressure sensor 25 and / or one second temperature sensor 26, which is arranged in the combustion unit supply line 21. Furthermore, the at least one combustion unit 20 can include a first proportional valve 28a and at least one second proportional valve 28b. The first proportional valve 28a can be arranged upstream of the main burner 22a in a first section of the combustion unit supply line 21. The second proportional valve 28b can be arranged upstream of the pilot burner 22b in a second section of the combustion unit supply line 21. The first proportional valve 28a and the at least one second proportional valve 28b are designed to control a portion of the fuel that is to be supplied to the main burner 22a and the pilot burner 22b, respectively.Alternatively or additionally, the fuel mass flow in the combustion unit supply line 21 and / or in the fuel distribution line 130 can be controlled depending on a pressure value adjustable in the fuel compressor 200 (in particular the target fuel pressure value), especially by means of an adjustable speed of the fuel compressor 200.

[0078] In some embodiments, the at least one combustion unit 20 can have at least one second shut-off valve 27, 27a, 27b, which is arranged in the combustion unit supply line 21. The at least one second shut-off valve 27, 27a, 27b can be arranged downstream of the pressure regulating element 24. As in Fig. As shown in Figure 2, two shut-off valves 27a, 27b can be arranged in the combustion unit supply line 21. The third vent line 140c can be connected to the combustion unit supply line 21 between these two shut-off valves 27a, 27b. The second pressure sensor 25 can also be provided between the two shut-off valves 27a, 27b in order to control the third vent valve 142c depending on pressure sensor data.

[0079] In various configurations, as in Fig. 2 and Fig. Figure 3 shows that at least one gas turbine 2 comprises a compressor unit 30, which is arranged upstream of the combustion unit 20 and fluidically connected to it. The compressor unit can be supplied with fluid to be compressed (in particular, air) via a compressor unit supply line 71. The compressor unit 30 can be fluidically connected to a mixing zone of the at least one burner 22 and is designed to supply compressed air to the mixing zone. The mixing zone can be designed to mix the fuel and the compressed air. In embodiments, the mixing zone can be located upstream of or within a section of a combustion chamber of the at least one burner 22. The hot, compressed air can preheat the fuel, which can promote reaction kinetics in the mixing zone, and in particular in the combustion chamber.

[0080] The at least one gas turbine 2 can comprise a turbine unit 40, which is arranged downstream of the combustion unit 20 and is fluidically connected to it. As further in Fig. As shown in Figure 3, the at least one gas turbine 2 can comprise a generator unit 50, which is operationally coupled to the turbine unit 40. The at least one gas turbine 2 can comprise a shaft 60, which is rotatably mounted in a bearing housing. A rotor of the generator unit 50 can be rotationally coupled to a turbine wheel of the turbine unit 40 via the shaft 60. "Operationally" means that the turbine unit can generate a rotational movement of the shaft by the expansion of fluid from the combustion unit, which is then transmitted to the rotor of the generator unit (which subsequently generates electrical power). In some embodiments, the turbine unit 40 can be rotationally coupled to the compressor unit 30 via the shaft 60. In other embodiments, the compressor unit 30 can be supplied with electrical power generated by the generator unit 50 to drive a compressor wheel.The same can be provided for the fuel compressor 200 of the fuel supply system 10.

[0081] As in Fig. As shown in Figure 3, at least one gas turbine 2 can have a first gas turbine line 70a and a second gas turbine line 70b. The first gas turbine line 70a can fluidically connect the turbine unit 40 to the combustion unit 20. The second gas turbine line 70b can be arranged downstream of the turbine unit 40 and fluidically connected to it. The second gas turbine line 70b is designed to discharge expanded fluid from the turbine unit 40.

[0082] In embodiments, at least one gas turbine 2 can include a third gas turbine line 70c, which fluidically connects the compressor unit 30 to the combustion unit 20 and is designed to supply compressed air from the compressor unit 30 to the combustion unit 20.

[0083] In some embodiments, the at least one gas turbine 2 can comprise at least one recuperator unit 90. The at least one recuperator unit 90 can be arranged and configured in the first gas turbine line 70a and the second gas turbine line 70b in such a way as to transfer heat output from the first gas turbine line 70a to the second gas turbine line 70b (in Fig. 3 not shown). Alternatively or additionally, at least one recuperator unit 90 can be arranged and configured between the third gas turbine line 70c and the second gas turbine line 70b to transfer heat 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 recuperator 90 and combustion unit 20 (as shown in Fig. 3 shown). The heat output transferred by the recuperator 90 can be used to further heat the compressed air upstream of the combustion unit, in particular the combustion chamber of the burner. This increases the efficiency of the power generation system 1, as the energy supplied by heat no longer needs to be supplied by fuel energy. The recuperator unit can also comprise a first recuperator unit and a second recuperator unit, which are arranged at the positions described above. In one example, the following temperature sequence can occur at nominal load of the power generation system 1: in the third gas turbine line 70c, the temperature of the air before entering the recuperator 90 (arranged as shown in Figure 3) can be... Fig. (3 shown) approximately 250°C. At the outlet of the recuperator 90, the air temperature can be approximately 500°C. At the outlet of at least one combustion chamber 20, 20a in the first gas turbine line 70a, the fluid (especially exhaust gas) can have a temperature of approximately 1050°C. After exiting the turbine unit 40, the expanded fluid in the second gas turbine line 70b can have a temperature of approximately 700°C before entering the recuperator 90. At the outlet of the recuperator 90, the fluid in the second gas turbine line 70b can have a temperature of approximately 550°C.

[0084] As in Fig. As further shown in Figure 3, the second gas turbine line 70b is fluidically connected to a fluid outlet 72. In certain embodiments, at least one additional heat exchanger 80 can be provided in the second gas turbine line 70b. This heat exchanger can be arranged and designed between the second gas turbine line 70b, downstream of the at least one recuperator 70, and an external line 73 in such a way as to transfer heat from the second gas turbine line 70b to the external line 73.

[0085] Fig. Figure 4 shows a schematic flowchart of the inventive method for controlling the fuel supply system 10 for a power generation system, in particular for a gas turbine system or a micro gas turbine system. The method can be used to control the fuel supply system 10 according to the invention, as well as the power generation system 1 comprising the fuel supply system 10.

[0086] The inventive method 800 for controlling the fuel supply system 10 comprises: a) Query and retrieve 810 at least one fuel parameter target value which is linked to fuel in a decoupling tank 300, b) Determine 820 at least one operating parameter value of a fuel compressor 200, which is fluidically connected to the decoupling tank 300, based on the at least one fuel parameter target value, c) Operating 830 of the fuel compressor 200 based on at least one operating parameter to provide fuel with at least one fuel parameter target value in the decoupling tank 300.

[0087] This method 800 can provide the advantageous effects of the fuel supply system 10 and the power generation system 1 described above. Furthermore, method 800 can provide optimized and tailored control of the fuel supply system 10 and / or the power generation system 1. Method 800 can be applied analogously to the control of the power generation system 1. According to one aspect of the present invention, a method for controlling a power generation system 1, in particular a (micro) gas turbine system, can therefore comprise all the steps and features of the described method 800. The fuel supply system 10 and the power generation system 1 can include the features and configurations described above. In particular, a fuel distribution line 130 is arranged downstream of the decoupling tank 300 and fluidically connected to it.The fuel distribution line 130 is fluidically connectable (or connected) to at least one combustion unit 20 of the power generation system 1 and is designed to supply at least one combustion unit 20 with fuel with at least one fuel parameter target value from the decoupling tank 300.

[0088] The method 800 can further comprise supplying 840 at least one combustion unit 20 with fuel with at least one target fuel parameter value from the decoupling tank 300. The at least one target fuel parameter value can be a target fuel pressure value of the fuel in the decoupling tank 300. The at least one operating parameter value can be a speed of the fuel compressor 200.

[0089] As described above, the power generation system 1 can include a first gas turbine 2, 2a and at least one second gas turbine 2, 2b. Querying and obtaining at least one fuel parameter target value can include: Obtaining an initial required fuel parameter value, which is linked to fuel required to supply a combustion unit 20, 20a of the first gas turbine 2, 2a, and Obtain at least one second required fuel parameter value, which is linked to fuel required to supply a combustion unit 20, 20b or at least one second gas turbine 2, 2b.

[0090] Furthermore, querying and receiving 810 of at least one fuel parameter target value can include: Determine which of the first required fuel parameter values ​​and of at least one second required fuel parameter value has the highest required fuel parameter value, and Set the fuel parameter target value such that it corresponds at least to the highest required fuel parameter value.

[0091] In other words, the target fuel parameter value can be set so that it is equal to or greater than the highest required fuel parameter value. The first required fuel parameter value and at least one second required fuel parameter value can each be a required fuel pressure value.

[0092] In its various forms, procedure 800 may also include: Querying and obtaining 850 at least one second fuel parameter target value, which is linked to fuel in a fuel distribution line 130, wherein the fuel distribution line 130 is arranged downstream of the decoupling tank 300 and fluidically connected to it, Determining at least one operating parameter value of the fuel compressor 200 based on at least one second fuel parameter target value, and operating the fuel compressor 200 based on at least one operating parameter in order to provide fuel with at least one second fuel parameter target value in the fuel distribution line 130.

[0093] The at least one second fuel parameter target value can be a fuel mass flow in the fuel distribution line 130. In embodiments, the at least one second fuel parameter target value can also be a fuel mass flow in the combustion unit supply line 21 of the at least one combustion unit 20. In this case, the method can comprise querying and obtaining at least one second fuel parameter target value 850, which is linked to fuel in a combustion unit supply line 21, wherein the combustion unit supply line 21 is arranged downstream of the decoupling container 300 and is fluidically connected to the fuel distribution line 130.

[0094] The decoupling container 300 comprises at least two container chambers 310a, 310b, 310c, each of which can be fluidically connected to the at least two combustion units. The querying and receiving 810 of the at least one fuel parameter target value comprises: Querying and receiving 810 a fuel parameter target value, which is linked to fuel in a first reservoir chamber 310a of the decoupling tank 300, Query and receive 810 at least one further fuel parameter target value which is linked to fuel in at least a second container chamber 310b, 310c of the decoupling container 300.

[0095] In these configurations, querying and receiving 810 of at least one fuel parameter target value can further include: Obtaining a first required fuel parameter value, which is linked to fuel required to supply a combustion unit 20, 20a of the first gas turbine 2, 2a, wherein the first combustion unit 20, 20a is connected to the first storage chamber 310a, and Obtaining at least one second required fuel parameter value, which is linked to fuel required to supply a combustion unit 20, 20b of the at least one second gas turbine 2, 2b, wherein the at least one second combustion unit 20, 20b is connected to the at least one second container chamber 310a.

[0096] Since the respective combustion unit 20, 20a, 20b is connected to the respective container chamber, the first required fuel parameter value can thus be linked to the target fuel parameter value in the first container chamber, and the at least one second required fuel parameter value can be linked to the at least one further target fuel parameter value in the at least one second container chamber. Furthermore, querying and obtaining the at least one target fuel parameter value can include: Determine which of the first required fuel parameter values ​​and of at least one second required fuel parameter value has the highest required fuel parameter value, and Set the fuel parameter target value such that it corresponds at least to the highest required fuel parameter value.

[0097] Since the respective required fuel parameter values ​​are linked to the respective target fuel parameter values, it is ensured that the highest target fuel parameter value is provided in the reservoir chamber connected to the combustion unit with the highest required fuel parameter value. The at least one operating parameter value of the fuel compressor 200, which is fluidically connected to the first reservoir chamber 310a and the at least one second reservoir chamber, can then be determined accordingly (step 820). Furthermore, the fuel compressor 200 can be operated based on the at least one operating parameter to provide fuel with the at least one target fuel parameter value in the first reservoir chamber 310a and / or the at least one second reservoir chamber 310b, 310c of the decoupling reservoir 300.If no distribution valve elements 121a, 121b, 121c are provided in the separate sub-lines 120a, 120b, 120c of the main fuel line described above, the same (highest) target fuel parameter value can be provided in each reservoir chamber. If distribution valve elements 121a, 121b, 121c are provided, the method can include controlling these distribution valve elements 121a, 121b, 121c to provide target fuel parameter values ​​in the respective reservoir chambers 310a, 310b, 310c according to the respective required fuel parameter values. In this case as well, the fuel compressor 200 is operated in such a way that it provides the target fuel parameter value that is equal to or greater than the highest required fuel parameter value.

[0098] In various embodiments, method 800 can be a computer-implemented method. Supplying 840 at least one combustion unit 20 with fuel with at least one target fuel parameter value can be implemented by appropriately controlling at least one outlet valve element, which is provided, for example, between the decoupling tank 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 implemented by controlling a drive device (e.g., an electric motor) coupled to a rotatable compressor wheel of the fuel compressor 200.

[0099] According to another aspect of the present invention, a computer system can be configured to execute the computer-implemented method. According to another aspect, a computer program can be configured to execute the computer-implemented method. Furthermore, a computer-readable medium or signal can be provided that stores the computer program.

[0100] The computer-implemented procedure described above can involve or be executable via a computer or computer network, wherein the computer or computer network includes at least one processing unit (e.g., a processor) and at least one data storage device (i.e., a memory). The described procedural logic can be stored as executable code in at least one data storage device and executed by the at least one processing unit. The systems and subsystems (e.g., the power generation system 1 and / or the fuel supply system 10, as well as individual components such as the fuel compressor and the sensors) can send data to the at least one processing unit and, in examples, also receive instructions from the at least one processing unit.The processing unit can direct user-initiated and / or automatically generated queries to the power generation system 1 and / or the fuel supply system. The power generation system 1 and / or the fuel supply system is not limited to a specific hardware environment. Thus, distributed devices connected via a network can execute the techniques described herein. The 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 can include at least one database. Alternatively or additionally, the power generation system 1 and / or the fuel supply system 1 can access a database in a cloud (via a communication interface).The power generation system 1 and / or the fuel supply system 10 may include one (or more) communication interface for coupling with the individual elements of the processing unit and / or the database. The communication interface may include one or more of the following: a network, the internet, a local area network, a wireless local area network, a cellular broadband network, and / or a wired network. In examples, the power generation system 1 and / or the fuel supply system 10 may be connected to one or more functions via a server hosted in a cloud. The power generation system 1 and / or the fuel supply system 10 may also be connected to an external control and / or monitoring device.

[0101] Although the present invention has been described above and is defined in the attached claims, it should be understood that the invention can alternatively also be defined according to the following embodiments: 1. Fuel supply system (10) for a power generation system (1), in particular for a micro gas turbine system, comprising: a fuel supply line (110), a main fuel line (120) and a fuel distribution line (130), a fuel compressor (200), and a decoupling tank (300), wherein the fuel supply line (110) is fluidically connected to the fuel compressor (200) and can be connected to a fuel source (11) in order to supply fuel from the fuel source (11) to the fuel compressor (200), wherein the decoupling tank (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 line (130) is arranged downstream of the decoupling tank (300) and fluidically connected to it, and wherein 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 tank (300). 2. Fuel supply system (10) according to embodiment 1, wherein the fuel supply system (10) comprises exactly one fuel compressor (200), in particular a high-pressure fuel compressor. 3. Fuel supply system (10) according to embodiment 1 or embodiment 2, wherein the fuel is a gaseous fuel, in particular propane, natural gas, hydrogen or biogas. 4. Fuel supply system (10) according to any of the preceding embodiments, wherein the fuel distribution line (130) is fluidically connectable 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 tank (300), in particular wherein the fuel distribution line (130) comprises at least two sub-lines (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 provided in at least one or each of the sub-lines (130a, 130b). 5. Fuel supply system (10) according to any of the preceding embodiments, wherein the power generation system (1) comprises at least one gas turbine (2) which has the at least one combustion unit (20), and wherein the fuel distribution line (130) is fluidically connectable to the combustion unit (20) of the at least one gas turbine (2) of the power generation system (1) and is designed to supply the combustion unit (20) of the at least one gas turbine (2) with fuel from the decoupling tank (300). 6. Fuel supply system (10) according to any of the preceding embodiments, wherein the power generation system (1) comprises at least two gas turbines (2, 2a, 2b) each having a combustion unit (20, 20a, 20b), and wherein the fuel distribution line (130) is fluidically connectable to the respective combustion unit (20, 20a, 20b) of the at least two gas turbines (2, 2a, 2b) of the power generation system (1) and is 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 tank (300). 7. Fuel supply system (10) according to any of the preceding embodiments, comprising a fuel heat exchanger (400) which is arranged in the main fuel line (120) downstream of the fuel compressor (200) and is designed to dissipate heat from the main fuel line (120). 8. Fuel supply system (10) according to any of the preceding embodiments, comprising at least one vent line (140) which fluidically connects the main fuel line (120) and an atmosphere outlet (141) of the vent line (140). 9. Fuel supply system (10) according to embodiment 8, wherein at least one vent valve (142) is provided in the at least one vent line (140), wherein the vent line (140) is designed to discharge fuel from the main fuel line (120) when the at least one vent valve (142) is in an open position. 10. Fuel supply system (10) according to embodiment 8 or embodiment 9, wherein the at least one vent line (140) is fluidically connectable to a combustion unit supply line (21) and is designed to discharge fuel from the combustion unit supply line (21). 11. Fuel supply system (10) according to any of the preceding embodiments, comprising exactly one decoupling reservoir (300). 12. Fuel supply system (10) according to any of the preceding 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 separate partial lines (130a, 130b, 130c), wherein each container chamber (310a, 310b, 310c) is separately fluidically connectable to a respective combustion unit (20, 20a, 20b) via a corresponding partial line (130a, 130b, 130c), and in particular wherein the main fuel line (120) comprises at least two partial lines (120a, 120b, 120c), each of which connects the main fuel line (120) to a respective container chamber (310a, 310b, 310c). connect. 13. Fuel supply system (10) according to any of the preceding embodiments, comprising a decoupling tank bypass (150) which fluidically connects the main fuel line (120) and the fuel distribution line (130) and is designed to supply fuel around the decoupling tank (300) from the main fuel line (120) to the fuel distribution line (130). 14. Fuel supply system (10) according to any of the preceding embodiments, comprising at least one check valve (510) which is arranged upstream of the decoupling reservoir (300) in the main fuel line (120). 15. Fuel supply system (10) according to any of the preceding embodiments, wherein the fuel compressor (200) is designed to provide fuel at a target fuel pressure value in the decoupling reservoir (300). 16. Fuel supply system (10) according to any of the preceding embodiments, comprising a fuel compressor bypass (160) which fluidically 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). 17. Fuel supply system (10) according to any of the preceding embodiments, comprising at least a first shut-off valve (520) which is arranged in the main fuel line (120) downstream or upstream of the fuel compressor (200). 18. Fuel supply system (10) according to any of the preceding embodiments, comprising a filter device (600) which is arranged in the fuel supply line (110) upstream of the fuel compressor (200). 19. Fuel supply system (10) according to any of the preceding embodiments, comprising at least one pressure reducing valve (530) which is arranged in the fuel distribution line (130) downstream of the decoupling tank (300). 20. Fuel supply system (10) according to any of the preceding embodiments, comprising at least a first pressure sensor (700, 700a, 700b) and / or a first temperature sensor (710, 710a, 710b) arranged in the fuel supply line (110), the main fuel line (120) and / or in the fuel distribution line (130), and in particular comprising at least a first mass flow sensor (720) arranged in the main fuel line (120) upstream of the decoupling tank (300) and designed to measure a mass flow in the main fuel line (120) upstream of the decoupling tank (300). 21. Fuel supply system (10) according to any of the preceding embodiments, wherein the fuel source (11) is a supply network. 22. Power generation system (1), in particular a micro gas turbine system, comprising: a fuel supply system (10) according to any of the preceding embodiments, and at least one combustion unit (20), wherein the at least one combustion unit (20) is arranged downstream of the fuel supply system (10) and is fluidically connected to the decoupling tank (300) via the fuel distribution line (130), wherein the at least one combustion unit (20) is supplied with fuel from the decoupling tank (300). 23. Power generation system (1) according to embodiment 22, wherein the power generation system (1) comprises at least one gas turbine (2) which has the at least one combustion unit (20), and wherein the fuel distribution line (130) is fluidically connected to the combustion unit (20) of the at least one gas turbine (2) of the power generation system (1) and supplies the combustion unit (20) of the at least one gas turbine (2) with fuel from the decoupling tank (300). 24. Power generation system (1) according to embodiment 22 or embodiment 23, comprising at least two combustion units (20, 20a, 20b) which are arranged downstream of the fuel supply system (10) and are fluidically connected to the decoupling tank (300) via the fuel distribution line (130), wherein the at least two combustion units (20, 20a, 20b) are supplied with fuel from the decoupling tank (300). 25. Power generation system (1) according to any of the embodiments 22 to 24, wherein the power generation system (1) comprises at least two gas turbines (2, 2a, 2b) each having a combustion unit (20, 20a, 20b), and wherein the fuel distribution line (130) is fluidically connected to the respective combustion unit (20, 20a, 20b) of the at least two gas turbines (2, 2a, 2b) of the power generation system (1) and supplies the respective combustion units (20, 20a, 20b) of the at least two gas turbines (2, 2a, 2b) with fuel from the decoupling tank (300). 26. Power generation system (1) according to any of embodiments 22 to 25, wherein the at least one combustion unit (20) comprises a combustion unit supply line (21) and at least one burner (22), wherein the combustion unit supply line (21) fluidically connects the burner (22) to the fuel distribution line (130). 27. Power generation system (1) according to embodiment 26, wherein the at least one burner (22) comprises a main burner (22a) and a pilot burner (22b). 28. Power generation system (1) according to embodiment 26 or embodiment 27, wherein the fuel supply system (10) comprises at least one vent line (140) which fluidically connects the combustion unit supply line (21) and an atmosphere outlet (141) of the vent line (140). 29. Power generation system (1) according to any of embodiments 25 to 28, wherein the at least two gas turbines (2, 2a, 2b) provide the same power, or provide different power. 30. Power generation system (1) according to any 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 a mass flow in the combustion unit supply line (21). 31. Power generation system (1) according to any of embodiments 26 to 30, wherein the combustion unit (20) has at least one pressure control element (24, 24a, 24b) which is arranged in the combustion unit supply line (21) and is designed to set a fuel parameter value of the fuel, in particular a fuel pressure value, in the combustion unit supply line (21), and in particular wherein the at least one pressure control element (24) is designed to maintain the fuel pressure value between a lower and an upper pressure threshold value. 32. Power generation system (1) according to any of embodiments 26 to 31, wherein the combustion unit (20) comprises at least a second pressure sensor (25) and / or a second temperature sensor (26) which is arranged in the combustion unit supply line (21). 33. Power generation system (1) according to any of embodiments 27 to 32, comprising a first proportional valve (28a) and at least one second proportional valve (28b), wherein the first proportional valve (28a) is arranged upstream of the main burner (22a) in a first partial line of the combustion unit supply line (21), and wherein the second proportional valve (28b) is arranged upstream of the pilot burner (22b) in a second partial line of the combustion unit supply line (21), in particular wherein the first proportional valve (28a) and the at least one second proportional valve (28b) are designed to control a fuel component which is to be supplied to the main burner (22a) and the pilot burner (22b), respectively. 34. Power generation system (1) according to any of embodiments 22 to 33, wherein the at least one gas turbine (2) comprises a compressor unit (30) which is arranged upstream of the combustion unit (20) and is fluidically connected to it. 35. Power generation system (1) according to embodiment 34, depending on embodiment 26, wherein the compressor unit (30) is fluidically connected to a mixing zone of the 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 the fuel and the compressed air. 36. Power generation system (1) according to any 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 fluidically connected to it. 37. Power generation system (1) according to embodiment 36, wherein the at least one gas turbine (2) comprises a generator unit (50) which is operationally coupled to the turbine unit (40). 38. Power generation system (1) according to embodiment 37, depending on embodiment 34, wherein the gas turbine (2) comprises a shaft (60) which is rotatably mounted in a bearing housing, wherein a rotor of the generator unit (50) is rotationally coupled to the turbine unit (40) via the shaft (60), and in particular wherein the turbine unit (40) is rotationally coupled to the compressor unit (30) via the shaft (60). 39. Power generation system (1) according to any 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) fluidically 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 fluidically connected to it, wherein the second gas turbine line (70b) is designed to discharge expanded fluid from the turbine unit (40). 40. Power generation system (1) according to any of embodiments 34 to 39, wherein the at least one gas turbine (2) comprises a third gas turbine line (70c) which fluidically connects the compressor unit (30) to the combustion unit (20) and is designed to supply compressed air from the compressor unit (30) to the combustion unit (20). 41. Power generation system (1) according to embodiment 39 or embodiment 40, wherein the at least one gas turbine (2) comprises at least one recuperator unit which is arranged and configured between the first gas turbine line (70a) and the second gas turbine line (70b) in such a way as to transfer heat power from the first gas turbine line (70a) to the second gas turbine line (70b), and / or which is arranged and configured between the third gas turbine line (70c) and the second gas turbine line (70b) in such a way as to transfer heat power from the third gas turbine line (70c) to the second gas turbine line (70b). 42. Method (800) for controlling a fuel supply system (10) for a power generation system (1), in particular a fuel supply system (10) according to any of embodiments 1 to 21, comprising: a) Querying and receiving (810) at least one fuel parameter target value associated with fuel in a decoupling tank (300), b) Determining (820) at least one operating parameter value of a fuel compressor (200) which is fluidically connected to the decoupling tank (300), based on the at least one fuel parameter target value, c) Operating (830) the fuel compressor (200) based on at least one operating parameter to provide fuel with at least one fuel parameter target value in the decoupling tank (300). 43. Method (800) according to embodiment 42, further comprising: Supply (840) at least one combustion unit (20) with fuel with at least one fuel parameter target value from the decoupling tank (300). 44. Method (800) according to embodiment 42 or embodiment 43, wherein the at least one fuel parameter target value is a fuel pressure target value in the decoupling tank (300). 45. Method (800) according to any embodiment 42 to 44, wherein the at least one operating parameter value is a speed of the fuel compressor (200). 46. ​​Method (800) according to any embodiment 42 to 45, wherein the power generation system (1) comprises a first gas turbine (2, 2a) and at least a second gas turbine (2, 2b), wherein querying and obtaining (810) at least one fuel parameter target value comprises: Obtaining an initial required fuel parameter value, which is linked to fuel required to supply a combustion unit (20, 20a) of the first gas turbine (2, 2a), Obtain at least one second required fuel parameter value, which is linked to fuel required to supply a combustion unit (20, 20b) of the at least one second gas turbine (2, 2b), Determine which fuel parameter value of the first required fuel parameter value and of at least one second required fuel parameter value has the highest fuel parameter value, and set the target fuel parameter value such that it corresponds at least to the highest required fuel parameter value. 47. Method (800) according to any embodiment 42 to 46, further comprising: Querying and obtaining (850) at least a second fuel parameter target value, which is linked to fuel in a fuel distribution line (130), wherein the fuel distribution line (130) is arranged downstream of the decoupling tank (300) and fluidically connected to it, Determining (820) at least one operating parameter value of the fuel compressor (200) based on at least one second fuel parameter target value, Operating (830) the fuel compressor (200) on the basis of at least one operating parameter to provide fuel with at least one second fuel parameter target value in the fuel distribution line (130), in particular wherein the at least one second fuel parameter target value is a fuel mass flow in the fuel distribution line (130). 48. Method (800) according to any embodiment 42 to 47, wherein the method is a computer-implemented method. 49. A computer system configured to execute the computer-implemented method according to embodiment 48. 50. A computer program configured to execute the computer-implemented method according to embodiment 48. 51. A computer-readable medium or signal that stores the computer program of embodiment 50.

Claims

[1] Fuel supply system (10) for a power generation system (1), comprising: a fuel supply line (110), a main fuel line (120) and a fuel distribution line (130), a fuel compressor (200), and a decoupling tank (300), wherein the fuel supply line (110) is fluidically connected to the fuel compressor (200) and can be connected to a fuel source (11) in order to supply fuel to the fuel compressor (200) from the fuel source (11), wherein the decoupling tank (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 line (130) is arranged downstream of the decoupling tank (300) and fluidically connected to it, and wherein the fuel distribution line (130) is fluidically connectable 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 tank (300), characterized by , that the decoupling container (300) comprises at least two container chambers (310a, 310b, 310c) and that the fuel distribution line (130) comprises at least two separate partial lines (130a, 130b, 130c), wherein each container chamber (310a, 310b, 310c) can be fluidically connected separately to a respective combustion unit (20, 20a, 20b) via a corresponding partial line (130a, 130b, 130c). [2] Fuel supply system (10) according to claim 1, wherein the fuel supply system (10) comprises exactly one fuel compressor (200) and exactly one decoupling tank (300). [3] Fuel supply system (10) according to claim 1 or claim 2, wherein a first distribution valve element (170a, 170b, 170c) is provided in at least one or each of the partial lines (130a, 130b, 130c). [4] Fuel supply system (10) according to any of the preceding claims, wherein the main fuel line (120) comprises at least two sub-lines (120a, 120b, 120c) which each connect the main fuel line (120) to a respective reservoir chamber (310a, 310b, 310c). [5] Fuel supply system (10) according to claim 4, wherein a second distribution valve element (121a, 121b, 121c) is provided in at least one or in each of the partial lines (120a, 120b, 120c), and / or wherein a check valve (510a, 510b, 510c) is provided in each of the partial lines (120a, 120b, 120c). [6] Fuel supply system (10) according to any of the preceding claims, wherein the fuel compressor (200) is designed to supply fuel at a target fuel pressure value in the decoupling reservoir (300). [7] Fuel supply system (10) according to any of the preceding claims, wherein the fuel source (11) is a supply network and wherein the fuel is a gaseous fuel. [8] Power generation system (1), comprising: a fuel supply system (10) according to any of the preceding claims, and at least two combustion units (20, 20a, 20b), wherein the at least two combustion units (20, 20a, 20b) are arranged downstream of the fuel supply system (10) and are fluidically connected to the decoupling tank (300) via the fuel distribution line (130). [9] Power generation system (1) according to claim 8, wherein the power generation system (1) comprises at least two gas turbines (2, 2a, 2b) each having a combustion unit (20, 20a, 20b), and wherein the fuel distribution line (130) is fluidically connected to the respective combustion unit (20, 20a, 20b) of the at least two gas turbines (2, 2a, 2b) of the power generation system (1) and supplies the respective combustion units (20, 20a, 20b) of the at least two gas turbines (2, 2a, 2b) with fuel from the decoupling tank (300), wherein the at least two gas turbines (2, 2a, 2b) provide the same power, or provide different power. [10] Power generation system (1) according to claim 8 or claim 9, wherein the respective combustion unit (20, 20a, 20b) has at least one pressure control element (24, 24a, 24b) which is arranged in a combustion unit supply line (21) and is designed to adjust a fuel parameter value of the fuel in the combustion unit supply line (21), and wherein the at least one pressure control element (24) is designed to maintain the fuel pressure value between a lower and an upper pressure threshold value. [11] Power generation system (1) according to any one of claims 8 to 10, wherein the 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 it, and wherein the at least one gas turbine (2) comprises a generator unit (50) which is operationally coupled to the turbine unit (40). [12] Method (800) for controlling a fuel supply system (10) for a power generation system (1), comprising: a) Querying and retrieving (810) a fuel parameter target value associated with fuel in a first reservoir chamber (310a) of a decoupling tank (300), querying and retrieving (810) at least one further fuel parameter target value associated with fuel in at least a second reservoir chamber (310b, 310c) of the decoupling tank (300), b) Determining (820) at least one operating parameter value of a fuel compressor (200) which is fluidically connected to the first reservoir chamber (310a) and the at least one second reservoir chamber (310b, 310c) of the decoupling tank (300), based on the fuel parameter target value or the at least one further fuel parameter target value, c) Operating (830) the fuel compressor (200) based on at least one operating parameter to supply fuel with the fuel parameter target value or at least one further fuel parameter target value to the first reservoir chamber (310a) and the at least one second reservoir chamber (310b, 310c) of the decoupling tank (300). [13] Method (800) according to claim 12, wherein the fuel parameter target value is a fuel pressure target value in the first container chamber (310a) and wherein the at least one further fuel parameter target value is a fuel pressure target value in the at least one second container chamber (310b, 310c) and wherein the at least one operating parameter value is a speed of the fuel compressor (200). [14] Method (800) according to claim 12 or claim 13, wherein the power generation system (1) comprises a first gas turbine (2, 2a) comprising the first combustion unit (20, 20a) and at least a second gas turbine (2, 2b) comprising the at least one second combustion unit (20, 20b), wherein querying and obtaining (810) the fuel parameter target value and the at least one further fuel parameter target value comprises: Obtaining an initial required fuel parameter value, which is linked to the fuel required to supply the first combustion unit (20, 20a), Obtain at least one second required fuel parameter value, which is linked to fuel required to supply at least one second combustion unit (20, 20b), Determine which of the first required fuel parameter values ​​and of at least one second required fuel parameter value has the highest fuel parameter value, and Setting the fuel parameter target value, or at least one other fuel parameter target value, such that it corresponds at least to the highest required fuel parameter value. [15] Method (800) according to any one of claims 12 to 14, wherein the method is a computer-implemented method.

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