Fuel supply system for a power generation system

Abstract

The present invention relates to a fuel supply system (10) for a power generation system (1), in particular for a micro gas turbine system. The fuel supply system (10) comprises a fuel supply line (110), a main fuel line (120), a fuel distribution line (130), a fuel compressor (200), and a decoupling tank (300). 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). 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). The fuel distribution line (130) is arranged downstream of the decoupling tank (300) and is fluidly connected to the latter.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).

Description

Technical area

[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, having such a fuel supply system and a method for controlling the fuel supply system for a power generation system. background

[0002] Power generation systems, in particular gas turbine systems or micro gas turbine systems, are used to generate electrical power and / or heat by burning a gaseous or liquid fluid (in particular fuel). The medium burned in a combustion unit can be expanded in a turbine, which in turn can be functionally connected to a generator for generating electrical power. Additionally or alternatively, a heat exchanger can be provided to utilize the waste heat generated by the combustion. Depending on requirements, power generation systems can have one or more (micro) gas turbines, each with a combustion unit. The gas turbines can each provide the same power or different power outputs.Particularly for power generation systems that comprise multiple (micro) gas turbines, each with a combustion unit, a separate fuel supply system is required for each gas turbine due to different operating conditions (e.g., transient operation) and / or different load conditions. The combustion units are therefore each supplied by a separate fuel supply system in order to provide fuel to the individual combustion units at a specific pressure, temperature, and / or mass flow (or flow rate), which is adapted to the corresponding power, 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 the latter. The gas turbine can be used as a marine propulsion system for a tanker. The system enables 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 17 558 428 U, which deals with a fuel system for a micro gas turbine, to JP 2002 - 195 055 A, which deals with a micro gas turbine, and to CN 2 05 858 495 U, which deals with an internal combustion engine.

[0004] Every fuel supply system usually has several components such as lines, seals, valves, and pumps or compressors. Some of the components can be actively controlled, such as actuatable valves, to deliver fuel with specific parameters such as a flow rate. Other components can be safety components that meet certain safety standards for the overall system and are intended to 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, which can be used to provide a specific pressure or mass flow to the respective combustion units.Power generation systems with one or more conventional fuel delivery systems require a large number of components, resulting in high costs, space requirements, and complexity. Furthermore, the application range of conventional fuel delivery 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 power generation system, in particular a gas turbine system or micro gas turbine system, with a fuel supply system according to claim 1, 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 power generation system and of 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. Furthermore, the fuel supply system comprises a fuel compressor and a decoupling tank. The fuel supply line is fluidly connected to the fuel compressor and connectable to a fuel source in order to supply fuel from the fuel source to the fuel compressor. The decoupling tank is arranged downstream of the fuel compressor and is fluidly connected to the fuel compressor via the main fuel line. The fuel distribution line is arranged downstream of the decoupling tank and is fluidly connected to it.The fuel distribution line is fluidly connectable to at least one combustion unit of a power generation system and is designed to supply the at least one combustion unit with fuel from the decoupling tank.

[0008] Using the fuel supply system according to the invention, one or more combustion units can be reliably supplied with fuel. In particular, by providing the decoupling tank, one or more combustion units can be supplied with just a single fuel supply system, even under different load conditions, operating states (e.g., transient operation), and / or different power levels. The fuel compressor can provide the required target pressure in the decoupling tank, which leads to a reduction in components, particularly in power generation systems with multiple (micro) gas turbines. This can also reduce costs and / or the complexity of the system. Since only one fuel compressor is required together with the decoupling tank, the installation space and / or space requirement can be reduced.More specifically, the decoupling tank eliminates the need for many additional components in the fuel supply system, such as individual main gas compressors and / or pre-compressors (especially compared to multiple fuel supply systems). Furthermore, the decoupling tank and fuel compressor can be located outside the combustion unit, resulting in a simplification of 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 compressors and / or pre-compressors, can be eliminated. Furthermore, the application range of the fuel supply system can be expanded.

[0009] The decoupling tank can also be referred to as a decoupling tank. In this context, "decoupling tank or decoupling tank" means that an (intermediate) component is provided 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, in particular one or more combustion units, to be supplied from the decoupling tank of the fuel supply system. This is achieved by providing and / or storing fuel with a fuel parameter target value, in particular a fuel pressure target value, in the decoupling tank. The fuel pressure target value can correspond to a highest required fuel pressure target 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 the one or more consumers via the intermediate component in the form of the decoupling tank. 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 function of fuel storage and / or the provision of fuel with the fuel parameter target value cannot be provided. In particular, multiple consumers or combustion units, each of which may at least partially have a different fuel parameter target value (e.g., a fuel pressure target value) (e.g., due to different load conditions, operating conditions, and / or power levels), cannot be supplied from the decoupling tank.In embodiments, the fuel supply line may be optional, for example if the fuel compressor is directly connectable or connected to the fuel source.

[0010] In some embodiments, the fuel supply system may comprise precisely one fuel compressor, in particular a high-pressure fuel compressor. The fuel may be a gaseous fuel, in particular propane, natural gas, hydrogen, or biogas.

[0011] In embodiments, the fuel distribution line can be fluidly connected to at least two combustion units of the power generation system and can be designed to supply the at least two combustion units with fuel from the decoupling tank. For example, the at least two combustion units can have different power levels, different load conditions, and / or different operating conditions. The at least two combustion units can require different fuel parameter values, for example, different fuel pressure values. The decoupling tank can be designed to supply the at least two combustion units with fuel with a respectively required fuel parameter value. Fuel with a fuel parameter target value can be provided in the decoupling tank, which corresponds to a highest required fuel parameter value of the at least two combustion units.The fuel distribution line may comprise at least two sub-lines, each of which is connected to the at least two combustion units.

[0012] In embodiments, the power generation system may comprise at least one gas turbine having the at least one combustion unit. The fuel distribution line may be fluidly connectable to the combustion unit of the at least one gas turbine of the power generation system and configured to supply the combustion unit of the at least one gas turbine with fuel from the decoupling tank.

[0013] In embodiments, the power generation system may comprise at least two gas turbines, each having a combustion unit. The fuel distribution line may be fluidly connectable to the respective combustion unit of the at least two gas turbines of the power generation system and configured to supply the respective combustion units of the at least two gas turbines with fuel from the decoupling tank.

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

[0015] In embodiments, the fuel supply system may comprise at least one vent line which fluidically connects the main fuel line and an atmosphere outlet of the vent line or the fuel supply system.

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

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

[0018] In some embodiments, the fuel supply system can comprise precisely one decoupling tank. In some embodiments, a plurality of decoupling tanks can also be provided. These can be connected in parallel to one another. This makes it possible to provide energy optimization with greatly differing power levels of several gas turbines. In some embodiments, these can also be provided in series. In some embodiments, the decoupling tank can comprise a plurality of tank chambers. Alternatively, the decoupling tank can comprise precisely one tank chamber. In some embodiments, the decoupling tank can comprise at least two tank chambers. The fuel distribution line can comprise at least two separate sub-lines. Each tank chamber can be separately fluidically connected to a respective combustion unit via a corresponding sub-line.The main fuel line may comprise at least two sub-lines, each connecting the main fuel line to a respective container chamber.

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

[0020] In some embodiments, the fuel supply system may include at least one check valve arranged 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 that is lower than the pressure in the decoupling tank is built up).

[0021] In embodiments, the fuel compressor may be designed to provide fuel with a fuel parameter target value, in particular a fuel pressure target value, in the decoupling tank.

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

[0023] In some embodiments, the fuel supply system may comprise at least a first shut-off valve, which is arranged in the main fuel line downstream or upstream of the fuel compressor. Using the shut-off valve, the fuel supply can be shut off or prevented quickly and centrally, for example, in a dangerous, emergency, or maintenance situation.

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

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

[0026] In some embodiments, the fuel source may be a supply network, in particular a supply network, e.g., of a decentralized energy supply. In other embodiments, the fuel source may be a fuel storage facility.

[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 fluidly connected to the decoupling tank via the fuel distribution line, wherein the at least one combustion unit is supplied with fuel from the decoupling tank. This system can also provide the above-described advantageous effects of the power generation system. A micro gas turbine system is understood to be a system having one or more micro gas turbines, each capable of providing an output of 30 kW to 500 kW.However, the designs described here can also be applied to higher power gas turbine systems.

[0028] In embodiments, the power generation system may comprise at least one (micro) gas turbine having the at least one combustion unit. The fuel distribution line may be fluidly 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 embodiments, the power generation system can comprise at least two combustion units, which are arranged downstream of the fuel supply system and are fluidly 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 a plurality of sub-lines, each of which then branches off from the fuel distribution line to the respective combustion units. In other embodiments, the fuel distribution line can have a plurality of sub-lines, which are provided separately from one another and separately connect the respective combustion units to the decoupling tank.

[0030] The power generation system comprises at least two (micro) gas turbines, each having a combustion unit. The fuel distribution line is fluidly connected to the respective combustion unit of the at least two gas turbines of the power generation system in order to 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 may comprise a combustion unit supply line and at least one burner. The combustion unit supply line may fluidically connect the burner to the fuel distribution line. In some embodiments, the at least one burner may comprise a main burner and a pilot burner.

[0032] In embodiments, the fuel supply system may comprise 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 embodiments, the at least two (micro) gas turbines can provide the same power or provide a different power.

[0034] In embodiments, the combustion unit may comprise 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 some embodiments, the combustion unit may have at least one pressure adjustment element arranged in the combustion unit supply line and configured to adjust a fuel parameter value of the fuel, in particular a fuel pressure value, in the combustion unit supply line. In some embodiments, the at least one pressure adjustment element may be configured to maintain the fuel parameter value, in particular the fuel pressure value, between a lower and an upper pressure threshold value.

[0036] In embodiments, the combustion unit may comprise at least one second pressure sensor and / or a second temperature sensor arranged in the combustion unit supply line.

[0037] In embodiments, the power generation system may comprise a first proportional valve and at least one second proportional valve. The first proportional valve may be arranged upstream of the main burner in a first sub-line of the combustion unit supply line. The second proportional valve may be arranged upstream of the pilot burner in a second sub-line of the combustion unit supply line. The first proportional valve and the at least one second proportional valve may be configured to control a fuel proportion to be supplied to the main burner and the pilot burner, respectively.

[0038] In some embodiments, the at least one gas turbine may comprise a compressor unit arranged upstream of the combustion unit and fluidly connected thereto. In some embodiments, the compressor unit may be fluidly connected to a mixing zone of the at least one burner and configured to supply compressed air to the mixing zone. The mixing zone may be configured to mix the fuel and the compressed air.

[0039] In embodiments, the at least one gas turbine may comprise a turbine unit arranged downstream of the combustion unit and fluidly connected thereto. In embodiments, the at least one gas turbine may comprise a generator unit operatively coupled to the turbine unit. In embodiments, the gas turbine may comprise a shaft rotatably mounted in a bearing housing. A rotor of the generator unit may be rotationally fixedly coupled to the turbine unit via the shaft. In embodiments, the turbine unit may be rotationally fixedly coupled to the compressor unit via the shaft.

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

[0041] In embodiments, the at least one gas turbine can comprise at least one recuperator unit. The at least one recuperator unit can be arranged and configured in the first gas turbine line and the second gas turbine line in such a way to transfer heat power from the first gas turbine line to the second gas turbine line. In embodiments, the at least one recuperator unit can also be arranged and configured between the third gas turbine line and the second gas turbine line in such a way to transfer heat power from the third gas turbine line to the second gas turbine line. The at least one recuperator unit can also comprise a first recuperator unit and a second recuperator unit, which are arranged at 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 associated with fuel in a decoupling tank, b) determining at least one operating parameter value of a fuel compressor fluidically connected to the decoupling tank on the basis of the at least one fuel parameter target value, c) operating the fuel compressor based on the at least one operating parameter to provide fuel having the at least one fuel parameter target value in the decoupling tank.

[0043] This method can provide the above-described advantageous effects of the fuel supply system and the power generation system. The method can be applied analogously to the control of the power generation system according to the second aspect of the present invention. Consequently, 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 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 embodiments, the method may further comprise: Supplying at least one combustion unit with fuel having the at least one fuel parameter target value from the decoupling tank.

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

[0046] In embodiments, the power generation system may include a first gas turbine and at least one second gas turbine. Requesting and obtaining at least one fuel parameter target value may include: Obtaining a first required fuel parameter value associated with fuel required to supply a combustion unit of the first gas turbine; Obtaining at least one second required fuel parameter value associated with fuel required to supply a combustion unit of the at least one second gas turbine; Determining which of the first required fuel parameter values ​​and the at least one second required fuel parameter value has the highest fuel parameter value; and Setting the fuel parameter target value such that it corresponds to at least the highest required fuel parameter value.

[0047] In embodiments, the method may further comprise: Querying and obtaining at least one second fuel parameter target value associated with fuel in a fuel distribution line, the fuel distribution line being located downstream of and fluidly connected to the decoupling reservoir; Determining the at least one operating parameter value of the fuel compressor based on the at least one second fuel parameter target value; Operating the fuel compressor based on the at least one operating parameter to provide fuel having the at least one second fuel parameter target value in the fuel distribution line.

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

[0049] In embodiments, the method can be a computer-implemented method. Supplying at least one combustion unit with fuel having the at least one fuel parameter target value can be implemented by appropriately controlling at least one outlet valve element, which is provided, for example, between the decoupling tank and the fuel distribution line. Operating the fuel compressor based on the 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.

[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, there is provided a computer-readable medium or signal storing the computer program according to the fifth aspect of the present invention. Short description of the characters Fig. 1 shows a schematic view of a fuel supply system according to the invention for a power generation system connected to at least one combustion unit; Fig. Figure 2 is a detailed view of the fuel supply system according to the invention and the at least one combustion unit of Fig. 1; Fig. 3 shows a power generation system according to the invention with the fuel supply system and at least one gas turbine; Fig. 4 shows a schematic flow diagram of the method according to the invention for controlling the fuel supply system; Fig. 5 shows the fuel supply system according to the invention with a decoupling tank, which can have several tank chambers. Detailed description

[0053] Fig. 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. In addition, the fuel supply system comprises a fuel compressor 200 and a decoupling tank 300. As in Fig. 1, the fuel supply line 110 is fluidly connected at one end to the fuel compressor 200. At the other end, the fuel supply line 110 is fluidly connectable to a fuel source 11 in order to supply fuel from the fuel source 11 to the fuel compressor 200. In Fig. 1, the fuel supply line 110 is shown as being fluidly connected to the fuel source 11. The decoupling tank 300 is arranged downstream of the fuel compressor 200 and is fluidly 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 is fluidly connected to the decoupling tank at a first end. The fuel distribution line 130 is fluidly connectable to at least one combustion unit 20 of a power generation system 1, in particular a (micro) gas turbine system, at a second end and is designed to supply the at least one combustion unit 20 with fuel from the decoupling tank 300. In Fig. 1, the fuel distribution line 130 is fluidly connected to the at least one combustion unit 20.

[0055] Using the fuel supply system 10 according to the invention, one or more combustion units 20 can 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 with a target fuel pressure in the decoupling tank 300. Consequently, the fuel compressor 200 can provide a target pressure (or fuel with a target fuel pressure) required for the supply in the decoupling tank 300, which can lead to a reduction in components, particularly in power generation systems 1 with multiple (micro) gas turbines 2, 2a, 2b.This can also reduce costs and / or the complexity of the overall system. Since only one fuel compressor 200 is required together with the decoupling tank 300, the installation space or space requirement can be reduced. More specifically, the decoupling tank 300 in the fuel supply system 10 makes many other components such as individual main gas compressors and / or pre-compressors unnecessary (particularly in comparison to several individual fuel supply systems per combustion unit). In addition, the decoupling tank 300 and the fuel compressor 200 can be provided outside the combustion unit 20, which can lead to a simplification of 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 compressors and / or pre-compressors can also be omitted.In addition, an application range of the fuel supply system 10 can be expanded.

[0056] The decoupling tank 300 can also be referred to as a decoupling tank. In this context, "decoupling tank 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 tank 300 enables one or more consumers, in particular, one or more combustion units 20, to be supplied from the decoupling tank 300 of the (single) fuel supply system 10. This is achieved by providing and / or storing fuel with a fuel parameter target value, in particular a fuel pressure target value, in the decoupling tank 300. The fuel parameter target value can correspond to at least one highest required fuel pressure value of the one or more combustion units 20.In other words, the fuel line in which fuel is compressed by the fuel compressor may not be directly connected to one or more consumers, but may 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 may also be influenced or prevented by a shut-off valve or throttle valve - however, in this case, the function of fuel storage and / or the provision of fuel with the fuel parameter target value for multiple consumers, in particular combustion units 20, cannot be provided. Sometimes, multiple consumers or combustion units 20, which at least partially require a different fuel parameter value (e.g., a fuel pressure value) (e.g.,The fuel supply line 110 can be optional, for example, if the fuel compressor 200 is directly connectable to or connected to the fuel source 11 (depending on the load conditions, operating conditions, and / or power levels). The fuel supply line 110 can be optional, for example, if the fuel compressor 200 is directly connectable to or connected to the fuel source 11. The fuel supply line 110 can comprise at least one outlet valve element, by means of which an outlet of fuel into the fuel distribution line 130 from the fuel supply line 130 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., of a decentralized energy supply. In other embodiments, the fuel source 11 can be a fuel storage facility.

[0058] Fig. 2 is a detailed view of the fuel supply system 10 according to the invention and the at least one combustion unit 20 of Fig. 1. As in Fig. 1 and Fig. 2, the fuel supply system 10 can comprise precisely 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 multiple combustion units 20, 20a, 20b, 20c, 20d are supplied with fuel. Costs and the complexity of the entire power generation system 1 can also be reduced. 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 which can be arranged downstream in the main fuel line 120 of the first fuel compressor.For example, the at least one second fuel compressor can 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 can be a low-pressure compressor, and the at least one second fuel compressor can be a high-pressure compressor. For example, intermediate cooling can be provided between the two compressors to increase efficiency.

[0059] In 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 configured to supply fuel around the fuel compressor 200 from the fuel supply line 110 to the main fuel line 120. For example, the fuel source 11 can already provide fuel at a certain pressure level or comprise 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, for example, in low-load conditions of the at least one combustion unit 20, the fuel compressor bypass 160 can be opened using a bypass valve element or closed again as needed.

[0060] As in the Fig. 1 and Fig. 2, the fuel distribution line 130 can be fluidically connectable (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. In the Fig. 1 and Fig. 2, the fuel distribution line 130 is shown 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 fuel to multiple combustion units 20, 20a, 20b, 20c, 20d. 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 to the respective combustion unit 20, 20a, 20b, 20c, 20d.

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

[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 can be designed to control a fuel portion to be supplied to the respective one 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 alternatively to a pressure adjustment 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 adjustment element. In other embodiments, the 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 adjustment 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, for example, FIG. Fig. 5), a distribution valve element 121a, 121b, 121c can be provided in at least one or all of the at least two sub-lines 120a, 120b, 120c of the main fuel line 120. Using the distribution valve element 121a, 121b, 121c, fuel with a specific fuel parameter value, in particular fuel pressure, can be provided in the respective container chamber 310a, 310b, 310c. In other words, a respective fuel parameter value can be provided in the respective container chamber 310a, 310b, 310c by 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 provided in the main fuel line 120).

[0063] In embodiments, the fuel distribution line 130 can be fluidically connectable (or connected) to at least three combustion units 20a, 20b, 20c or at least four combustion units 20a, 20b, 20c, 20d and can be designed to supply the at least three combustion units 20a, 20b, 20c or at least four combustion units 20a, 20b, 20c, 20d with fuel from the decoupling tank 300. In one embodiment, only one combustion unit 20, 20a can be provided. The fuel distribution line 130 can be fluidically connectable (or connected) to this and can be designed to supply it with fuel from the decoupling tank 300. As in Fig. 1, exactly four combustion units 20a, 20b, 20c, 20d can be provided. As shown in Fig. As shown in Figure 2, exactly three combustion units 20a, 20b, 20c can be provided. In embodiments, exactly two combustion units 20a, 20b can be provided. The number of combustion units 20 can depend on the total power to be provided by the power generation system 1 (described further 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 embodiments, a plurality of decoupling tanks 300 may also be provided. These may be provided parallel to one another and, in particular, each connected to the main fuel line 120 and the fuel distribution line 130. This allows for energy optimization at greatly differing power levels of several gas turbines 2, 2a, 2b. As described above, in embodiments, the decoupling tank 300 may comprise a plurality of tank chambers. Alternatively, the decoupling tank 300 may comprise exactly one tank chamber. In all embodiments, as in Fig. 2, the fuel supply system 10 may include a decoupling tank bypass 150 fluidly connecting the main fuel line 120 and the fuel distribution line 130 and configured to supply fuel around the decoupling tank 300 from the main fuel line 120 to the fuel distribution line 130. In particular, a first bypass valve may be arranged in the decoupling tank bypass 150. The decoupling tank bypass 150 may be used when supplying multiple combustion units that each have the same power levels and / or operating states or load states at a time. The decoupling tank bypass 150 may be used when the at least one combustion unit is operated in a low-load state. The decoupling tank bypass 150 may also be used when only one combustion unit 20 is supplied with fuel.If at least two separate partial lines 130a, 130b, 130c of the fuel distribution line 130 are provided (see . Fig. 5), the decoupling tank bypass 150 can connect the main fuel line 120 to the respective separate sublines 130a, 130b, 130c. In this case, the bypass can have several bypass sublines. These can each have a bypass valve.

[0065] As in Fig. 1 and Fig. As shown in Figure 2, the fuel supply system 10 may include a fuel heat exchanger 400. This may be arranged in the main fuel line 120 downstream of the fuel compressor 200 and configured to remove heat from the main fuel line 120. In particular, it may be necessary to limit a 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 into a cooling medium (e.g., oil, gas, water, or air) in the heat exchanger may be adjusted.

[0066] The fuel supply system 10 may comprise at least one vent line 140, which fluidically connects the main fuel line 120 and an atmosphere 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 through the 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 in the open position. The at least one vent line 140 can be fluidically connectable (or connected) to a combustion unit supply line 21 and can be designed to discharge fuel from the combustion unit supply line 21. As shown in Fig. 2, the at least one vent line 140 may include a first vent line 140a fluidly connecting 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 may be arranged in the first vent line 140a. The at least one vent line 140 may include a second vent line 140b fluidly connecting 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 may be arranged in the second vent line 140b. The at least one vent line 140 may comprise 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 vent valve 142c may be arranged in the at least one third vent line 140c.

[0067] As in Fig. 2, the fuel supply system 10 may include at least one check valve 510, which is arranged upstream of the decoupling tank 300 in the main fuel line 120. The check valve 510 may prevent a backflow of compressed fuel from the decoupling tank 300, in particular when the fuel compressor 200 is not operating or is operating at low speeds (and thus only a pressure is built up which is lower than a pressure in the decoupling tank 300). In the embodiments in which at least two partial lines 120a, 120b, 120c of the main fuel line 120 are provided (see, for example, Fig. 5), alternatively or additionally, a check valve 510a, 510b, 510c may be provided in each partial line 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. Using the first shut-off valve 520, a fuel supply can be shut off or prevented quickly and centrally, for example, in a dangerous situation, emergency situation, 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 contaminants from the fuel.

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

[0071] The fuel supply system 10 may include at least one first pressure sensor 700, 700a, 700b and / or a 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 may 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 configured 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 the embodiments in which at least two separate partial lines 130a, 130b, 130c of the fuel distribution line 120 and / or at least two partial 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 can be provided in the corresponding sub-line.

[0072] Fig. 3 shows a power generation system 1 according to the invention with the fuel supply system 10 and at least one gas turbine 2, 2a, 2b. The power generation system 1 comprises 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 fluidly 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, may comprise at least one (micro) gas turbine 2, which has the at least one combustion unit 20. The fuel distribution line 130 may be fluidly connectable (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 in Fig. 3, the power generation system 1 can comprise at least two (micro) gas turbines 2, 2a, 2b, each having a combustion unit 20, 20a, 20b. The fuel distribution line 130 can be fluidly connectable (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 configured 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 embodiments, the at least two gas turbines 2, 2a, 2b can provide the same power or a different power. In embodiments, the power generation system 1 can provide a total power of 1 MW. In a first example, the power generation system 1 can comprise three gas turbines, each with a power of 333 kW, to provide the total power. In this case, all gas turbines supply the same power (e.g., electrical power and / or thermal power). The respective combustion units 20a, 20b, 20c can be supplied with fuel at approximately the same pressure level and / or mass flow from the decoupling vessel 300. In a further example, four gas turbines can be provided, with two gas turbines each having a power of 200 kW and two gas turbines each having a power of 300 kW, in order to be able to provide the total power 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 output can have a greater fuel requirement (or require fuel at a higher pressure and / or mass flow) than the gas turbines with the lower output. The decoupling tank 300 can provide fuel with a fuel pressure target 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 embodiments, the decoupling tank 300 can have a capacity of approximately 2000 liters. The respective fuel requirement (orFuel with a required fuel parameter value, in particular a fuel pressure and / or mass flow) to the individual combustion units 20 of the gas turbines 2, 2a, 2b can then be regulated. For such power generation systems 1 with a plurality of gas turbines 2, 2a, 2b, only a (single) fuel supply system 10 according to the invention with the decoupling tank 300 is required in order to be able to provide the corresponding fuel. Particularly for systems with a plurality of gas turbines 2, 2a, 2b, components can therefore be saved, the required space can be reduced, complexity can be reduced and / or costs can be reduced because no fuel supply system 10 needs to be provided for each combustion unit 20 or gas turbine 2. In this example, in at least one of the gas turbines 2, 2a, 2b, the highest required fuel pressure value 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 in the decoupling tank 300 of approximately 14 bar. This can be higher than the highest required fuel pressure value to account for potential losses. The fuel compressor 200 can be controlled accordingly to provide the fuel pressure from approximately 5 bar from 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 the embodiments in which multiple tank chambers 310a, 310b, 310c are provided (see ). Fig. 5), which are fluidically connected to the respective combustion units of the gas turbines via the separate sub-lines 130a, 130b, 130c. Via the described components (such as pressure adjustment elements (described further below), corresponding proportional valves, and / or distribution valve elements), fuel with a required fuel parameter value for the respective gas turbine can be provided in the respective container chamber 310a, 310b, 310c.

[0075] As in Fig. 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 sub-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 may be provided in the combustion unit supply line 21 upstream of the burner 22.

[0076] As already briefly mentioned above and in Fig. 2, the at least one combustion unit 20 can have at least one pressure setting 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 setting element 24 can be designed to keep 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 fuel pressure target value. In particular, a first pressure setting element 24a and a second pressure setting element 24b can be provided. The first pressure setting element 24a can be designed to keep the fuel pressure value at or above a lower pressure threshold value.The second pressure adjustment element 24b can be configured to maintain the fuel pressure value at or below an upper pressure threshold. The first pressure adjustment element 24a can be arranged upstream of the second pressure adjustment element 24b in the combustion unit supply line 21.

[0077] The at least one combustion unit 20 can comprise at least one second pressure sensor 25 and / or a second temperature sensor 26, which is arranged in the combustion unit supply line 21. Furthermore, the at least one combustion unit 20 can comprise 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 sub-line of the combustion unit supply line 21. The second proportional valve 28b can be arranged upstream of the pilot burner 22b in a second sub-line 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 fuel proportion 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 regulated depending on a pressure value that can be set in the fuel compressor 200 (in particular the fuel pressure target value), in particular based on an adjustable speed of the fuel compressor 200.

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

[0079] In embodiments, as in Fig. 2 and Fig. 3, the at least one gas turbine 2 comprises a compressor unit 30, which is arranged upstream of the combustion unit 20 and is fluidly connected thereto. 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 fluidly connected to a mixing zone of the at least one burner 22 and can be 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 provided upstream of or in 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 may comprise a turbine unit 40, which is arranged downstream of the combustion unit 20 and is fluidly connected thereto. As further described in Fig. 3, the at least one gas turbine 2 may include a generator unit 50 that is operatively coupled to the turbine unit 40. The at least one gas turbine 2 may include a shaft 60 that is rotationally mounted in a bearing housing. A rotor of the generator unit 50 may be rotationally coupled to a turbine wheel of the turbine unit 40 via the shaft 60. “Operationally” means that the turbine unit may generate a rotational movement of the shaft by expanding fluid from the combustion unit, which is then transferred to the rotor of the generator unit (which subsequently generates electrical power). In embodiments, the turbine unit 40 may be rotationally coupled to the compressor unit 30 via the shaft 60. In embodiments, the compressor unit 30 may 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, the 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 thereto. The second gas turbine line 70b is designed to discharge expanded fluid from the turbine unit 40.

[0082] In embodiments, the at least one gas turbine 2 may comprise 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 embodiments, the at least one gas turbine 2 may comprise at least one recuperator unit 90. The at least one recuperator unit 90 may 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 power from the first gas turbine line 70a to the second gas turbine line 70b (in Fig. 3 not shown). Alternatively or additionally, the at least one recuperator unit 90 between the third gas turbine line 70c and the second gas turbine line 70b is arranged and configured 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 the recuperator 90 and the combustion unit 20 (as in Fig. 3). 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 can increase the efficiency of the power generation system 1, since 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, at rated load of the power generation system 1, the following temperature sequence can occur: in the third gas turbine line 70c, the temperature of the air upstream of the entry into the recuperator 90 (arranged as in Fig. 3) may be approximately 250°C. At the outlet of the recuperator 90, the temperature of the air may be approximately 500°C. At the outlet of the at least one combustion chamber 20, 20a in the first gas turbine line 70a, the fluid (in particular exhaust gas) may have a temperature of approximately 1050°C. After exiting the turbine unit 40, the expanded fluid in the second gas turbine line 70b may 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 may have a temperature of approximately 550°C.

[0084] As in Fig. As further illustrated in Figure 3, the second gas turbine line 70b is fluidically connected to a fluid outlet 72. In 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 power from the second gas turbine line 70b to the external line 73.

[0085] Fig. Figure 4 shows a schematic flow diagram of the method according to the invention 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) querying and obtaining 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 fluidly 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 the at least one operating parameter to provide fuel having the at least one fuel parameter target value in the decoupling tank 300.

[0087] This method 800 can provide the above-described advantageous effects of the fuel supply system 10 and the power generation system 1. Furthermore, the method 800 can be used to provide optimized and tailored control of the fuel supply system 10 or the power generation system 1. The 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 steps and features of the described method 800. The fuel supply system 10 and the power generation system 1 can comprise the features or configurations described above. In particular, a fuel distribution line 130 is arranged downstream of the decoupling tank 300 and is fluidly connected thereto.The fuel distribution line 130 is fluidly connectable (or connected) to at least one combustion unit 20 of the power generation system 1 and configured to supply the at least one combustion unit 20 with fuel having the at least one fuel parameter target value from the decoupling reservoir 300.

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

[0089] As described above, the power generation system 1 may include a first gas turbine 2, 2a and at least one second gas turbine 2, 2b. Querying and obtaining 810 at least one fuel parameter target value may 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, 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.

[0090] In addition, querying and obtaining 810 the at least one fuel parameter target value may include: Determining which of the first required fuel parameter value and the at least one second required fuel parameter value has the highest required fuel parameter value, and Setting the fuel parameter target value such that it corresponds to at least the highest required fuel parameter value.

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

[0092] In embodiments, the method 800 may further include: Querying and obtaining 850 at least one second fuel parameter target value associated with fuel in a fuel distribution line 130, wherein the fuel distribution line 130 is arranged downstream of the decoupling tank 300 and is fluidly connected thereto, Determining the at least one operating parameter value of the fuel compressor 200 based on the at least one second fuel parameter target value, and operating the fuel compressor 200 based on the at least one operating parameter to provide fuel having the at least one second fuel parameter target value in the fuel distribution line 130.

[0093] The at least one second fuel parameter target value may be a fuel mass flow in the fuel distribution line 130. In embodiments, the at least one second fuel parameter target value may 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 may comprise querying and obtaining 850 at least one second fuel parameter target value associated with fuel in a combustion unit supply line 21, wherein the combustion unit supply line 21 is arranged downstream of the decoupling tank 300 and fluidly connected to the fuel distribution line 130.

[0094] Alternatively or additionally, in the embodiments in which at least two container chambers 310a, 310b, 310c are present and are each fluidically connected to the at least two combustion units, the querying and obtaining 810 of the at least one fuel parameter target value may comprise: Querying and obtaining 810 a fuel parameter target value associated with fuel in a first reservoir chamber 310a of the decoupling reservoir 300, Querying and obtaining 810 at least one further fuel parameter target value associated with fuel in at least one second reservoir chamber 310b, 310c of the decoupling reservoir 300.

[0095] In these embodiments, querying and obtaining 810 the at least one fuel parameter target value may further include: Obtaining a first required fuel parameter value associated with 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 container chamber 310a, and Obtaining at least one second required fuel parameter value associated with 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 fuel parameter target 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 fuel parameter target value in the at least one second container chamber. Furthermore, querying and obtaining 810 of the at least one fuel parameter target value can include: Determining which of the first required fuel parameter value and the at least one second required fuel parameter value has the highest required fuel parameter value, and Setting the fuel parameter target value such that it corresponds to at least the highest required fuel parameter value.

[0097] Since the respective required fuel parameter values ​​are linked to the respective fuel parameter target values, it is ensured that the highest fuel parameter target 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 fluidly 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 fuel parameter target 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 above-described separate sub-lines 120a, 120b, 120c of the main fuel line, the same (highest) fuel parameter target 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 fuel parameter target values ​​in the respective reservoir chambers 310a, 310b, 310c corresponding to the respective required fuel parameter values. In this case, too, the fuel compressor 200 is operated such that it provides the fuel parameter target value that is equal to or greater than the highest required fuel parameter value.

[0098] In embodiments, method 800 can be a computer-implemented method. Supplying 840 at least one combustion unit 20 with fuel having the at least one fuel parameter target value can be implemented by appropriately controlling at least one outlet valve element, which is provided, for example, between decoupling tank 300 and fuel distribution line 130 (or the corresponding sub-lines 130a, 130b, 130c). Operating 830 the fuel compressor 200 based on the 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 fuel compressor 200.

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

[0100] The computer-implemented method described above may comprise or be executable via a computer or a computer network, wherein the computer or the computer network comprises at least one processing unit (e.g., a processor) and at least one data storage (i.e., a memory). The described procedural logic may be stored in the form of executable code in at least one data storage and executed by the at least one processing unit. The systems and subsystems (e.g., the power generation system 1 and / or the fuel delivery system 10, as well as individual components such as the fuel compressor and the sensors) may 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 encompasses electrical signals and computer-readable media defining instructions that, 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 10 can comprise at least one database. Alternatively or additionally, the power generation system 1 and / or the fuel supply system 10 can access a database in a cloud (via a communications interface).The power generation system 1 and / or the fuel supply system 10 may comprise (at least one) communication interface for coupling to the individual elements of the processing unit and / or the database. The communication interface may comprise one or more of the following elements: a network, the Internet, a local area network, a wireless local area network, a cellular broadband network, and / or a wired network. In 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 defined in the appended claims, it should be understood that the invention may alternatively 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 fluidly connected to the fuel compressor (200) and connectable 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 fluidly 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 is fluidly connected thereto, 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 one 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), which are each 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 one of the preceding embodiments, wherein the power generation system (1) comprises at least one gas turbine (2) having the at least one combustion unit (20), and wherein the fuel distribution line (130) is fluidly 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 one 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 one of the preceding embodiments, comprising a fuel heat exchanger (400) arranged in the main fuel line (120) downstream of the fuel compressor (200) and adapted to remove heat from the main fuel line (120). 8. Fuel supply system (10) according to any one of the preceding embodiments, comprising at least one vent line (140) fluidly connecting 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 one of the preceding embodiments, comprising exactly one decoupling tank (300). 12. Fuel supply system (10) according to any one 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 sub-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 sub-line (130a, 130b, 130c), and in particular 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 container chamber (310a, 310b, 310c). 13. A fuel supply system (10) according to any one of the preceding embodiments, comprising a decoupling tank bypass (150) fluidly connecting the main fuel line (120) and the fuel distribution line (130) and configured 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 one of the preceding embodiments, comprising at least one check valve (510) arranged upstream of the decoupling tank (300) in the main fuel line (120). 15. The fuel supply system (10) of any of the preceding embodiments, wherein the fuel compressor (200) is configured to provide fuel at a target fuel pressure in the decoupling tank (300). 16. Fuel supply system (10) according to any one of the preceding embodiments, comprising a fuel compressor bypass (160) which fluidly connects the fuel supply line (110) and the main fuel line (120) and is designed to supply fuel around the fuel compressor (200) from the fuel supply line (110) to the main fuel line (120). 17. Fuel supply system (10) according to any one of the preceding embodiments, comprising at least one first shut-off valve (520) arranged in the main fuel line (120) downstream or upstream of the fuel compressor (200). 18. Fuel supply system (10) according to any one of the preceding embodiments, comprising a filter device (600) arranged in the fuel supply line (110) upstream of the fuel compressor (200). 19. Fuel supply system (10) according to any one of the preceding embodiments, comprising at least one pressure reduction valve (530) arranged in the fuel distribution line (130) downstream of the decoupling tank (300). 20. Fuel supply system (10) according to any one of the preceding embodiments, comprising at least one 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 one 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 one 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 fluidly 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) having the at least one combustion unit (20), and wherein the fuel distribution line (130) is fluidly 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 fluidly 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 one of 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. The power generation system (1) according to any one 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) fluidly 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) fluidly connecting the combustion unit supply line (21) and an atmosphere outlet (141) of the vent line (140). 29. Power generation system (1) according to any one of embodiments 25 to 28, wherein the at least two gas turbines (2, 2a, 2b) provide the same power, or provide a different power. 30. Power generation system (1) according to any one of embodiments 26 to 29, wherein the combustion unit (20) comprises at least one second mass flow sensor (23, 23a, 23b) arranged in the combustion unit supply line (21) and configured to measure a mass flow in the combustion unit supply line (21). 31. Power generation system (1) according to any one of embodiments 26 to 30, wherein the combustion unit (20) comprises at least one pressure adjusting element (24, 24a, 24b) which is arranged in the combustion unit supply line (21) and is designed to adjust 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 adjusting 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 one of embodiments 26 to 31, wherein the combustion unit (20) comprises at least one second pressure sensor (25) and / or a second temperature sensor (26) arranged in the combustion unit supply line (21). 33. Power generation system (1) according to any one 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 sub-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 sub-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 proportion which is to be supplied to the main burner (22a) and the pilot burner (22b) respectively. 34. Power generation system (1) according to any one of embodiments 22 to 33, wherein the at least one gas turbine (2) comprises a compressor unit (30) arranged upstream of the combustion unit (20) and fluidly connected thereto. 35. Power generation system (1) according to embodiment 34, when dependent on embodiment 26, wherein the compressor unit (30) is fluidly 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 one of embodiments 22 to 35, wherein the at least one gas turbine (2) comprises a turbine unit (40) arranged downstream of the combustion unit (20) and fluidly connected thereto. 37. Power generation system (1) according to embodiment 36, wherein the at least one gas turbine (2) comprises a generator unit (50) operatively coupled to the turbine unit (40). 38. Power generation system (1) according to embodiment 37, when dependent 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 fixedly coupled to the turbine unit (40) via the shaft (60), and in particular wherein the turbine unit (40) is rotationally fixedly coupled to the compressor unit (30) via the shaft (60). 39. Power generation system (1) according to any one of embodiments 36 to 38, wherein the at least one gas turbine (2) has a first gas turbine line (70a) and a second gas turbine line (70b), wherein the first gas turbine line (70a) 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 is fluidly connected thereto, wherein the second gas turbine line (70b) is designed to discharge expanded fluid from the turbine unit (40). 40. The power generation system (1) according to any one of embodiments 34 to 39, wherein the at least one gas turbine (2) comprises a third gas turbine line (70c) fluidly connecting the compressor unit (30) to the combustion unit (20) and is configured 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 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 to transfer heat power from the third gas turbine line (70c) to the second gas turbine line (70b). 42. A 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 one of embodiments 1 to 21, comprising: a) querying and obtaining (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 fluidly connected to the decoupling tank (300) on the basis of the at least one fuel parameter target value, c) operating (830) the fuel compressor (200) based on the at least one operating parameter to provide fuel having the at least one fuel parameter target value in the decoupling tank (300). 43. The method (800) of embodiment 42, further comprising: Supplying (840) at least one combustion unit (20) with fuel having the at least one fuel parameter target value from the decoupling tank (300). 44. The method (800) of 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. The method (800) of any of embodiments 42 to 44, wherein the at least one operating parameter value is a speed of the fuel compressor (200). 46. ​​The method (800) of any of embodiments 42 to 45, wherein the power generation system (1) comprises a first gas turbine (2, 2a) and at least one second gas turbine (2, 2b), wherein querying and obtaining (810) at least one fuel parameter target value comprises: Obtaining a 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), 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), Determining which of the first required fuel parameter value and the at least one second required fuel parameter value has the highest fuel parameter value, and setting the target fuel parameter value to be at least equal to the highest required fuel parameter value. 47. The method (800) of any of embodiments 42 to 46, further comprising: Querying and obtaining (850) at least one second fuel parameter target value associated with fuel in a fuel distribution line (130), wherein the fuel distribution line (130) is arranged downstream of the decoupling tank (300) and is fluidly connected thereto, Determining (820) the at least one operating parameter value of the fuel compressor (200) based on the at least one second fuel parameter target value, Operating (830) the fuel compressor (200) based on the at least one operating parameter to provide fuel with the 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. The method (800) of any of embodiments 42 to 47, wherein the method is a computer-implemented method. 49. A computer system configured to perform the computer-implemented method of embodiment 48. 50. A computer program configured to perform the computer-implemented method of embodiment 48. 51. A computer-readable medium or signal storing the computer program of embodiment 50.

Claims

[1] Power generation system (1), comprising: at least two gas turbines (2, 2a, 2b), each having a combustion unit (20, 20a, 20b), and a fuel supply system (10) for the 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 fluidly connected to the fuel compressor (200) and connectable 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 fluidly 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 is fluidly connected thereto, 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 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). [2] Power generation system (1) according to claim 1, wherein the fuel supply system (10) comprises exactly one fuel compressor (200). [3] Power generation system (1) according to claim 1 or claim 2, wherein the fuel distribution line (130) comprises at least two sub-lines (130a, 130b), each connected to one of the 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). [4] Power generation system (1) according to any one of the preceding claims, comprising exactly one decoupling tank (300). [5] Power generation system (1) according to claim 3 or claim 4, wherein the decoupling reservoir (300) comprises at least two reservoir chambers (310a, 310b, 310c) and wherein the fuel distribution line (130) comprises at least two separate sub-lines (130a, 130b, 130c), wherein each reservoir chamber (310a, 310b, 310c) is separately fluidically connected to a respective combustion unit (20, 20a, 20b) via a corresponding sub-line (130a, 130b, 130c), and wherein the main fuel line (120) comprises at least two sub-lines (120a, 120b, 120c), each connecting the main fuel line (120) to a respective reservoir chamber (310a, 310b, 310c). [6] Power generation system (1) according to any one of the preceding claims, wherein the fuel compressor (200) is configured to provide fuel at a target fuel pressure in the decoupling tank (300). [7] A power generation system (1) according to any one of the preceding claims, wherein the fuel source (11) is a utility network, and wherein the fuel is a gaseous fuel. [8] Power generation system (1) according to any one of the preceding claims, wherein the at least two gas turbines (2, 2a, 2b) provide the same power, or provide a different power. [9] Power generation system (1) according to any one of the preceding claims, wherein the respective combustion unit (20, 20a, 20b) comprises at least one pressure adjusting element (24, 24a, 24b) arranged in a combustion unit supply line (21) and adapted to adjust a fuel parameter value of the fuel in the combustion unit supply line (21). [10] The power generation system (1) of claim 9, wherein the fuel parameter value of the fuel is a fuel pressure value, and wherein the at least one pressure adjusting element (24) is configured 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 the preceding claims, wherein the respective gas turbine (2, 2a, 2b) comprises a turbine unit (40) arranged downstream of the respective combustion unit (20, 20a, 20b) and fluidly connected thereto, and wherein the respective gas turbine (2, 2a, 2b) comprises a generator unit (50) operatively coupled to the turbine unit (40). [12] Method (800) for controlling a fuel supply system (10) for a power generation system (1) comprising a first gas turbine (2, 2a) and at least one second gas turbine (2, 2b), the method (800) comprising: a) querying and obtaining (810) at least one fuel parameter target value associated with fuel in a decoupling tank (300), comprising: 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), 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), Determining which of the first required fuel parameter value and the at least one second required fuel parameter value has the highest fuel parameter value, and Setting the fuel parameter target value such that it corresponds to at least the highest required fuel parameter value, b) determining (820) at least one operating parameter value of a fuel compressor (200) which is fluidly connected to the decoupling tank (300) on the basis of the at least one fuel parameter target value, and c) operating (830) the fuel compressor (200) based on the at least one operating parameter to provide fuel having the at least one fuel parameter target value in the decoupling tank (300). [13] The method (800) of claim 12, wherein the at least one fuel parameter target value is a fuel pressure target value in the decoupling tank (300), and wherein the at least one operating parameter value is a speed of the fuel compressor (200). [14] The method (800) of claim 12 or claim 13, wherein the power generation system (1) is a power generation system (1) according to any one of claims 1 to 11. [15] The method (800) of any one of claims 12 to 14, wherein the method is a computer-implemented method.

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