Device and method for starting and shutting down fuel supply for turbine plant

Abstract

For example, an apparatus may be arranged and configured such that a higher auto-ignition temperature fuel may be utilized to purge a fuel delivery system after a gas turbine is shut down due to detected conditions and facilitate faster restart of the turbine. Embodiments may utilize conduits, valves, and control systems to detect fault conditions to ensure shutdown, purge lower auto-ignition temperature fuel through exhaust, and purge using higher auto-ignition temperature fuel to facilitate subsequent restart of the turbine. Embodiments may be configured such that no inert gas purge is required to exhaust and purge the fuel delivery system.

Description

[0001] Cross-reference to related applications This application claims priority to U.S. Provisional Patent Application No. 63 / 530,757, filed August 4, 2023. Technical Field

[0002] The present invention relates to methods and apparatus for starting and stopping turbine operation (e.g., gas turbine operation). Background Technology

[0003] Gas turbines can burn fuel to produce work or power. Examples of different types of gas turbines and gas turbine arrangements can be understood from U.S. Patent Nos. 11,592,178 and 6,752,620, and U.S. Patent Application Publications Nos. 2022 / 0268444 and 2013 / 0127163. Summary of the Invention

[0004] We have determined that gas turbine arrangements may typically require large quantities of inert fluid (e.g., oxidizer-free gases such as nitrogen, argon, or dry carbon dioxide, which can react non-combustibly with the fuel) to purge turbine fuel and combustion system components in response to safety alarm conditions being triggered, thereby helping to prevent spontaneous combustion outside the turbine system's combustor. We have determined that this type of problem can be particularly severe in turbine arrangements using hydrogen as the primary fuel source (e.g., hydrogen fuel, refinery exhaust gas (ROG), which may contain 70 mol% to 90 mol% hydrogen and other heavy hydrocarbons). In some cases, the amount of inert fluid that may need to be stored under such safety conditions can be substantial and may delay the resolution of the safety conditions, potentially prolonging the turbine engine restart delay. We have determined that a new purging system arrangement can be provided that reduces these types of delays and also reduces the amount of inert fluid that may need to be stored to address such situations. In some embodiments, inert fluid storage can be reduced by 50% to 70%, and the delay in restarting the turbine engine can be reduced by 20 to 35 minutes (e.g., 30 minutes).

[0005] In a first aspect, an apparatus for starting and stopping a fuel supply to a turbine is provided. The apparatus for starting and stopping a fuel supply to a turbine may include a conduit arrangement having at least one low auto-ignition temperature fuel supply conduit capable of connecting to at least one low auto-ignition temperature fuel source and a high auto-ignition temperature fuel supply conduit capable of connecting to a high auto-ignition temperature fuel source. The conduit arrangement is connectable to a combustion system and is configured such that, in response to a detected trip condition, at least one valve assembly of at least one exhaust conduit of the conduit arrangement is adjustable to an open position for venting, while at least one valve assembly of at least one low auto-ignition temperature fuel supply conduit is in a closed position to isolate at least one low auto-ignition temperature fuel source, and at least one valve assembly of the high auto-ignition temperature fuel supply conduit is also in a closed position to vent the conduit arrangement, and at least one valve assembly of the high auto-ignition temperature fuel supply conduit is openable, while at least one valve assembly of at least one low auto-ignition temperature fuel supply conduit remains in a closed position to purge the conduit arrangement upstream of the combustion system and repressurize the conduit arrangement with high auto-ignition temperature fuel to facilitate the restart of the turbine.

[0006] The detected trip condition can be any of a variety of different conditions that meet the pre-selected trip condition criteria. This trip condition can be based on a temperature and / or pressure level exceeding a pre-selected operating temperature level and / or a pre-selected operating pressure level. Pre-defined trip conditions can also be detected based on other criteria such as oxygen concentration levels, fuel type, high vibration, or other mechanical failures. A pre-defined trip condition can also be a normal shutdown of the turbine equipment (e.g., initiating a normal shutdown operation of the turbine equipment via operator input).

[0007] In a second aspect, the conduit arrangement for the fuel supply equipment used to start and stop the turbine equipment may include other elements. For example, the conduit arrangement may include a mixer and / or a fuel cleaning device. The mixer may be located between the fuel cleaning device and at least one low auto-ignition temperature fuel supply conduit, and the mixer may also be located between the fuel cleaning device and a high auto-ignition temperature fuel supply conduit. The fuel cleaning device may include a coalescer, a particulate removal device, and / or a droplet removal device for cleaning gaseous fuel to make it suitable for combustion within the combustion system. In some embodiments, the conduit arrangement may include a fuel cleaning device supply conduit located between the mixer and the fuel cleaning device, and a combustion system supply conduit connecting the fuel cleaning device and the combustion system.

[0008] In a third aspect, the duct arrangement may also include a valve assembly for the combustion system supply duct, which is adjustable to a closed position in response to a detected trip condition. The valve assembly may also be adjustable from its closed position to an open position to facilitate fuel flow into the combustion system.

[0009] In a fourth aspect, the device for starting and stopping the fuel supply to the turbine equipment may include a distributed control system controller that is communicatively connected to different valve assemblies (e.g., valve assemblies of duct arrangements). For example, the distributed control system controller may be communicatively connected to valve assemblies of combustion system supply ducts, at least one valve assembly of at least one exhaust duct, at least one valve assembly of at least one low auto-ignition temperature fuel supply duct, and at least one valve assembly of a high auto-ignition temperature fuel supply duct. The distributed control system controller may also be communicatively connected to a controller or other type of computer device that can be configured to monitor turbine equipment operation or control the engine performance of the turbine equipment.

[0010] In a fifth aspect, the device for starting and stopping the fuel supply to the turbine equipment may include an inert fluid source connectable to the combustion system via at least one inert fluid connection conduit located between the combustion system and the inert fluid source. The inert fluid source may include a tank storing a cryogenic fluid (e.g., liquid nitrogen), which may be connected to a carburetor and a buffer tank for vaporizing the cryogenic fluid to supply inert gas to the combustion system via one or more inert fluid connection conduits. In other embodiments, the inert fluid source may include at least one storage tank positioned to hold a fluid consisting of nitrogen or other inert fluids that are not flammable with fuel (e.g., argon, dry carbon dioxide, etc.).

[0011] In a sixth aspect, there may be means for starting and stopping the fuel supply to the turbine equipment, such that at least one inert fluid connection conduit positioned to supply an inert fluid (e.g., an inert gas or a gas that reacts non-combustibly with the fuel) to the combustion system has at least one valve assembly. For example, at least one inert fluid connection conduit may be configured to supply a non-combustible gas (e.g., nitrogen, dry carbon dioxide gas, argon, etc.) to the combustion chamber of the combustion system.

[0012] In some embodiments, the combustion system may include, for example, a compression section, an exhaust section, a combustion chamber, and a rotatable shaft. In some embodiments, the combustion system may be configured to receive an oxidant supply for combustion within the combustion chamber of the combustion system. For example, the oxidant may be mixed with fuel in the combustion chamber for combustion of the fuel.

[0013] In a seventh aspect, at least one low auto-ignition temperature fuel source may include a hydrogen source and / or a refinery exhaust gas (ROG) source. At least one low auto-ignition temperature fuel supply conduit may include a hydrogen supply conduit capable of being connected to a hydrogen source and / or an ROG supply conduit capable of being connected to an ROG source. At least one valve assembly of at least one low auto-ignition temperature fuel supply conduit may include a valve assembly of the hydrogen supply conduit and / or a valve assembly of the ROG supply conduit.

[0014] In the eighth aspect, the apparatus for starting and stopping the fuel supply to a turbine device according to the first aspect may include one or more features described in the second, third, fourth, fifth, sixth, and / or seventh aspects to form other embodiments. Therefore, it should be understood that other embodiments of the apparatus for starting and stopping the fuel supply to a turbine device may include other features, including those discussed in the exemplary embodiments of the turbine device discussed herein.

[0015] In a ninth aspect, a method for starting and stopping a fuel supply to a turbine unit may include one or more method steps. For example, the method may include cutting off the flow of at least one low auto-ignition temperature fuel to the combustion system of the turbine unit in response to a trip condition detected during operation of the turbine unit. The method may also include venting the fuel delivery system of the combustion system to depressurize the fuel delivery system, supplying high auto-ignition temperature fuel to the fuel delivery system to purge the fuel delivery system, and subsequently repressurizing the fuel delivery system to a preselected pressure, while at least one low auto-ignition temperature fuel is positively isolated from the fuel delivery system, so that when high auto-ignition temperature fuel is supplied to the fuel delivery system to purge the fuel delivery system and subsequently repressurized to the preselected pressure, no low auto-ignition temperature fuel can be supplied to the combustion system through the fuel delivery system. The method may also include supplying high auto-ignition temperature fuel to the combustion system to facilitate the start-up (or restart) operation of the turbine unit.

[0016] As described above, the detectable trip condition can be any of a variety of different conditions that meet the pre-selected trip condition criteria. This trip condition can be based on a temperature and / or pressure level exceeding a pre-selected operating temperature level and / or a pre-selected operating pressure level. Pre-defined trip conditions can also be detected based on other criteria such as oxygen concentration levels, fuel type, high vibration, or other mechanical failures. A pre-defined trip condition can also be a normal shutdown of the turbine equipment (e.g., initiating a normal shutdown operation of the turbine equipment via operator input).

[0017] In a tenth aspect, the method may further include, after the turbine equipment has been started (or restarted), supplying at least one low auto-ignition temperature fuel to the combustion system after a preselected set of criteria has been met. In the eleventh aspect, supplying high auto-ignition temperature fuel to the combustion system to facilitate the start-up of the turbine equipment may include adjusting the position of the valve assembly of the combustion system supply duct from a closed position to an open position.

[0018] In the twelfth aspect, supplying high auto-ignition temperature fuel to a fuel delivery system to purge the fuel delivery system, and subsequently repressurizing the fuel delivery system to a preselected pressure, while at least one low auto-ignition temperature fuel is absolutely isolated from the fuel delivery system, so that when high auto-ignition temperature fuel is supplied to the fuel delivery system to purge the fuel delivery system and subsequently repressurize the fuel delivery system to the preselected pressure, no low auto-ignition temperature fuel can be supplied to the combustion system through the fuel delivery system. This may include adjusting a valve assembly of a high auto-ignition temperature fuel supply conduit from a closed position to an open position, while at least one valve assembly of at least one low auto-ignition temperature fuel supply conduit is in a closed and isolated position, and at least one valve assembly of at least one exhaust conduit of the fuel delivery system conduit arrangement is in an open position for venting the fuel delivery system upstream of the combustion system, and subsequently closing at least one valve assembly of at least one exhaust conduit to repressurize the fuel delivery system upstream of the combustion system with high auto-ignition temperature fuel.

[0019] In the thirteenth aspect, the high auto-ignition temperature fuel may be natural gas, and at least one low auto-ignition temperature fuel may include hydrogen.

[0020] In the fourteenth aspect, the flow of at least one low auto-ignition temperature fuel can be provided by the conduit arrangement of the fuel delivery system.

[0021] In the fifteenth aspect, cutting off the flow of at least one low auto-ignition temperature fuel to the combustion system of the turbine equipment may include (i) adjusting the position of a valve assembly of the combustion system supply conduit of the fuel delivery system from an open position to a closed position and / or (ii) adjusting the position of at least one valve assembly of at least one low auto-ignition temperature fuel supply conduit from an open position to a closed and isolated position.

[0022] In a sixteenth aspect, the method may further include supplying inert gas to the combustion system to purge the combustion system after cutting off the flow of at least one low auto-ignition temperature fuel to the combustion system of the turbine equipment. In some embodiments, cutting off the flow of at least one low auto-ignition temperature fuel to the combustion system of the turbine equipment may include adjusting the position of a valve assembly of a combustion system supply conduit of the fuel delivery system from an open position to a closed position, and adjusting the position of at least one valve assembly of at least one low auto-ignition temperature fuel supply conduit from an open position to a closed and isolated position. In some embodiments, at least one valve assembly of at least one low auto-ignition temperature fuel supply conduit may include a valve assembly of a hydrogen supply conduit and / or a valve assembly of a refinery exhaust gas supply conduit.

[0023] In the seventeenth aspect, embodiments of devices for starting and stopping the fuel supply to a turbine device may be provided and configured to perform embodiments of methods for starting and stopping the fuel supply to a turbine device.

[0024] In the eighteenth aspect, embodiments of the method according to the ninth aspect may include one or more features described in the tenth, eleventh, twelfth, thirteenth, fourteenth, fifteenth, sixteenth, and / or seventeenth aspects. Therefore, it should be understood that embodiments of the method may also include other features or method steps. Examples of such other features or method steps include those of the exemplary embodiments discussed herein.

[0025] It should be understood that embodiments of the method and apparatus can utilize a variety of conduit arrangements and process control elements. Embodiments may utilize sensors (e.g., pressure sensors, temperature sensors, flow rate sensors, composition sensors, etc.), controllers, valves, piping, and other process control elements. For example, some embodiments may utilize automated process control systems and / or distributed control systems (DCS). A variety of different conduit arrangements and process control systems can be used to meet a specific set of design criteria.

[0026] Further details, objectives, and advantages of the apparatus for starting and stopping the fuel supply to a turbine system, the method apparatus for starting and stopping the fuel supply to a turbine system, and the methods for manufacturing and using such apparatus will become apparent as some exemplary embodiments of the invention are described below. Attached Figure Description

[0027] The accompanying drawings illustrate exemplary embodiments of the present invention, including methods for starting and stopping the fuel supply to a turbine, apparatus for starting and stopping the fuel supply to a turbine, systems for starting or stopping the fuel supply to a gas turbine, and methods for manufacturing and using these apparatuses and systems. It should be understood that the same reference numerals used in the drawings may identify the same parts.

[0028] Figure 1 This is a block diagram of a first exemplary embodiment of a gas turbine device 1, which may include an exemplary embodiment of a system for starting and stopping the fuel supply to the turbine device, the system utilizing an exemplary embodiment of a method for starting and stopping the fuel supply to the turbine device.

[0029] Figure 2 This is a block diagram of a first exemplary embodiment of a system for starting and stopping the fuel supply to a turbine device, which may be included in the first exemplary embodiment of a gas turbine device 1. Embodiments of this system may utilize exemplary embodiments of methods for starting and stopping the fuel supply to a turbine device.

[0030] Figure 3 This is a block diagram of an exemplary embodiment of a distributed control system controller (DCS), which may include... Figure 2 In the first exemplary embodiment of the system shown.

[0031] Figure 4 This is a flowchart illustrating a first exemplary embodiment of a method for starting and stopping the fuel supply to a turbine device. Detailed Implementation

[0032] refer to Figures 1 to 3 The device 1a for starting and stopping the fuel supply to the turbine 1 may include a fuel delivery system 2 configured to supply fuel to a combustion system 4 (e.g., a turbine combustion system). The combustion system 4 may be connected to at least one oxidant source (e.g., air, oxygen, a combination thereof) for burning at least one type of fuel received from the fuel delivery system 2. The combustion of the fuel may be configured to drive the shaft when the combustion gases formed by the fuel combustion are output as at least one exhaust stream 10ex, which may be supplied to an exhaust system 6 connected to the combustion system 4 for discharge into the atmosphere.

[0033] The fuel delivery system 2 may include a plurality of fuel sources 2a, which may be connected to the combustion system 4 for combustion in at least one combustion chamber of the combustion system 4. Furthermore, in some embodiments, the exhaust system 6 may be omitted, and at least one exhaust stream 10ex may be discharged from the combustion system 4 to the atmosphere.

[0034] The device 1a for starting and stopping the fuel supply to the turbine equipment 1 may include a fuel delivery system 2 and a duct arrangement 10 of the system. The device may also include at least one source of inert fluid (such as an inert gas, for example, nitrogen). The inert gas in the device for starting and stopping the fuel supply to the turbine equipment may be configured to help mitigate or prevent combustion by undergoing a non-combustible reaction with the fuel (e.g., without an oxidizer). Examples of inert gases may include dry carbon dioxide, argon, or nitrogen and / or combinations thereof.

[0035] An inert gas source 2b may be connected to the combustion system 4, allowing at least one stream of inert gas to be supplied to the combustion system 4 to purge the fuel system, thereby preventing and / or mitigating fuel combustion until the combustion process within the combustion chamber of the combustion system 4 can be stopped. In some embodiments, the inert gas source 2b may include a storage tank configured to store compressed cryogenic liquid (e.g., liquid nitrogen) and an inert gas storage tank or inert gas buffer tank, which may be positioned to store inert gas formed by the vaporization of the stored liquid for supply to the combustion system 4. Vaporization of the inert liquid may be provided by an ambient air vaporizer or other type of vaporizer, which may be located between the cryogenic liquid storage tank and the inert gas storage tank or inert gas buffer tank. In other embodiments, it is conceivable that the inert gas source 2b may consist only of an inert gas storage tank.

[0036] Inert gas source 2b can be used to help address safety issues that may be detected during the operation of turbine equipment 1. For example, the temperature, pressure, and / or oxygen level within combustion system 4 can be detected to meet predefined safety thresholds, indicating that the combustion process may pose a safety problem or cause undesirable combustion outside the combustion chamber of combustion system 4. In response to such detection, fuel supply to combustion system 4 can be stopped, oxidant supply to combustion system 4 can be stopped, and combustion system 4 can be purged (e.g., through exhaust system 6 and / or at least one other openable valve that can be opened for purging and closed when purging is not required) to facilitate purging of combustion system 4. The gas in fuel delivery system 2 can also be purged by purging the gas in the system through at least one exhaust duct (Vent) of fuel delivery system 2.

[0037] Fuel delivery system 2 may include a distributed control system controller (DCS). The DCS may be a computer device 20 communicatively connected to the valves V and sensors S of fuel delivery system 2 and / or duct arrangement 10 to monitor the operation of the fuel delivery system and detect a trip of at least one pre-selected safety threshold, thereby initiating a purging operation. The DCS may also be configured to communicate with the controller of turbine unit 1, which can monitor turbine engine operation and / or performance to facilitate the restart of turbine unit 1 after a detected safety condition has been determined to have been resolved by purging. This actuation of valve regulation of valve assembly V for purging and restart can be facilitated through communicative connections CC between the DCS and various valves of duct arrangement 10, as well as the controller and other components that can monitor turbine engine operation of turbine unit 1.

[0038] If passed Figure 2 Ideally, the multiple fuel sources 2a can include natural gas (NG), hydrogen (H2), and refinery exhaust gas (ROG). Natural gas can be considered a high auto-ignition temperature fuel, while hydrogen and refinery exhaust gas (ROG) can be considered different types of low auto-ignition temperature fuels. All of these fuels can be gaseous fuels.

[0039] Refinery exhaust gas (ROG) may include a gas containing between 60 mol% and 90 mol% hydrogen and a substantial amount of residual heavy hydrocarbons (such as propane, butane, pentane, hexane, etc.). In some embodiments, for example, hydrogen may constitute between 60 mol% and 80 mol% of the refinery exhaust gas, and propane may constitute between 5 mol% and 13 mol%. Hydrogen (H2) may be at least 95 mol% hydrogen (e.g., between 95 mol% and 100 mol% hydrogen, between 99 mol% and 100 mol% hydrogen, etc.). Natural gas (NG) may include methane gas and is primarily composed of methane (e.g., between 95 mol% and 100 mol% methane, between 80 mol% and 100 mol% methane, etc.).

[0040] Fuel delivery system 2 can be connected to natural gas source 3. Natural gas source 3 can be a pipeline through which natural gas can pass and / or at least one storage container (e.g., tank, storage unit, etc.) for storing natural gas.

[0041] Fuel delivery system 2 can be connected to refinery exhaust gas (ROG) source 5. Refinery exhaust gas (ROG) source 5 can be a pipeline through which refinery exhaust gas (ROG) can pass and / or at least one storage container (e.g., tank, storage unit, etc.) for storing refinery exhaust gas (ROG).

[0042] The fuel delivery system 2 can also be connected to a hydrogen (H2) source 7. The hydrogen source 7 can be a pipeline through which hydrogen can pass and / or at least one storage container (e.g., tank, storage unit, etc.) for storing hydrogen.

[0043] The fuel delivery system 2 may include a conduit arrangement 10, which may include multiple conduits connected to each other and multiple valve assemblies V. Each valve assembly V may include a single valve or at least two valves (e.g., a pressure valve adjacent to an absolute isolation valve). Each valve assembly V for the low-auto-ignition fuel supply conduits of the conduit arrangement 10 may include at least one valve that allows for pressure regulation within the fuel delivery system (e.g., including a pressure valve or pressure relief valve) and also allows low-auto-ignition fuel sources (e.g., ROG source 5 and hydrogen source 7) to be absolutely isolated from the rest of the fuel delivery system 2 in response to a detected safety condition trip, to prevent fuel combustion outside the combustion chamber of the combustion system 4 (e.g., fuel auto-ignition outside the combustion chamber).

[0044] The conduit arrangement 10 may also include multiple sensors positioned to detect temperature, pressure, and / or flow rate at different flow rates through the conduit arrangement 10 or other units of the fuel delivery system 2. Valve assemblies V, sensors, and other components may be communicatively connected to a distributed control system controller (DCS). The controller may be configured to receive data from the sensors, communicate with valve assemblies V to adjust valve positions between open and closed positions, and also communicate with at least one operator device via a communication connection CC of these components through the DCS. The DCS can assist in monitoring operation and provide automated process control supervision for the operation of the fuel delivery system 2 and / or the equipment 1a used for starting and stopping the fuel supply to the turbine unit 1.

[0045] The fuel delivery system 2 may also include other components. These components may include a mixer 9 configured to mix one or more fuels, and a fuel cleaning device 11 (FCD). The fuel cleaning device 11 (FCD) may include a filtration mechanism that may include a coalescer and other filtration devices configured to remove particles and droplets from the fuel, such that the fuel output from, for example, the fuel from the fuel cleaning device 11 is a gaseous purge fuel suitable for combustion in the combustion chamber of the combustion system 4. In some embodiments, the mixer 9 and the fuel cleaning device 11 may be considered as components of the duct arrangement 10 of the fuel delivery system 2.

[0046] The conduit arrangement 10 may include a natural gas supply conduit 10a, which may be connected to a hydrogen fuel supply conduit 10c and / or a mixer supply conduit 10d. The hydrogen fuel supply conduit 10c may be connected to at least one hydrogen-containing fuel source. The hydrogen-containing fuel may include a hydrogen source 7 and / or a refinery exhaust gas (ROG) source 5. In some embodiments, there may be only a single hydrogen fuel source (e.g., only hydrogen source 7 or refinery exhaust gas source 5). In other embodiments, the fuel delivery system may include connections to both hydrogen source 7 and refinery exhaust gas (ROG) source 5.

[0047] For example, hydrogen supply conduit 10c may include a conduit connecting mixer 9 and hydrogen source 7 for supplying hydrogen to mixer 9. Hydrogen supply conduit 10c may also be connected to refinery exhaust gas supply conduit 10b, which connects refinery exhaust gas source (ROG) 5 and mixer 9. Each of refinery exhaust gas supply conduit 10b, hydrogen supply conduit 10c, and natural gas supply conduit 10a may include a valve assembly V, such that only one of these fuels can be supplied to mixer 9, only two of these fuels can be supplied to mixer 9 simultaneously, or (when all three fuel sources are present) all three fuels can be supplied to the mixer simultaneously. Valve assembly V may be adjustable, allowing only a single fuel to be supplied to mixer 9, or allowing combinations of fuels to be supplied to mixer 9 at different times based on different operating conditions.

[0048] Natural gas supply conduit 10a can be considered as a high auto-ignition temperature fuel supply conduit capable of connecting to a high auto-ignition temperature fuel source. Hydrogen supply conduit 10c and refinery exhaust gas supply conduit 10b can be considered as low auto-ignition temperature fuel supply conduits capable of connecting to different low auto-ignition temperature fuel sources.

[0049] In some embodiments, the mixer supply conduit 10d may be connected to the hydrogen supply conduit 10c, the refinery exhaust gas supply conduit 10b, and the natural gas supply conduit 10a, so that these fuels can be supplied to the mixer 9 for mixing therein. The mixer 9 may be an in-line mixer, a mixing device, a mixing vessel, or other type of mixer. The mixer 9 may be configured to facilitate fuel mixing. For example, the fuel supplied to the mixer 9 may be gaseous to facilitate mixing by the mixer 9. The mixer 9 may output mixed fuel or single fuel for downstream supply to the fuel cleaning device 11. For example, the fuel cleaning device supply conduit 10e may be connected between the mixer 9 and the fuel cleaning device 11 for supplying fuel from the mixer 9 to the fuel cleaning device 11. The fuel cleaning device 11 may remove particulates and liquids from the fuel, so that the fuel can be output from the fuel cleaning device 11 under adequately purged conditions for combustion in the combustion chamber of the combustion system 4. The fuel cleaning device 11 can be connected to the combustion system 4 via a combustion system supply conduit 10h connecting the fuel cleaning device 11 and the combustion system 4, such that fuel output from the fuel cleaning device 11 can be supplied to the combustion system 4, for example. The combustion system supply conduit 10h may include a valve assembly V that is adjustable between an open position and a closed position to control how much fuel is supplied to the combustion system, and also to allow the supply of fuel to the combustion system 4 to be stopped (e.g., by closing at least one valve of the valve assembly V of the combustion system supply conduit 10h).

[0050] The mixer exhaust duct 10f can be connected to the mixer 9 and / or the fuel cleaning device supply duct 10e to facilitate exhaust from at least the mixer 9 when mixing is required. Additionally (or alternatively), the fuel cleaning device 11 can be connected to the exhaust duct 10g for exhaust from the mixer 9 and / or the fuel cleaning device 11. This exhaust can also be used to exhaust from the ducts of the duct arrangement 10 upstream of the combustion system supply duct valve assembly.

[0051] Combustion system 4 can be connected to an oxidant source to receive at least one stream of oxidant. The oxidant may include, for example, air, and can be supplied to the combustion chamber of combustion system 4 via, for example, a compressor or fan in fluid communication with the intake duct of combustion system 4. The oxidant can be supplied to the combustion chamber to promote fuel combustion in the presence of oxygen and the oxidant.

[0052] The fuel delivery system 2 may also include at least one inert fluid source 2b, which may include, for example, at least one inert gas source 8. The inert gas may be, for example, a gas formed by the vaporization of stored liquid nitrogen, stored liquid argon, or dry carbon dioxide. As described above, the inert gas may be inert (e.g., nitrogen or argon) or a gas that undergoes a non-combustible reaction with the fuel (e.g., excluding oxygen). The inert fluid source is connected to the combustion system 4 via at least one inert fluid connection conduit 10i of the conduit arrangement 10. Each inert fluid connection conduit 10i may include at least one valve assembly V adjustable between an open position and a closed position, such that when the valve assembly V is in the open position, inert fluid may be supplied to the combustion system 4, and when the valve assembly V is in its closed position, no inert fluid is supplied to the combustion system 4.

[0053] An inert fluid may be supplied as an inert gas to at least the combustion chamber of the combustion system or at least the upstream portion of the combustion system 4, which is located downstream of the valve assembly V of the combustion system supply conduit 10h. In some embodiments, only a single inert fluid may be supplied to the combustion system 4 for injection at a location downstream of the valve assembly V of the combustion system supply conduit 10h and upstream of and / or at the combustion chamber of the combustion system 4. In other embodiments, two or more inert fluids (e.g., inert gases such as nitrogen) may be supplied to the combustion system 4 via an inert fluid connection conduit 10i, such that a first inert gas flow may be supplied to the combustion system 4 for injection of inert fluid at a location downstream of the valve assembly V of the combustion system supply conduit 10h and upstream of the combustion chamber of the combustion system 4, and a second inert gas flow may be supplied to the combustion chamber of the combustion system 4. The combustion system 4 may also be connected to at least one purge conduit 10j to facilitate exhaust and / or purging of the combustion system 4. Alternatively, it is conceivable that the exhaust from the combustion system 4 can be provided solely through a duct for at least one exhaust stream 10ex, which can be output from the turbine combustion chamber of the combustion system 4. In embodiments including at least one purge duct 10j, each purge duct 10j may include a valve assembly V capable of being adjusted between an open position for exhaust and / or purge and a closed position for closing the combustion chamber, thereby outputting one or more exhaust streams 10ex to be discharged directly into the atmosphere through at least one exhaust duct and / or through the exhaust system 6.

[0054] like Figure 3As best shown, the distributed control system controller (DCS) can be a computer device 20, which may include a processor (Proc.) communicatively connected to at least one transceiver (Trcvr) and at least one non-transitory computer-readable medium (Mem), which may be a solid-state drive, flash drive, hard disk drive, or other type of non-transitory memory. The transceiver may include one or more communication interfaces, such as at least one network transceiver, at least one near-field communication transceiver, and / or at least one wireless transceiver. The transceiver (Trcvr) may be configured to facilitate communication connections between the computer device 20 and other computer devices 10, input devices (ID), output devices (OD), fuel delivery system 2 and / or valves (V) of device 1a for starting and stopping the fuel supply to the turbine equipment and / or sensors (S) of device 1a for starting and stopping the fuel supply to the turbine equipment and / or fuel delivery system 2. The non-transitory computer-readable medium (Mem) may have one or more applications (Apps) and one or more data storage (DS) stored thereon, such as files, databases, or other types of data storage. The application's code can be executed by a processor (Proc.) to cause the computer device 20 to perform various actions and / or processes. The execution of the application's code can also result in the use of one or more data stores (DS) during the operation of the application (App).

[0055] One or more input devices (IDs) may include a keyboard, keypad, pointer device, touchscreen, microphone, or other types of input devices that can be communicatively connected to the processor or computer device 20. One or more output devices (ODs) may include speakers, displays, printers, or other types of output devices that can be communicatively connected to the processor or computer device 20. Other computer devices 20 may be communicatively connected to computer devices 20 via network connections (e.g., local area network connections, wide area network connections, cellular network connections, Internet connections, etc.). Communication connections between computer devices 20 (e.g., between a distributed control system controller (DCS) and operator devices (e.g., laptop computers, desktop computers, etc.) and / or turbine engine controllers) may involve intermediate devices, such as boundary control devices, access points, or other types of intermediate nodes between communicatively connected computer devices 20.

[0056] from Figure 2 and Figure 4Exemplary embodiments of methods for operating and controlling fuel delivery system 2 and / or methods for starting and stopping fuel supply to turbine equipment, as well as exemplary embodiments of methods for restarting fuel supply to turbine equipment operation, can be best understood in the present invention. For example, in one method embodiment, first step S1 may include detecting a trip condition when the turbine is burning fuel with a low auto-ignition temperature (e.g., refinery exhaust gas or hydrogen). The detected trip condition may be due to a safety issue identified based on sensor data, indicating that a preselected set of or more criteria for shutting down turbine equipment 1 has been met. The detected trip condition may also be a normal shutdown condition, which may be based on a preselected set of criteria and / or operator input to shut down the operation of turbine equipment 1. The detected trip condition may also be other conditions based on a preselected set of criteria. Examples of other trip conditions may include, for example, vibration exceeding a preselected threshold.

[0057] In the second step S2, the flow of low auto-ignition temperature fuel can be stopped, preventing fuel from being supplied from the fuel source to the combustion system 4. Stopping this fuel flow can include adjusting valve V6 of the combustion system supply conduit 10h to the closed position to stop fuel flow to the combustion system 4, and can also include adjusting valve assembly V2 of the refinery exhaust gas supply conduit 10b and / or valve assembly V3 of the hydrogen supply conduit 10c from their open positions to the closed positions to prevent low auto-ignition temperature fuel from flowing out of the fuel source and to completely isolate the fuel from the combustion system 4. If the fuel supplied to the combustion system also includes natural gas, valve assembly V1 of the natural gas supply conduit 10a can also be closed to cut off fuel flow. If natural gas fuel has not yet been supplied to the combustion system, valve assembly V1 may already be in the closed position and will therefore remain closed.

[0058] In response to a detected trip condition, the supply of oxidizer to combustion system 4 can also be stopped. For example, in response to a detected trip condition, a fan or compressor that can operate to facilitate the inflow of air or other oxidizer into the combustion chamber of the combustion system can be stopped to cease the supply of oxidizer to combustion system 4. In some configurations, combustion system 4 may include a compressor section that may be directly connected to an exhaust section to facilitate the supply of oxidizer to the combustion chamber of combustion system 4. A distributed control system controller (DCS) may be configured to communicate with the controller of turbine device 1, which may monitor the operation of combustion system 4 to facilitate termination of operation in response to, for example, a detected trip condition. In some embodiments, termination may be provided in conjunction with communication received from the controller of turbine device 1 or the motor in turbine device 1, such communication providing, for example, data indicating termination of operation of turbine device 1. For example, in some embodiments, termination of operation of turbine device 1 may result in a rolling stop of turbine device 1 or a cessation of rotation of its shaft.

[0059] In this second step S2, the fuel delivery system can also be vented to remove fuel from the duct arrangement 10 and other components (e.g., mixer 9, fuel cleaning device 11, etc.) that may be located upstream of the valve assembly V6 of the combustion system supply duct 10h. Venting can be achieved by depressurizing the duct arrangement 10, mixer 9, and / or fuel cleaning device 11 upstream of the valve assembly V6 of the combustion system supply duct 10h after the valve assembly is closed. This venting can be facilitated by adjusting the valve assembly V4 of the mixer vent 10f from its closed position to its open position and / or adjusting the valve assembly V5 of the fuel cleaning device vent 10g from its closed position to its open position. This venting can be an exhaust port leading to a flare, allowing the discharged fuel to be burned through the flare for release into the atmosphere. Fuel in the duct arrangement 10 upstream of the closed valve assembly V6 of the combustion system supply duct 10h can be discharged into the atmosphere through this exhaust, which can also reduce the pressure on the duct arrangement 10 and other components upstream of the closed valve assembly V6 of the combustion system supply duct 10h (such as the mixer 9 and the fuel cleaning device 11).

[0060] When the fuel delivery system 2 depressurizes and vents in response to a detected trip condition, the combustion system 4 can also vent through its exhaust stream 10ex exposed to the atmosphere. This venting can also be accelerated by adjusting the valve assembly V8 of at least one purge duct 10j, which helps to speed up the depressurization process of the combustion system 4. When the valve assembly V8 and the purge duct 10j are used, fuel venting can be provided, allowing fluid to be discharged into the flare to promote venting.

[0061] The venting and depressurization of the fuel delivery system 2 and combustion system 4 can help remove unburned fuel from the turbine unit 1 (e.g., unburned fuel within the turbine unit 1) to facilitate safe shutdown of the turbine unit 1 and / or avoid detected unsafe conditions that could lead to tripping. Removal of unburned fuel can help ensure safety by helping to avoid potential spontaneous combustion events, thus preventing such a hazard. This can also promote a reduction in temperature and pressure, further mitigating the problem. In some embodiments, venting and / or depressurization can occur within a pre-selected venting time period to provide sufficient venting to address detected conditions or otherwise help ensure safety.

[0062] After exhausting for at least a pre-selected exhaust period, at least one purge duct 10j's valve assembly V8 can be moved back to its closed position (e.g., via communication between the distributed control system controller (DCS) and the valve assembly). Furthermore, the mixer exhaust duct 10f's valve assembly V4 can be adjusted from its open position to its closed position, and / or the fuel cleaning device exhaust duct 10g's valve assembly V5 can be adjusted from its open position to its closed position to terminate the exhaust and depressurization operations and allow the fuel delivery system 2 and combustion system 4 to be repressurized so as to restart the operation of the turbine unit 1 through combustion of fuel within the combustion system 4.

[0063] Before or after the valve assembly V8 of at least one purge duct 10j returns to its closed position, inert gas from the inert gas source 8 (Inert) can be supplied to the combustion system 4 to purge the system and help ensure that fuel present therein during a detected trip condition is removed, thereby facilitating an efficient and safe restart of the combustion system 4. Inert gas can be supplied to the combustion system 4 by adjusting the valve assembly V7 of the inert fluid connection duct 10i, thereby adjusting the valve assembly V7s from its closed position to its open position, allowing inert gas to flow into the combustion system 4 from the inert gas source 8 through the inert fluid connection duct 10i to remove any residual fuel that may be present in the combustion system 4. The inert purge gas can be output through at least one exhaust duct connected to the combustion chamber of the combustion system 4.

[0064] The inert gas used for purging can be positioned and arranged so that it is supplied only to the combustion system 4, and not to the upstream fuel delivery system 2. This helps limit the amount of inert gas required to perform the purging. In some embodiments, the type of configuration and the inert fluid storage capacity used in this safe operating condition are reduced by 50% to 70%. For example, in some embodiments, only 5 kg to 7 kg of inert fluid may need to be stored to provide sufficient purging, instead of the 25 kg of inert fluid required if the inert gas is also used to purge the upstream fuel delivery system components. The total reduction in the required inert gas mass can vary depending on the size of the turbine unit 1 and other operating requirements. This non-limiting example of the reduction in inert gas storage is provided herein to help illustrate the substantial storage reduction that some embodiments of the apparatus 1a and method of the present invention for starting and stopping the fuel supply to the turbine unit 1 and the fuel delivery system 2 can provide.

[0065] Instead of using inert gas to purge fuel delivery system 2, fuel with a higher auto-ignition temperature can be used to purge and repressurize fuel delivery system 2 upstream of combustion system 4. This can occur while valve assembly V6 of combustion system supply conduit 10h is still in its closed position and / or while inert gas from inert gas source 8 is supplied to combustion system 4 for purging.

[0066] For example, the auto-ignition temperature of hydrogen is approximately 800°F (426.7°C). The auto-ignition temperature of refinery exhaust gas (ROG) may also be lower, approximately 800°F to 850°F (426.7°C to 454.4°C), depending on the fuel mixture in the gas. A low auto-ignition temperature can be equal to or significantly lower than 500°C, and in some embodiments may include an auto-ignition temperature in the range of 400°C to 450°C. In contrast, a high auto-ignition temperature can be significantly higher than a low auto-ignition temperature, and can be at least about 1000°F (537.7°C), in the range of 530°C to 600°C, or greater than 535°C. For example, natural gas from natural gas source 3 is an example of a fuel with a high auto-ignition temperature compared to hydrogen or refinery exhaust gas.

[0067] Therefore, in the third step S3, the fuel delivery system 2 can be purged, and the pressure of the fuel delivery system 2 can then be increased to a preselected operating pressure (e.g., a pressure of 40 bar (4 MPa), a pressure in the range of 35 to 45 bar (3.5 MPa to 4.5 MPa), or other suitable operating pressure range) to repressurize the conduit arrangement 10 upstream of the closed valve assembly V6 of the natural gas supply conduit 9, fuel cleaning device 11, and combustion system supply conduit 10h by supplying natural gas from the natural gas source 3 to the mixer 9, fuel cleaning device 11, and combustion system supply conduit 10h. This supply of natural gas can be provided by adjusting the valve assembly V1 of the natural gas supply conduit 10a from the closed position to the open position when the valve assembly V2 of the refinery exhaust gas supply conduit 10b and the valve assembly V3 of the hydrogen fuel supply conduit 10c are in their closed, isolated positions. Of course, in embodiments that may only have a hydrogen source 7 or a refinery exhaust gas source 5, only one of these valve assemblies can remain in its closed position when the valve assembly of the natural gas supply conduit 10a is open for purging with fuel at a higher auto-ignition temperature.

[0068] After the valve assembly V1 of the natural gas supply conduit 10a is opened, natural gas from the natural gas source can be supplied to the fuel delivery system 2 to help purge the conduit arrangement 10 upstream of the closed valve V6 of the combustion system supply conduit 10h. During the initial purging provided at least by the natural gas supply, one or more conduit arrangement exhaust conduits can be opened by keeping the valve assembly V4 of the mixer exhaust conduit 10f and / or the valve assembly V5 of the exhaust conduit 10g open for at least a portion of the time the natural gas purging is provided, so that the natural gas purging can help discharge low auto-ignition temperature fuel from the conduit arrangement 10 upstream of the valve assembly V6 of the combustion system supply conduit 10h, the mixer 9, and / or the fuel cleaning device 11.

[0069] To repressurize conduit arrangement 10, one or more exhaust conduit valve assemblies V4 and / or V5 can be closed, allowing natural gas supplied to conduit arrangement 10 via natural gas source 3 to repressurize the conduit arrangement to a preselected operating pressure (e.g., pressures in the range of 2 MPa and 5 MPa or other suitable operating pressure range). It should be understood that this type of higher auto-ignition temperature fuel supply can be performed in the third step S3 for purging and repressurization, after the detected trip conditions have been adequately resolved through exhaust.

[0070] Using natural gas or other fuels with higher auto-ignition temperatures for purging in the fuel delivery system 2 can facilitate faster restart operations of the turbine unit 1. For example, we have found that some embodiments can restart turbine operations at least 20-30 minutes faster (e.g., reducing restart operation time by 30% to 70%) by avoiding slower inert gas purging and allowing fuel to repressurize the duct arrangement 10 more quickly, while also allowing fuel to be more readily available for supply to the combustion system 4 to restart the turbine unit (e.g., eliminating the need to remove inert gas purging from the duct arrangement 10 and avoiding further delays associated with inert gas removal). Furthermore, in cases where restarting the turbine unit 1 results in an incorrect start-up type problem, a secondary purging of the inert gas may not be necessary because higher auto-ignition temperature fuels are available and can be used for restart operations, and can provide an improved safety margin to help avoid such problems due to their higher auto-ignition temperatures. We have determined that the improved safety factor that can be provided by using higher auto-ignition temperature fuel with a higher auto-ignition temperature at startup or restart of turbine unit 1 can help avoid this inert gas purging requirement, for example, due to the increased safety factor tolerance that can be provided by a higher auto-ignition temperature at startup (or restart).

[0071] In the fourth step S4, after sufficient exhaust and purging have resolved the detected safety conditions that triggered the trip condition, the turbine equipment can be started (or restarted). To facilitate this restart, the valve assembly V6 of the combustion system supply duct 10h can be adjusted from its closed position to the open position, allowing natural gas supplied through the duct arrangement 10 via the natural gas source 3 to be supplied to the combustion chamber of the combustion system 4 for combustion. The oxidant flow supplied to the combustion system can also be restarted (e.g., by restarting the turbine equipment 1, allowing airflow through the compression section of the combustion system 4 to the turbine equipment, etc.). Combustion of fuel (e.g., natural gas) can then be initiated to restore the operation of the turbine equipment 1. After sufficient time and / or after meeting other criteria indicating that the combustion system 4 can resume combustion of fuels with low auto-ignition temperatures, the valve assembly V2 of the refinery exhaust gas supply duct 10b can be adjusted from its closed and isolated position to the open position, and / or the valve assembly V3 of the hydrogen supply duct 10c can be adjusted from its closed and isolated position to the open position to supply the fuel (e.g., hydrogen and / or refinery exhaust gas) to the combustion system 4. In this case, the valve assembly V1 of the natural gas supply conduit 10a can be closed or otherwise regulated to facilitate the supply of the required fuel mixture to the combustion system 4 for combustion of fuel for turbine operation.

[0072] Then, turbine unit 1 can resume operation by burning fuel with a low auto-ignition temperature until another trip condition is detected, such as... Figure 4 As shown by the dashed arrow in the diagram. Then, the process for detecting trip conditions and the corresponding actions taken to resolve detected trip conditions can be restarted and re-executed to resolve newly detected conditions.

[0073] It should be understood that detectable trip conditions may be based on the temperature, pressure, and / or oxygen concentration or oxygen availability within the combustion chamber of the turbine equipment or combustion system 4. In addition to one or more of these factors, trip conditions may also be based on other criteria, or as alternatives.

[0074] It should also be understood that, in some embodiments, different valve assemblies V can be actuated via a communication connection CC between the valves of the valve assembly and the distributed control system controller (DCS) to adjust their positions between closed and open positions in steps S1 to S4 of the method. The distributed control system controller (DCS) can be configured to provide communication for initiating such adjustment based on data received from one or more sensors S or other elements, according to a predefined automatic control process defined, for example, in the code of an application program (App) in the memory (Mem) of the distributed control system (DCS). The distributed control system controller (DCS) can also provide such communication in response to input provided by an operator device 20 or according to a predefined automatic control process, which can also be communicatively connected to the distributed control system controller (DCS). The operator device 20 can be a computer device used by an operator to assist in monitoring and / or controlling the operation of the turbine equipment 1 or fuel generation processes that can be performed upstream of the fuel delivery system 2.

[0075] As described above, the turbine unit 1 and the fuel supply device 1a for starting and stopping the turbine unit can be configured to operate at a preselected operating pressure. This preselected operating pressure can be a suitable pressure selected taking into account the size of the turbine unit, the fuel to be burned, and other design criteria. The operating temperature within a preselected temperature range can also be selected based on the type of fuel to be burned, the size of the turbine unit 1, and other design criteria. Predefined tripping conditions can be based on temperature and / or pressure levels exceeding the preselected operating temperature and / or pressure levels. Predefined tripping conditions can also be detected based on other criteria (e.g., oxygen concentration levels, type of fuel burned, high vibration, or other mechanical failures).

[0076] As described above, embodiments of the methods, systems, and apparatus of the present invention can be configured and implemented such that natural gas or other fuels with higher auto-ignition temperatures used for purging in the fuel delivery system 2 can help facilitate faster restart operations of the turbine unit 1, which also helps to better mitigate problems associated with erroneous starts that may occur during the restart process of the turbine unit 1. Furthermore, embodiments can facilitate a significant reduction in the amount of inert fluid required to support the safe operation of the turbine unit (e.g., between 30% and 70% in some embodiments as described above). These types of improvements can facilitate improved turbine operation, providing more efficient performance by reducing downtime during turbine unit operation, and also promote greater use of low auto-ignition temperature fuel sources available from green production (e.g., the use of green hydrogen produced from water electrolysis driven by renewable energy sources).

[0077] Embodiments of the methods, apparatus, and systems of the present invention can be adapted to different turbine equipment design standards. For example, it should be understood that other embodiments may utilize additional exhaust ducts to exhaust the duct arrangement 10 and / or combustion system 4. It should also be understood that other modifications may be made to meet a specific set of standards for different embodiments of turbine equipment 1 or fuel delivery system 2.

[0078] It should be understood that modifications can be made to the embodiments explicitly shown and discussed herein to meet a specific set of design objectives or a specific set of design criteria. For example, valves, pipes, and other conduit elements (e.g., conduit connections, tubing, seals, valves, etc.) of different units of a fluid transport device for interconnecting fluid flow between different components (e.g., pumps, valves, conduits, compressors, etc.) can be arranged to meet a specific plant layout design that takes into account the available area of ​​the equipment, the size configuration of the equipment, and other design considerations. As another example, the flow rate, pressure, and temperature of the fluid through various equipment or system components can vary to accommodate different design configurations and other design criteria. As yet another example, each valve assembly V may include pressure valves, solenoid valves, and / or isolation valves within the assembly. For example, when a valve assembly V includes more than one valve, these valves can be arranged in series with each other to allow pressure regulation, flow regulation, and / or absolute isolation to meet a specific set of design criteria.

[0079] Embodiments of the apparatus 1a for starting and stopping the fuel supply to a turbine, the method for starting and stopping the fuel supply to a turbine, and / or the system for starting and stopping the fuel supply to a turbine can each be configured to include a process control element positioned and configured to monitor and control operations (e.g., temperature and pressure sensors, flow sensors, an automated process control system having at least one workstation including a processor, non-transitory memory, and at least one transceiver for communicating with sensor elements, valves, and controllers, and for providing a user interface for the automated process control system that can run on the workstation and / or another computer device in the plant, etc.). It should be understood that embodiments may also utilize a distributed control system (DCS) to implement one or more processes and / or control operations on the equipment.

[0080] As another example, it is contemplated that specific features described separately or as part of an embodiment can be combined with other separately described features or portions of other embodiments. Therefore, elements and actions of the various embodiments described herein can be combined to provide additional embodiments. Thus, while certain exemplary embodiments of the methods, apparatus, systems, and methods of manufacture and use thereof have been shown and described above, it should be clearly understood that the invention is not limited thereto, but can be practiced and implemented in various other ways within the scope of the appended claims.

Claims

1. A device for starting and stopping the fuel supply to a turbine device, comprising: A conduit arrangement having at least one low auto-ignition temperature fuel supply conduit capable of being connected to at least one low auto-ignition temperature fuel source and a high auto-ignition temperature fuel supply conduit capable of being connected to a high auto-ignition temperature fuel source. The duct arrangement is connectable to a combustion system and configured such that, in response to a detected trip condition, at least one valve assembly of at least one exhaust duct of the duct arrangement is adjustable to an open position for exhaust, while at least one valve assembly of at least one low auto-ignition temperature fuel supply duct is in a closed position to isolate the at least one low auto-ignition temperature fuel source and at least one valve assembly of the high auto-ignition temperature fuel supply duct is also in a closed position to allow the duct arrangement to exhaust, and while the at least one valve assembly of the at least one low auto-ignition temperature fuel supply duct remains in the closed position, the at least one valve assembly of the high auto-ignition temperature fuel supply duct is open to facilitate the restart of the turbine equipment by purging the duct arrangement upstream of the combustion system with high auto-ignition temperature fuel and repressurizing the duct arrangement.

2. The device according to claim 1, wherein the conduit arrangement comprises: A mixer and a fuel cleaning device, the mixer being located between the fuel cleaning device and the at least one low auto-ignition temperature fuel supply conduit, and the mixer also being located between the fuel cleaning device and the high auto-ignition temperature fuel supply conduit; The conduit arrangement includes a fuel cleaning device supply conduit located between the mixer and the fuel cleaning device, and a combustion system supply conduit connected between the fuel cleaning device and the combustion system.

3. The device of claim 2, wherein the conduit arrangement further comprises a valve assembly for the combustion system supply conduit, the valve assembly being adjustable to a closed position in response to a detected trip condition.

4. The device according to claim 3, comprising: A distributed control system controller, communicatively connectable to the valve assembly of the combustion system supply duct, the at least one valve assembly of the at least one exhaust duct, the at least one valve assembly of the at least one low auto-ignition temperature fuel supply duct, and the at least one valve assembly of the high auto-ignition temperature fuel supply duct.

5. The device according to claim 4, comprising: An inert fluid source is provided, which can be connected to the combustion system via at least one inert fluid connection conduit located between the combustion system and the inert fluid source.

6. The apparatus of claim 5, wherein the inert fluid source comprises at least one storage tank, the at least one storage tank being configured to retain a fluid consisting of nitrogen.

7. The device of claim 5, wherein the at least one inert fluid connection conduit has at least one valve assembly.

8. The apparatus of claim 7, wherein the at least one inert fluid connection conduit is configured to supply a non-combustible gas to the combustion chamber of the combustion system.

9. The apparatus of claim 1, wherein the at least one low auto-ignition temperature fuel source comprises a hydrogen source and a refinery exhaust gas (ROG) source, and the at least one low auto-ignition temperature fuel supply conduit comprises a hydrogen supply conduit connectable to the hydrogen source and an ROG supply conduit connectable to the ROG source; and The at least one valve assembly of the at least one low auto-ignition temperature fuel supply conduit includes: The valve assembly of the hydrogen supply conduit and the valve assembly of the ROG supply conduit.

10. A method for starting and stopping a fuel supply for a turbine device, the method comprising: In response to a trip condition detected during turbine operation, the flow of at least one low auto-ignition temperature fuel to the combustion system of the turbine is cut off; To depressurize the fuel delivery system of the combustion system by venting exhaust gas; While the at least one low auto-ignition temperature fuel is absolutely isolated from the fuel delivery system, a high auto-ignition temperature fuel is supplied to the fuel delivery system to purge the fuel delivery system and then the fuel delivery system is repressurized to the preselected pressure, so that while the high auto-ignition temperature fuel is supplied to the fuel delivery system for purging the fuel delivery system and then the fuel delivery system is repressurized to the preselected pressure, no low auto-ignition temperature fuel can be supplied to the combustion system via the fuel delivery system; The high auto-ignition temperature fuel is supplied to the combustion system to facilitate the start-up operation of the turbine equipment.

11. The method of claim 10, comprising: After the turbine equipment is started, and after a pre-selected set of criteria are met, at least one low auto-ignition temperature fuel is supplied to the combustion system.

12. The method of claim 10, wherein supplying the high auto-ignition temperature fuel to the combustion system to facilitate the start-up operation of the turbine device comprises adjusting the position of a valve assembly of the combustion system supply duct from a closed position to an open position.

13. The method according to claim 12, wherein, While the at least one low auto-ignition temperature fuel is absolutely isolated from the fuel delivery system, the high auto-ignition temperature fuel is supplied to the fuel delivery system to purge the system and then the system is repressurized to the preselected pressure, such that while the high auto-ignition temperature fuel is supplied to the fuel delivery system for purging and subsequently the system is repressurized to the preselected pressure, no low auto-ignition temperature fuel can be supplied to the combustion system via the fuel delivery system, including: The valve assembly of the high auto-ignition temperature fuel supply conduit is adjusted from the closed position to the open position, while at least one valve assembly of at least one low auto-ignition temperature fuel supply conduit is in the closed and isolated position, and at least one valve assembly of at least one exhaust conduit of the fuel delivery system conduit arrangement is in the open position for venting the fuel delivery system upstream of the combustion system, and then the at least one valve assembly of the at least one exhaust conduit is closed for repressurizing the fuel delivery system upstream of the combustion system via the high auto-ignition temperature fuel.

14. The method of claim 13, wherein the high auto-ignition temperature fuel is natural gas, and the at least one low auto-ignition temperature fuel comprises hydrogen.

15. The method of claim 14, wherein the flow of at least one low auto-ignition temperature fuel is provided via a conduit arrangement of the fuel delivery system.

16. The method of claim 10, wherein cutting off the flow of the at least one low auto-ignition temperature fuel to the combustion system of the turbine equipment comprises: Adjust the position of the valve assembly of the combustion system supply duct of the fuel delivery system from the open position to the closed position; and / or Adjust the position of at least one valve assembly of at least one low auto-ignition temperature fuel supply conduit from an open position to a closed and isolated position.

17. The method of claim 16, comprising: After cutting off the flow of the at least one low auto-ignition temperature fuel to the combustion system of the turbine equipment, inert gas is supplied to the combustion system to purge the combustion system.

18. The method of claim 10, wherein cutting off the flow of the at least one low auto-ignition temperature fuel to the combustion system of the turbine equipment comprises: Adjust the position of the valve assembly of the combustion system supply duct of the fuel delivery system from the open position to the closed position; as well as Adjust the position of at least one valve assembly of at least one low auto-ignition temperature fuel supply conduit from an open position to a closed and isolated position.

19. The method of claim 18, wherein the at least one valve assembly of the at least one low auto-ignition temperature fuel supply conduit comprises: Valve assembly for hydrogen supply conduit.

20. The method of claim 18, wherein the at least one valve assembly of the at least one low auto-ignition temperature fuel supply conduit comprises: Valve assemblies for hydrogen supply conduits and valve assemblies for refinery waste gas supply conduits.

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