Apparatus and method for igniting highly reactive fuel gas

Abstract

An ignition apparatus for controlling ignition of one or more burners of a gas turbine is disclosed. The ignition apparatus includes an isolation module for selectively allowing passage of fuel from a fuel source and an adjustment module capable of adjusting fuel delivered to a nozzle manifold of the gas turbine during an ignition phase. A method of igniting a gas turbine is also disclosed.

Description

[Technical field]

[0001] SUMMARY The present disclosure relates to an ignition system for starting and fueling a gas turbine with highly reactive fuel gases and an ignition method for igniting a gas turbine. [Background technology]

[0002] As is known, a gas turbine comprises a combustion chamber provided with nozzles for injecting the fuel gas to be combusted, the fuel gas being intended to be combusted in the combustion chamber, after which the hot exhaust gases leave the combustion chamber and move an impeller mounted on a shaft, thus providing the mechanical work that is used as required.

[0003] Fuel is delivered to the gas turbine through a delivery line. A device with a valve is disposed along the delivery line to control the amount of fuel provided to the combustor and to shut off the fuel delivery when the gas turbine engine must be shut off. The ignition device also includes a shutoff valve for shutting off the fuel delivery to the combustor section.

[0004] Ignition devices are typically implemented to control fuel delivery to gas turbines, providing a fuel metering valve to measure in real time the amount of fuel delivered to the combustor section of the gas turbine based on a turbine controller input signal. In particular, ignition devices are intended to prevent excess fuel to the start-up phase of the gas turbine. In fact, excess fuel supplied during the ignition phase can overheat the gas turbine itself and cause danger to the rotating machinery, which increases maintenance costs as well as peak periods.

[0005] In addition to the above, one important aspect of known ignition devices is that they typically have a significant number of parts, thus increasing the probability of failure and the average maintenance cost. Summary of the Invention [Problem to be solved by the invention]

[0006] Another drawback of known ignition devices is that they are often cumbersome, taking into account the large number of parts from which they are made. Modern gas turbines are usually compact, and the market generally requires power units that are as compact as possible in order to better organize such types of components in larger energy production systems. Therefore, one design trend is to save space, and compact and reliable components would be welcomed by the market.

[0007] In one aspect, the subject matter disclosed herein relates to an ignition device for controlling ignition of a gas turbine. The ignition device mainly comprises a shutoff module that allows selective passage of fuel gas from a fuel source, and a regulation module connected between the shutoff module and an outlet connected to a nozzle manifold. The regulation module can have a first operating state in which the regulation module allows flow of fuel gas to the nozzle manifold, and a second operating state in which the regulation module allows fuel supply to the gas turbine over all conditions, particularly over start-up, operating and shutdown conditions.

[0008] In another aspect, the regulation module includes at least one control valve, such as a metering valve, connected between the shutoff module and the nozzle manifold. The control valve is configured to regulate the fuel gas flow when the regulation module is in the second operating state. The regulation module also includes an ignition valve assembly capable of selectively opening the fuel gas flow delivered to the nozzle manifold when the regulation module is in the first operating state. The ignition valve assembly has a nominal flow rate that is lower than the nominal flow rate of the control valve.

[0009] In another aspect, the ignition valve assembly is connected in series with the control valve, the control valve being open when the regulation module is in the first operating state. The ignition valve assembly may also be connected in parallel with the control valve, the control valve being closed when the regulation module is in the first operating state.

[0010] A further aspect of the present disclosure relates to an ignition valve assembly having a nominal flow rate lower than the nominal flow rate of the control valve, in particular, the ignition valve assembly includes an orifice member sized to prevent the passage of an amount of fuel that may cause over-fueling.

[0011] In another aspect, disclosed herein is an ignition valve assembly that includes a metering valve that may be connected in series or parallel to an orifice member. The ignition valve assembly may also include a valve seal that may be connected in series or parallel to the orifice member.

[0012] In another aspect, disclosed herein is that the ignition valve assembly can include a shutoff valve that can be connected in series upstream of the control valve. Also, a metering valve can be connected in parallel with the shutoff valve.

[0013] In another aspect, disclosed herein is a shutoff module comprising two shutoff valves and a vent valve.

[0014] In one aspect, the subject matter disclosed herein relates to a gas turbine having an ignition device, one or more burners for combusting a fuel, and one or more nozzle manifolds each having one or more nozzles for injecting fuel to a respective burner.

[0015] In a further aspect, the subject matter disclosed herein relates to an ignition valve assembly including a valve seal connected between a first shutoff valve and a second shutoff valve of the shutoff module or downstream of the shutoff module, and an orifice member connected between the valve seal and at least one of the nozzle manifolds.

[0016] In one aspect, the subject matter disclosed herein also relates to a shutoff valve connected between the valve seal and a first shutoff valve and a second shutoff valve of the shutoff module, the shutoff valve configured to open when the adjustment stage has a first operating state and to close when the adjustment stage has a second operating state.

[0017] In one aspect, the subject matter disclosed herein relates to a method for igniting a gas turbine including an ignition device, the method including the steps of opening a shutoff module to allow passage of fuel gas coming from a source connected to the ignition device, and igniting the gas turbine by controlling a fuel flow delivered to at least one nozzle or at least one nozzle manifold of a burner by enabling an ignition valve assembly of a regulation module of the ignition device and disabling or regulating a control valve of the regulation module to ignite at least one nozzle or at least one nozzle manifold of the gas turbine. The method also includes fueling the gas turbine (1) over start-up, operating, and shutdown conditions by regulating the control valve to allow delivery of fuel gas to the gas turbine after the ignition step is completed. [Brief description of the drawings]

[0018] A complete understanding of the disclosed embodiments of the present invention and many of the attendant advantages thereof will be readily obtained as the same become better understood by reference to the following detailed description when considered in connection with the accompanying drawings, in which: [Figure 1] FIG. 1 is a schematic diagram of an apparatus for igniting a gas turbine according to a first embodiment. [Diagram 2] FIG. 2 is a schematic diagram of an apparatus for igniting a gas turbine according to a second embodiment. [Diagram 3] FIG. 3 is a schematic diagram of an apparatus for igniting a gas turbine according to a third embodiment. [Figure 4] FIG. 4 is a schematic diagram of an apparatus for igniting a gas turbine according to a fourth embodiment. [Diagram 5] FIG. 5 is a schematic diagram of an apparatus for igniting a gas turbine according to a fifth embodiment. [Figure 6] FIG. 6 is a schematic diagram of an apparatus for igniting a gas turbine according to a sixth embodiment. [Figure 7]FIG. 7 is a schematic diagram of an apparatus for igniting a gas turbine according to a seventh embodiment. [Figure 8] FIG. 8 is a flow diagram of a method for igniting a gas turbine in accordance with the present disclosure. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0019] When a gas turbine must be ignited, the fuel delivered to the burner must be properly controlled and an excess of such fuel must be avoided. Devices and apparatus exist for controlling the ignition phase of a gas turbine. According to one aspect, the present subject matter is directed to an ignition apparatus that can assume different operating states to enable ignition of the gas turbine and to enable delivery of fuel to drive the gas turbine when the ignition step is completed.

[0020] In the various figures, similar parts are designated by the same reference numbers.

[0021] Referring now to the drawings, Figure 1 shows diagrammatically a gas turbine 1 connected to a fuel source 2 via a delivery line 3. The gas turbine 1 is shown diagrammatically as a dashed box and not all of the main parts of the gas turbine 1 are represented in the figures referred to.

[0022] The fuel source 2 may be a fuel gas tank or a gas supply streamline or any other source of gas fuel.

[0023] The gas turbine 1 mainly comprises a nozzle manifold 5 having a number of nozzles for injecting fuel to be combusted in a combustion chamber (not shown) of the gas turbine 1, and an ignition device 4 fluidly connected to the delivery line 3 and the nozzle manifold 5. The ignition device 4 is adapted to control the amount of fuel injected into the burners of the gas turbine 1 during an ignition sequence, regardless of the fuel composition and supply pressure. It is contemplated that the fuel may be of any type.

[0024] The nozzles of the nozzle manifold 5 depend on the number, size and shape of the burners. The amount of fuel taken from the fuel source 2 and appropriately controlled by the ignition device 4 according to the operation phase of the gas turbine 1 is distributed and injected by each nozzle of the nozzle manifold 5.

[0025] The igniter 4 has an inlet 41 fluidly connected to the delivery line 3 and an outlet 42 fluidly connected to the nozzle manifold 5. The igniter 4 includes a shutoff module 44 for allowing passage of fuel from the fuel source 2 and at least one adjustment module 45 connected to the shutoff module 44 via a fuel line 43.

[0026] The ignition device 4 shows several regulating modules 45, all except one of them shown in dashed lines. The regulating modules 45 form the regulating stage ADJ of the ignition device 4. In the figure, only one regulating module 45 is shown and will be disclosed in detail below. The regulating module 45 is configured to control the fuel delivered to the burner of the gas turbine 1 through the nozzle manifold 5 during the ignition sequence so as not to overload the burner with fuel that may overheat the gas turbine 1. In this embodiment, the shutoff module 44 comprises a first shutoff valve 441 fluidly connected to the inlet 41, a second shutoff valve 442 fluidly connected between the first shutoff valve 441 and the regulating module 45, and a vent valve 443 interposed between the first shutoff valve 441 and the second shutoff valve 442 and the environment. As can be seen, the first shutoff valve 441 and the second shutoff valve 442 are connected in series.

[0027] 1, the regulation module 45 comprises a main metering valve 451, which is a control valve connected between the shutoff module 44 and the nozzle manifold 5, and an ignition valve assembly 452 having a volume smaller than that of the main metering valve 451. The ignition valve assembly 452 is connected in parallel to the main metering valve 451. In this embodiment, the ignition valve assembly 452 comprises a solenoid valve that automatically controls the valve seal 4521 and is therefore electrically controlled, and an orifice member 4522 having a passage sized to prevent the passage of an amount of fuel that could cause over-fueling. In this way, the ignition valve assembly 452 has a flow rate lower than that of the main metering valve 451.

[0028] The valve seals 4521 may be connected to the orifice members 4522 in series or in parallel.

[0029] Typically, a plurality of nozzle manifolds 5 are connected and supplied, and in some embodiments a plurality of conditioning modules 45 are provided, each fluidly connected to an associated nozzle manifold 5 through an outlet 42, as shown generally in FIG.

[0030] A plurality of nozzle manifolds 5 are connected and supplied. Also, in some embodiments, a plurality of conditioning modules 45 are provided, each of which is fluidly connected to a nozzle manifold 5 through an outlet 42.

[0031] In some embodiments, a main metering valve 451 may be provided in each nozzle manifold 5. In this case, the flow rate of fuel gas reaching the main metering valve 451, or generally through the respective control valve, may be individually controlled and regulated, while the ignition valve assembly 452 allows the passage of fuel gas only during the ignition phase.

[0032] More specifically, the adjustment module 45 (and generally the adjustment stage ADJ) can operate according to a first operating state in which the adjustment module 45 allows a limited amount of fuel to reach the nozzle manifold for igniting the gas turbine 1, and a second operating state in which the adjustment module 45 allows the passage of fuel to supply to the gas turbine throughout regime condition operation, i.e. in all so-called conditions, in particular throughout start-up, operation and shutdown conditions.

[0033] The fuel source 2 may generally be a tank or a gas line fluidly connected to a delivery line 4. The fuel, which is typically a gas, is delivered at a nominal pressure, as is well known.

[0034] The ignition device 4 operates as follows.

[0035] When the gas turbine 1 is shut down, the shut-off module 44 is closed to prevent fuel coming from the fuel source 2 from reaching the burners of the gas turbine 1 .

[0036] Specifically, the first and second isolation valves 441, 442 were closed while the vent valve 443 was opened, resulting in a double block and bleed (DDB) system solution for reliable isolation.

[0037] Instead, at the start-up of the gas turbine 1, the shut-off module 44 allows the fuel coming from the fuel source 2 through the delivery line 3 to pass through and reach the adjustment stage ADJ, specifically the adjustment module 45. In particular, the first and second shut-off valves 441 and 442 are open and the vent valve 443 is closed to prevent the fuel (i.e., gas) from dispersing to the surroundings. In this state (first operating state of the adjustment module 451), the adjustment module 45 allows a reduced amount of suitable fuel to reach the nozzle manifold 5 to allow the burner to start the gas turbine 1.

[0038] Specifically, to ignite the gas turbine 1, the main metering valve 451 is closed and at the same time the ignition valve assembly 452 is opened, so that the amount of fuel that can pass the valve seal 4521 through the orifice member 4522 to the nozzle manifold 5, actually restricting the gas flow that reaches the nozzle. The valve seal 4521 is opened and can therefore be appropriately controlled electrically. Also, the orifice member 4522 has a flow rate that is appropriately designed to allow the correct controlled fuel flow to reach the nozzle manifold 5 in order to structurally prevent any fuel overload of the burner.

[0039] When the gas turbine 1 starts, the main metering valve 451 opens and the control valve 452 possibly closes so that all fuel can pass through the main metering valve 451 (second operating state of the regulation module 451). In any event, in other embodiments, the control valve 452 can remain open without affecting the operation of the gas turbine 1.

[0040] Generally, the metering valve 451 does not completely close the fuel passage. A small amount of leakage is possible. Thus, the control valve 452, and in the disclosed embodiment, the flow meter of the orifice member 4522, is designed to account for (and thus reduce) such leakage.

[0041] 2 shows a second embodiment of the ignition device 4, which differs from the one in FIG. 1 in that the regulating module 45 comprises a main metering valve 451 as a control valve and an ignition valve assembly 452 connected in parallel to the main metering valve 451, and the ignition valve assembly 452 comprises an additional metering valve 4523 as a control valve connected in series to an orifice member 4522. The additional metering valve 4523 has a lower flow rate than the flow rate of the main metering valve 451.

[0042] The operation of the ignition device 4 is similar to that of the first embodiment, but when the gas turbine 1 is started, after the shutoff module 44 has passed the fuel coming from the fuel source 2 through the delivery line 3 to reach the regulating module 45, the main metering valve 451 is closed, while the additional metering valve 4523 of the ignition valve assembly, which in this case also functions as a control valve, opens to allow the fuel to reach the nozzle manifold 5 (first operating state of the regulating module 451). As mentioned above, the flow rate or capacity of the additional metering valve 4523 in series with the orifice member 4522 is lower than that of the main metering valve 451, and therefore the fuel to the nozzle manifold 5 is controlled in terms of quantity.

[0043] Also in this case, the capacity of the orifice member 4522 can be designed taking into consideration leakage when the main metering valve 451 is closed.

[0044] Referring now to FIG. 3, a third embodiment of an ignition device 4 is shown which, like the previous embodiments already disclosed, has a shut-off module 44 similar to that of the embodiment shown in FIG. 1 and therefore has first and second shut-off valves 441, 442, as well as a vent valve 443, which operate and are connected in the same way.

[0045] The ignition device 4 according to the third embodiment also comprises a regulating module 45 having an ignition valve assembly 452 consisting of a main metering valve 451 as a control valve and an additional metering valve 4523 connected in series upstream of the metering valve 451. The additional metering valve 4523 is designed to regulate the supply of fluid (i.e. fuel) to the burner of the gas turbine 1 and is automatically operated.

[0046] In addition, the ignition valve assembly 452 of the regulation module 45 comprises an orifice member 4522 connected in parallel to the additional metering valve 4523 so as to bypass the additional metering valve, the orifice member having a passage sized to prevent the passage of a quantity of fuel that could cause over-fueling. To ignite the gas turbine 1, as in the previous embodiment, the cut-off module 44 allows the fuel flowing through the fuel line 43 to reach the regulation module 45. Then, the main metering valve 451 opens and the additional metering valve 4523 remains closed, so that the fuel coming from the fuel source 2, passing through the regulation module 45 and reaching the nozzle manifold 5 is controlled or limited in quantity by the orifice member 4522.

[0047] After igniting the burner, the additional metering valve 4523 opens and the fuel flow reaches the nozzle manifold 5 and then the burner, which is finally regulated by the main metering valve 451. The regulated metering valve 4523 thus acts as a bypass for the orifice member 4522.

[0048] It should be noted that if the additional metering valve 4523 does not open, for example due to a failure, the orifice member 4522, being a passive member rather than an active member, prevents over-fuelling of the burner and limits the amount of fuel passing through it.

[0049] In the embodiment of FIG. 1, as shown in FIGS. 2 and 3, the ignition device 4 according to any one of claims 2 to 4 may include an ignition valve assembly 452 comprising a shut-off valve 4524.

[0050] 4, a fourth embodiment of the ignition device 4 is shown, which is generally similar to the previous embodiment. In this case, the regulation module 45 still comprises a main metering valve 451 and an ignition valve assembly 452 connected in series with the main metering valve 451. The ignition valve assembly 452 comprises a shutoff valve 4524 and an additional metering valve 4523 connected in parallel with the shutoff valve 4524 of the ignition valve assembly 452. The upstream connected metering valve 451 is also suitable for controlling the pressure upstream of the ignition valve assembly 454.

[0051] As for the shutoff module 44, it has the same structure as in the other embodiments, and thus includes two shutoff valves and a vent valve.

[0052] During firing operation (first operating state of the regulating module 451), the metering valve 451 is opened and the shutoff valve 4524 of the ignition valve assembly 452 is closed. At the same time, the additional metering valve 4523 of the ignition valve assembly 452 is opened to allow the passage of fuel gas for the ignition phase and to control the amount of fuel gas reaching the nozzle manifold 5.

[0053] After the ignition run is completed, the gas turbine 1 can start operating. The shutoff valve 4524 then opens, allowing the passage of fuel gas from the metering valve 451 to allow the fuel coming from the source 2 to reach the nozzle manifold 5. At the same time, the additional metering valve 4523 of the ignition valve assembly 452 may remain closed or open without affecting the operation of the gas turbine.

[0054] 5, a fifth embodiment of the ignition device 4 is shown, in particular the shutoff module 44 is similar to the shutoff module of the above-mentioned embodiment. In particular, the ignition device 45 comprises a main metering valve 451 having the same function as the above-mentioned embodiment, and an ignition valve assembly 452 is connected upstream of the main metering valve 451 and provides a pressure control valve 4524 arranged between the shutoff module 44 and the control valve, the main metering valve 451. As can be seen, this fifth embodiment is similar to the fourth embodiment shown in FIG.

[0055] During the ignition phase of the gas turbine 1, the main metering valve 451 remains open to control the fuel gas flow rate. After the ignition phase, the pressure control valve 4524 checks a higher pressure or can even open completely. The regulation of the fuel delivered to the nozzle manifold 5 is also controlled by the pressure control valve 4524. In other words, the pressure control valve 4524 checks the pressure upstream of the main metering valve 451, which controls the flow rate of the fuel gas ignition line as described above. The pressure is low enough to allow appropriate regulation by the main metering valve 451.

[0056] At the end of the ignition phase of the gas turbine 1 , the pressure control valve 4524 opens, allowing the fuel coming from the fuel source 2 to pass through and be regulated by the main metering valve 451 .

[0057] 6 shows a sixth embodiment of the ignition device 4, in which a shut-off module 44 comprises a first shut-off valve 441 connected to the inlet 41 and a second shut-off valve 442 connected between the first shut-off valve 441 and the fuel line 43. The adjustment stage ADJ comprises a plurality of metering valves 451, each metering valve being connected between the fuel line 43 (thus downstream of the shut-off module 44) and a respective nozzle manifold 5.

[0058] The adjustment stage ADJ also includes an ignition valve assembly 452 having a shutoff valve 4525 connected between the first shutoff valve 441 and the second shutoff valve 442 of the shutoff module 44, an automatic control valve seal 4521, and an orifice member 4522 directly connected between the automatic control valve seal 4521 and each nozzle manifold 5 or one of the nozzle manifolds 5 to which one of the main metering valves 451 is connected.

[0059] Again, when the gas turbine 1 is shut down, the shutoff module 44 is closed and fuel from the fuel source 2 does not reach the burners of the gas turbine 1. In this case, the first shutoff valve 441 and the second shutoff valve 442 are closed and the vent valve 443 is open. The shutoff valve 4525 of the ignition valve assembly 452 is also closed and the metering valve 451 is also closed.

[0060] Then, instead, at the start of the gas turbine 1, the shutoff module 44 allows the fuel coming from the fuel source 2 through the delivery line 3 to pass through and reach the adjustment stage ADJ. Specifically, in a first operating state, the first shutoff valve 441 is opened and the second shutoff valve 442 is closed, so that fuel does not reach the main metering valve 451, and the shutoff valve 4525 of the adjustment stage ADJ is opened, so that fuel passes through the valve seal 4521, reaches the nozzle manifold 5, passes through the orifice member 4522, and restricts the gas flow reaching the nozzle, as in the other embodiments. Again, the valve seal 4521 is open and can therefore be controlled electrically.

[0061] As with other embodiments, the orifice member 4522 has a properly designed flow rate to allow a correct and controlled flow of fuel to reach the nozzle manifold 5 to structurally prevent any fuel overload of the burner.

[0062] In the second operating phase, all metering valves 451 are open and the second shutoff valve 442 of the shutoff module 44 is open, so that fuel can pass through the main metering valve 451. The control valve 452 may remain open or closed without affecting the operation of the gas turbine 1. In other words, in the second operating phase, when the gas turbine 1 is normally fueled and the ignition step is performed, the shutoff valve 4525 of the adjustment phase ADJ may remain open or closed.

[0063] 7, a seventh embodiment of the ignition device 4 is shown, in which the shutoff module 44 always comprises a first shutoff valve 441 and a second shutoff valve 442, as well as a vent valve 443, in a normal double block-and-bleed connection. The adjustment stage ADJ comprises a safety stage 453 having a vent valve 4531 and a shutoff valve 4532. The shutoff valve 4532 is connected downstream of the shutoff module 44 and upstream of the main metering valve 451. The ignition valve assembly 452 comprises an automatic control valve seal 4521 connected downstream of the shutoff module 44, generally connected to the node to which the vent valve 4531 is connected, and an orifice member 4522 connected directly between the automatic control valve seal 4521 and the respective nozzle manifold 5 or one of the nozzle manifolds 5 to which one of the main metering valves 451 is connected.

[0064] The adjustment stage ADJ also comprises a safety stage 453 having a vent valve 4531 and a shutoff valve 4532. When the gas turbine 1 is shut down, the shutoff module 44 is closed. Thus, both the first shutoff valve 441 and the second shutoff valve 442 are closed and the vent valve 443 is opened. With reference to the safety stage 453, the shutoff valve 4532 is also closed and the vent valve 4531 is opened.

[0065] In a first operating state of the adjustment stage ADJ, then the first shut-off valve 441 and the second shut-off valve 442 are opened while the vent valve 443 is closed and fuel passes through the valve seal 4521, reaches the nozzle manifold 5 and passes through the orifice member 4522 which restricts the fuel flow.

[0066] After ignition of the gas turbine 1, i.e. when a flame to the gas burner is detected, the shutoff valve 4532 of the safety stage 453 is opened and the vent valve 4531 is closed so that fuel can reach the nozzle manifold 5 through the main metering valve 451.

[0067] It is also possible to foresee a vent valve (not shown) downstream of each metering valve 451 so that it closes only when the gas turbine 2 is actually supplied.

[0068] FIG. 8 shows a method 6 of igniting a gas turbine 1 by an ignition device 4 according to the present disclosure. The ignition method 6 includes a step 61 of enabling the shutoff module 44 to allow the passage of fuel gas coming from a fuel source 2 connected to the ignition device 4. Then, the ignition phase is performed by controlling the fuel flow delivered to the nozzle manifold 5 by enabling the ignition valve assembly 452 of the regulation module 45 of the ignition device 4. At the same time, the control valve 451 is regulated. After the ignition phase is completed, the gas turbine 1 is fueled for all operating conditions, i.e., start-up, running and stop conditions, by enabling (step 63) the regulation module 45 by enabling the control valve 451, which is a metering valve and allows the gas flow to pass and to supply the fuel gas to the gas turbine 1. The fuel supply step starts after the ignition step 62 is completed.

[0069] An advantage of the ignition device of the present disclosure is that it has simplified hardware, which is accompanied by improved reliability.

[0070] Another advantage of the ignition system of the present disclosure is that it is tolerant to multiple fuel gas compositions.

[0071] A further advantage of the ignition system of the present disclosure is that it eliminates the need to seal the main lines after flame detection.

[0072] While aspects of the invention have been described in terms of various specific embodiments, it will be apparent to those skilled in the art that many modifications, changes, and omissions are possible without departing from the spirit and scope of the claims. In addition, unless otherwise specified herein, the order or sequence of any process or method steps may be changed or rearranged according to alternative embodiments.

[0073] Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are illustrated in the drawings. Each example is provided as an explanation of the present disclosure, not as a limitation of the disclosure. Indeed, it will be apparent to those skilled in the art that various modifications and variations can be made to the present disclosure without departing from the scope or spirit of the disclosure. References throughout this specification to "one embodiment" or "an embodiment" or "some embodiments" mean that a particular feature, structure, or characteristic described in connection with an embodiment is included in at least one embodiment of the disclosed subject matter. Thus, the appearance of the phrases "in one embodiment" or "in an embodiment" or "in some embodiments" in various places throughout this specification do not necessarily refer to the same embodiment. Furthermore, particular features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0074] When presenting elements of various embodiments, the articles "a," "an," "the," and "said" are intended to mean that there are one or more of the elements. The terms "comprising," "including," and "having" are intended to be non-exclusive and mean that there may be additional elements other than the listed elements.

Claims

1. An ignition device for controlling ignition of a gas turbine, comprising: an inlet connectable to a fuel gas source; an outlet for supplying a controlled amount of fuel gas to at least one nozzle or at least one nozzle manifold of the burner; a shutoff module for selectively allowing the passage of the fuel gas from the fuel source; at least one adjustment module connected between the shutoff module and the outlet via a fuel line; The adjustment module includes: a first operating state in which the conditioning module allows the flow of the fuel gas to ignite the at least one nozzle of a burner or flow to the at least one nozzle manifold of the gas turbine; and a second operating state that enables the regulation module to fuel the gas turbine across start-up, operating, and shutdown conditions.

2. The adjustment module includes: at least one control valve connected between the shutoff module and the at least one nozzle or the at least one nozzle manifold of a burner, the control valve configured to regulate the fuel gas flow when the regulation module is in the second operating state; and an ignition valve assembly capable of selectively opening the fuel gas flow delivered to at least one nozzle of a burner or to the at least one nozzle manifold when the adjustment module is in the first operational state.

3. 3. The ignition system of claim 2, wherein the ignition valve assembly has a nominal flow rate that is lower than a nominal flow rate of the control valve.

4. 3. The ignition system of claim 2, wherein said at least one control valve is a metering valve.

5. the ignition valve assembly is connected in series with the control valve; 3. The ignition system of claim 2, wherein the control valve is open when the regulation module is in the first operating state.

6. the ignition valve assembly is connected in parallel with the control valve; 3. The ignition system of claim 2, wherein the control valve is closed when the regulation module is in the first operating state.

7. 2. The ignition device of claim 1, wherein the ignition valve assembly includes an orifice member sized to prevent the passage of a quantity of fuel that may cause over-fueling.

8. the ignition valve assembly includes a metering valve; 8. The ignition device of claim 7, wherein the metering valve is connected in series or parallel to the orifice member.

9. the ignition valve assembly includes a valve seal; 8. The ignition device of claim 7, wherein the valve seal is connected in series or parallel to the orifice member.

10. The ignition device of claim 1 , wherein the ignition valve assembly comprises a shutoff valve.

11. 11. The ignition system of claim 10, wherein the shutoff valve is connected in series upstream of the control valve.

12. the ignition valve assembly includes a metering valve connected in parallel with the shutoff valve; 11. The ignition system of claim 10, wherein the ignition valve assembly is connected in series downstream of the main metering valve.

13. The interruption module includes: a first shutoff valve fluidly connected to the inlet; a second shutoff valve fluidly connected between the first shutoff valve and the regulation module; 2. The ignition device of claim 1, further comprising: a vent valve interposed between the first and second shutoff valves and the surroundings.

14. The ignition device of claim 1 , wherein the outlet is connected to a plurality of nozzles or a plurality of nozzle manifolds.

15. 1. A gas turbine comprising:

1. An ignition device for controlling ignition of a gas turbine connected to a fuel source, comprising: an inlet connectable to a fuel gas source; an outlet for supplying a controlled amount of fuel gas to at least one nozzle or at least one nozzle manifold of the burner; a shutoff module for selectively allowing passage of the fuel gas from the fuel source; at least one adjustment module connected between the shutoff module and the outlet via a fuel line; The adjustment module includes: a first operating state in which the conditioning module allows the flow of the fuel gas to ignite the at least one nozzle of a burner or flow to the at least one nozzle manifold of the gas turbine; a second operating state that enables the regulation module to fuel the gas turbine across start-up, operating, and shutdown conditions; and one or more burners for combusting a fuel; one or more nozzle manifolds, each having one or more nozzles for injecting fuel to a respective burner.

16. 1. A method of igniting a gas turbine having an ignition device, comprising: activating a shutoff module to allow the passage of the fuel gas coming from a source connected to the ignition device; igniting the gas turbine by controlling the fuel flow delivered to the at least one nozzle or at least one nozzle manifold of a burner by enabling an ignition valve assembly of an adjustment module of the ignition device and disabling or adjusting the control valve of the adjustment module to ignite at least one nozzle or at least one nozzle manifold of the gas turbine; after the ignition step is completed, fueling the gas turbine through start-up, operation, and shutdown conditions by enabling the regulation module to regulate the control valve to supply the fuel gas to the gas turbine; A method comprising:

17. The ignition step includes:

17. The method of claim 16, comprising controlling the fuel flow delivered to the at least one nozzle or the at least one nozzle manifold of a burner by opening a metering valve or valve seal to allow the passage of fuel gas through the ignition valve assembly and allowing the passage of the fuel gas through an orifice member.

18. The ignition step includes: allowing the passage of fuel gas through the ignition valve assembly by opening the pressure control valve to control a pressure of the fuel gas; and controlling the flow rate of the fuel gas by adjusting the control valve; The method of claim 16, further comprising controlling the fuel flow delivered to the at least one nozzle or the at least one nozzle manifold of a burner.

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