Gas turbine engine with first and second stage fuel control and method of controlling the same

Abstract

A gas turbine engine comprising: a first stage combustor (3) having a plurality of first fuel injector assemblies (17); a second stage combustor (7) having a plurality of second fuel injector assemblies (30) downstream of the first stage combustor (3); a fuel supply system (9) configured to supply a respective first fuel flow rate (FM1) to each first fuel injector assembly (17) and a respective second fuel flow rate (FM2) to each second fuel injector assembly (30); and a controller (10) configured to control the first fuel flow rate (FM1) and the second fuel flow rate (FM2). The controller (10) is further configured to selectively enable and disable the second fuel injector assemblies (30) and to supply a first fuel flow rate (FM1) of a first value to a first set of first fuel injector assemblies (17) and a first fuel flow rate (FM1) of a second value to a second set of first fuel injector assemblies (17) in a partial load operating condition when at least the first set of second fuel injector assemblies (30) is inactive, the first fuel flow rate (FM1) of the first value being lower than the first fuel flow rate (FM1) of the second value or zero flow rate.

Description

[0001] Cross-reference to related applications This patent application claims priority to European Patent Application No. 20217235.9, filed on 24 December 2020, the full disclosure of which is incorporated herein by reference. Technical Field

[0002] This invention relates to a gas turbine engine having a first-stage fuel control and a second-stage fuel control, and to a method for controlling the gas turbine engine. Background Technology

[0003] As is known, controlling pollutant emissions is a primary objective in the design of any type of heat engine, and especially in gas turbines used in power plants. Indeed, the awareness of environmental risks is driving the development of increasingly stringent regulations. On the other hand, the organization of modern power markets and the constantly fluctuating demand do not allow for the operation of plants under constant load conditions. Instead, the need to meet demand fluctuations (including sudden increases or decreases) and to help control grid frequency requires considerably flexible operation. However, it is precisely because of this operational flexibility that the reduction of pollutant emissions becomes crucial.

[0004] One of the problems to be solved involves operating at very low partial loads. Burner shutdown sequences are implemented to achieve a partial load mode where the burner remains active in the low load range. However, reducing the number of active burners in the combustor assembly may not be sufficient to meet both market and low emission requirements, and active burners often need to be used in the lowest part of their power range. CO emissions are generally not a problem at full load, but the low temperature and pressure at low loads can prevent complete carbon oxidation and favor carbon monoxide formation, thus limiting the ability of gas turbine engines to operate at very low power outputs. A method to (partially) overcome this limitation is to deactivate individual burners at low engine loads. Thus, the remaining active burners can operate at higher temperature levels, which keeps the amount of carbon monoxide formed low.

[0005] However, there is a general expectation to further reduce the minimum power delivered by gas turbine engines in order to meet increasingly flexible market demands and comply with stringent legal requirements regarding emissions and grid frequency control. Summary of the Invention

[0006] The objective of this invention is to provide a gas turbine engine and a method for controlling the gas turbine engine, which allows for overcoming or at least mitigating the limitations described.

[0007] According to the present invention, a gas turbine engine is provided, comprising: A first-stage burner having multiple first-stage burner assemblies; A second-stage burner having multiple second burner assemblies is located downstream of the first-stage burner; A fuel supply system configured to supply a corresponding first fuel flow rate to each first burner assembly and a corresponding second fuel flow rate to each second burner assembly; A controller configured to control a first fuel flow rate and a second fuel flow rate; The controller is further configured to selectively enable and disable the second burner assembly and, under partial load operating conditions when at least the first group of second burner assemblies is inactive, supply a first fuel flow rate of a first value to the first group of first burner assemblies and a first fuel flow rate of a second value to the second group of first burner assemblies, wherein the first fuel flow rate of the first value is lower than the first fuel flow rate of the second value or is zero.

[0008] To some extent, load reduction can be achieved by disabling the second burner assembly. Control of the fuel flow rate of the first set of first burner assemblies, and possible shutdown, allows for a further reduction in the power delivered by the gas turbine engine. This enables extremely low loads without impacting frequency control requirements or emissions compliance.

[0009] According to an aspect of the invention, the controller is further configured to supply a first fuel flow rate of a partial value to the first group of first burner assemblies when the second group of second burner assemblies is active.

[0010] The active second burner assembly can operate with full fuel supply, thus maintaining high hot gas temperatures. No risk of increased harmful emissions arises from keeping the active second burner assembly active during stable operation. Load shedding procedures, reduced to very low partial loads, can benefit from the combustion conditions of the active second burner assembly.

[0011] According to an aspect of the invention, the controller is further configured to supply a first fuel flow rate of a partial value to the first group of first burner assemblies when all second burner assemblies are inactive.

[0012] The load on the gas turbine engine can therefore be driven as low as required by the circumstances.

[0013] According to an aspect of the invention, the composition of the first group of first burner assemblies varies from a first partial load operating condition to a second partial load operating condition.

[0014] Different modes of the first burner assembly can be unloaded or deactivated to implement flexible control strategies, which also helps to ensure consistent aging and lifespan of the components and prevent premature failure of mechanical integrity.

[0015] According to an aspect of the invention, each of the first burner assemblies includes a corresponding main burner and a corresponding pilot burner, and the fuel supply system is configured to supply a corresponding first fuel flow rate to the main burner and a pilot fuel flow rate to the pilot burner.

[0016] According to an aspect of the invention, the fuel supply system includes: a first-stage supply system coupled to a first-stage burner and controlled by a controller to supply a first fuel flow rate to a first burner assembly; and a second-stage supply system coupled to a second-stage burner and controlled by a controller to supply a second fuel flow rate to a second burner assembly.

[0017] According to an aspect of the invention, the first-stage supply system includes: a main supply line connected to a main burner of a first group of first burner assemblies; and a plurality of first main valves independently controlled by a controller, each having an inlet connected to the first main supply line and an outlet connected to a corresponding one of the main burners of the first group of first burner assemblies.

[0018] Individual and independent control of the first main valve allows for flexible selection of the first main fuel valve. For example, the main burners of the first group of first burner assemblies can be sequentially deactivated or receive correspondingly different values ​​of the first fuel flow rate. In addition, the number of first burner assemblies in the first group and the composition of the first group (i.e., the specific first burner assemblies actually selected) can vary according to preference or current requirements.

[0019] According to an aspect of the invention, the first-stage supply system includes: a main supply line connected to a main burner of a first group of first burner assemblies; a first main valve controlled by a controller and having an inlet connected to the first main supply line and an outlet connected to the main burner of the first group of first burner assemblies; and a second main valve controlled by a controller and having an inlet connected to the first main supply line and an outlet connected to the main burner of a second group of first burner assemblies, the second group of first burner assemblies being complementary to the first group of first burner assemblies.

[0020] The structure of the first-stage supply system, having a first main valve and a second main valve for the first group of first burner assemblies and the second group of first burner assemblies respectively, is simple yet effective in achieving a reduction in the selectivity of fuel supply in the first-stage burner. The simple structure results in relatively low costs for both manufacturing and maintenance, and also a low risk of sudden failure.

[0021] According to an aspect of the invention, the first-stage supply system includes: a pilot supply line configured to supply a pilot fuel flow rate to a pilot burner of a first burner assembly; and a pilot valve controlled by a controller and having an inlet connected to the pilot supply line and an outlet connected to the pilot burner of the first burner assembly; and wherein the controller is configured to maintain the pilot fuel flow rate when a portion of the first fuel flow rate is supplied to the first group of first burner assemblies.

[0022] Even when the fuel supply to the main burner is removed, the first burner assembly of the first group is not completely shut off. Maintaining pilot burner activity independently of load conditions helps maintain appropriate temperature levels and improves the responsiveness of the gas turbine engine for frequency response control purposes.

[0023] According to an aspect of the invention, the controller is further configured to simultaneously or sequentially shut off the main burners of the first group of first burner assemblies under partial load operating conditions.

[0024] Shutting down the main burner allows for a reduction in the power delivered by the gas turbine engine without the risk of increased pollutant emissions. Sequential shutdown allows the gas turbine engine to gradually reduce its load under safe and clean conditions.

[0025] According to an aspect of the invention, the first-stage burner includes a first annular combustion chamber, and the second-stage burner includes a second annular combustion chamber, wherein the first burner assembly and the second burner assembly are arranged circumferentially around an axis.

[0026] According to an aspect of the present invention, a method for controlling a gas turbine engine is provided, the gas turbine engine including a first-stage combustor having a plurality of first burner assemblies and a second-stage combustor having a plurality of second burner assemblies located downstream of the first-stage combustor; The method includes: A corresponding first fuel flow rate is supplied to each first burner assembly, and a corresponding second fuel flow rate is supplied to each second burner assembly; Selectively enabling and disabling the second burner assembly; and Under partial load operating conditions when at least the first group of second burner assemblies is inactive, a partial value of the first fuel flow rate is supplied to at least the first group of first burner assemblies, the partial value of the first fuel flow rate being lower than the full load value or being zero. Attached Figure Description

[0027] The invention will now be described with reference to the accompanying drawings, which illustrate some non-limiting embodiments of the invention, in which: - Figure 1 This is a simplified block diagram of a gas turbine engine; - Figure 2 It is incorporated into Figure 1 A schematic diagram of a portion of a first fuel supply system and a first burner assembly manufactured in a gas turbine engine according to an embodiment of the present invention; - Figure 3 It is incorporated into Figure 1 A schematic diagram of a portion of a second fuel supply system and a second burner assembly manufactured in a gas turbine engine according to an embodiment of the present invention; - Figure 4-11 The first and second burner assemblies are schematically shown under different operating conditions; - Figure 12 It is incorporated into Figure 1 A schematic diagram of a portion of a first fuel supply system and a first burner assembly manufactured in a gas turbine engine according to another embodiment of the present invention; - Figure 13 It is incorporated into Figure 1 A schematic diagram of a portion of a first fuel supply system and a first burner assembly manufactured in a gas turbine engine according to another embodiment of the invention; and - Figure 14 It is incorporated into Figure 1 A schematic diagram of a portion of a first fuel supply system and a first burner assembly manufactured in a gas turbine engine according to another embodiment of the invention. Detailed Implementation

[0028] Figure 1 A simplified view of the gas turbine engine, designated as a whole by the number 1, is shown. The gas turbine engine 1 includes a compressor 2, a first-stage combustor 3, optionally a high-pressure turbine 5, a second-stage combustor 7 (also referred to as a sequential combustor), and a low-pressure turbine 8.

[0029] The gas turbine engine further includes a fuel supply system 9 and a controller 10.

[0030] The fuel supply system 9, which delivers fuel flow rate for the operation of the first-stage burner 3 and the second-stage burner 7, includes a first-stage supply system 11 connected to the first-stage burner 3 and a second-stage supply system 12 connected to the second-stage burner 7. Both the first-stage supply system 11 and the second-stage supply system 12 are controlled by a controller 10.

[0031] The controller 10 receives status signals from the system sensor 13 and operates the gas turbine via an actuator to provide controlled power output. As shown in detail below, the actuator includes an oriented inlet guide vane 14 of the compressor 2 and valves for the first-stage supply system 11 and the second-stage supply system 12.

[0032] The compressed air stream supplied by compressor 2 is supplemented with fuel, and the resulting air / fuel mixture is burned in the first-stage combustor 3. The exhaust gas from the first-stage combustor 3 expands in the high-pressure turbine 5, and then, after possibly adding a dilution air stream, the additional fuel is mixed and burned in the second-stage combustor 7. The exhaust gas finally expands in the low-pressure turbine 8 and is discharged either externally or, for example, to a heat recovery steam generator. The amount of fuel delivered by the first-stage supply system 11 and the second-stage supply system 12 is controlled by controller 10.

[0033] Figure 2 A portion of the first-stage supply system 11 and the first-stage burner 3 are schematically shown.

[0034] The first-stage combustor 3 includes an annular combustion chamber 15 extending around the longitudinal axis A of the gas turbine engine 1 and a plurality of first burner assemblies 17 circumferentially distributed around the longitudinal axis A. Each first burner assembly 17 includes a corresponding pilot burner 18 and a corresponding main burner 20.

[0035] The first-stage supply system 11 is configured to supply pilot fuel flow rate FP to each pilot burner 18 and a corresponding first main fuel flow rate FM1 to the main burner 20.

[0036] The pilot branch of the first-stage supply system 11 includes a pilot supply line 21, a pilot valve 22, and a pilot gas chamber 23 in the form of a distribution ring. The pilot valve 22 (e.g., a control valve or shut-off valve) is controlled by the controller 10 and has an inlet connected to the pilot supply line 21 and an outlet connected to each of the pilot burners 18 of the first burner assembly 17 via the pilot gas chamber 23 and the conduit 24.

[0037] The main branch of the first-stage supply system 11 includes a main supply line 25, a main valve 27, and a main gas chamber 28, which is also in the form of a distribution ring. The main valve 27 (e.g., a control valve) is individually and independently controlled by the controller 10 in one embodiment and has: an inlet connected to the main gas chamber 28, which in turn is connected to the main supply line 25 via a conduit 26; and an outlet, each connected to a corresponding one of the main burners 20 in the first burner assembly 17. The controller 10 is thus in a condition to individually control the first main fuel flow rate FM1 supplied to each of the main burners 20.

[0038] refer to Figure 3The diagram schematically illustrates a second-stage fuel supply system 12 and a second-stage burner 7, which includes an annular combustion chamber 29 extending around a longitudinal axis A and a plurality of second burner assemblies 30 arranged circumferentially around the machine axis A. The second-stage fuel supply system 12 includes a second-stage fuel supply line 32, a second-stage fuel valve 33, and a fuel gas chamber 35. The second-stage fuel valve 33 has an inlet connected to the second-stage fuel supply line 32 and an outlet connected to each of the second burner assemblies 30 via the fuel gas chamber 35 and a conduit 36. A corresponding second main fuel flow rate FM2, controlled by the controller 10, can thus be supplied to each second burner assembly 30. A shut-off valve 37 is arranged along the supply conduit 36, one for each second burner assembly 30. Thus, the shut-off valve 37 is arranged between the second-stage fuel valve 33 and the fuel inlet of the corresponding second burner assembly 30. The shut-off valve 37 is controlled independently by the controller 10, such that the controller 10 can enable and disable each of the other second burner assemblies 30 independently of the other second burner assemblies 30.

[0039] The controller 10 is configured to control at least a first main fuel flow rate FM1 and a second main fuel flow rate FM2 supplied to the main burner 20 and the second burner assembly 30, respectively, of the first burner assembly 17. Specifically, when all second burner assemblies are active and receiving the corresponding second main fuel flow rate FM2, the controller operates the first-stage supply system 11 and the second-stage supply system 12 to supply the first main fuel flow rate FM1 at full load value to each main burner 20 under full load operating conditions (see [link]). Figure 4 ).

[0040] When a load reduction is required, for example, due to a decrease in load demand from the power grid at night, the controller 10 sequentially deactivates the first group of second burner assemblies 30 until only the second group of programmed numbers (e.g., eight) of second burner assemblies 30 remain active and the first partial load operating conditions and load threshold are met. Figure 5 The fully active burners of both the first-stage burner 3 and the second-stage burner 7 are shown in dark gray, and the inactive burners are shown in white (see enlarged details). In this step, the controller 10 still sends the first main fuel flow rate FM1 to all main burners 20.

[0041] If the request further reduces the load below the load threshold ( Figure 6 Under the second partial load operating condition, when the first group of second burner assemblies 30 is inactive and the second group of second burner assemblies 30 is active, the controller 10 supplies a portion of the first value of the first main fuel flow rate FM1 to the first group of first burner assemblies 17. Figure 6(See enlarged details). In other words, fuel supply is reduced for the first burner assembly 17 of the first group, while the complementary first burner assembly 17 of the second group receives a first main fuel flow rate FM1 that may correspond to a second value corresponding to full load or partial load. In any case, the first main fuel flow rate FM1 of the first value supplied to the first burner assembly 17 is lower than the first main fuel flow rate FM1 of the second value supplied to the first burner assembly 17 of the second group. Specifically, in the described embodiment, fuel supply is reduced for the main burner 20 of the first burner assembly 17 of the first group, while fuel supply remains unchanged for all pilot burners 18. When all second burner assemblies 30 of the first group have been deactivated, the controller 10 begins to reduce the first main fuel flow rate FM1 of the first burner assembly 17 of the first group. The first main fuel flow rate FM1 of the first burner assembly 17 of the first group can be reduced to zero, that is, the main burner 20 of the first burner assembly 17 of the first group is shut off ( Figure 7 (See enlarged details).

[0042] In the described embodiment, the main valve 27 and the shut-off valve 37 can also be independently controlled by the controller 10. Therefore, the composition of the first group (i.e., the individual first burner assemblies 17 forming the first group) is not strictly fixed and can be selected according to the situation, varying from first partial load operating conditions to second partial load operating conditions. Similarly, the controller 10 can select the active second burner assembly 30. For example ( Figure 8 and Figure 9 Four second burner assemblies 30 on one side (e.g., the lower side) of the second-stage burner 7 are activated. Simultaneously, the main valve 27 can be controlled such that the same or more (e.g., eight) number of first burner assemblies 17 on the same (lower) side of the first-stage burner assembly 3 receive a first main fuel flow rate FM1 (second group) of a second value; and all other first burner assemblies 17 (first group) receive a first main fuel flow rate FM1 of a first value. Figure 8 ) or zero flow rate ( Figure 9 The configuration described above (in which most of the first burner assembly 17 is controlled or deactivated) has a beneficial effect on the turndown of the gas turbine engine.

[0043] In another example, such as Figure 10 and Figure 11 As illustrated, the first group of first burner assemblies 17 defines an alternation pattern. In this case, the alternation pattern may include: a first configuration, for example, wherein four first burner assemblies 17 located on one side of the first-stage supply system 11 receive a first main fuel flow rate FM1 (… Figure 10); and a second configuration, for example, wherein four first burner assemblies 17 located on the opposite side of the first-stage burner 3 receive a first main fuel flow rate FM1 ( Figure 11 ).

[0044] The second burner assembly 30 of the second-stage burner 7 can also be enabled and disabled according to an alternation mode. For example, the alternation mode may include: a first configuration, for example, in which only four lower second burner assemblies 30 are enabled ( Figure 10 ); and a second configuration, for example, in which only four upper second burner assemblies 17 are activated ( Figure 11 ).

[0045] In one embodiment (not shown), all second burner assemblies 30 can be deactivated before fuel reduction of the main burner 20 of the first burner assembly 17 begins; that is, the first group of second burner assemblies 30 is idle (void).

[0046] According to Figure 12 In another embodiment illustrated together with the annular combustion chamber 15 of the first-stage burner 3, the first supply system, indicated herein by 111, includes a pilot branch and a main branch. The pilot branch includes a pilot supply line 121, a pilot valve 122, and a pilot gas chamber 123. The pilot valve 122 is controlled by a controller 10 and has an inlet connected to the pilot supply line 121 and an outlet connected via the pilot gas chamber 123 and a conduit 124 to each of the pilot burners 18 of the first burner assembly 17.

[0047] The main branch of the first-stage supply system 111 includes a main supply line 125, a first main valve 127, a second main valve 128, a first main gas chamber 129, and a second main gas chamber 130. The first main valve 127, controlled by the controller 10, has an inlet connected to the main supply line 125 and an outlet connected to the first main gas chamber 129, which is further connected via a conduit 126 to the main burners 20 of the first group of first burner assemblies 17. The second main valve 128, controlled by the controller 10, has an inlet connected to the main supply line 125 and an outlet connected to the second main gas chamber 130, which is further connected to the main burners 20 of the second group of first burner assemblies 17, which are complementary to the first group. Each of the first and second groups includes two adjacent groups of first burner assemblies 17 arranged opposite each other relative to the longitudinal axis A.

[0048] Once the first group of second burner assemblies 30 has been deactivated, the controller operates the first main valve 127 to supply a first main fuel flow rate FM1, which is lower than the full-load flow rate and lower than the second value, to the main burner 20 of the first group of first burner assemblies 17. The main burner 20 of the second group of first burner assemblies 17 continuously receives the second value of the first main fuel flow rate FM1. This allows the load to be reduced to a very low level without affecting frequency response and emissions compliance.

[0049] exist Figure 13 In another embodiment illustrated herein, the main branch of the first-level supply system, indicated by 211, is configured to implement... Figure 10 and Figure 11 In the static mode control or such Figure 8 and Figure 9 The alternating mode control in the middle further implements the alternating mode of the upper and lower first burner assemblies 17. The first-stage supply system 211 includes a main supply line 225, two first main valves 227, two second main valves 228, two first main gas chambers 229, and two second main gas chambers 230. Each first main gas chamber 229, for example, supplies gas to the corresponding side of the first-stage burner 3. Figure 8 and Figure 9 The first burner assembly 17 in the first stage burner 3 is supplied with fuel. A first main valve 227 is independently controlled by a controller 10, and each main supply line 225 is connected to a corresponding first main gas chamber 229. Similarly, two second main gas chambers 230 supply fuel to the first burner assembly 17 in the upper and lower portions of the first stage burner 3, respectively. A second main valve 228 is independently controlled by a controller 10, and each main supply line 225 is connected to a corresponding second main gas chamber 230. Figure 13 Pilot supply line 221, pilot valve 222, pilot air chamber 223, and conduit 224 are also shown.

[0050] Therefore, it is possible to drive the first-stage burner 3 according to a four-stage alternating mode in which the first main fuel flow rate FM1 is sequentially supplied to the first burner assembly 17 in the groups on one side, the opposite side, the upper part and the lower part of the first-stage burner 3.

[0051] exist Figure 14In the embodiment illustrated, the main branch of the first-stage supply system 311 includes a main supply line 325, a first main valve 327, a second main valve 328, a first main gas chamber 329, and a second main gas chamber 330. The first main valve 327, controlled by the controller 10, has an inlet connected to the main supply line 325 and an outlet connected to the first main gas chamber 329, which is further connected via a conduit 326 to the main burners 20 of a first group of first burner assemblies 17. The first group includes eight first burner assemblies 17 located below the first-stage burner 3. The second main valve 328, controlled by the controller 10, has an inlet connected to the main supply line 325 and an outlet connected to the second main gas chamber 330, which is further connected to the main burners 20 of a second group of first burner assemblies 17 that complement the first group. Figure 14 Pilot supply line 321, pilot valve 322, pilot air chamber 323, and conduit 324 are also shown. Figure 14 The embodiments are implemented in a structurally simple yet effective manner. Figure 8 and Figure 9 The pattern.

[0052] Ultimately, it is apparent that the described gas turbine engine and method of controlling the gas turbine engine can be modified and varied without departing from the scope of the invention as defined in the appended claims.

[0053] Specifically, the number and distribution of the first burner assemblies forming the first group can be selected according to design preferences, or where the first burner assemblies can be individually controlled, or even depending on the situation. For example, the number of the first burner assemblies in the first group can vary based on the current load request.

[0054] Furthermore, the first burner assembly 17 can be selected in any static or variable mode, including a rotating mode, to receive the first main fuel flow rate, depending on design preferences.

Claims

1. A gas turbine engine, comprising: A first-stage burner (3) having multiple first burner assemblies (17); A second-stage burner (7) having multiple second burner assemblies (30) is located downstream of the first-stage burner (3); A fuel supply system (9) configured to supply a corresponding first fuel flow rate (FM1) to each first burner assembly (17) and a corresponding second fuel flow rate (FM2) to each second burner assembly (30); A controller (10) configured to control the first fuel flow rate (FM1) and the second fuel flow rate (FM2); The controller (10) is further configured to selectively enable and disable the second burner assembly (30) and, under partial load operating conditions when at least the first group of the second burner assemblies (30) is inactive, supply the first fuel flow rate (FM1) of a first value to the first group of the first burner assemblies (17) and supply the first fuel flow rate (FM1) of a second value to the second group of the first burner assemblies (17), wherein the first fuel flow rate (FM1) of the first value is lower than the first fuel flow rate (FM1) of the second value or is zero.

2. The gas turbine engine according to claim 1, wherein, The controller (10) is further configured to supply the first fuel flow rate (FM1) of the first value to the first group of the first burner assemblies (17) when the second group of the second burner assemblies (30) is active.

3. The gas turbine engine according to claim 1, wherein, The controller (10) is further configured to supply the first fuel flow rate (FM1) of the first value to the first group of the first burner assemblies (17) when all the second burner assemblies (30) are inactive.

4. The gas turbine engine according to any one of the preceding claims, wherein, The composition of the first burner assembly (17) in the first group changes from the first part of the load operating conditions to the second part of the load operating conditions.

5. The gas turbine engine according to claim 1, wherein, Each of the first burner assemblies (17) includes a corresponding main burner (20) and a corresponding pilot burner (18), wherein the fuel supply system (9) is configured to supply the main burner (20) with the corresponding first fuel flow rate (FM1) and to supply the pilot burner (18) with a pilot fuel flow rate.

6. The gas turbine engine according to claim 5, wherein, The fuel supply system (9) includes: a first-stage supply system (11; 111; 211; 311) connected to the first-stage burner (3) and controlled by the controller (10) to supply the first fuel flow rate (FM1) to the first burner assembly (17); and a second-stage supply system (12) connected to the second-stage burner (7) and controlled by the controller (10) to supply the second fuel flow rate (FM2) to the second burner assembly (30).

7. The gas turbine engine according to claim 6, wherein, The first-stage supply system (11) includes: a main supply line (25) connected to the main burner (20) of the first group of first burner assemblies (17); and a plurality of first main valves (27) independently controlled by the controller (10), each having an inlet connected to the main supply line (25) and an outlet connected to a corresponding one of the main burners (20) of the first group of first burner assemblies (17).

8. The gas turbine engine according to claim 6, wherein, The first-level supply system (111; 211; 311) includes: a main supply line (125; 225; 325) connected to the main burner (20) of the first group of first burner assemblies (17); at least a first main valve (127; 227; 327) controlled by the controller (10) and having an inlet connected to the main supply line (125; 225; 325) and an outlet connected to the main burner (20) of the first group of first burner assemblies (17); And at least a second main valve (128; 228), which is controlled by the controller (10) and has an inlet connected to the main supply line (125; 225; 325) and an outlet connected to the main burner (20) of the second set of first burner assemblies (17), the second set of first burner assemblies (17) being complementary to the first set of first burner assemblies (17).

9. The gas turbine engine according to claim 6, wherein, The first-stage supply system (11; 111; 211; 311) includes: a pilot supply line (21; 121; 221; 321) configured to supply a pilot fuel flow rate (FP) to the pilot burner (18) of the first burner assembly (17); and a pilot valve (22; 122; 222; 322) controlled by the controller (10) and having an inlet connected to the pilot supply line (21; 121; 221; 321) and an outlet connected to the pilot burner (18) of the first burner assembly (17); and wherein the controller (10) is configured to maintain the pilot fuel flow rate (FP) when the first fuel flow rate (FM1) of the first value is supplied to the first set of the first burner assemblies (17).

10. The gas turbine engine according to claim 5, wherein, The controller (10) is further configured to simultaneously or sequentially shut off the main burner (20) of the first group of first burner assemblies (17) under the partial load operating conditions.

11. The gas turbine engine according to claim 1, wherein, The first-stage burner (3) includes a first annular combustion chamber (15), and the second-stage burner (7) includes a second annular combustion chamber (29), wherein the first burner assembly (17) and the second burner assembly (30) are arranged circumferentially around an axis (A).

12. A method for controlling a gas turbine engine, the gas turbine engine comprising a first-stage combustor (3) having a plurality of first burner assemblies (17) and a second-stage combustor (7) having a plurality of second burner assemblies (30) located downstream of the first-stage combustor (3); The method includes: A corresponding first fuel flow rate (FM1) is supplied to each first burner assembly (17), and a corresponding second fuel flow rate (FM2) is supplied to each second burner assembly (30); Selectively enable and disable the second burner assembly (30); as well as Under a first load operating condition when at least the first group of the second burner assemblies (30) is inactive, a first value of the first fuel flow rate (FM1) is supplied to the first group of the first burner assemblies (17), and a second value of the first fuel flow rate (FM1) is supplied to the second group of the first burner assemblies (17), wherein the first value of the first fuel flow rate (FM1) is lower than the second value of the first fuel flow rate (FM1) or is zero.

13. The method of claim 12, further comprising supplying the first fuel flow rate (FM1) of the first value to the first group of the first burner assemblies (17) when the second group of the second burner assemblies (30) is active.

14. The method of claim 12, further comprising supplying the first fuel flow rate (FM1) of the first value to the first group of the first burner assemblies (17) when all the second burner assemblies (30) are inactive.

15. The method according to any one of claim 12 or 14, comprising: From the basic load operating condition where all of the second burner assemblies (30) are active, the first group of second burner assemblies (30) is deactivated until the load threshold is reached; as well as After the load threshold has been reached, the first fuel flow rate (FM1) of the first value is supplied to at least the first set of the first burner assemblies (17).

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