Methods of operating a burner with a variable combustion chamber

Abstract

A method of operating a combustor for a gas turbine, the combustor including a combustor liner defining a total combustion chamber volume and having a primary combustion zone defining a primary volume. The combustor liner includes a movable portion arranged to be actuated to adjust the percentage of the primary volume relative to the total combustion chamber volume. The method includes, in a first operating state of the gas turbine, adjusting the size of the primary volume to a first percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume, and in a second operating state of the gas turbine, different from the first operating state, adjusting the size of the primary volume to a second percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume.

Description

Technical Field

[0001] This disclosure relates to a combustion chamber in a gas turbine. More specifically, this disclosure relates to a method of operating a variable contraction-expansion combustion chamber that adjusts the volume of the primary combustion zone throughout the various operating states of the gas turbine. Background Technology

[0002] In conventional gas turbine engines, a combustor liner is provided to define the combustion chamber. The combustion chamber is generally defined by a primary combustion zone and a mixer assembly at the front end of the combustion chamber closest to the fuel nozzle. The mixer assembly injects a fuel-air mixture into the combustion chamber, where the fuel-air mixture is ignited and burned to form combustion gases. The combustion chamber may also include a dilution zone downstream of the primary combustion zone, where dilution air is supplied through the combustor liner to quench the combustion gases. The combustion chamber may further include a secondary combustion zone, where the quenched combustion gases are further mixed with the dilution air before flowing through the turbine nozzles into the turbine section of the gas turbine engine. Typically, the combustor liner has a fixed length and geometry, such that the various zones of the combustion chamber (e.g., primary zone, dilution zone, secondary zone) have fixed volumes for operation in all various operating conditions, such as startup, takeoff, cruise, and approach. Summary of the Invention

[0003] This disclosure provides a method of operating a combustor for a gas turbine, the combustor including a combustor liner defining a combustion chamber therein, the combustion chamber defining a total combustion chamber volume, the combustion chamber including a primary combustion zone at an upstream end of the combustion chamber defining a primary volume, the combustor liner including a movable portion arranged to be actuated to adjust the percentage of the primary volume relative to the total combustion chamber volume, the method comprising: in a first operating state of the gas turbine, adjusting the size of the primary volume to a first percentage of the total combustion chamber volume by actuating the movable portion; and in a second operating state of the gas turbine different from the first operating state, adjusting the size of the primary volume to a first percentage of the total combustion chamber volume by actuating the movable portion. The size is adjusted to a second percentage of the total combustion chamber volume, wherein the movable portion of the burner liner includes a contraction-expansion portion extending into the combustion chamber and having at least one dilution opening therethrough, the contraction-expansion portion being arranged in the dilution zone of the combustion chamber downstream of the primary combustion zone, wherein the burner liner includes an upstream liner section fixedly mounted in the burner and a downstream liner section fixedly mounted in the burner, a gap being present between the upstream liner section and the downstream liner section, the contraction-expansion portion extending across the gap and engaging with the upstream liner section and the downstream liner section, wherein the translation of the diluted oxidant flow in the upstream and downstream directions through the contraction-expansion portion and through the dilution opening aerodynamically and / or structurally adjusting the percentage of the primary volume. Attached Figure Description

[0004] The features, advantages, and embodiments of this disclosure will become apparent from the following more detailed description of various exemplary embodiments as shown in the accompanying drawings, wherein similar reference numerals denote substantially the same, functionally similar, and / or structurally similar elements.

[0005] Figure 1 This is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine according to an embodiment of the present disclosure.

[0006] Figure 2 This is a cross-sectional side view of an exemplary combustion section according to an embodiment of the present disclosure.

[0007] Figure 3 It is based on one aspect of this disclosure. Figure 2 A detailed view of the burner lining and shrinkage / expansion section, taken at point 100.

[0008] Figure 4 It is based on one aspect of this disclosure. Figure 2 A detailed view of the burner lining and shrinkage / expansion section, taken at point 100.

[0009] Figure 5 It is based on one aspect of this disclosure. Figure 2 A detailed view of the burner lining and shrinkage / expansion section, taken at point 100.

[0010] Figure 6 It is based on another aspect of this disclosure. Figure 2 A detailed view of the burner lining and shrinkage / expansion section, taken at point 100.

[0011] Figure 7 It is based on another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 164 in the detailed view.

[0012] Figure 8 It is based on one aspect of this disclosure. Figure 7 The view Figure 8-8 A top view of a portion of the diluted lining section captured at the location.

[0013] Figure 9 It is based on another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 164 in the detailed view.

[0014] Figure 10 It is based on yet another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 164 in the detailed view.

[0015] Figure 11 It is based on another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 164 in the detailed view.

[0016] Figure 12 It is based on another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 164 in the detailed view.

[0017] Figure 13 It is based on another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 164 in the detailed view.

[0018] Figure 14 It is based on yet another aspect of this disclosure. Figure 2A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 100 in the detailed view.

[0019] Figure 15 This is a flowchart of the method steps for operating a gas turbine according to one aspect of this disclosure. Detailed Implementation

[0020] Various embodiments are discussed in detail below. Although specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and constructions can be used without departing from the spirit and scope of this disclosure.

[0021] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the components.

[0022] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which fluid flows, and "downstream" refers to the direction from which fluid flows.

[0023] Various features, advantages, and embodiments of this disclosure are set forth or become apparent from consideration of the following detailed description, drawings, and claims. Furthermore, it should be understood that the following detailed description is exemplary and intended to provide further explanation without limiting the scope of the claimed disclosure.

[0024] In conventional gas turbine engines, the combustor liner has a fixed length and geometry, resulting in fixed volumes for the various zones of the combustion chamber (e.g., primary zone, dilution zone, secondary zone) for operation in all operating conditions, such as startup, takeoff, cruise, and approach. However, due to increasingly stringent emission requirements for gas turbine engines, there is a need to continue reducing NOx emissions and achieving more efficient combustion of the fuel-air mixture. This disclosure aims to reduce NOx emissions and improve operability by reducing the overall length of the combustion chamber and adjusting the volume of the primary combustion zone throughout all operating conditions. According to this disclosure, the combustor liner includes a translational contraction-expansion section in the dilution zone. The contraction-expansion section can be translated in both upstream and downstream directions based on power variations throughout all operating conditions by an actuator to adjust the volume of the primary combustion zone. For example, during ground startup, the contraction-expansion section can be actuated to adjust the size of the primary combustion zone to a first percentage of the overall total combustion chamber volume. Then, during takeoff and climb when power demand increases, the contraction-expansion section is actuated to adjust the primary combustion zone volume to a second percentage, which can be smaller than the first percentage, thus making the primary combustion zone smaller. Therefore, a smaller primary combustion zone allows for more efficient combustion of the fuel-air mixture in the primary combustion zone during high-power operation, while simultaneously increasing the downstream secondary volume, thereby providing a longer period for the combustion gases to mix with the dilution air. As a result, combustor operability and efficiency can be increased, and emissions can be reduced.

[0025] Now refer to the attached diagram, Figure 1 This is a schematic partial cross-sectional side view of an exemplary high-bypass turbofan jet engine 10, referred to herein as "engine 10," and can be incorporated into various embodiments of this disclosure. Although this disclosure is further described below with reference to turbofan engines, it is also applicable to general turbomachinery, including turbojet engines, turboprop engines, and turboshaft gas turbine engines, including marine and industrial turbine engines and auxiliary power units. Figure 1 As shown, engine 10 has an axial centerline axis 12 extending from upstream end 98 through it to downstream end 99, for reference. Generally, engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0026] The core engine 16 generally includes a housing 18 defining an annular inlet 20. The housing 18 encloses, or at least partially forms, in a series flow relationship, a compressor section having a turbocharger or low-pressure (LP) compressor and a high-pressure (HP) compressor 24, a combustor 26, a turbine section including a high-pressure (HP) turbine 28 and a low-pressure (LP) turbine 30, and an injection exhaust nozzle section 32. A high-pressure (HP) rotor shaft 34 drives the HP turbine 28 to the HP compressor 24. A low-pressure (LP) rotor shaft 36 drives the LP turbine 30 to the LP compressor 22. The LP rotor shaft 36 may also be connected to the fan shaft 38 of the fan assembly 14. In certain embodiments, such as Figure 1 As shown, the LP rotor shaft 36 can be connected to the fan shaft 38 via a reduction gear 40, such as in an indirect drive configuration or a gear drive configuration. In other embodiments, although not shown, the engine 10 may further include an intermediate pressure (IP) compressor and a turbine capable of rotating with the intermediate pressure shaft.

[0027] like Figure 1 As shown, the fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from the fan shaft 38. An annular fan housing or nacelle 44 circumferentially surrounds the fan assembly 14 and / or at least a portion of the core engine 16. In one embodiment, the nacelle 44 may be supported relative to the core engine 16 by a plurality of circumferentially spaced outlet guide vanes or struts 46. Furthermore, at least a portion of the nacelle 44 may extend over the outer portion of the core engine 16 to define a bypass airflow passage 48 therebetween.

[0028] Figure 2 Is it like this? Figure 1 A cross-sectional side view of an exemplary combustor 26 of the core engine 16 shown. Figure 2 As shown, the combustor 26 generally includes an annular combustor liner 50 and a dome assembly 56. The combustor liner 50 extends circumferentially around the combustor centerline 13 and includes an inner liner 52 and an outer liner 54. The inner liner 52, the outer liner 54, and the dome assembly 56 together define a combustion chamber 62 between them. The combustion chamber 62 may more specifically define various regions, including a primary combustion zone 70 at an upstream end 102 of the combustion chamber 62, where the initial chemical reaction of the fuel-oxidant mixture 85 and / or the recirculation of the combustion gases 86 may occur before flowing further downstream to a dilution zone 72, where the mixing and / or recirculation of the combustion gases 86 and air may occur before flowing to a secondary combustion zone 74 at a downstream end 104 of the combustion chamber 62, where combustion products flow into the turbine nozzle 29. The dome assembly 56 extends radially between the upstream end 76 of the outer liner 54 and the upstream end 77 of the inner liner 52.

[0029] like Figure 2 As shown, the outer liner 54 can be enclosed within the outer housing 64, and the inner liner 52 can be enclosed within the inner housing 65. An outer flow passage 68 is defined between the outer housing 64 and the outer liner 54, and an inner flow passage 69 is defined between the inner housing 65 and the inner liner 52. The inner liner 52 can extend from an upstream end 77 at the dome assembly 56 to a downstream end 67 at the turbine nozzle 29. The outer liner 54 can extend from an upstream end 76 at the dome assembly 56 to a downstream end 66 at the turbine nozzle 29. Therefore, the outer liner 54 and the inner liner 52 at least partially define the hot gas path between the combustor liner 50 and the turbine nozzle 29.

[0030] For example, further Figure 2 As seen below, the inner liner 52 may include a plurality of dilution openings 90, and the outer liner 54 may include a plurality of dilution openings 88. As will be described in more detail below, the dilution openings 88 and 90 provide a flow of compressed air 82(c) passing through them and entering the combustion chamber 62. Therefore, the flow of compressed air 82(c) as dilution air can be used to provide quenching of the combustion gases 86 in the dilution zone 72 downstream of the primary combustion zone 70, in order to cool the flow of combustion gases 86 entering the turbine nozzle 29.

[0031] During the operation of engine 10, such as Figure 1 and Figure 2 As shown, a certain amount of air 73, as indicated by the arrow, enters the engine 10 from the upstream end 98 through the associated inlet 75 of the nacelle 44 and / or fan assembly 14. As the air 73 passes through the fan blades 42, a portion of the air, as indicated by arrow 78, is directed or directed into the bypass airflow passage 48, while another portion, as indicated by arrow 80, is directed or directed into the LP compressor 22 via the annular inlet 20. The portion 80 of air entering the annular inlet 20 is gradually compressed as it flows through the LP compressor 22 and the HP compressor 24 towards the combustor 26. Figure 2 As shown, as indicated by arrow 82, the compressed air now flows into the diffuser cavity 84 of the burner 26.

[0032] Compressed air 82 pressurizes the diffuser chamber 84. A first portion of the compressed air 82, schematically indicated by arrow 82(a), flows from the diffuser chamber 84 into the pressure chamber 59. This first portion of the compressed air 82 is then swirled through the mixer assembly 60 and mixed with fuel supplied by the fuel nozzle assembly 58 to produce a swirling fuel-oxidizer mixture 85, which is then ignited and burned, thereby producing combustion gases 86 within the primary combustion zone 70 of the burner liner 50. Typically, the LP compressor 22 and HP compressor 24 supply more compressed air 82 to the diffuser chamber 84 than is required for combustion. Therefore, a second portion of the compressed air 82, schematically indicated by arrow 82(b), can be used for various purposes other than combustion. For example, as... Figure 2 As shown, a second portion of the compressed air 82 can be directed into the outer flow passage 68 and the inner flow passage 69. A portion of this second portion of the compressed air 82 can then be directed through the dilution opening 88 (schematically shown as compressed air 82(c)) and into the dilution zone 72 of the combustion chamber 62 to provide quenching of the combustion gases 86 in the dilution zone 72 and to introduce turbulence into the flow of the combustion gases 86, thereby providing better mixing of the compressed air 82(c) with the combustion gases 86. A similar flow of compressed air 82(c) from the inner flow passage 69 flows through the dilution opening 90 and into the dilution zone 72. Alternatively or additionally, at least a portion of the second portion of the compressed air 82 can be directed out of the diffuser cavity 84 and can be directed through various flow passages (not shown) to provide cooling air to at least one of the HP turbine 28 or the LP turbine 30.

[0033] Return to common reference Figure 1 and 2 The combustion gases 86 generated in the combustion chamber 62 flow from the burner liner 50 into the HP turbine 28 via the turbine nozzle 29, thereby rotating the HP rotor shaft 34 and supporting the operation of the HP compressor 24. Figure 1 As shown, the combustion gases 86 are then directed through the LP turbine 30, thereby rotating the LP rotor shaft 36 to support the operation of the LP compressor 22 and / or the rotation of the fan shaft 38. The combustion gases 86 are then discharged through the injection exhaust nozzle section 32 of the core engine 16 to provide propulsion at the downstream end 99.

[0034] As will be described in more detail below, the burner liner 50 includes an outer liner contraction-expansion section 92 and an inner liner contraction-expansion section 94. Both the outer liner contraction-expansion section 92 and the inner liner contraction-expansion section 94 extend into the dilution zone 72 of the combustion chamber 62. It can be seen that a dilution opening 88 extends through the outer liner contraction-expansion section 92, and it can be seen that a dilution opening 90 extends through the inner liner contraction-expansion section 94. Furthermore, both the outer liner contraction-expansion section 92 and the inner liner contraction-expansion section 94 are connected to corresponding actuators 96. The corresponding actuators 96 drive the outer liner contraction-expansion section 92 and the inner liner contraction-expansion section 94 in both upstream and downstream directions (i.e., upstream of the upstream ends 76, 77, or downstream of the downstream ends 66, 67). As a result, the size (volume) of the primary combustion zone 70 and the secondary combustion zone 74 can be adjusted by shifting the contraction-expansion sections 92, 94.

[0035] Figure 3 It is based on one aspect of this disclosure. Figure 2 A detailed view, taken at point 100, showing a partial cross-sectional side view of the burner liner and contraction / expansion section. Figure 3 The diagram depicts a configuration in which an outer liner 54 and an inner liner 52 are two-part liners, with contraction-expansion sections 92 and 94 connecting the separate liner portions. More specifically, it can be seen that the outer liner 54 includes an upstream liner section 106 and a downstream liner section 108. Both the upstream liner section 106 and the downstream liner section 108 are fixedly connected within the burner 26, with a gap 114 between them. The upstream liner section 106 and the downstream liner section 108, together with the gap 114, extend circumferentially around the burner centerline 13. Similarly, the inner liner 52 includes an upstream liner section 110 and a downstream liner section 112, both of which are also fixedly connected within the burner 26, with a gap 116 between them. Extending across the gap 114 is a dilution liner section 120. Figure 3In this aspect, the diluent liner section 120 constitutes the outer liner shrinkage-expansion section 92. The entire diluent liner section 120 constitutes a movable portion, and the upstream end 125 of the diluent liner section 120 is slidably engaged with the upstream liner section 106, while the downstream end 127 of the diluent liner section 120 is slidably engaged with the downstream liner section 108. A seal 121 may be disposed between the upstream end 125 and the upstream liner section 106 of the diluent liner section 120, and may also be disposed between the downstream end 127 and the downstream liner section 108 of the diluent liner section 120. Similarly, extending across the gap 116 is the diluent liner section 122, which constitutes the inner liner shrinkage-expansion section 94. The entire diluent liner section 122 constitutes a movable portion, with its upstream end 129 slidably engaged with the upstream liner section 110, and its downstream end 131 slidably engaged with the downstream liner section 112. A seal 123 may be disposed between the upstream end 129 and the upstream liner section 110 of the diluent liner section 122, and also between the downstream end 131 and the downstream liner section 112. Further arrangements of the diluent liner sections 120 and 122 will be described below.

[0036] The dilution liner section 120 is a movable portion that translates in the upstream direction 118 and the downstream direction 124. Translation is controlled by an actuator 96 connected to an actuator connection member 126 of the dilution liner section 120. Of course, multiple actuators 96 can be disposed in the burner 26 and can be circumferentially spaced around the burner centerline 13. The actuator 96 can be, for example, a pneumatic or hydraulic actuator with an extension / retraction link 128 attached to the actuator connection member 126. For example, the actuator 96 can be fixedly mounted to the upstream liner section 106 via an actuator support member 130, or it can be mounted to the housing 64. Figure 2 Similarly, the dilution liner section 122 is a movable portion that translates in the upstream direction 118 and the downstream direction 124. Translation is controlled by an actuator 132, which is connected via a link 136 to an actuator connection member 134 of the dilution liner section 122. The actuator 132 may have the same structure as the actuator 96 (i.e., the same pneumatic or hydraulic actuator) and may be fixedly mounted to the downstream liner section 112 via a support member 138, or may be mounted to the inner housing 65. Figure 2Actuator 96 is shown connected to the upstream side of dilution liner section 120, but it can alternatively be connected to the downstream side of dilution liner section 120, similar to actuator 132. Similarly, while actuator 132 is shown connected to the downstream side of dilution liner section 122, it can alternatively be connected to the upstream side of dilution liner section 122, similar to actuator 96.

[0037] In operation, dilution liner sections 120 and 122, or, as described below, movable portions of dilution liner section 120 and 122, are actuated by actuators 96 and 132 to adjust the primary volume (PV) (i.e., the volume of the primary combustion zone 70) relative to the total combustion chamber volume (V) throughout all operating states of the engine 10. T The percentage of ). In Figure 3 As can be seen, the primary volume (PV) generally corresponds to the volume defined by the primary region between the downstream surface 140 of the dome 57, the inner surface 142 of the outer liner upstream liner section 106, the upstream surface 144 of the dilution liner section 120, the primary volume boundary line 146 extending through the combustion chamber 62, the upstream surface 148 of the inner liner dilution liner section 122, and the inner surface 150 of the inner liner upstream liner section 110, which is then circumferentially truncated around the burner centerline 13. Similarly, the secondary volume (SV) (i.e., the volume of the secondary combustion zone 74) can be defined by the downstream surface 152 of the dilution liner section 120, the inner surface 154 of the downstream liner section 108, the outlet boundary line 156 of the combustion chamber 62, and the primary region between the downstream surface 140 of the dome 57, the inner surface 142 of the outer liner upstream liner section 106, the upstream surface 144 of the dilution liner section 120, the primary volume boundary line 146 extending through the combustion chamber 62 ... Figure 2 The secondary region defined by the inner surface 158 of the downstream lining section 112, the downstream surface 160 of the dilution lining section 122, and the secondary volume boundary line 162, wherein this secondary region is then circumferentially truncated around the burner centerline 13. Total volume (V T The volume includes the primary volume (PV) and the secondary volume (SV), as well as the volume of the dilution zone 72, which can be generally defined as the dilution region between the primary volume boundary 146, the inner surface 165 of the dilution zone 72 of the dilution liner section 120, the secondary volume boundary 162, and the inner surface 167 of the dilution zone 72 of the dilution liner section 122, wherein the dilution region is then circumferentially truncated around the burner centerline 13.

[0038] In what can be considered a neutral position, dilution liner section 120 and dilution liner section 122 are actuated by their respective actuators 96 and 132 to define a neutral primary volume (PV). N ),like Figure 3 As shown. Neutral primary volume (PV) N This could be, for example, the total burner volume V.T Forty percent. Then, during operation, in the first operating state of engine 10, such as during ground start-up of engine 10, the size of the primary volume (PV) is adjusted by actuating actuators 96 and 132 to translate the dilution liner section 120 and dilution liner section 122 in the upstream direction 118 or the downstream direction 124, thereby setting the primary volume as a first percentage (V) of the total volume. T For example, such as Figure 4 As seen, actuator 96 is actuated to retract link 128 to translate the dilution liner section 120 in the upstream direction 118, and actuator 132 is actuated to extend link 136 to translate the dilution liner section 122 in the upstream direction 118. In this case, the primary volume (PV) N The primary volume (PV1) is reduced to define a smaller primary volume. The primary volume (PV1) is mechanically or structurally reduced by shifting the upstream surface 144 of the dilution liner section 120 in the upstream direction 118, and by shifting the upstream surface 148 of the dilution liner section 122 in the upstream direction 118. The primary volume (PV1) is also aerodynamically reduced by shifting the dilution openings 88 and 90 in the upstream direction 118, which shifts the compressed air 82(c) in the upstream direction 118 so that the primary volume boundary line 146 is shifted in the upstream direction 118. In the same manner, the size of the secondary volume (SV) is reduced from the secondary volume (SV). N The volume (SV1) is increased to a larger volume. Therefore, as an example, during ground initiation, the first percentage of the primary volume (PV) can be set to have a total volume (V). T The range is 40% to 60%. Alternatively, the first operating state can be considered as an altitude re-ignition state, and actuators 96 and 132 can be controlled to set the primary volume to have a total volume (V). T The range is between 40% and 70%.

[0039] Alternatively, such as Figure 5 As seen, actuator 96 is actuated to extend link 128 to translate dilution liner section 120 in the downstream direction 124, and actuator 132 is actuated to retract link 136 to translate dilution liner section 122 in the downstream direction 124. In this case, the primary volume (PV) NThe primary volume (PV2) is increased to define a larger primary volume. The primary volume (PV2) is mechanically or structurally increased by the displacement of the upstream surface 144 of the dilution liner section 120 in the downstream direction 124, and by the displacement of the upstream surface 148 of the dilution liner section 122 in the downstream direction 124. The primary volume (PV2) is also aerodynamically increased by displacing the dilution openings 88 and 90 in the downstream direction 124, which displaces the flow of compressed air 82(c) in the downstream direction 124, thereby displacing the primary volume boundary line 146 in the downstream direction 124. In the same manner, the size of the secondary volume (SV) is increased from the secondary volume (SV). N This reduces the volume to a smaller size (SV2).

[0040] Continue with engine 10 ( Figure 1 In various operating states of the gas turbine, when the primary volume (PV) has already been set based on a first operating state as ground start-up, for example, in a second operating state of the gas turbine different from the first operating state, such as during takeoff or climb operations, actuators 96 and 132 are controlled to translate the dilution liner section 120 and dilution liner section 122 in the upstream direction 118 or the downstream direction 124, so as to set the primary volume (PV) to the total volume (V). T The second percentage, where the second percentage can have the total volume (V) T The NOx emissions range from 30% to 40%. Therefore, during takeoff or climb, when the combustion gases may be hot due to the higher power applied to the engine, reducing the size of the primary stage can quickly and effectively cool the hot gases, thereby reducing NOx emissions.

[0041] In another example, in a third operating state of the gas turbine, different from the first operating state (ground start-up or altitude re-ignition) and the second operating state (take-off or climb), such as in a cruise operating state, actuators 96 and 132 can be controlled to adjust the size of the primary volume (PV) to the total volume (V). T The third percentage for cruise operation status. The third percentage for cruise operation status can have a total volume (V). T The range is 30% to 50%. Furthermore, in a fourth operating state of the gas turbine, different from the first operating state (ground start-up or altitude re-ignition), the second operating state (takeoff or climb), and the third operating state (cruise), such as during a landing approach operating state, actuators 96 and 132 are controlled to adjust the size of the primary volume (PV) to the total volume (V). T The fourth percentage. The fourth percentage used for landing approach operations can have a total volume (V). TThe range is between 30% and 50%.

[0042] Now regarding Figures 6 to 13 To describe the various alternative arrangements for the diluted lining section. Figure 6 It is based on another aspect of this disclosure. Figure 2 A detailed view of the burner lining and shrinkage / expansion section, taken at point 100. Figure 6 The layout and Figure 3 The similarity in their arrangement lies in the fact that both the dilution lining section 120 and the dilution lining section 122 are generally movable parts. However, in Figure 6 In the arrangement, it can be seen that the dilution liner section 120 is arranged to engage with the inner surface 142 of the upstream liner section 106 and the inner surface 154 of the downstream liner section 108. Similarly, it can be seen that the dilution liner section 122 is arranged to engage with the inner surface 150 of the upstream liner section 110 and the inner surface 158 of the downstream liner section 112. The dilution liner section 120 can be coupled to the above-mentioned... Figures 3 to 5 The same manner described applies, translating in the upstream direction 118 and the downstream direction 124. Similarly, the dilution liner section 122 can be moved via actuator 132 in accordance with the above-described manner. Figures 3 to 5 The same manner described applies to translation in the upstream direction 118 and the downstream direction 124. Although Figure 6 Not shown in the image, but such an arrangement can be implemented, such as... Figure 6 As shown, the upstream end 113 of the dilution lining section 120 is joined to the inner surface 142 of the upstream lining section 106, but at the downstream end 115 of the dilution lining section 120, the downstream surface 152 of the dilution lining section 120 is joined to the outer surface 109 of the downstream lining section 108. Similarly, as Figure 6 As shown, the downstream end 117 of the dilution lining section 122 can be engaged with the inner surface 158 of the downstream lining section 112, but at the upstream end 119 of the dilution lining section 122, the upstream surface 148 of the dilution lining section 122 can be engaged with the outer surface 111 of the upstream lining section 110.

[0043] Figure 7 It is based on another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 164 in the detailed view. Figures 3 to 6 In the detailed view 100, the arrangement of both the outer lining 54 side of the dilution lining section 120 and the inner lining 52 side of the dilution lining section 122 is depicted. The depiction of both the outer lining 54 side and the inner lining 52 side is provided to illustrate how the primary volume is adjusted by the synergistic action of both sides. In the following... Figures 7 to 13 The description only describes the dilution lining section for one side (outer lining 54 side), but it should be understood that the various constructions described below also apply to the inner lining 52 side of the burner lining 50.

[0044] Figure 7 An arrangement of the dilution liner section 166, which can be implemented as a box-type slider arrangement, is depicted. Figure 4 The outer lining 54 is implemented as a two-piece lining (i.e., the upstream lining section 106 and the downstream lining section 108, with a gap 114 between them) in the opposite arrangement. Figure 7 The outer liner 54 is implemented as a single liner without gaps 114. Therefore, the upstream liner section 106 and the downstream liner section 108 are connected to the dilution liner 168, which is a fixed portion of the dilution liner section 166. Boundary line 170 indicates the connection between the upstream liner section 106 and the dilution liner 168, and boundary line 172 indicates the connection between the downstream liner section 108 and the dilution liner 168. The dilution liner section 166 further includes a box-type slider 174, which may also be referred to as a movable portion of the dilution liner section 166. The box-type slider 174 may be implemented as a contraction-expansion member 179 similar to that of the dilution liner section 120, extending into the combustion chamber 62. The box-type slider 174 may include a transverse member 175, which forms a cavity 176 therein. The transverse member 175 has an opening 177 therethrough, and the contraction-expansion member 179 includes at least one dilution opening 178 extending through the box-type slider 174. The dilution opening 178 may be similar to the dilution opening 88 of the dilution liner section 120. It can be seen that the dilution liner 168 includes a slotted opening 180 therethrough. Figure 8 Is Figure 7 The view Figure 8-8 A top view of a portion of the dilution liner section 166, taken at the point of view, depicts an example of a slotted opening 180 extending through the dilution liner 168. Thus, compressed air 82(c) can pass through the slotted opening 180 and enter the cavity 176 via the opening 177, and then enter the dilution zone 72 through the dilution opening 178 of the contraction expansion member 179.

[0045] The box slider 174 also includes an actuator connecting member 182 connected to the transverse member 175. The linkage 128 of the actuator 96 is connected to the actuator connecting member 182 to allow the box slider 174 to translate in the upstream direction 118 and the downstream direction 124. The transverse member 175 is slidably engaged with the inner surface 173 of the upstream liner section 106, the downstream liner section 108, and the dilution liner 168. Therefore, the primary volume (PV) is adjusted by actuation of the box slider 174 in both the upstream direction 118 and the downstream direction 124 in a manner similar to that described above.

[0046] Figure 9 It is based on another aspect of this disclosure. Figure 2 A detailed view, taken at point 164, showing a partial cross-sectional side view of the burner liner and contraction / expansion section. Figure 9 In this configuration, the contraction-expansion portion 185 of the dilution liner section 184 can be arranged as a separate unit. The dilution liner section 184 includes a fixed portion 192 that includes an expansion portion 188 connected to the upstream end 194 of the downstream liner section 108 and extending into the combustion chamber 62. The expansion portion 188 is fixed to the downstream liner section 108 and can be integrally formed with the downstream liner section 108. The dilution liner section 184 also includes a movable portion 186 that includes a contraction portion 190 extending into the combustion chamber 62. The contraction portion 190 of the movable portion 186 includes a dilution opening 200 therethrough. The contraction portion 190 slidably engages with the expansion portion 188 of the fixed portion 192 of the dilution liner section 184, with a seal 121 therebetween. The upstream end 196 of the movable portion 186 slidably engages with the upstream liner section 106, with a seal 121 therebetween.

[0047] Actuator connecting member 198 is connected to movable part 186, and linkage 204 of actuator 202 is connected to actuator connecting member 198. Actuator 202 can be similar to actuator 96. However, in Figure 9 In this aspect, a spring-like device 206 may be included between the actuator 202 and the actuator connecting member 198 to provide a retraction force (i.e., a first translational force) or an extension force (i.e., a second translational force) between the actuator 202 and the actuator connecting member 198. The spring-like device 206 may be, for example, a spring, a bellows, or a sealing device. Although in Figures 3 to 8 While not depicted in any of the figures, the spring-like device 206 can still be implemented in conjunction with either actuator 96 or actuator 132. When the spring-like device 206 applies a retraction force (first translational force), actuator 202 can be actuated to increase the extension pressure, extending link 204 and causing movable portion 186 to translate in the downstream direction 124. The extension pressure in actuator 202 can be released, causing the spring-like device 206 to apply a second translational force to retract link 204, thereby translating movable portion 186 in the upstream direction 118. Therefore, actuator 202 can cause contraction portion 190 to translate in the upstream direction 118 and downstream direction 124, but fixed expansion portion 188 does not translate in either direction. As a result, the size of the primary volume (PV) can be adjusted by actuating movable portion 186. Translation of movable portion 186 also results in adjustment of the dilution volume (DV), while the secondary volume (SV) remains unchanged.

[0048] Figure 10 It is based on another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 164 in the detailed view. Figure 10 The arrangement depicts the dilution lining section 232, which, together with the dilution lining section 184, Figure 9 The arrangement is similar in that the dilution liner section 232 provides a separation unit. However, unlike the expansion section 188, which is fixed to the downstream liner section 108... Figure 9 The arrangement is different, Figure 10 The arrangement includes a movable expansion section 208. In Figure 10 As can be seen, the dilution liner section 232 includes an upstream portion 224, which includes a shrinkage portion 190 and a first transition portion 220 downstream of the shrinkage portion 190. A dilution opening 200 extends through the first transition portion 220. The dilution liner section 232 also includes a downstream portion 226, which includes an expansion portion 208 and a second transition portion 222 upstream of the expansion portion 208. The upstream end 228 of the upstream portion 224 is slidably engaged with the upstream liner section 106, and the downstream end 230 of the downstream portion 226 is slidably engaged with the downstream liner section 108. The first transition portion 220 of the upstream portion 224 and the second transition portion 222 of the downstream portion 226 are slidably engaged with each other.

[0049] The upstream portion 224 includes a first actuator connecting member 199 at the upstream end 228, and the downstream portion 226 includes a second actuator connecting member 210 at the downstream end 230. It can be seen that the actuator 212 is connected to the first actuator connecting member 199 via an upstream link 214, and the actuator 212 is connected to the second actuator connecting member 210 via a downstream link 216. The actuator 212 can be connected to the housing 64 via an actuator support member 218. The actuator 212 can simultaneously actuate both the upstream portion 224 and the downstream portion 226 in opposite directions, or the actuator 212 can individually actuate only one of the upstream portion 224 or the downstream portion 226. Thus, for example, the actuator 212 can be actuated to extend the upstream link 214 to translate the upstream portion 224 in the upstream direction 118, thereby reducing the size of the primary volume (PV), and the downstream portion 226 can be left unacted to maintain the same secondary volume (SV). Alternatively, actuator 212 can be actuated to extend upstream link 214, thereby translating upstream portion 224 in the upstream direction 118, and also extend downstream link 216, thereby translating downstream portion 226 in the downstream direction 124. In this case, the size of the primary volume (PV) decreases, the size of the secondary volume (SV) also decreases, while the size of the dilution volume (DV) increases.

[0050] Figure 11 It is based on another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 164 in the detailed view. Figure 11 In the middle, the diluted lining section 234 is depicted as being in conjunction with... Figure 7 The arrangement is similar to that of the box-type slider. Therefore, the upstream liner section 106 and the downstream liner section 108 are connected via a dilution liner 168, and the dilution liner 168 includes a slotted opening 180 therethrough.

[0051] With the entire contraction and expansion member 179 being movable Figure 7 The arrangements are different, in Figure 11 In this arrangement, the shrinkage-expansion member 236 is fixed to the dilution liner 168 and / or the downstream liner section 108, and the corrugated movable portion 238 is arranged on the upstream side of the shrinkage-expansion member 236. The shrinkage-expansion member 236 is a generally fixed structure and, as an example, can constitute a muffler. Figure 11 As seen, the contraction-expansion member 236 is depicted as a muffler, which includes a muffler inlet feed pipe 240 on the downstream side of the contraction-expansion member 236 and includes a dilution opening 242 for providing a flow of compressed air 82(c) through which it enters the dilution zone 72. The corrugated movable portion 238 may have a corrugated upstream side 246, which is shaped to be substantially aligned with the shape of the upstream side 248 of the contraction-expansion member 236. The corrugated movable portion 238 includes an actuator connecting member 244 attached thereto. The link 128 of the actuator 96 is connected to the actuator connecting member 244. Thus, in operation, the actuator can translate the corrugated movable portion 238 in the upstream direction 118 to reduce the size of the primary volume (PV), or can translate the corrugated movable portion 238 in the downstream direction 124 to increase the size of the primary volume (PV). By implementation Figure 11 The fixed contraction and expansion member 236 in the arrangement maintains a generally constant secondary volume (SV).

[0052] Figure 12 It is based on another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 164 in the detailed view. Figure 12 The text describes the dilution lining section 250, and the dilution lining section 250 and... Figure 11The dilution liner section 234 is somewhat similar in that the dilution liner section 250 comprises a single liner, wherein the upstream liner section 106 and the downstream liner section 108 are connected via a dilution liner 252. The dilution liner 252 may be similar to the dilution liner 168, except that the dilution liner 252 includes a dilution opening 253 instead of a slotted opening 180. Furthermore, Figure 12 The aspect includes a fixed shrinkage-expansion member 254, which is connected to the dilution liner 252 and / or downstream liner section 108, and includes a dilution opening 264 through a transition portion 262 of the fixed shrinkage-expansion member 254. Similar to... Figure 11 In this aspect, the dilution liner section 250 includes a movable portion 256 having a contraction portion 258 and a transition portion 260. The transition portion 260 of the movable portion 256 engages with the transition portion 262 of the fixed contraction-expansion member 254, with a seal 274 therebetween. The upstream end 276 of the movable portion 256 engages with the upstream liner section 106, with a seal 278 therebetween.

[0053] Actuator 266 can be mounted to dilution liner 252 via actuator support member 268. Figure 12 In this embodiment, actuator 266 is shown arranged within a cavity 280 defined by a fixed contraction-expansion member 254, rather than as actuator 96 is located within a cavity 280 defined by a fixed contraction-expansion member 254. Figure 11 The actuator 266 is arranged within the external flow channel 68 as depicted in the diagram. The actuator 266 includes a link 270 connected to the movable portion 256 and may also include a spring-like device 272. Therefore, similar to... Figure 11 In this respect, actuator 266 can translate movable portion 256 in the upstream direction 118 to reduce the size of the primary volume (PV), and can also translate movable portion 256 in the downstream direction 124 to increase the size of the primary volume. Similar to... Figure 11 In terms of volume, the secondary volume (SV) remains constant due to the inclusion of fixed contraction and expansion members 254.

[0054] Figure 13 It is based on another aspect of this disclosure. Figure 2 A partial cross-sectional side view of the burner lining and dilution lining section, taken at point 164 in the detailed view. Figure 13 In the text, a dilution lining section 282, which can be referred to as the ventilated dilution lining section, is depicted. Similar to... Figure 12A single liner is provided, wherein an upstream liner segment 106 and a downstream liner segment 108 are connected by a dilution liner 252, which includes a dilution opening 253 therethrough. A shrinkage-expansion member 283 includes a fixed expansion member 284, which is fixedly mounted to the upstream end 194 of the dilution liner 252 and / or the downstream liner segment 108. The fixed expansion member 284 includes an expansion portion 288 and a transition portion 290, which includes a dilution opening 291 therethrough. The shrinkage-expansion member 283 also includes a shrinkage member 286, which is a movable portion of the shrinkage-expansion member 283. The shrinkage member 286 has a shrinkage portion 292 and a transition portion 294. The upstream end 277 of the shrinkage portion 292 slidably engages with the upstream liner segment 106, with a seal 278 therebetween. A bellows portion 296 is disposed within the contraction-expansion member 283 to connect the transition portion 294 of the contraction member 286 to the transition portion 290 of the expansion member 284. Similar to... Figure 11 In this arrangement, actuator 266 is mounted to dilution liner 252 via actuator support member 268 within cavity 298, and linkage 270 is connected to contraction member 286. Therefore, actuator 266 can be actuated to translate contraction member 286 (i.e., the movable portion) in the upstream direction 118 to reduce the size of the primary volume (PV) and thus increase the volume of cavity 298. Alternatively, actuator 266 can be actuated to translate contraction member 286 in the downstream direction 124 to increase the size of the primary volume (PV) and thus decrease the volume of cavity 298.

[0055] Figure 14 It is based on yet another aspect of this disclosure. Figure 2 A detailed view, taken at point 100, showing a partial cross-sectional side view of the burner lining and dilution lining section. Figures 2 to 13 In each of the aforementioned arrangements, a contraction-expansion section is described for implementing a dilution lining section of the burner liner 50 to adjust the volume of the primary combustion zone 70 both structurally and aerodynamically. However, in Figure 14 In this arrangement, the dilution lining section is implemented as a straight section, rather than a contraction-expansion section, and provides aerodynamic adjustment of the primary volume. Figure 14As can be seen, the outer liner 54 includes an upstream liner section 106 and a downstream liner section 108 with a gap 114 between them, and a dilution liner section 300 extends across the gap 114 to connect with the upstream liner section 106 and the downstream liner section 108. Similarly, it can be seen that the inner liner 52 includes an upstream liner section 110 and a downstream liner section 112 with a gap 116 between them, and a dilution liner section 302 extends across the gap 116 to connect with the upstream liner section 110 and the downstream liner section 112. The dilution liner section 300 of the outer liner 54 includes a movable portion 304 having at least one dilution opening 306 therethrough. The movable portion 304 includes an actuator connecting member 126 connected to a link 128 of the actuator 96. Therefore, actuator 96 can translate movable portion 304 in the upstream direction 118 or downstream direction 124 based on the operating state. By translating movable portion 304 in the upstream direction 118, dilution opening 306 is translated upstream to aerodynamically reduce the primary volume. On the other hand, by translating movable portion 304 in the downstream direction 124, dilution opening is translated downstream to aerodynamically increase the primary volume. A similar operation occurs when actuator 96 translates movable portion 308 of dilution liner section 302 in the upstream direction 118 or downstream direction 124 to translate dilution opening 310 upstream or downstream. It should be noted that movable portion 304 and movable portion 308 can be actuated independently of each other by their respective actuators 96, such that, for example, movable portion 304 can translate in the upstream direction 118, while movable portion 308 may not translate, or may translate in the upstream direction less than movable portion 304. Of course, movable part 304 and movable part 308 can be translated by the same amount and in the same direction.

[0056] Figure 15 This is a flowchart describing the processing steps of operating engine 10. Figure 15 The method can be described as above. Figures 1 to 14 This is implemented in any of the aspects depicted. In step 1500, the engine start-up operation state is activated to start the engine 10. The engine controller (e.g., the flight controller of the aircraft, not shown) controls the engine start-up operation, and in step 1501, control signals are sent to actuators (e.g., any of the actuators 96, 132, 202, 212, and 266 described above) to adjust the size of the primary volume (PV) of the primary combustion zone 70 based on the start-up operation power. The primary volume (PV) is adjusted based on controlling any of the dilution liner sections described above. For ground start-up operations, the primary volume may be referred to as the primary volume (PV1) and can be adjusted and set to have a total volume (V TThe range is 40% to 60%. In step 1502, for the pre-takeoff taxiing operation, engine power is increased, and in step 1503, based on the power change during the taxiing operation, the adjustment can be referred to as the primary volume (PV). 1a The primary volume used for taxiing operations. Typically, before takeoff, engine power can be reduced while the crew is preparing for takeoff, and in this case, in step 1504, the engine power can be reduced to an idle state similar to the ground start-up state. Therefore, in step 1505, the controller sends a signal to the actuator to adjust the primary volume to a state that can be referred to as the primary volume (PV) based on the idle power state. 1b The primary volume of the idle state.

[0057] Next, in step 1506, for takeoff and climb operations, engine power is increased, and in step 1507, the controller sends a signal to the actuator to adjust the primary volume (PV) for takeoff and climb. The primary volume for takeoff and climb operation states, which may be referred to as the primary volume (PV2), can have a total volume (V... T The range is 30% to 40% of the total volume (V). Once the cruise altitude is reached, in step 1508, the engine power is typically reduced, and in step 1509, the controller sends a signal to the actuator to adjust the primary volume (PV) based on the engine power during cruise. The size of the primary volume during cruise operation, which may be referred to as the primary volume (PV3), can be adjusted to the total volume (V). T The range is between 30% and 50%.

[0058] Engine stalling may occur during cruise operation or in any other operating state. When engine stalling occurs during cruise operation (Yes in 1510), a high-altitude restart operation is initiated. In this case, at step 1514, the controller sends a signal to the actuator to adjust the primary volume to a restart operation primary volume, which may be referred to as the primary volume (PV5), for the high-altitude restart operation. It is known that signals are also sent to various other engine components, such as fuel injectors, igniters, etc., for restart operation, but these are not discussed herein. At step 1515, if the restart operation is determined to be successful (Yes in step 1515), then at step 1516, the controller again sends a signal to the actuator to adjust the primary volume size to the primary volume (PV3) for the cruise operation state.

[0059] At the end of the cruise operation, in step 1511, the landing approach operation state begins, during which engine power is typically reduced. In step 1512, the controller sends a signal to the actuator to adjust the primary volume to the approach primary volume, which may be referred to as the primary volume (PV4), for both the approach and landing operation states. In the approach / landing operation state, the primary volume (PV4) can be adjusted to the total volume V. T The range is between 30% and 50%. Finally, after the landing and taxiing operations, in step 1513, the engine shutdown sequence is initiated.

[0060] While the foregoing description generally pertains to gas turbine engines, it is readily understood that gas turbine engines can be implemented in a variety of environments. For example, the engine can be implemented in aircraft, but it can also be implemented in non-aircraft applications such as power plants, marine applications, or oil and gas production applications. Therefore, this disclosure is not limited to use in aircraft.

[0061] Further aspects of this disclosure are provided by the subject matter of the following provisions.

[0062] A method of operating a combustor for a gas turbine, the combustor including a combustor liner defining a combustion chamber therein, the combustion chamber defining a total combustion chamber volume, the combustion chamber including a primary combustion zone at an upstream end of the combustion chamber defining a primary volume, the combustor liner including a movable portion arranged to be actuated to adjust the percentage of the primary volume relative to the total combustion chamber volume, the method comprising: in the first operating state of the gas turbine, adjusting the size of the primary volume to a first percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume; and in the second operating state of the gas turbine, different from the first operating state, adjusting the size of the primary volume to a second percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume.

[0063] The method according to any of the foregoing clauses, wherein the first operating state is a ground start-up state, and the second operating state is a take-off state or a climb state.

[0064] According to the method of any of the foregoing clauses, the movable portion includes translation of the diluted oxidant flow through at least one dilution opening in the primary volume in the upstream and downstream directions of the flow, thereby aerodynamically adjusting the percentage of the primary volume.

[0065] According to any of the foregoing provisions, the burner liner is an annular liner and includes an outer liner and an inner liner, defining the combustion chamber between the outer liner and the inner liner, and both the outer liner and the inner liner include their respective movable portions to adjust the primary volume.

[0066] According to the method of any of the foregoing clauses, the movable portion is actuated by an actuator in response to a change in the percentage of power applied to the gas turbine through a plurality of operating states, the plurality of operating states including the first operating state and the second operating state.

[0067] According to the method described in any of the foregoing clauses, the first percentage has a range of 40% to 60% of the total combustion chamber volume.

[0068] According to the method described in any of the foregoing clauses, the second percentage has a range of 30% to 40% of the total combustion chamber volume.

[0069] The method according to any of the foregoing clauses further includes, in a third operating state of the gas turbine, different from the first operating state and the second operating state, adjusting the size of the primary volume to a third percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume.

[0070] The method described according to any of the foregoing clauses, wherein the third operating state is a cruise state.

[0071] According to the method described in any of the foregoing clauses, the third percentage has a range of 30% to 50% of the total combustion chamber volume.

[0072] The method according to any of the foregoing clauses further includes, in a fourth operating state of the gas turbine, different from the first operating state, the second operating state, and the third operating state, adjusting the size of the primary volume to a fourth percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume.

[0073] The fourth operating state is an approach state according to any of the foregoing clauses.

[0074] According to the method described in any of the foregoing clauses, the fourth percentage has a range of 30% to 50% of the total combustion chamber volume.

[0075] The method according to any of the foregoing clauses further includes, in a fifth operating state of the gas turbine, which is different from the first operating state, the second operating state, the third operating state, and the fourth operating state, adjusting the size of the primary volume to a fifth percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume.

[0076] According to the method described in any of the foregoing clauses, the fifth operating state is an altitude re-ignition state, and the fifth percentage has a range of 40% to 70% of the total combustion chamber volume.

[0077] According to any of the foregoing provisions, the movable portion of the burner liner includes a shrinkage-expansion portion extending into the combustion chamber and having at least one dilution opening therethrough, the shrinkage-expansion portion being disposed in the dilution zone of the combustion chamber downstream of the primary combustion zone.

[0078] According to any of the foregoing provisions, the burner liner includes an upstream liner section fixedly mounted in the burner and a downstream liner section fixedly mounted in the burner, with a gap between the upstream liner section and the downstream liner section, and the shrinkage expansion portion extends across the gap and engages with the upstream liner section and the downstream liner section.

[0079] The method according to any of the foregoing clauses, wherein the percentage of the primary volume is aerodynamically and / or structurally adjusted by translation of the upstream and downstream directions of the contraction-expansion portion and the dilution oxidant flow through the dilution opening.

[0080] The method according to any of the foregoing clauses further includes, in a third operating state of the gas turbine different from the first operating state and the second operating state, adjusting the size of the primary volume to a third percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume; and in a fourth operating state of the gas turbine different from the first operating state, the second operating state, and the third operating state, adjusting the size of the primary volume to a fourth percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume, wherein the first percentage has a range of 40% to 60% of the total combustion chamber volume, the second percentage has a range of 30% to 40% of the total combustion chamber volume, the third percentage has a range of 30% to 50% of the total combustion chamber volume, and the fourth percentage has a range of 30% to 50% of the total combustion chamber volume.

[0081] The method according to any of the foregoing clauses, wherein the first operating state is a ground start-up state or an altitude re-ignition state, the second operating state is a takeoff state or a climb state, the third operating state is a cruise state, and the fourth operating state is an approach state.

[0082] While the foregoing description is directed to some exemplary embodiments of the present disclosure, it should be noted that other changes and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of the present disclosure. Furthermore, features described in connection with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A method for operating a combustor of a gas turbine, characterized in that, The burner includes a burner liner defining a combustion chamber therein, the combustion chamber defining a total combustion chamber volume, the combustion chamber including a primary combustion zone at an upstream end of the combustion chamber defining a primary volume, the burner liner including a movable portion arranged to be actuated to adjust the percentage of the primary volume relative to the total combustion chamber volume, the method comprising: In the first operating state of the gas turbine, by actuating the movable part to adjust the size of the primary volume, the size of the primary volume is adjusted to a first percentage of the total combustion chamber volume; and In a second operating state of the gas turbine, different from the first operating state, the size of the primary volume is adjusted to a second percentage of the total combustion chamber volume by actuating the movable portion. The movable portion of the burner liner includes a contraction-expansion portion extending into the combustion chamber and having at least one dilution opening therethrough, the contraction-expansion portion being disposed in the dilution zone of the combustion chamber downstream of the primary combustion zone. The burner liner includes an upstream liner section fixedly installed in the burner and a downstream liner section fixedly installed in the burner, with a gap between the upstream liner section and the downstream liner section, and the shrinkage expansion portion extends across the gap and engages with the upstream liner section and the downstream liner section. The percentage of the primary volume is aerodynamically and / or structurally adjusted by the translation of the upstream and downstream directions of the contraction-expansion portion and the dilution oxidant flow through the dilution opening.

2. The method according to claim 1, characterized in that, The first operating state is the ground start-up state, and the second operating state is the take-off state or the climb state.

3. The method according to claim 1, characterized in that, The movable portion includes at least one dilution opening therethrough, and the translation of the diluted oxidant flow through the dilution opening in the upstream and downstream directions of the flow aerodynamically adjusts the percentage of the primary volume.

4. The method according to claim 1, characterized in that, The burner liner is an annular liner and includes an outer liner and an inner liner, defining the combustion chamber between the outer liner and the inner liner, and both the outer liner and the inner liner include their respective movable portions to adjust the primary volume.

5. The method according to claim 1, characterized in that, The movable portion is actuated by an actuator in response to changes in the percentage of power applied to the gas turbine through a plurality of operating states, including a first operating state and a second operating state.

6. The method according to claim 1, characterized in that, The first percentage ranges from 40% to 60% of the total combustion chamber volume.

7. The method according to claim 6, characterized in that, The second percentage has a range of 30% to 40% of the total combustion chamber volume.

8. The method according to claim 1, characterized in that, Further, in a third operating state of the gas turbine, which is different from the first and second operating states, the size of the primary volume is adjusted to a third percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume.

9. The method according to claim 8, characterized in that, The third operating state is the cruise state.

10. The method according to claim 8, characterized in that, The third percentage is in the range of 30% to 50% of the total combustion chamber volume.

11. The method according to claim 8, characterized in that, Further, in a fourth operating state of the gas turbine, which is different from the first, second, and third operating states, the movable portion is actuated to adjust the size of the primary volume to a fourth percentage of the total combustion chamber volume.

12. The method according to claim 11, characterized in that, The fourth operating state is the approach state.

13. The method according to claim 11, characterized in that, The fourth percentage is in the range of 30% to 50% of the total combustion chamber volume.

14. The method according to claim 11, characterized in that, Further, in a fifth operating state of the gas turbine, which is different from the first operating state, the second operating state, the third operating state, and the fourth operating state, the movable part is actuated to adjust the size of the primary volume to a fifth percentage of the total combustion chamber volume.

15. The method according to claim 14, characterized in that, The fifth operating state is an altitude-based re-ignition state, and the fifth percentage ranges from 40% to 70% of the total combustion chamber volume.

16. The method according to claim 1, characterized in that, Further, in a third operating state of the gas turbine, which is different from the first and second operating states, the size of the primary volume is adjusted to a third percentage of the total combustion chamber volume by actuating the movable portion to adjust the size of the primary volume; and In a fourth operating state of the gas turbine, different from the first, second, and third operating states, the movable portion is actuated to adjust the size of the primary volume, thereby adjusting the size of the primary volume to a fourth percentage of the total combustion chamber volume. The first percentage has a range of 40% to 60% of the total combustion chamber volume, the second percentage has a range of 30% to 40% of the total combustion chamber volume, the third percentage has a range of 30% to 50% of the total combustion chamber volume, and the fourth percentage has a range of 30% to 50% of the total combustion chamber volume.

17. The method according to claim 16, characterized in that, The first operating state is ground start-up state or altitude re-ignition state, the second operating state is take-off state or climb state, the third operating state is cruise state, and the fourth operating state is approach state.

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