JP2017527765A - Burner with fluid oscillator for gas turbine and gas turbine with at least one such burner - Google Patents

Abstract

The present invention relates to a burner having a premixing channel (68), said premixing channel being delimited by a wall radially outward and used for premixing fuel and air during operation. A burner lance (72, 94) and a plurality of fuel injectors are arranged in the premixing flow path, and the fuel injector extends from the burner lance (72) in the direction of the wall. The fuel nozzles (80, 80a, 80b) are provided. The burner allows a reduction in the emission of harmful substances during operation or a reduction in pressure fluctuations. To that end, the fuel supply includes at least one fluid oscillator (85) having an interaction chamber (26), the inlet (28) of the interaction chamber being a fuel conduit (82) of the fuel supply. ), The first discharge conduit (86) of the interaction chamber extends to at least the first fuel nozzle (80a), and the second discharge conduit (88) is at least a second Extending to a fuel nozzle (80b), the fluid oscillator includes a feedback conduit (38a, 38b) for each of the discharge conduits, the feedback conduit having at least one at one end thereof In the region downstream of the fuel nozzle, it merges into the respective discharge conduit and, at the other end, merges into the inlet region (30) of the interaction chamber.

Description

  The present invention relates to a burner for a gas turbine having a central burner shaft and a premixing channel that at least partially surrounds the burner shaft. Accordingly, the premix channel has a cross-sectional area of the channel, and the cross-sectional area extends around the burner shaft. The central burner axis is a mathematically infinite length line. The cross-sectional area of the channel can be annular, for example, or it can be arranged around the burner axis as a full circle. In other words, the premix channel may extend coaxially (same rotational axis) with respect to the burner axis. The diameter of the ring or the full circle can vary along the part of the burner axis. In particular, the premixing channel can be configured at least partially as an annular space channel (circular cross section), and the annular space channel is configured as a full circle in the cross section. It is possible to move to the mixing channel part.

  The premixing channel is delimited by walls toward the radially outer side. In operation, the premix channel can flow through with compressed air. The premixing channel is used for premixing fuel and air, and a burner lance or burner hub and a plurality of fuel injectors are arranged in the premixing channel. A fuel injector extending from the burner lance / burner hub in the direction of the wall is fluidly connected to a fuel supply device at least partially surrounded by the burner lance / burner hub and has a fuel nozzle. The fuel injector may include, for example, a fuel nozzle for gaseous fuel as well as a fuel nozzle for operation with fuel oil. The same applies to an alternative structure of the burner lance / burner hub without a fuel nozzle.

  A burner lance may also be referred to as a burner hub within the scope of the present invention.

  The burner lance can be placed in the center of the premix channel. Since the burner lance can protrude from the upstream into the premixing channel, the channel is only partially delimited by the burner lance towards the inside in the radial direction. In this case, the premix channel may have a full circular cross-sectional area, for example downstream of the burner lance. However, the burner lance can also extend almost to the outlet of the premix channel.

  Alternatively, the premixing channel can be delimited by a burner hub having a generally frustoconical side surface located at least partially in the middle of the channel, radially inward. The burner hub divides the premix channel from the upstream side to the end region of the hub inward in the radial direction. The premix flow path transitions to a premix region downstream of the hub and having a full circular cross section. Thus, along the hub, the premix channel has an annular channel cross-sectional area whose diameter can decrease in the direction of flow. In particular, further premixing channels or, for example, a central pilot burner may be arranged in the burner hub.

  The premix channel may also be referred to as a premix tube within the scope of the present invention. Through the fuel injector, fuel is injected into the premixing channel, and the fuel can be mixed with the compressed air flow that flows through the premixing channel up to the outlet of the premixing channel disposed downstream. The burner supplies at its outlet a fuel / air mixture for discharge into the combustion chamber. In addition, it is also possible to inject fuel through a fuel nozzle arranged directly on the burner lance.

  Attempts are made to obtain combustion with as little harmful substances as possible and avoidance of thermoacoustic instabilities during combustion by the burner of the same genus. In particular, premixed burners do not emit much harmful substances during operation, but are subject to pressure fluctuations.

  The object of the present invention is to describe a burner for a gas turbine of the type mentioned at the outset, which makes it possible to reduce the emission of harmful substances or reduce pressure fluctuations during the operation of the burner. It is in.

  According to the invention, in a burner of the type mentioned at the outset, the problem is solved by the fact that the fuel supply device includes at least one fluid oscillator having an interaction chamber, the inlet of the interaction chamber being A first exhaust conduit of the interaction chamber extends to at least the first fuel nozzle and a second exhaust conduit extends to at least the second fuel nozzle. The fluid oscillator includes a feedback conduit for each discharge conduit, the feedback conduit merges with each discharge conduit at one end thereof in the region downstream of the at least one fuel nozzle and the other end. At the junction of the entrance region of the interaction chamber.

  For example, at least a first fuel nozzle and at least a second fuel nozzle, or a first fuel nozzle group and a second fuel nozzle group, are arranged in a common fuel injector and are capable of fuel in the premix channel. For as uniform dispersion as possible, they can be distributed radially. For example, at least the first fuel nozzle can be arranged on the suction side, and at least the second fuel nozzle can be arranged on the pressure side of the fuel injector configured in the form of a swirling blade. The first fuel nozzle group and the second fuel nozzle group may be arranged in different fuel injectors, for example. For example, it can be located in a fuel injector that is located substantially opposite the fuel lance.

  Fluid oscillators have long been known as fluid control elements that do not require expensive valves. For example, fluid oscillators are used to supply air to the boundary layer of the support surface and avoid boundary layer separation.

  The fluid oscillator is in contact with its inlet and operates with a fluid flow under pressure. Since this fluid flow is oscillated in the interaction chamber, at least one outlet of the chamber is alternately impinged by the outgoing jet. Accordingly, a pulsating fluid flow flows out of the fluid oscillator discharge conduit, and the discharge conduit alternately discharges fluid. From the prior art, fluid oscillators with feedback conduits are known, which feedback conduits are connected to the interaction chamber outlet region and the interaction chamber inlet region in order to stabilize vibrations in the interaction chamber. Connected. The prior art feedback conduit joins the interaction chamber at one end near the exit of the interaction chamber, and at the other end, upstream of the exit, near the entrance of the interaction chamber. Merge into the interaction chamber. Each outlet impinges on fluid flow while oscillating, thereby increasing the pressure at the end of the feedback conduit, which pressure is further transmitted through the conduit to the inlet region and the flow is reduced. It is transmitted to the area just in contact with the side wall of the interaction chamber. Thereby, the oscillating flow has a tendency to separate from the sidewall. This leads to feedback of pressure conditions between the exit region and the entrance region of the interaction chamber that stabilizes the vibration.

  In the present invention, it is proposed that the feedback conduits are joined to the respective discharge conduits in the region downstream of at least one fuel nozzle or group of fuel nozzles, rather than joining the outlet region of the interaction chamber as in the prior art. And the exhaust conduit extends to at least one fuel nozzle or group of fuel nozzles. According to the invention, this makes it possible to incorporate in the feedback signal the pressure conditions in the premixing channel in the premixing region immediately upstream of the fuel nozzle. The discharge conduit may have a distal end where the feedback conduit joins downstream of the fuel nozzle or group of fuel nozzles.

  If the static pressure in the region of the fuel nozzle group in the premix channel is relatively high, less fuel will pass through the discharge conduit and the dynamic pressure in the discharge conduit will be lower. Thereby, in constructing the feedback conduit according to the present invention, the feedback signal is reduced and the fuel flows in the exhaust conduit more than in the case of reverse pressure conditions upstream of the fuel nozzle of the exhaust conduit in the premix channel. Also flows long. If the static pressure in the region of the fuel nozzle group in the premixing channel is relatively low, more fuel will flow through the associated exhaust conduit during the collision of the associated outlet of the interaction chamber and into the exhaust conduit. The dynamic pressure is higher. Since the attached feedback conduit joins the exhaust conduit downstream of at least one fuel nozzle of the exhaust conduit, the pressure in the feedback conduit joining the end region of the exhaust conduit is higher and the accompanying fuel jet is It separates faster from the side walls of the interaction chamber inlet region and causes fuel to impinge on the nearest outlet. Thus, the vibration of the fuel jet in the interaction chamber causes the fuel to collide longer with the discharge conduit, and at least one of the fuel nozzles merges into a region of the premix channel where the higher pressure is dominant. This has the effect that generally less fuel flows out of the fuel nozzle that joins the region of higher flow path pressure, or more fuel is injected into the region of lower pressure. Compensated. With this compensation, the present invention provides a more uniform fuel concentration in the premixing channel. Thus, the injection of fuel through at least two fuel nozzle groups or fuel nozzles connected to the fluid oscillator is adjusted independently without the need for additional control devices. The resulting more uniform distribution of fuel concentration in the premix flow path reduces the emissions of harmful substances. The injection of fuel, which varies in time and location, also provides a good mixing of the fuel discharged by the fuel nozzle group and the compressed air flowing through the sides. According to the present invention, based on the fuel injection fluctuated by the fluid oscillator, it also leads to a broader residence time profile of the burner, thereby reducing the burner-flame interaction and causing thermoacoustic oscillations. Decrease.

  To illustrate the concept of thermoacoustic vibration and residence time, it should be noted that interaction between acoustic vibration and fluctuations in heat release can occur in the combustion chamber. These can increase with respect to each other when the frequencies correspond to the so-called eigenmodes of the gas turbine. These eigenmodes depend on the size and style of each gas turbine. Such thermoacoustic vibration may significantly damage the members during the operation of the gas turbine, forcing the facility to stop operating.

  In order not to cause thermoacoustic vibrations, the residence time profile of the burner that occurs during operation may be as wide as possible, which residence time is required for the fluid discharged from the fuel nozzle to reach the flame. It's time.

  The fuel nozzle or fuel nozzle group of the burner supplied with fuel by the fluid oscillator is conditioned by a fuel jet that pulsates in time and location, so that the fuel concentration in the compressed air flowing through the conditionally at the outlet of the nozzle Has a profile variation, so that again the thermoacoustic stability is improved based on the burner's extended residence time profile, for example compared to a burner with a conventional pressure swirling nozzle or a full jet nozzle Is done. The frequency of pulsating fuel injection can be adjusted, for example, by the size of the interaction chamber. The burner may include a plurality of fluid oscillators that each supply fuel to at least two discharge conduits using at least one fuel nozzle or group of fuel nozzles, respectively.

  Various types of fluid oscillators with different structures are known. The present invention is not limited to a particular type of these fluid oscillators. All these types are common in that they have an interaction chamber through which a fluid jet under pressure flows through the inlet. Since the jet is periodically in contact with various side walls or side wall regions of the interaction chamber, it is possible to refer to the interaction between the jet and the side walls of the chamber, causing vibrations of the jet, The jets flow through the chamber in periodically different paths and thus periodically leave the interaction chamber through various outlets of the interaction chamber or in various directions in the exit region. Leave the central outlet of the interaction chamber. Thus, the jets are periodically in contact with at least two opposite side wall regions or separated again by flow stagnation.

  Since the manner of functioning of the fluid oscillator is prior art, only a brief description of the fluid oscillator will be given here. In addition, several types of fluid oscillators are shown in the drawings. The present invention does not depend on the type of fluid oscillator used. The present invention preferably starts with a fluid oscillator that causes oscillations of the incoming jet, based on the side walls that diverge in the inlet region of the interaction chamber. In particular, the invention preferably starts from a substantially rotationally symmetric configuration of the interaction chamber, which configuration is arranged around the axis of rotation at one end of the chamber and has at least one outlet. It has an inlet located opposite the outlet area. In order to induce vibrations, in the case of this type of interaction chamber, the interaction chamber expands like a diffuser in the direction towards the outlet region, at least in the inlet region of the chamber. The function of the feedback conduit has already been described above.

  Advantageous aspects of the invention are described in the following description and in the subclaims, whose features can be used individually or in any combination.

  Advantageously, the first exhaust conduit extends to the first fuel nozzle group, the second exhaust conduit extends to the second fuel nozzle group, and the feedback conduits each for each fuel nozzle. In the region downstream of the group, it can be defined that it joins the discharge conduit.

  The first fuel nozzle group and the second fuel nozzle group, or the first fuel nozzle and the second fuel nozzle may be disposed, for example, in a common fuel injector. The fuel injector can be, for example, a swirl blade of a swirl generator. Since different pressures are dominant in the premixing flow path on the suction side and the pressure side of the blade, the first fuel nozzle or the first fuel nozzle group is located on the suction side of the swirl blade. The second fuel nozzle group may be disposed on the pressure side. According to the present invention, this allows approximately the same amount of fuel to be injected on both sides of the blade.

  It may also be advantageous to have a feedback conduit connected to the discharge conduit downstream of the at least one fuel nozzle.

  In so doing, the drain tube and the feedback conduit may have different diameters.

  It may also be considered advantageous that at least the first fuel nozzle and at least the second fuel nozzle are arranged in different fuel injectors.

  In particular, it can be considered advantageous that both fuel injectors are arranged in the burner lance approximately opposite each other.

  Therefore, the fuel concentration in the premixing channel adapts to each other at least in both facing regions even though the pressure conditions are different in the regions.

  At least two fuel nozzles or at least two fuel nozzle groups are arranged in a common fuel injector and differ in the radial arrangement in their premixing channels, so that the fuel concentration is in the radial direction, It may also be considered advantageous to be homogenized despite the different pressure conditions in the region near and far from the burner lance of the premix channel. The fluid oscillator may be located in the burner hub or also in the fuel injector.

  Advantageously, it may further be provided that the burner comprises two or more fuel nozzle groups thus connected to the fluid oscillator in different fuel injectors.

  Thereby, the fuel concentration can be made uniform downstream of the various fuel injectors in the premixing channel.

  A further advantageous aspect of the invention provides that the various fuel injectors are arranged on the burner lance so as to make a circuit and the associated discharge conduit is arranged on the interaction chamber so as to make a circuit. Can do.

  The at least one fuel injector includes a base in which a fuel nozzle surrounded by the fuel injector is arranged, which base may be considered to be particularly a swirl blade of a swirl generator.

  Advantageously, the interaction chamber further has an inlet at one end thereof and an outlet region at the opposite end, extending from the inlet of the chamber to the outlet region containing the outlet. It may be defined that the at least two oppositely arranged side walls or side wall regions are delimited by a side wall or a side wall region, at least at the inlet region and in the direction towards the outlet.

  According to this aspect of the invention, the vibration of the fuel jet flowing through the inlet into the interaction chamber under pressure is caused by alternating contact of the jet with the side wall regions having a branching structure. The occurrence of vibrations in the interaction chamber according to the invention is based on the flow dwell caused by the branching sidewall / sidewall region in the inlet region.

  It is also possible that at least two oppositely arranged side walls diverge in the inlet region of the interaction chamber in the outlet direction at an angle greater than 7.5 ° with respect to the flow inlet direction of the interaction chamber inlet. It can be considered advantageous.

  The open angle of the interaction chamber that is suitable for causing vibrations is known from the prior art. An angle of at least 7.5 ° with respect to the flow inflow direction has proven particularly advantageous.

  Advantageously, the interaction chamber may be configured to be substantially rotationally symmetric, and the interaction chamber may be defined as spreading in a diffuser direction toward the outlet, at least in the inlet region.

  The rotationally symmetric structure of the fluid oscillator allows fuel to be injected all around the discharge conduit starting from the exit region of the interaction chamber.

  The fluid oscillator is, for example, arranged in the center of the burner lance and can be rotated to supply fuel to the entire circumference of a fuel injector arranged on the burner lance, each of which has at least one discharge of the fluid oscillator. The conduit extends to each fuel nozzle group of the fuel injector. A round fuel injector may both include two fuel stages. Each stage can be provided with a suitable fluid oscillator.

  A further object of the present invention is to describe a burner assembly having a plurality of burners, in which the main burners are arranged in one or more circles arranged concentrically with respect to each other. This makes it possible to reduce the emission of harmful substances or to reduce pressure fluctuations during operation of the burner assembly.

  For this purpose, at least one burner is configured according to any one of claims 1 to 11.

  The burner can be, for example, a pilot burner located in the center of the burner assembly. According to a further embodiment, additionally or alternatively, the main burner of the burner assembly can also be configured according to any one of claims 1 to 11.

  The burner according to the invention or the burner assembly according to the invention enables particularly stable combustion, especially even in part-load operation.

  It is a further object of the present invention to describe a combustion chamber and gas turbine for a gas turbine that, during operation, allows for reduced emissions of hazardous substances and reduced pressure fluctuations in the combustion chamber. is there.

  For this purpose, the combustion chamber includes at least one burner according to any one of claims 1 to 12, and the gas turbine includes at least one combustion chamber according to claim 13.

  Further suitable aspects and advantages of the present invention are the subject of the description of the embodiments of the present invention with reference to the drawings, wherein the same reference numerals denote members of the same function.

It is the figure which showed schematically the gas turbine which concerns on a prior art in the longitudinal cross-section. It is the figure which showed schematically two types of fluid oscillators based on a prior art in the longitudinal cross-section. It is the figure which showed schematically two types of fluid oscillators based on a prior art in the longitudinal cross-section. It is the figure which showed roughly a part of combustion chamber 10 concerning a prior art with the longitudinal section. It is the figure which showed schematically the main burner of the burner assembly shown by FIG. 4 in the longitudinal cross-section. It is the figure which showed schematically the burner concerning the present invention based on the 1st example of the present invention in the longitudinal section. It is the figure which showed schematically the burner concerning the present invention based on the 2nd example of the present invention in the longitudinal section.

  FIG. 1 shows a cross-section of a gas turbine 1 according to the prior art in a schematically simplified depiction. The gas turbine 1 has a rotor 3 with a shaft 4 that is rotatably supported around a rotary shaft 2 in the interior thereof, and the rotor is also referred to as a turbine rotor. Along the rotor 3, combustion having a plurality of combustion chambers 10 each including an intake housing 6, a compressor 8, a burner assembly having a burner 11, a fuel supply system (not shown) for the burner, and a housing 12. The system 9, the turbine 14, and the exhaust housing 15 are arranged in succession. The combustion chamber 10 can be, for example, an annular combustion chamber. However, the gas turbine may also include a tubular combustion chamber, for example arranged annularly at the inlet of the turbine.

  The combustion system 9 is in communication with, for example, an annular hot gas conduit. There, a plurality of turbine stages connected to the front and rear form a turbine 14. Each turbine stage is formed from a blade ring. As viewed in the direction of flow of the working medium, in the hot conduit, the rows formed from the guide vanes 17 are followed by the rows formed from the rotor blades 18. At this time, the guide vanes 17 are fixed to the inner housing of the stator 19, but the rotor blades 18 in the row are attached to the rotor 3 by using, for example, a turbine disk. For example, a generator is connected to the rotor 3 (not shown).

  During operation of the gas turbine, air is drawn in and compressed by the compressor 8 through the intake housing 6. The compressed air L "supplied to the turbine side end of the compressor 8 is guided along the burner plenum 7 to the combustion system 9 and is guided into the burner 11 in the region of the burner assembly, And / or fuel is added at the exit region of the burner 11. In this case, the fuel supply system supplies fuel to the burner, which mixture or compressed air and fuel are fed from the burner 11 to the combustion chamber 10. Introduced and combusted, a hot working gas flow is formed in a combustion region within the combustion chamber housing 12 of the combustion chamber, from which the working gas flow passes along the hot gas conduit along the guide vane 17 and the rotor. Passes beside the blade 18. In the rotor blade 18, the working gas flow expands to transmit impulses, so Over blade 18 drives the rotor 3, the rotor 3 drives itself linked generator (not shown).

  FIG. 2 shows a first type of fluid oscillator according to the prior art in longitudinal section.

  The oscillator 24a includes an interaction chamber 26 having an inlet 28 and an inlet region 30 and an outlet region 32 having a first outlet 34 and a second outlet 36 disposed on opposite sides thereof. For each outlet, a relatively thin feedback conduit 38 is arranged, connecting the inlet region with the outlet region.

  Since the side wall region 40 branches off in the direction of the outlet, the interaction chamber 26 has a triangular longitudinal section. The oscillator 24a is not configured to be rotationally symmetric, and has a certain longitudinal section perpendicular to the horizontal plane of the drawing.

  FIG. 3 shows in longitudinal section a second type of fluid oscillator 24b according to the prior art. Similarly, the oscillator 24b is not configured to be rotationally symmetric and has a certain vertical cross section perpendicular to the horizontal plane of the drawing. Since the inlet 28 is located in the center of the interaction chamber 26 and inside the guide means 42, the jet flowing under pressure is directed to the opposite side wall 44 from the front. The jet flows alternately in the direction of the outlet region 32 to the left and right sides of the guide means, and at this time, the fluid collides with the outlets 34 and 36 alternately, so that the jet flows alternately from one outlet to the other. And out of the chamber at a frequency determined by the size of the interaction chamber 26.

  FIG. 4 schematically illustrates a portion of a prior art combustion chamber 10 having a burner assembly 48 at the upper end of the combustion chamber. The combustion chamber includes a combustion chamber wall having a flame tube 50 including a combustion region and a transition portion 52 connected to the flame tube, the transition portion extending to a turbine inlet of the gas turbine. . A resonator 54 is placed on the combustion chamber wall at the height of the flame for damping thermoacoustic vibrations that occur during operation. The burner assembly 48 includes a central pilot burner 56 having a central pilot burner lance 58 and a pilot burner premix channel 60. The pilot burner 56 includes a pilot cone 62 that expands conically in the direction of flow. A main burner 64 is arranged in a circle around the central pilot burner. Each main burner 64 has a burner shaft 66 and a premixing channel 68 disposed concentrically with the burner shaft. And is capable of flowing through with compressed air L "during operation, and is used for premixing of fuel and air L". Inside the premixing channel 68, there is a central burner lance 72 and a plurality of A fuel injector, which extends from the burner lance in the direction of the wall 70 and is fluidly connected to a fuel supply device surrounded by the burner lance 72, with a fuel nozzle Have. The fuel injector is configured as a swirl blade of the swirl generator 74, and the fuel nozzle is disposed on the swirl blade.

  FIG. 5 schematically shows the main burner 64 of the burner assembly of FIG. 4 in longitudinal section. The burner 64 has a central burner shaft 66 and a premixing channel 68 that at least partially surrounds the burner shaft, and the premixing channel faces the wall 70 radially outward. And is capable of flowing through compressed air L ″ during operation and is used for fuel and air premixing. The premixing channel 68 includes a central burner lance 72 and a plurality of fuel injectors 79. Each of the fuel injectors 79 includes a base 71 disposed in the premixing channel, and the base is configured as a swirl blade 76 of a swirl generator 74. The fuel injector 79 is The fuel nozzle 80 includes a fuel nozzle 80 that opens to the premixing flow path 68 at the surface of the swirl blade 76. The fuel nozzle 80 is used to supply fuel. The fuel supply device 73 includes a fuel conduit 82 extending into the burner lance and a fuel supply pipe 78 extending to the respective fuel nozzles 80 in the swirl blade 76. Contains.

  FIG. 6 schematically shows the burner 84 according to the first embodiment of the present invention in a longitudinal section. Unlike the prior art burner 64 shown in FIG. 5, the fuel supply device 73 includes at least one fluid oscillator 85 having an interaction chamber 26, the inlet 28 of the interaction chamber being a fuel supply Connected to the fuel conduit 82 of the device 73. The interaction chamber 26 has an outlet region 32 having two outlets 34 and 36 on the opposite side of the inlet region 30 having the inlet 28. The first discharge conduit 86 extends from the outlet 34 to the first fuel nozzle group 80a in the first fuel injector 79a. The second discharge conduit 88 extends from the outlet 36 to a second fuel nozzle group 80b in the fuel injector 79b disposed on the opposite side, and a fluid oscillator 85 is provided for each discharge conduit with a feedback conduit 38a, 38b, the feedback conduits 38a, 38b join at their one end to the respective discharge conduits 86, 88 downstream of the fuel nozzles 80a, 80b surrounded by the discharge conduits, At the end of the chamber merges with the inlet region 30 of the interaction chamber 26.

  The inlet 28 of the fluid oscillator 85 is supplied with pressurized fuel flow using the fuel conduit 82 during operation of the burner so that the fuel flow in the interaction chamber 26 branches off in the inlet region 30. Because of the side walls that are in contact, the chamber side walls are oscillatingly contacted, thereby alternately supplying fuel to the outlets 34 and 36. Since the fuel flows through the discharge conduits 86 and 88 to the respective fuel nozzle groups, a pulsating fuel flow is injected from the fuel nozzle groups into the premixing flow path 68. The fuel nozzle can be, for example, a full jet nozzle or a pressure swirl nozzle. The feedback conduit 38a is connected to the exhaust conduit 86 downstream of the fuel nozzle 80a and feeds back the dominant pressure at the end of the exhaust conduit to the inlet region 30 of the interaction chamber. At that time, the pressure prevailing at the end of the discharge conduit is affected by the pressure in the premixing channel slightly upstream of the fuel nozzle 80a, so if the pressure in that region is high, the fuel supply will be It switches to the second fuel nozzle group 80b more slowly than in the case where it is relatively low. Therefore, the fuel nozzle group injects fuel into the compressed air flow passing aside for a relatively long time, and the upstream of the fuel nozzle group has a higher pressure in the premixing channel, so the outlet of the burner Then, even when pressure conditions are different on both sides of the burner lance 72, a uniform fuel concentration is generated. This resists the occurrence of pressure fluctuations and reduces the generation of harmful substances.

  FIG. 7 schematically shows a burner 90 according to a second embodiment of the present invention. The burner 90 is centrally disposed with a central burner shaft 66, an annular space concentrically extending with respect to the burner shaft 66, and a premix channel 92 bounded outwardly by a wall 70. And a burner hub 94. An oblique grid 96 is disposed in the premixing channel 92, and the oblique lattice causes the compressed air L ″ flowing through the premixing channel to swirl. The oblique lattice surrounds the periphery of the hub. The base part arrange | positioned in the several fuel injector 98 arrange | positioned and arrange | positioned in the premixing flow path adds the velocity component which points to the circumferential direction of a flow path to the compressed air L "which passes. Extending within the burner hub 94 is at least one fuel conduit 82 that is configured to circulate in the cone of the burner hub and through the fuel nozzles 80, 80a, 80b of the fuel injector 98. Can be fueled. According to an embodiment, at least two discharge conduits of a fluid oscillator extend within the at least one fuel injector 100 (not shown). The fluid oscillator is fluidly disposed between the fuel conduit 82 and at least the first fuel nozzle group and the second fuel nozzle group, and within the fuel injector 100, the fuel nozzle group includes: Fuel is supplied through a first discharge conduit and a second discharge conduit (not shown) of the fluid oscillator. The first fuel nozzle group is indicated by 80a and is disposed on the fuel injector on the hub side, and the second fuel nozzle group is indicated by 80b and is directed radially outward from the fuel injector. Then, the fuel is injected into the premix channel. This embodiment makes it possible to maintain a uniform fuel concentration in the radial direction at the outlet of the premixing channel even if the flow rate or pressure conditions at the outside or hub side region of the premixing channel are different.

DESCRIPTION OF SYMBOLS 1 Gas turbine 2 Rotating shaft 3 Rotor 4 Shaft 6 Intake housing 7 Burner plenum 8 Compressor 9 Combustion system 10 Combustion chamber 11 Burner 12 Combustion chamber housing 14 Turbine 15 Exhaust housing 17 Guide vane 18 Rotor blade 19 Stator 24a Fluid oscillator 24b Fluid oscillator 26 Interaction chamber 28 Inlet 30 Inlet region 32 Outlet region 34 First outlet 36 Second outlet 38, 38a, 38b Feedback conduit 40 Side wall region 42 Guide means 44 Side wall 48 Burner assembly 50 Flame tube 52 Transition portion 54 Resonator 56 Pilot burner 58 Pilot burner lance 60 Pilot burner premix flow path 62 Pilot cone 64 Main burner 66 Burner shaft 68 Premix flow path 70 Wall 71 Base 72 Bar Nurance 73 Fuel supply device 74 Swivel generator 76 Swivel blade 78 Fuel supply pipe 79 Fuel injector 79a Fuel injector 79b Fuel injector 80 Fuel nozzle 80a First fuel nozzle group 80b Second fuel nozzle group 82 Fuel conduit 84 Burner 85 Fluid oscillator 86 First discharge conduit 88 Second discharge conduit 90 Burner 92 Premix flow path 94 Burner hub 96 Oblique lattice 98 Fuel injector 100 Fuel injector L "Compressed air

Claims (14)

A burner (56, 64, 84) having a central burner shaft and a premixing channel (60, 68, 92) at least partially surrounding the burner shaft, the premixing channel comprising: Radially outwardly bounded by a wall (70) and capable of flowing through compressed air during operation and used for premixing of fuel and air, the premix channel has burner lances (58, 72). , 94) or a burner hub and a plurality of fuel injectors (79, 79a, 79b, 98, 100), the fuel injector from the burner lance or the burner hub to the wall (70). A fuel nozzle fluidly connected to a fuel supply device (73) extending in the direction of and surrounded at least in part by the burner lance or the burner hub 0,80a, 80b) in to which burner has,
The fuel supply device (73) includes at least one fluid oscillator (24a, 24b, 85) having an interaction chamber (26), and an inlet (28) of the interaction chamber is connected to the fuel supply device. Connected to a fuel conduit (82), the first exhaust conduit (86) of the interaction chamber extends to at least the first fuel nozzle (80a), and the second exhaust conduit (88) Extending to at least the second fuel nozzle (80b), the fluid oscillator includes a feedback conduit (38, 38a, 38b) for each of the discharge conduits (86, 88), wherein the feedback conduit is At one end thereof in the region downstream of the at least one fuel nozzle into the respective discharge conduit and at the other end the inlet of said interaction chamber (26) Burner characterized in that it joins the band (30) (56,64,84).   The first discharge conduit (86) extends to the first fuel nozzle group (80a), and the second discharge conduit (88) extends to the second fuel nozzle group (80b). The feedback conduits (38a, 38b) each join a respective discharge conduit in a region downstream of each fuel nozzle group (80, 80a, 80b). Burner (56, 64, 84).   3. The feedback conduit (38a, 38b) is connected to the exhaust conduit (86, 88) downstream of at least one fuel nozzle (80a, 80b). Burner.   Burner according to any one of the preceding claims, characterized in that at least a first fuel nozzle and at least a second fuel nozzle are arranged in different fuel injectors (79a, 79b).   Burner according to any one of the preceding claims, characterized in that both fuel injectors (79a, 79b) are arranged on the burner lance (72) substantially opposite each other.   The burner comprises two or more fuel nozzle groups (80a, 80b) thus connected to the fluid oscillator in different fuel injectors (79a, 79b). The burner according to 4 or 5.   Different fuel injectors (79a, 79b) are arranged in the burner lance (72) so as to make a round, and the associated discharge conduits (86, 88) are arranged in the interaction chamber (26) so as to make a round. 7. Burner according to claim 6, characterized in that it is arranged.   At least one fuel injector (79) includes a base (71), in which the fuel nozzle (80) surrounded by the fuel injector is arranged, the base particularly generating a swivel Burner according to any one of the preceding claims, characterized in that it is a swirl blade (76) of a vessel (74).   The interaction chamber includes the inlet (28) at one end thereof and an outlet region (32) at the opposite end, from the inlet of the chamber to the outlet (34, 36). At least two oppositely disposed side walls or side wall regions (40) at least at the inlet region (30), separated by a side wall or side wall region (40) extending to the outlet region (32) comprising The burner according to claim 1, wherein the burner is branched in the direction of the exit area.   6. At least two oppositely disposed sidewall regions (40) at the inlet region of the interaction chamber, in the direction to the outlet region, with respect to the flow inflow direction of the inlet of the interaction chamber. The burner according to any one of claims 1 to 9, characterized in that it is branched at an angle greater than 5 °.   The interaction chamber is configured to be substantially rotationally symmetric, and the interaction chamber (26) is enlarged at least in the inlet region and has a diffuser shape in the direction toward the outlet region. The burner according to any one of claims 1 to 10. A burner assembly (48) having a plurality of burners, wherein the main burner (64) is arranged in one or more concentrically arranged circles,
Burner assembly (48), characterized in that at least one burner (56, 64) is constructed according to any one of claims 1 to 11. In the combustion chamber (10) for the gas turbine (1),
A combustion chamber (10), characterized in that the combustion chamber comprises at least one burner (11, 48, 56, 64) according to any one of the preceding claims. In a gas turbine having at least one combustion chamber,
A gas turbine characterized in that the combustion chamber is configured according to claim 13.