CN105318354A - Systems and methods for coherence reduction in combustion system - Google Patents
Systems and methods for coherence reduction in combustion system Download PDFInfo
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- CN105318354A CN105318354A CN201510280947.7A CN201510280947A CN105318354A CN 105318354 A CN105318354 A CN 105318354A CN 201510280947 A CN201510280947 A CN 201510280947A CN 105318354 A CN105318354 A CN 105318354A
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- plunger
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
Abstract
The invention relates to systems and methods for coherence reduction in a combustion system. A system includes a gas turbine engine having a first combustor and a second combustor. The first combustor includes a first set of fuel nozzles and a first plurality of injection pegs. The first plurality of injection pegs are disposed in a first configuration upstream of the first set of fuel nozzles, along a first fuel path, and the first plurality of injection pegs are configured to route a fuel to the first set of fuel nozzles. The system further includes a second combustor having a second set of fuel nozzles and a second plurality of injection pegs. The second plurality of injection pegs are disposed in a second configuration upstream of the second set of fuel nozzles, along a second fuel path, and the second plurality of injection pegs are configured to route the fuel to the second set of fuel nozzles. The second configuration has at least one difference relative to the first configuration.
Description
Technical field
Theme of the present disclosure relates generally to combustion gas turbine systems, and more specifically, relates to for control combustion dynamic, and more specifically, for reducing the system and method for the dynamic modal coupling of burning.
Background technology
Combustion gas turbine systems comprises gas-turbine unit substantially, and it has compressor section, combustor section and turbine.Combustor section can comprise one or more burner (such as, burn pot) with fuel nozzle, and this fuel nozzle is configured to fuel and oxidant (such as air) are ejected in combustion chamber in each burner.In each burner, the mixture burns of fuel and oxidant generates hot combustion gas, and then it to flow in one or more stage of turbine in turbine and drive it.Each burner can generate burning dynamically, and this burning dynamically occurs at that time in one or more acoustic mode reciprocation or encourage of flame dynamically (being also known as the oscillationg component of Thermal release) and burner, causes the pressure oscillation in burner.
Burning dynamically can occur under multiple discrete frequency or across frequency range, and upstream can advance with downstream to relative to related burner.Such as, pressure and/or sound wave can such as enter in turbine to downstream through one or more stage of turbine, or upstream advance in fuel system.Some downstream component of turbine can potentially in response to burning dynamically, if the burning especially generated by independent burner dynamically presents and homophase each other and coherent relationships, and have the intrinsic of component or resonant frequency place or near frequency.As discussed herein, " coherence " can refer to the intensity of the linear relationship between two Dynamic Signals, and can be subject to the frequency overlap degree impact between them strongly.In some cases, " coherence " is the modal coupling or burner and the interactive measurement result of burner acoustics that are presented by combustion system.Therefore, need control combustion dynamically and/or dynamic modal coupling of burning, to be reduced in the possibility of any unwanted resonance vibration response (behavior of such as, resonating) of the component in turbine system.
Summary of the invention
Summarize some embodiment suitable mutually with original invention of advocating to protect in scope below.These embodiments are not intended to limit the scope of invention of this opinion protection, but these embodiments intention only provides the short summary of possibility form of the present invention.In fact, the present invention can contain various ways that can be similar or different from the embodiment proposed below.
In a first embodiment, system comprises gas-turbine unit, and it has the first burner and the second burner.First burner comprises first group of fuel nozzle and first multiple injection plunger.This first multiple injection plunger is configured in the upstream of this first group of fuel nozzle with the first structure along the first fuel path, and this first multiple injection plunger is configured to make fuel advance to this first group of fuel nozzle.This system also comprises second burner with second group of fuel nozzle and second multiple injection plunger.This second multiple injection plunger is configured in the upstream of this second group of fuel nozzle with the second structure along the second fuel path, and this second multiple injection plunger is configured to make fuel advance to this second group of fuel nozzle.This second structure first there is at least one difference relative to this.
In a second embodiment, system comprises the first turbine burner.First burner comprises first multiple fuel nozzle, and this first multiple fuel nozzle is configured to make air-fuel mixture advance to the combustion chamber of this first turbine burner.This more than first fuel nozzle comprises first group of fuel nozzle and second group of fuel nozzle.This system also comprises first multiple injection plunger, and this first multiple injection plunger is configured to make fuel advance to this first multiple fuel nozzle.These more than first are injected plungers and comprise relevant to this first group of fuel nozzle first group and injects plunger and second group of being correlated with this second group of fuel nozzle injects plunger.This first group is injected plunger and has at least one difference relative to this second group injection plunger.
In the third embodiment, method comprises utilizing and is configured in the first burning that more than first of the upstream of this first group of fuel nozzle inject the first orecontrolling factor first burner of plungers dynamically or first group of this first burner the first convection current time of injecting plunger along the first fuel path.The method also comprises, and utilizes and is configured in the second burning that more than second of the upstream of this second group of fuel nozzle inject the second orecontrolling factor second burner of plungers dynamically or second group of this second burner the second convection current time of injecting plunger along the second fuel path.These more than second are injected plunger and have at least one difference relative to these more than first injection plungers.
Technical scheme 1: a kind of system, comprising:
Gas-turbine unit, comprising:
First burner, it has first group of fuel nozzle and more than first injection plungers, wherein, described more than first are injected plunger is configured in described first group of fuel nozzle with the first structure upstream along the first fuel path, and described more than first injection plungers are configured to make fuel advance to described first group of fuel nozzle; With
Second burner, it has second group of fuel nozzle and more than second injection plungers, wherein, described more than second are injected plunger is configured in described second group of fuel nozzle with the second structure upstream along the second fuel path, and described more than second are injected plunger and are configured to make fuel advance to described second group of fuel nozzle, and described second structure there is at least one difference relative to described first.
Technical scheme 2: the system according to technical scheme 1, it is characterized in that, at least one difference described is configured by the first convection current time that the second convection current time of injecting plunger relative to described second group changes described first group of injection plunger, reduces the coherence between described first burner and described second burner.
Technical scheme 3: the system according to technical scheme 1, it is characterized in that, at least one difference described is configured by the first ratio changing the air-fuel mixture of described first group of fuel nozzle relative to the second ratio of the air-fuel mixture of described second group of fuel nozzle, and the burning changed between described first burner and described second burner is dynamic.
Technical scheme 4: the system according to technical scheme 1, it is characterized in that, described more than first inject plungers and described more than second at least one differences described injected between plunger and comprise described more than first at least one injecting plunger and inject plunger and described more than second at least one injecting plunger individual and inject difference between plunger.
Technical scheme 5: the system according to technical scheme 4, it is characterized in that, described more than first are injected plunger and comprise following at least one from described more than second at least one differences described injected between plunger: axially different structure, different circumference construct or different geometrical condition, or their any combination.
Technical scheme 6: the system according to technical scheme 5, it is characterized in that, described axially different structure comprise following at least one: the axially different placement between one or more axis of the described first or second burner, axially different place, axially different position or axially different layout, or their any combination.
Technical scheme 7: the system according to technical scheme 5, it is characterized in that, described different circumference structure comprise following at least one: the difference circumference placement between the first axle of described first and second burners, different circumferential place, different circumferential position or difference are circumferentially or their any combination.
Technical scheme 8: the system according to technical scheme 5, it is characterized in that, described different geometrical condition comprise following at least one: described more than first inject plungers and described more than second and inject different angles, different size or difformity between plunger or their any combination.
Technical scheme 9: the system according to technical scheme 1, it is characterized in that, described first group of fuel nozzle is arranged in one or more fuel circuit, and wherein, described more than first the first injection plungers injecting plunger are relevant with the second fuel circuit to the first fuel circuit of one or more fuel circuit described respectively with the second injection plunger.
Technical scheme 10: the system according to technical scheme 9, it is characterized in that, described first injects plunger comprises at least one difference relative to described second injection plunger, and wherein, at least one difference described comprises axially different structure, different circumference structure, different geometrical condition or their any combination.
Technical scheme 11: a kind of system, comprising:
First turbine burner, comprising:
More than first fuel nozzle, it is configured to make air-fuel mixture advance to the combustion chamber of described first turbine burner, and wherein, described more than first fuel nozzle comprises first group of fuel nozzle and second group of fuel nozzle; With
More than first is injected plunger, it is configured to make fuel advance to described more than first fuel nozzle, wherein, described more than first inject plungers comprise relevant to described first group of fuel nozzle first group injects plunger and second group relevant with described second group of fuel nozzle injects plunger, and described first group of injection plunger has at least one difference relative to described second group of injection plunger.
Technical scheme 12: the system according to technical scheme 11, it is characterized in that, at least one difference described is configured by the first convection current time that the second convection current time of injecting plunger relative to described second group changes described first group of injection plunger, reduces the coherence between the first burner and the second burner.
The system of technical scheme 13. according to technical scheme 11, is characterized in that, comprises the second turbine burner, and described second turbine burner comprises:
More than second fuel nozzle, it is configured to make described air-fuel mixture advance to the second combustion chamber of described second turbine burner, and wherein, described more than second fuel nozzle comprises the 3rd group of fuel nozzle and the 4th group of fuel nozzle; And
More than second is injected plunger, it is configured to make described fuel advance to described more than second fuel nozzle, wherein, described more than second inject plungers and comprise relevant to described 3rd group of fuel nozzle the 3rd group and injects plunger and the 4th group of being correlated with described 4th group of fuel nozzle injects plunger.
Technical scheme 14: the system according to technical scheme 13, is characterized in that, injects plunger or described 4th group of injection plunger relative to described 3rd group, described first group of injection plunger or described second group of injection plunger comprise at least one difference.
Technical scheme 15: the system according to technical scheme 14, it is characterized in that, at least one difference described is configured by the first ratio changing the air-fuel mixture of described first group of fuel nozzle relative to the second ratio of the air-fuel mixture of described second group of fuel nozzle, and the burning changed between described first burner and described second burner is dynamic.
Technical scheme 16: the system according to technical scheme 11, it is characterized in that, described first group is injected that plunger comprises axially different structure from least one difference described that described second group is injected between plunger, different circumference constructs, different geometrical condition or their any combination.
Technical scheme 17: the system according to technical scheme 11, is characterized in that, described first group of injection plunger or described second group of injection plunger comprise one group zero and inject plunger.
Technical scheme 18: a kind of method, comprising:
Utilize and be configured in along the first fuel path the first structure that more than first of first group of fuel nozzle upstream inject plungers and control the first convection current time that first group of dynamic or described first burner of the first burning of the first burner injects plunger; And
Utilize and be configured in along the second fuel path the second structure that more than second of second group of fuel nozzle upstream inject plungers and control the second convection current time that second group of dynamic or described second burner of the second burning of the second burner injects plunger, wherein, described more than second injection plungers have at least one difference relative to described more than first injection plungers.
Technical scheme 19: the method according to technical scheme 18, is characterized in that, at least one difference described comprises axially different structure, different circumference structure, different geometrical condition or their any combination.
Technical scheme 20: the method according to technical scheme 18, it is characterized in that, described more than first injection plungers and described more than second at least one differences described injected between plunger are configured to reduce the modal coupling between described first burner and described second burner.
Accompanying drawing explanation
When reading following detailed description with reference to accompanying drawing, these and other feature of the present invention, aspect and advantage will become better understood, and wherein, throughout accompanying drawing, identical label represents identical part, wherein:
Fig. 1 is the schematic diagram of the embodiment of the combustion gas turbine systems with multiple burner, this burner has corresponding fuel circuit structure, fuel circuit configurations be control combustion dynamically and/or dynamic modal coupling of burning, reduce the possibility of the unwanted vibratory response in downstream component;
Fig. 2 is the generalized section of the embodiment of in the burner of Fig. 1, and wherein, this burner comprises the first quaternary system (quaternary) fuel circuit structure, and this fuel circuit there is the axis injecting plunger and interlocks.
Fig. 3 is the generalized section of the embodiment of in the burner of Fig. 1, and wherein this burner comprises the second quaternary system fuel circuit structure, and this fuel circuit there is and injects plunger circumferentially.
Fig. 4 is the generalized section of the embodiment of the burner of the Fig. 3 obtained along 4-4 line, it illustrates around axis arranged and by towards biased quaternary (quat) plunger of the first fuel circuit; And
Fig. 5 is the generalized section of the embodiment of the combustion gas turbine systems of the Fig. 1 obtained along 5-5 line, it illustrates multiple burners with corresponding quaternary system fuel circuit structure, this fuel circuit configurations becomes control combustion dynamically and/or dynamic modal coupling of burning, and reduces the possibility of the unwanted vibratory response in downstream component.
Detailed description of the invention
One or more specific embodiment of the present invention will be described below.In order to provide the simple and clear description of these embodiments, all features of actual implementation can not be described in the description.Should be understood that, in the exploitation of any this actual implementation, as in any engineering or design object, the objectives that many implementations specifically determine to realize developer must be carried out, such as, meet the system that can change to another implementation from an implementation and to be correlated with the constraint relevant with business.And should be understood that, this development effort may be complicated and time-consuming, but will be design for enjoying those skilled in the art of benefit of the present disclosure, manufacture and the regular works of processing.
When introducing elements of various embodiments of the present invention, article " ", " one ", " being somebody's turn to do " and " described " refer to there is one or more element.Term " comprises, " comprising " and " having " is intended to comprise and refer to the add ons that can exist except the element listed.
Embodiment of the present disclosure relates to and reduces burning in combustion gas turbine systems dynamically and/or dynamic modal coupling of burning (such as, reducing the unwanted vibratory response in downstream component) by changing fuel circuit structure (such as the structure of quaternary system fuel circuit or manifold).Specifically, embodiment of the present disclosure relates to the structure changing the interior multiple injection plungers (such as quaternary plunger) changed of one or more quaternary system fuel circuit relevant to one or more burner of combustion gas turbine systems, makes the layout of quaternary plunger be configured to reduce the dynamic and/or unwanted vibratory response of intrasystem burning.
As above-mentioned, due to combustion process, to entering fluid stream (such as in burner, fuel, oxidant, diluent etc.) characteristic and various other factors, gas turbine combustor (or burner assembly) can produce burning dynamically.Burning can qualitatively be dynamically pressure oscillation under some frequency, pulsation, vibration and/or ripple.Fluid flow characteristics can comprise the fluctuation of speed, pressure, speed and/or pressure, the change (such as, turn to, shape, interruption etc.) of stream or their any combination.Jointly, burning dynamically can cause vibratory response in the various components in the upstream/of burner or downstream and/or resonance behavior potentially.Such as, burning dynamically (such as, in some frequency, under frequency range, amplitude, burner and burner stage etc.) not only upstream but also to downstream can enter in combustion gas turbine systems.If gas turbine combustor, upstream member and/or downstream component have the intrinsic or resonant frequency driven by these pressure oscillations (such as, burning dynamically), so pressure oscillation can cause vibration, stress, fatigue etc. potentially.This component can comprise combustion liner, burner flowing sleeve, burner cap, fuel nozzle, turbine nozzle, turbo blade, turbine shroud, turbine wheel, bearing, fuel supply component or their any combination.Downstream component allows people interested especially, because they are to homophase and relevant burning tone is more responsive.Thus, the possibility that coherence especially reduces the unwanted vibration in downstream component is reduced.
As discussed in detail below, embodiment of the present disclosure can be equipped with has special fuel loop layout (such as, quaternary system fuel circuit arrange) one or more gas turbine combustor, this fuel circuit arranges that the burning being configured to revise gas turbine combustor is dynamic, such as, frequency, amplitude, burner and burner coherence, frequency range or their any combination is changed.Specifically, multiple quaternary system plunger of each quaternary system fuel circuit system relevant to particular burner or quaternary plunger are (such as, inject plunger) layout can change convection current time of one or more quaternary plunger, and/or the fuel-gas ratio at nozzle level place, this can change burning dynamically in the mode of any unwanted vibratory response of the component and gas turbine combustor that significantly reduce or eliminate this turbine burner upstream and/or downstream.The Fuel-air ratio changing nozzle level place can revise the distribution of Thermal release, and it is dynamic that this changes flame, and therefore changes burning dynamically.In addition, the convection current time is the key factor of burning in dynamic frequency and/or amplitude.This convection current time refers to inject the delay between time and the time when fuel arrives combustion chamber and lights that fuel injected by the fuel port of gas turbine combustor.The axial location changing quaternary plunger changes the traveling time of fuel between quaternary plunger and flame zone, and therefore changes the convection current time.Usually, there is inversely related between convection current Time And Frequency.That is, when the convection current time increases, the frequency of combustion instability reduces, and when the convection current time reduces, the frequency of combustion instability increases.In addition, the convection current time changed between quaternary plunger can promote to be produced by quaternary plunger, or by the dynamic destructive interference of the burning impelled, this can reduce the dynamic amplitude of burning and/or change the dynamic frequency of burning.Such as, head end around burner axially and/or circumferentially changes the structure of quaternary plunger (such as, placement, layout, position, place etc.) the tuning of the convection current time of one or more quaternary plunger and/or the fuel-gas ratio at nozzle level place can be contributed to, and the amplitude with reduction can be caused, and/or frequency that is different relative to any resonant frequency of the component in combustion gas turbine systems and/or that be dispersed in larger frequency range, or the burning of their any combination is dynamic.In addition, change the geometrical condition of quaternary plunger (such as, size, shape, angle etc.) convection current time of one or more quaternary plunger can be introduced, and/or the change of the fuel-gas ratio aspect at nozzle level place, and the amplitude with reduction can be caused, and/or frequency that is different relative to any component resonant frequency frequency in combustion gas turbine systems and/or that be dispersed in larger frequency range, or the burning of their any combination is dynamic.
Except burner level (namely, independent turbine burner) on amendment outside, embodiment of the present disclosure can change the structure of the quaternary plunger in each quaternary system fuel circuit between multiple gas turbine combustor (such as, layout, place, position etc.), and/or geometrical condition (such as, angle, size, shape etc.), thus from burner to burner, change burning dynamically in the mode of the burning dynamic amplitude reduced between multiple gas turbine combustor and/or dynamic modal coupling of burning.Such as, change axially and/or circumferentially between the burner of system (between) or between (among) quaternary plunger structure (such as, placement, place, position, layout etc.) inducible burning dynamic frequency is (such as, different, the frequency be dispersed in larger frequency range, or their any combination) burner of aspect to burner change, thus reduce the possibility of the modal coupling of the burner at the frequency place of especially mating at the resonant frequency of the component with combustion gas turbine systems.Similarly, the geometrical condition (such as, size, shape, angle etc.) of quaternary plunger can between the burner of system or between change, to help to reduce unwanted vibratory response.
In view of aforementioned, Fig. 1 is the schematic diagram of the embodiment of the combustion gas turbine systems 10 with multiple burner 12, and wherein, each burner 12 is correlated with one or more quaternary system fuel circuit 13 (such as, quaternary fuel circuit 13).Each quaternary fuel circuit 13 can comprise multiple quaternary system plunger 14 (such as, injecting plunger, quaternary plunger), and wherein, fuel is injected burner 12 by fuel nozzle 18 upstream that each quaternary plunger 14 can be configured in burner 12.Such as, each quaternary burner loop 13 can comprise 1,2,3,4,5,6,7,8,9,10 or more quaternary plungers 14, its surrounding's layout in the upstream of fuel nozzle 18 (such as, main fuel spray nozzle 18) around burner 12.Can within burner 12 and/or between change structure and/or the geometrical condition of the quaternary plunger 14 of each quaternary fuel circuit 13, dynamic with the burning changed in particular burner 12 and/or between burner 12, thus any unwanted vibratory response contributed in the component in reduction system 10 downstream, as described in further detail below.Particularly, within burner 12 and/or change the structure of quaternary plunger 14 and/or geometrical condition can change convection current time between this quaternary plunger between burner 12, and/or the Fuel-air ratio between the fuel nozzle 18 relevant to this quaternary plunger 14, thus in particular burner 12 and/or between adjacent burners 12 and/or between multiple burner 12, reduce burning dynamic amplitude and/or change burning dynamic frequency, expect that this reduces the coherence of burner 12, as described in further detail below.
In the illustrated embodiment, gas-turbine unit 10 comprises one or more burner 12, compressor 11 and the turbine 16 separately with quaternary fuel circuit 13.Each quaternary fuel circuit 13 can comprise one or more quaternary plunger 14, fuel guides to burner 12 from one or more fuels sources by its upstream that can be configured to one or more fuel nozzle in burner 12 18 (such as, 1,2,3,4,5,6 or more).Burner 12 light in combustion chamber 19 and burn pressurization oxidant (such as, air) and fuel mixture is (such as, air-fuel mixture), and then the hot pressurized combustion gases 24 (such as, waste gas) of gained is led in turbine 16.In certain embodiments, fuel nozzle 18 can be grouped in one or more main fuel loop (such as, 1,2,3,4,5 or more fuel circuits), comprises one or more fuel nozzle 18 in this each main fuel loop.Each main fuel loop can be relevant to fuels sources.The fuel nozzle 18 relevant to one or more main fuel loop also can be correlated with one or more quaternary plunger 14, such as, fuel can be injected flow passage 64 (as shown in Figure 2) by one or more quaternary plunger 14, at this, it mixed with the air stream 67 from compressor discharge 68 (as shown in Figure 2) before entering one or more fuel nozzle 18 relevant to one or more fuel circuit, thus generation fuel-air mixture, then fuel-air mixture enters fuel nozzle 18, extra fuel is injected by by fuel nozzle 18 at this.In certain embodiments, change the structure of quaternary plunger 14 and/or the convection current time of geometrical condition one or more quaternary plunger tunable and/or the air/fuel ratio of one or more fuel nozzle 18 relevant to quaternary plunger 14, thus burner 12 in and/or between the burner 12 of system 10, change is burnt dynamic amplitude and/or frequency.
Specifically, the structure of change quaternary plunger 14 and/or geometrical condition can change the convection current time of one or more quaternary plunger, and/or the Fuel-air ratio of one or more fuel nozzle 18.Therefore, changed the convection current time of one or more quaternary plunger by the structure of quaternary plunger and/or geometrical condition, and/or the Fuel-air ratio of one or more fuel nozzle 18 can revise burner 12 and/or system 10 burner between the burning of gained dynamic.Amendment burning dynamically can reduce again the possibility of the unwanted vibratory response in burner 12 and/or downstream component.Such as, in certain embodiments, the burner 12 of system 10 can be identical, except the structure of the quaternary plunger 14 in each burner 12 and/or the change of geometrical condition aspect.Therefore, the structure of the quaternary plunger 14 between burner 12 and/or the change of geometrical condition aspect can contribute to the dynamic modal coupling of burning revised or reduce between burner 12.
Turbo blade in turbine 16 is attached to the axle 26 of combustion gas turbine systems 10, and it also can be attached to other components some throughout turbine system 10.At burning gases 24 relative to the turbo blade of turbine 16 and when flowing between which, turbine 16 is driven in rotation, this causes axle 26 to rotate.Finally, burning gases 24 leave turbine system 10 via waste gas outlet 28.In addition, in the illustrated embodiment, axle 26 is attached to load 30, load 30 by the rotation of axle 26 by energy supply.This load 30 can be any suitable device of the moment of torsion generating power by turbine system 10, such as generator, wind stick or other loads.
The compressor 11 of combustion gas turbine systems 10 comprises compressor blade.As discussed above, the compressor blade in compressor 11 is attached to axle 26, and will rotate when axle 26 is driven in rotation by turbine 16.When compressor blade rotates in compressor 11, compressor 11 compresses the air (or any suitable oxidant) received from air intlet 32 and produces forced air 34.Then forced air 34 is supplied in the fuel nozzle 18 of burner 12.As above-mentioned, fuel nozzle 18 mixes forced air 34 and fuel, produces the suitable mixing ratio for burning.In discussion below, reference can be carried out to the axial direction of burner 12 or axis 42 (such as, longitudinal axis), the radial direction of burner 12 or the circumferential direction of axis 44 and burner 12 or axis 46.
In certain embodiments, axially and/or circumferentially the structure of the quaternary plunger 14 of change quaternary fuel circuit 13 and/or the geometrical condition (such as, shape, size, angle etc.) of change quaternary plunger 14 can contribute to the burner 12 in reduction system 10 and/or the unwanted vibratory response in downstream turbine component.Such as, in the illustrated embodiment, system 10 comprises first burner 17 relevant to the first quaternary fuel circuit 13 and second burner 21 relevant with the second quaternary fuel circuit 13.Each quaternary fuel circuit 13 can be configured to make fuel and/or air/fuel mixture to advance to multiple quaternary plungers 14 of fuel nozzle 18 relevant.In certain embodiments, the structure of relevant from particular burner 12 multiple quaternary plungers 14 can with different with the structure of adjacent or that non-conterminous burner 12 is relevant multiple quaternary plungers 14.Such as, the circumferential direction 46 that first group of relevant with the first burner 17 quaternary plunger 14 can be similar to along first axle 48 along system 10 configures.In the illustrated embodiment, second group of relevant to the second burner 21 quaternary plunger 15 can configure along the second axis 50 being approximately parallel to axis 48.Specifically, second group of quaternary plunger 15 axially can interlock relative to first group of quaternary plunger 14, makes first of quaternary plunger 14 the structure construct different from second of quaternary plunger 15.
Although the axis of the quaternary plunger 14 between the embodiment illustrated describes by the adjacent burners 12 of system 10 is interlocked change the structure of quaternary plunger 14, but it should be noted that the structure of quaternary plunger 14 by along 1,2,3,4,5,6 or more axial locations circumferentially the quaternary plunger 14 of direction 46 axially between 2,3,4,5,6 in interleaving systems 10 or more burner 12 change.In certain embodiments, by particular burner 12 along 1,2,3,4,5,6 or more axial locations circumferentially direction 46 axially staggered quaternary plunger 14 in this particular burner 12 (as further illustrated in fig. 2), change the structure of quaternary plunger 14.In addition, in certain embodiments, it should be noted that the structure of the quaternary plunger 14 between one or more burner 12 changes, as further described with reference to figure 3-5 by the quaternary plunger 14 that circumferentially distributes with various structure.
Fig. 2 is the generalized section of the embodiment of burner 12 in the system 10 of Fig. 1, wherein, burner 12 comprises the first quaternary system fuel circuit structure, at this, quaternary plunger 14 (such as, injecting plunger) circumferentially axially interlocks in direction 46 in 1,2,3,4,5,6 an or more axial positions.As mentioned above with reference to Fig. 1, the structure of quaternary plunger 14 is changing by be between one or more burner 12 axially staggered quaternary plunger 14 at one or more axial location 48,50.In the illustrated embodiment, in single burner 12, change quaternary plunger 14, make this quaternary plunger 14 along the first axial location 48, second axial location 50 and the 3rd axial location 52 circumferentially interlock along the circumferential direction 46 of system 10.As above mentioned, in burner 12, change quaternary plunger 14 structure and/or geometrical condition can change the convection current time of one or more quaternary plunger and/or the Fuel-air ratio of the fuel nozzle 18 relevant to quaternary plunger 14, thus the burning dynamic amplitude reduced in system 10, expect that this reduces the unwanted vibratory response in combustion gas turbine systems 10.
In the illustrated embodiment, burner 12 comprises head end 54 and combustion chamber 19.The head end 54 of burner 12 encapsulates cap assembly 56 and fuel nozzle 18 substantially, such as 1,2,3,4,5,6,7 or more fuel nozzles 18.In certain embodiments, fuel nozzle 18 makes fuel, air, fuel-air mixture and sometimes make other liquid advance to combustion chamber 19.Specifically, fuel nozzle 18 can be grouped or be arranged in one or more different fuel circuit, make each fuel circuit comprise one or more fuel nozzle 18, and wherein, each fuel circuit can make fuel and/or air/fuel mixture advance from one or more fuels sources.Burner cap assembly 56 configures along a part for the length of fuel nozzle 18, thus is contained in burner 12 by fuel nozzle 18.Each fuel nozzle 18 contributes to the mixing of forced air and fuel, and guides mixture by burner cap assembly 56 and enter in combustion chamber 19.Then air-fuel mixture can burn in the main combustion zone 57 of combustion chamber 19, thus produces the hot pressurised exhaust gas flowed along downstream direction 69.These pressurised exhaust gas drive the blade rotary in turbine 16.Burner 12 has axis 42 circumferentially 46 one or more walls extended around combustion chamber 19 and burner 12, and one that substantially represents in the multiple burners 12 circumferentially configured around the rotation (such as, axle 26) of combustion gas turbine systems 10 with the layout at interval.
Each burner 12 comprises outer wall (such as, flow sleeve 58), and it circumferentially configures around inwall (such as, combustion liner 60), and to limit intermediate flow path or space 64, and combustion liner 60 circumferentially extends around combustion chamber 19.Inwall 60 also can comprise transition piece 66, and it is restrained towards the first order of turbine 16 substantially.Impingement sleeve 59 circumferentially configures around transition piece 66.Lining 60 limits the inner surface of burner 12, this inner surface directly towards and be exposed to combustion chamber 19.Flow sleeve 58 and impingement sleeve 59 comprise multiple perforation 61, and the air stream 67 from compressor discharge 68 is directed in flow passage 64 by perforation 61, also make air impact lining 60 and transition piece 66, for impinging cooling simultaneously.Flow passage 64 then along updrift side towards head end 54 (such as, downstream direction 69 relative to hot combustion gas) draw airflow guiding 67, make air stream 67 flowing through burner cap assembly 56, through fuel nozzle 18 and the cooling bushing 60 that takes a step forward entering combustion chamber 19.
In certain embodiments, burner 12 can comprise quaternary system fuel circuit 13, and quaternary system fuel circuit 13 has the multiple quaternary plungers 14 being in different structure and/or geometrical condition.Particularly, quaternary plunger 14 circumferentially can configure around burner 12 near head end.In certain embodiments, the air stream 67 flowing through burner cap assembly 56 can run into the quaternary plunger 14 relevant to fuel nozzle 18.Particularly, quaternary plunger 14 can be configured to fueling charger, and a part for fuel is injected air stream 67 in the upstream of fuel nozzle 18 by it.Especially, the fuel nozzle 18 that one or more quaternary plunger 14 can be corresponding to one or more is relevant.In certain embodiments, each fuel nozzle 18 can be relevant to one or more quaternary plunger 14.In addition, in certain embodiments, one or more quaternary plunger 14 can be relevant with one group of fuel nozzle 18, one group of fuel nozzle 18 in such as special fuel loop, as explained further with reference to figure 5.The fuel injected by quaternary plunger 14 can be provided by one or more fuels sources being connected to quaternary fuel circuit 13 via fuel manifold.In certain embodiments, quaternary plunger 14 can comprise with the downstream direction 69 of burner 12 in the face of and/or approximately perpendicularly one or more fuel openings (not shown) angled.The fuel provided by quaternary plunger 14 can mix with the air stream 67 flowed towards fuel nozzle 18, to form air/fuel mixture, then makes this this air/fuel mixture advance to combustion chamber 19 via fuel nozzle 18.
As above mentioned, the structure of quaternary plunger 14 is changed (such as between burner 12, position, place, layout, placement, axially staggered, circumference change) and/or geometrical condition is (such as, size, shape, angle etc.) convection current time of one or more quaternary plunger can be changed between burner 12, and/or the Fuel-air ratio of the fuel nozzle 18 relevant to quaternary plunger 14, thus reduce burning dynamic amplitude, and/or between burner, change burning dynamic frequency, expect that this reduces the dynamic modal coupling of burning.Such as, in the embodiment illustrated of burner 12, first group of quaternary plunger 14 is similar to and configures along the first axial location 48, second group of quaternary plunger 15 is similar to and configures along the second axial location 50, and the 3rd group of quaternary plunger 23 is approximate configures along the 3rd axial location 52, make the contiguous head end 54 of each group of quaternary plunger 14,15 and 23 and the surrounding around burner 12 axially interlocks.Each group of quaternary plunger 14 can comprise 0,1,2,3,4,5,6,7,8,9,10 or more the quaternary plunger 14 being configured to make fuel to advance towards one or more special fuel nozzle 18.In certain embodiments, axially staggered quaternary plunger 14 can change the convection current time of one or more quaternary plunger, and/or can change the air/fuel ratio of one or more fuel nozzle 18.Such as, in the illustrated embodiment, the air/fuel ratio of one or more fuel nozzle 18 relevant with first group of quaternary plunger 14 (it has three quaternary plungers 14) can be different from the air/fuel ratio with one or more fuel nozzle 18 of the 3rd group of quaternary plunger 14 (it has four quaternary plungers 14), thus the burning changing burner 12 is dynamic, to reduce the unwanted vibratory response in burner and/or in downstream component.
Although the embodiment illustrated describes each group of quaternary plunger 14,15 and 23 with approximate same size and/or shape, but should be noted that, in certain embodiments, each quaternary plunger 14 and/or each group quaternary plunger 14,15 or 23 can have different geometrical conditions (such as, size, shape, angle etc.).Such as, in certain embodiments, first group of quaternary plunger 14 relative to second group of quaternary plunger 15 can in size difference (such as, being the ratio of 1:1,1.5:1,2:1,2.5:1 etc.).Similarly, first group of quaternary plunger 14 can vpg connection difference (such as square, conical etc.) relative to second group of quaternary plunger 15, or different angles can be in relative to second group of quaternary plunger 15, thus the burning changing burner 12 is dynamic, to reduce the unwanted vibratory response in combustion gas turbine systems 10.Such as, quaternary plunger 14 can comprise in the face of burner 12 downstream direction 69 and/or with its approximately perpendicularly one or more fuel openings (not shown) angled.In certain embodiments, the angle relative to downstream direction 69 of the fuel openings on specific quaternary plunger 14 is from fuel openings and another quaternary plunger 14 upper shed different relative to the angle of downstream direction 69 (such as, large or little approximate 1,2,3,4,5,10,15,20,30,40,50,60,70,80,90,100,110,120,130,140,150,160,170,180 degree).In other embodiments, whole quaternary plunger 14 can be approximately perpendicularly angled with downstream direction 69, the angle of specific quaternary plunger 14 is made to be different from the angle (such as, large or little approximate 1,2,3,4,5,10,15,20,30,40,50,60,70,80,90,100,110,120,130,140,150,160,170,180 degree) of another quaternary plunger 14.
In certain embodiments, as further described with reference to figure 3, by the quaternary plunger 14 that distributes in various structure in circumferential direction 46 along specific axial location, the structure of quaternary plunger 14 can be changed at single axial location (such as, the first axial location 48, second axial location 50 or the 3rd axial location 52) place in particular burner 12.In addition, in certain embodiments, as further described with reference to figure 5, by differently circumferentially scattering quaternary plunger 14 in specific axial positions in various structure in a burner 12 compared with at least one other burner 12, can in system 10 between adjacent burners 12 and/or change the structure of quaternary plunger 14 between multiple burner 12.
Fig. 3 is the generalized section of the embodiment of burner 12 in the system 10 of Fig. 1, in FIG, burner 12 comprises the second quaternary system fuel circuit structure, it has the quaternary plunger 14 of specific axial positions (such as, inject plunger) circumference scatter (that is, circumferentially axis 46).Such as, in the illustrated embodiment, the 4th group of quaternary plunger 25 comprising five quaternary plungers 14 and the 5th group of quaternary plunger 27 comprising three quaternary plungers 14 approximate along the second axial location 50 circumferentially axis 46 circumferentially configure (such as, arrange, construct).Specifically, each group quaternary plunger 25,27 can be configured to make fuel advance to the particular group (such as, comprising the fuel circuit of one or more fuel nozzle 18) of one or more special fuel nozzle 18 and/or fuel nozzle 18.As above mentioned, the structure changing quaternary plunger 14 in burner 12 can change the convection current time of one or more quaternary plunger 14 and/or change the Fuel-air ratio of one or more fuel nozzle 18 relevant to one or more quaternary plunger 14, thus reduces coherence and reduce the unwanted vibratory response in system 12 and in downstream component.
In certain embodiments, quaternary plunger 14 can be similar to and be configured in single axial location (such as, second axial location 50) place, quaternary plunger 14 is made circumferentially to arrange in various configurations and be correlated with the group (such as, comprising the fuel circuit of one or more fuel nozzle 18) of various fuel nozzle 18 and/or various fuel nozzle 18.Such as, in the illustrated embodiment, the 4th group of 25 quaternary plunger 14 comprising five quaternary plungers 14 can away from the layout spatially of the 5th group of 27 quaternary plunger 14 and/or the gathering comprising three quaternary plungers 14.In such an embodiment, as further described with reference to figure 4, each group of quaternary plunger 14 (such as, 4th group 25 and/or the 5th group 27) can be relevant to one or more fuel nozzle 18, such as single fuel nozzle 18 and/or be grouped into the group of the fuel nozzle 18 in single fuel circuit.Each group of quaternary plunger 14 can comprise 0,1,2,3,4,5,6,7,8,9,10 of the Fuel-air ratio being configured to the particular group increasing or reduce special fuel nozzle 18 or fuel nozzle 18 or more a quaternary plunger 14.In certain embodiments, the specific axial positions in various circumference structure circumferentially configures the air-fuel ratio that quaternary plunger 14 can change one or more fuel nozzle 18 relevant to one or more quaternary plunger 14.Such as, in the embodiment illustrated of Fig. 3, the air/fuel ratio of the fuel nozzle 18 relevant to the 4th group of quaternary plunger 25 (it has 5 quaternary plungers 14) can be different from the air-fuel ratio of one or more fuel nozzle 18 relevant with the 5th group of quaternary plunger 27 (it has 3 quaternary plungers 14).In addition, the air-fuel ratio of one or more neither also not relevant with the 5th group of quaternary plunger 27 from the 4th group of quaternary plunger 25 fuel nozzle also can be different, thus the burning changing burner 12 is dynamic, to reduce the unwanted vibratory response in burner 12 or in downstream component.
In certain embodiments, except various quaternary plunger 14 constructs (such as, specific axial location 48,50 or 52 place is circumferentially) outside, each quaternary plunger 14 and/or each group quaternary plunger 25 or 27 also can have different geometrical conditions (such as, size, shape, angle etc.).Such as, in certain embodiments, 4th group of quaternary plunger 25 can in size, difference be (such as relative to the 5th group of quaternary plunger 25, ratio for approximate 1:1,1.5:1,2:1,2.5:1 etc.), make one or more quaternary plunger 14 from the 4th group 25 be greater than or less than size from one or more quaternary plunger 14 of the 5th group 27.Similarly, 4th group of quaternary plunger 25 can in vpg connection difference (such as relative to the 5th group of quaternary plunger 25, square, conical etc.), or different angles can be had relative to the 5th group of quaternary plunger 27, thus the burning changing burner 12 is dynamic, to reduce the unwanted vibratory response in burner 12 or in downstream component.Such as, quaternary plunger 14 can comprise in the face of burner 12 downstream direction 69 and/or with its approximately perpendicularly angled one or more fuel openings (not shown).In certain embodiments, fuel openings on specific quaternary plunger 14 can be greater than or less than the angle (such as, large or little 1,2,3,4,5,10,15,20,30,40,50,60,70,80,90,100,110,120,130,140,150,160,170,180 degree) of the fuel openings on another quaternary plunger 14 relative to downstream direction 69 relative to the angle of downstream direction 69.
Fig. 4 is the generalized section of the embodiment 69 of the burner 12 of Fig. 3, and it illustrates circumferentially to arrange at the second axial location 50 place and to be biased by the quaternary plunger 14 towards the first fuel circuit 72.In certain embodiments, burner 12 can comprise a four or more fuel circuit, such as the first fuel circuit 72, center fuel loop 74, second fuel circuit 76 and one or more quaternary fuel circuit 13.Particularly, the first fuel circuit 72 can comprise three fuel nozzles 18 (such as, the first fuel nozzle 73, second fuel nozzle 75 and the 3rd fuel nozzle 77).In addition, center fuel loop 74 can comprise single fuel nozzle and the second fuel circuit 76 can comprise two fuel nozzles 18 (such as, the 4th fuel nozzle 79 and the 5th fuel nozzle 81).Specifically, each fuel nozzle 18 and/or each fuel circuit (such as the first fuel circuit 72, center fuel loop 74 or the second fuel circuit 76) can be configured to make fuel to advance to one or more quaternary plunger 14 of respective fuel injector 18 and/or corresponding fuel circuit (such as, one or more fuel nozzle 18) relevant.Therefore, quaternary plunger 14 can be configured to the air/fuel ratio changing the fuel nozzle 18 relevant to quaternary plunger 14 and/or fuel circuit, thus reduces coherence and reduce the unwanted vibratory response in burner 12 and/or downstream component.
In certain embodiments, multiple quaternary plunger can be relevant to one or more fuel nozzle 18 of burner 12.Such as, in the illustrated embodiment, the 4th group of quaternary plunger 25 is relevant to the first fuel circuit 72 with the 5th group of quaternary plunger 27.Particularly, the 4th group of quaternary plunger 25 and the 5th group of quaternary plunger 27 can be relevant with the 3rd fuel nozzle 77 to the first fuel nozzle 73, second fuel nozzle 75.Therefore, the 4th group of quaternary plunger 25 and the 5th group of quaternary plunger 27 can be configured to fueling charger, to advance or be injected in air stream 67 to make a part for fuel in the upstream of the fuel nozzle 18 relevant to the first fuel circuit 72.In this way, relevant to the first fuel circuit 72 quaternary plunger 14 can be configured to the air/fuel ratio changing or be biased the first fuel circuit 72 relative to the second fuel circuit 76 and/or center fuel loop 74.In addition, as above mentioned, the air/fuel ratio changing fuel nozzle 18 can reduce burning dynamic amplitude and/or coherence and the unwanted vibratory response that can therefore reduce in burner 12 and/or downstream component.
In certain embodiments, quaternary plunger 14 (such as, one or more quaternary plunger 14 and/or a group or more groups quaternary plunger 14) can be arranged to towards any fuel nozzle 18 and/or fuel circuit (such as, second fuel circuit 76 and/or center fuel loop 74) biased flow in fuel, to make between fuel circuit and air/fuel ratio therefore between fuel nozzle 18 in burner 12 and/or between different.In addition, except changing the structure of the axial and circumferential of quaternary plunger 14, make quaternary plunger 14 biased by outside the quaternary loop flow in fuel of some fuel nozzle 18 and/or some fuel circuit, in certain embodiments, the geometrical condition of quaternary plunger 14 can be different between each fuel nozzle 18 and/or each fuel circuit.Such as, the size of the quaternary plunger 14 relevant to the first fuel circuit 72, shape and/or angle can be different from and relevant those of the second fuel circuit 76 or center fuel loop 74, to make between fuel circuit and convection current time therefore between fuel nozzle 18 and/or air/fuel ratio can within burner 12 and/or between different.
Fig. 5 is the generalized section of embodiment of the combustion gas turbine systems 10 of the Fig. 1 intercepted along 5-5 line, it illustrates multiple burners 12 separately with corresponding quaternary plunger 14 structure, this configurations becomes control combustion dynamically and/or dynamic modal coupling of burning, to reduce the possibility of the unwanted vibratory response in downstream component.Particularly, it should be noted that each quaternary plunger 14 structure can comprise any change technique (such as, the change of the aspect such as axial staggered, circumferential placement and/or size, shape, angle) and/or can comprise any combination of change technique.Each change technique, can be configured to contribute to reducing the dynamic amplitude and/or reduce coherence, to reduce the unwanted vibratory response in the downstream component in system 10 of burning individually or with other change technique in combination.In addition, as described further below, quaternary plunger 14 constructs and can change with the different pattern in system 10 or grouping.
In certain embodiments, the structure of quaternary plunger 14 can be biased quaternary fuel towards one or more fuel circuit, makes adjacent burners 12 have quaternary plunger 14 towards different fuel loop offset fuel.Such as, in the illustrated embodiment, first structure 70 of the quaternary plunger 14 in the first burner 17 is configured to be biased quaternary flow in fuel towards the first fuel circuit 72, makes the fuel nozzle 73,75 and 77 of the first burner 17 have the air/fuel ratio be differently biased with other fuel circuits of the first burner 17.In addition, the quaternary plunger 14 of the second structure 78 is arranged to be biased quaternary flow in fuel towards the second fuel circuit 76, makes the fuel nozzle 79 and 81 of the second burner 21 have the air/fuel ratio be differently biased with other fuel circuits of the second burner 21.And, first structure 70 of quaternary plunger 14 can be different from the second structure 78 of quaternary plunger 14, make the first burner 17 have different burning dynamic frequencies relative to the second burner 20, thus reduce coherence and reduce the unwanted vibratory response in combustion gas turbine systems 10.
In certain embodiments, the geometrical condition of quaternary plunger 14 can change between burner 12, makes particular burner 12 have different burning dynamic frequencies relative at least one other burner 12.Such as, in the illustrated embodiment, first structure 70 of the quaternary plunger 14 in the first burner 17 comprises and constructs quaternary plunger 14 shape of 80 (such as with the 3rd of the quaternary plunger 14 in the 3rd burner 83 the, square) different quaternary plunger 14 shape (such as, circular).In certain embodiments, the size of quaternary plunger 14 can change between burner 12.Such as, the 4th structure 82 in the 4th burner 85 comprise construct 84 with the 5th in the 5th burner quaternary plunger 14 compared with quaternary plunger 14 different in size.Especially, the quaternary plunger 14 of the 4th structure 82 dimensionally can be less, makes the ratio between the quaternary plunger of the 4th and the 5th structure 82,84 to be approximately 1:1,1.5:1,2:1,2.5:1 etc.
In certain embodiments, except the change relevant with geometrical condition, the structure of quaternary plunger 14 (such as, 3rd structure 80 is relative to the first structure 70) also comprise and to interlock with the axis along various axis and/or the circumference of quaternary plunger 14 locates relevant change, to be biased quaternary fuel towards other fuel circuits.In this way, the combination of different parameters can be used for helping to reduce the unwanted vibratory response in the downstream component in coherence and reduction system 10.In addition, in certain embodiments, particular burner 12 can not have any change in quaternary plunger 14 and/or can without any quaternary plunger 14 relative to other burners 12.Such as, in the 6th structure 86 in the 6th burner 89, quaternary plunger 14 is not had to be configured in burner 89.In this way, the 6th burner 89 can have the burning dynamic frequency different from the first burner 17, second burner 21, the 3rd burner 83, the 4th burner 85 and/or the 5th burner 87.
In certain embodiments, system 10 can comprise one or more grouping (such as, 1,2,3,4,5 or more) of burner 12, wherein, each group of burner 12 comprises one or more burner 12 (such as, 1,2,3,4,5 or more).In some cases, each group burner 12 can comprise from system 10 one or more other organize the different identical burner 12 of burner 12.Such as, first group of burner 12 can comprise the identical burner 12 of first structure with quaternary plunger 14, and second group of burner 12 can comprise the second identical burner 12 constructed with quaternary plunger 14.In addition, the first structure of quaternary plunger 14 can construct different in one or more from second of quaternary plunger 14, as described above the change etc. of staggered, circumferential placement and/or size, shape, angle aspect (such as, axially).Therefore, first group of burner 12 can produce the burning dynamic frequency different from the burning dynamic frequency of group burner of second in system 10 12.
Technique effect of the present invention comprises by changing the multiple injection plungers 14 relevant to one or more burner 12 of combustion gas turbine systems 10 (such as, quaternary plunger 14) structure reduce burning in combustion gas turbine systems 10 dynamically and/or dynamic modal coupling of burning (such as, reducing unwanted vibratory response in downstream component).The layout of the multiple quaternary plungers 14 relevant to particular burner 12 can change in the mode of the unwanted vibratory response significantly reducing or eliminating the component in burner and/or burner 12 downstream burns dynamically.Such as, axially and/or circumferentially change the structure of quaternary plunger 14 (such as, placement, layout, position, place etc.) the tuning of the convection current time of one or more quaternary plunger and/or the Fuel-air ratio at fuel nozzle 18 level place can be contributed to, and relative to any resonant frequency of the component in combustion gas turbine systems 10, and/or one or more burning in other burners 12 in combustion gas turbine systems 10 is dynamic, can cause difference, be dispersed in burning dynamic frequency in larger frequency range or their any combination.In addition, change the geometrical condition of quaternary plunger 14 (such as, size, shape, angle etc.) change of the Fuel-air ratio between convection current time between two or more quaternary plungers and/or two or more fuel nozzles 18 can be introduced, and therefore can contribute to reducing burning dynamic amplitude and/or dynamic modal coupling of burning, this can reduce the burner 12 in system 10 and/or the unwanted vibratory response in downstream component.
This written explanation use-case, with open the present invention, comprises preferred forms, and enables any those skilled in the art put into practice the present invention, comprises and manufactures and use any equipment or system and carry out the method for any merging.Patentable scope of the present invention is defined by the claims, and can comprise the example that other those skilled in the art expect.If other examples this have not different from the word language of claim structural details, if or other examples this comprise and the equivalent structural elements of the word language of claim without marked difference, then this other examples intention within the scope of the claims.
Claims (10)
1. a system, comprising:
Gas-turbine unit, comprising:
First burner, it has first group of fuel nozzle and more than first injection plungers, wherein, described more than first are injected plunger is configured in described first group of fuel nozzle with the first structure upstream along the first fuel path, and described more than first injection plungers are configured to make fuel advance to described first group of fuel nozzle; With
Second burner, it has second group of fuel nozzle and more than second injection plungers, wherein, described more than second are injected plunger is configured in described second group of fuel nozzle with the second structure upstream along the second fuel path, and described more than second are injected plunger and are configured to make fuel advance to described second group of fuel nozzle, and described second structure there is at least one difference relative to described first.
2. system according to claim 1, it is characterized in that, at least one difference described is configured by the first convection current time that the second convection current time of injecting plunger relative to described second group changes described first group of injection plunger, reduces the coherence between described first burner and described second burner.
3. system according to claim 1, it is characterized in that, at least one difference described is configured by the first ratio changing the air-fuel mixture of described first group of fuel nozzle relative to the second ratio of the air-fuel mixture of described second group of fuel nozzle, and the burning changed between described first burner and described second burner is dynamic.
4. system according to claim 1, it is characterized in that, described more than first inject plungers and described more than second at least one differences described injected between plunger and comprise described more than first at least one injecting plunger and inject plunger and described more than second at least one injecting plunger individual and inject difference between plunger.
5. system according to claim 4, it is characterized in that, described more than first are injected plunger and comprise following at least one from described more than second at least one differences described injected between plunger: axially different structure, different circumference construct or different geometrical condition, or their any combination.
6. system according to claim 5, it is characterized in that, described axially different structure comprise following at least one: the axially different placement between one or more axis of the described first or second burner, axially different place, axially different position or axially different layout, or their any combination.
7. system according to claim 5, it is characterized in that, described different circumference structure comprise following at least one: the difference circumference placement between the first axle of described first and second burners, different circumferential place, different circumferential position or difference are circumferentially or their any combination.
8. system according to claim 5, it is characterized in that, described different geometrical condition comprise following at least one: described more than first inject plungers and described more than second and inject different angles, different size or difformity between plunger or their any combination.
9. system according to claim 1, it is characterized in that, described first group of fuel nozzle is arranged in one or more fuel circuit, and wherein, described more than first the first injection plungers injecting plunger are relevant with the second fuel circuit to the first fuel circuit of one or more fuel circuit described respectively with the second injection plunger.
10. system according to claim 9, it is characterized in that, described first injects plunger comprises at least one difference relative to described second injection plunger, and wherein, at least one difference described comprises axially different structure, different circumference structure, different geometrical condition or their any combination.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14/288974 | 2014-05-28 | ||
| US14/288,974 US20150345794A1 (en) | 2014-05-28 | 2014-05-28 | Systems and methods for coherence reduction in combustion system |
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| CN105318354A true CN105318354A (en) | 2016-02-10 |
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| JP (1) | JP2015224867A (en) |
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| US9845956B2 (en) * | 2014-04-09 | 2017-12-19 | General Electric Company | System and method for control of combustion dynamics in combustion system |
| US11156164B2 (en) | 2019-05-21 | 2021-10-26 | General Electric Company | System and method for high frequency accoustic dampers with caps |
| US11174792B2 (en) | 2019-05-21 | 2021-11-16 | General Electric Company | System and method for high frequency acoustic dampers with baffles |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101586812A (en) * | 2008-05-20 | 2009-11-25 | 通用电气公司 | Methods and systems for combustion dynamics reduction |
| CN101818907A (en) * | 2009-01-30 | 2010-09-01 | 通用电气公司 | Be used for suppressing the system and method for turbine combustion instability |
| CN102087026A (en) * | 2009-12-08 | 2011-06-08 | 通用电气公司 | Fuel injection in secondary fuel nozzle |
| CN102183020A (en) * | 2010-01-15 | 2011-09-14 | 通用电气公司 | Premix fuel nozzle internal flow path enhancement |
| CN102213426A (en) * | 2010-04-06 | 2011-10-12 | 通用电气公司 | Segmented annular ring-manifold quaternary fuel distributor |
| CN103080653A (en) * | 2011-03-16 | 2013-05-01 | 三菱重工业株式会社 | Gas turbine combustor and gas turbine |
| CN103629698A (en) * | 2012-08-21 | 2014-03-12 | 通用电气公司 | System and method for reducing modal coupling of combustion dynamics |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6269646B1 (en) * | 1998-01-28 | 2001-08-07 | General Electric Company | Combustors with improved dynamics |
| US20070107437A1 (en) * | 2005-11-15 | 2007-05-17 | Evulet Andrei T | Low emission combustion and method of operation |
| US7966820B2 (en) * | 2007-08-15 | 2011-06-28 | General Electric Company | Method and apparatus for combusting fuel within a gas turbine engine |
| US20110072826A1 (en) * | 2009-09-25 | 2011-03-31 | General Electric Company | Can to can modal decoupling using can-level fuel splits |
| JP2011111964A (en) * | 2009-11-26 | 2011-06-09 | Mitsubishi Heavy Ind Ltd | Gas turbine combustor |
-
2014
- 2014-05-28 US US14/288,974 patent/US20150345794A1/en not_active Abandoned
-
2015
- 2015-05-18 DE DE102015107767.1A patent/DE102015107767A1/en not_active Withdrawn
- 2015-05-21 JP JP2015103293A patent/JP2015224867A/en active Pending
- 2015-05-21 CH CH00713/15A patent/CH709640A8/en not_active Application Discontinuation
- 2015-05-28 CN CN201510280947.7A patent/CN105318354A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101586812A (en) * | 2008-05-20 | 2009-11-25 | 通用电气公司 | Methods and systems for combustion dynamics reduction |
| CN101818907A (en) * | 2009-01-30 | 2010-09-01 | 通用电气公司 | Be used for suppressing the system and method for turbine combustion instability |
| CN102087026A (en) * | 2009-12-08 | 2011-06-08 | 通用电气公司 | Fuel injection in secondary fuel nozzle |
| CN102183020A (en) * | 2010-01-15 | 2011-09-14 | 通用电气公司 | Premix fuel nozzle internal flow path enhancement |
| CN102213426A (en) * | 2010-04-06 | 2011-10-12 | 通用电气公司 | Segmented annular ring-manifold quaternary fuel distributor |
| CN103080653A (en) * | 2011-03-16 | 2013-05-01 | 三菱重工业株式会社 | Gas turbine combustor and gas turbine |
| CN103629698A (en) * | 2012-08-21 | 2014-03-12 | 通用电气公司 | System and method for reducing modal coupling of combustion dynamics |
Also Published As
| Publication number | Publication date |
|---|---|
| US20150345794A1 (en) | 2015-12-03 |
| CH709640A2 (en) | 2015-11-30 |
| CH709640A8 (en) | 2016-01-15 |
| DE102015107767A1 (en) | 2015-12-03 |
| JP2015224867A (en) | 2015-12-14 |
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