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WO2015040228A1 - Brûleur pour turbine à gaz et procédé de réduction des vibrations thermoacoustiques dans une turbine à gaz - Google Patents

Brûleur pour turbine à gaz et procédé de réduction des vibrations thermoacoustiques dans une turbine à gaz Download PDF

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Publication number
WO2015040228A1
WO2015040228A1 PCT/EP2014/070168 EP2014070168W WO2015040228A1 WO 2015040228 A1 WO2015040228 A1 WO 2015040228A1 EP 2014070168 W EP2014070168 W EP 2014070168W WO 2015040228 A1 WO2015040228 A1 WO 2015040228A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
burner
passage
combustion chamber
fuel passage
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/EP2014/070168
Other languages
German (de)
English (en)
Inventor
Berthold Köstlin
Bernd Prade
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to US14/911,766 priority Critical patent/US20160195271A1/en
Priority to CN201480040866.3A priority patent/CN105393057B/zh
Priority to EP14780788.7A priority patent/EP3004743B1/fr
Publication of WO2015040228A1 publication Critical patent/WO2015040228A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F23D14/70—Baffles or like flow-disturbing devices
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/06043—Burner staging, i.e. radially stratified flame core burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • 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
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
    • 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
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means

Definitions

  • the invention relates to a burner for a gas turbine, which is designed in particular for the combustion of low calorific fuel gas.
  • the invention also relates to a ⁇ Ver drive for the reduction of thermoacoustic vibrations in a gas turbine, wherein the burner is adapted for carrying out the method.
  • thermoacoustic oscillations which in particular in the combustion chamber of a gas turbine auftre ⁇ th, can lead to significant damage to the components during operation of the gas turbine and force shutdown of the system.
  • the invention also relates to a method for reducing thermoacoustic oscillations in a gas turbine comprising at least one burner, in which a delay time profile of a fuel stream flowing in a first fuel passage of the burner is adapted to reduce the thermoacoustic oscillations.
  • the generic burner comprises to provide a to be combusted in the combustion chamber of the gas turbine fuel gas at least the above-mentioned first to be supplied with fuel ⁇ hydrogen gas fuel passage and for providing ⁇ position of the air required for combustion with a
  • the two passages each have a main outlet opening into the combustion chamber of the gas turbine.
  • the fuel passage may be formed as Vormischpassage or diffusion passage.
  • the fuel passage to at least one drove for the fuel gas connected.
  • the burner may include further passages. For example, to initiate with the burner a variety of different fuels for combustion in the combustion chamber.
  • the individual passages can also be connected to a plurality of feed systems, depending on the operating state of the burner to pressurize the passages with different fuels or flushing fluids.
  • the invention relates to a generic burner which comprises at least one connection channel arranged upstream of the main outlet openings and fluidically connecting the air passageway and the fuel passageway.
  • Burners are known from the prior art, which includes a number of fuel nozzles to broaden a delay time profile of a flowing in a first fuel passage fuel gas flow, which lead into the first Brennstoffpas ⁇ sage and offset in the flow direction to each other.
  • the invention has for its object to provide a burner and a method of the type mentioned, with which the reduction of thermoacoustic oscillations in a combustion chamber of a gas turbine is made possible in an alternative manner.
  • the burner is designed such that a part of the air flowing into the Brennstoffpas ⁇ say fuel gas at least flows in at least a first operating state of the burner at impinged air ⁇ passage with compressor air and impinged fuel ⁇ passage with fuel gas via a Verbin ⁇ dung channel in the air passage.
  • the branched off part of the fuel stream is to its combustion through the main exit opening of the air passage into the interior of the
  • Combustion chamber can be introduced.
  • a remaining in the fuel passage portion of the fuel gas can be introduced through the main outlet ⁇ opening of the fuel passage in the interior of the combustion chamber.
  • the amount and radial fuel distribution of the branched portion of the fuel stream is such that the feedback of the heat release variations with the pressure variations in the combustion chamber is reduced.
  • the invention is based on the recognition that the radial
  • Distribution of the fuel - especially in a synthesis gas mixture - plays a crucial role in the acoustic ⁇ cal stability of the burner.
  • the burner according to the invention allows a better acoustic stability, so that an extended operating range of the burner is possible in terms of load and fuel quality.
  • the radial fuel / air distribution of a fuel stream flowing in a fuel passage may be adjusted without significantly altering basic aerodeign parameters of the fuel passage such as swirl number, pressure loss, and major dimensions of the passage.
  • the invention allows Also, with different fuel compositions to adapt the burner to the thermoacoustic behavior of the combustion chamber, without requiring an adjustment of the entire fuel passage would be required.
  • the burner according to the invention is designed such that in at least a first operating state of the burner when acted upon air passage with compressor air and at
  • the burner is designed such that the fuel stream, after it already flows in the fuel passage, is split.
  • kei ⁇ ne division in the area of the supply system of the fuel instead but instead takes the division / branch after the introduction of the fuel in the fuel passage, but upstream of the main outlet.
  • the burner is configured such that the feedback of the heat release fluctuations with the pressure fluctuations in the combustion chamber is reduced by the division / branching of the fuel stream flowing in the first fuel passage.
  • the flame front changes in front of the burner. This can be adjusted by means of the amount and the radial distribution of the branched portion of the fuel stream such that the feedback of the heat release fluctuations is reduced with the pressure fluctuations in the combustion chamber. To achieve a relevant change in the flame front, the radial extends
  • Fuel distribution of the branched portion of the fuel flow substantially over the thickness of one between the Emerging streams occurring shear layer out into the air passage.
  • the invention thus is not related to a manipulation of the thickness of the shear layer between the emerging from the air passage and the compressor air stream exiting the main outlet opening of the fuel passage fuel ⁇ current. Rather, to reduce feedback of the heat release variations with the pressure variations in the combustion chamber, the invention proceeds in a different way by varying the amount and radial fuel distribution of a branched portion of the fuel gas flowing in the fuel passage such that a change in flame front (i.e. accompanied by a change in the delay time profile of the fuel flow) the reduction of a feedback of the heat release fluctuations with the pressure fluctuations in the combustion chamber is effected.
  • Diameter should be selected accordingly in the two passages.
  • the burner for producing suitable pressure conditions on the connecting channels comprises flow guiding means in the fuel gas and / or adjusting element in the region of the connecting channels, which suitably determine the static pressure in the inlet region of the connecting channels.
  • the flow guide and / or adjusting elements can be changed or exchanged to adapt the distribution / branching of the fuel stream, for example, in their position or shape.
  • the position of the connection channels in the passages can be freely selected over a wide range.
  • connection channels are arranged downstream of the Zulei ⁇ lines used in the first operating condition of air or supply line of the fuel gas and upstream of the two main outlet openings of the two passages, so that fuel gas can be diverted into the air flow.
  • the main outlet opening may be formed, for example, as an annular opening at the outlet of the passage.
  • the Hauptaus ⁇ outlet opening of a plurality of holes in a (covering the outlet opening of the burner passage) sheet exist.
  • the main exit opening is arranged at the combustion chamber end of the passage.
  • the connecting channels are arranged along a fuel passage delimiting wall, for example in a running order ⁇ sequence so that their inlet openings are arranged in a circumferential row in the fuel passage and the channels through the wall to the Heilpas ⁇ say extend.
  • the pressure conditions in the burner can be designed such that the kauska ⁇ ducts also a flashback in the burner at sketch ⁇ off supply of the fuel supply in the first
  • the burner is designed such that the bewirk ⁇ te through the branch common delay time profile of the remaining portion and the diverted portion of the fuel stream is adapted to a thermo-acoustic behavior of the combustion chamber, so that the feedback of heat release fluctuations with the Pressure fluctuations in the combustion chamber is reduced.
  • the flame front changes in front of the burner. It may thus set a different common delay profile of the diverted and the remaining part of the fuel flow.
  • the delay time is the period of time that the fuel from the Outlet from the burner to the flame front needed. Since the fuel having different delay in Brennstoffström ⁇ times (depending on the point of exit at the burner outlet and depending on the location of the flame front of the exit location), is located in the respective operating state, a delay time profile of the combustion ⁇ a material stream.
  • An undesirable feedback of heat ⁇ release variations and pressure fluctuations in the combustion chamber can be reduced by means of the division and diversion of the fuel flow, since depending on the amount and radial fuel profile of the branched portion of the fuel stream, the common delay profile can change. For example, if the proportion of the profile reduces whose Ver ⁇ zugszeit substantially corresponds to the frequency of a preferential combustion chamber pressure fluctuation, this reduces a feedback of heat release fluctuations and pressure variations in the combustion chamber.
  • the inventive design of the burner is thus the ⁇ art that at least in the first operating state for the thermoacoustic behavior of the combustion chamber damping or
  • thermoacoustic vibration behavior is meant that gas turbine combustors depending on the power range preferably at certain frequencies / frequency bands for rocking thermoacoustic oscillations tend (characteristic buzzing behavior). These frequencies are also referred to as preferential combustion chamber pressure fluctuations. If the delay profile of a burner is adjusted accordingly-in particular widened-this can counteract a rocking of the oscillations in the range of at least one such characteristic hum / frequency band. In this sense, the delay profile can be adapted to the thermo-acoustic behavior of the combustion chamber or tuned thereto and counteract a buildup of thermoacoustic oscillations in the combustion chamber.
  • the delay profile can be, for example, by means of the proportion and / or the penetration depth (radial profile) and / or the distribution of the branched fuel stream to the individual ⁇ nen connecting channels influence.
  • the burner comprises ⁇ be consulted the first fuel passage a correspondingly-trained branch that the fuel stream be ⁇ acts at least in the first operating state, a damping acting on the thermo-acoustic behavior of the combustion chamber late time profile.
  • An advantageous embodiment of the invention can provide that the first fuel passage is designed at least for a Beauf ⁇ regain with low calorific fuel gas.
  • a low calorific fuel - in contrast to a standard fuel - in particular a fuel with a calorific value of below 20 MJ / kg, preferably below ⁇ 10 MJ / kg, to understand.
  • Synthesis gas usually has main components of CO, H 2 and, if appropriate, secondary components such as N 2 and Co 2 as well as water vapor.
  • Standard fuel is usually a normal and / or high calorific fuel whose calorific value is well above 30 MJ / kg. Normal natural gas has in ⁇ play a calorific value usually between 40 to 50 MJ / kg.
  • the combustible component of standard fuels for gas turbines consists essentially of hydrocarbons.
  • the combustible constituents of the synthesis gas are essentially CO and H2. Due to the low calorific value consequently high volume flows of fuel gas must be supplied through the burner of the combustion chamber. This has the consequence that for the combustion of low calorific fuels - such as synthesis gas - one or more separate fuel ⁇ fuel passages must be made available. Because of the high reactivity of synthesis gases compared to conventional fuels such as natural gas and oil, there is a significantly higher risk of flashback.
  • the present invention can be applied in a particularly vorteilhaf ⁇ ter way to this fuel passage for low calorific fuels.
  • the fuel passage may be configured for a diffusion operation or a premix operation for introducing the low-calorie fuel gas into the combustion chamber.
  • the low calorie fuel gas which may be in particular synthesis gas - premixed with air to a low calorific fuel-air mixture and a conversion of low calorie fuel-air mixture avoided in the fuel passage, so that the fuel-air Mixture is first converted into a hot gas in the combustion chamber.
  • the invention preferably starts from a synthesis gas passage for a diffusion operation in which a swirl is imparted to the fuel flow by means of swirl generators by means of blades.
  • the synthesis gas passage is formed as an annular space before Trains t ⁇ passage and may be tapered downstream formed.
  • the burner can be arranged substantially rotationally symmetrical about a longitudinal axis, so that a main ⁇ flow direction of the flowing in the passages of the burner fluid substantially in the direction of the longitudinal axis has (in particular in the radially closer to the longitudinal axis arranged passages) or at least one Component has in the direction of the longitudinal axis (in particular in the radially outer passages, which can run upstream substantially first diagonal to the longitudinal axis and downstream approach a parallel course of the longitudinal axis).
  • the air passage and the fuel passage can be arranged at least in sections ko ⁇ axially to each other, in particular the Lucaspassa ⁇ ge coaxially around the fuel passage.
  • the Hauptaus ⁇ openings of the air passage and the fuel passage are arranged such that the coaxially surrounding the passage with respect to an axis perpendicular to the longitudinal axis projective is arranged on-level around the other main outlet opening around.
  • a particularly simple structure results when the Heilpas ⁇ say and the fuel passage adjacent at least partially along a substantially cylinder and / or truncated cone-shaped wall adjacent to each other, wherein the connecting channels are formed as holes in the wall.
  • an adjustment member can be at least Any artwork ⁇ arranged in the region of the connecting channels, so that the proportion and / or the radial
  • Inflow profile and / or the division of the kausungska ⁇ channels of bring from the fuel passage in the air passage ask ⁇ fuel gas is set and / or adjustable by means of at least one input element.
  • the adjustment member can the static pressure in the region of the inlet opening of at least one connecting channel impressed ⁇ influence, so that an appropriate position of the inlet opening is set not only by the self-adjusting in the first operating state in the fuel passage pressure conditions.
  • the adjustment can be more easily adjusted to a desired delay time profile (at ⁇ example by replacing or changing its shape) as the position or size of the at least one connecting channel.
  • a flow guiding means is arranged in the fuel gas passage, which increases the static pressure in the region of the inlet openings of the connecting channel when the fuel passage is exposed to fuel gas.
  • the Strö ⁇ mungsleitsch includes a substantially toroidally-shaped plate, wherein the plate is arranged circumferentially on an inside of a fuel passage defining wall.
  • sheet metal refers to the shape, but is not to be understood as limiting the choice of material in the context of this invention.
  • the sheet metal can, contrary to a main flow direction in the fuel passage, extend obliquely into the interior of the fuel passage. For example, it may project beyond at least a portion of the inlet openings of the connection channels.
  • the substantially annular plate between the downstream of the inlet openings of the connecting channels nen nen areas each have a recess, so that the sheet, for example, downstream of the inlet openings comprises a triangular or trapezoidal pinnacle ,
  • the adjustment element may comprise a number of flow-guiding means which are designed as triangular or trapezoidal sheets.
  • the triangular sheets may be arranged on the inside of the fuel passage analogous to the above-mentioned substantially annular sheet.
  • the individual sheets have Allerding the advantage that downstream of the areas between the inlet openings no unfavorable pressure loss raised stabili ⁇ Henden areas of a flow guide are arranged.
  • An alternative, advantageous embodiment of the flow ⁇ conducting means may comprise at least one cap-shaped element having an input opening, which is arranged with the input opening in the direction of the inlet opening of a connecting channel downstream of the inlet opening on an inner side ei ⁇ ner the fuel passage limiting wall.
  • the cap-shaped element in wesent ⁇ union have the shape of a quarter-hollow sphere. This can project beyond the inlet opening at least partially.
  • At least one adjusting element is tubular, wherein the tubular adjusting element is in particular at least partially disposed in each case one of the connecting channels.
  • the at least one tubular Einstellele- elements are each partially inserted in a connecting channel and protrude into the air passage, so that the radial position of the junction of flowing through the respective connecting channel, branched partial flow accurately positioned ⁇ who can. How far the tubular adjusting element protrudes into the air passage can, depending on the desired radial
  • the at least one tubular adjusting element can for example be arranged completely in each case in a connecting channel.
  • the wall thicknesses of the at least one tubular adjustment member may be selected according to adjust the ra ⁇ Dialen Einströmprofils of the diverted fuel flow.
  • for example approximately can be fastened in extension of a connecting channel on the inside of the air passage at least one rohrför ⁇ -shaped adjusting element.
  • the at least one tubular adjusting element additionally or alternatively to the aforementioned embodiments protrude into the fuel passage and include, for example, at its projecting into the Brennstoffpassa ⁇ ge end an inlet shell.
  • the inlet shell can be designed, for example, analogously to the triangular metal sheets or the quarter-hollow sphere.
  • the ge ⁇ named embodiments of the tubular Einstellele ⁇ ment can be combined with each other, for example, or used individually. If a plurality of such tubular adjustment elements are provided, they may all be of the same design depending on the desired radial inflow profile of the branched fuel stream or may differ from one another, for example in accordance with the exemplary embodiments mentioned and their combinations.
  • Another object of the invention is to provide a method of the type mentioned, with which the reduction of thermo-acoustic vibrations in a combustion chamber of a gas turbine is made possible in an alternative manner.
  • the object is achieved with a method of the type mentioned at the outset a ⁇ characterized in that for adjusting the delay time profile of a fluid flowing in a first fuel passage fuel stream, a remaining part of the
  • BrennstoffStromes is introduced through at least one main outlet opening of the first passage in the combustion chamber and a branched off part of the fuel stream is introduced downstream of its introduction into the fuel passage and upstream of the main outlet opening via at least one connecting channel in at least a second passage, wherein the branched-off part of the fuel stream separately is initiated by the verblei ⁇ reproduced Brennstoffström into the combustion chamber so that the partial flows are incinerated after their emergence from the burners with different delay times or delay time profiles in the combustion chamber, for adjusting the delay time profile of the proportion of the branched-off partial ⁇ current and / or the inflow profile and / or its implementation distribution is provided on the at least one connecting channel in such a ⁇ that the feedback of the heat release ⁇ fluctuations is reduced with the pressure fluctuations in the combustion chamber.
  • Inflow and / or its distribution to the at least one connecting channel of the branched portion of the fuel stream ⁇ are set before starting the burner and / or during operation of the burner.
  • the adaptation of the at least one Strömungsleitschs and / or adjusting element can be done by replacing and / or adjusting its shape and / or position.
  • Another object of the invention is to provide a combustion chamber with at least one burner and a gas turbine having Minim ⁇ least such a combustion chamber with which the suppression of thermoacoustic oscillations in a Combustion chamber of a gas turbine is made possible in an alternative manner.
  • FIG. 1 schematically shows a longitudinal section through a gas turbine according to the prior art
  • Figure 4 shows schematically a longitudinal section through a burner according to the invention according to a third embodiment.
  • FIG. 1 shows a schematic sectional view of a gas turbine 1 according to the prior art.
  • the gas turbine 1 has inside a rotatably mounted about a rotation axis 2 rotor 3 with a shaft 4, which is also referred to as a turbine runner.
  • a turbine runner which is also referred to as a turbine runner.
  • the combustion chambers 10 each include a burner assembly 11 and a housing 12, which is lined with a heat shield 20 for protection against hot gases.
  • the combustion system 9 communicates with a beispielswei ⁇ ring hot gas channel.
  • a beispielswei ⁇ ring hot gas channel There form a plurality hinterei ⁇ Nander turbine stages, the turbine 14.
  • Each turbine nenlargement is formed of blade rings. Viewed in the flow direction of a working medium follows in the hot runner formed by a number 17 vanes row formed from blades 18 row.
  • the guide vanes 17 are secured to an inner housing of a stator 19 whereas the blades 18 running a series, for example by means of a Turbi ⁇ nenrace on the rotor 3 are attached.
  • ⁇ is coupled to the rotor 3, a generator, for example (not shown).
  • FIG. 2 shows schematically a section of a burner 24 according to the invention for a gas turbine according to a first embodiment in a longitudinal section.
  • the burner 24 includes one with compressor air
  • an annular channel air passage 26 an opening formed for the application of synthesis gas fuel passage 28, and a secondary feeding unit 30 (not explicitly shown) may comprise for introducing fluid egg nes a pilot burner and white ⁇ tere passages (not explicitly shown).
  • the burner has a substantially rotationally symmetrical structure about a longitudinal axis 32.
  • the air passage 26 coaxial with the designed for Syn ⁇ synthesis gas fuel passage 28, which in turn koaxi ⁇ al surrounds the secondary feeding unit 30 comprises.
  • Both the second coordination sphere feed unit 30 and the two passages 26 and 28 each have an opening into the combustion chamber 34 Hauptaus ⁇ opening 36, 38, 40th
  • the main outlet openings 36 are arranged around the main outlet opening 38 with respect to the projection plane 50 running perpendicular to the longitudinal axis 32.
  • the main flow direction is illustrated in the inlet region with an arrow L xx , is impressed by a in the air passage to ⁇ arranged swirler 42 (Swirler) a twist.
  • the vanes of the swirl generator extend from a passage defining inner wall 44 to a passage defining outer wall 46, the vanes being annular over the circumference of the wall.
  • a synthesis gas ⁇ stream 48 (which also before entry into the illustrated exhaust of the fuel passage section 28 provided with compressor air can be ⁇ mixed) via a Zu110 Gustavssystem.
  • the supply line system is not shown in the figure, because it is outside the section shown.
  • a swirl generator in the fuel passage 28 to 52 are also finely ⁇ sorted. Downstream of the blades 52, the fuel passage 28 and the air passage 26 are fluidly connected to each other via connection channels 54.
  • connection channels 54 are in the illustrated embodiment in a range angeord ⁇ net, in which the air passage 26 and the fuel passage 28 along a substantially cylinder jacket-shaped wall 56 adjacent to each other, wherein the connecting channels 54 are formed as holes in the cylinder jacket-shaped wall 54.
  • the burner 24 is designed such that in at least ei ⁇ nem first operating state of the burner when acted upon air passage 26 with compressor air and when acted upon
  • the configuration of the diversion is such that the common delay time profile of the fuel stream a Aufschau ⁇ angles of thermoacoustic oscillations, which occur in the respective gene combustion chamber 34 of the gas turbine in dependence on the Leis ⁇ processing area at characteristic frequency bands is at least prevented in a frequency band or reduced , Thus, a feedback of cherriesstreietzungs ⁇ fluctuations and pressure fluctuations in the combustion chamber is reduced.
  • the delay time profile is adapted to the thermoacoustic behavior of the combustion chamber 34 by means of an adjustment element 60.
  • the adjusting element 60 consists of a flow guide 62, which is arranged downstream of the fuel passage side inlet openings 64 of the connecting channels 54 in the fuel passage 28 and when the fuel passage 28 with fuel gas 28, the static pressure in the region of the inlet openings 64 of Connection channels 54 increased.
  • the flow ⁇ guiding means 62 has the shape of a substantially annular plate 66 formed. This is circumferentially on the inner ⁇ side 68 of the fuel passage 28 bounding wall 56th arranged and extends against a Hauptströmungs ⁇ direction 70 in the fuel passage 28 inclined into the interior of the fuel passage into it.
  • the sheet 66 extends in this case while maintaining a distance over at least a portion of the inlet openings 64.
  • the proportion and / or the radial inflow profile and / or the allocation to the a ⁇ individual connecting channels can of the fuel gas branched off from the fuel passage 28 into the air passage 26 by means of the at least one adjusting element 60.
  • Inlets of the connection channels located areas are arranged.
  • the adjustment member 60 may consist of a number of sheets best ⁇ hen, which are each arranged downstream of the inlet openings 64th These can, for example, as shown in Figure 3 Darge ⁇ , have the shape of triangular sheets 74 which are bent over the inlet openings. For the sake of clarity, only a single such sheet 74 is shown in FIG.
  • the adjusting element 60 may consist of a series of cap-shaped elements 84 which each comprise an inlet opening 86 and point downstream of the inlet opening 64 in the direction of the inlet opening 64 of a connecting channel 54 an inside 68 of the fuel passage 28 bounding wall 56 are arranged and preferably at least partially project beyond the inlet opening 64.
  • the cap-shaped element 84 essentially comprises the Shape of a quarter-hollow sphere on. In FIG. 4, for the sake of clarity, only such a quarter-hollow sphere is shown. The invention shown in Figures 2 to 4
  • Burners 24 are suitable for carrying out the method according to the invention.
  • a remaining portion 80 of the fuel stream is at least one main outlet opening 38 of the fuel passage 28
  • a branched off part 82 of the fuel stream is, downstream of its introduction into the fuel passage and current ⁇ on the main outlet openings 36 and 38, via the connecting channels 54 in the air passage 26 introduced.
  • the burner 24 is designed such that the common delay time profile of the fuel streams 82 and 80 on the proportion of the branched partial stream 82 and / or its inflow and / or its distribution to the at least one connecting channel 54 is tuned to a thermoacoustic behavior of the combustion chamber 34, so a feedback of heat release fluctuations and pressure fluctuations in the combustion chamber is reduced.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Abstract

L'invention concerne un brûleur (24) destiné à une turbine à gaz (1), comportant au moins un passage d'air (26) pouvant être alimenté avec l'air d'un compresseur et au moins un passage de combustible (28) pouvant être alimentée avec au moins un gaz combustible. Les deux passages (26, 28) comportent chacun un orifice de sortie principal (36, 38) qui débouche dans la chambre de combustion (34) de la turbine à gaz (1). Le passage d'air (26) et le passage de combustible (28) sont en communication fluidique par le biais d'au moins un conduit de communication (54) disposé en amont des orifices de sortie principaux (36, 38). Le brûleur permet de réduire les vibrations thermoacoustiques dans une chambre de combustion d'une turbine à gaz d'une manière alternative. Pour cela, le brûleur (24) est configuré de telle sorte que, dans au moins un premier état de fonctionnement du brûleur, lorsque le passage d'air (26) est alimenté avec l'air du compresseur et que le passage de combustible (28) est alimenté avec le gaz combustible, une partie (82) du gaz combustible s'écoulant dans le passage de combustible s'écoule dans le passage d'air (26) par le biais d'au moins un conduit de communication (54) et, en vue de sa combustion, il peut être introduit à l'intérieur de la chambre de combustion (34) par l'orifice de sortie principal (36) du passage d'air et une partie restante (80) du gaz combustible peut être introduite à l'intérieur de la chambre de combustion par l'orifice de sortie principal (38) du passage de combustible, et la quantité et la distribution radiale de combustion de la partie déviée (82) du flux de combustible sont telles que la rétroaction des vibrations de dégagement de chaleur sont réduites par les vibrations de pression dans la chambre de combustion.
PCT/EP2014/070168 2013-09-23 2014-09-23 Brûleur pour turbine à gaz et procédé de réduction des vibrations thermoacoustiques dans une turbine à gaz Ceased WO2015040228A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US14/911,766 US20160195271A1 (en) 2013-09-23 2014-09-23 Burner for a gas turbine and method for reducing thermoacoustic oscillations in a gas turbine
CN201480040866.3A CN105393057B (zh) 2013-09-23 2014-09-23 用于燃气涡轮机的燃烧器和用于减少燃气涡轮机中的热声振荡的方法
EP14780788.7A EP3004743B1 (fr) 2013-09-23 2014-09-23 Brûleur pour une turbine à gaz et procédé de réduction d'oscillations thermoacoustiques dans une turbine à gaz

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP13185537 2013-09-23
EP13185537.1 2013-09-23

Publications (1)

Publication Number Publication Date
WO2015040228A1 true WO2015040228A1 (fr) 2015-03-26

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PCT/EP2014/070168 Ceased WO2015040228A1 (fr) 2013-09-23 2014-09-23 Brûleur pour turbine à gaz et procédé de réduction des vibrations thermoacoustiques dans une turbine à gaz

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Country Link
US (1) US20160195271A1 (fr)
EP (1) EP3004743B1 (fr)
CN (1) CN105393057B (fr)
WO (1) WO2015040228A1 (fr)

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US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
CN116624895A (zh) * 2022-02-18 2023-08-22 通用电气公司 将燃料喷嘴吹扫流直接联接到旋流器

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US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
CN116624895A (zh) * 2022-02-18 2023-08-22 通用电气公司 将燃料喷嘴吹扫流直接联接到旋流器

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EP3004743B1 (fr) 2017-05-17
US20160195271A1 (en) 2016-07-07
CN105393057B (zh) 2017-06-30
EP3004743A1 (fr) 2016-04-13
CN105393057A (zh) 2016-03-09

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