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WO2015043749A1 - Tête de brûleur et turbine à gaz équipée d'un tel brûleur - Google Patents

Tête de brûleur et turbine à gaz équipée d'un tel brûleur Download PDF

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Publication number
WO2015043749A1
WO2015043749A1 PCT/EP2014/002604 EP2014002604W WO2015043749A1 WO 2015043749 A1 WO2015043749 A1 WO 2015043749A1 EP 2014002604 W EP2014002604 W EP 2014002604W WO 2015043749 A1 WO2015043749 A1 WO 2015043749A1
Authority
WO
WIPO (PCT)
Prior art keywords
burner
fuel
channel
longitudinal axis
nozzle
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/EP2014/002604
Other languages
German (de)
English (en)
Inventor
Axel Widenhorn
Thilo KISSEL
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.)
Duerr Systems AG
Original Assignee
Duerr Systems AG
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 Duerr Systems AG filed Critical Duerr Systems AG
Priority to CN201490000443.4U priority Critical patent/CN205156035U/zh
Priority to DE102015003920.2A priority patent/DE102015003920A1/de
Publication of WO2015043749A1 publication Critical patent/WO2015043749A1/fr
Priority to EP15766402.0A priority patent/EP3198199A1/fr
Priority to PCT/EP2015/001864 priority patent/WO2016045779A1/fr
Anticipated expiration legal-status Critical
Priority to US15/470,725 priority patent/US10712009B2/en
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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

Definitions

  • the invention relates to a burner head of a burner of the type specified in the preamble of claim 1 and a gas turbine with a burner having such a burner head.
  • Combined heat and power systems of this type include in a known design in addition to the internal combustion engine itself nor a drivable by the internal combustion engine power converter, in particular in the form of an electric generator and a waste heat for the use of waste heat contained in the exhaust gas of the internal combustion engine.
  • the gas turbines mentioned have a burner between the compressor and the turbine, in which fuel is oxidized or burned with an oxidizing agent, as a rule with air.
  • the required mixing of fuel and oxidant takes place in a burner head, which is typically designed as a burner flange, and a combustion chamber is connected downstream.
  • the burner head extends along a burner longitudinal axis and usually comprises a plurality of arranged at a radial distance from the burner longitudinal axis in a body oxidant channels.
  • Oxidant channels each open a fuel nozzle, which is formed according to the prior art as a nozzle lance.
  • a nozzle lance is preferably coaxial in each case an oxidant channel.
  • the nozzle lances are usually kept at Burner flange, where they are aligned and stored by a constructive paragraph in the axial direction.
  • the fixation of the burner nozzles is usually done by means of plates, which are bolted to the burner flange.
  • the nozzle lances are placed on the individual located in the burner flange, designed as through holes oxidant channels in the combustion chamber.
  • the fuel is supplied via individual hoses, which are fed via an upstream external distributor ring. In the systems realized so far, the fuel nozzles are made of solid material.
  • the invention has the object of developing a generic burner head such that with a simplified structure increased reliability is achieved.
  • the invention is further based on the object of specifying a turbine, in particular a gas turbine or a micro gas turbine with an improved burner.
  • At least one supply channel for fuel supply of the at least one fuel nozzle is formed in the main body of the burner head.
  • a plurality of arranged around the burner longitudinal axis in the main body oxidant channels is provided with at least one each opening into an oxidant fuel nozzle, the fuel nozzles are at least partially and in particular all connected to the at least one supply channel for supplying fuel.
  • the at least one fuel nozzle is at least partially formed by a fuel channel opening into the associated oxidant channel in the base body, wherein a nozzle axis of the fuel channel has a radial direction component relative to the channel longitudinal axis of the oxidant channel and / or to the burner longitudinal axis of the burner head.
  • a fuel channel can be formed easily and with little effort, for example, through a hole, a groove or any other recess in the main body of the burner head.
  • nozzle lances can be completely dispensed with, so that also eliminates the associated high assembly, sealing and manufacturing costs.
  • the aligned with radial direction component fuel channels lead the fuel with just this radial direction component in the oxidant or combustion air stream, resulting in a good mixing and thus a stable oxidation or combustion takes place.
  • the aforementioned good mixing can be further improved by different spatial angles of the nozzle axes, for example in the form of a helix angle.
  • a fuel channel body is guided into the oxidant channel, wherein the at least one fuel nozzle is formed on the fuel channel body and in particular is arranged at least approximately on the channel longitudinal axis.
  • a simple design waiving the usual prior art nozzle lances given. The named design leads to a positioning of the fuel nozzle on the channel longitudinal axis or at least sufficiently close thereto. In any case, an at least substantially central fuel injection can be achieved, which can promote a clean mixture formation.
  • the oxidant channels and the associated fuel nozzles, in particular fuel channels are divided at least into a first burner stage and into a second burner stage, wherein separate and independent fuel supplies, in particular fuel supply channels, are provided for the various burner stages.
  • the burner head in this case has a central pilot stage and a, preferably concentrically arranged around the pilot stage main stage, wherein the main stage by the at least two different fuel supplies, in particular fuel supply channels, are provided for the various burner stages.
  • the burner head in this case has a central pilot stage and a, preferably concentrically arranged around the pilot stage main stage, wherein the main stage by the at least two different
  • Burner stages is formed. As a result, an optimal adaptation to different load conditions can be achieved.
  • the central pilot stage stabilizes combustion and ensures safe operation in transient control processes. In the pilot stage but only a small part of the total fuel flow is implemented. By far the largest share of fuel and power is provided by the two-stage main stage.
  • the two-stage or multi-stage design allows for adaptation to changes in power requirements such that one or more stages of the main stage are shut down while one or more remaining stages of the main stage are operating at their optimum operating point.
  • the invention described above in more detail and in more detail below finds its preferred use in a gas turbine, which in turn is preferably part of a combined heat and power system.
  • the burner head according to the invention can also be used equally advantageously in other burners, for example for heating systems, boilers, exhaust air purification systems, furnaces or the like.
  • FIG. 1 is a schematic block diagram of a gas turbine with a burner according to the invention
  • FIG. 2 shows a longitudinal section of the burner according to the invention according to FIG. 1 with a burner head and a downstream combustion chamber for illustrating the gas flow
  • FIG. 3 is a longitudinal sectional view of a burner head in the form of a burner flange according to the prior art for a burner according to FIG. 2 with fuel nozzles designed as nozzle lances, FIG.
  • Fig. 4 is a longitudinal sectional view of a first embodiment of a
  • burner head with a formed in the body, annular supply channel for fuel in the form of a sealed, formed in the peripheral surface annular groove, and channels leading from the supply channel to the respective oxidant channel, the fuel nozzles forming fuel,
  • Fig. 5 shows a variant of the arrangement according to Fig. 4, in which the annular
  • Supply channel is formed in an end face of the burner head
  • Fig. 6 shows a further variant of the burner head according to Fig. 4 or 5 with two
  • Fig. 7 shows a modification of the burner head of Fig. 6, in which the two separate
  • Supply channels are formed in the end face of the burner head,
  • FIGS. 4 to 7 are schematic detail of a single oxidant channel according to FIGS. 4 to 7 with an optional annular channel running around the oxidant channel,
  • FIG. 9 shows in a perspective longitudinal sectional view of the burner head according to FIG. 4 for illustrating different angles of the nozzle axes to the burner longitudinal axis or to the respective channel longitudinal axis and the consequent flow pattern
  • FIG. 10 is a schematic cross-sectional view of the burner head of Figure 4 illustrating an optional spin angle of the respective nozzle axes.
  • Fig. 11 shows a variant of the arrangement of FIG. 4 with two differently executed
  • Fuel channel bodies which in the respective oxidant channel into it wherein the respective fuel nozzle is formed on the fuel channel body and at least approximately disposed on the channel longitudinal axis, wherein in one embodiment, the fuel nozzle is connected to a transversely extending to the channel longitudinal axis, continuous fuel channel portion, and wherein in the other embodiment, the fuel nozzle from an angled fuel channel section is fed
  • FIG. 12 shows the arrangement according to FIG. 11 with alternatively configured fuel channel bodies, wherein in one embodiment the fuel nozzle is fed by an inclined fuel channel section, and in the other embodiment two near-axis fuel nozzles are connected to a fuel channel section extending transversely to the channel longitudinal axis.
  • the gas turbine 30 includes a compressor 32, a turbine 33 and a burner 35, the compressor 32 being driven by the turbine 33 by means of a shaft 34.
  • the shaft 34 also drives a schematically indicated generator 31 or other engine.
  • the compressor 32 air or another oxidizing agent is sucked in, compressed, and supplied to the burner 35, which is also indicated only schematically, as the oxidant stream or combustion air stream 37.
  • the burner 35 is also supplied fuel, which is oxidized or burned in the burner 35 together with the oxidant stream 37. This results in a high-energy exhaust stream 38, which is derived by the turbine 33 and thereby relaxed, as a result, the turbine 33 and from this, the compressor 32 and the generator 31 is driven.
  • Fig. 1 power-heat coupling system but also additional or alternative forms of Use of useful energy will be used.
  • the waste heat of the exhaust stream 38 can be used directly for heating purposes.
  • Fig. 2 shows in a longitudinal sectional view of an embodiment of the invention burner 35 of the gas turbine 30 of FIG. 1.
  • the burner 35 and its burner head 36 can also be used for other purposes, for example in heating systems, boilers, kilns, in an exhaust air purification or the like come.
  • the burner 35 comprises at least one combustion chamber 39, at the one end of which a burner head 36 is arranged.
  • the burner head 36 extends along a burner longitudinal axis 1 or concentrically around it, with the burner longitudinal axis extending through the combustion chamber 39 or concentrically therethrough.
  • combustion chambers 39 may also be advantageous.
  • the burner head 36 comprises a basic body 2 which is preferably designed in one piece and in which at least one oxidant channel 3 arranged at a radial distance from the burner longitudinal axis 1 is formed.
  • a plurality of concentrically arranged around the burner longitudinal axis 1 in the base body 2 oxidant channels is provided.
  • the oxidizing agent channels 3 of the preferred example of FIG. 4 are in uniform
  • the oxidant channels 3 have a uniform radial distance to the burner longitudinal axis 1. Furthermore, the oxidant channels 3 in the example according to FIG. 4 have a uniform, circular cross-sectional contour with almost identical channel diameters, as best seen in FIG. 10. However, it may also be advantageous if neighboring ones
  • Oxidizing agent channels 3 varying angular distances on the circumferential line around the burner longitudinal axis 1 and / or varying radial distances from the burner longitudinal axis 1 and / or divergent channel cross-sections, in particular cross-sectional contours and / or diameter.
  • a preferred embodiment may also include two, three or more groups of oxidant channels 3 include, which differ in groups in terms of their angular distance and / or their radial distance and / or their channel cross-section.
  • the base body 2 according to FIG. 4 still bears centrally on the longitudinal axis of the burner 1 a pilot fuel nozzle 19 whose function will be described in more detail below.
  • the combustion chamber 39 or its outer wall is enclosed by a jacket 40, whereby an annular space is formed.
  • the oxidant stream or the combustion air stream 37 is introduced and guided to the opposite side of the burner head 36.
  • an oxidizing agent or combustion air plenum 23 which surrounds the burner longitudinal axis 1 is formed, in which the oxidizing agent collects, deflected in accordance with an arrow 41 and fed into the at least one or into the plurality of oxidant channels 3 on the side opposite the combustion chamber 39 becomes.
  • a flow restrictor element 24 for the oxidant stream 37 which is only schematically indicated, not shown in detail, can be optionally arranged, with which the flow rate of the oxidizer can be adjusted, controlled or regulated if required.
  • the illustrated construction of the burner 35 is only a preferred embodiment.
  • the burner head 36 according to the invention, which is described in more detail below, can also be advantageously used in other types of burners 35.
  • 3 shows a longitudinal section of a burner head 36 'in the form of a burner flange according to the prior art.
  • the main body 2 ' also carries in the center a pilot fuel nozzle 19' for forming a pilot stage 11 '.
  • oxidation channels 3 ' By means of the fuel nozzles 4 'designed as nozzle lances, fuel is introduced into the oxidant flow through the oxidant channels 3' in the same direction and coaxially, thereby producing an oxidation or combustible mixture.
  • FIG. 4 shows a longitudinal section of a first exemplary embodiment of a burner head 36 according to the invention, which in its configuration resembles the burner head 36 according to FIG.
  • Identical features are provided here with the same reference numerals, wherein individual features have already been described above in connection with FIG.
  • the supply channel 13 is supplied with fuel in particular by a single fuel supply 9, wherein the fuel supply 9 may have a flow-limiting element 22, not shown here but shown in FIGS. 1 and 9.
  • the supply channel 13 is designed as an at least partially circumferential annular groove 15 in the base body 2, wherein the annular groove 15 is sealed on its open side.
  • the rotating body around the burner longitudinal axis 1 rotating body 2 has a radially outer peripheral surface 17, in which the annular groove 15 is incorporated from the outside and radially outwardly closed.
  • the burner head 36 has at least one, in this case exactly one fuel nozzle 4, for each oxidant channel 3. From the additional illustration according to FIG. 10, it is apparent that eight oxidant channels 3 each having a fuel nozzle 4 are provided here by way of example. But it can also be a different number appropriate.
  • the fuel nozzles 4 are at least partially, here all formed by incorporated into the body 2 fuel channels 5, wherein the fuel channels 5 are connected on its input side to the supply channel 13 and open on its output side in the respective oxidant channel 3.
  • the fuel nozzles 4 and the fuel channels 5 are at least partially and here all connected to the supply channel 13 for the supply of fuel.
  • the fuel channels 5 have nozzle axes 6, which have a radial direction component to the channel longitudinal axis 20 of the oxidant channel 3 and / or to the burner longitudinal axis 1 of the burner head 36.
  • the channel longitudinal axes 20 are parallel to the axis of the burner longitudinal axis 1, so that said radial direction components apply equally relative to the channel longitudinal axis 20 and the burner longitudinal axis 1.
  • said axis parallelism does not have to be given so that the radial directional component applies at least with respect to one of the two axes.
  • the longitudinal section shown leads to a sectional plane which is spanned by the burner longitudinal axis 1 and a radial direction 26 thereto. In a same, but possibly also different cutting plane, a further cutting plane is spanned by the channel longitudinal axis 20 and a radial direction 27 for this purpose.
  • the nozzle axis 6 lies in a first
  • the said first and second Tilt angles ⁇ , ⁇ are advantageously in a range of> 0 ° to 90 ° inclusive, and preferably in a range of 60 ° to 90 ° inclusive. In the exemplary embodiment shown, both inclination angles ⁇ , ⁇ are at least approximately 90 °. Further details of the burner head 36 according to FIGS. 2 and 4 and in particular further details of the angular position of the nozzle axes 6 are still shown in FIGS. 9, 10 and described in more detail below in their context.
  • FIG. 5 shows a variant of the arrangement according to FIG. 4, wherein the supply channel 13 designed as an annular groove 15 is not formed in the peripheral surface 17 (FIG. 4) but in an end face 18 perpendicular to the longitudinal axis of the burner 1.
  • the supply channel 13 can, as in the embodiment of FIG. 4, orbit on the outside around the multiplicity of oxidant channels 3, but in the exemplary embodiment according to FIG. 5 lies radially on the inside of the oxidant channels 3. Accordingly, the fuel channels 5 do not lead from the outside to the inside with a radial direction component, but instead vice versa with radial direction component from the inside to the outside of the supply channel 13 in the oxidant channels 3.
  • the embodiment of FIG. 5 is consistent with that of FIG.
  • FIG. 6 shows a longitudinal section of a further variant of the burner head 36 according to FIG. 4 or 5.
  • the oxidant channels 3 and the associated fuel nozzles 4 or fuel channels 5 are at least exactly here in a first
  • the at least two, here exactly two burner stages 7, 8 together form the main stage 12.
  • the burner head 36 has a central pilot stage 11 with the associated pilot fuel nozzle 19. The divided into the two burner stages 7, 8 main stage 12 and their
  • Oxidant channels 3 and fuel channels 5 are arranged concentrically around the pilot stage 11.
  • separate and independent fuel supplies 9, 10 are provided, as shown in the illustration Fig. 1 and 9 may be provided with independent fürfiussbegrenzungs instituten 22.
  • the two fuel feeds 9, 10 lead into two separate
  • Supply channels 13, 14, which are both formed in the peripheral surface 17 of the base body 2 as an annular groove 15, 16 with mutual axial displacement. Both annular grooves 15, 16 with the associated fuel channels 5 are executed according to the annular groove 15 of FIG. 4.
  • the fuel channels 5 of the upper supply channel 13 open into at least one, preferably in a first group of several Oxidationsstoff- channels 3, while the fuel channels 5 in at least one other, preferably in a second group of multiple oxidant channels 3 open.
  • individual oxidant channels 3 or individual groups thereof can be switched off or operated with different operating parameters than a respective different oxidant channel 3 or another group thereof.
  • the two burner stages 7, 8 of the main stage 12 can be operated independently of each other and, if necessary, switched off individually.
  • FIG. 7 shows a modification of the burner head 36 according to FIG. 6, in which the two separate supply channels 13, 14 are formed in the end face of the burner head 36 or its basic body 2.
  • This is comparable to the embodiment of FIG. 5 to two in the end face 18 of the body 2 incorporated annular grooves 15, 16, which are arranged in the preferred embodiment shown in the axial direction one above the other and separated by a separating plate.
  • the first fuel supply 9 opens directly into the upper annular groove 15, while the second fuel supply 10 is passed from above through the upper annular groove 15 and below it opens into the annular groove 16.
  • the two can
  • Supply channels 13, 14 and the two annular grooves 15, 16 may be radially offset from one another, wherein, for example, a supply channel 13 radially on the inside of the Oxidationsffenkanäle 3 and the other supply channel 14 may be positioned radially outside thereof.
  • Supply channel 13 and the annular groove 15 of the exemplary embodiment of FIG. 5 match.
  • FIGS. 4 to 7 shows, in a schematic detail illustration, a single oxidant channel 3 according to FIGS. 4 to 7 with an optional annular channel 21 which surrounds the oxidant channel 3 in an annular manner.
  • the annular channel 21 is in a manner not shown with one of the two supply channels described above 13, 14 connected and is supplied in this way with fuel.
  • the annular channel 21 runs at least partially, in this case completely closed around the oxidant channel 3. In the illustrated embodiment, it is designed as an annular groove which is closed at the top by a cover 25 and by a cover plate. From the annular channel 21, at least one fuel channel 5, in this case a plurality of fuel channels 5 with associated nozzle axes 6, leads into the oxidant channel 3.
  • FIGS. 2 and 4 to 8 coincide with each other in their other features, reference numerals and optional design possibilities, whereby a combination of such features as, for example, the combination of an end-side supply channel 13 with a peripheral side Supply channel 14 comes into consideration.
  • FIG. 9 shows, in a perspective longitudinal section illustration, the burner head 36 according to FIGS. 2 and 4 for illustrating different angles of the nozzle axis 6.
  • the nozzle axes 6 have first and second angles of inclination ⁇ , ⁇ which are smaller than 90 °.
  • the two angles of inclination a, ß are determined such that at an amount of ⁇ 90 °, the respective nozzle axis 6 is inclined starting from the supply channel 13 to the oxidant channel 3 in the flow direction or to the output of the oxidant channel 3.
  • the two angles of inclination ⁇ , ⁇ apply in connection with FIG. 4.
  • Fig. 10 shows a schematic cross-sectional view of the burner head according to FIGS. 2, 4 and 9 for illustrating further optional angular positions of the nozzle axes 6.
  • the cross-sectional plane shown here is perpendicular both to the burner longitudinal axis 1 and to the respective channel longitudinal axis 20. If the channel longitudinal axes 20th deviate from the illustration of FIG. 10 is not parallel to the axis of the burner longitudinal axis 1, then the two mentioned cross-sectional planes are not congruent.
  • three different fuel channels 5, 5 ', 5 "with associated nozzle axes 6, 6', 6" are shown in FIG. In practice, however, preferably only one design of the fuel channels 5, 5 ', 5 "described in more detail below with nozzle axes 6, 6', 6" in a single burner head 36 is used. Of course, a combination of it is possible.
  • the nozzle axis 6 of the fuel channel 5 lies in the perpendicular to the burner longitudinal axis 1 cross-sectional plane exactly radially to the burner longitudinal axis 1, ie in the radial direction 26.
  • the nozzle axis 6 passes through the burner longitudinal axis 1.
  • the nozzle axis 6 of the combustion Material channel 5 in the plane perpendicular to the channel longitudinal axis 20 cross-sectional plane exactly radially to the channel longitudinal axis 20, so runs exactly on the channel longitudinal axis 20.
  • the nozzle axis 6 'of the fuel nozzle 5' in the cross-sectional plane perpendicular to the burner longitudinal axis 1 is measured at a side angle ⁇ to the burner longitudinal axis 1, so that the nozzle axis 6 'does not pass through the burner longitudinal axis 1. But well, the nozzle axis 6 'passes through the associated channel longitudinal axis 20'. From the burner longitudinal axis 1 extends through the associated channel longitudinal axis 20 ', a radial direction 26', wherein the side angle ⁇ between the radial direction 26 'and the nozzle axis 6' is measured.
  • a fuel channel 5 "with a nozzle axis 6" is shown.
  • the nozzle axis 6 of the fuel channel 5 has neither a side angle ⁇ , nor a helix angle ⁇ . In other words, the amounts of the side angle ⁇ and the helix angle ⁇ equal 0.
  • ß can be a swirled fuel entry in the respective oxidant channel 20 corresponding to a spiral line 28 of FIG. 9 for a good mixing of the fuel with the oxidizing agent.
  • FIGS. 11 and 12 show variants of the exemplary embodiment according to FIG. 4, wherein instead of a fuel channel 5 (FIG. 4) formed in the base body 2 and forming the respective fuel nozzle 4, a fuel channel body 42 is provided which led into the associated oxidant channel 3 is.
  • the fuel channel body 42 is shown in Figures 11 and 12 in a total of four different exemplary embodiments, wherein in practice preferably a plurality of fuel channel body 42 of the same design are used. Of course, it is also possible to provide mixed designs within a burner head 36.
  • Common features of the various fuel channel bodies 42 are the formation of at least one fuel nozzle 4 on each of a fuel channel body 42 and the optional, preferred positioning of the fuel nozzle 4 at least approximately on the channel longitudinal axis 20.
  • a fuel channel section 43 for the supply of Fuel to the respective fuel nozzle 4.
  • the fuel channel portion 43 is fed from an associated supply channel 13, 14, as described above in connection with Figures 4 to 7, 9 and 10.
  • the respective fuel channel body 42 may protrude beyond the associated oxidant channel 3 on only one side in a cantilever manner. In the preferred exemplary embodiments shown, it is guided into the respective oxidant channel 3 in such a way that it passes completely through it transversely to its channel longitudinal axis 20 and is supported on both sides on the opposite walls of the respective oxidant channel 3.
  • the fuel channel bodies 42 have a circular cross-section, wherein they are here overall cylindrical. But there are also deviating cross-sectional shapes, in particular for reducing the flow resistance into consideration, such as elliptical, teardrop-shaped or otherwise streamlined cross-sectional shapes.
  • the fuel channel section 43 is formed as a through-hole, which completely passes through the fuel channel section 43 in its longitudinal direction, that is to say perpendicular to the channel longitudinal axis 20.
  • a shortened, designed as a blind bore fuel channel section 43 may be provided which extends only to the fuel nozzle 4 according to the right half of FIG.
  • a channel section branches off, which forms the fuel nozzle 4, the associated nozzle axis 6 being congruent with the channel longitudinal axis 20. It but can also be an axis parallelism with a distance between the nozzle axis 6 and the channel longitudinal axis 20 may be appropriate.
  • a further variant is shown in the right-hand half of FIG. 12, wherein instead of a single fuel nozzle 4, a plurality of fuel nozzles 4, for example two fuel nozzles 4, are formed at a distance from the channel walls of the associated oxidant channel 5 and in particular in the vicinity lie to the associated channel longitudinal axis 20.
  • the plurality of fuel nozzles 4 are advantageously fed from a common fuel channel section 43.
  • a shortened fuel channel section 43 analogous to the right-hand half of FIG. 11 may also be expedient.
  • the fuel nozzles 4 are aligned in the flow direction of the oxidant channel 3, wherein an at least approximately central injection of the fuel into the respective oxidant channel 3 takes place.
  • FIG. 12 shows yet another variant with a fuel channel section 43 guided obliquely through the fuel channel body 42.
  • the fuel channel section 43 directly forms the fuel nozzle 4 whose nozzle axis 6 is equal to the fuel channel axis directly at its output end.
  • the nozzle axis 6 thus has both an axial and a radial direction component with respect to the plane of the burner longitudinal section shown here.
  • the nozzle axis 6 is based on the direction of the burner longitudinal axis 1 or the channel longitudinal axis 20, as well as with respect to the direction of the respective associated radial direction 26, 27 in an angle deviating from 0 ° and 90 °.
  • the various embodiments of the fuel channel body 42 agree in their other features and reference numerals, which also applies to the comparison of the burner heads 36 according to Figures 11 and 12 with the burner head 36 of FIG.
  • the fuel channel body 42 according to the invention can also be described in any other burner heads, in particular in burner heads 36 according to the further described here in total

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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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

L'invention concerne une tête de brûleur (36) destinée à un brûleur (35) et une turbine à gaz (30) équipée d'un brûleur (35) comportant une telle tête de brûleur (36). La tête de brûleur (36) s'étend le long d'un axe longitudinal (1) du brûleur et comprend au moins un conduit d'oxydant (3), qui est placé dans un corps de base (2) à une distance radiale de l'axe longitudinal (1) du brûleur et qui possède un axe longitudinal de conduit (20), et au moins un injecteur de carburant (4) débouchant dans au moins un passage d'oxydant (3). Dans le corps de base (2) sont formés au moins un conduit d'alimentation (13, 14) destiné à alimenter en carburant le ou les injecteurs de carburant (4) et/ou au moins un conduit de carburant (5) destiné à former l'injecteur de carburant (4). Dans la turbine à gaz (30), la tête de brûleur (36) comporte un étage pilote central (11) et un étage principal (12) disposé concentriquement autour de l'étage pilote (11). L'étage principal (12) est formé par au moins les deux étages de brûleur (7, 8) différents. Pour chaque étage de brûleur (7, 8), un conduit d'alimentation (13, 14) indépendant, se présentant sous la forme d'une gorge annulaire (15, 16) au moins partiellement périphérique et fermée, sont ménagés dans le corps de base (2) pour former des conduits d'alimentation en carburant (9, 10) distincts et indépendants destinés aux étages de brûleur (7, 8). La turbine à gaz (30) est entraînée au moins partiellement par un flux de gaz d'échappement (38) du brûleur (35).
PCT/EP2014/002604 2013-09-28 2014-09-25 Tête de brûleur et turbine à gaz équipée d'un tel brûleur Ceased WO2015043749A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
CN201490000443.4U CN205156035U (zh) 2013-09-28 2014-09-25 燃烧器的燃烧器头和具有这样的燃烧器的燃气涡轮
DE102015003920.2A DE102015003920A1 (de) 2014-09-25 2015-03-27 Brennerkopf eines Brenners und Gasturbine mit einem solchen Brenner
EP15766402.0A EP3198199A1 (fr) 2014-09-25 2015-09-19 Tête de brûleur et turbine à gaz pourvue d'un tel brûleur
PCT/EP2015/001864 WO2016045779A1 (fr) 2014-09-25 2015-09-19 Tête de brûleur et turbine à gaz pourvue d'un tel brûleur
US15/470,725 US10712009B2 (en) 2014-09-25 2017-03-27 Burner head of a burner and gas turbine having a burner of this type

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102013016201.7A DE102013016201A1 (de) 2013-09-28 2013-09-28 "Brennerkopf eines Brenners und Gasturbine mit einem solchen Brenner"
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EP2230458A1 (fr) * 2009-03-17 2010-09-22 Siemens Aktiengesellschaft Agencement de brûleur pour combustibles liquides et procédé de fabrication d'un agencement de brûleur
JP5372815B2 (ja) * 2010-03-17 2013-12-18 株式会社日立製作所 ガスタービン燃焼器
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EP2597374A1 (fr) * 2011-11-28 2013-05-29 Siemens Aktiengesellschaft Agencement de brûleur pour une turbine à gaz

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US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
US4845952A (en) * 1987-10-23 1989-07-11 General Electric Company Multiple venturi tube gas fuel injector for catalytic combustor
US20110057056A1 (en) * 2009-09-08 2011-03-10 General Electric Company Monolithic fuel injector and related manufacturing method
US20130036743A1 (en) * 2011-08-08 2013-02-14 General Electric Company Turbomachine combustor assembly

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