EP2077421B1 - Dispositif pour attacher un brûleur à fonctionnement séquentiel dans une turbine à gaz - Google Patents

Dispositif pour attacher un brûleur à fonctionnement séquentiel dans une turbine à gaz Download PDF

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Publication number
EP2077421B1
EP2077421B1 EP09155057.4A EP09155057A EP2077421B1 EP 2077421 B1 EP2077421 B1 EP 2077421B1 EP 09155057 A EP09155057 A EP 09155057A EP 2077421 B1 EP2077421 B1 EP 2077421B1
Authority
EP
European Patent Office
Prior art keywords
burner
sev
flow channel
sev burner
flow duct
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.)
Active
Application number
EP09155057.4A
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German (de)
English (en)
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EP2077421A2 (fr
EP2077421A3 (fr
Inventor
Urs Benz
Thorsten Christoph Motzkus
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Publication date
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Publication of EP2077421A2 publication Critical patent/EP2077421A2/fr
Publication of EP2077421A3 publication Critical patent/EP2077421A3/fr
Application granted granted Critical
Publication of EP2077421B1 publication Critical patent/EP2077421B1/fr
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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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances

Definitions

  • the invention relates to a device for fastening a second burner, in short SEV burner, in a sequentially operated gas turbine arrangement in which a fuel / air mixture is burned in a first burner to form hot gases, which subsequently partially expanded the SEV Burners are supplied for a second combustion, which is formed substantially as a flow channel, with a flow channel wall having an opening through which a fuel supply to the interior of the SEV burner is insertable, and on the in the axial direction of the opening in each case two opposite Fastening structures are provided, in each of which a support structure for further attachment of the SEV burner to an outer support can be inserted.
  • a gas turbine arrangement with a sequential combustion is, for example, from the EP 0 620 362 B1 forth, in which along a uniform rotor shaft in the direction of flow of the gas turbine assembly of an air compressor unit is arranged a circularly arranged around the rotor shaft annular combustion chamber, which is fed by a plurality of annularly distributed premix burner with an ignitable fuel-air mixture, which is brought to the ignition, from which hot gases driving a first turbine stage provided downstream of the annular combustor and connected to the rotor shaft.
  • the partially expelled from the first turbine stage hot gases then pass into an annular flow channel, in which the teilppand faced hot gases again with Mixed fuel and are brought to form a sezündTen hot gas fuel mixture within a second circular or the rotor shaft ring surrounding the second annular combustion chamber for ignition.
  • the resulting hot gases go downstream in a second, a so-called. Low-pressure turbine stage, to make further expansion work.
  • the second or sequential burner designed as a flow channel which is referred to below as an SEV burner, should be considered in more detail, in particular with regard to the attachment of the flow channel within the gas turbine plant and its thermal and mechanical properties.
  • SEV burner goes out EP 0 620 362 B1 forth; There this burner is marked with Pos. 5
  • a SEV burner 1 which is known per se as a flow channel, follows from the image representation according to FIG. 2 which, in the exemplary embodiment shown, has a rectangular flow channel cross section and is bounded by four flow channel walls, an upper 1o, lower 1u and two lateral flow channel walls 1s.
  • an opening 2 is introduced, through which a fuel lance 3 for fuel enrichment of the entering into the SEV burner part-expanded hot gases is used.
  • this is inserted through the opening 2 of the flow channel 1 from above, the lance tip 3 terminates with a defined game to the upper flow channel wall 1o and is positioned.
  • the game to be provided between the lance tip and the upper flow channel wall should allow the simplest possible assembly of the lance tip, yet cause the smallest possible leakage between the components.
  • the SEV burner 1 has upstream of its flow channel to a mounting flange 4, which is connected to a not shown further expansion stage of the gas turbine plant, ie, a first turbine stage.
  • the SEV burner is connected at least one side axially fixed to the gas turbine.
  • each two screw or pin-like fastening means 7 are provided which fix the support structures 6 each with a SEV burner 1 towering outer support 8 of the gas turbine assembly.
  • the fuel lance 3 also extends through the outer support 8, wherein a support ring 3 'with integrated piston ring serve to ensure a seal between the radially inner region and the outer support 8, especially in thermally induced changes in shape, especially at the start but also occur during operation of the gas turbine arrangement.
  • the fuel lances tip is displaced by the burner in the flow direction or elastically bent, so that on the one hand a required minimum clearance between the outer carrier and the fuel lance tip must be provided, on the other hand, it is to avoid leakage currents, this game with a not out FIG. 2 seal apparent piston ring.
  • the mounting flange 4 opposite flange 4 'of the flow channel 1 via, provided on the upper side channel wall 1o fixing lugs 9 is directly connected to the outer support 8, so that the SEV burner 1 is axially locked. In the circumferential direction, however, the SEV burner 1 is fixed by the two support structures 6 and the associated fastening means 7 relative to the outer support 8.
  • the invention is based on the object, a device for fastening a second burner, short SEV burner, in a sequentially operated gas turbine arrangement in which a fuel-air mixture is burned in a first burner to form hot gases, which subsequently partially expanded the SEV burner be supplied for a second combustion, which is formed substantially as a flow channel having a flow channel wall having an opening through which a fuel supply into the interior of the SEV burner is insertable, and provided on the opposite in the axial direction of the opening in each case two attachment structures are, in each of which a support structure for further attachment of the SEV burner to an outer support can be introduced in such a way that operational and structural, in particular occurring at the location of the opening between the SEV burner and the fuel lance vibrations should be avoided.
  • a device is formed in that the support structure is formed as a unitary support plate, are provided on the mating contours for attachment to the two, the opening opposite mounting structures and which provides a recess, the least of the size corresponds to the opening in the flow channel wall, so that the support plate in the attached state on the outer support does not cover the opening of the flow channel wall.
  • the idea underlying the invention provides for the substitution of the two separately formed support structures which are axially insertable into the two separately axially spaced receiving rails by a uniform, continuous support plate, which also in the provided on the sokanalwandoberseite attachment structures or receiving rails axially inserted.
  • a particularly advantageous embodiment also provides that in the region of the opening additional connecting means between the opening edge and the support plate are provided through which an additional radial support between the opening edge and the support plate is possible.
  • at the opening is at least one collar, preferably provided on the opening edge diametrically opposite two arranged collar which project vertically beyond the flow channel wall and each having a mounting lip which is insertable into a provided on the support plate groove-shaped recess.
  • the at least one plate member mounted on the lower flow channel wall via spacer means on the one hand the at least one plate element at least partially spaced from the lower flow channel wall and on the other hand is slidably attached to this.
  • the plate member mounted on the lower flow channel wall via spacer means
  • the at least one plate element at least partially spaced from the lower flow channel wall and on the other hand is slidably attached to this.
  • the hitherto existing problem of oxidation of adjacent gas turbine components due to the very high heat radiation exposure severely limit, so that the provision of previously conventional coatings to protect against surface oxidation to the corresponding system components using the device according to the solution is no longer necessary.
  • the plate member while being slidably mounted relative to the lower flow channel wall, contributes to some extent to an increase in rigidity of the at least lower flow channel wall, particularly since it is not connected to a support member as stated above for the upper flow channel wall.
  • FIG. 1a is a perspective view of a SEV burner 1 is shown, the upper flow channel wall 1o is visible, at which the known per se, designed as receiving rails 5 mounting structures are provided in the axial direction of the SEV burner 1, a one-piece component carrier plate 10, in turn via corresponding lateral effetsnut Modellen 11 has, can be inserted.
  • the support plate 10 has an opening ( Fig. 1b ), which in the case of the embodiment according to FIG. 1a the opening 2 within the upper flow channel wall 1o surrounds like a frame, without even partially overlap, so as to ensure that the not in FIG. 1a illustrated burner lance unhindered through the opening 2 can be mounted in the SEV burner 1.
  • the screw or pin-like fastening means 7 are used for fixing the support plate 10 to an outer support 8.
  • FIG. 1b the assembly process of the support plate 10 for attachment to the upper flow channel wall 1o of the SEV burner is visible.
  • the receiving grooves 11 of the support plate 10 pass through axial displacement (see arrow) in the corresponding mounting structures 5, which are preferably integrally connected to the SEV burner 1 and serve as receiving rails.
  • the carrier plate assembly in the opposite direction to the in FIG. 1b direction indicated by the arrows.
  • solely by providing a one-piece support plate 10, which is fixed in axially opposite to the opening 2 areas on the SEV burner, caused by the opening 2 within the SEV burner structural weakness can be at least partially compensated.
  • the embodiment according to the FIG. 1 it can be seen if at least two, preferably two diametrically opposite the opening edge collar 12 are provided at the opening 2, in particular in the region of the opening edge, which project beyond the surface of the upper flow channel wall 1o vertically and provide lateral fixing lips 13, which engage with a corresponding groove-shaped recess 14 pass within the support plate 10, according to partial image representation in Figure 1c ,
  • a solid radial connection of the opening edge is made with the support plate 10, whereby the circumferential stiffness of the opening edge of the opening 2 is significantly increased, on the other hand serve the collar 12 as a centering aid for the installation of the introduced into the opening 2 lance tip not shown burner lance.
  • the support plate 10 can be mounted by mere axial displacement relative to the support structures formed as a mounting rails 5 and the collar 12, it requires the axial fixing of the support plate 10 an additional attachment via the fastening means 7 on the outer support 8 as it were previously in the state of Technique usual practice.
  • the formation of the collar 12 can on the one hand be made in one piece from the same material from which the at least upper flow channel wall 1o is formed, alternatively, it is also possible, the collar 12 in the form of an additional, modular insert from below into the opening 2 of the SEV- Burner to use, as is the embodiment hereinafter with reference to FIG. 3 shows.
  • FIG. 3a the assembled state of a support plate 10 is shown relative to the SEV burner 1, wherein the burner lance 3 is shown in the mounted state and extends through both the support plate 10 and provided in the SEV burner opening 2.
  • a modular designed insert element 15 is provided, which is inserted from the inside of the flow channel into the opening of the SEV burner and the upper flow channel wall 1 o protrudes vertically.
  • the insert element 15 For fluid-tight closure between the modular-shaped insert element 15 and the flow channel wall, the insert element 15 has a lower circumferential support web 16 which is flush and fit into a receiving contour 17 along the peripheral edge of the opening 2 can be used.
  • collar-like sections 18 are provided which can be inserted into corresponding receiving grooves provided in the carrier plate 10.
  • the support plate 10 undergoes a radial connection to the insert element 15 and is thus centered and fixed relative to the SEV burner. Due to the axially symmetrical design of both the support plate 10 and the insert element 15, it is possible depending on the existing mounting space, the support plate 10 on both sides Axial direction for purposes of introduction to assemble.
  • additional sealing materials 19, or sealing means as shown in the detail illustration in FIG Figure 3c is removable, provide.
  • the insert element 15 Due to the separate formation of the insert element 15 thus a handy component is created, the entire surface or at least the contact surfaces can be provided to the SEV burner and the fuel lance with a wear-resistant surface layer. As a result, the hitherto complex surface protection, which is to be carried out by means of a plasma treatment, in particular on the so-called balcony of the fuel lance, can be saved. Should there still be wear on the contact surface between the fuel lance and the insert element, on which the fuel lance centered and flush, so it only requires the replacement and replacement of the otherwise inexpensive producible insert element 15th
  • the easy mountability of the insert element 15 is seen from below in the direction of the opening 2 of the SEV burner.
  • a sealing means 19 which runs along the receiving contour 17 at the opening 2 are provided in order to provide a fluid-tight seal of the inner flow channel with respect to the use of the burner lance to be carried out hereinafter.
  • a further fixation of the insert element 15 relative to the SEV burner is not required, especially as a result of axial displacement of the carrier plate 10 and the engagement between the collar-like sections 18 with the groove-shaped recesses 14 of the carrier plate 10 a mutual firm joining between the carrier plate 10 and insert member 15 made can be. This also goes from the partial cross-sectional view according to FIG. 4b out.
  • the insert member 15 is flush with its support web 16 partially overlapping with the receiving contour 17 at the opening edge of the upper flow channel wall 1o.
  • the receiving contour 17 further provides a groove-shaped recess 17 'into which the sealing means 19 is introduced.
  • the insert member 15 vertically sees the Upper flow channel wall 1o superior to a collar-like portion 18 which opens into a groove-shaped recess 14 of the support plate 10 and is pressed by this vertically upwards against the receiving contour 17.
  • the insert element 15 provides for its cooling so-called effusion holes 20, which open at the surface which faces the hot gases within the flow channel.
  • the partial cross-sectional view according to FIG. 4b be taken that the insert member 15 has a relation to the vertical obliquely inclined and the opening 2 facing the introduction edge 21, which allows a better and easier centering and assembly of the fuel lance in the SEV burner 1.
  • FIG. 5a shows a further alternative embodiment with respect to the support plate 10 in FIG. 5a.
  • FIG. 5a shows a partial longitudinal section through the opening portion 2 of the upper flow channel wall 1o, wherein in the right portion of the partial longitudinal sectional view of a portion of the mounting flange 4 is shown, which is connected flush with an upstream first turbine stage region.
  • the support plate 10 has an axial, in the direction of the mounting flange 4 oriented extension 10 ', with which the support plate 10 abuts in the axial direction of the region of the mounting flange 4 and thus undergoes an axial locking.
  • the mounting of the carrier plate 10 relative to the SEV burner takes place counter to the flow direction with which the hot gases entering the SEV burner from the turbine stage flow through the SEV burner.
  • FIG. 5b is a representation in the axial direction opposite to the flow direction of the flow channel of the SEV burner shown. It can be seen that at the burner flange 4 additional fastening hooks 22 are provided, on which the carrier plate 10 are axially and radially fixed, whereby the outer diameter of the burner inlet is defined radially relative to the gas turbine outlet not shown. This prevents lowering of the SEV burner inlet from the upstream first turbine stage due to creep. Furthermore, the SEV burner is still against axial displacement relative to the outer support 8 (not shown) fixed via corresponding fastening means 7 on the support plate 10.
  • the lower flow channel wall 1 u is supported in contrast to the upper only by the two burner flanges 4 and 4 'and the flow channel side walls 1s (see, for example, the illustration of the figures according to FIG. 2 ).
  • the lower flow channel wall 1 u is not connected to a provided for the upper flow channel wall support member.
  • the inherent rigidity of the lower flow channel wall 1 u is therefore provided exclusively by the flanges 4 and 4 'and optionally by an additional rib. It is obvious that due to thermal stresses and compressive forces deformations along the lower flow channel wall 1 u can occur.
  • FIG. 6a Such a plate element is in FIG. 6a shown, the bottom flow channel wall 1 u of the SEV burner 1 shows in plan view. So suppose that the SEV burner 1 is connected via the mounting flange 4 with a first turbine stage not shown.
  • the plate member 22 is connected along its planar axial extent via individual linearly arranged spacer means with the lower flow channel wall 1 u, wherein from the detailed illustration according to FIG FIG. 6c the exact attachment mechanism can be seen.
  • a so-called mounting pin 23 is provided directly with the lower flow channel wall 1 u each at the location of a sliding attachment, which provides a mushroom-shaped portion 23 'on which the plate member 22 slidably abuts.
  • the plate member 22 is slidably pressed against the mushroom-shaped portion 23 'via a type of clip connection 24. This applies to all attachment points of the plate member 22 with respect to the lower flow channel wall 1 u, as for example. From a cross-sectional view according to FIG. 6b can be seen. The distance between the plate member 22 and the lower flow channel wall 1 u is chosen so that effusion cooling of the SEV burner is not affected. Different thermal expansions of the SEV burner and the plate element 22 can be absorbed or compensated due to the sliding suspension as described above. In order to increase the surface stiffness of the plate element 22, the surface element 22 provides local profile offsets 25 (FIG. Fig. 6a ), along which the sliding attachment points are mounted.
  • FIG. 7 is another embodiment of the formation and attachment of a plate member 22 on the lower flow channel wall 1 u shown. This shows FIG. 7 a longitudinal sectional view through the one SEV burner 1 and the radially inner inner support 26.
  • the plate member 22 projects beyond the region of the SEV burner up to the burner flange 4, wherein the burner or inlet flange 4 is formed offset over which the plate member 22 is suitably guided and fixed with this hook.
  • the flat plate element 22 is formed reduced exclusively to the areas of the profile subsidence 25, although while weight can be reduced, however, this variant does not protect the radially inner inner support from the direct heat radiation of the SEV burner 1. Rather, the rigidity of the sheets is increased by the U-shape of the Profilabsenkitch 25 and thus the rigidity of the lower flow channel wall 1 u.
  • This embodiment represents only an alternative to the usual wall stiffening by means of profiles.

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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)

Claims (4)

  1. Dispositif de fixation d'un deuxième brûleur, en abrégé brûleur SEV (1), dans un ensemble de turbines à gaz conduites séquentiellement et dans lequel un mélange de combustible et d'air est brûlé dans un premier brûleur en formant des gaz chauds qui peuvent ensuite être apportés dans le brûleur SEV (1) pour une deuxième combustion après détente partielle, ce brûleur étant configuré essentiellement comme canal d'écoulement présentant une paroi de canal d'écoulement dotée d'une ouverture (2) par laquelle une amenée (3) de combustible peut être insérée à l'intérieur du brûleur SEV (1) et sur laquelle deux structures de fixation (5) dans chacune desquelles une structure de support peut être insérée pour encore fixer le brûleur SEV (1) sur un support extérieur (8) sont prévues l'une en face de l'autre dans la direction axiale de l'ouverture (2),
    caractérisé en ce que
    le canal d'écoulement présente une paroi (1u) de canal d'écoulement située face à l'ouverture et sur laquelle au moins un élément (22) en plaque est placé par l'intermédiaire de moyens d'écartement de telle sorte qu'au moins certaines parties du ou des éléments en plaque (22) soient placées d'une part à distance de la paroi du canal d'écoulement et d'autre part de manière à pouvoir coulisser en direction de la paroi du canal d'écoulement.
  2. Dispositif selon la revendication 1, caractérisé en ce que la distance entre le ou les éléments (22) en plaque et la paroi (1u) du canal d'écoulement est dimensionnée de telle sorte que l'on puisse réaliser un refroidissement du brûleur SEV par effusion.
  3. Dispositif selon les revendications 1 ou 2, caractérisé en ce que l'élément (22) en plaque peut être placé et sélectionné de telle sorte qu'une partie (26) de l'installation située face au brûleur SEV (1) soit protégée du rayonnement thermique direct du brûleur SEV.
  4. Dispositif selon l'une des revendications 1 à 3, caractérisé en ce que le ou les éléments (22) en plaque s'étendent dans la direction axiale du canal d'écoulement jusqu'au niveau de la bride d'admission (4) qui fixe le canal d'écoulement et sont fixés à cette dernière.
EP09155057.4A 2006-03-31 2007-03-05 Dispositif pour attacher un brûleur à fonctionnement séquentiel dans une turbine à gaz Active EP2077421B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006015093 2006-03-31
EP07103514A EP1840471B1 (fr) 2006-03-31 2007-03-05 Dispositif pour attacher un brûleur à fonctionnement séquentiel dans une turbine à gaz

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
EP07103514A Division EP1840471B1 (fr) 2006-03-31 2007-03-05 Dispositif pour attacher un brûleur à fonctionnement séquentiel dans une turbine à gaz

Publications (3)

Publication Number Publication Date
EP2077421A2 EP2077421A2 (fr) 2009-07-08
EP2077421A3 EP2077421A3 (fr) 2009-07-15
EP2077421B1 true EP2077421B1 (fr) 2014-04-30

Family

ID=38292665

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07103514A Active EP1840471B1 (fr) 2006-03-31 2007-03-05 Dispositif pour attacher un brûleur à fonctionnement séquentiel dans une turbine à gaz
EP09155057.4A Active EP2077421B1 (fr) 2006-03-31 2007-03-05 Dispositif pour attacher un brûleur à fonctionnement séquentiel dans une turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP07103514A Active EP1840471B1 (fr) 2006-03-31 2007-03-05 Dispositif pour attacher un brûleur à fonctionnement séquentiel dans une turbine à gaz

Country Status (4)

Country Link
US (1) US7937950B2 (fr)
EP (2) EP1840471B1 (fr)
AT (1) ATE518101T1 (fr)
ES (2) ES2476916T3 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2116768B1 (fr) * 2008-05-09 2016-07-27 Alstom Technology Ltd Brûleur
EP3029378B1 (fr) 2014-12-04 2019-08-28 Ansaldo Energia Switzerland AG Brûleur séquentiel pour une turbine à gaz axiale
EP3296638B1 (fr) * 2016-09-20 2020-02-19 General Electric Technology GmbH Brûleur complet et procédé pour brûleur d'une turbine à gaz

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3147594A (en) 1962-03-19 1964-09-08 Continental Aviat & Eng Corp Fuel injection device
US3565968A (en) * 1967-07-31 1971-02-23 Ashland Oil Inc Cracking and recovery of hydrocarbons
FR2646880A1 (fr) * 1989-05-11 1990-11-16 Snecma Chemise de protection thermique pour canal de post-combustion ou de transition d'un turboreacteur
JPH0772616B2 (ja) 1989-05-24 1995-08-02 株式会社日立製作所 燃焼器及びその運転方法
EP0550126A1 (fr) * 1992-01-02 1993-07-07 General Electric Company Bouclier thermique pour post-combusteur
DE4223733C2 (de) * 1992-07-18 1995-05-18 Gutehoffnungshuette Man Verbindung von Mischrohr und Flammrohr einer Gasturbine
GB9304994D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc Improvements in or relating to gas turbine engines
CH687269A5 (de) * 1993-04-08 1996-10-31 Abb Management Ag Gasturbogruppe.
US6339923B1 (en) * 1998-10-09 2002-01-22 General Electric Company Fuel air mixer for a radial dome in a gas turbine engine combustor
DE19948956A1 (de) 1999-10-11 2001-04-12 Asea Brown Boveri Montagevorrichtung
GB2432198B (en) * 2005-11-15 2007-10-03 Rolls Royce Plc Sealing arrangement

Also Published As

Publication number Publication date
ES2476916T3 (es) 2014-07-15
EP2077421A2 (fr) 2009-07-08
EP1840471A3 (fr) 2008-02-20
EP1840471B1 (fr) 2011-07-27
ATE518101T1 (de) 2011-08-15
EP1840471A2 (fr) 2007-10-03
EP2077421A3 (fr) 2009-07-15
ES2369524T3 (es) 2011-12-01
US20070227157A1 (en) 2007-10-04
US7937950B2 (en) 2011-05-10

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