EP2463583A1 - Turbine à gaz et procédé de reconditionnement d'une telle turbine à gaz - Google Patents

Turbine à gaz et procédé de reconditionnement d'une telle turbine à gaz Download PDF

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Publication number
EP2463583A1
EP2463583A1 EP11190982A EP11190982A EP2463583A1 EP 2463583 A1 EP2463583 A1 EP 2463583A1 EP 11190982 A EP11190982 A EP 11190982A EP 11190982 A EP11190982 A EP 11190982A EP 2463583 A1 EP2463583 A1 EP 2463583A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
cooling plate
plate
outer sealing
segments
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.)
Granted
Application number
EP11190982A
Other languages
German (de)
English (en)
Other versions
EP2463583B1 (fr
Inventor
Andreas De Fazio
Urs Benz
Remigi Tschuor
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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Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2463583A1 publication Critical patent/EP2463583A1/fr
Application granted granted Critical
Publication of EP2463583B1 publication Critical patent/EP2463583B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R2900/00012—Details of sealing 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00019—Repairing or maintaining combustion chamber liners or subparts

Definitions

  • the present invention relates to the field of gas turbines. It relates to a gas turbine according to the preamble of claim 1. It further relates to a method for reconditioning such a gas turbine.
  • Fig. 13 shows in a highly simplified representation of a stationary gas turbine with sequential combustion, as known from the prior art.
  • the illustrated gas turbine 10 includes a compressor 11 for compressing aspirated air, a first annular combustor 14 into which is mixed fuel injected with pre-mix type burners 13 supplied via a fuel supply 12. The resulting hot gas drives a first Turbine 15, and is then reheated by injecting a fuel from a second fuel supply 16 into a second combustion chamber 17, to then drive a second turbine 18.
  • Modern stationary gas turbines are usually designed with an annular combustion chamber, as in Fig. 1 is reproduced.
  • the local gas turbine 20 with annular combustion chamber 24 of the combustion chamber is limited by an outer side wall 25 and by an inner side wall 26.
  • the hot gas path 27 is divided in the combustion chamber 24 by an inlet and an exit plane.
  • the entry level is characterized by a plurality of burners 21, 22 and one or more front segments 23.
  • the burners 21, 22 are positioned in the front segments and sealed in the flow direction.
  • the attachment of the front segments themselves as well as their sealing must meet the requirements of the combustion.
  • the combustion chamber 24 is operated for a long time, with or without interruptions (start and stop cycles). Examples of arrangements of front panels and front segments are from WO 96/04510 A1 or the DE 44 32 558 A1 known.
  • This module is then delivered as a "front panel complete" to the installation site.
  • the gas turbine according to the invention which is in particular a stationary gas turbine, comprises an annular combustion chamber which is bounded in the radial direction by an inner side wall and an outer side wall and in the axial direction by an annular front plate through which front plate burners communicate with the combustion chamber wherein the front plate is covered to the combustion chamber towards protection against heat by a plurality of circular ring forming, flat front segments, each comprising a front plate forming the front and a parallel to and spaced behind the front plate cooling plate.
  • front segments are releasably hooked to the front panel, that for sealing the front segments in
  • Circumferentially one another between adjacent front segments each extending in the radial direction seal is arranged, and that the seal by two parallel running, in the middle between the adjacent front segments abutting outer sealing strip is formed, each of which on the outside at the edge of the cooling plate the associated front segment is attached.
  • An embodiment of the gas turbine according to the invention is characterized in that the front segments have on their back a plurality of hooks, and that on the front of the front plate fixing bolts are arranged, each having a hook receptacle, and in which the front segments are hooked with their hooks ,
  • the hooks are arranged distributed on the edges of the front segments running in the radial direction, and if the hooks and the hook receivers are oriented such that the front segments are largely fixed perpendicular to the segment surface, while they have sufficient freedom of movement parallel to the segment surface Compensation of thermally induced strains.
  • the fastening bolts are screwed to the front panel, means being provided for securing the fastening bolts against rotation.
  • a further embodiment is characterized in that the cooling plate has holes distributed over the surface through which cooling air can flow into the intermediate space between the front plate and the cooling plate for impingement cooling of the front plate.
  • Another embodiment of the invention is characterized in that in the front segments in each case the cooling plate is held by distributed in the area arranged spacer bolts at a distance from the front plate, and that the Fuse plate is fixed to the standoff bolt by means of the back of the standoff pins and fixed to the standoffs by a weld firmly connected washers.
  • the lock washers are each composed of a lower ring and an upper ring, and when the lock washers are firmly connected only in the region of the upper ring with the associated standoff bolt through the weld.
  • a further embodiment is characterized in that the outer sealing strips consist of a precipitation-hardened, high-temperature-resistant nickel-based alloy, that the outer sealing strips are biased to one another in the cold state of the gas turbine, that the outer sealing strips extend with their sealing lips against the flow direction, and that the outer sealing lips To reduce the mutual wear at their free ends are provided with a radius.
  • Another embodiment of the invention is characterized in that for securing the outer sealing strips distributed along the edge of the cooling plate arranged fixing clips are provided, that the outer sealing strips are slidably held between the fixing clips and the respective heat sink, and that the fixing Clips are each outside the range of the outer sealing strip firmly connected by a weld with the heat sink
  • the displacement of the outer sealing strip between the fixing clips and the associated cooling plate is limited in each case by a knob formed on the fixing clip, which penetrates through a larger cutout in the outer sealing strip into a pocket arranged underneath in the cooling plate.
  • the inventive method for reconditioning a gas turbine according to the invention is characterized in that for removing the cooling plate, the welded with the standoffs upper rings are separated, that the remaining lower rings are deducted from the standoffs, and that for re-fixing the cooling plate on the standoffs The remaining lower rings are put back on the distance bolts and firmly connected to the distance bolts by welding.
  • FIGS. 2 and 3 show in a view obliquely from the front or from behind a front segment 23 according to an embodiment of the invention.
  • the front segment 23 has on the front side (towards the combustion chamber) a front plate 28 provided with distributed first holes 33.
  • On the back of a cooling plate 29 is arranged parallel to the front plate 28, which is equipped with second holes 34.
  • On the front panel 28, an upper edge 36 and a lower edge 37 are integrally formed at the top and bottom to the rear protruding.
  • Also formed on the front plate 28 to the rear protruding are on the sides a plurality of along the side edges distributed hooks 35, the attachment of the front segment 23 on the front panel (45 in Fig. 5 ) serve.
  • in the Front segment 23 are furthermore circular openings 31 and 32 for the burners 21 and 22 (FIG. Fig. 1 ) intended.
  • the attachment of the front segments 23 on the front plate 45 is carried out according to 4 and 5 respectively.
  • Fig. 9 by means of fastening bolts 39.
  • the fastening bolts 39 have two mounting features: on the one hand, a securing pin 43, which is inserted into a securing bore 42 in the fastening bolt and in the front plate 45 in order to prevent the fastening bolt 39 from rotating ( Fig. 5 ).
  • an Allen screw 44 which guided through the front panel 45 via a threaded hole 41, the fastening bolts 39 attached. This Allen screw 44 is finally protected against sweat.
  • the fastening principle of the front segment 23 by means of the fastening bolts 39 is based on clamping, i. the hook receptacle 40 of the fastening bolt 39 clamps on the bearing surface of the hook 35 of the front segment 23 in the axial direction (perpendicular to the segment surface) the front segment 23 fixed.
  • This principle still allows a displacement of the front segment in the radial and in the circumferential direction (in the plane of the segment surface) even with a large force. This mobility is necessary to compensate for the different thermal expansions of different components.
  • spacers 46 include to maintain the desired distance to each other, and on the other hand have lock washers 47, which are welded to the standoffs 46 (weld 48) and thus the so-called sandwich construction of front panel 28 and heat sink 29 together.
  • the standoffs 46 are connected to the front panel 28 by spot welding.
  • the spacer bolts 46 can absorb forces in the radial and in the circumferential direction. These forces can arise due to the greater thermal expansion of the front plate relative to the heat sink.
  • the lock washers 47 absorb all the axial forces, which are caused by pulsations of the combustion chamber 24 and thermal deformation of the front segment.
  • the lock washers 47 are designed in two stages (47a, 47b in Fig. 7 ) so that they can be reused a second time during reconditioning. The idea is to cut open only the upper first welded ring 47b of the lock washer 47. The lower second ring 47a can then be used again with the spacer bolt 46 or welded (welding 49 in Fig. 8 ).
  • outer sealing strip 30 which serve to seal the front segments with each other in the circumferential direction.
  • the seals which are preferably made of a precipitation-hardened, high-temperature-resistant nickel-base alloy, eg Waspaloy®, are already pre-stressed to each other when cold. This principle provides optimal sealing in all operating conditions.
  • the sealing lips of the outer sealing strips 30 are according to Fig. 9 designed opposite to the flow direction 52.
  • the sealing is improved by taking advantage of the pressure difference in the flow direction to press the outer sealing strips 30 against each other.
  • the outer sealing strips 30 have at the ends of the sealing lips 59 radii R ( Fig. 11 ), so that the mutual wear in the arrangement according to Fig. 9 is minimized. Tilting of the outer weather strip 30 during installation and operation is thus avoided.
  • the outer sealing strips 30 are fastened by six fixing clips 53 per seal (FIG. 10, 11 ). These fixing clips 53 have a knob 54, which is guided in a cut-out pocket 57 on the cooling plate 29. This knob 54 absorbs forces in the radial and in the circumferential direction and thus prevents the falling out of the outer weather strip 30.
  • a cutout on the fixing clip 53 which is designed to be greater than the thickness of the outer sealing strip 30, allows free movement of the outer sealing strip 30. This prevents stresses in the outer sealing strip 30, which are caused by different thermal expansions of the front plate 28 and heat sink 29.
  • the fixing clips 53 are fastened by welding to the cooling plate 29 (FIG. Fig. 11 ). The welding 56 takes place between two feet 58 on the fixing clip 53 (FIG. Fig. 12 ). These feet 58 cause that the fixing clips 53 do not lift by the action of heat of the welding process and thus are no longer parallel to the cooling plate 29. A controlled mobility of the outer weather strip 30 would not be guaranteed in such a case.
  • the seal is located above the cooling plate, on the cold side, therefore the cooling plate does not need to be removed.
  • the standoffs no longer have to be cut open and hooks and spacers are no longer bent open or removed. Only the fixing clips must be dismantled. Seen from the other side, this also has the advantage that the seals can be mounted after coating.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11190982.6A 2010-12-06 2011-11-28 Turbine à gaz et procédé de reconditionnement d'une telle turbine à gaz Not-in-force EP2463583B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH02032/10A CH704185A1 (de) 2010-12-06 2010-12-06 Gasturbine sowie verfahren zum rekonditionieren einer solchen gasturbine.

Publications (2)

Publication Number Publication Date
EP2463583A1 true EP2463583A1 (fr) 2012-06-13
EP2463583B1 EP2463583B1 (fr) 2016-09-21

Family

ID=43920352

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11190982.6A Not-in-force EP2463583B1 (fr) 2010-12-06 2011-11-28 Turbine à gaz et procédé de reconditionnement d'une telle turbine à gaz

Country Status (4)

Country Link
EP (1) EP2463583B1 (fr)
AU (1) AU2011253595B2 (fr)
CH (1) CH704185A1 (fr)
MY (1) MY157102A (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105465830A (zh) * 2014-09-30 2016-04-06 阿尔斯通技术有限公司 燃烧器前面板
EP3299720A1 (fr) * 2016-09-22 2018-03-28 Ansaldo Energia IP UK Limited Ensemble avant de chambre de combustion pour turbine à gaz

Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5285632A (en) * 1993-02-08 1994-02-15 General Electric Company Low NOx combustor
WO1996004510A1 (fr) 1994-08-01 1996-02-15 Bmw Rolls-Royce Gmbh Bouclier thermique pour chambre de combustion d'une turbine a gaz
DE4432558A1 (de) 1994-09-13 1996-03-14 Bmw Rolls Royce Gmbh Gasturbinen-Brennkammer mit Hitzeschild
EP0724119A2 (fr) * 1995-01-26 1996-07-31 General Electric Company DÔme pour une chambre de combustion d'une turbine à gaz
US5799491A (en) * 1995-02-23 1998-09-01 Rolls-Royce Plc Arrangement of heat resistant tiles for a gas turbine engine combustor
WO1999061840A1 (fr) * 1998-05-25 1999-12-02 Abb Ab Chambre de combustion d'une turbine a gaz
EP1130219A1 (fr) * 2000-03-02 2001-09-05 Siemens Aktiengesellschaft Turbine avec joints d'étanchéitée entre les panneaux des parois
US6298667B1 (en) * 2000-06-22 2001-10-09 General Electric Company Modular combustor dome
EP1413831A1 (fr) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Chambre de combustion annulaire pour turbine à gaz et turbine à gaz
EP1555443A1 (fr) * 2004-01-13 2005-07-20 Siemens Westinghouse Power Company Dispositif de fixation pour chemise de chambre de combustion de turbine
EP1818615A1 (fr) * 2006-02-10 2007-08-15 Snecma Chambre de combustion annulaire d'une turbomachine
EP2012061A1 (fr) * 2007-07-05 2009-01-07 Snecma Déflecteur de fond de chambre, chambre de combustion le comportant et moteur à turbine à gaz en étant équipé
EP2040001A2 (fr) * 2007-09-21 2009-03-25 Snecma Chambre de combustion annulaire de moteur à turbine à gaz
EP2107308A1 (fr) * 2008-04-03 2009-10-07 Snecma Propulsion Solide Chambre de combustion sectorisée en CMC pour turbine à gaz

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5285632A (en) * 1993-02-08 1994-02-15 General Electric Company Low NOx combustor
WO1996004510A1 (fr) 1994-08-01 1996-02-15 Bmw Rolls-Royce Gmbh Bouclier thermique pour chambre de combustion d'une turbine a gaz
DE4432558A1 (de) 1994-09-13 1996-03-14 Bmw Rolls Royce Gmbh Gasturbinen-Brennkammer mit Hitzeschild
EP0724119A2 (fr) * 1995-01-26 1996-07-31 General Electric Company DÔme pour une chambre de combustion d'une turbine à gaz
US5799491A (en) * 1995-02-23 1998-09-01 Rolls-Royce Plc Arrangement of heat resistant tiles for a gas turbine engine combustor
WO1999061840A1 (fr) * 1998-05-25 1999-12-02 Abb Ab Chambre de combustion d'une turbine a gaz
EP1130219A1 (fr) * 2000-03-02 2001-09-05 Siemens Aktiengesellschaft Turbine avec joints d'étanchéitée entre les panneaux des parois
US6298667B1 (en) * 2000-06-22 2001-10-09 General Electric Company Modular combustor dome
EP1413831A1 (fr) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Chambre de combustion annulaire pour turbine à gaz et turbine à gaz
EP1555443A1 (fr) * 2004-01-13 2005-07-20 Siemens Westinghouse Power Company Dispositif de fixation pour chemise de chambre de combustion de turbine
EP1818615A1 (fr) * 2006-02-10 2007-08-15 Snecma Chambre de combustion annulaire d'une turbomachine
EP2012061A1 (fr) * 2007-07-05 2009-01-07 Snecma Déflecteur de fond de chambre, chambre de combustion le comportant et moteur à turbine à gaz en étant équipé
EP2040001A2 (fr) * 2007-09-21 2009-03-25 Snecma Chambre de combustion annulaire de moteur à turbine à gaz
EP2107308A1 (fr) * 2008-04-03 2009-10-07 Snecma Propulsion Solide Chambre de combustion sectorisée en CMC pour turbine à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105465830A (zh) * 2014-09-30 2016-04-06 阿尔斯通技术有限公司 燃烧器前面板
CN105465830B (zh) * 2014-09-30 2020-06-05 安萨尔多能源瑞士股份公司 燃烧器前面板
EP3299720A1 (fr) * 2016-09-22 2018-03-28 Ansaldo Energia IP UK Limited Ensemble avant de chambre de combustion pour turbine à gaz
CN107869735A (zh) * 2016-09-22 2018-04-03 安萨尔多能源英国知识产权有限公司 用于燃气涡轮机的燃烧室前组件
CN107869735B (zh) * 2016-09-22 2021-12-14 安萨尔多能源英国知识产权有限公司 用于燃气涡轮机的燃烧室前组件

Also Published As

Publication number Publication date
AU2011253595B2 (en) 2015-07-16
MY157102A (en) 2016-04-29
CH704185A1 (de) 2012-06-15
AU2011253595A1 (en) 2012-06-21
EP2463583B1 (fr) 2016-09-21

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