US20180080651A1 - Combustor front assembly for a gas turbine - Google Patents

Combustor front assembly for a gas turbine Download PDF

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Publication number
US20180080651A1
US20180080651A1 US15/708,696 US201715708696A US2018080651A1 US 20180080651 A1 US20180080651 A1 US 20180080651A1 US 201715708696 A US201715708696 A US 201715708696A US 2018080651 A1 US2018080651 A1 US 2018080651A1
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US
United States
Prior art keywords
combustor
combustor front
front plate
rotor
assembly
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.)
Abandoned
Application number
US15/708,696
Other languages
English (en)
Inventor
Marijan BEG
Urs Benz
Branko CVITAK
Ivo BELINA
Piotr SIEWERT
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Ansaldo Energia IP UK Ltd
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 Ansaldo Energia IP UK Ltd filed Critical Ansaldo Energia IP UK Ltd
Publication of US20180080651A1 publication Critical patent/US20180080651A1/en
Abandoned legal-status Critical Current

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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
    • F23R3/007—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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/52—Toroidal combustion chambers
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • 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
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • the present invention relates to a combustor front assembly for a gas turbine power plant.
  • the present invention refers to an annular combustor front assembly suitable to be preferably associated with a plurality of EV burners.
  • the present invention refers to a gas turbine power plant provided with the above combustor front assembly.
  • a gas turbine power plant (in the following only gas turbine) comprises, following the main gas flow, a compressor fed with air, one or more combustors fed with the compressed air wherein a fuel is injected, mixed to the air flow and burnt in order to generate an high pressure gas, and a turbine fed with the high pressure gas.
  • the combustion chamber is an annular structure around the gas turbine axis.
  • This annular combustion chamber is outwardly and inwardly delimited by side walls, upstream by a front assembly coupled with a plurality of burners and downstream by a hot gas discharge passage facing the turbine.
  • outwardly/outer and inwardly/inner refer to the gas turbine axis.
  • upstream and downstream refer to the main gas flow direction.
  • FIG. 1 An example of this kind of gas turbine is schematically represented in FIG. 1 wherein the reference M refers to the main gas flow direction.
  • the gas turbine 1 comprises a casing 2 covering a rotor 3 able to rotate around an axis 4 .
  • the gas turbine 1 comprises a compressor 5 for compressing air that flows into a plenum 6 .
  • the gas turbine 1 comprises an annular combustion chamber 7 arranged concentrically to the axis 4 and provided with an inner 13 and an outer shell 14 .
  • the annular combustion chamber 7 comprises a combustor front assembly 8 that is ring-shaped around the axis 4 .
  • the annular combustion chamber 7 comprises a hot gas passage 9 connected with the inlet of the turbine 10 .
  • FIG. 1 discloses a burner 11 , in particular an EV-burner, coupled to the combustor front assembly 8 .
  • the gas turbine 1 comprises a plurality of burner 11 equally spaced. The gas leaves the burner and enters the annular combustion chamber 7 passing thought the combustor front assembly 8 .
  • a hot air flow 12 formed during the combustion reaches the turbine 10 passing through the above mentioned hot gas passage 9 at the outlet side of the annular combustion chamber 7 .
  • the hot air flow expands performing rotating work on the axis 4 .
  • the combustion chamber 7 is preferably enclosed by an outer 15 and inner cooling shroud 16 in order to realize an outer 17 and inner cooling passage 18 .
  • cooling air flows in the opposite direction with respect to the hot gas flow 12 along the walls of the combustion chamber 7 into a combustor hood 19 . From the combustor hood 19 the air flows into the burner 11 or, passing thought front cooling passages 20 , directly into the combustion chamber 7 .
  • the burner disclosed in FIG. 1 is preferably a EV burner where EV stand for “enVironmental” burner.
  • the burners can be AEV-burners where AEV stand for “Advanced EnVironmental”.
  • This kind of burners is characterized by a very low NOx levels.
  • EP0851172, EP2423597 and WO 2009/019113 disclose EV burners provided with a single or double cone and comprising a swirl generator and a mixing tube at the exit of a burner prior the combustion chamber.
  • the mixing tube is configured to stabilize the swirl flow.
  • an EV burner comprises also a transition piece.
  • FIG. 2 shows an enlarged view of a portion of a combustor front assembly according to the prior art.
  • the combustor front assembly comprises a combustor front plate 32 that is ring-shaped around the gas turbine axis.
  • the combustor front plate 32 can be arranged orthogonal with respect to the gas turbine axis 4 or inclined as disclosed in FIG. 1 .
  • the combustor front plate 32 comprises a plurality of through holes 21 equally spaced along the combustor front plate 32 . These through holes 21 define a plurality of passages for the hot gas from the burners 11 to the annular combustion chamber 7 .
  • each through hole 21 of the front plate 32 is coupled with the relevant burner 11 , preferably with the mixing tube in case of a EV burner.
  • the combustor front assembly comprises a plurality of combustor front segments 22 that are tile-shaped and cover, on the burner 11 side, the entire length of the front plate 32 .
  • Each front segment 22 comprises a through hole 23 that, once the segment 22 is coupled with the plate 32 , is axially aligned with the front plate through hole 21 .
  • the front segment 22 comprises a front wall 29 and side walls 30 .
  • FIG. 3 is a schematic section view of the combustor front assembly of the FIG. 2 according to prior art along the section line A-A.
  • FIG. 3 shows how the front segment 22 is coupled with the front plate 32 according the prior art.
  • the combustor front assembly comprises a hook member 24 having a base 25 housed in a relative seat 26 realized in the front plate 32 and a hook end 27 configured to be coupled with a through slot 28 realized in the lateral wall 20 of the front segment 22 .
  • the hook member 24 is fixed and pushed against the front plate 32 by a screw or bolt member 31 in order to maintain the front segment 22 in the correct position.
  • a primary object of the present invention is to provide a combustor front assembly for a gas turbine that allows to increase the lifetime and the reliability of the fixation and sealing system between the combustor front plate and the combustor front segments.
  • the present invention provides a combustor front assembly for a gas turbine wherein the gas turbine comprises:
  • the combustion chamber comprising is an annular combustion chamber arranged concentrically to the turbine axis and comprises a combustor front assembly coupled with a plurality of burners, for instance EV-burners.
  • the combustor front assembly is provided with at least a though hole (a plurality of though holes in case of an annular combustion chamber) in order to allow the gas flow to leave the burners and to enter the combustion chamber.
  • the combustor front assembly comprises:
  • the combustor front segment is clamped to the outer surface of the combustor front plate.
  • the combustor front segment is kept in position in abutment against the front plate in a clamped manner.
  • the combustor front assembly comprises a plurality of combustor front segments tile-shaped covering the entire outer surface of the combustor front plate.
  • the fixation system of the present invention based on a clamping system between the front segment and the front plate, ensures robustness and reduces the risk of failure due front segment disengage during the start-up phase, the steady state operating regime and also after long operating periods.
  • each tile-shaped combustor front segments comprises a front wall, spaced and parallel to the outer surface of the combustor front plate, and two opposite L-shaped side walls.
  • Each L-shaped side wall comprises a first portion, orthogonal to the outer surface of the combustor front plate and connected with the front wall, and a second portion spaced and parallel to the front wall facing the outer surface of the combustor front plate. This second portion of the side walls of the combustor front segments is clamped and forced against to the outer surface of the combustor front plate.
  • each tile-shaped combustor front segments comprises two side clamping strips having length equal to the side walls and are also configured to push the second portion of the side walls against the outer surface of the combustor front plate.
  • the clamping and pushing effects are acting along the entire length of the side wall and therefore the contact pressure is distributed over a large area. Consequently, this solution allows to reduce the risk of wear along the side walls of the front segment.
  • each tile-shaped combustor front segment comprises two side closing strips facing the side clamping strips and configured for clamping the free end of the second portion of the side walls between the side clamping strips and the side closing strips.
  • each tile-shaped combustor front segment comprises an L-shaped outer and inner wall having a first portion, orthogonal to the outer surface of the combustor front plate and connected with the front wall, and a second portion spaced and parallel to the front wall.
  • the second portion of such outer and inner wall of the combustor front segments are clamped and pushed against the outer surface of the combustor front plate.
  • the clamping system of the present invention between the front segment and the front plate ensure sufficient robustness also along the inner and outer walls.
  • each tile-shaped combustor front segment comprises an inner and an outer middle clamping plate arranged in the middle of the outer and inner wall.
  • Such middle clamping plates are configured to clamp and push the second portion of the outer and inner wall against the outer surface of the combustor front plate.
  • each tile-shaped combustor front segment comprises an inner and outer closing strip. Each closing strip is facing the relative middle clamping plate for clamping the free end of the second portion of the outer and inner wall between the middle clamping plates and the inner and outer closing strip.
  • the clamping effect is acting along the entire length of the middle clamping plate and therefore the contact pressure is distributed over a large area. Consequently, this solution allows to reduce the risk of wear along the inner and an outer walls of the front segment.
  • the middle clamping plates are also in abutment against a step seat realized in the inner surface of the through hole of the front segment.
  • this solution allows to ensure the correct position of the middle clamping plates. Moreover, according to this feature, the front segment during the steady state operating condition is self-restraining due to its thermal deformation.
  • the inner and outer closing strip and the side closing strips are integral each-others to form a single square frame.
  • this solution allow to ensure an easy and quick assembly of the front segment.
  • the combustor front assembly comprises a seal between the combustor front segment and the outer surface of the combustor front plate.
  • the seal is a rope seal housed in a perimetric groove realized in the outer surface of the combustor front plate.
  • this solution allow the seal to be clamped in position with limited movements. Consequently, the seal lifetime is optimized.
  • the outer surface of the combustor front plate consists in straight portions.
  • planar portions ensures to realize well-controlled clearances between the front plate and the front segments.
  • FIG. 1 is a schematic section view of a gas turbine provided with an annular combustion chamber
  • FIG. 2 is a schematic partial prospective view of a front combustor assembly according to the prior art
  • FIG. 3 is a schematic section view of the combustor front assembly of the FIG. 2 along the section line A-A;
  • FIG. 4 is a schematic partial prospective view of a front combustor assembly according to the invention.
  • FIG. 5 is a schematic section view of the combustor front assembly of the FIG. 4 along the section line B-B;
  • FIG. 6 is a schematic section view of the combustor front assembly of the FIG. 4 along the section line C-C;
  • FIG. 7 is a schematic partial prospective view of the combustor front assembly of the FIG. 4 under thermal deformation during the steady state operation regime of the relative gas turbine;
  • FIG. 8 is a schematic section view of the combustor front assembly of the FIG. 7 along the section line C-C;
  • FIG. 9 is a schematic section view of the combustor front assembly of the FIG. 7 along the section line D-D;
  • FIG. 10 is a schematic partial prospective view of the combustor front plate without any front segment according to the invention.
  • FIG. 11 is a schematic exploded prospective view of the combustor front segment according to the invention.
  • FIGS. 4-11 that disclose in detail an embodiment of the present invention.
  • FIG. 1 that is a schematic view of a gas turbine, will be made only in order to explain how the invention cooperates with the relative gas turbine.
  • FIG. 4 is a schematic partial prospective view of a front combustor assembly, on the burner side, according to the invention.
  • FIG. 4 discloses a portion of a ring-shaped combustor front plate 34 centered around the turbine axis 4 (see also FIG. 1 ) and a tile-shaped combustor front segments 38 coupled to the outer surface 36 of the combustor front plate 34 .
  • the outer surface 36 is the surface of the front plate 34 that is outside the combustion chamber 7 facing the burner 11 (see also FIG. 1 ).
  • the combustor front plate 34 is provided with a plurality of through holes 35 equally spaced whereas each combustor front segment 38 comprises a through hole 39 .
  • the through hole 39 of the front segment 38 is aligned with the through hole 35 of the front plate 34 in order to realize a passage for the gas flowing from the burner 11 to the combustion chamber 7 .
  • the front segments 38 are arranged along the front plate 34 in order to cover the entire outer surface 36 .
  • the front plate 34 comprises fixing portions 55 configured to couple the front plate 34 to the inner 13 and outer shell 14 of the combustion chamber 7 (see also FIG. 1 ).
  • Each tile-shaped combustor front segment 38 comprises a front wall 40 , side walls 41 , an inner and an outer wall 46 .
  • FIG. 5 is a schematic section view of the combustor front assembly of the FIG. 4 along the section line B-B.
  • the front wall 40 of the front segments 38 is spaced and parallel with respect to the outer surface 36 of the front plate 34 .
  • the side walls 41 of the front segments 38 are L-shaped and comprise a first portion 42 , orthogonal to the outer surface 36 of the combustor front plate 34 , and a second portion 43 , having a free end, spaced and parallel to the front wall 40 .
  • the second portion 43 of the side walls 41 of the combustor front segments 38 is facing the outer surface 36 of the front plate 34 .
  • the free end of such second portion 43 is clamped between the side clamping strip 44 , in form of a rail parallel to the side wall 41 , and the relative side closing strip 45 .
  • the side clamping strip 44 is coupled with the inner surface (inside the front segment 38 ) of the second portion 43 of the side wall 41 of the combustor front segments 38
  • the side closing strip 45 is coupled to the outer surface (facing the front plate 34 ) of the second portion 43 of the side wall 41 of the combustor front segments 38 .
  • FIG. 5 discloses a seal 53 arranged in a groove 54 realized in the perimetric higher portion 57 of the outer surface 36 of the combustor front plate 34 .
  • the seal is between the outer surface 36 of the combustor front plate 34 and the second portions 43 of the side wall 41 .
  • the front segment 38 can be defined as clamped against the front plate 34 because the free ends of the side walls 41 of the front segment 38 are clamped and pressed against the outer surface 36 , in particular against the perimetric higher portion 57 .
  • FIG. 6 is a schematic section view of the combustor front assembly of the FIG. 4 along the section line C-C.
  • FIG. 6 discloses that also the inner and outer wall of the front segment 38 are L-shaped and comprise a first portion 47 , orthogonal to the outer surface 36 of the combustor front plate 34 and connected with the front wall 40 , and a second portion 48 .
  • Such second portion 48 is spaced and parallel to the front wall 40 facing the outer surface 36 of the front plate 34 .
  • the free end of the second portion 38 of the outer and inner wall 46 is clamped between an inner and an outer middle clamping plate 49 , arranged in the middle of the outer and inner wall 46 , and an inner and outer closing strip 50 .
  • the middle clamping plate 49 Acting on a screw or bolt member 31 passing the front plate 34 and the middle clamping plate 49 (see FIG. 6 ), the middle clamping plate 49 proceed with clamping the free and of the second portion 48 , and push the second portion 48 against the outer surface 36 of the combustor front plate 34 .
  • the middle clamping plate 49 is also resting on a step seat 52 realized in the inner surface of the hole 39 .
  • FIG. 6 also discloses a seal 53 arranged in a groove 54 realized in the perimetric higher portion 57 of the outer surface 36 of the combustor front plate 34 .
  • the seal 53 is placed between the outer surface 36 of the combustor front plate 34 and the second portions 48 of the inner and outer wall 46 .
  • FIGS. 7-9 are schematic view of the combustor front assembly of the FIG. 4 during the steady state operation regime of the relative gas turbine.
  • FIG. 7 discloses the combustor front assembly of the FIG. 4 under the operation thermal deformation.
  • FIG. 8 and are schematic section views of the combustor front assembly of the FIG. 7 along the section lines C-C and D-D.
  • the clamping system of the present invention is self-restraining. Indeed, along the line C-C, i.e. at the inner or outer wall 46 , the thermal deformation acting on the side clamping strips 44 generates an additional pushing force located at the clamping zone and at the step seat 52 .
  • the thermal deformation generates an additional pushing force acting at the front segment 38 against the front plate 34 .
  • the location where these additional pushing forces are acting have been schematically represented by the reference number 58 .
  • the dotted line 59 above the front wall 40 schematically represents the deformation of the front segment 38 during the steady state operation regime of the gas turbine.
  • FIG. 10 is a schematic partial prospective view of the combustor front plate 34 of FIG. 4 without the front segment 38 .
  • FIG. 10 discloses the lower portion 56 and the higher portion 57 of the outer surface 36 of the combustor front plate 34 .
  • these portions 56 57 of the outer surface 36 of the combustor front plate 34 are straight.
  • the outer surface 36 of the combustor front plate 34 comprises a step that realizes a seat for the seal 53 .
  • FIG. 11 is a schematic exploded prospective view of the combustor front segment according to the invention.
  • the inner and outer closing strip 50 and the side closing strips 45 are integral each-others to form a single square frame 51 .
  • such square frame 51 is fixed in position with respect to the middle clamping plates 49 and to the side clamping strips 44 by bolt or screw 60 .

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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)
US15/708,696 2016-09-22 2017-09-19 Combustor front assembly for a gas turbine Abandoned US20180080651A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP16190197.0A EP3299720B1 (de) 2016-09-22 2016-09-22 Brennkammerfrontanordnung für eine gasturbine
EP16190197.0 2016-09-22

Publications (1)

Publication Number Publication Date
US20180080651A1 true US20180080651A1 (en) 2018-03-22

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Application Number Title Priority Date Filing Date
US15/708,696 Abandoned US20180080651A1 (en) 2016-09-22 2017-09-19 Combustor front assembly for a gas turbine

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US (1) US20180080651A1 (de)
EP (1) EP3299720B1 (de)
CN (1) CN107869735B (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111520761B (zh) * 2020-04-22 2022-02-01 中国空气动力研究与发展中心 一种可实现隔离段流场结构观测的旋转爆震燃烧室

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5291733A (en) * 1993-02-08 1994-03-08 General Electric Company Liner mounting assembly
GB2295887A (en) * 1994-12-08 1996-06-12 Rolls Royce Plc Combustor assembly
DE19654116A1 (de) 1996-12-23 1998-06-25 Abb Research Ltd Brenner zum Betrieb einer Brennkammer mit einem flüssigen und/oder gasförmigen Brennstoff
EP1302723A1 (de) * 2001-10-15 2003-04-16 Siemens Aktiengesellschaft Auskleidung für Innenwände von Brennkammern
US6871501B2 (en) * 2002-12-03 2005-03-29 General Electric Company Method and apparatus to decrease gas turbine engine combustor emissions
WO2009019113A2 (de) 2007-08-07 2009-02-12 Alstom Technology Ltd Brenner für eine brennkammer einer turbogruppe
CH703655A1 (de) 2010-08-27 2012-02-29 Alstom Technology Ltd Vormischbrenner für eine gasturbine.
CH704185A1 (de) * 2010-12-06 2012-06-15 Alstom Technology Ltd Gasturbine sowie verfahren zum rekonditionieren einer solchen gasturbine.
EP2685160B1 (de) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Multikonus-Vormischungsbrenner für eine Gasturbine
EP2952812B1 (de) * 2014-06-05 2018-08-08 General Electric Technology GmbH Ringbrennkammer einer gasturbine und verkleidungssegment
US9840932B2 (en) * 2014-10-06 2017-12-12 General Electric Company System and method for blade tip clearance control

Also Published As

Publication number Publication date
CN107869735B (zh) 2021-12-14
EP3299720B1 (de) 2020-11-04
EP3299720A1 (de) 2018-03-28
CN107869735A (zh) 2018-04-03

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