EP3845810A1 - Stützvorrichtung für wärmeisolierende kacheln einer brennkammer einer gasturbinenanlage für kraftwerke und eine gasturbinenanlage - Google Patents

Stützvorrichtung für wärmeisolierende kacheln einer brennkammer einer gasturbinenanlage für kraftwerke und eine gasturbinenanlage Download PDF

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Publication number
EP3845810A1
EP3845810A1 EP19425104.7A EP19425104A EP3845810A1 EP 3845810 A1 EP3845810 A1 EP 3845810A1 EP 19425104 A EP19425104 A EP 19425104A EP 3845810 A1 EP3845810 A1 EP 3845810A1
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EP
European Patent Office
Prior art keywords
supporting device
hooked head
gas turbine
combustion chamber
tile
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
EP19425104.7A
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English (en)
French (fr)
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EP3845810B1 (de
Inventor
Daniele Licata
Valerio Pistone
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 SpA
Original Assignee
Ansaldo Energia SpA
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 SpA filed Critical Ansaldo Energia SpA
Priority to EP19425104.7A priority Critical patent/EP3845810B1/de
Priority to CN202011614284.5A priority patent/CN113124419B/zh
Publication of EP3845810A1 publication Critical patent/EP3845810A1/de
Application granted granted Critical
Publication of EP3845810B1 publication Critical patent/EP3845810B1/de
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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
    • F23R3/002—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
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/04—Supports for linings
    • 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
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05002—Means for accommodate thermal expansion of the wall liner

Definitions

  • the present invention relates to the technical filed of the gas turbine assembly for power plants.
  • a gas turbine assembly in the following only gas turbine
  • an incoming air flow is compressed by a compressor and combusted with an added fuel in a combustion chamber for producing a hot gas flow to be expanded in a turbine for generating a rotating work on a rotor in turn connected to a generator.
  • the inner surface of the combustion chamber is provided with a plurality of heat-insulating tiles preferably made of refractory or ceramic material.
  • the present invention refers to a supporting or holding device configured for supporting or keeping in position the heat-insulating tiles on the inner surface of the combustion chamber.
  • a gas turbine assembly for power plants comprises a compressor assembly, a combustor assembly and a turbine assembly.
  • the compressor assembly is configured for compressing incoming air supplied at a compressor inlet.
  • the compressed air leaving the compressor assembly flows into a volume (called "plenum") and from there into the combustor assembly.
  • This combustor assembly comprises usually a plurality of burners configured for injecting fuel (oil and/or gas fuel) in the compressed air flow.
  • the mixture of fuel and compressed air enters a combustion chamber where this mixture is combusted.
  • the resulting hot gas flow leaves the combustion chamber and drives in rotation the turbine assembly that performs a work on the rotor (in turn connected to a power generator).
  • the turbine assembly comprises a plurality of stages, or rows, of rotating blades that are interposed by a plurality of stages, or rows, of stator vanes.
  • the rotating blades are supported by the rotor whereas the stator vanes are supported by a casing (called “vane carrier”) that is concentric and surrounding the turbine assembly.
  • a sequential gas turbine comprises a first and a second combustor or a first and a second combustion stage wherein each combustor is provided with a plurality of burners and with at least a relative combustion chamber.
  • the first and the second combustor are annular shaped and are physically separated by a stage of turbine blades, called high pressure turbine.
  • a second turbine unit Downstream the second combustor a second turbine unit is present (called low pressure turbine).
  • the gas turbine is not provided with the high pressure turbine and the combustor assembly is realized in form of a plurality of can-combustors arranged as a ring around the rotor.
  • Each can-combustor comprises a first combustor and a second combustor arranged directly one downstream the other inside a common can shaped casing.
  • the inner surface of the combustion chamber of gas turbines must be provided with a heat-insulating layer made of refractory material, because of the high temperatures which are developed during operation.
  • the heat-insulating layer is generally formed by a plurality of ceramic tiles arranged in continuous rows on the inner surface of the combustion chamber casing or combustion chamber shell, so as to define an essentially continuous heat-insulating surface.
  • each refractory tile is supported in position by a supporting device housed in part (by sliding) in grooves obtained on the inner surface of the combustion chamber casing.
  • the supporting devices need to have an elastic and spring features for keeping the ceramic tiles in position in all gas turbine working condition.
  • the supporting device comprises a plate configured to be housed by sliding in a groove of the combustion chamber casing and a hooked head protruding orthogonally outside the groove and configured to be coupled to an edge of the tile.
  • An example of this known hooked supporting device is disclosed in EP2741001 .
  • the hooked head comprises is series two portions; a first portion extending orthogonally from the plate and a second portion parallel to the plate.
  • the edge of the tile can be provided with a lateral groove for housing the second portion of the hooked head.
  • This hooked supporting device is made by metallic material and due to the high temperature it needs to be cooled.
  • the combustion chamber casing comprises holes for feeding cooling air running outside the combustion chamber to the supporting device.
  • a primary object of the present invention is to provide a supporting or holding device for supporting or keeping in position a heat-insulating tile (preferably a ceramic tile) of a combustion chamber of a gas turbine assembly for power plant.
  • a heat-insulating tile preferably a ceramic tile
  • the inner metallic surface of the combustion chamber has to be thermally protected due to the extreme high hot gas temperature and the protective layer is realized by a plurality of heat-insulating tiles.
  • each supporting device comprises:
  • the supporting device moreover comprises at least an additional element or body, i.e. the claimed at least an intermediate or spacing device, that is coupled to the hooked head and is configured for realizing a cooling channel between the hooked head and the tile. Therefore, according to this feature a space is present between the hooked head and the tile (space define by the interposition of the intermediate device) so that cooling air fed at the plate can flow in this channel and reach at least part of the metallic hooked head.
  • the cooling of the supporting device is improved avoiding any overheating.
  • the intermediate device comprises two bodies coupled to the first portion of the hooked head, wherein these two bodies are spaced each other for realizing a cooling channel between them along the first portion of the hooked head.
  • the cooling air flow can rise along the entire extent of the first portion of the hooked head.
  • these two bodies may have an extension less than the first portion of the hooked head so that to realize two upper lateral cooling channels between the upper edges of the bodies and the second portion of the hooked head.
  • the cooling air flow can rise along the entire extent of first portion towards the connection between the first and second portion of the hooked head and from there it can flow outside the supporting device passing by the upper channels.
  • the cooling air flow can reach also the connection between the first portion and second portion of the hooked head and it avoid hot gas ingestion.
  • the intermediate device may be realized in form of a single body coupled to the first portion of the hooked head.
  • the single body is spaced from the first portion of the hooked head and comprises an opening facing at one side the first portion of the hooked head and at the opposite side the side of the tile.
  • This channel may be realized in form of a recessed portion of the first portion of the hooked head.
  • the intermediate or spacing device can also be coupled to the second portion of the hooked head.
  • the single body is configured also for realizing cooling channels between the body itself and the second portion of the hooked head.
  • the hooked head may be T shaped.
  • the supporting device may be provided with a passing hole for allowing the cooling air (coming by passing holes obtained in the combustion chamber casing) to enter the claimed channel realized by the intermediate or spacing device between the tile and the hooked head.
  • connection between the first portion and the second portion of the hooked head of the supporting device may be provided with at least a passing hole connected to the cooling channel so that the cooling air can avoid any hot gas ingestion.
  • the supporting device may comprise an additional hooked head with the relative spacing device at the opposite end of the plate.
  • the present invention not only refers to supporting device itself but may be extended to the any gas turbine assembly for power plant comprising at least a supporting device as claimed in the enclosed claims.
  • the minimal components defining a gas turbine that can be provided by the present invention are a compressor unit, at least a combustion unit and at least a turbine unit wherein the combustion unit comprises at least a combustion chamber defined by a casing provided with a plurality of groves.
  • a plurality of tiles are provided for heat-insulating the combustion chamber casing and each tile is supported in position by a claimed supporting device.
  • the gas turbine may comprise in series a first combustion unit, a first turbine unit, a second combustion unit and a second turbine unit.
  • the gas turbine may comprise a plurality of can combustor wherein each can combustor may be configured for producing two combustion stages in series.
  • a gas turbine according to the present invention may be a gas turbine having a single combustion stage, i.e. a gas turbine comprising in series a compressor, a combustor and a turbine.
  • FIG. 1 is a schematic view of a first example of a gas turbine 1 that can be improved with the present invention.
  • the gas turbine 1 of figure 1 comprises a compressor 3, a first combustion stage, a high-pressure turbine 5, a second combustion stage and a low-pressure turbine 7.
  • the compressor 3 and the two turbines 5, 7 are connected to a common rotor 8 rotating around an axis 9 and surrounded by a concentric casing 10.
  • the compressor 3 is supplied with air and is provided with rotating blades 18 and stator vanes 19 configured for compressing the air entering the compressor 3.
  • the compressed air leaving the compressor flows into a plenum 11 and from there into a plurality of first burners 12 where this compressed air is mixed with fuel supplied by a first fuel supply 13.
  • the fuel/compressed air mixture flows into a first combustion chamber 4 where this mixture are ignited and combusted.
  • the resulting hot gas leaves the first combustor chamber 4 and drives the high-pressure turbine 5 performing work on the rotor 8.
  • Downstream of the high-pressure turbine 5 the gas partially expanded flows into a plurality of second burners where additional fuel is supplied by second fuel source 14.
  • the partially expanded gas has a high temperature and contains sufficient oxygen for a further combustion that, based on a self-ignition, takes place in a second combustion chamber 6 arranged downstream the second burners.
  • the reheated gas leaves the second combustion chamber 6 and flows in the low-pressure turbine 7 for performing rotating work on the rotor 8.
  • the low-pressure turbine 7 comprises a plurality of stages, or rows, of rotor blades 15 arranged in series in the main flow direction. Such stages of blades 15 are interposed by stages of stator vanes 16.
  • the rotor blades 15 are connected to the rotor 8 whereas the stator vanes 16 are connected to a vane carrier 17 that is a concentric casing surrounding the low-pressure turbine 7.
  • Each burner of this example is configured for injecting different kinds of fuel, namely gas fuel and oil fuel, i.e. each burner comprises a plurality of nozzles configured for injecting gas fuel and connected to a gas fuel source and a plurality of nozzles configured for injecting oil fuel and connected to an oil fuel source.
  • FIG. 2 is a schematic view of a second example of a gas turbine 1 that can be improved with the present invention.
  • figure 2 discloses a sequential gas turbine 20 provided with a compressor 29, an only a turbine 21 and a sequential combustor arrangement 22.
  • the sequential combustor arrangement 22 of figure 2 comprises a plurality of can combustors wherein each can combustor comprises first burners 24, a first combustion chamber 25, a second burner 26, and a second combustion chamber 27.
  • the first burner 24, the first combustion chamber 25, the second burner 26 and the second combustion chamber 27 are arranged sequentially in a fluid flow connection.
  • the sequential combustor is housed in a combustor can casing 28 of a plurality of cans arranged as a ring around the turbine axis.
  • a first fuel is introduced via a first fuel injector (not shown) into the first burner 24 wherein the fuel is mixed with the compressed gas supplied by the compressor 29.
  • a second fuel is introduced into the second burner 26 via a second fuel injector (not shown) and mixed with hot gas leaving the first combustion chamber 25.
  • the hot gas leaving the second combustion chamber 27 drives the turbine 21 performing work on a rotor 30.
  • gas turbine of figure 1 and 2 have been cited only as example of gas turbines that can be improved by the present invention.
  • Figure 3 discloses a solution proposed by the prior art for solving the problem of supporting or keeping in position a tile of a combustion chamber.
  • figure 3 discloses a portion of a combustion chamber casing 31 wherein the inner surface 32 of this casing 31 is provided with a plurality of grooves 33. The opposite surface 34 is in contact with cooling air.
  • a portion of a tile 35 is disclosed wherein this tile is coupled to the inner surface 32 of the casing 31 for thermally protecting the casing itself 31.
  • this tile 35 is made by a heat-insulating material, preferably a ceramic material.
  • This tile 35 is supported in position on the inner surface 32 by a supporting device according to the prior art, i.e.
  • a supporting device 36' comprising a plate 37 housed by sliding in a groove 33 and a hooked head 38 configured for being coupled to a groove 39 obtained in a side of the tile 35.
  • This supporting device 36' is made of a metallic material and is cooled by air coming from holes 40 obtained in the casing 31.
  • the hooked head 38 comprises in series a first portion 41 orthogonal to the plate 37 protruding inside the combustion chamber and a second portion 42 orthogonal to the first 41 and parallel to the plate 37, wherein both the first 41 and the second portion 42 are in direct contact to the tile 35.
  • Figure 4 discloses a first embodiment of a supporting device according to the invention, i.e. a supporting device 36 according to figure 3 but provided with the new intermediate or spacing device 43.
  • the intermediate or spacing device 43 of figure 4 comprises two spacing bodies 43 coupled to the first portion 41 of the hooked head 38 and spaced each other to realize a cooling channel 44 between them. Once coupled with the tile 35, the cooling channel 44 is limited by the first portion 41 of the hooked head 38, the tile 35 and the spacing bodies 43. The cooling air can enter this channel by a hole 45 obtained at the connection between the plate 37 and the hooked head 38.
  • Figure 5 discloses a portion of the supporting device 36 of figure 4 coupled to the combustor casing 31.
  • the new cooling channel 44 is disclosed and the arrow F1 represents the cooling air flow entering the channel 41 by the hole 45.
  • the air flow F1 reaches the second portion 42 of the hooked head 38, this air can flow in two lateral channels limited by the upper edges of the bodies 43 and the second portion 42 of the hooked head 38.
  • these lateral flows are represented by the arrows F2.
  • Figure 6 discloses two tiles 35 respectively supported by a supporting device 36' according to figure 3 (prior art) and a supporting device 36 according to figure 4 (new) wherein the spacing device 43 is interposed between the first portion 41 of the hooked head 38 and the tile 35.
  • Figure 7 discloses a second embodiment of a supporting device 36 according to the invention coupled to a tile 35.
  • the intermediate or spacing device 43' is also coupled to the second portion 42 of the hooked head 38 so that the tile 35 is in direct contact only with the intermediate or spacing device 43'.
  • Figure 8 and 9 disclose the supporting device 36 of figure 7 isolated from the tile 35.
  • the intermediate or spacing device 43' is a single body spaced to the first portion 41 of the hooked head 38.
  • the spacing device 43' comprises an opening 46 connected to the channel 44 and facing at one side the tile 35 and at the opposite side the first portion 41 of the hooked head 38.
  • Figures 10-12 disclose some components of the supporting device of figure 9 . These figures allow to recognize that the channel 44 between the first portion 41 of the hooked head 38 and the spacing device 43' is obtained by a recessed portion 47 of the first portion 41 of the hooked head 38. According to this embodiment the spacing device 43' is coupled to the second portion 42 of the hooked head 38 by ribs 48 obtained in the upper part of the spacing device 43' housed in grooves 49 obtained in the second portion 42 of the hooked head 38.
  • Figure 13-14 disclose some components of an alternative embodiment similar to the embodiment of the previous figures.
  • the spacing device 43' is coupled to the second portion 42 of the hooked head 38 by grooves 48' obtained in the upper part of the spacing device 43' housing ribs 49' obtained in the second portion 42 of the hooked head 38.
  • Figure 15 discloses an embodiment similar to the embodiment disclosed in figure 4 wherein the second portion 42 of the hooked head 38 is also provided with holes 50 for discharging the air from the channel 44 in order to prevent hot gas ingestion.
  • figure 16 discloses a schematic view of an additional example of a gas turbine 1' suitable for being provided with the present invention.
  • the present invention can be applied not only in gas turbines having two combustion stages a disclosed in figures 1 and 2 but also in a gas turbines having a single combustion stage regardless of the shape of the combustor unit. Therefore, figure 16 discloses a generic gas turbine 1' having a rotor 6' defining an axis 2'. This gas turbine 1' comprises in series along the main flow M:

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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)
EP19425104.7A 2019-12-31 2019-12-31 Stützvorrichtung für wärmeisolierende kacheln einer brennkammer einer gasturbinenanlage für kraftwerke und eine gasturbinenanlage Active EP3845810B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP19425104.7A EP3845810B1 (de) 2019-12-31 2019-12-31 Stützvorrichtung für wärmeisolierende kacheln einer brennkammer einer gasturbinenanlage für kraftwerke und eine gasturbinenanlage
CN202011614284.5A CN113124419B (zh) 2019-12-31 2020-12-31 燃气涡轮组件及用于其燃烧室的绝热砖瓦的支承装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19425104.7A EP3845810B1 (de) 2019-12-31 2019-12-31 Stützvorrichtung für wärmeisolierende kacheln einer brennkammer einer gasturbinenanlage für kraftwerke und eine gasturbinenanlage

Publications (2)

Publication Number Publication Date
EP3845810A1 true EP3845810A1 (de) 2021-07-07
EP3845810B1 EP3845810B1 (de) 2023-11-22

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EP19425104.7A Active EP3845810B1 (de) 2019-12-31 2019-12-31 Stützvorrichtung für wärmeisolierende kacheln einer brennkammer einer gasturbinenanlage für kraftwerke und eine gasturbinenanlage

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EP (1) EP3845810B1 (de)
CN (1) CN113124419B (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4206532A1 (de) * 2021-12-30 2023-07-05 ANSALDO ENERGIA S.p.A. Brennkammer für ein gasturbinentriebwerk

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59162323A (ja) * 1983-03-07 1984-09-13 Hitachi Ltd 断熱材の呼吸構造
US20060176671A1 (en) * 2005-02-07 2006-08-10 Siemens Aktiengesellschaft Heat shield
US20090056339A1 (en) * 2005-04-19 2009-03-05 Marcus Fischer Retaining Element and Heat Shield Element for a Heat Shield and Combustion Chamber Provided with a Heat Shield
EP2741001A1 (de) 2012-12-10 2014-06-11 Ansaldo Energia S.p.A. Stützstruktur für Hitzeschildplatten einer Gasturbinenbrennkammer, Hitzeschildeinheit und Gasturbinenbrennkammer

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1557611B1 (de) * 2004-01-21 2014-12-31 Siemens Aktiengesellschaft Strömungsbarriere, Verkleidung und Brennkammer
ATE514905T1 (de) * 2004-04-30 2011-07-15 Siemens Ag Spaltdichtelement für einen hitzeschild
EP2711630A1 (de) * 2012-09-21 2014-03-26 Siemens Aktiengesellschaft Vorrichtung zum Kühlen einer Tragstruktur eines Hitzeschildes und Hitzeschild
WO2015022222A1 (de) * 2013-08-15 2015-02-19 Siemens Aktiengesellschaft Hitzeschild mit mindestens einem helmholtzresonator
DE102017206502A1 (de) * 2017-04-18 2018-10-18 Siemens Aktiengesellschaft Halteelement zum Fixieren eines Hitzeschildelements und Brennkammer mit Hitzeschild, das ein derartiges Halteelement umfasst

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59162323A (ja) * 1983-03-07 1984-09-13 Hitachi Ltd 断熱材の呼吸構造
US20060176671A1 (en) * 2005-02-07 2006-08-10 Siemens Aktiengesellschaft Heat shield
US20090056339A1 (en) * 2005-04-19 2009-03-05 Marcus Fischer Retaining Element and Heat Shield Element for a Heat Shield and Combustion Chamber Provided with a Heat Shield
EP2741001A1 (de) 2012-12-10 2014-06-11 Ansaldo Energia S.p.A. Stützstruktur für Hitzeschildplatten einer Gasturbinenbrennkammer, Hitzeschildeinheit und Gasturbinenbrennkammer

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4206532A1 (de) * 2021-12-30 2023-07-05 ANSALDO ENERGIA S.p.A. Brennkammer für ein gasturbinentriebwerk

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Publication number Publication date
CN113124419A (zh) 2021-07-16
CN113124419B (zh) 2024-05-24
EP3845810B1 (de) 2023-11-22

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