EP4372281A1 - Chambre de combustion pour un ensemble turbine à gaz de centrale électrique comprenant une pluralité de tuiles métalliques de protection thermique présentant une caractéristique de refroidissement d'air améliorée - Google Patents

Chambre de combustion pour un ensemble turbine à gaz de centrale électrique comprenant une pluralité de tuiles métalliques de protection thermique présentant une caractéristique de refroidissement d'air améliorée Download PDF

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Publication number
EP4372281A1
EP4372281A1 EP22425055.5A EP22425055A EP4372281A1 EP 4372281 A1 EP4372281 A1 EP 4372281A1 EP 22425055 A EP22425055 A EP 22425055A EP 4372281 A1 EP4372281 A1 EP 4372281A1
Authority
EP
European Patent Office
Prior art keywords
plenum
combustion chamber
tile
pipes
layer
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.)
Pending
Application number
EP22425055.5A
Other languages
German (de)
English (en)
Inventor
Daniele Licata
Alberto Amato
Armando Alsina Torrent
Ivo Belina
Michael Klaus DUESING
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 EP22425055.5A priority Critical patent/EP4372281A1/fr
Priority to PCT/IB2023/061594 priority patent/WO2024105611A1/fr
Publication of EP4372281A1 publication Critical patent/EP4372281A1/fr
Pending 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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow

Definitions

  • the present invention relates to the technical filed of the gas turbine assembly for power plants.
  • a power plant gas turbine assembly in the following only gas turbine
  • an incoming air flow is compressed by a compressor and mixed 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.
  • Due to the high temperature it is common to provide the inner surface of the combustion chamber with a plurality of heat shieling tiles arranged in rows.
  • the present invention refers the technical problem of how to improve the cooling the heat shieling tiles when these tile are metallic tiles and the cooling medium is air.
  • 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.
  • this heat shielding layer is formed by a plurality of tiles arranged in circumferential rows on the inner surface of the combustion chamber casing, so as to define an essentially continuous heat-insulating surface. It is common to realize tiles made of metallic material and to use air as cooling medium. In order to improve the efficiency of the assembly, today there is the need to improve the air cooling feature of these metallic heat shielding tiles.
  • a primary object of the present invention is to provide a new and inventive combustion chamber for a power plant gas turbine assembly.
  • scope to the present invention is to offer a metallic heat shielding tile having an improved air cooling feature for heat shielding the inner surface of the combustion chamber.
  • the combustion chamber may have any shape and the turbine assembly may be of any type.
  • a skill person in this field well know what a combustor chamber and a metallic heat shielding tile are and thus no additional details are due for the understanding of the context of the invention.
  • a combustion chamber is a space, preferably but not limiting annular shaped, defined by an outer casing wherein an hot gas flow runs along a main direction M. Due to the high temperature of this hot gas, it is common to provide the combustor casing with a plurality of heat shielding tiles supported by the outer casing itself.
  • two layers of pipes are provided for cooling the tile device wherein, preferably, the tile body and the pipes are made as a single piece by using a metallic additive process, as SLM.
  • the cooling air entering the pipes are coming from a plenum (the skill person well knows what a plenum is, i.e. a dedicated isolated volume) called in this invention as tile plenum because it is preferably provided and obtained directly on the outer face of the tile body. Thus, the size of the tile is very small.
  • Each cooling pipe comprises an inlet facing the tile plenum and least an inlet air hole is provided for connecting the tile plenum to an outer cooling air source (for instance a plenum arranged outside the combustor casing).
  • the cooling pipes of each layer are configured so that the cooling air flowing in two adjacent cooling pipes of the same layer is in counter flow.
  • the cooling pipes of the first layer are orthogonal to the cooling pipes of the second layer.
  • the cooling pipes of the first layer are parallel to the hot gas flow main direction M.
  • a bolt is provided for fixing the metallic tile body to the combustion chamber outer casing; the bolt is orthogonal to the tile body and passing by a fixing hole obtained substantially in the middle of the tile body.
  • a thermal barrier coating is provided on the inner face of the tile body.
  • the bridge plenum is parallel to the pipes of the second layer and two air inlet holes are provided for delivering air into the second plenum from a plenum outside the casing.
  • the pipes and the tile plenum are connected as in the following for allowing the air to e enter the pipes:
  • each line is divided in two pipes upstream and downstream the bridge plenum.
  • the tile plenum are made in a single piece by a selective adding process with the tile body and the pipes.
  • the present invention extends its protection to any power plant gas turbine assembly comprising:
  • figure 1 is a schematic view of a power plant gas turbine assembly that may be improved by the present invention.
  • a power plant gas turbine assembly suitable to be improved by the present invention.
  • a such gas turbine assembly is an assembly 1 as comprising:
  • FIG. 2 is a schematic view of a portion of a combustion chamber.
  • the combustion chamber 3 is limited by an outer casing 7 defining a channel for the hot gas M.
  • the reference 21 in figure 2 refers to holes realized in each tile for housing a bolt configured for fixing the tile to the casing. As known, these tiles are substantially flat and are configured for following the shape of the casing.
  • each tile is a metallic tile made in a single piece by an additive process.
  • FIG. 3 is a cross section view of an example of a heat shielding tile device according to the present invention coupled to the combustor casing.
  • This figure discloses the presence of a tile body 9 having an inner face 10 facing the hot gas and an outer face 11 spaced and facing the casing 7.
  • the body 9 is substantially flat and discloses raised edges projecting towards the casing. As it will be clear in the following, these raised edges allow to define a tile plenum fed by cooling air that coming from an outer plenum 19 enters the tile plenum 14 passing by air inlet holes 18.
  • Reference 20 refers to fixing bolt connecting the tile to a swirlock assembly in turn coupled to the outer face of the casing.
  • FIG 4 is a schematic view of the tile device alone disclosing the outer face of the tile of figure 3 .
  • a plurality of parallel pipes 12 are obtained on the outer face or directly inside the tile body forming a first or inner layer 16 of pipes parallel to the hot gas flow M.
  • a plurality of parallel pipes 13 are provided for forming a second or outer layer 17 of pipes orthogonal to the hot gas flow M.
  • the pipes 13 of the second layer 17 run along the entire face of the tile from the edge 24 to the opposite edge 25.
  • the pipes 12 of the second layer 16 run from a central portion 15 of the tile to opposite edges 22 and 23.
  • the tile plenum of this example comprises:
  • Figure 5 is a schematic view disclosing the cooling air flow flowing in the pipes of the first layer.
  • the circles refer to inlets of the pipes 12 and the arrows the outlets.
  • Figure 6 is a schematic view disclosing the cooling air flow flowing in the pipes of the second layer obtained on the first layer.
  • the circles refer to inlets of the pipes 13 and the arrows the outlets.
  • central pipes 13 of the second layer 17 have inlets in the bridge plenum 15 and outlets facing tiles adjacent to the third 24 and fourth 25 portion of the square plenum 14.
  • some central pipes 13 of the second layer 17 disclose inlets in the third 24 and fourth 25 portion of the square plenum and outlets on the inner face 10 of the tile 9 at the bolt hole 20.
  • Figure 7 is a cross section view of the tile of figure 4 along the line VII and figures 8-10 are enlarged views of portions labelled as VIII, IX, and X in figure 7 .
  • These figures allow to discloses how the air enter into the pipes 12 of the first layer and where are located the corresponding outlets.
  • the pipe 12 in the right part of the tile discloses an inlet inside the portion 22 of the plenum 14 and outlet on the outer face of the tile upstream the bridge plenum 15.
  • the pipe 12 in the right part of the tile discloses an inlet inside the bridge plenum 15 and an outlet facing the tile beyond the portion 23 of the plenum 14.
  • FIG 11 is a cross section view of the tile of figure 4 along the line XI and figures 12-14 are enlarged views of portions labelled as XII, XIII, and XIV in figure 7 .
  • These figures allow to discloses how the air enter into the central pipes 13 of the second layer and where are located the corresponding outlets.
  • the pipe 13 in the right part of the tile discloses an inlet inside the bridge plenum 15 and outlet facing the tile beyond the portion 24 of the plenum 14.
  • the pipe 13 in the right part of the tile discloses an inlet inside the portion 25 of the plenum 14 and an outlet on the inner face of the tile at the hole 21 housing the bolt 20.
  • Apart the central pipes 13, the remaining pipes 13 of the second layer run along the entire tile body from side to opposite side taking air from one edge of the plenum and discarding air outside the opposite edge.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP22425055.5A 2022-11-18 2022-11-18 Chambre de combustion pour un ensemble turbine à gaz de centrale électrique comprenant une pluralité de tuiles métalliques de protection thermique présentant une caractéristique de refroidissement d'air améliorée Pending EP4372281A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP22425055.5A EP4372281A1 (fr) 2022-11-18 2022-11-18 Chambre de combustion pour un ensemble turbine à gaz de centrale électrique comprenant une pluralité de tuiles métalliques de protection thermique présentant une caractéristique de refroidissement d'air améliorée
PCT/IB2023/061594 WO2024105611A1 (fr) 2022-11-18 2023-11-16 Chambre de combustion pour ensemble turbine à gaz de centrale électrique comprenant une pluralité de carreaux de protection thermique métalliques ayant une caractéristique de refroidissement d'air améliorée

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP22425055.5A EP4372281A1 (fr) 2022-11-18 2022-11-18 Chambre de combustion pour un ensemble turbine à gaz de centrale électrique comprenant une pluralité de tuiles métalliques de protection thermique présentant une caractéristique de refroidissement d'air améliorée

Publications (1)

Publication Number Publication Date
EP4372281A1 true EP4372281A1 (fr) 2024-05-22

Family

ID=85122264

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22425055.5A Pending EP4372281A1 (fr) 2022-11-18 2022-11-18 Chambre de combustion pour un ensemble turbine à gaz de centrale électrique comprenant une pluralité de tuiles métalliques de protection thermique présentant une caractéristique de refroidissement d'air améliorée

Country Status (2)

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EP (1) EP4372281A1 (fr)
WO (1) WO2024105611A1 (fr)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5363654A (en) * 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components
US20080127652A1 (en) * 2004-12-16 2008-06-05 Heinrich Putz Heat Shield Element
US20160230994A1 (en) * 2015-02-06 2016-08-11 Rolls-Royce Plc Combustion chamber
US20170211418A1 (en) * 2016-01-25 2017-07-27 Ansaldo Energia Switzerland AG Cooled wall of a turbine component and a method for cooling this wall
EP3183497B1 (fr) * 2014-10-20 2018-07-18 Siemens Aktiengesellschaft Élément formant bouclier thermique et procédé de fabrication de celui-ci
US20180252413A1 (en) * 2017-03-01 2018-09-06 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber shingle arrangement of a gas turbine
EP3674519A1 (fr) * 2018-12-27 2020-07-01 Siemens Aktiengesellschaft Ecomposant refroidissable pour une turbomachine et procédé de fabrication associé

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5363654A (en) * 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components
US20080127652A1 (en) * 2004-12-16 2008-06-05 Heinrich Putz Heat Shield Element
EP3183497B1 (fr) * 2014-10-20 2018-07-18 Siemens Aktiengesellschaft Élément formant bouclier thermique et procédé de fabrication de celui-ci
US20160230994A1 (en) * 2015-02-06 2016-08-11 Rolls-Royce Plc Combustion chamber
US20170211418A1 (en) * 2016-01-25 2017-07-27 Ansaldo Energia Switzerland AG Cooled wall of a turbine component and a method for cooling this wall
US20180252413A1 (en) * 2017-03-01 2018-09-06 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber shingle arrangement of a gas turbine
EP3674519A1 (fr) * 2018-12-27 2020-07-01 Siemens Aktiengesellschaft Ecomposant refroidissable pour une turbomachine et procédé de fabrication associé

Also Published As

Publication number Publication date
WO2024105611A1 (fr) 2024-05-23

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