EP3117147B1 - Chambre de combustion d'un ensemble turbine à gaz - Google Patents
Chambre de combustion d'un ensemble turbine à gaz Download PDFInfo
- Publication number
- EP3117147B1 EP3117147B1 EP15715825.4A EP15715825A EP3117147B1 EP 3117147 B1 EP3117147 B1 EP 3117147B1 EP 15715825 A EP15715825 A EP 15715825A EP 3117147 B1 EP3117147 B1 EP 3117147B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- tiles
- combustion chamber
- casing
- chamber according
- heat insulating
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000002485 combustion reaction Methods 0.000 title claims description 44
- 239000011810 insulating material Substances 0.000 claims description 7
- 239000011819 refractory material Substances 0.000 claims description 6
- 239000000956 alloy Substances 0.000 claims description 2
- 229910045601 alloy Inorganic materials 0.000 claims description 2
- 229910010293 ceramic material Inorganic materials 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 13
- 230000006378 damage Effects 0.000 description 6
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 4
- 239000002184 metal Substances 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 229910017052 cobalt Inorganic materials 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 206010053615 Thermal burn Diseases 0.000 description 1
- 238000003491 array Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003546 flue gas Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 230000002427 irreversible effect Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000001902 propagating effect Effects 0.000 description 1
Images
Classifications
-
- 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
- F23R3/007—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
- F23R3/60—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
- F23M2900/05004—Special materials for walls or lining
-
- 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
- F23R2900/03342—Arrangement of silo-type combustion chambers
Definitions
- the present invention relates to a combustion chamber of a gas turbine assembly.
- combustion chambers of gas turbines must be internally lined with heat shields that allow protecting the structure and the members of the machine from very high temperatures. Inside the combustion chamber, in fact, temperatures can exceed 1500-1600 °C and are therefore high enough to melt the surrounding metal structures.
- heat shields In gas turbines of plants for the production of electricity, heat shields generally include a plurality of contiguous tiles of a refractory material arranged in arrays or rows along respective circumferences, so as to form a surface as much as possible continuous.
- the tiles are fixed to a casing of the combustion chamber by respective metal supporting elements.
- the supporting elements are defined by pairs of elastic guides which extend longitudinally with respect to the casing and act in contrast with the sidewalls of the tiles.
- the latter are shaped so as to be contiguous to the sidewalls of adjacent tiles and also protect the respective supporting elements from the effects of combustion.
- the elastic guides are normally fixed permanently to the wall and the tiles are slidably inserted along the wall of the combustion chamber casing in the longitudinal direction.
- At least one row of tiles must be fixed by removable supporting elements to be tightened after the placement of the tiles themselves. For this reason, part of the removable supporting elements remains necessarily exposed to high temperatures.
- Combustion chambers are normally provided with cooling systems which, through the circulation of a stream of relatively cool air, allow limiting the temperatures of the tile supports and the damage that might result therefrom.
- the exposed portions of the supporting elements tend to deteriorate and may undergo irreversible and potentially catastrophic damage.
- extensive burns and cracks may occur which impair the functionality of the supports.
- the detachment of metal portions may occur, which may be conveyed towards the turbine by the flow of flue gas and cause the destruction of several blades.
- DE 36 25 056 A1 discloses a combustion chamber of a gas turbine assembly, comprising a casing, defining a combustion volume therein; a heat shield, which lines the inside of the casing and comprises a plurality of tiles of a refractory material; and structural elements shaped so as to define housing seats of the tiles and to withhold the tiles in the respective housing seats.
- the structural elements comprise supporting elements for a group of tiles.
- the supporting elements have respective protecting plates which delimit a respective portion of the combustion volume.
- each supporting element comprises a base, fixed to the casing, and a pair of elastic fastening elements, extending from the base opposite to each other and shaped so as to withhold portions of respective first tiles against the casing.
- the protecting plate of each supporting element is carried by at least one respective elastic fastening element and is arranged to cover the base.
- a combustion chamber of a gas turbine assembly is provided, as defined in claim 1.
- a gas turbine assembly of a plant for the production of electricity is indicated as a whole with reference numeral 1.
- the gas turbine assembly 1 comprises a compressor 2, a combustion chamber 3 and a gas turbine 5.
- a rotor 7 comprises a compressor portion 7a and turbine portion 7b.
- the combustion chamber 3 also shown in figure 2 , is of the silo type and, in one embodiment, comprises a casing 8 defined by a substantially cylindrical tower which extends about a vertical axis A and defines a combustion volume 8a therein.
- the combustion volume is superiorly delimited by a roof 8b of the casing 8 and fluidically communicates on an opposite side with the gas turbine 5.
- the combustion chamber 3 is provided with burners 9 which allow burning a mixture of air coming from compressor 2 and fuel supplied through a supply line (not shown).
- the combustion chamber 3 is also internally lined with a heat shield 10, which comprises a plurality of tiles 12 arranged in adjacent rows about axis A.
- Tiles 12a of a closing row are fixed to casing 8 by supporting elements 15, described in detail hereafter. Tiles 12 of the other rows may be fixed to casing 8 by conventional supporting elements, not shown herein for convenience.
- the closing row of tiles 12a is arranged centrally. Tiles 12a of the closing row are the last ones to be mounted after all the other tiles have been placed in their respective positions, normally by sliding them along longitudinal rails (not shown) with respect to casing 8. Conversely, tiles 12a are the first ones to be removed when part or all of the heat shield 10 needs to be removed.
- Tiles 12a of the closing row are fixed to the casing 8 each by four respective supporting elements 15, two on each sidewall, as shown in more detail in figure 3 .
- FIGS 4-7 show one of the supporting elements 15, to which reference shall be made, meaning that the others are the same.
- the supporting element 15 comprises a base 16, a pair of elastic fastening elements 17 and a protecting plate 18 which, in one embodiment, are made in one piece.
- Base 16 is tightened against casing 8 by a fixing plate 19 ( figure 3 ).
- the elastic fastening elements 17 extend in opposite directions from base 16 in a substantially symmetrical way and are shaped so as to withhold portions of respective tiles 12a against casing 8, as shown in figure 7 (where casing 8 and tiles 12a are shown with a dashed and dotted line). More precisely, the elastic fastening elements 17 are inclined by angles ⁇ substantially symmetrical with respect to base 16 and extend transversely to the sidewalls of the respective tiles 12a. Angles ⁇ are comprised between 30° and 60° and, in one embodiment, they are about 46.5°. Ends of the elastic fastening elements 17 opposite to base 16 are arranged in contrast against respective edges of tiles 12a, so as to prevent tiles 12a themselves from separating from casing 8.
- the protecting plate 18 substantially rectangular in shape, is connected to one of the elastic fastening elements 17 and is arranged to cover base 16.
- the protecting plate 18 is substantially parallel to base 16 and extends between tiles 12a supported by the supporting element 15.
- the protecting plate 18 closes the gap between tiles 12a, where the supporting element 15 is arranged ( figures 3 and 7 ), and prevents base 16 and the elastic fastening elements 17 from being directly exposed to the atmosphere present in the combustion volume 8a.
- One side of the protecting plate 18 not engaged against tiles 12a is shaped to accommodate a fastening element 20 ( figure 3 ).
- each supporting element 15 a face 18a of the protecting plate 18 oriented towards the inside of casing 8 is covered with a heat insulating layer 22 of a heat insulating material which acts as a thermal protection element for the protecting plate 18 itself.
- the heat insulating layer 22 completely covers the protecting plate 18 and slopes down to disappear on a connecting portion 24 of the supporting element 15 between the protecting plate 18 and the elastic fastening element 17 connected thereto.
- the heat insulating material is a refractory material, for example a ceramic material having a porosity value greater than 20%.
- the heat insulating material contains a MCrAlY alloy, where M can be iron, cobalt, nickel or cobalt/nickel.
- the heat insulating layer 22 has such a thickness as to prevent potentially harmful temperatures from propagating to the supporting element 15.
- the thickness of the heat insulating layer 18 is between 75 ⁇ m and 175 ⁇ m, preferably between 100 ⁇ m and 150 ⁇ m.
- annular ridge 25 axially delimits a seat 26 for housing an upper row of tiles 12b adjacent to a roof 8b of casing 8.
- the annular ridge 25, which is part of the structure of casing 8, is made of a metal material while roof 8b is lined with a refractory material.
- Tiles 12b are arranged in seat 26 and have upper edges 12c protruding towards roof 8b of casing 8, so as to cover respective portions of the annular ridge 25. Edges 12c therefore perform the function of thermal protection elements for the annular ridge 25.
- tiles 12b have a first face 12d, adjacent to casing 8, and a second face 12e, oriented towards the combustion volume 8a, inclined with respect to each other.
- tiles 12b have a first thickness S1 at edges 12c and a second thickness S2, smaller than the first thickness S1, at second edges 12f, opposite to the first edges 12c.
- the first thickness S1 is sufficient to shape tiles 12b so that edges 12c may cover the annular ridge 25.
- the second thickness at edges 12f is substantially equal to the thickness of the contiguous tiles 12.
- the surface of the heat shield 10, which delimits the combustion volume 8a, is therefore substantially free from discontinuity, without the need to increase the thickness of the other tiles 12 in order to obtain the protruding edges 12c beyond what is required by the insulation needs.
- a combustion chamber 103 of a gas turbine comprises a casing 108 which extends about an axis A' and internally delimits a combustion volume 108a.
- Casing 108 is internally lined with a heat shield 110, which comprises a plurality of tiles 112 arranged in adjacent rows about axis A'.
- the heat shield 110 has two closing rows, more precisely comprising tiles 112a adjacent to a roof 108b of casing 108 and tiles 112b contiguous to tiles 112a.
- Tiles 112a, 112b are fixed to casing 108 by means of supporting elements 15, of the type already described with reference to figure 4-7 .
- Each tile 112a, 112b has a pair of supporting elements 15 on each sidewall.
Landscapes
- 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)
Claims (12)
- Chambre de combustion d'un ensemble de turbine à gaz comprenant :un blindage (8 ; 108) définissant un volume de combustion (8a ; 108a) à l'intérieur de ce dernier ;un bouclier thermique (10 ; 110) qui recouvre l'intérieur du blindage (8 ; 108) et comprend une pluralité de carreaux (12, 12a, 12b ; 112, 112a, 112b) réalisés avec un matériau réfractaire ;des éléments structurels (15 ; 25) formés afin de définir des sièges de logement (26) des carreaux (12, 12a, 12b ; 112, 112a, 112b) et afin de retenir les carreaux (12, 12a, 12b ; 112, 112a, 112b) dans les sièges de logement (26) respectifs ;dans laquelle les éléments structurels (15; 25) comprennent des éléments de support (15) pour un groupe de premiers carreaux (12a ; 112a, 112b), ayant chacun une plaque de protection (18) qui délimite une partie respective du volume de combustion (8a ; 108a) ;dans laquelle chaque élément de support (15) comprend une base (16), fixée sur le blindage (8 ; 108) et une paire d'éléments de fixation élastiques (17), s'étendant à partir de la base (16) à l'opposé l'un de l'autre et formés afin de retenir des parties des premiers carreaux (12a ; 112a, 112b) respectifs contre le blindage (8 ; 108) ; dans laquelle la plaque de protection (18) de chaque élément de support (15) est portée par au moins un élément de fixation élastique (17) respectif et est agencée pour recouvrir la base (16) ;caractérisée par des éléments de protection thermique (22), agencés pour recouvrir des parties des éléments structurels (15; 25) orientées vers l'intérieur du blindage (8 ; 108) ; dans laquelle les éléments de protection thermique comprennent des couches thermiquement isolantes (22) réalisées à partir d'un matériau thermiquement isolant, recouvrant des faces (18a) respectives des plaques de protection (18) respectives orientées vers l'intérieur du blindage (8 ; 108).
- Chambre de combustion selon la revendication 1, dans laquelle le matériau thermiquement isolant est un matériau réfractaire.
- Chambre de combustion selon la revendication 1 ou 2, dans laquelle le matériau thermiquement isolant est un matériau en céramique avec une valeur de porosité supérieure à 20%.
- Chambre de combustion selon la revendication 1 ou 2, dans laquelle le matériau thermiquement isolant contient un alliage de MCrAlY.
- Chambre de combustion selon l'une quelconque des revendications précédentes, dans laquelle une épaisseur des couches thermiquement isolantes (22) est comprise entre 75 µm et 175 µm, de préférence entre 100 µm et 150 µm.
- Chambre de combustion selon l'une quelconque des revendications précédentes, dans laquelle la plaque de protection (18) est essentiellement parallèle à la base (16) respective dans chaque élément de support (15).
- Chambre de combustion selon l'une quelconque des revendications précédentes, dans laquelle les couches thermiquement isolantes (22) sont agencées sur des faces (18a) des plaques de protection (18) opposées aux bases (16) respectives.
- Chambre de combustion selon l'une quelconque des revendications précédentes, dans laquelle les plaques de protection (18) s'étendent entre les premiers carreaux (12a ; 112a, 112b) supportés par les éléments de support (15) respectifs.
- Chambre de combustion selon l'une quelconque des revendications précédentes, dans laquelle les éléments structurels (15; 25) comprennent une crête annulaire (25), délimitant axialement le siège de logement (26) d'un groupe de deuxièmes carreaux (12b) adjacents à un toit (8b) du blindage (8) ; et dans laquelle les éléments de protection thermique comprennent des premiers bords (12c) des deuxièmes carreaux (12b), en saillie afin de recouvrir des parties respectives de la crête annulaire (25).
- Chambre de combustion selon la revendication 9, dans laquelle les deuxièmes carreaux (12b) ont une première épaisseur (S1) au niveau des premiers bords (12c) et une seconde épaisseur (S2) inférieure à la première épaisseur (S1), au niveau des seconds bords (12f), opposés aux premiers bords (12c).
- Chambre de combustion selon la revendication 10, dans laquelle l'épaisseur des troisièmes carreaux (12) adjacents aux deuxièmes carreaux (12b) est égale à la seconde épaisseur (S2).
- Chambre de combustion selon la revendication 10 ou 11, dans laquelle chaque deuxième carreau (12) a une première face (12d) et une seconde face (12e) inclinée par rapport à la première face (12d) dans une direction allant du premier bord (12c) au second bord (12f).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ITMI20140323 | 2014-03-03 | ||
PCT/IB2015/051554 WO2015132728A1 (fr) | 2014-03-03 | 2015-03-03 | Chambre de combustion d'un ensemble turbine à gaz et élément de support pour carreaux d'isolation thermique d'une chambre de combustion d'un ensemble turbine à gaz |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3117147A1 EP3117147A1 (fr) | 2017-01-18 |
EP3117147B1 true EP3117147B1 (fr) | 2019-01-16 |
Family
ID=50877558
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15715825.4A Active EP3117147B1 (fr) | 2014-03-03 | 2015-03-03 | Chambre de combustion d'un ensemble turbine à gaz |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP3117147B1 (fr) |
CN (1) | CN106164590B (fr) |
WO (1) | WO2015132728A1 (fr) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11255547B2 (en) | 2018-10-15 | 2022-02-22 | Raytheon Technologies Corporation | Combustor liner attachment assembly for gas turbine engine |
US11293637B2 (en) * | 2018-10-15 | 2022-04-05 | Raytheon Technologies Corporation | Combustor liner attachment assembly for gas turbine engine |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3625056C2 (de) * | 1986-07-24 | 1997-05-28 | Siemens Ag | Feuerfeste Auskleidung, insbesondere für Brennkammern von Gasturbinenanlagen |
US5113660A (en) * | 1990-06-27 | 1992-05-19 | The United States Of America As Represented By The Secretary Of The Air Force | High temperature combustor liner |
DE59706557D1 (de) * | 1997-07-28 | 2002-04-11 | Alstom | Keramische Auskleidung |
DE19825546C1 (de) * | 1998-06-08 | 1999-08-26 | Didier Werke Ag | Einrichtung zum Befestigen von Auskleidungsplatten |
CN201106863Y (zh) * | 2007-09-13 | 2008-08-27 | 天津大沽化工股份有限公司 | 防炉衬脱落装置 |
CN201152541Y (zh) * | 2007-12-17 | 2008-11-19 | 张宝祯 | 多功能耐火砖的砖座 |
EP2452126B1 (fr) * | 2009-07-08 | 2016-12-14 | Berry Metal Company | Appareil pour constructions à ossature bois et en briques |
-
2015
- 2015-03-03 EP EP15715825.4A patent/EP3117147B1/fr active Active
- 2015-03-03 CN CN201580011658.5A patent/CN106164590B/zh active Active
- 2015-03-03 WO PCT/IB2015/051554 patent/WO2015132728A1/fr active Application Filing
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
CN106164590A (zh) | 2016-11-23 |
CN106164590B (zh) | 2019-11-26 |
WO2015132728A1 (fr) | 2015-09-11 |
EP3117147A1 (fr) | 2017-01-18 |
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