EP3132201B1 - Élément de bouclier thermique révêtu latéralement avec refroidissement par impact aux surfaces non-couverts - Google Patents

Élément de bouclier thermique révêtu latéralement avec refroidissement par impact aux surfaces non-couverts Download PDF

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Publication number
EP3132201B1
EP3132201B1 EP15750951.4A EP15750951A EP3132201B1 EP 3132201 B1 EP3132201 B1 EP 3132201B1 EP 15750951 A EP15750951 A EP 15750951A EP 3132201 B1 EP3132201 B1 EP 3132201B1
Authority
EP
European Patent Office
Prior art keywords
heat shield
cooling air
shield element
air openings
opposite
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.)
Not-in-force
Application number
EP15750951.4A
Other languages
German (de)
English (en)
Other versions
EP3132201A1 (fr
Inventor
Andreas Böttcher
Christopher Grandt
Andre Kluge
Tobias Krieger
Kai-Uwe Schildmacher
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Publication of EP3132201A1 publication Critical patent/EP3132201A1/fr
Application granted granted Critical
Publication of EP3132201B1 publication Critical patent/EP3132201B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—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
    • F23R3/007—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
    • 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
    • F23R2900/03042—Film 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 invention relates to a heat shield element, in particular for lining a combustion chamber wall, and a heat shield element consisting of heat shield elements.
  • the invention further relates to a method for producing a heat shield element.
  • the heat shield elements In order to protect the structure of a combustion chamber from high temperatures, it can be lined, for example, with ceramic bricks (Ceramic Heat Shields) and / or metallic bricks (Metallic Heat Shields).
  • the heat shield elements generally have a planar shape with a hot side facing the combustion chamber and an opposite cold side and peripheral edges, wherein a plurality of heat shield elements arranged next to one another form a heat shield. In this case, the heat shield elements are positioned at a distance from one another, so that in each case a side gap is formed between the edges of adjacent heat shield elements.
  • the object of the invention is therefore to provide a heat shield element and a heat shield assembly of the type mentioned above, which have a longer life, in particular an improved introduction of the cooling air in the side gap.
  • Another object of the invention is a method to specify for producing such a heat shield element.
  • the generic heat shield elements are usually used in a heat shield assembly for lining a combustion chamber of a gas turbine.
  • the heat shield elements have a hot side, which can be acted upon by a hot medium, and a cold side which is opposite to the hot side, and a peripheral edge which adjoins the hot side and the cold side. In the case of the generic heat shields, this extends from the hot side to beyond the plane of the cold side.
  • the edge raised on the cold side has an inner side and an outer side and in this case comprises a plurality of edge sections. In this case, it is not mandatory for each of the individual peripheral edge forming edge sections to project beyond the cold side starting from the hot side.
  • cooling air can thus be blown into the side gap between two heat shield elements through the cooling air openings.
  • an improved air flow into the side gap is achieved by the cooling air openings of an edge section offset from the cooling air openings of the opposite edge portion are arranged.
  • a heat shield member having a left edge portion in which the first cooling air hole at a distance X from the end of the edge portion, for example, from an upper edge portion, and the following cooling air openings each have the distance X
  • the opposite edge sections are provided on the outer sides with a thermal barrier coating. How the thermal barrier coating is carried out is irrelevant here at first.
  • At least the heat shield element in this exemplary embodiment initially consists of a carrier material, wherein at least the opposite, the cooling air openings having edge portions on the outer sides have a deviating, heat-insulating material. It can also be provided that the entire hot side and / or the entire peripheral edge are provided with the same or a similar thermal barrier coating.
  • the invention thus provides to carry out a heat shield element with at least coated side surfaces.
  • the thermal barrier coating insulates the underlying areas from the high combustion temperatures and ensures that the substrate temperature remains in a non-critical area.
  • the sole coating of the side surfaces of the heat shield elements reduces primarily the heat transfer and thus the heat input into the heat shield element, it does not protect against a hot gas inlet into the gap between two adjacent heat shield elements. For this reason, the known cooling air openings are maintained in order to effectively block the gap against hot gas intake. However, this leads to the problem that it may lead to cracks or flaking of this coating in this area due to the exiting from the cooling air openings cooling jet on a thermal barrier coating.
  • open spaces are areas that are not coated, but rather the open spaces are formed directly from the substrate.
  • the open spaces are to be arranged in alternation with the cooling air openings at the opposite edge portions.
  • the first embodiment according to the invention is combined with the second embodiment according to the invention in a particularly advantageous embodiment.
  • the heat shield element particularly advantageous at the two opposite edge portions in alternation cooling air openings and open spaces, wherein further the positions of the cooling air openings and open spaces are exchanged to each other from the one of the opposite edge portions to the other of the opposite edge portion.
  • the free surfaces are positioned so that impact cooling jets from adjacent heat shield elements impinge exactly on these free surfaces. A flaking off of the coating by an impingement cooling jet is thus avoided. Thus, an effective locking of the gap and an effective cooling of the side walls of the heat shield elements are ensured.
  • the support material has elevations in the size and the position of the desired free surfaces before applying the thermal insulation layer on the edge portions. These can be adapted in height to the subsequently applied thermal barrier coating, so that the advantageous heat shield element with a flat on the outer sides of the opposite edge portions surface of thermal insulation layer and open spaces.
  • a first heat shield arrangement according to the invention is formed in their adjacent arrangement.
  • the cooling air bores of an edge section of a heat shield element of an open space of the edge section of the following heat shield element adjacent to the side gap lie opposite one another at the side gap. In this arrangement, it is ensured that the particular advantages of the heat shield elements according to the invention come into play.
  • a second heat shield assembly allows the positioning of the cooling air holes in an edge portion at the side gap offset to the cooling air holes in an adjacent edge portion of the following heat shield element.
  • a heat shield arrangement is not provided here, that the respective heat shield element having different opposite edge portions.
  • first and second heat shield elements are used for this purpose, in which the position of the cooling air holes in the opposite edge sections differs such that, in the case of an alternating arrangement of the first heat shield element and the second heat shield element, an offset sequence of the cooling air openings again occurs the two adjacent edge portions of successive heat shield elements (here first and second heat shield element in alternation) allows an offset cooling air flow.
  • the generic shape of the first and second mutually different heat shield element in this case again corresponds to the above-mentioned generic shape of the first and the second embodiment of the invention heat shield elements.
  • both the first heat shield element and the second heat shield element alternately have cooling air openings and open spaces at the opposite side edges, the positions of which are the same when viewing the individual heat shield elements at the opposite edge sections, but differ from the first heat shield element to the second heat shield element, i. H. the position of cooling air opening and free space is reversed.
  • elevations are provided in at least one edge portion on the outside during the production of the carrier element formed from the carrier material during the casting of the heat shield element.
  • Their height is in this case advantageously dimensioned such that, after a coating applied after at least the outer side of the opposite edge sections on the outside, after coating a flat surface formed from the applied thermal barrier coating and the free surfaces formed by the surveys.
  • the side-coated heat shield element according to the invention with impingement cooling on open spaces combines several aspects and thus leads to an improved design.
  • the heat transfer and thus the heat input into the heat shield element is reduced by the side coating.
  • cooling air openings ensure a blockage of the gap between two heat shield elements. The introduction of open spaces at the points where the cooling air jet impinges, provides for cooling of the support structure of the heat shield element and at the same time for a robust design without the risk of chipping the heat protection layer or cracks at these locations.
  • the heat shield elements according to the invention and the heat shield assemblies according to the invention enable a technically simple feasible, since uncomplicated, and cost-effective solution to avoid corner overheating before and has no negative impact on the cooling air balance, ie There is no additional cooling air due to the invention.
  • the side coating in combination with open space for impingement cooling provides improved cooling and a robust design against chipping or cracks in the thermal barrier coating.
  • the modified design is service-friendly, so that the geometry of the heat shield elements can remain unchanged.
  • the FIG. 1 shows schematically and by way of example a first embodiment of a heat shield element 1 according to the invention.
  • the heat shield element 1 is essentially metallic, ie it comprises a metallic base body. It has a hot side 2 which can be acted upon by a hot medium and a cold side 3 which lies opposite the hot side 2. Adjacent to the hot side 2 and the cold side 3 is an encircling edge 4 which extends beyond the plane of the cold side 3 and has an inner 5 and an outer side 6 and a plurality of edge sections 7a, 7b, 7c and 7d.
  • cooling air openings 8a in the edge portion 7a and cooling air openings 8c in the edge portion 7c are arranged, each extending from the inner 5 to the outer side 6.
  • the arrangement of the cooling air openings 8a, 8c is selected so that cooling air openings 8a of a Edge portion 7a offset to cooling air openings 8c of an opposite edge portion 7c are arranged.
  • the outer sides 6 of at least two opposite edge sections 7a and 7c have a thermal barrier coating 9. This thermal barrier coating 9 is interrupted at least there and forms open spaces 10a, where in the opposite edge portion 7a, 7c, the cooling air openings 8a, 8c are arranged.
  • FIG. 2 shows a section of a first heat shield assembly 11 and with respect to the section corresponding to a second heat shield assembly 21 and there in particular the gap 13 between two heat shield elements 1 and 22 and 23, which are arranged side by side, that cooling air openings 8a and 26 of a heat shield element 1 and 22nd Open spaces 10c and 28 of an adjacent heat shield element 1 and 23 are opposite, which is achieved in that at the gap 13, the cooling air openings 8a, 8c and 26, 27 of the two adjacent heat shield elements 1 and 22, 23 offset from each other.
  • FIG. 3 shows a section of a heat shield element 1 after casting and before the coating of the outside 6 with a thermal barrier coating 9.
  • the outside 6 elevations 12 can be seen, the surfaces of which are the later free surfaces 10.
  • the height of the elevations 12 is ideally equal to the still applied to the surrounding surfaces thermal barrier coating 9, so that on the outside 6 after the coating, ie after the application of the thermal barrier coating 9, a flat surface is formed as in FIG. 4 is shown.
  • This shape also applies to the first and second heat shield elements 22, 23 of the alternative heat shield assembly 21.
  • FIG. 3 a second heat shield element 23 is sketched, which up to the position of the cooling air holes 27 and open spaces 29 coincident with the heat shield element 1 of the first heat shield assembly and the first heat shield element 22 lying for this embodiment, the second heat shield assembly 21 - see also Fig. 6 - is.
  • the first heat shield element 22 and also in the second heat shield element 23 shown here in contrast to the heat shield element 1 are made Fig. 1 the cooling air holes 25 and the open spaces 29 at the opposite edge portions 25 at the same place.
  • the invention provided for offset arrangement of the cooling air openings 24, 25, as in Fig. 2 sketched, is achieved in this second heat shield assembly 21 rather by different embodiments of the first heat shield element 22 and second heat shield element 23 with mutually exchanged position of cooling air holes 26, 27 and open spaces 28, 29 with alternating use of the first heat shield element 22 and the second heat shield element 23.

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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)

Claims (7)

  1. Elément (1, 22, 23) de bouclier thermique pour l'habillage d'une paroi de chambre de combustion ayant un côté (2) chaud, pouvant être soumis à un fluide chaud, et un côté (3) froid, opposé au côté (2) chaud, et ayant un bord (4), qui s'étend au-delà du plan du côté (3) froid, en faisant le tour au voisinage du côté (2) chaud et du côté (3) froid et qui a un côté (5) intérieur et un côté (6) extérieur et qui comprend plusieurs parties (7a, 7b, 7c, 7c, 24, 25) de bord, dans lequel, dans au moins deux parties (7a, 7c, 24, 25) de bord opposées l'une à l'autre, sont prévues des ouies (8a, 8c, 26, 27) pour de l'air de refroidissement, s'étendant du côté (5) intérieur au côté (6) extérieur,
    caractérisé
    en ce que l'élément (1, 22, 23) de bouclier thermique a un matériau support et au moins les côtés (6) extérieurs des parties (7a, 7c, 24, 25) de bord opposées ont une couche (9) calorifuge, qui est interrompue en alternance par les ouies (8a, 8c, 26, 27) d'air de refroidissement et qui forment des surfaces (10a, 28, 29) libres.
  2. Elément (1) de bouclier thermique suivant la revendication 1,
    caractérisé
    en ce que les ouies (8a) d'air de refroidissement d'une partie (7a) de bord sont disposées de manière décalée par rapport aux ouies (8c) d'air de refroidissement de la partie (7c) de bord opposée.
  3. Elément (1, 22, 23) de bouclier thermique suivant la revendication 1 ou 2,
    caractérisé
    en ce que le matériau support a, sur les parties (7a, 7c, 24, 25) de bord opposées, des surélévations (12) du côté (6) extérieur, qui forment les surfaces (10a, 28, 29) libres et qui sont réalisées dans une surface plane par la couche (9) calorifuge entourante.
  4. Elément (1) de bouclier thermique suivant l'une des revendications 1 à 3,
    caractérisé
    en ce que le matériau de support est métallique.
  5. Agencement (11) de bouclier thermique ayant plusieurs éléments (1, 22, 23) de bouclier thermique suivant l'une des revendications 1 à 4,
    caractérisé
    en ce que les élément (1) de bouclier thermique sont disposés les uns à côté des autres, de manière à ce que des ouies (8a, 8c) d'air de refroidissement d'un élément (1) de bouclier thermique soient opposées à des surfaces 10a, 28, 29) libres d'un élément (1) de bouclier thermique voisin.
  6. Agence de bouclier thermique suivant la revendication 5,
    caractérisé
    en ce que les ouies (26) d'air de refroidissement, dans les parties (24) de bord d'un premier élément (22) de bouclier thermique, sont disposées de manière opposée les unes aux autres et les ouies (27) d'air de refroidissement, dans les parties (25) de bord d'un deuxième élément (23) de bouclier thermique, sont disposées de manière opposée les unes aux autres, les ouies (26) d'air de refroidissement du premier élément (22) de bouclier thermique étant disposées de manière décalée par rapport aux ouies (27) d'air de refroidissement du deuxième élément (23) de bouclier thermique voisin.
  7. Procédé de production d'un élément (1, 22, 23) de bouclier thermique ayant un côté (2) chaud soumis à un fluide chaud et un côté (3) froid, opposé au côté (2) chaud, et un bord (4) s'étendant au-delà du plan du côté (3) froid faisant le tour et voisin du côté (2) chaud et du côté (3) froid, en ayant un côté (5) intérieur et un côté (6) extérieur et plusieurs parties (7a, 7b, 7c, 7c, 24, 25) de bord et comprenant une pluralité d'ouies (8a, 8c, 26, 27) d'air de refroidissement prévues dans le bord (4) et s'étendant du côté (5) intérieur au côté (6) extérieur,
    caractérisé
    en ce que, à la coulée de l'élément (1, 22, 23) de bouclier thermique, on forme, sur au moins une partie (7a, 7c, 24, 25) de bord du côté (6) extérieur, des surélévations (12), dont la hauteur est égale à celle de la couche (9) calorifuge déposée ensuite sur les surfaces entourantes, de manière à créer une surface plane du côté (6) extérieur, après le dépôt de la couche (9) calorifuge.
EP15750951.4A 2014-07-30 2015-07-29 Élément de bouclier thermique révêtu latéralement avec refroidissement par impact aux surfaces non-couverts Not-in-force EP3132201B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014214981.9A DE102014214981B3 (de) 2014-07-30 2014-07-30 Seitenbeschichtetes Hitzeschildelement mit Prallkühlung an Freiflächen
PCT/EP2015/067330 WO2016016280A1 (fr) 2014-07-30 2015-07-29 Élément de bouclier thermique pourvu d'un revêtement latéral à refroidissement par impact sur des surfaces dégagées

Publications (2)

Publication Number Publication Date
EP3132201A1 EP3132201A1 (fr) 2017-02-22
EP3132201B1 true EP3132201B1 (fr) 2018-01-03

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP15750951.4A Not-in-force EP3132201B1 (fr) 2014-07-30 2015-07-29 Élément de bouclier thermique révêtu latéralement avec refroidissement par impact aux surfaces non-couverts

Country Status (4)

Country Link
EP (1) EP3132201B1 (fr)
CN (1) CN107003001A (fr)
DE (1) DE102014214981B3 (fr)
WO (1) WO2016016280A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3252378A1 (fr) 2016-05-31 2017-12-06 Siemens Aktiengesellschaft Agencement de chambre de combustion annulaire de turbine à gaz
DE102016224632A1 (de) * 2016-12-09 2018-06-14 Rolls-Royce Deutschland Ltd & Co Kg Plattenförmiges Bauteil einer Gasturbine sowie Verfahren zu dessen Herstellung
DE102017207487A1 (de) * 2017-05-04 2018-11-08 Siemens Aktiengesellschaft Brennkammer

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US6250082B1 (en) * 1999-12-03 2001-06-26 General Electric Company Combustor rear facing step hot side contour method and apparatus
GB0117110D0 (en) * 2001-07-13 2001-09-05 Siemens Ag Coolable segment for a turbomachinery and combustion turbine
US6749396B2 (en) * 2002-06-17 2004-06-15 General Electric Company Failsafe film cooled wall
EP1482246A1 (fr) * 2003-05-30 2004-12-01 Siemens Aktiengesellschaft Chambre de combustion
DE102005046731A1 (de) * 2005-04-19 2006-11-02 Siemens Ag Hitzeschildanordnung
US7278820B2 (en) * 2005-10-04 2007-10-09 Siemens Power Generation, Inc. Ring seal system with reduced cooling requirements
US7669422B2 (en) * 2006-07-26 2010-03-02 General Electric Company Combustor liner and method of fabricating same
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US8499566B2 (en) * 2010-08-12 2013-08-06 General Electric Company Combustor liner cooling system
US8931280B2 (en) * 2011-04-26 2015-01-13 General Electric Company Fully impingement cooled venturi with inbuilt resonator for reduced dynamics and better heat transfer capabilities
CN103115381B (zh) * 2011-11-17 2015-04-01 中航商用航空发动机有限责任公司 一种火焰筒的筒壁结构
DE102012204103A1 (de) * 2012-03-15 2013-09-19 Siemens Aktiengesellschaft Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer
CN202792104U (zh) * 2012-09-10 2013-03-13 中航商用航空发动机有限责任公司 火焰筒壁板、火焰筒以及燃气轮机燃烧室

Also Published As

Publication number Publication date
CN107003001A (zh) 2017-08-01
DE102014214981B3 (de) 2015-12-24
WO2016016280A1 (fr) 2016-02-04
EP3132201A1 (fr) 2017-02-22

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