EP3132201A1 - Élément de bouclier thermique pourvu d'un revêtement latéral à refroidissement par impact sur des surfaces dégagées - Google Patents

Élément de bouclier thermique pourvu d'un revêtement latéral à refroidissement par impact sur des surfaces dégagées

Info

Publication number
EP3132201A1
EP3132201A1 EP15750951.4A EP15750951A EP3132201A1 EP 3132201 A1 EP3132201 A1 EP 3132201A1 EP 15750951 A EP15750951 A EP 15750951A EP 3132201 A1 EP3132201 A1 EP 3132201A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
shield element
hot
cooling air
edge
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
EP15750951.4A
Other languages
German (de)
English (en)
Other versions
EP3132201B1 (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

Links

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 composed of heat shield elements heat shield assembly.
  • 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 (Metalic Heat Shields).
  • the heat shield elements have a planar shape with a hot side facing the combustion chamber and an opposite cold side and peripheral edges, with a plurality of heat shield elements arranged next to one another forming a heat shield.
  • the heat shield elements have a planar shape with a hot side facing the combustion chamber and an opposite cold side and peripheral edges, with a plurality of heat shield elements arranged next to one another forming a heat shield.
  • Gas turbine in particular local temperature peaks, lead to premature wear, for example, a spalling of a coating with insufficient cooling of the components.
  • Higher gas turbine stages which work at higher and higher temperatures, increase this effect, so that the wear mechanisms are further enhanced.
  • One measure to extend the life of the heat shields is the use of cooling air. This is introduced in particular to prevent the penetration of hot combustion gases into the side gap.
  • the cooling air supply is not always optimal. In some areas cooling is not sufficient, in other areas cooling air is wasted, which should also be avoided.
  • the page gaps between two adjacent heat shield elements are often poorly cooled or poorly blocked against ingress of hot gas.
  • WO 2004/106809 AI an embodiment ei ⁇ ner combustion chamber with Hitzschildianan known, which are acted upon on the back with a cooling air, wherein the heat ⁇ shield elements - as usual - spaced angeord ⁇ net are net.
  • a ceramic coating is provided on the actual 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 on ⁇ .
  • Another object of the invention is to provide a drive for producing such a heat shield element to ⁇ give.
  • 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 can be acted upon with a hot medium hot side and a hot side opposite to the cold side and an adjoining the hot side and the cold side, the peripheral edge to have. This extends in the genus ⁇ proper heat shields from the hot side to the cold side on the level addition.
  • 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.
  • the heat shield elements an improved air flow into the Be ⁇ tenspalt is achieved by the cooling air openings of a edge distance Sectionally offset from the cooling air openings of wholie ⁇ ing edge portion are arranged.
  • the first cooling air hole of the right opposite edge portion at a distance of approximately 0.5 x x or an Ab ⁇ was of about 1.5 x x from the end of the edge portion, the following case ⁇ game from the top Edge portion to arrange, with the following cooling air openings would also be arranged at a distance of approximately X to each other.
  • the opposite edge sections are provided on the outer sides with a thermal barrier coating.
  • the thermal barrier coating is carried out is initially un ⁇ significant.
  • 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 provides for carrying out a heat shield element to ⁇ minimum coated faces.
  • the thermal barrier coating insulates the underlying areas from the high combustion temperatures and ensures that the carrier germaterialtemperatur remains in a non-critical range.
  • the sole coating the side surfaces of the heat shield elements reduces the heat transfer and thus the heat input into the heat shield element in the first place, it does not protect against a hot gas feed into the gap Zvi ⁇ rule two adjacent heat shield elements.
  • the known cooling air openings are maintained in order to effectively block the gap against hot gas intake.
  • 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 areas are areas which are not coated, but rather the free ⁇ surfaces are formed directly from the carrier material.
  • the open spaces are to be arranged in alternation with the cooling air openings at the opposite edge portions.
  • 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. It is furthermore particularly advantageous if the
  • Open spaces are positioned so that impact cooling jets from adjacent heat shield elements impinge exactly on these open spaces. A flaking off of the coating by a baffle cooling jet is thus avoided.
  • a viersvol ⁇ les blocking the gap and effective cooling of the Be ⁇ tenrow 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.
  • they can be adapted in height to the subsequently applied thermal barrier coating, so that the advantageous heat shield element is a surface of thermal barrier coating and open spaces that is flat on the outer sides of the opposite edge sections. Basically, it does not matter from which carrier material the heat shield element is made.
  • use of the first or the second embodiment according to the invention or an embodiment which is advantageous for this purpose is again particularly advantageous when a metallic carrier material is selected.
  • a first heat shield arrangement according to the invention is formed in their adjacent arrangement. It is particularly advantageous if the side gap the cooling air holes of an edge portion of a heat shield element ei ⁇ ner free surface of the adjacent the side gap edge portion of the subsequent heat shield element opposite. In this arrangement, it is ensured that the particular advantages of the heat shield elements according to the invention come into play.
  • Analogously to this invention allows a second heat shield arrangement, the positioning of the cooling air holes in an edge portion on the side gap offset from the cooling air ⁇ holes in an adjacent edge portion of the following heat shield element.
  • the respective heat shield element ment different opposite edge portions on ⁇ has.
  • first and second heat shield element used in which the polyvinyl sition of the cooling air holes in the opposite edge portions is different such that when one alternate ⁇ the arrangement of the first heat shield member and the second heat shield element in turn, an offset sequence of cooling air openings ⁇ the two adjacent edge portions of the consecu- following heat shield elements (here first and second heat shield element alternating) an offsetde Kunststoffströ ⁇ mung possible.
  • the generic shape of the first and the second heat shield element which differs from one another, in this case corresponds in turn to the above-mentioned generic shape of the first or the second embodiment of the heat shield elements according to the invention.
  • both the first heat shield member and the second heat shield element at the opposite side edges alternately cooling air intakes and open spaces, whereby the positions thereof are at Betrach- the individual heat shield elements tung in principlelie ⁇ constricting edge portions of the same, but from the first heat shield member for second heat shield element different ⁇ that, ie the position of the cooling air opening and the free surface is reversed.
  • the carrier element formed from the support member during casting of the heat shield element at least one edge portion on the outside Erhebun ⁇ gen are provided in the manufacture of the carrier element formed from the support member during casting of the heat shield element at least one edge portion on the outside Erhebun ⁇ gen.
  • Their height is advantageously to be determined in such a way that after a coating applied after at least the outside of the opposite edge sections coating on the outside, after coating a flat surface formed 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 as well as the heat shield arrangements according to the invention make possible a technically simple, uncomplicated and cost-effective solution for preventing corner overheating and has no negative influence 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 un changed ⁇ .
  • Figure 2 shows the gap between two heat shield elements of a
  • Figure 3 open spaces of a heat shield element as a small
  • FIG. 4 shows a planar side surface of the heat shield element
  • FIG. 5 shows a second heat shield element analogous to the Ausu ⁇ tion of Fig. 1 and
  • FIG. 1 shows schematically and by way of example a first embodiment
  • the heat shield element 1 is substantially metal ⁇ lisch, 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. On the hot side and the cold side 2 3 narrows the orbit ⁇ , above the plane of the cold side 3 extending beyond the edge 4 having an inner 5 and an outer side 6 and a plurality of edge portions 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 thede Kunststofföff ⁇ voltages 8a, 8c is selected so that the cooling air openings 8a of a Edge section 7a offset to cooling air openings 8c of a ge ⁇ 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 heat-insulating layer 9 is at least there niebro ⁇ Chen and forms open areas 10a where the opposite edge portion 7a, 7c, the cooling air openings 8a, 8c are arranged.
  • Figure 2 shows a section of a first Hitzeschildanord ⁇ tion 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 or 22 open spaces
  • Figure 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 coating, ie after the application of the thermal barrier coating 9, a flat surface is formed, as shown in Figure 4.
  • This shape applies to the first and second heat shield elements 22, 23 of the alternatively ⁇ ven heat shield assembly 21.
  • a second heat shield member 23 is skiz ⁇ sheet, which up to the position of cooling air holes corresponding to the 27 and open areas 29 with the heat shield element 1 first heat shield arrangement as well as the first heat shield Shield element 22 of the underlying for this embodiment second heat shield assembly 21 - see also Fig. 6 - is.
  • first heat shield element 22 and also in the second heat shield element 23 shown here lie ⁇ gene, in contrast to the heat shield element 1 of FIG. 1, the cooling air holes 25 and the open spaces 29 at the opposite edge portions 25 at the same place.

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)

Abstract

L'invention concerne un élément de bouclier thermique (1), ainsi qu'un ensemble de bouclier thermique (11) servant à habiller une paroi de chambre de combustion. L'élément de bouclier thermique (1) comporte un côté chaud (2) pouvant être soumis à l'action d'un milieu chaud et un côté froid (3) faisant face au côté chaud (2), et un bord (4) périphérique adjacent au côté chaud (2) et au côté froid (3). Le bord (4) s'étend au-delà du plan du côté froid (3) et comporte au moins par endroits une multitude d'ouvertures d'air froid (8a, 8c). Les ouvertures d'air froid (8a) d'une section de bord (7a) d'un élément de bouclier thermique (1) sont disposées de manière décalée par rapport aux ouvertures d'air froid (8c) dans la section de bord (7c) de l'élément de bouclier thermique (1) adjacent. L'invention concerne en outre un procédé servant à fabriquer un élément de bouclier thermique (1).
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 true EP3132201A1 (fr) 2017-02-22
EP3132201B1 EP3132201B1 (fr) 2018-01-03

Family

ID=53879470

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

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US8118546B2 (en) * 2008-08-20 2012-02-21 Siemens Energy, Inc. Grid ceramic matrix composite structure for gas turbine shroud ring segment
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
EP3132201B1 (fr) 2018-01-03
WO2016016280A1 (fr) 2016-02-04
DE102014214981B3 (de) 2015-12-24
CN107003001A (zh) 2017-08-01

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