EP1741981A1 - Bouclier thermique en céramique et réacteur à gaz hautes températures recouvert d'un tel bouclier - Google Patents

Bouclier thermique en céramique et réacteur à gaz hautes températures recouvert d'un tel bouclier Download PDF

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Publication number
EP1741981A1
EP1741981A1 EP05014474A EP05014474A EP1741981A1 EP 1741981 A1 EP1741981 A1 EP 1741981A1 EP 05014474 A EP05014474 A EP 05014474A EP 05014474 A EP05014474 A EP 05014474A EP 1741981 A1 EP1741981 A1 EP 1741981A1
Authority
EP
European Patent Office
Prior art keywords
ceramic
heat shield
support structure
shield element
elements
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.)
Withdrawn
Application number
EP05014474A
Other languages
German (de)
English (en)
Inventor
Holger Grote
Andreas Heilos
Marc Tertilt
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP05014474A priority Critical patent/EP1741981A1/fr
Publication of EP1741981A1 publication Critical patent/EP1741981A1/fr
Withdrawn legal-status Critical Current

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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
    • 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
    • F23R3/002—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
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05004—Special materials for walls or lining

Definitions

  • the present invention relates to a ceramic heat shield element for constructing a heat shield on a support structure of a hot gas-carrying high-temperature gas reactor.
  • the walls of high temperature gas reactors require suitable shielding of their support structure against attack by the hot gas. Due to their high temperature resistance, corrosion resistance and their low thermal conductivity compared to metallic materials, ceramic materials are particularly suitable for building up a heat shield shielding the support structure.
  • the possibility of thermal expansion of the ceramic heat shield must be ensured so that no component-destructive thermal stresses occur by hindering thermal expansion.
  • the possibility of temperature-dependent expansion can be ensured by the heat shield is expanded from a number of ceramic heat shield elements, wherein between adjacent heat shield elements, the thermal expansion of the elements enabling expansion gaps are kept. For safety reasons, these expansion gaps should only be designed so that they are not closed even at maximum temperature.
  • the expansion gaps in principle allow the passage of the hot gas through the heat shield in the direction of the support structure, measures must be taken to this passage to prevent.
  • the simplest and safest measure which is used in particular in gas turbine combustion chambers, is the rinsing of the expansion gaps with sealing air. In other words, compressed air is directed from the support structure in the direction of the heat shield elements, which enters the combustion chamber through the expansion gaps and thus prevents the entry of hot gas from the combustion chamber into the expansion gaps.
  • the heat shield elements are usually fixed by means of retaining clips on the support structure, which engage in peripheral surfaces of the heat shield elements which connect a combustion chamber interior facing the hot side with a support structure facing cold side of the heat shield element.
  • a heat shield is for example in EP 0 558 540 B1 described.
  • the heat shield elements are formed flat in a gas turbine combustor and disposed parallel to the support structure.
  • a temperature gradient which runs perpendicular to the surface of the support structure, only leads to comparatively low thermal stresses, as long as the ceramic heat shield element in the installed state, a prevention in the direction of the interior of the combustion chamber without obstruction is possible.
  • the retaining clips exert as possible no tensile or bending stresses on the hot ceramic heat shield elements, the retaining clips are arranged so that the introduction of the holding force in the heat shield elements in the vicinity of the corners, preferably above the support points.
  • the ceramic heat shield elements can be held in the vicinity of the corners resting on the support structure in the hot state, a plurality of arranged near the corners and in the peripheral sides of the ceramic heat shield elements engaging metallic retaining clips are used, the cooling need to one at the edges of the ceramic heat shield elements outflowing cooling air flow leads.
  • the cooling air requirement of the retaining clips therefore also leads to a Temperature gradients within the ceramic heat shield elements which are parallel to their surface.
  • the first object is achieved by a ceramic heat shield element according to claim 1, the second object by a high-temperature gas reactor according to claim 13.
  • the dependent claims obtain advantageous embodiments of the invention.
  • a ceramic heat shield element according to the invention for constructing a heat shield on a support structure of a hot gas-carrying high-temperature gas reactor, in particular a gas turbine combustor comprises a ceramic body with a hot side facing the hot gas and a cold side facing the support structure and a fixing section provided in the ceramic body.
  • the fixing section is arranged in a central region of the ceramic body at least in its cold side.
  • the cold side in the region of the fixing section has a projection with a support surface for supporting the heat shield element on the support structure.
  • the fixing section may, for example, have an opening extending from the cold side to the hot side through the ceramic body. This opening can serve approximately for receiving a screw, with which the heat shield element is screwed to the support structure.
  • the retaining clips engage in a profile of the support structure.
  • the fixing section in the ceramic body can in particular be used as a ceramic insert, for example in the form of a ceramic Sleeve, be formed, which is materially connected to the ceramic body and having a higher strength than the ceramic material of the ceramic body.
  • a ceramic insert for example in the form of a ceramic Sleeve, be formed, which is materially connected to the ceramic body and having a higher strength than the ceramic material of the ceramic body.
  • the increased strength of the ceramic insert can ensure that the ceramic heat shield member is not damaged in the fixing portion even if stress due to fixation occurs due to heat expansion of the ceramic heat shield member in the fixing portion.
  • the ceramic insert has a strength of at least 100 MPa both at room temperature and at 1000 ° C.
  • the ceramic insert has a compressive strength of at least 150 MPa.
  • Ceramic materials which comprise at least 80% by weight Al 2 O 3 and at most 20% by weight SiO 2 and which have a porosity of at most 5% are particularly suitable as ceramic material for ceramic use. But also other ceramic materials with higher strength than the ceramic material of the ceramic body are basically. By way of example, zirconium oxide (ZrO 2 ), silicon carbide (SiC) and spinel (MgAl 2 O 4 ) are mentioned here as possible materials.
  • the ceramic insert can be poured during the casting of the ceramic body. This allows a comparatively simple production of a ceramic insert provided with a ceramic insert.
  • a high-temperature gas reactor according to the invention which may be designed, for example, as a gas turbine combustor and in particular as an annular combustor of a gas turbine plant, comprises a support structure and a heat shield constructed from a number of heat shield elements according to the invention, the heat shield elements each being provided by means of a heat shield are fixed to the support structure cooperating with the fixing portion fixing.
  • the replacement of a heat shield element is simplified compared to high-temperature gas reactors with conventional ceramic heat shields, since each heat shield element can be removed individually.
  • the cooling air requirement can be reduced because the fixing now no longer protrude into the Dehnspalte between adjacent heat shield elements and therefore are no longer exposed to a direct hot gas attack. It is therefore sufficient if the fixing elements are cooled with cooling air from the inside.
  • the heat shield elements are in direct or indirect contact with the support structure only in the fixing section.
  • the shape of the ceramic body of the heat shield elements is adapted to the support structure of the high-temperature gas reactor that both in the stationary operation of the reactor and in the transient operation of the reactor, ie the transition between two states, for example when starting or stopping or when changing the load , Always a gap between the cold side of the ceramic body limiting edges and corners and the support structure remains. In this way it can be ensured that no load is exerted on the corners and edges during operation of the high-temperature gas reactor, which would lead to mechanical stresses in the heat shield element.
  • An existing in the region of the fixing section support surface of the heat shield element for resting on the support structure may also allow a largely free thermal movement of the heat shield element.
  • the heat shield elements with the interposition of spring assemblies in particular plate spring packages, can be fixed to the support structure.
  • the spring packs then form a support surface for supporting the heat shield elements on the support structure.
  • the fixation by means of the fixing then only needs to go so far that the spring force of the spring assemblies ensures a secure fit of the heat shield element, however, in a heating of the heat shield element enough space for expansion against the spring force of the spring assemblies is possible.
  • This type of fixation also provides an improved tolerance, if it comes to unwanted support on the support structure in the edge or corner areas of the heat shield elements.
  • metallic or ceramic fixing elements for example metallic or ceramic screws, come into consideration as fixing elements.
  • the heat shield elements according to the invention can be secured by a positive connection against rotation relative to the support structure.
  • the peripheral sides of the heat shield elements can be designed such that an overlap of the peripheral sides is possible when the heat shield elements are installed in the heat shield.
  • the peripheral sides may have steps, with opposing sides each having a mutually complementary step.
  • maintenance-related downtimes of high-temperature gas reactors can be reduced due to the possibility of individual replacement of individual heat shield elements without having to remove and install adjacent heat shield elements.
  • FIG. 1 shows a perspective view of a ceramic heat shield element according to the invention.
  • the ceramic heat shield element 1 is composed of a ceramic body 3, which has a hot side facing a hot gas 5, a cold side 7 facing a support structure, and four peripheral sides 9 connecting the hot side 5 to the cold side 7.
  • a ceramic sleeve 13 is arranged as a ceramic element, which has an increased strength compared to the ceramic material of the ceramic body 3 both at room temperature and at 1000 ° C. At both temperatures its strength is at least 1000MPa. In addition, its pressure resistance at room temperature is at least 150 MPa.
  • the ceramic sleeve 13 is made of a material containing at least 80% by weight of alumina (Al 2 O 3 ) and at most 20% by weight of silica (SiO 2 ).
  • the ceramic material of the ceramic sleeve 13 has a porosity of at most 5%.
  • the ceramic sleeve 13 may, for example, be made of zirconium oxide (ZrO 2 ), silicon carbide (SiC) or spinel (MgAl 2 O 4 ) comprising material. Also dopings of the material of the ceramic sleeve are possible to adjust its properties targeted.
  • the material of the ceramic sleeve 13 is selected in the exemplary embodiment in particular such that it has the same or a very similar coefficient of thermal expansion as the ceramic material of the ceramic body 3. As a result, stresses in the boundary region between the ceramic sleeve 13 and the ceramic body 3 due to different thermal expansion can be avoided.
  • the ceramic heat shield element 1 is formed as a molded casting.
  • the ceramic sleeve 13 is poured during the casting process in the ceramic body, so that a material-fit connection between the ceramic body 3 and ceramic sleeve 13 is formed.
  • An alternative possibility for attaching the ceramic sleeve 13 is to glue them by means of a high temperature resistant ceramic adhesive in a ceramic body 3 of the ceramic heat shield element 1 existing recording.
  • the ceramic sleeve 13 surrounds an opening 15 extending through ceramic bodies 3 from the hot side 5 to the cold side 7, which opening is designed to receive a ceramic screw 17 which fixes the heat shield element 1 to a support structure 50 and serves as a fixing element.
  • the fixation of the heat shield element 1 on a support structure 50 is shown in FIG. 2 in a sectional side view of the heat shield element and the support structure.
  • the ceramic screw 17 may alternatively find a metal screw use, which is preferably made of high temperature resistant material and may also be optionally provided with a heat-insulating coating.
  • the ceramic screw 17 is guided through the opening 15 of the ceramic sleeve 13 and screwed into a threaded bore 52 of the support structure.
  • the support structure with a bore extending through the entire support structure and to provide the ceramic screw 17 with a length which allows it to extend through the opening 15 and the threaded bore to such an extent that beyond the bores a mother can be screwed on her.
  • a threaded pin fastened to the supporting structure, which can extend through the opening 15 of a heat shield element 1 arranged on the supporting structure, so that a nut can be screwed onto the threaded pin from the combustion chamber interior.
  • a plate spring package 54 is arranged, via which the heat shield element 1 is indirectly in contact with the support structure 50.
  • the plate springs of the disc spring assembly 54 are slightly compressed, so that the heat shield element 1 is securely fixed in the direction of the support structure 50.
  • This first increases the elasticity of the screw connection with the material-typically comparatively stiff Schaub connection.
  • the plate springs of the plate spring package 54 can be further compressed. They therefore oppose the thermal expansion of the ceramic heat shield element 1 and the ceramic sleeve 13 only a relatively low resistance.
  • the plate spring package 54 can serve as a spacer between the ceramic heat shield element 1 and the support structure 50, which ensures that there is sufficient space between them for the flow of cooling air.
  • the cooling air is supplied via arranged in the support structure 50 cooling air channels 56 and blown through cooling air openings 58 in the direction of the cold side 7 of the heat shield element 1.
  • the blown-out cooling air flows along the cold side of the heat shield element 1 in the direction of expansion gaps 60 present between the heat shield elements.
  • a convective cooling of the heat shield elements flows around.
  • the cooling air passes through the expansion gaps 60 into the interior of the combustion chamber and thus blocks the expansion gaps 60 against the entry of hot gas from the combustion chamber.
  • the heat shield elements according to the invention can be used, in particular, to construct a surface-covering heat shield for a high-temperature gas reactor, such as a gas turbine combustion chamber.
  • a number of ceramic heat shield elements 1 are fixed over the entire surface of the support structure of the combustion chamber, as shown in Figure 3. Between adjacent heat shield elements 1 are doing Dehnspalte 60 left to allow thermal expansion of the heat shield elements 1 parallel to the support structure without obstruction.
  • the removal of a ceramic heat shield element 1 according to the invention from a heat shield can be carried out in a simple manner such that the ceramic screw 17 is released from the combustion chamber interior and the heat shield element 1 is subsequently removed.
  • the installation of the heat shield element 1 can be done in an analogous manner by inserting the heat shield element and then screwing to the support structure.
  • FIG. 4 An alternative embodiment of the heat shield element is shown in Fig. 4.
  • the figure shows a section of the wall of a gas turbine combustor with a support structure 50 and a heat shield attached thereto, which is constructed from a number of inventive heat shield elements 100.
  • the screws which fix the heat shield elements to the support structure 50 and the associated threads in the support structure 50 are not shown.
  • the ceramic heat shield elements 100 have a ceramic body 103 with a ceramic sleeve 113 arranged in its central region 111.
  • the peripheral sides 90, 91 of the ceramic body 103 are formed in such a stepped manner that mutually opposite circumferential sides 90, 91 are complementary to each other. In this way, an overlap occurs in the heat shield in the region of the gap between two adjacent heat shield elements 100, which leads to a reduced need for blocking air.
  • the ceramic heat shield elements 100 each have on their cold side a projection 112 surrounding the ceramic sleeve 113.
  • the underside 114 of the projection 112 forms a support with which the ceramic heat shield element 100 rests on the support structure 50. Since the force fixing the heat shield element 100 to the support structure 50 is transmitted centrally to the support structure via the projection 112 and the support 114, bends in the ceramic heat shield element 100 can be reliably avoided.

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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)
EP05014474A 2005-07-04 2005-07-04 Bouclier thermique en céramique et réacteur à gaz hautes températures recouvert d'un tel bouclier Withdrawn EP1741981A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05014474A EP1741981A1 (fr) 2005-07-04 2005-07-04 Bouclier thermique en céramique et réacteur à gaz hautes températures recouvert d'un tel bouclier

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05014474A EP1741981A1 (fr) 2005-07-04 2005-07-04 Bouclier thermique en céramique et réacteur à gaz hautes températures recouvert d'un tel bouclier

Publications (1)

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EP1741981A1 true EP1741981A1 (fr) 2007-01-10

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2261564A1 (fr) * 2009-06-09 2010-12-15 Siemens Aktiengesellschaft Agencement d'élément d'un bouclier thermique doté d'un moyen de guidance de vis et procédé de montage d'un élément d'un bouclier thermique
EP2270395A1 (fr) * 2009-06-09 2011-01-05 Siemens Aktiengesellschaft Agencement d'élément de bouclier thermique et procédé de montage d'un élément de bouclier thermique
ITMI20092346A1 (it) * 2009-12-30 2011-06-30 Ansaldo Energia Spa Metodo di manutenzione di una camera di combustione di un impianto a turbina a gas e telaio di montaggio di una piastrella di una camera di combustione
US8113004B2 (en) 2007-10-23 2012-02-14 Rolls-Royce, Plc Wall element for use in combustion apparatus
AT12612U1 (de) * 2011-07-01 2012-08-15 Lasco Heutechnik Gmbh Brennkammer für eine mobile festbrennstofffeuerungsanlage
US8256223B2 (en) 2007-10-16 2012-09-04 United Technologies Corporation Ceramic combustor liner panel for a gas turbine engine
EP2522907A1 (fr) * 2011-05-12 2012-11-14 Siemens Aktiengesellschaft Agencement de bouclier thermique
US8313288B2 (en) 2007-09-06 2012-11-20 United Technologies Corporation Mechanical attachment of ceramic or metallic foam materials
DE102012022199A1 (de) * 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine
US8833084B2 (en) 2009-08-05 2014-09-16 Rolls-Royce Plc Combustor tile mounting arrangement
WO2015036430A1 (fr) * 2013-09-11 2015-03-19 Siemens Aktiengesellschaft Bouclier thermique céramique cunéiforme d'une chambre de combustion de turbine à gaz
EP3139092A1 (fr) * 2015-09-02 2017-03-08 General Electric Company Ensemble chambre de combustion pour une turbomachine
US9643712B1 (en) 2015-11-03 2017-05-09 Northrop Grumman Systems Corporation Thermal protection system and method
US9970660B2 (en) 2014-07-25 2018-05-15 Rolls-Royce Plc Liner element for a combustor
US10168051B2 (en) 2015-09-02 2019-01-01 General Electric Company Combustor assembly for a turbine engine
KR20200020963A (ko) * 2017-07-21 2020-02-26 지멘스 악티엔게젤샤프트 가스 터빈의 성능을 개선하기 위한 방법
US10773817B1 (en) 2018-03-08 2020-09-15 Northrop Grumman Systems Corporation Bi-directional flow ram air system for an aircraft
US11402097B2 (en) 2018-01-03 2022-08-02 General Electric Company Combustor assembly for a turbine engine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5083424A (en) * 1988-06-13 1992-01-28 Siemens Aktiengesellschaft Heat shield configuration with low coolant consumption
EP0706009A2 (fr) * 1994-10-07 1996-04-10 Solar Turbines Incorporated Tuile céramique avec bord bisauté pour chambre de combustion
US5957067A (en) * 1997-07-28 1999-09-28 Abb Research Ltd. Ceramic liner
US6145452A (en) * 1997-07-28 2000-11-14 Abb Research Ltd. Ceramic lining
US6267066B1 (en) * 2000-03-15 2001-07-31 Saint-Gobain Industrial Ceramics Refractory tile system for boiler tube/heat exchanger

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5083424A (en) * 1988-06-13 1992-01-28 Siemens Aktiengesellschaft Heat shield configuration with low coolant consumption
EP0706009A2 (fr) * 1994-10-07 1996-04-10 Solar Turbines Incorporated Tuile céramique avec bord bisauté pour chambre de combustion
US5957067A (en) * 1997-07-28 1999-09-28 Abb Research Ltd. Ceramic liner
US6145452A (en) * 1997-07-28 2000-11-14 Abb Research Ltd. Ceramic lining
US6267066B1 (en) * 2000-03-15 2001-07-31 Saint-Gobain Industrial Ceramics Refractory tile system for boiler tube/heat exchanger

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8313288B2 (en) 2007-09-06 2012-11-20 United Technologies Corporation Mechanical attachment of ceramic or metallic foam materials
US8505306B2 (en) 2007-10-16 2013-08-13 United Technologies Corporation Ceramic combustor liner panel for a gas turbine engine
US8256223B2 (en) 2007-10-16 2012-09-04 United Technologies Corporation Ceramic combustor liner panel for a gas turbine engine
US8113004B2 (en) 2007-10-23 2012-02-14 Rolls-Royce, Plc Wall element for use in combustion apparatus
CN102460022A (zh) * 2009-06-09 2012-05-16 西门子公司 带有螺栓穿引器件的热屏元件装置和安装热屏元件的方法
EP2270395A1 (fr) * 2009-06-09 2011-01-05 Siemens Aktiengesellschaft Agencement d'élément de bouclier thermique et procédé de montage d'un élément de bouclier thermique
WO2010142510A1 (fr) * 2009-06-09 2010-12-16 Siemens Aktiengesellschaft Agencement d'éléments de protection thermique avec un élément permettant d'engager une vis et procédé de montage d'un élément de protection thermique
EP2261564A1 (fr) * 2009-06-09 2010-12-15 Siemens Aktiengesellschaft Agencement d'élément d'un bouclier thermique doté d'un moyen de guidance de vis et procédé de montage d'un élément d'un bouclier thermique
CN102460022B (zh) * 2009-06-09 2015-05-06 西门子公司 带有螺栓穿引器件的热屏元件装置和安装热屏元件的方法
US8800292B2 (en) 2009-06-09 2014-08-12 Siemens Aktiengesellschaft Heat shield element arrangement and method for installing a heat shield element
RU2528217C2 (ru) * 2009-06-09 2014-09-10 Сименс Акциенгезелльшафт Система элементов теплозащитного экрана и способ монтажа элемента теплозащитного экрана
US8833084B2 (en) 2009-08-05 2014-09-16 Rolls-Royce Plc Combustor tile mounting arrangement
EP2341287A1 (fr) * 2009-12-30 2011-07-06 Ansaldo Energia S.p.A. Méthode de maintenance d'une chambre de combustion d'une centrale de turbine à gaz et structure de montage pour un carreau d'une chambre de combustion
ITMI20092346A1 (it) * 2009-12-30 2011-06-30 Ansaldo Energia Spa Metodo di manutenzione di una camera di combustione di un impianto a turbina a gas e telaio di montaggio di una piastrella di una camera di combustione
EP2522907A1 (fr) * 2011-05-12 2012-11-14 Siemens Aktiengesellschaft Agencement de bouclier thermique
WO2012152530A1 (fr) * 2011-05-12 2012-11-15 Siemens Aktiengesellschaft Ensemble de boucliers thermiques
AT12612U1 (de) * 2011-07-01 2012-08-15 Lasco Heutechnik Gmbh Brennkammer für eine mobile festbrennstofffeuerungsanlage
DE102012022199A1 (de) * 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine
US9683743B2 (en) 2012-11-13 2017-06-20 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber tile of a gas turbine
CN105531545A (zh) * 2013-09-11 2016-04-27 西门子股份公司 燃气轮机燃烧室的楔形陶瓷热屏
WO2015036430A1 (fr) * 2013-09-11 2015-03-19 Siemens Aktiengesellschaft Bouclier thermique céramique cunéiforme d'une chambre de combustion de turbine à gaz
US10408451B2 (en) 2013-09-11 2019-09-10 Siemens Aktiengesellschaft Wedge-shaped ceramic heat shield of a gas turbine combustion chamber
CN105531545B (zh) * 2013-09-11 2017-09-22 西门子股份公司 燃气轮机燃烧室的楔形陶瓷热屏
US9970660B2 (en) 2014-07-25 2018-05-15 Rolls-Royce Plc Liner element for a combustor
EP3139092A1 (fr) * 2015-09-02 2017-03-08 General Electric Company Ensemble chambre de combustion pour une turbomachine
US9976746B2 (en) 2015-09-02 2018-05-22 General Electric Company Combustor assembly for a turbine engine
US10168051B2 (en) 2015-09-02 2019-01-01 General Electric Company Combustor assembly for a turbine engine
US9643712B1 (en) 2015-11-03 2017-05-09 Northrop Grumman Systems Corporation Thermal protection system and method
KR20200020963A (ko) * 2017-07-21 2020-02-26 지멘스 악티엔게젤샤프트 가스 터빈의 성능을 개선하기 위한 방법
US11402097B2 (en) 2018-01-03 2022-08-02 General Electric Company Combustor assembly for a turbine engine
US10773817B1 (en) 2018-03-08 2020-09-15 Northrop Grumman Systems Corporation Bi-directional flow ram air system for an aircraft

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