EP1528343A1 - Tuile réfractaire avec des éléments de renforcement noyés pour révêtement d'une chambre de combustion de turbines à gaz - Google Patents

Tuile réfractaire avec des éléments de renforcement noyés pour révêtement d'une chambre de combustion de turbines à gaz Download PDF

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Publication number
EP1528343A1
EP1528343A1 EP03024560A EP03024560A EP1528343A1 EP 1528343 A1 EP1528343 A1 EP 1528343A1 EP 03024560 A EP03024560 A EP 03024560A EP 03024560 A EP03024560 A EP 03024560A EP 1528343 A1 EP1528343 A1 EP 1528343A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
combustion chamber
shield element
reinforcing
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Withdrawn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
EP03024560A
Other languages
German (de)
English (en)
Inventor
Holger Grote
Wolfgang Dr. Kollenberg
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
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
Priority to EP03024560A priority Critical patent/EP1528343A1/fr
Priority to PCT/EP2004/012142 priority patent/WO2005043058A2/fr
Priority to US10/577,383 priority patent/US7805945B2/en
Priority to EP04790917A priority patent/EP1678454A2/fr
Priority to JP2006536072A priority patent/JP4499737B2/ja
Priority to CN 200480031021 priority patent/CN1871488A/zh
Publication of EP1528343A1 publication Critical patent/EP1528343A1/fr
Priority to US11/215,392 priority patent/US7540710B2/en
Priority to US12/751,194 priority patent/US8857190B2/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D1/00—Casings; Linings; Walls; Roofs
    • F27D1/0003—Linings or walls
    • F27D1/0033—Linings or walls comprising heat shields, e.g. heat shieldsd
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21B—MANUFACTURE OF IRON OR STEEL
    • C21B7/00—Blast furnaces
    • C21B7/04—Blast furnaces with special refractories
    • C21B7/06—Linings for furnaces
    • 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
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D1/00—Casings; Linings; Walls; Roofs
    • F27D1/04—Casings; Linings; Walls; Roofs characterised by the form, e.g. shape of the bricks or blocks used
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D1/00—Casings; Linings; Walls; Roofs
    • F27D1/04—Casings; Linings; Walls; Roofs characterised by the form, e.g. shape of the bricks or blocks used
    • F27D1/06—Composite bricks or blocks, e.g. panels, modules
    • F27D1/08—Bricks or blocks with internal reinforcement or metal backing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS, OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D1/00—Casings; Linings; Walls; Roofs
    • F27D1/10—Monolithic linings; Supports therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/29—Coated or structually defined flake, particle, cell, strand, strand portion, rod, filament, macroscopic fiber or mass thereof
    • Y10T428/2913—Rod, strand, filament or fiber
    • Y10T428/2933—Coated or with bond, impregnation or core
    • Y10T428/294—Coated or with bond, impregnation or core including metal or compound thereof [excluding glass, ceramic and asbestos]
    • Y10T428/2942—Plural coatings
    • Y10T428/2949—Glass, ceramic or metal oxide in coating
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/29—Coated or structually defined flake, particle, cell, strand, strand portion, rod, filament, macroscopic fiber or mass thereof
    • Y10T428/2913—Rod, strand, filament or fiber
    • Y10T428/2973—Particular cross section

Definitions

  • the invention relates to a heat shield element, in particular for the inner lining of a combustion chamber or a Oven.
  • the invention further relates to a combustion chamber with an inner lining formed of heat shield elements and a gas turbine with a combustion chamber.
  • a thermally and / or thermomechanically highly loaded Combustion chamber such as a kiln, a hot gas channel or a combustion chamber in a gas turbine in which a hot Medium is generated and / or out, is for protection against high thermal stress with a corresponding lining Mistake.
  • the lining is usually made heat-resistant material and protects a wall of the combustion chamber before direct contact with the hot medium and the associated strong thermal load.
  • US Pat. No. 4,840,131 relates to an attachment of ceramic lining elements on a wall of a furnace.
  • a rail system which is attached to the wall is.
  • the lining elements have a rectangular shape with a planar surface and consist of a heat insulating, refractory, ceramic fiber material.
  • U.S. Patent 4,835,831 also deals with application a refractory lining from a wall of a Furnace, in particular a vertically arranged wall.
  • a refractory lining from a wall of a Furnace, in particular a vertically arranged wall.
  • On the metallic wall of the furnace becomes one of glass, ceramic, or mineral fibers existing layer applied.
  • These Layer is attached by metallic clips or by adhesive attached to the wall.
  • On this layer is a wire mesh with applied honeycomb meshes. The mesh is used also securing the layer of ceramic fibers against a fall down.
  • it is fastened by means of a bolt a uniform closed surface of refractory Material applied.
  • a ceramic lining of the walls of thermally highly stressed combustion chambers for example of gas turbine combustion chambers, is described in EP 0 724 116 A2.
  • the lining consists of wall elements made of high temperature resistant structural ceramic, such. As silicon carbide (SiC) or silicon nitrite (Si 3 N 4 ).
  • the wall elements are mechanically fixed by means of a central fastening bolt to a metallic support structure (wall) of the combustion chamber.
  • a thick thermal insulation layer is provided, so that the wall element is spaced correspondingly from the wall of the combustion chamber.
  • About three times as thick in relation to the wall element insulation layer consists of ceramic fiber material, which is prefabricated in blocks. The dimensions and the external shape of the wall elements are adaptable to the geometry of the space to be lined.
  • the lining consists of heat shield elements that mechanically a metallic wall of the combustion chamber are supported.
  • the heat shield elements touch the metallic wall directly.
  • z. B. as a result of direct heat transfer from the heat shield element or by penetration of hot medium in the through formed the adjacent heat shield elements Column, is that of the wall of the combustion chamber and the heat shield element formed space with cooling or sealing air acted upon. The blocking air prevents the penetration of hot Medium up to the wall and at the same time cool the wall and the heat shield element.
  • WO 99/47874 relates to a wall segment for a combustion chamber and a combustion chamber of a gas turbine.
  • This is a Wall segment for a combustion chamber, which with a hot Fluid, e.g. As a hot gas, can be acted upon, with a metallic Support structure and one on the metallic support structure attached heat shield element specified.
  • a hot Fluid e.g. As a hot gas
  • the possible relative movements receive the heat shield element and the support structure and compensate.
  • Such relative movements can for example, in the combustion chamber of a gas turbine, in particular an annular combustion chamber, by different thermal expansion behavior the materials used and pulsations in the combustion chamber, during an irregular combustion can arise to produce the hot working medium, be caused.
  • the separating layer causes that the relatively inelastic heat shield element as a whole area on the release layer and the metallic support structure rests, since the heat shield element partially in the release layer penetrates.
  • the release layer can be so production-related Unevenness on the support structure and / or the heat shield element, locally to an unfavorable point force entry can lead, balance.
  • the invention is based on the object, a heat shield element specify that a high strength at a particular have a long life. Furthermore, a special Low-maintenance combustion chamber and a gas turbine with a be specified such combustion chamber.
  • this object is achieved according to the invention dissolved with a solidified poured one formed ceramic material body, in a number is introduced by reinforcing elements.
  • the invention is based on the consideration that a for a particularly long life designed heat shield element in particular to the extreme conditions of use should be adjusted. To make this possible and a special one high number of degrees of freedom for individual adaptation measures To provide, is moving away from the past customary production of the heat shield elements by pressing now a preparation provided by pouring. Indeed could be due to a cast ceramic heat shield a comparatively low tensile strength in particular in the longitudinal and transverse direction of the heat shield element the life be limited by the heat shield element.
  • reinforcing elements provided in the body of the heat shield element are integrated. These reinforcing elements should firmly connected to the heat shield element to the material property of the tensile strength of the reinforcing elements to transfer to the heat shield element. These Function is positioned by those within the heat shield elements Reinforced elements fulfilled by the ceramic Casting material poured into the body and characterized are firmly connected to this or with the ceramic.
  • the respective reinforcing element is advantageously formed of a ceramic material, preferably of an oxide ceramic material with an Al 2 O 3 Content of at least 60% by weight and with an SiO 2 content of at most 20% by weight. This has a comparatively high tensile strength and combines due to the similar ceramic materials in solidification with the ceramic casting material.
  • the thermal expansion of the reinforcing material is similar to the remaining ceramic material of the heat shield element, so that no adverse stresses occur in the heat shield element with temperature changes.
  • the reinforcing element may advantageously be made of ceramic fibers such as CMC materials or structural ceramic material having a pore content of at most 10%.
  • the respective reinforcing element is preferably of the type a long, round ceramic rod in the style of a Reinforcement performed.
  • a reinforcing element especially firmly integrated into a heat shield element and around the reinforcing element as stiff as possible this has expediently a number of beads and thickenings on. Over this is the reinforcing element in the surrounding Anchored ceramic material, which increases the tensile strength of Reinforcement element on the entire heat shield element transfers.
  • the reinforcing element especially at its end areas Have thickening, so that results in a bone shape.
  • this compound can also be non-positively, for example via a sintering process or a grain, be executed.
  • a reinforcing element expediently also be designed plate-shaped, in particular a parallel and spaced from the surface of the heat shield element arranged flat plate can be provided. It can each a plate on the working medium side facing be positioned during the cooler side of the heat shield element also assigned a plate for reinforcement is.
  • the plate advantageously a number of recesses.
  • the plate can in particular as a perforated plate be executed, where number, size and positioning the holes expediently depending on input purpose and material parameters are selected appropriately.
  • a reinforcing element of a heat shield element preferably a grid structure on.
  • the grid elements one with diamond-shaped or square cutouts train structured grid.
  • a reinforcing element can also be formed by a plate, the circular Has recesses that are evenly spaced from each other are positioned so that a grid-shaped structure arises.
  • a reinforcing element is suitably rod-shaped and along a peripheral edge positioned the heat shield element.
  • a reinforcing element preferably an annular closed shape and extends along the circumference of the heat shield element.
  • a heat shield element For stabilization and consolidation of the corners of a heat shield element has a reinforcing element advantageously a cruciform shape, with the ends in the region of Corners of the heat shield element are positioned.
  • a reinforcing element advantageously a cruciform shape, with the ends in the region of Corners of the heat shield element are positioned.
  • the ends of the cross-shaped reinforcing element thickened be such that the reinforcing element in the heat shield element is anchored.
  • heat shield elements are those described above Type components of the inner lining of a combustion chamber.
  • This combustion chamber is advantageously part of a Gas turbine.
  • the combustion chamber could be silo-shaped Combustion chamber or as from several smaller combustion systems
  • the composite combustion chamber is designed to be preferably formed as an annular combustion chamber.
  • the advantages achieved by the invention are in particular in the possibility of resorting to a casting process with the possible creative degrees of freedom To produce heat shield elements that are particularly high Have tensile strength.
  • the material properties the reinforcing elements in particular to transfer the tensile strength to a heat shield element.
  • the shape of a heat shield element can be flexible being held.
  • Another advantage is that through the choice of different embodiments of reinforcing elements and the positioning of these in the heat shield element an individual adaptation to the on a heat shield element acting thermal and mechanical Loads is possible. Due to the increased strength The heat shield elements also extends the life a heat shield element, since the spread of Cracks reduced and the structural integrity of the component (passive safety) is increased.
  • the advantage of a casting process is the possibility of produce more complex forms of heat shield elements. So on the one hand, the outer basic shape comparatively easily and inexpensively varied. On the other hand, it is at one Casting possible, fixtures the heat shield elements on the combustion chamber wall with pour. For example, in cast heat shield elements Grooves, holes, threads or mounting devices be poured.
  • the gas turbine 1 has a compressor 2 for Combustion air, a combustion chamber 4 and a turbine 6 for Drive of the compressor 2 and a generator, not shown or a work machine. These are the turbine 6 and the compressor 2 on a common, as a turbine rotor designated turbine shaft 8 is arranged, with the also the generator or the work machine is connected, and which is rotatably mounted about its central axis 9.
  • a turbine rotor designated turbine shaft 8 is arranged, with the also the generator or the work machine is connected, and which is rotatably mounted about its central axis 9.
  • the type of an annular combustion chamber running combustion chamber 4 is with a number of burners 10 for burning a liquid or gaseous fuel.
  • the turbine 6 has a number of with the turbine shaft. 8 connected, rotatable blades 12.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine 6 includes a number of stationary vanes 14, which is also coronal under the formation of Guide vane rows attached to an inner housing 16 of the turbine 6 are.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from the turbine. 6 flowing through the working medium M.
  • the guide vanes 14 serve however, to the flow of the working medium M between two seen in the flow direction of the working medium M. successive rows of blades or blade rings.
  • a successive pair of a wreath of Vanes 14 or a row of vanes and one Wreath of blades 12 or a blade row is also referred to as turbine stage.
  • Each vane 14 has a so-called blade root Platform 18 on, which fixes the respective vane 14 on the inner housing 16 of the turbine 6 as a wall element is arranged.
  • the platform 18 is a thermal comparatively heavily loaded component, which is the outer boundary a Schugaskanals for the turbine 6 flowing through Working medium M forms.
  • Each blade 12 is in analog Way about referred to as a blade root platform 20th attached to the turbine shaft 8.
  • each guide ring 21 on the inner housing 16 of Turbine 6 is arranged between the spaced apart platforms 18 of the vanes 14 of two adjacent rows of vanes.
  • the outer surface of each guide ring 21 is also the hot, the turbine 6 flowing through Working medium M exposed and in the radial direction from the outer end 22 of the blade opposite it 12 spaced by a gap.
  • the between adjacent Guide blade rows arranged guide rings 21st serve in particular as cover elements that the inner wall 16 or other housing-mounted components before a thermal Overuse by the turbine 6 flowing through hot Working medium M protects.
  • the combustion chamber 4 is in the embodiment, as shown in FIG represented, designed as a so-called annular combustion chamber, in the case of a plurality of circumferentially around the turbine shaft 8 around arranged burners 10 in a common Combustor chamber lead.
  • the combustion chamber 4 in her Entity as an annular structure designed around the Turbine shaft 8 is positioned around.
  • the combustion chamber 4 for a comparatively high temperature the working medium M of about 1200 ° C to 1500 ° C designed. Even with these unfavorable for the materials operating parameters to allow a comparatively long service life is the combustion chamber wall 24 on the working medium M facing side with a heat shield elements 26th provided inner lining. Due to the high temperatures inside the combustion chamber 4 is for the heat shield elements 26 provided a cooling system.
  • the heat shield elements 26 are especially for a long time Lifetime designed so as to minimize damage by the extreme influences, such as the high temperature and vibration the combustion chamber 4, occur. These exist from a formed of a cast ceramic material Base 28, integrated in the reinforcing elements 30 are. For a suitable temperature resistance of the reinforcing elements These consist of a ceramic material or composite material. The reinforcing elements 30 can do so for the influences acting on a heat shield element 26 influences be interpreted. In the figures 3 to 7 are different Embodiments of heat shield elements 26 with reinforcing elements 30 listed.
  • a heat shield element 26 is plate-shaped Reinforcement elements 30 shown, wherein in each case for the the working medium M and the cooled side facing Surface a reinforcing element 30 is provided.
  • the plate-shaped reinforcing elements 30 for a better bond with the surrounding ceramic can be provided with a grid-shaped structure or are designed as a grid, in particular as a cross grid (FIG 4a) or as a perforated grid (FIG 4b).
  • FIG. 6 shows that for a reinforcement of a heat shield element 26 along its circumference an annular Structure (FIG 6a) of the reinforcing elements 30 are used can, taking these in a particularly torsion-resistant Execution circular (FIG 6b) may be executed.
  • FIG. 7 shows a heat shield element 26 that stabilizes it acting tension of the corners of a heat shield element 26 a cross-shaped reinforcing element 30 is provided, that at its ends each thickenings for anchoring in the ceramic material 26 has.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03024560A 2003-10-27 2003-10-27 Tuile réfractaire avec des éléments de renforcement noyés pour révêtement d'une chambre de combustion de turbines à gaz Withdrawn EP1528343A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP03024560A EP1528343A1 (fr) 2003-10-27 2003-10-27 Tuile réfractaire avec des éléments de renforcement noyés pour révêtement d'une chambre de combustion de turbines à gaz
PCT/EP2004/012142 WO2005043058A2 (fr) 2003-10-27 2004-10-27 Element d'ecran thermique destine notamment a la garniture d'une paroi d'une chambre de combustion
US10/577,383 US7805945B2 (en) 2003-10-27 2004-10-27 Thermal shield, especially for lining the wall of a combustion chamber
EP04790917A EP1678454A2 (fr) 2003-10-27 2004-10-27 Tuile refractaire avec des elements de renforcement noyes pour revetement d'une chambre de combustion de turbines a gaz
JP2006536072A JP4499737B2 (ja) 2003-10-27 2004-10-27 熱シールド要素
CN 200480031021 CN1871488A (zh) 2003-10-27 2004-10-27 尤其用于砌衬燃气轮机燃烧室壁的带有埋置在内的加强元件的陶瓷热屏砖
US11/215,392 US7540710B2 (en) 2003-10-27 2005-08-30 Turbine blade for use in a gas turbine
US12/751,194 US8857190B2 (en) 2003-10-27 2010-03-31 Heat shield element, in particular for lining a combustion chamber wall

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03024560A EP1528343A1 (fr) 2003-10-27 2003-10-27 Tuile réfractaire avec des éléments de renforcement noyés pour révêtement d'une chambre de combustion de turbines à gaz

Publications (1)

Publication Number Publication Date
EP1528343A1 true EP1528343A1 (fr) 2005-05-04

Family

ID=34400464

Family Applications (2)

Application Number Title Priority Date Filing Date
EP03024560A Withdrawn EP1528343A1 (fr) 2003-10-27 2003-10-27 Tuile réfractaire avec des éléments de renforcement noyés pour révêtement d'une chambre de combustion de turbines à gaz
EP04790917A Withdrawn EP1678454A2 (fr) 2003-10-27 2004-10-27 Tuile refractaire avec des elements de renforcement noyes pour revetement d'une chambre de combustion de turbines a gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP04790917A Withdrawn EP1678454A2 (fr) 2003-10-27 2004-10-27 Tuile refractaire avec des elements de renforcement noyes pour revetement d'une chambre de combustion de turbines a gaz

Country Status (5)

Country Link
US (3) US7805945B2 (fr)
EP (2) EP1528343A1 (fr)
JP (1) JP4499737B2 (fr)
CN (1) CN1871488A (fr)
WO (1) WO2005043058A2 (fr)

Cited By (10)

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WO2007025842A1 (fr) * 2005-08-30 2007-03-08 Siemens Aktiengesellschaft Aube ou ailette de turbine utilisée, en particulier, dans une turbine à combustion
EP2012061A1 (fr) * 2007-07-05 2009-01-07 Snecma Déflecteur de fond de chambre, chambre de combustion le comportant et moteur à turbine à gaz en étant équipé
US7540710B2 (en) 2003-10-27 2009-06-02 Siemens Aktiengesellschaft Turbine blade for use in a gas turbine
US8262345B2 (en) 2009-02-06 2012-09-11 General Electric Company Ceramic matrix composite turbine engine
US8347636B2 (en) 2010-09-24 2013-01-08 General Electric Company Turbomachine including a ceramic matrix composite (CMC) bridge
US8382436B2 (en) 2009-01-06 2013-02-26 General Electric Company Non-integral turbine blade platforms and systems
LU92472B1 (en) * 2014-06-06 2015-12-07 Wurth Paul Sa Heat protection assembly for a charging installation of a metallurgical reactor
US20170146295A1 (en) * 2014-06-06 2017-05-25 Paul Wurth S.A. Charging installation of a metallurgial reactor
DE102019204544A1 (de) * 2019-04-01 2020-10-01 Siemens Aktiengesellschaft Rohrbrennkammersystem und Gasturbinenanlage mit einem solchen Rohrbrennkammersystem
AT523403B1 (de) * 2021-01-21 2021-08-15 Andritz Fbb Gmbh Abschirmschuh fuer hubbalkenoefen

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EP1645805A1 (fr) * 2004-10-11 2006-04-12 Siemens Aktiengesellschaft brûleur pour combustible fluide et procédé pour uriliser un tel brûleur
US7785076B2 (en) * 2005-08-30 2010-08-31 Siemens Energy, Inc. Refractory component with ceramic matrix composite skeleton
GB2453946B (en) * 2007-10-23 2010-07-14 Rolls Royce Plc A Wall Element for use in Combustion Apparatus
US8899470B2 (en) 2007-11-29 2014-12-02 Corning Incorporated Method for bonding refractory ceramic and metal
GB0800294D0 (en) * 2008-01-09 2008-02-20 Rolls Royce Plc Gas heater
GB0801839D0 (en) * 2008-02-01 2008-03-05 Rolls Royce Plc combustion apparatus
GB2457281B (en) * 2008-02-11 2010-09-08 Rolls Royce Plc A Combustor Wall Arrangement with Parts Joined by Mechanical Fasteners
GB2460634B (en) * 2008-06-02 2010-07-07 Rolls Royce Plc Combustion apparatus
FR2935764B1 (fr) * 2008-09-05 2014-06-13 Snecma Carter de compresseur resistant au feu de titane, compresseur haute pression comprenant un tel carter et moteur d'aeronef equipe d'un tel compresseur
US20100095680A1 (en) * 2008-10-22 2010-04-22 Honeywell International Inc. Dual wall structure for use in a combustor of a gas turbine engine
US20100095679A1 (en) * 2008-10-22 2010-04-22 Honeywell International Inc. Dual wall structure for use in a combustor of a gas turbine engine
US20140325823A1 (en) * 2011-07-22 2014-11-06 Snecma Method for assembling a titanium shell with a titanium fire resistant alloy shell
US9689265B2 (en) * 2012-04-09 2017-06-27 General Electric Company Thin-walled reinforcement lattice structure for hollow CMC buckets
US20140123679A1 (en) * 2012-11-07 2014-05-08 United Technologies Corporation Flexible heat shield for a gas turbine engine
US10036258B2 (en) 2012-12-28 2018-07-31 United Technologies Corporation Gas turbine engine component having vascular engineered lattice structure
US10018052B2 (en) 2012-12-28 2018-07-10 United Technologies Corporation Gas turbine engine component having engineered vascular structure
JP6059042B2 (ja) * 2013-02-28 2017-01-11 東京窯業株式会社 マンホール
US9651258B2 (en) 2013-03-15 2017-05-16 Rolls-Royce Corporation Shell and tiled liner arrangement for a combustor
EP3042060B1 (fr) 2013-09-04 2018-08-15 United Technologies Corporation Moteur de turbine à gaz comprenant une chambre de combustion munie d'un écran thermique
WO2015036430A1 (fr) * 2013-09-11 2015-03-19 Siemens Aktiengesellschaft Bouclier thermique céramique cunéiforme d'une chambre de combustion de turbine à gaz
WO2015070413A1 (fr) * 2013-11-14 2015-05-21 深圳智慧能源技术有限公司 Pièce de bouclier thermique en céramique et structure résistant à la chaleur
US9664389B2 (en) 2013-12-12 2017-05-30 United Technologies Corporation Attachment assembly for protective panel
US10094287B2 (en) 2015-02-10 2018-10-09 United Technologies Corporation Gas turbine engine component with vascular cooling scheme
CN106247399B (zh) * 2015-06-08 2020-01-31 A.S.En.安萨尔多开发能源有限责任公司 用于燃气轮机的燃烧室的具有较薄的厚度的绝热陶瓷砖瓦
DE102015220321A1 (de) * 2015-10-19 2017-04-20 Robert Bosch Gmbh Pumpengehäuse mit Bewehrung
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US7540710B2 (en) 2009-06-02
WO2005043058A3 (fr) 2005-08-11
US20060039793A1 (en) 2006-02-23
CN1871488A (zh) 2006-11-29
JP4499737B2 (ja) 2010-07-07
WO2005043058A2 (fr) 2005-05-12
US8857190B2 (en) 2014-10-14
US7805945B2 (en) 2010-10-05
JP2007510121A (ja) 2007-04-19
US20070028592A1 (en) 2007-02-08
EP1678454A2 (fr) 2006-07-12

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