EP1817528B1 - Procédé de production d'un élément d'écran thermique - Google Patents

Procédé de production d'un élément d'écran thermique Download PDF

Info

Publication number
EP1817528B1
EP1817528B1 EP05811090.9A EP05811090A EP1817528B1 EP 1817528 B1 EP1817528 B1 EP 1817528B1 EP 05811090 A EP05811090 A EP 05811090A EP 1817528 B1 EP1817528 B1 EP 1817528B1
Authority
EP
European Patent Office
Prior art keywords
heat shield
shield element
thermal expansion
region
coefficient
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.)
Ceased
Application number
EP05811090.9A
Other languages
German (de)
English (en)
Other versions
EP1817528A1 (fr
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
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 EP05811090.9A priority Critical patent/EP1817528B1/fr
Publication of EP1817528A1 publication Critical patent/EP1817528A1/fr
Application granted granted Critical
Publication of EP1817528B1 publication Critical patent/EP1817528B1/fr
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used
    • 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

Definitions

  • the present invention relates to a heat shield element, in particular a ceramic heat shield element, a method for producing a ceramic heat shield element, a built-up of heat shield elements Heisgasausposed and provided with a Heisgasausposed combustion chamber, which may be formed in particular as a gas turbine combustor.
  • the walls of hot gas-carrying combustors, such as gas turbine plants require thermal shielding of their supporting structure against hot gas attack.
  • the thermal shielding can be realized, for example, by means of a hot gas lining upstream of the actual combustion chamber wall, for example in the form of a ceramic heat shield.
  • a ceramic heat shield Such a Heisgasausstage usually constructed of a number of metallic or ceramic heat shield elements with which the combustion chamber wall is lined flat. Ceramic materials are ideally suited for the construction of a hot gas lining compared to metallic materials because of their high temperature resistance, corrosion resistance and low thermal conductivity.
  • a ceramic heat shield is, for example, in EP 0 558 540 B1 described.
  • the US 4,485,630 A shows a burner flame tube having a flat first alloy strip having the first heat transfer coefficient C1 and a second planar alloy strip having the heat transfer coefficient C2.
  • the US 4,838,030 detects heat shields with 3 layers, a first ceramic layer, a second fibrous steel wool layer and a third metal layer.
  • the metal layer has cooling channels.
  • a heat shield element which is made of a base material mixture by pressing and subsequent sintering.
  • a heat shield element is made of a base material mixture by pressing and subsequent sintering.
  • thermal shock-resistant heat shields discloses the EP 1 142 852 A2 .
  • a fiber-reinforced composite ceramic as the base body, which is provided on the hot side with a thermally sprayed temperature-resistant layer.
  • a gradual structure in the material composition starting from the main body toward the hot side is selected.
  • the thermal mobility particular ceramic heat shields must be guaranteed as a result of temperature-dependent expansion, so that no heat shield destructive thermal stresses by obstruction of temperature-dependent strain occur.
  • expansion gaps are therefore present to the thermal expansion to enable the heat shield elements.
  • the expansion gaps are designed so that they are never completely closed even at maximum temperature of the hot gas. It must therefore be ensured that the hot gas does not reach the load-bearing wall structure of the combustion chamber via the expansion gaps. In order to block the expansion gaps against the entry of hot gas, they are often flushed with a flowing in the direction of the combustion chamber interior air flow.
  • air is used as the sealing air, which at the same time serves as cooling air for cooling retaining elements holding the heat shield elements, which leads inter alia to the occurrence of temperature gradients in the region of the edges of a heat shield element. Therefore, in particular with ceramic heat shield elements, even without the contact of adjacent heat shield elements, stresses occur on the hot side, which can lead to cracking and thus adversely affect the life of the heat shield elements.
  • metallic heat shield elements have a higher resistance to thermal fluctuations and mechanical loads than ceramic heat shield elements, however, for example in gas turbine combustion chambers, they require complex cooling of the heat shield, since they have a higher thermal conductivity than ceramic heat shield elements.
  • metallic heat shield elements are more susceptible to corrosion and, due to their lower temperature stability, can not be subjected to temperatures as high as those of ceramic heat shield elements. In order to minimize the formation of cracks, it is therefore generally endeavored to minimize the thermal load on the heat shield elements of a heat shield.
  • a heat shield element has a hot side facing a hot medium, a cold side to be turned away from the hot medium, and circumferential surfaces connecting the hot side with the cold side.
  • the hot side, the cold side and the peripheral surfaces limit the material volume of the heat shield element.
  • the advantageous heat shield element is characterized in that the volume of material comprises at least two areas of material which differ from each other in their coefficients of thermal expansion.
  • the thermal expansion of the material regions can be influenced in a targeted manner.
  • the stresses within the heat shield element can be reduced during operation of a heat shield.
  • the advantageous heat shield element is designed as a ceramic heat shield element.
  • the reduced voltage formation due to the different coefficients of thermal expansion when spatial temperature gradients occur within the ceramic heat shield element leads to a reduced tendency to crack. This reduces the risk in a ceramic heat shield of formation of long cracks, which would lead to an exchange of the heat shield element. In addition, the reduced cracking tendency leads to a longer life of the heat shield elements and thus to a reduction the replacement rates of heat shield elements in hot gas linings.
  • At least one material region with a relatively low coefficient of thermal expansion adjoins the hot side of the heat shield element, whereas at least one material region with a relatively high coefficient of thermal expansion adjoins the cold side of the heat shield element.
  • On the hot side occur at the transition from the ambient temperature (for example, when a gas turbine plant) to maximum operating temperature (for example, at full load of a gas turbine plant) greater temperature differences than on the cooled cold side of the heat shield element.
  • At least one material region with a relatively high coefficient of thermal expansion adjoins the peripheral surface of the heat shield element, and at least one material region with a relatively low coefficient of thermal expansion, viewed from the peripheral surfaces, can be arranged inside the material volume.
  • a material region with a relatively low coefficient of thermal expansion on the hot side and a material region with a relatively high coefficient of thermal expansion can also adjoin the cold side. Since, in particular in the area of the peripheral surfaces, the heat shield elements of a heat shield are cooled due to the blocking air flow, high temperature stresses occur in heat shield elements with a homogeneous coefficient of thermal expansion in the area of the peripheral surfaces Heat shield element particularly low operating temperatures arise. The fact that the coefficient of thermal expansion is increased in the region of the peripheral surfaces compared to the interior (seen from the peripheral surfaces) of the heat shield element, the voltages occurring can be reduced.
  • adjacent material regions with different coefficients of thermal expansion are configured in such a way that a smooth transition from the thermal expansion coefficient of one material region to the thermal expansion coefficient of the other material region takes place in the zone of the transition from one material region to the other material region. Due to the smooth transition of the thermal expansion coefficient, the risk of destruction of the heat shield during the manufacturing process, in particular during the sintering process, which takes place at elevated, approximately homogeneous temperature, can be reduced.
  • the object of the present invention is to provide a method for producing heat shield elements in which the material properties are adapted to the respective different loads and in this case take into account the thermal stresses within the heat shield element.
  • the object of the invention is achieved by a method according to claim 1.
  • the further claim contains an advantageous development of the invention.
  • pressing or casting of a base material mixture takes place and subsequent sintering of the pressed or cast base material mixture.
  • the inventive method is characterized in that prior to sintering the pressed or cast base material mixture adjusting the thermal expansion coefficient different material areas. By adjusting the thermal expansion coefficients of different material regions, the resistance of a heat shield element produced by means of the method according to the invention to temperature gradients within the heat shield element can be increased.
  • the invention provides to adjust the thermal expansion coefficients by aftertreatment of at least one material area after pressing or casting of the base material mixture and before sintering, which after sintering compared to the rest of the base material mixture changed, for example.
  • a relatively low coefficient of thermal expansion should have.
  • the aftertreatment can be carried out, for example, by impregnating the at least one material area to be post-treated with a liquid. This approach allows a particularly good definition of material areas, which should have a relation to the rest of the base material mixture modified thermal expansion coefficient.
  • the FIG. 1 shows a ceramic heat shield element 1 in a perspective view.
  • the heat shield element 1 has a hot side 3, which faces the hot medium after installation of the heat shield element 1 in a heat shield.
  • the hot side 3 is opposite the cold side 5 of the heat shield element 1, which faces after installation in a heat shield of the supporting structure of the combustion chamber wall and thus faces away from the hot medium.
  • Hot side 3 and cold side 5 are connected to each other via first peripheral surfaces 7 and second peripheral surfaces 9.
  • the second peripheral surfaces 9 have grooves 11 into which retaining clips (not shown) connected to the supporting structure of the combustion chamber wall can engage in order to hold the heat shield element in position after installation in a ceramic hot gas lining.
  • the first peripheral surfaces 7, however, have no groove.
  • the hot side 3, the cold side 5, the first peripheral surfaces 7 and the second peripheral surfaces 9 enclose the material volume of the heat shield element, which provides the thermal shielding effect.
  • FIG. 2a A first embodiment of the heat shield element is shown in FIG. 2a shown in section.
  • the cut runs along from the line AA FIG. 1 , It can be seen the hot side 13, the cold side 15 and the groove-free peripheral surfaces 17 of the heat shield element 10 of the first embodiment.
  • the heat shield element 10 has a first material region 19 and second material regions 21, which differ from the material region 19 by their thermal expansion coefficient.
  • the thermal expansion coefficient of the material regions 21 is greater than the thermal expansion coefficient of the material region 19. In this sense, the material region 19 has a relatively low thermal expansion coefficient, whereas the material regions 21 have a relatively high coefficient of thermal expansion.
  • the load-bearing structure of the combustion chamber wall is lined with a number of heat shield elements 10 area-covering.
  • the heat shield elements 10 are attached to one another in such a way that expansion gaps remain between adjacent heat shield elements 10. These expansion gaps serve to allow expansion of the heat shield elements 10 during operation of the combustion chamber due to the high operating temperatures without the heat shield elements 10 touching each other.
  • the relatively cool material regions 21 in a conventional heat shield element would be subject to stress due to their relatively low thermal expansion from the hot central region 19 experiencing greater thermal expansion, and could crack when exceeding the material strength.
  • the cracks would emanate from the edges of the heat shield and extend toward the heat shield interior. Such cracking can reduce the life of a heat shield element.
  • the stresses are reduced, in particular in the cool peripheral regions, since the material regions 21 have a higher coefficient of thermal expansion than the central material region 19.
  • the higher temperature of the central material region 19 is thus due to the larger thermal expansion coefficient of the material regions 21 in the region of the peripheral surfaces 17th balanced.
  • the thermal expansion coefficients of the material regions 19 and 21 and the extent of these material regions in the material volume of the heat shield element 10 can be numerically optimized in such a way that the stresses in the heat shield element 10 are minimized.
  • the expansion of the material regions 21 can be determined with relatively high coefficients of thermal expansion, by first performing a calculation of the temperature field which is established in the desired operating state under corresponding boundary conditions in the heat shield element. Subsequently, on the basis of this result, the size of the regions 21 for the selected coefficient of thermal expansion can be adjusted such that a minimization of the stresses in the heat shield element 10 takes place.
  • you can too the thermal expansion coefficients and the expansions of the material areas are simultaneously optimized.
  • FIG. 2a In the area of the groove-free circumferential surfaces 17 of the heat shield element, material regions 21 with an increased thermal expansion coefficient and reduced thermal conductivity compared to the central material region 19 are present. Additionally or alternatively, the heat shield element 10 can also have material regions 20 with an increased thermal expansion coefficient and reduced thermal conductivity in the region of the second peripheral surfaces compared to the central material region 19, ie in the region of the peripheral surfaces (18). Fig. 2b ).
  • FIG. 3 A second embodiment of the heat shield element is in FIG. 3 shown in section.
  • the section runs along the in FIG. 1 represented line AA. Accordingly, the hot side 113, the cold side 115 and the groove-free peripheral surfaces 117 of the heat shield element 110 can be seen.
  • the heat shield element 110 has on the hot side a material region 119 with a relatively low coefficient of thermal expansion and a relatively low thermal conductivity. On the cold side, it has a material region 121 with a thermal expansion coefficient which is increased compared to the hot-side material region 119, an increased thermal conductivity and increased mechanical strength.
  • This embodiment takes into account the fact that the hot side 113 of a heat shield element during operation of a combustion chamber is exposed to a higher temperature than the generally cooled cold side 115. In the heat shield element 110, therefore, a temperature gradient forms from the hot side 113 to the cold side 115 out. The lower temperature of the cold side material portion 121 is then during operation of the combustion chamber by its compared to the hot side Material range 119 compensated higher thermal expansion coefficient. Stress due to the temperature gradient can therefore be reliably avoided.
  • FIG. 4 A third embodiment of the heat shield element is shown in FIG FIG. 4 shown in section.
  • the section runs along the in FIG. 1 represented line AA. Accordingly, the cold side 213, the hot side 215 and the groove-free peripheral surfaces 217 of the heat shield element 210 can be seen.
  • the heat shield element 210 has a first, hot-side material region 219 having a first coefficient of thermal expansion, peripheral second material regions 221 having a second thermal expansion coefficient, and a cold-side material region 223 having a third coefficient of thermal expansion.
  • the second and the third thermal expansion coefficient may also be identical.
  • the heat shield element shown here there are relatively abrupt transitions between the different material regions and thus relatively abrupt transitions between different thermal expansion coefficients.
  • the areas with different coefficients of expansion should, if possible, not be in the form of sharp boundaries of the material properties, but rather in the form of smooth transitions of the material properties in order to avoid the risk of destruction of the heat shield during the manufacturing process, in particular during sintering. which occurs at elevated, largely homogeneous temperature, to avoid.
  • FIGS. 5a and 5b A manufacturing method for heat shield elements will now be described with reference to FIGS FIGS. 5a and 5b described.
  • a material mixture 419 is placed in a mold 440, 450 and then pressed.
  • the result is a green body 410 of the heat shield element.
  • This green compact 410 is in FIG. 5b shown. It can be seen the hot side 413, the cold side 415 and the groove-free peripheral surfaces 417 of the green body 410.
  • the green body 410 is impregnated with a liquid which influences the sintering process.
  • the liquid is selected such that the impregnated regions 421 after sintering have a higher coefficient of thermal expansion than the non-impregnated region 419.
  • the grooved peripheral surfaces of the green body 410 (in FIG Fig. 5b not visible) are soaked to increase the thermal expansion coefficient of the corresponding areas.
  • the result of with regard to the FIGS. 5a and 5b described method is a heat shield element, as in FIG. 2 is shown.
  • the mold When pressing the heat shield element, the mold can be filled horizontally or vertically and the filling of material mixtures using stencils done.
  • the mold can be placed or filled at any angle.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (2)

  1. Procédé de production d'un élément céramique de bouclier thermique, dans lequel on effectue d'abord un moulage par compression ou une coulée d'un mélange ( 419, 421 ) de matériau de base et ensuite un frittage du mélange ( 419, 421 ) de matériau de base moulé par compression ou coulé,
    caractérisé
    en ce que, pour régler le coefficient de dilatation thermique de parties différentes du matériau après le moulage ou la coulée du mélange ( 419 ) de matériau de base et avant le frittage, on effectue un post-traitement au moins d'une partie ( 421 ) du matériau, qui doit avoir, après le frittage, un coefficient de dilatation thermique modifié par rapport au reste du mélange ( 419 ) du matériau de base.
  2. Procédé suivant la revendication 1,
    caractérisé
    en ce qu'on effectue le post-traitement en imprégnant d'un liquide la au moins une partie ( 421 ) du matériau? qui a été post-traitéE.
EP05811090.9A 2004-12-01 2005-11-22 Procédé de production d'un élément d'écran thermique Ceased EP1817528B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05811090.9A EP1817528B1 (fr) 2004-12-01 2005-11-22 Procédé de production d'un élément d'écran thermique

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04028445A EP1666797A1 (fr) 2004-12-01 2004-12-01 Elément de bouclier thermique, son procédé de fabrication, bouclier thermique et chambre de combustion
PCT/EP2005/056127 WO2006058851A1 (fr) 2004-12-01 2005-11-22 Element ecran thermique, son procede de production, revetement gaz chaud et chambre de combustion
EP05811090.9A EP1817528B1 (fr) 2004-12-01 2005-11-22 Procédé de production d'un élément d'écran thermique

Publications (2)

Publication Number Publication Date
EP1817528A1 EP1817528A1 (fr) 2007-08-15
EP1817528B1 true EP1817528B1 (fr) 2016-10-19

Family

ID=34927604

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04028445A Withdrawn EP1666797A1 (fr) 2004-12-01 2004-12-01 Elément de bouclier thermique, son procédé de fabrication, bouclier thermique et chambre de combustion
EP05811090.9A Ceased EP1817528B1 (fr) 2004-12-01 2005-11-22 Procédé de production d'un élément d'écran thermique

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP04028445A Withdrawn EP1666797A1 (fr) 2004-12-01 2004-12-01 Elément de bouclier thermique, son procédé de fabrication, bouclier thermique et chambre de combustion

Country Status (3)

Country Link
US (1) US20080104963A1 (fr)
EP (2) EP1666797A1 (fr)
WO (1) WO2006058851A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2428647B1 (fr) * 2010-09-08 2018-07-11 Ansaldo Energia IP UK Limited Zone de transition pour une chambre de combustion d'une turbine à gaz
DE102012201650A1 (de) 2012-02-03 2013-08-08 Sgl Carbon Se Hitzeschild mit äußerer Faserwicklung
WO2014149108A1 (fr) 2013-03-15 2014-09-25 Graves Charles B Agencement d'enceinte et de chemisage à dalles pour une chambre de combustion
US20160109129A1 (en) * 2013-05-21 2016-04-21 Siemens Aktiengesellschaft Heat shield tile for a heat shield of a combustion chamber
US10935236B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US10935235B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US10830433B2 (en) 2016-11-10 2020-11-10 Raytheon Technologies Corporation Axial non-linear interface for combustor liner panels in a gas turbine combustor
US10655853B2 (en) 2016-11-10 2020-05-19 United Technologies Corporation Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1142852A2 (fr) * 2000-04-07 2001-10-10 DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. Matériau composite céramique comportant une couche protectrice thermochimique à gradient de composition
WO2002033322A1 (fr) * 2000-10-16 2002-04-25 Siemens Aktiengesellschaft Pierre de protection thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz
US20030207155A1 (en) * 1998-03-27 2003-11-06 Siemens Westinghouse Power Corporation Hybrid ceramic material composed of insulating and structural ceramic layers

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3174444A (en) * 1964-01-27 1965-03-23 Harbison Walker Refractories Suspended hot patch brick
GB1272591A (en) * 1968-03-28 1972-05-03 Delaney Gallay Ltd Improvements in and relating to heat shields
US4485630A (en) * 1982-12-08 1984-12-04 General Electric Company Combustor liner
US4838030A (en) * 1987-08-06 1989-06-13 Avco Corporation Combustion chamber liner having failure activated cooling and dectection system
FR2664585B1 (fr) * 1990-07-13 1993-08-06 Europ Propulsion Structures refractaires refroidies et procede pour leur fabrication.
JPH0739859B2 (ja) * 1990-11-29 1995-05-01 シーメンス アクチエンゲゼルシヤフト 支持構造のセラミック製熱遮蔽体
DE10046094C2 (de) * 2000-09-18 2002-09-19 Siemens Ag Hitzeschildstein zur Auskleidung einer Brennkammerwand
EP1191285A1 (fr) * 2000-09-22 2002-03-27 Siemens Aktiengesellschaft Bouclier thérmique , chambre de combustion avec garnissage interne et turbine à gaz
EP1302723A1 (fr) * 2001-10-15 2003-04-16 Siemens Aktiengesellschaft Revêtement pour parois intérieures de chambre de combustion
US7291407B2 (en) * 2002-09-06 2007-11-06 Siemens Power Generation, Inc. Ceramic material having ceramic matrix composite backing and method of manufacturing
US20060141237A1 (en) * 2004-12-23 2006-06-29 Katherine Leighton Metal-ceramic materials

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030207155A1 (en) * 1998-03-27 2003-11-06 Siemens Westinghouse Power Corporation Hybrid ceramic material composed of insulating and structural ceramic layers
EP1142852A2 (fr) * 2000-04-07 2001-10-10 DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. Matériau composite céramique comportant une couche protectrice thermochimique à gradient de composition
WO2002033322A1 (fr) * 2000-10-16 2002-04-25 Siemens Aktiengesellschaft Pierre de protection thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz

Also Published As

Publication number Publication date
WO2006058851A1 (fr) 2006-06-08
US20080104963A1 (en) 2008-05-08
EP1666797A1 (fr) 2006-06-07
EP1817528A1 (fr) 2007-08-15

Similar Documents

Publication Publication Date Title
EP1817528B1 (fr) Procédé de production d'un élément d'écran thermique
DE60201079T2 (de) Wärmedämmschicht mit unter der oberfläche vorliegenden einschlüssen für verbesserte temperaturwechselbeständigkeit
WO2006058629A1 (fr) Element ecran thermique, procede et moule pour sa fabrication, revetement a gaz chaud et chambre de combustion
EP1183120B1 (fr) Outil de coulee et procede pour la fabrication d'un element
EP0974414B1 (fr) Moule de coulée et procédé de coulée pour la fabrication d'un bloc moteur
EP1029154B1 (fr) Carter de turbine et son procede de production
WO2006056315A1 (fr) Piston de construction legere soumis a une forte contrainte thermique
EP2527743B1 (fr) Composant segmenté à base de matériau réfractaire pour une chambre de combustion annulaire, chambre de combustion annulaire pour un moteur d'aéronef, moteur d'aéronef et procédé de fabrication d'une chambre de combustion annulaire
DE69009116T2 (de) Verbrennkammer mit Wärmedämmung.
DE102009011913A1 (de) Wärmedämmschichtsystem
EP3097298B1 (fr) Pièce coulée et insert destiné à une telle pièce coulée
DE19926794C2 (de) Zylinderbüchse für eine flüssigkeitsgekühlte Brennkraftmaschine
DE69110777T2 (de) Statorschaufeln für Turbinen, hergestellt aus einem thermostrukturellen Verbundmaterial.
EP0439760B1 (fr) Dispositif pour supporter les produits en traitement thermique dans un four de réchauffage
DE60313455T2 (de) Wandkonstruktion
DE69003629T2 (de) Vorbrennkammer mit Wärmedämmung und Verfahren für seine Herstellung.
EP2483017B1 (fr) Moule
DE69003620T2 (de) Vorbrennkammer mit Wärmedämmung.
EP1855824B1 (fr) Procédé de production d'une coquille pour la coulée continue et coquille pour la coulée continue
EP1019208B1 (fr) Tube pour lingotiere de coulee continue d'aciers, notamment d'aciers peritectiques
DE102017102544A1 (de) Ventilsitzring eines Gaswechselventils, Gaswechselventil und Verfahren zum Herstellen des Ventilsitzrings
EP2022951A1 (fr) Procédé destiné à la fabrication d'un boîtier de turbine et boîtier de turbine
EP1797976A2 (fr) Pierre de lavage à gaz
EP1660833A2 (fr) Pierre servant de bouclier thermique pour garnir une paroi de chambre de combustion, chambre de combustion et turbine a gaz correspondantes
EP1480915B1 (fr) Paroi de delimitation d'une installation de fonte de verre refroidie et soumise a l'action du verre fondu

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20070307

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH DE ES GB IT LI PL

DAX Request for extension of the european patent (deleted)
RBV Designated contracting states (corrected)

Designated state(s): CH DE ES GB IT LI PL

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

17Q First examination report despatched

Effective date: 20130805

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160511

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE ES GB IT LI PL

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502005015406

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161019

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161019

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502005015406

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20161130

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20161130

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

26N No opposition filed

Effective date: 20170720

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20170119

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170119

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20181127

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20190118

Year of fee payment: 14

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502005015406

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200603

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191122