EP1899582A1 - Bouclier thermique et aube directrice de turbine pour une turbine a gaz - Google Patents

Bouclier thermique et aube directrice de turbine pour une turbine a gaz

Info

Publication number
EP1899582A1
EP1899582A1 EP06764023A EP06764023A EP1899582A1 EP 1899582 A1 EP1899582 A1 EP 1899582A1 EP 06764023 A EP06764023 A EP 06764023A EP 06764023 A EP06764023 A EP 06764023A EP 1899582 A1 EP1899582 A1 EP 1899582A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
hot gas
shield element
flow
platform
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP06764023A
Other languages
German (de)
English (en)
Other versions
EP1899582B1 (fr
Inventor
Marc Tertilt
Beate Seiler
Andreas Böttcher
Christian Lerner
Jens Kleinfeld
Uwe Gruschka
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 EP06764023.5A priority Critical patent/EP1899582B1/fr
Publication of EP1899582A1 publication Critical patent/EP1899582A1/fr
Application granted granted Critical
Publication of EP1899582B1 publication Critical patent/EP1899582B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity

Definitions

  • the present invention relates to a flow housing with a wall structure surrounding a flow path, Wenig ⁇ least a wall structure integral vane for directing a flow in the flow path and at a
  • the present invention relates to a flow housing for a gas turbines ⁇ plant .
  • the present invention relates to a guide vane and a heat shield element for a flow housing.
  • Flow housing for a hot gas flow usually include egg ⁇ ne wall structure with a support structure and a support structure for the housing towards the interior of the upstream heat shield.
  • the heat shield is intended to protect the support structure from excessive heating and corrosion and / or oxidation.
  • guide vanes are often arranged to direct the flow.
  • the combustion chamber and the turbine section downstream in the flow direction can be regarded as a flow housing for a hot gas flow. At the transition from the combustion chamber to the turbine section this guide vanes are arranged ⁇ , which serve to guide the hot gas flow.
  • Cool air may be blown into the flow path through this gap to secure the gaps against hot gas flow.
  • the pressure of the outflowing cooling air must be higher than the pressure of the hot gas in the direction of the cooling air gap.
  • Such a cooling air gap exists, for example, in gas turbine plants at the transition between the combustion chamber and the turbine section of the gas turbine plant, more precisely between the heat shield elements of the combustion chamber arranged at the boundary between combustion chamber and turbine section and the guide vanes of the turbine section adjacent to these heat shield elements in the flow direction other hand.
  • Object of the present invention is therefore to provide a flow housing for a hot gas flow, in particular a Strö ⁇ tion housing for a gas turbine plant, in which even without an increase in the cooling air supply, the thermal load of the flow housing in Be ⁇ rich between a heat shield element and a adjacent vane reduced compared to the prior art can be.
  • Another object of the invention is to Ge ⁇ pliusebaumaschinener to make available, which can be beneficial ⁇ adhesive used in the construction of a flow housing.
  • the first object is achieved by a flow housing according to claim 1.
  • ⁇ and the second object is achieved by a guide vane of claim 13 or a heat shield element according to claim 16th
  • the dependent claims contain advantageous Ausges ⁇ taltitch the invention.
  • a flow housing for a hot gas flow which in particular ⁇ sondere as a flow body for a gas turbine engine of ⁇ can be designed, comprising a wall structure surrounding a flow path, at least one in the wall structure inte- grated vane for directing a flow in Strö ⁇ mung path and to a support structure of the wall structure arranged heat shield.
  • the vane is equipped with a paddle platform, also called a fairfoot or a blade head. This has a platform surface which forms a wall portion of the Strö ⁇ mung path. In order to protect the blade and the Schaufelplatt ⁇ form from the flowing hot gas, they can have a heat-insulating and a corrosion and / or oxidation-inhibiting coating.
  • the heat shield comprises a heat shield element which is located directly upstream of the blade platform upstream of the gap and which has a hot gas side heat shield surface facing away from the wall structure, which forms a wall section of the flow path.
  • the heat shield element is usually made of metal and may have a heat-insulating as well as a corrosion and / or oxidation-inhibiting coating aufwei ⁇ sen.
  • the vanes and the heat shield element relative to each other angeord ⁇ net that the hot gas side surface of the heat shield further in- NEN is arranged relative to the flow path, as the Platt ⁇ form surface or that the hot gas side Hitzeschildober ⁇ surface is aligned at least with the platform surface.
  • the hot gas side heat shield surface hereinafter hot gas surface called
  • the platform ⁇ surface a dew point free guide surface for the hot gas, which is continuous in the case of alignment alignment.
  • the guide vane has a leading edge and the vane platform has a surface area upstream of the leading edge element in the direction of the heat shield element.
  • the upstream surface area forms a Wandab ⁇ section of the flow path.
  • This surface area can in particular be designed such that it is aligned with the hot gas surface of the heat shield element.
  • this surface region further comprises a surface facing the heat shield element edge with a small Krümmungsra ⁇ dius, the hot gas-carrying surface of the pre ⁇ superimposed surface portion can be particularly close air gap to the cooling and are thus brought particularly close to the hot gas-carrying surface of the heat shield element without while a step is created.
  • this is designed such that aquonaus ⁇ expansion of the guide vane when pressurized with flowing hot gas is not hindered.
  • the Materialparame ⁇ ter the heat shield element are chosen such that the Heat shield element when applied with flowing hot gas defined deformed so that its hot gas surface of the upper ⁇ surface of the blade platform follows with a longitudinal expansion of the guide vane.
  • the heat shield elements adjoining the guide blade are screwed in a central region to the support structure of the flow housing.
  • the heat shield element can be fastened to the support structure in such a way that a gap remains between a section of the heat shield element facing the blade platform and at least in the cold state of the heat shield element, ie in the state not acted upon by flowing hot gas.
  • the guide blade expands in the longitudinal direction, so that the surfaces of the blade platform and the heat shield element are no longer aligned without further measures.
  • a deflection of the heat shield element when acted upon by hot gas takes place in such a way is that the gap between the vane portion facing the heat shield element and the supporting ⁇ structure is reduced or even completely closed.
  • the vane-facing portion of the hot gas surface moves toward the support structure, following the surface of the vane platform as the vane extends longitudinally.
  • the heat shield element has a circumferential side facing the blade platform, which is angled away from the hot gas surface in the direction of the support structure, in which cooling air openings are arranged.
  • the cooling air openings can be used to specifically set the outflowing cooling air quantity.
  • An optimization of Cooling air flow can be effected by different distribution of the cooling air openings.
  • cooling air openings may be arranged near the hot gas surface. This pier ⁇ ren to a particularly favorable cooling air flow and can be used in certain circumstances even to generate a cooling air film in the surface of the blade platform.
  • the heat shield element partially overlaps the blade platform. In this way, the penetration of hot gas into the gap between the blade platform and the heat shield element and thus a hot ⁇ gas attack in the gap region can be particularly effectively avoided. In addition, the amount of cooling air required to block the gap against the penetration of hot gas can be reduced.
  • the overlapping can, for example, be achieved in that the edge of the blade platform has a recess extending transversely to the flow direction and the heat shield element has a web aligned with its hot gas surface and projecting into the recess of the blade platform on its side facing the blade platform.
  • the web has a groove, preferably even more grooves. The grooves allow even with the gap closed an escape of cooling air.
  • the outlet of cooling air can also be ensured by the fact that the web is formed segmented.
  • the flow housing described can particularly advantageous ⁇ come in a gas turbine system used.
  • a guide vane according to the invention which may in particular be configured as a guide vane for a gas turbine plant, has an inflow edge and an inflow edge in the direction of flow, ie in the direction from which the inflow occurs, upstream surface area on. This can have an upstream edge portion with a small radius Krüm ⁇ mung. In addition, in the edge portion a transverse to the direction of flow recess may be present. Such a vane can be used to construct a he ⁇ inventive flow housing.
  • May be an inventive heat shield element which insbesonde re ⁇ for use in a gas turbine system formed has a hot gas to be directed towards a hot gas surface and a web.
  • the web has, at an edge located in the outflow direction, that is to say the direction which runs counter to the direction of flow, on a web surface aligned with the hot gas surface. This may in particular have one or more grooves or be formed segmented.
  • Such a heat shield element can be used to construct a flow housing according to the invention.
  • the heat shield element whose material parameters are selected such that it performs a defined and tailored to the geometry of its installation location in a hot gas path deformation when Beaufschla ⁇ conditions with hot gas.
  • a heat shield element allows its hot gas surface, for example, to expand in length when exposed to hot gas
  • An adjacent vane can ⁇ follow are net if angeord- in a downstream angled from the hot gas surface peripheral side air intakes. It is particularly advantageous ifdeluftöffnun ⁇ gene are present in the vicinity of the hot gas surface, since then the training if necessary a cooling air film over the surface of an adjacent element, eg. Above the surface of Blade platform of an adjacent vane, can be generated.
  • Figure 1 shows a section of a flow housing according to the prior art.
  • Figure 2 shows a first embodiment of a dung OF INVENTION ⁇ according flow housing.
  • Figure 3 shows a second embodiment of a dung OF INVENTION ⁇ according flow housing.
  • FIG. 4 shows a third exemplary embodiment of a flow housing according to the invention.
  • Figure 5 shows a fourth embodiment of a dung OF INVENTION ⁇ according flow housing.
  • Figure 6 shows a first embodiment of a dung OF INVENTION ⁇ according heat shield element.
  • Figure 7 shows a second embodiment of a dung OF INVENTION ⁇ according heat shield element.
  • Figure 8 shows an alternative variant of Darge in Figure 6 ⁇ presented heat shield element.
  • Figure 1 shows a section of a gas turbine plant, the nenleitschaufel a portion of the combustion chamber 1 and the first turbine 3 is a sectional side view ⁇ represents.
  • the turbine vane 3 comprises a blade 5, and two blade platforms, namely the blade root 7 and the blade head 9.
  • the combustion chamber 1 and the walls of the door ⁇ binenabismees the gas turbine plant together form a flow housing for the hot combustion gases.
  • the support structure 2 and attached metallic heat shield elements 13 are shown.
  • the heat shield elements 13 and the blade Platt ⁇ form 7, 9 have a surface facing the flowing hot gas hot gas surface 8, 10, 14.
  • the hot gas surfaces are provided with a heat-insulating coating and a corrosion and oxidation-inhibiting coating arranged under the heat-insulating coating.
  • Cooling air gaps 15 are present between the heat shield elements 13 and the blade platforms 7, 9, through which the air is blown into the interior of the flow housing in order to block the gaps 15 against the penetration of hot gas.
  • the gaps serve to facilitate a heat-related relative movement between the heat shield elements 13.
  • Figure 2 shows a first embodiment of a dung OF INVENTION ⁇ according flow housing.
  • the flow housing is part of a gas turbine plant and is formed on the one hand by the wall of the combustion chamber and on the other hand by the wall of the turbine section of the gas turbine plant.
  • Figure 1 shows a detail of the flow housing, ⁇ wel cher the transition between the combustion chamber 101 and the first vane 103 illustrating the turbine section.
  • the managing ⁇ bucket 103 includes an airfoil 105 and fel duen two Schau-, namely a blade root 107 and a
  • Blade head 109 In contrast to the prior art blade platforms, the blade platforms 107, 109 of the blade 103 have sections 111, 112, which are the Leading edge 106 of the airfoil 105 are upstream in the flow direction. The surfaces 108, 110 of these sections 111, 112 form hot gas-carrying surfaces of the blade platforms 107, 109, which run largely parallel to the flow direction R of the hot gas in the flow path. Inflow side have the blade platforms 107, 109, an edge 119, 121 with a small compared to the blade platforms of Figure 1 radius of curvature is formed at a right angle starting cowge ⁇ angling of the blade platform 107, 109th
  • the metallic heat shield elements 113 of the gas turbine combustion chamber 101 and the blade platforms 107, 109 of the turbine guide vane 105 are arranged relative to one another such that the hot gas surfaces 114 of the heat shield elements 113 are aligned with the hot gas surfaces 108, 110 of the blade platforms 107, 109 running parallel to the flow direction.
  • no steps in Studentsgangsbe ⁇ are rich between the combustion chamber 101 and the Turbinenleitschau- fei 103 available, so that can avoid stagnation points.
  • the existing between the heat shield elements 113 and the blade platforms 107, 109 gap can be shut off with low compared to the prior art cooling air requirement against ingress of hot gas.
  • FIG. 1 A second exemplary embodiment of the flow housing according to the invention is shown in FIG.
  • the blade root 207 and the airfoil 205 of the turbine vane 203 have the same shape as in the turbine vane 3 of Figure 1.
  • the hot gas Upper ⁇ surface 214 of the metal heat shield element 213 is JE but further away from the support structure 202 as in the heat shield element 13 of Figure 1. 213
  • the heat shield ⁇ element an overlap 216 with which it is the blade 207 is partially overlapped.
  • the shape of the overlap Rich 216 is adapted to the shape of the blade root 207 such that a substantially continuous, flush transition from the hot gas surface 214 of the heat ⁇ shield element 213 to the hot gas surface 208 of the Schaufelfu- ßes 207 takes place.
  • the overlap region 216 has a circumferential section 217 facing the blade root 207.
  • This peripheral section extends in the direction of the support structure 202 and is adapted to the contour of the blade root 207.
  • Indiumsab ⁇ section 207 cooling air holes 218 are provided, can be blown through the cooling air into the gap 215 between the heat shield element 213 and the blade root 207.
  • FIG. 4 A third exemplary embodiment of the hit ⁇ zeschildelement according to the invention is shown in Figure 4.
  • the turbine guide vane 303 with the airfoil 305 and the blade root 307 and the support structure 302 of the combustion chamber with the metallic heat shield element 313 attached thereto can be seen.
  • the heat shield element 313 differs from the heat shield element 113 of Figure 2 in that it has a nearly off ström detox bent at right angles in the direction of the support structure 302 with peripheral side 317 is ordered to ⁇ cooling air holes 318th
  • a perspective view of this heat shield element is shown in detail in FIG.
  • the support structure 302 is also informed ⁇ det, that it does not hinder a longitudinal expansion of the guide vane 305 when exposed to hot gas. Due to such a longitudinal extent, the blade root 307 of the vane 305 moves toward the support structure 302.
  • the material parameters of the heat shield element 313 are selected such that it is seen from the attachment section 322 Guide vane-side section 323 in contact with the hot gas due to the cooling air flowing between the support structure 302 and the heat shield member 313 he ⁇ moves, which bends the guide vane-side portion 323 in the direction of the support structure 302.
  • the gap joins 321.
  • the portion 324 of the movement of the blade root 307 to follow and thus forming a step between the hot gas leading surfaces 314, 308 of the heat shield element 313 and the blade root 307 largely avoid.
  • the gap 305 between the heat shield element 313 and the blade root 307 can be kept to a minimum during the operation of the flow housing, so that it is to be blocked with comparatively little sealing air.
  • FIG. 4 A modification of the exemplary embodiment illustrated in FIG. 4 is shown in FIG. Again, the turbine guide vane 403 with the vane blade 405 and blade root 407 and the support structure 402 of the combustion chamber with a metallic heat shield element 413 attached to the support structure 402 can again be seen.
  • the heat shield element 413 has a web 424 which projects beyond the angled peripheral side 417 in the direction of the blade root 407.
  • the hot gas side Oberflä ⁇ surface of the web 424 is flush on the hot gas side O- ber Design 414 of the heat shield element 413th
  • the blade 407 of the turbine vane 405 includes combustible chamber side one portion 420 that is formed in the top thereof ei ⁇ ne recess 422nd
  • the recess 422 forms a receptacle for the web 424, which is designed such that the surface of the arranged in the receptacle 422 Ste ⁇ ges 424 with the surface 408 of the blade root 407 curse ⁇ tet.
  • cooling air holes 418 are arranged un ⁇ indirectly below the web 424, is to blow through the cooling air in the direction of the blade root 407.
  • the movement of the blade-side portion 423 due to the heat shield element 413 to the support structure 402 includes the cooling air gap 415 between the recess 422 and the web 424 located almost completely, so that the cooling may be air consumption minimized.
  • the cooling air gap 415 is even a zero gap.
  • FIG. 5 A modification of the heat shield element 413 shown in FIG. 5 is shown in FIG. To even with a closed gap in a controlled outflow of cooling air to ermögli ⁇ chen, in the side remote from the hot gas side of the Ste- ges 424a of the heat shield element 413a grooves 425 are provided.
  • the cooling ⁇ are air holes 418a in the peripheral side 417a is not in the vicinity of the web 424a in the heat shield element 413a of Figure 6 but ordered in the made facing the support structure edge 419th Alternatively, however, the cooling air openings 418a could be arranged as shown in FIG.
  • the exiting amount of cooling air can be adjusted specifically ⁇ who.
  • Such an optimization is possible by adapting the cooling air flow to the shape of the respective blade platform.
  • they may be provided with a coating as described with reference to the heat shield element shown in FIG. 1 and with reference to FIGS 1 turbine blade have been described.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La présente invention concerne un boîtier d'écoulement, en particulier pour une installation de turbine à gaz, comprenant au moins une aube directrice et au moins un élément de bouclier thermique. Le boîtier d'écoulement pour un écoulement de gaz chaud selon cette invention présente une structure de paroi (102, 113, 107) qui entoure une voie d'écoulement, au moins une aube directrice (103), intégrée dans la structure de paroi, qui est conçue pour diriger un écoulement dans la voie d'écoulement et qui présente une plate-forme d'aube (107, 109) avec une surface de plate-forme (108, 110) formant une section de paroi de la voie d'écoulement, ainsi qu'un bouclier thermique qui est placé sur une structure de support (102) de la structure de paroi et qui présente un élément de bouclier thermique (113) placé immédiatement en amont de la plate-forme d'aube (107, 109), laissant une fente (115). Cet élément de bouclier thermique présente une surface à gaz chaud (114) qui est opposée à la structure de support (102) et qui forme une section de paroi de la voie d'écoulement. L'aube directrice (103) et l'élément de bouclier thermique (113) sont placés l'un par rapport à l'autre de manière que la surface du bouclier thermique côté gaz chaud (114, 214, 314, 414) se trouve davantage à l'intérieur par rapport à la voie d'écoulement que la surface de plate-forme (108, 110, 208, 308, 408) ou de manière que la surface du bouclier thermique côté gaz chaud (114, 214, 314, 414) s'aligne au moins sur la surface de plate-forme (108, 110, 208, 308, 408).
EP06764023.5A 2005-07-04 2006-07-03 Écran thermique et aube de distributeur pour une turbine à gaz Not-in-force EP1899582B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06764023.5A EP1899582B1 (fr) 2005-07-04 2006-07-03 Écran thermique et aube de distributeur pour une turbine à gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05014475A EP1741877A1 (fr) 2005-07-04 2005-07-04 Écran thermique et aube de distributeur pour une turbine à gaz
EP06764023.5A EP1899582B1 (fr) 2005-07-04 2006-07-03 Écran thermique et aube de distributeur pour une turbine à gaz
PCT/EP2006/063813 WO2007003629A1 (fr) 2005-07-04 2006-07-03 Bouclier thermique et aube directrice de turbine pour une turbine a gaz

Publications (2)

Publication Number Publication Date
EP1899582A1 true EP1899582A1 (fr) 2008-03-19
EP1899582B1 EP1899582B1 (fr) 2016-08-31

Family

ID=35207644

Family Applications (2)

Application Number Title Priority Date Filing Date
EP05014475A Withdrawn EP1741877A1 (fr) 2005-07-04 2005-07-04 Écran thermique et aube de distributeur pour une turbine à gaz
EP06764023.5A Not-in-force EP1899582B1 (fr) 2005-07-04 2006-07-03 Écran thermique et aube de distributeur pour une turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP05014475A Withdrawn EP1741877A1 (fr) 2005-07-04 2005-07-04 Écran thermique et aube de distributeur pour une turbine à gaz

Country Status (3)

Country Link
EP (2) EP1741877A1 (fr)
CN (1) CN101208497B (fr)
WO (1) WO2007003629A1 (fr)

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Also Published As

Publication number Publication date
EP1899582B1 (fr) 2016-08-31
CN101208497B (zh) 2011-06-15
EP1741877A1 (fr) 2007-01-10
WO2007003629A1 (fr) 2007-01-11
CN101208497A (zh) 2008-06-25

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