EP1899582B1 - Écran thermique et aube de distributeur pour une turbine à gaz - Google Patents

Écran thermique et aube de distributeur pour une turbine à gaz Download PDF

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Publication number
EP1899582B1
EP1899582B1 EP06764023.5A EP06764023A EP1899582B1 EP 1899582 B1 EP1899582 B1 EP 1899582B1 EP 06764023 A EP06764023 A EP 06764023A EP 1899582 B1 EP1899582 B1 EP 1899582B1
Authority
EP
European Patent Office
Prior art keywords
heat shield
hot gas
shield element
flow
vane
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.)
Not-in-force
Application number
EP06764023.5A
Other languages
German (de)
English (en)
Other versions
EP1899582A1 (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

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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 having a wall structure surrounding a flow path, at least one vane integrated with the wall structure for conducting a flow in the flow path and a heat shield arranged on the wall structure.
  • the present invention relates to a flow housing for a gas turbine plant.
  • the present invention relates to a vane and a heat shield element for a flow housing.
  • Flow casings for hot gas flow include i.d.R. a wall structure with a support structure and a support structure to the housing interior 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 downstream turbine section may be considered as a hot gas flow housing. 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 arranged at the boundary between the combustion chamber and turbine section heat shield elements of the combustion chamber on the one hand and in the flow direction of these heat shield elements adjacent vanes of the turbine section on the other.
  • cooling air may flow in the region of these stagnation points in the opposite direction to the general flow direction. Due to the stagnation also creates a back pressure, which may be higher than the pressure of the cooling air, which exits the cooling air gap between the heat shield element and the guide vane. Since the cooling air preferably emerges from the cooling gaps in regions of low hot gas pressure, the cooling is reduced where stagnation points occur. As a result, increased thermal stress can occur. In addition, it may happen that the pressure of the hot gas at the stagnation point is so great that hot gas can penetrate into the gap against the flow of cooling air, which leads to increased corrosion of the adjacent wall structure. More frequent component replacement and / or welding repair as part of inspections or revisions of the gas turbine plant are the result.
  • Object of the present invention is therefore to provide a flow housing for a hot gas flow, in particular a flow 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 the area between a heat shield element and an adjacent vane in comparison reduced to the prior art can be.
  • the invention makes it possible to provide housing components which can be used to advantage in the construction of a flow housing.
  • a flow housing for a hot gas flow which may be configured in particular as a flow housing for a gas turbine plant comprises a wall structure which surrounds a flow path, at least one integrated in the wall structure guide vane for guiding a flow in the flow path and arranged on a support structure of the wall structure heat shield.
  • the vane is equipped with a blade platform, also called blade root or blade head.
  • a blade platform also called blade root or blade head.
  • This has a platform surface which forms a wall portion of the flow path.
  • they may have a heat-insulating as well as a corrosion and / or oxidation-inhibiting coating.
  • the heat shield comprises a heat shield element which is located immediately upstream of the blade platform upstream of the gap and which has a hot gas side heat shield surface which faces away from the wall structure and forms a wall section of the flow path.
  • the heat shield element is i.d.R. made of metal and may have a heat-insulating and a corrosion and / or oxidation-inhibiting coating.
  • the guide vanes and the heat shield element are arranged relative to one another such that the hot gas side heat shield surface further nen is arranged relative to the flow path, as the platform surface or that the hot gas side heat shield surface is at least flush with the platform surface.
  • the hot gas side heat shield surface hereinafter referred to as hot gas surface
  • the platform surface a dew point-free guide surface for the hot gas, which is infinitely variable in the case of 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 wall portion of the flow path. This surface area can in particular be designed so that it is aligned with the hot gas surface of the heat shield element. If this surface area also has an edge facing the heat shield element with a small radius of curvature, the hot gas-conducting surface of the upstream surface section can be brought particularly close to the cooling air gap and thus particularly close to the hot gas-conducting surface of the heat shield element, without creating a step.
  • this is designed such that a longitudinal expansion of the guide blade is not hindered when exposed to flowing hot gas.
  • material parameters of 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 surface of the blade platform follows with a longitudinal expansion of the guide vane.
  • the heat shield elements adjacent the vane are bolted in a central area to the support structure of the flow housing.
  • the heat shield element can be fastened to the support structure in such a way that, between at least one of the blade platform facing portion of the heat shield element and the support structure, at least in the cold state of the heat shield element, i. in not charged with flowing hot gas state, a gap remains.
  • 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.
  • the material parameters of the heat shield element can be achieved, however, that a bending of the heat shield element when hot gas is applied so that the gap between the vane facing portion of the heat shield element and the support structure is reduced or even completely.
  • 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 peripheral 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. These lead to a particularly favorable flow of cooling air and may even be used to produce a cooling air film in the region of 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 hot gas penetration 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 be used particularly advantageously in a gas turbine plant.
  • 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 may have an edge portion with a small radius of curvature upstream. In addition, in the edge portion a transverse to the direction of flow recess may be present.
  • a guide vane can be used to construct a flow housing according to the invention.
  • a heat shield element according to the invention which may be designed in particular for use in a gas turbine plant, has a hot gas surface facing a hot gas 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 chosen such that it performs a defined and tailored to the geometry of its installation location in a hot gas path deformation when exposed to hot gas.
  • a heat shield element makes it possible for its hot gas surface, for example, a guide blade which expands in length when supplied with hot gas, to follow such that the hot gas surface is also aligned substantially flush with a surface of the blade platform even if the blade lengthwise expands.
  • a defined supply of cooling air through the heat shield element in the direction of, for example, an adjacent guide vane can take place if cooling air openings are arranged in a downstream side, which is angled away from the hot gas surface. It is particularly advantageous if cooling air openings are present in the vicinity of the hot gas surface, since then possibly the formation of a cooling air film over the surface of an adjacent element, for example. Above the surface of Blade platform of an adjacent vane, can be generated.
  • FIG. 1 shows a section of a gas turbine plant, which represents a portion of the combustion chamber 1 and the first turbine vane 3 in a sectional side view.
  • the turbine vane 3 comprises an airfoil 5 and two blade platforms, namely the blade root 7 and the blade head 9.
  • the combustion chamber 1 and the walls of the turbine section of the gas turbine plant together form a flow housing for the hot combustion exhaust gases.
  • the support structure 2 and attached metallic heat shield elements 13 are shown. Both the heat shield elements 13 and the blade platforms 7, 9 have a hot gas surface 8, 10, 14 facing the flowing hot gas.
  • the hot gas surfaces are provided with a heat-insulating coating and arranged under the heat-insulating coating corrosion and oxidation-inhibiting 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.
  • FIG. 2 shows a first embodiment of an inventive 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.
  • FIG. 1 shows FIG. 2 a section of the flow housing, which represents the transition between the combustion chamber 101 and the first guide vane 103 of the turbine section.
  • the vane 103 comprises an airfoil 105 and two blade platforms, namely a blade root 107 and a blade head 109.
  • the blade platforms 107, 109 of the blade 103 have sections 111, 112, which 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 extend substantially parallel to the flow direction R of the hot gas in the flow path.
  • the blade platforms 107, 109 have an edge 119, 121 with one in comparison to the blade platforms FIG. 1 small radius of curvature on which a largely rectangular angled portion of the blade platform 107, 109 is formed.
  • the metallic heat shield elements 113 of the gas turbine combustor 101 and the blade platforms 107, 109 of the turbine vane 105 are arranged relative to each other such that the hot gas surfaces 114 of the heat shield elements 113 are aligned with the parallel to the flow direction hot gas surfaces 108, 110 of the blade platforms 107, 109. In this way, there are no steps in the transition region between the combustion chamber 101 and the turbine vane 103, so that stagnation points can be avoided.
  • 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. 3 A second embodiment of the flow housing according to the invention is shown in FIG FIG. 3 shown.
  • the turbine guide vanes 203 of a gas turbine plant and a heat shield element 213 of the combustion chamber 201 immediately adjacent to the turbine guide vanes 203 can be seen.
  • the blade root 207 and the airfoil 205 of the turbine vane 203 have the same shape as in the turbine vane 3 FIG. 1 on.
  • the hot gas surface 214 of the metallic heat shield element 213 is farther from the support structure 202 than the heat shield element 13 FIG. 1
  • the heat shield element 213 has an overlap region 216, with which it partially overlaps the blade root 207.
  • the shape of the overlap area 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 blade root 207 takes place.
  • the overlap region 216 has a circumferential section 217 facing the blade root 207.
  • This peripheral portion extends in the direction of the support structure 202 and is adapted to the contour of the blade root 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 embodiment of the heat shield element according to the invention is shown in FIG FIG. 4 shown.
  • the turbine 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 member 313 is different from the heat shield member 113 FIG. 2 in that, on the outflow side, it has a peripheral side 317 which is angled almost at right angles in the direction of the support structure 302 and has cooling air bores 318 arranged therein.
  • a perspective view of this heat shield element is fragmentary in FIG. 7 shown.
  • the support structure 302 is formed so as not to hinder longitudinal expansion of the vane 305 when hot gas is applied. 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
  • the gap 321 closes.
  • the section 324 can follow the movement of the blade root 307, thus forming a step between the hot gas bearing surfaces 314, 308 of the heat shield element 313. of 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. 5 A variation of the in FIG. 4 illustrated embodiment is in FIG. 5 shown.
  • the turbine guide vane 403 with the vane blade 405 and the vane root 407 and the support structure 402 of the combustion chamber with a metallic heat shield element 413 fastened to the supporting 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 surface of the web 424 is flush with the hot gas side surface 414 of the heat shield member 413.
  • the blade root 407 of the turbine guide vane 405 has, on the combustion chamber side, a section 420, in the upper side of which a recess 422 is formed.
  • the recess 422 forms a receptacle for the web 424, which is configured such that the surface of the web 424 arranged in the receptacle 422 is aligned with the surface 408 of the blade root 407.
  • cooling air holes 418 are arranged immediately below the web 424, is blown through the cooling air in the direction of the blade root 407.
  • the heat shield element 413 is disposed between the mounting portion 432 and the peripheral portion 417 with a gap 421 to the supporting structure 402, which closes during operation of the gas turbine plant. Due to the movement of the blade-side portion 423 of the heat shield member 413 toward the support structure 402, the cooling air gap 415 located between the recess 422 and the land 424 almost completely closes, so that the cooling air consumption can be minimized. Ideally, the cooling air gap 415 is even a zero gap.
  • FIG. 6 A variation of the in FIG. 5 shown heat shield element 413 is in FIG. 6 shown.
  • grooves 425 are provided in the side of the web 424a of the heat shield element 413a facing away from the hot gas side.
  • the cooling air openings 418a in the peripheral side 417a are not arranged in the vicinity of the web 424a but in the edge 419 facing the support structure.
  • the cooling air openings 418a could be arranged as shown in FIG FIG. 5 is shown.
  • FIG. 6 illustrated embodiment with grooves 425 may also be a variant used, in which the web is segmented.
  • the segmentation of the web also allows a controlled flow of cooling air.
  • a segmented land heat shield element 424b is shown in FIG FIG. 8 shown.
  • the exiting amount of cooling air can be adjusted specifically. It is such an optimization by adjusting the cooling air flow to the shape of the respective blade platform possible.
  • they may be provided in all embodiments with a coating, as described with reference to the in FIG FIG. 1 shown heat shield element and with reference to in FIG. 1 illustrated turbine vane have been described.

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

Claims (6)

  1. Enveloppe d'écoulement pour un écoulement de gaz chaud, comprenant :
    - une structure (402, 413, 407) de paroi, qui entoure un trajet d'écoulement,
    - au moins une aube (403) directrice intégrée dans la structure de paroi pour conduire un écoulement dans le trajet d'écoulement, qui a une lame (405) d'aube ayant un bord (106) d'attaque, l'aube (403) directrice ayant une plateforme (407) d'aube ayant une surface (408) de plateforme, qui forme une partie de paroi du trajet d'écoulement, et une zone (112) de surface en amont du bord (106) d'attaque dans le sens vers l'élément (413) de bouclier thermique, laquelle zone forme une partie de paroi du trajet d'écoulement et
    - un bouclier thermique mis sur une structure (402) porteuse de la structure de paroi et ayant un élément (413) de bouclier thermique mis juste en amont de la plateforme (407) d'aube en laissant un intervalle (415), élément de bouclier thermique, qui a une surface (414) de bouclier thermique du côté du gaz chaud, éloignée de la structure (402) porteuse et formant une partie de paroi du trajet d'écoulement,
    dans laquelle l'aube (403) directrice et l'élément (413) de bouclier thermique sont disposés relativement l'un à l'autre, de manière à ce que la surface (414) de bouclier thermique du côté du gaz chaud soit alignée au moins avec la surface (408) de la plateforme,
    caractérisée en ce que
    - l'élément (413) de bouclier thermique chevauche en partie la plateforme (407) d'aube et
    - le bord de la plateforme (407) de l'aube a un évidement (415) s'étendant transversalement au sens d'écoulement et l'élément (413) de bouclier thermique a, du côté tourné vers la plateforme (407) de l'aube, une nervure (424) alignée avec la surface (414) pour du gaz chaud et pénétrant dans l'évidement (415) de la plateforme de l'aube.
  2. Enveloppe d'écoulement suivant la revendication 1, caractérisée par sa conformation, de manière à ce qu'une dilatation en longueur de l'aube (403) directrice ne soit pas empêchée lors de l'alimentation en gaz chaud en écoulement, et par un choix des paramètres de l'élément (413) de bouclier thermique, de manière à ce que l'élément (413) de bouclier thermique se déforme d'une manière définie lors de l'alimentation en gaz chaud en écoulement, de manière à ce que la surface (414) pour le gaz chaud de la surface (408) de la plateforme (407) de l'aube suive lors de la dilatation en longueur de l'aube (403) directrice.
  3. Enveloppe d'écoulement suivant la revendication 2, caractérisée en ce que l'élément (413) de bouclier thermique est fixé à la structure (402) porteuse, de manière à laisser subsister un intervalle (421) entre une partie (423, tournée vers la plateforme (407) de l'aube, de l'élément (413) de bouclier thermique et la structure (402) porteuse, au moins dans l'état de l'élément (413) de bouclier thermique, où il n'est pas alimenté par du gaz chaud en écoulement.
  4. Enveloppe d'écoulement suivant l'une des revendications 1 à 3, caractérisée en ce que la nervure est pourvue d'au moins une rainure.
  5. Enveloppe d'écoulement suivant l'une des revendications 1 à 3, caractérisée en ce que la nervure est segmentée.
  6. Installation de turbine à gaz ayant une enveloppe d'écoulement suivant l'une des revendications 1 à 5.
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 EP1899582A1 (fr) 2008-03-19
EP1899582B1 true EP1899582B1 (fr) 2016-08-31

Family

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Family Applications (2)

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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)

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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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* Cited by examiner, † Cited by third party
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DE102016116222A1 (de) 2016-08-31 2018-03-01 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine

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* Cited by examiner, † Cited by third party
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ATE497087T1 (de) 2007-08-06 2011-02-15 Alstom Technology Ltd Spaltkühlung zwischen brennkammerwand und turbinenwand einer gasturbinenanlage
GB0808206D0 (en) * 2008-05-07 2008-06-11 Rolls Royce Plc A blade arrangement
US9650903B2 (en) * 2009-08-28 2017-05-16 United Technologies Corporation Combustor turbine interface for a gas turbine engine
CN103184896B (zh) * 2011-12-27 2015-12-16 中航商用航空发动机有限责任公司 一种涡轮导向叶片
EP2634373A1 (fr) 2012-02-28 2013-09-04 Siemens Aktiengesellschaft Agencement pour turbomachine
EP2754858B1 (fr) 2013-01-14 2015-09-16 Alstom Technology Ltd Dispositif pour étanchéifier une cavité ouverte contre un entraînement gazeux chaud
CN103061889B (zh) * 2013-01-17 2014-08-27 中国科学院工程热物理研究所 一种隔热结构
US9752447B2 (en) * 2014-04-04 2017-09-05 United Technologies Corporation Angled rail holes
DE102014221783A1 (de) 2014-10-27 2016-04-28 Siemens Aktiengesellschaft Heißgaskanal
DE102016104957A1 (de) 2016-03-17 2017-09-21 Rolls-Royce Deutschland Ltd & Co Kg Kühleinrichtung zur Kühlung von Plattformen eines Leitschaufelkranzes einer Gasturbine
US11181005B2 (en) * 2018-05-18 2021-11-23 Raytheon Technologies Corporation Gas turbine engine assembly with mid-vane outer platform gap
WO2021246999A1 (fr) * 2020-06-01 2021-12-09 Siemens Aktiengesellschaft Segment de bague pour turbine à gaz

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3286461A (en) * 1965-07-22 1966-11-22 Gen Motors Corp Turbine starter and cooling
JP2005030680A (ja) * 2003-07-14 2005-02-03 Mitsubishi Heavy Ind Ltd ガスタービン尾筒の冷却構造
EP1731715A1 (fr) * 2005-06-10 2006-12-13 Siemens Aktiengesellschaft Transition d'une chambre de combustion à une turbine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3511577A (en) * 1968-04-10 1970-05-12 Caterpillar Tractor Co Turbine nozzle construction
GB1488481A (en) * 1973-10-05 1977-10-12 Rolls Royce Gas turbine engines
GB1578474A (en) * 1976-06-21 1980-11-05 Gen Electric Combustor mounting arrangement
US4244178A (en) * 1978-03-20 1981-01-13 General Motors Corporation Porous laminated combustor structure
DE59709701D1 (de) * 1997-09-15 2003-05-08 Alstom Switzerland Ltd Plattformkühlung für Gasturbinen
US7234304B2 (en) * 2002-10-23 2007-06-26 Pratt & Whitney Canada Corp Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine
US7000406B2 (en) * 2003-12-03 2006-02-21 Pratt & Whitney Canada Corp. Gas turbine combustor sliding joint

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3286461A (en) * 1965-07-22 1966-11-22 Gen Motors Corp Turbine starter and cooling
JP2005030680A (ja) * 2003-07-14 2005-02-03 Mitsubishi Heavy Ind Ltd ガスタービン尾筒の冷却構造
EP1731715A1 (fr) * 2005-06-10 2006-12-13 Siemens Aktiengesellschaft Transition d'une chambre de combustion à une turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016116222A1 (de) 2016-08-31 2018-03-01 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine

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EP1899582A1 (fr) 2008-03-19
WO2007003629A1 (fr) 2007-01-11
CN101208497A (zh) 2008-06-25
CN101208497B (zh) 2011-06-15
EP1741877A1 (fr) 2007-01-10

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