EP3976934B1 - Procédé de modernisation d'une installation de turbine à gaz et turbine à gaz - Google Patents

Procédé de modernisation d'une installation de turbine à gaz et turbine à gaz Download PDF

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Publication number
EP3976934B1
EP3976934B1 EP20739891.8A EP20739891A EP3976934B1 EP 3976934 B1 EP3976934 B1 EP 3976934B1 EP 20739891 A EP20739891 A EP 20739891A EP 3976934 B1 EP3976934 B1 EP 3976934B1
Authority
EP
European Patent Office
Prior art keywords
cooling
guide vanes
air
guide
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.)
Active
Application number
EP20739891.8A
Other languages
German (de)
English (en)
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EP3976934A1 (fr
Inventor
Harald KUNTE
Robert Kunte
Karen Lee
Michael Wagner
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 Energy Global GmbH and Co KG
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Siemens Energy Global GmbH and Co KG
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Publication of EP3976934A1 publication Critical patent/EP3976934A1/fr
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Publication of EP3976934B1 publication Critical patent/EP3976934B1/fr
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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • 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
    • F05D2240/35—Combustors or associated equipment
    • 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
    • F05D2240/81—Cooled platforms
    • 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

Definitions

  • the present invention relates to a method for modernizing a gas turbine plant.
  • the invention also relates to a gas turbine system.
  • Gas turbine systems are known in the prior art in a wide variety of configurations. They comprise a combustion chamber lined with heat shield elements and a gas turbine, which is arranged downstream of the combustion chamber and comprises guide vanes and rotor blades.
  • Those heat shield elements that are held in the downstream direction directly in front of the gas turbine on the outside of a stationary annular support structure, and blade platforms of the guide vanes of a first guide vane stage held on a stationary support structure define between them a radially inner and a radially outer annular gap due to the design.
  • Cooling air is introduced into these annular gaps via cooling air supply ducts, which supply the guide vanes of the first guide vane stage with cooling air, in order to prevent overheating in particular of the supporting structure, the supporting structure and the areas of said vane platforms facing the annular gap.
  • the introduction of the cooling air into the annular gap usually takes place in the axial direction via cooling air openings formed on the face side of the heat shield elements and distributed uniformly over the circumference of the annular gap. In other words, the cooling air that is used to cool the heat shield elements is also used to cool the annular gap.
  • inhomogeneous pressure fields form in the area of the annular gaps, which are primarily caused by the fact that the hot gas flowing from the combustion chamber into the gas turbine is in the area of the leading edges of the blade leaves of the guide vanes of the first vane stage jams.
  • These inhomogeneous pressure fields have pressure maxima in the area of the leading edges, which cause the hot gas to penetrate into the annular gaps in the area of the leading edges.
  • EP2754858A1 , US2018/195400A1 and US8118554B1 each disclose a gas turbine system with a combustion chamber lined with heat shield elements, with guide vanes arranged downstream, with blade platforms of the guide vanes held on a stationary support structure, the blade platforms being provided with cooling air bores for cooling the guide vanes, the cooling air being fluidically connected to a cooling air supply duct and an annular gap .
  • EP0902164 discloses vanes as turbine inlet vanes.
  • the present invention provides a method for modernizing a gas turbine system that has a combustion chamber lined with heat shield elements and a gas turbine that is arranged downstream of the combustion chamber and includes guide vanes and rotor blades, with those heat shield elements that are located immediately upstream of the gas turbine on the outside of a fixed support structure, and vane platforms of the guide vanes of a first guide vane stage held on one and another fixed support structure define annular gaps between them, the method having the steps of: a) removing all guide vanes of the first guide vane stage; b) Replacing the removed guide vanes of the first guide vane stage with new or overhauled guide vanes, with the platforms of the new or overhauled guide vane being provided with cooling air bores for the first time, which fluidically connect a cooling air supply duct supplying cooling air to the guide vanes of the first guide vane stage with one of the annular gaps and into the corresponding annular gap flow, and The cooling air bores are arranged such that more cooling air bores open into areas of
  • the modernization method according to the invention is applied to gas turbine systems that do not yet have any additional cooling in sections of the annular gaps in the area of the leading edges of the guide vanes of the first guide vane stage or the pressure maxima caused by them, there is a particular advantage in that there is no cutting to produce the cooling air bores Working in situ or on components that are difficult to dismantle, such as must be carried out on the supporting structure in particular, thereby avoiding unnecessary contamination of the gas turbine plant during the implementation of the modernization process. Rather, thanks to the fact that these are provided on one or both blade platforms of the relevant guide vanes, the cooling air bores can be produced outside of the gas turbine system when new guide vanes are produced or when old guide vanes are overhauled.
  • the cooling air ducts extending through the support structure are preferably at least partially closed after step a) has been carried out and before step b) has been carried out, with all cooling air ducts in particular being closed.
  • the positions of the cooling air outlet openings are correct of the cooling channels formed in the support structure no longer correspond to the positions of the pressure maxima, which is why it is no longer possible to reliably prevent hot gas from penetrating into the annular gaps in the area of the leading edges of the guide vanes.
  • the present invention proposes replacing the cooling previously effected by these cooling ducts at least partially, preferably completely, with cooling via the cooling air bores of the new guide vanes installed in step b). In this way, the advantage is also achieved that machining operations in situ or on components of the gas turbine system that are difficult to dismantle are avoided.
  • the cooling air bores formed in airfoil platforms of the new or refurbished vanes define circumferentially spaced sets of cooling air bores, resulting in ease of manufacture of the vanes.
  • surfaces of the blade platforms of the vanes removed in step a) that point in the radial direction are provided with film cooling holes that are fluidically connected to one of the cooling air supply channels when the vanes are installed, and surfaces of the blade platforms that point in the radial direction of the in step b) installed new guide vanes are provided with film cooling holes which are fluidically connected to one of the cooling air supply ducts when the guide vanes are installed, the number of film cooling holes of the new or overhauled guide vanes being less than the number of film cooling holes of the guide vanes removed in step a).
  • the cooling air mass flow saved by reducing the film cooling holes can then be directed in whole or in part through the cooling air holes formed in the airfoil platforms of the new or refurbished vanes.
  • Baffle plates provided with through holes are preferably arranged on blade platforms of the new or overhauled guide vanes, which are designed and arranged in such a way that the cooling air coming from the corresponding cooling air supply duct must pass them in order to reach the film cooling holes. Improved cooling is achieved with such baffle plates.
  • each of the baffles is designed and arranged in such a way that a gap remains between it and the film cooling holes (16).
  • cooling air holes formed in the blade platforms of the new or refurbished vanes are arranged to open into the gap.
  • the present invention creates a gas turbine plant which has a combustor lined with heat shield elements and a gas turbine which is arranged downstream of the combustor and comprises guide vanes and rotating blades, with those heat shield elements which are held in the downstream direction immediately in front of the gas turbine on the outside of a stationary support structure, and on blade platforms of the guide vanes of a first guide vane stage, which are held in one and another stationary support structure, define annular gaps between them, wherein blade platforms of the guide vanes are provided with cooling air bores, which fluidly connect a cooling air supply duct supplying the guide vanes of the first guide vane stage with cooling air to one of the annular gaps and into the corresponding annular gap open out, while facing in the radial direction surfaces of the vane platforms of the guide vanes of the first guide vane stage are provided with film cooling holes, which are fluidically connected to one of the cooling air supply channels when the vanes are installed.
  • More cooling air bores preferably open into regions of an annular gap which are arranged radially inward of the leading edges of the guide vanes than into other regions of the annular gap.
  • the cooling air bores formed in the vane platforms of the guide vanes of the first guide vane stage define circumferentially spaced groups of cooling air bores.
  • the cooling air holes of each cooling air hole group are positioned identically.
  • baffles provided with through holes are arranged on the blade platforms of the guide vanes of the first guide vane stage.
  • Each of the baffles is preferably constructed and arranged such that there is a gap between it and the film cooling holes.
  • Some of the cooling air bores are advantageously arranged in such a way that some of the cooling air bores open into the intermediate space.
  • the gas turbine system 1 shown comprises a combustion chamber 3 lined with heat shield elements 2 and a gas turbine 6 arranged downstream of the combustion chamber 3 and comprising guide vanes 4 and rotor blades 5 vane platforms 11 of the guide vanes 4 of the first guide vane stage, which are held on the stationary support structure 7 on the one hand and on a further stationary support structure 10 on the other hand, define annular gaps 12 between them cooling air openings 13 which extend in the axial direction A and are distributed uniformly over the circumference of the annular gaps 12 in the circumferential direction U and which obtain cooling air via cooling air supply ducts 14 , 15 .
  • the annular gap 12 is cooled via these cooling air openings 13 with cooling air that was previously used to cool the heat shield elements 2 .
  • cooling air ducts 17 extending from the corresponding cooling air supply duct 14, 15 through the supporting structures 7 and 8. These cooling air ducts 17 serve to prevent the entry of Prevent hot gas in the annular gap 12 due to an inhomogeneous pressure distribution in the annular gap 12.
  • This inhomogeneous pressure distribution is caused by the fact that the hot gas accumulates at the leading edges 16 of the guide vanes 4 of the first guide vane stage when it enters the gas turbine 6, as a result of which pressure maxima are generated in the area of the leading edges 16, as a result of which the hot gas is pressed into the annular gaps 12.
  • the guide vane 4 shown which is one of several identically designed guide vanes 4 of the first guide vane stage, is provided with a large number of film cooling holes 19 on the surfaces pointing in the radial direction R.
  • baffle plates 20, not shown provided with through holes, which are designed and arranged in such a way that the cooling air coming from the cooling air supply ducts 14, 15 must be passed through them in order to reach the film cooling holes 19, with between a baffle plate 20 and the film cooling holes 19 an intermediate space 21 is present in each case on a blade platform 11 .
  • the guide vanes 4 must be replaced.
  • the removed guide vanes 4 of the first guide vane stage are replaced by new guide vanes 4.
  • the cooling air ducts 17 extending through the supporting structures 7, 8 also no longer open at the correct positions in order to be able to effectively counteract penetration of hot gas into the annular gaps 12 in the region of the leading edges 16 of the guide vanes 4.
  • the blade platforms 11 of the new vanes 4, one of which in the figures 4 and 5 is shown provided with cooling air bores 22 which fluidly connect the cooling air supply duct 14, 15 with the annular gaps 12 and open into the annular gaps 12.
  • These cooling air bores 22 are arranged in such a way that more cooling air bores 22 open into areas of the annular gaps 12 that are arranged radially in relation to the leading edges 16 of the guide vanes 4 than in other areas of the annular gaps 12.
  • cooling air bores 22 therefore assume the function of the cooling air ducts 17
  • six cooling air bores 22 are provided on each blade platform 11 .
  • the other three cooling air bores 22 enclose an angle ⁇ in the range between 15°-28° with the axial direction and open in the direction of flow of the cooling air in front of the baffle plate 20.
  • the angles ⁇ and ⁇ can have values depending on the design of the guide vane in the range between 0° and 30°.
  • the new guide vanes 4 are provided with film cooling holes 19, but the number of them is smaller than the number of film cooling holes 19 of the removed guide vanes 4.
  • the new guide vanes show 4 fewer film cooling holes 19 than the old guide vanes 4, as can be seen by comparing the Figures 3 and 4 emerges.
  • This has the advantage that part of the cooling air previously used for film cooling is now available for cooling the annular gaps 12, so that the total cooling air flow is not impaired due to the additional cooling air bores 22.
  • the cooling air ducts 17 extending through the supporting structures 7 and 8 can be left as they are. Alternatively, however, they can also be closed before the new guide vanes 4 are installed.
  • a significant advantage associated with the design of the new guide vanes 4 is that no new cooling air ducts 17 have to be introduced into the supporting structures 7, 8 in order to direct the cooling air supply into the annular gaps 12 at the changing positions of the leading edges 16 of the guide vanes 4 and thus adapt to the maximum pressure.
  • no machining operations have to be carried out in situ or on components of the gas turbine system 1 that are difficult to dismantle. Rather, the cooling air bores 22 can be made directly during the manufacture of the new guide vanes 4 .
  • the method described above can also be carried out in gas turbine systems 1 that do not have cooling air ducts 17 that counteract penetration of hot gas into the annular gaps 12 in the area of the leading edges 16 of the guide vanes 4 . Accordingly, the installation of the new guide vanes 4 provides for the first time a corresponding countermeasure against the ingress of hot air due to inhomogeneous pressure distribution, regardless of whether the number of new or overhauled guide vanes 4 is less than, equal to or greater than the number of existing guide vanes 4 of the modernizing gas turbine plant 1 is. Furthermore, it should be clear that the positions, the orientations and the number of the cooling air bores 22 of the new guide vanes 4 can vary.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Procédé de modernisation d'une installation (1) de turbine à gaz,
    qui a une chambre (3) de combustion revêtue d'éléments (2) de bouclier thermique, et
    une turbine (6) à gaz disposée en aval de la chambre de combustion et comprenant des aubes (4) directrices et des aubes (5) mobiles,
    dans lequel les éléments (2) de bouclier thermique,
    qui sont maintenus sur la face extérieure d'une structure (7, 8) porteuse, fixe en emplacement, dans le sens en aval de l'écoulement directement avant la turbine (6) à gaz, et des plateformes (11), maintenues sur une autre structure (7, 10) porteuse fixe en position, des aubes (4) directrices, définissent un premier étage d'aubes directrices entre des intervalles (12) annulaires,
    dans lequel le procédé comporte les stades :
    a) démontage de l'ensemble des aubes (4) directrices du premier étage d'aubes directrices ;
    b) remplacement des aubes (4) directrices démontées du premier étage d'aubes directrices par des aubes (4) directrices neuves ou remises en état,
    dans lequel des plateformes (11) des aubes (4) directrices neuves ou remises en état sont pourvues, pour la première fois, de trous (22) d'air de refroidissement, qui mettent un conduit (14, 15) d'apport d'air de refroidissement, alimentant en air de refroidissement les aubes (4) directrices du premier étage d'aubes directrices, en communication en technique des fluides avec l'un des intervalles (12) annulaires et débouchent dans l'intervalle (12) annulaire correspondant, et
    dans lequel les trous (22) d'air de refroidissement sont disposés de manière à ce que, dans des parties de l'intervalle (12) annulaire ou des intervalles (12) annulaires,
    qui sont disposées dans la direction radiale dans la partie des bords (16) d'attaque des aubes (4) directrices, débouchent plus de trous (22) d'air de refroidissement que dans d'autres parties de l'intervalle (12) annulaire ou des intervalles (12) annulaires.
  2. Procédé suivant la revendication 1,
    caractérisé en ce que
    l'installation (1) de turbine à gaz à moderniser a des conduits (17) d'air de refroidissement s'étendant dans la structure (7, 8) porteuse, mettant entre eux respectivement l'un des conduits (14, 15) d'apport d'air de refroidissement en communication en technique des fluides avec l'un des intervalles (12) annulaire et débouchant dans l'intervalle (12) annulaire correspondant, en ce que le nombre des aubes (4) directrices neuves ou remises en état ne coïncide pas avec le nombre des aubes (4) directrices démontées, et
    en ce que on ferme au moins en partie les conduits (17) d'air de refroidissement s'étendant dans la structure (7, 8) porteuse, après avoir effectué le stade a) et avant d'effectuer le stade b).
  3. Procédé suivant l'une des revendications précédentes,
    caractérisé en ce que
    les trous (22) d'air de refroidissement, formés dans les plateformes (11) des aubes (4) directrices neuves ou remises en état, définissent des groupes de trous d'air de refroidissement disposés à distance les uns des autres sur le pourtour.
  4. Procédé suivant la revendication 3,
    caractérisé en ce que
    les trous (22) d'air de refroidissement de chaque groupe de trous d'air de refroidissement sont mis en de mêmes positions.
  5. Procédé suivant l'une des revendications précédentes,
    caractérisé en ce que
    des surfaces, tournées dans la direction radiale des plateformes (11) des aubes (4) directrices démontées au stade a), sont pourvues de trous (19) de refroidissement pelliculaire,
    qui, dans l'état monté des aubes (4) directrices, communiquent en technique des fluides avec l'un des conduits (14, 15) d'apport d'air de refroidissement,
    en ce que des surfaces, tournées dans la direction radiale des plateformes (11) des aubes (4) directrices neuves montées au stade b), sont pourvues de trous (19) de refroidissement pelliculaire,
    qui, dans l'état monté des aubes (4) directrices communiquent en technique des fluides avec l'un des conduits (14, 15) d'apport d'air de refroidissement,
    dans lequel le nombre des trous (19) de refroidissement pelliculaire des aubes (4) directrices neuves ou remises en état est plus petit que le nombre des trous (19) de refroidissement pelliculaire des aubes (4) directrices démontées au stade a).
  6. Procédé suivant la revendication 5,
    caractérisé en ce que
    dans les plateformes (11) des aubes (4) directrices neuves ou remises en étant sont disposées des tôles (20) de rebondissement, qui sont pourvues de trous de passage et qui sont constituées et disposées de manière à ce que de l'air de refroidissement arrivant du conduit (14, 15) correspondant d'apport d'air de refroidissement doive y passer pour arriver aux trous (19) de refroidissement pelliculaire.
  7. Procédé suivant la revendication 5 et 6,
    caractérisé en ce que
    chacune des tôles (20) de rebondissement est constituée et disposée, de manière à ce qu'il reste un espace (21) intermédiaire entre celle-ci et les trous (19) de refroidissement pelliculaire.
  8. Procédé suivant la revendication 7,
    caractérisé en ce que
    certains des trous (22) d'air de refroidissement, formés dans les plateformes (11) des aubes (4) directrices neuves ou remises en état, sont disposées de manière à déboucher dans l'espace (21) intermédiaire.
  9. Installation (1) de turbine à gaz,
    qui a une chambre (3) de combustion revêtue d'éléments (2) de bouclier thermique, et une turbine (6) à gaz disposée en aval de la chambre (3) de combustion et comprenant des aubes (4) directrices et des aubes (5) mobiles,
    dans lequel les éléments (2) de bouclier thermique, qui sont maintenus sur la face extérieure d'une structure (7, 8) porteuse, fixe en emplacement, dans le sens d'écoulement en aval directement avant la turbine (6) à gaz, et
    des plateformes (11), maintenues sur une autre structure (7, 10) porteuse, fixe en position, des aubes (4) directrices, définissent un premier étage d'aubes directrices entre des intervalles (12) annulaires,
    dans laquelle des plateformes (11) des aubes (4) directrices sont pourvues de trous (22) d'air de refroidissement,
    qui mettent respectivement un conduit (14, 15) d'apport d'air de refroidissement, alimentant en air de refroidissement les aubes (4) directrices du premier étage d'aubes directrices, en communication en technique des fluides avec l'un des intervalles (12) annulaire et débouchent dans l'intervalle (12) annulaire correspondant, dans lequel des surfaces, tournées dans la direction radiale des plateformes (11) des aubes (4) directrices du premier groupe d'aubes directrices, sont pourvues de trous (19) de refroidissement pelliculaire, qui, dans l'état monté des aubes (4) directrices, communiquent en technique des fluides avec l'un des conduit (14, 15) d'apport d'air de refroidissement.
  10. Installation (1) de turbine à gaz suivant la revendication 9,
    caractérisée en ce que
    dans des parties d'un intervalle (12) annulaire, qui sont disposées du côté vers l'intérieur radialement des bords (16) d'attaque des aubes (4) directrices, débouchent plus de trous (22) d'air de refroidissement que dans d'autres parties de l'intervalle (12) annulaire.
  11. Installation (1) de turbine à gaz suivant la revendication 9 ou 10,
    caractérisée en ce que
    les trous (22) d'air de refroidissement, formés dans les plateformes (11) des aubes (4) directrices neuves ou remises en état, définissent des groupes de trous d'air de refroidissement disposés à distance les uns des autres sur le pourtour.
  12. Installation (1) de turbine à gaz suivant la revendication 11,
    caractérisée en ce que
    les trous (22) d'air de refroidissement de chaque groupe de trous d'air de refroidissement sont mis en de mêmes positions.
  13. Installation (1) de turbine à gaz suivant la revendication 12,
    caractérisée en ce que
    dans les plateformes (11) des aubes (4) directrices neuves ou remises en étant sont disposées des tôles (20) de rebondissement, qui sont pourvues de trous de passage, et qui sont constituées et disposées de manière à ce que de l'air de refroidissement arrivant du conduit (14, 15) correspondant d'apport d'air de refroidissement doive y passer pour arriver aux trous (19) de refroidissement pelliculaire.
  14. Installation (1) de turbine à gaz suivant les revendications 12 et 13,
    caractérisée en ce que
    chacune des tôles (20) de rebondissement est constituée et disposée de manière à ce qu'il y ait un espace (21) intermédiaire entre elle et les trous (19) de refroidissement pelliculaire.
  15. Installation (1) de turbine à gaz suivant la revendication 14,
    caractérisée en ce que
    certains des trous (22) d'air de refroidissement sont disposés de manière à déboucher dans l'espace (21) intermédiaire.
EP20739891.8A 2019-07-31 2020-06-29 Procédé de modernisation d'une installation de turbine à gaz et turbine à gaz Active EP3976934B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102019211418.0A DE102019211418A1 (de) 2019-07-31 2019-07-31 Verfahren zur Modernisierung einer Gasturbinenanlage sowie Gasturbinenanlage
PCT/EP2020/068226 WO2021018495A1 (fr) 2019-07-31 2020-06-29 Procédé d'amélioration d'une turbine à gaz et turbine à gaz

Publications (2)

Publication Number Publication Date
EP3976934A1 EP3976934A1 (fr) 2022-04-06
EP3976934B1 true EP3976934B1 (fr) 2023-06-14

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EP20739891.8A Active EP3976934B1 (fr) 2019-07-31 2020-06-29 Procédé de modernisation d'une installation de turbine à gaz et turbine à gaz

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US (1) US11879346B2 (fr)
EP (1) EP3976934B1 (fr)
DE (1) DE102019211418A1 (fr)
WO (1) WO2021018495A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE112022005272T5 (de) 2022-01-06 2024-08-14 Mitsubishi Heavy Industries, Ltd. Turbinenstatorschaufel, Passstruktur und Gasturbine

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3324256B2 (ja) * 1994-02-01 2002-09-17 石川島播磨重工業株式会社 タービン静翼の組立方法
EP0902164B1 (fr) * 1997-09-15 2003-04-02 ALSTOM (Switzerland) Ltd Refroidissement de la platte-forme dans les turbines à gas
US6154959A (en) * 1999-08-16 2000-12-05 Chromalloy Gas Turbine Corporation Laser cladding a turbine engine vane platform
US7775050B2 (en) * 2006-10-31 2010-08-17 General Electric Company Method and apparatus for reducing stresses induced to combustor assemblies
US8973374B2 (en) * 2007-09-06 2015-03-10 United Technologies Corporation Blades in a turbine section of a gas turbine engine
WO2009083456A2 (fr) 2007-12-29 2009-07-09 Alstom Technology Ltd Turbine à gaz
US8118554B1 (en) * 2009-06-22 2012-02-21 Florida Turbine Technologies, Inc. Turbine vane with endwall cooling
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
EP3085900B1 (fr) * 2015-04-21 2020-08-05 Ansaldo Energia Switzerland AG Lèvre abradable pour une turbine à gaz
EP3141702A1 (fr) * 2015-09-14 2017-03-15 Siemens Aktiengesellschaft Segment d'aube directrice de turbine à gaz et procédé de fabrication
US10252790B2 (en) * 2016-08-11 2019-04-09 General Electric Company Inlet assembly for an aircraft aft fan
DE102017212575A1 (de) * 2017-07-21 2019-01-24 Siemens Aktiengesellschaft Verfahren zur Erhöhung der Leistung einer Gasturbine

Also Published As

Publication number Publication date
WO2021018495A1 (fr) 2021-02-04
US20220268172A1 (en) 2022-08-25
EP3976934A1 (fr) 2022-04-06
US11879346B2 (en) 2024-01-23
DE102019211418A1 (de) 2021-02-04

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