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EP3816402B1 - Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble de stator - Google Patents

Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble de stator Download PDF

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Publication number
EP3816402B1
EP3816402B1 EP19425078.3A EP19425078A EP3816402B1 EP 3816402 B1 EP3816402 B1 EP 3816402B1 EP 19425078 A EP19425078 A EP 19425078A EP 3816402 B1 EP3816402 B1 EP 3816402B1
Authority
EP
European Patent Office
Prior art keywords
leading
stator
stator assembly
annular
primary
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
EP19425078.3A
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German (de)
English (en)
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EP3816402A1 (fr
Inventor
Marco TAPPANI
Vera D'Oriano
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.)
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia SpA
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 Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Priority to EP19425078.3A priority Critical patent/EP3816402B1/fr
Priority to CN202011217289.4A priority patent/CN112780359A/zh
Publication of EP3816402A1 publication Critical patent/EP3816402A1/fr
Application granted granted Critical
Publication of EP3816402B1 publication Critical patent/EP3816402B1/fr
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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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the present invention relates to a stator assembly for a gas turbine and to a gas turbine comprising said stator assembly.
  • the gas turbine of the present invention is part of a plant for the production of electrical energy.
  • a gas turbine for power plants comprises a compressor, a combustor and a turbine.
  • the compressor comprises an inlet supplied with air and a plurality of rotating blades compressing the passing air.
  • the compressed air leaving the compressor flows into a plenum, i.e. a closed volume delimited by an outer casing, and from there into the combustor.
  • a plenum i.e. a closed volume delimited by an outer casing
  • the compressed air is mixed with at least one fuel and combusted.
  • the resulting hot gas leaves the combustor and expands in the turbine. In the turbine the hot gas expansion moves rotating blades connected to a rotor, performing work.
  • Both the compressor and the turbine comprise a plurality of stator assemblies axially interposed between rotor assemblies.
  • Each rotor assembly comprises a rotor disk rotating about a main axis and a plurality of blades supported by the rotor disk.
  • Each stator assembly comprises a plurality of stator vanes supported by a respective vane carrier and a stator ring arranged about the rotor.
  • a plurality of inter-assembly cavities are defined between the stator assemblies and the rotor assemblies.
  • sealing air is normally bled from the compressor and introduced in said inter-assembly cavities in order to avoid or limit the hot gas ingestion from the hot gas path in the inter-assemblies cavities.
  • the object of the present invention is therefore to provide a stator assembly for a gas turbine, which enables avoiding or at least mitigating the described drawbacks.
  • stator assembly having an improved structure able to minimize the amount of sealing air and guaranteeing, at the same time, a sufficient protection from thermal damages.
  • a stator assembly for a gas turbine comprising:
  • the curved shape of the surface of the leading border facing the primary radial gap deflects the hot gas ingested flow into a confined area: the primary radial gap, where the gas ingested flow can be cooled, managed and washed out again.
  • the present invention allows to confine hot gas inlet in the upper part of the inter-assembly cavity.
  • the presence of at least primary cooling hole in the leading flange improves the thermal status of the upper part of the inter-assembly leading cavity.
  • the primary cooling hole improves the thermal status of the annular leading axial face of the leading wall, which is normally made of a material having poorer properties as compared to the vane.
  • cooling air is provided where it is more needed.
  • the first surface is convex and is curved with a first radius of curvature.
  • the first radius of curvature of the first surface is comprised between 10% and 50% of a distance between the outer axial surface of the platform and a lower point of the annular leading axial face.
  • the leading border comprises a second surface facing the airfoil, which is curved.
  • the second surface is convex and is curved with a second radius of curvature.
  • the stator assembly comprises a connecting surface, which connects the platform and the leading surface; the connecting surface being concave with a third radius of curvature.
  • the hot gas ingested is forced to recirculate inside the primary radial gap creating a vortex.
  • the annular leading axial face of the leading wall is concave with a fourth radius of curvature.
  • the leading flange is provided with a plurality of primary cooling holes circumferentially aligned, which are preferably evenly distributed.
  • the primary cooling hole extends along a primary extension axis; on a longitudinal axial plane defined by the longitudinal axis and a radial direction orthogonal to the longitudinal axis and intersecting the primary extension axis, a first angle defined by a projection of the primary extension axis on the longitudinal axial plane and the radial direction is comprised between 70° and 110°.
  • the primary cooling hole extends along a primary extension axis; on a circumferential plane defined by the longitudinal axis and a circumferential direction, which is orthogonal to the longitudinal axis and orthogonal to a radial direction in turn orthogonal to the longitudinal axis, a second angle is defined by a projection of the primary extension axis on the circumferential plane and an axial direction of the longitudinal axis is comprised between 100° and 200°.
  • reference numeral 1 indicates a gas turbine electric power plant (schematically shown in Figure 1 ).
  • the plant 1 comprises a compressor 3, a combustion chamber 4, a gas turbine 5 and a generator (for simplicity, not show in the attached figures).
  • the compressor 3, turbine 5 and generator (not shown) are mounted on the same shaft to form a rotor 8, which is housed in stator casings 9 and extends along an axis A.
  • the rotor 8 comprises a front shaft 10, a plurality of rotor assemblies 11 and a rear shaft 13.
  • Each rotor assembly 11 comprises a rotor disk 15 and a plurality of rotor blades 16 coupled to the rotor disk 15 and radially arranged.
  • the plurality of rotor disks 15 are arranged in succession between the front shaft 10 and the rear shaft 13 and preferably clamped as a pack by a central tie rod 14. As an alternative, the rotor disks may be welded together.
  • a central shaft 17 separates the rotor disks 15 of the compressor 3 from the rotor disks 15 of the turbine 5 and extends through the combustion chamber 4.
  • stator assemblies 22 are alternated with the compressor rotor assemblies 11.
  • Each stator assembly 22 comprises a stator ring 24 and a plurality of stator vanes 25, which are radially arranged and coupled to the stator ring 24 and to the respective stator casing 9.
  • FIG 2 an enlarged view of a stator assembly 22 between two rotor assemblies 11 in the turbine 5 is shown.
  • Arrow D indicates the direction of the hot gas flow flowing in a hot gas channel 18 of the turbine 5.
  • inter-assembly cavities 27 are arranged.
  • each stator assembly 22 defines a leading inter-assembly cavity 27a and a trailing inter-assembly cavity 27b, wherein the leading inter-assembly cavity 27a is upstream the trailing inter-assembly cavity 27b along the hot gas flow direction D.
  • stator ring 24 extends about the longitudinal axis A and comprises an inner edge 28 and an outer edge 29, which is provided with an annular groove 30.
  • the plurality of stator vanes 25 are coupled alongside one another to the outer edge 29 of the stator ring 24 so as to close the annular groove 30 and define an annular cooling channel 32.
  • the annular cooling channel 32 is fed with air preferably coming from the compressor 3.
  • the annular groove 30 defines a leading wall 34 and a trailing wall 35.
  • the leading wall 34 is upstream the trailing wall 35 along the hot gas flow direction D.
  • leading wall 34 is provided with a plurality of cooling openings 36 in fluidic communication with the annular cooling channel 32.
  • the cooling openings 36 are arranged in the proximity of the inner edge 28.
  • cooling openings 36 are circumferentially aligned and evenly distributed.
  • the trailing wall is provided with the cooling openings in fluidic communication with the annular cooling channel.
  • Each stator vane 25 comprises an airfoil 38, an outer shroud 39 and an inner shroud 40 coupled to the stator ring 24.
  • the airfoil 38 is provided with a cooling air duct 41a fed by a dedicated opening 41b on the outer shroud 39.
  • the outer shroud 39 is coupled to the respective stator casing 9.
  • the inner shroud 40 comprises a platform 42, a leading flange 43 and a trailing flange 44 extending radially inward from the platform 42.
  • the leading flange 43 is upstream the trailing flange 44 along the hot gas flow direction D.
  • leading flange 43 is coupled to the leading wall 34, while the trailing flange 44 is coupled to the trailing wall 35.
  • leading flange 43 engages a respective annular seat 46 of the leading wall 34, while the trailing flange 44 engages a respective annular seat 47 of the trailing wall 35.
  • leading flange 43 is coupled to the leading wall 34 so as to leave a primary radial gap 48 between the leading wall 34 and the platform 42 and to define a leading surface 50 of the leading flange 43 facing said primary radial gap 48.
  • the trailing flange 44 is coupled to the trailing wall 35 so as to leave a secondary radial gap 52 between the trailing wall 35 and the platform 42 and to define a trailing surface 53 of the trailing flange 44 facing said secondary radial gap 52.
  • the platform 42 comprises a leading border 54a and a trailing border 54b extending circumferentially.
  • the leading border 54a is upstream the trailing border 54b along the hot gas flow direction D.
  • the leading flange 43 is provided, on the leading surface 50, with at least one primary cooling hole 55 in fluid communication with the annular cooling channel 32.
  • leading flange 43 is provided, on the leading surface 50, with a plurality of primary cooling holes 55 circumferentially aligned.
  • the primary cooling holes 55 are evenly distributed.
  • each primary cooling hole 55 extends along a primary extension axis Op.
  • an angle ⁇ is defined by the projection of the primary extension axis Op on the longitudinal axial plane A-R and the radial direction R.
  • the angle ⁇ is measured from the radial direction R to the projection of the primary extension axis Op in accordance with the hot gas flow direction D.
  • the angle ⁇ of the primary cooling holes 55 is comprised between 70° and 110°.
  • an angle ⁇ is defined by the projection of the primary extension axis O P on the circumferential plane A-C and the axial direction A.
  • the angle ⁇ is measured from the axial direction A to the projection of the primary extension axis O P on the tangential plane A-C in a clockwise direction looking radially inward.
  • the angle ⁇ is comprised between 100° and 200°.
  • the primary cooling holes 55 have different angles ⁇ and/or different angles ⁇ .
  • primary cooling holes can be substantially identical to each other.
  • leading wall 34 is provided with an annular leading radial face 56 and with an annular leading axial face 57.
  • the annular leading axial face 57 of the leading wall 34 is concave with radius of curvature r4.
  • the leading border 54a comprises at least one surface 61 facing the primary radial gap 48 and at least one surface 60 facing the airfoil 18.
  • the surface 61 faces, in use, the leading inter-assembly cavity 27a and the surface 60 faces the hot gas channel 18.
  • the surface 60 and the surface 61 are curved.
  • surface 60 and surface 61 are contiguous.
  • the surface 60 has a radius of curvature r1 and is convex.
  • the surface 61 has a radius of curvature r2 and is convex too.
  • the stator assembly 22 comprises also a connecting surface 65, which connects the platform 42 and the leading surface 50.
  • the connecting surface 65 is concave with a third radius of curvature r3.
  • the connecting surface is not rounded and has a triangular section along the longitudinal axial plane.
  • the radius of curvature r1 of the surface 60 is comprised between 5% and 40% of the distance h between the outer axial surface 59 of the platform and the lower point T of the annular leading axial face 57.
  • the radius of curvature r2 of the surface 61 is comprised between 10% and 50% of the distance h between the outer axial surface 59 of the platform and the lower point T of the annular leading axial face 57.
  • the radius of curvature r3 of the connecting surface 65 is comprised between 20% and 40% of the distance h between the outer axial surface 59 of the platform and the lower point T of the annular leading axial face 57.
  • the radius of curvature r4 of the annular leading axial face 57 is comprised between 45% and 60% of the distance h between the outer axial surface 59 of the platform and the lower point T of the annular leading axial face 57.
  • the axial distance s between the outermost point P of the leading border 54a and the outermost point Q of the annular leading axial face 57 is comprised between - 50% and +50% of the axial length L of the leading inter-assembly cavity 27a ( figure 2 ).
  • the leading surface 50 has a planar and radially arranged portion arranged radially inward. While the portion of the leading surface 50 arranged radially outward the primary cooling holes 55 and connected to the connecting surface 65 is tangential to the connecting surface 65.
  • the hot gas flowing in the hot gas channel 18 is ingested in the leading and flows in to the primary radial gap 48.
  • the hot gas ingested flow is first deflected by the leading border 54a, then is forced to recirculate inside the primary radial gap 48 creating a vortex.
  • the primary cooling holes 55 cool the hot gas ingested flow and push it back outside the inter-assembly cavity 27a, by energizing the vortex recirculation and exploiting the pumping effect on the rotor side.
  • Secondary cooling openings 36 on the leading wall 34 provide also a film-cooling effect on the upper edge of the stator ring 24.

Landscapes

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

Claims (14)

  1. Ensemble stator (22) d'une turbine à gaz comprenant :
    une roue de stator (24), qui s'étend autour d'un axe longitudinal (A), et qui comprend un bord extérieur (29) doté d'une rainure annulaire (30) ; la rainure annulaire (30) définissant une paroi d'attaque (34) et une paroi de fuite (35) ; la paroi d'attaque (34) étant dotée d'une face radiale d'attaque annulaire (56) et d'une face axiale d'attaque annulaire (57) ; une pluralité d'aubes de stator (25) agencées radialement et accouplées les unes aux autres au bord extérieur (29) de la roue de stator (24) afin de fermer la rainure annulaire (30) et de définir un canal de refroidissement annulaire (32) ; chaque aube de stator (25) comprend un profil aérodynamique (38), une enveloppe extérieure (39) et une enveloppe intérieure (40) accouplées à la roue de stator (24) ; l'enveloppe intérieure (40) comprenant une plate-forme (42), une bride d'attaque (43) et une bride de fuite (44) s'étendant radialement vers l'intérieur à partir de la plate-forme (42) ; la bride d'attaque (43) étant accouplée à la paroi d'attaque (34), et la bride de fuite (44) étant accouplée à la paroi de fuite (35) ; la bride d'attaque (43) étant accouplée à la paroi d'attaque (34) afin de laisser un intervalle radial primaire (48) entre la paroi d'attaque (34) et la plate-forme (42), et de définir une surface d'attaque (50) de la bride d'attaque (43) ; la plate-forme (42) présentant une bordure d'attaque (54a) et une bordure de fuite (54b), toutes deux s'étendant de manière circonférentielle ; la bordure d'attaque (54a) comprenant au moins une première surface (61) qui fait face à l'intervalle radial primaire (48) ; la première surface (61) étant incurvée ;
    l'ensemble stator étant caractérisé en ce que la bride d'attaque (43) est disposée sur la surface d'attaque (50), un trou de refroidissement primaire (55) au moins étant en communication de fluide avec le canal de refroidissement annulaire (32).
  2. Stator selon la revendication 1, dans lequel la première surface (61) est convexe.
  3. Ensemble stator selon la revendication 2, dans lequel la première surface (61) est incurvée avec un premier rayon de courbure (r2).
  4. Ensemble stator selon la revendication 3, dans lequel le rayon de courbure (r2) de la surface (61) est compris entre 10 % et 50 % de la distance (h) entre une surface axiale extérieure (59) de la plate-forme, et le point le plus bas (T) de la face axiale d'attaque annulaire (57).
  5. Ensemble stator selon l'une quelconque des revendications précédentes, dans lequel la bordure d'attaque (54a) comprend une seconde surface (60) qui fait face au profil aérodynamique (18), qui est incurvée.
  6. Stator selon la revendication 5, dans lequel la seconde surface (60) est convexe.
  7. Ensemble stator selon la revendication 6, dans lequel la seconde surface (60) est incurvée avec un deuxième rayon de courbure (r1).
  8. Ensemble stator selon l'une quelconque des revendications précédentes, comprenant une surface de connexion (65), qui connecte la plate-forme (42) et la surface d'attaque (50) ; la surface de connexion (65) étant concave avec un troisième rayon de courbure (r3).
  9. Ensemble stator selon l'une quelconque des revendications précédentes, dans lequel la face axiale d'attaque annulaire (57) de la paroi d'attaque (34), est concave avec un quatrième rayon de courbure (r4).
  10. Ensemble stator selon l'une quelconque des revendications précédentes, dans lequel la bride d'attaque (43) est disposée sur la surface d'attaque (50), une pluralité de trous de refroidissement primaires (55) étant alignés de manière circonférentielle.
  11. Ensemble stator selon la revendication 10, dans lequel les trous de refroidissement primaires (55) sont répartis de manière régulière.
  12. Ensemble stator selon l'une quelconque des revendications précédentes, dans lequel le trou de refroidissement primaire (55) s'étend le long d'un axe d'extension primaire (Op) ; dans un plan axial longitudinal (A-R) défini par l'axe longitudinal (A) et une direction radiale (R) orthogonale à l'axe longitudinal (A) et coupant l'axe d'extension primaire (Op), un premier angle (α) défini par la projection de l'axe d'extension primaire (Op) sur le plan axial longitudinal (A-R) et la direction radiale (R), est compris entre 70° et 110°.
  13. Ensemble stator selon l'une quelconque des revendications précédentes, dans lequel le trou de refroidissement primaire (55) s'étend le long d'un axe d'extension primaire (Op) ; dans un plan circonférentiel défini par l'axe longitudinal (A) et une direction circonférentielle (C), qui est orthogonale à l'axe longitudinal (A), et orthogonale à une direction radiale (R), orthogonale à son tour à l'axe longitudinal (A), un second angle (θ) est défini par une projection de l'axe d'extension primaire (Op) sur le plan circonférentiel, et une direction axiale de l'axe longitudinal (A), est compris entre 100° et 200°.
  14. Turbine à gaz s'étendant le long d'un axe longitudinal (A) et comprenant :
    une pluralité d'ensembles rotors (11), chacun d'eux comprenant une roue de rotor (15) et une pluralité d'aubes de rotor (16) agencées radialement, et accouplées à la roue de rotor (15) ;
    une pluralité d'ensembles stators (22) ; les ensembles stators (22) et les ensembles rotors (11) sont alternés le long d'une direction axiale de l'axe longitudinal (A) ;
    l'un au moins des ensembles stators (22) étant selon l'une quelconque des revendications précédentes.
EP19425078.3A 2019-11-04 2019-11-04 Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble de stator Active EP3816402B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP19425078.3A EP3816402B1 (fr) 2019-11-04 2019-11-04 Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble de stator
CN202011217289.4A CN112780359A (zh) 2019-11-04 2020-11-04 用于燃气涡轮的定子组件和包括所述定子组件的燃气涡轮

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19425078.3A EP3816402B1 (fr) 2019-11-04 2019-11-04 Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble de stator

Publications (2)

Publication Number Publication Date
EP3816402A1 EP3816402A1 (fr) 2021-05-05
EP3816402B1 true EP3816402B1 (fr) 2023-01-04

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ID=68887365

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19425078.3A Active EP3816402B1 (fr) 2019-11-04 2019-11-04 Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble de stator

Country Status (2)

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EP (1) EP3816402B1 (fr)
CN (1) CN112780359A (fr)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6481959B1 (en) * 2001-04-26 2002-11-19 Honeywell International, Inc. Gas turbine disk cavity ingestion inhibitor
US8262342B2 (en) * 2008-07-10 2012-09-11 Honeywell International Inc. Gas turbine engine assemblies with recirculated hot gas ingestion
US9062557B2 (en) * 2011-09-07 2015-06-23 Siemens Aktiengesellschaft Flow discourager integrated turbine inter-stage U-ring
WO2015104695A1 (fr) * 2014-01-13 2015-07-16 Ansaldo Energia S.P.A. Aube pour turbine à gaz et son procédé de fabrication

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Publication number Publication date
EP3816402A1 (fr) 2021-05-05
CN112780359A (zh) 2021-05-11

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