EP3816405B1 - Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble stator - Google Patents

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

Info

Publication number
EP3816405B1
EP3816405B1 EP19425077.5A EP19425077A EP3816405B1 EP 3816405 B1 EP3816405 B1 EP 3816405B1 EP 19425077 A EP19425077 A EP 19425077A EP 3816405 B1 EP3816405 B1 EP 3816405B1
Authority
EP
European Patent Office
Prior art keywords
trailing
stator
stator assembly
assembly according
annular
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
EP19425077.5A
Other languages
German (de)
English (en)
Other versions
EP3816405A1 (fr
Inventor
Francesco BAVASSANO
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 EP23170966.8A priority Critical patent/EP4230844A1/fr
Priority to EP19425077.5A priority patent/EP3816405B1/fr
Priority to CN202011216063.2A priority patent/CN112780358A/zh
Publication of EP3816405A1 publication Critical patent/EP3816405A1/fr
Application granted granted Critical
Publication of EP3816405B1 publication Critical patent/EP3816405B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F01D11/02—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
    • 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
    • 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
    • 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

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 is 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 preserving, at the same time, the thermal conditions of the stator and rotor parts.
  • the present invention relates to a stator assembly for a gas turbine as claimed in claim 1.
  • trailing cooling holes creates a sealing flow in the trailing inter-assembly cavity interacting with the hot gas flow deriving from the ingestion.
  • each stator vane comprises an airfoil, an outer shroud and an inner shroud coupled to the stator ring; the inner shroud comprising a platform.
  • the radial distance between the center of the outlet of the trailing cooling hole and the inner edge of the stator ring being comprised in the range 0,45.DP and 0,75-DP, wherein DP is the radial distance between the outer face of the platform and the inner edge of the stator ring.
  • the trailing cooling hole extends along an extension axis; on a longitudinal axial plane defined by the longitudinal axis and a radial direction orthogonal to the longitudinal axis and intersecting the extension axis, a first angle defined by the projection of the extension axis on the longitudinal axial plane (A-R) and the radial direction is comprised between 0° and 50°.
  • the trailing cooling hole extends along an extension axis; on a tangential 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 the projection of the extension axis on the tangential plane and the axial direction is comprised between 20° and 70°.
  • the sealing cooling air coming from the trailing cooling holes is directed towards the entrance of the trailing inter-assembly cavity.
  • the inlet of the trailing cooling hole has a diameter comprised between 1 mm and 5 mm.
  • the trailing cooling hole has a constant cross section.
  • the stator ring is provided with a plurality of trailing cooling holes.
  • outlets of the plurality of trailing cooling holes are evenly distributed along the annular trailing radial face.
  • the number of trailing cooling holes is comprised in the range 0,5-NV -2.NV; wherein NV is the number of stator vanes of the stator assembly.
  • the trailing flange is provided on the trailing surface with a plurality of secondary cooling holes circumferentially aligned.
  • the secondary cooling holes are evenly distributed.
  • 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 shown 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.
  • the trailing wall 35 is also provided with an annular trailing radial face 36a and with an annular trailing axial face 36b.
  • leading wall 34 is provided with a plurality of leading cooling holes 37 in fluidic communication with the annular cooling channel 32.
  • the cooling openings 37 are arranged in the proximity of the inner edge 28.
  • cooling openings 37 are circumferentially aligned and evenly distributed.
  • the trailing wall 35 is provided with at least one trailing cooling hole 39 in fluidic communication with the annular cooling channel 32.
  • each trailing cooling hole 39 passes through the trailing wall 35 and has an inlet 40 facing the annular cooling channel 32 and an outlet 41 arranged on the annular trailing radial face 36a facing, in use, the trailing inter-assembly cavity 27b.
  • Each stator vane 25 comprises an airfoil 42, an outer shroud 43 and an inner shroud 44 coupled to the stator ring 24.
  • the airfoil 42 is provided with a cooling air duct 45a fed by a dedicated opening 45b on the outer shroud 43.
  • the outer shroud 43 is coupled to the respective stator casing 9.
  • the inner shroud 44 comprises a platform 46, a leading flange 48 and a trailing flange 49 extending radially inward from the platform 46.
  • the leading flange 48 is upstream the trailing flange 49 along the hot gas flow direction D.
  • leading flange 48 is coupled to the leading wall 34, while the trailing flange 49 is coupled to the trailing wall 35.
  • leading flange 48 engages a respective annular seat 50 of the leading wall 34, while the trailing flange 49 engages a respective annular seat 51 of the trailing wall 35.
  • leading flange 48 is coupled to the leading wall 34 so as to leave a leading radial gap 53 between the leading wall 34 and the platform 46 and to define a leading surface 54 of the leading flange 48 facing said leading radial gap 53.
  • the trailing flange 49 is coupled to the trailing wall 35 so as to leave a trailing radial gap 55 between the trailing wall 35 and the platform 46 and to define a trailing surface 56 of the trailing flange 49 facing said trailing radial gap 55.
  • the leading flange 48 is provided, on the leading surface 54, with at least one primary cooling hole 60 in fluid communication with the annular cooling channel 32.
  • leading flange 48 is provided, on the leading surface 54, with a plurality of primary cooling holes 60 circumferentially aligned.
  • the trailing flange 49 is provided, on the trailing surface 56, with at least one secondary cooling hole 61 in fluid communication with the annular cooling channel 32.
  • the trailing flange 49 is provided, on the trailing surface 56, with a plurality of secondary cooling holes 61 circumferentially aligned.
  • the secondary cooling holes 61 are evenly distributed.
  • the secondary cooling holes 61 have a passage section smaller than the passage section of the primary cooling holes 60.
  • the stator assembly 22 preferably comprises a plurality of trailing cooling holes 39, which are evenly distributed and preferably circumferentially aligned on the annular trailing radial face 36a.
  • the number of trailing cooling holes 39 is comprised in the range 0,5 ⁇ NV - 2 ⁇ NV; wherein NV is the number of stator vanes 25 of the stator assembly 22.
  • the distance DH between the centre of the outlet 41 of the cooling hole 39 and the inner edge 28 of the stator ring 24 is comprised in the range 0.45*(DP) e 0.75*(DP), wherein DP is the radial distance between the outer face 46a of the platform 46 and the inner edge 28 of the stator ring 24.
  • the inlet 40 of the trailing cooling hole 39 has preferably a diameter d comprised between 1 mm and 5 mm.
  • the trailing cooling hole 39 has a constant cross section.
  • the trailing cooling hole 39 extends along an extension axis O; on a longitudinal axial plane A-R defined by the longitudinal axis A and a radial direction R orthogonal to the longitudinal axis A and intersecting the extension axis O, a first angle ⁇ defined by the projection of the extension axis O on the longitudinal axial plane A-R and the axial direction is comprised between 0° and 50°.
  • the angle ⁇ is measured from the axial direction A to the projection of the extension axis O in a counter-clockwise direction looking in a tangential direction having on the left the compressor side.
  • a second angle ⁇ is defined by the projection of the extension axis on the tangential plane and the axial direction A.
  • the trailing cooling hole 39 has a tangential inclination (defined by angle ⁇ ), which is concordant with the direction of rotation of the machine W (counter-clock wise around axis A looking from the compressor side).
  • Said second angle ⁇ is preferably comprised between 20° and 70°.
  • the angle ⁇ is measured from the axial direction A to the projection of the extension axis O in a counter-clockwise direction looking in a tangential direction having on the left the compressor side.
  • the hot gas flowing in the hot gas channel 18 is ingested in the trailing inter-assembly cavity 27b. however, thanks to the radial position and inclination of the trailing cooling holes 39, the sealing cooling air coming from the trailing cooling holes 39 is directed towards the entrance of the trailing inter-assembly cavity 27b.
  • the claimed solution allows to enhance the sealing effectiveness and the thermal state of the trailing inter-assembly cavity 27b and therefore to significantly reduce the total sealing air amount spent to seal the trailing inter-assembly cavity 27b, with a consequent improvement in engine performance.

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 (12)

  1. Ensemble stator (22) d'une turbine à gaz comprenant :
    - un anneau de stator (24), qui s'étend autour d'un axe longitudinal (A) et qui comprend un bord intérieur et un bord extérieur (29) ; le bord extérieur étant doté d'une rainure annulaire (30) ; la rainure annulaire (30) définissant une paroi d'attaque (34) et une paroi de fuite (35) ; la paroi de fuite (34) étant dotée d'une face radiale de fuite annulaire (36a) et d'une face axiale de fuite annulaire (36b) ;
    - une pluralité d'aubes de stator (25) agencées radialement et accouplées à côté les unes des autres au bord extérieur (29) de l'anneau de stator (24), pour fermer la rainure annulaire (30) et définir un canal de refroidissement annulaire (32) ;
    l'anneau de stator (24) étant dotée d'au moins un trou de refroidissement de fuite (39) qui présente une entrée (40) qui fait face au canal de refroidissement annulaire (32) et une sortie (41) agencée sur la face radiale de fuite annulaire (36b) ; dans lequel chaque aube de stator (25) comprend un profil aérodynamique (38), un plateau extérieur (43) et un plateau intérieur (44) accouplés à l'anneau de stator (24) ; le plateau intérieur (44) comprenant une plate-forme (46) ; dans lequel le plateau intérieur (44) comprend une bride d'attaque (48) et une bride de fuite (49), toutes deux s'étendant radialement vers l'intérieur à partir de la plate-forme (46) ; la bride d'attaque (48) étant couplée à la paroi d'attaque (34), et la bride de fuite (49) étant accouplée à la paroi de fuite (35) ; la bride de fuite (49) étant couplée à la paroi de fuite (34) pour laisser un intervalle radial de fuite (55) entre la paroi de fuite (35) et la plate-forme (46) et définir une surface de fuite (56) de la bride de fuite (49) faisant face audit intervalle radial de fuite (55) ;
    l'ensemble stator étant caractérisé en ce que la bride de fuite (49) est dotée sur la surface de fuite (56) d'au moins un trou de refroidissement secondaire (61) en communication de fluide avec le canal de refroidissement annulaire (32).
  2. Ensemble stator selon la revendication 1, dans lequel la distance radiale (DH) entre le centre de la sortie (41) du trou de refroidissement de fuite (39) et le bord intérieur (28) de l'anneau de stator (24) se situant dans une plage comprise entre 0,45 × DP et 0,75 × DP, dans lequel DP est la distance radiale entre la face extérieure (46a) de la plate-forme (46) et le bord intérieur (28) de l'anneau de stator (24).
  3. Ensemble stator selon l'une quelconque des revendications précédentes, dans lequel le trou de refroidissement de fuite (39) s'étend le long d'un axe d'extension (O) ; 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 qui coupe l'axe d'extension (O), un premier angle (α) est défini par la projection de l'axe d'extension (O) sur le plan axial longitudinal (AR) et par la direction axiale (A), et est compris de préférence entre 0° et 50°.
  4. Ensemble stator selon l'une quelconque des revendications précédentes, dans lequel le trou de refroidissement de fuite (39) s'étend le long d'un axe d'extension (O) ; dans un plan tangentiel 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 (β) est défini par la projection de l'axe d'extension (O) sur le plan tangentiel et par la direction axiale (A) et est compris de préférence entre 20° et 70°.
  5. Ensemble stator selon l'une quelconque des revendications précédentes, dans lequel l'entrée (40) du trou de refroidissement de fuite (39) présente un diamètre (d) compris entre 1 mm et 5 mm.
  6. Ensemble stator selon l'une quelconque des revendications précédentes, dans lequel le trou de refroidissement de fuite (39) présente une section transversale constante.
  7. Ensemble stator selon l'une quelconque des revendications précédentes, dans lequel l'anneau de stator (24) est doté d'une pluralité de trous de refroidissement de fuite (39).
  8. Ensemble stator selon la revendication 7, dans lequel les sorties de la pluralité de trous de refroidissement de fuite (39) sont réparties de manière régulière le long de la face radiale de fuite annulaire (36b).
  9. Ensemble stator selon la revendication 7 ou 8, dans lequel le nombre de trous de refroidissement de fuite (39) se situe dans la plage comprise entre 0,5 × NV et 2 × NV ; dans lequel NV est le nombre d'aubes de stator de l'ensemble stator (24).
  10. Ensemble stator selon l'une quelconque des revendications précédentes, dans lequel la bride de fuite (49) est dotée, sur la surface de fuite (56), d'une pluralité de trous de refroidissement secondaires (61) alignés de manière circonférentielle.
  11. Ensemble stator selon la revendication 10, dans lequel les trous de refroidissement secondaires (61) sont répartis de manière régulière.
  12. Turbine à gaz s'étendant le long d'un axe longitudinal (A), et comprenant :
    une pluralité d'ensembles rotors (11), chacun d'eux comprenant un disque de rotor (15) et une pluralité de pales de rotor (16) agencées radialement et couplées au disque de rotor (15) ;
    une pluralité d'ensembles stators (22) ; les ensembles stators (22) et les ensembles rotors (11) sont alternés le long de la direction axiale (A) ;
    l'un au moins des ensembles stators (22) étant du type revendiqué selon l'une quelconque des revendications précédentes.
EP19425077.5A 2019-11-04 2019-11-04 Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble stator Active EP3816405B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP23170966.8A EP4230844A1 (fr) 2019-11-04 2019-11-04 Ensemble stator pour une turbine à gaz et turbine à gaz comprenant ledit ensemble stator
EP19425077.5A EP3816405B1 (fr) 2019-11-04 2019-11-04 Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble stator
CN202011216063.2A CN112780358A (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
EP19425077.5A EP3816405B1 (fr) 2019-11-04 2019-11-04 Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble stator

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP23170966.8A Division EP4230844A1 (fr) 2019-11-04 2019-11-04 Ensemble stator pour une turbine à gaz et turbine à gaz comprenant ledit ensemble stator

Publications (2)

Publication Number Publication Date
EP3816405A1 EP3816405A1 (fr) 2021-05-05
EP3816405B1 true EP3816405B1 (fr) 2023-05-03

Family

ID=68887364

Family Applications (2)

Application Number Title Priority Date Filing Date
EP23170966.8A Pending EP4230844A1 (fr) 2019-11-04 2019-11-04 Ensemble stator pour une turbine à gaz et turbine à gaz comprenant ledit ensemble stator
EP19425077.5A Active EP3816405B1 (fr) 2019-11-04 2019-11-04 Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble stator

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP23170966.8A Pending EP4230844A1 (fr) 2019-11-04 2019-11-04 Ensemble stator pour une turbine à gaz et turbine à gaz comprenant ledit ensemble stator

Country Status (2)

Country Link
EP (2) EP4230844A1 (fr)
CN (1) CN112780358A (fr)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3182343B2 (ja) * 1996-07-09 2001-07-03 株式会社日立製作所 ガスタービン静翼及びガスタービン
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
JP6344869B2 (ja) * 2014-06-30 2018-06-20 三菱日立パワーシステムズ株式会社 タービン静翼、タービン、及び、タービン静翼の改造方法
US9771820B2 (en) * 2014-12-30 2017-09-26 General Electric Company Gas turbine sealing
KR102028591B1 (ko) * 2018-01-08 2019-10-04 두산중공업 주식회사 터빈 베인 조립체 및 이를 포함하는 가스터빈

Also Published As

Publication number Publication date
CN112780358A (zh) 2021-05-11
EP4230844A1 (fr) 2023-08-23
EP3816405A1 (fr) 2021-05-05

Similar Documents

Publication Publication Date Title
US9765699B2 (en) Gas turbine sealing
EP2586996B1 (fr) Éléments d'aile d'ange d'une aube de turbine pour la commande d'écoulement de cavité avant et procédé associé
US9518478B2 (en) Microchannel exhaust for cooling and/or purging gas turbine segment gaps
US8727735B2 (en) Rotor assembly and reversible turbine blade retainer therefor
US9771820B2 (en) Gas turbine sealing
WO2016057112A1 (fr) Commande de couche limite de passage de diffuseur de compresseur centrifuge
US9366148B2 (en) Assembly of an axial turbomachine and method for manufacturing an assembly of this type
US10619490B2 (en) Turbine rotor blade arrangement for a gas turbine and method for the provision of sealing air in a turbine rotor blade arrangement
EP2904241B1 (fr) Dispositif anti-erreur de joint d'étanchéité de chambre de combustion de turbine à gaz
GB2536628A (en) HPT Integrated interstage seal and cooling air passageways
US11047246B2 (en) Blade or vane, blade or vane segment and assembly for a turbomachine, and turbomachine
EP2649279B1 (fr) Machine à écoulement de fluide, en particulier turbine à gaz pénétrée axialement par un écoulement de gaz chaud
US20170175557A1 (en) Gas turbine sealing
CN110431286B (zh) 用于涡轮机的尖端平衡狭缝
US20140056690A1 (en) Gas turbine
US9765629B2 (en) Method and cooling system for cooling blades of at least one blade row in a rotary flow machine
EP3816405B1 (fr) Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble stator
EP3663522B1 (fr) Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble de stator
JP6961340B2 (ja) 回転機械
EP3816402B1 (fr) Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble de stator
US10738638B2 (en) Rotor blade with wheel space swirlers and method for forming a rotor blade with wheel space swirlers
EP4019742A1 (fr) Ensemble d'étanchéité pour un jeu d'aubes d'un moteur à turbine à gaz et moteur à turbine à gaz comprenant un tel ensemble d'étanchéité

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

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

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20211105

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 9/06 20060101ALI20221012BHEP

Ipc: F01D 9/04 20060101ALI20221012BHEP

Ipc: F01D 5/30 20060101ALI20221012BHEP

Ipc: F01D 11/00 20060101ALI20221012BHEP

Ipc: F01D 11/04 20060101AFI20221012BHEP

INTG Intention to grant announced

Effective date: 20221116

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602019028343

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1564752

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230515

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20230503

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1564752

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230503

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

Ref country code: SE

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

Effective date: 20230503

Ref country code: PT

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

Effective date: 20230904

Ref country code: NO

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

Effective date: 20230803

Ref country code: NL

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

Effective date: 20230503

Ref country code: ES

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

Effective date: 20230503

Ref country code: AT

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

Effective date: 20230503

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

Ref country code: RS

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

Effective date: 20230503

Ref country code: PL

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

Effective date: 20230503

Ref country code: LV

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

Effective date: 20230503

Ref country code: LT

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

Effective date: 20230503

Ref country code: IS

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

Effective date: 20230903

Ref country code: HR

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

Effective date: 20230503

Ref country code: GR

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

Effective date: 20230804

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

Ref country code: FI

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

Effective date: 20230503

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

Ref country code: SK

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

Effective date: 20230503

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

Ref country code: SM

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

Effective date: 20230503

Ref country code: SK

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

Effective date: 20230503

Ref country code: RO

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

Effective date: 20230503

Ref country code: EE

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

Effective date: 20230503

Ref country code: DK

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

Effective date: 20230503

Ref country code: CZ

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

Effective date: 20230503

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602019028343

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

26N No opposition filed

Effective date: 20240206

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

Ref country code: DE

Payment date: 20240130

Year of fee payment: 5

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

Ref country code: SI

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

Effective date: 20230503

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

Ref country code: SI

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

Effective date: 20230503

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

Ref country code: IT

Payment date: 20240130

Year of fee payment: 5

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20240430

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: MC

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

Effective date: 20230503

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

Ref country code: LU

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

Effective date: 20231104

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

Ref country code: CH

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

Effective date: 20231130

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

Effective date: 20231104

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

Ref country code: MC

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

Effective date: 20230503

Ref country code: LU

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

Effective date: 20231104

Ref country code: CH

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

Effective date: 20231130

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20231130