EP3663522A1 - Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung - Google Patents

Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung Download PDF

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Publication number
EP3663522A1
EP3663522A1 EP18425095.9A EP18425095A EP3663522A1 EP 3663522 A1 EP3663522 A1 EP 3663522A1 EP 18425095 A EP18425095 A EP 18425095A EP 3663522 A1 EP3663522 A1 EP 3663522A1
Authority
EP
European Patent Office
Prior art keywords
leading edge
primary
annular
trailing edge
stator
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP18425095.9A
Other languages
English (en)
French (fr)
Other versions
EP3663522B1 (de
Inventor
Francesco BAVASSANO
Marco TAPPANI
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 EP18425095.9A priority Critical patent/EP3663522B1/de
Priority to RU2019139258A priority patent/RU2795241C2/ru
Priority to CN201911242895.9A priority patent/CN111287803B/zh
Publication of EP3663522A1 publication Critical patent/EP3663522A1/de
Application granted granted Critical
Publication of EP3663522B1 publication Critical patent/EP3663522B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection 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
    • F01D9/04—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
    • F01D11/001—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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

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.
  • minimization of the amount of air spent to seal and cool the inter-assembly cavities is beneficial to the power plant performance.
  • said minimization implies the use of expensive advanced materials and/or the adoption of arrangements having a very complex geometry.
  • 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 presence of at least primary cooling hole in the leading edge flange improves the thermal status of the upper part of the inter-assembly leading edge cavity.
  • the primary cooling hole improves the thermal status of the annular leading edge axial face of the leading edge 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 present invention allows to confine hot gas inlet in the upper part of the inter-assembly cavity.
  • the stator assembly comprises a plurality of primary cooling holes circumferentially aligned. In this way the cooling air could be provided along a circumferential direction.
  • the primary cooling holes are evenly distributed. In this way the cooling air in uniformly 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, the angle defined by the projection of the primary extension axis on the longitudinal axial plane and the radial direction is preferably comprised between 80° and 135°, while 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 orthogonal to the longitudinal axis, the angle defined by the projection of the primary extension axis on the circumferential plane and the axial direction is preferably comprised between 100° and 200°.
  • the primary baffle has an inner face facing the at least one primary cooling hole and an outer face opposite to the inner face; the primary baffle protruding radially from the annular leading edge axial face so as the outer face is an extension of the annular leading edge radial face.
  • the baffle is easy to make and creates a recirculation zone sufficiently large.
  • the primary baffle has at least one rounded connection to the annular leading edge axial face, which is preferably concave. In this way the deflection of flow induced by the baffle is improved. Specifically, rounded connection allows the recirculating hot gas ingested to be blown out from the cavity to the main stream.
  • the primary baffle has an inner face facing the at least one primary cooling hole and an outer face opposite to the inner face; wherein the primary baffle comprises at least one fin protruding axially from the outer face.
  • the fin defines a sort of barrier for the entry of hot gas in the inter-assembly cavity.
  • the fin drives the hot gas in the recirculation zone towards the main flow in the gas turbine channel avoiding the entry of said hot gas in the inter-assembly cavity.
  • the primary baffle comprises at least one fin protruding from the outer face in a direction which forms, on a radial plane, an angle ⁇ with respect to the axial direction. In this way, the driving action of the fin on the hot gas in the recirculation zone towards the main flow is improved.
  • the primary baffle is made integral with the stator ring. In this way the time and costs to realize the stator assembly are reduced.
  • the primary baffle is made of a material different from the one of the stator ring.
  • the baffle can be made of a material having high thermomechanical properties with respect to the material used for realizing the stator ring.
  • the trailing edge flange is coupled to the trailing edge wall so as to leave a secondary radial gap between the trailing edge wall and the platform and define a trailing edge surface of the trailing edge flange; the trailing edge flange being provided, on the trailing edge surface, with at least one secondary cooling hole in fluid communication with the annular cooling channel.
  • the trailing edge wall is provided with an annular trailing edge radial face and with an annular trailing edge axial face; the trailing edge wall comprising a secondary baffle protruding radially from the annular trailing edge axial face and axially facing the at least one secondary cooling hole. Thanks to the presence of a secondary baffle facing the secondary cooling hole some hot gas can be ingested in the zone comprising the secondary radial gap from the main hot gas flow. This zone, in fact, is sufficiently cooled by cooling air coming from the secondary cooling holes. Moreover the secondary baffle deflects the flow of hot gas air ingested outside the zone comprising the secondary radial gap.
  • the ingested hot gas is therefore purged by the cooling hole and then expelled by means of the secondary baffle.
  • 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 the turbine 5.
  • inter-assembly cavities 27 are arranged.
  • each stator assembly 22 defines a leading edge inter-assembly cavity 27a and a trailing edge inter-assembly cavity 27b, wherein the leading edge inter-assembly cavity 27a is upstream the trailing edge 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 edge wall 34 and a trailing edge wall 35.
  • the leading edge wall 34 is upstream the trailing edge wall 35 along the hot gas flow direction D.
  • leading edge 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 edge 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 edge flange 43 and a trailing edge flange 44 extending radially inward from the platform 42.
  • the leading edge flange 43 is upstream the trailing edge flange 44 along the hot gas flow direction D.
  • leading edge flange 43 is coupled to the leading edge wall 34, while the trailing edge flange 44 is coupled to the trailing edge wall 35.
  • leading edge flange 43 engages a respective annular seat 46 of the leading edge wall 34, while the trailing edge flange 44 engages a respective annular seat 47 of the trailing edge wall 35.
  • leading edge flange 43 is coupled to the leading edge wall 34 so as to leave a primary radial gap 48 between the leading edge wall 34 and the platform 42 and to define a leading edge surface 50 of the leading edge flange 43 facing said primary radial gap 48.
  • the trailing edge flange 44 is coupled to the trailing edge wall 35 so as to leave a secondary radial gap 52 between the trailing edge wall 35 and the platform 42 and to define a trailing edge surface 53 of the trailing edge flange 44 facing said secondary radial gap 52.
  • the leading edge flange 43 is provided, on the leading edge surface 50, with at least one primary cooling hole 55 in fluid communication with the annular cooling channel 32.
  • leading edge flange 43 is provided, on the leading edge 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 O.
  • 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 ⁇ of the primary cooling holes 55 is comprised between 80° and 135°.
  • an angle is defined by the projection of the primary extension axis Op on the circumferential plane A-C and the axial direction A. preferably, 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 edge wall 34 is provided with an annular leading edge radial face 56 and with an annular leading edge axial face 57.
  • the leading edge wall 34 comprises a primary baffle 59 protruding radially outward from the annular leading edge axial face 57 and axially facing the at least one primary cooling hole 55.
  • the radial height w of the primary baffle 59 is comprised between 1% and 60% of a reference radial distance RF defined by the radial distance between the outer axial surface 58 of the platform 42 and the annular leading edge axial face 57.
  • the primary baffle 59 has an inner face 60 facing the at least one primary cooling hole 55 and an outer face 61 opposite to the inner face 50.
  • the primary baffle 59 protrudes radially from the annular leading edge axial face 57 so as the outer face 61 is an extension of the annular leading edge radial face 56.
  • the primary baffle 59 has at least one connection 63, preferably rounded, connecting the primary baffle 59 to the annular leading edge axial face 57.
  • the rounded connection 63 is concave.
  • connection is not rounded and has a triangular section along the longitudinal axial plane.
  • the primary baffle 59 is made integral with the stator ring 24.
  • the primary baffle and the stator ring are separate pieces coupled together. In this way, each piece can be replaced if required.
  • the primary baffle can be made of a material different from the one of the stator ring.
  • the primary baffle can be made of a material having higher thermomechanical properties with respect to the material of the stator ring.
  • the primary baffle and the stator ring can be separate pieces made of the same material.
  • stator ring could be coated with a specific material in order to improve its thermomechanical resistance.
  • the radial distance S between the extension axis O of each primary cooling hole 55 and the annular leading edge axial face 57 is comprised between the 1% and the 40% of the reference radial distance RF defined by the radial distance between the outer axial surface 58 of the platform 42 and the annular leading edge axial face 57. It has to be considered, however, that the radial distance S should obviously have a value that allows the perforation of the leading edge surface 50.
  • the radial distance h between the lower point of the outlet of each primary cooling hole 55 and the annular leading edge axial face 57 is comprised between the 0% and the 20% of the reference radial distance' RF defined by the radial distance between the outer axial surface 58 of the platform 42 and the annular leading edge axial face 57.
  • FIG 6 is illustrated a variant of the present invention wherein the primary baffle 59 comprises at least one fin 65 protruding axially from the outer face 61.
  • the primary baffle 59 comprises at least one fin 66 protruding from the outer face 61 in a direction which forms, on a radial plane A-R defined by the longitudinal axis A and a radial direction R orthogonal to the longitudinal axis A, an angle ⁇ with respect to the axial direction.
  • angle ⁇ is lower than 90°.
  • FIG 8 is illustrated another variant of the present invention wherein the trailing edge flange 44 is provided, on the trailing edge surface 53, with at least one secondary cooling hole 68 in fluid communication with the annular cooling channel 32.
  • the trailing edge flange 44 is provided, on the trailing edge surface 53, with a plurality of secondary cooling holes 68 circumferentially aligned.
  • the secondary cooling holes 68 are evenly distributed.
  • the secondary cooling holes 68 have a passage section smaller than the passage section of the primary cooling holes 55.
  • the trailing edge wall 44 is also provided with an annular trailing edge radial face 70 and with an annular trailing edge axial face 71.
  • the trailing edge wall 44 comprises a secondary baffle 73 protruding radially from the annular trailing edge axial face 71 and axially facing the at least one secondary cooling hole 68.
  • the secondary baffle 73 has an inner face 75 facing the at least one secondary cooling hole 68 and an outer face 76 opposite to the inner face 75.
  • the secondary baffle 73 protrudes radially from the annular trailing edge axial face 71 so as the outer face 76 is an extension of the annular trailing edge radial face 70.
  • the secondary baffle 73 has at least one rounded connection 78 to the annular trailing edge axial face 71.
  • the rounded connection 78 is concave.
  • the secondary baffle 73 is made integral with the stator ring 24.
  • the secondary baffle and the stator ring are separate pieces coupled together.
  • the secondary baffle comprises at least one fin protruding axially from the outer face 76.
  • the secondary baffle comprises at least one fin protruding from the outer face 76 in a direction which forms, on a radial plane A-R defined by the longitudinal axis A and a radial direction R orthogonal to the longitudinal axis A, an angle with respect to the axial direction, which is preferably lower than 90°.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP18425095.9A 2018-12-07 2018-12-07 Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung Active EP3663522B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP18425095.9A EP3663522B1 (de) 2018-12-07 2018-12-07 Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung
RU2019139258A RU2795241C2 (ru) 2018-12-07 2019-12-03 Статорный узел для газовой турбины и газовая турбина, содержащая такой статорный узел
CN201911242895.9A CN111287803B (zh) 2018-12-07 2019-12-06 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
EP18425095.9A EP3663522B1 (de) 2018-12-07 2018-12-07 Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung

Publications (2)

Publication Number Publication Date
EP3663522A1 true EP3663522A1 (de) 2020-06-10
EP3663522B1 EP3663522B1 (de) 2021-11-24

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EP18425095.9A Active EP3663522B1 (de) 2018-12-07 2018-12-07 Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung

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EP (1) EP3663522B1 (de)
CN (1) CN111287803B (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4019742A1 (de) 2020-12-23 2022-06-29 ANSALDO ENERGIA S.p.A. Dichtungsanordnung für einen schaufelsatz eines gasturbinenmotors und gasturbinenmotor mit einer solchen dichtungsanordnung
EP4621190A1 (de) * 2024-03-13 2025-09-24 Rolls-Royce plc Deckband einer gasturbine und verfahren zur herstellung davon

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0864728A2 (de) * 1997-03-11 1998-09-16 Mitsubishi Heavy Industries, Ltd. Kühlluftzufuhrsystem für die Schaufeln einer Gasturbine
US20130058756A1 (en) * 2011-09-07 2013-03-07 Kok-Mun Tham Flow discourager integrated turbine inter-stage u-ring
WO2015104695A1 (en) * 2014-01-13 2015-07-16 Ansaldo Energia S.P.A. Blade for a gas turbine and method for manufacturing said blade
DE112015003047T5 (de) * 2014-06-30 2017-03-16 Mitsubishi Hitachi Power Systems, Ltd. Turbinenleitschaufel, turbine und verfahren zum modifizieren einer turbinenleitschaufel

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US3829233A (en) * 1973-06-27 1974-08-13 Westinghouse Electric Corp Turbine diaphragm seal structure
EP1657407B1 (de) * 2004-11-15 2011-12-28 Rolls-Royce Deutschland Ltd & Co KG Verfahren zur Kühlung der äusseren Deckbänder der Rotorschaufeln einer Gasturbine
US8262342B2 (en) * 2008-07-10 2012-09-11 Honeywell International Inc. Gas turbine engine assemblies with recirculated hot gas ingestion
JP2010077868A (ja) * 2008-09-25 2010-04-08 Mitsubishi Heavy Ind Ltd ガスタービンのリムシール構造
JP5449225B2 (ja) * 2011-02-08 2014-03-19 株式会社日立製作所 ガスタービン
JP5885935B2 (ja) * 2011-04-19 2016-03-16 三菱重工業株式会社 タービン静翼およびガスタービン
EP2759675A1 (de) * 2013-01-28 2014-07-30 Siemens Aktiengesellschaft Turbinenbaugruppe mit verbesserter Abdichtwirkung einer Dichtungsanordnung
EP2824279B1 (de) * 2013-07-09 2019-04-03 MTU Aero Engines GmbH Strömungsmaschine mit Dichtungsstruktur
US9765699B2 (en) * 2014-12-30 2017-09-19 General Electric Company Gas turbine sealing

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0864728A2 (de) * 1997-03-11 1998-09-16 Mitsubishi Heavy Industries, Ltd. Kühlluftzufuhrsystem für die Schaufeln einer Gasturbine
US20130058756A1 (en) * 2011-09-07 2013-03-07 Kok-Mun Tham Flow discourager integrated turbine inter-stage u-ring
WO2015104695A1 (en) * 2014-01-13 2015-07-16 Ansaldo Energia S.P.A. Blade for a gas turbine and method for manufacturing said blade
DE112015003047T5 (de) * 2014-06-30 2017-03-16 Mitsubishi Hitachi Power Systems, Ltd. Turbinenleitschaufel, turbine und verfahren zum modifizieren einer turbinenleitschaufel

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4019742A1 (de) 2020-12-23 2022-06-29 ANSALDO ENERGIA S.p.A. Dichtungsanordnung für einen schaufelsatz eines gasturbinenmotors und gasturbinenmotor mit einer solchen dichtungsanordnung
EP4621190A1 (de) * 2024-03-13 2025-09-24 Rolls-Royce plc Deckband einer gasturbine und verfahren zur herstellung davon

Also Published As

Publication number Publication date
CN111287803B (zh) 2023-07-14
EP3663522B1 (de) 2021-11-24
RU2019139258A (ru) 2021-06-03
CN111287803A (zh) 2020-06-16

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