EP4230844A1 - Statoranordnung für eine gasturbine und gasturbine mit der statoranordnung - Google Patents

Statoranordnung für eine gasturbine und gasturbine mit der statoranordnung Download PDF

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Publication number
EP4230844A1
EP4230844A1 EP23170966.8A EP23170966A EP4230844A1 EP 4230844 A1 EP4230844 A1 EP 4230844A1 EP 23170966 A EP23170966 A EP 23170966A EP 4230844 A1 EP4230844 A1 EP 4230844A1
Authority
EP
European Patent Office
Prior art keywords
trailing
stator
annular
stator assembly
assembly according
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.)
Pending
Application number
EP23170966.8A
Other languages
English (en)
French (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/de
Publication of EP4230844A1 publication Critical patent/EP4230844A1/de
Pending legal-status Critical Current

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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
    • 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
    • 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
    • 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.
  • 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 preserving, at the same time, the thermal conditions of the stator and rotor parts.
  • a stator assembly for a gas turbine comprising:
  • trailing cooling holes creates a sealing flow in the trailing inter-assembly cavity interacting with the hot gas flow deriving from the ingestion.
  • the sealing cooling air coming from the trailing cooling holes is directed towards the entrance of the trailing inter-assembly cavity.
  • 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 second 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 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 inner shroud comprises a leading flange and a trailing flange, both extending radially inward from the platform; the leading flange being coupled to the leading wall and the trailing flange being coupled to the trailing wall; the trailing flange being coupled to the trailing wall so as to leave a trailing radial gap between the trailing wall and the platform and to define a trailing surface of the trailing flange facing said trailing radial gap.
  • the trailing flange is provided on the trailing surface with at least one secondary cooling hole in fluid communication with the annular cooling channel.
  • 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, an 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.
  • an 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-clockwise around axis A looking from the compressor side).
  • Said 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.

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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)
EP23170966.8A 2019-11-04 2019-11-04 Statoranordnung für eine gasturbine und gasturbine mit der statoranordnung Pending EP4230844A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP23170966.8A EP4230844A1 (de) 2019-11-04 2019-11-04 Statoranordnung für eine gasturbine und gasturbine mit der statoranordnung

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP23170966.8A EP4230844A1 (de) 2019-11-04 2019-11-04 Statoranordnung für eine gasturbine und gasturbine mit der statoranordnung
EP19425077.5A EP3816405B1 (de) 2019-11-04 2019-11-04 Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
EP19425077.5A Division EP3816405B1 (de) 2019-11-04 2019-11-04 Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung

Publications (1)

Publication Number Publication Date
EP4230844A1 true EP4230844A1 (de) 2023-08-23

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EP23170966.8A Pending EP4230844A1 (de) 2019-11-04 2019-11-04 Statoranordnung für eine gasturbine und gasturbine mit der statoranordnung
EP19425077.5A Active EP3816405B1 (de) 2019-11-04 2019-11-04 Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP19425077.5A Active EP3816405B1 (de) 2019-11-04 2019-11-04 Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung

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EP (2) EP4230844A1 (de)
CN (1) CN112780358A (de)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH1026003A (ja) * 1996-07-09 1998-01-27 Hitachi Ltd 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
US20100008760A1 (en) * 2008-07-10 2010-01-14 Honeywell International Inc. Gas turbine engine assemblies with recirculated hot gas ingestion
DE112015003047T5 (de) * 2014-06-30 2017-03-16 Mitsubishi Hitachi Power Systems, Ltd. Turbinenleitschaufel, turbine und verfahren zum modifizieren einer turbinenleitschaufel
US9771820B2 (en) * 2014-12-30 2017-09-26 General Electric Company Gas turbine sealing
US20190211698A1 (en) * 2018-01-08 2019-07-11 Doosan Heavy Industries & Construction Co., Ltd. Turbine vane assembly and gas turbine including the same

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH1026003A (ja) * 1996-07-09 1998-01-27 Hitachi Ltd 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
US20100008760A1 (en) * 2008-07-10 2010-01-14 Honeywell International Inc. Gas turbine engine assemblies with recirculated hot gas ingestion
DE112015003047T5 (de) * 2014-06-30 2017-03-16 Mitsubishi Hitachi Power Systems, Ltd. Turbinenleitschaufel, turbine und verfahren zum modifizieren einer turbinenleitschaufel
US9771820B2 (en) * 2014-12-30 2017-09-26 General Electric Company Gas turbine sealing
US20190211698A1 (en) * 2018-01-08 2019-07-11 Doosan Heavy Industries & Construction Co., Ltd. Turbine vane assembly and gas turbine including the same

Also Published As

Publication number Publication date
EP3816405A1 (de) 2021-05-05
EP3816405B1 (de) 2023-05-03
CN112780358A (zh) 2021-05-11

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