EP3816405B1 - Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung - Google Patents
Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung Download PDFInfo
- 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
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- 238000001816 cooling Methods 0.000 claims description 71
- 238000000429 assembly Methods 0.000 claims description 15
- 230000000712 assembly Effects 0.000 claims description 14
- 239000012530 fluid Substances 0.000 claims description 3
- 238000007789 sealing Methods 0.000 description 18
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000037406 food intake Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000008698 shear stress Effects 0.000 description 1
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)
- Statoranordnung (22) für eine Gasturbine, umfassend:• einen Statorring (24), der sich um eine Längsachse (A) erstreckt und einen inneren Rand und einen äußeren Rand (29) umfasst, wobei der äußere Rand mit einer Ringnut (30) versehen ist, wobei die Ringnut (30) eine Vorderwand (34) und eine hintere Wand (35) bildet, wobei die hintere Wand (35) mit einer ringförmigen hinteren Radialfläche (36a) und mit einer ringförmigen hinteren Axialfläche (36b) versehen ist;• eine Vielzahl von Statorschaufeln (25), die radial angeordnet sind und nebeneinander mit dem äußeren Rand (29) des Statorrings (24) gekoppelt sind, sodass sie die Ringnut (30) schließen und einen ringförmigen Kühlkanal (32) bilden;wobei der Statorring (24) mit mindestens einer hinteren Kühlöffnung (39) versehen ist, die einen zu dem ringförmigen Kühlkanal (32) weisenden Einlass (40) und einen an der ringförmigen hinteren Radialfläche (36b) angeordneten Auslass hat, wobei jede Statorschaufel (25) ein Schaufelblatt (38), eine äußere Abdeckung (43) und eine mit dem Statorring (24) gekoppelte innere Abdeckung (44) hat, wobei die innere Abdeckung (44) eine Plattform (46) umfasst, wobei die innere Abdeckung (44) einen Vorderflansch (48) und einen hinteren Flansch (49) umfasst, die sich beide von der Plattform (46) radial nach innen erstrecken, wobei der Vorderflansch (48) mit der Vorderwand (34) gekoppelt ist und der hintere Flansch (49) mit der hinteren Wand (35) gekoppelt ist, wobei der hintere Flansch (49) mit der hinteren Wand (34) so gekoppelt ist, dass er einen hinteren Radialspalt (55) zwischen der hinteren Wand (35) und der Plattform (46) belässt und eine hintere Oberfläche (56) des hinteren Flansches (49), die zu dem hinteren Radialspalt (55) weist, bildet;wobei die Statoranordnung durch die Tatsache gekennzeichnet ist, dass der hintere Flansch (49) an der hinteren Oberfläche (56) mit mindestens einer Sekundärkühlöffnung (61) in Fluidverbindung mit dem ringförmigen Kühlkanal (32) versehen ist.
- Statoranordnung nach Anspruch 1, wobei der radiale Abstand (DH) zwischen der Mitte des Auslasses (41) der hinteren Kühlöffnung (39) und dem inneren Rand (28) des Statorrings (24) im Bereich von 0,45·DP bis 0,75·DP liegt, wobei DP der radiale Abstand zwischen der Außenfläche (46a) der Plattform (46) und dem inneren Rand (28) des Statorrings (24) ist.
- Statoranordnung nach einem der vorhergehenden Ansprüche, wobei die hintere Kühlöffnung (39) sich entlang einer Verlaufsachse (O) erstreckt, wobei in einer axialen Längsebene (A-R), die durch die Längsachse (A) und eine radiale Richtung (R) orthogonal zu der Längsachse (A) und die Verlaufsachse (O) schneidend definiert ist, ein erster Winkel (α) durch die Projektion der Verlaufsachse (O) auf die axiale Längsebene (AR) und die axiale Richtung (A) definiert ist und vorzugsweise zwischen 0° und 50° liegt.
- Statoranordnung einem der vorhergehenden Ansprüche, wobei die hintere Kühlöffnung (39) sich entlang einer Verlaufsachse (O) erstreckt, wobei in einer Tangentialebene, die durch die Längsachse (A) und eine Umfangsrichtung (C) definiert ist, die orthogonal zu der Längsachse (A) und orthogonal zu einer radialen Richtung (R) ist, die wiederum orthogonal zu der Längsachse (A) ist, ein zweiter Winkel (β) durch die Projektion der Verlaufsachse (O) auf die Tangentialebene und der Axialrichtung (A) definiert ist und vorzugsweise zwischen 20° und 70° liegt.
- Statoranordnung nach einem der vorhergehenden Ansprüche, wobei der Einlass (40) der hinteren Kühlöffnung (39) einen Durchmesser (d) hat, der zwischen 1 mm und 5 mm liegt.
- Statoranordnung nach einem der vorhergehenden Ansprüche, wobei die hintere Kühlöffnung (39) einen konstanten Querschnitt hat.
- Statoranordnung nach einem der vorhergehenden Ansprüche, wobei der Statorring (24) mit einer Vielzahl von hinteren Kühlöffnungen (39) versehen ist.
- Statoranordnung nach Anspruch 7, wobei die Auslässe der Vielzahl von hinteren Kühlöffnungen (39) entlang der ringförmigen hinteren Radialfläche (36b) gleichmäßig verteilt sind.
- Statoranordnung nach Anspruch 7 oder 8, wobei die Anzahl der hinteren Kühlöffnungen (39) in dem Bereich 0,5·NV- 2·NV liegt, wobei NV die Anzahl der Statorschaufeln der Statoranordnung (24) ist.
- Statoranordnung nach einem der vorhergehenden Ansprüche, wobei der hintere Flansch (49) an der hinteren Oberfläche (56) mit einer Vielzahl von Sekundärkühlöffnungen (61) versehen ist, die über den Umfang ausgerichtet sind.
- Statoranordnung nach Anspruch 10, wobei die Sekundärkühlöffnungen (61) gleichmäßig verteilt sind.
- Gasturbine, die sich entlang einer Längsachse (A) erstreckt und umfasst:eine Vielzahl von Rotoranordnungen (11), von welchen jede eine Rotorscheibe (15) und eine Vielzahl von Rotorschaufeln (16) umfasst, die radial angeordnet sind und mit der Rotorscheibe (15) gekoppelt sind;eine Vielzahl von Statoranordnungen (22), wobei die Statoranordnungen (22) und die Rotoranordnungen (11) entlang der Axialrichtung (A) abwechselnd angeordnet sind;wobei mindestens eine der Statoranordnungen (22) der in einem der vorstehenden Ansprüche beanspruchten Bauart entspricht.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP19425077.5A EP3816405B1 (de) | 2019-11-04 | 2019-11-04 | Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung |
EP23170966.8A EP4230844A1 (de) | 2019-11-04 | 2019-11-04 | Statoranordnung für eine gasturbine und gasturbine mit der statoranordnung |
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 (de) | 2019-11-04 | 2019-11-04 | Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP23170966.8A Division EP4230844A1 (de) | 2019-11-04 | 2019-11-04 | Statoranordnung für eine gasturbine und gasturbine mit der statoranordnung |
Publications (2)
Publication Number | Publication Date |
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EP3816405A1 EP3816405A1 (de) | 2021-05-05 |
EP3816405B1 true EP3816405B1 (de) | 2023-05-03 |
Family
ID=68887364
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
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EP19425077.5A Active EP3816405B1 (de) | 2019-11-04 | 2019-11-04 | Statoranordnung für eine gasturbine und gasturbine mit dieser statoranordnung |
EP23170966.8A Pending EP4230844A1 (de) | 2019-11-04 | 2019-11-04 | Statoranordnung für eine gasturbine und gasturbine mit der statoranordnung |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
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EP23170966.8A Pending EP4230844A1 (de) | 2019-11-04 | 2019-11-04 | Statoranordnung für eine gasturbine und gasturbine mit der statoranordnung |
Country Status (2)
Country | Link |
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EP (2) | EP3816405B1 (de) |
CN (1) | CN112780358A (de) |
Family Cites Families (6)
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 |
-
2019
- 2019-11-04 EP EP19425077.5A patent/EP3816405B1/de active Active
- 2019-11-04 EP EP23170966.8A patent/EP4230844A1/de active Pending
-
2020
- 2020-11-04 CN CN202011216063.2A patent/CN112780358A/zh active Pending
Also Published As
Publication number | Publication date |
---|---|
CN112780358A (zh) | 2021-05-11 |
EP4230844A1 (de) | 2023-08-23 |
EP3816405A1 (de) | 2021-05-05 |
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