EP3663522B1 - Stator assembly for a gas turbine and gas turbine comprising said stator assembly - Google Patents
Stator assembly for a gas turbine and gas turbine comprising said stator assembly Download PDFInfo
- Publication number
- EP3663522B1 EP3663522B1 EP18425095.9A EP18425095A EP3663522B1 EP 3663522 B1 EP3663522 B1 EP 3663522B1 EP 18425095 A EP18425095 A EP 18425095A EP 3663522 B1 EP3663522 B1 EP 3663522B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- primary
- leading edge
- annular
- trailing edge
- face
- 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
Links
- 238000001816 cooling Methods 0.000 claims description 73
- 238000000429 assembly Methods 0.000 claims description 15
- 230000000712 assembly Effects 0.000 claims description 14
- 239000000463 material Substances 0.000 claims description 11
- 239000012530 fluid Substances 0.000 claims description 6
- 238000007789 sealing Methods 0.000 description 5
- 230000037406 food intake Effects 0.000 description 3
- 230000000930 thermomechanical effect Effects 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000004519 manufacturing process Methods 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
- 230000003134 recirculating effect Effects 0.000 description 1
- 230000003685 thermal hair damage 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
- 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
- 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
- Each rotor assembly comprises a rotor disk rotating about a main axis and a plurality of blades supported by the rotor disk.
- 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.
- connection is not rounded and has a triangular section along the longitudinal axial plane.
- 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.
- 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 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 secondary baffle 73 has at least one rounded connection 78 to the annular trailing edge axial face 71.
- the rounded connection 78 is concave.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- The present invention relates to a stator assembly for a gas turbine and to a gas turbine comprising said stator assembly. In particular, the gas turbine of the present invention is part of a plant for the production of electrical energy.
- As is known, a gas turbine for power plants comprises a compressor, a combustor and a turbine.
- In particular, 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. Inside the combustor, 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. Document
DE112015003047T discloses a stator ring attached to a leading edge flange and a trailing edge flange of an inner shroud of a vane, wherein the trailing edge flange is comprising a cooling hole. - A plurality of inter-assembly cavities are defined between the stator assemblies and the rotor assemblies.
- In the turbine, 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 minimization of the amount of air spent to seal and cool the inter-assembly cavities is beneficial to the power plant performance. However, 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.
- In particular, it is an object of the present invention to provide a 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.
- According to said objects the present invention relates to a stator assembly for a gas turbine comprising:
- a stator ring, which extends about a longitudinal axis A and comprises an outer edge provided with an annular groove; the annular groove defining a leading edge wall and a trailing edge wall; the leading edge wall being provided with an annular leading edge radial face and with an annular leading edge axial face;
- a plurality of stator vanes radially arranged and coupled alongside one another to the outer edge of the stator ring so as to close the annular grove and define an annular cooling channel; each stator vane comprises an airfoil, an outer shroud and an inner shroud coupled to the stator ring; the inner shroud comprising a platform and a leading edge flange and a trailing edge flange extending radially inward from the platform; the leading edge flange being coupled to the leading edge wall and the trailing edge flange being coupled to the trailing edge wall; the leading edge flange being coupled to the leading edge wall so as to leave a primary radial gap between the leading edge wall and the platform and define a leading edge surface of the leading edge flange;
- the leading edge flange being provided, on the leading edge surface, with at least one primary cooling hole in fluid communication with the annular cooling channel;
- the leading edge wall comprising a primary baffle protruding radially from the annular leading edge axial face and axially facing the at least one primary cooling hole.
- 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. In particular, 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.
- Instead of providing a lot of air as usually done in the prior art solutions, cooling air is provided where it is more needed.
- Moreover, thanks to the presence of a baffle facing the primary cooling hole some hot gas can be ingested in the zone comprising the primary radial gap from the main hot gas flow. This zone, in fact, is sufficiently cooled by cooling air coming from the primary cooling holes and the baffle deflects the flow of hot gas air ingested outside the zone comprising the primary radial gap.
- The ingestion of hot gas can therefore be accepted, purged by means of the primary cooling holes and deflected away by means of the primary baffle. This leads to less overall consumption of sealing air therefore improving the engine global performance and the thermal status and integrity of the components of the stator assembly.
- In other words, instead of completely avoiding hot gas ingestion by using high flow rate of sealing air, the present invention allows to confine hot gas inlet in the upper part of the inter-assembly cavity.
- According to an embodiment of the present invention, 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.
- According to an embodiment of the present invention, the primary cooling holes are evenly distributed. In this way the cooling air in uniformly distributed.
- According to an embodiment of the present invention, 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°.
- According to an embodiment of the present invention, 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. In this way, the baffle is easy to make and creates a recirculation zone sufficiently large.
- According to an embodiment of the present invention, 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.
- According to an embodiment of the present invention, 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. In this way, the fin defines a sort of barrier for the entry of hot gas in the inter-assembly cavity. Moreover, 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. According to an embodiment of the present invention, the primary baffle comprises at least one fin protruding from the outer face in a direction which forms, on a radial plane, an angle β 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.
- According to an embodiment of the present invention, the primary baffle is made integral with the stator ring. In this way the time and costs to realize the stator assembly are reduced.
- According to an embodiment of the present invention, the primary baffle is made of a material different from the one of the stator ring. In this way the baffle can be made of a material having high thermomechanical properties with respect to the material used for realizing the stator ring.
- According to an embodiment of the present invention, 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 presence of at least secondary cooling hole in the trailing edge flange improves the thermal status of the upper part of the inter-assembly trailing edge cavity.
- According to an embodiment of the present invention, 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.
- It is also an object of the present invention to provide a gas turbine which is reliable and wherein the consumption of sealing air is reduced. According to said objects the present invention relates to a gas turbine as claimed in
claim 15. - The present invention will now be described with reference to the accompanying drawings, which illustrate some non-limitative embodiment, in which:
-
Figure 1 is a schematic sectional front view, with parts removed for clarity, of a gas turbine electric power plant according to the present invention; -
Figure 2 is a schematic sectional front view, with parts removed for clarity, of a first detail ofFigure 1 ; -
Figure 3 is a schematic perspective view, with parts in section and parts removed for clarity, of a second detail ofFigure 1 ; -
Figure 4 is a schematic sectional lateral view, with parts removed for clarity, of a third detail ofFigure 1 ; -
Figure 5 is a schematic up view, with parts in section and parts removed for clarity, of the third detail ofFigure 4 ; -
Figure 6 is a schematic sectional lateral view, with parts removed for clarity, of the detail offigure 4 according to a first variant of the present invention; -
Figure 7 is a schematic sectional lateral view, with parts removed for clarity, of the detail offigure 4 according to a second variant of the present invention; -
Figure 8 is a schematic sectional lateral view, with parts removed for clarity, of the detail offigure 4 according to a third variant of the present invention. - In
figure 1 reference numeral 1 indicates a gas turbine electric power plant (schematically shown inFigure 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 instator casings 9 and extends along an axis A. - In greater detail, the
rotor 8 comprises afront shaft 10, a plurality ofrotor assemblies 11 and arear shaft 13. - Each
rotor assembly 11 comprises arotor disk 15 and a plurality ofrotor blades 16 coupled to therotor disk 15 and radially arranged. - The plurality of
rotor disks 15 are arranged in succession between thefront shaft 10 and therear shaft 13 and preferably clamped as a pack by acentral tie rod 14. As an alternative, the rotor disks may be welded together. - A
central shaft 17 separates therotor disks 15 of the compressor 3 from therotor disks 15 of the turbine 5 and extends through thecombustion chamber 4. - Further,
stator assemblies 22 are alternated with thecompressor rotor assemblies 11. - Each
stator assembly 22 comprises astator ring 24 and a plurality ofstator vanes 25, which are radially arranged and coupled to thestator ring 24 and to therespective stator casing 9. - In
figure 2 an enlarged view of astator assembly 22 between tworotor assemblies 11 in the turbine 5 is shown. - Arrow D indicates the direction of the hot gas flow flowing in the turbine 5.
- Between the
rotor assemblies 11 and thestator assembly 22 inter-assembly cavities 27 are arranged. - In particular, each
stator assembly 22 defines a leading edgeinter-assembly cavity 27a and a trailing edgeinter-assembly cavity 27b, wherein the leading edgeinter-assembly cavity 27a is upstream the trailing edgeinter-assembly cavity 27b along the hot gas flow direction D. - With reference to
figure 3 , the stator ring 24 (only a part of which is visible infigure 3 ) extends about the longitudinal axis A and comprises aninner edge 28 and anouter edge 29, which is provided with anannular groove 30. - The plurality of
stator vanes 25 are coupled alongside one another to theouter edge 29 of thestator ring 24 so as to close theannular groove 30 and define anannular cooling channel 32. - The
annular cooling channel 32 is fed with air preferably coming from the compressor 3. - The
annular groove 30 defines aleading edge wall 34 and a trailingedge wall 35. Theleading edge wall 34 is upstream the trailingedge wall 35 along the hot gas flow direction D. - Preferably, the leading
edge wall 34 is provided with a plurality of coolingopenings 36 in fluidic communication with theannular cooling channel 32. - Preferably, the cooling
openings 36 are arranged in the proximity of theinner edge 28. - In the non-limiting example here disclosed and illustrated, the cooling
openings 36 are circumferentially aligned and evenly distributed. - According to a variant not illustrated, also the trailing edge wall is provided with the cooling openings in fluidic communication with the annular cooling channel.
- Each
stator vane 25 comprises anairfoil 38, anouter shroud 39 and aninner shroud 40 coupled to thestator ring 24. - The
airfoil 38 is provided with a coolingair duct 41a fed by adedicated opening 41b on theouter shroud 39. - The
outer shroud 39 is coupled to therespective stator casing 9. - The
inner shroud 40 comprises aplatform 42, aleading edge flange 43 and a trailingedge flange 44 extending radially inward from theplatform 42. Theleading edge flange 43 is upstream the trailingedge flange 44 along the hot gas flow direction D. - The
leading edge flange 43 is coupled to theleading edge wall 34, while the trailingedge flange 44 is coupled to the trailingedge wall 35. In the non-limiting example here disclosed and illustrated, the leadingedge flange 43 engages a respectiveannular seat 46 of theleading edge wall 34, while the trailingedge flange 44 engages a respectiveannular seat 47 of the trailingedge wall 35. - In particular, the leading
edge flange 43 is coupled to theleading edge wall 34 so as to leave aprimary radial gap 48 between theleading edge wall 34 and theplatform 42 and to define aleading edge surface 50 of theleading edge flange 43 facing saidprimary radial gap 48. - Preferably, also the trailing
edge flange 44 is coupled to the trailingedge wall 35 so as to leave a secondaryradial gap 52 between the trailingedge wall 35 and theplatform 42 and to define a trailingedge surface 53 of the trailingedge flange 44 facing said secondaryradial gap 52. - The
leading edge flange 43 is provided, on theleading edge surface 50, with at least oneprimary cooling hole 55 in fluid communication with theannular cooling channel 32. - Preferably, the leading
edge flange 43 is provided, on theleading edge surface 50, with a plurality of primary cooling holes 55 circumferentially aligned. - In the non-limiting example here disclosed and illustrated, the primary cooling holes 55 are evenly distributed.
- With reference to
figure 4 , eachprimary cooling hole 55 extends along a primary extension axis O. - 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, an angle α is defined by the projection of the primary extension axis Op on the longitudinal axial plane A-R and the radial direction R. Preferably the angle α of the primary cooling holes 55 is comprised between 80° and 135°.
- With reference to
figure 5 on a circumferential plane defined by the longitudinal axis A and a circumferential direction C, which is orthogonal to the longitudinal axis A and orthogonal to the radial direction R (in turn orthogonal to the longitudinal axis A), 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 θ is comprised between 100° and 200°. - Preferably, the primary cooling holes 55 have different angles α and/or different angles θ.
- According to a variant, primary cooling holes can be substantially identical to each other.
- With reference to
figure 3 and4 , the leadingedge wall 34 is provided with an annular leading edgeradial face 56 and with an annular leading edgeaxial face 57. - The
leading edge wall 34 comprises aprimary baffle 59 protruding radially outward from the annular leading edgeaxial face 57 and axially facing the at least oneprimary 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 outeraxial surface 58 of theplatform 42 and the annular leading edgeaxial face 57. - In the non-limiting example here disclosed and illustrated, the
primary baffle 59 has aninner face 60 facing the at least oneprimary cooling hole 55 and anouter face 61 opposite to theinner face 50. - Preferably, the
primary baffle 59 protrudes radially from the annular leading edgeaxial face 57 so as theouter face 61 is an extension of the annular leading edgeradial face 56. - In the non-limiting example here illustrated, the
primary baffle 59 has at least oneconnection 63, preferably rounded, connecting theprimary baffle 59 to the annular leading edgeaxial face 57. Preferably, therounded connection 63 is concave. - According to a variant not illustrated, the connection is not rounded and has a triangular section along the longitudinal axial plane.
- In the non-limiting example here disclosed and illustrated, the
primary baffle 59 is made integral with thestator ring 24. - According to a variant not illustrated, the primary baffle and the stator ring are separate pieces coupled together. In this way, each piece can be replaced if required. Moreover, the primary baffle can be made of a material different from the one of the stator ring. For example, the primary baffle can be made of a material having higher thermomechanical properties with respect to the material of the stator ring. Alternatively, the primary baffle and the stator ring can be separate pieces made of the same material.
- According to a further variant not illustrated, the stator ring could be coated with a specific material in order to improve its thermomechanical resistance.
- With reference to
figure 4 , the radial distance S between the extension axis O of eachprimary cooling hole 55 and the annular leading edgeaxial face 57 is comprised between the 1% and the 40% of the reference radial distance RF defined by the radial distance between the outeraxial surface 58 of theplatform 42 and the annular leading edgeaxial face 57. It has to be considered, however, that the radial distance S should obviously have a value that allows the perforation of theleading edge surface 50. - The radial distance h between the lower point of the outlet of each
primary cooling hole 55 and the annular leading edgeaxial face 57 is comprised between the 0% and the 20% of the reference radial distance RF defined by the radial distance between the outeraxial surface 58 of theplatform 42 and the annular leading edgeaxial face 57. - With the expression "lower point of the outlet of each primary cooling hole" is intended the point having the minimum radial distance from the longitudinal axis at the outlet of the
primary cooling hole 55; wherein the outlet is the terminal of theprimary cooling hole 55 facing theprimary baffle 59. - In
figure 6 is illustrated a variant of the present invention wherein theprimary baffle 59 comprises at least onefin 65 protruding axially from theouter face 61. - In
figure 7 is illustrated another variant of the present invention wherein theprimary baffle 59 comprises at least one fin 66 protruding from theouter 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 β with respect to the axial direction. Preferably angle β is lower than 90°. - In
figure 8 is illustrated another variant of the present invention wherein the trailingedge flange 44 is provided, on the trailingedge surface 53, with at least onesecondary cooling hole 68 in fluid communication with theannular cooling channel 32. - Preferably, the trailing
edge flange 44 is provided, on the trailingedge surface 53, with a plurality of secondary cooling holes 68 circumferentially aligned. - In the non-limiting example here disclosed and illustrated, the secondary cooling holes 68 are evenly distributed.
- According to the non-limitative embodiment here disclosed and illustrated, 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 edgeradial face 70 and with an annular trailing edgeaxial face 71. - The trailing
edge wall 44 comprises asecondary baffle 73 protruding radially from the annular trailing edgeaxial face 71 and axially facing the at least onesecondary cooling hole 68. - In the non-limiting example here disclosed and illustrated, the
secondary baffle 73 has aninner face 75 facing the at least onesecondary cooling hole 68 and anouter face 76 opposite to theinner face 75. - Preferably, the
secondary baffle 73 protrudes radially from the annular trailing edgeaxial face 71 so as theouter face 76 is an extension of the annular trailing edgeradial face 70. - In the non-limiting example here illustrated, the
secondary baffle 73 has at least onerounded connection 78 to the annular trailing edgeaxial face 71. Preferably, therounded connection 78 is concave. - In the non-limiting example here disclosed and illustrated, the
secondary baffle 73 is made integral with thestator ring 24. - According to a variant not illustrated, the secondary baffle and the stator ring are separate pieces coupled together.
- According to a variant not illustrated, the secondary baffle comprises at least one fin protruding axially from the
outer face 76. - According to a variant not illustrated, 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°. - Finally, it is clear that modifications and variants can be made to the stator assembly and to the gas turbine described herein without departing from the scope of the present invention, as defined in the appended claims.
Claims (15)
- Stator assembly (22) for a gas turbine comprising:a stator ring (24), which extends about a longitudinal axis (A) and comprises an outer edge (29) provided with an annular groove (30); the annular groove (30) defining a leading edge wall (34) and a trailing edge wall (35); the leading edge wall (34) being provided with an annular leading edge radial face (56) and with an annular leading edge axial face (57);a plurality of stator vanes (25) radially arranged and coupled alongside one another to the outer edge (29) of the stator ring (24) so as to close the annular grove (30) and define an annular cooling channel (32); each stator vane (25) comprises an airfoil (38), an outer shroud (39) and an inner shroud (40) coupled to the stator ring (24); the inner shroud (40) comprising a platform (42) and a leading edge flange (43) and a trailing edge flange (44) extending radially inward from the platform (42); the leading edge flange (43) being coupled to the leading edge wall (34) and the trailing edge flange (44) being coupled to the trailing edge wall (35); the leading edge flange (43) being 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 define a leading edge surface (50) of the leading edge flange (43);characterized bythe leading edge flange (43) being provided, on the leading edge surface (50), with at least one primary cooling hole (55) in fluid communication with the annular cooling channel (32) ;the leading edge wall (34) comprising a primary baffle (59) protruding radially from the annular leading edge axial face (57) and axially facing the at least one primary cooling hole (55).
- Stator assembly according to anyone of the foregoing claims, comprising a plurality of primary cooling holes (55) circumferentially aligned.
- Stator assembly according to claim 2, wherein the primary cooling holes (55) are evenly distributed.
- Stator assembly according to anyone of the foregoing claims, wherein the primary cooling hole (55) extends along a primary 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 primary extension axis (O), a first angle (α) defined by the projection of the primary extension axis (OP) on the longitudinal axial plane (A-R) and the radial direction (R) is comprised between 80° and 135°.
- Stator assembly according to anyone of the foregoing claims, wherein the primary cooling hole (55) extends along a primary extension axis (O) ; on a circumferential plane defined by the longitudinal axis (A) and a circumferential direction (C), which is orthogonal to the longitudinal axis (A) and orthogonal to a radial direction (R) in turn orthogonal to the longitudinal axis (A), a second angle (θ) is defined by the projection of the primary extension axis (Op) on the circumferential plane and the axial direction (A) is comprised between 100° and 200°.
- Stator assembly according to anyone of the foregoing claims, wherein 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 (60); the primary baffle (59) protruding 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).
- Stator assembly according to anyone of the foregoing claims, wherein the primary baffle (59) has at least one rounded connection (63) to the annular leading edge axial face (57).
- Stator assembly according to claim 7, wherein the rounded connection (63) is concave.
- Stator assembly according to anyone of the foregoing claims, wherein 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 (60); wherein the primary baffle (59) comprises at least one fin (65) protruding axially from the outer face (61).
- Stator assembly according to anyone of claims from 1 to 8, wherein 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 (60); the primary baffle (59) comprises at least one fin (65) protruding from the outer face (61) in a direction which forms, on a radial plane, a third angle (β) with respect to the axial direction (A); the angle (β) being preferably lower than 90°.
- Stator assembly according to anyone of the foregoing claims, wherein the primary baffle (59) is made integral with the stator ring (24).
- Stator assembly according to anyone of the foregoing claims, wherein the primary baffle (59) is made of a material different from the one of the stator ring (24).
- Stator assembly according to anyone of the foregoing claims, wherein 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 define a trailing edge surface (53) of the trailing edge flange (44); the trailing edge flange (44) being provided, on the trailing edge surface (53), with at least one secondary cooling hole (68) in fluid communication with the annular cooling channel (32).
- Stator assembly according to claim 14, wherein the trailing edge wall (35) is provided with an annular trailing edge radial face (70) and with an annular trailing edge axial face (71); the trailing edge wall (35) comprising 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).
- Gas turbine extending along a longitudinal axis (A) and comprising:a plurality of rotor assemblies (11), each of which comprises a rotor disk (15) and a plurality of rotor blades (16) radially arranged and coupled to the rotor disk (15);a plurality of stator assemblies (22); the stator assemblies (22) and the rotor assemblies (11) are alternated along the axial direction (A);at least one of the stator assemblies (22) being of the type claimed in anyone of the foregoing claims.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP18425095.9A EP3663522B1 (en) | 2018-12-07 | 2018-12-07 | Stator assembly for a gas turbine and gas turbine comprising said stator assembly |
RU2019139258A RU2795241C2 (en) | 2018-12-07 | 2019-12-03 | Stator assembly for a gas turbine and a gas turbine containing such stator assembly |
CN201911242895.9A CN111287803B (en) | 2018-12-07 | 2019-12-06 | Stator assembly for a gas turbine and gas turbine comprising said stator assembly |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP18425095.9A EP3663522B1 (en) | 2018-12-07 | 2018-12-07 | Stator assembly for a gas turbine and gas turbine comprising said stator assembly |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3663522A1 EP3663522A1 (en) | 2020-06-10 |
EP3663522B1 true EP3663522B1 (en) | 2021-11-24 |
Family
ID=64901460
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18425095.9A Active EP3663522B1 (en) | 2018-12-07 | 2018-12-07 | Stator assembly for a gas turbine and gas turbine comprising said stator assembly |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP3663522B1 (en) |
CN (1) | CN111287803B (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP4019742A1 (en) | 2020-12-23 | 2022-06-29 | ANSALDO ENERGIA S.p.A. | A sealing assembly for a vane set of a gas turbine engine and gas turbine engine comprising such a sealing assembly |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3829233A (en) * | 1973-06-27 | 1974-08-13 | Westinghouse Electric Corp | Turbine diaphragm seal structure |
JP3416447B2 (en) * | 1997-03-11 | 2003-06-16 | 三菱重工業株式会社 | Gas turbine blade cooling air supply system |
EP1657407B1 (en) * | 2004-11-15 | 2011-12-28 | Rolls-Royce Deutschland Ltd & Co KG | Method for the cooling of the outer shrouds of the rotor blades of a gas turbine |
US8262342B2 (en) * | 2008-07-10 | 2012-09-11 | Honeywell International Inc. | Gas turbine engine assemblies with recirculated hot gas ingestion |
JP2010077868A (en) * | 2008-09-25 | 2010-04-08 | Mitsubishi Heavy Ind Ltd | Rim seal structure of gas turbine |
JP5449225B2 (en) * | 2011-02-08 | 2014-03-19 | 株式会社日立製作所 | gas turbine |
JP5885935B2 (en) * | 2011-04-19 | 2016-03-16 | 三菱重工業株式会社 | Turbine vane and gas turbine |
US9062557B2 (en) * | 2011-09-07 | 2015-06-23 | Siemens Aktiengesellschaft | Flow discourager integrated turbine inter-stage U-ring |
EP2759675A1 (en) * | 2013-01-28 | 2014-07-30 | Siemens Aktiengesellschaft | Turbine arrangement with improved sealing effect at a seal |
ES2724533T3 (en) * | 2013-07-09 | 2019-09-11 | MTU Aero Engines AG | Turbomachine with sealing structure |
EP3094822B1 (en) * | 2014-01-13 | 2021-10-06 | Ansaldo Energia S.p.A. | Blade for a gas turbine and method for manufacturing said blade |
CN106460534B (en) * | 2014-06-30 | 2018-05-18 | 三菱日立电力***株式会社 | The remodeling method of Turbomachinery, turbine and Turbomachinery |
US9765699B2 (en) * | 2014-12-30 | 2017-09-19 | General Electric Company | Gas turbine sealing |
-
2018
- 2018-12-07 EP EP18425095.9A patent/EP3663522B1/en active Active
-
2019
- 2019-12-06 CN CN201911242895.9A patent/CN111287803B/en active Active
Also Published As
Publication number | Publication date |
---|---|
EP3663522A1 (en) | 2020-06-10 |
RU2019139258A (en) | 2021-06-03 |
CN111287803A (en) | 2020-06-16 |
CN111287803B (en) | 2023-07-14 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20170248155A1 (en) | Centrifugal compressor diffuser passage boundary layer control | |
CN110300838B (en) | Thermal structure for outer diameter mounted turbine blades | |
JP6739934B2 (en) | Gas turbine seals | |
CN107084004B (en) | Impingement hole for a turbine engine component | |
JP2015086872A (en) | Microchannel exhaust for cooling and/or purging gas turbine segment gaps | |
US20120032403A1 (en) | Seal assembly | |
US20160177833A1 (en) | Engine and method for operating said engine | |
US9366148B2 (en) | Assembly of an axial turbomachine and method for manufacturing an assembly of this type | |
EP2264283A2 (en) | A cooled component for a gas turbine engine | |
JP2016125486A (en) | Gas turbine sealing | |
US10066488B2 (en) | Turbomachine blade with generally radial cooling conduit to wheel space | |
CA3065116C (en) | Turbine assembly for impingement cooling and method of assembling | |
US11047246B2 (en) | Blade or vane, blade or vane segment and assembly for a turbomachine, and turbomachine | |
US10408075B2 (en) | Turbine engine with a rim seal between the rotor and stator | |
CN110431286B (en) | Tip balancing slit for a turbomachine | |
EP3156607A1 (en) | Turbine nozzle with cooling channel coolant distribution plenum | |
US9995172B2 (en) | Turbine nozzle with cooling channel coolant discharge plenum | |
EP2649279B1 (en) | Fluid flow machine especially gas turbine penetrated axially by a hot gas stream | |
US9689272B2 (en) | Gas turbine and outer shroud | |
EP3663522B1 (en) | Stator assembly for a gas turbine and gas turbine comprising said stator assembly | |
US9765629B2 (en) | Method and cooling system for cooling blades of at least one blade row in a rotary flow machine | |
JP6961340B2 (en) | Rotating machine | |
CN110735664A (en) | Component for a turbine engine having cooling holes | |
EP3816402B1 (en) | Stator assembly for a gas turbine and gas turbine comprising said stator assembly | |
EP3816405B1 (en) | Stator assembly for a gas turbine and gas turbine comprising said stator assembly |
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 |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
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: 20201209 |
|
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 |
|
INTG | Intention to grant announced |
Effective date: 20210617 |
|
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: AT Ref legal event code: REF Ref document number: 1450011 Country of ref document: AT Kind code of ref document: T Effective date: 20211215 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602018027101 Country of ref document: DE |
|
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: 20211124 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 1450011 Country of ref document: AT Kind code of ref document: T Effective date: 20211124 |
|
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: 20211124 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: 20211124 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: 20211124 Ref country code: BG 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: 20220224 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: 20211124 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20220324 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: 20211124 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: 20220324 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: 20211124 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: 20220224 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: 20211124 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: 20211124 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: 20211124 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: 20220225 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: 20211124 |
|
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: 20211124 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: 20211124 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: 20211124 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: 20211124 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: 20211124 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: 20211124 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602018027101 Country of ref document: DE |
|
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: 20211124 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20211231 |
|
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 |
|
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: 20211207 Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20211207 Ref country code: AL 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: 20211124 |
|
26N | No opposition filed |
Effective date: 20220825 |
|
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: 20211124 Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220124 Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20211231 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20211231 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20211231 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CY 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: 20211124 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: HU Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO Effective date: 20181207 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20221207 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20221207 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MK 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: 20211124 |
|
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: 6 |
|
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: 6 |
|
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20240430 |