EP3762587B1 - Pale d'aube pour une aube de turbine - Google Patents

Pale d'aube pour une aube de turbine Download PDF

Info

Publication number
EP3762587B1
EP3762587B1 EP19723730.8A EP19723730A EP3762587B1 EP 3762587 B1 EP3762587 B1 EP 3762587B1 EP 19723730 A EP19723730 A EP 19723730A EP 3762587 B1 EP3762587 B1 EP 3762587B1
Authority
EP
European Patent Office
Prior art keywords
aerofoil
cooling holes
height
series
blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP19723730.8A
Other languages
German (de)
English (en)
Other versions
EP3762587A1 (fr
Inventor
Fathi Ahmad
Daniela Koch
Marco Schüler
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.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens Energy Global GmbH and Co KG
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 Siemens Energy Global GmbH and Co KG filed Critical Siemens Energy Global GmbH and Co KG
Publication of EP3762587A1 publication Critical patent/EP3762587A1/fr
Application granted granted Critical
Publication of EP3762587B1 publication Critical patent/EP3762587B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D5/186—Film cooling
    • 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
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the invention relates to a blade for a turbine blade, comprising a leading edge against which a hot gas can flow, from which a suction side wall and a pressure side wall extend to a trailing edge of the blade, the blade extending in a transverse direction thereto from a root end with a blade height of 0 % to a tip end with an airfoil height of 100%, with at least two rows of cooling holes arranged along the leading edge and having a first distance from one another to be measured perpendicular to the leading edge.
  • Such a turbine blade is, for example, from EP 2 154 333 A2 famous.
  • the cooling holes arranged in the leading edge serve to produce a cooling protective film over the leading edge during operation of a gas turbine equipped therewith, in order to counteract the incoming flow of hot gas.
  • the cooling holes are therefore also referred to as film cooling holes, which are also known in English as “shower head film cooling holes” due to their dense arrangement.
  • the airfoil divides the incoming hot gas flow at the leading edge into two partial flows, one of which flows along the suction side of the airfoil and the other part along the pressure side.
  • the location of the flow distribution on the blade profile is called the stagnation point, since in the idealized sense no cross flow occurs there.
  • film cooling holes are arranged on both sides of the front edge or the previously determined stagnation line, in order to prevent the hot gas flow impinging there from coming into too close contact with the component wall.
  • the invention is based on the object of providing an airfoil for a turbine blade which is designed in the best possible way for different operating conditions of a gas turbine, in particular in order to achieve adequate cooling with the longest possible service life of the airfoil when using an acceptable amount of coolant .
  • This object is achieved with a blade of the type mentioned at the outset in that the at least two rows of cooling holes are arranged at least partially along the leading edge on a wavy line.
  • the wavy line is slightly curved, without changing the sign of its curvature, such that the cooling holes of each of the at least two rows are arranged further downstream at both the root end and the tip end of the airfoil than the cooling holes of the corresponding row at half-height of the airfoil.
  • the invention is based on the finding that the actual hot gas flow direction depends on the design of the Airfoil used flow direction can differ on the one hand due to different operating modes of the gas turbine. The deviations can occur due to a change in the load output compared to the nominal load.
  • the stagnation point of a blade profile in the area of the leading edge can oscillate due to flow effects which are caused by a guide blade arranged upstream of the moving blade. The oscillation of the stagnation point of a blade profile leads to a locally increased surface temperature of the blade airfoil, which can be counteracted effectively with the invention.
  • the invention now proposes providing at least two rows of cooling holes in the area of the leading edge, which are at least partially arranged on a curved wavy line.
  • the cooling holes are shifted towards the pressure side or the suction side in relation to the oscillating stagnation point of the relevant blade profile.
  • an area is determined for each blade profile in which the stagnation point can occur.
  • Each of these areas is defined by two end points, from which an average stagnation point can then be determined.
  • the two cooling holes are then positioned in such a way that the best possible cooling is achieved. This allows the cooling effect to be optimized locally.
  • the amount of coolant required for cooling can be reduced. The reduced consumption of coolant contributes to the increase in efficiency of the gas turbine during operation.
  • each of the at least two rows are located near the root end and near the tip end of the airfoil further downstream than the cooling holes of the corresponding half-airfoil row.
  • the wavy line then extends between these points without one Changing the sign of its curvature so that it is only slightly curved.
  • this variant represents a more favorable cooling configuration, especially for guide vanes, since with these vanes the stagnation point shift occurs more at the ends of the airfoil than in its center and also towards the suction side.
  • the maximum displacement of the relevant cooling holes near the ends of the airfoil is then only a few millimeters, in particular 2 mm, towards the suction side, compared to the position of the cooling holes of the same row at half the airfoil height, ie at 50% of the airfoil height.
  • the first distance between the at least two rows of cooling holes varies along the leading edge, so that the first distance is different for some blade heights.
  • the local cooling capacity of the turbine blade in the area of the leading edge can be adapted locally to the individual temperature load.
  • a blade profile can be determined by examining a cross section, which profile is known to have the shape of a curved drop.
  • Each blade profile therefore has a nose radius in the area of the leading edge, with the blade profiles having a first distance between the at least two rows at the level of cooling holes, the size of which is in the range between 0.4 times and 0.7 times the associated nose radius located.
  • the effectiveness of the cooling depends on the distance between the cooling holes of different rows and the curvature of the leading edge, the so-called nose radius, as well as the length of the camberline, the number of blades and the turning of the blade profile. It was then found that a particularly efficient cooling of the leading edge region can be achieved if the first distance between the cooling holes of different rows that are at the same blade height lies within the claimed interval.
  • the first distance is smallest at half the height of the airfoil and increases towards the two ends.
  • the increase is particularly moderate.
  • each cooling hole preferably has a throttle cross section that adjusts the coolant flow, the throttle cross sections of some cooling holes being of different sizes.
  • the throttle cross sections of the cooling holes in the region of half the blade height are particularly preferably larger than the throttle cross section of the cooling holes in the region further away from half the blade height.
  • This configuration is based on the finding that at half the blade height and in the regions immediately adjacent thereto, there is a somewhat greater cooling requirement than in those regions of the leading edge which are further away from half the blade height.
  • the configuration in which the at least two rows of cooling holes are arranged on both sides of a central stagnation point line of the incoming hot gas flow is particularly preferred.
  • the hot gas flow is divided into a part flowing to the pressure side and a part flowing to the suction side, which is diverted to both sides, so that the component wall underneath is particularly efficiently protected from the high temperatures of the hot gas due to the arrangement of the cooling holes on both sides.
  • a further but shortened row of essentially evenly spaced cooling holes is provided on the pressure side in addition to the at least two rows, with the length of the further row between 50% and 60% of the airfoil height and the further row of cooling holes is arranged substantially centrally between the two ends of the airfoil.
  • the further row is arranged essentially centrally as long as it is divided by half the airfoil height into two parts, the shorter part of which is not shorter than 1/3 of the length of the further row.
  • the length of the further row of cooling holes is recorded in the same direction as the airfoil height.
  • the airfoil is preferably part of a turbine blade, in particular a turbine guide blade of a stationary gas turbine.
  • FIG 1 a turbine rotor blade 10 is shown in a perspective view.
  • the turbine blade 10 successively comprises an essentially fir-tree-shaped blade root 12, which is adjoined by a hot-gas platform 14 as the end wall.
  • an airfoil 16 On its surface facing the hot gas S, an airfoil 16 according to a first example is arranged.
  • the airfoil 16 is known to include a leading edge 18 and a trailing edge 20 between which a suction sidewall 17 and a pressure sidewall 19 extend. In a direction transverse thereto, the airfoil 16 extends from a root end 21 at 0% airfoil height to a tip end 23 at 100% airfoil height.
  • Two rows R 1 , R 2 of cooling holes 22 are arranged along the leading edge 18 .
  • the two rows R 1 , R 2 run along a wavy line with a plurality of wave troughs and wave crests and are simultaneously arranged on both sides of a central stagnation point line 24
  • a second example is in figure 2 shown.
  • a region is straight, followed by a bulbous section.
  • the two rows R 1 , R 2 of cooling holes 22 are arranged in the first, radially inner area in such a way that they are arranged parallel to the leading edge 18 on both sides thereof.
  • This first range B 1 extends between 0% and about 40% airfoil height.
  • a second area B 2 is provided radially on the outside. This ends at an airfoil height of about 75%.
  • the cooling holes 22 of both rows R 1 , R 2 move further towards the pressure side with increasing height until they have reached the maximum displacement away from the leading edge 18 at about 75% airfoil height.
  • the cooling holes 22 of the two rows R 1 , R 2 shift back again in the direction of the front edge 18 .
  • cooling holes 22 are shown only schematically as circles, with their throttle cross sections being shown schematically by circles of different sizes.
  • the cooling holes 22 can be film cooling holes that have a diffuser-like opening. Its diffuser can even be designed with a profile.
  • a distance A between the cooling holes 22 to be measured transversely on the surface of the airfoil 16 can also be of different sizes at different airfoil heights.
  • FIG. 12 also shows, as a blade profile 28, the cross section through the airfoil 16 of the first example according to FIG figure 1 .
  • the blade profile center line is provided with reference number 30 .
  • the foremost arranged point of the blade profile center line 30 defines the leading edge 18.
  • the stagnation point 25 can be slightly shifted away from the leading edge 18 towards the pressure side 19 or towards the suction side 17.
  • the (middle) stagnation points 25 of each blade profile section which can be determined at any blade height, together form the stagnation point line 24.
  • the nose radius is denoted by R.
  • FIG 4 An embodiment of the invention is in figure 4 shown. It shows a perspective view of a turbine blade configured as a guide blade, with the blade root 12 comprising two hook-shaped rails for fastening the blade to a blade carrier (not shown in any more detail).
  • a platform 14 is provided at both the root end 21 and the tip end 23 of the airfoil to limit the flow path.
  • the airfoil 16 extends along its airfoil height.
  • the at least two rows R 1 , R 2 of cooling holes 18 are also arranged analogously: starting with the cooling holes at half the height of the airfoil, within each row R 1 , R 2 the cooling holes arranged with decreasing spacing towards the platforms 14 are arranged further on the suction side .
  • the stagnation point line 24 is slightly curved without changing the sign of its curvature.
  • a further but shortened row of substantially evenly spaced cooling holes 18 is provided on the pressure side next to the two rows R 1 , R 2 .
  • This further row R 3 is according to this embodiment in the middle between the two platforms 14 and the two ends 21, 23 and extends over a length of only 55% of the blade height. It is therefore shorter than the two rows R 1 , R 2 .
  • the invention relates to an airfoil 16 for a turbine blade 10, comprising a leading edge 18 against which a hot gas S can flow, from which a suction sidewall 17 and a pressure sidewall 19 extend to a trailing edge 20 of the airfoil 16, the airfoil 16 being in a transverse direction thereto extending from a root end 21 with an airfoil height of 0% to a tip end 23 with an airfoil height of 100%, with two rows R 1 , R 2 of cooling holes 22 arranged along the leading edge, the mutually perpendicular to the leading edge 18 to be detected have first distance A.
  • the two rows R 1 , R 2 of cooling holes 22 be arranged at least partially along the leading edge 18 on a wavy line.
  • the wavy line 24 is slightly curved without changing the sign of its curvature such that the cooling holes 18 of each of the at least two rows (Ri, R2) are arranged further on the suction side than the cooling holes at both the root end 21 and the tip end 23 of the airfoil 18 of the corresponding row (Ri, R2) at half blade height.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Corps (16) creux d'une aube de turbine, comprenant un bord avant sur lequel peut passer un gaz (S) chaud et duquel s'étend une paroi (17) d'extrados et une paroi (19) d'intrados vers un bord (20) arrière du corps (16) de l'aube, le corps (16) de l'aube s'étendant dans une direction perpendiculaire à cela d'une extrémité du côté de l'emplanture en ayant une hauteur de corps d'aube de 0% à une extrémité (23) du côté de la pointe en ayant une hauteur de corps d'aube de 100%,
    comprenant au moins deux rangées (R1, R2) de trous (22) de refroidissement, qui sont disposées le long du bord (18) avant et qui ont entre elles une première distance (A), à prendre perpendiculairement au bord (18) avant, les au moins deux rangées (R1, R2) de trous (22) de refroidissement étant disposées au moins en partie sur une ligne ondulée le long du bord (18) avant,
    caractérisé en ce que
    la ligne (24) ondulée est, sans modification du signe de sa courbure, incurvée légèrement de manière à ce que les trous (22) de refroidissement de chacune des au moins deux rangées (R1, R2) soient disposés à la fois, à l'extrémité (21) du côté de l'emplanture et à l'extrémité (23) du côté de la pointe du corps de l'autre, davantage du côté de l'extrados que les trous (22) de refroidissement des rangées (R1, R2) correspondantes à mi-hauteur du corps de l'aube.
  2. Corps d'aube suivant la revendication 1,
    dans lequel la première distance (A) entre les au moins deux rangées (R1, R2) varie le long du bord (18) avant.
  3. Corps d'aube suivant l'une des revendications précédentes, dans lequel, pour chaque hauteur du corps de l'aube, un profil (28) d'aube peut être déterminé, lequel profil (28) d'aube a, dans la partie du bord (18) avant, un rayon (R) de bec, dans lequel les profils de l'aube ont, au niveau des trous (22) de refroidissement, une première distance (A) entre les au moins deux rangées (R1, R2), dont la dimension est dans la plage comprise entre 0,4 fois et 0,7 fois le rayon du bec associé.
  4. Corps d'aube suivant l'une des revendications précédentes, dans lequel la première distance (A) est la plus petite à mi-hauteur du corps de l'aube et augmente vers les deux extrémités.
  5. Corps d'aube suivant l'une des revendications précédentes, dans lequel chaque trou de refroidissement a une surface transversale d'étranglement réglant le débit de fluide de refroidissement, les sections transversales d'étranglement de certains trous (22) de refroidissement ayant des dimensions différentes.
  6. Corps d'aube suivant l'une des revendications précédentes, dans lequel les sections transversales d'étranglement des trous (22) de refroidissement sont plus grandes dans la partie de la mi-hauteur du corps de l'aube que la section transversale d'étranglement des trous (22) de refroidissement dans la partie plus loin de la mi-hauteur du corps de l'aube.
  7. Corps d'aube suivant l'une des revendications précédentes, dans lequel les au moins deux rangées (R1, R2) de trous (22) de refroidissement sont disposées des deux côtés d'une ligne (24) de points d'arrêt du courant de gaz chaud arrivant.
  8. Corps d'aube suivant l'une des revendications précédentes, dans lequel il est prévu, outre les au moins deux rangées (R1, R2), au voisinage de l'intrados, une autre rangée (R3) de trous (22) de refroidissement, une longueur de l'autre rangée (R3) représentant entre 50% et 60% de la hauteur du corps de l'aube et l'autre rangée (R3) étant disposée sensiblement au milieu entre les deux extrémités (21, 23) du corps (16) de l'aube.
  9. Aube (10) d'une turbine à gaz fixe,
    comprenant un corps (16) d'aube suivant l'une des revendications précédentes, conformée de préférence en aube directrice de turbine.
EP19723730.8A 2018-05-04 2019-05-03 Pale d'aube pour une aube de turbine Active EP3762587B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP18170731.6A EP3564483A1 (fr) 2018-05-04 2018-05-04 Pale d'aube pour une aube de turbine
PCT/EP2019/061354 WO2019211427A1 (fr) 2018-05-04 2019-05-03 Pale d'aube pour une aube de turbine

Publications (2)

Publication Number Publication Date
EP3762587A1 EP3762587A1 (fr) 2021-01-13
EP3762587B1 true EP3762587B1 (fr) 2022-04-13

Family

ID=62116325

Family Applications (2)

Application Number Title Priority Date Filing Date
EP18170731.6A Withdrawn EP3564483A1 (fr) 2018-05-04 2018-05-04 Pale d'aube pour une aube de turbine
EP19723730.8A Active EP3762587B1 (fr) 2018-05-04 2019-05-03 Pale d'aube pour une aube de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP18170731.6A Withdrawn EP3564483A1 (fr) 2018-05-04 2018-05-04 Pale d'aube pour une aube de turbine

Country Status (6)

Country Link
US (1) US11326458B2 (fr)
EP (2) EP3564483A1 (fr)
JP (1) JP7124122B2 (fr)
KR (1) KR102505046B1 (fr)
CN (1) CN112074652B (fr)
WO (1) WO2019211427A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3564483A1 (fr) * 2018-05-04 2019-11-06 Siemens Aktiengesellschaft Pale d'aube pour une aube de turbine
JP7224928B2 (ja) * 2019-01-17 2023-02-20 三菱重工業株式会社 タービン動翼及びガスタービン
KR102507408B1 (ko) 2022-11-11 2023-03-08 터보파워텍(주) 3d프린팅에 의한 가스터빈 블레이드의 에어포일 수리 공정

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6869268B2 (en) * 2002-09-05 2005-03-22 Siemens Westinghouse Power Corporation Combustion turbine with airfoil having enhanced leading edge diffusion holes and related methods
US7217094B2 (en) 2004-10-18 2007-05-15 United Technologies Corporation Airfoil with large fillet and micro-circuit cooling
EP1898051B8 (fr) * 2006-08-25 2017-08-02 Ansaldo Energia IP UK Limited Aube de turbine à gaz avec refroidissement du bord d'attaque
US8105030B2 (en) * 2008-08-14 2012-01-31 United Technologies Corporation Cooled airfoils and gas turbine engine systems involving such airfoils
WO2014025571A1 (fr) 2012-08-06 2014-02-13 General Electric Company Composant de turbine rotatif à alignement de trou préférentiel
US11143038B2 (en) * 2013-03-04 2021-10-12 Raytheon Technologies Corporation Gas turbine engine high lift airfoil cooling in stagnation zone
US10329923B2 (en) * 2014-03-10 2019-06-25 United Technologies Corporation Gas turbine engine airfoil leading edge cooling
US9976423B2 (en) * 2014-12-23 2018-05-22 United Technologies Corporation Airfoil showerhead pattern apparatus and system
US10240462B2 (en) * 2016-01-29 2019-03-26 General Electric Company End wall contour for an axial flow turbine stage
US11286787B2 (en) 2016-09-15 2022-03-29 Raytheon Technologies Corporation Gas turbine engine airfoil with showerhead cooling holes near leading edge
EP3564483A1 (fr) * 2018-05-04 2019-11-06 Siemens Aktiengesellschaft Pale d'aube pour une aube de turbine

Also Published As

Publication number Publication date
EP3762587A1 (fr) 2021-01-13
JP7124122B2 (ja) 2022-08-23
WO2019211427A1 (fr) 2019-11-07
US11326458B2 (en) 2022-05-10
KR20210002709A (ko) 2021-01-08
US20210156263A1 (en) 2021-05-27
EP3564483A1 (fr) 2019-11-06
KR102505046B1 (ko) 2023-03-06
CN112074652A (zh) 2020-12-11
JP2021522444A (ja) 2021-08-30
CN112074652B (zh) 2023-05-02

Similar Documents

Publication Publication Date Title
EP2087206B1 (fr) Aube de turbine
DE60218776T2 (de) Filmgekühlte Turbinenschaufel
EP3762587B1 (fr) Pale d'aube pour une aube de turbine
EP1766192B1 (fr) Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant
EP2384393B1 (fr) Aube refroidie pour turbine a gaz
CH695788A5 (de) Schaufelblatt für eine Gasturbine mit einer Kühlkonstruktion für seine Schaufelblatthinterkante.
EP2696031B1 (fr) Aube pour une turbomachine et turbomachine correspondante
EP0825332B1 (fr) Aube refroidissable
WO2007042522A1 (fr) Aube de turbomachine
DE60220556T2 (de) Kühlung der Übergangsradien einer Statorschaufel
EP2746533B1 (fr) Grille d'aube et turbomachine
DE102014100087A1 (de) Innenaufbau einer Turbinenlaufschaufel
EP3056677B1 (fr) Aube et turbomachine
DE69925447T2 (de) Kühlbare Schaufelblätter
EP3473808B1 (fr) Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale
EP3358135A1 (fr) Contournage d'une plate-forme de grille d'aube
DE102013020826A1 (de) Radialverdichterstufe
EP1016773B1 (fr) Aube de turbine refroidissable
EP2860356A1 (fr) Turbomachine
EP2868867A1 (fr) Aube de turbine
EP3404211A1 (fr) Segment de grille d'aubes d'une turbine avec paroi de plateforme contourée, grille d'aubes, canal d'aube, plateforme, turbine et moteur d'aéronef associés
EP0825333B1 (fr) Aube de turbine pouvant être refroidie
EP2650475B1 (fr) Pale pour une turbomachine, agencement d'aubes ainsi que la turbomachine
EP3369892B1 (fr) Contournage d'une plate-forme de grille d'aube
DE102010004854A1 (de) Laufschaufel für eine Strömungsmaschine und Strömungsmaschine

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

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

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20201008

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

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
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: 20211129

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

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502019004063

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1483565

Country of ref document: AT

Kind code of ref document: T

Effective date: 20220515

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: 20220413

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

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: 20220413

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

Ref country code: SE

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

Effective date: 20220413

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: 20220816

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: 20220713

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: 20220413

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: 20220413

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: 20220714

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: 20220413

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: 20220413

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: 20220713

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: 20220413

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: 20220413

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: 20220413

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: 20220813

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: 502019004063

Country of ref document: DE

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20220531

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: 20220413

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: 20220413

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: 20220413

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: 20220413

Ref country code: LU

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

Effective date: 20220503

Ref country code: LI

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

Effective date: 20220531

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: 20220413

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: 20220413

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: 20220413

Ref country code: CH

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

Effective date: 20220531

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

26N No opposition filed

Effective date: 20230116

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

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: 20220413

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

Ref country code: IE

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

Effective date: 20220503

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: 20220413

Ref country code: BE

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

Effective date: 20220531

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

Ref country code: IT

Payment date: 20230525

Year of fee payment: 5

Ref country code: FR

Payment date: 20230523

Year of fee payment: 5

Ref country code: DE

Payment date: 20220617

Year of fee payment: 5

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

Ref country code: GB

Payment date: 20230523

Year of fee payment: 5

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

Effective date: 20231222

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: 20220413

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: 20220413