EP3341568A1 - Turbine blade having a groove in the crown base - Google Patents
Turbine blade having a groove in the crown baseInfo
- Publication number
- EP3341568A1 EP3341568A1 EP16762993.0A EP16762993A EP3341568A1 EP 3341568 A1 EP3341568 A1 EP 3341568A1 EP 16762993 A EP16762993 A EP 16762993A EP 3341568 A1 EP3341568 A1 EP 3341568A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- wall
- turbine blade
- relief
- flow chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000001816 cooling Methods 0.000 claims abstract description 39
- 238000005192 partition Methods 0.000 claims description 73
- 238000011144 upstream manufacturing Methods 0.000 claims description 2
- 230000008646 thermal stress Effects 0.000 description 6
- 239000011248 coating agent Substances 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 238000000926 separation method Methods 0.000 description 3
- 239000002689 soil Substances 0.000 description 3
- 230000001419 dependent effect Effects 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 241000270728 Alligator Species 0.000 description 1
- 210000004072 lung Anatomy 0.000 description 1
- 229920000136 polysorbate Polymers 0.000 description 1
- 108090000623 proteins and genes Proteins 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
- F05D2240/307—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 tip 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
Definitions
- Turbine blade groove in the crown ground The invention relates to a turbine blade for use in a gas turbine having a blade root and a display ⁇ felblatt, wherein the crown base of the airfoil is a cooling air opening exists.
- Turbine blades for use in a gas turbine are known in various embodiments, which usually have at least one blade root for attachment in the jewei ⁇ term turbine stage and an on the blade root anschlie ⁇ nddes airfoil.
- the blade is in this case aerodynamically shaped, wherein the specific shape of the inventive embodiment is initially irrelevant.
- the blade is first formed once by a blade wall, which extends from the blade root to ei ⁇ nem free end. There, as a rule, the free end of the blade by a crown land is striglos ⁇ sen.
- Cooling air ducts pass through the interior of the turbine blade.
- both exporting ⁇ approximately forms are known, in which the cooling air is returned to the blade root, as well as cooling air holes in the blade wall and the bottom crown are arranged, via which the cooling air can escape.
- Known embodiments for a turbine blade with cooling channels are disclosed in the publications EP 1 557 553 A1 and EP 2 863 013 A1. For selective determination of the cooling air flow through the generally existing in plurality cooling air openings on the blade blade this cooling air opening are distributed in a suitable manner and usually out as a round hole out ⁇ leads.
- the object of the present invention is therefore to reduce thermal stresses due to different temperature distributions in the airfoil.
- the object is achieved by an inventive from ⁇ guide die according to the teaching of claim 1.
- a generic turbine blade initially serves for use in a turbine of a gas turbine.
- the turbine blade has a blade root and an airfoil adjoining the blade root.
- the blade is curved aerodynamically, so that by means of the turbine blade effective generation of rotation in the rotor of the gas turbine can be effected.
- the blade is initially formed by a blade wall, which extends from the blade root in the direction of a free end.
- the blade wall comprises a pressure-side Wandab ⁇ section and a suction-side wall portion, both of which extend from a leading edge (rounded off as a rule) of the airfoil to a trailing edge (usually tapered) of the airfoil.
- a crown bottom is arranged, which is the
- a cavity is formed, which encloses at least a first and a second flow chamber.
- At least the first flow chamber is separated from the second flow chamber by a first partition wall.
- ⁇ at both the first and second flow chamber, and the first partition wall extending also from the blade root in the direction of the free end of the airfoil.
- a free opening is present, which forms a connection between the first and second flow chamber so that the
- Cooling air coming from the second flow chamber can flow through the opening into the first flow chamber.
- the breakthrough extends over the entire width of the partition wall and thus limited to the top or one with respect to the partition has smaller width and thus on the one and / or other Be ⁇ te a piece of the partition remains ,
- the generic turbine blade in Kro ⁇ nen at least one cooling air opening, which opens into the first and / or second flow chamber and can escape through the consequently cooling air from the interior of the turbine blade to the free end.
- the cooling air opening is in this case arranged at a distance from the wall sections, wherein generically the exact position is initially insignificant.
- the object is achieved according to the invention in that instead of a further distribution of cooling air openings over the surface of the crown base at least one cooling air opening is executed as a relief groove, which is arranged above the ers ⁇ th breakthrough.
- two embodiments according to the invention are contemplated, wherein in a first embodiment of the invention, a single relief groove is used.
- a second embodiment according to the invention on the other hand, it is provided that at least two relief grooves are used, which in this case are to be arranged offset next to one another above the first opening.
- the one relief groove or the Entlastungsnu ⁇ th together at least a minimum length, which corresponds to half the width of the partition.
- the length of the relief can be true ⁇ be in two ways. On one hand, the immediate length can be measured inde ⁇ dependent of the shape of one end of the relief groove to the other end of the relief, ie, the length of a straight line connecting the two ends of the respective relief. However, to take into account the effectiveness of the reduction of thermally induced stresses, the shape of the relief groove in relation to the position of the partition.
- the effective minimum ge the individual relief groove or by the relief grooves measured together in a direction transverse to the first partition. That is, in this case, the minimum length corresponds to a perpendicular to the partition, which in each case to the first
- ⁇ corresponds to the immediate length of the minimum length. If there are two or more relief grooves, this consideration of the minimum effective length applies to a common consideration of the two or more relief grooves measured in a direction transverse to the first partition.
- each of the least two relief grooves In the case of at least two relief grooves, they must overlap in such a way that, in the region of the first partition wall, above the first opening there is an interruption in the crown bottom in the connection from the pressure-side wall section to the suction-side wall section.
- the two or more relief grooves are likewise to be arranged, as in the case of the use of a single relief groove, such that they extend on both sides beyond the opening when they are viewed together. Furthermore, each of the least two relief grooves extend at least until breakthrough.
- the individual relief groove or the two or more relief grooves are located substantially centrally between the suction-side wall section and the pressure-side wall section in the crown bottom. The exact position is reciprocable against unimportant so long as a thermally induced expansion of the top of the soil due to the crown Entlas ⁇ tungsnut or relief grooves on both sides is possible.
- the individual relief groove or, in an alternative embodiment, the two or more relief grooves are located substantially in the middle of the dividing wall. Since in particular the first partition wall is the cause of the thermal stresses in the crown bottom, it is correspondingly advantageous to arrange the relief groove or the relief grooves centrally to this first partition wall. Provided that the length of the relief groove is extended beyond the required level, it is by contrast of undergeordne ⁇ ter importance whether the extension of one side only is carried by the partition.
- the specific orientation of the relief groove or the plurality of relief grooves is irrelevant initially, provided that a corresponding thermal expansion of the crown base on the outwardly facing side is possible due to the presence of the relief groove.
- a straight line rectangular orientation is not required here, but it is sufficient if the relief groove ver ⁇ runs according to the course of the pressure-side wall portion and the suction-side wall portion. In this respect, for example, angle deviations of 15 ° from an orientation perpendicular to the partition wall unerheb ⁇ Lich.
- the effectiveness of the relief groove is improved in a particularly advantageous manner ⁇ when the single relief egg having ne minimum effective length corresponding to the width of the separation ⁇ wall, ie, the minimum length is equal to at least 1 times the width of the first partition wall.
- each of the relief grooves has a length of at least 0.3 times the width of the first partition wall. Particularly advantageous is the length of the respective relief grooves at least the
- the minimum length of the at least two relief grooves ⁇ together at least the
- the relief grooves together have a minimum length of at least 1 times, preferably 1.2 times, the width of the first dividing wall.
- the first breakthrough vorranging is used to relieve the crown bottom and nachranging the cooling air flow. It is particularly advantageous if the height of the first breakthrough measured from the inwardly facing bottom of the crown bottom to the largest distance of the first opening to the crown bottom corresponds to a maximum of 2 times the thickness of the crown bottom. In any case, it is particularly advantageous for enabling the thermally induced expansions in the crown bottom when the height (as indicated above) of the first breakthrough corresponds to at least 0.5 times the thickness of the crown bottom.
- the first aperture has a free cross-section (area of the first aperture viewed in a plane of the first partition) which is at most 0.8 times the smallest free cross-section (viewed in a plane parallel to the top of the crown ) corresponds to the individual relief groove in the first embodiment or the at least two relief grooves together in the second embodiment.
- the free cross-section of the first opening should advantageously be at least equal to 0.2 times the free cross-section of the relief groove or the relief grooves.
- the course of the relief groove or the relief grooves is initially irrelevant, in the simplest way a geradli ⁇ niger course is selected.
- the side facing the pressure side wall portion sides ⁇ surface of the relief groove or the relief grooves a bo- genförmigen course corresponding to the curvature of tikseiti ⁇ gene wall section has or have.
- the suction-side wall portion facing side surface of the relief groove or the relief grooves nen arcuate course corresponding to the curvature of the suction ⁇ side wall section has or have.
- the relief groove follows the course of the pressure-side or suction-side wall section.
- the relief groove is performed inclined. It is advantageous if the wegwei ⁇ send from the blade end of the relief, that is, to the outside wei ⁇ send end of the relief groove, closer to the pressure side WALL COMP ⁇ cut than facing the blade root end of Entlas ⁇ tungsnut, that is adjacent to the breakthrough end the relief groove, is located.
- the relief invention is used in particular before ⁇ more advantageous manner at a partition wall, wherein the first flow chamber is disposed at a downstream edge or trailing edge of the airfoil. Adjoining the ers ⁇ th flow chamber trailing edge connects the pressure side wall portion to the suction side wall clearances cut. In this regard, it is irrelevant whether elements for guiding the flow and / or stiffening of the airfoil are present in the first flow chamber facing the downstream edge.
- the second partition also adjoins the second flow chamber and is located opposite the first partition in connection with the pressure-side wall section with the suction-side wall section.
- Above the second partition is the same ⁇ if a second free breakthrough.
- Adjacent to the second partition wall opposite the second flow chamber is a third flow chamber, wherein cooling air can flow from the third flow chamber to the second flow chamber through the second passage.
- the third flow chamber adjoins an inflow-side edge of the airfoil or a leading edge, which connects the pressure-side wall section with the suction-side wall section opposite the trailing edge.
- the size of the second breakthrough is initially irrelevant, which advantageously has at least twice the size of the first breakthrough.
- the free cross-section ⁇ of the first aperture is not more than 0.5 times the free cross section of the second breakthrough.
- the second opening has at least 5 times the size of the first opening.
- both the second opening may have a width which is smaller than the width of the second partition wall, and the second opening may extend over the width of the second partition wall in an advantageous manner, limiting it to the top on the side facing the crown bottom.
- the cooling air flowing through the turbine blade is guided essentially through the second opening, but only to a small extent through the first opening.
- the first opening has a free cross section of at most 0.1 times the free cross section of the second opening.
- Partition wall for dividing the cavity present in the blade in a first flow chamber, a second Strö ⁇ tion chamber and a third flow chamber it is particularly advantageous if the first flow chamber and the first partition on the side facing the downstream edge and the third flow chamber and the second partition wall the side of the airfoil facing the upstream side is arranged.
- the end of the first partition wall also has a free third one on the blade root
- Breakthrough is present, so that the cooling air from the drit ⁇ th flow chamber via the second opening in the second flow chamber and proportionately over the first opening and the majority via the third opening in the first flow chamber to flow.
- the crown bottom is located exactly at the end of the blade wall and thus forms the end of the blade.
- it is above ⁇ geous when the crown ground against the end of the blade wall is reset, and so far at least portion ⁇ , the pressure side wall section and / or the suction-side wall section extends beyond the crown ground.
- ⁇ tive it is also possible to Kronenteil at the end of
- a coating is advantageously applied to the crown bottom.
- vorgese ⁇ hen be that a coating is applied prior to the generation of the relief groove.
- a coating is applied to the relief with the shipping ⁇ Henen crown ground.
- the second variant bie ⁇ tet the particular advantage that the coating can be applied to the outside ends of the side surfaces of the relief, at least to some extent, whereby the gap is wide reduced.
- the cooling air flow can be reduced by the relief groove, wherein the desired expansion clearance is maintained to a sufficient extent.
- FIG. 2 shows a section through the blade leaf in the middle between the pressure-side and the suction-side wall section; 3 shows a plan view of the blade with a first embodiment of a relief groove;
- FIG. 4 shows a plan view of the blade with an age ⁇ native arrangement of relief grooves.
- FIG 5 shows a section through the blade parallel to the ers ⁇ th partition with an inclined relief groove
- 6 shows a section similar to FIG 5 with an expanding relief groove.
- the FIG 1 shows an example of a turbine blade oil with egg ⁇ nem blade root 02 and one is subsequently ⁇ sequent at the vane airfoil 03.
- the embodiment of the Schaufelfu ⁇ SSES 02 is irrelevant to the present invention and domestic long as is not to be discussed in more detail on this.
- the airfoil 03 comprises first of all the show ⁇ felwand 04, which 04 in this embodiment is formed by a pressure-side wall portion 05 (in drawing ⁇ level front lying) and a suction-side wall portion 06 (lying in the drawing plane behind), which 05, 06 both extend from a leading edge to a trailing edge.
- the blade wall encloses a cavity 04, in turn wel ⁇ cher from flow chambers 11, 12 is formed. 13
- the on alligator is nenboden 07, which in this embodiment opposite to the end of the airfoil is 07 03 slightly Retired ⁇ sets.
- the cavity through a first separation element 08 and a second Trennele ⁇ element 09 into a first flow chamber 11 between the rear edge and the first partition wall 08 and a second Strö ⁇ mung chamber 12 between the first partition wall 08 and the second partition wall is 09 and in a third flow chamber 13 between ⁇ tween the second partition wall 09 and the leading edge under ⁇ divides.
- the relief groove 21 in the crown bottom 07 can be seen.
- FIG 2 now shows a schematic section through the blade 03 in a view cut centrally between the pressure-side wall portion 05 and the suction-side wall portion 06.
- the blade ⁇ wall 04 can be seen with the leading edge and the trailing edge.
- the crown bottom 07 On the upper side is the crown bottom 07, which 07 is slightly set back relative to the end of the blade wall 04.
- Within ⁇ within the airfoil 03 are the first partition wall 08 and the second partition 09, which 08, 09 the hollow ⁇ space in the interior of the airfoil 04 in the first flow ⁇ chamber 11, the second flow chamber 12 and the third flow chamber thirteenth divide.
- a flow of cooling air flows from the third flow chamber 13 into the second flow chamber 12 and subsequently into the first flow chamber 11.
- the cooling air can be arranged on the trailing edge in the blade wall 04 cooling air holes 18.
- a second free breakthrough 15 To Reali ⁇ tion of the transition of the cooling air from the first flow ⁇ chamber 11 to the second flow chamber 12 is located between the second partition 09 and the crown floor 07, a second free breakthrough 15.
- Partition 15 a first free opening 14 arranged at the crown bottom 07 facing end. Also located in the crown bottom 07 has at least one relief groove 21. This 21 he ⁇ extends in this case centrally over the opening 14 and made ⁇ light thus thermal expansion of the top of Kro ⁇ nenteils 07 while holding the pressure-side wall portion 05 with the suction-side wall portion 06 through the first partition 08.
- FIG 3 now shows a plan view of the blade 03, wherein first again the blade wall 04 with the pressure-side wall portion 05 and the suction-side wall portion 06 can be seen.
- ⁇ disposed relief groove 21 Above the first partition wall 08 is located centrally in the crown bottom 07 is ⁇ disposed relief groove 21.
- This comprises 21 in this exemplary embodiment a Length L, measured transversely to the dividing wall, which L approximately corresponds to the width B of the partition wall.
- FIG 4 a plan view of the blade is 03 outlined in a further embodiment analogous to FIG.
- ⁇ extending relief grooves 22a in the bottom 07 instead of a single crown ⁇ NEN relief groove 21, 22b and 22cenfin- puts.
- These 22, 22b2, 22c extend in this case also over the first partition wall 08 and in this case are arranged centrally to the first partition wall 08.
- the length L of the considered three relief grooves 22a, 22b and 22c measured transversely to the first partition wall 08 is hereby slightly larger than the width B of the first partition wall 08th
- the relief groove 21 is sketched by way of example in a section parallel to the partition wall 08.
- the relief groove 21 is inclined ⁇ ge in this embodiment.
- the upper-side, outwardly wei ⁇ send end of the relief groove 21 is approximately centrally in Kronenbo- 07 between the pressure-side wall portion 05 and the suction-side wall portion 06.
- the relief groove 21st is outlined, in which the representation is carried out analogously to FIG.
- the Ent ⁇ lastungsnut 23 centrally between the two ends of the ⁇ Entlas tungsnut a smallest cross-section, starting the relief in both directions, that widens from the 23 inwardly and outwardly. This allows on the one hand a limitation of the cooling air and on the other hand this simplifies the production of the relief groove 23rd
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP15187014.4A EP3147456A1 (en) | 2015-09-28 | 2015-09-28 | Turbine blade with groove in crown base |
PCT/EP2016/070352 WO2017054996A1 (en) | 2015-09-28 | 2016-08-30 | Turbine blade having a groove in the crown base |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3341568A1 true EP3341568A1 (en) | 2018-07-04 |
EP3341568B1 EP3341568B1 (en) | 2021-03-24 |
Family
ID=54207376
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15187014.4A Withdrawn EP3147456A1 (en) | 2015-09-28 | 2015-09-28 | Turbine blade with groove in crown base |
EP16762993.0A Active EP3341568B1 (en) | 2015-09-28 | 2016-08-30 | Turbine blade with groove in crown base |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15187014.4A Withdrawn EP3147456A1 (en) | 2015-09-28 | 2015-09-28 | Turbine blade with groove in crown base |
Country Status (3)
Country | Link |
---|---|
US (1) | US20180298764A1 (en) |
EP (2) | EP3147456A1 (en) |
WO (1) | WO2017054996A1 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11021967B2 (en) * | 2017-04-03 | 2021-06-01 | General Electric Company | Turbine engine component with a core tie hole |
US10815816B2 (en) | 2018-09-24 | 2020-10-27 | General Electric Company | Containment case active clearance control structure |
US11459894B1 (en) | 2021-03-10 | 2022-10-04 | Raytheon Technologies Corporation | Gas turbine engine airfoil fairing with rib having radial notch |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2468727A1 (en) * | 1979-10-26 | 1981-05-08 | Snecma | IMPROVEMENT TO COOLED TURBINE AUBES |
US6491496B2 (en) * | 2001-02-23 | 2002-12-10 | General Electric Company | Turbine airfoil with metering plates for refresher holes |
FR2865502B1 (en) | 2004-01-23 | 2006-03-03 | Snecma Moteurs | MONOBLOC ARM-FLAMES ARM FOR A POST COMBUSTION DEVICE OF A DOUBLE FLOW TURBOREACTOR |
US7118337B2 (en) * | 2004-06-17 | 2006-10-10 | Siemens Power Generation, Inc. | Gas turbine airfoil trailing edge corner |
EP2196625A1 (en) * | 2008-12-10 | 2010-06-16 | Siemens Aktiengesellschaft | Turbine blade with a hole extending through a partition wall and corresponding casting core |
EP2863013A1 (en) | 2013-10-21 | 2015-04-22 | Siemens Aktiengesellschaft | Arrangement of cooling channels in a turbine blade in a bowed structure |
-
2015
- 2015-09-28 EP EP15187014.4A patent/EP3147456A1/en not_active Withdrawn
-
2016
- 2016-08-30 US US15/762,687 patent/US20180298764A1/en not_active Abandoned
- 2016-08-30 WO PCT/EP2016/070352 patent/WO2017054996A1/en active Application Filing
- 2016-08-30 EP EP16762993.0A patent/EP3341568B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
WO2017054996A1 (en) | 2017-04-06 |
US20180298764A1 (en) | 2018-10-18 |
EP3147456A1 (en) | 2017-03-29 |
EP3341568B1 (en) | 2021-03-24 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1113145B1 (en) | Blade for gas turbines with metering section at the trailing edge | |
EP2384393B1 (en) | Cooled vane for a gas turbine | |
DE69916368T2 (en) | Particle trap in the cooling system of gas turbines | |
EP2696029B1 (en) | Blade row with side wall contours and fluid flow engine | |
DE102007037924A1 (en) | Turbomachine with Ringkanalwandausnehmung | |
DE102010061376A1 (en) | Improvement of heat transfer in internal cavities of turbine blades | |
EP3329120B1 (en) | Wind turbine rotor blade | |
CH698339B1 (en) | Turbine blade having a cooled shroud. | |
DE2241194A1 (en) | FLOW MACHINE SHOVEL WITH A WING-SHAPED CROSS-SECTIONAL PROFILE AND WITH A NUMBER OF COOLING DUCTS RUNNING IN THE LENGTH DIRECTION OF THE SHOVEL | |
EP3341568A1 (en) | Turbine blade having a groove in the crown base | |
EP2538024A1 (en) | Blade of a turbomaschine | |
EP3548732A1 (en) | Rotor blade for a wind turbine and wind turbine | |
EP3207217B1 (en) | Film-cooled gas turbine component | |
EP3263838A1 (en) | Turbine blade having internal cooling passage | |
DE3148995A1 (en) | Axial turbine | |
WO2017148669A1 (en) | Serrations comprising relief slots | |
EP2679803A1 (en) | Wind energy assembly rotor blade with a thick profile trailing edge | |
EP3269928A1 (en) | Turbine blade with strut- shaped cooling fins | |
WO2015158514A1 (en) | Turbine blade and turbine | |
DE102013221227A1 (en) | Device for cooling a wall of a component | |
WO2015044008A1 (en) | Insert made of multiple segments, for cooling a turbine blade | |
EP2860348A1 (en) | Insert consisting of several parts for a turbine blade and corresponding method | |
EP3085894A1 (en) | Blade and corresponding manufacturing method | |
EP3839347A1 (en) | Heat shield tile of a combustion chamber | |
EP3199760A1 (en) | Turbine blade with a throttle element |
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: 20180209 |
|
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 |
|
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: 20201119 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG |
|
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: 502016012670 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: 1374693 Country of ref document: AT Kind code of ref document: T Effective date: 20210415 |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG9D |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20210624 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: 20210324 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: 20210625 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: 20210324 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: 20210624 |
|
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: 20210324 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: 20210324 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: 20210324 |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20210324 |
|
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: 20210324 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20210324 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: 20210324 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: 20210324 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: 20210324 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20210726 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: 20210324 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: 20210324 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: 20210324 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: 20210724 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502016012670 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20210324 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: 20210324 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: 20210324 |
|
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: 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: 20210324 |
|
26N | No opposition filed |
Effective date: 20220104 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
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: 20210324 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20210831 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20210830 |
|
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: 20210831 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210831 |
|
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: 20210724 Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210830 |
|
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: 20210830 Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210830 Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210831 Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210831 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MM01 Ref document number: 1374693 Country of ref document: AT Kind code of ref document: T Effective date: 20210830 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210830 |
|
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: 20160830 |
|
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: 20210324 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20230822 Year of fee payment: 8 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20230828 Year of fee payment: 8 |
|
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: 20210324 |