EP4136323B1 - Aube de turbine et procédé d'usinage associé - Google Patents
Aube de turbine et procédé d'usinage associé Download PDFInfo
- Publication number
- EP4136323B1 EP4136323B1 EP21731686.8A EP21731686A EP4136323B1 EP 4136323 B1 EP4136323 B1 EP 4136323B1 EP 21731686 A EP21731686 A EP 21731686A EP 4136323 B1 EP4136323 B1 EP 4136323B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- cooling
- air outlet
- outlet opening
- leaf
- 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
- 238000000034 method Methods 0.000 title claims description 6
- 238000003754 machining Methods 0.000 title claims description 4
- 238000001816 cooling Methods 0.000 claims description 79
- 238000011144 upstream manufacturing Methods 0.000 claims description 7
- 230000035882 stress Effects 0.000 description 7
- 238000005266 casting Methods 0.000 description 5
- 230000008646 thermal stress Effects 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000008092 positive effect 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
- 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
- F01D5/185—Liquid 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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on 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
- F01D5/186—Film 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
- F01D5/18—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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
-
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
-
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
-
- 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
- F05D2240/304—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 trailing 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
- 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
- F05D2240/305—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 pressure side 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/12—Two-dimensional rectangular
-
- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/13—Two-dimensional trapezoidal
-
- 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 turbine blade for a gas turbine with a blade root and an aerodynamically curved blade arranged above the blade root, wherein the blade has a pressure-side blade wall and a suction-side blade wall, which together extend from a front edge of the blade against which a working medium can flow to a trailing edge of the blade, wherein a plurality of cooling air outlet openings are formed on the pressure-side blade wall, each of which extends upstream from the trailing edge in relation to the flow direction of a working medium flowing around the blade and through which cooling air guided through the interior of the blade can exit, wherein at least one of the cooling air outlet openings has a substantially rectangular or trapezoidal shape with rounded corners, which preferably widens in the direction of exit of the cooling air.
- the invention further relates to a method for machining such a turbine blade.
- Turbine blades of the type mentioned at the outset are known in the prior art in various designs. During operation, they are exposed to high thermal loads, which is why their blades are cooled to increase their service life. For this purpose, cooling air is introduced through the blade root into the blade, which exits essentially axially into the flow channel of the working medium through the cooling air outlet openings provided on the pressure-side blade wall in the area of the trailing edge.
- the cooling air outlet openings have an essentially trapezoidal and/or rectangular shape, which widens in the direction of the cooling air exit, and are often also referred to as cut-back openings.
- One problem is that the provision of such cooling air outlet openings geometric stresses are induced in the blade.
- the cooling caused by the cooling air is not uniform in the area of the cooling air outlet openings, which leads to thermally induced stresses.
- These geometric and thermal stresses can limit the service life of the turbine blade and mean that turbine blades have to be replaced frequently as part of maintenance work. Attempts to counteract the negative effects of the stresses by stiffening the blade in the area of the cooling air outlet openings were unsuccessful. As a result, either an increased risk was permitted or the turbine blades were restricted in terms of their service life.
- the EP 1 555 390 A1 discloses a turbine blade for a gas turbine with a blade root and an aerodynamically curved blade arranged above the blade root, wherein the blade has a pressure-side blade wall and a suction-side blade wall, which together extend from a front edge of the blade against which a working medium can flow to a trailing edge of the blade, wherein a plurality of cooling air outlet openings are formed on the pressure-side blade wall, each of which extends upstream from the trailing edge with respect to the flow direction of a working medium flowing around the blade and through which cooling air guided through the interior of the blade can exit, wherein at least one of the cooling air outlet openings has a substantially rectangular or trapezoidal shape with rounded corners, which preferably widens in the outlet direction of the cooling air.
- the present invention provides a turbine blade for a gas turbine with a blade root and an aerodynamically curved blade arranged above the blade root, wherein the blade has a pressure-side blade wall and a suction-side blade wall, which together extend from a front edge of the blade against which a working medium can flow to a rear edge of the blade, wherein a plurality of cooling air outlet openings are formed on the pressure-side blade wall, each of which extends upstream from the rear edge with respect to the flow direction of a working medium flowing around the blade and through which cooling air guided through the interior of the blade can exit, wherein at least one of the cooling air outlet openings has a substantially rectangular or trapezoidal shape with rounded corners, which preferably widens in the outlet direction of the cooling air, characterized in that at least the lower corner of this at least one cooling air outlet opening pointing towards the front edge forms a relief notch with a rounded notch base protruding outwards from the rectangular shape.
- the relief notch sets the line of a lower edge of the cooling outlet opening with the notch base arranged above the lower edge of the cooling outlet opening pointing towards the front edge of the blade.
- the blade can be manufactured by casting without an undercut in the area of the cooling air outlet opening, which is fundamentally desirable.
- the relief notch extends diagonally downwards at an obtuse angle from the lower edge of the cooling outlet opening, with the notch base arranged below the lower edge of the cooling outlet opening pointing in the direction of the blade root.
- the relief notch widens in a cup-like manner starting from its notch base, whereby a particularly good thermal expansion capacity of the blade in the area of the cooling air outlet opening is achieved.
- At least one cooling air outlet opening is the lowest cooling air outlet opening, since this is where the greatest thermal stresses occur.
- the present invention provides a method for machining a turbine blade with a blade root and an aerodynamically curved blade, wherein the blade has a pressure-side blade wall and a suction-side blade wall, which together extend from a front edge of the blade against which a working medium can flow to a trailing edge of the blade, wherein a plurality of cooling air outlet openings are formed on the pressure-side blade wall, each of which extends upstream from the trailing edge in relation to the direction of a working medium flowing around the blade extend and through which cooling air guided through the interior of the blade can exit, and wherein one of the cooling air outlet openings has a substantially rectangular or trapezoidal shape with rounded corners, characterized in that in at least the lower corner of this at least one cooling air outlet opening pointing towards the front edge, a relief notch with a rounded notch base protruding outwards from the rectangular shape is formed in order to produce a turbine blade according to the invention.
- FIG. 1 shows a known turbine blade 1 for a gas turbine, which in this case is a rotor blade.
- the turbine blade 1 comprises a blade root 2 and an aerodynamically curved blade 3 arranged above the blade root 2.
- the blade 3 has a pressure-side blade wall 4 and a suction-side blade wall 5, which together extend from a front edge 7 of the blade 3, against which a working medium can flow in the direction of arrow 6, to a trailing edge 8 of the blade 3.
- On the pressure-side blade wall 4 a series of cooling air outlet openings 9 are provided along the trailing edge 8, which are designed as so-called cut-back openings.
- the cooling air outlet openings 9 each extend from the trailing edge 8 upstream in relation to the flow direction of the working medium flowing around the blade 3 and serve to discharge cooling air guided through cooling channels present in the interior of the blade 3, not shown in detail here, essentially axially into a flow channel of the working medium.
- the cooling air outlet openings 9 have an essentially rectangular or trapezoidal shape with rounded corners 10, which in the present case widen in the outlet direction of the cooling air.
- the shapes of the lowest cooling air outlet opening 9 and the top three cooling air outlet openings 9 are considered to be rather rectangular, even if they widen slightly in the direction of the cooling air outlet, while all other cooling air outlet openings 9 are more trapezoidal in shape.
- Figure 2 shows an enlarged view of the lowest cooling air outlet opening 9, which is characterized by the fact that In their area the thermal stresses are particularly high or highest during operation of the turbine blade 1.
- the Figures 3 and 4 show a turbine blade 1 according to a first embodiment of the present invention, which is based on the Figures 1 and 2 The turbine blade 1 shown was manufactured.
- the turbine blade 1 shown differs from the one shown in the Figures 1 and 2 shown turbine blade 1 only with regard to the design of the lowermost cooling air outlet opening 9, as can be seen from a comparison of the Figures 2 and 4 is evident.
- the lower corner 10 of the cooling air outlet opening 9 facing the front edge was Figure 4 shown cooling air outlet opening 9 is provided with a relief notch 11 with a rounded notch base 12 that protrudes outward from the rectangular shape.
- the relief notch 11 here continues the line of the lower edge 13 of the cooling outlet opening 9, with the notch base 12 arranged above the lower edge 13 of the cooling outlet opening 9 pointing in the direction of the front edge 7 of the blade 3.
- Such a relief notch 11 can be machined into the shape shown in Figure 2 shown cooling air outlet opening 9. It results in thermal stresses in the area of the cooling air outlet opening 9 being significantly reduced during operation of the turbine blade 1, which results in a noticeable extension of the service life of the turbine blade 1.
- the Figures 5 and 6 show a turbine blade 1 according to a second embodiment of the present invention, which is based on the Figures 1 and 2 The turbine blade 1 shown was manufactured.
- the turbine blade 1 shown differs from the one shown in the Figures 1 and 2 shown turbine blade 1 only with regard to the design of the lowermost cooling air outlet opening 9, as can be seen from a comparison of the Figures 2 and 6 is evident.
- the lower corner 10 of the cooling air outlet opening 9 facing the front edge 7 was Figure 6 shown cooling air outlet opening 9 is provided with a relief notch 11 with a rounded notch base 12 that protrudes outwards from the rectangular shape.
- the relief notch 11 extends diagonally downwards at an obtuse angle starting from the lower edge 13 of the cooling outlet opening 9.
- the notch base 12 arranged below the lower edge 13 of the cooling outlet opening 9 points in the direction of the blade root 2, with the relief notch 11 widening like a cup starting from its notch base 12.
- the Figure 6 The relief notch 11 shown can be machined into the recess 12 shown in Figure 2
- the cooling air outlet opening 9 shown in FIG. 1 is designed to reduce thermal stresses in the area of the cooling air outlet opening 9 during operation of the turbine blade 1, which results in a noticeable extension of the service life of the turbine blade 1.
- the shape of the cooling air outlet opening 9 shown in FIG. 1 is Figure 6 cooling air outlet opening 9 or its relief notch 11 is more favorable than the cooling air outlet opening 9 Figure 4 shown form.
- They have undercuts that can only be realized with increased effort in terms of casting technology if the Figures 5 and 6
- the turbine blade 1 shown is realized as part of a new production.
- cooling air outlet openings 9 and/or other cooling air outlet openings than the lowest cooling air outlet opening 9 can be provided with a relief notch 11.
- the present invention is defined by the appended claims 1 to 6.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (6)
- Aube (1) de turbine pour une turbine à gaz comprenant une emplanture (2) d'aube et un corps (3) d'aube incurvé aérodynamiquement et disposé au-dessus de l'emplanture (2) de l'aube, dans laquelle le corps (3) de l'aube a un intrados (4) et un extrados (5), qui s'étendent conjointement d'un bord (7) avant, où peut affluer un fluide de travail, du corps (3) de l'aube, à un bord (8) arrière du corps (3) de l'aube, dans laquelle sur l'intrados (4) est constitué une pluralité d'ouvertures (9) de sortie d'air de refroidissement, qui chacune, à partir du bord (8) arrière, rapporté au sens d'écoulement d'un fluide de travail passant autour du corps (3) de l'aube, s'étendent vers l'amont et par lesquelles de l'air de refroidissement passant à l'intérieur du corps (3) de l'aube peut sortir, dans laquelle au moins l'une des ouvertures (9) de sortie de l'air de refroidissement a une forme sensiblement rectangulaire ou trapézoïdale à sommets arrondis, qui de préférence s'élargit dans le sens de sortie de l'air de refroidissement, caractérisée en ce qu'au moins le sommet (10) inférieur, tourné vers le bord (7) avant de cette au moins une ouverture (9) de sortie de l'air de refroidissement, forme une encoche (11) de détente en saillie vers l'extérieur de la forme rectangulaire à fond (12) d'encoche arrondie.
- Aube (1) de turbine suivant la revendication 1,
caractérisée en ce que
l'encoche (11) de détente suit la ligne d'un bord (13) inférieur de l'ouverture (9) de sortie de refroidissement, et en ce que le fond (12) de l'encoche disposé au-dessus du bord (13) inférieur de l'ouverture (9) de sortie de refroidissement est tourné dans la direction du bord (7) avant du corps (3) de l'aube. - Aube (1) de turbine suivant la revendication 1,
caractérisée en ce que
l'encoche (11) de détente s'étend à partir du bord (13) inférieur de l'ouverture (9) de sortie de refroidissement vers le bas d'une manière inclinée suivant un angle obtus, et en ce que le fond (12) de l'encoche disposé en-dessous du bord inférieur de l'ouverture (9) de sortie de refroidissement est tourné dans la direction de l'emplanture (2) de l'aube. - Aube (1) de turbine suivant la revendication 3,
caractérisée en ce que
l'encoche (11) de décharge s'élargit en forme de coupe à partir de son fond (12) d'encoche. - Aube (1) de turbine suivant l'une des revendications précédentes,
caractérisée en ce que la au moins une ouverture (9) de sortie d'air de refroidissement est l'ouverture (9) de sortie de l'air de refroidissement la plus basse. - Procédé d'usinage d'une aube (1) de turbine, comprenant une emplanture (2) d'aube et un corps (3) d'aube incurvé aérodynamiquement, dans lequel le corps (3) de l'aube a un intrados (4) et un extrados (5), qui s'étendent conjointement d'un bord (7) avant, où peut affluer un fluide de travail du corps (3) de l'aube, à un bord (8) arrière du corps (3) de l'aube, dans lequel sur l'intrados (4) est constitué une pluralité d'ouvertures (9) de sortie de l'air de refroidissement, qui chacune, à partir du bord (8) arrière, rapporté au sens d'écoulement d'un fluide de travail passant autour du corps (3) de l'aube, s'étendent vers l'amont et par lesquelles de l'air de refroidissement passant à l'intérieur du corps (3) de l'aube peut sortir, dans lequel au moins l'une des ouvertures (9) de sortie de l'air de refroidissement a une forme sensiblement rectangulaire ou trapézoïdale à sommets (10) arrondis, caractérisé en ce que l'on forme dans au moins le sommet (10) inférieur, tourné vers le bord (7) avant, de cette au moins une ouverture (9) de sortie de l'air de refroidissement, une encoche (11) de détente en saillie vers l'extérieur de la forme rectangulaire à fond (12) d'encoche arrondie, afin de fabriquer une aube (1) de turbine suivant l'une des revendications 1 à 5.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102020207646.4A DE102020207646A1 (de) | 2020-06-22 | 2020-06-22 | Turbinenschaufel und Verfahren zum Bearbeiten einer solchen |
PCT/EP2021/063617 WO2021259569A1 (fr) | 2020-06-22 | 2021-05-21 | Aube de turbine et son procédé d'usinage |
Publications (2)
Publication Number | Publication Date |
---|---|
EP4136323A1 EP4136323A1 (fr) | 2023-02-22 |
EP4136323B1 true EP4136323B1 (fr) | 2024-05-29 |
Family
ID=76392325
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP21731686.8A Active EP4136323B1 (fr) | 2020-06-22 | 2021-05-21 | Aube de turbine et procédé d'usinage associé |
Country Status (5)
Country | Link |
---|---|
US (1) | US11867083B2 (fr) |
EP (1) | EP4136323B1 (fr) |
KR (1) | KR20230027211A (fr) |
DE (1) | DE102020207646A1 (fr) |
WO (1) | WO2021259569A1 (fr) |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1318274B1 (fr) * | 2001-12-10 | 2004-09-22 | Snecma Moteurs | Aube de turbine haute-pression ayant un bord de fuite refroidi |
EP1555390B1 (fr) * | 2004-01-14 | 2006-11-22 | Snecma | Fentes d'évacuation de l'air de refroidissement d'aubes de turbine |
EP2685049B1 (fr) * | 2011-03-11 | 2018-05-23 | IHI Corporation | Aube de turbine |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6612811B2 (en) | 2001-12-12 | 2003-09-02 | General Electric Company | Airfoil for a turbine nozzle of a gas turbine engine and method of making same |
US20100034662A1 (en) * | 2006-12-26 | 2010-02-11 | General Electric Company | Cooled airfoil and method for making an airfoil having reduced trail edge slot flow |
JP6025110B2 (ja) | 2011-11-30 | 2016-11-16 | 株式会社Ihi | タービン翼 |
US9175569B2 (en) | 2012-03-30 | 2015-11-03 | General Electric Company | Turbine airfoil trailing edge cooling slots |
US9045987B2 (en) | 2012-06-15 | 2015-06-02 | United Technologies Corporation | Cooling for a turbine airfoil trailing edge |
US8920123B2 (en) * | 2012-12-14 | 2014-12-30 | Siemens Aktiengesellschaft | Turbine blade with integrated serpentine and axial tip cooling circuits |
US9732617B2 (en) * | 2013-11-26 | 2017-08-15 | General Electric Company | Cooled airfoil trailing edge and method of cooling the airfoil trailing edge |
FR3021699B1 (fr) * | 2014-05-28 | 2019-08-16 | Safran Aircraft Engines | Aube de turbine a refroidissement optimise au niveau de son bord de fuite |
WO2016068856A1 (fr) | 2014-10-28 | 2016-05-06 | Siemens Aktiengesellschaft | Agencement de passages de refroidissement pour aubes de moteur de turbine |
EP3043025A1 (fr) * | 2015-01-09 | 2016-07-13 | Siemens Aktiengesellschaft | Composant de turbine à gaz refroidi par couche d'air |
US11002138B2 (en) * | 2017-12-13 | 2021-05-11 | Solar Turbines Incorporated | Turbine blade cooling system with lower turning vane bank |
-
2020
- 2020-06-22 DE DE102020207646.4A patent/DE102020207646A1/de not_active Withdrawn
-
2021
- 2021-05-21 KR KR1020237002086A patent/KR20230027211A/ko unknown
- 2021-05-21 WO PCT/EP2021/063617 patent/WO2021259569A1/fr unknown
- 2021-05-21 US US18/009,402 patent/US11867083B2/en active Active
- 2021-05-21 EP EP21731686.8A patent/EP4136323B1/fr active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1318274B1 (fr) * | 2001-12-10 | 2004-09-22 | Snecma Moteurs | Aube de turbine haute-pression ayant un bord de fuite refroidi |
EP1555390B1 (fr) * | 2004-01-14 | 2006-11-22 | Snecma | Fentes d'évacuation de l'air de refroidissement d'aubes de turbine |
EP2685049B1 (fr) * | 2011-03-11 | 2018-05-23 | IHI Corporation | Aube de turbine |
Also Published As
Publication number | Publication date |
---|---|
US20230220778A1 (en) | 2023-07-13 |
EP4136323A1 (fr) | 2023-02-22 |
DE102020207646A1 (de) | 2021-12-23 |
KR20230027211A (ko) | 2023-02-27 |
WO2021259569A1 (fr) | 2021-12-30 |
US11867083B2 (en) | 2024-01-09 |
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