EP4136323A1 - Aube de turbine et son procédé d'usinage - Google Patents

Aube de turbine et son procédé d'usinage

Info

Publication number
EP4136323A1
EP4136323A1 EP21731686.8A EP21731686A EP4136323A1 EP 4136323 A1 EP4136323 A1 EP 4136323A1 EP 21731686 A EP21731686 A EP 21731686A EP 4136323 A1 EP4136323 A1 EP 4136323A1
Authority
EP
European Patent Office
Prior art keywords
blade
cooling air
air outlet
outlet opening
turbine
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
Application number
EP21731686.8A
Other languages
German (de)
English (en)
Other versions
EP4136323B1 (fr
Inventor
Martin Boeff
Thomas Ruda
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 EP4136323A1 publication Critical patent/EP4136323A1/fr
Application granted granted Critical
Publication of EP4136323B1 publication Critical patent/EP4136323B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • 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, the blade having a pressure-side blade wall and a suction-side blade wall which are joined together by a leading edge of the blade which can be flown against by a working medium
  • the rear edge of the airfoil extends, with a plurality of cooling air outlet openings being formed on the pressure-side airfoil wall, each of which extends upstream from the rear edge based on the flow direction of a working medium flowing around the airfoil and exits through the cooling air directed through the interior of the airfoil can, wherein at least one of the cooling air outlet openings has a substantially union rectangular or trapezoidal shape with rounded corners, which preferably expands in the exit direction of the cooling air.
  • the invention also relates to a method for processing such a turbine blade.
  • Turbine blades of the type mentioned at the beginning are known in the prior art in different configurations. During operation, they are exposed to high thermal loads, which is why their blades are cooled to increase their lifespan.
  • cooling air is introduced through the blade root into the blade, which exits through the cooling air outlet openings provided on the pressure side blade wall in the region of the rear edge essentially axially into the flow channel of the working medium.
  • the cooling air outlet openings have an essentially trapezoidal and / or rectangular shape, which expands in the outlet direction of the cooling air, and are often also referred to as cut-back openings.
  • cut-back openings One problem is that the provision of such cooling air outlet Openings geometric stresses are induced in the airfoil.
  • the cooling caused by the cooling air is not uniform in the area of the cooling air outlet openings, which results in 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 frequently replaced during maintenance work.
  • the attempt to counteract the negative effects of the stresses by stiffening the blade in the area of the cooling air outlet openings was unsuccessful. As a result, either an extended risk was permitted or the turbine blades were given a restriction with regard to their service life.
  • the present invention creates a turbine blade for a gas turbine with a blade root and an aerodynamically curved blade arranged above the blade root, the blade having a pressure-side blade wall and a suction-side blade wall, which jointly extend from one of an Ar
  • the leading edge of the airfoil that can flow against the airflow to a rear edge of the airfoil extend to a rear edge of the airfoil, with a plurality of cooling air outlet openings being formed on the pressure-side airfoil wall, each of which extends upstream from the rear edge in relation to the flow direction of a working medium flowing around the airfoil and through which through the interior of the airfoil Airfoil guided cooling air can exit, wherein at least one of the cooling air outlet openings has a substantially rectangular or trapezoidal shape with rounded corners, which extend in the exit direction of the cooling air preferably expands, characterized in that at least the lower corner facing the front edge of this at least one cooling air outlet opening protrudes outwards from the rectangular
  • the relief notch continues the line of a lower edge of the cooling outlet opening, the notch base arranged above the lower edge of the cooling outlet opening pointing in the direction of the leading edge of the airfoil.
  • the blade in the area of the cooling air outlet opening can be produced by casting without an undercut, which is fundamentally desirable.
  • the relief notch extends from the lower edge of the cooling outlet opening at an obtuse angle obliquely downwards, with the notch base located below the lower edge of the cooling outlet opening pointing towards the blade foot.
  • This variant is of advantage in terms of voltage.
  • the relief notch preferably widens in a cup-like manner starting from its notch base, as a result of which a particularly good thermal expansion capacity of the blade is achieved in the region of the cooling air outlet opening.
  • the at least one cooling air outlet opening is advantageously the lowermost cooling air outlet opening, since this is where the greatest thermal stresses occur.
  • the present invention also provides a method for machining a turbine blade with a blade root and an aerodynamically curved blade, the blade having a pressure-side blade wall and a suction-side blade wall, which jointly extend from a leading edge of the blade that can flow against a working medium to a trailing edge of the blade Extend the airfoil, with a plurality of cooling air outlet openings being formed on the pressure-side airfoil wall, each of which, starting from the rear edge in relation to the direction of a working medium flowing around the airfoil, extends upstream and through which a cooling air guided through the interior of the airfoil 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 facing the front edge of this has at least one In the cooling air outlet opening, a relief notch projecting outwards from the rectangular shape with a rounded notch base is formed in order to produce a turbine blade according to the invention.
  • Figure 1 is a perspective view of a known turbine blade
  • FIG. 2 shows an enlarged view of the section marked with reference number II in FIG. 1, which shows a cooling air outlet opening with a known design
  • FIG. 3 shows a perspective view of the turbine blade shown in FIG. 1 after a method has been carried out according to an embodiment of the present invention
  • FIG. 4 shows an enlarged view of the section identified by reference number IV in FIG. 3, which shows a cooling air outlet opening with a relief notch according to a first embodiment of the present invention
  • FIG. 5 shows a perspective view of the turbine blade shown in FIG. 1 after a method has been carried out according to an embodiment of the present invention.
  • FIG. 6 shows an enlarged view of the section identified by reference number VI in FIG. 5, which shows a cooling air outlet opening with a relief notch according to a second embodiment of the present invention.
  • FIG. 1 shows a known turbine blade 1 for a gas turbine, which in the present 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 are joined together by a leading edge that can be approached by a working medium in the direction of arrow 6 7 of the airfoil 3 extend to a rear edge 8 of the airfoil 3.
  • On the pressure-side vane wall 4 are long the rear edge 8 a number ofdeluftausbergsöff openings 9 are provided, which are presently designed as so-called cut-back openings.
  • the cooling air outlet openings 9 each extend upstream from the rear edge 8 with respect to the flow direction of the working medium flowing around the blade 3 and serve to guide cooling air essentially axially into a flow channel through cooling channels present in the interior of the blade 3, which are not shown in detail here 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 each expands in the outlet direction of the cooling air.
  • the shapes of the lowermost cooling air outlet opening 9 and the top three cooling air outlet openings 9 are viewed as more rectangular, even if they expand slightly in the outlet direction of the cooling air, while all other cooling air outlet openings 9 are more trapezoidal.
  • FIG. 2 shows an enlarged view of the lowermost cooling air outlet opening 9, which is characterized in that the thermal stresses in its area are particularly high or highest during operation of the turbine blade 1.
  • FIGS. 3 and 4 show a turbine blade 1 according to a first embodiment of the present invention, which was produced on the basis of the turbine blade 1 shown in FIGS. 1 and 2.
  • the turbine blade 1 shown in Figures 3 and 4 differs from the turbine blade 1 shown in Figures 1 and 2 only in terms of the design of the lower cooling air outlet opening 9, as can be seen from a comparison of Figures 2 and 4.
  • the lower corner 10 of the cooling air outlet opening 9 shown in FIG rounded notch base 12 provided.
  • the relief notch 11 continues the line of the lower edge 13 of the cooling outlet opening 9, the notch base 12 arranged above the lower edge 13 of the cooling outlet opening 9 pointing in the direction of the leading edge 7 of the blade 3.
  • Such a relief notch 11 can, for example, be introduced into the cooling air outlet opening 9 shown in FIG. 2 using a machining process. It leads to 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 increase in the service life of the turbine blade 1.
  • the turbine blade 1 shown in FIGS. 3 and 4 can be cast and, if necessary, thermally and / or mechanically reworked.
  • the cooling air outlet opening 9 shown in FIG. 4 is particularly suitable for the casting process, since the relief notch 11 does not create any undercut areas that would make the geometry of the casting cores unnecessarily complicated.
  • FIGS. 5 and 6 show a turbine blade 1 according to a second embodiment of the present invention, which was produced on the basis of the turbine blade 1 shown in FIGS. 1 and 2.
  • the turbine blade 1 shown in Figures 5 and 6 differs from the turbine blade 1 shown in Figures 1 and 2 only in terms of the design of the lower cooling air outlet opening 9, as can be seen from a comparison of Figures 2 and 6.
  • the cooling air outlet opening 9 shown is provided with a relief notch 11 projecting outwards from the rectangular shape with a rounded notch base 12.
  • the relief notch 11 extends from the lower edge 13 of the cooling outlet opening 9 at an obtuse angle obliquely downwards.
  • the underneath the lower edge 13 of the cooling outlet opening 9 is arranged notch base 12 points in the direction of the blade root 2, the relief notch 11, starting from its notch base 12, widens like a goblet.
  • the relief notch 11 shown in FIG. 6 can also be introduced into the cooling air outlet opening 9 shown in FIG. 2, for example using a machining process. It leads to 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 increase in the service life of the turbine blade 1. With regard to the stress reduction, the shape of the cooling air outlet opening 9 shown in FIG. 6 or its relief notch 11 is more favorable than the shape shown in FIG. However, it has undercuts that can only be realized with increased effort in terms of casting technology if the turbine blade 1 shown in FIGS. 5 and 6 is realized as part of a new production.
  • cooling air outlet openings 9 and / or other than the lowermost cooling air outlet opening 9 can be provided with a relief notch 11.

Landscapes

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

Abstract

L'invention se rapporte à une aube de turbine (1) pour une turbine à gaz, ayant un pied d'aube (2) et une surface portante d'aube incurvée de manière aérodynamique (3) disposée au-dessus du pied d'aube (2), la surface portante d'aube (3) présentant une paroi d'aube côté pression (4) et une paroi d'aube côté aspiration (5) qui s'étendent ensemble à partir d'un bord d'attaque (7), qui peuvent recevoir un flux de fluide de travail, de la surface portante d'aube (3) à un bord de fuite (8) de la surface portante d'aube (3). Une pluralité d'ouvertures de sortie d'air de refroidissement (9) sont formées sur la paroi d'aube côté pression (4), lesquelles ouvertures s'étendent dans chaque cas en amont du bord de fuite (8) par rapport à la direction d'écoulement d'un fluide de travail s'écoulant autour de la surface portante d'aube (3), et à travers ces ouvertures de l'air de refroidissement qui est transporté à travers l'intérieur de la surface portante d'aube (3) peut sortir. Au moins une des ouvertures de sortie d'air de refroidissement (9) a une forme sensiblement rectangulaire ou trapézoïdale présentant des coins arrondis (10), qui s'élargit de préférence dans la direction de sortie de l'air de refroidissement, caractérisé en ce qu'au moins le coin inférieur, orienté vers le bord d'attaque (7), de ladite ouverture de sortie d'air de refroidissement (9) forme une encoche de dégagement (11), qui fait saillie vers l'extérieur à partir de la forme rectangulaire, présentant un fond d'encoche arrondi (12). L'invention se rapporte en outre à un procédé d'usinage d'une aube de turbine (1).
EP21731686.8A 2020-06-22 2021-05-21 Aube de turbine et procédé d'usinage associé Active EP4136323B1 (fr)

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 true EP4136323A1 (fr) 2023-02-22
EP4136323B1 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 (6)

Country Link
US (1) US11867083B2 (fr)
EP (1) EP4136323B1 (fr)
KR (1) KR102874670B1 (fr)
DE (1) DE102020207646A1 (fr)
PL (1) PL4136323T3 (fr)
WO (1) WO2021259569A1 (fr)

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2833298B1 (fr) 2001-12-10 2004-08-06 Snecma Moteurs Perfectionnements apportes au comportement thermique du bord de fuite d'une aube de turbine haute-pression
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
DE50306044D1 (de) 2003-09-05 2007-02-01 Siemens Ag Schaufel einer Turbine
FR2864990B1 (fr) 2004-01-14 2008-02-22 Snecma Moteurs Perfectionnements apportes aux fentes d'evacuation de l'air de refroidissement d'aubes de turbine haute-pression
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
JP2012189026A (ja) 2011-03-11 2012-10-04 Ihi Corp タービン翼
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
EP2868867A1 (fr) 2013-10-29 2015-05-06 Siemens Aktiengesellschaft Aube de turbine
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
US10718219B2 (en) * 2017-12-13 2020-07-21 Solar Turbines Incorporated Turbine blade cooling system with tip diffuser

Also Published As

Publication number Publication date
US11867083B2 (en) 2024-01-09
EP4136323B1 (fr) 2024-05-29
KR20230027211A (ko) 2023-02-27
US20230220778A1 (en) 2023-07-13
DE102020207646A1 (de) 2021-12-23
WO2021259569A1 (fr) 2021-12-30
PL4136323T3 (pl) 2024-11-04
KR102874670B1 (ko) 2025-10-22

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