EP4136323B1 - Turbinenschaufel und zugehöriges herstellungsverfahren - Google Patents

Turbinenschaufel und zugehöriges herstellungsverfahren Download PDF

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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
Application number
EP21731686.8A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP4136323A1 (de
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/de
Application granted granted Critical
Publication of EP4136323B1 publication Critical patent/EP4136323B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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)
EP21731686.8A 2020-06-22 2021-05-21 Turbinenschaufel und zugehöriges herstellungsverfahren Active EP4136323B1 (de)

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 (de) 2020-06-22 2021-05-21 Turbinenschaufel und verfahren zum bearbeiten einer solchen

Publications (2)

Publication Number Publication Date
EP4136323A1 EP4136323A1 (de) 2023-02-22
EP4136323B1 true EP4136323B1 (de) 2024-05-29

Family

ID=76392325

Family Applications (1)

Application Number Title Priority Date Filing Date
EP21731686.8A Active EP4136323B1 (de) 2020-06-22 2021-05-21 Turbinenschaufel und zugehöriges herstellungsverfahren

Country Status (5)

Country Link
US (1) US11867083B2 (ko)
EP (1) EP4136323B1 (ko)
KR (1) KR20230027211A (ko)
DE (1) DE102020207646A1 (ko)
WO (1) WO2021259569A1 (ko)

Citations (3)

* Cited by examiner, † Cited by third party
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 (en) * 2011-03-11 2018-05-23 IHI Corporation Turbine blade

Family Cites Families (11)

* Cited by examiner, † Cited by third party
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 (en) 2014-10-28 2016-05-06 Siemens Aktiengesellschaft Cooling passage arrangement for turbine engine airfoils
EP3043025A1 (de) * 2015-01-09 2016-07-13 Siemens Aktiengesellschaft Filmgekühltes Gasturbinenbauteil
US10718219B2 (en) * 2017-12-13 2020-07-21 Solar Turbines Incorporated Turbine blade cooling system with tip diffuser

Patent Citations (3)

* Cited by examiner, † Cited by third party
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 (en) * 2011-03-11 2018-05-23 IHI Corporation Turbine blade

Also Published As

Publication number Publication date
DE102020207646A1 (de) 2021-12-23
WO2021259569A1 (de) 2021-12-30
US20230220778A1 (en) 2023-07-13
EP4136323A1 (de) 2023-02-22
US11867083B2 (en) 2024-01-09
KR20230027211A (ko) 2023-02-27

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