EP2565383B1 - Schaufelprofil mit Kühlkanälen - Google Patents

Schaufelprofil mit Kühlkanälen Download PDF

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Publication number
EP2565383B1
EP2565383B1 EP12182433.8A EP12182433A EP2565383B1 EP 2565383 B1 EP2565383 B1 EP 2565383B1 EP 12182433 A EP12182433 A EP 12182433A EP 2565383 B1 EP2565383 B1 EP 2565383B1
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EP
European Patent Office
Prior art keywords
airfoil
cooling passage
cooling
turbine engine
cooling channel
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
EP12182433.8A
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English (en)
French (fr)
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EP2565383A3 (de
EP2565383A2 (de
Inventor
William Abdel-Messeh
Justin D. Piggush
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.)
RTX Corp
Original Assignee
United Technologies Corp
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Filing date
Publication date
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Publication of EP2565383A3 publication Critical patent/EP2565383A3/de
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Publication of EP2565383B1 publication Critical patent/EP2565383B1/de
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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
    • F01D5/186—Film cooling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/103—Multipart cores
    • 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
    • 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
    • F05D2250/50—Inlet or outlet
    • 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
    • F05D2250/70—Shape
    • 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
    • F05D2260/204—Heat transfer, e.g. cooling by the use of microcircuits
    • 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
    • F05D2260/221—Improvement of heat transfer

Definitions

  • This disclosure relates to a cooling passage for an airfoil.
  • Turbine blades are utilized in gas turbine engines.
  • a turbine blade typically includes a platform having a root on one side and an airfoil extending from the platform opposite the root. The root is secured to a turbine rotor.
  • Cooling circuits are formed within the airfoil to circulate cooling fluid, such as compressor bleed air.
  • cooling fluid such as compressor bleed air.
  • multiple relatively large cooling channels extend radially from the root toward a tip of the airfoil. Air flows through the channels and cools the airfoil, which is relatively hot during operation of the gas turbine engine.
  • Some advanced cooling designs use one or more radial cooling passages arranged between the cooling channels and an airfoil exterior surface that extend from the root toward the tip.
  • the cooling passages provide high convective cooling.
  • EP 1 972 396 , EP 2 159 375 , EP 1 790 823 , US 2005/265838 , EP 2 131 011 and GB 2 358 226 all relate to airfoils with cooling passages.
  • An example method of manufacturing an airfoil includes providing a ceramic core corresponding to an interior cooling channel.
  • a refractory metal core is provided that corresponds to a cooling passage.
  • the cores are arranged in a mold.
  • An airfoil structure is cast about the cores to provide a turbine engine airfoil.
  • a turbine engine airfoil according to claim 1 is provided.
  • a method of manufacturing the airfoil of the first aspect according to claim 7 is provided.
  • a gas turbine engine (GTE) 10 is illustrated schematically in Figure 1 .
  • the GTE 10 includes a core section downstream from a fan section 14.
  • the core section 12 includes a compressor section 18 supplying compressed air to a combustor 20.
  • the combusted air expands over a turbine section 22 that rotationally drives a fan 16 within the fan section 14 about an axis A.
  • the turbine section 22 includes turbine blades 24 rotatable about the axis A and arranged in a circumferential direction C, shown in Figure 2 .
  • One example turbine blade is illustrated in Figure 2 .
  • the turbine blade 24 has a root 26 that supports a platform 28.
  • An airfoil structure 30 extends in a radial direction R from the platform 28 to a tip 32.
  • the airfoil structure 30 provides an exterior airfoil surface 34 having leading and trailing edges 36, 38 with adjoining spaced apart sides 40.
  • the example turbine blade 24 includes a wall 44 that provides the exterior airfoil surface 34.
  • One or more interior cooling channels 42 are provided by the wall 44 and supply cooling air, for example, compressor bleed air, for cooling the turbine blade 24.
  • This cooling fluid is supplied to various cooling features that ultimately flow through the wall 44 to provide internal convective cooling and a cooling film to the exterior airfoil surface 34.
  • a cooling passage 46 fluidly interconnects the interior cooling channel 42 to the exterior airfoil surface 34 and is arranged on the pressure side of the turbine blade 24.
  • the cooling passage 46 includes multiple inlets 48 adjoining a radially extending intermediate passage 50. Multiple outlets 52 adjoin the intermediate passage 50, which enables the pressure to be better equalized across the outlets 52.
  • the inlets 48 each provide an entrance 54 at the interior cooling channel 42.
  • the extended intermediate passage 50 provide exits 56 arranged at the end of the airfoil structure near the tip 32.
  • the cooling passage 46 has a generally S-shaped cross-section. The flow path from the entrance 54 to the exit 56 can replace the straight, drilled holes previously used.
  • Trip strips 58 are arranged in the cooling passage 46 as desired, for example, along portions of the outlets 52 to improve cooling.
  • Cross-section of the trip strips can be any shapes such as block (as shown), semi-circular, triangular, semi-elliptic, and alike. Pedestals may also be provided.
  • the interior cooling channel 42 and cooling passage 46 are provided by one or more ceramic cores arranged within a mold.
  • a ceramic core 64 provides the interior cooling channel 42.
  • a refractory metal core (RMC) 66 provides the cooling passage 46.
  • the ceramic core and the refractory metal core are provided using different materials than one another.
  • One or more locating features 68 such as interlocking protrusions and recesses, locate the RMC 66 relative to the ceramic core 64.
  • the cores 64, 66 are arranged within a cavity 62 of the mold 60.
  • the airfoil structure 30 is typically cast into the mold 60 to provide a structure, such as a single-crystal nickel alloy structure.
  • the RMC 66 is formed to provide a desired core shape. Typically, the RMC can be stamped out of a flat sheet metal. Subsequently, this stamped RMC shape is bent to a desired shape to provide a correspondingly shaped cooling passage 46, an example of which is illustrated in Figure 6 .
  • the RMC 66 includes a first and second ends (generally, 70 and 72), which correspond to the inlets and outlets 48 and 52, joined by a radially extending intermediate portion 74.
  • the first ends 70A, 70B respectively include a first and second inlet area 76, 78 that can be different in shape and size than one another.
  • the outlets 72A, 72B, 72C include first, second and third outlet areas 80, 82, 84 (shown in Figures 6A-6C and respectively represented by cross-sectional lines A-A, B-B, C-C in Figure 6 ) that can be different than one another.
  • Notches 86 are provided in the RMC 66 to provide corresponding trip strips 58.
  • the RMC 66 can be configured provide different structural flow characteristics with any desired geometry to produce holes of any desired length, path and exit shape, for example. For example, by utilizing different cross-sectional areas along the length of the RMC 66 (for example in along the flow path from the entrance 54 to the exit 56), each hole may be designed to provide desired pressure drop control across the radial length of the cooling passage 46 rather than over pressurizing many of the drilled holes with only a few holes optimized.
  • the cooling passage 46 may include any heat transfer augmentation features such as trip strips to improve heat transfer characteristics and control pressure drops through the holes. Diffuser features 90 may also be provided in the cooling passage 46 and in the exits 56 (see, e.g., Figure 4 ).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)

Claims (12)

  1. Schaufelprofil (30) eines Turbinentriebwerks, umfassend eine Schaufelprofilstruktur, die eine Wand (44) aufweist, die einen inneren Kühlkanal (42) und eine äußere Schaufelprofilfläche (34) bereitstellt, wobei ein Kühlkanal (46), der in der Wand (44) vorgesehen ist, eine Fluidverbindung vom inneren Kühlkanal (42) zur äußeren Schaufelprofilfläche (34) herstellt, wobei der Kühlkanal (46) mindestens einen Einlass (48) und mehrere Auslässe (52) beinhaltet, die an den inneren Kühlkanal (42) beziehungsweise die äußere Schaufelprofilfläche (34) angrenzen, wobei das Schaufelprofil mehrere Einlässe (48) aufweist, die jeweils einen Zugang (54) am inneren Kühlkanal (42) beinhalten, und wobei die Auslässe (52) jeweils einen Ausgang (56) an der äußeren Schaufelprofilfläche (34) beinhalten, wobei die Zugänge (54) eine größere Querschnittsfläche aufweisen als diejenige der Ausgänge (56)
    dadurch gekennzeichnet, dass ein erster Auslass (52) eine andere Querschnittsfläche als ein zweiter Auslass (52) aufweist.
  2. Schaufelprofil (30) eines Turbinentriebwerks nach Anspruch 1, wobei der Kühlkanal (46) im Allgemeinen axial innerhalb der Wand (44) verläuft und einen im Allgemeinen axial verlaufenden Zwischenkanal (50) beinhaltet, der eine Fluidverbindung von den Einlässen (48) zu den Auslässen (52) herstellt.
  3. Schaufelprofil (30) eines Turbinentriebwerks nach Anspruch 1, wobei ein erster Zugang (54) eine Fläche beinhaltet, die größer ist als ein zweiter Zugang (54).
  4. Schaufelprofil (30) eines Turbinentriebwerks nach Anspruch 1 oder 3, wobei ein erster Ausgang (56) eine Fläche aufweist, die größer als ein zweiter Ausgang (56) ist.
  5. Schaufelprofil (30) eines Turbinentriebwerks nach einem der vorstehenden Ansprüche, wobei der Kühlkanal (46) Stolperstreifen (58) umfasst.
  6. Schaufelprofil (30) eines Turbinentriebwerks nach einem der vorstehenden Ansprüche, wobei der Kühlkanal (46) nichtlinear ist.
  7. Verfahren zum Herstellen eines Schaufelprofils (30) nach Anspruch 1, umfassend die folgenden Schritte:
    Bereitstellen eines Keramikkerns (64), der einem inneren Kühlkanal (42) entspricht;
    Bereitstellen eines Kerns aus hochschmelzendem Metall (66), der einem Kühlkanal (46) entspricht;
    Anordnen der Kerne (64, 66) in einer Gießform (60); und
    Gießen einer Schaufelprofilstruktur (30) um die Kerne (64, 66), wobei die Schaufelprofilstruktur (30) eine Wand (44) beinhaltet, die den inneren Kühlkanal (42) von einer äußeren Schaufelprofilfläche (34) trennt, wobei der Kühlkanal (46), der in der Wand (44) vorgesehen ist, eine Fluidverbindung vom inneren Kühlkanal (42) zur äußeren Schaufelprofilfläche (36) herstellt, wobei der Kühlkanal (46) mindestens einen Einlass (48) und mehrere Auslässe (52) beinhaltet, die an den inneren Kühlkanal (42) beziehungsweise die äußere Schaufelprofilfläche (34) angrenzen, wobei mindestens einer aus einem ersten Einlass (48) und Auslass (52) unterschiedliche strukturelle Strömungseigenschaften als mindestens einer aus einem zweiten Einlass (48) und Auslass (52) aufweist.
  8. Verfahren nach Anspruch 7, wobei der Schritt des Bereitstellens des Kerns aus hochschmelzendem Metall (66) das Herstellen einer gewünschten Kernform und das Biegen der hergestellten gewünschten Kernform, so dass sie dem Kühlkanal (46) entspricht, beinhaltet.
  9. Verfahren nach Anspruch 8, wobei der Schritt des Biegens das Biegen des Kühlkanals (46) in eine im Allgemeinen S-Form in einer lateralen Richtung beinhaltet.
  10. Verfahren nach einem der Ansprüche 7 bis 9, wobei der Schritt des Bereitstellens des Kerns aus hochschmelzendem Metall (66) das Bereitstellen von Kerben (86) in dem Kühlkanal (46), die Stolperstreifen (58) entsprechen, beinhaltet.
  11. Verfahren nach einem der Ansprüche 7 bis 10, wobei der Schritt des Anordnens das Positionieren des Kerns aus hochschmelzendem Metall (66) relativ zum Keramikkern (64) beinhaltet.
  12. Verfahren nach einem der Ansprüche 7 bis 11, wobei der Schritt des Gießens das Herstellen eines Diffusorelements in dem Kühlkanal herein (46) beinhaltet.
EP12182433.8A 2011-08-31 2012-08-30 Schaufelprofil mit Kühlkanälen Active EP2565383B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/222,490 US20130052037A1 (en) 2011-08-31 2011-08-31 Airfoil with nonlinear cooling passage

Publications (3)

Publication Number Publication Date
EP2565383A2 EP2565383A2 (de) 2013-03-06
EP2565383A3 EP2565383A3 (de) 2016-09-07
EP2565383B1 true EP2565383B1 (de) 2019-10-02

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EP12182433.8A Active EP2565383B1 (de) 2011-08-31 2012-08-30 Schaufelprofil mit Kühlkanälen

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US (1) US20130052037A1 (de)
EP (1) EP2565383B1 (de)

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WO2014126565A1 (en) * 2013-02-14 2014-08-21 United Technologies Corporation Gas turbine engine component having surface indicator
EP2971667B1 (de) * 2013-03-15 2024-06-12 RTX Corporation Bauteil für ein gasturbinentriebwerk und verfahren zur herstellung eines bauteils für ein gasturbinentriebwerk
US20140360155A1 (en) * 2013-06-07 2014-12-11 General Electric Company Microchannel systems and methods for cooling turbine components of a gas turbine engine
JP6245740B2 (ja) * 2013-11-20 2017-12-13 三菱日立パワーシステムズ株式会社 ガスタービン翼
US10352181B2 (en) * 2014-11-26 2019-07-16 Ansaldo Energia Ip Uk Limited Leading edge cooling channel for airfoil
US9963975B2 (en) 2015-02-09 2018-05-08 United Technologies Corporation Trip strip restagger
US10156157B2 (en) * 2015-02-13 2018-12-18 United Technologies Corporation S-shaped trip strips in internally cooled components
US10408079B2 (en) 2015-02-18 2019-09-10 Siemens Aktiengesellschaft Forming cooling passages in thermal barrier coated, combustion turbine superalloy components
US10323569B2 (en) 2016-05-20 2019-06-18 United Technologies Corporation Core assemblies and gas turbine engine components formed therefrom
US20170335692A1 (en) * 2016-05-20 2017-11-23 United Technologies Corporation Refractory metal core and components formed thereby
US10422232B2 (en) * 2017-05-22 2019-09-24 United Technologies Corporation Component for a gas turbine engine
US10648345B2 (en) 2017-12-05 2020-05-12 United Technologies Corporation Double wall turbine gas turbine engine blade cooling configuration
US10626735B2 (en) * 2017-12-05 2020-04-21 United Technologies Corporation Double wall turbine gas turbine engine blade cooling configuration
US10508555B2 (en) 2017-12-05 2019-12-17 United Technologies Corporation Double wall turbine gas turbine engine blade cooling configuration
US11149556B2 (en) * 2018-11-09 2021-10-19 Raytheon Technologies Corporation Minicore cooling passage network having sloped impingement surface
US11339718B2 (en) * 2018-11-09 2022-05-24 Raytheon Technologies Corporation Minicore cooling passage network having trip strips

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Publication number Publication date
EP2565383A3 (de) 2016-09-07
EP2565383A2 (de) 2013-03-06
US20130052037A1 (en) 2013-02-28

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