EP2565383A2 - Schaufel mit nichtlinearen Kühlkanälen - Google Patents

Schaufel mit nichtlinearen Kühlkanälen Download PDF

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Publication number
EP2565383A2
EP2565383A2 EP12182433A EP12182433A EP2565383A2 EP 2565383 A2 EP2565383 A2 EP 2565383A2 EP 12182433 A EP12182433 A EP 12182433A EP 12182433 A EP12182433 A EP 12182433A EP 2565383 A2 EP2565383 A2 EP 2565383A2
Authority
EP
European Patent Office
Prior art keywords
airfoil
cooling passage
turbine engine
cooling channel
exterior
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
EP12182433A
Other languages
English (en)
French (fr)
Other versions
EP2565383A3 (de
EP2565383B1 (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
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP2565383A2 publication Critical patent/EP2565383A2/de
Publication of EP2565383A3 publication Critical patent/EP2565383A3/de
Application granted granted Critical
Publication of EP2565383B1 publication Critical patent/EP2565383B1/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
    • F01D5/186—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.
  • 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.
  • the turbine engine airfoil includes a wall providing the interior cooling channel and an exterior airfoil surface.
  • the cooling passage is provided in the wall and fluidly connects the interior cooling channel to the exterior airfoil surface.
  • the cooling passage includes multiple inlets and multiple outlets respectively adjoining the interior cooling channel and the exterior airfoil surface. At least one of a first inlet and outlet has a different structural flow characteristic than at least one of a second inlet and outlet.
  • 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)
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 true EP2565383A2 (de) 2013-03-06
EP2565383A3 EP2565383A3 (de) 2016-09-07
EP2565383B1 EP2565383B1 (de) 2019-10-02

Family

ID=46888909

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12182433.8A Active EP2565383B1 (de) 2011-08-31 2012-08-30 Schaufelprofil mit Kühlkanälen

Country Status (2)

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

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2971667A4 (de) * 2013-03-15 2016-12-14 United Technologies Corp Kühlungsbohrung aus einem geformten film für einen gasturbinenmotor
EP2956644A4 (de) * 2013-02-14 2017-03-15 United Technologies Corporation Gasturbinenmotorkomponente mit oberflächenindikator
EP3246110A1 (de) * 2016-05-20 2017-11-22 United Technologies Corporation Kern aus hochschmelzendem metall und dadurch geformte komponenten
EP3406851A1 (de) * 2017-05-22 2018-11-28 United Technologies Corporation Komponente für einen gasturbinenmotor und verfahren zum herstellen einer kernanordnung
US10323569B2 (en) 2016-05-20 2019-06-18 United Technologies Corporation Core assemblies and gas turbine engine components formed therefrom
EP3650645A1 (de) * 2018-11-09 2020-05-13 United Technologies Corporation Gekühlter gasturbinenartikel
EP3650648A1 (de) * 2018-11-09 2020-05-13 United Technologies Corporation Gekühlter gasturbinenartikel

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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
WO2016133987A2 (en) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Forming cooling passages in combustion turbine superalloy castings
US20160146019A1 (en) * 2014-11-26 2016-05-26 Elena P. Pizano Cooling channel for airfoil with tapered pocket
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
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
US10648345B2 (en) 2017-12-05 2020-05-12 United Technologies Corporation Double wall turbine gas turbine engine blade cooling configuration
KR102817125B1 (ko) * 2023-03-21 2025-06-04 두산에너빌리티 주식회사 에어포일 및 이를 포함하는 가스 터빈

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US5486093A (en) * 1993-09-08 1996-01-23 United Technologies Corporation Leading edge cooling of turbine airfoils
DE10001109B4 (de) * 2000-01-13 2012-01-19 Alstom Technology Ltd. Gekühlte Schaufel für eine Gasturbine
US6994521B2 (en) * 2003-03-12 2006-02-07 Florida Turbine Technologies, Inc. Leading edge diffusion cooling of a turbine airfoil for a gas turbine engine
US7306026B2 (en) * 2005-09-01 2007-12-11 United Technologies Corporation Cooled turbine airfoils and methods of manufacture
US7364405B2 (en) * 2005-11-23 2008-04-29 United Technologies Corporation Microcircuit cooling for vanes
US7845906B2 (en) * 2007-01-24 2010-12-07 United Technologies Corporation Dual cut-back trailing edge for airfoils
US7980819B2 (en) * 2007-03-14 2011-07-19 United Technologies Corporation Cast features for a turbine engine airfoil
US7857589B1 (en) * 2007-09-21 2010-12-28 Florida Turbine Technologies, Inc. Turbine airfoil with near-wall cooling
US8105033B2 (en) * 2008-06-05 2012-01-31 United Technologies Corporation Particle resistant in-wall cooling passage inlet
US8572844B2 (en) * 2008-08-29 2013-11-05 United Technologies Corporation Airfoil with leading edge cooling passage
US8449254B2 (en) * 2010-03-29 2013-05-28 United Technologies Corporation Branched airfoil core cooling arrangement
US8366395B1 (en) * 2010-10-21 2013-02-05 Florida Turbine Technologies, Inc. Turbine blade with cooling

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Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2956644A4 (de) * 2013-02-14 2017-03-15 United Technologies Corporation Gasturbinenmotorkomponente mit oberflächenindikator
EP3460216A1 (de) * 2013-02-14 2019-03-27 United Technologies Corporation Verfahren zum bestimmen ob eine komponente innerhalb einer zulässigen fertigungstoleranz liegt unter verwendung eines oberflächenindikators
US10294798B2 (en) 2013-02-14 2019-05-21 United Technologies Corporation Gas turbine engine component having surface indicator
US10563517B2 (en) 2013-03-15 2020-02-18 United Technologies Corporation Gas turbine engine v-shaped film cooling hole
EP2971667A4 (de) * 2013-03-15 2016-12-14 United Technologies Corp Kühlungsbohrung aus einem geformten film für einen gasturbinenmotor
EP3246110A1 (de) * 2016-05-20 2017-11-22 United Technologies Corporation Kern aus hochschmelzendem metall und dadurch geformte komponenten
US10323569B2 (en) 2016-05-20 2019-06-18 United Technologies Corporation Core assemblies and gas turbine engine components formed therefrom
EP3406851A1 (de) * 2017-05-22 2018-11-28 United Technologies Corporation Komponente für einen gasturbinenmotor und verfahren zum herstellen einer kernanordnung
US10422232B2 (en) 2017-05-22 2019-09-24 United Technologies Corporation Component for a gas turbine engine
EP3650645A1 (de) * 2018-11-09 2020-05-13 United Technologies Corporation Gekühlter gasturbinenartikel
EP3650648A1 (de) * 2018-11-09 2020-05-13 United Technologies Corporation Gekühlter gasturbinenartikel
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

Also Published As

Publication number Publication date
US20130052037A1 (en) 2013-02-28
EP2565383A3 (de) 2016-09-07
EP2565383B1 (de) 2019-10-02

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