WO2017082907A1 - Surface portante de turbine avec bord de fuite refroidi - Google Patents

Surface portante de turbine avec bord de fuite refroidi Download PDF

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Publication number
WO2017082907A1
WO2017082907A1 PCT/US2015/060334 US2015060334W WO2017082907A1 WO 2017082907 A1 WO2017082907 A1 WO 2017082907A1 US 2015060334 W US2015060334 W US 2015060334W WO 2017082907 A1 WO2017082907 A1 WO 2017082907A1
Authority
WO
WIPO (PCT)
Prior art keywords
trailing edge
airfoil
lands
exit slots
upstream lip
Prior art date
Application number
PCT/US2015/060334
Other languages
English (en)
Inventor
Ching-Pang Lee
Nan Jiang
Anil L. Salunkhe
Caleb Myers
Erik Johnson
Original Assignee
Siemens Aktiengesellschaft
Siemens Energy, Inc.
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 Aktiengesellschaft, Siemens Energy, Inc. filed Critical Siemens Aktiengesellschaft
Priority to PCT/US2015/060334 priority Critical patent/WO2017082907A1/fr
Publication of WO2017082907A1 publication Critical patent/WO2017082907A1/fr

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
    • 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
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the present invention relates to an airfoil in a turbine engine, and in particular, to trailing edge cooling features incorporated in a turbine airfoil.
  • Effective cooling of turbine airfoils requires delivering the relatively cool air to critical regions such as along the trailing edge of a turbine blade or a stationary vane.
  • the associated cooling apertures may, for example, extend between an upstream, relatively high pressure cavity within the airfoil and one of the exterior surfaces of the turbine blade. Blade cavities typically extend in a radial direction with respect to the rotor and stator of the machine.
  • Airfoils commonly include internal cooling channels which remove heat from the pressure sidewall and the suction sidewall in order to minimize thermal stresses. Achieving a high cooling efficiency based on the rate of heat transfer is a significant design consideration in order to minimize the volume of coolant air diverted from the compressor for cooling.
  • the relatively narrow trailing edge portion of a gas turbine airfoil may include, for example, up to about one third of the total airfoil external surface area.
  • the trailing edge is made relatively thin for aerodynamic efficiency. Consequently, with the trailing edge receiving heat input on two opposing wall surfaces which are relatively close to each other, a relatively high coolant flow rate is entailed to provide the requisite rate of heat transfer for maintaining mechanical integrity.
  • An object of the invention is to provide improved trailing edge cooling features for a turbine airfoil.
  • an airfoil for a turbine engine comprises: an outer wall delimiting an airfoil interior, the outer wall including a leading edge, a trailing edge, a pressure side, a suction side, a radially inner end, and a radially outer end, wherein a chordal direction is defined between the leading edge and the trailing edge; a plurality of trailing edge exit slots located along an inner suction wall of the suction side of the airfoil facing the pressure side in the chordal direction, wherein at least one turbulating feature is positioned along each of the plurality of trailing edge exit slots facing the pressure side, wherein an inlet to the plurality of trailing edge exit slots comprises an upstream lip; a plurality of lands defined by material extending out from the inner suction wall towards the pressure side between each of the plurality of trailing edge exit slots and generally extending from a slot radially inner end to a slot radially outer end, wherein the plurality of lands each have
  • the inventive trailing edge cooling features provide a coolant flow path that flows differently than in conventional designs, for absorbing more heat from the upstream lip of the plurality of trailing edge exit slots, and for absorbing more heat along the sidewalls and tip of the plurality of lands before exiting the airfoil at the trailing edge into the high temperature working gas path.
  • the amount of coolant flow may be reduced.
  • the at least one turbulating feature increases the heat transfer surface while also providing increased turbulence within the plurality of trailing edge exit slots.
  • the inventive trailing edge cooling features are therefore particularly suitable for low cooing flow design airfoils, for example, first row vanes and blades.
  • the airfoil further comprises a specific radial profiled upstream lip for the plurality of trailing edge exit slots reducing the hot spots along the entrance of the plurality of trailing edge exit slots.
  • the airfoil further comprises tapered sidewalls for the plurality of lands, the tapered sidewalls receiving coolant fluid from the plurality of trailing edge exit slots with at least one turbulating feature directing a portion of the coolant fluid along the tapered sidewalls towards the tip of each of the plurality of lands.
  • FIG 1 is a side view of an airfoil assembly wherein a portion of a pressure side of the airfoil assembly has been removed to expose trailing edge cooling features according to one embodiment of the invention;
  • FIG 2 is a detailed view of a portion of the trailing edge cooling features according to one embodiment of the present invention.
  • FIG 3 is a cross-sectional view of a portion of the airfoil assembly taken along the section line A- A in FIG 2;
  • FIG 4 is a cross-sectional view of a portion of the airfoil assembly taken along the section line B-B in FIG 2;
  • FIG 5 is a detailed view of a portion of the trailing edge cooling features according to one embodiment of the present invention.
  • FIG 6 is a cross-sectional view of a portion of the airfoil assembly taken along the section line C-C in FIG 5.
  • an embodiment of the present invention provides an airfoil for a turbine engine with trailing edge cooling features including a plurality of trailing edge exit slots located along an inner suction wall of a suction side of the airfoil facing a pressure side in a chordal direction.
  • An inlet to the plurality of trailing edge slots includes an upstream lip.
  • At least one turbulating feature is positioned along each of the plurality of trailing edge exit slots facing the pressure side.
  • a plurality of lands defined by material extending out from the inner suction wall towards the pressure side between each of the plurality of trailing edge exit slots and generally extending from a slot radially inner end to a slot radially outer end.
  • the plurality of lands each have a set of sidewalls that lead to a tip or top end of each of the plurality of lands.
  • the airfoil assembly 10 constructed in accordance with an embodiment of the present invention is illustrated.
  • the airfoil assembly 10 includes an airfoil 12 that includes cooling concepts that may be used in combination with a rotatable blade or stationary vane.
  • the airfoil assembly 10 is used in a turbine section 14 of a gas turbine engine.
  • the gas turbine engine includes a compressor section (not shown), a combustor section (not shown), and the turbine section 14 (not shown).
  • the compressor section includes a compressor that compresses ambient air, at least a portion of which is conveyed to the combustor section.
  • the combustor section includes one or more combustors that combine the compressed air from the compressor section with a fuel and ignite the mixture creating combustion products defining a high temperature working gas 38 (not shown).
  • the high temperature working gas 38 travels to the turbine section 14 where the high temperature working gas 38 passes through one or more turbine stages, each turbine stage comprising a row of stationary vanes and a row of rotating blades.
  • the airfoil assembly 10 illustrated in FIG 1 may be included in a first row of rotating blade assemblies or vane assemblies in the turbine section 14, although the incorporation of the same features in other rows of blades and/or vanes may be readily conceived.
  • the vane and blade assemblies in the turbine section 14 are exposed to the high temperature working gas 38 as the high temperature working gas 38 passes through the turbine section 14. Cooling air from the compressor section may be provided to cool the vane and blade assemblies, as will be described herein.
  • the airfoil assembly 10 comprises the airfoil 12 and a platform assembly 16 that is coupled to a turbine rotor (not shown) and to which the airfoil 12 is affixed.
  • the airfoil 12 comprises an outer wall 18 (see FIG 1) that extends span- wise along a radial direction R with respect to a rotation axis A of the turbine engine, and comprises a radially inner end 18A and a radially outer end 18B.
  • the radially inner end 18A is affixed to the platform assembly 16.
  • the radially outer end 18B forms the tip of the airfoil 12.
  • the outer wall 18 further includes a leading edge 20, a trailing edge 22, a concave-shaped pressure side 24 and a convex-shaped suction side 26.
  • a chordal direction C is defined as a direction from the leading edge 20 to the trailing edge 22. It is noted that a portion of the pressure side 24 of the airfoil 12 illustrated in FIG 1 , 2, and 5 has been removed to show selected internal structures within the airfoil 12, as will be described herein.
  • an inner surface 26A of the outer wall 18 defines a hollow interior portion 28, which is delimited by the outer wall 18.
  • the hollow interior portion 28 extends between the pressure and suction sides 24, 26 from the leading edge 20 to the trailing edge 22 and from the radially inner end 18A to the radially outer end 18B.
  • a conventional thermal barrier coating (TBC) 42 may be provided on an outer surface 18C of the outer wall 18 to increase the heat resistance of the airfoil 12, as will be apparent to those skilled in the art.
  • the TBC 42 may be along the outer surface 18C of the pressure side and suction side, where the high temperature working gas 38 may pass.
  • the TBC 42 may not be applied within each of a trailing edge coolant exit slot of a plurality of trailing edge coolant exit slots 30.
  • the airfoil assembly 10 may be provided with trailing edge cooling features for effecting cooling of the airfoil 12 toward the trailing edge 22 of the outer wall 18.
  • the airfoil assembly including the trailing edge cooling features, may be incorporated into a blade assembly or a vane assembly.
  • the trailing edge cooling features are located in the hollow interior portion 28 of the outer wall 18 toward the trailing edge 22.
  • the airfoil 12 includes a plurality of extending outlet passages or plurality of trailing edge exit slots 30 formed in the outer wall 18 at the trailing edge 22.
  • the plurality of trailing edge exit slots 30 is positioned radially along a suction side inner wall 26A facing the pressure side 24 opening in an axial direction A.
  • a plurality of lands 36 In between the plurality of trailing edge exit slots 30 are a plurality of lands 36 with a land between each trailing edge exit slot.
  • the plurality of trailing edge exit slots 30 receive a coolant fluid 40 sent from the compressor section and discharge the coolant fluid 40 (not shown) from the airfoil 12 via the plurality of exit slots 30.
  • the plurality of lands 36 extend away from the suction side 26 towards the pressure side 24.
  • the plurality of lands 36 receive portions of the high temperature working gas 38 that passes along the pressure side 24.
  • the TBC 42 may be added to the plurality of lands 36 along a tip 46 or top edge of each land 36.
  • the coolant fluid 40 that has passed through the plurality of trailing edge exit slots 30 is then mixed with the high temperature working gas 38 passing through the turbine section 14 as can be shown in Fig. 4.
  • the plurality of exit slots 30 may be located along substantially the entire radial length of the trailing edge 22 of the outer wall 18, or may be selectively located along the trailing edge 22 for cooling of specific areas.
  • the trailing edge cooling features are illustrated in greater detail in the detailed views shown in FIG 2 through FIG 6.
  • the trailing edge cooling features include at least one turbulating feature 32 positioned within each of the plurality of trailing edge coolant exit slots 30.
  • the turbulating features 32 are embodied as ribs. Alternating geometries, such as dimples or grooves may also be provided as turbulating features 32.
  • the at least one turbulating feature 32 may be positioned at an angle off of, and in reference to, the axial direction A.
  • the at least one turbulating feature 32 is curved and includes an open face directed towards one of the plurality of lands 36.
  • Each turbulating feature 32 may be angled so that the turbulating feature 32 effects a turbulation of the coolant fluid 40 flowing there through so as to increase cooling provided to the plurality of lands 36 by coolant fluid 40 passing through the plurality of trailing edge exit slots 30 and being directed towards the plurality of lands 36 by the at least one turbulating feature 32.
  • the trailing edge exit slots 30 may each include an upstream lip 34 that extends span-wise generally in the radial direction R along a profiled contour (see FIG 2 for an example).
  • the trailing edge cooling features include a specific radial profiled upstream lip 34.
  • the upstream lip 34 may include a profile that may be radially curved.
  • the upstream lip 34 may include a profile that may have a circular radius.
  • the upstream lip 34 may include a profile that may have compound radii.
  • the upstream lip 34 may include a profile that may have chamfered ends.
  • the upstream lip 34 may include a profile that may come to a point approximately center of the plurality of trailing edge exit slots 30.
  • the upstream lip 34 may include a profile that may be straight across the entire upstream lip 34.
  • the specific radial profiled upstream lip 34 may remove hot spots that can occur along an opening of the plurality of trailing edge exit slots 30.
  • profiled and “profile”, in the context of this discussion, implies having a contour that can be a straight line along the radial direction R, and/or having a plurality of angular turns, which may be smooth or sharp, as it extends generally in the radial direction R from the slot radially inner end 30A to the slot radially outer end 30B of each upstream lip 34.
  • the angular turns divide the contour into a plurality of sections, which may be straight or curved.
  • the plurality of lands 36 includes sidewalls 44 that connect along a tip 46 or top edge of each of the plurality of lands 36.
  • the top edge may connect each of the sidewalls to form a raised rectangular cubic shape.
  • the plurality of lands 36 may include sidewalls 44 with a rectangular cross- section.
  • the plurality of lands 36 may include tapered sidewalls 44.
  • the tapered sidewalls 44 may allow the coolant fluid 40 to move towards the top surface of the plurality of lands 36 and improve film cooling coverage.
  • the tapered sidewalls 44 may come to a tip 46 or point.
  • the sidewalls 44 may be tapered in the axial and/or circumferential directions.
  • the sidewalls 44 may be tapered in the radial direction.
  • coolant fluid 40 is provided to the platform assembly 16 and then to the hollow interior portion 28 of the outer wall 18 toward the trailing edge 22 in any known manner, as will be apparent to those skilled in the art.
  • the coolant fluid 40 passes into the hollow interior portion 28 and flows serially in the chordal direction C through the plurality of trailing edge exit slots 30 via the specific radial profiled upstream lip 34 of each of the plurality of trailing edge exit slots 30.
  • the at least one turbulating feature 32 effects a turbulation of the coolant fluid 40 flowing there through so as to turbulate the coolant fluid 40 as well as increase cooling provided to the plurality of lands 36 by the coolant fluid 40.
  • the angles of the at least one turbulating feature 32 may allow for a directional shift of a portion of the coolant fluid 40 towards the sidewalls 44 of the plurality of lands 36.
  • the plurality of lands 36 has a rectangular cross-section.
  • the coolant fluid 40 directed towards the plurality of lands 36 from the at least one turbulating feature 32 may flow against each land sidewall 44.
  • the plurality of lands 36 include tapered sidewalls 44. The tapered sidewalls 44 of the plurality of lands 36 may allow for the directed coolant fluid 40 to extend onto the top surface of each land 36.

Landscapes

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

Abstract

L'invention concerne une surface portante (12) pour un moteur à turbine avec des caractéristiques de refroidissement de bord de fuite comprenant une pluralité de fentes de sortie de bord de fuite (30) situées le long d'une paroi d'aspiration intérieure (26 A) d'un côté d'aspiration (26) de la surface portante (12) faisant face à un côté de refoulement (24) dans la direction de la corde (C). Une entrée vers la pluralité de fentes de bord de fuite (30) comprend une lèvre amont (34). Au moins un élément de turbulence (32) est positionné le long de chacune des fentes de la pluralité de fentes de sortie de bord de fuite (30) et est orienté vers le côté de refoulement (24). Une pluralité de méplats (36) est définie par de la matière s'étendant vers l'extérieur à partir de la paroi d'aspiration intérieure (26 A) vers le côté de refoulement (24) entre chaque fente de la pluralité de fentes de sortie de bord de fuite (30) et s'étendant généralement à partir d'une extrémité radialement intérieure de fente (30A) jusqu'à une extrémité radialement extérieure de fente (30B). Les méplats de la pluralité de méplats (36) comportent chacun un ensemble de parois latérales (44) qui conduisent à un bout (46) ou une extrémité supérieure de chaque méplat de la pluralité de méplats (36).
PCT/US2015/060334 2015-11-12 2015-11-12 Surface portante de turbine avec bord de fuite refroidi WO2017082907A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US2015/060334 WO2017082907A1 (fr) 2015-11-12 2015-11-12 Surface portante de turbine avec bord de fuite refroidi

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2015/060334 WO2017082907A1 (fr) 2015-11-12 2015-11-12 Surface portante de turbine avec bord de fuite refroidi

Publications (1)

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WO2017082907A1 true WO2017082907A1 (fr) 2017-05-18

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3107562A1 (fr) * 2020-02-20 2021-08-27 Safran Aube de turbomachine comportant des fentes de refroidissement de son bord de fuite équipées de perturbateurs

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH03141801A (ja) * 1990-09-19 1991-06-17 Hitachi Ltd ガスタービンの冷却翼
US20060222496A1 (en) * 2005-04-01 2006-10-05 General Electric Company Turbine nozzle with trailing edge convection and film cooling
US20060239819A1 (en) * 2005-04-22 2006-10-26 United Technologies Corporation Airfoil trailing edge cooling
US20100074763A1 (en) * 2008-09-25 2010-03-25 Siemens Energy, Inc. Trailing Edge Cooling Slot Configuration for a Turbine Airfoil
US20110176930A1 (en) * 2008-07-10 2011-07-21 Fathi Ahmad Turbine vane for a gas turbine and casting core for the production of such
EP2685049A1 (fr) * 2011-03-11 2014-01-15 IHI Corporation Aube de turbine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH03141801A (ja) * 1990-09-19 1991-06-17 Hitachi Ltd ガスタービンの冷却翼
US20060222496A1 (en) * 2005-04-01 2006-10-05 General Electric Company Turbine nozzle with trailing edge convection and film cooling
US20060239819A1 (en) * 2005-04-22 2006-10-26 United Technologies Corporation Airfoil trailing edge cooling
US20110176930A1 (en) * 2008-07-10 2011-07-21 Fathi Ahmad Turbine vane for a gas turbine and casting core for the production of such
US20100074763A1 (en) * 2008-09-25 2010-03-25 Siemens Energy, Inc. Trailing Edge Cooling Slot Configuration for a Turbine Airfoil
EP2685049A1 (fr) * 2011-03-11 2014-01-15 IHI Corporation Aube de turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3107562A1 (fr) * 2020-02-20 2021-08-27 Safran Aube de turbomachine comportant des fentes de refroidissement de son bord de fuite équipées de perturbateurs

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