EP2954169B1 - Composant de turbine - Google Patents

Composant de turbine Download PDF

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Publication number
EP2954169B1
EP2954169B1 EP14706400.0A EP14706400A EP2954169B1 EP 2954169 B1 EP2954169 B1 EP 2954169B1 EP 14706400 A EP14706400 A EP 14706400A EP 2954169 B1 EP2954169 B1 EP 2954169B1
Authority
EP
European Patent Office
Prior art keywords
component
inner surfaces
cooling
channel
width
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
EP14706400.0A
Other languages
German (de)
English (en)
Other versions
EP2954169A1 (fr
Inventor
Christian X CAMPBELL
Ching-Pang Lee
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 Inc
Mikro Systems Inc
Original Assignee
Siemens Energy Inc
Mikro Systems 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
Priority claimed from US13/760,107 external-priority patent/US9017027B2/en
Application filed by Siemens Energy Inc, Mikro Systems Inc filed Critical Siemens Energy Inc
Priority to EP20188996.1A priority Critical patent/EP3767074B1/fr
Publication of EP2954169A1 publication Critical patent/EP2954169A1/fr
Application granted granted Critical
Publication of EP2954169B1 publication Critical patent/EP2954169B1/fr
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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
    • F01D5/187—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
    • F01D5/12—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
    • 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
    • F05D2250/131—Two-dimensional trapezoidal polygonal
    • 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
    • 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 application relates to components of a turbine.
  • Cooling effectiveness is important to minimize thermal stress on these components, and cooling efficiency is important to minimize the volume of air diverted from the compressor for cooling.
  • Film cooling provides a film of cooling air on outer surfaces of a component via holes from internal cooling channels. Film cooling can be inefficient, because a high volume of cooling air is required. Thus, film cooling has been used selectively in combination with other techniques. Impingement cooling is a technique in which perforated baffles are spaced from a surface to create impingement jets of cooling air against the surface.
  • Serpentine cooling channels have been provided in turbine components, including airfoils such as blades and vanes. The present invention increases effectiveness and efficiency in cooling channels.
  • US 2012 0177503 A1 discloses the subject-matter of the preamble of claim 1.
  • FIG 1 is a sectional view of a turbine blade 20 having a leading edge 21 and a trailing edge 23.
  • Cooling air 22 from the turbine compressor enters an inlet 24 in the blade root 26, and flows through channels 28, 29, 30, 31 in the blade. Some of the coolant may exit film cooling holes 32.
  • a trailing edge portion TE of the blade may have turbulator pins 34 and exit channels 36.
  • Each arrow 22 indicates an overall coolant flow direction at the arrow, meaning a predominant or average flow direction at that point.
  • FIG 2 is a sectional view of a turbine airfoil trailing edge portion TE taken along line 2-2 of FIG 1 .
  • the trailing edge portion has first and second exterior surfaces 40, 42 on suction and pressure side walls 41, 43 of the airfoil.
  • Cooling channels 36 may have fins 44 on inner surfaces 48, 50 of the exterior walls 41, 43 according to aspects of the invention. These inner surfaces 48 and 50 are called “near-wall inner surfaces” in the art, meaning an interior surface of a cooling channel that is closest to a cooled exterior surface. Gaps G between the channels produce gaps in cooling efficiency and uniformity. The inventors recognized that cooling effectiveness, efficiency, and uniformity could be improved by increasing the cooling rate in the corners C of the cooling channels, since these corners are nearest to the gaps G.
  • One way to accomplish this preferential cooling is to provide an hourglass-shaped channel profile in which the side surfaces 52, 54 of the channel form a waist that is narrower than a width of each of the first and second inner surfaces 48 and 50.
  • the waist functions to increase the flow resistance in the center of the channel, thereby urging the coolant toward the corners of the channel. Since coolant flow in the center of the channel does not contact a heat transfer surface whereas flow in the corners does function to remove heat, the present invention is effective to increase the efficiency of the cooling.
  • FIG 3 is a transverse sectional profile 46 of a cooling channel that is shaped to efficiently cool two opposed exterior surfaces.
  • the channel may be a trailing edge channel 36 or any other cooling channel, such as channels 29 and 30 in FIG 1 . It has two opposed near-wall inner surfaces 48, 50, which may be parallel to the respective exterior surfaces 40, 42 of FIG 2 .
  • parallel means with respect to the portions of the near-wall inner surface closest to the exterior surface, not considering the fins 44.
  • the channel has widths W1, W3 at the near-wall inner surfaces 48, 50.
  • Two interior side surfaces 52, 54 taper toward each other from the sides of the inner surfaces 48, 50, defining a minimum channel width W2 or waist in the side surfaces.
  • the inner surface widths W1 and W3 are greater than the waist width W2, so the channel profile 46 has an hourglass shape formed by convexity of the side surfaces 52, 54. This shape increases the coolant flow 25 toward the corners C of the channel.
  • the overall coolant flow direction is normal to the page in this view.
  • the arrows 25 illustrate a flow-increasing aspect of the profile 46 relative to a channel without an hourglass shape and/or without fins next described.
  • Fins 44 may be provided on the inner surfaces 48, 50.
  • the fins may be aligned with the overall flow direction 22 ( FIG 1 ) which is normal to the plane of FIG 3 . If fins are provided, they may have heights that follow a convex profile such as 56A or 56B, providing a maximum fin height H at mid-width of the near-wall inner surface 48 and/or 50.
  • These fins 44 increase the surface area of the near-wall surfaces 48, 50, and also increase the flow 25 in the corners C.
  • the taller middle fins reduce the flow centrally, while the shorter distal fins encourage flow 25 in the corners C.
  • the combination of convex sides 52, 54 and a convex fin height profile 56A, 56B provides synergy that focuses cooling toward the channel corners C.
  • the side taper angle A -30° in this example.
  • a negative taper angle A of sides 52, 54 in the profile 46 means the sides converge toward each other toward an intermediate position between the inner surfaces 48, 50, forming a waist W2 as shown. In some embodiments the taper angle A may range from -1° to -30°.
  • the waist width W2 may be determined by the taper angle. Alternately it may be 80% or less of one or both of the near wall widths W1, W3, or 65% or less in certain embodiments. One or more proportions and/or dimensions may vary along the length of the cooling channel. For example, dimension B may vary with the thickness of the airfoil.
  • the widths W1, W3 of the two inner surfaces 48 and 50 may differ from each other in some embodiments. In this case, the waist W2 may be narrower than each of the widths W1, W3.
  • FIG 4 shows a cooling channel 36B shaped to cool a single exterior surface 40 or 42. It uses the fin and taper angle concepts of the cooling channel 36 previously described.
  • the near-wall inner surface width W1 is greater than the minimum channel width W2 due to tapered interior side surfaces 52, 54. Fins 44 may be provided on the near-wall inner surface 48, and they may have a convex height profile centered on the width W1 of the near-wall inner surface.
  • Such cooling channels 36B may be used for example in a relatively thicker part of a trailing edge portion TE of an airfoil rather than the relatively thinner part of the trailing edge portion TE where a cooling profile 46 as in FIG 3 might be used.
  • the transverse sectional profile of this embodiment may be trapezoidal, in which the near-wall inner surface 48 defines a longest side thereof.
  • FIG 5 shows that the exterior surfaces 40 and 42 may be non-parallel in a transverse section plane of the channel 36.
  • the near-wall inner surfaces 48, 50 may be parallel to the exterior surfaces 40, 42.
  • FIG 6 shows a transverse section of a turbine airfoil 60 with hourglass-shaped span-wise cooling channels 63, 64, 65, and 66.
  • span-wise means the channel is oriented in a direction between radially inner and outer ends of the airfoil.
  • Ring is with respect to the turbine axis of rotation.
  • channels 28, 29, 30, and 31 are span-wise channels. These channels may optionally have fins 44 as previously described regarding FIG 3 .
  • FIG 7 shows a process of forming ceramic cores 74, 75 for an airfoil mold.
  • the cores may be chemically removed after casting of the airfoil 60.
  • Flexible dies 84A, 84B, 85A, 85B or dies with flexible liners may be used to form the cores 74, 75 of a green-body ceramic that is stiff enough for pulling 89 of the dies elastically past interference points 91.
  • Such technology is taught for example in US patents 7,141,812 and 7,410,606 and 7,411,204 assigned to Mikro Systems Inc. of Charlottesville, Virginia. Even small negative taper angles such as -1 to -3 degrees are significant and useful for cooling efficiency compared to the positive taper angles required for removal of conventional rigid dies.
  • FIG 8 shows a transverse sectional view of an hourglass shaped cooling channel 65 with converging side surfaces 52, 54 defined by turbulators 92.
  • Each turbulator has a peak 97 in a middle portion thereof that defines the waist of the cooling channel.
  • the side surfaces 52, 54 on the turbulators may have the taper range previously described, or especially in the range of -2 to -5 degrees (-5 degrees shown).
  • the turbulators 92 may alternate with surfaces 95, 96 that are flat (shown) or have positive taper (not shown).
  • FIG. 9 shows an embodiment as in FIG 8 combined with profiled fins 44 on the near-wall inner surfaces 48, 50 as previously described.
  • FIG. 10 is a view taken along line 10-10 of FIG 8 showing peaked turbulators 92 with convex upstream sides 93 and straight downstream sides 94.
  • the convex upstream sides 93 urge the flow 22 toward the corners C.
  • the straight downstream sides 94 facilitate pulling the dies 84A, 84B, 85A, 85B of FIG 7 straight out, normal to the cores 74, 75.
  • the downstream sides 94 of the turbulators may be convex (not shown) such as parallel to the upstream sides 93.
  • FIGs 8-10 can be fabricated using the cost-effective process of FIG 7 .
  • the turbulators 92 concentrate the coolant flow toward the near-wall inner surfaces 48 and 50 and into the corners C.
  • the combination features shown in FIG 9 is especially effective and efficient, since the turbulators 92 slow the flow 22 centrally while concentrating it toward the inner surfaces 48 and 50, where the ribs 44 transfer heat from the exterior surfaces 40, 42, and increase the flow 22 toward the corners C.
  • the present hourglass-shaped channels are useful in any near-wall cooling application, such as in vanes, blades, shrouds, and possibly in combustors and transition ducts of gas turbines. They increase uniformity of cooling, especially in a parallel series of channels with either parallel flows or alternating serpentine flows.
  • the present channels may be formed by known fabrication techniques -- for example by casting an airfoil over a positive ceramic core that is chemically removed after casting.
  • a benefit of the invention is that the near-wall distal corners C of the channels remove more heat than prior cooling channels for a given coolant flow volume. This improves efficiency, effectiveness, and uniformity of cooling by overcoming the tendency of coolant to flow more slowly in the corners. Increasing the corner cooling helps compensate for the cooling gaps G between channels.
  • the invention also provides increased heat transfer from the primary surfaces 40, 42 to be cooled through the use of the fins 44.

Landscapes

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

Claims (9)

  1. Composant d'une turbine comprenant un canal de refroidissement intérieur (65), le canal de refroidissement (65) comprenant en outre :
    des première et seconde surfaces intérieures (48, 50) des première et seconde parois extérieures respectives (41, 43) du composant ; et
    des première et seconde surfaces latérales (52, 54) s'étendant entre les surfaces intérieures (48, 50),
    dans lequel une section transversale du canal (65) a un profil en forme de sablier dans lequel les surfaces latérales (52, 54) s'effilent l'une vers l'autre jusqu'à un rétrécissement qui est plus étroit qu'une largeur de chacune des première et seconde surfaces intérieures (48, 50) ; et
    dans lequel une direction globale d'un écoulement de liquide de refroidissement (22) dans le canal (65) est perpendiculaire au profil en forme de sablier,
    dans lequel le composant comprend en outre une pluralité de turbulateurs (92) sur chacune des surfaces latérales (52, 54) qui poussent le liquide de refroidissement vers les surfaces intérieures (48, 50), dans lequel un sommet (97) dans une partie médiane de chaque turbulateur (92) définit le rétrécissement du canal de refroidissement (65).
  2. Composant selon la revendication 1, dans lequel les première et seconde surfaces intérieures (48, 50) sont parallèles aux première et seconde parties respectives des surfaces extérieures (40, 42) des parois extérieures respectives (41, 43).
  3. Composant selon la revendication 1, dans lequel les première et seconde parois extérieures (41, 43) sont respectivement des intrados et extrados d'une surface aérodynamique de turbine (60).
  4. Composant selon la revendication 1, dans lequel la taille comprend une largeur de 80 % ou moins par rapport à la largeur d'au moins l'une des surfaces intérieures (48, 50).
  5. Composant selon la revendication 1, dans lequel chacune des surfaces latérales (52, 54) a un angle de conicité dans le profil d'au moins -1 degré vers le rétrécissement par rapport à une ligne droite entre les extrémités correspondantes des deux surfaces latérales (52, 54).
  6. Composant selon la revendication 1, comprenant en outre une pluralité d'ailettes parallèles (44) avec un profil de hauteur transversal qui est convexe sur une largeur d'au moins l'une des surfaces intérieures (48, 50), dans lequel les ailettes (44) sont orientées avec la direction d'écoulement de liquide de refroidissement (22).
  7. Composant selon la revendication 1, dans lequel chaque turbulateur (92) comprend un côté amont convexe (93).
  8. Composant selon la revendication 1, dans lequel chaque turbulateur (92) comprend un côté amont convexe (93) et un côté aval droit (94).
  9. Composant selon la revendication 1, comprenant en outre une pluralité d'ailettes parallèles (44) orientées avec la direction d'écoulement de liquide de refroidissement (22) sur chacune des surfaces intérieures (48, 50), dans lequel un profil de hauteur qui relie transversalement les sommets adjacents des ailettes (44) est convexe sur une largeur de chacune des surfaces intérieures (48, 50), dans lequel chaque turbulateur (92) comprend un côté amont convexe (93).
EP14706400.0A 2013-02-06 2014-02-05 Composant de turbine Active EP2954169B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20188996.1A EP3767074B1 (fr) 2013-02-06 2014-02-05 Composant d'une turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/760,107 US9017027B2 (en) 2011-01-06 2013-02-06 Component having cooling channel with hourglass cross section
PCT/US2014/014858 WO2014123994A1 (fr) 2013-02-06 2014-02-05 Composant possédant un canal de refroidissement doté d'une section transversale en sablier et composant de surface aérodynamique de turbine correspondant

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP20188996.1A Division EP3767074B1 (fr) 2013-02-06 2014-02-05 Composant d'une turbine

Publications (2)

Publication Number Publication Date
EP2954169A1 EP2954169A1 (fr) 2015-12-16
EP2954169B1 true EP2954169B1 (fr) 2020-08-05

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Application Number Title Priority Date Filing Date
EP14706400.0A Active EP2954169B1 (fr) 2013-02-06 2014-02-05 Composant de turbine
EP20188996.1A Active EP3767074B1 (fr) 2013-02-06 2014-02-05 Composant d'une turbine

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Application Number Title Priority Date Filing Date
EP20188996.1A Active EP3767074B1 (fr) 2013-02-06 2014-02-05 Composant d'une turbine

Country Status (5)

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EP (2) EP2954169B1 (fr)
JP (1) JP6120995B2 (fr)
CN (1) CN105829654B (fr)
RU (1) RU2629790C2 (fr)
WO (1) WO2014123994A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9803939B2 (en) * 2013-11-22 2017-10-31 General Electric Company Methods for the formation and shaping of cooling channels, and related articles of manufacture

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU444888A1 (ru) * 1973-01-03 1974-09-30 Предприятие П/Я В-2504 Охлаждаема лопатка турбины
US5695321A (en) * 1991-12-17 1997-12-09 General Electric Company Turbine blade having variable configuration turbulators
US5752801A (en) * 1997-02-20 1998-05-19 Westinghouse Electric Corporation Apparatus for cooling a gas turbine airfoil and method of making same
US7141812B2 (en) 2002-06-05 2006-11-28 Mikro Systems, Inc. Devices, methods, and systems involving castings
CA2448736C (fr) 2001-06-05 2010-08-10 Mikro Systems, Inc. Procedes de fabrication de dispositifs tridimensionnels, et dispositifs crees par ces procedes
GB0127902D0 (en) * 2001-11-21 2002-01-16 Rolls Royce Plc Gas turbine engine aerofoil
JP4191578B2 (ja) * 2003-11-21 2008-12-03 三菱重工業株式会社 ガスタービンエンジンのタービン冷却翼
US7080683B2 (en) * 2004-06-14 2006-07-25 Delphi Technologies, Inc. Flat tube evaporator with enhanced refrigerant flow passages
GB0418906D0 (en) * 2004-08-25 2004-09-29 Rolls Royce Plc Internally cooled aerofoils
GB0909255D0 (en) * 2009-06-01 2009-07-15 Rolls Royce Plc Cooling arrangements
US8764394B2 (en) * 2011-01-06 2014-07-01 Siemens Energy, Inc. Component cooling channel

Non-Patent Citations (1)

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Title
None *

Also Published As

Publication number Publication date
CN105829654A (zh) 2016-08-03
JP2016510380A (ja) 2016-04-07
EP2954169A1 (fr) 2015-12-16
RU2629790C2 (ru) 2017-09-04
EP3767074A1 (fr) 2021-01-20
WO2014123994A1 (fr) 2014-08-14
CN105829654B (zh) 2018-05-11
EP3767074B1 (fr) 2023-03-29
JP6120995B2 (ja) 2017-04-26
RU2015132763A (ru) 2017-03-15

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