WO2013076110A1 - Système d'ailette de refroidissement pour un canal de refroidissement d'une aube de turbine - Google Patents

Système d'ailette de refroidissement pour un canal de refroidissement d'une aube de turbine Download PDF

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Publication number
WO2013076110A1
WO2013076110A1 PCT/EP2012/073158 EP2012073158W WO2013076110A1 WO 2013076110 A1 WO2013076110 A1 WO 2013076110A1 EP 2012073158 W EP2012073158 W EP 2012073158W WO 2013076110 A1 WO2013076110 A1 WO 2013076110A1
Authority
WO
WIPO (PCT)
Prior art keywords
cooling
fin
turbine blade
blade
rib
Prior art date
Application number
PCT/EP2012/073158
Other languages
German (de)
English (en)
Inventor
Marcel Eifel
Daniel Gloss
Andreas Heselhaus
Stephan Klumpp
Marco Link
Uwe Sieber
Stefan Völker
Michael Wagner
Original Assignee
Siemens Aktiengesellschaft
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 filed Critical Siemens Aktiengesellschaft
Publication of WO2013076110A1 publication Critical patent/WO2013076110A1/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
    • F05D2240/126—Baffles or ribs
    • 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
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • 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
    • 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
    • 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

  • Cooling fin system for a cooling channel of a turbine blade
  • the invention relates to a cooling rib system for a cooling channel of a turbine blade.
  • a gas turbine has a turbine in which hot gas, which has previously been compressed in a compressor and heated to a combustion chamber, is depressurized for work recovery.
  • the turbine is converted into ⁇ axial construction, the turbine is formed by a plurality of successive processing in fürströmungsrich- blade rings.
  • the blade rings have arranged over the circumference running ⁇ blades and vanes, wherein the blades are mounted on a rotor of the gas turbine and the guide vanes on the housing of the gas turbine.
  • thermodynamic efficiency of the gas turbine is the more hö ⁇ forth, the higher the inlet temperature of the hot gas in the turbine.
  • thermal load capacity of the turbine blades there are limits with regard to the thermal load capacity of the turbine blades.
  • corresponding materials and material combinations are available for the turbine blades, which, however, according to the current state of the art, only allow an insufficient expansion of the potential for increasing the thermal efficiency of the gas turbine.
  • the object of the invention is to provide a cooling fin system for a cooling channel of a turbine blade, wherein the turbine blade is effectively cooled with the cooling fin system.
  • the object is solved with the features of claim 1. Advantageous embodiments thereof are given in the further claims.
  • the cooling fin system according to the invention for a cooling channel of a turbine blade has at least one cooling rib which is arranged on the blade inner side of the cooling channel, so that the cooling rib is flowed transversely by cooling fluid flowing in the cooling channel, wherein the cooling rib has a downstream rear side , which runs in such a profiled manner towards the blade inner side, that the cooling fluid flow passes through the rear side during the operation of the turbine blade.
  • the turbine blade has the cooling passage in which the cooling fluid for cooling the turbine blade during operation of the same ⁇ flows, whereby the turbine blade is cooled by the cooling fluid.
  • This can be relaxed with the turbine blade hot gas at such a high temperature, without the Cooling would lead to an impermissibly high thermal load on the turbine blade.
  • the cooling of the turbine show ⁇ fel via convection by the cooling fluid, so that the convection effect replaced by the provision of the fin is increased. Characterized in that the cooling fluid from the cooling fin at the rear free transfer flows, induced by the cooling rib ⁇ flow resistance is less, as if the cooling fin provided with for example a rectangular cross section.
  • the cooling fin in the cooling channel whose rear side is designed so that the flow of cooling fluid can flow freely in the transfer operation of the door ⁇ binenschaufel, whereby any pressure losses in the cooling fluid flow are low. This advantageously prevents the possible entry of the hot gas into the cooling channel during operation of the turbine blade.
  • the heat transfer characteristics of the fin is substantially defined by the geometry of the front face, which faces the inflow
  • Inventive ⁇ modern profiling of the rear side of the cooling fin has virtually no influence on the quality of the cooling of the cooling fin compared in the cooling channel with the example, a rectangular cross-section having cooling rib.
  • the inventive cooling fin system provides effective cooling of the turbine blade, whereby in example, the collection of the hot gas in the cooling ⁇ channel is advantageously prevented.
  • the cooling rib preferably has a front side which faces away from the rear side and protrudes perpendicularly from the blade inner side.
  • the cooling fin has a plateau which is disposed between the front side and the rear side, and bridges the front and Hin ⁇ underside.
  • the plateau is arranged parallel to the blade inside, so that the edge formed by the front side and the plateau has a right angle.
  • the trailing edge is ramped, in particular rectilinear and / or convex and concave contours, formed.
  • Boundary layer in the cooling fluid flow at the rear improves the heat transfer from the cooling fin to the cooling fluid.
  • a recirculation area would form downstream, in the area of the re-application an impingement cooling effect locally increasing the heat transfer from the blade inside to the cooling fluid.
  • This effect which would be lost by the free flow of cooling fluid out at the rear of the erfindungsge ⁇ equipped radiator, is substantially compensated by increasing the degree of turbulence of the boundary layer flow by means of the dimples.
  • the cooling rib is preferably swept, ie, arranged obliquely to the on ⁇ flow direction.
  • the fin is swept preferably arranged such that, in the cooling fluid flow ei ⁇ ne component from the rear edge to the front edge of the turbo is generated binenschaufel.
  • the temperature of the hot gas in the region of the trailing edge of the turbine blade tends to be lower than in the region of the leading edge. Due to the fact that the flow component of the cooling fluid from the trailing edge to the leading edge during operation of the turbine blade arises with the sweep of the cooling rib, the cooling rib system for the turbine blade acts more or less like a countercurrent heat exchanger.
  • the fin preferably has at each side a cooling ⁇ rib laterally delimiting side edge, with the side facing the incoming flow of the cooling fluid first side edge to the front side in the plan view of the cooling fin a peak ⁇ angle and / or the inflow of the cooling fluid facing away from second side edge with the Front in the top view of the fin includes a right angle. Further, it is sawn vorzugt that the cooling system includes at least two cooling fins on ⁇ which are arranged in a row next to each other.
  • the cooling fins are arranged at a distance zuein ⁇ other, so that between the cooling fins in each case a gap is formed, which passes the cooling fluid flow during operation of the turbine blade.
  • Thederippensys ⁇ system preferably has a plurality of rows, which are formed by the cooling fins, wherein the rows are arranged one behind the other.
  • the cooling ribs are preferably arranged in the rows in such a way that the cooling ribs with their intervening gaps are in gap.
  • the fact that the rows are formed by the cooling fins are provided with the gaps, the relative to the flow resistance surface of thederip ⁇ pen is reduced, whereby the pressure loss induced by the cooling fins is additionally lowered. Further, by providing the gaps, the degree of turbulence of the cooling fluid flow is increased, thereby additionally increasing the heat transfer from the cooling fins to the cooling fluid.
  • Figure 1 shows a cross section of a first embodiment of the cooling fin according to the invention
  • FIG. 2 is a cross-section of a second embodiment of the cooling fin according to the invention
  • FIG. 3 shows a cross section of a third embodiment of the cooling rib according to the invention
  • Figure 4 is a plan view of a cross section of a cooling ⁇ channel with the inventive cooling fin system, which is formed by an arrangement of the second embodiment of the fin according to Figure 2, and
  • FIG. 5 shows a plan view of a cross section of the cooling channel with the cooling fin system, which is formed by the embodiment of the cooling fin according to FIG.
  • FIGS. 4 and 5 show a detail of a turbine blade 1 is shown with the plan view of a cut ⁇ cooling channel 2 is shown, formed within the turbine blade.
  • a blade inner side is lying 3
  • Darge ⁇ represents which delimits the cooling channel 2 is substantially in the drawing plane.
  • 2 limits the cooling passage means disposed at the front edge 4 of the turbine blade 1 leading edge wall 5 and one of the leading edge wall 5 against oppositely disposed channel wall 6.
  • aderip ⁇ pen system 7 At the blade ⁇ inside 3 is arranged in each case aderip ⁇ pen system 7 according to Figures 4 and 5, wherein the cooling fins System 7 According to FIG. 4, a plurality of cooling ribs 8 and the cooling rib system 7 according to FIG. 5 have a single cooling rib 8.
  • FIGS. 1 to 3 show cross sections of embodiments of the cooling rib 8.
  • the cooling rib 8 flows against a cooling fluid flow 18, the direction of the cooling fluid flow 18 in FIGS. 1 to 3 extending from left to right.
  • the first embodiment of the cooling rib 8 shown in FIG. 1 has a front side 9 which projects perpendicularly from the blade inner side 3.
  • the blade inside 3 faces away forms the
  • Downstream of the plateau 11 includes a rear side 12, which is formed in a ramp shape and extends to a cooling fin end 13 of the plateau 11 to the blade inner side 3 out linear.
  • the contour transitions from the plateau 11 to the rear side 12 and from the rear side 12 to the blade inner side 3 via the cooling fin end 13 are formed so that during operation of the turbine blade 1 the
  • Cooling fluid flow 18 the cooling fin 8 flows around free of charge.
  • the second embodiment of the cooling fin 8 is shown, which differs from the first embodiment shown in Figure 1 only in that the rear side 12 gebo ⁇ gen is formed, whereas the rear side 12 according to the first embodiment of Figure 1 is rectilinear.
  • the rear side 12 adjoins the plateau 11 without kinking and, downstream of the plateau 11, runs convexly curved toward the blade side 3.
  • the third embodiment shown in FIG. 3 of the cooling rib 8 differs from the second embodiment shown in FIG. 2 in that a plurality of dimples 14 are arranged in the plateau 11 and the rear side 12.
  • the dimples 14 act as turbulators, so that the boundary layer of the cooling fluid flow 18 at the plateau 11 and at the rear 12 has a high degree of turbulence.
  • the embodiment of the cooling rib system 7 shown in FIG. 4 is formed by a plurality of cooling ribs 8 which are the ones of FIG second embodiment according to FIG 2 correspond.
  • the cooling ribs 8 are arranged in four rows one behind the other, wherein gaps 17 are provided in each row between the individual cooling ribs 18, whereby the individual cooling ribs 8 are arranged in each row at a distance from each other.
  • the cooling fins of each of the rows are arranged in alignment with each other, wherein the cooling fins are arranged in the individual rows such that the individual rows are in gap. That is, one of the cooling fins of the adjacent row is arranged transversely to each gap 17 of each of the rows, so that the cooling fluid flow 18 has a meandering flow path when passing through the gaps 17.
  • the cooling ribs 8 are arranged in the cooling channel on the blade upper side 3 with respect to the front edge 4 of the turbine blade 1, whereby the cooling fluid flow 18 receives a flow component to the leading edge 4 during the flow around the cooling ribs 8.
  • the tendency for the fluid flow 18 to flow is that the cooling fluid flow 18 flows from the channel wall 6 to the front edge wall 5.
  • Each of the cooling fins 8 shown in figure 4 has a first side edge 15 and a second side edge 16, wherein the side flanks 15, 16 respectively that limit its associated cooling ⁇ rib 8 side.
  • the embodiment of the cooling fins system 7 shown in Figure 5 is formed of a cooling fin 8, which corresponds to the third embodiment of the cooling fin 8 ⁇ gur 3 shown in Fi.
  • the cooling fin 8 extends transversely to the channel from the channel wall 6 to the front edge wall 5, wherein the cooling fin 8 with ih ⁇ rer front side 9 and its rib end 13 is arranged in the cooling channel 12 arrowed. Thereby obtains the cooling fluid ⁇ flow 18 when flowing over the fin 8 to flow as an indication of the channel wall 6 to the leading edge wall. 5
  • the attached ⁇ arranged in the plateau 11 and the rear side 12 of the fin 8 dimples 14 serve as turbulators and increase the degree of turbulence of the boundary layer of the cooling fluid flow 18 in the region of the plateau 11 and the back 12.

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

Abstract

L'invention concerne un système d'ailette de refroidissement destiné à un canal de refroidissement (2) d'une aube de turbine (1) et comprenant au moins une ailette de refroidissement (8) qui est placée sur la face intérieure d'aube (6) du canal de refroidissement (2) en saillie par rapport à cette face de sorte qu'elle est exposée transversalement au fluide de refroidissement (18) s'écoulant dans le canal de refroidissement (2). L'ailette de refroidissement (8) présente une face arrière (12) située en aval, qui est profilée par rapport à la face intérieure d'aube (3) de sorte que l'écoulement de fluide de refroidissement (18) franchit la face arrière (12) sans phénomène de décollement lors du fonctionnement de l'aube de turbine (1).
PCT/EP2012/073158 2011-11-21 2012-11-21 Système d'ailette de refroidissement pour un canal de refroidissement d'une aube de turbine WO2013076110A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP11189911.8 2011-11-21
EP11189911.8A EP2599957A1 (fr) 2011-11-21 2011-11-21 Système de nervure de refroidissement pour un canal de refroidissement d'une aube de turbine

Publications (1)

Publication Number Publication Date
WO2013076110A1 true WO2013076110A1 (fr) 2013-05-30

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2012/073158 WO2013076110A1 (fr) 2011-11-21 2012-11-21 Système d'ailette de refroidissement pour un canal de refroidissement d'une aube de turbine

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Country Link
EP (1) EP2599957A1 (fr)
WO (1) WO2013076110A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6806599B2 (ja) 2017-03-10 2021-01-06 三菱パワー株式会社 タービン翼、タービン及びタービン翼の冷却方法

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5472316A (en) * 1994-09-19 1995-12-05 General Electric Company Enhanced cooling apparatus for gas turbine engine airfoils
EP0939196A2 (fr) * 1998-02-26 1999-09-01 Kabushiki Kaisha Toshiba Aube de turbine à gaz
JP2000282804A (ja) * 1999-03-30 2000-10-10 Toshiba Corp ガスタービン翼
US20020025248A1 (en) * 1999-08-16 2002-02-28 Ching-Pang Lee Method for enhancing heat transfer inside a turbulated cooling passage
US20060099073A1 (en) * 2004-11-05 2006-05-11 Toufik Djeridane Aspherical dimples for heat transfer surfaces and method
US20060239820A1 (en) * 2005-04-04 2006-10-26 Nobuaki Kizuka Member having internal cooling passage
EP1818504A2 (fr) * 2006-02-09 2007-08-15 Hitachi, Ltd. Matériau comportant un canal de refroidissement interne et procédé de refroidissement d'un matériau comportant un canal de refroidissement interne
GB2473949A (en) * 2009-09-24 2011-03-30 Gen Electric Heat transfer apparatus with turbulators

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5472316A (en) * 1994-09-19 1995-12-05 General Electric Company Enhanced cooling apparatus for gas turbine engine airfoils
EP0939196A2 (fr) * 1998-02-26 1999-09-01 Kabushiki Kaisha Toshiba Aube de turbine à gaz
JP2000282804A (ja) * 1999-03-30 2000-10-10 Toshiba Corp ガスタービン翼
US20020025248A1 (en) * 1999-08-16 2002-02-28 Ching-Pang Lee Method for enhancing heat transfer inside a turbulated cooling passage
US20060099073A1 (en) * 2004-11-05 2006-05-11 Toufik Djeridane Aspherical dimples for heat transfer surfaces and method
US20060239820A1 (en) * 2005-04-04 2006-10-26 Nobuaki Kizuka Member having internal cooling passage
EP1818504A2 (fr) * 2006-02-09 2007-08-15 Hitachi, Ltd. Matériau comportant un canal de refroidissement interne et procédé de refroidissement d'un matériau comportant un canal de refroidissement interne
GB2473949A (en) * 2009-09-24 2011-03-30 Gen Electric Heat transfer apparatus with turbulators

Also Published As

Publication number Publication date
EP2599957A1 (fr) 2013-06-05

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