EP2599957A1 - Système de nervure de refroidissement pour un canal de refroidissement d'une aube de turbine - Google Patents

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

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Publication number
EP2599957A1
EP2599957A1 EP11189911.8A EP11189911A EP2599957A1 EP 2599957 A1 EP2599957 A1 EP 2599957A1 EP 11189911 A EP11189911 A EP 11189911A EP 2599957 A1 EP2599957 A1 EP 2599957A1
Authority
EP
European Patent Office
Prior art keywords
cooling
cooling fin
rib
fin system
turbine blade
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.)
Withdrawn
Application number
EP11189911.8A
Other languages
German (de)
English (en)
Inventor
Marcel Eifel
Daniel Gloss
Andreas Heselhaus
Stephan Klumpp
Marco Link
Uwe Sieber
Stefan Völker
Michael Wagner
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 AG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Priority to EP11189911.8A priority Critical patent/EP2599957A1/fr
Priority to PCT/EP2012/073158 priority patent/WO2013076110A1/fr
Publication of EP2599957A1 publication Critical patent/EP2599957A1/fr
Withdrawn legal-status Critical Current

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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
    • 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

  • 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 designed in Axialbauweise, wherein the turbine is formed by a plurality of successively arranged in the flow direction blade rings.
  • the blade rings have circumferentially disposed blades and vanes, the blades being mounted on a rotor of the gas turbine and the vanes secured to the housing of the gas turbine.
  • thermodynamic efficiency of the gas turbine is the higher, the higher the inlet temperature of the hot gas into 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 turbine blade It is known to make the turbine blade hollow, wherein the interior of the turbine blade serves as a cooling passage through which cooling fluid flows during operation of the gas turbine.
  • the cooling fluid is air drawn from the compressor.
  • convection removes heat from the turbine blade, thereby reducing the contact temperature at the surface of the turbine blade.
  • the thermal load of the turbine blade is reduced, whereby the hot gas temperature can be increased accordingly, without the thermal load of the turbine blade is unacceptably high.
  • 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 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 projecting therefrom, so that the cooling rib has flowing transversely through cooling fluid flowing in the cooling channel, wherein the cooling rib has a downstream rear side in such a profiled manner towards the inner side of the blade, that the flow of cooling fluid during the operation of the turbine blade passes through the rear side without a release.
  • the turbine bucket has the cooling passage in which the cooling fluid for cooling the turbine bucket flows during operation thereof, whereby the turbine bucket 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 blade via convection by means of the cooling fluid, whereby the Konvetations Sab is increased by the provision of the cooling fin. Due to the fact that the cooling fluid flows off from the cooling rib at the rear without being detached, the flow resistance induced by the cooling rib is less than if the cooling rib had been provided with, for example, a rectangular cross section.
  • the cooling fluid would detach downstream and form a separation region, which leads to high pressure losses.
  • these pressure losses are so high that an intake of the hot gas into the cooling channel, for example through cooling air bores provided in the turbine blade, occurs, as a result of which the cooling of the turbine blade is interrupted.
  • the turbine blade would be subject to intense heating. In general, this heating of the turbine blade is so extreme that this leads to an unduly high thermal load on the turbine blade, whereby the turbine blade is destroyed.
  • cooling fin according to the invention in the cooling channel whose rear side is designed so that the cooling fluid flow can flow off during the operation of the turbine blade free of charge, 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 profiling of the rear side of the cooling rib according to the invention has virtually no influence on the quality of the cooling of the cooling rib in the cooling duct compared with FIG for example, a rectangular cross-section having cooling rib.
  • the inventive cooling rib system provides effective cooling of the turbine blade, wherein For example, the collection of the hot gas is advantageously prevented in the cooling channel.
  • the cooling rib preferably has a front side facing away from the rear side, which protrudes perpendicularly from the blade inner side.
  • the plateau is arranged parallel to the blade inner side, 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.
  • a plurality of dimples is preferably provided, which are dimensioned and distributed such that the dents act as turbulators during operation of the turbine blade for the cooling fluid flow.
  • the degree of turbulence of the boundary layer of the cooling fluid flow at the rear side is increased.
  • the flow of the cooling fluid at the rear side tends less to detach, whereby the rear side may tend to be formed steeper sloping towards the blade inner side.
  • the extension of the cooling fin and thus their use of material is reduced.
  • the turbulent boundary layer in the cooling fluid flow at the rear the heat transfer from the cooling fin to the cooling fluid is improved.
  • a recirculation area would be formed downstream of which a rebound cooling effect locally increases the heat transfer from the blade inner side to the cooling fluid in the area of the restarting. This effect, which would be lost by the free flow of the cooling fluid at the rear of the inventive fin equipped, is substantially compensated by the increase of the degree of turbulence of the boundary layer flow by means of the dimples.
  • the cooling fin is preferably swept, i. obliquely to the direction of flow, arranged. Furthermore, the cooling rib is preferably arranged in such a swept manner that a component can be generated in the cooling fluid flow from the trailing edge to the leading edge of the turbine blade.
  • 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 cooling rib preferably has laterally in each case one lateral flank delimiting the cooling rib, wherein the first side flank facing the inflow of the cooling fluid with the front side in the plan view of the cooling fin has a point angle and / or the second side flank facing away from the inflow of the cooling fluid with the front side in plan view the cooling fin forms a right angle.
  • the cooling system has at least two cooling ribs which are arranged next to one another in a row. In this case, it is preferred that the cooling ribs are arranged at a distance from each other, so that in each case a gap is formed between the cooling ribs, which passes through the cooling fluid flow during operation of the turbine blade.
  • the cooling fin system preferably has a plurality of rows formed by the cooling fins, wherein the rows are arranged one behind the other.
  • the cooling fins are preferably arranged in the rows such that the cooling fins are in gap with their gaps in between.
  • the fact that the rows are formed by the cooling fins are provided with the gaps the relative to the flow resistance of the cooling fins 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.
  • FIGS. 4 and 5 a section of a turbine blade 1 is shown, wherein the top view of a cut-open cooling channel 2, which is formed within the turbine blade 1, is shown.
  • FIGS. 4 and 5 is essentially lying in the plane of a blade inside 3, which defines the cooling channel 2.
  • the cooling channel 2 limits a front edge wall 5 arranged at the front edge 4 of the turbine blade 1 and a channel wall 6 arranged opposite the front edge wall 5.
  • FIGS. 1 to 3 are cross sections of embodiments of the cooling fin 8 shown.
  • the cooling rib 8 is flown by a cooling fluid flow 18, wherein the direction of the cooling fluid flow 18 in FIGS. 1 to 3 from left to right.
  • first embodiment of the cooling fin 8 has a front side 9 which protrudes perpendicularly from the blade inner side 3. Facing away from the blade inner side 3, the front side 9 with a plateau 11 forms an edge 10 at which a right angle is enclosed by the front side 9 and the plateau 11 and the plateau 11 is arranged parallel to the blade inner side 3.
  • 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 designed so that during operation of the turbine blade 1, the cooling fluid flow 18 flows around the cooling rib 8 without a release.
  • the second embodiment of the cooling fin 8 is shown, which differs from the first embodiment according to FIG. 1 only differs in that the rear side 12 is formed bent, whereas the rear side 12 according to the first embodiment according to FIG. 1 is formed straight.
  • the rear side 12 includes kink-free to the plateau 11 and runs downstream of the plateau 11 convexly curved toward the blade side 3.
  • the third in FIG. 3 shown embodiment of the cooling fin 8 differs from the second in FIG. 2 shown embodiment in that in the plateau 11 and the rear side 12 a plurality of dents 14 are arranged.
  • 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 second embodiment according to FIG. 2 corresponds.
  • the cooling fins 8 are arranged in four successive rows, 18 gaps 17 are provided in each row between the individual cooling fins, whereby the individual cooling fins 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 in FIG. 4 shown cooling ribs 8 has a first side edge 15 and a second side edge 16, wherein the side edges 15, 16 respectively delimit their associated cooling rib 8 side.
  • the first side edge 15 closes with the front side 9 in the in FIG. 4 shown top view, while the second side edge 16 with the front side 9 in the in FIG. 4 shown top view includes a right angle.
  • the first side flank 15 is that side flank of the cooling rib 8 which is arranged facing the inflow of the cooling fluid flow 18, wherein the second side flank 16 is that of the side flanks of the cooling fin 8 which faces the outflow of the cooling fluid flow 18.
  • the cooling fin system 7 is formed by a cooling fin 8
  • the third in FIG. 3 shown embodiment of the cooling fin 8 corresponds.
  • the cooling fin 8 extends transversely of the channel from the channel wall 6 to the front edge wall 5, wherein the cooling fin 8 is arranged with its front side 9 and its rib end 13 swept in the cooling channel 12.
  • the cooling fluid flow 18 when flowing over the cooling fin 8 has a tendency to flow from the channel wall 6 to the front edge wall 5.
  • the arranged in the plateau 11 and the rear side 12 of the fin 8 dents 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 rear 12. This is the one hand, the separation tendency of the boundary layer of the cooling fluid flow 18 at overcurrents of Cooling fin 8 reduced and on the other hand, the heat transfer from the cooling fin 8 to the cooling fluid flow 18 increases.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11189911.8A 2011-11-21 2011-11-21 Système de nervure de refroidissement pour un canal de refroidissement d'une aube de turbine Withdrawn EP2599957A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
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
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

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
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)

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EP2599957A1 true EP2599957A1 (fr) 2013-06-05

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EP11189911.8A Withdrawn EP2599957A1 (fr) 2011-11-21 2011-11-21 Système de nervure de refroidissement pour un canal de refroidissement d'une aube de turbine

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11313232B2 (en) 2017-03-10 2022-04-26 Mitsubishi Heavy Industries, Ltd. Turbine blade, turbine, and method for cooling turbine blade

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11313232B2 (en) 2017-03-10 2022-04-26 Mitsubishi Heavy Industries, Ltd. Turbine blade, turbine, and method for cooling turbine blade
DE112018001275B4 (de) 2017-03-10 2022-12-08 Mitsubishi Heavy Industries, Ltd. Turbinenschaufel, turbine und verfahren zum kühlen einer turbinenschaufel

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Publication number Publication date
WO2013076110A1 (fr) 2013-05-30

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