EP1614861A1 - Roue de turbine comprenant des aubes de turbine avec turbulateurs sur la surface radiale interne de la plate-forme - Google Patents

Roue de turbine comprenant des aubes de turbine avec turbulateurs sur la surface radiale interne de la plate-forme Download PDF

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Publication number
EP1614861A1
EP1614861A1 EP04016237A EP04016237A EP1614861A1 EP 1614861 A1 EP1614861 A1 EP 1614861A1 EP 04016237 A EP04016237 A EP 04016237A EP 04016237 A EP04016237 A EP 04016237A EP 1614861 A1 EP1614861 A1 EP 1614861A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbulators
platform
cooling
turbine
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Withdrawn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
EP04016237A
Other languages
German (de)
English (en)
Inventor
Hans-Thomas Dr. Bolms
Andreas Dr. Heselhaus
Roland Häbel
Torsten Koch
Ralf Müsgen
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 EP04016237A priority Critical patent/EP1614861A1/fr
Priority to PL05766734T priority patent/PL1766192T3/pl
Priority to EP05766734A priority patent/EP1766192B1/fr
Priority to DE502005010841T priority patent/DE502005010841D1/de
Priority to ES05766734T priority patent/ES2358336T3/es
Priority to PCT/EP2005/052714 priority patent/WO2006005659A1/fr
Priority to CN2005800300077A priority patent/CN101014752B/zh
Priority to US11/632,013 priority patent/US7758309B2/en
Priority to AT05766734T priority patent/ATE495347T1/de
Priority to JP2007519759A priority patent/JP4637906B2/ja
Publication of EP1614861A1 publication Critical patent/EP1614861A1/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Withdrawn legal-status Critical Current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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/12—Manufacture by removing material by spark erosion methods
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/291—Three-dimensional machined; miscellaneous hollowed
    • 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 invention relates to a blade wheel of a turbine with a blade whose blade root is supported on a wheel disc, and in which there is at least one cooling channel between the wheel disc of the turbine and the blade root. Furthermore, the invention relates to a blade of such a paddle wheel.
  • Paddle wheels of the type mentioned are used, for example, in stationary gas turbines as blade wheels, which are arranged in the flow direction of fuel gas behind a combustion chamber of the gas turbine and exposed there to high temperatures.
  • the cooling of the blades and in particular the blade roots of such high-temperature loaded gas turbine blades is particularly complicated due to the required complex cooling fluid management and difficult seals at the same time high centrifugal force.
  • Turbine blades are currently operating with convective cooling and other means to enhance heat transfer between a cooling fluid flowing through cooling channels on the blade root and the blade root. Often, only a comparatively small amount of cooling fluid is available, so that only a small heat flow can be dissipated through a platform of the blade root. Thus, the platform surface temperature can only be lowered slightly.
  • the invention has for its object to provide a paddle wheel of a turbine with a blade, achieved at the blade root or blade platform increased cooling and a relatively high heat flow can be dissipated. It is another object of the invention to provide a manufacturing method for such a blade.
  • This first object is inventively achieved in that a plurality of turbulators is formed on at least one of the walls of the cooling channel of a paddle wheel according to the invention, which are designed such that they increase the turbulence of a cooling fluid flowing through the cooling channel.
  • the cooling fluid does not flow along more or less smooth walls in the at least one cooling channel between the wheel disc and the blade root, but rather a plurality of turbulators or turbulence elements are provided on at least one of the walls the cooling channel are formed and increase the turbulence of the cooling fluid within the cooling channel.
  • turbulators With these turbulators, the heat transfer between the cooling fluid and the associated wall of the cooling channel is increased and the blade root is thereby increasingly cooled.
  • the turbulators or turbulence elements are adapted in accordance with the desired heat transfer, so that a maximum hot gas-side material temperature can be specifically predetermined on the associated blade and the cooling fluid flow can be dimensioned correspondingly through the cooling channel.
  • turbulators ribs or nipples or dimples can be used.
  • the plurality of turbulators is advantageously formed on the underside of a platform of the blade root.
  • the plurality of turbulators is advantageously designed in the form of pockets, which are formed in the at least one wall of the cooling channel forming material. Such pockets can also be subsequently formed in existing blades and thus the invention desired enlargement of the heat transfer at the blade root can be achieved.
  • the turbulators or pockets are also advantageously aligned in each case substantially transversely or obliquely to the flow direction of the cooling fluid flowing through the cooling channel. Such turbulators lead to a particularly strong turbulence of cooling fluid flowing in the cooling channel.
  • the number of turbulators or pockets provided per unit area should be increased in comparison to areas of lower heat load in such areas of increased heat load.
  • the blade root of at least one blade should also advantageously be designed with a platform on each side of which a cooling channel is located along an elongate neck of the blade root and the plurality of turbulators in the form of a extending in the associated cooling channel at the bottom of the platform Series is designed.
  • paddle wheels can be upgraded without much structural change for use at higher temperatures.
  • the turbulators according to the invention can also be formed in an operation forming the blade and in particular its blade, so that almost no additional effort is required for its production.
  • the turbulators can be formed in a separate operation after at least one operation forming the blade and in particular its blade.
  • paddle wheels of existing turbines can be retrofitted in accordance with the invention with turbulators or pockets, which lead to the above-described improved heat transfer at the blade root.
  • the object of the invention is further achieved with a blade of a blade wheel of a turbine, in particular a gas turbine, which is provided with an airfoil and a blade root, which has a platform and in which on the side facing away from the airfoil underside of the platform formed a plurality of turbulators which are designed such that they increase the turbulence of a flowing along the bottom cooling fluid in the installed state of the blade.
  • a blade of a blade wheel of a turbine in particular a gas turbine, which is provided with an airfoil and a blade root, which has a platform and in which on the side facing away from the airfoil underside of the platform formed a plurality of turbulators which are designed such that they increase the turbulence of a flowing along the bottom cooling fluid in the installed state of the blade.
  • the plurality of turbulators on such a blade should be designed in the form of pockets which are formed in the material of the platform.
  • the turbulators are formed in a the blade forming operation with.
  • the turbulators are thus mitgeformt directly in the re-production of the blade.
  • an already existing and used blade during an inspection incident of the gas turbine be retrofitted with the turbulators by these are formed in a separate operation after at least one of the blade (14) forming operation.
  • the service life of the blade can be further increased while saving of cooling air, which also has a positive effect on the efficiency of the gas turbine.
  • a blade 10 is illustrated according to the prior art, which has a blade root 12 and an adjoining blade 14.
  • the blade root 12 is designed as a fir tree root with a platform 16 on which a neck 18 and farther away teeth 20 are arranged on the side opposite the blade blade 14.
  • the platform 16, the neck 18 and the teeth 20 are designed as an elongated profile, which is arranged with built-in blade 10 in a not shown groove of a wheel disc 22 of a turbine runner and there is provided for holding the airfoil 14 and for receiving in particular its centrifugal forces.
  • FIG. 3 Such an installation position of a blade 10 on a wheel disc 22 is basically illustrated in FIG. 3.
  • the underside of the platform 16 facing the neck 18 and the teeth 20 is provided with a substantially smooth surface.
  • blade 10 which is basically designed with respect to the blade root 12 as the example of FIG. 1, the bottom 24, however, designed with a plurality of turbulators 26, each arranged in a row on both sides of the neck 18 are.
  • the turbulators 26 are turned to a cooling channel 28 which is provided between the built-in wheel disc 22 blade root 12 and the wheel disc 22.
  • the cooling channel 28 flows through a cooling fluid, not shown, in a flow direction 30.
  • the turbulators 26 are designed transversely or obliquely to the flow direction 30 as pockets which are formed in the material of the platform 16 and to whose underside 24 in each case have an opening. In these pockets there is an additional turbulence of the cooling fluid flowing through the cooling channel 28 and thus to an improved heat transfer from the platform 16 into the cooling fluid.
  • the pockets lead to increased heat dissipation and improved cooling of the blade root 12 and the platform 16.
  • the pockets of the turbulators 26 may, for example, be anodized into the material of the platform 16 and advantageously have a length which corresponds approximately to two to seven times, in particular three to five times, particularly advantageously four times the width of a pocket.
  • the turbulators 26 may also be designed in the form of nipples or dimples on the underside 24 of the platform 16. With such turbulators 26 slots or webs are respectively formed on the underside 24, which Represent partial flow resistance for the flowing through the cooling passage 28 cooling fluid and thus lead to turbulence within the cooling fluid.
  • additional material can be applied to the underside of the platform for the turbulators by build-up welding. This additional material is then at least partially removed in a subsequent step by suitable methods, so as to form the turbulators.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
EP04016237A 2004-07-09 2004-07-09 Roue de turbine comprenant des aubes de turbine avec turbulateurs sur la surface radiale interne de la plate-forme Withdrawn EP1614861A1 (fr)

Priority Applications (10)

Application Number Priority Date Filing Date Title
EP04016237A EP1614861A1 (fr) 2004-07-09 2004-07-09 Roue de turbine comprenant des aubes de turbine avec turbulateurs sur la surface radiale interne de la plate-forme
PL05766734T PL1766192T3 (pl) 2004-07-09 2005-06-13 Koło łopatkowe turbiny z łopatką i co najmniej jednym kanałem chłodzącym
EP05766734A EP1766192B1 (fr) 2004-07-09 2005-06-13 Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant
DE502005010841T DE502005010841D1 (de) 2004-07-09 2005-06-13 Indestens einem kühlkanal
ES05766734T ES2358336T3 (es) 2004-07-09 2005-06-13 Rueda de álabes de una turbina con un álabe y al menos un canal de refrigeración.
PCT/EP2005/052714 WO2006005659A1 (fr) 2004-07-09 2005-06-13 Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant
CN2005800300077A CN101014752B (zh) 2004-07-09 2005-06-13 带有叶片和至少一个冷却通道的透平叶轮
US11/632,013 US7758309B2 (en) 2004-07-09 2005-06-13 Vane wheel of turbine comprising a vane and at least one cooling channel
AT05766734T ATE495347T1 (de) 2004-07-09 2005-06-13 Schaufelrad einer turbine mit einer schaufel und mindestens einem kühlkanal
JP2007519759A JP4637906B2 (ja) 2004-07-09 2005-06-13 タービンの翼と少なくとも１個の冷却通路を備えた翼車

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04016237A EP1614861A1 (fr) 2004-07-09 2004-07-09 Roue de turbine comprenant des aubes de turbine avec turbulateurs sur la surface radiale interne de la plate-forme

Publications (1)

Publication Number Publication Date
EP1614861A1 true EP1614861A1 (fr) 2006-01-11

Family

ID=34925688

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04016237A Withdrawn EP1614861A1 (fr) 2004-07-09 2004-07-09 Roue de turbine comprenant des aubes de turbine avec turbulateurs sur la surface radiale interne de la plate-forme
EP05766734A Active EP1766192B1 (fr) 2004-07-09 2005-06-13 Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05766734A Active EP1766192B1 (fr) 2004-07-09 2005-06-13 Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant

Country Status (9)

Country Link
US (1) US7758309B2 (fr)
EP (2) EP1614861A1 (fr)
JP (1) JP4637906B2 (fr)
CN (1) CN101014752B (fr)
AT (1) ATE495347T1 (fr)
DE (1) DE502005010841D1 (fr)
ES (1) ES2358336T3 (fr)
PL (1) PL1766192T3 (fr)
WO (1) WO2006005659A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8152436B2 (en) * 2008-01-08 2012-04-10 Pratt & Whitney Canada Corp. Blade under platform pocket cooling

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US8408872B2 (en) * 2009-09-24 2013-04-02 General Electric Company Fastback turbulator structure and turbine nozzle incorporating same
FR2961845B1 (fr) * 2010-06-28 2013-06-28 Snecma Propulsion Solide Aube de turbomachine a geometrie complementaire paire/impaire et son procede de fabrication
US10253642B2 (en) 2013-09-16 2019-04-09 United Technologies Corporation Gas turbine engine with disk having periphery with protrusions
EP3047112B1 (fr) 2013-09-17 2018-11-14 United Technologies Corporation Turbine à gaz dotée d'un joint d'étanchéité présentant des saillies
US10001013B2 (en) * 2014-03-06 2018-06-19 General Electric Company Turbine rotor blades with platform cooling arrangements
CA2950011C (fr) 2014-05-29 2020-01-28 General Electric Company Generateur de turbulence fastback
US10364684B2 (en) 2014-05-29 2019-07-30 General Electric Company Fastback vorticor pin
US10280785B2 (en) 2014-10-31 2019-05-07 General Electric Company Shroud assembly for a turbine engine
US10233775B2 (en) 2014-10-31 2019-03-19 General Electric Company Engine component for a gas turbine engine
US10030523B2 (en) * 2015-02-13 2018-07-24 United Technologies Corporation Article having cooling passage with undulating profile
US10047611B2 (en) 2016-01-28 2018-08-14 United Technologies Corporation Turbine blade attachment curved rib stiffeners
US10077665B2 (en) * 2016-01-28 2018-09-18 United Technologies Corporation Turbine blade attachment rails for attachment fillet stress reduction
US10822987B1 (en) 2019-04-16 2020-11-03 Pratt & Whitney Canada Corp. Turbine stator outer shroud cooling fins

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Publication number Priority date Publication date Assignee Title
US5252026A (en) * 1993-01-12 1993-10-12 General Electric Company Gas turbine engine nozzle
US5531568A (en) * 1994-07-02 1996-07-02 Rolls-Royce Plc Turbine blade
EP1074695A2 (fr) * 1999-08-02 2001-02-07 United Technologies Corporation Méthode pour réaliser un passage de refroidissement dans une aube de turbine
US20040081556A1 (en) * 2002-10-24 2004-04-29 Andre Chevrefils Blade passive cooling feature
DE10355449A1 (de) * 2002-12-02 2004-06-09 Alstom Technology Ltd Turbinenschaufel

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US3800864A (en) * 1972-09-05 1974-04-02 Gen Electric Pin-fin cooling system
US4712979A (en) * 1985-11-13 1987-12-15 The United States Of America As Represented By The Secretary Of The Air Force Self-retained platform cooling plate for turbine vane
JPS6463605A (en) * 1987-09-04 1989-03-09 Hitachi Ltd Gas turbine moving blade
US5201847A (en) * 1991-11-21 1993-04-13 Westinghouse Electric Corp. Shroud design
US6158962A (en) * 1999-04-30 2000-12-12 General Electric Company Turbine blade with ribbed platform
EP1128023A1 (fr) * 2000-02-25 2001-08-29 Siemens Aktiengesellschaft Aube rotorique de turbine
FR2833035B1 (fr) * 2001-12-05 2004-08-06 Snecma Moteurs Plate-forme d'aube de distributeur pour moteur a turbine a gaz
EP1413715A1 (fr) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Dispositif de refroidissement pour une plate-forme d'une aube d'une turbine à gaz
DE10332561A1 (de) * 2003-07-11 2005-01-27 Rolls-Royce Deutschland Ltd & Co Kg Gekühltes Turbinenlaufrad, insbesondere Hochdruckturbinenlaufrad für ein Flugtriebwerk
US7186089B2 (en) * 2004-11-04 2007-03-06 Siemens Power Generation, Inc. Cooling system for a platform of a turbine blade

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5252026A (en) * 1993-01-12 1993-10-12 General Electric Company Gas turbine engine nozzle
US5531568A (en) * 1994-07-02 1996-07-02 Rolls-Royce Plc Turbine blade
EP1074695A2 (fr) * 1999-08-02 2001-02-07 United Technologies Corporation Méthode pour réaliser un passage de refroidissement dans une aube de turbine
US20040081556A1 (en) * 2002-10-24 2004-04-29 Andre Chevrefils Blade passive cooling feature
DE10355449A1 (de) * 2002-12-02 2004-06-09 Alstom Technology Ltd Turbinenschaufel

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8152436B2 (en) * 2008-01-08 2012-04-10 Pratt & Whitney Canada Corp. Blade under platform pocket cooling

Also Published As

Publication number Publication date
CN101014752B (zh) 2011-06-08
WO2006005659A1 (fr) 2006-01-19
EP1766192A1 (fr) 2007-03-28
PL1766192T3 (pl) 2011-06-30
DE502005010841D1 (de) 2011-02-24
US20080267784A1 (en) 2008-10-30
US7758309B2 (en) 2010-07-20
JP2008506061A (ja) 2008-02-28
ATE495347T1 (de) 2011-01-15
CN101014752A (zh) 2007-08-08
ES2358336T3 (es) 2011-05-09
EP1766192B1 (fr) 2011-01-12
JP4637906B2 (ja) 2011-02-23

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