EP1953342A1 - Turbinenschaufel - Google Patents

Turbinenschaufel Download PDF

Info

Publication number
EP1953342A1
EP1953342A1 EP07002215A EP07002215A EP1953342A1 EP 1953342 A1 EP1953342 A1 EP 1953342A1 EP 07002215 A EP07002215 A EP 07002215A EP 07002215 A EP07002215 A EP 07002215A EP 1953342 A1 EP1953342 A1 EP 1953342A1
Authority
EP
European Patent Office
Prior art keywords
support structure
turbine blade
blade
cooling
sheath
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Withdrawn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
EP07002215A
Other languages
German (de)
English (en)
French (fr)
Inventor
Fathi Ahmad
Scarlett Fajardo-Reina
Markus Gill
Stefan Werner Dr. Kiliani
Silvio-Ulrich Dr. Martin
Ralf Müsgen
Oliver Dr. Schneider
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP07002215A priority Critical patent/EP1953342A1/de
Priority to JP2009547622A priority patent/JP4959811B2/ja
Priority to US12/525,156 priority patent/US8267659B2/en
Priority to PCT/EP2008/050325 priority patent/WO2008092725A1/de
Priority to CN200880003931XA priority patent/CN101600853B/zh
Priority to RU2009132675/06A priority patent/RU2430240C2/ru
Priority to EP08701454A priority patent/EP2126286A1/de
Publication of EP1953342A1 publication Critical patent/EP1953342A1/de
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D5/181—Blades having a closed internal cavity containing a cooling medium, e.g. sodium
    • 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
    • F01D5/182—Transpiration 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/238—Soldering
    • 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
    • F05D2240/24—Rotors for turbines
    • F05D2240/241—Rotors for turbines of impulse type
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • Y10T29/49341—Hollow blade with cooling passage

Definitions

  • the invention relates to a turbine blade.
  • Turbine blades in particular turbine blades for gas turbines, are exposed during operation to high temperatures, which may also exceed the limit of material stress. This applies in particular to the regions in the vicinity of the flow inlet edge of the turbine blades.
  • high temperatures which may also exceed the limit of material stress.
  • turbine blades suitable In order to use turbine blades even at high temperatures, it has long been known to cool turbine blades suitable, so that they have a higher temperature resistance, the importance of blade cooling, especially in gas turbines due to the increasing gas turbine inlet temperatures steadily increases. With turbine blades, which have a higher temperature resistance, higher energy efficiencies can be achieved in particular.
  • Cooling cooling is probably the most common type of blade cooling.
  • This type of cooling cooling air is passed through channels in the interior of the blade and uses the convective effect to dissipate the heat.
  • impingement cooling a cooling air flow impinges on the blade surface from the inside. In this way, a very good cooling effect is made possible at the point of impact, but this is limited only to the narrow area of the point of impact and the closer environment.
  • This type of cooling is therefore usually used for cooling the flow inlet edge of a turbine blade, which is exposed to high local temperature loads.
  • film cooling cooling air is directed out through openings in the turbine blade from the interior of the turbine blade. This cooling air flows around the turbine blade and forms an insulating layer between the turbine blade hot process gas and the blade surface off.
  • the types of cooling described are suitably combined depending on the application in order to achieve the most effective blade cooling possible.
  • the blade is cast including a shroud, for example in the form of a shovel, and cooling channels. Additional coatings are applied by coating methods. In this case, in particular, the production of the cooling channels formed in known turbine blades by means of a casting process is very complicated and cost-intensive.
  • the invention has for its object to provide a turbine blade, with a very effective Konventionsksselung is possible, and also can be made easier and cheaper compared to known turbine blades.
  • a turbine blade having a support structure and a surrounding the support structure sheath, which is connected to the support structure by at least one spacer spaced to form between the support structure and the shroud a gap which can be traversed by a cooling medium.
  • the sheathing preferably in the form of a blade shroud, is used only to transmit the aerodynamic forces when the turbine blade flows around or flows into an underlying support structure via the spacer elements according to the invention.
  • the support structure essentially carries the sheath and also takes over the centrifugal force effect by rotation, provided that the turbine blade according to the invention is used as a moving blade.
  • the intermediate space forming through the spacing can be traversed with a cooling medium, preferably in the form of a gas or fluid, in order to achieve effective cooling of the jacket by convection cooling when using the turbine blade.
  • a cooling medium preferably in the form of a gas or fluid
  • the turbine blade according to the invention can be made simpler in comparison to known turbine blades, since no casting mold has to be provided that is correspondingly elaborately designed to form cooling channels. It is only necessary to create a connection between the support structure and the sheathing over the spacer elements according to the invention, in order to form a flow-through cooling channel in the form of the intermediate space according to the invention.
  • a turbine blade designed for convention cooling which, in addition to a simple production, has the advantage, in particular, of a significant improvement in heat removal and heat transfer to the cooling medium.
  • the at least one spacer element is designed in the form of a solder ball, which is connected by soldering, in particular soldering, with the support structure and the sheath.
  • soldering in particular soldering
  • the solder consists according to the invention of small solder balls that do not completely melt during the soldering process. These solder balls are often referred to in electrical engineering with the term "ball grid".
  • the solder balls form a large surface, so that heat can be transmitted directly to the cooling medium flowing through the intermediate space.
  • the turbine blade has a blade root, which is designed in such a way that the intermediate space can be flowed through by cooling medium, starting from the blade root.
  • a flow through the gap according to the invention can be provided.
  • the invention further relates to a method for producing a turbine blade according to the invention, which has a support structure and a casing surrounding the support structure, which is connected to the support structure at a distance, wherein the shell is soldered to the support structure at at least one point of the support structure to the shell spaced to connect to the support structure.
  • FIG. 1 3 shows a sectional view of a turbine blade 10 according to the present invention.
  • the turbine blade 10 includes a support structure 12, a shroud 14 sheath connected by solder balls 16 spaced apart from the support structure 12 to form a gap 18 in the form of a narrow gap defined by a Coolant is flowed through.
  • the vane shirt 14 serves to transmit the aerodynamic forces forming on the flow of the vane neck 14 to the carrier structure 12.
  • the connection via the solder balls 16, which are referred to in the jargon of electrical engineering as a "ball grid" is carried out by appropriate soldering at individual points of the support structure 12 and the blade 14, wherein the solder balls 16 do not completely melt during the soldering process.
  • the blade 14 When flowing through the gap 18 with a cooling medium, the blade 14 can be effectively convectively cooled by heat energy of the blade 14 is dissipated via the flowing cooling medium. Since heat transfer between the blade skirt 14 and the support structure 12 can only take place via the solder balls 16, the support structure 12 is only slightly heated by a heated blade skirt 14. Most of the heat energy of the blade 14 is dissipated via the cooling medium, wherein the solder balls 16 form a large surface, which transfers heat energy directly to the cooling medium.
  • FIG. 2 shows a shell of the turbine blade 10 in the form of a blade skirt 14 together with the connecting Lotkugeln 16.
  • the solder balls 16 are provided only at individual, spaced-apart locations in order to provide the most effective connection between the support structure 12 and the blade 14, and in conjunction with a streamlined as possible intermediate space 18th
  • FIG. 3 shows an enlarged sectional view of a connection between the blade 14 and the carrier structure 12 by solder balls 16, wherein the blade shirt 14 further has through holes 20 which serve to provide film cooling in addition to the convection cooling, such that cooling medium can flow outward through the through holes 20 ,

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07002215A 2007-02-01 2007-02-01 Turbinenschaufel Withdrawn EP1953342A1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP07002215A EP1953342A1 (de) 2007-02-01 2007-02-01 Turbinenschaufel
JP2009547622A JP4959811B2 (ja) 2007-02-01 2008-01-14 タービン翼
US12/525,156 US8267659B2 (en) 2007-02-01 2008-01-14 Turbine blade
PCT/EP2008/050325 WO2008092725A1 (de) 2007-02-01 2008-01-14 Turbinenschaufel
CN200880003931XA CN101600853B (zh) 2007-02-01 2008-01-14 涡轮叶片
RU2009132675/06A RU2430240C2 (ru) 2007-02-01 2008-01-14 Турбинная лопатка и способ ее изготовления
EP08701454A EP2126286A1 (de) 2007-02-01 2008-01-14 Turbinenschaufel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07002215A EP1953342A1 (de) 2007-02-01 2007-02-01 Turbinenschaufel

Publications (1)

Publication Number Publication Date
EP1953342A1 true EP1953342A1 (de) 2008-08-06

Family

ID=38193432

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07002215A Withdrawn EP1953342A1 (de) 2007-02-01 2007-02-01 Turbinenschaufel
EP08701454A Withdrawn EP2126286A1 (de) 2007-02-01 2008-01-14 Turbinenschaufel

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08701454A Withdrawn EP2126286A1 (de) 2007-02-01 2008-01-14 Turbinenschaufel

Country Status (6)

Country Link
US (1) US8267659B2 (enExample)
EP (2) EP1953342A1 (enExample)
JP (1) JP4959811B2 (enExample)
CN (1) CN101600853B (enExample)
RU (1) RU2430240C2 (enExample)
WO (1) WO2008092725A1 (enExample)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7871246B2 (en) * 2007-02-15 2011-01-18 Siemens Energy, Inc. Airfoil for a gas turbine
US8753083B2 (en) * 2011-01-14 2014-06-17 General Electric Company Curved cooling passages for a turbine component
US8875870B2 (en) 2011-03-31 2014-11-04 Benetech, Inc. Conveyor belt cleaner scraper blade and assembly
CN103061827B (zh) * 2013-01-06 2015-05-06 北京航空航天大学 一种混合型陶瓷基复合材料涡轮导向器叶片
EP3075531B1 (en) 2015-03-31 2024-03-20 Ansaldo Energia IP UK Limited Sandwich arrangement with ceramic panels and ceramic felts
EP3115199A1 (en) 2015-07-10 2017-01-11 General Electric Technology GmbH Manufacturing of single or multiple panels
CN105397223A (zh) * 2015-12-25 2016-03-16 中国航空工业集团公司沈阳发动机设计研究所 一种吸附式空心静子叶片的制造方法
US10436048B2 (en) * 2016-08-12 2019-10-08 General Electric Comapny Systems for removing heat from turbine components
US11333022B2 (en) * 2019-08-06 2022-05-17 General Electric Company Airfoil with thermally conductive pins
US11203947B2 (en) * 2020-05-08 2021-12-21 Raytheon Technologies Corporation Airfoil having internally cooled wall with liner and shell
CN112610285B (zh) * 2020-12-18 2021-09-14 武汉大学 一种仿金刚石晶胞拓扑的汽轮机空心静叶强化除湿结构及汽轮机除湿装置

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2642263A (en) * 1951-01-05 1953-06-16 Westinghouse Electric Corp Blade apparatus
US2906495A (en) * 1955-04-29 1959-09-29 Eugene F Schum Turbine blade with corrugated strut
US6238182B1 (en) * 1999-02-19 2001-05-29 Meyer Tool, Inc. Joint for a turbine component

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2801073A (en) 1952-06-30 1957-07-30 United Aircraft Corp Hollow sheet metal blade or vane construction
US3700348A (en) * 1968-08-13 1972-10-24 Gen Electric Turbomachinery blade structure
US3806276A (en) * 1972-08-30 1974-04-23 Gen Motors Corp Cooled turbine blade
JPS52139903A (en) * 1976-05-18 1977-11-22 Toyo Electric Mfg Co Ltd Commutator manufacturing method
JPS55109704A (en) * 1979-02-19 1980-08-23 Hitachi Ltd Gas-turbine blade capable of being cooled
US5328331A (en) * 1993-06-28 1994-07-12 General Electric Company Turbine airfoil with double shell outer wall
JP3110227B2 (ja) * 1993-11-22 2000-11-20 株式会社東芝 タービン冷却翼
DE19737845C2 (de) * 1997-08-29 1999-12-02 Siemens Ag Verfahren zum Herstellen einer Gasturbinenschaufel, sowie nach dem Verfahren hergestellte Gasturbinenschaufel
US6237344B1 (en) * 1998-07-20 2001-05-29 General Electric Company Dimpled impingement baffle
RU2154169C2 (ru) 1998-11-10 2000-08-10 Ао "К.Т.С." Перо оболочковой турбинной лопатки "флокс 2"
US6508000B2 (en) * 2001-02-08 2003-01-21 Siemens Westinghouse Power Corporation Transient liquid phase bonding repair for advanced turbine blades and vanes
EP1533481A3 (en) * 2003-11-19 2009-11-04 General Electric Company Hot gas path component with a meshed and dimpled cooling structure
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

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2642263A (en) * 1951-01-05 1953-06-16 Westinghouse Electric Corp Blade apparatus
US2906495A (en) * 1955-04-29 1959-09-29 Eugene F Schum Turbine blade with corrugated strut
US6238182B1 (en) * 1999-02-19 2001-05-29 Meyer Tool, Inc. Joint for a turbine component

Also Published As

Publication number Publication date
EP2126286A1 (de) 2009-12-02
JP4959811B2 (ja) 2012-06-27
US8267659B2 (en) 2012-09-18
JP2010518300A (ja) 2010-05-27
RU2009132675A (ru) 2011-03-10
CN101600853B (zh) 2013-09-11
US20090324421A1 (en) 2009-12-31
RU2430240C2 (ru) 2011-09-27
WO2008092725A1 (de) 2008-08-07
CN101600853A (zh) 2009-12-09

Similar Documents

Publication Publication Date Title
EP1953342A1 (de) Turbinenschaufel
EP2737178B1 (de) Verfahren zum herstellen, reparieren und/oder austauschen eines triebwerkgehäuses, sowie ein entsprechendes gehäuse
DE102007017973B4 (de) Dampfgekühlte Turbinenummantelung mit geschlossenem Kreislauf
DE4447507B4 (de) Ringförmige Dichtung
EP1105623B1 (de) Turbinengehäuse
EP1098725B1 (de) Verfahren und vorrichtung zur herstellung eines metallischen hohlkörpers
DE4441507C3 (de) Gekühlte Turbinenschaufel
DE3345263C2 (de) Gekühlte Turbinenschaufel
EP2511030B1 (de) Verfahren zum herstellen eines bauteils mit wenigstens einem in dem bauteil angeordneten bauelement, sowie ein bauteil mit wenigstens einem bauelement
DE102014111837A1 (de) Gasturbinenbauteile mit porösen Kühlungsmerkmalen
WO2008055737A1 (de) Turbinenschaufel
EP0995880A2 (de) Turbinenschaufel
EP1954922B1 (de) Dampfturbine mit lagerstreben
DE1938326C3 (de) Flammrohr für ein Gasturbinentriebwerk
EP3397859B1 (de) Windenergieanlage und kühlvorrichtung für eine windenergieanlage
EP2087207A1 (de) Turbinenschaufel
DE102017210237A1 (de) Schaltungsträger für eine elektronische Schaltung und Verfahren zu dessen Herstellung
EP2860852A1 (de) Einrichtung zum Ablenken von zumindest einem Teil eines axial in einem zwischen einem Rotor und einem Stator einer rotierenden elektrischen Maschine angeordneten Zwischenraum strömenden Kühlfluids
EP2372087A1 (de) Komponente mit einer einem Heissgas einer Gasturbine aussetzbaren Aussenwand und Verfahren zum Herstellen einer derartigen Komponente
DE102016119303A1 (de) System mit einem Träger und einer Elektronik und Verfahren zur Herstellung eines Trägers
EP0851095B1 (de) Innengekühlte Turbomaschinenschaufel
DE1895660U (de) Schutzkappe fuer elektrische bauelemente fuer fernmelde-, insbesondere fernsprechanlagen.
DE3032593A1 (de) Verfahren zum herstellen eines radialturbinenrades
DE102015215144A1 (de) Vorrichtung und Verfahren zum Beeinflussen der Temperaturen in Innenringsegmenten einer Gasturbine
EP2119878A1 (de) Dampfturbine mit geteiltem Innengehäuse

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

AKX Designation fees paid
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20090207

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566