EP1355042A2 - Aube de turbine - Google Patents

Aube de turbine Download PDF

Info

Publication number
EP1355042A2
EP1355042A2 EP03006498A EP03006498A EP1355042A2 EP 1355042 A2 EP1355042 A2 EP 1355042A2 EP 03006498 A EP03006498 A EP 03006498A EP 03006498 A EP03006498 A EP 03006498A EP 1355042 A2 EP1355042 A2 EP 1355042A2
Authority
EP
European Patent Office
Prior art keywords
turbine blade
channel
insert
partition
channels
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Withdrawn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
EP03006498A
Other languages
German (de)
English (en)
Other versions
EP1355042A3 (fr
Inventor
Peter Tiemann
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
Publication of EP1355042A2 publication Critical patent/EP1355042A2/fr
Publication of EP1355042A3 publication Critical patent/EP1355042A3/fr
Withdrawn legal-status Critical Current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
    • 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
    • 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

Definitions

  • the invention relates to a turbine blade according to the generic term of claim 1.
  • Turbine blades are often made by a casting process, where it makes sense inside the turbine blade insert more channels than necessary for cooling are.
  • the Rule plates that have rectangular edges on the Welded ends of the inner partitions that form the cooling channels. At these right-angled edges, however, this must be done Flow cooling medium past, which among other things leads to pressure loss leads.
  • FIG. 1 shows a turbine blade 1 with an airfoil area 4, a base 7, by means of which they e.g. in a disk (not shown in detail) a rotor Turbine (not shown) is attached, as well as a Platform 10 and which has a radial axis 2.
  • FIG. 2 shows a top view of a section along line BB of FIG. 1.
  • a first channel 13, a second channel 16 and a third channel 19 run in the interior of the turbine blade 1 in the area of the airfoil area 4, which, for example, form cooling channels.
  • Other channels are conceivable. From a structural point of view, such channels 13, 16, 19 make sense because the material saved reduces the weight and the mechanical loads on the turbine blade. A core that is cast around during casting can be easily removed if the channels 13, 16, 19 extend along the radial axis 2.
  • FIG. 3 shows a section along the line II-II of FIG. 2 parallel to the radial axis 2.
  • the second channel 16 is delimited on two sides, inter alia, by a first partition 31 and a second partition 34.
  • the third channel 19 is delimited laterally, inter alia, by the second partition 34 and a base wall 22 of the base 7.
  • the cooling medium which flows from the disk of the turbine rotor into the base 7, should not, as shown by the arrows 37, flow through the second channel and the third channel 16, 19, but through at least one other channel 13, into the interior of the Flow turbine blade 1 in the blade area 4.
  • the first partition 31 has at its one axial end 49 a first shoulder 25 directed into the second channel 16, ie on its inner surface 52.
  • the base wall 22 has a second shoulder 28 in the interior of the channel 19 at the same radial height as the first shoulder 25. If there is a corresponding insert 40 on the heels 25 and 28, the second channel 16 and the third channel 19 are completely closed off from the outside.
  • a transition 43 which runs from the insert 40 via the first partition 31 into the axially adjacent first channel 13, is rounded and therefore optimized in terms of flow technology, so that there is no turbulence, pressure loss or turbulence as would be caused by a sharp edge ,
  • the thickness of the insert 40 corresponds to the depth of the shoulder 25, 28 in the radial direction (FIG. 4).
  • Paragraphs 25, 28 are circumferential and together connected, i.e. an opening 46 of the channels 16, 19 in their cross section is enlarged in the area of the opening (Fig. 2) and forms a recess 55.
  • the second partition 34 borders with its radial end 49 For example, directly on the insert 40, so that this on the Insert 40 rests.
  • a radial end 49 of further partitions 58 is rounded or fluidically optimized.
  • the insert 40 is welded to the partitions 31, 34 or 22, soldered, glued or otherwise attached.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03006498A 2002-04-18 2003-03-21 Aube de turbine Withdrawn EP1355042A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10217389A DE10217389A1 (de) 2002-04-18 2002-04-18 Turbinenschaufel
DE10217389 2002-04-18

Publications (2)

Publication Number Publication Date
EP1355042A2 true EP1355042A2 (fr) 2003-10-22
EP1355042A3 EP1355042A3 (fr) 2005-03-30

Family

ID=28458917

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03006498A Withdrawn EP1355042A3 (fr) 2002-04-18 2003-03-21 Aube de turbine

Country Status (5)

Country Link
US (1) US20040022629A1 (fr)
EP (1) EP1355042A3 (fr)
JP (1) JP2003314202A (fr)
CN (1) CN1451849A (fr)
DE (1) DE10217389A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1832712A1 (fr) * 2006-03-08 2007-09-12 Snecma Aube mobile de turbomachine à cavité commune d'alimentation en air de refroidissement
EP2990597A1 (fr) * 2014-08-28 2016-03-02 Siemens Aktiengesellschaft Procédé de fabrication d'un ensemble turbine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004037444A1 (de) * 2004-03-30 2005-10-20 Alstom Technology Ltd Baden Vorrichtung zur Kühlluftbeaufschlagung einer rotierenden Komponente, insbesondere für eine Laufschaufel in einer Rotationsmaschine
DE102011121634B4 (de) * 2010-12-27 2019-08-14 Ansaldo Energia Ip Uk Limited Turbinenschaufel

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3369792A (en) * 1966-04-07 1968-02-20 Gen Electric Airfoil vane
US4236870A (en) * 1977-12-27 1980-12-02 United Technologies Corporation Turbine blade
US5624231A (en) * 1993-12-28 1997-04-29 Kabushiki Kaisha Toshiba Cooled turbine blade for a gas turbine
EP1094199A1 (fr) * 1999-10-18 2001-04-25 ABB (Schweiz) AG Rotor pour une turbine à gaz

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL88170C (fr) * 1952-10-31 1900-01-01
US4224011A (en) * 1977-10-08 1980-09-23 Rolls-Royce Limited Cooled rotor blade for a gas turbine engine
DE3606597C1 (de) * 1986-02-28 1987-02-19 Mtu Muenchen Gmbh Schaufel- und Dichtspaltoptimierungseinrichtung fuer Verdichter von Gasturbinentriebwerken
US5669759A (en) * 1995-02-03 1997-09-23 United Technologies Corporation Turbine airfoil with enhanced cooling

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3369792A (en) * 1966-04-07 1968-02-20 Gen Electric Airfoil vane
US4236870A (en) * 1977-12-27 1980-12-02 United Technologies Corporation Turbine blade
US5624231A (en) * 1993-12-28 1997-04-29 Kabushiki Kaisha Toshiba Cooled turbine blade for a gas turbine
EP1094199A1 (fr) * 1999-10-18 2001-04-25 ABB (Schweiz) AG Rotor pour une turbine à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1832712A1 (fr) * 2006-03-08 2007-09-12 Snecma Aube mobile de turbomachine à cavité commune d'alimentation en air de refroidissement
FR2898384A1 (fr) * 2006-03-08 2007-09-14 Snecma Sa Aube mobile de turbomachine a cavite commune d'alimentation en air de refroidissement
EP2990597A1 (fr) * 2014-08-28 2016-03-02 Siemens Aktiengesellschaft Procédé de fabrication d'un ensemble turbine
WO2016030231A1 (fr) * 2014-08-28 2016-03-03 Siemens Aktiengesellschaft Procédé pour fabriquer un ensemble de turbine
RU2688124C2 (ru) * 2014-08-28 2019-05-17 Сименс Акциенгезелльшафт Способ для изготовления узла турбины

Also Published As

Publication number Publication date
CN1451849A (zh) 2003-10-29
EP1355042A3 (fr) 2005-03-30
JP2003314202A (ja) 2003-11-06
US20040022629A1 (en) 2004-02-05
DE10217389A1 (de) 2003-10-30

Similar Documents

Publication Publication Date Title
EP1595058B1 (fr) Systeme de joint notamment destine a des segments d'ailettes de turbines a gaz
DE102005026553B3 (de) Schwenkmotor mit verringerter Leckage
EP3025077B2 (fr) Membrane et procédé de fabrication de ladite membrane
DE102009003327B4 (de) Turbinenlaufschaufel-Spitzendeckband
DE102008055590B4 (de) Turbinenschaufel-Deckband
DE2144595A1 (de) Gekühlte Turbinenschaufel
DE102007002326A1 (de) Turbinenschaufel- und Leitkranzkonstruktion
EP3176384B1 (fr) Virole interne, secteur de virole interne, aubage statorique et turbomachine
EP3219917B1 (fr) Agencement d'aubes de turbomachine, turbomachine et procédé de fabrication associés
DE602005000739T2 (de) Laufschaufel eines Verdichters oder einer Gasturbine
WO2017060086A1 (fr) Procédé permettant de pratiquer une marque d'équilibrage dans la roue de compresseur d'un turbocompresseur à gaz d'échappement et turbocompresseur à gaz d'échappement comportant une roue de compresseur munie d'une marque d'équilibrage
DE102014000183A1 (de) Verfahren zur Bildung eines Impellers mit einer durch eine Vielzahl an Linien und einen solchen Impeller definierten Form
EP1995413B1 (fr) Joint d'étanchéité pour le jeu d'aubes d'une turbomachine
WO2004103634A2 (fr) Procede de production d'un piston monobloc pour un moteur a combustion
EP3401504B1 (fr) Grille d'aube
EP1676980A1 (fr) Turbocompresseur à géométrie variable et procédé de fabrication
DE10012381A1 (de) Schaufelschloss und Verfahren zur Herstellung eines Schaufelschlosses
EP3428402B1 (fr) Segment d'aube directrice à joint de décharge courbé
DE102008060705A1 (de) Horizontal geteiltes Strömungsmaschinengehäuse
EP1355042A2 (fr) Aube de turbine
DE102012107135A1 (de) Turbinenschaufel mit sich axial erstreckender Nut
EP2860352A1 (fr) Rotor, procédé de manufacture et aube associés
EP3404211A1 (fr) Segment de grille d'aubes d'une turbine avec paroi de plateforme contourée, grille d'aubes, canal d'aube, plateforme, turbine et moteur d'aéronef associés
EP2907977A1 (fr) Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant
CH272378A (de) Beschaufelung an Rotoren von axial durchströmten, verwundene Schaufeln aufweisenden Kreiselmaschinen, insbesondere von Dampf-, Gasturbinen und Verdichtern.

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: A2

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

AX Request for extension of the european patent

Extension state: AL LT LV MK

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

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

AX Request for extension of the european patent

Extension state: AL LT LV MK

AKX Designation fees paid
REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566

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: 20051001