EP1541809B1 - Gasturbinenleitschaufel und entsprechendes Bildungsverfahren - Google Patents

Gasturbinenleitschaufel und entsprechendes Bildungsverfahren Download PDF

Info

Publication number
EP1541809B1
EP1541809B1 EP04257043.2A EP04257043A EP1541809B1 EP 1541809 B1 EP1541809 B1 EP 1541809B1 EP 04257043 A EP04257043 A EP 04257043A EP 1541809 B1 EP1541809 B1 EP 1541809B1
Authority
EP
European Patent Office
Prior art keywords
passages
seal strip
nozzle guide
guide vane
slots
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.)
Expired - Fee Related
Application number
EP04257043.2A
Other languages
English (en)
French (fr)
Other versions
EP1541809A2 (de
EP1541809A3 (de
Inventor
Kevin Paul Self
Mark John Simms
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP1541809A2 publication Critical patent/EP1541809A2/de
Publication of EP1541809A3 publication Critical patent/EP1541809A3/de
Application granted granted Critical
Publication of EP1541809B1 publication Critical patent/EP1541809B1/de
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • This invention concerns turbine nozzle guide vanes for gas turbine engines, and a method of forming such nozzle guide vanes.
  • Turbine nozzle guide vanes for gas turbine engines generally comprise inner and outer platforms with an aerofoil extending therebetween.
  • Such guide vanes are formed as a plurality of segments arranged in one or more rings around an engine. It is necessary for a gap to be left between adjacent guide vanes to allow for manufacturing tolerances and thermal expansion during use. These gaps are conventionally sealed by providing cooperating slots in each guide vane, with a metal seal strip extending in the slots and between the segments.
  • Nozzle guide vanes are generally air cooled, and passages can be provided in the platforms and aerofoil. It is generally difficult however to cool the abutment faces between adjacent vanes, and particularly due to the provision of the seal strips extending therebetween. Higher engine gas temperatures are generally now being used which make cooling of the nozzle guide vanes increasingly important.
  • EP1074696 discloses a stator vane having a coolable platform
  • EP1162346 discloses a cooling arrangement of a turbine shroud segment.
  • the invention yet further provides a method of forming turbine nozzle guide vanes for a gas turbine engine according to claim 5.
  • Fig. 1 shows a turbine nozzle guide vane 10.
  • the vane 10 has an outer platform 12 and an inner platform 14.
  • An aerofoil 16 extends between the platforms 12, 14.
  • Abutment faces 18 are provided on the ends of each of the platforms 12, 14, and seal strip slots 20 are provided in the abutment faces 18.
  • Figs. 2 and 3 show a ceramic core member 22 usable in investment casting of the guide vane 10.
  • the core member 22 has a body 24 to define a main hollow core in the guide vane 10, and four inclined projections 26 extending from the body 24 to define passages 28 extending into the seal strip slots 20.
  • Figs. 4 and 5 diagrammatically show the nozzle guide vane 10 in use.
  • Fig. 4 there is shown part of a seal strip 30 locating in the seal strip slot 20.
  • Fig. 4 shows part of an outer platform 12, and above the guide vane 10 as shown in the drawing would be the coolant side at high pressure. Cooling air would be supplied through the main hollow core 32 formed in the body 24 and would then pass through the passages 28 into the seal strip slot 20. The cooling air would generally pass under the seal strip 20 as shown by the arrow, and pass across the abutment face 18 which would face a similar nozzle guide vane 10, to beneath the guide vane 10 as shown, which would be the hot gas side at a lower pressure than the cooling air within the guide vane 10.
  • the nozzle guide vane 10 In use, the nozzle guide vane 10 would be formed by casting an appropriate metal around the core member 22 in an appropriate shape mould. Following casting the core member 22 would be destroyed, for instance by leaching. The seal strip slots 20 would then be formed by machining until the slot 20 exposes ends of the passages 28. By inclining the projections 26 and hence passages 28, it means that this machining operation will not affect the main hollow core 32 of the guide vane 10.
  • nozzle guide vane which provides for cooling of the abutment edge and is thus suitable for use at high gas temperatures. No additional manufacturing processes or steps are required in forming such a nozzle guide vane, and therefore such guide vanes can readily be manufactured.

Landscapes

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

Claims (6)

  1. Turbinendüsenleitschaufel (10) für ein Gasturbinentriebwerk, wobei die Düsenleitschaufel (10) Folgendes einschließt:
    ein Paar Plattformen (12, 14) mit einer Tragfläche (16), die sich dazwischen erstreckt,
    einen in jeder Plattform vorgesehenen hohlen Hauptkern,
    an jedem Ende von jeder Plattform (12, 14) vorgesehene Dichtungsstreifenschlitze (20),
    an jedem Ende von jeder Plattform (12, 14) vorgesehene Stirnflächen (18),
    wobei Durchgänge (28) vorgesehen sind, die sich innerhalb der Düsenleitschaufel (10) von den jeweiligen Plattformen (12,14) zu den jeweiligen Dichtungsstreifenschlitzen (20) erstrecken, und
    gekennzeichnet dadurch, dass sich die Durchgänge (28) vom hohlen Hauptkern (32) in den jeweiligen Plattformen (12,14) zu den Dichtungsstreifenschlitzen (20) erstrecken, zum Liefern von Kühlluft zu den jeweiligen Stirnflächen (18) der Leitschaufel (10), wobei die Durchgänge und Dichtungsstreifenschlitze so angeordnet sind, dass bei Verwendung Kühlluft durch die Durchgänge in die Dichtungsstreifenschlitze und unter den Dichtungsstreifen geht, bevor sie über die Stirnfläche geht.
  2. Turbinendüsenleitschaufel 1, gekennzeichnet dadurch, dass die Durchgänge (28) relativ zum hohlen Hauptkern (32) geneigt sind.
  3. Turbinendüsenleitschaufel gemäß einem der vorhergehenden Ansprüche, gekennzeichnet dadurch, dass sich eine Vielzahl von Durchgängen (28) zu jeden Dichtungsstreifenschlitz (20) erstrecken.
  4. Turbinendüsenleitschaufel (10) für ein Gasturbinentriebwerk, wobei die Turbine eine Vielzahl von Düsenleitschaufeln (10) einschließt, die in einem oder mehreren Ringen angeordnet sind, gekennzeichnet dadurch, dass die Düsenleitschaufeln (10) gemäß einem der vorhergehenden Ansprüche sind.
  5. Verfahren zum Ausbilden von Turbinendüsenleitschaufeln (10) gemäß Anspruch 1, für ein Gasturbinentriebwerk, wobei die Düsenleitschaufeln ein Paar Plattformen (12, 14) mit einer Tragfläche, die sich dazwischen erstreckt, und an jedem Ende von jeder Plattform (12, 14) vorgesehene Stirnflächen beinhalten, wobei das Verfahren Folgendes einschließt:
    Präzisionsgießen von Metall um ein Kernglied, wobei das Kernglied (22) Öffnungen in der Leitschaufel (10) definiert und wobei das Kernglied einen hohlen Hauptkern in jeder Plattform definiert und Vorsprünge (26) auf dem Kernglied (22) Durchgänge (28) definieren,
    anschließend Entfernen des Kernglieds (22),
    Vorsehen von Dichtungsstreifenschlitzen an jedem Ende von jeder Plattform, gekennzeichnet dadurch, dass die Schlitze so angeordnet sind, dass Enden der Durchgänge (28) exponiert sind, so dass sich die Durchgänge (28) da hinein erstrecken, wo die Dichtungsstreifenschlitze (20) vorgesehen sind, so dass sich die resultierenden Durchgänge (28) von einem hohlen Hauptkern (32) in den jeweiligen Plattformen (12,14) zu den Dichtungsstreifenschlitzen (20) erstrecken, wobei die Durchgänge und Dichtungsstreifenschlitze so angeordnet sind, dass bei Verwendung Kühlluft durch die Durchgänge in die Dichtungsstreifenschlitze und unter den Dichtungsstreifen geht, bevor sie über die Stirnfläche geht.
  6. Verfahren gemäß Anspruch 5, gekennzeichnet dadurch, dass die Dichtungsstreifenschlitze (20) in die Düsenleitschaufeln (10) nach Entfernen des Kernglieds (22) davon gefräst werden, um so Enden der Durchgänge (28) in den Schlitzen (20) zu exponieren.
EP04257043.2A 2003-12-12 2004-11-12 Gasturbinenleitschaufel und entsprechendes Bildungsverfahren Expired - Fee Related EP1541809B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0328952 2003-12-12
GBGB0328952.7A GB0328952D0 (en) 2003-12-12 2003-12-12 Nozzle guide vanes

Publications (3)

Publication Number Publication Date
EP1541809A2 EP1541809A2 (de) 2005-06-15
EP1541809A3 EP1541809A3 (de) 2012-10-17
EP1541809B1 true EP1541809B1 (de) 2015-03-04

Family

ID=30130196

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04257043.2A Expired - Fee Related EP1541809B1 (de) 2003-12-12 2004-11-12 Gasturbinenleitschaufel und entsprechendes Bildungsverfahren

Country Status (3)

Country Link
US (1) US20050220619A1 (de)
EP (1) EP1541809B1 (de)
GB (1) GB0328952D0 (de)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7597542B2 (en) * 2005-08-30 2009-10-06 General Electric Company Methods and apparatus for controlling contact within stator assemblies
GB2430170B (en) * 2005-09-15 2008-05-07 Rolls Royce Plc Method of forming a cast component
US9133855B2 (en) * 2010-11-15 2015-09-15 Mtu Aero Engines Gmbh Rotor for a turbo machine
US8845285B2 (en) * 2012-01-10 2014-09-30 General Electric Company Gas turbine stator assembly
US8905708B2 (en) * 2012-01-10 2014-12-09 General Electric Company Turbine assembly and method for controlling a temperature of an assembly
EP2881544A1 (de) * 2013-12-09 2015-06-10 Siemens Aktiengesellschaft Schaufelprofil für eine Gasturbine und zugehörige Anordnung
EP2907977A1 (de) * 2014-02-14 2015-08-19 Siemens Aktiengesellschaft Heißgasbeaufschlagbares Bauteil für eine Gasturbine sowie Dichtungsanordnung mit einem derartigen Bauteil
US10329934B2 (en) * 2014-12-15 2019-06-25 United Technologies Corporation Reversible flow blade outer air seal
US10648354B2 (en) 2016-12-02 2020-05-12 Honeywell International Inc. Turbine wheels, turbine engines including the same, and methods of forming turbine wheels with improved seal plate sealing

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4902198A (en) * 1988-08-31 1990-02-20 Westinghouse Electric Corp. Apparatus for film cooling of turbine van shrouds
JPH03213602A (ja) * 1990-01-08 1991-09-19 General Electric Co <Ge> ガスタービンエンジンの当接セグメントを連結する自己冷却式ジョイント連結構造
US5088888A (en) * 1990-12-03 1992-02-18 General Electric Company Shroud seal
US5531457A (en) * 1994-12-07 1996-07-02 Pratt & Whitney Canada, Inc. Gas turbine engine feather seal arrangement
DE59710924D1 (de) * 1997-09-15 2003-12-04 Alstom Switzerland Ltd Kühlvorrichtung für Gasturbinenkomponenten
DE59810806D1 (de) * 1998-12-10 2004-03-25 Alstom Switzerland Ltd Plattformkühlung in Turbomaschinen
US6254333B1 (en) * 1999-08-02 2001-07-03 United Technologies Corporation Method for forming a cooling passage and for cooling a turbine section of a rotary machine
US6241467B1 (en) * 1999-08-02 2001-06-05 United Technologies Corporation Stator vane for a rotary machine
US6340285B1 (en) * 2000-06-08 2002-01-22 General Electric Company End rail cooling for combined high and low pressure turbine shroud

Also Published As

Publication number Publication date
EP1541809A2 (de) 2005-06-15
US20050220619A1 (en) 2005-10-06
GB0328952D0 (en) 2004-01-14
EP1541809A3 (de) 2012-10-17

Similar Documents

Publication Publication Date Title
US7524163B2 (en) Nozzle guide vanes
EP1055800B1 (de) Turbinenschaufel mit interner Kühlung
KR100573658B1 (ko) 터빈 요소
US9581028B1 (en) Small turbine stator vane with impingement cooling insert
EP2071126B1 (de) Turbinenschaufeln und Verfahren zur Herstellung von Turbinenschaufeln
EP1043479B1 (de) Turbinenwand mit Rillen an der Innenseite
EP3068975B1 (de) Bauteil eines gasturbinentriebwerks und zugehörige herstellungsverfahren
JP4731238B2 (ja) ガスタービンエンジンロータブレードを冷却するための装置
EP3034808B1 (de) Gusskern für eine schaufelaussendichtung, schaufelaussendichtung und entsprechendes fertigungsverfahren
US8506256B1 (en) Thin walled turbine blade and process for making the blade
EP2213838B1 (de) Gussverfahren einer turbinenschaufel
EP1593812B1 (de) Gekühlte Turbinenschaufel
EP1921272B1 (de) Luftgekühlte Schaufel für eine Gasturbine
EP2340902B1 (de) Guss von internen Funktionen in einem Produkt
US10415403B2 (en) Cooled blisk for gas turbine engine
EP2565383B1 (de) Schaufelprofil mit Kühlkanälen
US10364683B2 (en) Gas turbine engine component cooling passage turbulator
JP2003106104A (ja) 選択された段差付きタービンノズル
EP1541809B1 (de) Gasturbinenleitschaufel und entsprechendes Bildungsverfahren
US20140064983A1 (en) Airfoil and method for manufacturing an airfoil
US7137783B2 (en) Cooled gas turbine blades
EP0694677B1 (de) Schaufelspitzendichtungsring für eine Gasturbine
EP2492446B1 (de) Turbinendeckbandring und verfahren zur herstellung desselben
EP3065896B1 (de) Feingussverfahren für ein schaufelsegment eines gasturbinenmotors
EP4028643B1 (de) Turbinenschaufel, verfahren zur herstellung einer turbinenschaufel und verfahren zur überholung einer turbinenschaufel

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 IS IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK YU

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 IS IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK YU

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/18 20060101ALI20120910BHEP

Ipc: F01D 25/12 20060101AFI20120910BHEP

Ipc: F01D 11/00 20060101ALI20120910BHEP

Ipc: F01D 9/04 20060101ALI20120910BHEP

17P Request for examination filed

Effective date: 20130410

AKX Designation fees paid

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 20130702

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20141204

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602004046724

Country of ref document: DE

Effective date: 20150409

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: ROLLS-ROYCE PLC

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602004046724

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20151207

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602004046724

Country of ref document: DE

Representative=s name: HERNANDEZ, YORCK, DIPL.-ING., DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20191127

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20191125

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20191127

Year of fee payment: 16

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602004046724

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20201112

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210601

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201112