EP1541809B1 - Aube de guidage de turbine et procédé de formation correspondant - Google Patents

Aube de guidage de turbine et procédé de formation correspondant Download PDF

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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
German (de)
English (en)
Other versions
EP1541809A3 (fr
EP1541809A2 (fr
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/fr
Publication of EP1541809A3 publication Critical patent/EP1541809A3/fr
Application granted granted Critical
Publication of EP1541809B1 publication Critical patent/EP1541809B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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.

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

Claims (6)

  1. Aube de distributeur de turbine (10) pour moteur de turbine à gaz, l'aube de distributeur de turbine (10) comprenant :
    une paire de plateformes (12,14) avec un aubage (16) s'étendant entre elles,
    un noyau creux principal prévu dans chaque plateforme,
    des fentes de bandelettes de scellement (20) prévues à chaque extrémité de chaque plateforme (12,14),
    des faces de butée (18) prévues à chaque extrémité de chaque plateforme (12, 14),
    dans laquelle sont pratiqués des passages (28) s'étendant dans l'aube de distributeur de turbine (10) depuis les plateformes respectives (12,14) jusqu'aux fentes de bandelettes de scellement respectives (20) et,
    caractérisée en ce que les passages (28) s'étendent depuis le noyau creux principal (32) dans les plateformes respectives (12,14) jusque dans les bandelettes de scellement (20) pour délivrer de l'air de refroidissement aux faces de butée respectives (18) de l'aube de distributeur (10), les passages et fentes de bandelettes de scellement étant disposés de manière à ce que, à l'usage, de l'air de refroidissement passe à travers les passages dans les fentes de bandelettes de scellement et sous la bandelette de scellement avant de traverser la face de butée.
  2. Aube de distributeur de turbine selon la revendication 1, caractérisée en ce que les passages (28) sont inclinés par rapport au noyau creux principal (32).
  3. Aube de distributeur de turbine selon l'une quelconque des revendications précédentes, caractérisée en ce qu'une pluralité de passages (28) s'étendent vers chaque fente de bandelette de scellement (20).
  4. Turbine pour moteur de turbine à gaz, la turbine comprenant une pluralité d'aubes de distributeur de turbine (10) disposées en un ou plusieurs anneaux, caractérisée en ce les aubes de distributeur de turbine (10) se présentent selon l'une quelconque des revendications précédentes.
  5. Procédé de formage pluralité d'aubes de distributeur de turbine (10) selon la revendication 1 pour moteur de turbine à gaz, les aubes de distributeur de turbine comprenant une paire de plateformes (12, 14) avec un aubage s'étendant entre elles et des faces de butée prévues à chaque extrémité de chaque plateforme (12, 14), ce procédé incluant :
    le moulage à la cire perdue de métal autour d'un élément de noyau, l'élément noyau (22) définissant des ouvertures dans l'aube de distributeur (10) et l'élément noyau définissant un noyau creux principal dans chaque plateforme et des projections (26) sur l'élément noyau (22) définissant des passages (28),
    le retrait subséquent de l'élément noyau (22),
    la création de fentes de bandelettes de scellement à chaque extrémité de chaque plateforme, caractérisé en ce que les fentes sont conçues de manière à exposer les extrémités des passages (28) pour que les passages (28) s'étendent là où les bandelettes de scellement (20) sont prévues, de sorte que les passages résultants (28) s'étendent depuis un noyau creux principal (32) dans des plateformes respectives (12,14) jusqu'aux fentes de bandelettes de scellement (20), les passages et fentes de bandelettes de scellement étant conçus pour que, à l'usage, de l'air de refroidissement passe à travers les passages jusque dans les fentes de bandelettes de scellement et sous la bandelette de scellement avant de traverser la face de butée
  6. Procédé selon la revendication 5, caractérisé en ce que les fentes de bandelettes de scellement (20) sont usinées dans les aubes de distributeur de turbine (10) après le retrait de l'élément noyau de celles-ci (22) de manière à exposer les extrémités desdits passages (28) dans les fentes (20).
EP04257043.2A 2003-12-12 2004-11-12 Aube de guidage de turbine et procédé de formation correspondant Expired - Fee Related EP1541809B1 (fr)

Applications Claiming Priority (2)

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

Publications (3)

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

Family

ID=30130196

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04257043.2A Expired - Fee Related EP1541809B1 (fr) 2003-12-12 2004-11-12 Aube de guidage de turbine et procédé de formation correspondant

Country Status (3)

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

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
US8905708B2 (en) * 2012-01-10 2014-12-09 General Electric Company Turbine assembly and method for controlling a temperature of an assembly
US8845285B2 (en) * 2012-01-10 2014-09-30 General Electric Company Gas turbine stator assembly
EP2881544A1 (fr) * 2013-12-09 2015-06-10 Siemens Aktiengesellschaft Profilé d'aube de turbine à gaz et agencement associé
EP2907977A1 (fr) * 2014-02-14 2015-08-19 Siemens Aktiengesellschaft Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant
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
EP1260678B1 (fr) * 1997-09-15 2004-07-07 ALSTOM Technology Ltd Arrangement des segments pour plate-formes
EP1008723B1 (fr) * 1998-12-10 2004-02-18 ALSTOM (Switzerland) Ltd Refroidissement de plateformes de turbomachines
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
GB0328952D0 (en) 2004-01-14
EP1541809A3 (fr) 2012-10-17
US20050220619A1 (en) 2005-10-06
EP1541809A2 (fr) 2005-06-15

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