EP2158381B1 - Aube directrice pour turbine à gaz - Google Patents

Aube directrice pour turbine à gaz Download PDF

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Publication number
EP2158381B1
EP2158381B1 EP08761302A EP08761302A EP2158381B1 EP 2158381 B1 EP2158381 B1 EP 2158381B1 EP 08761302 A EP08761302 A EP 08761302A EP 08761302 A EP08761302 A EP 08761302A EP 2158381 B1 EP2158381 B1 EP 2158381B1
Authority
EP
European Patent Office
Prior art keywords
groove
recess
components
surface roughness
process according
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.)
Not-in-force
Application number
EP08761302A
Other languages
German (de)
English (en)
Other versions
EP2158381A2 (fr
Inventor
Alexander Khanin
Igor Kurganov
Sergey Vorontsov
Victor Odinokov
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to SI200830147T priority Critical patent/SI2158381T1/sl
Publication of EP2158381A2 publication Critical patent/EP2158381A2/fr
Application granted granted Critical
Publication of EP2158381B1 publication Critical patent/EP2158381B1/fr
Not-in-force 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
    • 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
    • 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
    • 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
    • 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
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals
    • 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
    • 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

Definitions

  • the invention relates to a guide blade for a gas turbine, in particular a guide blade with a cover plate, according to the preamble of claim 1.
  • a plurality of stationary vanes are used, which are arranged in a turbine part along the circumference in rows. Since such guide vanes are exposed to the action of the hot gas flowing out of the combustion part and high pressure, high voltages can be generated in the guide vanes and in the cover plates during operation.
  • the cover plate is located between a hot gas flow and a space filled with cooling air. In order to seal this space from the hot gas stream, usually the cover plate has side walls which are each provided with a groove extending in the longitudinal direction of the cover plate. The grooves of two circumferentially adjacent cover plates receive a sealing plate extending between the cover plates. Such an arrangement is in the EP 0 147 354 A described.
  • the present invention has for its object to provide a guide vane for a gas turbine with a cover plate with an improved construction, which avoids the problems mentioned, that is, a construction that the stress concentrations in the trailing edge of the guide vane and in the cover plate in the region of the trailing edge of the Guide vane reduced.
  • a vane has a leading edge and a trailing edge and a cover plate extending at least between the leading edge and the trailing edge.
  • the cover plate has extending in the longitudinal direction of the gas turbine and extending substantially radially first and second side walls.
  • the first side wall is provided, at least in the region of the rear edge, with a groove extending in the longitudinal direction of the cover plate for receiving a sealing plate, the first side wall of the cover plate having a recess extending from the groove in the region of the rear edge.
  • the recess in the cover plate in the region of the trailing edge of the vane reduces the stress concentrations in the trailing edge of the vane and in the cover plate in the region of the trailing edge of the vane. This reduces the fatigue of the material at low load cycles and the creep speed in these areas.
  • the depth of the recess in the circumferential direction of the gas turbine is substantially equal to the depth of the groove.
  • a vane 1 is shown with a cover plate 2 according to the prior art.
  • a plurality of such stationary vanes 1 are used, which are arranged in a turbine part along the circumference in rows.
  • the vane 1 has a front edge 12 and a rear edge 8, wherein the cover plate 2 extends at least between the front edge 12 and the rear edge 8.
  • cover plate 2 extends in the longitudinal direction of the gas turbine and extending substantially radially extending first and second side walls 5, 6.
  • the cover plate 2 is located in the radial direction between a hot gas stream 3 and a space filled with cooling air 4.
  • the side walls 5, 6 are each provided with a groove 7 extending in the longitudinal direction of the cover plate 2.
  • the grooves 7 of two circumferentially adjacent cover plates 2 receive a sealing plate extending between the cover plates 2.
  • a groove 7 extends in the longitudinal direction of the gas turbine at least in the region of a trailing edge 8 of the guide vane 1 and the distance in the circumferential direction of the gas turbine between the trailing edge 8 of the guide vane 1 and the groove 7 can be very small, which from the FIG. 6 which shows a section through a radially outer region of the blade section and a partial view in the region of the groove 7 at the same time.
  • a vane 1 is provided with a radially outer cover plate 2.
  • the guide vane 1 can also have a radially inner cover plate, which is provided in a similar manner with a groove provided in the longitudinal direction of the cover plate, wherein in operation stress concentrations in the trailing edge region of the guide vane 1 and in the radially inner cover plate in the region of the trailing edge 8 of the guide vane 1 may also arise.
  • a vane 1 is shown with a cover plate 2 according to a preferred embodiment of the invention. Identical components are provided with the same reference numerals.
  • a first side wall 5 of the cover plate 2 in the region of a trailing edge 8 has a recess 10 extending from a groove 7.
  • the recess 10 is located in the longitudinal direction of the cover plate 2 substantially opposite to the trailing edge 8.
  • the recess 10 extends substantially at right angles to the groove 7 radially outwardly. In particular, therefore, only the first side wall 5 has such a recess 10.
  • the recess 10 in the radial direction opposite side of the cover plate 2 may be provided with an elevation 11, wherein the recess 10 is provided in the longitudinal direction of the cover plate 2 in the region of the elevation 11.
  • the recess 10 may be in the longitudinal direction of the cover plate 2 in the region of the downstream end of the elevation 11.
  • the distance between the trailing edge 8 and the recess 10 in the circumferential direction of the gas turbine may be less than the depth of the groove 7 or the depth the groove 7 same.
  • the recess 10 but the stress concentrations are reduced in this area and reduces the fatigue of the material at low load cycles and creeping speed.
  • the depth of the recess 10 in the circumferential direction of the gas turbine is substantially equal to the depth of the groove 7, as shown in FIG. 3 apparent is.
  • the width of the recess 10 in the longitudinal direction of the cover plate 2 is advantageously between once to three times their depth and the profile of the recess is preferably formed substantially rectangular.
  • the profile can take a different shape, for example, with side walls which extend obliquely to the longitudinal direction of the cover plate 2.
  • the vane is provided with a radially outer cover plate 2.
  • the vane can also have a radially inner cover plate (not shown) similarly provided with a groove 7 provided in the longitudinal direction of the cover plate, with stress concentrations in the trailing edge region of the vane and in the radially inner cover plate in the region of the trailing edge of the vane in operation Guide vane can also arise.
  • a first side wall of the radially inner cover plate in the region of the trailing edge 8 may have a recess extending radially inward from the groove 7.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Valve-Gear Or Valve Arrangements (AREA)
  • Control Of Turbines (AREA)

Claims (18)

  1. Procédé de fabrication d'un évidement (4) en forme de rainure, qui fait partie d'un ruban d'étanchéité entre deux composants (1, 2) renfermant un interstice (3), avec une technique de procédé par enlèvement de matière, pour produire l'évidement (4) en forme de rainure dans les deux composants (1, 2), de telle sorte que les évidements (4) en forme de rainure de chacun des deux composants (1, 2) soient sensiblement en regard après orientation mutuelle dans une position finale renfermant entre eux l'interstice (3), et de telle sorte qu'un élément en ruban (5) puisse être introduit dans les évidements (4) en forme de rainure de telle sorte que l'élément en ruban (5) pénètre au moins en partie dans les deux évidements (4) en forme de rainure et que dans le cas d'une application de force, produise avec les évidements (4) en forme de rainure des deux composants (1, 2) un assemblage essentiellement étanche aux gaz,
    caractérisé en ce que la technique de procédé par enlèvement de matière est mise en oeuvre dans au moins deux étapes successives, dans lesquelles, dans une première étape, de la matière est enlevée avec une première vitesse d'enlèvement de matière, et dans une deuxième étape suivante, de la matière est enlevée avec une deuxième vitesse d'enlèvement de matière,
    en ce que la première vitesse d'enlèvement de matière est supérieure à la deuxième vitesse d'enlèvement de matière,
    en ce que la technique de procédé par enlèvement de matière, conformément à la première étape, produit une région de surface de matière usinée (41) avec une première rugosité de surface,
    en ce que la technique de procédé par enlèvement de matière, conformément à la première étape, produit une région de surface de matière usinée (43) avec une deuxième rugosité de surface, et en ce que la deuxième rugosité de surface est inférieure à la première.
  2. Procédé selon la revendication 1,
    caractérisé en ce que la technique de procédé par enlèvement de matière selon la deuxième étape est utilisée au moins pour produire des régions de surface de matière (43) à l'intérieur de l'évidement (4) en forme de rainure, au niveau desquelles l'élément en ruban (5) produit avec les composants respectifs (1, 2), un assemblage étanche aux gaz.
  3. Procédé selon la revendication 1 ou 2,
    caractérisé en ce que l'évidement (4) en forme de rainure présente une profondeur de rainure le long de laquelle l'évidement (4) en forme de rainure présente une section transversale variable.
  4. Procédé selon la revendication 3,
    caractérisé en ce que la section transversale de l'évidement (4) en forme de rainure devient, continuellement ou par échelons, de plus en plus petite au fur et à mesure de l'augmentation de la profondeur de rainure.
  5. Procédé selon l'une quelconque des revendications 1 à 3,
    caractérisé en ce que l'on utilise comme technique de procédé par enlèvement de matière le meulage, le fraisage, l'érosion, le découpage au laser ou au jet d'eau.
  6. Procédé selon l'une quelconque des revendications 1 à 5,
    caractérisé en ce que l'on utilise comme technique de procédé par enlèvement de matière selon la première étape un procédé de dégrossissage par érosion et dans la deuxième étape un procédé de finition par érosion.
  7. Procédé selon l'une quelconque des revendications 1 à 6,
    caractérisé en ce que l'on utilise comme technique de procédé par enlèvement de matière selon la première étape un procédé d'érosion et dans la deuxième étape un procédé de meulage.
  8. Procédé selon la revendication 7,
    caractérisé en ce que le procédé d'érosion repose sur un procédé d'électroérosion.
  9. Procédé selon l'une quelconque des revendications 1 à 8,
    caractérisé en ce que l'évidement (4) en forme de rainure présente une largeur de rainure minimale, qui est supérieure à l'épaisseur (s) de l'élément en ruban (5).
  10. Procédé selon l'une quelconque des revendications 1 à 9,
    caractérisé en ce que l'on utilise comme élément en ruban (5) un ruban métallique déformable élastiquement.
  11. Procédé selon l'une quelconque des revendications 1 à 10,
    caractérisé en ce que la région de surface de matière (41) ayant la première rugosité de surface est adjacente, par une région de transition (45), à la région de surface de matière (43) ayant la deuxième rugosité de surface, et en ce que la région de transition (45) est arrondie au moyen d'un procédé d'usinage de surface de matière.
  12. Procédé selon la revendication 11,
    caractérisé en ce que l'on utilise comme procédé d'usinage de surface de matière un sablage, un grenaillage, un usinage par jets d'eau haute pression, ou un façonnage au moyen d'un poinçon.
  13. Evidement en forme de rainure, qui fait partie d'un ruban d'étanchéité entre deux composants (1, 2) renfermant un interstice (3), dans lesquels l'évidement (4) en forme de rainure est incorporé de telle sorte que les évidements (4) en forme de rainure de chacun des deux composants (1, 2) soient sensiblement en regard après orientation mutuelle dans une position finale renfermant entre eux l'interstice (3), et dans lesquels un élément en ruban (5) peut être introduit de telle sorte que l'élément en ruban (5) pénètre au moins en partie dans les deux évidements (4) en forme de rainure et dans le cas d'une application de force, produise avec les évidements (4) en forme de rainure des deux composants (1, 2) un assemblage essentiellement étanche aux gaz,
    caractérisé en ce que l'évidement (4) en forme de rainure présente au moins une première région de surface de matière (41) avec une première rugosité de surface ainsi qu'au moins une deuxième région de surface de matière (43) avec une deuxième rugosité de surface, et
    en ce que la première rugosité de surface est inférieure à la deuxième rugosité de surface.
  14. Evidement en forme de rainure selon la revendication 13,
    caractérisé en ce que la région de surface de matière (43) avec la deuxième rugosité de surface est disposée à l'intérieur de l'évidement (4) en forme de rainure de telle sorte que l'élément en ruban (5) produise avec cette région de surface de matière un assemblage étanche aux gaz.
  15. Utilisation de l'évidement (4) en forme de rainure selon l'une quelconque des revendications 13 ou 14 entre deux composants disposés à l'intérieur d'une turbomachine.
  16. Utilisation selon la revendication 15,
    caractérisée en ce que la turbomachine est une installation de turbine à gaz.
  17. Utilisation selon la revendication 16,
    caractérisée en ce que les composants (1, 2) sont des aubes de turbine à gaz et le ruban d'étanchéité sert à étancher le conduit chaud à l'intérieur d'une turbine à gaz vis-à-vis d'un volume d'air de refroidissement.
  18. Utilisation selon la revendication 17,
    caractérisée en ce que l'élément en ruban (5) est pressé de manière étanche aux gaz contre le composant respectif (1, 2) par une surpression régnant à l'intérieur du volume de refroidissement par rapport aux conditions de pression régnant dans le conduit chaud, à l'intérieur de l'évidement (4) en forme de rainure.
EP08761302A 2007-06-28 2008-06-23 Aube directrice pour turbine à gaz Not-in-force EP2158381B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SI200830147T SI2158381T1 (sl) 2007-06-28 2008-06-23 Vodilna lopatica za plinsko turbino

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH10442007 2007-06-28
PCT/EP2008/057947 WO2009000802A2 (fr) 2007-06-28 2008-06-23 Aube directrice pour turbine à gaz

Publications (2)

Publication Number Publication Date
EP2158381A2 EP2158381A2 (fr) 2010-03-03
EP2158381B1 true EP2158381B1 (fr) 2010-11-03

Family

ID=38566219

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08761302A Not-in-force EP2158381B1 (fr) 2007-06-28 2008-06-23 Aube directrice pour turbine à gaz

Country Status (8)

Country Link
US (1) US8152454B2 (fr)
EP (1) EP2158381B1 (fr)
AT (1) ATE487025T1 (fr)
CA (1) CA2691186C (fr)
DE (1) DE502008001731D1 (fr)
SI (1) SI2158381T1 (fr)
TW (1) TWI440768B (fr)
WO (1) WO2009000802A2 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8376705B1 (en) 2011-09-09 2013-02-19 Siemens Energy, Inc. Turbine endwall with grooved recess cavity
US9840917B2 (en) * 2011-12-13 2017-12-12 United Technologies Corporation Stator vane shroud having an offset
US9683446B2 (en) * 2013-03-07 2017-06-20 Rolls-Royce Energy Systems, Inc. Gas turbine engine shrouded blade
WO2014138320A1 (fr) * 2013-03-08 2014-09-12 United Technologies Corporation Composant de moteur à turbine à gaz ayant une fente de joint à couvre-joint à largeur variable
ES2664322T3 (es) * 2013-06-06 2018-04-19 MTU Aero Engines AG Segmento de álabes directores de una turbomáquina y una turbina
US10352180B2 (en) 2013-10-23 2019-07-16 General Electric Company Gas turbine nozzle trailing edge fillet
EP2985419B1 (fr) * 2014-08-13 2020-01-08 United Technologies Corporation Ensemble de pales de turbomachines avec étanchéités de pied d'aube
US10329931B2 (en) * 2014-10-01 2019-06-25 United Technologies Corporation Stator assembly for a gas turbine engine
US10876417B2 (en) 2017-08-17 2020-12-29 Raytheon Technologies Corporation Tuned airfoil assembly
US11506129B2 (en) 2020-04-24 2022-11-22 Raytheon Technologies Corporation Feather seal mateface cooling pockets

Family Cites Families (7)

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Publication number Priority date Publication date Assignee Title
US3542483A (en) * 1968-07-17 1970-11-24 Westinghouse Electric Corp Turbine stator structure
US3938906A (en) * 1974-10-07 1976-02-17 Westinghouse Electric Corporation Slidable stator seal
US4524980A (en) * 1983-12-05 1985-06-25 United Technologies Corporation Intersecting feather seals for interlocking gas turbine vanes
GB2195403A (en) * 1986-09-17 1988-04-07 Rolls Royce Plc Improvements in or relating to sealing and cooling means
JP2001152804A (ja) * 1999-11-19 2001-06-05 Mitsubishi Heavy Ind Ltd ガスタービン設備及びタービン翼
US7625174B2 (en) * 2005-12-16 2009-12-01 General Electric Company Methods and apparatus for assembling gas turbine engine stator assemblies
US7922444B2 (en) * 2007-01-19 2011-04-12 United Technologies Corporation Chamfer rail pockets for turbine vane shrouds

Also Published As

Publication number Publication date
ATE487025T1 (de) 2010-11-15
TWI440768B (zh) 2014-06-11
CA2691186A1 (fr) 2008-12-31
US8152454B2 (en) 2012-04-10
WO2009000802A3 (fr) 2009-03-19
DE502008001731D1 (de) 2010-12-16
US20100150710A1 (en) 2010-06-17
EP2158381A2 (fr) 2010-03-03
TW200925390A (en) 2009-06-16
WO2009000802A2 (fr) 2008-12-31
CA2691186C (fr) 2015-08-04
SI2158381T1 (sl) 2011-03-31

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