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EP2260181B1 - Aube fixe avec un élément de fixation en forme de crochet pour une turbine à gaz - Google Patents

Aube fixe avec un élément de fixation en forme de crochet pour une turbine à gaz Download PDF

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Publication number
EP2260181B1
EP2260181B1 EP09721575.0A EP09721575A EP2260181B1 EP 2260181 B1 EP2260181 B1 EP 2260181B1 EP 09721575 A EP09721575 A EP 09721575A EP 2260181 B1 EP2260181 B1 EP 2260181B1
Authority
EP
European Patent Office
Prior art keywords
cover plate
gas turbine
guide vane
rear edge
vane
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.)
Active
Application number
EP09721575.0A
Other languages
German (de)
English (en)
Other versions
EP2260181A1 (fr
Inventor
Igor Tsypkaykin
Beat Von Arx
Christoph Nagler
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
General Electric Technology GmbH
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 General Electric Technology GmbH filed Critical General Electric Technology GmbH
Publication of EP2260181A1 publication Critical patent/EP2260181A1/fr
Application granted granted Critical
Publication of EP2260181B1 publication Critical patent/EP2260181B1/fr
Active 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present invention relates to the field of gas turbines. It relates to a guide vane for a gas turbine according to the preamble of claim 1.
  • Gas turbines with sequential combustion are known and have proven themselves in industrial use.
  • Such a gas turbine which has become known in the art as GT24 / 26, for example, from an article of Joos, F. et al., "Field Experience of the Sequential Combustion System for the ABB GT24 / GT26 Gas Turbine Family", IGTI / ASME 98-GT-220, 1998 Sweden ,
  • the local Fig. 1 shows the basic structure of such a gas turbine, where the local Fig. 1 in the present application as Fig. 1 is reproduced. Furthermore, such a gas turbine goes out EP-B1-0 620 362 out.
  • the vanes 10 of Fig. 1 have a longitudinally extending airfoil 11, which in the flow direction of the hot gas (parallel arrows in Fig. 1 ) is bounded by a leading edge 14 and a trailing edge 15.
  • the blade 11 is bounded by a blade head 13 and an outer cover plate 12 (sometimes also referred to as shroud, this element being referred to below as the cover plate only).
  • the blade head 13 defines the annular hot gas channel of the turbine on the inside and usually abuts on the rotor shaft of the turbine via a seal segment not shown in detail.
  • the cover plate 12 defines with its inner side 19 the hot gas channel to the outside.
  • a front and rear hook-shaped fastening element 16 and 17 are formed, which serve on the one hand for fastening the guide vane 10 on the inner housing of the turbine and on the other hand to Absorption and fixation of heat shields adjacent to each other in the flow direction ("heat shields" Fig. 2 , Pos. 24) are available.
  • a receiving groove 18 is provided on the rear fastening element 17, in which a heat recovery segment can be inserted.
  • the receiving groove 18 is limited to the cover plate 12 through a horizontal base surface 18 ', which together with the oblique inner side 19 of this cover plate 12 in the region of the trailing edge 15 forms a wedge-shaped portion 19', which is characterized by a large volume of material.
  • the transition 21 between the trailing edge 15 of the vane 10 and the cover plate 12 is a critical range for the life of the vane 10, since it sets a high thermal load resulting from a thermal-mechanical mismatch between the cover plate 12 and the blade 11 This results in a peak being superimposed on the stress resulting from the load of the airfoil 11 loaded by the hot gas flow.
  • the above-mentioned large volume of material in the wedge-shaped portion 19 'above the trailing edge 15 now leads to a significant increase in the thermal stresses in this important for the life of the vane 10 area and thus to a reduction in the life itself, bearing in mind the fact that modern gas turbines high Require temperatures related to the working fluids, which are in many cases beyond the permissible material temperature economically useful materials.
  • the invention aims to remedy this situation. It is therefore an object of the invention to provide a guide vane for gas turbines, which avoids the disadvantages of the previous vanes with extremely small and targeted changes in the design and is characterized by a significantly improved life.
  • the object is solved by the entirety of the features of claim 1.
  • Essential to the invention is that means are provided on the cover plate of the guide vane between the receiving groove and the trailing edge, which ensure a reduction of the thermal and mechanical stresses in the region of the transition between the trailing edge and cover plate. As a result of this engagement directly on the cover plate in the region of the trailing edge, the thermal and mechanical loads with regard to the service life of the blade can be sustainably improved there in a very simple and efficient manner.
  • the cover plate has a reduced material thickness in the region between the trailing edge and the receiving groove. This material reduction effectively minimizes the stresses caused by thermal and mechanical stresses in this area.
  • the means for reducing the thermal and mechanical stresses preferably comprise a groove formed between receiving groove and trailing edge in the cover plate, which groove is arranged substantially parallel to the inside of the cover plate and directed counter to the flow direction.
  • the trailing edge of the blade is formed opposite to the fastening element in the flow direction set back by a distance.
  • the vane of the invention can be used to advantage in a gas turbine.
  • FIGS. 2 and 3 is in one too Fig. 1 comparable representation of a guide vane according to an embodiment of the invention.
  • the guide vane 20 in turn comprises an airfoil 11 with leading edge 14 and trailing edge 15 which is delimited in the longitudinal direction by a vane head 13 and a cover plate 12.
  • the cover plate 12 also here has an obliquely outwardly inclined inside in the flow direction 19.
  • hook-shaped fasteners 16 and 17 are formed, wherein the Rear fastening element 17 is formed on the rear side of a receiving groove 22 for an adjacent heat spreader 24.

Landscapes

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

Claims (3)

  1. Aube fixe (20) pour une turbine à gaz, laquelle aube fixe (20) comprend une pale (11), qui s'étend dans la direction longitudinale de l'aube et qui est limitée par une arête antérieure (14) et une arête postérieure (15), ainsi qu'une plaque de couverture (12) dont le côté intérieur (19) est exposé au gaz chaud traversant la turbine à gaz, et sur laquelle, en saillie vers l'extérieur dans la zone de l'arête postérieure (15), il est prévu au moins un élément de fixation (17) en forme de crochet pour la fixation de l'aube fixe (20) sur un carter ou sur des éléments de la turbine à gaz, l'élément de fixation en forme de crochet présentant au-dessus de l'arête postérieure (15) au moins une rainure de réception (22) pour la fixation d'un segment d'accumulation de chaleur (24) se raccordant à la plaque de couverture (12) extérieure de l'aube fixe (20) dans la direction d'écoulement du gaz chaud, caractérisée en ce que, sur la plaque de couverture (12) de l'aube fixe (20), entre la rainure de réception (22) et l'arête postérieure (15) de la pale (11), il est mis en place une gorge creuse (23) en sens contraire de la direction d'écoulement pour la réduction des contraintes thermiques et mécaniques dans la zone de la transition (21) entre l'arête postérieure (15) et la plaque de couverture (12), en ce que la plaque de couverture (12) présente une épaisseur réduite dans la zone entre l'arête postérieure (15) et la rainure de réception (22), en ce que le tracé de la gorge creuse (23) est constitué de façon essentiellement parallèle au côté intérieur (19) de la plaque de couverture (12) et en ce que l'arête postérieure (15) est décalée vers l'arrière selon une distance (a) par rapport à l'élément de fixation (17) dans la direction d'écoulement.
  2. Utilisation de l'aube fixe (20) selon la revendication 1 pour une turbine à gaz.
  3. Utilisation de l'aube fixe (20) selon la revendication 2 pour une turbine à gaz à combustion séquentielle.
EP09721575.0A 2008-03-19 2009-02-18 Aube fixe avec un élément de fixation en forme de crochet pour une turbine à gaz Active EP2260181B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH4162008 2008-03-19
PCT/EP2009/051883 WO2009115384A1 (fr) 2008-03-19 2009-02-18 Aube fixe avec un élément de fixation en forme de crochet pour une turbine à gaz

Publications (2)

Publication Number Publication Date
EP2260181A1 EP2260181A1 (fr) 2010-12-15
EP2260181B1 true EP2260181B1 (fr) 2016-08-17

Family

ID=39689493

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09721575.0A Active EP2260181B1 (fr) 2008-03-19 2009-02-18 Aube fixe avec un élément de fixation en forme de crochet pour une turbine à gaz

Country Status (3)

Country Link
US (1) US8147190B2 (fr)
EP (1) EP2260181B1 (fr)
WO (1) WO2009115384A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3128059B1 (fr) 2011-09-30 2021-02-24 Owens Corning Intellectual Capital, LLC Procédé de formation d'une bande à partir de matériaux fibreux
US9371555B2 (en) 2012-06-01 2016-06-21 Concordia Laboratories Inc. Lighting systems and methods of using lighting systems for in vitro potency assay for photofrin
ES2695723T3 (es) 2013-06-14 2019-01-10 United Technologies Corp Alabe de turbina con radio interior variable de borde posterior
US11111801B2 (en) * 2013-06-17 2021-09-07 Raytheon Technologies Corporation Turbine vane with platform pad
FR3048015B1 (fr) 2016-02-19 2020-03-06 Safran Aircraft Engines Aube de turbomachine, comprenant un pied aux concentrations de contrainte reduites
US20180340438A1 (en) * 2017-05-01 2018-11-29 General Electric Company Turbine Nozzle-To-Shroud Interface

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE755567A (fr) 1969-12-01 1971-02-15 Gen Electric Structure d'aube fixe, pour moteur a turbines a gaz et arrangement de reglage de temperature associe
US4573865A (en) 1981-08-31 1986-03-04 General Electric Company Multiple-impingement cooled structure
US4687413A (en) * 1985-07-31 1987-08-18 United Technologies Corporation Gas turbine engine assembly
US4820116A (en) 1987-09-18 1989-04-11 United Technologies Corporation Turbine cooling for gas turbine engine
US5201846A (en) 1991-11-29 1993-04-13 General Electric Company Low-pressure turbine heat shield
CH687269A5 (de) 1993-04-08 1996-10-31 Abb Management Ag Gasturbogruppe.
EP0844369B1 (fr) 1996-11-23 2002-01-30 ROLLS-ROYCE plc Assemblage d'un rotor à aubes et de son carter
JPH1150806A (ja) * 1997-08-04 1999-02-23 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンのノズル部材
US6761529B2 (en) 2002-07-25 2004-07-13 Mitshubishi Heavy Industries, Ltd. Cooling structure of stationary blade, and gas turbine
US7094029B2 (en) * 2003-05-06 2006-08-22 General Electric Company Methods and apparatus for controlling gas turbine engine rotor tip clearances
US6951447B2 (en) * 2003-12-17 2005-10-04 United Technologies Corporation Turbine blade with trailing edge platform undercut
DE102004004014A1 (de) * 2004-01-27 2005-08-18 Mtu Aero Engines Gmbh Leitschaufel für eine Turbomaschine
FR2896548B1 (fr) * 2006-01-24 2011-05-27 Snecma Ensemble de redresseurs fixes sectorise pour un compresseur de turbomachine
US7862300B2 (en) * 2006-05-18 2011-01-04 Wood Group Heavy Industrial Turbines Ag Turbomachinery blade having a platform relief hole

Also Published As

Publication number Publication date
US8147190B2 (en) 2012-04-03
WO2009115384A1 (fr) 2009-09-24
US20110016875A1 (en) 2011-01-27
EP2260181A1 (fr) 2010-12-15

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