EP1073827B1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP1073827B1
EP1073827B1 EP99937814A EP99937814A EP1073827B1 EP 1073827 B1 EP1073827 B1 EP 1073827B1 EP 99937814 A EP99937814 A EP 99937814A EP 99937814 A EP99937814 A EP 99937814A EP 1073827 B1 EP1073827 B1 EP 1073827B1
Authority
EP
European Patent Office
Prior art keywords
platform
hot gas
load
turbine
blading unit
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 - Lifetime
Application number
EP99937814A
Other languages
German (de)
English (en)
Other versions
EP1073827A1 (fr
Inventor
Peter Tiemann
Ariel Jacala
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 EP1073827A1 publication Critical patent/EP1073827A1/fr
Application granted granted Critical
Publication of EP1073827B1 publication Critical patent/EP1073827B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the invention relates to a cast turbine blade an airfoil and a platform area.
  • DE 26 28 807 A1 describes an impact cooling system for one Gas turbine blade.
  • the gas turbine blade is along directed a blade axis and points along the Bucket axis an airfoil and a platform area on.
  • In the platform area extends transversely to the blade axis a platform radially outward from the airfoil.
  • a such platform forms part of a flow channel for a working fluid that flows through a gas turbine into the the turbine blade is installed. Step on a gas turbine very high temperatures in this flow channel. Thereby becomes the surface of the platform exposed to the hot gas heavily thermally stressed.
  • To cool the platform is a perforated in front of the side of the platform facing away from the hot gas Wall element arranged. About the holes in the wall element cooling air enters and impinges on the hot gas Side of the platform. This will make it efficient Impact cooling reached.
  • GB-PS 1 289 435 relates to guide elements for gas flows, especially gas turbine blades. There is a on a casting Laminar guide element arranged that by perspiration cooling can be cooled. This setup is for cast turbine blades not applicable.
  • DE 26 43 049 A1 describes a cooling arrangement for cooling the platform of a turbine blade. Comparable to the arrangement in the above DE 26 28 807 A1 is before the side of the platform facing away from the hot gas side Plate with openings arranged through the cooling air against the Platform flows.
  • the object of the invention is to provide a thermally highly resilient, to specify cast turbine blade, at which only small thermal stresses occur in the platform area.
  • this object is achieved by a along Cast turbine blade directed towards a blade axis with one blade in succession along the blade axis and a platform area, the platform area a extending transversely to the blade axis to the Airfoil bordering hot gas platform and one of the hot gas platform opposite load platform, wherein the load platform is designed to absorb forces is caused by a working fluid flowing around the airfoil can be caused.
  • a turbine blade is placed over the platform area in the Turbine, in particular attached to the turbine housing.
  • the platform must absorb loads due to the airfoil attacking forces are caused.
  • Such powers are called by the pressure of the flowing through the turbine Working fluids, e.g. a hot gas or steam.
  • the inclusion of these loads requires that the platform has a minimum thickness to the forces without deformation to the To pass the turbine housing.
  • the Platform as stated above, from a hot gas flow channel.
  • the platform area is as a double platform made of two opposite one another Platforms trained. This ensures that the hot gas platform, which limits the flow channel and the exposed to hot gas that can be run.
  • the hot gas platform is in the essential for the limitation of the flow channel and thus responsible for channeling the hot gas.
  • the opposite one, unaffected by the hot gas Load platform takes over the through the on the airfoil attacking forces caused loads.
  • This separation of functions allows the hot gas platform to be so thin to ensure that the hot gas ducting is guaranteed, without having to intercept essential forces. Because of that won thin version of the hot gas platform results in particular the advantage of being in the hot gas platform form comparatively low thermal stresses.
  • the execution of the platform area is a double platform advantageous because at the transition points between the ribs and the platform can also handle high thermal stresses occur.
  • the hot gas platform is preferably substantially thinner than the load platform. Since the hot gas platform only one at most comparatively small part of the loads occurring it must be thinner than the load platform. The load platform catches the bulk of the occurring Forces.
  • the airfoil is part of a through the platform area extending profile
  • the hot gas platform and the load platform preferably each has an inner edge to which they are connected to the profile. Farther they each have an outer edge over which they join together are connected.
  • the hot gas platform is further preferred and the load platform only over their respective. inner edge and through their respective outer edge with each other connected. This results in a small connection area between the hot gas platform and the load platform. This small connection area and the connection over the respective outer edge result in a high mechanical stability of the double platform version only low thermal stresses. Thermal expansions are relative due to the small number of connection points freely possible.
  • Such guide elements can z. B. Be sheets that cover the space between the platforms divide like a chamber or z. B. also vertically between the Platform-facing channels.
  • a cooling medium especially cooling air, efficiently steered against the side of the hot gas platform facing away from the hot gas become. In particular, this can be an efficient Impact cooling are made possible.
  • the guide elements are preferably of a wall thickness trained, which is thin compared to the hot gas platform. Due to the thin design of the guide elements, none significant additional thermal stresses caused.
  • the load platform preferably has a plurality of the hot gas platform through holes.
  • a cooling medium especially cooling air from a compressor a gas turbine, through the load platform and flow against the hot gas platform, making it efficient cool.
  • the turbine blade is preferred as a gas turbine blade trained, especially for a stationary gas turbine.
  • Figure 1 shows a section of a along a blade axis 3 directed, cast gas turbine blade 1 with a profile 2.
  • the profile 2 partially forms an airfoil 5.
  • a platform area closes along the blade axis 3 7 on.
  • Profile 2 extends through the platform area 7 through.
  • the gas turbine blade 1 has inside the profile 2 along the blade axis 3 continuously extending cavity 8.
  • a stabilizing wall 6 extends along the blade axis 3 the cavity 8 of the turbine blade 1.
  • Transversely to the blade axis 3 connects to the airfoil 5 to the platform area 7 belonging hot gas platform 9.
  • the hot gas platform 9 opposite is a load platform 11.
  • the hot gas platform 9 has an inner edge 13, over which it with the Profile 2 is connected.
  • the platform area 7 is through Cast the entire gas turbine blade 1 in one piece with the Profile 2 connected.
  • the hot gas platform 9 continues to point an outer edge 15 which is approximately rectangular.
  • the Hot gas platform 9 is curved in the direction of the blade axis 9. This shape of the hot gas platform 9 results for a large number of similarly constructed turbine blades when installed in a turbine, it widens in the direction of flow Flow channel.
  • the load platform 11 has one inner edge 17, which is also limited by the profile 2 and at the same time the edge of an opening of itself is the turbine blade 1 extending cavity 8.
  • the Load platform 11 also has an approximately rectangular shape outer edge 19 and has approximately the same curvature on how the hot gas platform 9.
  • the hot gas platform 9 has a thickness D1 and the load platform a thickness D2.
  • This Thicknesses D1, D2 can optionally also be within the respective Platform vary, in which case with the thicknesses D1, D2 mean thicknesses are meant.
  • the load platform 11 and the hot gas platform 9 are above their respective inner ones Edge 13, 17 and the profile 2 connected to each other. Farther are the hot gas platform 9 and the load platform 11 through a connecting element 29 connected. This shows one in Area of the outer edges 15 and 19 arranged first part 29A on. Furthermore, it has an opposite, the first part 29A, also in the area of the outer edges 15, 19 lying second part 29B.
  • the connecting element 29 borders from the hot gas platform 9 two opposite one another Holding base 21 and 23 off. Likewise, from the load platform 11 delimited a holding base 25.
  • the holding base 25 opposite the load platform 11 still has a step-like Holding base 27 on.
  • the hot gas side 10 (see Figure 2) of the hot gas platform 9 through a flow path the gas turbine partially limited. A flowing through the gas turbine Hot working fluid flows around the airfoil 5. This results in high forces on the airfoil 5, which via the platform area 7 to the not shown Gas turbine casing can be transferred. The essential part this load is absorbed by the load platform 11. As a result, the hot gas platform 9 can be made thinner are called the load platform 13, i.e. the thickness D1 of the hot gas platform 9 is less than the thickness D2 of the load platform 11.
  • the hot gas side 10 opposite side 12 (see Figure 2) of the hot gas platform 9 can be cooled by a cooling air supply. Therefore is through holes 31 of the load platform 11 - it is only one through bore 31 shown by way of example - cooling air passed through the load platform 11. Guide elements 33 guide the cooling air thus passed on to the hot gas platform 9. This results in efficient prail cooling the hot gas platform 9.
  • FIG 2 shows a longitudinal section through the gas turbine blade 1 from Figure 1.
  • the cavity 8 is the Turbine blade 1 leading stiffening wall 6 visible.
  • the hot gas platform 9 and Load platform 11 are largely independent of each other.
  • the hot gas platform 9 takes over the sewerage of the hot working fluid and only needs one at most intercept small part of the forces caused by the working fluid be exerted on the airfoil 5. So that Hot gas platform 9 can be made thin. This gives the great advantage that only low thermal stresses in the Hot gas platform 9 occur.
  • the load platform 11 is thicker carried out since it absorbs most of the forces. she is but through the hot gas platform 9 before the hot working fluid protected, so that hardly any thermal in the load platform 11 Tensions occur.

Landscapes

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

Claims (9)

  1. Aube (1) de turbine coulée, dirigée le long d'un axe (3) d'aube et ayant, se succédant le long de l'axe (3) de l'aube, une lame (5) d'aube et une partie (7) de plate-forme qui comprend une plate-forme (9) pour du gaz chaud s'étendant transversalement à l'axe (3) de l'aube et voisine de la lame (5) de l'aube,
       caractérisée en ce que la partie (7) de plate-forme comprend une plate-forme (11) de charge opposée à la plate-forme (9) pour du gaz chaud, la plate-forme (11) de charge étant conçue pour absorber des forces qui peuvent être provoquées par un fluide de travail passant autour de la lame (5) de l'aube.
  2. Aube (1) de turbine suivant la revendication 1, caractérisée en ce que la plate-forme (9) pour du gaz chaud est plus mince que la plate-forme (11) de charge.
  3. Aube(1) de turbine suivant la revendication 1 ou 2, caractérisée en ce que la lame (5) de l'aube est un profilé (2) traversant la partie (7) de plate-forme, la plate-forme (9) pour le gaz chaud et la plate-forme (11) de charge ayant respectivement un bord (13, 17) intérieur par lequel elles sont assemblées au profilé (2).
  4. Aube (1) de turbine suivant la revendication 1, 2 ou 3, caractérisée en ce que la plate-forme (9) pour le gaz chaud et la plate-forme (11) de charge ont respectivement un bord (15, 19) extérieur sur lequel elles sont assemblées l'une à l'autre.
  5. Aube (1) de turbine suivant la revendication 3, caractérisée en ce que la plate-forme (9) pour du gaz chaud et la plate-forme (11) de charge ne sont assemblées l'une à l'autre que par leurs bord (13, 15) intérieurs respectifs, et par leurs bords (15, 19) extérieurs respectifs.
  6. Aube (1) de turbine suivant l'une des revendications précédentes, caractérisée en ce qu'entre la plate-forme (9) pour du gaz chaud et la plate-forme (11) de charge sont interposées des éléments (33) de conduite d'un fluide de refroidissement de la plate-forme (9) pour du gaz chaud.
  7. Aube (1) de turbine suivant la revendication 6, caractérisée en ce que les éléments (33) de conduite sont constitués sous la forme de paroi ayant une épaisseur (D3), épaisseur (D3) qui est petite par rapport à l'épaisseur (D1) de la plate-forme (9) pour du gaz chaud.
  8. Aube (1) de turbine suivant l'une des revendications précédentes, caractérisée en ce que la plate-forme (11) de charge comporte une pluralité de trous (31) traversants, dirigés sur la plate-forme (9) pour du gaz chaud.
  9. Aube (1) de turbine suivant l'une des revendications précédentes qui est constituée en aube (1) directrice, notamment pour une turbine à gaz fixe.
EP99937814A 1998-04-21 1999-04-14 Aube de turbine Expired - Lifetime EP1073827B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19817820 1998-04-21
DE19817820 1998-04-21
PCT/DE1999/001109 WO1999054597A1 (fr) 1998-04-21 1999-04-14 Pale de turbine

Publications (2)

Publication Number Publication Date
EP1073827A1 EP1073827A1 (fr) 2001-02-07
EP1073827B1 true EP1073827B1 (fr) 2003-10-08

Family

ID=7865335

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99937814A Expired - Lifetime EP1073827B1 (fr) 1998-04-21 1999-04-14 Aube de turbine

Country Status (5)

Country Link
US (1) US6533544B1 (fr)
EP (1) EP1073827B1 (fr)
JP (1) JP2002512334A (fr)
DE (1) DE59907300D1 (fr)
WO (1) WO1999054597A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7607889B2 (en) 2004-01-20 2009-10-27 Siemens Aktiengesellschaft Turbine blade and gas turbine equipped with a turbine blade
US8251665B2 (en) 2004-01-20 2012-08-28 Siemens Aktiengesellschaft Turbine blade and gas turbine equipped with a turbine blade

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1099825A1 (fr) * 1999-11-12 2001-05-16 Siemens Aktiengesellschaft Aube de turbine et sa méthode de production
US6375415B1 (en) * 2000-04-25 2002-04-23 General Electric Company Hook support for a closed circuit fluid cooled gas turbine nozzle stage segment
RU2272151C2 (ru) * 2000-12-28 2006-03-20 Альстом Текнолоджи Лтд Лопатка статора осевой турбины
EP1329593B1 (fr) * 2002-01-17 2005-03-23 Siemens Aktiengesellschaft Aube de turbine ayant une plateforme supportant les gaz chaux et une plateforme supportant les charges mécaniques
EP1331361B1 (fr) * 2002-01-17 2010-05-12 Siemens Aktiengesellschaft Aube statorique de turbine coulée ayant un crochet de fixation
US7255943B2 (en) * 2003-05-14 2007-08-14 Hoya Corporation Glass substrate for a magnetic disk, magnetic disk, and methods of producing the glass substrate and the magnetic disk
JP2005108578A (ja) * 2003-09-30 2005-04-21 Hitachi Ltd 質量分析装置
US7216694B2 (en) * 2004-01-23 2007-05-15 United Technologies Corporation Apparatus and method for reducing operating stress in a turbine blade and the like
US7604456B2 (en) * 2006-04-11 2009-10-20 Siemens Energy, Inc. Vane shroud through-flow platform cover
US8210819B2 (en) * 2008-02-22 2012-07-03 Siemens Energy, Inc. Airfoil structure shim
EP2282014A1 (fr) * 2009-06-23 2011-02-09 Siemens Aktiengesellschaft Section de canal d'écoulement annulaire pour une turbomachine
US9546557B2 (en) * 2012-06-29 2017-01-17 General Electric Company Nozzle, a nozzle hanger, and a ceramic to metal attachment system
WO2015023331A2 (fr) 2013-06-10 2015-02-19 United Technologies Corporation Aube de turbine à épaisseur de paroi non uniforme

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US2500745A (en) * 1944-09-21 1950-03-14 Gen Electric Bucket structure for high-temperature turbomachines
US3610769A (en) 1970-06-08 1971-10-05 Gen Motors Corp Porous facing attachment
BE794195A (fr) * 1972-01-18 1973-07-18 Bbc Sulzer Turbomaschinen Aube directrice refroidie pour des turbines a gaz
GB1605309A (en) * 1975-03-14 1989-02-01 Rolls Royce Stator blade for a gas turbine engine
IT1079131B (it) 1975-06-30 1985-05-08 Gen Electric Perfezionato raffreddamento applicabile particolarmente a elementi di turbomotori a gas
DE2643049A1 (de) 1975-10-14 1977-04-21 United Technologies Corp Schaufel mit gekuehlter plattform fuer eine stroemungsmaschine
US4283822A (en) * 1979-12-26 1981-08-18 General Electric Company Method of fabricating composite nozzles for water cooled gas turbines
US4987736A (en) * 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
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US5249418A (en) * 1991-09-16 1993-10-05 General Electric Company Gas turbine engine polygonal structural frame with axially curved panels
EP0550126A1 (fr) * 1992-01-02 1993-07-07 General Electric Company Bouclier thermique pour post-combusteur
FR2707698B1 (fr) * 1993-07-15 1995-08-25 Snecma Turbomachine munie d'un moyen de soufflage d'air sur un élément de rotor.
US5396763A (en) * 1994-04-25 1995-03-14 General Electric Company Cooled spraybar and flameholder assembly including a perforated hollow inner air baffle for impingement cooling an outer heat shield
JPH08135402A (ja) * 1994-11-11 1996-05-28 Mitsubishi Heavy Ind Ltd ガスタービン静翼構造

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7607889B2 (en) 2004-01-20 2009-10-27 Siemens Aktiengesellschaft Turbine blade and gas turbine equipped with a turbine blade
US7963746B2 (en) 2004-01-20 2011-06-21 Siemens Aktiengesellschaft Turbine blade and gas turbine equipped with a turbine blade
US8251665B2 (en) 2004-01-20 2012-08-28 Siemens Aktiengesellschaft Turbine blade and gas turbine equipped with a turbine blade

Also Published As

Publication number Publication date
EP1073827A1 (fr) 2001-02-07
DE59907300D1 (de) 2003-11-13
JP2002512334A (ja) 2002-04-23
US6533544B1 (en) 2003-03-18
WO1999054597A1 (fr) 1999-10-28

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