EP1257732A1 - Aube de turbine - Google Patents

Aube de turbine

Info

Publication number
EP1257732A1
EP1257732A1 EP01913779A EP01913779A EP1257732A1 EP 1257732 A1 EP1257732 A1 EP 1257732A1 EP 01913779 A EP01913779 A EP 01913779A EP 01913779 A EP01913779 A EP 01913779A EP 1257732 A1 EP1257732 A1 EP 1257732A1
Authority
EP
European Patent Office
Prior art keywords
blade
platform
cavity
turbine
walls
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.)
Granted
Application number
EP01913779A
Other languages
German (de)
English (en)
Other versions
EP1257732B1 (fr
Inventor
Peter Tiemann
Michael STRA BERGER
Dirk Anding
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
Priority to EP01913779A priority Critical patent/EP1257732B1/fr
Publication of EP1257732A1 publication Critical patent/EP1257732A1/fr
Application granted granted Critical
Publication of EP1257732B1 publication Critical patent/EP1257732B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the 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
    • 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
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the invention relates to a turbine blade with a non-cooled blade profile which extends from a blade platform to which a blade root engaging a turbine disc is connected, the radial cross section of which to the blade platform has a region of increasing width.
  • the blade profiles of the tower blades are extended as much as possible in order to achieve better utilization of the hot gas flowing past. This extension of the blade profile is limited by several parameters.
  • the object of the present invention is therefore to create a turbine rotor blade which enables an extension of the rotor blade profiles, without or with only a slight increase in local loads on the rotor disk or on the rotor blade feet.
  • the blade root has an open recess facing away from the platform, which ends blindly on the platform side and has a cross-sectional configuration in the area of the increasing width of the blade blade.
  • the blade root is usually to secure the Stao ⁇ l ⁇ - did solid formed un ⁇ , in comparison to the other dimensions ZJ ⁇ er Turbmenscnaufel a large Quersc h Nitt on.
  • its mass is still and it has a large proportion of the centrifugal force load of the turbine sleeve and the holding devices for the blade, which occurs when the turbine disk rotates.
  • the hollowing out of the foot reduces the mass of the foot and therefore the load on the radial force.
  • the fact that the cavity ends blindly on the platform side also meets the stability requirements, which are very high, particularly in the area between the platform and the blade profile, due to a wide range of strong forces and temperature attack.
  • the invention thus also makes it possible to keep the mass of the blade low and to maintain or even improve its stability.
  • the average tension level in the foot area is reduced and tension peaks on holding teeth of the foot and the adjacent turbine disk are alleviated, which leads to an extension of the service life of the turbine blade and in particular to an improvement in the durability of the foot. It is therefore without endangering the stability of the turbine blade and while maintaining the shape of the foot possible to extend the blade profile to the outside and thus increase the efficiency of the turbine.
  • the weight reduction is improved and an abrupt change in the curvature, which leads to local stress maxima leads, avoiding a rounded end area at the transition m.
  • the hot working gases particularly stress that edge area of the blade that is the first to be blown against.
  • the higher strength requirements of the hot gas flow side are taken into account by the fact that the wall thickness is greater near a hot gas flow side than on the hot gas flow side.
  • a material and mass-saving increase in the strength of the foot is given by the fact that the blade root is reinforced by cross struts formed between its longitudinal walls.
  • the forces acting on one longitudinal wall of the cavity are passed on through the transverse struts to the other longitudinal wall and through both walls into the turbine disk, without endangering the stability of the cavity, so that the mass is further reduced further relief of the foot due to the reduced centrifugal load.
  • cross struts on the platform side are at a distance from the walls or cavity and / or from the end of the blade root facing away from the platform, there is an additional saving in weight while maintaining stability.
  • the forces are optimally transmitted so that the positions and shapes of the cross struts are adapted to a line of force that arises from centrifugal forces acting on the blade profile.
  • an adapted number and shape of the cross struts it is thus possible, on the one hand, to greatly reduce the mass of the blade root by making the walls of the cavity thinner due to the supportive effect of the cross struts, and at the same time a more homogeneous stress curve along the longitudinal sides of the cavity due to To receive support from the cross struts.
  • the particularly high attacking forces in the central area are absorbed by the fact that the transverse struts of the hollow have the greatest height in the central area and are adapted to a decreasing course of the hollowing out of the honing.
  • FIG. 2 shows a longitudinal section through a foot region of a turbine blade according to FIG. 1 along the section line Z I - Z I
  • FIG. 3 shows a cross section through a foot region of a turbine blade according to FIG. 1 along the section line III-III
  • FIG. 4 shows a cross section through a foot region of a turbine blade according to FIG. 1 along the section line iv-iv and
  • FIG. 5 shows a cross section through a foot region of a turbine blade according to FIG. 1 along the section line V-V.
  • Fig.l shows a radial cross section through a foot 4 and a platform 2 and part of a blade profile 1 of a turbine blade.
  • the foot 4 is pushed into a right-hand opening 30 of a turbine disk 3 and held in a form-fitting manner by means of teeth 35 of the foot 4 and corresponding teeth 36 of the holding recess 30, as shown in FIG. Foot 4, platform 2 and profile 1 are in one piece, coherently shaped, preferably cast.
  • Adjacent blade profiles 1 offer passing heating gas a resistance and change its speed in the direction, whereby the turbine disc 3 is excited to rotate at a high speed around a disc axis.
  • Large parts of the turbine blades are generally The blade is solidly constructed and therefore has a high weight, which places a heavy load on the foot areas.
  • the foot 4 has a cavity 7 according to the invention, which is reduced in weight. This is shaped like a dome and ends blindly at the platform-side end 19 of the turbine blade underneath the upper side 21 of the platform 2.
  • the cavity 7 is open at an end 31 of the foot 4 facing the platform.
  • the foot 4 has an essentially constant length 32 in the region of the end 31 facing away from the platform. The length 32 initially increases somewhat when the platform 2 is approached because of a formation 37 in the transition area 38, in order to decrease continuously until the platform 2.
  • the cavity 7 has lengths 13 of longitudinal walls 12 and depths 33.
  • the lengths 13 increase starting from the platform-facing end 31 after a certain distance to the platform-side end 19 of the foot 4, in the transition area 38 of an arch-like shape become shorter to the highest point with the height 16 of the cavity 7, where the cavity 7 is blind ends.
  • the blade profile is solid in the platform area and may have a weight-saving blade profile hollow in the upper area of the blade profile, not shown, at a distance from the platform. This avoids endangering the strength of the blade in the platform area.
  • the cavity 7 has no connection to the blade profile cavity, since it is an uncooled turbine blade and therefore no coolant transport through the foot is necessary.
  • the depth 33 increases, as shown in FIG. 2, from an area 5 from the platform-distorted end 31 of the foot 4 to the platform-side end 19.
  • the cavity 7 then follows a turn of the turbine blade in the transition area 38.
  • the depth 33 initially increases somewhat in the transition area 38 in order to ⁇ then gradually decrease from approximately the middle of the transition region 38 to the platform 2.
  • the largest possible area within the foot 4 or the transition area 38 is hollowed out by e ne maximum to achieve reduction. It is particularly taken into account that the walls 8, 12 have sufficient wall thicknesses 1-. to ensure the stability of the foot 4 even with strong "attacking centrifugal forces. Due to the curved design of the cavity 7, stress peaks are avoided, which lead to a reduction in strength.
  • the preparation of the Ausnohlung 7 can durcn a G ⁇ e err done with lost mold, which is used in the root region ⁇ er SCNA "fel before ⁇ em molding un ⁇ protrudes of the foot 4 through the rigaoge..an ⁇ te end 31, a platform facing away from open cavity wo ⁇ urch formed.
  • the casting core is formed as an en ⁇ en ⁇ er flower core. After the casting, the core is destroyed and removed from the cavity 7, since it cannot be removed as a whole due to the width which becomes smaller as a result of the opening.
  • Cross struts 28 are attached within the cavity 7, and extend between the longitudinal walls 12.
  • the cross struts 28 support the cavity 7 against attacking forces which act on the walls 8, 12.
  • the cross struts 28 are rounded in order to avoid voltage peaks. They are arranged essentially parallel to one another at a distance of 34 m from a longitudinal axis 39 of the turbine blade. They then enter the entire area between the two opposite longitudinal walls 12.
  • cross-strut-free areas Only at the end of the cavity 7 on the platform side and facing away from the platform there are rounded, cross-strut-free areas with a distance ⁇ o to the upper limit of the cavity 7 and a distance 41 to the lower end 31 in the platform-facing end.
  • the cross-strut-free areas are essentially production-related, since fingers of a cast core, by means of which the material-free areas between the cross struts 28 are produced, are connected to one another at the ends, to be able to maintain correct dimensions. In addition, they also contribute to further weight savings.
  • FIG. 2 shows a radial cross section at an almost right angle to the first longitudinal section of FIG. 1 along the section line II-II.
  • the foot 4 has toothed teeth 35, which engage the correspondingly shaped tooth 36 ⁇ er holding recess 30 of the turbine disk 3, m ⁇ ie the foot 4, and thus ensure a secure positive fit against slipping out of the turbine blade when the centrifugal force is applied.
  • an average width 6 ′ of the foot 4 formed by the teeth 35 and intervening openings increases. This average width 6 'is followed by the depth 33 of the transverse region of the cavity 7 while maintaining minimum wall thicknesses of the walls 12 which ensure stability.
  • the transition region 38 adjoining the foot 4 is curved like a lens, as is clear in the cross section from FIG , Accordingly, the cavity 7 is shifted relative to its formation in the foot 4 so that sufficient wall thicknesses 14 are ensured on both sides of the cavity 7.
  • Section line III-III from Fig.l and Fig.2. The 3re ⁇ te 6 of the cross section through the foot is quite large, since the cut through an upper tooth 35 of the foot 4, that is in the area of the greatest width 6 of the foot 4, runs.
  • the hollow 7 consists of several chambers 29, the cross struts 28 corresponding to the partition walls of the chambers 29.
  • the chambers 29 point from the two transverse walls 8 of the foot 4 starting from an increasing depth 33, which has its greatest extent on the more rigid cross strut 28, in order to then remove the other transverse wall 8 of the foot 4 again as it approaches Cie.
  • the boundaries of the chambers 29 are rounded on all sides to avoid voltage peaks.
  • FIG. 4 shows a section along the section line IV-IV of FIG. 1 or FIG. 2 through the transition area 38.
  • the cut-out 7 has only five chambers 29 or four cross struts 28 in this area, since the section above the cross strut closest to the hot gas inflow side he follows. An enlarged chamber 29 can thus be seen at the area of the hot gas inflow side 17.
  • the wall thickness l ⁇ of the wall 8 is greater in the area of the hot gas inflow side 17 than in the opposite area on the hot gas outflow side 18.
  • FIG. 5 shows a section through the narrowest area of the foot 4 along the section line V-V of FIG. 1 or corresponding to F g.2.
  • the chambers 29 of the cavity 7 again have a cross-sectional depth 33 increasing from the transverse wall 8, but the cross-sectional change is not as great as in FIG. 3.
  • the maximum in turn lies in the area of the central cross strut 28.

Landscapes

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

Abstract

La présente invention concerne une aube de turbine comprenant un profilé d'aube à refroidissement interne (1) qui s'étend à partir d'une plate-forme d'aube (2) reliée à une emplanture d'aube (4) s'accouplant avec le disque de la turbine (3), la section radiale de ladite emplanture présentant une zone (5) de largeur croissante (6') en direction de la plate-forme d'aube (2). L'invention a pour objet la réalisation de l'aube de turbine permettant un allongement du profilé d'aube. Pour cela, l'emplanture d'aube (4) présente un évidement (7) ouvert en direction de la plate-forme qui se termine de façon invisible du côté plate-forme et qui s'élargit du point de vue de la section dans la zone (5) de largeur croissante (6') de l'emplanture d'aube (4).
EP01913779A 2000-02-25 2001-02-01 Aube de turbine Expired - Lifetime EP1257732B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01913779A EP1257732B1 (fr) 2000-02-25 2001-02-01 Aube de turbine

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP00104002 2000-02-25
EP00104002A EP1128023A1 (fr) 2000-02-25 2000-02-25 Aube rotorique de turbine
PCT/EP2001/001063 WO2001063098A1 (fr) 2000-02-25 2001-02-01 Aube de turbine
EP01913779A EP1257732B1 (fr) 2000-02-25 2001-02-01 Aube de turbine

Publications (2)

Publication Number Publication Date
EP1257732A1 true EP1257732A1 (fr) 2002-11-20
EP1257732B1 EP1257732B1 (fr) 2004-10-06

Family

ID=8167964

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00104002A Withdrawn EP1128023A1 (fr) 2000-02-25 2000-02-25 Aube rotorique de turbine
EP01913779A Expired - Lifetime EP1257732B1 (fr) 2000-02-25 2001-02-01 Aube de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP00104002A Withdrawn EP1128023A1 (fr) 2000-02-25 2000-02-25 Aube rotorique de turbine

Country Status (6)

Country Link
US (1) US6755986B2 (fr)
EP (2) EP1128023A1 (fr)
JP (1) JP4698917B2 (fr)
CN (1) CN1313705C (fr)
DE (1) DE50103981D1 (fr)
WO (1) WO2001063098A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2369134A1 (fr) * 2010-03-12 2011-09-28 Industria de Turbo Propulsores S.A. Aude de turbine avec des cavités pour la réduction du poid et des vibrations

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US6932570B2 (en) * 2002-05-23 2005-08-23 General Electric Company Methods and apparatus for extending gas turbine engine airfoils useful life
US20070006865A1 (en) * 2003-02-21 2007-01-11 Wiker John H Self-cleaning oven
EP1614861A1 (fr) * 2004-07-09 2006-01-11 Siemens Aktiengesellschaft Roue de turbine comprenant des aubes de turbine avec turbulateurs sur la surface radiale interne de la plate-forme
GB0613441D0 (en) * 2006-07-06 2006-08-16 Rolls Royce Plc Blades
US8157527B2 (en) * 2008-07-03 2012-04-17 United Technologies Corporation Airfoil with tapered radial cooling passage
CN101586475B (zh) * 2008-12-23 2011-04-27 张金山 航空发动机涡轮转子叶片的集束分流式热防护
DE102010004854A1 (de) 2010-01-16 2011-07-21 MTU Aero Engines GmbH, 80995 Laufschaufel für eine Strömungsmaschine und Strömungsmaschine
EP2385215A1 (fr) * 2010-05-05 2011-11-09 Alstom Technology Ltd Ailette de plateau légère pour pale de rotor
US9109456B2 (en) * 2011-10-26 2015-08-18 General Electric Company System for coupling a segment to a rotor of a turbomachine
EP2644834A1 (fr) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Aube de turbine ainsi que son procédé de fabrication correspondant
US10830065B2 (en) * 2015-06-02 2020-11-10 Siemens Aktiengesellschaft Attachment system for a turbine airfoil usable in a gas turbine engine
CN107143381A (zh) * 2017-06-06 2017-09-08 哈尔滨汽轮机厂有限责任公司 一种能够降低应力的燃气轮机透平第一级动叶片
CN112177678A (zh) * 2020-09-25 2021-01-05 厦门大学 带双内环空腔的涡轮盘结构及其设计方法

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2369134A1 (fr) * 2010-03-12 2011-09-28 Industria de Turbo Propulsores S.A. Aude de turbine avec des cavités pour la réduction du poid et des vibrations

Also Published As

Publication number Publication date
CN1313705C (zh) 2007-05-02
US6755986B2 (en) 2004-06-29
CN1406312A (zh) 2003-03-26
EP1257732B1 (fr) 2004-10-06
DE50103981D1 (de) 2004-11-11
US20030021686A1 (en) 2003-01-30
EP1128023A1 (fr) 2001-08-29
JP2003524104A (ja) 2003-08-12
JP4698917B2 (ja) 2011-06-08
WO2001063098A1 (fr) 2001-08-30

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