EP1128023A1 - Aube rotorique de turbine - Google Patents

Aube rotorique de turbine Download PDF

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Publication number
EP1128023A1
EP1128023A1 EP00104002A EP00104002A EP1128023A1 EP 1128023 A1 EP1128023 A1 EP 1128023A1 EP 00104002 A EP00104002 A EP 00104002A EP 00104002 A EP00104002 A EP 00104002A EP 1128023 A1 EP1128023 A1 EP 1128023A1
Authority
EP
European Patent Office
Prior art keywords
platform
blade
cavity
turbine rotor
rotor blade
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.)
Withdrawn
Application number
EP00104002A
Other languages
German (de)
English (en)
Inventor
Peter Dipl.-Ing. Tiemann
Michael Dr. Ing. Strassberger
Dirk Dr. Ing. 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 EP00104002A priority Critical patent/EP1128023A1/fr
Priority to DE50103981T priority patent/DE50103981D1/de
Priority to US10/204,693 priority patent/US6755986B2/en
Priority to EP01913779A priority patent/EP1257732B1/fr
Priority to CNB018056237A priority patent/CN1313705C/zh
Priority to JP2001561893A priority patent/JP4698917B2/ja
Priority to PCT/EP2001/001063 priority patent/WO2001063098A1/fr
Publication of EP1128023A1 publication Critical patent/EP1128023A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/02—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 internally uncooled blade profile that extends from a blade platform extends from which extends into a turbine disc engaging blade root adjoins its radial Cross section to the blade platform an area increasing Width.
  • the object of the present invention is therefore a turbine blade to create an extension of the blade profiles allows without or with only a minor Increase local loads on the turbine disc or from blade feet.
  • the blade root is a has open cavity facing away from the platform, the platform side ends blindly and in the area of increasing width of the Blade base is widened in cross section.
  • the blade root is usually used to ensure stability solidly trained and shows compared to the rest Dimensions of the turbine blade have a large cross section on. So its mass is high and it has a large proportion on the one that occurs when the turbine disc rotates Centrifugal load on the turbine disc and the holding devices for the shovel. Due to the hollowing out the mass of the foot and thus the centrifugal force considerably.
  • the special form of the excavation namely one cross-sectional widening on the longitudinal walls in the area increasing width of the blade root ensures a optimal use of the shape of the blade root in view on a decrease in mass. Because the hollowing out ends blindly on the platform side, are also the stability requirements, which in particular in the area between platform and Blade profile due to diverse strong forces and temperature attack are very high, met.
  • the invention enables thus at the same time to keep the mass of the shovel low and to maintain or even improve their stability.
  • the average tension level lowered in the foot area and tension peaks on holding teeth of the foot and the adjacent turbine disc resulting in an extension of the life of the turbine blade and especially to improve durability of the foot leads. It is therefore without endangering stability 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 hot working gases particularly stress that edge area the shovel that is the first to flow directly becomes.
  • the higher strength requirements on the hot gas inflow side is taken into account that the minimum wall thickness near a hot gas inflow side is larger than at the hot gas outflow side.
  • a material and mass-saving increase in the strength of the Foot is given in that the blade root from between its longitudinal walls trained cross struts is reinforced.
  • the forces acting on one longitudinal wall of the cavity are through the cross struts to the other longitudinal wall of the Excavation and passed through both walls into the turbine disc, without endangering the stability of the excavation. Due to the further reduction in mass also occurs due to the reduced centrifugal load further relief of the foot.
  • the particularly high attacking forces in the middle area are intercepted by the cross struts of the cavity have the greatest height in the middle and to one decrease the height of the sloping course of the excavation.
  • FIG. 1 shows a radial cross section through a foot 4 and a platform 2 and part of a blade profile 1 a turbine blade.
  • the foot 4 is in a holding recess 30 a turbine disk 3 and pushed by teeth 35 of the foot 4 and corresponding teeth 36 of the holding recess 30 held positively, as shown in Fig.2.
  • Foot 4, platform 2 and profile 1 are in one piece, connected shaped, preferably cast.
  • Juxtaposed Blade profiles 1 offer a hot gas flowing past Resistance and change its speed and direction, which causes the turbine disc 3 to rotate at a very high rate Speed is excited about a disk axis.
  • the one here Centrifugal forces must essentially come from the teeth 35 of the blade root 4 and the teeth 36 of the holding recess 30 can be caught.
  • Turbine blades are generally large parts of the turbine blade massively trained and therefore have a high Weight that puts a heavy load on the foot areas.
  • the foot 4 has a weight-reducing according to the invention Excavation 7 on. This is shaped like a vault and ends on Platform-side end 19 of the turbine blade blind below the top 21 of the platform 2. On a platform facing away from The end 7 of the foot 4, the cavity 7 is open.
  • the Foot 4 has one in the region of the end 31 facing away from the platform essentially constant length 32. The length 32 takes when approaching platform 2, first because of a molding 37 of the transition area 38 something to then to Take off platform 2 continuously.
  • the cavity 7 has lengths 13 of longitudinal walls 12 and depths 33.
  • the lengths 13 start from that facing away from the platform End 31 after a certain distance to the platform side End 19 of the foot 4 are in the transition area 38 in one arcuate shape shorter to the highest point with the Height 16 of the cavity 7, where the cavity 7 ends blindly. This end is preferably in the range or below Platform top 21 to ensure sufficient stability of the Ensure shovel.
  • the blade profile is in the platform area massive and possibly has a weight-saving Blade profile cavity in the upper, not shown Area of the blade profile at a distance from the platform. This avoids the strength of the blade in the Endanger the platform area.
  • the cavity 7 has none Connection to the blade profile cavity, since it is a internally uncooled turbine blade acts and therefore not Coolant transport through the foot is necessary.
  • the depth 33 decreases, as shown in Fig. 2, from the platform facing away End 31 of the foot 4 to the platform end 19 towards 5 in an area. Then the cavity 7 follows one Turning of the turbine blade in the transition area 38.
  • the depth 33 initially increases somewhat in the transition area 38 in order to then from approximately the middle of the transition region 38 to Platform 2 to decrease steadily. This is the greatest possible Area within foot 4 or respectively Transitional area 38 hollowed out for maximum weight reduction to achieve. It is particularly taken into account that the walls 8, 12 sufficient wall thicknesses 14 for Ensuring the stability of the foot 4 even with strong ones attacking centrifugal forces. Due to the domed training the hollow 7 voltage peaks are avoided, the lead to a reduction in strength.
  • the hollow 7 can be produced by a casting core with lost shape, that in the foot area of the shovel is used before casting and over the platform facing away End 31 of the foot 4 protrudes, whereby a platform faces away forms open cavity.
  • the casting core On the platform side End 19 of foot 4 is the casting core as the blind core ending there educated. After the casting, the core is destroyed and out the cavity 7 removed because it is due to the opening do not remove the narrowing width as a whole leaves.
  • Cross struts 28 are attached within the cavity 7, which run between the longitudinal walls 12. Through the cross struts 28 the cavity 7 becomes against attacking forces, which act on the walls 8, 12 supported.
  • the cross struts 28 are rounded, to avoid voltage peaks. They are essentially parallel to each other at intervals 34 in the direction a longitudinal axis 39 of the turbine blade. you take almost the entire area between the two opposite Longitudinal walls 12 a.
  • Fig.2 shows a radial cross section in an almost right Angle to the first longitudinal section of Figure 1 along the Section line II-II.
  • the foot 4 bulging teeth 35, the correspondingly shaped teeth 36 the holding recess 30 of the turbine disc 3, in which the foot 4 is used reach behind and so a safe Positive locking against slipping out of the turbine blade Ensure centrifugal load.
  • From the platform away End 31 to platform-side end 19 of the foot 4 takes one of the teeth 35 and intervening dents formed mean width 6 'of the foot 4 to.
  • This middle one Width 6 ' follows the depth 33 of the transverse region of the cavity 7 while maintaining minimum wall thicknesses that ensure stability of walls 12.
  • the one following foot 4 Transition area 38 is curved like a lens, as in cross section is clear from Fig.4. Accordingly, the excavation is 7 shifted relative to their training in the foot 4 so that sufficient wall thicknesses 14 on both sides of the cavity 7 are guaranteed.
  • FIG. 3 shows a cross section through the foot 4 along the Section line III-III from Fig. 1 and Fig. 2.
  • the width 6 the cross section through the foot is quite large since the cut by an upper tooth 35 of the foot 4, that is in the area the greatest width 6 of the foot 4, runs.
  • the excavation 7 consists in this section of several chambers 29, the Cross struts 28 partitions of the chambers 29 correspond.
  • the Chambers 29 point from the two transverse walls 8 of the foot 4 starting from an increasing depth 33 that has its greatest extent at the central cross strut 28 in order to then again with an approach to the other transverse wall 8 of the foot 4 decrease.
  • the boundaries of the chambers 29 are to be avoided rounded on all sides by voltage peaks.
  • the cavity 7 has only five chambers in this area 29 or four cross struts 28, since the Cut above the nearest hot gas upstream Cross strut is done. Thus is on the area of the hot gas inflow side 17 shows an enlarged chamber 29.
  • the wall thickness 14 of the wall 8 is in the region of the hot gas inflow side 17 larger than in the opposite area of 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 according to Fig. 2.
  • the chambers 29 of the cavity 7 also have a cross wall 8 starting increasing cross-sectional depth 33, but the change in cross-section is not as great as in Fig. 3.
  • the maximum is again 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)
EP00104002A 2000-02-25 2000-02-25 Aube rotorique de turbine Withdrawn EP1128023A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP00104002A EP1128023A1 (fr) 2000-02-25 2000-02-25 Aube rotorique de turbine
DE50103981T DE50103981D1 (de) 2000-02-25 2001-02-01 Turbinenlaufschaufel
US10/204,693 US6755986B2 (en) 2000-02-25 2001-02-01 Moving turbine blade
EP01913779A EP1257732B1 (fr) 2000-02-25 2001-02-01 Aube de turbine
CNB018056237A CN1313705C (zh) 2000-02-25 2001-02-01 涡轮工作叶片
JP2001561893A JP4698917B2 (ja) 2000-02-25 2001-02-01 タービン翼
PCT/EP2001/001063 WO2001063098A1 (fr) 2000-02-25 2001-02-01 Aube de turbine

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP1128023A1 true EP1128023A1 (fr) 2001-08-29

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 After (1)

Application Number Title Priority Date Filing Date
EP01913779A Expired - Lifetime EP1257732B1 (fr) 2000-02-25 2001-02-01 Aube 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 (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1365108A2 (fr) * 2002-05-23 2003-11-26 General Electric Company Aube pour un moteur à turbine à gaz et procedé de fabrication d'une telle aube
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
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

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004076928A2 (fr) * 2003-02-21 2004-09-10 Middleby Corporation Four autonettoyant
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
DE102010004854A1 (de) 2010-01-16 2011-07-21 MTU Aero Engines GmbH, 80995 Laufschaufel für eine Strömungsmaschine und Strömungsmaschine
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
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
CN107667205B (zh) * 2015-06-02 2019-11-01 西门子公司 可用于燃气涡轮发动机中的涡轮翼型件的附接系统
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

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3695778A (en) * 1970-09-18 1972-10-03 Trw Inc Turbine blade
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
US5407326A (en) * 1992-09-02 1995-04-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Hollow blade for a turbomachine
EP0924381A2 (fr) * 1997-12-22 1999-06-23 General Electric Company Aube de turbomachine amortie en vibration

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3936216A (en) * 1974-03-21 1976-02-03 United Technologies Corporation Blade sealing and retaining means
CH580750A5 (fr) * 1974-07-17 1976-10-15 Bbc Sulzer Turbomaschinen
JPH03902A (ja) * 1989-02-13 1991-01-07 Toshiba Corp タービン動翼
JPH0447101A (ja) * 1990-06-15 1992-02-17 Toshiba Corp ターボ機械の動翼
JPH1122404A (ja) * 1997-07-03 1999-01-26 Hitachi Ltd ガスタービン及びその動翼

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3695778A (en) * 1970-09-18 1972-10-03 Trw Inc Turbine blade
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
US5407326A (en) * 1992-09-02 1995-04-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Hollow blade for a turbomachine
EP0924381A2 (fr) * 1997-12-22 1999-06-23 General Electric Company Aube de turbomachine amortie en vibration

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1365108A2 (fr) * 2002-05-23 2003-11-26 General Electric Company Aube pour un moteur à turbine à gaz et procedé de fabrication d'une telle aube
EP1365108A3 (fr) * 2002-05-23 2004-10-06 General Electric Company Aube pour un moteur à turbine à gaz et procedé de fabrication d'une telle aube
US6932570B2 (en) 2002-05-23 2005-08-23 General Electric Company Methods and apparatus for extending gas turbine engine airfoils useful life
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
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

Also Published As

Publication number Publication date
EP1257732B1 (fr) 2004-10-06
JP4698917B2 (ja) 2011-06-08
CN1406312A (zh) 2003-03-26
US6755986B2 (en) 2004-06-29
EP1257732A1 (fr) 2002-11-20
WO2001063098A1 (fr) 2001-08-30
JP2003524104A (ja) 2003-08-12
CN1313705C (zh) 2007-05-02
US20030021686A1 (en) 2003-01-30
DE50103981D1 (de) 2004-11-11

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