EP1355041A2 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP1355041A2
EP1355041A2 EP03006497A EP03006497A EP1355041A2 EP 1355041 A2 EP1355041 A2 EP 1355041A2 EP 03006497 A EP03006497 A EP 03006497A EP 03006497 A EP03006497 A EP 03006497A EP 1355041 A2 EP1355041 A2 EP 1355041A2
Authority
EP
European Patent Office
Prior art keywords
blade
transition
turbine blade
area
platform
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
EP03006497A
Other languages
German (de)
English (en)
Other versions
EP1355041A3 (fr
EP1355041B1 (fr
Inventor
Peter Tiemann
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 EP1355041A2 publication Critical patent/EP1355041A2/fr
Publication of EP1355041A3 publication Critical patent/EP1355041A3/fr
Application granted granted Critical
Publication of EP1355041B1 publication Critical patent/EP1355041B1/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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on 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
    • 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 turbine blade according to the Generic term of claim 1.
  • Hollow turbine blades especially gas turbine blades, point in the area of a transition from the airfoil area to the platform a necessary in terms of load and casting technology Curvature on an outer surface, being in this transition to local mass accumulations that comes through a cooling medium is difficult to cool inside.
  • a turbine blade with the features specified in claim 1.
  • a contour profile of a cavity or an inner channel is adapted to a contour profile of the outer transition in such a way that an essentially uniform thickness is produced.
  • FIG. 1 shows a rotor blade 1 in perspective view, which extends along a radial axis 4.
  • the rotor blade 1 has, in succession along the radial axis 4, a fastening area 7, an adjoining blade platform 10 and an airfoil area 13.
  • a blade root 16 is formed, which serves to fasten the moving blade 1 to a shaft, not shown, of a turbomachine, also not shown.
  • the blade root 16 is designed, for example, as a hammer head. Other configurations are possible.
  • massive metallic materials in particular cobalt or nickel-based super alloys, are used.
  • the rotor blade can be made by a casting process a forging process, a milling process or combinations be made from it.
  • FIG. 2 shows a section along the radial axis 4 of FIG. 1.
  • the turbine blade 1 according to the invention in particular a gas turbine blade, is here, for example, a rotor blade 1 which is hollow on the inside, ie that it has a cavity 25 or at least one channel 25, in particular a cooling channel 25.
  • the turbine blade 1 therefore has a blade wall thickness 22 on a blade wall 40 which can vary in the radial direction.
  • transition 19 which is on an outer Surface 17 of the turbine blade 1 is rounded.
  • a transition 19 is for example in the direction the radial axis 4 seen above and below the Blade platform 10 and, for example, around the Radial axis all around.
  • the usual inner contour profile is shown by a dashed line 37 in the cavity 25 or in the channel 25 according to the state of technology indicated. It is therefore in this area the prior art to a much larger blade wall thickness as above or below the transition 19, i.e. to a Material accumulation, which is more difficult due to the higher mass is cool so that there is local overheating can (heat critical area).
  • an inner contour course 31 is in the area of the cavity 25 or the channel 25 at a radial height (radial axis 4) the blade platform 10 of the contour of the outer Transition 19 adapted so that the blade wall thickness 22 between Blade area 13 and blade root 16 at least in essentially has the same blade wall thickness 22.
  • FIG. 3 shows a further exemplary embodiment of a turbine blade 1 according to the invention.
  • the turbine blade 1 shown in FIG. 3 is, for example, a guide blade which has a blade platform 10 at both radial ends.
  • a transition 19 is present on both vane platforms 10, which specifies an inner contour course 31 of the cavity 25 or of the channel 25, as already described in FIG. 2.
  • Figure 4 shows a further embodiment of a section a turbine blade designed according to the invention 1.
  • the rounded transition 19 is only above, for example an axial plane 34 (perpendicular to the radial axis 4) and is, for example, only in the upper area of the turbine blade 1 available. In the lower area is the transition almost perpendicular between blade flow 16 and platform 10 executed because there is no heat-critical area is.
  • the inner contour progression 31 is nevertheless that of the blade root 16 seen in the direction of the radial axis 4 upper contour adjusted in the area of the transition 19, so that an almost uniform blade wall thickness 22 is reached.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03006497A 2002-04-18 2003-03-21 Aube de turbine Expired - Lifetime EP1355041B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10217390 2002-04-18
DE10217390A DE10217390A1 (de) 2002-04-18 2002-04-18 Turbinenschaufel

Publications (3)

Publication Number Publication Date
EP1355041A2 true EP1355041A2 (fr) 2003-10-22
EP1355041A3 EP1355041A3 (fr) 2005-04-06
EP1355041B1 EP1355041B1 (fr) 2007-05-09

Family

ID=28458918

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03006497A Expired - Lifetime EP1355041B1 (fr) 2002-04-18 2003-03-21 Aube de turbine

Country Status (6)

Country Link
US (1) US6979173B2 (fr)
EP (1) EP1355041B1 (fr)
JP (1) JP2003314203A (fr)
CN (1) CN100346058C (fr)
DE (2) DE10217390A1 (fr)
ES (1) ES2283670T3 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007012590A1 (fr) * 2005-07-25 2007-02-01 Siemens Aktiengesellschaft Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type
EP3112589A1 (fr) 2015-07-03 2017-01-04 Siemens Aktiengesellschaft Aube de turbine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2444483B (en) * 2006-12-09 2010-07-14 Rolls Royce Plc A core for use in a casting mould
GB2468528B (en) * 2009-03-13 2011-03-30 Rolls Royce Plc Vibration damper
CN103459776B (zh) 2011-04-22 2015-07-08 三菱日立电力系统株式会社 叶片部件及旋转机械
EP2990598A1 (fr) * 2014-08-27 2016-03-02 Siemens Aktiengesellschaft Aube de turbine et turbine
GB202107128D0 (en) * 2021-05-19 2021-06-30 Rolls Royce Plc Nozzle guide vane

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR969414A (fr) * 1948-07-20 1950-12-20 Const Et D Equipements Mecaniq Perfectionnement à la fabrication des aubes creuses pour turbines à gaz
US2861775A (en) * 1953-06-04 1958-11-25 Power Jets Res & Dev Ltd Tubular blades
EP0661414A1 (fr) * 1993-12-28 1995-07-05 Kabushiki Kaisha Toshiba Aube refroidie pour turbine à gaz
EP0940561A1 (fr) * 1998-03-03 1999-09-08 Mitsubishi Heavy Industries, Ltd. Plateau d'un ailette mobile d'une turbine à gaz
US6019579A (en) * 1997-03-10 2000-02-01 Mitsubishi Heavy Industries, Ltd. Gas turbine rotating blade
US20020012589A1 (en) * 2000-07-29 2002-01-31 Dailey Geoffrey M. Blade platform cooling

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB926084A (en) * 1962-01-11 1963-05-15 Rolls Royce Bladed member adapted for use on a fluid flow machine
GB1230325A (fr) * 1969-03-05 1971-04-28
US5165852A (en) * 1990-12-18 1992-11-24 General Electric Company Rotation enhanced rotor blade cooling using a double row of coolant passageways
JP2971386B2 (ja) * 1996-01-08 1999-11-02 三菱重工業株式会社 ガスタービン静翼
US6158962A (en) * 1999-04-30 2000-12-12 General Electric Company Turbine blade with ribbed platform
US6354797B1 (en) * 2000-07-27 2002-03-12 General Electric Company Brazeless fillet turbine nozzle

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR969414A (fr) * 1948-07-20 1950-12-20 Const Et D Equipements Mecaniq Perfectionnement à la fabrication des aubes creuses pour turbines à gaz
US2861775A (en) * 1953-06-04 1958-11-25 Power Jets Res & Dev Ltd Tubular blades
EP0661414A1 (fr) * 1993-12-28 1995-07-05 Kabushiki Kaisha Toshiba Aube refroidie pour turbine à gaz
US6019579A (en) * 1997-03-10 2000-02-01 Mitsubishi Heavy Industries, Ltd. Gas turbine rotating blade
EP0940561A1 (fr) * 1998-03-03 1999-09-08 Mitsubishi Heavy Industries, Ltd. Plateau d'un ailette mobile d'une turbine à gaz
US20020012589A1 (en) * 2000-07-29 2002-01-31 Dailey Geoffrey M. Blade platform cooling

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007012590A1 (fr) * 2005-07-25 2007-02-01 Siemens Aktiengesellschaft Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type
US7467922B2 (en) 2005-07-25 2008-12-23 Siemens Aktiengesellschaft Cooled turbine blade or vane for a gas turbine, and use of a turbine blade or vane of this type
EP3112589A1 (fr) 2015-07-03 2017-01-04 Siemens Aktiengesellschaft Aube de turbine
WO2017005484A1 (fr) 2015-07-03 2017-01-12 Siemens Aktiengesellschaft Aube de turbine
US10301944B2 (en) 2015-07-03 2019-05-28 Siemens Aktiengesellschaft Turbine blade

Also Published As

Publication number Publication date
US6979173B2 (en) 2005-12-27
US20050106011A1 (en) 2005-05-19
CN100346058C (zh) 2007-10-31
JP2003314203A (ja) 2003-11-06
CN1451848A (zh) 2003-10-29
ES2283670T3 (es) 2007-11-01
DE10217390A1 (de) 2003-10-30
EP1355041A3 (fr) 2005-04-06
DE50307214D1 (de) 2007-06-21
EP1355041B1 (fr) 2007-05-09

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