EP1355041B1 - Turbinenschaufel - Google Patents

Turbinenschaufel Download PDF

Info

Publication number
EP1355041B1
EP1355041B1 EP03006497A EP03006497A EP1355041B1 EP 1355041 B1 EP1355041 B1 EP 1355041B1 EP 03006497 A EP03006497 A EP 03006497A EP 03006497 A EP03006497 A EP 03006497A EP 1355041 B1 EP1355041 B1 EP 1355041B1
Authority
EP
European Patent Office
Prior art keywords
blade
vane
transition
turbine blade
region
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
EP03006497A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1355041A2 (de
EP1355041A3 (de
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/de
Publication of EP1355041A3 publication Critical patent/EP1355041A3/de
Application granted granted Critical
Publication of EP1355041B1 publication Critical patent/EP1355041B1/de
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 preamble of claim 1.
  • Hollow turbine blades in particular gas turbine blades, have in the region of a transition from the blade area to the platform a load and casting technology necessary curvature on an outer surface, wherein it comes in this transition to local mass accumulations, which are difficult to cool by a cooling medium inside.
  • a turbine blade is known from US 6,019,579. Further, document US-A-2,861,775 shows a turbine blade made of bent sheets.
  • a turbine blade with the features specified in claim 1.
  • a contour of a cavity or an inner channel is adapted to a contour of the outer transition in such a way that a substantially uniform thickness is formed.
  • FIG. 1 shows a perspective view of a moving blade 1 which extends along a radial axis 4.
  • the rotor blade 1 has, along the radial axis 4, a fastening area 7, an adjacent blade platform 10 and an airfoil area 13 in succession.
  • a blade root 16 is formed, which serves for fastening the 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 embodiments are possible.
  • massive metallic materials in particular cobalt- or nickel-based superalloys are used.
  • the blade can be made by a casting process, by a forging process, by a milling process or combinations thereof.
  • 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 designed to be hollow inside, ie 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 between the airfoil region 13 and the platform 10, which is rounded off on an outer surface 17 of the turbine blade 1.
  • Such a rounded transition 19 is for example in the direction the radial axis 4 seen above and below the blade platform 10 and, for example, also around the radial axis circumferentially available.
  • an inner contour 31 in the region of the cavity 25 or of the channel 25 at the radial height (radial axis 4) of the blade platform 10 is adapted to the contour of the outer transition 19 so that the blade wall thickness 22 between the blade area 13 and blade root 16 is at least substantially the same blade wall thickness 22 has.
  • outer transition 19 adapted i. approximately equidistant inner contour 31 occurs in the region of the cavity 25 or the channel 25 to a bulge 28 in the region of the blade platform 10th
  • 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, which defines an inner contour 31 of the cavity 25 or the channel 25 inside, as already described in Figure 2.
  • FIG. 4 shows a further exemplary embodiment of a detail of a turbine blade 1 according to the invention.
  • the rounded transition 19 is present, for example, only above an axial plane 34 (perpendicular to the radial axis 4) and is present, for example, only in the upper region of the turbine blade 1. In the lower area, the transition between the blade flow 16 and the platform 10 is made almost at right angles, since there is no heat-critical area.
  • the inner contour profile 31 is nevertheless adapted to the upper contour profile in the region of the transition 19, as seen from the blade root 16 in the direction of the radial axis 4, so that a virtually uniform blade wall thickness 22 is achieved.

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 Turbinenschaufel Expired - Lifetime EP1355041B1 (de)

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 EP1355041A2 (de) 2003-10-22
EP1355041A3 EP1355041A3 (de) 2005-04-06
EP1355041B1 true EP1355041B1 (de) 2007-05-09

Family

ID=28458918

Family Applications (1)

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

Country Status (6)

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

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
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
JP5655210B2 (ja) 2011-04-22 2015-01-21 三菱日立パワーシステムズ株式会社 翼部材及び回転機械
EP2990598A1 (de) * 2014-08-27 2016-03-02 Siemens Aktiengesellschaft Turbinenschaufel und Turbine
EP3112589A1 (de) 2015-07-03 2017-01-04 Siemens Aktiengesellschaft Turbinenschaufel
GB202107128D0 (en) * 2021-05-19 2021-06-30 Rolls Royce Plc Nozzle guide vane

Family Cites Families (12)

* 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
DE1049872B (es) * 1953-06-04 1954-02-05
GB926084A (en) * 1962-01-11 1963-05-15 Rolls Royce Bladed member adapted for use on a fluid flow machine
GB1230325A (es) * 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
JP3192854B2 (ja) * 1993-12-28 2001-07-30 株式会社東芝 タービン冷却翼
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
JP3411775B2 (ja) * 1997-03-10 2003-06-03 三菱重工業株式会社 ガスタービン動翼
US6190130B1 (en) * 1998-03-03 2001-02-20 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade platform
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
GB2365079B (en) * 2000-07-29 2004-09-22 Rolls Royce Plc Blade platform cooling

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP1355041A2 (de) 2003-10-22
US20050106011A1 (en) 2005-05-19
JP2003314203A (ja) 2003-11-06
DE10217390A1 (de) 2003-10-30
CN1451848A (zh) 2003-10-29
US6979173B2 (en) 2005-12-27
CN100346058C (zh) 2007-10-31
ES2283670T3 (es) 2007-11-01
DE50307214D1 (de) 2007-06-21
EP1355041A3 (de) 2005-04-06

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