EP3112589A1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP3112589A1
EP3112589A1 EP15175301.9A EP15175301A EP3112589A1 EP 3112589 A1 EP3112589 A1 EP 3112589A1 EP 15175301 A EP15175301 A EP 15175301A EP 3112589 A1 EP3112589 A1 EP 3112589A1
Authority
EP
European Patent Office
Prior art keywords
blade
wall thickness
transition
turbine blade
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.)
Withdrawn
Application number
EP15175301.9A
Other languages
German (de)
English (en)
Inventor
Björn Buchholz
Ralph Gossilin
Daniela Koch
Marco Schüler
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 EP15175301.9A priority Critical patent/EP3112589A1/fr
Priority to EP16733363.2A priority patent/EP3289182B1/fr
Priority to CN201680039384.5A priority patent/CN107735548B/zh
Priority to PCT/EP2016/064274 priority patent/WO2017005484A1/fr
Priority to US15/739,299 priority patent/US10301944B2/en
Priority to JP2017567740A priority patent/JP6469897B2/ja
Publication of EP3112589A1 publication Critical patent/EP3112589A1/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Withdrawn legal-status Critical Current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
    • F01D5/12—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
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/301—Cross-sectional characteristics
    • 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 to the platform to a load and casting technology necessary curvature on an outer surface, wherein in this hollow gutter-like transition leads to total local mass accumulation, which are difficult to cool by an internally flowable cooling medium.
  • a turbine blade is from the US 6,019,579 known.
  • the document shows US 2,861,775 a turbine blade made of bent sheets.
  • a turbine blade with a prolonged life is also from the EP 1 355 041 A1 known, wherein the contour of the transition from the blade to the platform in the blade interior is adapted to also obtain in the transition region an airfoil wall thickness which corresponds approximately to the wall thickness of the remaining airfoil.
  • the contour is adjusted along the entire, closed circulation, ie along the platform.
  • the reduced wall thickness for reasons of strength, can adversely affect the life of the turbine blade, which is undesirable.
  • a turbine blade corresponding to the generic term that, in the transition, the contour profile is at an inner surface section of the blade opposite the leading edge such that there the blade wall thickness is increased compared to the blade wall thickness of the transition, away from the local inner surface section.
  • the turbine blade in the interior at the level of the platform has a contour which is different along the circulation of the cavity.
  • the inner contour of the cavity is rather straight and aligned with the inner surface which lies opposite the front edge away from the transition.
  • the mass accumulation avoiding inner contour is provided only on those areas of the airfoil, which are located further downstream of the leading edge.
  • the increased blade wall thickness inner surface portion extends from the leading edge of the airfoil along the suction sidewall and / or the pressure sidewall along the profile centerline to a position equal to or less than 9% of the profile centerline length.
  • the strength, in particular in the leading edge region of the turbine blade be increased locally, which leads to an increased life of the respective areas.
  • the platform has a platform wall thickness and the blade has a blade wall thickness away from the transition, wherein in the region of substantially uniform blade wall thickness of the transition, the ratio of blade wall thickness to platform wall thickness is between 0.5 and 1.
  • Such a turbine blade can be cooled particularly homogeneously, which reduces thermomechanical stresses in the material of the turbine blade.
  • FIG. 1 shows a perspective view of a turbine blade 10.
  • the perspective is selected so that the top view is shown on a mounting portion 12 of the turbine blade 10 designed as a vane.
  • FIG. 2 is the longitudinal section through the turbine blade 10 according to the section line II-II FIG. 1 shown.
  • the turbine blade 10 has, along a radial axis 14, the attachment area 12, an adjacent blade platform 16, and an airfoil 18 in succession.
  • a blade root 20 is formed, which serves for fastening the turbine blade 10 to a turbine vane support, not shown.
  • the representation of the invention takes place by way of example with reference to a designed as a guide blade with two platforms turbine blade. Nevertheless, other embodiments are possible, in particular, the turbine blade can also be configured as a blade of a turbine. At least the main body of the turbine blade is by a casting process and comprises at least the airfoil 18, as well as at least one platform 16.
  • the turbine blade 10 according to the invention and in particular its blade 18 is hollow in the interior, so that it comprises a cavity 25 which may be configured in a known manner as a cooling channel with or without impingement cooling.
  • the airfoil 18 extends from a leading edge 28 to a trailing edge 30.
  • the airfoil 18 includes an in FIG. 1 only schematically indicated suction-side blade wall 32 and a pressure-side blade wall 34.
  • the blade walls 32, 34 a wall thickness D, which is substantially constant.
  • transition 36 between the blade 18 and the platform 16, which is rounded on the outer surface of the turbine blade 10 and thus hollow-chipped.
  • the airfoil 18 has an inner surface opposite the outer surfaces. This is in the region of the suction-side blade wall 32 such that it is partially adapted to the outer contour of the transition, so that there is a substantially uniform blade wall thickness D1 in the transition 36 there.
  • the inner surface in the region of the transition 36 comprises an inner surface section 40 opposite the front edge 28, the contour of which is such that the blade wall thickness (D 2 ) is increased compared to the blade wall thickness D 1 of the transition away from this inner surface section.
  • the inner surface portion is located only in the vicinity of the leading edge and forms a straight line with the inner surface of the remaining airfoil along the radial direction 14 and in longitudinal section, whereas the remaining inner surface of the Saugund / or Pressure side in the transition while maintaining an approximately uniform blade wall thickness D 1 is curved.
  • a transition region of a turbine blade 10 thickened in the region of the front edge 28 can be provided, which has a greater rigidity than in the remaining region. This can improve the life of the turbine blade 10.
  • the invention relates to a cast turbine blade 10 having a platform 16 and a hollow airfoil 18 disposed thereon, the airfoil 18 comprising a pressure-side airfoil 34 and a suction-side airfoil 32 extending along a center curved profile centerline 42 thereof from a common leading edge 28 extend to a common trailing edge 30 and having an outer contour having transition 36 between the blade and platform 36, wherein the blade walls 32, 34 each have a locally to be detected blade wall thickness D, wherein the turbine blade has a contour in the interior, which partially the outer Contour profile of the transition 36 is adapted in such a way that in the region of the transition 36, a substantially uniform blade wall thickness is present.
  • the contour is formed on an inner surface section 40 of the blade opposite the leading edge 28 in such a way that the blade wall thickness is increased compared to the blade wall thickness of the transition away from the leading edge.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15175301.9A 2015-07-03 2015-07-03 Aube de turbine Withdrawn EP3112589A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP15175301.9A EP3112589A1 (fr) 2015-07-03 2015-07-03 Aube de turbine
EP16733363.2A EP3289182B1 (fr) 2015-07-03 2016-06-21 Aube de turbine
CN201680039384.5A CN107735548B (zh) 2015-07-03 2016-06-21 涡轮机叶片
PCT/EP2016/064274 WO2017005484A1 (fr) 2015-07-03 2016-06-21 Aube de turbine
US15/739,299 US10301944B2 (en) 2015-07-03 2016-06-21 Turbine blade
JP2017567740A JP6469897B2 (ja) 2015-07-03 2016-06-21 タービンブレード

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15175301.9A EP3112589A1 (fr) 2015-07-03 2015-07-03 Aube de turbine

Publications (1)

Publication Number Publication Date
EP3112589A1 true EP3112589A1 (fr) 2017-01-04

Family

ID=53514053

Family Applications (2)

Application Number Title Priority Date Filing Date
EP15175301.9A Withdrawn EP3112589A1 (fr) 2015-07-03 2015-07-03 Aube de turbine
EP16733363.2A Active EP3289182B1 (fr) 2015-07-03 2016-06-21 Aube de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP16733363.2A Active EP3289182B1 (fr) 2015-07-03 2016-06-21 Aube de turbine

Country Status (5)

Country Link
US (1) US10301944B2 (fr)
EP (2) EP3112589A1 (fr)
JP (1) JP6469897B2 (fr)
CN (1) CN107735548B (fr)
WO (1) WO2017005484A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190040751A1 (en) * 2017-08-03 2019-02-07 General Electric Company Stress-relieving pocket in turbine nozzle with airfoil rib

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10422236B2 (en) * 2017-08-03 2019-09-24 General Electric Company Turbine nozzle with stress-relieving pocket
DE102018209610A1 (de) 2018-06-14 2019-12-19 MTU Aero Engines AG Schaufelblatt für eine Strömungsmaschine
JP7419002B2 (ja) * 2019-09-12 2024-01-22 三菱重工業株式会社 ストラットカバー、排気車室およびガスタービン
US11578607B2 (en) * 2020-12-15 2023-02-14 Pratt & Whitney Canada Corp. Airfoil having a spline fillet

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2861775A (en) 1953-06-04 1958-11-25 Power Jets Res & Dev Ltd Tubular blades
US6019579A (en) 1997-03-10 2000-02-01 Mitsubishi Heavy Industries, Ltd. Gas turbine rotating blade
EP1355041A2 (fr) 2002-04-18 2003-10-22 Siemens Aktiengesellschaft Aube de turbine
GB2395987A (en) * 2002-12-02 2004-06-09 Alstom Turbine blade with cooling bores
WO2007012592A1 (fr) * 2005-07-27 2007-02-01 Siemens Aktiengesellschaft Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type
EP2476863A1 (fr) * 2011-01-14 2012-07-18 Siemens Aktiengesellschaft Aube de turbine pour une turbine à gaz
WO2012172099A1 (fr) * 2011-06-17 2012-12-20 Alstom Technology Ltd. Aube de turbine coulée

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2334071C (fr) 2000-02-23 2005-05-24 Mitsubishi Heavy Industries, Ltd. Aube mobile de turbine a gaz
JP2001271603A (ja) 2000-03-24 2001-10-05 Mitsubishi Heavy Ind Ltd ガスタービン動翼
US7371046B2 (en) * 2005-06-06 2008-05-13 General Electric Company Turbine airfoil with variable and compound fillet
CH698109B1 (de) * 2005-07-01 2009-05-29 Alstom Technology Ltd Turbomaschinenschaufel.
JP4738176B2 (ja) * 2006-01-05 2011-08-03 三菱重工業株式会社 冷却翼
DE502006003548D1 (de) 2006-08-23 2009-06-04 Siemens Ag Beschichtete Turbinenschaufel
WO2009118235A2 (fr) 2008-03-28 2009-10-01 Alstom Technology Ltd Aube directrice pour turbine à gaz
JP5479032B2 (ja) * 2009-11-05 2014-04-23 三菱重工業株式会社 タービンホイール
WO2012144244A1 (fr) * 2011-04-22 2012-10-26 三菱重工業株式会社 Aube et machine rotative

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2861775A (en) 1953-06-04 1958-11-25 Power Jets Res & Dev Ltd Tubular blades
US6019579A (en) 1997-03-10 2000-02-01 Mitsubishi Heavy Industries, Ltd. Gas turbine rotating blade
EP1355041A2 (fr) 2002-04-18 2003-10-22 Siemens Aktiengesellschaft Aube de turbine
GB2395987A (en) * 2002-12-02 2004-06-09 Alstom Turbine blade with cooling bores
WO2007012592A1 (fr) * 2005-07-27 2007-02-01 Siemens Aktiengesellschaft Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type
EP2476863A1 (fr) * 2011-01-14 2012-07-18 Siemens Aktiengesellschaft Aube de turbine pour une turbine à gaz
WO2012172099A1 (fr) * 2011-06-17 2012-12-20 Alstom Technology Ltd. Aube de turbine coulée

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190040751A1 (en) * 2017-08-03 2019-02-07 General Electric Company Stress-relieving pocket in turbine nozzle with airfoil rib
US10655485B2 (en) * 2017-08-03 2020-05-19 General Electric Company Stress-relieving pocket in turbine nozzle with airfoil rib

Also Published As

Publication number Publication date
JP2018524511A (ja) 2018-08-30
JP6469897B2 (ja) 2019-02-13
CN107735548B (zh) 2019-07-12
US10301944B2 (en) 2019-05-28
EP3289182B1 (fr) 2020-03-25
US20180187551A1 (en) 2018-07-05
CN107735548A (zh) 2018-02-23
EP3289182A1 (fr) 2018-03-07
WO2017005484A1 (fr) 2017-01-12

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